Feb. 2025, 北海道大学, 令和6年度北海道大学教育研究総長表彰　　　　　　　　　　　　　　　
永田晴紀

Apr. 2024, 文部科学省, 令和6年度科学技術分野の文部科学大臣表彰　　　　　　　　　　　　　　　
科学技術賞（開発部門）
永田晴紀

Mar. 2023, 日本機械学会宇宙工学部門, 業績賞　　　　　　　　　　　　　　　
永田 晴紀

Aug. 2019, The American Institute of Aeronautics and Astronautics, 2018 AIAA Hybrid Rockets Best Paper Award　　　　　　　　　　　　　　　
Investigation of Graphite Nozzle Erosion in Hybrid Rockets Using O2/C2H4
Landon Kamps;Shota Hirai;Kazuhito Sakurai;Tor Viscor;Yuji Saito;Laymond Guan;Hikaru Isochi;Naoto Adachi;Mitsunori Ito;Harunori Nagata

Aug. 2018, International Astronautical Federation, Academy member　　　　　　　　　　　　　　　
NAGATA Harunori

Apr. 2018, 日本機械学会, Fellow member　　　　　　　　　　　　　　　
NAGATA Harunori

Jul. 2017, The American Institute of Aeronautics and Astronautics, 2016 Hybrid Rockets Student Best Paper Award　　　　　　　　　　　　　　　
Experimental and Analytical Investigation of Effect of Pressure on Regression Rate of Axial-Injection End-Burning Hybrid Rockets
Yuji Saito;Toshiki Yokoi;Hiroyuki Yasukochi;Kentaro Soeda;Tsuyoshi Totani;Masashi Wakita;Harunori Nagata

Mar. 2013, 日本航空宇宙学会, Fellow member　　　　　　　　　　　　　　　
NAGATA Harunori

2008, Japan Society for Aeronautics and Space Sciences, JSASS Award　　　　　　　　　　　　　　　
CAMUI型ハイブリッドロケット技術
永田 晴紀, Japan

2006, SI2006優秀講演賞　　　　　　　　　　　　　　　
Japan

May 2005, The Japan Society of Mechanical Engineers, Hokkaido branch, Research and Technology Award　　　　　　　　　　　　　　　
Development of CAMUI-type Hybrid Rocket
NAGATA Harunori

Apr. 2005, The Japan Society of Mechanical Engineers, Space Engineering Division, Frontier award　　　　　　　　　　　　　　　
Development of CAMUI-type Hybrid Rocket
NAGATA Harunori

Dec. 2003, Combustion Society of Japan, Encouraging Prize　　　　　　　　　　　　　　　
New Type of Hybrid Rocket
NAGATA Harunori

Physical mechanism of regression to flame spread transition under opposed forced flows in internal fuel pipes applied to AIEB rocket
Giuseppe Gallo, Mai Fukada, Harunori Nagata
FUEL, 405, 01 Feb. 2026
English, Scientific journal

Fuel Regression Characteristics of Axial-Injection End-Burning Hybrid Rockets Using LOX
Kaii Ri, Sho Suzuki, Keisuke Minami, Giuseppe Gallo, Harunori Nagata
Journal of Propulsion and Power, 1, 9, American Institute of Aeronautics and Astronautics (AIAA), 07 Apr. 2025, [Peer-reviewed], [Last author]
Scientific journal, Axial-injection end-burning hybrid rocket (AIEB-HR) is a nonconventional hybrid rocket, employing multiport fuel consumed along the axial direction by a diffusion flame established at the end of each port. The research aims to study the fuel axial regression rate using liquid oxygen at different pressures. A total of 21 firing tests performed in a pressure-controlled chamber with two different multiport grain geometries are discussed. Three different modes—regression mode, flame spread mode, and transition mode—were observed. As compared to the properties of GOX combustion, the flame spread is inhibited by the latent heat of LOX. An experimental correlation of the regression rate with the pressure, mass flow rate, and port diameter is obtained. The results show that the regression rate strongly depends on the pressure and is mostly insensitive to the other parameters, similar to solid propellants. The [Formula: see text] ratio obtained in this study was much higher than the optimal ratio. The optimal oxidizer-to-fuel-mass ratio ([Formula: see text]) requires a chamber pressure of approximately 5.7 MPa, oxidizer port velocities of 1.0 m/s, and a high filling rate of around 0.985.

Regenerative cooling in hybrid rocket engines based on Self-Pressurized liquid nitrous oxide
Giuseppe Gallo, Yuta Miyahara, Landon Kamps, Harunori Nagata
Applied Thermal Engineering, 254, 123928, 123928, Elsevier BV, Oct. 2024, [Peer-reviewed], [Last author]
Scientific journal

Computational Analysis and Regression Laws for Nozzle Erosion Prediction in Hybrid Rockets
Marco Rotondi, Mario Tindaro Migliorino, Daniele Bianchi, Landon Kamps, Harunori Nagata
Journal of Propulsion and Power, 40, 3, 439, 459, American Institute of Aeronautics and Astronautics (AIAA), May 2024, [Last author]
Scientific journal, The erosion of the nozzle throat can represent one of the major limitations against the future widespread use of hybrid rocket engines (HREs) in the space industry. In fact, nozzle erosion in HREs can be more severe and harder to predict than in solid rockets due to the higher concentration of oxidizing species in the combustion products and to mixture ratio shifts and/or throttling. Therefore, an accurate understanding of the erosion phenomenon is of fundamental importance for the technological advancement of HREs. This work is focused on the investigation of graphite nozzle erosion in HREs burning high-density polyethylene with two different oxidizers, oxygen and nitrous oxide. First, the results of a computational fluid dynamics parametric analysis are used to derive closed-form regression laws for the rapid estimation of nozzle throat erosion and wall temperature depending on chamber pressure and mixture ratio. Then, a one-dimensional transient heat conduction solver is loosely coupled with the aforementioned regression laws, allowing to reconstruct the transient heating process within the solid. The obtained numerical results are validated against experimental data. Finally, the effect of gas-phase reactions on the heterogeneous reactions occurring at the nozzle surface is highlighted when moving from fuel-rich to oxidizer-rich conditions.

Phenomenological regression rate model in axial injection end-burning hybrid rocket motor using different oxidizers
Giuseppe Gallo, Mai Fukada, Sho Suzuki, Harunori Nagata
Combustion and Flame, 263, 113409, 113409, Elsevier BV, May 2024, [Peer-reviewed], [Last author]
Scientific journal

Experimental investigation of regenerative cooling performance in hybrid rocket engines
Giuseppe Gallo, Hiroki Kojima, Landon Kamps, Harunori Nagata
Thermal Science and Engineering Progress, 49, 102481, 102481, Elsevier BV, Mar. 2024, [Peer-reviewed], [Last author]
Scientific journal

The influence of port diameter and oxidizer port velocity With burning spread of circular fuel duct with liquid oxygen
SON Taejun, SUZUKI Sho, LI Kaii, MINAMI Keisuke, FUKADA Mai, YAMAGUCHI Mao, WAKITA Masashi, NAGATA Harunori
The Proceedings of Mechanical Engineering Congress, Japan, 2024, J191p-05, The Japan Society of Mechanical Engineers, 2024
Japanese, Although much research has been carried out using gaseous oxygen as an oxidizer for axial-injection end-burning hybrid rockets (AIEB), liquid oxygen (LOX) is the best option for launch vehicle loading. Previous research using LOX as an oxidizer showed that the axial regression rate depends on ambient pressure, port oxidizer velocity, and port diameter. An optimum OF ratio is expected to be obtained at about 4.0 MPa. However, the dependence on ambient pressure and the dependence on port oxidizer velocity and port diameter have only been obtained in experiments on ambient pressure up to 1.0 MPa and at atmospheric pressure respectively. In this study, we compared the dependence on oxidizer mass flow rate and port diameter at atmospheric pressure and at 0.3 MPa with the aim of extending the experimental equation of flame spreading velocity. As a result, the dependence is qualitatively but not quantitatively consistent. There are three possibilities for why such a result arose: 1) there was not enough data on this study, 2) there was an incorrect pressure index, and 3) there was a possibility of multiphase in the previous study.

Prediction of the fuel regression-rate in a HDPE single port hybrid rocket fed by liquid nitrous oxide
Giuseppe Gallo, Landon Kamps, Shota Hirai, Carmine Carmicino, Nagata Harunori
Combustion and Flame, 259, 113160, 113160, Elsevier BV, Jan. 2024, [Last author]
Scientific journal

GEOspace X-ray imager (GEO-X)
Yuichiro Ezoe, Ryu Funase, Harunori Nagata, Yoshizumi Miyoshi, Hiroshi Nakajima, Ikuyuki Mitsuishi, Kumi Ishikawa, Masaki Numazawa, Yosuke Kawabata, Shintaro Nakajima, Ryota Fuse, Ralf C. Boden, Landon Kamps, Tomokage Yoneyama, Kouichi Hagino, Yosuke Matsumoto, Keisuke Hosokawa, Satoshi Kasahara, Junko Hiraga, Kazuhisa Mitsuda, Masaki Fujimoto, Munetaka Ueno, Atsushi Yamazaki, Hiroshi Hasegawa, Takefumi Mitani, Yasuhiro Kawakatsu, Takahiro Iwata, Hiroyuki Koizumi, Hironori Sahara, Yoshiaki Kanamori, Kohei Morishita, Daiki Ishi, Aoto Fukushima, Ayata Inagaki, Yoko Ueda, Hiromi Morishita, Yukine Tsuji, Runa Sekiguchi, Takatoshi Murakawa, Kazuma Yamaguchi, Rei Ishikawa, Daiki Morimoto, Yudai Yamada, Shota Hirai, Yuki Nobuhara, Yownin Albert M. Leung, Yamato Itoigawa, Ryo Onodera, Satoru Kotaki, Shotaro Nakamura, Ayumi Kiuchi, Takuya Matsumoto, Midori Hirota, Kazuto Kashiwakura
Journal of Astronomical Telescopes, Instruments, and Systems, 9, 03, SPIE-Intl Soc Optical Eng, 12 Sep. 2023
Scientific journal

One-dimensional modelling of the nozzle cooling with cryogenic oxygen flowing through helical channels in a hybrid rocket
Giuseppe Gallo, Landon Kamps, Shota Hirai, Carmine Carmicino, Harunori Nagata
Acta Astronautica, 210, 176, 196, Elsevier BV, Sep. 2023, [Peer-reviewed], [Last author]
Scientific journal

Numerical Analysis of Nozzle Erosion in Hybrid Rockets and Comparison with Experiments
Daniele Bianchi, Mario Tindaro Migliorino, Marco Rotondi, Landon Kamps, Harunori Nagata
JOURNAL OF PROPULSION AND POWER, 38, 3, 389, 409, May 2022
English, Scientific journal

Fuel Regression Characteristics of Axial-Injection End-Burning Hybrid Rocket Using Nitrous Oxide
Ryota Okuda, Kodai Komizu, Ayumu Tsuji, Takumi Miwa, Mai Fukada, Shuichi Yokobori, Kentaro Soeda, Landon Kamps, Harunori Nagata
JOURNAL OF PROPULSION AND POWER, 1, 14, Apr. 2022, [Peer-reviewed], [Last author]
English, Scientific journal

GEO-X (GEOspace X-ray imager)
Yuichiro Ezoe, Ryu Funase, Harunori Nagata, Yoshizumi Miyoshi, Hiroshi Nakajima, Ikuyuki Mitsuishi, Kumi Ishikawa, Yosuke Kawabata, Shintaro Nakajima, Landon Kamps, Masaki Numazawa, Tomokage Yoneyama, Kouichi Hagino, Yosuke Matsumoto, Keisuke Hosokawa, Satoshi Kasahara, Junko Hiraga, Kazuhisa Mitsuda, Masaki Fujimoto, Munetaka Ueno, Atsushi Yamazaki, Hiroshi Hasegawa, Takefumi Mitani, Yasuhiro Kawakatsu, Takahiro Iwata, Hiroyuki Koizumi, Hironori Sahara, Yoshiaki Kanamori, Kohei Morishita
SPACE TELESCOPES AND INSTRUMENTATION 2022: ULTRAVIOLET TO GAMMA RAY, 12181, 2022
English, International conference proceedings

Large-Scale CAMUI Type Hybrid Rocket Motor Scaling, Modeling, and Test Results
Tor Viscor, Landon Kamps, Kazuo Yonekura, Hikaru Isochi, Harunori Nagata
Aerospace, 9, 1, 1, 1, MDPI AG, Dec. 2021
Scientific journal, An understanding of the scalability of hybrid rocket regression models is critical for the enlargement and commercialization of small-scale engines developed within universities and similar research institutions. This paper investigates the fuel regression rates of recent 40 kN thrust-class motor experiments, which were designed based on fuel regression rate correlations of 2.5 kN thrust-class motors from previous research. The results show that fuel regression rates of the 40 kN experiments were within 26% of predictions made using correlations based on 2.5 kN experiments.

Burn Time Correction of Start-Up Transients for CAMUI Type Hybrid Rocket Engine
Tor Viscor, Hikaru Isochi, Naoto Adachi, Harunori Nagata
AEROSPACE, 8, 12, Dec. 2021
English, Scientific journal

Hybrid Rockets as Post-Boost Stages and Kick Motors
Landon Kamps, Shota Hirai, Harunori Nagata
AEROSPACE, 8, 9, Sep. 2021, [Peer-reviewed], [Last author]
English, Scientific journal

Reduction Mechanism of Transition Metal Oxide Particles in Thermally Induced Nanobubbles during Pulsed Laser Melting in Ethanol
Kentaro Suehara, Ryosuke Takai, Yoshie Ishikawa, Naoto Koshizaki, Kazunobu Omura, Harunori Nagata, Yuji Yamauchi
CHEMPHYSCHEM, 22, 7, 675, 683, Apr. 2021, [Peer-reviewed]
English, Scientific journal

Fuel Regression Characteristics in Hybrid Rockets Using Nitrous Oxide/High-Density Polyethylene
Seiji Ito, Landon Kamps, Harunori Nagata
JOURNAL OF PROPULSION AND POWER, 37, 2, 342, 348, Mar. 2021, [Peer-reviewed], [Last author]
English, Scientific journal

GEO-X (GEOspace X-ray imager)
Yuichiro Ezoe, Ryu Funase, Harunori Nagata, Yoshizumi Miyoshi, Satoshi Kasahara, Hiroshi Nakajima, Ikuyuki Mitsuishi, Kumi Ishikawa, Junko S. Hiraga, Kazuhisa Mitsuda, Masaki Fujimoto, Munetaka Ueno, Atsushi Yamazaki, Hiroshi Hasegawa, Yosuke Matsumoto, Yasuhiro Kawakatsu, Takahiro Iwata, Hironori Sahara, Yoshiaki Kanamori, Kohei Morishita, Hiroyuki Koizumi, Makoto Mita, Takefumi Mitani, Masaki Numazawa, Landon Kamps, Yusuke Kawabata
SPACE TELESCOPES AND INSTRUMENTATION 2020: ULTRAVIOLET TO GAMMA RAY, 11444, 2021, [Peer-reviewed]
English, International conference proceedings

Stabilized combustion of circular fuel duct with liquid oxygen
Ayumu Tsuji, Yuji Saito, Landon Kamps, Masashi Wakita, Harunori Nagata
PROCEEDINGS OF THE COMBUSTION INSTITUTE, 38, 3, 4845, 4855, 2021, [Peer-reviewed], [Last author]
English, Scientific journal

Investigation of Graphite Nozzle Erosion in Hybrid Rockets Using Oxygen/High-Density Polyethylene
Landon Kamps, Shota Hirai, Kazuhito Sakurai, Tor Viscor, Yuji Saito, Raymond Guan, Hikaru Isochi, Naoto Adachi, Mitsunori Itoh, Harunori Nagata
JOURNAL OF PROPULSION AND POWER, 36, 3, 423, 434, May 2020, [Peer-reviewed], [Last author]
English, Scientific journal

Experimental Investigation of the Continuous Transition of Flame-Spreading near the Blow-Off Limit
K. Komizu, Y. Saito, A. Tsuji, H. Nagata
Journal of Combustion, 2020, 2020, [Peer-reviewed], [Last author]
Scientific journal

Controlling heat release of crystallization from supercooling state of a solid-solid PCM, 2-amino-2-methyl-1,3-propanediol
Ryohei Gotoh, Tsuyoshi Totani, Masashi Wakita, Harunori Nagata
INTERNATIONAL JOURNAL OF HEAT AND MASS TRANSFER, 137, 1132, 1140, Jul. 2019, [Peer-reviewed], [Last author]
English, Scientific journal

Comprehensive Data Reduction for N2O/HDPE Hybrid Rocket Motor Performance Evaluation
Landon Kamps, Kazuhito Sakurai, Yuji Saito, Harunori Nagata
AEROSPACE, 6, 4, Apr. 2019, [Peer-reviewed], [Last author]
English, Scientific journal

High Pressure Fuel Regression Characteristics of Axial-Injection End-Burning Hybrid Rockets
Yuji Saito, Masaya Kimino, Ayumu Tsuji, Yushi Okutani, Kentaro Soeda, Harunori Nagata
JOURNAL OF PROPULSION AND POWER, 35, 2, 328, 341, Mar. 2019, [Peer-reviewed], [Last author]
English, Scientific journal

Exhaust Heat Characteristics of Single Liquid Droplet Stream for Liquid Droplet Radiator
TAKANASHI Tomohiro, TOTANI Tsuyoshi, SHIMADA Taizo, RYOMON Kento, WAKITA Masashi, NAGATA Harunori
Thermal Science and Engineering, 27, 1, 43, 52, The Heat Transfer Society of Japan, 2019, [Peer-reviewed], [Last author]
Japanese, In order to realize a liquid droplet radiator (LDR), which is an equipment used for waste heat rejection in large space structures, the exhaust heat characteristics of a single liquid droplet stream in vacuum are required. In this study, these characteristics were obtained by a combination of experiments and numerical analyses. Experiments were conducted for measuring the amount of waste heat coming from a single liquid droplet stream of silicone oil as the working fluid, using a radiant flux sensor (RFS). The emissivity of the RFS at low temperature was measured, using a black radiation ball with known emissivity at 26°C. Numerical analyses were also performed to separate the radiation from the background of the experimental apparatus included in the radiation measured by the RFS. It was determined that at approximately -180°C, the emissivity of the RFS falls from the catalog value of 0.8 to 0.5. Moreover, the emissivity of the liquid droplet was found to be approximately in the range 0.42–0.51 and the effective emissivity of the single droplet stream was approximately 0.10. The application of these results can improve the feasibility of LDRs.

Tubular Equivalent Regression Rate in Hybrid Rockets with Complex Geometries
KAMPS Landon, NAGATA Harunori
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 17, 4, 544, 551, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2019, [Peer-reviewed], [Last author]
English,

A new performance parameter titled “tubular equivalent regression rate” is introduced to evaluate burning rates in hybrid rockets with geometrically complex solid propellant grains. Tubular equivalent regression rates are calculated for eight previously reported CAMUI-type hybrid rocket firing tests and compared with extrapolations of previously reported empirical correlations for classic, swirl and vortex hybrid rockets. A non-dimensional number titled “CAMUI Number” is introduced to evaluate how CAMUI-like a solid propellant grain is. The CAMUI Number ranges from 0-1: 0 means no CAMUI-type blocks are used, 1 means only CAMUI-type blocks are used. The results show that the tubular equivalent regression rate increases logarithmically with CAMUI Number, and approaches a value of around 3 [mm/s] for a CAMUI Number of 1. This increase in tubular equivalent regression rate is shown to correspond to an increase in performance range from a classic (tubular) hybrid rocket at low CAMUI Numbers (0.1) to surpassing a vortex hybrid rocket for high CAMUI Numbers (>0.7). Furthermore, through the block-by-block analysis of tubular equivalent regression rate in a fuel grain with a CAMUI Number of 0.71, it is shown that maximum burning rates were achieved in blocks under slightly oxidizer rich conditions.

Error Analysis for CAMUI Type Hybrid Rocket Regression Simulation
TOR Viscor, NAGATA Harunori
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 17, 4, 519, 524, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2019, [Peer-reviewed], [Last author]
English,

This paper describes the error and uncertainty analysis of the CAMUI hybrid rocket regression simulator. Simulation errors compared to test firings are described and followed by an analysis of the potential uncertainties causing this error. For each uncertainty identified, a sensitivity analysis is then performed with the help of a custom-built simulator to evaluate its impact on the simulator accuracy. It was found that uncertainties in LOX travel time, Reynolds number grouping and model assumptions for the first upstream burning surface have the largest impact on the simulator accuracy and are identified as the main focus points for further research.

Study on Hysteresis Characteristics of Axial-injection End-burning Hybrid Rockets under Throttling Operation
Kimino Masaya, Saito Yuji, Okutani Yushi, Tsuji Ayumu, Soeda Kentaro, Nagata Harunori
JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 67, 4, 119, 125, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2019, [Peer-reviewed], [Last author]
Japanese,

In this study, the authors conduced ten firings to investigate a hysteresis characteristics in Axial-Injection End-Burning hybrid rockets under throttling operation. Oxidizer mass flow rate and chamber pressure were throttled by two methods, actuating valves in a fluid circuit consisting of two oxidizer supply lines and a motor controlling. Chamber pressure and oxidizer mass flow rate were measured during each firing. The results show that two types of hysteresis characteristics were observed when throttling operation is repeated. One is a hysteresis with respect to increase and decrease of the oxidizer mass flow rate. Another is a hysteresis for the cycle. It is considered that the former hysteresis has the influence of a chamber pressure response time. In addition, the latter hysteresis is not necessarily observed even in the same chamber pressure region.

Ultralightweight x-ray telescope missions: ORBIS and GEO-X
Yuichiro Ezoe, Yoshizumi Miyoshi, Satoshi Kasahara, Tomoki Kimura, Kumi Ishikawa, Masaki Fujimoto, Kazuhisa Mitsuda, Hironori Sahara, Naoki Isobe, Hiroshi Nakajima, Takaya Ohashi, Harunori Nagata, Ryu Funase, Munetaka Ueno, Graziella Branduardi-Raymont
JOURNAL OF ASTRONOMICAL TELESCOPES INSTRUMENTS AND SYSTEMS, 4, 4, Oct. 2018, [Peer-reviewed]
English, Scientific journal

Preliminary Thermal Design for Microsatellites Deployed from International Space Station's Kibo Module
Delburg P. Mitchao, Tsuyoshi Totani, Masashi Wakita, Harunori Nagata
JOURNAL OF THERMOPHYSICS AND HEAT TRANSFER, 32, 3, 789, 798, Jul. 2018, [Peer-reviewed], [Last author]
English, Scientific journal

Investigation of Throttling Response Characteristics of Axial-Injection End-Burning Hybrid Rockets
Yuji SAITO, Masaya KIMINO, Ayumu TSUJI, Kazunobu OMURA, Hiroyuki YASUKOCHI, Kentaro SOEDA, Tsuyoshi TOTANI, Masashi WAKITA, Harunori NAGATA
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 16, 1, 9, 18, Japan Society for Aeronautical and Space Sciences, 2018
English, Scientific journal

Application of Axial-injection End-burning Hybrid Rockets to Small Spacecraft Propulsion
SAITO Yuji, KIMINO Masaya, SOEDA Kentaro, TOTANI Tsuyoshi, NAGATA Harunori
Aeronautical and Space Sciences Japan, 66, 10, 291, 295, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2018, [Invited], [Last author]
Japanese,

超小型衛星の運用の高機能化および深宇宙探査には，推進器がますます不可欠な存在となる．化学エネルギを用いて大推力を得ることのできる化学ロケットは数km/sの増速が与えられるキックモータになる．主衛星に相乗りする形で打ち上げられる超小型衛星には厳格な安全基準が求められるため，プラスチック等を燃料とするハイブリッドロケットが注目を浴びている．その中でも，端面燃焼式ハイブリッドロケットは，従来型ハイブリッドロケットを凌駕する燃焼特性および推力制御特性が期待されてきた．端面燃焼式ハイブリッドロケットは，燃料製作に困難さを有していたが，高精度3Dプリンタの台頭によって，2014年に実証に成功した．これまでの間，筆者らは数多くの燃焼実験を実施し，研究成果を国内外の学会で発表してきた．本論文では今まで得られた端面燃焼式ハイブリッドロケットの知見をまとめ，今後の課題を紹介する．

Small satellites with MEMS X-ray telescopes for X-ray astronomy and solar system exploration
Yuichiro Ezoe, Yoshizumi Miyoshi, Satoshi Kasahara, Tomoki Kimura, Kumi Ishikawa, Masaki Fujimoto, Kazuhisa Mitsuda, Hironori Sahara, Naoki Isobe, Hiroshi Nakajima, Takaya Ohashi, Harunori Nagata, Ryu Funase, Munetaka Ueno, Graziella Branduardi-Raymont
SPACE TELESCOPES AND INSTRUMENTATION 2018: ULTRAVIOLET TO GAMMA RAY, 10699, 2018, [Peer-reviewed]
English, International conference proceedings

Fuel Regression Characteristics of a Novel Axial-Injection End-Burning Hybrid Rocket
Yuji Saito, Toshiki Yokoi, Hiroyuki Yasukochi, Kentaro Soeda, Tsuyoshi Totani, Masashi Wakita, Harunori Nagata
JOURNAL OF PROPULSION AND POWER, 34, 1, 247, 259, Jan. 2018, [Peer-reviewed], [Last author]
English, Scientific journal

Verification Firings of End-Burning Type Hybrid Rockets
Harunori Nagata, Hayato Teraki, Yuji Saito, Ryuichiro Kanai, Hiroyuki Yasukochi, Masashi Wakita, Tsuyoshi Totani
JOURNAL OF PROPULSION AND POWER, 33, 6, 1473, 1477, Nov. 2017, [Peer-reviewed], [Lead author]
English, Scientific journal

Method for Determining Nozzle-Throat-Erosion History in Hybrid Rockets
Landon Kamps, Yuji Saito, Ryosuke Kawabata, Masashi Wakita, Tsuyoshi Totani, Yusuke Takahashi, Harunori Nagata
JOURNAL OF PROPULSION AND POWER, 33, 6, 1369, 1377, Nov. 2017, [Peer-reviewed], [Last author]
English, Scientific journal

Investigation of axial-injection end-burning hybrid rocket motor regression
Yuji Saito, Toshiki Yokoi, Lukas Neumann, Hiroyuki Yasukochi, Kentaro Soeda, Tsuyoshi Totani, Masashi Wakita, Harunori Nagata
ADVANCES IN AIRCRAFT AND SPACECRAFT SCIENCE, 4, 3, 281, 296, May 2017, [Peer-reviewed], [Last author]
English, Scientific journal

Orbit manipulation by use of lunar swing-by on a hyperbolic trajectory
Shuntaro Suda, Yasuhiro Kawakatsu, Shujiro Sawai, Harunori Nagata, Tsuyoshi Totani
Advances in the Astronautical Sciences, 160, 4027, 4041, 2017
International conference proceedings

Hybrid Propulsion Technology Development in Japan for Economic Space Launch
Toru Shimada, Saburo Yuasa, Harunori Nagata, Shigeru Aso, Ichiro Nakagawa, Keisuke Sawada, Keiichi Hori, Masahiro Kanazaki, Kazuhisa Chiba, Takashi Sakurai, Takakazu Morita, Koki Kitagawa, Yutaka Wada, Daisuke Nakata, Mikiro Motoe, Yuki Funami, Kohei Ozawa, Tomoaki Usuki
CHEMICAL ROCKET PROPULSION: A COMPREHENSIVE SURVEY OF ENERGETIC MATERIALS, 545, 575, 2017, [Peer-reviewed]
English, International conference proceedings

ORBIT MANIPULATION BY USE OF LUNAR SWING-BY ON A HYPERBOLIC TRAJECTORY
Shuntaro Suda, Yasuhiro Kawakatsu, Shujiro Sawai, Harunori Nagata, Tsuyoshi Totani
SPACEFLIGHT MECHANICS 2017, PTS I - IV, 160, 4027, 4041, 2017, [Peer-reviewed]
English, International conference proceedings

Investigation of the Throttling Characteristics of Axial-injection End-burning Hybrid Rockets
SAITO Yuji, YOKOI Toshiki, TSUJI Ayumu, OMURA Kazunobu, YASUKOCHI Hiroyuki, SOEDA Kentaro, TOTANI Tsuyoshi, WAKITA Masashi, NAGATA Harunori
JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 65, 4, 157, 167, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2017, [Peer-reviewed], [Last author]
Japanese, In this study, the authors conducted twice experiments to verify the throttling characteristics of axial-injection end-burning hybrid rockets. Oxidizer mass flow rate and chamber pressure were throttled by actuating valves in a fluid circuit consisting of two oxidizer supply lines. Chamber pressure and oxidizer mass flow rate were measured during each firing. The results show that oxidizer to fuel ratio remains constant for similar values of oxidizer mass flow rate. However, two weak points were identified in these throttling firing tests. First, a pressure transient was observed when oxidizer mass flow rate was increased (turn-up operation). The pressure transient consisted of two distinguishable first order lags, a fast lag followed by a slow lag, which are treated by separate curve fitting functions. The fast response is explained by a thermal lag in the solid fuel, whereas the slow response requires further inquiry. Second, the chamber pressure history exhibited hysteresis characteristics of oxidizer mass flow rate due to the increasing fuel regression rate. Therefore, in the throttling tests where oxidizer flow rate was turned-up and returned to the initial condition twice back-to-back, the chamber pressure history was higher in the second iteration than in the first.

Modified Regression Rate Formula of PMMA Combustion by a Single Plane Impinging Jet
Tsuneyoshi Matsuoka, Kyohei Kamei, Yuji Nakamura, Harunori Nagata
INTERNATIONAL JOURNAL OF AEROSPACE ENGINEERING, 2017, 2017, [Peer-reviewed], [Last author]
English, Scientific journal

Development of Wall Regression Model of Hybrid Rocket Solid Fuel
Kazuya NAWATA, Shunya SASAKI, Tatsuya SAITO, Nobuyuki OSHIMA, Masashi WAKITA, Tsuyoshi TOTANI, Harunori NAGATA
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 14, ists30, 67, 72, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2016, [Peer-reviewed], [Last author]
English, Scientific journal,

The purpose of this study is to develop a computational method to predict fuel regressions for hybrid rocket solid fuels. The shape of the flow field changes depending on the regression and vaporization of the solid fuel. This shape change and the heat flux from the combustion gas to the fuel are mutually dependent. Therefore a computational method that can accurately predicts both of the fuel regression and the heat flux is necessary to clarify the mutual dependence of them. In this study, we have developed a computational method to predict the regression phenomenon including the effect of the shape change of the flow field. The developed code predicts the regression phenomena by repeating gas-phase calculations and regression-phase calculations. The wall consisting of grids permits the flow field to be an arbitrary shape. As the first step, the complex chemical reaction was not included and numerical results were compared with a sublimation phenomenon of naphthalene in a non-combustion flow. Numerical results successfully predicted Nusselt number change due to regression qualitatively.

Influence of Channel Width on Cylindrical Detonation Wave Propagation
Shota KAMEYAMA, Shun NAWATA, Tsunetaro HIMONO, Keita KIKUCHI, Masashi WAKITA, Tsuyoshi TOTANI, Harunori NAGATA
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 14, ists30, 39, 44, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2016, [Peer-reviewed], [Last author]
English, Scientific journal,

To achieve stable detonation wave propagation to large-bore pulse detonation engine (PDE) combustors, we investigated an initiator for PDEs that uses a pre-detonator, reflector, and driver gas. In this initiator, a planar detonation wave from the pre-detonator becomes a cylindrical detonation wave after collision with the reflector. Wakita et al. previously posited two hypotheses regarding the dominant factors that determine the threshold of propagation to the target gas, which is a stoichiometric hydrogen–oxygen mixture diluted with nitrogen. This study reveals whether the threshold is determined by w/λ or λ/r. To analyze the effect of channel width w on the transition of the cylindrical detonation wave, experiments were conducted for w = 10 mm and w = 15 mm. However, the results could not elucidate whether the threshold is determined by λ/r or w/λ. To clearly distinguish between the effects of w/λ and λ/r, a narrow channel width w' = 3 mm was chosen and implemented using a torus-shaped obstacle. The results showed that a cylindrical detonation wave propagates without quenching when the nitrogen concentration is above 40%, corresponding to the cell size λ greater than w. Accordingly, the cylindrical detonation propagation threshold was determined to be independent of w/λ.

Estimation of Hybrid Rocket Nozzle Throat Erosion History
Yuji SAITO, Tsutomu UEMATSU, Hikaru ISOCHI, Masashi WAKITA, Tsuyoshi TOTANI, Harunori NAGATA
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 14, ists30, Pa_145, Pa_151, 2016, [Peer-reviewed], [Last author]
English, Scientific journal

Heat Storage and Release Tests of Heat Storage Material with Crystal Transformation
Tsuyoshi TOTANI, Takuya KUNI, Toshifumi SATOH, Takuya ISONO, Masashi WAKITA, Harunori NAGATA
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 14, ists30, Pi_1, Pi_6, 2016, [Peer-reviewed], [Last author]
English, Scientific journal

Influence of Degradation on Storage of Heat of Heat Storage Material with Crystal Transformation
KUNI TAKUYA, TOTANI TSUYOSHI, SATO TOSHIFUMI, ISONO TAKUYA, WAKITA MASASHI, NAGATA HARUNORI
熱物性, 29, 4, 173, 178, JAPAN SOCIETY OF THERMOPHYSICAL PROPERTIES, Nov. 2015, [Peer-reviewed], [Last author]
Japanese, Trans-1,4-Polybutadiene (TPBD) transforms a crystal structure at the temperature of heat storage. In this study, the molecular structure of TPBD was measured using the Raman spectroscopy. The measurement of the amount of heat storage of TPBD was performed using a differential scanning calorimetry. It is found that there is a correlation between the amount of heat storage and the change of C-H bond by auto-oxidation. A thermal cycle test was carried out to obtain the change of heat storage and release amount of TPBD. The heat storage and release amount was calculated from the obtained temperature history. The heat storage amount became between 60 J/g and 90 J/g. The heat release amount became between -70 J/g and -100 J/g. It is verified that the amount of heat storage of TPBD does not deteriorate during 1700 cycles.

Thermal Analyses of Nano- and Micro- Satellites Pointing to the Earth with Deployable Solar Panel on Sun-synchronous Orbit by Small Number of Nodes　　　　　　　　　　　　　　　
Tilok Kumar DAS, Tsuyoshi TOTANI, Masashi WAKITA, Harunori NAGATA
Mechanical Engineering Research Journal, 9, 79, 85, Mar. 2015, [Peer-reviewed], [Last author]
English, Scientific journal

Rocket Developments in Universities : Past and Future
NAGATA Harunori, YUASA Saburo, WADA Yutaka, NAKAGAWA Ichiro
Journal of the Japan Society for Aeronautical and Space Sciences, 63, 2, 51, 57, 一般社団法人日本航空宇宙学会, Feb. 2015, [Invited], [Lead author]
Japanese, 大学宇宙工学コンソーシアム(UNISEC)設立当初のロケット関連団体の多くはハイブリッドロケット研究会のメンバーであり,この研究会の活動の一環として打上げられた機体が,我が国初のハイブリッドロケットとなった.2002年以降はUNISECを舞台に大学によるロケット関連活動は着実に広がり,打上げ実験が可能な場所も全国各地に整備された.非燃焼式ロケットや有翼実験機の開発等,活動内容の多様化も見られた.一方,大学研究室が開発したロケットは未だに宇宙に到達していない.自主開発ロケットによる宇宙到達は技術的ハードルが高く,UNISECにおけるロケット開発の延長上に宇宙をイメージするのは容易ではない.大学におけるロケット関連活動を活性化させ,ロケットが本来持っている若手技術者への強い訴求力を生かすためには,UNISECにおけるロケット関連活動の延長上に宇宙をイメージさせるための新たな方策が望まれる.

Scale effect on solid fuel regression in CAMUI-type hybrid rocket motor
Harunori Nagata, Mitsunori Ito
Progress in Scale Modeling, Volume II: Selections from the International Symposia on Scale Modeling, ISSM VI (2009) and ISSM VII (2013), 2, 249, 263, Springer International Publishing, 01 Jan. 2015, [Peer-reviewed], [Invited], [Lead author]
English, In book

Analytical Method for Prediction of Suction Performance of Ejector-Jet
Kouichiro Tani, Susumu Hasegawa, Shuichi Ueda, Takeshi Kanda, Harunori Nagata
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 58, 4, 228, 236, 2015, [Peer-reviewed], [Last author]
English, Scientific journal

Accuracy and applicable range of a reconstruction technique for hybrid rockets
Harunori Nagata, Hisahiro Nakayama, Mikio Watanabe, Masashi Wakita, Tsuyoshi Totani
Advances in Aircraft and Spacecraft Science, 1, 3, 273, 289, 01 Jul. 2014, [Peer-reviewed], [Lead author]
English, Scientific journal

Thermal Design Procedure for Micro- and Nanosatellites Pointing to Earth
Tsuyoshi Totani, Hiroto Ogawa, Ryota Inoue, Tilok K. Das, Masashi Wakita, Harunori Nagata
JOURNAL OF THERMOPHYSICS AND HEAT TRANSFER, 28, 3, 524, 533, Jul. 2014, [Peer-reviewed], [Last author]
English, Scientific journal

Influence of detonation cell size on propagation of cylindrical detonation wave
Masashi WAKITA, Kazuya SAJIKI, Tsunetaro HIMONO, Tsuyoshi TOTANI, Harunori NAGATA
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 12, ists29, Pa_1, Pa_7, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, Apr. 2014, [Peer-reviewed], [Last author]
English, Scientific journal, To achieve reliable transmission of detonation wave to a pulse detonation engine (PDE) combustor, authors examined a combination method of "predetonator", "reflector" and "overfilling of the driver gas" experimentally. A detonation wave propagates around our reflector changing its shape through three transition processes; from planer to cylindrical, toroidal, and planar again. Here, successful transmission to self-sustainable expanding cylindrical detonation wave is key issue. The authors used high sensitivity driver gas mixture (stoichiometric H₂-O₂ mixture) for the center of the cylindrical part to make the cylindrical detonation wave transmit in target gas mixture easily. To generalize the influence of the target gas composition on the necessary overfilling radius of the driver gas mixture, we employ stoichiometric H₂-O₂ mixture diluted by nitrogen or argon as target gas mixture. In this study, we showed that the ration of width of the cylindrical path on cell size of propagation limits of both dilution cases are about 1 when the driver gas is supplied enough to create a stable cylindrical detonation wave over 50 mm. Accordingly, when the cell size of the target gas mixture becomes over comparable size to the width of the cylindrical path, the stable expanding cylindrical detonation wave does not sustain.

Heat Storage Material without Phase-change for Micro and Nano Satellite
TOTANI Tsuyoshi, SATOH Toshifumi, WAKITA Masashi, NAGATA Harunori
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN, 12, 29, Po_4_1, Po_4_5, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2014, [Peer-reviewed], [Last author]
English, The thermal analysis of a micro cubic satellite pointing to the Earth on a sun-synchronous and circular orbit has been carried out using one-nodal analysis. The altitude of the orbit is 500 km. The local time of descending node of the orbit is 11 AM. The combination of the solar absorptivity and the infrared emissivity on the surface of the satellite under which the temperature of the satellite is kept within the allowable temperature range, from 0 to 40 degree Celsius, has been clarified. As the heat capacity is larger, the number of the combinations of the solar absorptivity and the infrared emissivity increases. In order to increase the heat capacity of nano and micro satellites, the development of a heat storage material has been performed. It is desirable that the heat storage materials for micro and nano satellites have the characteristic of not phase- change but crystal transformation at heat storage because a container for heat storage material is not required. Trans-1,4- polybutadiene transforms crystal structure at the temperature of heat storage. Trans-1,4-polybutadiene is produced and the heat storage performance is measured. The produced trans-1,4-polybutadiene has the amount of heat storage of about 80 J/g at the heat storage temperature of 74 deg. C. This amount corresponds to about 70% amount of heat storage of a literature data (112 kJ/kg).The density of the produced trans-1,4-polybutadiene is 706 kg/m3.

New Procedure for Thermal Design of Micro- and Nano-satellites Pointing to Earth
TOTANI Tsuyoshi, INOUE Ryota, OGAWA Hiroto, Kumar DAS Tilok, WAKITA Masashi, NAGATA Harunori
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN, 12, 29, Pf_11, Pf_20, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2014, [Peer-reviewed], [Last author]
A new procedure for the thermal design of micro- and nano-satellites is proposed for completing the thermal design of micro- and nano-satellites within about one year. First, two concepts of thermal design are considered for maintaining the temperature change of units within an allowable range. One concept involves decreasing the temperature change of units by using the whole thermal capacity of the micro- and nano-satellite. The other concept involves decreasing the temperature change of the inner structure on which units with a narrow allowable temperature range are mounted and which is insulated conductively from the outer structure. Then, the temperatures of micro- and nano-satellites designed with the former concept are calculated using a one-node analysis method. The temperatures of micro- and nano-satellites designed with the latter concept are calculated using a two-node analysis method. The combinations of optical properties of the structures and units to maintain the temperature of units within the allowable range are obtained by using one- or two-node analysis. Finally, the multinode analyses are carried out to obtain a detailed design based on the optical properties obtained from the one-node analysis or two-node analysis. This thermal design procedure is applied to the Hodoyoshi-1 satellite, which is about 50 cm wide, 50 cm deep, 50 cm high, has a mass of about 50 kg, two inner plates, and solar cells on the body, flies on the Sun-synchronous orbit at the altitude of 500 km, and is pointing to the Earth. The thermal design of this micro-satellite was completed within about ten months. Possible problems with the procedure are tested, and the procedure is verified.

Effect of combustion pressure on regression rate of solid fuel under an impinging oxidizer jet counterflow diffusion flame
Ken Terakawa, Tatsuya Saito, Yuji Nakamura, Tsuneyoshi Matsuoka, Harunori Nagata, Tsuyoshi Totani, Masashi Wakita
JOURNAL OF THERMAL SCIENCE AND TECHNOLOGY, 9, 2, JTST0010, JTST0010, 2014, [Peer-reviewed]
English, Scientific journal

One Nodal Thermal Analysis for Nano and Micro Satellites on Sun-Synchronous and Circular Orbits
Tsuyoshi TOTANI, Hiroto OGAWA, Ryota INOUE, Masashi WAKITA, Harunori NAGATA
Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan, 11, 71, 78, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, Aug. 2013, [Peer-reviewed], [Last author]
English, Scientific journal, One nodal thermal analysis of nano and micro cubic satellites pointing to the Earth on sun-synchronous and circular orbits is carried out. The altitudes of the orbits are from 300 to 1,000 km. The local time of descending node is from 6 to 12. The combinations of the solar absorptivity and the infrared emissivity on the surface of the satellite in which the satellite satisfies the allowable temperature range, from 0 to 40 deg. C., are clarified for each of the above orbits. As the parameter of heat capacity of the satellite over one surface area of the satellite increases, the choice of combinations of the solar absorptivity and the infrared emissivity increases. The number of combinations in the case of the orbits without the shadow region is much larger than that with the shadow region. The number of combinations in the orbits without the shadow region increases with higher altitude and larger projected area with respect to the sun. The number of combinations in the orbits with the shadow region increases with higher altitude, larger projected area and smaller angle of the shadow region.

Geometrical Similarity Condition of Flame Spread in Solid Fuel Tube
MATSUOKA Tsuneyoshi, NAGATA Harunori, NAKAMURA Yuji
Proceedings of the Japan Society for Photoelasticity, 13, 2, 178, 184, The Japanese Society for Experimental Mechanics, Jun. 2013, [Peer-reviewed]
Japanese, A number of studies about flame spread over solid combustibles have been reported over the past few decades. However, there are only a few studies about flame spread in a cylindrical enclosure. Especially, the static characteristics, such as flame height and width, have never been clarified. To reveal a geometrical similarity condition of flame spread in tube, we performed experiments in various conditions. The flame height increased as inner diameter, ambient pressure and oxidizer velocity increased. The non-dimensional flame height, determined as the flame height divided by the inner diameter, was proportional to Reynolds number. The flame spreading in different directions were compared and the shapes were almost similar to each other. It suggested that gravity effect on the flame shape was small. Meanwhile, the flame width did not depend on the flow field, and thus a quenching distance between the flame and the fuel surface was constant. From these results, it was found that the geometrical similarity condition was given by Reynolds number. In addition, considering the heat transfer from the flame to unburned fuel surface, we showed the similarity condition of the dynamic characteristic, i.e., non-dimensional flame spread rate. Also, the condition which can simultaneously satisfy both the static and the dynamic similarity was discussed in this paper.

Ten Years of CAMUI-type Hybrid Rocket
NAGATA Harunori
Journal of the Japan Society of Mechanical Engineers, 116, 1134, 323, 326, The Japan Society of Mechanical Engineers, May 2013, [Invited], [Lead author]
Japanese

Basic Mechanism of Anomalous Combustion on Startup Period of a Hybrid Rocket
NAGATA HARUNORI, IIJIMA NAOZUMI, KANAI RYUICHIRO
日本燃焼学会誌, 54, 170, 251-258, 258, Combustion Society of Japan, Nov. 2012, [Invited], [Lead author]
Japanese, During large scale CAMUI-type motor development, the authors frequently encountered anomalous combustion, a sudden pressure increase leading to destroy of the motor. Repeated static firing tests finally revealed that the cause of the anomalous combustion is the low initial fuel temperature. However, the mechanism responsible for the anomalous combustion is still unclear. Although a series of firing tests with a small combustor could not reproduce the anomalous combustion successfully, results showed a clear correlation between the initial fuel temperature and chamber pressure overshoot; chamber pressure overshoot does not occur when the fuel temperature is above the Leidenfrost point. From this result, the authors offer a hypothesis that the low fuel temperature below the Leidenfrost point enhanced heat transfer from the fuel to liquid oxygen and caused local blowoff. Accumulation of combustible mixture follows the blowoff and may cause the anomalous combustion. A possible reason why the firing tests could not reproduce the anomalous combustion is that Damkohler number in the combustion chamber was larger than those in the large-scale CAMUI-type motors. A preliminary experiment showed that the small combustor could reproduce the anomalous combustion by decreasing the Damkohler number in the combustion chamber. Detailed experimental study will follow the preliminary experiment to clarify the mechanism of the anomalous combustion.

結晶転移する蓄熱材の蓄熱性能
戸谷剛, 佐藤敏文, 脇田督司, 永田晴紀
Thermophys Prop, 33rd, 326-328, Oct. 2012, [Peer-reviewed], [Last author]
Japanese

表面微細周期構造を用いた波長選択性ラジエータの性能
戸谷剛, 脇田督司, 永田晴紀
Thermophys Prop, 33rd, 227-229, Oct. 2012, [Peer-reviewed], [Last author]
Japanese

Transition characteristics of combustion modes for flame spread in solid fuel tube
Tsuneyoshi Matsuoka, Shota Murakami, Harunori Nagata
COMBUSTION AND FLAME, 159, 7, 2466, 2473, Jul. 2012, [Peer-reviewed], [Last author]
English, Scientific journal

Development of Pulse Detonation Engine Initiator Using Reflector for Large Bore Combustor
Masashi WAKITA, Masayoshi TAMURA, Akihiro TERASAKA, Kazuya SAJIKI, Tsuyoshi TOTANI, Harunori NAGATA
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 10, ists28, Pa_31, Pa_36, Japan Society for Aeronautical and Space Sciences, 2012, [Peer-reviewed], [Last author]
English, Scientific journal, To achieve reliable transmission of detonation wave to a pulse detonation engine (PDE) combustor, authors have proposed a PDE initiator, which consists of a predetonator and a reflector. A detonation wave propagates around the reflector changing its shape through three transition processes; from planer to cylindrical, toroidal, and planar again. Our previous study revealed that the transition to the cylindrical detonation wave upstream of the board plays a significant role in detonating hydrogen-air mixture in a 100-mm-diam-combustor. A self-sustainable condition of the cylindrical detonation wave is severe when the radius of the wave front is small. In cases using hydrogen-oxygen mixture as driver gas for the 100-mm-diam-combustor, we had to fulfill with driver gas entire upstream of the board at the critical condition for the transition to the cylindrical wave. On the other hand, curvature of the cylindrical detonation wave front becomes smaller with increasing radius of the front, so the self-sustainable condition of the cylindrical wave must be mitigated for a large bore combustor. In this study, we investigated the necessary filling diameter of the driver gas to detonate hydrogen-air cylindrical detonation by using a 500-mm-diam-cylindrical-combustor.

CAMUI Type Hybrid Rocket as Small Scale Ballistic Flight Testbed
Harunori NAGATA, Tsutomu UEMATSU, Kenichi ITO
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 10, ists28, To_1_1, To_1_5, Japan Society for Aeronautical and Space Sciences, 2012, [Peer-reviewed], [Lead author]
English, Scientific journal, The authors have been developing CAMUI (Cascaded Multistage Impinging-jet) type hybrid rockets, explosive-flee small rocket motors. This is to downsize the scale of suborbital flight experiments on space related technology development. A key idea is a new fuel grain design to increase gasification rates of a solid fuels. By the new fuel grain design, the combustion gas repeatedly impinges on fuel surfaces to hasten the heat transfer to the fuel. Suborbital flight experiments by sounding rockets provide variety of test beds to accumulate basic technologies common to the next step of space development in Japan. By using hybrid rockets one can take the cost advantage of small-scale rocket experiments. This cost advantage improves robustness of space technology development projects by dispersion of risk.

Automatic Circulation Control of Working Fluid in Liquid Droplet Radiator
Tsuyoshi TOTANI, Takuhiro TAKEKOSHI, Masashi WAKITA, Harunori NAGATA
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 10, ists28, Pf_1, Pf_8, Japan Society for Aeronautical and Space Sciences, 2012, [Peer-reviewed], [Last author]
English, Scientific journal, Liquid Droplet Radiator (LDR) is an important candidate for disposing large quantities of waste heat more than 1 MW which will be handled by large space structures such as Space Power Satellite. The working fluid is heated through a heat exchanger by the waste heat generated in a large structure in space. Then, the working fluid is emitted in space through nozzles of the droplet generator toward a droplet collector as multiple streams of droplets. During the flight in space, the droplets lose thermal energy via radiative heat transfer. After the cooled droplets are captured by the droplet collector, the working fluid is recycled to the heat exchanger by a circulating pump. The automatic control system on the circulation of working fluid in a liquid droplet radiator has been built using a programmable logic controller. The proportional control of flow rate with the term of the variation of the counter flow in the gear pump and the relaxation of the change of an target flow rate has succeeded within 5 percent at the automatic circulation control of the working fluid from 100 ml/min to 200 ml/min and from 200 ml/min to 100 ml/min.

Effects of Heat Transfer in Divergent Section of Laval Nozzle on Exhaust Velocity and Area Ratio
Yuki Iwaki, Tsuyoshi Totani, Masashi Wakita, Harunori Nagata
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 54, 185-86, 212, 220, Nov. 2011, [Peer-reviewed], [Last author]
English, Scientific journal

Development and Utilization of CAMUI-type Hybrid Rocket
NAGATA HARUNORI
自動車技術, 65, 10, 56, 61, 自動車技術会, Oct. 2011, [Invited], [Lead author]
Japanese

Optimum Design CAMUI Type Fuel Grain Shape Using Genetic Algorithm
NOHARA MASAHIRO, KANEKO YUDAI, HAGIWARA SHUNSUKE, NAGATA HARUNORI
日本機械学会論文集 B編(Web), 77, 777, WEB ONLY 1249-1258, 1258, The Japan Society of Mechanical Engineers, 2011, [Peer-reviewed], [Last author]
Japanese

Driver Gas Reduction Effect of Pulse-Detonation-Engine Initiator Using Reflecting Board
Masashi Wakita, Ryusuke Numakura, Takatoshi Asada, Masayoshi Tamura, Tsuyoshi Totani, Harunori Nagata
JOURNAL OF PROPULSION AND POWER, 27, 1, 162, 170, Jan. 2011, [Peer-reviewed], [Last author]
English, Scientific journal

Combustion characteristics of the end burning hybrid rockets in laminar flow
Tsuneyoshi Matsuoka, Harunori Nagata
ACTA ASTRONAUTICA, 68, 1-2, 197, 203, Jan. 2011, [Peer-reviewed], [Last author]
English, Scientific journal

Optical Properties of Periodic Microscopic Structures on Ultra Violet Solidification Plastic with Metal Layer
ISHIKAWA Naoyuki, TOTANI Tsuyoshi, WAKITA Masashi, NAGATA Harunori
Thermophysical properties, 31, 0, 118, 120, Nov. 2010, [Peer-reviewed], [Last author]
Japanese

The Effect of Fuel Grain Size on the Combustion Characteristics in the Primary Combustion Chamber of Staged Combustion Hybrid Rocket
Harunori NAGATA, Kenta HASHIBA, Hiroya SAKAI, Tsuyoshi TOTANI, Masashi WAKITA
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 8, ists27, Pa7, Pa11, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, Jul. 2010, [Peer-reviewed], [Lead author]
English, Scientific journal, To clarify the fuel gasification characteristics in a primary combustion chamber of a staged combustion hybrid rocket, the effect of fuel grain size on the regression rate of a grain was investigated experimentally. The grain size distribution in the combustion region achieved a steady state in 30 seconds burning duration. Examining fuel size distributions and fuel consumption rate at steady states, we obtained a history of fuel size and the regression rate of a grain in the combustion region. Regression rate increases with decreasing grain size. With a constant oxidizer flow rate, the regression rate is a function of grain size and independent to the initial grain size. After an initial transient the grain size decreases following the classical d-square law in droplet combustion: The square of the grain size decreases linearly with time. Although why the regression history of a grain in the combustion region follows the d-square law is not clear, this result is useful to estimate the fuel gasification rate of a staged combustion hybrid rocket.

Thermal fluid dynamics for the complicated geometory of hybrid rocket engine using 3-dimentional measurning system
Koichi Kishida, Yudai Kaneko, Nobuyuki Oshima, Harunori Nagata
Nihon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B, 76, 765, 789, 794, Japan Society of Mechanical Engineers, 2010, [Peer-reviewed], [Last author]
Japanese

Effect of Temporal Variations of Internal Ballistics on Fuel Regression Rate in the CAMUI Hybrid Rocket
Yudai KANEKO, Kouichi KISHIDA, Nobuyuki OSHIMA, Takuji NAKASHIMA, Masashi WAKITA, Tsuyoshi TOTANI, Harunori NAGATA
Journal of Space Engineering, 3, 1, 52, 65, Japan Society of Mechanical Engineers, 2010, [Peer-reviewed], [Last author]
English, Scientific journal, In order to clarify the temporal variations of internal ballistics during firing in a cascaded multistage impinging-jet (CAMUI)-type fuel grain, observations of instantaneous flow fields by numerical analysis along with instantaneous grain geometries were conducted. Two static firing tests were conducted under the same conditions, with the exception of firing duration, to obtain the temporal shapes of fuel grains and the characteristics of the regression progress. Two numerical analyses were conducted using the initial and instantaneous geometries to observe internal flow fields. A pair of vortices that is formed near the circumference of the grain due to the change in direction of the flow from the wall jet to the port flow induces a fan-like regression distribution. Two wall jets collide with each other at the center of the grain, roll up and form a fountain-like flow and a pair of gap-scale vortices. These vortices cause an unequal regression distribution on the end faces. On the downstream-end face, the vortices enhance the local regression rate near the axis of the grain. On the forward-end face, in addition to the region near the axis of the grain, the local regression rate at the reattachment points of the vortices increases. These gap-scale vortices disappear as regression progresses because of the dilation of the clearance between the fuel blocks. As a result, the regression rate distributions on both end faces become nearly flat with the progress of fuel regression.

Preliminary Thermal Design of UNITEC-1
Tsuyoshi TOTANI, Haruaki II, Masashi WAKITA, Harunori NAGATA
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 8, ists27, Pf_1, Pf_6, Japan Society for Aeronautical and Space Sciences, 2010, [Peer-reviewed], [Last author]
English, Scientific journal, UNITEC-1 is a nano-spacecraft that flies to Venus. The preliminary thermal design of UNITEC-1 has been carried out. It has been clear from 1 node analysis that slow tumbling of the rotation axis is effective to reduce the temperature variations. It is difficult that both temperatures of the worst-case cold condition and the worst-case hot condition are within the allowable temperature ranges. It is desirable to conduct the survival competition as soon as possible after UNITEC-1 separates from a rocket. It is recommended from this viewpoint to use the black Kapton on the external surface except solar cells. It is clarified from the multi nodes analyses using Thermal Desktop/ SINDA/FLUINT that the temperature of the transmitter changes from 14.8 to 21.0 degree Celsius in an operational sequence under the worst-case cold condition. The temperature change of the battery can be suppressed from 15.5 to 16.6 degree Celsius in an operational sequence under the worst-case cold condition using the insulator between the battery and the internal surface. The maximum difference of temperature occurs between UOBC3 and UOBC6, and is 2.8 K. This difference is enough small to conduct the survival competition under the equal condition. The minimum period for the mission is about 114 days after UNITEC-1 separates from a rocket.

Investigation of an Evaluation Method on the Improvement of Thrust and Specific Impulse by Nozzle Heating
Tetsushi NAGANUMA, Yuuki IWAKI, Shunya SATO, Tsuyoshi TOTANI, Masashi WAKITA, Harunori NAGATA
Journal of the Japan Society for Aeronautical and Space Sciences, 58, 677, 171, 177, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2010, [Peer-reviewed], [Last author]
Japanese, A numerical analysis program is created to research effect of heat transfer for propellant flow in Laval nozzle and estimate improvements of thrust and specific impulse. Several types of gases are assumed as propellant. The energy ratio is defined as ratio of energy supplied to propellant by convective heat transfer to enthalpy of propellant at the inlet of nozzle. The energy ratio increases with elongating length of divergent nozzle, and finally becomes maximum value that depends on Prandtl number, propellant temperature and wall temperature at the inlet of nozzle. The conversion efficiency is defined as ratio of energy conversion to kinetic energy with nozzle to energy supplied to propellant. The conversion efficiency increases with elongating of divergent nozzle, and depends on profile of supplied heat.

EFFECT OF JET VELOCITY ON SCALE EFFECT IN OXIDIZER IMPINGING REGION
Yudai Kaneko, Mitsunori Itoh, Massasi Wakita, Tsuyoshi Totani, Harunori Nagata
Advances in the Astronautical Sciences, 138, 629, +, 2010, [Peer-reviewed], [Last author]
English, International conference proceedings

REGRESSION PROGRESS OF FUEL GRAIN IN CAMUI TYPE HYBRID ROCKET MOTOR
Harunori Nagata, Akihito Kakikura, Mitsunori Ito, Yudai Kaneko, Kazuhiro Mori, Kenta Ueshima, Tsutomu Uematsu, Tsuyoshi Totani
Advances in the Astronautical Sciences, 138, 611, +, 2010, [Peer-reviewed], [Last author]
English, International conference proceedings

Preliminary Design of Winged Experimental Rocket by University Consortium
WAKITA Masashi, YONEMOTO Koichi, AKIYAMA Tomoki, ASO Shigeru, KOHSETSU Yuji, NAGATA Harunori
Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan, 7, ists26, Tg_21-Tg_26, Tg_26, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2009, [Peer-reviewed], [Last author]
English, The project of Winged Experimental Rocket described here is a proposal by the alliance of universities (University Consortium) expanding and integrating the research activities of reusable space transportation system performed by individual universities, and is the proposal that aims at flight proof of the results of advanced research conducted by the universities and JAXA using the university-centered experimental launch systems. This paper verifies the validity of the winged experimental rocket by surveying the technical issues that should be demonstrated and by estimating the airframe scale, weight and finally the total cost. The development schedule of this project was set to five years, where two airframes of different scales will be developed to minimize the risks. A 1.5-meter-long airframe will be first manufactured and conduct flight tests in the third year to verify the design issues. Then, a 2.5-meter-long airframe will be finally developed and conduct a complete flight demonstration of various research issues in the fifth year.

Development of 90 kgf Class CAMUI Hybrid Rocket for a CanSat Experiment
NAGATA Harunori, UEMATSU Tsutomu, ITO Mitsunori, KAKIKURA Akihito, KANEKO Yudai, MORI Kazuhiro, MURAI Norikazu, SATO Tatsuhiro, MITSUHASHI Ryuichi, TOTANI Tsuyoshi
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 7, ists26, Tu_1-Tu_5, Tu_5, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2009, [Peer-reviewed], [Lead author]
English, A newly designed CAMUI hybrid rocket motor of 900 N (90 kgf) thrust class, CAMUI-90, was developed. It uses a combination of polyethylene and liquid oxygen as propellants. CAMUI hybrid rocket is an explosive-flee small rocket motor to realize a small launch system with low cost and flexibility. The motor produces a thrust of 900 N for four seconds, keeping the optimal characteristic exhaust velocity of the fuel-oxidizer combination (exceeding 1800 m/s). A main application of the CAMUI-90 motor is for a CanSat experiment. A launch vehicle employing CAMUI-90 motor, 120 mm in diameter and 3.05 m in length, accelerates a payload of 500 g to 140 m/s in four seconds and reaches to an altitude of about 1 km. The first launch of this vehicle was on December 2006.

Fuel Regression Rate Behavior of CAMUI Hybrid Rocket
Yudai KANEKO, Mitsunori ITOH, Akihito KAKIKURA, Kazuhiro MORI, Kenta UEJIMA, Takuji NAKASHIMA, Masashi WAKITA, Tsuyoshi TOTANI, Nobuyuki OSHIMA, Harunori NAGATA
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN, 7, ists26, Pa_77, Pa_80, Japan Society for Aeronautical and Space Sciences, 2009, [Peer-reviewed], [Last author]
English, Scientific journal, A series of static firing tests was conducted to investigate the fuel regression characteristics of a Cascaded Multistage Impinging-jet (CAMUI) type hybrid rocket motor. A CAMUI type hybrid rocket uses the combination of liquid oxygen and a fuel grain made of polyethylene as a propellant. The collision distance divided by the port diameter, H/D, was varied to investigate the effect of the grain geometry on the fuel regression rate. As a result, the H/D geometry has little effect on the regression rate near the stagnation point, where the heat transfer coefficient is high. On the contrary, the fuel regression rate decreases near the circumference of the forward-end face and the backward-end face of fuel blocks. Besides the experimental approaches, a method of computational fluid dynamics clarified the heat transfer distribution on the grain surface with various H/D geometries. The calculation shows the decrease of the flow velocity due to the increase of H/D on the area where the fuel regression rate decreases with the increase of H/D. To estimate the exact fuel consumption, which is necessary to design a fuel grain, real-time measurement by an ultrasonic pulse-echo method was performed.

Thermal Design of a Solar Thermal Thruster for Piggyback Satellites
Yuuki IWAKI, Tsuyoshi TOTANI, Harunori NAGATA
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN, 7, ists26, Pb_71, Pb_76, Japan Society for Aeronautical and Space Sciences, 2009, [Peer-reviewed], [Last author]
English, Scientific journal, A method of thermal analysis for a solar thermal thruster was created to aid in the thermal design of the thruster. The method consists of two types of thermal analysis: an analysis program for propellant flow, and an analysis of the temperature distribution of the thruster wall using Pro/Engineer. The numerical results were compared with experimental results to confirm the validity of the method, and there was good agreement between them. A thermal design was created using this thermal analysis method to estimate the performance of a solar thermal thruster for the orbital transfer of piggyback satellites mounted on an H2A rocket. When the thruster is made from heat-resistant steel and the propellant is water, the analytical results showed that the Isp is 203 s, the thrust is 16.6 mN, and the maximum temperature of the thruster is 1088 K. The diameter of the concentrator also was calculated, and it was found to be small enough for the concentrator to be mounted on piggyback satellites.

Fuel Regression Characteristics of Cascaded Multistage Impinging-Jet (CAMUI) Type Hybrid Rocket
ITOH Mitsunori, MAEDA Takenori, KAKIKURA Akihito, KANEKO Yudai, MORI Kazuhiro, NAKASHIMA Takuji, WAKITA Masashi, UEMATSU Tsutomu, TOTANI Tsuyoshi, OSHIMA Nobuyuki, NAGATA Harunori
JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 55, 646, 516, 526, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, Nov. 2007, [Peer-reviewed], [Last author]
Japanese, A series of lab-scale firing tests was conducted to investigate the fuel regression characteristics of Cascaded Multistage Impinging-jet (CAMUI) type hybrid rocket. The alternative fuel grain used in this rocket consists of a number of cylindrical fuel blocks with two ports, which were aligned along the axis of the combustion chamber with a small gap. The ports are aligned staggered with respect to ones of neighboring blocks so that the combustion gas flow impinges on the forward-end surface of each block. In this fuel grain, forward-end surfaces, back-end surfaces and ports of fuel blocks ...

Detonation transition limit at an abrupt area change using a reflecting board
Masashi Wakita, Ryusuke Numakura, Yusuke Itoh, Shigetoshi Sugata, Tsuyoshi Totani, Harunori Nagata
JOURNAL OF PROPULSION AND POWER, 23, 2, 338, 344, Mar. 2007, [Peer-reviewed], [Last author]
English, Scientific journal

Determining factor for the blowoff limit of a flame spreading in an opposed turbulent flow, in a narrow solid-fuel duct
Nozomu Hashimoto, Harunori Nagata, Tsuyoshi Totani, Isao Kudo
COMBUSTION AND FLAME, 147, 3, 222, 232, Nov. 2006, [Peer-reviewed]
English, Scientific journal

Promoting Effect of a Reflecting Board on the Diffraction of a Detonation Wave through a Mixture Change
NUMAKURA Ryusuke, WAKITA Masashi, ITOH Yusuke, SUGATA Shigetoshi, NAGATA Harunori, TOTANI Tsuyoshi, KUDO Isao
Journal of the Combustion Society of Japan, 48, 145, 265, 272, Combustion Society of Japan, Aug. 2006, [Peer-reviewed]
Japanese, To realize a quick initiation of detonation in insensitive fuel-air mixtures in the combustion chamber of a PDE operating in the air-breathing mode, the authors have proposed a new detonation initiator using a circular disk as a "reflecting board" near the exit of a predetonator tube. When a fuel-oxygen mixture fills the predetonator tube as a driver gas, the mixture change and the abrupt area change occur simultaneously at the exit. This paper describes the promoting effect of the reflecting board on the detonation transition through the mixture change. The combustible mixtures in the combustion chamber are stoichiometric hydrogen-oxygen mixtures diluted with nitrogen. Main results obtained in this study are in the followings: The detonation wave maintains the propagation velocity in the fuel-oxygen mixture right after the abrupt area change, this results in the increase of the distance at which the head of a rarefaction wave reaches the axis of the predetonator and the incident planar detonation wave disappears. Because the cell size right after the abrupt area change is near the size of the fuel-oxygen mixture, the cylindrical detonation wave survives the axial expansion even when the reflecting board separation is less than the propagation limit of the cylindrical detonation wave propagating in the diluted mixture.

Numerical and experimental studies on circulation of working fluid in liquid droplet radiator
T Totani, T Kodama, K Watanabe, K Nanbu, H Nagata, Kudo, I
ACTA ASTRONAUTICA, 59, 1-5, 192, 199, Jul. 2006, [Peer-reviewed]
English, Scientific journal

Development of CAMUI hybrid rocket to create a market for small rocket experiments
Harunori Nagata, Mitsunori Ito, Takenori Maeda, Mikio Watanabe, Tsutomu Uematsu, Tsuyoshi Totani, Isao Kudo
ACTA ASTRONAUTICA, 59, 1-5, 253, 258, Jul. 2006, [Peer-reviewed], [Lead author]
English, Scientific journal

Re-Initiation Mechanisms of a Detonation Wave in the PDE Initiator Using a Reflecting Board
WAKITA Masashi, NUMAKURA Ryusuke, ITO Yusuke, NAGATA Harunori, TOTANI Tsuyoshi, KUDO Isao
JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 53, 620, 414, 418, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 05 Sep. 2005
Japanese, Quick initiation of a detonation wave in a combustion chamber is important to realize high-performance pulse detonation engine. A possible method is to generate a detonation wave in a pre-detonator and release the detonation wave into the chamber. In this paper, a reflecting board is installed in the combustion chamber near the pre-detonator exit where the tube diameter expands abruptly. It prevents the detonation wave from disappearing at the expanding region near the tube exit. The re-initiation mechanisms of a detonation wave near the reflecting board were observed by using the soot film...

Numerical Simulation of the Flow Field in the Cascaded Multistage Impinging-Jet (CAMUI) Hybrid Rocket
WATANABE Mikio, NAGATA Harunori, TOTANI Tsuyoshi, KUDO Isao
JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 53, 618, 337, 342, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 05 Jul. 2005
Japanese, The authors have proposed an advanced fuel configuration to overcome the defect of conventional hybrid rockets, i.e., the low thrust level. The key feature of this new type of hybrid rocket, named Cascaded Multi-staged Impinging jet (CAMUI), is that the cylindrical fuel blocks with two ports parallel to the axis are arranged in a row in the combustion chamber. This fuel configuration allows mixing and combustion to occur in and around the impinging jet regions. In the present paper, a CFD simulation clarifies the fundamental features of the flow field and the heat transfer distributions in ...

Thermal design of liquid droplet radiator for space solar-power system
T Totani, T Kodama, H Nagata, Kudo, I
JOURNAL OF SPACECRAFT AND ROCKETS, 42, 3, 493, 499, May 2005
English, Scientific journal

Re-Initiation Mechanisms of a Detonation Wave in the PDE Initiator Using a Reflecting Board
WAKITA Masashi, NUMAKURA Ryusuke, ITO Yusuke, NAGATA Harunori, TOTANI Tsuyoshi, KUDO Isao
JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 53, 620, 414, 418, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2005
Japanese, Quick initiation of a detonation wave in a combustion chamber is important to realize high-performance pulse detonation engine. A possible method is to generate a detonation wave in a pre-detonator and release the detonation wave into the chamber. In this paper, a reflecting board is installed in the combustion chamber near the pre-detonator exit where the tube diameter expands abruptly. It prevents the detonation wave from disappearing at the expanding region near the tube exit. The re-initiation mechanisms of a detonation wave near the reflecting board were observed by using the soot film method. Main results obtained in this study are in the followings: Re-initiation of a detonation wave due to the Mach reflection of a shock wave is observed on the surface of the reflecting board and the propagation promoting effect is observed. The effectiveness of the reflecting board is a strong function of the clearance between the pre-detonator exit and the reflecting board, and the promotion effect sharply decreases with increasing the clearance beyond the distance, in which the incident planar detonation wave maintains. By equipping with a reflective board with a suitable clearance, the critical cell size increases by 2 or 3 times.

Experimental study on convergence of droplet streams under microgravity
T Totani, T Kodama, K Watanabe, H Nagata, Kudo, I
MICROGRAVITY SCIENCE AND TECHNOLOGY, 17, 3, 31, 38, 2005
English, Scientific journal

Development of CAMUI Hybrid Rocket and Application to Microgravity Rocket Experiment
Harunori Nagata
INTERNATIONAL JOURNAL OF MICROGRAVITY SCIENCE AND APPLICATION, 22, 1, 47, 2005
Japanese

Current Status of Rocket Developments in Universities – Development of CAMUI Hybrid Rocket
Nagata, H, Itoh, M, Maeda, T, Kato, R, Totani, T, Kudo, I, Uematsu, T
Journal of Space Technology and Science, 21, 1, 31, 38, 2005, [Peer-reviewed], [Lead author]
English, Scientific journal

Behavior of Concentration and Collision of Droplet Streams under Microgravity
TOTANI Tsuyoshi, KODAMA Takuya, WATANABE Kensuke, NAGATA Harunori, KUDO Isao
JASMA : Journal of the Japan Society of Microgravity Application = 日本マイクログラビティ応用学会誌, 21, 0, 14, 14, 04 Nov. 2004, [Peer-reviewed]
English

Totani, T., Nagata, H., Kudo, I. and Iwasaki, A.: "Measurement Technique for Pumping Performance of a Centrifugal Collector under Microgravity", Review of Scientific Instruments, 75(2): 515-523 (2004)*　　　　　　　　　　　　　　　
2004, [Peer-reviewed]

Relationship between platinum wire temperature and catalytic heat release rate on platinum in unsteady-state hydrogen-air mixture
Daisuke Nakamura, Harunori Nagata, Tsuyoshi Totani, Isao Kudo
Heat Transfer - Asian Research, 33, 1, 1, 11, Jan. 2004, [Peer-reviewed]
English

Leading Studies of the Staged Combustion Hybrid Rocket
AKIBA Ryojiro, AOKI Yoshinori, KAYUTA Seiyu, FUJII Atushi, NAGATA Harunori, SATORI Shin
JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 51, 591, 141, 150, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 05 Apr. 2003
Japanese, The staged combustion hybrid rocket is under development by our research group since 1999. This hybrid rocket engine consists of two combustion chambers. The primary combustion chamber is the fuel tank itself filled with granular solid fuels. The fuel rich gas generated by the first stage combustion flows into the secondary combustion chamber, which is located in the bottom of the primary combustion chamber. The additional oxidizer is injected to the secondary combustion chamber in order to attain an optimal specific impulse by completing combustion. There are two types of the primary combu...

Verification Tests on the Functions of the Liquid Droplet Radiator Elements under the short-Duration Microgravity Environment
TOTANI Tsuyoshi, NAGATA Harunori, KUDO Isao
JASMA, 20, 1, 22, 29, The Japan Society of Microgravity Application, 31 Jan. 2003
Japanese, The liquid droplet radiator (LDR) is an important candidate to resolve an technical issue that is how to reject of large quantities of waste heat from large structures in space, which handle high power (from megawatts to gigawatts). The performance of LDR elements under microgravity condition has been investigated. It has been clarified that (1) the diameters of droplets and spacing between droplets generated under microgravity can be formulated by the equations based on the law of conservation of mass in the process of generating droplets, (2) the uniform droplet stream is captured under microgravity without splashes, (3) the pumping performance of the working fluid of the centrifugal droplet collector under microgravity can be predicted by the sum of velocity head and pressure head generated in the gyrostatic flow, (4) the gear pump can also function normally under microgravity.

Hashimoto, N., Watanabe, S., Nagata, H., Totani, T., Kudo, I.:"Opposed-Flow Flame Spread in a Circular Duct of a Solid Fuel: Influence of Cannel Height on Spread Rate", Proceedings of the Combustion Institute, Vol.29, pp.245-250, 2003.*　　　　　　　　　　　　　　　
2003

Relation of Pt Wire Temperature and Catalytic Heat Release Rate on Pt in Unsteady State of H2-Air Mixture.
NAKAMURA Daisuke, NAGATA Harunori, TOTANI Tsuyoshi, KUDO Isao
TRANSACTIONS OF THE JAPAN SOCIETY OF MECHANICAL ENGINEERS Series B, 69, 677, 126, 131, The Japan Society of Mechanical Engineers, 2003
Japanese, The authors have proposed a hydrogen concentration probe using catalytic reaction on Pt wire surface. To use this probe to detect a concentration change in a supersonic mixing layer, the response of the catalytic heat release rate must depend only on concentration change around the probe. Catalytic heat release rate on the Pt wire surface in unsteady state is measured using a constant temperature type hotwire anemometer technique and a shock tube to investigate the relation of the response of the catalytic heat release rate and Pt wire temperature. Catalytic heat release rate begins increasing at the arrival of the shock wave. The increasing rate of the catalytic heat release depends on the Pt wire temperature when the wire temperature is low. However, the dependence is very weak when the wire temperature is over about 680 K. This shows that not the catalytic reaction but molecular transfer from the flow to the Pt wire surface is the controlling step when Pt wire temperature is high enough. As a conclusion, the Pt wire temperature over about 680 K is necessary to use the hydrogen concentration probe in a supersonic mixing layer.

Leading Studies of the Staged Combustion Hybrid Rocket
AKIBA Ryojiro, AOKI Yoshinori, KAYUTA Seiyu, FUJII Atushi, NAGATA Harunori, SATORI Shin
JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 51, 591, 141, 150, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2003
Japanese, The staged combustion hybrid rocket is under development by our research group since 1999. This hybrid rocket engine consists of two combustion chambers. The primary combustion chamber is the fuel tank itself filled with granular solid fuels. The fuel rich gas generated by the first stage combustion flows into the secondary combustion chamber, which is located in the bottom of the primary combustion chamber. The additional oxidizer is injected to the secondary combustion chamber in order to attain an optimal specific impulse by completing combustion. There are two types of the primary combustion. One is nicknamed as the incinerator type; the other is called the multi-grain type. This new type engine is featured with a wide range throttling capability and an extensive freedom in selecting the fuel material. This paper deals with the incinerator type. Presented are preliminary experiments as well as the systems description.

Relation of Pt wire temperature and catalytic heat release rate on Pt in unsteady state of H2-air mixture
Daisuke Nakamura, Harunori Nagata, Tsuyoshi Totani, Isao Kudo
Nippon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B, 69, 677, 126, 131, Japan Society of Mechanical Engineers, 2003
Japanese, Scientific journal

Opposed-flow flame spread in a circular duct of a solid fuel: Influence of channel height on spread rate
N Hashimoto, S Watanabe, H Nagata, T Totani, Kudo, I
PROCEEDINGS OF THE COMBUSTION INSTITUTE, 29, 245, 250, 2003, [Peer-reviewed]
English, Scientific journal

Development study of Hybrid Rocket Booster for Ballistic Lounch of Small Satellite
WATANABE Mikio, NAKAYAMA Hisahiro, NAGATA Harunori, TOTANI Tsuyoshi, KUDO Isao, ITO Kenichi, OOWADA Youichi
JASMA, 19, 2, 112, 116, The Japan Society of Microgravity Application, 30 Apr. 2002
Japanese, For the use of ballistic launches of a small satellite, the development study of a high thrust hybrid rocket motor has been made. To enhance the regression rate of the solid fuel and augment the thrust, the authors employed a new fuel configuration. This new configuration allows mixing and combustion to occur around the stagnation points on solid fuel surfaces. The static firing tests using a LOX/PMMA hybrid motor with a LOX cooling system have proved sufficiently prompt ignition, high thrust level, and stable combustion. Based on the obtained data, a flight performance of a small hybrid rocket for a ballistic test launch was estimated.

インターネットを利用したコラボレーション支援環境の構築とその運用
吉川 茂雄, 戸谷 剛, 永田 晴紀
日本ディスタンスラーニング学会会誌, 3, 0, 19, 25, 日本ディスタンスラーニング学会, Mar. 2002
Japanese

Flame shapes of fuel droplet cloud in high temperature gaseous environment under micro-gravity
H Enomoto, H Nagata, D Segawa, T Kadota
JSME INTERNATIONAL JOURNAL SERIES B-FLUIDS AND THERMAL ENGINEERING, 45, 1, 102, 107, Feb. 2002, [Peer-reviewed]
English, Scientific journal

Nagata, H., Kudo, I., Ito, K., Nakamura, S., Takeshita, Y.:"Interactive Combustion of Two-dimensionally Arranged Quasi-droplet Clusters under Microgravity", Combustion and Flame, 129:392-400(2002)*　　　　　　　　　　　　　　　
2002

Performance test under microgravity on a centrifugal droplet collector for liquid droplet radiator
Tsuyoshi Totani, Masahiro Itami, Shigeru Yabuta, Harunori Nagata, Isao Kudo, Akira Iwasaki, Shunsuke Hosokawa
Nippon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B, 68, 674, 2780, 2787, Japan Society of Mechanical Engineers, 2002
Japanese

Totani, T., Itami, M., Nagata, H., Kudo, I., Iwasaki, A., Hosokawa, S.:"Performance of Droplet Collector in Liquid Droplet Radiator under Microgravity", Microgravity Science and Technology, 13(2):42-45(2002)*　　　　　　　　　　　　　　　
2002

Performance of droplet emittor for liquid droplet radiator under microgravity
Tsuyoshi Totani, Masahiro Itami, Shigeru Yabuta, Harunori Nagata, Isao Kudo, Akira Iwasaki, Shunsuke Hosokawa
Nippon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B, 68, 668, 1166, 1173, Japan Society of Mechanical Engineers, 2002
Japanese

「小型衛星のためのハイブリッドロケットの打ち上げ機の開発」　　　　　　　　　　　　　　　
『日本マイクログラビティ応用学会誌』, 19, 2, 112, 116, 2002

Performance of droplet emittor for liquid droplet radiator under microgravity
Tsuyoshi Totani, Masahiro Itami, Shigeru Yabuta, Harunori Nagata, Isao Kudo, Akira Iwasaki, Shunsuke Hosokawa
Nippon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B, 68, 668, 1166, 1173, Japan Society of Mechanical Engineers, 2002
Japanese, Scientific journal

Performance test under microgravity on a centrifugal droplet collector for liquid droplet radiator
Tsuyoshi Totani, Masahiro Itami, Shigeru Yabuta, Harunori Nagata, Isao Kudo, Akira Iwasaki, Shunsuke Hosokawa
Nippon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B, 68, 674, 2780, 2787, Japan Society of Mechanical Engineers, 2002
Japanese, Scientific journal

An Experimental Test on Circulation of the Working Fluid in Liquid Droplet Radiator under Microgravity
TOTANI Tsuyoshi, YABUTA Shigeru, MIYAMOTO Takuya, NAGATA Harunori, KUDO Isao
JASMA : Journal of the Japan Society of Microgravity Application, 18, 0, 87, 87, 01 Oct. 2001
English

A Preliminary Study of End-Burning Hybrid Rocket:Part 2 Combustion Characteristics
HASHIMOTO Nozomu, KATO Takahiro, NAGATA Harunori, KUDO Isao
JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 49, 565, 40, 47, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 05 Feb. 2001
Japanese, To overcome defects of conventional hybrid rockets such as the loss of specific impulse, which is caused by the O/F shift during the combustion, and the low combustion efficiency, the authors have proposed a new idea of design. The point of this idea, named “End-Burning Hybrid Rocket, ” is that oxidizer gas flows in the gap space of a porous solid fuel bed. Diffusion flame is formed at the end of the solid fuel bed. Experimental studies were made to clarify the basic combustion characteristics of the propellant. Results show that pressure exponent of the burning rate with the same equivalence ratio is approximately 0.85 and virtually independent with the equivalence ratio. Using this result, a designing method of End-Burning Hybrid Rocket Motor is shown. Finally, thrust and specific impulse is estimated as functions of oxidizer gas flow rates to investigate the throttling characteristics of the motor.

A Preliminary Study of End-Burning Hybrib Rocket:Part 1 Combustion Stability
KATO Takahiro, HASHIMOTO Nozomu, NAGATA Harunori, KUDO Isao
JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 49, 565, 33, 39, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 05 Feb. 2001
Japanese, To overcome defects of conventional hybrid rockets such as low combustion efficiency and the O/F shift during the combustion, the authors have proposed a new form of hybrid rocket fuel. The fuel is a fibrous bed in which oxidizer gas flows. Stable diffusion flame appears at the exit surface. Previous researches show that sudden increase of the fuel regression rate occurs with the increase of ambient pressure. This sudden increase is attributed to the flame spreading between fuel fibers. To clarify the limit of fuel gap space the diffusion flame can spread into, experimental study was made. Critical gap space, which means the minimum gap space the diffusion flame can spread into, was obtained experimentally as a function of oxygen gas flow velocity and ambient pressure. Using this result, necessary conditions to realize a stable combustion with this new fuel form are shown.

A Preliminary Study of End-Burning Hybrid Rocket. Part 1. Combustion Stability.
KATO Takahiro, HASHIMOTO Nozomu, NAGATA Harunori, KUDO Isao
JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 49, 565, 33, 39, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2001
Japanese, To overcome defects of conventional hybrid rockets such as low combustion efficiency and the O/F shift during the combustion, the authors have proposed a new form of hybrid rocket fuel. The fuel is a fibrous bed in which oxidizer gas flows. Stable diffusion flame appears at the exit surface. Previous researches show that sudden increase of the fuel regression rate occurs with the increase of ambient pressure. This sudden increase is attributed to the flame spreading between fuel fibers. To clarify the limit of fuel gap space the diffusion flame can spread into, experimental study was made. Critical gap space, which means the minimum gap space the diffusion flame can spread into, was obtained experimentally as a function of oxygen gas flow velocity and ambient pressure. Using this result, necessary conditions to realize a stable combustion with this new fuel form are shown.

Harunori NAGATA, Masahiro SASAKI, Takakage ARAI, Tsuyoshi TOTANI, Isao KUDO, "Evaluation of Mass Transfer Coefficient and Hydrogen Concentration in Supersonic Flow by Using Catalytic Reaction," Proceedings of the Combustion Institute, 28: 713-719, 2001.*　　　　　　　　　　　　　　　
2001

Deployments of Inflatable Tubes with a Plastic Fold under Microgravity
Tsuyoshi Totani, Takayuki Ushio, Harunori Nagata, Isao Kudo
Nihon Kikai Gakkai Ronbunshu, C Hen/Transactions of the Japan Society of Mechanical Engineers, Part C, 67, 655, 633, 640, 2001
English, Scientific journal

Hydrogen concentration of 2-D supersonic air-hydrogen mixing layer using platinum catalytic reaction
Takakage Arai, Jiro Kasahara, Junji Miura, Fuminori Sakima, Harunori Nagata
Nihon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B, 67, 656, 934, 939, Japan Society of Mechanical Engineers, 2001
Japanese, Scientific journal

A Preliminary Study of End-Burning Hybrid Rocket. Part 2. Combustion Characteristics.
HASHIMOTO Nozomu, KATO Takahiro, NAGATA Harunori, KUDO Isao
JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 49, 565, 40, 47, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2001
Japanese, To overcome defects of conventional hybrid rockets such as the loss of specific impulse, which is caused by the O/F shift during the combustion, and the low combustion efficiency, the authors have proposed a new idea of design. The point of this idea, named “End-Burning Hybrid Rocket, ” is that oxidizer gas flows in the gap space of a porous solid fuel bed. Diffusion flame is formed at the end of the solid fuel bed. Experimental studies were made to clarify the basic combustion characteristics of the propellant. Results show that pressure exponent of the burning rate with the same equivalence ratio is approximately 0.85 and virtually independent with the equivalence ratio. Using this result, a designing method of End-Burning Hybrid Rocket Motor is shown. Finally, thrust and specific impulse is estimated as functions of oxidizer gas flow rates to investigate the throttling characteristics of the motor.

Deployments of Inflatable Tubes with a Plastic Fold under Microgravity
Tsuyoshi Totani, Takayuki Ushio, Harunori Nagata, Isao Kudo
Nihon Kikai Gakkai Ronbunshu, C Hen/Transactions of the Japan Society of Mechanical Engineers, Part C, 67, 655, 633, 640, The Japan Society of Mechanical Engineers, 2001
English

Hydrogen concentration of 2-D supersonic air-hydrogen mixing layer using platinum catalytic reaction
Takakage Arai, Jiro Kasahara, Junji Miura, Fuminori Sakima, Harunori Nagata
Nihon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B, 67, 656, 934, 939, Japan Society of Mechanical Engineers, 2001
Japanese

Performance of Liquid Droplet Radiator Elements (collector and gear pump) Under Microgravity
TOTANI Tsuyoshi, YABUTA Shigeru, NAGATA Harunori, KUDO Isao, IWASAKI Akira, HOSOKAWA Syunsuke
J. Jpn. Soc. Microgravity Appl., 17, 0, 18, 19, 01 Oct. 2000
English

Combustion Characteristics of Propellants for End-burning Hybrid Rockets
NAGATA Harunori, HASHIMOTO Nozomu, KATO Takahiro, FUJITA Osamu, ITO Kenichi, KUDO Isao, AKIBA Ryojiro
JASMA, 17, 3, 172, 177, The Japan Society of Microgravity Application, 31 Jul. 2000
Japanese, Experimental investigations are carried out about the combustion of new form of hybrid rocket propellants, in which oxidizer gas flows gap space in a fibrous fuel bed, under normal and micro gravity conditions. The new form of propel­lant has a potential to improve combustion efficiency and thrust level of hybrid rocket motors. Regression rates of fibrous strand fuels are measured with lower oxygen gas flow rates of near the combustion limit. Main results are in the followings: Gravity effects decrease with decreasing the oxygen gas flow rate until the effect almost diminishes near the combustion limit. In a certain range of oxygen gas flow rates near the combustion limit, the equivalence ratio keeps a constant value. The range of oxygen gas flow rates, in which equivalence ratio is constant, does not depend on the am­bient pressure.

Kentaro TAKAHASHI, Harunori NAGATA, Isao KUDO, "Behavior Monitoring of the Deployment of an Inflatable Disk under Microgravity for a Cold Welding Test Satellite," Space Forum, Vol. 6, pp. 397-402, 2000.　　　　　　　　　　　　　　　
2000

Sosuke NAKAMURA, Harunori NAGATA, Isao KUDO, Kenichi ITO, Yasuhiro TAKESHITA, "Research on Flame Shape of Spherical Quasi-Liquid Samples under Microgavity Conditions," Space Forum, Vol. 6, pp. 329-334, 2000.　　　　　　　　　　　　　　　
2000

Performance Test of Liquid Droplet Radiator Elements Under Microgravity
ITAMI Masahiro, TOTANI Tsuyoshi, NAGATA Harunori, KUDO Isao, IWASAKI Akira, HOSOKAWA Shunsuke
J. Jpn. Soc. Microgravity Appl., 16, 0, 114, 115, 01 Oct. 1999
English

Research on Flame Shapes of Quasi-Liquid Samples by 2-Dimensional Arrangement
NAKAMURA Sosuke, NAGATA Harunori, KUDO Isao, ITO Ken'ichi, KITANO Kunihiro, TAKESITA Yasuhiro
JASMA, 16, 3, 191, 197, The Japan Society of Microgravity Application, 31 Jul. 1999
Japanese, To investigate the interaction between the droplets in the spray combustion, microgravity experi­ments were performed. The experimental apparatus mainly consists of a combustion chamber, an 8 mm video camera and a 35 mm single-lens reflex camera. Fuel droplets of butanol or hexanol are arranged 2-dimensionally, representing the fuel droplet cloud in the splay. Electrically heated nichrome wires ignite the fuel samples simultaneously. The 35 mm camera observes the flame shape history. The effects of sample space on the flame shape are investigated . Main results obtained are in the followings: Because of the interaction between droplets, the unsteady combustion period. in which fuel vapor is accumulated around the droplets, becomes long . As the result, the steady state combustion is not observed in the combustion process and the flame size keeps increasing until it dis­ appears.

Deployment of an Inflatable Tube under Microgravity Condition
TAKANO Masahiro, NAGATA Harunori, KUDO Isao
Transactions of the Japan Society of Mechanical Engineers. C, 65, 633, 1978, 1984, The Japan Society of Mechanical Engineers, 25 May 1999
Japanese, An inflatable tube is used for separation of two satellites which artificially generate variable gravity environment by rotating each other. This tube is deployed by nitrogen gas and it gets sufficient rigidity finally. Behavior at deployment of the inflatable tube which had been stowed in a test apparatus at first was monitored under microgravity using the world longest dropshaft. The satellite model was successfully deployed, even though it encountered a catastrophic break Up. It verified that inflatable tube had excellent characteristics of recovering from a break up by increasing inner ...

Evaluation of supersonic turbulent mixing using catalytic combustion of constant temperature Pt wire
T Arai, H Nagata, A Endo, H Sugiyama, S Morita, H Hosokawa
JSME INTERNATIONAL JOURNAL SERIES B-FLUIDS AND THERMAL ENGINEERING, 42, 1, 65, 70, Feb. 1999
English, Scientific journal

Combustion Characteristics of Fibrous Fuels for Dry Towel Hybrid Rocket Motor　　　　　　　　　　　　　　　
Harunori NAGATA, Keiji OKADA, Takashi SAN'DA, Takahiro KATO, Ryojiro AKIBA, Shin SATORI, Isao KUDO
Journal of Space Technology and Science, 13, 1, 1, 1999, [Peer-reviewed]
English, Scientific journal

Takakage ARAI, Harunori NAGATA, Akira Endo, Hiromu SUGIYAMA, Shuji MORITA, and Hiroshi HOSOKAWA, "Evaluation of Supersonic Turbulent Mixing Using Catalytic Combustion of Constant Temperature Pt Wire", JSME International Journal, Series B, Vol.42, No.1,・・・　　　　　　　　　　　　　　　
1999
Takakage ARAI, Harunori NAGATA, Akira Endo, Hiromu SUGIYAMA, Shuji MORITA, and Hiroshi HOSOKAWA, "Evaluation of Supersonic Turbulent Mixing Using Catalytic Combustion of Constant Temperature Pt Wire", JSME International Journal, Series B, Vol.42, No.1, pp.65-70 (1999).

Research on Flame Shapes of Quasi-Liquid Samples by 2-Dimensional Arrangement
NAKAMURA Sosuke, NAGATA Harunori, KUDO Isao, ITO Ken'ichi, KITANO Kunihiro, TAKESITA Yasuhiro
JASMA, Vol.16, No.3, 191, 197, 日本マイクログラビティ応用学会, 1999
Japanese

Evaluation of hydrogen concentration of supersonic flow using catalytic reaction on Pt wire
Harunori Nagata, Yasuhiko Sakai, Moto-Omi Iwatsuki, Syuji Morita, Isao Kudo
Nihon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B, 65, 636, 2666, 2671, Japan Society of Mechanical Engineers, 1999
Japanese, Scientific journal

Deployment of an Inflatable Tube under Microgravity Condition
TAKANO Masahiro, NAGATA Harunori, KUDO Isao
Transactions of the Japan Society of Mechanical Engineers. Series C., 65, 633, 1978, 1984, The Japan Society of Mechanical Engineers, 1999
Japanese, An inflatable tube is used for separation of two satellites which artificially generate variable gravity environment by rotating each other. This tube is deployed by nitrogen gas and it gets sufficient rigidity finally. Behavior at deployment of the inflatable tube which had been stowed in a test apparatus at first was monitored under microgravity using the world longest dropshaft. The satellite model was successfully deployed, even though it encountered a catastrophic break Up. It verified that inflatable tube had excellent characteristics of recovering from a break up by increasing inner gas pressure. Typical break up condition of tube was analyzed by numerical simulation. Experimental data was successfully explained by the analysis.

Evaluation of hydrogen concentration of supersonic flow using catalytic reaction on Pt wire
Harunori Nagata, Yasuhiko Sakai, Moto-Omi Iwatsuki, Syuji Morita, Isao Kudo
Nihon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B, 65, 636, 2666, 2671, Japan Society of Mechanical Engineers, 1999
Japanese

Combustion Characteristics of Filter-type Fuels Burning at the Oxygen Gas Exit
KATO Takahiro, NAGATA Harunori, AKIBA Ryojiro, KUDO Isao
JASMA : Journal of the Japan Society of Microgravity Application, 15, 0, 63, 64, 01 Oct. 1998
English

Performance Evaluation of a Liquid Droplet Radiator Under Microgravity
ITAMI Masahiro, TOTANI Tsuyoshi, NAGATA Harunori, KUDO Isao, IWASAKI Akira, HOSOKAWA Shunsuke
J.Jan.Soc.Microgravity.Appl., 15, 0, 38, 39, 01 Oct. 1998
English

The Effects of DC Electric Fields on Ignition Delay of a Hydrogen-Air Mixture in Hot Surface Ignition
SEGAWA Daisuke, NAGATA Harunori, KISHI Takeyuki, KADOTA Toshikazu, TSUE Mitsuhiro, KONO Michikata
Transactions of the Japan Society of Mechanical Engineers. B, 64, 623, 2319, 2324, The Japan Society of Mechanical Engineers, 25 Jul. 1998
Japanese, The present study was carried out to reveal the possibility of controlling the ignition delay of hydrogen-air mixtures by applying electric fields. A quiescent stoichiometric hydrogen-air mixture was ignited by a suddenly heated thin wire of nickel or tungsten. DC electric fields were applied between the wire and outer electrode plates parallel with the wire. The mean ignition delay was calculated stochastically from the measured ignition delays which scattered considerably. Both with the nickel wire and with the tungsten wire, positive voltages applied to the outer electrode plates resulte...

Evaluation of Supersonic Turbulent Mixing Using Catalytic Combustion of Constant Temperature Pt Wire
ARAI Takakage, NAGATA Harunori, ENDO Akira, SUGIYAMA Hiromu, MORITA Shuji, HOSOKAWA Hiroshi
Transactions of the Japan Society of Mechanical Engineers. B, 64, 619, 793, 799, The Japan Society of Mechanical Engineers, 25 Mar. 1998
Japanese, Supersonic combustion using catalytic wire at constant temperature in a cold supersonic flow field was investigated in a square duct with a backward-facing step. The free stream Mach number was of M_m=1.81. Hydrogen was injected transversely behind a backward-facing step into a cold air free stream. The heat release due to the catalytic combustion has no effect of the temperature of catalyst. It indicates that the reaction rate of the catalytic combustion observed in this study was determined by the consentration of H_2 and/or O_2 on the surface of the catalyst. The spatial distribution of ...

The Effects of Electric Fields on Ignition Delay of Combustible Mixtures in Hot Surface Ignition
SEGAWA Daisuke, NAGATA Harunori, KISHI Takeyuki, KADOTA Toshikazu, TSUE Mitsuhiro, KONO Michikata
Transactions of the Japan Society of Mechanical Engineers. B, 64, 617, 298, 304, The Japan Society of Mechanical Engineers, 25 Jan. 1998
Japanese, The present study was carried out to reveal the possibility of controlling the ignition delay of combustible mixtures by applying electric fields. A thin nickel wire was used as a hot surface to ignite the mixtures. It was suddenly heated up and then its temperature was kept constant. Quiescent propane-air mixtures were used as combustible mixtures. DC electric fields were applied between the nickel wire and the outer electrode plates parallel with the nickel wire. As the applied voltage to the electrode plates increased, both the mean values and the fluctuations of the ignition delay decre...

The Effects of Electric Fields on Ignition Delay of Combustible Mixtures in Hot Surface Ignition
SEGAWA Daisuke, NAGATA Harunori, KISHI Takeyuki, KADOTA Toshikazu, TSUE Mitsuhiro, KONO Michikata
Transactions of the Japan Society of Mechanical Engineers. Series B., 64, 617, 298, 304, The Japan Society of Mechanical Engineers, 1998
Japanese, The present study was carried out to reveal the possibility of controlling the ignition delay of combustible mixtures by applying electric fields. A thin nickel wire was used as a hot surface to ignite the mixtures. It was suddenly heated up and then its temperature was kept constant. Quiescent propane-air mixtures were used as combustible mixtures. DC electric fields were applied between the nickel wire and the outer electrode plates parallel with the nickel wire. As the applied voltage to the electrode plates increased, both the mean values and the fluctuations of the ignition delay decreased regardless of the electric polarities. Without electric fields, both the mean ignition delay and the fluctuation varied with the equivalence ratio of the mixture. With increasing the applied voltage up to =2kV, the variations became to disappear. When the surface temperature was low, the stoichiometric mixture could be ignited only by applying the electric fields.

The Effects fo DC Electric Fields on Ignition Delay of a Hydrogen-Air Mixture in Hot Surface Ignition
SEGAWA Daisuke, NAGATA Harunori, KISHI Takeyuki, KADOTA Toshikazu, TSUE Mitsuhiro, KONO Michikata
Transactions of the Japan Society of Mechanical Engineers. Series B., 64, 623, 2319, 2324, The Japan Society of Mechanical Engineers, 1998
Japanese, The present study was carried out to reveal the possibility of controlling the ignition delay of hydrogen-air mixtures by applying electric fields. A quiescent stoichiometric hydrogen-air mixture was ignited by a suddenly heated thin wire of nickel or tungsten. DC electric fields were applied between the wire and outer electrode plates parallel with the wire. The mean ignition delay was calculated stochastically from the measured ignition delays which scattered considerably. Both with the nickel wire and with the tungsten wire, positive voltages applied to the outer electrode plates resulted in almost the same change of the mean ignition delay ; The mean ignition delay showed a slight increase at the lower applied voltages, while it became very short at the highest applied voltages. When the nickel wire was used and negative voltages were applied, the mean ignition delay decreased even at the lower voltages. However, it showed little change with the tungsten wire and the negative applied voltages.

「定温触媒線を用いた触媒燃焼による超音速乱流混合の評価方法」
新井隆景, 永田晴紀, 遠藤彰, 杉山弘, 森田修至, 細川博
『日本機械学会論文集（B編）』, 64, 619, 793, 799, 一般社団法人日本機械学会, 1998
Japanese

Catalytic Combustion of Transverse Hydrogen Jet Injection behind a Rear-Facing Step into a Cold Supersonic Flow
ARAI Takakage, ENDO Akira, NAGATA Harunori, SUGIYAMA Hiromu, MORITA Shuji
Transactions of the Japan Society of Mechanical Engineers. B, 63, 614, 3318, 3324, The Japan Society of Mechanical Engineers, 25 Oct. 1997
Japanese, Supersonic combustion using a catalytic combustion in a cold supersonic flow field was investigated in a square duct with a backward-facing step. The free stream Mech number was M_m=1.81. Hydrogen was injected transversely behind a backward-facing step into a cold air free stream. Using a catalyst in a cold supersonic turbulent mixing layer, it was found that hydrogen reacted stably to oxygen in the air flow. The relationship between the heat release due to catalytic combustion and supersonic flow properties, which influence the supersonic combustion, was clarified experimentally. The spati...

Flame Spread of a Quasi-Droplet Fuel Array under Microgravity
NAGATA Harunori, KUDO Isao, KITANO Kunihiro, NAKAMURA Sosuke, ITO Kenichi, TAKESHITA Yasuhiro
JASMA : Journal of the Japan Society of Microgravity Application, 14, 0, 41, 42, 01 Oct. 1997
English

Deployment of inflatable tube under micro gravity
TAKANO Masahiro, NAGATA Harunori, KUDO Isao
JASMA : Journal of the Japan Society of Microgravity Application, 14, 0, 27, 28, 01 Oct. 1997
English

A Preliminary Study of the Wet Towel Hybrid Racket Motor
NAGATA Harunori, AKIBA Ryoziro, TANATSUGU Nobuhiro, KOHNO Masahiro, YOKOTA Rikio, KAYUTA Seiyu
Aeronautical and space sciences Japan, 45, 522, 365, 370, 日本航空宇宙学会, Jul. 1997
Japanese

Catalytic combustion of transverse hydrogen jet injection behind a rear-facing step into a cold supersonic flow
Takakage Arai, Akira Endo, Harunori Nagata, Hiromu Sugiyama, Shuji Morita
Nippon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B, 63, 614, 3318, 3324, The Japan Society of Mechanical Engineers, 1997, [Domestic magazines]
Japanese

A Preliminary Study of the Wet Towel Hybrid Racket Motor
NAGATA Harunori, AKIBA Ryoziro, TANATSUGU Nobuhiro, KOHNO Masahiro, YOKOTA Rikio, KAYUTA Seiyu
Aeronautical and space sciences Japan, 45, 522, 365, 370, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 1997
Japanese, To overcome defects of conventional hybrid rocket motors such as poor mass ratio and low combustion efficiency, the authors propose a new idea of design. The point of this idea is that the motor uses ‘wet towel propellant’, in which liquid oxidizer fills gap space in the fuel bed consisting of plastic fibers or films. Specific impulses of the propellants are estimated theoretically with HAN and LOX as liquid oxidizer. To investigate pressure sensitivity of the burning rates of the propellants, burning rates of LOX-polyaramid propellants are measured in a pressure range of 0.1 to 2MPa with a specially designed strand burner. A striking feature in the experimental results is that the enhancement of the burning rate with ambient pressure is as big as the pressure exponent being larger than one. Further innovation is necessary for realization of the proposed idea.

CAMUI type using hydrogen peroxide water as oxidant Combustion characteristics of hybrid rocket
桜井光, 小野玄太, 金城亮太, 信原祐樹, 江澤悠太, 脇田督司, 永田晴紀, 航空原動機・宇宙推進講演会講演論文集(CD-ROM), 63rd, 2024

The influence of port diameter and oxidizer port velocity With burning spread of circular fuel duct with liquid oxygen
SON Taejun, 鈴木翔, 李介維, 南圭亮, 深田真衣, 山口舞恩, 脇田督司, 永田晴紀, 日本機械学会年次大会講演論文集(CD-ROM), 2024, 2024

地球磁気圏X線撮像計画GEO-X(GEOspace X-ray imager)の現状 VII
沼澤正樹, 江副祐一郎, 船瀬龍, 船瀬龍, 永田晴紀, 三好由純, 中嶋大, 三石郁之, 布施綾太, 川端洋輔, BODEN Ralf C., 中島晋太郎, KAMPS Landon, 信原佑樹, 平井翔大, 石川久美, 佐藤佑樹, 萩野浩一, 松本洋介, 細川敬祐, 伊師大貴, 上野宗孝, 山崎敦, 長谷川洋, 三田信, 三谷烈史, 藤本正樹, 川勝康弘, 岩田隆浩, 米山友景, 満田和久, 平賀純子, 笠原慧, 小泉宏之, 佐原宏典, 金森義明, 森下浩平, 日本天文学会年会講演予稿集, 2024, 2024

Status of GEO-X mission
江副祐一郎, 船瀬龍, 船瀬龍, 永田晴紀, 三好由純, 中嶋大, 三石郁之, 石川久美, 沼澤正樹, 佐藤佑樹, 川端洋輔, 布施綾太, 中島晋太郎, BODEN Ralf, KAMPS Landon, 信原佑樹, 平井翔太, 米山友景, 萩野浩一, 松本洋介, 細川敬祐, 笠原慧, 伊師大貴, 平賀純子, 満田和久, 藤本正樹, 上野宗孝, 山崎敦, 長谷川洋, 三谷烈史, 川勝康弘, 岩田隆浩, 地球電磁気・地球惑星圏学会総会及び講演会(Web), 156th, 2024

地球磁気圏X線撮像衛星GEO-Xの現状
江副祐一郎, 船瀬龍, 船瀬龍, 永田晴紀, 三好由純, 中嶋大, 三石郁之, 布施綾太, 川端洋輔, BODEN Ralf C., 中島晋太郎, KAMPS Landon, 信原佑樹, 平井翔太, 石川久美, 沼澤正樹, 佐藤佑樹, 萩野浩一, 松本洋介, 細川敬祐, 伊師大貴, 米山友景, 上野宗孝, 山崎敦, 長谷川洋, 三田信, 三谷烈史, 藤本正樹, 川勝康弘, 岩田隆浩, 満田和久, 平賀純子, 笠原慧, 小泉宏之, 佐原宏典, 金森義明, 森下浩平, 日本天文学会年会講演予稿集, 2024, 2024

Effect of Carbon Black Ratio on Electroconductive Fuel for Rocket Ignition Applications
Feb. 2023
English

Regenerative Cooling of Graphite Nozzles for Throat Erosion Suppression
Hiroki Kojima, Landon T. Kamps, Yuki Nobuhara, Giuseppe Gallo, Harunori Nagata, AIAA SCITECH 2023 Forum, 19 Jan. 2023
American Institute of Aeronautics and Astronautics

c* efficiency of hybrid rocket using oxygenated low-concentration hydrogen peroxide as oxidizer
金城亮汰, 小野玄太, 江澤悠太, 桜井光, 脇田督司, KAMPS Landon, 永田晴紀, 燃焼シンポジウム講演論文集(CD-ROM), 61st, 2023

地球磁気圏X線撮像計画GEO-X(GEOspace X-ray imager)の現状 V
中嶋大, 江副祐一郎, 船瀬龍, 永田晴紀, 三好由純, 沼澤正樹, 石川久美, 萩野浩一, 三石郁之, KAMPS Landon, 川端洋輔, 布施綾太, BODEN Ralf, 三谷烈史, 米山友景, 中島晋太郎, 上野宗孝, 山崎敦, 長谷川洋, 三田信, 藤本正樹, 川勝康弘, 岩田隆浩, 松本洋介, 細川敬祐, 平賀純子, 満田和久, 小泉宏之, 笠原慧, 佐原宏典, 金森義明, 森下浩平, 日本天文学会年会講演予稿集, 2023, 2023

20-year history and future prospects of UNISEC
川島レイ, 桑原聡文, 坂本啓, 永田晴紀, 船瀬龍, 宮崎康行, 山崎政彦, 中須賀真一, 宇宙科学技術連合講演会講演集(CD-ROM), 67th, 2023

Bus System Design of Microsatellite “GEO-X” with High Thrust Propulsion System
布施綾太, BODEN Ralf, 中島晋太郎, 川端洋輔, 松下将典, 秋山茉莉子, 船瀬龍, 船瀬龍, 江副祐一郎, KAMPS Landon, 永田晴紀, 鈴木聡宏, NERY Vinicius, 伊藤湧太郎, 筒井真輝, 望月友貴, 小川巧海, 荻野浩佑, 草野湧貴, 下村俊介, 瀬戸翔一, 中村陸希, 宇宙科学技術連合講演会講演集(CD-ROM), 67th, 2023

X-ray imaging observation of planetary magnetospheres by small satellite
中嶋大, 江副祐一郎, 三好由純, 永田晴紀, 船瀬龍, 宇宙科学技術連合講演会講演集(CD-ROM), 67th, 2023

Development of Hybrid Chemical Propulsion System for Small-size Rideshare Spacecraft (Letara Ltd.)
KAMPS Landon, 平井翔大, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 67th, 2023

Optimal diffuser geometry design and verification for micro-scale high altitude test stand
ITOIGAWA Yamato, Onodera Ryo, GALLO Giuseppe, KAMPS Landon, NAGATA Harunori, The Proceedings of Mechanical Engineering Congress, Japan, 2023, S191p-06, 2023
In order to increase the opportunities for deep space exploration by small satellites, our laboratory has been working on developing a safe, high-thrust hybrid rocket motor. To obtain the thrust characteristics of the hybrid rocket under low-pressure conditions, the authors developed a HATS (High Altitude Test Stand) for small satellite thrusters that can maintain a low-pressure environment during combustion tests and found that the current combustion conditions and diffuser shape could not maintain a low-pressure environment. Therefore, this study designed and verified a new diffuser with a second throat in the middle of the diffuser to maintain a low-pressure environment. Using the two theoretical models presented in a previous study, we confirmed that there exists a design solution for a diffuser shape that can maintain a low-pressure environment under the current combustion conditions. Although the design solution is close to the lower limit of the second throat diameter, the design solution obtained from the theoretical model is not highly reliable because few previous studies experimentally investigated the lower limit. Therefore, the design solution was verified using a sub-scale diffuser and cold gas., The Japan Society of Mechanical Engineers, Japanese

Combustion Characteristics of Hybrid Rocket Using Nytrox/HDPE
IKEDA Takuya, NOBUHARA Yuki, KAMPS Landon, NAGATA Harunori, The Proceedings of Mechanical Engineering Congress, Japan, 2023, S191p-04, 2023
A hybrid rocket kick motor is being developed for low-cost deep space exploration. Nytrox, a mixture of nitrous oxide (N₂O) and oxygen, will be investigated as an oxidizer for the kick motor. Nytrox has the advantage for use in kick motors of being safer than N₂O because it is less likely to cause decomposition reactions. The objective of this study is to obtain the fuel regression rate equation by conducting combustion tests to design a kick motor using Nytrox and high-density polyethylene (HDPE). The Nytrox used in this study was generated under conditions where the probability of N₂O decomposition reactions occurring was as low as possible. The fuel regression rate equation of Nytrox/HDPE was obtained from five combustion tests. Comparison with the fuel regression rate of N₂O /HDPE obtained from two combustion tests indicated that the fuel regression rate of Nytrox may be larger than that of N₂O, depending on the fuel. However, the number of experiments is small, and more data is needed to obtain accurate data., The Japan Society of Mechanical Engineers, Japanese

Flow Characteristics of Self-Pressurized Nitrous Oxide
ONODERA Ryo, ITOIGAWA Yamato, Landon Kamps, NAGATA Harunori, The Proceedings of Mechanical Engineering Congress, Japan, 2023, S191p-09, 2023
Nitrous oxide is an attractive option as an oxidizer for rockets because of its self-pressurized supply and safety. On the other hand, it is very close to the critical point at room temperature, so the prediction of its state quantity requires very complicated calculations. Prediction of the oxidizer flow rate is important for hybrid rockets, and various prediction equations have been proposed. In particular, the Homogeneous Non-Equilibrium Flow Model, which assumes that the mass flow rate of nitrous oxide takes a value between liquid single-phase flow and gas-liquid two-phase flow, is considered to be accurate. However, this HNE flow model does not consider the effect of injector geometry, and the authors proposed a new model, HNEIS, which considers injector geometry. From flow rate tests using several injectors with different geometries, it was found that the flow rate varies depending on the injector geometry even when the supply pressure is equal. It was also clear that the HNEIS could express this trend, whereas the HNE could not. On the other hand, there is a dissociation between the actual flow rate and the predicted flow rate by HNEIS, and the model needs to be improved., The Japan Society of Mechanical Engineers, Japanese

Combustion characteristics of fuel resins with conductivity imparted by carbon particles
EZAEA Yuta, NAGATA Harunori, Landon Kamps, NOBUHARA Yuki, The Proceedings of Mechanical Engineering Congress, Japan, 2023, S191p-07, 2023
The objective of this study is to design and develop a hybrid rocket that is re-ignitable and does not require an igniter, focusing on the conductivity obtained by the addition of a large amount of carbon black. By conducting five and eight combustion tests using pure PLA fuel and conductive fuel with a large amount of carbon black added to PLA as solid fuel and gaseous oxygen as oxidizer, respectively, the fuel regression rate equations necessary for the proper design of hybrid rockets were established. The respective fuel regression rate equations were as follows (R² = 0.8154), Conductive fuel: (R² = 0.3975). Since the oxidizer index in the fuel regression rate equation exceeded 1 in the conductive fuel results, more data should be collected in the future to improve the equation., The Japan Society of Mechanical Engineers, Japanese

Application of Low Concentration Hydrogen Peroxide for Hybrid Rocket Propulsion System for Small Spacecraft
Masashi Wakita, Yusuke Takada, Kodai Iwanaga, Toshiaki Iizuka, Hironori Sahara, Landon T. Kamps, Harunori Nagata, AIAA AVIATION 2022 Forum, 27 Jun. 2022
American Institute of Aeronautics and Astronautics

Proposal for Hybrid Kick Motor Experiment in Space Environment Using the S-520 Sounding Rocket
ケンプス, ランドン, 平井, 翔大, 永田, 晴紀, KAMPS, Landon, HIRAI, Shota, NAGATA, Harunori, 観測ロケットシンポジウム2021 講演集 = Proceedings of Sounding Rocket Symposium 2021, Mar. 2022
第4回観測ロケットシンポジウム（2022年3月14-15日. ハイブリッド開催（JAXA相模原キャンパス& オンライン）)
4th Sounding Rocket Symposium(March 14-15, 2022. Hybrid(in-person & online) Conference (Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan
資料番号: SA6000175012
レポート番号: Ⅱ-7, 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS), English

Ignition Criteria for Ignition Devices Using Electrically Conductive Plastics
信原佑樹, 平井翔大, LEUNG Yownin Albert, KAMPS Landon, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 66th, 2022

Status of GEO-X mission and beyond
江副祐一郎, 船瀬龍, 船瀬龍, 川端洋輔, 中島晋太郎, 永田晴紀, KAMPS Landon, 中嶋大, 三石郁之, 石川久美, 沼澤正樹, 三好由純, 上野宗孝, 宇宙科学技術連合講演会講演集(CD-ROM), 66th, 2022

Blow-off Mechanism in Axial-Injection End-Burning Hybrid Roket
早坂宏己, 深田真衣, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 66th, 2022

Development of Hybrid Kick Motor for Small Piggybacking Spacecraft
平井翔大, KAMPS Landon, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 66th, 2022

Development of End-burning Hybrid Rocket Using Liquid Oxygen as Oxidizer
永田晴紀, 鈴木翔, 李介維, 添田健太郎, KAMPS Landon, 脇田督司, 宇宙科学技術連合講演会講演集(CD-ROM), 66th, 2022

Analysis of graphite nozzle throat erosion in liquid rockets using ethanol/LOX
ITOIGAWA Yamato, HIRAI Shota, TSUJI Ayumu, KANAI Ryuichiro, KAMPS Landon, NAGATA Harunori, The Proceedings of Mechanical Engineering Congress, Japan, 2022, J191p-03, 2022
Interstellar Technologies, Inc. has been developing a series of liquid rockets using ethanol/LOX called MOMO. These rockets use graphite nozzle throat inserts for which nozzle erosion, referring to the increase in diameter of the nozzle throat due to the chemical reactions between the combustion gas and the graphite, has become a problem. This study aims to develop a predictive equation for the nozzle erosion rate of liquid rockets using ethanol/LOX. The authors analyzed data from seven long-duration combustion experiments and calculated the nozzle erosion rate. Using the heat transfer coefficient of the nozzle throat, the heat transfer equation at the nozzle throat was solved and the nozzle wall temperature was also estimated. As a result, it was found that the nozzle erosion phenomenon of liquid rockets using ethanol/LOX has a similar trend to that of nozzle erosion in hybrid rockets using HDPE/LOX. A good correlation was obtained by using the nozzle erosion rate prediction equation of Kamps et al., which has chamber pressure, equivalence ratio and nozzle wall temperature as parameters., The Japan Society of Mechanical Engineers, Japanese

Flame-Holding Characteristics of a Hybrid Rocket using Pre-heated 60wt% Hydrogen Peroxide
ONO Genta, IWANAGA Kodai, TAKADA Yusuke, WAKITA Masashi, Kamps Landon, NAGATA Harunori, The Proceedings of Mechanical Engineering Congress, Japan, 2022, J191-07, 2022
As the number of micro-deep space probes launched by large rockets using the piggyback increases, the demand for safe, low-cost, re-ignitable, and high-thrust kick motors for efficient inter-orbit satellite transfer is expected to increase as well. Low-concentration hydrogen peroxide is the most suitable oxidizer for hybrid kick motors for micro-spacecraft in terms of safety, low cost, and ease of storage. However, it has difficulty in ignitability and flame holding due to its high water content. In this study, we considered a method to decompose low-concentration hydrogen peroxide by external heating using a heat exchanger before supplying it to a CAMUI-type fuel. A ground combustion experiment showed that flame holding was successfully achieved, however, there were vibrations in the combustion chamber pressure. In order to obtain the lower limit of the heating required for stable combustion, we plan to evaluate the flame holding limit and calculate the heat input to the hydrogen peroxide., The Japan Society of Mechanical Engineers, Japanese

地球磁気圏X線撮像計画GEO-X(GEOspace X-ray imager)の現状 IV
中嶋大, 江副祐一郎, 船瀬龍, 永田晴紀, 三好由純, 萩野浩一, 沼澤正樹, 石川久美, 三石郁之, KAMPS L., 川端洋輔, 布施綾太, 米山友景, 中島晋太郎, 上野宗孝, 山崎敦, 長谷川洋, 三田信, 藤本正樹, 川勝康弘, 岩田隆浩, 平賀純子, 満田和久, 小泉宏之, 笠原慧, 佐原宏典, 金森義明, 森下浩平, 日本天文学会年会講演予稿集, 2022, 2022

液体酸素が流れる固体燃料管列の燃え拡がり特性—Flame Spreading Characteristics of Solid Fuel Tube Row with Liquid Oxygen
野中, 響己, 津地, 歩, 李, 介維, 永田, 晴紀, 脇田, 督司, NONAKA, Hibiki, TSUJI, Ayumu, LI, Kaii, NAGATA, Harunori, WAKITA, Masashi, 令和3年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium FY2021, Jan. 2022
令和3年度宇宙輸送シンポジウム（2022年1月13日-14日. オンライン開催)
Space Transportation Symposium FY2021 (January 13-14, 2022. Online Meeting)
資料番号: SA6000173012
STCP-2021-012, 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS), Japanese

Throttling Response Mechanisms in Axial Injection End-Burning Hybrid Rockets
千葉健太郎, 鈴木翔, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 66th, 2022, [Peer-reviewed]
American Institute of Aeronautics and Astronautics

Development of safe, low-cost, re-ignitable rocket ignition system
Shota Hirai, Landon T. Kamps, Harunori Nagata, AIAA Propulsion and Energy 2021 Forum, 09 Aug. 2021
American Institute of Aeronautics and Astronautics

Fuel Regression Characteristics of CAMUI type Hybrid Rocket Using Nitrous Oxide
Yuki Nobuhara, Landon T. Kamps, Harunori Nagata, AIAA Propulsion and Energy 2021 Forum, 09 Aug. 2021
American Institute of Aeronautics and Astronautics

Numerical Analysis of Nozzle Transient Heating and Erosion in Hybrid Rockets burning HDPE
Marco Rotondi, Mario Tindaro Migliorino, Daniele Bianchi, Landon T. Kamps, Harunori Nagata, AIAA Propulsion and Energy 2021 Forum, 09 Aug. 2021
American Institute of Aeronautics and Astronautics

Influence of Port Manufacturing Accuracy on Backfiring in Axial-Injection End-Burning Hybrid Rocket
Sho Suzuki, Ayumu Tsuji, Kentaro Soeda, Landon T. Kamps, Harunori Nagata, AIAA Propulsion and Energy 2021 Forum, 09 Aug. 2021
American Institute of Aeronautics and Astronautics

Ignition and flame-holding characteristics of 60wt% hydrogen peroxide in a CAMUI-type hybrid rocket fuel
Yusuke Takada, Kodai Iwanaga, Hajime Inoue, Shota Inoue, Masashi Wakita, Landon T. Kamps, Hironori Sahara, Toshiaki Iizuka, Harunori Nagata, AIAA Propulsion and Energy 2021 Forum, 09 Aug. 2021
American Institute of Aeronautics and Astronautics

Reconstruction techniques for determining O/F in hybrid rockets
Yuji Saito, Landon T. Kamps, Ayumu Tsuji, Harunori Nagata, AIAA Propulsion and Energy 2021 Forum, 09 Aug. 2021
American Institute of Aeronautics and Astronautics

Development of Hybrid Kick Motor for Small Piggybacking Spacecraft
平井翔大, KAMPS Landon, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 65th, 2021

Thermal Design of Micro Spacecraft for Deep Space Mission with Hybrid Kick Motor
友永優太, 戸谷剛, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 65th, 2021

GEO-X mission and future prospects-“X-ray solar system astronomy“
江副祐一郎, 船瀬龍, 船瀬龍, 永田晴紀, 三好由純, 中嶋大, 三石郁之, 川端洋輔, KAMPS Landon, 石川久美, 上野宗孝, 宇宙科学技術連合講演会講演集(CD-ROM), 65th, 2021

Status of the GEO-X (Geospace X-ray imager) mission
江副祐一郎, 船瀬龍, 船瀬龍, 永田晴紀, 三好由純, 中嶋大, 三石郁之, 石川久美, 上野宗孝, 山崎敦, 長谷川洋, 三田信, 藤本正樹, 川勝康弘, 岩田隆浩, 満田和久, 平賀純子, 笠原慧, 佐原宏典, 金森義明, 森下浩平, 三谷烈史, 沼澤正樹, 日本地球惑星科学連合大会予稿集(Web), 2021, 2021

Experimental investigation on the reignition devices using 3D printed fuels
HIRAI Shota, KAMPS Landon, NAGATA Harunori, The Proceedings of Mechanical Engineering Congress, Japan, 2021, J191-16, 2021
The authors are developing a safe, low-cost, compact, and lightweight reignition device to provide reignition capability to a hybrid kick motor as a propulsion system for small satellites. So far, only HDPE has been used as a solid fuel for the reignition device, with which the desired results have not been obtained. In this study, we measured the amount of gasification of fuel due to the radiant heat of glow plugs using multiple filaments for 3D printing, with the aim of identifying suitable replacement materials for HDPE. A total of more than 100 experiments, including preliminary experiments, revealed that HDPE was the least suitable fuel for the reignition system. On the other hand, it was found that Carbon Fibered PLA is the most effective as it has a large amount of fuel gasification and can maintain the fuel shape., The Japan Society of Mechanical Engineers, Japanese

The innovative aircraft unit in f³ center of Hokkaido univ. and Muroran IT
UCHIUMI Masaharu, IMAI Ryoji, Mizobata Kazuhide, NAKATA Daisuke, NAGATA Harunori, The Proceedings of Conference of Hokkaido Branch, 2021.58, 1311, 2021
The Japan Society of Mechanical Engineers, Japanese

Green Ship Unit, f3 Center of Hokkaido University and Muroran Institute of Technology
Murai Yuichi, HORIMOTO Yasufumi, PARK Hyun Jin, TASKA Yuji, OISHI Yoshihiko, NAGATA Harunori, The Proceedings of Conference of Hokkaido Branch, 2021.58, 1312, 2021
The Japan Society of Mechanical Engineers, Japanese

Micro space propulsion unit in f³ engineering center
NAGATA Harunori, KAMPS Landon, HIRAI Shota, TOTANI Tsuyoshi, MURAI Yuichi, UCHIUMI Masaharu, The Proceedings of Conference of Hokkaido Branch, 2021.58, 1314, 2021
The Japan Society of Mechanical Engineers, Japanese

Microsatellite Unit in f³ Engineering Education and Research Center in Hokkaido University and Muroran Institute of Technology
TOTANI Tsuyoshi, SAKAMOTO Yuji, NAGATA Harunori, The Proceedings of Conference of Hokkaido Branch, 2021.58, 1313, 2021
The Japan Society of Mechanical Engineers, Japanese

地球磁気圏X線撮像計画GEO-X(GEOspace X-ray imager)の現状 III
江副祐一郎, 船瀬龍, 船瀬龍, 永田晴紀, 三好由純, 中嶋大, 三石郁之, 石川久美, 川端洋輔, 中島晋太郎, KAMPS Landon, 上野宗孝, 山崎敦, 長谷川洋, 三田信, 三谷烈史, 藤本正樹, 川勝康弘, 岩田隆浩, 満田和久, 平賀純子, 笠原慧, 小泉宏之, 佐原宏典, 金森義明, 森下浩平, 沼澤正樹, 日本天文学会年会講演予稿集, 2021, 2021

Visualization of Hybrid Rocket Technology-Based Igniter Interior and Elucidation of Combustion Mode
井上翔太, KAMPS Landon, 平井翔大, 高田裕亮, 深田真衣, LEUNG Yownin Albert, 永田晴紀, 燃焼シンポジウム講演論文集(CD-ROM), 59th, 2021

Flame-Holding Characteristics of 60wt% Hydrogen Peroxide Hybrid Rocket with Platinum Catalysts
岩永昂大, 高田裕亮, 小野玄太, 脇田督司, KAMPS Landon, 佐原宏典, 飯塚俊明, 永田晴紀, 燃焼シンポジウム講演論文集(CD-ROM), 59th, 2021

Effect of Pressure on Regression Shape Formed by Stabilized Combustion
YAMADA Ai, TSUJI Ayumu, HUKADA Mai, NAGATA Harunori, WAKITA Masashi, The Proceedings of Mechanical Engineering Congress, Japan, 2020, J19111, 2020
The Japan Society of Mechanical Engineers, Japanese

Ignition characteristics of 60wt% hydrogen peroxide in a CAMUI-type fuel
TAKADA Yusuke, TAKANASHI Tomohiro, WAKITA Masashi, NAGATA Harunori, The Proceedings of Mechanical Engineering Congress, Japan, 2020, J19103, 2020
Micro-space-probes are ideal platforms for future deep space exploration missions because multiple micro-space-probes can piggyback together on most existing Earth launch vehicles. If the piggyback destination is GTO, the microsatellite can escape from the earth's gravity to go into deep space with only 700 m/s of additional acceleration. Low-concentration (60wt%) hydrogen peroxide has favorable storage characteristics as an oxidizer for in-space hybrid rocket propulsion but has unfavorable ignition and flame holding characteristics due to its high-water content. In this study, separate tests for ignition and flame holding were attempted using 60wt% hydrogen peroxide as an oxidizer and high-density polyethylene as fuel in a CAMUI-type configuration. A Pt catalyst, pressurized chamber, and low flow-rate oxidizer bypass line were used to promote ignition. The results of visualization experiments show that ignition was achieved, but flame holding was not achieved, probably due to an excessive oxidizer flow rate., The Japan Society of Mechanical Engineers, Japanese

Development of Hybrid Rocket Thrusters for Space-Probe Propulsion
KAMPS Landon, KAGEYAMA Lisa, WAKITA Masashi, NAGATA Harunori, The Proceedings of Mechanical Engineering Congress, Japan, 2020, J19121, 2020
Hybrid rockets are suitable candidate propulsion systems for space exploration missions because they can produce similar levels of thrust to solid and liquid bi-propellant rockets without the fire/explosion safety hazard. Space probes equipped with a hybrid rocket thrust can more readily be integrated in piggy-back launches without the need for lengthy and expensive risk mitigation activities. This study reports the results of four static firing tests of an engineering model hybrid rocket thruster using high-density polyethylene as fuel and liquid nitrous oxide as oxidizer for space-probe propulsion. Measurements of thrust, chamber pressure and propellant mass flow rates reveal that performance in atmospheric conditions was nominal: I_sp ≦ 220s; C_F ≦ 1.4., The Japan Society of Mechanical Engineers, Japanese

Simulation of Throttling Response in Axial-Injection End-Burning Hybrid Rocket
TSUJI Ayumu, YAMADA Ai, FUKADA Mai, WAKITA Masashi, NAGATA Harunori, The Proceedings of Mechanical Engineering Congress, Japan, 2020, J19109, 2020
Axial-injection end-burning hybrid rocket (EBHR) is excellent in fuel regression rate and throttling characteristics than conventional hybrid rockets. However, in the firing tests of throttling operation using multiple port fuel, a very long response time was observed. In this research, the authors postulated that the fuel regression shape of each port might be affected by chamber pressure to explain the reason for long response time and verified this hypothesis by using numerical simulation. The calculation result showed the long response time, and the response time coincides with the shape-changing time, which indicates that the shape-changing causes a long response time. Moreover, the history of characteristic exhaust velocity suggests that the fuel-rich condition may make response time short., The Japan Society of Mechanical Engineers, Japanese

Dr. Stone and the Robustness of Life
NAGATA Harunori, Journal of JSEE, 68, 4, 4_108, 4_108, 2020
Japanese Society for Engineering Education, Japanese

Boundary Condition between Flame Spreading and Stabilized Combustion with Nitrous Oxide and PMMA
FUKADA Mai, SATO Motoki, TSUJI Ayumu, NAGATA Harunori, WAKITA Masashi, The Proceedings of Mechanical Engineering Congress, Japan, 2020, J19110, 2020
When designing axial- injection end-burning hybrid rocket (EBHR), it is essential to obtain the boundary between stabilized combustion mode and flame spreading mode. Oxidizer friction velocity has been used as an indicator of them. The threshold value has obtained in the case with PMMA fuel and O₂ as a constant value and used when designing EBHR. Recently, however, N₂O is said to be useful for oxidizer, so we have to research if we can use N₂O for EBHR. In this study, we aim to obtain the threshold value of friction velocity with PMMA fuel and N₂O as the oxidizer. We conducted some combustion experiments and explored the relationship between friction velocity, chamber pressure, and flame behavior. As a result, we observed pressure dependencies of the threshold value of friction velocity, which is different from the result of the O₂ experiment. There are two possibilities why such a result arose, 1) difference of oxidizer chemical species, 2) development of boundary layer., The Japan Society of Mechanical Engineers, Japanese

Development of Reconstruction Techniques in Hybrid Rockets
永田晴紀, KAMPS Landon, 齋藤勇士, 燃焼シンポジウム講演論文集(CD-ROM), 58th, 2020

The ignitor of the hybrid rocket
池田華子, KAMPS Landon, 永田晴紀, 燃焼シンポジウム講演論文集(CD-ROM), 58th, 2020

Fuel regression mechanism of End-Burning Hybrid Rocket with Nitrous Oxide
奥田椋太, 小水弘大, 津地歩, 三輪拓実, 横堀秀一, 添田建太郎, 永田晴紀, 燃焼シンポジウム講演論文集(CD-ROM), 58th, 2020

Evaluation of axial fuel regression rate in hybrid rocket fuels using 3D scanner
奥田晃崇, KAMPS Landon, 伊藤聖司, 影山理沙, VISCOR Tor, 井上翔太, 池田華子, 高田祐亮, 脇田督司, 永田晴紀, 燃焼シンポジウム講演論文集(CD-ROM), 58th, 2020

Visualization of fuel regression rate in axial-injection end-burning hybrid rocket
Takumi Miwa, Ayumu Tsuji, Ryota Okuda, Shuichi Yokobori, Kentaro Soeda, Landon Kamps, Harunori Nagata, AIAA Propulsion and Energy 2020 Forum, 1, 11, 2020

Evaluation of the thermal onset of graphite nozzle erosion
Seiji Ito, Landon Kamps, Satoshi Yoshimaru, Harunori Nagata, AIAA Propulsion and Energy 2020 Forum, 1, 14, 2020

地球磁気圏X線撮像計画GEO-X(GEOspace X-ray imager)の現状 II
江副祐一郎, 船瀬龍, 永田晴紀, 三好由純, 笠原慧, 中嶋大, 三石郁之, 石川久美, 上野宗孝, 山崎敦, 長谷川洋, 三田信, 満田和久, 藤本正樹, 川勝康弘, 岩田隆浩, 平賀純子, 小泉宏之, 佐原宏典, 金森義明, 森下浩平, 日本天文学会年会講演予稿集, 2020, 2020

地球磁気圏X線撮像計画GEO-X(GEOspace X-ray imager)の現状 III
江副祐一郎, 船瀬龍, 永田晴紀, 三好由純, 笠原慧, 中嶋大, 三石郁之, 石川久美, 上野宗孝, 山崎敦, 長谷川洋, 三田信, 藤本正樹, 川勝康弘, 岩田隆浩, 満田和久, 平賀純子, 小泉宏之, 佐原宏典, 金森義明, 森下浩平, 沼澤正樹, 日本天文学会年会講演予稿集, 2020, 2020

Status of GEO-X (GEOspace X-ray imager) mission
江副祐一郎, 船瀬龍, 永田晴紀, 三好由純, 中嶋大, 三石郁之, 石川久美, 山崎敦, 長谷川洋, 藤本正樹, 上野宗孝, 地球電磁気・地球惑星圏学会総会及び講演会(Web), 148th, 2020

Stabilized Combustion Characteristics of Nitrous Oxide - Photocurable Resin Single Port Fuel
深田真衣, 津地歩, 奥田椋太, 山田藍, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 64th, 2020

Investigation of Graphite Nozzle Erosion Thermal Onset
伊藤聖司, KAMPS Landon, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 64th, 2020

Thermal Design of Upper Boost Stage with Hybrid Kick Motor for Microspacecraft
田端健一, 友永優太, 戸谷剛, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 64th, 2020

Initial Firing Tests of Aluminum Rod/Water Hybrid Rockets
Yuji Saito, Landon Kamps, Ayumu Tsuji, Masashi Wakita, Hiroyuki Koizumi, Keisuke Asai, Harunori Nagata, AIAA Propulsion and Energy 2020 Forum, 1, 11, 2020, [Peer-reviewed]
American Institute of Aeronautics and Astronautics

Evaluation of Anti-erosion Effect of Ablator in Hybrid Rocket Nozzle
奥田晃崇, KAMPS Landon, 櫻井和人, 井上卓, VISCOR Tor, 内山絵里香, 池田華子, 吉丸利, 脇田督司, 永田晴紀, 燃焼シンポジウム講演論文集(CD-ROM), 57th, Nov. 2019, [Last author]

冷却によるグラファイトノズルの浸食抑制効果　　　　　　　　　　　　　　　
吉丸 利,永田 晴紀,伊藤 聖司,Landon T. Kamps, 第57回燃焼シンポジウム講演論文集, Nov. 2019, [Last author]

端面燃焼式ハイブリッドロケットにおける燃焼室特性長さが及ぼす c*効率への影響　　　　　　　　　　　　　　　
押見 灯里,津地 歩,小水 弘大,添田 建太郎,横堀 秀一, 永田 晴紀, 第57回燃焼シンポジウム講演論文集, Nov. 2019

亜酸化窒素を用いた端面燃焼式ハイブリッドロケットの推力制御特性　　　　　　　　　　　　　　　
小水 弘大,奥田 椋太,津地 歩,押見 灯里, 添田 建太郎,横堀 秀一,永田 晴紀, 第57回燃焼シンポジウム講演論文集, Nov. 2019, [Last author]

Effects of Detonation Cell Regularity on the Propagation Characteristic in Gradually Expanding Toroidal Channel
本谷誠正, 桧物恒太郎, 脇田督司, 永田晴紀, 燃焼シンポジウム講演論文集(CD-ROM), 57th, Nov. 2019, [Last author]

地球磁気圏X線撮像計画GEO-X(GEOspace X-ray imager)の現状
江副祐一郎, 三好由純, 笠原慧, 船瀬龍, 永田晴紀, 中嶋大, 三石郁之, 石川久美, 山崎敦, 長谷川洋, 三田信, 満田和久, 藤本正樹, 川勝康弘, 岩田隆浩, 上野宗孝, 平賀純子, 小泉宏之, 佐原宏典, 日本天文学会年会講演予稿集, 2019, 2019

Fuel regression characteristics in hybrid rockets using n2o/hdpe
Seiji Ito, Landon Kamps, Kazuhito Sakurai, Lisa Kageyama, Terutaka Okuda, Harunori Nagata, AIAA Propulsion and Energy Forum and Exposition, 2019, 2019

Development of N2O/HDPE hybrid rocket for microsatellite propulsion
Landon Kamps, Pau Molas-Roca, Erica Uchiyama, Tomohiro Takanashi, Harunori Nagata, Proceedings of the International Astronautical Congress, IAC, 2019-October, 2019

Effect of aft chamber volume on hybrid rocket combustion efficiency
L. Kageyama, L. Kamps, H. Nagata, AIAA Propulsion and Energy Forum and Exposition, 2019, 2019

Development of Hybrid Kick Motor for Ultra-small Deep Space Exploration Satellite
ITO Seiji, UCHIYAMA Erika, SAKURAI Kazuhito, KAMPS Landon, KAGEYAMA Lisa, NAGATA Harunori, The Proceedings of Mechanical Engineering Congress, Japan, 2019, 0, J19105P, 2019

There are few opportunities to launch a satellite for deep space exploration, because of the low budget in Japan. A piggy-back microsatellite takes lower cost than a satellite launched alone. A microsatellite can go GTO with the main satellite, and then the microsatellite goes to deep space using a kick motor. To achieve the thrust and specific impulse that the kick motor requires, we need chemical rockets. Hybrid rockets are the best choice from the viewpoint of safety. Nitrous oxide is selected as the oxidizer because the kick motor also requires storable oxidizer. The relationship between L* and c* efficiency, the fuel regression rate formula and the characteristic of nozzle erosion are obtained from static firing tests. Furthermore, the change in velocity is calculated for each size of the kick motor.

, The Japan Society of Mechanical Engineers, Japanese

EXPERIMENTAL INVESTIGATION OF C* EFFICIENCY IN NITROUS OXIDE HYBRID ROCKETS
Erika Uchiyama, Yurika Kiyotani, Landon Kamps, Harunori Nagata, PROMOTE THE PROGRESS OF THE PACIFIC-BASIN REGION THROUGH SPACE INNOVATION, 166, 109, 115, 2019, [Peer-reviewed]
English

Investigation of graphite nozzle erosion in hybrid rockets using N2O/HDPE
Landon Kamps, Kazuhito Sakurai, Kohei Ozawa, Harunori Nagata, AIAA Propulsion and Energy Forum and Exposition, 2019, 2019, [Peer-reviewed]
English

Limit condition of hemispherical detonation waves propagating into diluted mixtures
中西勇作, 桧物恒太郎, 本谷誠正, 脇田督司, 永田晴紀, 燃焼シンポジウム講演論文集, 56th, ROMBUNNO.B214, 14 Nov. 2018
Japanese

MEASUREMENT OF THE EFFECTIVE EMISSIVITY OF DROPLET STREAM IN LIQUID DROPLET RADIATOR
両門健人, 高梨知広, 戸谷剛, 脇田督司, 永田晴紀, Thermophysical Properties, 39th, 166‐168, 13 Nov. 2018
Japanese

Thermal decomposition behavior of organic solvents by nano-scale pulsed heating during laser melting in liquid
Suehara Kentaro, Ishikawa Yoshie, Koshizaki Naoto, Omura Kazunobu, Nagata Harunori, JSAP Annual Meetings Extended Abstracts, 2018.2, 775, 775, 05 Sep. 2018
The Japan Society of Applied Physics, Japanese

ハイブリッドロケットの燃焼データ解析法の開発とその応用
永田, 晴紀, ケンプス, ランドン, 齋藤, 勇士, Nagata, Harunori, Kamps, Landon, Saito, Yuji, 第1回ハイブリッドロケットシンポジウム 講演集 = Proceedings of the 1st Hybrid Rocket Symposium, Jun. 2018
第1回ハイブリッドロケットシンポジウム（2018年6月28日-29日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県
1st Hybrid Rocket Symposium (June 28-29, 2018. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan
資料番号: SA6000126019
レポート番号: HR-2018-Keynote2, 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS), Japanese

Estimation of Nozzle Throat Wall Temperature History in Hybrid Rockets
Jun. 2018
English

亜酸化窒素を用いたハイブリッドロケットの特性排気速度効率—c* efficiency in nitrous oxide hybrid rockets
内山, 絵里香, 清谷, 優理香, Kamps, Landon, 永田, 晴紀, Uchiyama, Erika, Kiyotani, Yurika, Nagata, Harunori, 第1回ハイブリッドロケットシンポジウム 講演集 = Proceedings of the 1st Hybrid Rocket Symposium, Jun. 2018
第1回ハイブリッドロケットシンポジウム（2018年6月28日-29日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県
1st Hybrid Rocket Symposium (June 28-29, 2018. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan
資料番号: SA6000126013
レポート番号: HR-2018-012, 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS), Japanese

地球磁気圏X線撮像計画GEO-Xの現状
江副祐一郎, 三好由純, 笠原慧, 船瀬龍, 永田晴紀, 上野宗孝, 中嶋大, 木村智樹, 石川久美, 三田信, 満田和久, 藤本正樹, 大橋隆哉, 日本天文学会年会講演予稿集, 2018, 2018

Modeling of Fuel Regression Rate of Axial-Injection End-Burning Hybrid Rocket with Liquid Oxygen
TSUJI Ayumu, NAGATA Harunori, The Proceedings of Mechanical Engineering Congress, Japan, 2018, 0, J1920101, 2018
The Japan Society of Mechanical Engineers, Japanese

Outcomes and Challenges of Project Education suggested by the History of Mini‐CAMUI Projects
永田晴紀, 高梨知広, 脇田督司, 宇宙科学技術連合講演会講演集(CD-ROM), 62nd, ROMBUNNO.1S05, 2018
Japanese

Study on visualization of combustion field in CAMUI type hybrid rocket by using acrylic fuel
井上卓, KAMPS Landon, 櫻井和人, 内山絵里香, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 62nd, ROMBUNNO.1N05, 2018
Japanese

Expansion of the application range of the thermal design concept which uses the heat capacity of the whole satellite
神谷朋兆, 戸谷剛, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 62nd, ROMBUNNO.2F19, 2018
Japanese

超小型深宇宙探査機用ハイブリッドキックモータの開発
永田晴紀, 清谷優理香, 櫻井和人, 脇田督司, 戸谷剛, 衝撃波シンポジウム講演論文集(CD-ROM), 2017, ROMBUNNO.2A1‐2, 2018
To realize deep space missions on a limited budget, a hybrid rocket kick motor for a laboratory-scale space probe being kicked from GTO to a deep space trajectory is being developed. Nitrous Oxide (N2O) is selected as an oxidizer to allow for long-term non-cryogenic storage in space, and High Density Polyethylene (HDPE) is selected as a fuel for safety and affordability.Two fuel configurations are being considered for this mission: a conventional tubular fuel grain, and a Cascaded Multistage Impinging-jet (CAMUI) type fuel grain. This study presents results and analysis from the first set of CAMUI-type static firing tests employing N2O as an oxidizer, with the aim of clarifying performance related issues such as achieving an optimum oxidizer to fuel mass ratio O/F of around 6~7, quantifying fuel regression rate etc. for design purposes. The results of two gaseous N2O firing tests and two liquid N2O firing test lead to the following two conclusions. The use of liquid N2O will be necessary to realize an appropriate flowrate for space applications, and CAMUI-type motors may not be suitable for achieving optimum O/F because they tend to burn extremely fuel rich. Additional firing tests are necessary to quantify the fuel regression rate in CAMUI-type fuel and conventional tubular fuel grains using N2O., The Japan Society of Mechanical Engineers, Japanese

Investigation of graphite nozzle erosion in hybrid rockets using o2/c2h4
Landon Kamps, Shota Hirai, Kazuhito Sakurai, Tor Viscor, Yuji Saito, Raymond Guan, Hikaru Isochi, Naoto Adachi, Mitsunori Itoh, Harunori Nagata, 2018 Joint Propulsion Conference, 01 Jan. 2018

Investigation of regression rate under high-pressure in axial-injection end-burning hybrid rockets
Yushi Okutani, Yuji Saito, Masaya Kimino, Ayumu Tsuji, Kentaro Soeda, Harunori Nagata, 2018 Joint Propulsion Conference, 01 Jan. 2018

The accuracy of reconstruction techniques for determining hybrid rocket fuel regression rate
Yuji Saito, Landon Kamps, Kodai Komizu, Kentaro Soeda, Daniele Bianchi, Francesco Nasuti, Harunori Nagata, 2018 Joint Propulsion Conference, 01 Jan. 2018

Control of heat release energy during heating from solid-solid phase change material
Ryohei Gotoh, Tsuyoshi Totani, Masashi Wakita, Harunori Nagata, International Heat Transfer Conference, 2018-August, 4425, 4432, 2018

Experimental investigation of c* efficiency in nitrous oxide hybrid rockets
Erika Uchiyama, Yurika Kiyotani, Landon Kamps, Harunori Nagata, Advances in the Astronautical Sciences, 166, 109, 115, 01 Jan. 2018

Evaluation of Detonation Initiation Energy by collisions and reflections
松岡将司, 大関敦, 桧物恒太郎, 脇田督司, 戸谷剛, 永田晴紀, 燃焼シンポジウム講演論文集, 55th, 386‐387, 13 Nov. 2017
Japanese

THE EFFECT OF Q FACTORS ON THE EMITTANCE OF MICRO-CAVITIES
佐藤潤弥, 戸谷剛, 脇田督司, 永田晴紀, Thermophysical Properties, 38th, 111‐113, 01 Nov. 2017
Japanese

防衛分野と民生分野の研究連携について成熟した議論を
永田 晴紀, 翼 : 航空自衛隊連合幹部会機関誌, 41, 0, 105, 109, Oct. 2017
航空自衛隊連合幹部会, Japanese

Study on Response Time under Throttling Operation of End-Burning Hybrid Rockets
齋藤 勇士, 君野 正弥, 津地 歩, 尾村 和信, 安河内 裕之, 添田 建太郎, 戸谷 剛, 脇田 督司, 永田 晴紀, 年会講演会講演集, 48, 8p, 13 Apr. 2017
日本航空宇宙学会, Japanese

c* Efficiency of Hybrid Rockets
片野田 洋, 永田 晴紀, 鹿児島大学工学部研究報告, 58, 58, 1, 6, Mar. 2017
A c* efficiency of a hybrid rocket calculated by reconstruction technique, ηrec, is compared with the traditional c* efficiency, ηtrad, obtained by the time-averaged O/F ratio. Simulation data of combustion pressure and mass flow rate of oxidizer are provided for different three cases to calculate two types of c* efficiency. The calculated results show that 1) ηrec and ηtrad are almost equal when the theoretical characteristic exhaust velocity, c*th, varies almost linearly against the variation of O/F ratio during the firing, 2) ηrec is greater than ηtrad when c*th varies non-linearly against the variation of O/F ratio, 3) ηrec is appropriate as a c* efficiency of a hybrid rocket., 鹿児島大学, Japanese

Application of Axial-Injection End-Burning Hybrid Rockets to Spacecraft propulsion
齋藤勇士, 君野正弥, 津地歩, 尾村和信, 安河内裕之, 添田建太郎, 戸谷剛, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 61st, 2017

Combustion Technologies Relating to Hybrid Rockets
NAGATA Harunori, Journal of the Combustion Society of Japan, 59, 190, 243, 252, 2017
This paper summarizes researches about combustion technologies related to hybrid rockets, focusing on the enhancement of regression rates of solid fuels and the development of techniques for measuring fuel gasification rate. Methods for enhancing the regression rate were divided into two groups: improving the physical or chemical properties of a solid fuel, and improving the combustion flow field in a combustion chamber. In the former group, the use of liquefying fuels like paraffin-wax has become the mainstream of recent hybrid rocket development activities because these fuels have been shown to provide regression rates that are two to three times higher than values encountered with conventional solid fuels. Measuring the history of the fuel gasification rate in a hybrid rocket is not easy, and it has been an important subject in this field. Measurement techniques fall into two categories: the direct measurement of fuel thickness or fuel weight, and reconstruction techniques that estimate fuel flow rate through easily measurable histories such as liquid oxidizer flow rate, chamber pressure, thrust, etc. Recently, a new method to estimate the nozzle throat area history during firing was developed by improving on a reconstruction technique., Combustion Society of Japan, Japanese

Consideration on System and Flight Trajectory Analysis of Flying Test Bed for Technologies needed for Spaceplane
丸祐介, 澤井秀次郎, 永田晴紀, 小林弘明, 坂東信尚, 吉光徹雄, 江口光, 宇宙科学技術連合講演会講演集(CD-ROM), 61st, 2017

超小型探査機による惑星探査技術の開発
杉田精司, 鈴木宏二郎, 中須賀真一, 吉川一朗, 今村剛, 船瀬龍, 小泉宏之, 笠原慧, 吉岡和夫, 永田晴紀, 藤本正樹, 日本惑星科学会秋季講演会予稿集(Web), 2017, 2017

Development of a Hybrid Kick Motor for Extremely Small Deep Space Probes
KIYOTANI Yurika, HIRAI Shota, KAMPS Landon, YAMAGUCHI Ryo, SAKURAI Kazuhito, WAKITA Masashi, TOTANI Tsuyoshi, NAGATA Harunori, The Proceedings of Mechanical Engineering Congress, Japan, 2017, 0, S1920105, 2017, [Last author]

To realize deep space missions on a limited budget, a hybrid rocket kick motor for a laboratory-scale space probe being kicked from GTO to a deep space trajectory is being developed. Nitrous Oxide (N2O) is selected as an oxidizer to allow for long-term non-cryogenic storage in space, and High Density Polyethylene (HDPE) is selected as a fuel for safety and affordability.Two fuel configurations are being considered for this mission: a conventional tubular fuel grain, and a Cascaded Multistage Impinging-jet (CAMUI) type fuel grain. This study presents results and analysis from the first set of CAMUI-type static firing tests employing N2O as an oxidizer, with the aim of clarifying performance related issues such as achieving an optimum oxidizer to fuel mass ratio O/F of around 6~7, quantifying fuel regression rate etc. for design purposes. The results of two gaseous N2O firing tests and two liquid N2O firing test lead to the following two conclusions. The use of liquid N2O will be necessary to realize an appropriate flowrate for space applications, and CAMUI-type motors may not be suitable for achieving optimum O/F because they tend to burn extremely fuel rich. Additional firing tests are necessary to quantify the fuel regression rate in CAMUI-type fuel and conventional tubular fuel grains using N2O.

, The Japan Society of Mechanical Engineers, Japanese

Study on Hysteresis Characteristics of Axial-Injection End-Burning Hybrid Rockets under Throttling Operation
君野正弥, 齋藤勇士, 津地歩, 尾村和信, 安河内裕之, 添田建太郎, 戸谷剛, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 61st, ROMBUNNO.3H01, 2017
Japanese

Fuel Regression Characteristics of Axial-Injection End-Burning Hybrid Rockets Using N2O as an Oxidizer
尾村和信, 津地歩, 齋藤勇士, 君野正弥, 奥谷勇士, 小水弘大, 戸谷剛, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 61st, ROMBUNNO.3H04, 2017
Japanese

Feasibility of End-Burning Hybrid Rockets with Liquid Oxygen
津地歩, 齋藤勇士, 尾村和信, 君野正弥, 戸谷剛, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 61st, ROMBUNNO.3H03, 2017
Japanese

The relationship of chamber pressure and combustion efficiency on hybrid rocket using N2O as an oxidizer
清谷優理香, 山口亮, 櫻井和人, KAMPS Landon, 井上卓, 脇田督司, 戸谷剛, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 61st, ROMBUNNO.3H02, 2017
Japanese

ふく射センサの低温環境下でのふく射率および単一液滴流からの排熱量
嶋田泰三, 高梨知広, 両門健人, 戸谷剛, 永田晴紀, 脇田督司, 日本伝熱シンポジウム講演論文集(CD-ROM), 54th, ROMBUNNO.C332, 2017
Japanese

2‐amino‐2‐methyl‐1,3‐propanediolの固相‐固相結晶転移による潜熱を利用した蓄熱材の開発 過冷却状態の結晶化による発熱とガラス転移点の関係
後藤凌平, 永田晴紀, 戸谷剛, 脇田督司, 日本伝熱シンポジウム講演論文集(CD-ROM), 54th, ROMBUNNO.D124, 2017
Japanese

Thermal Design of 50kg Class Satellites Deployed from JEM Small Satellite Orbital Deployer J-SSOD
PANES Mitchao Delburg, 戸谷剛, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 61st, ROMBUNNO.2F21, 2017
Japanese

Thermal Design and On-orbit Validation of the First Philippine Micro-satellite: DIWATA-1
Delburg Mitchao, Tsuyoshi Totani, Yuji Sakamoto, Masashi Wakita, Harunori Nagata, Proceedings of 47th International Conference on Environmental Systems, ICES-2017-130, 2017, [Peer-reviewed]
English

Investigation of graphite nozzle-throat-erosion in a laboratory-scale hybrid rocket using GOX and HDPE
Landon Kamps, Shota Hirai, Yassine Ahmimache, Raymond Guan, Harunori Nagata, 53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017, 01 Jan. 2017

Investigation of regression characteristics under relatively high-pressure in Axial-injection End-Burning Hybrid Rockets
Yuji Saito, Masaya Kimino, Tsuji Ayumu, Yushi Okutani, Kazunobu Omura, Hiroyuki Yasukochi, Kentaro Soeda, Tsuyoshi Totani, Masashi Wakita, Harunori Nagata, 53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017, 01 Jan. 2017

Numerical and experimental investigation of nozzle thermochemical erosion in hybrid rockets
Daniele Bianchi, Landon Kamps, Francesco Nasuti, Harunori Nagata, 53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017, 01 Jan. 2017

Using equivalent burn time to improve regression characterization of the CAMUI type hybrid rocket engine
T. Viscor, H. Nagata, 53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017, 01 Jan. 2017

円筒デトネーション波の伝播限界へ流路幅と円筒波面の曲率が与える影響—Influence of channel width and curvature of cylindrical detonation wave on propagation limit
桧物, 恒太郎, 亀山, 頌太, 大関, 敦, 榎並, 聖也, 脇田, 督司, 戸谷, 剛, 永田, 晴紀, Himono, Tsunetaro, Kameyama, Shota, Ozeki, Atsushi, Enami, Takaya, Wakita, Masashi, Totani, Tsuyoshi, Nagata, Harunori, 宇宙航空研究開発機構特別資料: 第48回流体力学講演会/第34回航空宇宙数値シミュレーション技術シンポジウム論文集 = JAXA Special Publication: Proceedings of the 48th Fluid Dynamics Conference / the 34th Aerospace Numerical Simulation Symposium, JAXA-SP-16-007, 211, 216, 27 Dec. 2016
第48回流体力学講演会/第34回航空宇宙数値シミュレーション技術シンポジウム (2016年7月6日-8日. 金沢歌劇座), 金沢市, 石川
48th Fluid Dynamics Conference /the 34th Aerospace Numerical Simulation Symposium (July 6-8, 2016. The Kanazawa Theatre), Kanazawa, Ishikawa, Japan
To realize practical use of a Pulse Detonation Engine, reliable initiation of detonation waves is important and the amount of oxidizer for initiation is needed to decrease to get high specific impulse. So the authors propose a detonation initiator to solve these problems. In this initiator, detonation waves propagate around a reflector through some transition. First, planar detonation waves transit to cylindrical detonation waves. Second, cylindrical detonation waves transit to toroidal detonation waves. Finally, toroidal detonation waves propagate to planar detonation waves propagating large bore chamber. In the propagation and transition process, the propagation limit of cylindrical detonation waves is unclear even though there is some hypothesis. That is to say, cylindrical detonation waves are quenched by its curvature or the formation of their cell structure is inhibited by narrow channel. In this paper, cell sizes are correlated to threshold condition for quenching. The proportion of cell sizes to the channel width of planer channel and the radius of cylindrical detonation waves are researched. It became obvious that cylindrical detonation waves can propagate stably if the proportion of the cell size to the radius of cylindrical detonation waves is larger than 25 and have the potential to survive and propagate if the proportion of the cell size to the radius of cylindrical detonation waves is larger than 17.
形態: カラー図版あり
Physical characteristics: Original contains color illustrations
資料番号: AA1630031030
レポート番号: JAXA-SP-16-007, 宇宙航空研究開発機構(JAXA), Japanese

液滴ラジエータにおける単一液滴流からの排熱量
嶋田泰三, 高梨知広, 戸谷剛, 永田晴紀, 脇田督司, Thermophysical Properties, 37th, 96‐98, 28 Nov. 2016
Japanese

液体酸素を用いた固体燃料管内燃え拡がりに関する研究
津地歩, 齋藤勇士, 横井俊希, 尾村和信, 嶋田泰三, 戸谷剛, 脇田督司, 永田晴紀, 燃焼シンポジウム講演論文集, 54th, C323, 26 Nov. 2016
Japanese

端面燃焼式ハイブリッドロケットの燃料後退モデルに関する考察
齋藤勇士, 横井俊希, 津地歩, 尾村和信, 安河内裕之, 添田建太郎, 戸谷剛, 脇田督司, 永田晴紀, 燃焼シンポジウム講演論文集, 54th, P222, 26 Nov. 2016
Japanese

燃料微小管内を燃え拡がる火炎への雰囲気圧力の影響
横井俊希, 齋藤勇士, 尾村和信, 津地歩, 安河内裕之, 添田建太郎, 脇田督司, 戸谷剛, 永田晴紀, 燃焼シンポジウム講演論文集, 54th, C324, 26 Nov. 2016
Japanese

デトネーション波の衝突・反射による遷移促進効果に関する研究
大関敦, 松岡将司, 桧物恒太郎, 脇田督司, 戸谷剛, 永田晴紀, 燃焼シンポジウム講演論文集, 54th, E341, 26 Nov. 2016
Japanese

Development Study of a Flight Demonstrator for Spaceplane Technologies utilizing a High-Altitude Balloon
Maru Yusuke, Sawai Shujiro, Nagata Harunori, Bando Nobutaka, Sakai Shinichiro, Yoshimitsu Tetsuo, Eguchi Hikaru, 大気球シンポジウム: 平成28年度 = Balloon Symposium: 2016, Nov. 2016
Balloon Symposium 2016 (November 1-2, 2016. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS), Japanese

Measurement and prediction of local regression rate of solid burning with impinging oxidizer jet　　　　　　　　　　　　　　　
Tsuneyoshi Matsuoka, Kyohei Kamei, Takafumi Yamazaki, Harunori Nagata, Yuji Nakamura, Thirteenth International Conference on Flow Dynamics (ICFD 2016), Oct. 2016, [Peer-reviewed]
English

High Speed Flight Test Bed System using a High Altitude Balloon
丸 祐介, 澤井 秀次郎, 坂東 信尚, 永田 晴紀, 吉光 徹雄, 坂井 真一郎, 後藤 健, 江口 光, 宇宙科学技術連合講演会講演集, 60, 6p, 06 Sep. 2016
日本航空宇宙学会, Japanese

Flight experiment of a two-stage CAMUI type hybrid rocket to verify a liquid oxygen settling sequence for air launch
五十地 輝, 植松 努, 川端 良輔, 高梨 知広, 永田 晴紀, 宇宙科学技術連合講演会講演集, 60, 4p, 06 Sep. 2016
日本航空宇宙学会, Japanese

Enhancement of Earth Escape Energy by use of Sequential Lunar Swing-by on a Hyperbolic Orbit
須田 俊太郎, 川勝 康弘, 澤井 秀次郎, 永田 晴紀, 戸谷 剛, 宇宙科学技術連合講演会講演集, 60, 5p, 06 Sep. 2016
日本航空宇宙学会, Japanese

Accuracy and Applicability of a Reconstruction Technique for Determining Nozzle Throat Erosion History in Hybrid Rockets
ケンプス ランドン, サイトウ ユウジ, ヒライ ショウタ, ナガタ ハルノリ, 宇宙科学技術連合講演会講演集, 60, 6p, 06 Sep. 2016
日本航空宇宙学会, English

Verification of Thermal Design Procedure for Short-term Development of Micro-satellite
戸谷 剛, 毛利 正宏, 脇田 督司, 永田 晴紀, 宇宙科学技術連合講演会講演集, 60, 6p, 06 Sep. 2016
日本航空宇宙学会, Japanese

Investigation of the Throttling Characteristics of Axial-injection End-burning Type Hybrid Rockets
Yuji SAITO, Masaya KIMINO, Ayumu TSUJI, Kazunobu OMURA, Hiroyuki YASUKOCHI, Kentaro SOEDA, Tsuyoshi TOTANI, Masashi WAKITA, Harunori NAGATA, TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 60, 1, 6p, 18, 06 Sep. 2016
日本航空宇宙学会, Japanese

夏燕随筆 「わからなさ」とリスク管理
永田 晴紀, 翼 : 航空自衛隊連合幹部会機関誌, 40, 0, 62, 64, Jul. 2016
航空自衛隊連合幹部会, Japanese

Verification of Rapid Thermal Design Approach using Design and Flight Data of Hodoyoshi-1 Microsatellite
Tsuyoshi Totani, Hiroto Ogawa, Masashi Wakita, Harunori Nagata, Yusuke Kuramoto, Naoki Miyashita, Proceeding of 46th International Conference on Environmental Systems, ICES-2016-116, Jul. 2016, [Peer-reviewed]
English

Experimental and Analytical Investigation of Effect of Pressure on Regression Rate of Axial-Injection End-Burning Hybrid Rockets
Yuji Saito, Toshiki Yokoi, Harunori Nagata, Hiroyuki Yasukochi, Kentaro Soeda, Tsuyoshi Totani, Masashi Wakita, 52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016, 47, 9p, 14 Apr. 2016
日本航空宇宙学会, Japanese

端面燃焼式ハイブリッドロケットにおける燃料後退特性の圧力依存性に関する実験的および解析的考察
齋藤勇士, 横井俊希, 嶋田泰三, 安河内裕之, 添田建太郎, 戸谷剛, 脇田督司, 永田晴紀, 日本航空宇宙学会年会講演会講演集(CD-ROM), 47th, ROMBUNNO.2D8, 2016
Japanese

円筒デトネーション波の伝播限界へ流路幅と円筒波面の曲率が与える影響
桧物恒太郎, 亀山頌太, 大関敦, 榎並聖也, 脇田督司, 戸谷剛, 永田晴紀, 流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM), 48th-34th, ROMBUNNO.2E13, 2016
Japanese

Throttling characteristics of end-burning type hybrid rockets
NAGATA Harunori, SAITO Yuji, YOKOI Toshiki, SHIMADA Taizo, YASUKOCHI Hiroyuki, SOEDA Kentaro, TOTANI Tsuyoshi, WAKITA Masashi, The Proceedings of Mechanical Engineering Congress, Japan, 2016, 0, S1920202, 2016

The authors have previously proposed the concept of end burning type hybrid rockets which would use cylindrical fuel grains consisting of an array of many small ports running in the axial direction through which oxidizer gas would flow. Because of difficulty in manufacturing a fuel grain that satisfied requirements such as high volumetric filling rate (above 0.97) and micro-sized port intervals, the end burning hybrid rocket had yet to be achieved. The authors succeeded to verify the novel end burning type hybrid rocket for the first time owing recent progress in 3D printing technology. This paper reports throttling firing tests to verify the excellent throttling characteristic of end-burning type hybrid rockets, that is, virtually no O/F shift during throttling.

, The Japan Society of Mechanical Engineers, Japanese

Evaluation of anti-erosion materials for hybrid rocket nozzles
YAMAGUCHI Ryo, KAWABATA Ryosuke, HIRAI Shota, KAMPS Landon, WAKITA Masashi, TOTANI Tsuyoshi, NAGATA Harunori, The Proceedings of Mechanical Engineering Congress, Japan, 2016, 0, S1920201, 2016

These days, CAMUI type hybrid rocket has been developed. The rocket is faced with the problem of erosion of graphite nozzle. Nozzle erosion, which is mainly caused by oxidation reaction, decreases specific impulse of rockets. The authors selected some materials which can prevent nozzle erosion and evaluated anti-erosion materials for hybrid rocket nozzle by combustion experiments. We used 2.5 kN class CAMUI type hybrid rocket motor for combustion experiment. The authors used two types of fiber reinforced ceramics, silicon carbide ceramics, zirconia, tungsten carbide, silicon nitride ceramics, graphite coated by silicon carbide, alumina and carbon fiber carbon composite for nozzles. As an experimental result, tungsten carbide and graphite coated by silicon carbide showed good anti-erosion characteristics for hybrid rocket nozzles. High melting point and high thermal conductivity seem favorable for anti-erosion materials for hybrid rocket nozzles.

, The Japan Society of Mechanical Engineers, Japanese

Method for determining nozzle throat erosion history in hybrid rockets
Landon Kamps, Yuji Saito, Ryosuke Kawabata, Yusuke Takahashi, Harunori Nagata, 52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016, 01 Jan. 2016

Verification of the throttling characteristics of axial-injection end-burning type hybrid rockets
Yuji Saito, Toshiki Yokoi, Hiroyuki Yasukochi, Kentaro Soeda, Tsuyoshi Totani, Masashi Wakita, Harunori Nagata, Proceedings of the International Astronautical Congress, IAC, 2016, S1920202, 01 Jan. 2016
The Japan Society of Mechanical Engineers, Japanese

ハイブリッドロケットのノズル侵食履歴およびノズルスロート温度履歴の取得
永田晴紀, 川端良輔, 遠藤瞳, 金井竜一郎, 平井翔大, 脇田督司, 戸谷剛, 五十地輝, 燃焼シンポジウム講演論文集, 53rd, 244, 245, 04 Nov. 2015
Japanese

燃料微小管内での燃え広がり現象に関する研究
横井俊希, 齋藤勇士, 脇田督司, 戸谷剛, 永田晴紀, 燃焼シンポジウム講演論文集, 53rd, 308, 309, 04 Nov. 2015
Japanese

気球を利用したスペースプレーン技術実証機の研究
丸 祐介, 澤井 秀次郎, 永田 晴紀, 坂東 信尚, 坂井 真一郎, 吉光 徹雄, 江口 光, Maru Yusuke, Sawai Shujiro, Nagata Harunori, Bando Nobutaka, Sakai Shin-ichiro, Yoshimitsu Tetsuo, 大気球シンポジウム: 平成27年度 = Balloon Symposium: 2015, Nov. 2015
大気球シンポジウム 平成27年度（2015年11月5-6日. 宇宙航空研究開発機構宇宙科学研究所 (JAXA)(ISAS)）, 相模原市, 神奈川県資料番号: SA6000044003レポート番号: isas15-sbs-003, 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS), Japanese

液滴流からの排熱量測定法
高梨知広, 戸谷剛, 脇田督司, 永田晴紀, Thermophysical Properties, 36th, 180‐182, 19 Oct. 2015
Japanese

金属膜を持つ表面微細構造の光学特性
戸谷剛, 戸谷剛, 近藤良夫, 山木宏, 脇田督司, 永田晴紀, Thermophys Prop, 36th, 213, 215, 19 Oct. 2015
Japanese

Study of a High-Speed Flight Experiment System with combination of a High Altitude Balloon and a Rocket Booster
丸 祐介, 澤井 秀次郎, 永田 晴紀, 宇宙科学技術連合講演会講演集, 59, 6p, 07 Oct. 2015
日本航空宇宙学会, Japanese

Initiation of cylindrical detonation wave in an enhanced reflection type detonation initiator in multi-cycle operation conditions
亀山頌太, 菊地敬太, 桧物恒太郎, 脇田督司, 戸谷剛, 永田晴紀, 宇宙航空研究開発機構特別資料 JAXA-SP-, JAXA-SP-14-010, 14-010, 173, 178, 25 Mar. 2015
第46回流体力学講演会/第32回航空宇宙数値シミュレーション技術シンポジウム (2014年7月3日-4日. 弘前文化センター), 弘前市, 青森県
46th Fluid Dynamics Conference / 32nd Aerospace Numerical Simulation Symposium (July 3-4, 2014. Hirosaki Bunka Center), Hirosaki, Aomori, Japan
To achieve practical uses of large bore Pulse Detonation Engines, the authors have proposed the enhanced reflection type detonation initiator. Here, successful transmission from a planar detonation wave in a predetonator to a self-sustainable expanding cylindrical detonation wave at a cylindrical path is a key issue. In a previous single-cycle research, the authors revealed that the necessary overfilling radius of the driver gas (stoichiometric H2-O2 mixture) to initiate a cylindrical wave is 75 mm. The aim of this study is to investigate the effect of multi-cycle operation condition on the transmission to a cylindrical detonation wave. The result shows that a planar detonation wave with theoretical CJ speed is formed but a cylindrical detonation wave is not formed at any overfilling radius from 50 to 175 mm. Soot track records at the cylindrical path surfaces and a mixing analysis of driver and target mixtures using ANSYS FLUENT strongly indicate that residual nitrogen gases at the exit of the predetonator have a negative effect on the transmission.
形態: カラー図版あり
Physical characteristics: Original contains color illustrations
資料番号: AA1530023031
レポート番号: JAXA-SP-14-010, 宇宙航空研究開発機構(JAXA), Japanese

端面燃焼式ハイブリッドロケットの燃料後退特性に関する研究
横井俊希, 齋藤勇士, NEUMANN Lukas, 脇田督司, 戸谷剛, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 59th, 2015

金属膜を持つ表面微細構造の放射率
戸谷剛, 戸谷剛, 櫻井篤, 近藤良夫, 脇田督司, 永田晴紀, 日本機械学会熱工学コンファレンス講演論文集(CD-ROM), 2015, ROMBUNNO.C121, _C121-2_, 2015
Technologies for drying a material with a flammable solvent at a low temperature are required. It is reasonable to evaporate a flammable solvent using radiation at the absorption band of a flammable solvent and to eject the flammable vapor with a cold air. The meta material with Au/Al2O3/Au was fabricated by using an sputtering equipment, an atomic layer deposition equipment, and an electron beam lithography equipment. The reflectances of the meta material structure were measured by using an FT-IR equipment with an integral sphere. It is clarified that the emissivities of the meta material structure are larger than 0.8 at the absorption band of toluene., The Japan Society of Mechanical Engineers, Japanese

超小型衛星に対する新しい熱設計手順の妥当性検証
毛利正宏, 須田俊太郎, 尾形明仁, 戸谷剛, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 59th, ROMBUNNO.3M01, 2015
Japanese

表面微細構造による放射波長制御に及ぼす形状の効果
戸谷剛, 戸谷剛, 色川俊雄, 脇田督司, 永田晴紀, 日本伝熱シンポジウム講演論文集(CD-ROM), 52nd, ROMBUNNO.G122, 2015
Japanese

反射を利用した大口径PDEイニシエータにおける円筒デトネーション波から円環デトネーション波への遷移に関する研究
大関敦, 菊地敬太, 桧物恒太郎, 亀山頌太, 脇田督司, 戸谷剛, 永田晴紀, 流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM), 47th-33rd, ROMBUNNO.2E12, 2015
Japanese

ハイブリッドロケットにおけるノズルスロートエロージョンに関する研究
川端良輔, 齋藤勇士, 平井翔大, 脇田督司, 戸谷剛, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 59th, ROMBUNNO.1A06, 2015
Japanese

液滴流からの排熱量測定と数値解析
高梨知広, 戸谷剛, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 59th, ROMBUNNO.3M09, 2015
Japanese

展開型太陽電池パネルを有する超小型衛星の新しい熱設計手順
尾形明仁, 戸谷剛, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 59th, ROMBUNNO.3M02, 2015
Japanese

結晶構造変化により蓄熱する蓄熱材の地上および軌道上試験
戸谷剛, 國拓也, 磯野拓也, 佐藤敏文, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 59th, ROMBUNNO.3M06, 2015
Japanese

Verification firings of end-burning type hybrid rockets
Harunori Nagata, Hayato Teraki, Yuji Saito, Ryuichiro Kanai, Hiroyuki Yasukochi, Masashi Wakita, Tsuyoshi Totani, 51st AIAA/SAE/ASEE Joint Propulsion Conference, 01 Jan. 2015

金属薄膜を持つ表面微細構造による放射率ピークの理論値とのずれ
色川俊雄, 戸谷剛, 永田晴紀, 脇田督司, Thermophys Prop, 35th, 40, 42, 22 Nov. 2014
Japanese

結晶転移により蓄熱する蓄熱材の蓄熱量に及ぼす劣化の影響
國拓也, 戸谷剛, 佐藤敏文, 脇田督司, 永田晴紀, Thermophys Prop, 35th, 226, 228, 22 Nov. 2014
Japanese

端面燃焼式ハイブリッドロケット用固体燃料の後退特性
寺木勇人, 齋藤勇士, 金井竜一郎, 脇田督司, 戸谷剛, 永田晴紀, 燃焼シンポジウム講演論文集, 52nd, 556, 557, 20 Nov. 2014
Japanese

低レイノルズ数域におけるCAMUI型固体燃料の燃料後退特性
遠藤瞳, 川端良輔, 脇田督司, 戸谷剛, 永田晴紀, 燃焼シンポジウム講演論文集, 52nd, 554, 555, 20 Nov. 2014
Japanese

反射体を用いたPDEイニシエータの円錐部の短縮が爆轟波の伝播に与える影響
菊地敬太, 桧物恒太郎, 亀山頌太, 脇田督司, 戸谷剛, 永田晴紀, 燃焼シンポジウム講演論文集, 52nd, 332, 333, 20 Nov. 2014
Japanese

一定レイノルズ数酸化剤衝突噴流のよどみ点近傍における固体燃料燃焼速度に雰囲気圧力が及ぼす影響
斉藤竜也, 寺川健, 脇田督司, 戸谷剛, 永田晴紀, 燃焼シンポジウム講演論文集, 52nd, 538, 539, 20 Nov. 2014
Japanese

Development of 15 kN thrust class CAMUI-type Hybrid Rocket Motor
川端良輔, 永田晴紀, 戸谷剛, 脇田督司, 五十地輝, 植松努, 宇宙科学技術連合講演会講演集(CD-ROM), 58, 4p, 12 Nov. 2014
日本航空宇宙学会, Japanese

Numerical Analysis of Thermal Radiation from Parallel Streams of Liquid Droplets in Liquid Droplets Radiator
高梨知広, 戸谷剛, 永田晴紀, 脇田督司, 宇宙科学技術連合講演会講演集(CD-ROM), 58, 3p, 12 Nov. 2014
日本航空宇宙学会, Japanese

大気球を利用したスペースプレーン技術の高速飛行実験システムの開発研究
丸 祐介, 澤井 秀次郎, 小林 弘明, 坂東 信尚, 坂井 真一郎, 後藤 健, 永田 晴紀, スペースプレーン技術実証機WG, Maru Yusuke, Sawai Shujiro, Kobayashi Hiroaki, Bando Nobutaka, Sakai Shin-ichiro, Goto Ken, Nagata Harunori, 大気球シンポジウム: 平成26年度 = Balloon Symposium: 2014, Nov. 2014
大気球シンポジウム 平成26年度（2014年11月6-7日. 宇宙航空研究開発機構宇宙科学研究所 (JAXA)(ISAS)）, 相模原市, 神奈川県資料番号: SA6000021011レポート番号: isas14-sbs-011, 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS), Japanese

Radiation Enhancement by Metal Film on Micro Cavities in Resin
Tsuyoshi TOTANI, Toshio IROKAWA, Minoru IWATA, Masashi WAKITA, Harunori NAGATA, Proceedings of the 15th International Heat Transfer Conference, IHTC-15, IHTC15-8771, Aug. 2014, [Peer-reviewed]
English

スペースプレーン技術の飛行実証のための気球を利用した飛行実験システムの開発
丸祐介, 澤井秀次郎, 小林弘明, 坂東信尚, 坂井真一郎, 後藤健, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 58th, 2014

結晶構造変化により蓄熱する蓄熱材の軌道上試験
戸谷剛, 國拓也, 佐藤敏文, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 58th, ROMBUNNO.2E12, 2014
Japanese

酸化剤衝突噴流による固体燃料燃焼場の数値解析
縄田和也, 大島伸行, 斉藤達也, 脇田督司, 戸谷剛, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 58th, ROMBUNNO.2J08, 2014
日本航空宇宙学会, Japanese

単一液滴流からの排熱量の測定と数値解析
高梨知広, 戸谷剛, 木村優斗, 永田晴紀, 脇田督司, 日本伝熱シンポジウム講演論文集(CD-ROM), 51st, ROMBUNNO.FSP406, 2014
Japanese

ハイブリッドロケット燃焼データ解析法の精度と適用範囲に関する研究
齋藤勇士, LAMBOURG Aurelien, 川端良輔, 脇田督司, 戸谷剛, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 58th, ROMBUNNO.2J02, 2014
Japanese

円筒波の起爆と希釈燃料への伝播に流路幅が与える影響
桧物恒太郎, 菊地敬太, 亀山頌太, 脇田督司, 戸谷剛, 永田晴紀, 衝撃波シンポジウム講演論文集(CD-ROM), 2013, ROMBUNNO.3A2-5, 2014
Japanese

反射を利用した爆轟波生成装置の連続運転条件における円筒爆轟波の生成
亀山頌太, 菊地敬太, 桧物恒太郎, 脇田督司, 戸谷剛, 永田晴紀, 流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM), 46th-32nd, ROMBUNNO.2E03, 2014
Japanese

S1920103 Preliminary Study of LOX Tank Insulation to Air-launch a Hybrid Rocket
KAWABATA Ryosuke, INABA Yasuhiko, ISHIYAMA Tatsuya, WAKITA Masashi, TOTANI Tsuyoshi, NAGATA Harunori, The Proceedings of Mechanical Engineering Congress, Japan, 2014, 0, _S1920103, -_S1920103-, 2014
A hypersonic flight experiment by a combination of a scientific observation balloon and a CAMUI-type hybrid rocket is proposed. This is one of the rockoon methods. In this experiment, liquid oxygen (LOX) is filled on the ground and thermally insulated until the launch in high altitudes. The gas phase volume in the LOX tank decrease with time due to heat input from ambient. Eventually, the gas phase disappears, followed by a sudden increase of the LOX tank pressure. The heat insulation of the LOX tank has to provide no less than five hours from the LOX filing to the sudden pressure increase. In this study, a numerical model to predict pressure histories in the LOX tank was developed. The results were compared and verified with experimental results in a small scale. Finally, pressure histories at a full-scale system were predicted to provide a guideline for the design of a thermal insulator., The Japan Society of Mechanical Engineers, Japanese

金属膜を持つ微小キャビティの構造と放射ピークの関係
戸谷剛, 戸谷剛, 色川俊雄, 脇田督司, 永田晴紀, 日本機械学会熱工学コンファレンス講演論文集(CD-ROM), 2014, ROMBUNNO.E215, _E215-2_, 2014
Micro-cavities were made from Zr dispersing liquid on SiO_2 bases and were coated by Au for generating resonance phenomena. The theoretical wavelength of reflectance drop differed 4% from the experiment data. A numerical analysis taking into account the pitch was carried out to find causes of the difference. The wavelength of reflectance drop in the analysis were closer to experiment data than theoretical predictions. On the other hand, the wavelengths of reflectance drop except for the fundamental vibrational mode obtained in the analysis did not accord 7.6 to 8.5 % with experimental data. The reflectance obtained in the analysis was 4 to 11% different from experimental data., The Japan Society of Mechanical Engineers, Japanese

マイクロキャビティを持つラジエータの冷却効果
戸谷剛, 色川俊雄, 脇田督司, 永田晴紀, 日本伝熱シンポジウム講演論文集(CD-ROM), 51st, ROMBUNNO.H341, 2014
Japanese

結晶変化を伴う蓄熱材の蓄熱・放熱試験
戸谷剛, 國拓也, 佐藤敏文, 脇田督司, 永田晴紀, 日本機械学会熱工学コンファレンス講演論文集(CD-ROM), 2014, ROMBUNNO.F117, _F117-2_, 2014
It is desirable that the heat storage materials for nano and micro satellites have the characteristic of not phase change but crystal transformation for the heat storage. Trans-1,4-polybutadien has the desirable characteristic of crystal transformation at the heat storage temperature. The heat storage and release tests were conducted on the ground and in orbit. It is clarified that the heat storage and release characteristics do not change in heat storage and release cycle of 300 times and Trans-1,4-polybutadien can storage and release heat in orbit., The Japan Society of Mechanical Engineers, Japanese

A numerical analysis and measurement of radiation heat from a liquid droplet stream under gravitational environment
Tomohiro Takanashi, Tsuyoshi Totani, Yuto Kimura, Harunori Nagata, Masashi Wakita, Proceedings of the International Astronautical Congress, IAC, 1, 519, 522, 01 Jan. 2014

液滴流からの放射廃熱量の数値解析および測定
高梨知広, 戸谷剛, 永田晴紀, 脇田督司, Thermophys Prop, 34th, 141, 143, 20 Nov. 2013
Japanese

円盤状流路に入射する平面デトネーション波の半径方向に伝播する円筒波への遷移にプリデトネータ直径が与える影響
桧物恒太郎, 菊地敬太, 脇田督司, 戸谷剛, 永田晴紀, 燃焼シンポジウム講演論文集, 51st, 544, 545, 20 Nov. 2013
Japanese

表面微細構造を用いた放射波長制御
戸谷剛, 色川俊雄, 脇田督司, 永田晴紀, Thermophys Prop, 34th, 307, 309, 20 Nov. 2013
Japanese

結晶転移する蓄熱材の蓄熱量
戸谷剛, 國拓也, 佐藤敏文, 脇田督司, 永田晴紀, Thermophys Prop, 34th, 96, 98, 20 Nov. 2013
Japanese

Scale effect on flame spread rate in narrow cylindrical gap　　　　　　　　　　　　　　　
Tsuneyoshi Matsuoka, Yuji Nakamura, Harunori Nagata, Takuya Yamazaki, The 8th International Symposium on Advanced Science and Technology in Experimental Mechanics (8th ISEM’13-Sendai), Nov. 2013, [Peer-reviewed]
English

1212 Failure analysis for launch experiments of CAMUI-Avionics
SAITO Shin-nosuke, ITO Tomonori, IINO Takayuki, HASEGAWS Takayuki, Mitsuhashi Ryuichi, Satori Shin, NAGATA Harunori, CHIBA Kazuhisa, The Proceedings of Design & Systems Conference, 2013, 23, "1212, 1"-"1212-5", 23 Oct. 2013
A students group Hokkaido Space Union had been to space development for nine years. HSU made data handling unit named Sprit-nexus. It has been mounted on the CAMUI hybrid rocket. The objective obtain a telemetry data of the Sprit-nexus for the CAMUI hybrid rocket recovery. Telemetry data is composed of position coordinates and altitude and acceleration and attitude. CAMUI hybrid rocket is being developed by professor Harunori Nagata in Hokkaido University. CAMUI hybrid rocket was launched in Taiki Aerospace Research Field on July 28 2012. It was to go recovery by the ships from the sea after launch but, Sprit-nexus could not obtained a telemetry data. I will tried to find the cause of failure. As a result, the visual observation proved simple faulty electrical wiring., The Japan Society of Mechanical Engineers, Japanese

表面微細構造による放射波長制御
戸谷剛, 色川俊雄, 脇田督司, 永田晴紀, 日本機械学会熱工学コンファレンス講演論文集, 2013, 153‐154, 154, 18 Oct. 2013
A periodic micro structure of the cubic cavity of 6.0μm×6.0μm×6.0μm is built on an ultra violet curable resin by the UV nanoimprint method. A gold film is sputtered on the periodic micro structure. This method can manufacture the periodic micro structure with the metal surface on a large area at a lower cost than etching. It is measured that the maximum normal emissivity of the periodic micro structure is 0.6 near 10μm in the case of the gold film of 200 nm thick on the surface facing a sputter source. The periodic micro structure with the gold film contributes to the prevention of global warming., The Japan Society of Mechanical Engineers, Japanese

液滴流の熱放射測定のための数値解析
高梨知広, 戸谷剛, 永田晴紀, 脇田督司, 日本機械学会熱工学コンファレンス講演論文集, 2013, 163‐164, 164, 18 Oct. 2013
Waste heat from liquid droplet flow is due to be measured by a part of research of the liquid droplet radiator which is a radiator for large-sized spacecrafts. In order to take the influence of absorption or dispersion into consideration, the simulation inside an experimental device was performed. In the case of the single liquid droplet flow, the energy from the liquid droplet flow in a measuring range was set to 0.252 w/m^2. The energy from the surface of a wall was set to 0.116 w/m2. A possibility of separating the amount of thermal radiation obtained in an experiment was able to be shown., The Japan Society of Mechanical Engineers, Japanese

結晶転移する蓄熱材の蓄熱量
戸谷剛, 國拓也, 佐藤敏文, 脇田督司, 永田晴紀, 日本機械学会熱工学コンファレンス講演論文集, 2013, 115‐116, 116, 18 Oct. 2013
In order to increase the heat capacity of nano and micro satellites, the development of a heat storage material for nano and micro satellites has been performed. It is desirable that the heat storage materials for nano and micro satellites have the characteristic of not phase change but crystal transformation for the heat storage. Trans-1,4-polybutadien transforms crystal structure at the temperature of heat storage. Trans-1,4-polybutadien is produced and the heat storage performance is measured. It is clarified that the produced trans-1,4-polybutadien has 80 J/g of heat storage performance. This value corresponding to 70 % of heat storage performance pointed out in the previous literature., The Japan Society of Mechanical Engineers, Japanese

Progress of CAMUI-type hybrid rocket as a flying test bed
永田 晴紀, 植松 努, 伊藤 献一, 宇宙科学技術連合講演会講演集, 57, 7p, 09 Oct. 2013
日本航空宇宙学会, Japanese

Network-Construction for Development of Human Resources on Creative Science and Technology Using CanSat and Pico-Satellite
宮崎 康行, 永田 晴紀, 木村 真一, 宇宙科学技術連合講演会講演集, 57, 5p, 09 Oct. 2013
日本航空宇宙学会, Japanese

Numerical Analysis to Measure Radiative Waste Heat from Liquid Droplet Flow
高梨 知広, 脇田 督司, 永田 晴紀, 宇宙科学技術連合講演会講演集, 57, 4p, 09 Oct. 2013
日本航空宇宙学会, Japanese

Development and flight demonstration of 5 kN thrust class CAMUI type hybrid rocket
Harunori Nagata, Masashi Wakita, Tsuyoshi Totani, Tsutomu Uematsu, 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 12, 29, Ta_1, Ta_4, 16 Sep. 2013
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, English

Proposal of procedure of thermal design on micro and nano satellites pointing to earth
Tsuyoshi Totani, Hiroto Ogawa, Ryota Inoue, Tilok K. Das, Masashi Wakita, Harunori Nagata, 43rd International Conference on Environmental Systems, 16 Sep. 2013

Scale Effect on Flame Spreading in Narrow Gap of Solid Combustibles
松岡常吉, 中村祐二, 永田晴紀, 山崎拓也, 日本実験力学会講演論文集, 13, 394, 399, 20 Aug. 2013
日本実験力学会, Japanese

Gravity effect on flow field of flame spread in fuel tube　　　　　　　　　　　　　　　
Tsuneyoshi Matsuoka, Harunori Nagata, Yuji Nakamura, Seventh International Symposium on Scale Modeling (ISSM-7), Aug. 2013, [Peer-reviewed]
English

Detonation Transition Around Cylindrical Reflector of Pulse Detonation Engine Initiator
Masashi Wakita, Masayoshi Tamura, Akihiro Terasaka, Kazuya Sajiki, Tsuyoshi Totani, Harunori Nagata, JOURNAL OF PROPULSION AND POWER, 29, 4, 825, 831, Jul. 2013, [Peer-reviewed]
English

Effect of Reynolds number and flow channel geometry on regression formula for forward-end faces in CAMUI type fuel grain
Ryuichiro Kanai, Tatsuya Ishiyama, Masahiro Nohara, Hirokazu Izumo, Masashi Wakita, Tsuyoshi Totani, Harunori Nagata, Advances in the Astronautical Sciences, 146, 79, 84, 24 Apr. 2013

大口径パルスデトネーションエンジン用イニシエータにおける円筒デトネーション波の伝播に関する研究
桧物恒太郎, 棧敷和弥, 脇田督司, 戸谷剛, 永田晴紀, 宇宙航空研究開発機構特別資料 JAXA-SP-, 12-010, 73, 78, 29 Mar. 2013
Japanese

大口径パルスデトネーションエンジン用イニシエータにおける円筒デトネーション波の伝播に関する研究—Propagation Characteristics of Cylindrical Detonation Wave in Detonation Initiator for Large Bore Pulse Detonation Engines
桧物, 恒太郎, 棧敷, 和弥, 脇田, 督司, 戸谷, 剛, 永田, 晴紀, Himono, Tsunetaro, Sajiki, Kazuya, Wakita, Masashi, Totani, Tsuyoshi, Nagata, Harunori, 宇宙航空研究開発機構特別資料 = JAXA Special Publication: Proceedings of 44th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2012, JAXA-SP-12-010, 73, 78, 29 Mar. 2013
第44回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2012 (2012年7月5日-6日. 富山国際会議場大手町フォーラム), 富山市, 富山県
44th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2012 (July 5-6, 2012. Toyama International Conference Center), Toyama Japan
Detonation initiation is one of the most important problems of pulse detonation engines. A reflector installed near a predetonator exit is effective to maintain detonation waves. The incident detonation waves from the predetonator transform its shape from planer detonation wave to cylindrical detonation wave and from cylindrical detonation wave to toroidal detonation wave around the reflector. To prevent the detonation wave downstream of a reflector from disappearing, it is important to form a cylindrical detonation waves upstream of the reflector. To define the minimal quantity of driver gas to form cylindrical detonation waves and to make sense of the mechanism that determine the quantity, the authors uses a large-bore plate combustor and varied the following parameters to find the quantity to form a cylindrical detonation wave : the quantity of driver gas and nitrogen concentration. To evaluate the quantity of the driver gas, the authors us""" es overfilling radius. The over filling radius is the radius of the cylinder that is equal to the driver gas filled in the combustion chamber. Results indicate that the mixing between driver gas and target gas is critical to successful transmission. To form the cylindrical detonation wave reliably, the concentration of driver gas must be maintained at a high level so that the cell size doesn’t become large.
形態: カラー図版あり
Physical characteristics: Original contains color illustrations
資料番号: AA0061958013
レポート番号: JAXA-SP-12-010, 宇宙航空研究開発機構(JAXA), Japanese

平成24年度先進的燃焼技術の調査研究：推進薬の燃焼技術　　　　　　　　　　　　　　　
永田晴紀, 松岡常吉, 和田豊, 福地亜宝郎, 藤里公司, Mar. 2013, [Invited]
Japanese, Book review

Development of GOX Hybrid Rocket Test Engine Facility in Hybrid Rocket ResearchWorking Group
KITAGAWA Koki, SHIMADA Toru, HORI Keiichi, TAKEMAE Toshiaki, SHIRAISHI Noriko, TOMIZAWA Toshio, SUZUKI Naohiro, YAGISHITA Tsuyoshi, OSHIMA Nobuyuki, NAGATA Harunori, WAKITA Masashi, CHIBA Kazuhisa, SAWADA Keisuke, NAGAI Hiroki, WADA Yutaka, YUASA Saburo, SAKURAI Takashi, KANAZAKI Masahiro, NAKAGAWA Ichiro, MORITA Takakazu, NAKAMIYA Masaki, ASO Shigeru, TANI Yasuhiro, TSUBOI Nobuyuki, Proceedings. International Conference on Flow Dynamics (CD-ROM), 10th, 2013

Development of a Liquid Oxygen Supply System for a Small-scale Sounding Rocket
NAGATA Harunori, JAPANESE JOURNAL OF MULTIPHASE FLOW, 27, 4, 393, 400, 2013
A liquid oxygen supply system for a small-scale sounding rockets was developed. The sounding rokets are hybrid type employing a combination of plastics (PMMA or high density polyethylene) and liquid oxygen as propellants. Key points for the miniaturization were using no valve in the liquid oxygen feeding line and omitting precooling treatment of the line. Without precooling treatment, the liquid oxygen in the feeding line becomes multiphase flow until the temperature of the feeding line falls below the boiling temperature of the liquid oxygen. A characteristic time of multiphase flow duration was proposed to evaluate the duration a multiphase flow holds in the feeding line. Static firing tests showed that the multiphase flow ends within the half the characteristic time, showing that the liquid oxygen flow rate history without a precooling treatment is acceptable for an actual operation of the rocket motor. Finally, an impinging type injector was developed to remove a combustion instability, caused by a coupling of the combustion chamber pressure and the propellant (liquid oxygen) feed system., THE JAPANESE SOCIETY FOR MULTIPHASE FLOW, English

大学でできる再使用型ロケット実験(その6)
米本, 浩一, 相良, 慎一, 松本, 剛明, 永田, 晴紀, 越智, 徳昌, 石本, 真二, 麥谷, 高志, 牧野, 隆, 木元, 健一, Yonemoto, Koichi, Sagara, Shinichi, Matsumoto, Takaaki, Nagata, Harunori, Ochi, Yoshimasa, Ishimoto, Shinji, Mugitani, Takashi, Makino, Takashi, Kimoto, Kenichi, 平成24年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium: FY2012, Jan. 2013
平成24年度宇宙輸送シンポジウム (2013年1月17日-1月18日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県
Space Transportation FY2012 (January 17-18, 2013. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan
九州工業大学では、2005年より有翼ロケットによる無人のサブオービタル飛行システムの研究を進めてきた。航法誘導制御システム、推進システム、回収システムや複合材構造設計技術等の個別要素研究を進める一方、それらの技術実証を目的とした小型有翼ロケット実験機を用いた飛行実験を行ってきた。2010年からは、北海道大学、防衛大学大学校およびJAXA宇宙輸送ミッション本部や航空宇宙機メーカー等と連携し、高々度飛行を目指す有翼ロケット実験機の開発を進めている。これまでに行ってきた飛行実験結果を紹介し、サブオービタル飛行を目指す将来計画についても報告する。
形態: カラー図版あり
形態: PDF
Physical characteristics: Original contains color illustrations
Physical characteristics: PDF
Translation title: Experiment of reusable rocket performable in the university (part 5)
資料番号: AA0061856056
レポート番号: STCP-2012-056, 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS), Japanese

推力5000N級CAMUI型ハイブリッドロケットの推進系及び機体構造の開発
五十地, 輝, 前田, 祐義, 橋本, 祐治, 植松, 努, 永田, 晴紀, Isochi, Hikaru, Maeda, Hiroyoshi, Hashimoto, Yuji, Uematsu, Tsutomu, Nagata, Harunori, 平成24年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium: FY2012, Jan. 2013
平成24年度宇宙輸送シンポジウム (2013年1月17日-1月18日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県
Space Transportation FY2012 (January 17-18, 2013. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan
Uematsu Electric Co., Ltd. has been developing CAMUI-type hybrid rockets in collaboration with Hokkaido University. In July 2012 a flight test with a 5000 N thrust class CAMUI-type rocket was conducted. Main objectives of this flight test were technology acquisition concerning supersonic flight, tracking/telemetry and command subsystem, and airframe recovery from sea-water. This paper describes the development outline of the propulsion system and airframe structure of the test vehicle.
形態: カラー図版あり
形態: PDF
Translation title: Development of the propulsion system and airframe structure of 5000 N thrust class CAMUI-type hybrid rocket
Physical characteristics: Original contains color illustrations
Physical characteristics: PDF
資料番号: AA0061856077
レポート番号: STCP-2012-077, 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS), Japanese

無火薬化によるロケット実験のダウンサイジング
永田 晴紀, 日本航空宇宙学会西部支部講演会講演集, 18p, 2013
[日本航空宇宙学会西部支部], Japanese

気球とロケットを組み合わせた揚力飛翔体の極超音速飛行実験の検討
丸 祐介, 澤井 秀次郎, 坂井 真一郎, 坂東 信尚, 小林 弘明, 永田 晴紀, スペースプレーン技術実証機ワーキング・グループ, Maru Yusuke, Sawai Shujiro, Sakai Shinichiro, Bando Nobutaka, Kobayashi Hiroaki, Nagata Harunori, 平成24年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium: FY2012, Jan. 2013
平成24年度宇宙輸送シンポジウム (2013年1月17日-1月18日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県形態: カラー図版あり形態: PDF資料番号: AA0061856060レポート番号: STCP-2012-060, 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS), Japanese

S192021 Air drag coefficient estimation using supersonic flight data of a CAMUI type hybrid rocket.
ISOCHI Hikaru, MAEDA Hiroyoshi, HASHIMOTO Yuji, SEO Yohei, UEMATSU Tsutomu, NAGATA Harunori, The Proceedings of Mechanical Engineering Congress, Japan, 2013, 0, _S192021, 1-_S192021-4, 2013
The authors have been developing CAMUI (Cascaded Multistage Impinging-jet) type hybrid rockets, explosive-flee small rocket motors. This is to downsize the scale of suborbital flight experiments on space related technology development. To demonstrate flight performance of a newly developed 5000 N thrust class motor and accumulate flight data around the sonic speed, a launch test was conducted from a coast to the sea. Test results were successful and all of the fuselage was recovered. To obtain drag coefficient, we used flight data, histories of thrust and propellant flow rates obtained by the static firing test. A typical drag coefficient profile around the sonic speed was obtained., The Japan Society of Mechanical Engineers, Japanese

S192022 Flight Test of Small Winged Rocket Test Vehicle and Its Future Plan
MATSUMOTO Takaaki, YONEMOTO Koichi, SAGARA Shinichi, NAGATA Harunori, OCHI Yoshimasa, ISHIMOTO Shinji, MUGITANI Takashi, The Proceedings of Mechanical Engineering Congress, Japan, 2013, 0, _S192022, 1-_S192022-5, 2013
Since 2005, Kyushu Institute of Technology has been conducting researches on a new unmanned sub-orbital system based on the research and development achievements of reusable sounding rocket called HIMES (Highly Maneuverable Experimental Space vehicle), the concept of which was first proposed by the Institute of Space and Astronautical Sciences of former Ministry of Education in the 1980s, but failed its commercialization. Flight experiments have been performed using small test vehicles of winged rocket in order to demonstrate guidance and control system performance and terminal recovery technologies. A larger winged rocket test vehicle that aims at higher altitude flight demonstration and a sub-orbital prototype vehicle are under design by industry-government-academia collaboration since 2010. This paper introduces the future research and development plan., The Japan Society of Mechanical Engineers, Japanese

EFFECT OF REYNOLDS NUMBER AND FLOW CHANNEL GEOMETRY ON REGRESSION FORMULA FOR FORWARD-END FACES IN CAMUI TYPE FUEL GRAIN
Ryuichiro Kanai, Tatsuya Ishiyama, Masahiro Nohara, Hirokazu Lzumo, Masashi Wakita, Tsuyoshi Totani, Harunori Nagata, SPACE FOR OUR FUTURE, 146, 79, 84, 2013, [Peer-reviewed]
English

2次元流れ場のよどみ点近傍におけるPMMA燃料の後退特性
斉藤竜也, 松岡常吉, 寺川健, 脇田督司, 戸谷剛, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 57th, ROMBUNNO.2A01, 2013
Japanese

環状爆轟波から平面爆轟波への遷移に流路形状が及ぼす影響
菊地敬太, 桧物恒太郎, 脇田督司, 戸谷剛, 永田晴紀, 流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM), 45th-2013, ROMBUNNO.1C05, 2013
Japanese

CAMUI型ハイブリッドロケットの作動履歴におけるスケール則の構築
稲場康彦, 石山達也, 金井竜一朗, 脇田督司, 戸谷剛, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 57th, ROMBUNNO.2A03, 2013
Japanese

表面微細構造を持つ波長選択性ラジエータ
戸谷剛, 脇田督司, 永田晴紀, 日本伝熱シンポジウム講演論文集(CD-ROM), 50th, ROMBUNNO.G123, 2013
Japanese

超小型衛星の熱設計手順の提案
戸谷剛, DAS Tilok Kumar, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 57th, ROMBUNNO.3H15, 2013
Japanese

高レイノルズ数域におけるCAMUI型固体燃料の後退特性におよぼすスケールの影響
石山達也, 稲場康彦, 寺川健, 遠藤瞳, 永田晴紀, 戸谷剛, 脇田督司, 宇宙科学技術連合講演会講演集(CD-ROM), 57th, ROMBUNNO.2A02, 2013
Japanese

構造転移する蓄熱材の蓄熱量
戸谷剛, 國拓也, 佐藤敏文, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 57th, ROMBUNNO.2I03, 2013
Japanese

S192023 Thermal Design Guide for Micro and Nano Satellite developed for Short Period
TOTANI Tsuyoshi, DAS Kumar Tilok, WAKITA Masashi, NAGATA Harunori, The Proceedings of Mechanical Engineering Congress, Japan, 2013, 0, _S192023, 1-_S192023-5, 2013
A guide for the thermal design of micro and nano satellites is proposed in order to complete the thermal design of micro and nano satellites for about 1 year. Two concepts of thermal design are considered to keep the temperature change of components within the design temperature range of components. One concept is to decrease the temperature change using the whole heat storage of the micro and nano satellite. The other is to decrease the temperature change of the inner structure where the components with the narrow design temperature range are mounted. The temperature of micro and nano satellites designed in the former concept is calculated using one-nodal analysis method. The temperature of micro and nano satellites designed in the latter concept is calculated using twonodal analysis method. The combinations of optical properties on structures and components to keep the temperature within the design temperature range of components are clarified using one- or two-nodal analysis. Then, the multinodal analyses are carried out to be designed in detail based on the optical properties clarified from the one-nodal analysis and two-nodal analysis. This guide of thermal design is applied to Hodoyoshi-1 satellite. Hodoyoshi-1 satellite is the micro satellite that is about 50 cm in width, 50 cm in depth, 50 cm in height, is about 50 kg in mass, has two inner plates, has solar cells on the body, flies on the sun-synchronous orbit of the 500 km of altitude and is pointing to the Earth. The thermal design of Hodoyoshi-1 satellite has been completed for about ten months. The validity of this procedure is confirmed and the problems of this procedure are clarified., The Japan Society of Mechanical Engineers, Japanese

結晶転移する蓄熱材の蓄熱特性
戸谷剛, 佐藤敏文, 脇田督司, 永田晴紀, 日本伝熱シンポジウム講演論文集(CD-ROM), 50th, ROMBUNNO.F131, 2013
Japanese

EMISSIVITY OF WAVELENGTH-SELECTIVE RADIATOR WITH PERIODIC MICROCAVITIES
Tsuyoshi Totani, Minoru Iwata, Masashi Wakita, Harunori Nagata, PROCEEDINGS OF THE 11TH INTERNATIONAL CONFERENCE ON NANOCHANNELS, MICROCHANNELS, AND MINICHANNELS, 2013, 2013, [Peer-reviewed]
English

Effect of reynolds number and flow channel geometry on fuel regression characteristics in camui type hybrid rocket
H. Nagata, M. Nohara, R. Kanai, M. Wakita, T. Totani, Proceedings of the International Astronautical Congress, IAC, 10, 8049, 8055, 01 Dec. 2012

円筒デトネーション波の遷移及び伝播条件に関する研究
棧敷和弥, 桧物恒太郎, 脇田督司, 戸谷剛, 永田晴紀, 燃焼シンポジウム講演論文集, 50th, 306, 307, 20 Nov. 2012
Japanese

一定レイノルズ数のよどみ点近傍における固体燃料の燃焼速度におよぼす酸化剤流速の影響
寺川健, 永田晴紀, 戸谷剛, 脇田督司, 金子雄大, 燃焼シンポジウム講演論文集, 50th, 82, 83, 20 Nov. 2012
Japanese

相似形状のCAMUI型ハイブリッドロケットの燃焼特性におけるスケール効果
永田晴紀, 脇田督司, 戸谷剛, 植松努, 燃焼シンポジウム講演論文集, 50th, 78, 79, 20 Nov. 2012
Japanese

表面微細周期構造を用いた波長選択性ラジエータ
戸谷剛, 脇田督司, 永田晴紀, 日本機械学会熱工学コンファレンス講演論文集, 2012, 505, 506, 16 Nov. 2012
A periodic micro structure of the cubic cavity of 6.0 μm x 6.0μm x 6.0μm is built on an ultra violet curable resin by the UV nanoimprint method. A gold film is sputtered on the periodic micro structure. The maximum normal emissivity of the periodic micro structure is 0.6 near 10 μm in the case of the gold film of 200 nm thick on the surface facing the gold source in a sputtering equipment. The resonance wavelength measured in experiments is shorter than that calculated from theory. It may be caused that a part of the bottom of the micro structure is shallower than 6.0 μm and the opening shape is rounded off., The Japan Society of Mechanical Engineers, Japanese

Scale modeling on flame shape spreading inside fuel tube　　　　　　　　　　　　　　　
Tsuenyoshi Matsuoka, Harunori Nagata, Yuji Nakamura, ISEM-ACEM-SEM-7th ISEM’12-Taipei (The 7th ISEM’ 12-Taipei), Nov. 2012, [Peer-reviewed]
English

Optical properties of wavelength-selective radiator with periodic microcavities　　　　　　　　　　　　　　　
Tsuyoshi Totani, Naoyuki Ishikawa, Minoru Iwata, Masashi Wakita, Harunori Nagata, Proceedings of the 3rd International Forum on Heat Transfer (CD-ROM), IFHT2012-101, Nov. 2012, [Peer-reviewed]
English

Cylindrical exploding detonation wave propagating in large-bore plate combustor
SAJIKI KAZUYA, TERASAKA AKIHIRO, WAKITA MASASHI, TOTANI TSUYOSHI, NAGATA HARUNORI, 宇宙航空研究開発機構特別資料 JAXA−SP−, JAXA-SP-11-015, 11-015, 27-32, 32, 30 Mar. 2012
第43回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2011 (2011年7月7日-8日. 早稲田大学国際会議場) 東京
43rd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2011 (July 7-8, 2011. Waseda University, International Conference Center), Tokyo Japan
Detonation initiation is one of the important problems of pulse detonation engines. A reflector installed near a predetonator exit is effective to maintain detonation waves. The incident detonation wave from the predetonator transforms its shape from planer to cylindrical and cylindrical to toroidal around the reflector. To prevent the detonation wave downstream of reflector from disappearing, it is important to form a cylindncal detonation wave upstream of the reflector. In this paper, the authors used a large-bore plate combustor and varied the following parameters to find the necessary condition to form a cylindrical detonation wave: the quantity of the driver gas and time from the ball valve opening to the ignition. To evaluate the quantity of the driver gas, an overfilling distance is used. The overfilling distance is the radius of the 10 mm high cylinder whose volume is equivalent to the total amount of the driver gas used in the experiment. Results indicate that the mixing between the driver and target gases affects the ability of successful transition. When a cylindrical detonation wave is formed, an annular soot track structure appears in the vicinity of the predetonator exit. This structure and velocity of detonation waves show that the transformation of the incident detonation wave into the cylindrical detonation wave resuls from the twice reflection from the plates of the combustor. To form a cylindrical detonation Wave, the driver gas should fill the volume much larger than the annular structure area.
形態: カラー図版あり
Physical characteristics: Original contains color illustrations
資料番号: AA0065207005
レポート番号: JAXA-SP-11-015, 宇宙航空研究開発機構, Japanese

CAMUIロケット開発者 : 火薬を使わないロケットの開発
永田 晴紀, 妹尾 俊明, 三宅 龍馬, 日本機械学會誌 = Journal of the Society of Mechanical Engineers, 115, 1120, 170, 173, 05 Mar. 2012
一般社団法人日本機械学会, Japanese

Development Plan of Hybrid Rocket Test Engine Facility in Hybrid Rocket Research Working Group
KITAGAWA Koki, SHIMADA Toru, HORI Keiichi, TAKEMAE Toshiaki, SHIRAISHI Noriko, TOMIZAWA Toshio, SUZUKI Naohiro, YAGISHITA Tsuyoshi, OSHIMA Nobuyuki, NAGATA Harunori, WAKITA Masashi, SAWADA Keisuke, NAGAI Hiroki, WADA Yutaka, YUASA Saburo, SAKURAI Takashi, KANAZAKI Masahiro, NAKAGAWA Ichiro, MORITA Takakazu, NAKAMIYA Masaki, ASO Shigeru, TANI Yasuhiro, TSUBOI Nobuyuki, Proceedings. International Conference on Flow Dynamics (CD-ROM), 9th, 2012

CAMUI型ハイブリッドロケットにおける異常燃焼の克服
永田晴紀, 2, 1, 1, 11, 2012

S192013 Thermal design of the micro-satellite "HODOYOSHI-1"
OGAWA Hiroto, INOUE Ryota, TOTANI Tsuyoshi, WAKITA Masashi, NAGATA Harunori, The Proceedings of Mechanical Engineering Congress, Japan, 2012, 0, _S192013, 1-_S192013-5, 2012
"HODOYOSHI-1" is the a micro satellite which is about 60 cm cube and about 60 kg. This satellite is scheduled to be launch at the end of 2012 into a sun-synchronous orbit of the altitude 500 to 600 km for optical remote sensing mission. Using Fortran and thermal analysis software "Thermal Desktop", thermal design has been performed for this satellite. One-nodal analysis and two-nodal analysis are performed using Fortran programs and multi-nodal analysis is carried out by Thermal Desktop for thermal design. One and two-nodal analysis decide optical properties of each surface and thermal conductivity between inside structure and outside structure. As a result, optic properties are decided that the outer surface of outside structure is alodine 1000, and the inner surface of outside structure and the surface of inside structure are black anodized. These analyses decide that GFRP is inserted between the outside structure and the inside structure, and thermal conductive sheet "DENKA BFG20" is inserted between each component and the surface mounted on it. Thermal Desktop calculates temperatures of components on HODOYOSHI-1. Optical property of-X panel is modified from alodine 1000 to white anodized. GFRP is inserted between the battery and the surface mounted on it. The result of these analyses shows that the temperatures of components are within the allowable temperature range. The thermal design of HODOYOSHI-1 have completed for 10 month. This thermal design is useful for the micro and nano satellites producing at a low cost and a short duration., The Japan Society of Mechanical Engineers, Japanese

S192023 Downsizing and flight demonstration of CAMUI type hybrid rocket system
ISHIYAMA Tatsuya, TOTANI Tsuyoshi, NAGATA Harunori, INABA Yasuhiko, INOUE Ryota, SASAKI Shunya, TERAKAWA Ken, HIMONO Tsunetaro, Lee Sang Jun, KANAI Ryuichiro, WAKITA Masashi, The Proceedings of Mechanical Engineering Congress, Japan, 2012, 0, _S192023, 1-_S192023-5, 2012
Although many groups are developing Cansat, a can-sized mock satellite, they have few opportunities to test due to difficulties for students to launch Cansats domestically. To provide the chance to launch Cansats, the authors downsized CAMUI type hybrid rocket and created easy-to-use launch system. The new launcher, miniCAMUI, uses gas oxygen (GOX) as oxidizer and high density polyethylene as fuel. Using GOX instead of liquid oxygen contributes to downsizing and weight saving, reduction of turnaround time for launch due to the simplified procedure to fill the oxidizer. A GOX tank connects to a motor through a valve. An air-driven actuator operates the valve miniCAMUI was launched 6 times in June and July 2012. Three of them were serial successful launches with two rockets in a day, with a turnaround time about 45 minutes. Two of the three launches were with the same rocket in the day. With the wind velocity of 1 to 2 m/s, the apogee altitude was about 74 m, being very close to the predetermined altitude of 80 m. This result shows that miniCAMUI was successfully developed as a small launch system with high operability. miniCAMUI is available for launches to various altitudes below 250 m., The Japan Society of Mechanical Engineers, Japanese

S192022 Ignition Characteristics of CAMUI-type Solid Fuel Grain Cooled to Liquid Oxygen Temperature
KANAI Ryuichiro, TERAKAWA Ken, INABA Yasuhiko, ISHIYAMA Tatsuya, SASAKI Shunya, WAKITA Masashi, TOTANI Tsuyoshi, NAGATA Harunori, The Proceedings of Mechanical Engineering Congress, Japan, 2012, 0, _S192022, 1-_S192022-4, 2012
During development of a large size CAMUI-type hybrid rocket motor in 2006, anomalous combustion associated with large pressure spike frequently occurred. After troubleshooting, low temperature of the fuel was found to have caused anomalous combustion. Because a cryogenic liquid oxygen tank is around the motor, polyethylene fuel grain is cooled to liquid oxygen temperature. The anomalous combustion was duplicated with a downsized motor. The size of the fuel grain was 2/5 of large size motor. Because Damkohler number is proportional to the ratio of pressure and oxygen mass flux, the ratio for the subscale motor was conformed to that for the full-scale motor. In a reproductive experiment, pressure spike also appeared. This result suggests that blow-off occurs before the pressure spike. After the blow-off, gas mixture in the chamber may ignite to cause the pressure spike., The Japan Society of Mechanical Engineers, Japanese

S192011 Thermal Analyses and Thermal Design of Nano and Micro Satellites on Sun-synchronous Orbits
INOUE Ryota, OGAWA Hiroto, TOTANI Tsuyoshi, WAKITA Masashi, NAGATA Harunori, The Proceedings of Mechanical Engineering Congress, Japan, 2012, 0, _S192011, 1-_S192011-5, 2012
This paper presents a thermal design method of nano and micro satellites by one-nodal and two-nodal thermal analyses. The orbit is the sun-synchronous and circular orbit at an altitude of 500 km and at the local time at descending node of 11 o'clock. The attitude is pointing to the Earth. The combinations of optical properties, solar absorptivity and infrared emissivity, on surfaces of Inner Structure and Outer Structure under which the temperature of a satellite is within an allowable temperature range are clarified. The results show a correspondence relation between analytical methods and forms of heat transfer (heat conduction or radiation) between Inner Structure and Outer Structure. A thermal design in which there is little difference between analytical value and experimental value is realized by setting appropriate thermal control products on the contact faces between Inner Structure and Outer Structure. The combinations of optical properties are larger in the design focusing on radiation than in that focusing on heat conduction. A configuration of Inner Structure influences the combination. Finally, thermal design method by the one-nodal and two-nodal analyses which allows one to develop a satellite in short period at low cost is proposed., The Japan Society of Mechanical Engineers, Japanese

短期開発を実現する少節点解析と多節点解析を併用した超小型衛星の熱設計法
小川洋人, 井上遼太, 戸谷剛, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD−ROM), 56th, ROMBUNNO.2M07, 2012
Japanese

金属膜を付与した表面微細周期構造の垂直放射率特性
戸谷剛, 石川直幸, 脇田督司, 永田晴紀, 日本伝熱シンポジウム講演論文集(CD−ROM), 49th, ROMBUNNO.D125, 2012
Japanese

CAMUI型燃料グレインの熱伝達特性に及ばす流路形状とレイノルズ数の影響
佐々木俊也, 大島伸行, 永田晴紀, 脇田督司, 宇宙科学技術連合講演会講演集(CD−ROM), 56th, ROMBUNNO.3H01, 2012
Japanese

大口径パルスデトネーションエンジン用イニシエータにおける円筒デトネーション波の伝播に関する研究
桧物恒太郎, 棧敷和弥, 脇田督司, 戸谷剛, 永田晴紀, 流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD−ROM), 44th-2012, ROMBUNNO.1E05, 2012
Japanese

パネルディスカッション:ハイブリッドロケット研究開発の今後を語ろう
嶋田徹, 北川幸樹, 湯浅三郎, 那賀川一郎, 永田晴紀, 福地亜宝郎, 和田豊, 宇宙科学技術連合講演会講演集(CD-ROM), 56th, ROMBUNNO.3H13, 2012
Japanese

構造転移により蓄熱する超小型衛星用蓄熱材の開発
戸谷剛, 佐藤敏文, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 56th, ROMBUNNO.1N05, 2012
Japanese

推力5000N級CAMUI型ハイブリッドロケットの開発と打上げ実証
永田晴紀, 脇田督司, 戸谷剛, 植松努, 安本裕紀, 三橋龍一, 宇宙科学技術連合講演会講演集(CD−ROM), 56th, ROMBUNNO.3H04, 2012
Japanese

産官学連携による準軌道型再使用宇宙輸送システム開発の提案
米本浩一, 相良慎一, 松本剛明, 永田晴紀, 越智徳昌, 石本真二, 麥谷高志, 牧野隆, 木元順一, 日本航空宇宙学会年会講演会講演集(CD−ROM), 43rd, ROMBUNNO.B08, 2012
Japanese

Thermal Analyses of Nano and Micro Satellites on Sun-synchronous Orbit by One Nodal Analysis Method　　　　　　　　　　　　　　　
Tsuyoshi Totani, Hiroto Ogawa, Ryota Inoue, Masashi Wakita, Harunori Nagata, The proceedings of 1st International Conference on Mechanical Engineering and Renewable Energy, ICMERE2011-PI-148, Dec. 2011, [Peer-reviewed]
English

Optimal fuel grain design method for CAMUI type hybrid rocket
Harunori Nagata, Shunsuke Hagiwara, Nasashi Wakita, Tsuyoshi Totani, Tsutomu Uematsu, 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011, 01 Dec. 2011

表面微細周期構造を用いた波長選択性ラジエータ
石川直幸, 戸谷剛, 脇田督司, 永田晴紀, Thermophys Prop, 32nd, 307, 309, 21 Nov. 2011
Japanese

大口径大推力パルスデトネーションエンジン用イニシエータにおける円筒デトネーション波の伝播に関する研究
寺坂昭宏, 桟敷和弥, 脇田督司, 戸谷剛, 永田晴紀, 燃焼シンポジウム講演論文集, 49th, 328, 329, 20 Nov. 2011
Japanese

吹き飛び限界以下のダムケラー数で燃え拡がる火炎の保持機構
松岡常吉, 村上翔太, 中村祐二, 永田晴紀, 燃焼シンポジウム講演論文集, 49th, 258, 259, 20 Nov. 2011
Japanese

酸化剤噴流淀み点近傍におけるポリエチレン燃料の後退特性
永田晴紀, 金子雄大, 脇田督司, 戸谷剛, 燃焼シンポジウム講演論文集, 49th, 248, 249, 20 Nov. 2011
Japanese

E135 Numerical Prediction of Flame Spreading Rate in a PMMA Duct
Matsuoka Tsuneyoshi, Murakami Shouta, Nagata Harunori, Nakamura Yuji, Procee[d]ings of Thermal Engineering Conference, 2011, 125, 126, 28 Oct. 2011
We studied numerically the flame spreading phenomena in a narrow circular duct made by PMMA in order to capture the time-depended transport processes during the event. The main aim of this study is to clarify the stability mechanism near the extinction limit (i.e. low Damkohler number limit) which is one of unique feature in this system, which might be different from the conventional flat-plate flame spreading as suggested in our previous works. Numerical model includes time-dependent mass and heat transfer with one-step finite rate of chemical reactions both in gas and solid phase. In this study, it is successfully simulated the nearly steady flame movement under the condition studied. Moreover, it is accomplished to reproduce the two distinctive spreading modes, such as the one belongs in thermal regime and chemical regime, which have already been observed experimentally. Although there is quantitative disagreement between experimental and numerical results, it is confirmed that our numerical model should be satisfactory to capture the qualitative behavior of flame spreading in the narrow duct., The Japan Society of Mechanical Engineers, Japanese

9-105 Coordination between upper secondary schools and university in School of Engineering Hokkaido University
NAGATA Harunori, SUGAWARA Hirotake, NISHIGUCHI Norihiko, Proceedings of Annual Conference of Japanese Society for Engineering Education, 23, 59, 182, 183, 22 Aug. 2011
Japanese Society for Engineering Education, Japanese

無火薬式小型ロケットによる宇宙工学研究のダウンサイジング
永田晴紀, 化学工学会大会講演要旨集(CD-ROM), 2011, ROMBUNNO.E122, 25 Jul. 2011
Japanese

微小重力環境を利用した固体燃焼現象研究(H22研究班WG報告)
藤田修, 中村祐二, 永田晴紀, 菊池政雄, 伊藤昭彦, 鳥飼宏之, 梅村章, 高橋周平, 池田光優, CHUNG Suk Ho, OLSON Sandra L, 宇宙利用シンポジウム, 27th, 31, 32, Mar. 2011
第27回宇宙利用シンポジウム (2011年1月24日-25日, 宇宙航空研究開発機構宇宙科学研究所相模原キャンパス), 相模原市, 神奈川県
The Twenty-seventh Space Utilization Symposium (January 24-25, 2011. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan
Since solid combustion is dominated by diffusion process of pyrolyzed gas as well as heat transfer process around the combustion region, flammability limit becomes very different depending on the gravitational conditions. In the present work, an attempt to know the mechanism of the extension of ignition limit of overloaded wire has been made by numerical calculation. The results showed that the Joule energy more than a critical value causes release of degradation gas and its ignition, and the critical value becomes smaller in microgravity than that in normal gravity. Further, the preparation status of the ISS experiment including the wire ignition and flame spread over solid material is introduced.
著者人数: 11人
形態: カラー図版あり
Number of authors: 11
Physical characteristics: Original contains color illustrations
資料番号: AA0065129013, 宇宙航空研究開発機構宇宙科学研究所 (JAXA)(ISAS), Japanese

急性肝機能障害を来した24歳女性
本城晴紀, 永田紘子, 渡邉直昭, 野内俊彦, 日本内科学会関東支部関東地方会, 582nd, 2011

大口径平板燃焼器を伝播する円筒デトネーション波に関する研究
棧敷和弥, 寺坂昭宏, 脇田督司, 戸谷剛, 永田晴紀, 流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM), 43rd-2011, ROMBUNNO.1B03, 2011
Japanese

金属膜を持つ表面微細周期構造の分光特性
石川直幸, 戸谷剛, 脇田督司, 永田晴紀, 日本伝熱シンポジウム講演論文集(CD-ROM), 48th, ROMBUNNO.H312, 2011
Japanese

CAMUIロケットを利用したエジェクタ・ジェット試験の数値解析
長谷川進, 谷香一郎, 平岩徹夫, 植田修一, 永田晴紀, 流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM), 43rd-2011, ROMBUNNO.2D02, 2011
Japanese

推力900N級CAMUI型ハイブリッドロケットによる打上げ・海上回収実験
永田晴紀, 前田祐義, 鈴木恭兵, 五十地輝, 安中俊彦, 稲石卓也, 清尾陽平, 植松努, 宇宙科学技術連合講演会講演集(CD-ROM), 55th, ROMBUNNO.3B10, 2011
Japanese

超小型衛星の熱設計と熱制御材
戸谷剛, 小川洋人, 井上遼太, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 55th, ROMBUNNO.2G16, 2011
Japanese

太陽同期軌道を周回する超小型衛星の熱設計
井上遼太, 小川洋人, 戸谷剛, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD-ROM), 55th, ROMBUNNO.3S12, 2011
Japanese

S192013 Derivation Method of Fuel Regression Formulas for CAMUI Type Hybrid Rocket
NOHARA Masahiro, IZUMO Hirokazu, WAKITA Masashi, TOTANI Tsuyoshi, NAGATA Harunori, The Proceedings of Mechanical Engineering Congress, Japan, 2011, 0, _S192013, 1-_S192013-5, 2011
Regression formulas for solid fuels in CAMUI type hybrid rockets were developed. A fuel grain in this rocket consists of multiple stages of cylindrical fuel blocks with two ports. A Fuel block in a CAMUI type grain has three burning surface, i.e., the upstream end face, port inner walls, and the downstream end face. A series of static firing tests by laboratory model motor and 2500 N thrust class flight model motor gave empirical constants in the regression formulas. There regression formulas are used to obtain an optimal design of a grain configuration. However, the empirical constants provided by these two series of firing tests did not agree with each other. To investigate the cause of this disagreement, additional static firing tests by 2500 N thrust class flight model motor was conducted. Results show that the empirical constants depend on Re number. In contrast, the dependence was not observed in the firing tests by the laboratory model motor. This difference may be caused by the difference in L/D (the ratio of the length of the port and the diameter of port)., The Japan Society of Mechanical Engineers, Japanese

S192022 Thermal design of micro-satellites and nano-satellites on sun-synchronous orbits
OGAWA Hiroto, INOUE Ryota, TOTANI Tsuyoshi, WAKITA Masashi, NAGATA Harunori, The Proceedings of Mechanical Engineering Congress, Japan, 2011, 0, _S192022, 1-_S192022-5, 2011
The thermal analyses of micro and nano satellites on sun-synchronous orbits are performed by using one nodal analysis. Three models of the satellites are considered. The size and mass of model A, B, C are respectively 0.1 m cube and 1 kg, 0.25 m cube and 25 kg, 0.5 m cube and 50 kg. The analyses are carried out under the conditions of the altitude of 300, 500, 700, and 1 000 km, and the local time of descending node (LTDN) from 6 to 12. The combinations of solar absorptivity and infrared emissivity in the case that the temperature of the satellite is within the allowable temperature range (273.15-313.15 K) increase with the larger parameter of the mass times the heat capacity over one area on surface of satellite. The combinations increase with the higher altitudes and decrease with larger LTDN. The combinations in the case of the orbits without an eclipse are larger than with an eclipse. These results are useful for the preliminary thermal design of micro and nano satellites., The Japan Society of Mechanical Engineers, Japanese

Automatic Control on Circulation of Working Fluid in Liquid Droplet Radiator
Tsuyoshi Totani, Takuhiro Takekoshi, Masashi Wakita, Harunori Nagata, Proceedings of the 13th Asian Congress of Fluid Mechanics, 10, 28, 586, 589, Dec. 2010, [Peer-reviewed]
Liquid Droplet Radiator (LDR) is an important candidate for disposing large quantities of waste heat more than 1 MW which will be handled by large space structures such as Space Power Satellite. The working fluid is heated through a heat exchanger by the waste heat generated in a large structure in space. Then, the working fluid is emitted in space through nozzles of the droplet generator toward a droplet collector as multiple streams of droplets. During the flight in space, the droplets lose thermal energy via radiative heat transfer. After the cooled droplets are captured by the droplet collector, the working fluid is recycled to the heat exchanger by a circulating pump. The automatic control system on the circulation of working fluid in a liquid droplet radiator has been built using a programmable logic controller. The proportional control of flow rate with the term of the variation of the counter flow in the gear pump and the relaxation of the change of an target flow rate has succeeded within 5 percent at the automatic circulation control of the working fluid from 100 ml/min to 200 ml/min and from 200 ml/min to 100 ml/min., THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, English

Micro flame spreading in solid fuel ducts
Tsuneyoshi Matsuoka, Harunori Nagata, 61st International Astronautical Congress 2010, IAC 2010, 4, 2863, 2869, 01 Dec. 2010

Effect of jet velocity on scale effect in oxidizer impinging region
Yudai Kaneko, Mitsunori Itoh, Massasi Wakita, Tsuyoshi Totani, Harunori Nagata, Advances in the Astronautical Sciences, 138, 629, 634, 01 Dec. 2010

Regression progress of fuel grain in CAMUI type hybrid rocket motor
Harunori Nagata, Akihito Kakikura, Mitsunori Ito, Yudai Kaneko, Kazuhiro Mori, Kenta Ueshima, Tsutomu Uematsu, Tsuyoshi Totani, Advances in the Astronautical Sciences, 138, 611, 616, 01 Dec. 2010

Development of 2500 N class CAMUI type hybrid rocket for winged flight experiments
H. Nagata, M. Wakita, T. Totani, T. Uematsu, K. Yonemoto, 61st International Astronautical Congress 2010, IAC 2010, 3, 2144, 2148, 01 Dec. 2010

流路幅とセルサイズが円環デトネーション波から平面デトネーション波への遷移過程に与える影響
田村正佳, 寺坂昭宏, 脇田督司, 戸谷剛, 永田晴紀, 燃焼シンポジウム講演論文集, 48th, 486-487, 20 Nov. 2010
Japanese

亜酸化窒素の触媒分解反応を用いたハイブリッドロケット用点火器の開発
榎本剛矩, 永田晴紀, 戸谷剛, 脇田督司, 徳留真一郎, 燃焼シンポジウム講演論文集, 48th, 542-543, 20 Nov. 2010
Japanese

512 Spectroscopic Characteristics of Resinous Microstructure Surface
ISHIKAWA Naoyuki, TOTANI Tsuyoshi, NAGATA Harunori, WAKITA Masashi, The Proceedings of Conference of Hokkaido Branch, 2010, 49, 133, 134, 07 Nov. 2010
The Japan Society of Mechanical Engineers, Japanese

612 Optimum design CAMUI type fuel grain shape using genetic algorithm
NOHARA Masahiro, KANEKO Yudai, HAGIWARA Shunsuke, WAKITA Masashi, TOTANI Tuyoshi, NAGATA Harunori, The Proceedings of Conference of Hokkaido Branch, 2010, 49, 161, 162, 07 Nov. 2010
The Japan Society of Mechanical Engineers, Japanese

613 Effect of channel width on toroidal detonation wave propagating through expanding annular channel
TERASAKA Akihiro, TAMURA Masayoshi, WAKITA Masashi, TOTANI Tsuyoshi, NAGATA Harunori, The Proceedings of Conference of Hokkaido Branch, 2010, 49, 163, 164, 07 Nov. 2010
The Japan Society of Mechanical Engineers, Japanese

115 Robustness Enhancement of Space Engineering R&D Projects by Explosive-free Small Rockets
NAGATA Harunori, 学術講演会講演論文集, 59, 0, 219, 220, 21 May 2010
The Society of Materials Science, Japan, Japanese

微小重力環境を利用した固体燃焼現象研究 (H21研究班WG報告)—Solid Combustion Research in Microgravity（2009 Research WG Report
藤田, 修, 中村, 祐二, 永田, 晴紀, 菊池, 政雄, 伊藤, 昭彦, 鳥飼, 宏之, 梅村, 章, 高橋, 周平, 池田, 光優, Fujita, Osamu, Nakamura, Yuji, Nagata, Harunori, Kikuchi, Masao, Ito, Akihiko, Torikai, Hiroyuki, Umemura, Akira, Takahashi, Shuhei, Ikeda, Mitsumasa, Chung, Suk Ho, 宇宙利用シンポジウム = Space Utilization Research: Proceedings of Space Utilization Symposium, 26, 137, 138, Feb. 2010
第26回宇宙利用シンポジウム(2010年1月25日-26日, 宇宙航空研究開発機構宇宙科学研究本部相模原キャンパス)
The Twenty-sixth Space Utilization Symposium (January 25-26, 2010: ISAS/JAXA Sagamihara, Japan)
Since solid combustion is dominated by diffusion process of pyrolyzed gas as well as heat balance around combustion area, flammability limit becomes very different depending on the gravitational conditions. In the present work, the attempt to obtain ignition limit for overloaded electric wire and extinction limits for spreading flame over flat sheet has been made under the limit of 4.5 sec microgravity time provided by MGLAB. According to the experiments, it is found that the flammable limits, ignition and extinction limits, significantly extend in microgravity in comparison with those in normal gravity.
形態: カラー図版あり
共催: 日本学術会議
Physical characteristics: Original contains color illustrations
joint hosting: The Science Council of Japan
資料番号: AA0064730020, 宇宙航空研究開発機構宇宙科学研究本部, Japanese

CAMUI型ハイブリッドロケット燃料の後退速度に及ぼす圧力の影響
永田晴紀, 金子雄大, 萩原俊輔, 伊藤光紀, 脇田督司, 戸谷剛, 植松努, 宇宙科学技術連合講演会講演集(CD−ROM), 54th, ROMBUNNO.2B15, 2010
Japanese

紫外線硬化樹脂に形成された表面微細周期構造の透過率特性
戸谷剛, 石川直幸, 脇田督司, 永田晴紀, 日本伝熱シンポジウム講演論文集(CD−ROM), 47th, ROMBUNNO.C321, 285, 2010
UVナノインプリント法によって作成された表面微細周期構造の太陽光吸収率と全半球赤外線放射率について報告する。表面微細周期構造の周期は、1 マイクロメートルと10 マイクロメートルである。, The Heat Transfer Society of Japan, Japanese

超小型宇宙探査機「しんえん(UNITEC‐1)」の熱設計と通信途絶原因の一考察
戸谷剛, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD−ROM), 54th, ROMBUNNO.2C01, 2010
Japanese

流路幅と流路傾斜角が円環デトネーション波の伝播に与える影響
寺坂昭宏, 田村正佳, 脇田督司, 戸谷剛, 永田晴紀, 流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD−ROM), 42nd-2010, ROMBUNNO.1B2, 2010
Japanese

液滴ラジエータの作動流体循環における自動制御可能範囲の拡大
竹腰卓博, 戸谷剛, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD−ROM), 54th, ROMBUNNO.1K08, 2010
Japanese

S1901-1-1 Thermal Design and Temperature on Orbit of Micro Spacecraft UNITEC-1
TOTANI Tsuyoshi, WAKITA Masashi, NAGATA Harunori, UNITEC-I Developing Team, The proceedings of the JSME annual meeting, 2010, 0, 359, 360, 2010
UNITEC-1 (UNIsec Technology Experiment Carrier-1) is an interplanetary probe that is developed by 22 universities in UNISEC (University Space Engineering Consortium). The dimensions and weight of UNITEC-1 are about 35cm×35cm×40cm and 22kg, respectively. UNITEC-1 was launched by H-IIA rocket on May 21, 2010 as a piggyback payload of Planet-C (Akatsuki) Venus probe developed by JAXA/ISAS. It is expected that the temperature of UNITEC-1 in the worst hot condition near Earth is 40.6 degree Celsius at the battery. UNITEC-1 will pass outside the orbital path of Earth partly in our expecting orbit and will become the lowest temperature. The temperature of UNITEC-1 in the worst cold condition at the furthest point from the sun will be 3.8 degree Celsius. The temperature of UNITEC-1 in the worst hot condition near Venus will be 84.8 degree Celsius., The Japan Society of Mechanical Engineers, Japanese

S1901-1-2 Development and Operation of Small-Scale CAMUI Hybrid Rocket
TAKEKOSHI Takahiro, SATO Syunya, TAMURA Masayoshi, HAGIHARA Syunsuke, WAKITA Masashi, TOTANI Tsuyoshi, NAGATA Harunori, UEMATSU Tsutomu, The proceedings of the JSME annual meeting, 2010, 0, 361, 362, 2010
The authors developed a 1.3-m-long small scale CAMUI hybrid rocket of 4.7 kg in total weight to obtain an easy test launch system for CanSat. Two test launches without CanSat made altitude less than 250 m. Launches below 250 m is not regulated by the Civil Aeronautics Act in Japan. The avionics system loaded in the rocket consisted of a microcomputer, acceleration sensor, angular velocity sensor and altitude sensor. The avionics system can do wireless communication using the Bluetooth technology, real-time onboard data were obtained during the test flights successfully., The Japan Society of Mechanical Engineers, Japanese

S1901-1-5 Improvement of Method to Obtain Regression Formulae of CAMUI Type Fuel Grain
HAGIHARA Shunsuke, KANEKO Yudai, NOHARA Masahiro, NAGATA Harunori, TOTANI Tuyoshi, WAKITA Masashi, MATUOKA Tuneyoshi, UEJIMA Kenta, UEMATU Tutomu, The proceedings of the JSME annual meeting, 2010, 0, 367, 368, 2010
The authors have been developing CAMUI type hybrid rockets which have a new fuel grain design to accelerate burning rate. Regression formulae for CAMUI type rockets have been developed as functions of local O/F. The authors carried out combustion tests with various oxidizer flow rate and burning duration to obtain empirical constants of these regression formulae. Additionally, a simulation model of static firing was built using the fuel regression formulae. In these studies, regression rates were mean values during firing. This paper discusses the effect of firing duration on the accuracy of regression formulae by using the simulation model., The Japan Society of Mechanical Engineers, Japanese

S1901-2-5 Flight Tests of Small Scaled Winged Rocket Using Hybrid Rocket
YONEMOTO Koichi, NAGATA Harunori, WATANABE Daichi, The proceedings of the JSME annual meeting, 2010, 0, 379, 380, 2010
The Space Systems Laboratory of Kyushu Institute of Technology has been studying unmanned suborbital winged rocket as a research subject of future fully reusable space transportation system since 2005. The flight tests of a small scaled winged rocket were conducted five times from 2008 to 2009. A larger winged rocket with a hybrid rocket developed by Hokkaido University, which will reach to a higher altitude, is under development for validating INS/GPS hybrid navigation system, real time trajectory generation and guidance algorithm using GA implemented on FPGA, H_∞ and adaption control theory. This paper reports current design, development and flight test plan of the winged rocket., The Japan Society of Mechanical Engineers, Japanese

G1900-1-3 Effect of heat transfer in supersonic region of Laval nozzle on thrust and specific impulse
IWAKI Yuki, TOATNI Tsuyoshi, WAKITA Masashi, NAGATA Harunori, The proceedings of the JSME annual meeting, 2010, 0, 407, 408, 2010
The variation of the thrust and the specific impulse was revealed numerically with calculating the change of the exhaust velocity. Both cooling and heating the propellant flowing in the divergent section of Laval nozzle were treated. The expansion ratio were 30, 600, and 2000. The specific heat ratio was 1.3. Two types of heat profile were considered; pulsed heat transfer (PHT) and distributed heat transfer (DHT). The relations of Rayleigh flow and isentropic change were used for PHT. The exhaust velocity is higher than the isentropic value in the case that the heat is provided near the throat. In other cases, the exhaust veolocity is less than the isentropic case. The equivalent point of heat transfer is introduced for DHT. Results of DHT is coincident with PHT by using this equivalent point. This results indicates that the effect with DHT can be predicted from PHT., The Japan Society of Mechanical Engineers, Japanese

Combustion characteristics of the end burning hybrid rockets at laminar flow
Tsuneyoshi Matsuoka, Harunori Nagata, 60th International Astronautical Congress 2009, IAC 2009, 8, 6293, 6300, 01 Dec. 2009

Numerical simulation of the ejector-jet flowfield around small rocket exhaust
Susumu Hasegawa, Kouichiro Tani, Kenji Kudo, Noboru Sakuranaka, Shuichi Ueda, Harunori Nagata, 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference, 01 Dec. 2009

Subsonic flight experiments of ejector-rocket using hybrid-rocket CAMUI
Shuichi Ueda, Tetsuo Hiraiwa, Masao Takegoshi, Kouichiro Tani, Takeshi Kanda, Harunori Nagata, 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference, 01 Dec. 2009

Improvement of thrust and specific impulse by convective heat transfer in Laval nozzle
Yuuki Iwaki, Tsuyoshi Totani, Tetsushi Naganuma, Syunya Sato, Masashi Wakita, Harunori Nagata, 60th International Astronautical Congress 2009, IAC 2009, 8, 6563, 6573, 01 Dec. 2009

Numerical simulation of CAMUI-type hybrid rocket combustor
Kouichi Kishida, Kouichi Kishida, Yudai Kaneko, Yudai Kaneko, Nobuyuki Oshima, Nobuyuki Oshima, Harunori Nagata, Harunori Nagata, 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 01 Dec. 2009

619 Downsizing and operating more than once of CAMUI type hybrid rocket
Sato Shunya, Takekoshi Takahiro, Tamura Masayoshi, Hagihara Shunsuke, Wakita Masashi, Totani Tsuyoshi, Nagata Harunori, The Proceedings of Conference of Hokkaido Branch, 2009, 48, 211, 212, 28 Nov. 2009
The Japan Society of Mechanical Engineers, Japanese

620 Construction of Active Roll Control System for Hybrid Rocket CAMUI
TAMURA Masayoshi, SATOH Syunya, TAKEKOSHI Takahiro, HAGIWARA Syunsuke, WAKITA Masashi, TOTANI Tsuyoshi, NAGATA Harunori, The Proceedings of Conference of Hokkaido Branch, 2009, 48, 213, 214, 28 Nov. 2009
The Japan Society of Mechanical Engineers, Japanese

拡大する流路内を伝播する円環デトネーション波の挙動
田村正佳, 脇田督司, 永田晴紀, 戸谷剛, 燃焼シンポジウム講演論文集, 47th, 72-73, 18 Nov. 2009
Japanese

ライデンフロスト温度以下に冷却された固体燃料の燃焼特性
飯島直純, 金子雄大, 脇田督司, 戸谷剛, 永田晴紀, 燃焼シンポジウム講演論文集, 47th, 302-303, 18 Nov. 2009
Japanese

熱硬化性樹脂単一粒子の高温ガス流れ場における気化特性
堺裕哉, 榎本剛矩, 脇田督司, 戸谷剛, 永田晴紀, 燃焼シンポジウム講演論文集, 47th, 300-301, 18 Nov. 2009
Japanese

反射板を有する円管状燃焼器におけるデトネーション遷移過程の研究
浅田隆利, 脇田督司, 戸谷剛, 永田晴紀, 坪井伸幸, 林光一, 衝撃波シンポジウム講演論文集, 2008, 211-214, 17 Mar. 2009
Japanese

円錐形状反射板を用いたPDEイニシエータによるドライバーガス削減
脇田督司, 浅田隆利, 戸谷剛, 永田晴紀, 衝撃波シンポジウム講演論文集, 2008, 239-240, 17 Mar. 2009
Japanese

微小重力環境を利用した固体燃焼現象研究（H20研究班WG報告）—Solid combustion research in microgravity (2008 Research WG Report)
藤田, 修, 中村, 祐二, 永田, 晴紀, 菊池, 政雄, 伊藤, 昭彦, 鳥飼, 宏之, 梅村, 章, 高橋, 周平, 池田, 光優, Fujita, Osamu, Nakamura, Yuji, Nagata, Harunori, Kikuchi, Masao, Ito, Akihiko, Torikai, Hiroyuki, Umemura, Akira, Takahashi, Shuhei, Ikeda, Mitsumasa, Chung, Suk Ho, 宇宙利用シンポジウム = Space Utilization Research: Proceedings of Space Utilization Symposium, 25, Mar. 2009
第25回宇宙利用シンポジウム(2009年1月14日-15日, 宇宙航空研究開発機構宇宙科学研究本部相模原キャンパス)
The Twenty-fifth Space Utilization Symposium (January 14-15, 2009: ISAS/JAXA Sagamihara, Japan)
Since solid combustion is dominated by diffusion process of pyrolyzed gas as well as heat balance around combustion area, which are strongly affected by convective flow, micorgravity could be an effective tool to understand its mechanism. One of the most important contributions of solid combustion research in microgravity is fire safety in space. In the present report, some researches on going regarding fire safety in space will be introduced.
資料番号: AA0064297124, 宇宙航空研究開発機構宇宙科学研究本部, Japanese

Development of hybrid rocket engine
室井 典和, 登坂 茂, 永田 晴紀, Memoirs of the Hokkaido Institute of Technology, 0, 37, 141, 146, Mar. 2009
北海道工業大学, Japanese

ノズル加熱による推力および比推力の向上に関する評価方法の検討
長沼哲史, 岩城裕樹, 佐藤峻哉, 戸谷剛, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD−ROM), 53rd, 3G03, 2009
Japanese

PDE燃焼器内の円環流路部を通過するデトネーション波の伝播挙動
脇田督司, 田村正佳, 戸谷剛, 永田晴紀, 宇宙科学技術連合講演会講演集(CD−ROM), 53rd, 2G14, 2009
Japanese

自己加圧供給を利用した液体酸素供給開始方式の検討
和久宏之, 金子雄大, 飯島直純, 萩原俊輔, 脇田督司, 戸谷剛, 永田晴紀, 宇宙科学技術連合講演会講演集(CD−ROM), 53rd, 2B08, 2009
Japanese

液滴ラジエータにおける自動制御による作動流体の循環
仁木雄大, 竹腰卓博, 戸谷剛, 永田晴紀, 脇田督司, 宇宙科学技術連合講演会講演集(CD−ROM), 53rd, 2J02, 2009
Japanese

ラバールノズルにおける推進剤への対流熱伝達による推力・比推力の向上
岩城裕樹, 長沼哲史, 佐藤峻哉, 戸谷剛, 脇田督司, 永田晴紀, 日本航空宇宙学会北部支部講演会ならびに再使用型宇宙推進系シンポジウム講演論文集, 2009-10th, 112-117, 2009
Japanese

環状流路を有するPDEイニシエーター内のデトネーション波の挙動
田村正佳, 脇田督司, 浅田隆利, 戸谷剛, 永田晴紀, 流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集, 41st-2009, 357-360, 2009
Japanese

ポリエチレン燃料の酸化剤衝突領域での燃焼における流速の効果
金子雄大, 脇田督司, 戸谷剛, 永田晴紀, 宇宙科学技術連合講演会講演集(CD−ROM), 53rd, 2B06, 2009
Japanese

超小型宇宙機UNITEC‐1の基本熱設計
伊井晴明, 戸谷剛, 脇田督司, 永田晴紀, 宇宙科学技術連合講演会講演集(CD−ROM), 53rd, 2F11, 2009
Japanese

CAMUI型ハイブリッドロケット用固体燃料の後退履歴特性
永田晴紀, 柿倉彰人, 伊藤光紀, 金子雄大, 森一大, 植嶋健太, 植松努, 戸谷剛, 宇宙科学技術連合講演会講演集(CD−ROM), 53rd, 2B05, 2009
Japanese

UNITEC‐1の初期熱設計
伊井晴明, 田島康晴, 戸谷剛, 永田晴紀, 脇田督司, 日本航空宇宙学会北部支部講演会ならびに再使用型宇宙推進系シンポジウム講演論文集, 2009-10th, 281-286, 2009
Japanese

S1901-2-5 Numerical Study of CAMUI-type Hybrid Rocket Combustor
Kishida Kouichi, Kaneko Yudai, Oshima Nobuyuki, Nagata Harunori, The proceedings of the JSME annual meeting, 2009, 0, 259, 260, 2009
CAMUI (Cascaded Multistage Impinging-jet) type hybrid rocket has been developed in Hokkaido University. The 3-dimensional shape of combustion chamber of hybrid rocket changes considerably during the operation because it is constructed of solid fuel itself. The shape of combustion chamber is related with the performance of the rocket directly, so it is important to understand the relationship between flow and shape. To clarify this issue, numerical simulations were conducted using three different 3D shapes. These shapes were measured from partially burned fuel blocks by the non-contact measuring system. These blocks were obtained by the combustion test where the blocks were taken out before they completely burn out., The Japan Society of Mechanical Engineers, Japanese

S1904-2-2 Improvement of thrust and specific impulse by convective heat transfer in Laval nozzle
IWAKI Yuuki, NAGANUMA Tetsushi, SATO Syunya, TOTANI Tsuyoshi, WAKITA Masashi, NAGATA Harunori, The proceedings of the JSME annual meeting, 2009, 0, 297, 298, 2009
The one-dimensional analysis has been performed using the analysis program for the flow of the propellant of Laval nozzles. The propellant is nitrogen. Two kinds of nozzle that has a throat diameter of 0.5 mm and 1 mm are assumed. Heat flow to the propellant by convective heat transfer in the supersonic region is increased by elongating of the divergent section of the nozzle. The ratio of the exhaust velocity with the heat transfer in the nozzle to the exhaust velocity without the heat transfer is not affected by the throat diameter, inlet pressure, and temperature difference between the nozzle wall and the propellant. In the case that the throat diameter of 0.5 mm, inlet pressure of 1 MPa, temperature difference of 300 K and length of the divergent section of 200 mm, the ratio of the exhaust velocity becomes 1.05., The Japan Society of Mechanical Engineers, Japanese

The improvement of the thrust and specific impulse by heating and elongating of De Laval nozzle
Yuuki Iwaki, Tsuyoshi Totani, Tetsushi Naganuma, Harunori Nagata, International Astronautical Federation - 59th International Astronautical Congress 2008, IAC 2008, 10, 6403, 6410, 01 Dec. 2008

CAMUI型ハイブリッドロケット固体燃料の燃焼速度に及ぼすスケールの影響
永田晴紀, 伊藤光紀, 金子雄大, 柿倉彰人, 森一大, 植松努, 戸谷剛, 燃焼シンポジウム講演論文集, 46th, 56-57, 20 Nov. 2008
Japanese

二段燃焼式ハイブリッドロケット一次燃焼室における燃料定常分布に初期粒径が及ぼす影響
羽柴健太, 堺裕哉, 戸谷剛, 永田晴紀, 燃焼シンポジウム講演論文集, 46th, 516-517, 20 Nov. 2008
Japanese

管内を燃え広がる火炎の伝播機構の解明
松岡常吉, 戸谷剛, 永田晴紀, 燃焼シンポジウム講演論文集, 46th, 194-195, 20 Nov. 2008
Japanese

605 Dependence of the Regression Rate on the Grain Diameter in the Primary Combustion Chamber of Staged Combustion Hybrid Rocket
HASHIBA Kenta, SAKAI Hiroya, TOTANI Tsuyoshi, NAGATA Harunori, The Proceedings of Conference of Hokkaido Branch, 2008, 47, 149, 150, 27 Sep. 2008
The Japan Society of Mechanical Engineers, Japanese

606 Optimal design of the Reflecting Board Diameter in a PDE Initiator with a Reflecting Board
ASADA Takatoshi, WAKITA Masashi, TOTANI Tsuyoshi, NAGATA Harunori, The Proceedings of Conference of Hokkaido Branch, 2008, 47, 151, 152, 27 Sep. 2008
The Japan Society of Mechanical Engineers, Japanese

Development of CAMUI Hybrid Rocket : How we overcame the anomalous combustion
NAGATA Harunori, Journal of the Heat Transfar Society of Japan, 47, 199, 23, 29, 01 Apr. 2008
日本伝熱学会, Japanese

反射板を用いたPDEイニシエーターにおけるドライバーガス削減に関する研究
浅田隆利, 脇田督司, 沼倉龍介, 戸谷剛, 永田晴紀, 衝撃波シンポジウム講演論文集, 2007, 275-278, 17 Mar. 2008
Japanese

B-2-24 Experiment equipped with micro model satellite to 90&250kgf class CAMUI hybrid rocket
Mitsuhashi Ryuichi, Sato Tatsuhiro, Takenami Kyohei, Abe Junichiro, Yoshio Naoto, Totani Tsuyoshi, Nagata Harunori, Proceedings of the IEICE General Conference, 2008, 1, 266, 266, 05 Mar. 2008
The Institute of Electronics, Information and Communication Engineers, Japanese

高Ohnesorge数領域における液滴流の捕集と飛散を分ける閾値—Threshold between spreading and splashing of droplet streams in the region of high Ohnesorge number
戸谷, 剛, 南部, 航太, 川上, 哲人, 由利, 泰史, 永田, 晴紀, Totani, Tsuyoshi, Nanbu, Kota, Kawakami, Akihito, Yuri, Yasufumi, Nagata, Harunori, 宇宙利用シンポジウム 第24回 平成19年度 = Space Utilization Research: Proceedings of the Twenty-fourth Space Utilization Symposium, 117, 120, Mar. 2008
This research has aimed to prevent the working fluid from dispersing at the droplet collector of liquid droplet radiators by specifying the threshold in which splashing and spreading of droplets in space are divided. The following results have been achieved by this research. (1) It was clarified not to be able to arrange the threshold in which splashing and spreading were divided only by a past arrangement type of the threshold. (2) The threshold approved to fluids with the different viscosity is discovered. (3) It is discovered that the droplets splashes more hardly under microgravity than under normal gravity. (4) The cause that the threshold between splashing and spreading under microgravity are different from that under normal gravity has been specified. The above-mentioned results greatly contribute to the proof examination on the orbit of the liquid droplet radiator.
資料番号: AA0063706028, 宇宙航空研究開発機構宇宙科学研究本部, Japanese

高Ohnesorge数領域における液滴流の捕集と飛散を分ける閾値
戸谷剛, 南部航太, 川上哲人, 由利泰史, 永田晴紀, 宇宙利用シンポジウム, 24th, 117-120, Mar. 2008
Japanese

バルブレス技術による小型ロケットの開発
永田晴紀, バルブ技報, 23, 1, 15, 20, 2008

CAMUI方式によるハイブリッドロケット燃料後退速度向上の定量的評価
森一大, 伊藤光紀, 柿倉彰仁, 金子雄大, 植嶋健太, 室井典和, 植松努, 戸谷剛, 永田晴紀, 日本航空宇宙学会北部支部講演会講演論文集, 2008, 135-138, 2008
Japanese

小型衛星用太陽熱スラスタの熱設計
岩城裕樹, 長沼哲史, 戸谷剛, 永田晴紀, 日本航空宇宙学会北部支部講演会講演論文集, 2008, 1-6, 2008
Japanese

CAMUIハイブリッドロケットの起動特性シミュレーション
植嶋健太, 伊藤光紀, 前田剛典, 柿倉彰仁, 金子雄大, 森一大, 室井典和, 植松努, 戸谷剛, 永田晴紀, 日本航空宇宙学会北部支部講演会講演論文集, 2008, 139-142, 2008
Japanese

液滴ラジエータにおける液滴流の飛散と捕集を分ける閾値
川上哲史, 由利泰史, 仁木雄大, 戸谷剛, 永田晴紀, 日本航空宇宙学会北部支部講演会講演論文集, 2008, 149-153, 2008
Japanese

CAMUIハイブリッドロケットの性能履歴予測に関する研究
柿倉彰仁, 伊藤光紀, 金子雄大, 森一大, 植嶋健太, 飯嶋直純, 室井典和, 植松努, 戸谷剛, 永田晴紀, 日本航空宇宙学会北部支部講演会講演論文集, 2008, 143-147, 2008
Japanese

ボルト締結体における接触熱コンダクタンスの温度依存性
榊原隆浩, 伊井晴明, 戸谷剛, 永田晴紀, 日本航空宇宙学会北部支部講演会講演論文集, 2008, 55-60, 2008
Japanese

4037 Improvement of the thrust and specific impulse by elongating and heating the Laval nozzle
IWAKI Yuuki, NAGANUMA Tetsushi, TOTANI Tsuyoshi, NAGATA Harunori, The proceedings of the JSME annual meeting, 2008, 0, 395, 396, 2008
The one-dimensional analysis has been performed using the analysis program for the flow of the propellant and the wall temperature of Laval nozzles. The material of the nozzles is A5056 and the propellant is water. In the case that the diameter of the nozzle inlet is 0.6 mm, the diameter of the throat is 0.1 mm, the mass flow rate of the propellant is 1 g/min, the inlet temperature of the propellant and wall are 500 K, Outlet pressure of the propellant is 400 Pa, the radial thickness of the nozzle is 2 mm, and the length of the divergent nozzle is 36 mm, the 151 s of the specific impulse has been achieved whereas the specific impulse with an adiabatically change is 137 s., The Japan Society of Mechanical Engineers, Japanese

4038 University Consortium Project : Development Status of Winged Experimental
WAKITA Masashi, YONEMOTO Koichi, ASO Shigeru, KOHSETSU Yuji, NAGATA Harunori, UZAWA Kiyoshi, The proceedings of the JSME annual meeting, 2008, 0, 397, 398, 2008
The project of Winged Experimental Rocket described here is a proposal by the alliance of universities (University Consortium) expanding and integrating the research activities of reusable space transportation system performed by individual universities, and is the proposal that aims at flight proof of the results of advanced research conducted by the universities and JAXA using the university-centered experimental launch systems. This paper verifies the validity of the winged experimental rocket by surveying the technical issues that should be demonstrated and by estimating the airframe scale, weight and structural type. To minimize the development risks of winged experimental rocket, two kinds of airframe with different scales are developed., The Japan Society of Mechanical Engineers, Japanese

4040 Designing the Fuel Grain of CAMUI Hybrid Rocket Using the Prediction Model of Performance History
Uejima Kenta, Nagata Harunori, Itoh Mitsunori, Kakikura Akihito, Kaneko Yudai, Mori Kazuhiro, Iijima Naozumi, Muroi Norikazu, Uematsu Tsutomu, Totani Tsuyoshi, The proceedings of the JSME annual meeting, 2008, 0, 401, 402, 2008
In order to enlarge the system of CAMUI hybrid rocket, it is essential to estimate its performance with a minimum of combustion experiments to reduce research and development costs. The authors had built up "Prediction Model for Startup Characteristic", which simulate the pressure history of each part of the system, and "Fuel Regression History Model", which predict the weight and shape history of fuel under combustion. In this study, the authors combined the two models mentioned above, and built up the program that predict the pressure history of each part of the system, and the weight and shape history of the fuel directly from the initial parameters. The result obtained by the program agreed well with the experimental value and got adequacy. With the program, the authors designed the CAMUI fuel grain which realize the optimal fuel flow rate on 90kgf thrust class motor, of which fuel has not been optimized yet., The Japan Society of Mechanical Engineers, Japanese

4041 Ultrasonic Pulse-echo Measurement of Hybrid Rocket Fuel Regression
KANEKO Yudai, Itoh Mitsunori, UEJIMA Kenta, TOTANI Tsuyoshi, NAGATA Harunori, The proceedings of the JSME annual meeting, 2008, 0, 403, 404, 2008
A series of the firing rest was conducted to obtain the history of the instantaneous value of the fuel thickness during the firing test. An ultrasonic pulse-echo method was used to the firing test for that purpose. Gaseous oxygen and polyethylene were used to the firing test about the combustion of the solid fuel in the oxygen jet collision area. A preliminary experiment revealed that the variation of the propagation time caused by the change of fuel temperature is negligible small because the thermal boundary layer in the solid fuel is thin. The fuel regression rate at the stagnation point of oxidizer jet depends on Reynolds number., The Japan Society of Mechanical Engineers, Japanese

推力250kgf級CAMUI型ハイブリッドロケットの燃焼特性
永田晴紀, 植松努, 伊藤光紀, 柿倉彰人, 金子雄大, 森一大, 戸谷剛, 燃焼シンポジウム講演論文集, 45th, 508-509, 20 Nov. 2007
Japanese

Development of CAMUI hybrid rocket: present and future
ITO KENICHI, NAGATA HARUNORI, UEMATSU TSUTOMU, LAUER CHARLES, Aeronautical and space sciences Japan, 55, 646, 292, 295, Nov. 2007
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, Japanese

250kgf級CAMUI型ハイブリッドロケットへの超小型モデル衛星搭載実験
三橋龍一, 佐藤立博, 竹浪恭平, 安部潤一郎, 吉尾直人, 戸谷剛, 永田晴紀, 電気・情報関係学会北海道支部連合大会講演論文集(CD−ROM), 2007, ROMBUNNO.47, 27 Oct. 2007
Japanese

Panel Discussion "Does Space Transportation Give the Future Perspectives?"
久保田 弘敏, 棚次 亘弘, 有田 誠, 永田 晴紀, 稲谷 芳文, 苅田 丈士, Aeronautical and space sciences Japan, 55, 645, 275, 285, 05 Oct. 2007
日本航空宇宙学会, Japanese

503 The automatic control of the circulation of working fluid in Liquid Droplet Radiator
由利 泰史, 川上 哲史, 戸谷 剛, 永田 晴紀, The Proceedings of Conference of Hokkaido Branch, 2007, 46, 129, 130, 29 Sep. 2007
The Japan Society of Mechanical Engineers, Japanese

504 Mission Design of Payload Transportation by Solar Orbit Transfer Vehicle Using Water as Propellant
岩城 裕樹, 戸谷 剛, 永田 晴紀, The Proceedings of Conference of Hokkaido Branch, 2007, 46, 131, 132, 29 Sep. 2007
The Japan Society of Mechanical Engineers, Japanese

505 The threshold between splashing and spreading of colliding droplet stream with an inclining wall
川上 哲史, 由利 泰史, 戸谷 剛, 永田 晴紀, The Proceedings of Conference of Hokkaido Branch, 2007, 46, 133, 134, 29 Sep. 2007
The Japan Society of Mechanical Engineers, Japanese

506 Gasification History of Pellet Fuels in the Primary Combustion Chamber of Staged Combustion Hybrid Rocket
KATANO Hikaru, HASHIBA Kenta, TOTANI Tsuyoshi, NAGATA Harunori, The Proceedings of Conference of Hokkaido Branch, 2007, 46, 135, 136, 29 Sep. 2007
The Japan Society of Mechanical Engineers, Japanese

507 Scale Effects on the Regression Rate of CAMUI Hybrid Rocket Fuel
MORI Kazuhiro, ITOH Mitsunori, KAKIKURA Akihito, KANEKO Yudai, UEJIMA Kenta, MUROI Kazunori, TOTANI Tuyosih, UEMATSTU Tsutomu, NAGATA Harunori, The Proceedings of Conference of Hokkaido Branch, 2007, 46, 137, 138, 29 Sep. 2007
The Japan Society of Mechanical Engineers, Japanese

205 Prediction of geometric history of CAMUI hybrid rocket fuel grain
KAKIKURA Akihito, ITOH Mitsunori, KANEKO Yuudai, MORI Kazuhiro, UEJIMA Kenta, MUROI Norikazu, UEMATSU Tsutomu, TOTANI Tsuyoshi, NAGATA Harunori, The Proceedings of Conference of Hokkaido Branch, 2007, 46, 127, 128, 29 Sep. 2007
The Japan Society of Mechanical Engineers, Japanese

Combustion of Solid Fuels in CAMUI Rocket Combustion Chamber
NAGATA Harunori, Journal of the Combustion Society of Japan, 49, 149, 163, 169, 31 Aug. 2007
Combustion Society of Japan, Japanese

Goal of the small hybrid rocket development
永田 晴紀, Engine technology, 9, 4, 29, 33, Aug. 2007
山海堂, Japanese

Research on Development of Autonomous Control System for CAMUI Hybrid Rocket Small Movable Wing
Takeoka Kazuhiko, Sato Tatsuhiro, Abe Junichiro, Takenami Kyohei, Mitsuhashi Ryuichi, Satori Shin, Ohtaki Seiichi, Toyoda Kuniaki, Nakamura Akihiro, Nagata Harunori, Memoirs of the Hokkaido Institute of Technology, 35, 0, 361, 364, 26 Mar. 2007
CAMUI hybrid rocket is safety, low-cost and low-pollution rocket that was developed in Hokkaido. In this research, it aims at the construction of the system that lands in a target place, it safely and surely of rocket. The basic research is described, change of control wing by enlargement of rocket and development of autonomous control system., Hokkaido Institute of Technology, Japanese

反射板を用いたPDEイニシエーターによる爆轟波の伝播促進
脇田督司, 沼倉龍介, 菅田成俊, 戸谷剛, 永田晴紀, 衝撃波シンポジウム講演論文集, 2006, 47-48, 15 Mar. 2007
Japanese

Large Eddy Simulation of a Turbulent Flow in a CAMUI Hybrid Rocket Combustor
WAKITA MASASHI, ITO MITSUNORI, KANEKO YUDAI, NAKASHIMA TAKUJI, NAGATA HARUNORI, OSHIMA NOBUYUKI, 流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集, 39th-2007, 373-376, 2007
Japanese

4131 Ultrasonic Pulse-echo Measurement of Hybrid Rocket Fuel Regression
KANEKO Yudai, Itoh Mitsunori, KAKIKURA Akihito, MORI Kazuhiro, UEJIMA Kenta, TOTANI Tsuyoshi, NAGATA Harunori, The proceedings of the JSME annual meeting, 2007, 0, 407, 408, 2007
A hybrid rocket is a high safety and low cost propulsion system. However, conventional hybrid rockets have a defect of are low thrust because of the low gasification rate of the solid fuel. Therefore, many researches of a hybrid rocket aimed at the improvement of the gasification rate of the solid fuel, being evaluated by a regression rate. We have been developing a new type hybrid rocket named CAMUI that improves the regression rate of solid fuels by using an impinging jet heat transfer. In many cases, a fuel regression rate is obtained as an average during the combustion. However, when the fuel shape changes dramatically during the combustion, this method is not suitable. Therefore, it is necessary to measure the history of the fuel thickness during the combustion. Therefore, we are trying to use ultrasonic pulse-echo measurement system and this paper describes the result of a basic research about the real-time measurement., The Japan Society of Mechanical Engineers, Japanese

4130 Scale Effect on Fuel Regression Characteristics of CAMUI Hybrid Rocket
ITOH Mitsunori, MAEDA Takenori, KAKIKURA Akihito, KANEKO Yuudai, MORI Kazuhiro, UEMATSU Tsutomu, TOTANI Tsuyoshi, NAGATA Harunori, The proceedings of the JSME annual meeting, 2007, 0, 405, 406, 2007
CAMUI type hybrid rocket has a distinctive configuration of fuel grain to overcome the defect of the low fuel regression rate of conventional hybrid rockets. In CAMUI type fuel grain, a number of surfaces perpendicular to the thrust axis, as well as port surfaces, contribute as burning surfaces. Static firing tests with three scales of analogous motors were conducted to investigate the scaling effect on the fuel regression characteristics of CAMUI type fuel grain. LOX and Polyethylene were used as a propellant, and tests were conducted with the same Reynolds number condition, at the chamber pressure of 1MPa and the mass flux of 150-300kg/(m^2s)., The Japan Society of Mechanical Engineers, Japanese

SP1 Launch Test of 400kgf Thrust Class CAMUI Hybrid Rocket(1)
永田 晴紀, Fluids engineering conference ..., 2006, 0, "SP1, a", 28 Oct. 2006
The Japan Society of Mechanical Engineers, Japanese

SP1 Lanuch Test of 400kgf Thrust Class CAMUI Hybrid Rocket(2)
永田 晴紀, Fluids engineering conference ..., 2006, 0, "SP1, 1"-"SP1-3", 28 Oct. 2006
A joint research team of universities and private companies in Hokkaido, Japan has been organized to develop a small-scale reusable launch system based on CAMUI hybrid rocket. The main purpose is to drastically reduce the cost of rocket experiments and thus attract potential users such as metrological and microgravity researchers. The meteorological observation model of 400-kgf class motor is under development and a launch test in 10 km altitude is planned. Anomalous combustion occurred in the last four static firing tests out of seven serial tests with a flight model motor. This anomalous ..., The Japan Society of Mechanical Engineers, Japanese

117 Structural Design and Mechanical Tests of HIT-SAT Flight Model
SAKAKIBARA Takahiro, TOTANI Tsuyoshi, YASUNAKA Toshihiko, SATORI Shin, NAGATA Harunori, The Proceedings of Conference of Hokkaido Branch, 2006, 45, 33, 34, 25 Sep. 2006
The Japan Society of Mechanical Engineers, Japanese

116 Deposition and Splash of Liquid Droplet Stream at Liquid Droplet Collector
Nanbu Kouta, Kawakami Akihito, Yuri Yasuhumi, Totani Tsuyoshi, Nagata Harunori, The Proceedings of Conference of Hokkaido Branch, 2006, 45, 31, 32, 25 Sep. 2006
The Japan Society of Mechanical Engineers, Japanese

118 Engineering Model Design of Staged-Combustion Hybrid Rocket
SAKAMOTO Masashi, KATANO Hikaru, TOTANI Tsuyoshi, NAGATA Harunori, The Proceedings of Conference of Hokkaido Branch, 2006, 45, 35, 36, 25 Sep. 2006
The Japan Society of Mechanical Engineers, Japanese

119 Rigidity of Multi-Cellular Inflatable Structures
KATO Ryuzo, TOTANI Tsuyoshi, ISHIMURA Kosei, NAGATA Harunori, The Proceedings of Conference of Hokkaido Branch, 2006, 45, 37, 38, 25 Sep. 2006
The Japan Society of Mechanical Engineers, Japanese

120 Influence of Amount of Driver Gas Mixture on Promotion of Detonation Wave Propagation
SUGATA Shigetoshi, WAKITA Masashi, NUMAKURA Ryusuke, NAGATA Harunori, TOTANI Tsuyoshi, The Proceedings of Conference of Hokkaido Branch, 2006, 45, 39, 40, 25 Sep. 2006
The Japan Society of Mechanical Engineers, Japanese

B-2-1 Drop Control Experiment for CAMUI Hybrid Rocket Scale Model
Takeoka Kazuhiko, Sato Tatsuhiro, Nabae Akira, Mitsuhashi Ryuichi, Satori Shin, Ohtaki Seiichi, Toyoda Kuniaki, Nakamura Akihiro, Nagata Harunori, Proceedings of the IEICE General Conference, 2006, 1, 239, 239, 08 Mar. 2006
The Institute of Electronics, Information and Communication Engineers, Japanese

B-2-2 Experiment of Avionics for 400 kgf Thrust Class CAMUI Hybrid Rocket
Mitsuhashi Ryuichi, Sato Tatsuhiro, Takeoka Kazuhiko, Ohno Tsutomu, Nakamura Akihiro, Satori Shin, Nagata Harunori, Proceedings of the IEICE General Conference, 2006, 1, 240, 240, 08 Mar. 2006
The Institute of Electronics, Information and Communication Engineers, Japanese

微小重力環境を利用した固体燃焼現象検討ＷＧ報告—WG report on Solid Combustion in Microgravity
藤田, 修, 中村, 祐二, 永田, 晴紀, 菊池, 政雄, 伊藤, 昭彦, 岡島, 敏, 梅村, 章, 高橋, 周平, Fujita, Osamu, Nakamura, Yuji, Nagata, Harunori, Kikuchi, Masao, Ito, Akihiko, Okajima, Satoshi, Umemura, Akira, Takahashi, Shuhei, 宇宙利用シンポジウム = Space Utilization Research: Proceedings of Space Utilization Symposium, 22, Mar. 2006
第22回宇宙利用シンポジウム(2006年1月17日-19日, 日本学術会議6階会議室 六本木、東京)
The Twenty-second Space Utilization Symposium (January 17-19, 2006: Science Council of Japan, Roppongi, Tokyo, Japan)
Since solid combustion, which has long time scale, is dominated by diffusion process of pyrolyzed gas, micorgravity could be an effective tool to understand its mechanism. One of the most important contributions of solid combustion research in microgravity is fire safety in space. In the present report, some researches attained previously as well as future expected subjects regarding fire safety in space will be introduced. Because individual physical processes included in the solid combustion have different time scale, combination of short-term and long-term microgravity experiments is requisite to proceed the research on solid combustion in microgravity.
形態: カラー図版あり
共催: 日本学術会議
Physical characteristics: Original contains color illustrations
Meeting sponsors: The Science Council of Japan, The Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (ISAS)(JAXA)
資料番号: AA0064113029, 宇宙航空研究開発機構宇宙科学研究本部, Japanese

The Challenges of Developing a Hybrid Launch System for Microsatellite Payloads Using CAMUI Hybrid Upperstages with the Rocketplane XP
C. Lauer, H. Nagata, T. Uematsu, Proceedings of the 25th ISTS Selected Papers, 821, 827, 2006, [Peer-reviewed]

Consideration of Autonomous Control System Small Movable Wing for CAMUI Hybrid Rocket
武岡和彦, 佐藤立博, 安部潤一郎, 竹浪恭平, 三橋龍一, 佐鳥新, 大滝誠一, 豊田国昭, 中村明広, 永田晴紀, 加藤聡貴, 大野努, 宇宙科学技術連合講演会講演集(CD-ROM), 50th, 2006

スペースプレーンのための革新的な基盤技術研究開発における大学およびベンチャの役割
棚次亘弘, 麻生茂, 新井隆景, 永田晴紀, 姫野武洋, 日本航空宇宙学会年会講演会講演集, 37th, 2006

1024 Development of 400kgf thrust class CAMUI type sounding rocket
MAEDA Takenori, ITO Mitsunori, KAKIKURA Akihito, NABAE Akira, NAGATA Harunori, TOTANI Tsuyoshi, KUDO Isao, UEMATSU Tsutomu, The proceedings of the JSME annual meeting, 2006, 0, 341, 342, 2006
Cascaded Multistage Impinging-jet (CAMUI) is one of the combustion methods of hybrid rocket. This is the way of burning solid fuel and liquid oxidizer at stagnation point. By this way, we can expect to get high regression rate and high combustion efficiency. Now, with this combustion method, we developed the 400kgf thrust class flight model to observe upper air and did experiments to confirm its performance. This summer, our aim is to make this hybrid rocket reach 10km altitude. This paper describes the outline of the mission and the combustion characteristics which we got by the static firing test., The Japan Society of Mechanical Engineers, Japanese

Development of CAMUI hybrid rocket to create a market for small rocket experiments
Harunori Nagata, Mitsunori Ito, Takenori Maeda, Mikio Watanabe, Tsutomu Uematsu, Tsuyoshi Totani, Isao Kudo, International Astronautical Federation - 56th International Astronautical Congress 2005, 7, 4763, 4767, 01 Dec. 2005

Numerical and experimental studies on circulation of working fluid in liquid droplet radiator
Tsuyoshi Totani, Takuya Kodama, Kensuke Watanabe, Kota Nanbu, Harunori Nagata, Isao Kudo, International Astronautical Federation - 56th International Astronautical Congress 2005, 6, 3842, 3852, 01 Dec. 2005

反射板を用いたPDEにおける爆轟波伝播に及ぼす過供給の影響
沼倉龍介, 脇田督司, 伊藤雄介, 菅田成俊, 永田晴紀, 戸谷剛, 工藤勲, 燃焼シンポジウム講演論文集, 43rd, 498-499, 20 Nov. 2005
Japanese

反射板によるデトネーション波の伝播促進効果に対するセルサイズの影響
脇田督司, 沼倉龍介, 伊藤雄介, 菅田成俊, 永田晴紀, 戸谷剛, 工藤勲, 燃焼シンポジウム講演論文集, 43rd, 480-481, 20 Nov. 2005
Japanese

216 The Effect of Incidence Shock Strength on the Performance Characteristic of PDE with a Reflecting Board
ITO Yusuke, WAKITA Masashi, NUMAKURA Ryusuke, SUGATA Shigetoshi, NAGATA Harunori, TOTANI Tsuyoshi, KUDO Isao, The Proceedings of Conference of Hokkaido Branch, 2005, 44, 70, 71, 08 Oct. 2005
The Japan Society of Mechanical Engineers, Japanese

217 Thermal-design of Staged Combustion Hybrid Rocket
FUKUYAMA Hisashi, SAKAMOTO Masashi, NAGATA Harunori, TOTANI Tsuyoshi, KUDO Isao, The Proceedings of Conference of Hokkaido Branch, 2005, 44, 72, 73, 08 Oct. 2005
The Japan Society of Mechanical Engineers, Japanese

218 Transient characteristics after the change of circulation flow in Liquid Droplet Radiator
Watanabe Kensuke, Nanbu Kota, Totani Tsuyoshi, Nagata Harunori, Kudo Isao, The Proceedings of Conference of Hokkaido Branch, 2005, 44, 74, 75, 08 Oct. 2005
The Japan Society of Mechanical Engineers, Japanese

219 Concept Design of Biological Experiments for Mouse in a Reentry Space System
IIDA Kyohei, TOTANI Tsuyoshi, NAGATA Harunori, KUDO Isao, YANO Shoki, The Proceedings of Conference of Hokkaido Branch, 2005, 44, 76, 77, 08 Oct. 2005
The Japan Society of Mechanical Engineers, Japanese

無火薬式ロケットによる小型ロケット実験の低価格化
永田 晴紀, 日本機械学會誌, 108, 1043, 819, 819, 05 Oct. 2005
一般社団法人日本機械学会, Japanese

Development Study at University Laboratories of Small-Scale Reusable Launch Systems : Part 1 : Development of CAMUI Hybrid Rocket
NAGATA Harunori, Aeronautical and space sciences Japan, 53, 616, 142, 146, 05 May 2005
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, Japanese

Thermal design of liquid droplet radiator for space solar-power system
T Totani, T Kodama, H Nagata, Kudo, I, JOURNAL OF SPACECRAFT AND ROCKETS, 42, 3, 493, 499, May 2005
English

B-2-38 Experiment of CanSat by CAMUI Hybrid Rocket and Development of Autonomous Controller for Fly-Back System
Mitsuhashi Ryuichi, Satoh Tatsuhiro, Takeoka Kazuhiko, Nabae Akira, Shimooka Ayako, Nakamura Akihiro, Satori Shin, Ohtaki Seiichi, Toyoda Kuniaki, Nagata Harunori, Proceedings of the IEICE General Conference, 2005, 1, 324, 324, 07 Mar. 2005
The Institute of Electronics, Information and Communication Engineers, Japanese

Research on dynamic response of catalytic heat release rate on platinum wire to a shock wave in hydrogen-air mixture
D Nakamura, H Nagata, T Totani, Kudo, I, JSME INTERNATIONAL JOURNAL SERIES B-FLUIDS AND THERMAL ENGINEERING, 48, 1, 144, 150, Feb. 2005
English

Creation of a Market for Small Rocket Experiment through CAMUI Hybrid Rocket
NAGATA Harunori, WATANABE Mikio, ITO Mitsunori, MAEDA Takenori, TOTANI Tsuyoshi, KUDO Isao, The Proceedings of the Space Engineering Conference, 2004, 13, 1, 4, 20 Jan. 2005
Small-scale reusable sounding rocket system is under development to provide means of stratosphere observation and three-minutes microgravity experiment. The propulsion system is a hybrid type that uses solid fuel (plastics) and liquid oxygen as propellants and free from explosives, resulting in the dramatically reduced launch cost. To enhance the burning rate of the solid fuel and to augment the thrust, the rocket has employed a new fuel grain design. This new design, named CAMUI as an abbreviation of "Cascaded Multistage Impinging-jet", allows mixing and combustion to occur around stagnati..., The Japan Society of Mechanical Engineers, Japanese

日本の最新の小型民間ロケット(日本の小型ロケット)
永田 晴紀, 日本機械学會誌, 108, 1034, 78, 78, 05 Jan. 2005
一般社団法人日本機械学会, Japanese

Influence of the Composition of Mixture for Propagation of Detonation Wave at an Abrupt Area Change
NUMAKURA RYUSUKE, WAKITA MASASHI, ITO YUSUKE, SUGATA SHIGETOSHI, NAGATA HARUNORI, TOTANI TSUYOSHI, KUDO ISAO, 流体力学講演会講演集, 37th, 155-158, 2005
Japanese

Creation of a market for small rocket experiments through CAMUI hybrid rocket
H Nagata, M Watanabe, M Ito, T Maeda, T Uematsu, T Totani, Kudo, I, 17th ESA Symposium on European Rocket and Balloon Programmes and Related Research, 590, 375, 379, 2005
English

CAMUI型(縦列多段衝突噴流型)ハイブリッドロケットの開発と微小重力ロケット実験への応用 (小特集2 短時間微小重力環境を利用した最近の燃焼研究)
永田 晴紀, 日本マイクログラビティ応用学会誌, 22, 1, 47, 50, 2005
日本マイクログラビティ応用学会, Japanese

3321 CanSat experiment by CAMUI Hybrid Rocket
Aoyanagi Yoshihide, Toyota Kuniaki, Nagata Harunori, Sato Tatuhiro, Iwamoto Takatoshi, Nabae Akira, Simooka Ayako, Satori Shin, Mitsuhashi Ryuichi, Ohtaki Seiichi, The proceedings of the JSME annual meeting, 2005, 0, 369, 370, 2005
The CanSat project was conducted by undergraduate students who had designed and fabricated a small experimented module called "CanSat". The CanSat was launched by a CAMUI-type hybrid rocket up to the height of 330meters. The CanSat was ejected from the rocket by the releasing mechanism that was installed inside the fairing of rocket, and fell down safely by using a parachute., The Japan Society of Mechanical Engineers, Japanese

3329 Thermal Analysis and Performance Characteristics on Solar Thermal Thruster
TAKANO Chihiro, MURAKI Yusuke, TOTANI Tsuyoshi, NAGATA Harunori, KUDO Isao, The proceedings of the JSME annual meeting, 2005, 0, 385, 386, 2005
The experiments in which water as propellant is heated and ejected from the nozzle of the solar thermal thruster has been conducted. Thermal analysis of the solar thermal thruster and the propellant has been conducted These results indicate that the highest performance is achieved at a largest mass flow rate for a heat input, where propellant finish boiling at the entrance of the nozzle. Analytical result has indicated that the temperature distribution of the thruster was not ideal for heating propellant because of the heat lost at a nozzle. This is the problem to try to improve propulsive performance. It is possible that this problem is solved by using plug nozzle as a nozzle., The Japan Society of Mechanical Engineers, Japanese

3331 Wind tunnel test of CAMUI model
NABAE Akira, TOYODA Kuniaki, UEMATU Tutomu, NAGATA Harunori, The proceedings of the JSME annual meeting, 2005, 0, 389, 390, 2005
The launching project of a hybrid rocket has been conducted by the research stuffs in the universities in Hokkaido. The CAMUI (CAscaded Multistage Impinging-jet) hybrid rocket has been developed in Hokkaido university, and three launching tests of the rocket showed good results. As the next stage, we are developing a more powerful motor and arocket body to reach to 60km altitude. In the present study, we report the results of the wind test which was carried out to obtain the basicmaterials of the aerodynamic performance of rocket body models., The Japan Society of Mechanical Engineers, Japanese

3332 Fuel Design of 70kgf Thrust Class CAMUI type Rocket Motor
ITOH Mitsunori, MAEDA Takenori, NAGATA Harunori, TOTANI Tsuyoshi, KUDO Isao, UEMATSU Tsutomu, The proceedings of the JSME annual meeting, 2005, 0, 391, 392, 2005
CAMUI type hybrid rocket has a distinctive configuration of fuel grain resulting in unique characteristics of fuel regression. In CAMUI type fuel grain, not only port surfaces but also a number of surfaces perpendicular to the thrust axis contribute as burning surfaces. The authors conducted static firing tests of 70kg thrust class CAMUI type motor to obtain quantitative formulas of the fuel regression as a function of oxidizer flow rate and the initial configuration of the port. These formulas enable us to calculate the instantaneous configuration of the grain, fuel flow rate, and any other performances of the firing motor. They are indispensable to obtain an optimal design of the grain for any missions., The Japan Society of Mechanical Engineers, Japanese

3422 Characteristics on Circulation of Working Fluid in Liquid Droplet Radiator
TOTANI Tsuyoshi, KODAMA Takuya, WATANABE Kensuke, NANBU Kouta, NAGATA Harunori, KUDO Isao, The proceedings of the JSME annual meeting, 2005, 0, 445, 446, 2005
Experiments have been carried out under normal gravity in order to examine characteristics on circulation of working fluid in a liquid droplet radiator. The experimental setup had functioned under microgravity. The working fluid is silicon oil. It has been clear that the liquid droplet radiator has the function to stabilize flow rate without flow rate controllers. Flow rate controllers will be used in a real machine. Even if the flow rate controllers is malfunctioned, the liquid droplet radiator circulates the working fluid stably., The Japan Society of Mechanical Engineers, Japanese

航空宇宙工学便覧第三版　　　　　　　　　　　　　　　
日本航空宇宙学会, 2005

Creation of a Market for Small Rocket Experiment through CAMUI (Cascaded Multistage Impinging-jet) Rocket
NAGATA Harunori, 化学工学 = CHEMICAL ENGINEERING OF JAPAN, 68, 12, 738, 739, 05 Dec. 2004
Japanese

固体燃料表面上を燃え広がる火炎の吹き飛びを支配する要因
橋本望, 永田晴紀, 戸谷剛, 工藤勲, 燃焼シンポジウム講演論文集, 42nd, 275-276, 20 Nov. 2004
Japanese

反射板を用いたPDEイニシエータにおける爆轟波の消炎と再点火の機構
脇田督司, 沼倉龍介, 永田晴紀, 戸谷剛, 工藤勲, 衝撃波シンポジウム講演論文集, 2003, 129-132, 18 Mar. 2004
Japanese

B-2-9 A Launch Experiment of Winged Hybrid Rocket
Mitsuhashi Ryuichi, Nakamura Naoki, Nabae Akira, Kubota Masashi, Suzuki Tomotaka, Satoh Tatsuhiro, Satori Shin, Ohtaki Seiichi, Toyoda Kuniaki, Nagata Harunori, Proceedings of the IEICE General Conference, 2004, 1, 293, 293, 08 Mar. 2004
The Institute of Electronics, Information and Communication Engineers, Japanese

Measurement technique for pumping performance of a centrifugal collector under microgravity
T Totani, M Itami, H Nagata, Kudo, I, A Iwasaki, REVIEW OF SCIENTIFIC INSTRUMENTS, 75, 2, 515, 523, Feb. 2004
English

反射板を利用したPDEイニシエータの連続作動実験
沼倉龍介, 脇田督司, 永田晴紀, 戸谷剛, 工藤勲, 日本航空宇宙学会北部支部講演会講演論文集, 2004, 49-54, 2004
Japanese

Self-pressure Supply System of Oxidizing Agent for Two-staged Combustion Hybrid Rocket Engine
KANAME Takahiro, TOYODA Kuniaki, AKIBA Ryojiro, NAGATA Harunori, The proceedings of the JSME annual meeting, 2004, 0, 479, 480, 2004
The basic experiments have been conducted to develop the staged combustion hybrid rocket engine with two combustion chambers. In the present study, we visualized the flow phenomenon around the orifice used for the flow measurement of the oxidizer N_2O, and the condition to suppress the liquid-gas two-phase flow was obtained. The result is useful to design the self-pressure supply system of N_2O for two-staged combustion hybrid-rocket engine., The Japan Society of Mechanical Engineers, Japanese

Aerodynamic Performance of Delta Wine for Hybrid Rocket
NABAE Akira, TOYODA Kuniaki, AKIBA Ryojiro, NAGATA Harunori, The proceedings of the JSME annual meeting, 2004, 0, 481, 482, 2004
The winged-vehicle for the fly-back system of CAMUI (CAscaded Multistage Impinging-jet) hybrid-rocket has been developed. As the first stage, we carried out the gliding test of a Space-shuttle type winged-vehicle. In the test, the winged-vehicle was carried by a radio-controlled airplane, separated, glided and landed. Then, we conducted a launching test using model rocket engine. The results encouraged us to proceed to further development of the fly-back system. As the second stage, we carried out the tests to develop the delta wing assembled to, CAMUI hybrid-rocket. In the wind tunnel test, the aerodynamic characteristics of the delta wing were investigated. Also, the flight performance of the delta wing was checked by the water-rocket test. These results provided useful data to design and make a delta wing of optimal shape. The present results led to the success of the fly-back test of CAMUI hybrid rocket., The Japan Society of Mechanical Engineers, Japanese

火炎先端部の直上流に形成される循環領域が固体燃料の燃え広がりに与える影響
橋本望, 永田晴紀, 戸谷剛, 工藤勲, 燃焼シンポジウム講演論文集, 41st, 509-510, 20 Nov. 2003
Japanese

Preliminary Design of Fully Reusable CAMUI Hybrid Rocket for Upper-layers Stratosphere Observations
MIURA Takashi, WATANABE Mikio, NAGATA Harunori, TOTANI Tsuyosi, KUDO Isao, The Proceedings of Conference of Hokkaido Branch, 2003, 43, 154, 155, 28 Sep. 2003
The Japan Society of Mechanical Engineers, Japanese

Conceptual Design of Mars Probe with Micro Rover
MASUDA Noriaki, TOTANI Tsuyoshi, NAGATA Harunori, KUDO Isao, The Proceedings of Conference of Hokkaido Branch, 2003, 43, 156, 157, 28 Sep. 2003
The Japan Society of Mechanical Engineers, Japanese

The Re-ignition Mechanism of Detonation Wave around a Reflecting Board
NUMAKURA Ryusuke, WAKITA Masashi, NAGATA Harunori, TOTANI Tusyoshi, KUDO Isao, The Proceedings of Conference of Hokkaido Branch, 2003, 43, 162, 163, 28 Sep. 2003
The Japan Society of Mechanical Engineers, Japanese

Avionics System Experiments for Fly-back Hybrid Rocket
Nakamura Naoki, Shiba Kuniaki, Shimooka Ayako, Mitsuhashi Ryuichi, Satori Shin, Ohtaki Seiichi, Tyoda Kuniaki, Nagata Harunori, Proceedings of the IEICE General Conference, 2003, 1, 311, 03 Mar. 2003
The Institute of Electronics, Information and Communication Engineers, Japanese

VSRLの利用状況評価および教育プロジェクトにおける用例
吉川 茂雄, 戸谷 剛, 永田 晴紀, 日本ディスタンスラーニング学会会誌, 4, 0, 13, 20, Mar. 2003
日本ディスタンスラーニング学会, Japanese

Avionics Loading Winged Vehicle Gliding Experiment for Fly-Back Hybrid Rocket System
Mitsuhashi Ryuichi, Nakamura Naoki, Shiba Kuniaki, Shimooka Ayako, Satori Shin, Ohtaki Seiichi, Toyoda Kuniaki, Nagata Harunori, Memoirs of the Hokkaido Institute of Technology, 31, 0, 37, 42, Mar. 2003
Hokkaido Institute of Technology, Japanese

Relation of Pt wire temperature and catalytic heat release rate on Pt in unsteady state of H2-air mixture
Daisuke Nakamura, Harunori Nagata, Tsuyoshi Totani, Isao Kudo, Nippon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B, 69, 677, 126, 131, 2003
Japan Society of Mechanical Engineers, Japanese

Ballistic Flight and Recovery Demonstration of Fully Reusable CAMUI Hybrid Rocket
WATANABE Mikio, KUBOTA Isao, MIURA Takashi, ITO Mitsunori, YMURAKI Yusuke, NAGATA Harunori, TOTANI Tsuyoshi, KUDO Iso, SHIBA Kuniaki, SHIMOKA Ayako, The proceedings of the JSME annual meeting, 2003, 0, 363, 364, 2003
To develop a reusable launch system, development study of jet-impinging hybrid rocket has been made. To prove a reliability and safety of a launch-recover system with jet-impinging hybrid rocket motor, a ballistic launch test of CAMUI (Cascaded Multistage Impinging-jet)-02 was performed on a January 13,2003 at TAIKI Hokkaido. The CAMUI-02 went up stably and reached about 500m in altitude. the rocket was recovered safely by parachute. These results prove reliability and safety of the launch-recover system with CAMUI hybrid rocket., The Japan Society of Mechanical Engineers, Japanese

熱的に薄い固体燃料の隙間に燃え広がる火炎に関する研究
橋本望, 渡辺賢, 永田晴紀, 戸谷剛, 工藤勲, 燃焼シンポジウム講演論文集, 40th, 163-164, 01 Nov. 2002
Japanese

Development of a Winged Vehicle for Fly-back Hybrid-rocket : Aerodynamics of a Winged Vehicle
SHIMOOKA Ayako, SHIBA Kuniaki, NABAE Akira, MATSUO Akihiro, TOYODA Kuniaki, MITSUHASHI Ryuichi, SATORI Shin, NAGATA Harunori, The Proceedings of Conference of Hokkaido Branch, 2002, 42, 20, 21, 05 Oct. 2002
The launching project of a hybrid rocket from Taiki Multi-purpose Aerospace Park has been conducted by the research groups in the universities in Hokkaido. In the plan, after the flight in outer space, the rocket is taken back using a parafoil-glider with of GPS (Grobal Positioning System). The present study deals with the development of the winged vehicle to obtain the basic materials of the parafoil-glider system., The Japan Society of Mechanical Engineers, Japanese

Promotion of Detonation Wave Propagation by a Reflecting Board : Effect of the Distance between the Shock-tube Exit and the Reflecting Board
WAKITA Masashi, NUMAKURA Ryusuke, NAGATA Harunori, TOTANI Tusyoshi, KUDO Isao, The Proceedings of Conference of Hokkaido Branch, 2002, 42, 82, 83, 05 Oct. 2002
Quick initiation of a detonation wave in a combustion chamber is important to realize a high-performance pulse detonation engine. A possible method is to generate a detonation wave in a shock-tube and release the detonation wave into the chamber. In this paper, a reflecting board is installed in the combustion chamber near the shock-tube exit where the pipe diameter expands sharply. It prevents the detonation wave disappearing at the expanding area near the shock tube exit. The relation of the cell size at the shock-tube exit and the distance between the shock-tube exit and the reflecting b..., The Japan Society of Mechanical Engineers, Japanese

Gasification of solid fuel pellets in a pressurized combustion chamber
FUJII Atsushi, KURITA Shinichiro, NAGATA Harunori, TOTANI Tsuyoshi, KUDO Isao, The Proceedings of Conference of Hokkaido Branch, 2002, 42, 86, 87, 05 Oct. 2002
The authors have been proposed staged combustion hybrid rocket to overcome defects of conventional hybrid rockets such as low combustion efficiency, Isp loss due to O/F shift, and poor throttling characteristics. This hybrid rocket mainly consists of primary and secondary combustion chambers. The primary combustion chamber, which generates fuel-rich combustion gas, functions as a fuel tank and contains unsaturated polyester resin pellets as solid fuels. Experimental results show that O/F in the primary combustion chamber is independent of oxygen flow rate if the residence time is long enoug..., The Japan Society of Mechanical Engineers, Japanese

Conceptual design of Jupiter probe using TOPAZ reactor
KATO Kentaro, NAGATA Harunori, TOTANI Tsuyoshi, KUDO Isao, The Proceedings of Conference of Hokkaido Branch, 2002, 42, 104, 105, 05 Oct. 2002
The purpose of this conceptual study is to design a Jupiter probe for investigating the origin of Great Red Spot which has continued to exist on the planet for more than 300 years. The probe is equipped with TOPAZ, Russian nuclear reactor which is used for a power source for ion thrusters which must shorten the interplanetary time of flight from an orbit whose radius is the sphere of influence of the Earth to Jovian orbit and for one for mission equipments observing the Great Red where solar power is quite faint., The Japan Society of Mechanical Engineers, Japanese

Development of a Winged Vehicle for Fly-back Hybrid-rocket : Development of the Launch Equipment for a Winged Vehicle
SHIBA Kuniaki, SHIMOOKA Ayako, MATSUO Akihiro, NABAE Akira, TOYODA Kuniaki, SATORI Shin, MITSUHASHI Ryuichi, NAGATA Harunori, The Proceedings of Conference of Hokkaido Branch, 2002, 42, 110, 111, 05 Oct. 2002
The launching project of a hybrid rocket from Taiki Multi-purpose Aerospace Park has been conducted by the research groups in the universities in Hokkaido. In the plan, after the flight in outer space, the rocket is taken back using a parafoil-glider with of GPS (Grobal Positioning System). The present study deals with the development of the winged vehicle to obtain the basic materials of the parafoil-glider system., The Japan Society of Mechanical Engineers, Japanese

Interactive combustion of two-dimensionally arranged quasi-droplet clusters under microgravity
H Nagata, Kudo, I, K Ito, S Nakamura, Y Takeshita, COMBUSTION AND FLAME, 129, 4, 392, 400, Jun. 2002
English

Fly-Back Style Winged Vehicle Control Experiment for Hybrid Rocket
三橋龍一, 佐鳥新, 中村直紀, 芝邦明, 下岡彩子, 大滝誠一, 豊田国昭, 永田晴紀, 宇宙科学技術連合講演会講演集, 46th, Pt.3, 2002

Performance of droplet generator and droplet collector in liquid droplet radiator under microgravity
T Totani, M Itami, H Nagata, Kudo, I, A Iwasaki, S Hosokawa, MICROGRAVITY SCIENCE AND TECHNOLOGY, 13, 2, 42, 45, 2002
English

A new era of the hybrid rocket
Ryojiro Akiba, Takashi Nakajima, Harunori Nagata, Advances in the Astronautical Sciences, 110, 325, 329, 01 Jan. 2002

Opposed-flow flame spread in a circular duct of a solid fuel: Influence of channel height on spread rate
Nozomu Hashimoto, Satoshi Watanabe, Harunori Nagata, Tsuyoshi Totani, Isao Kudo, Proceedings of the Combustion Institute, 29, 1, 245, 250, 2002
Elsevier Ltd, English

Performance of droplet emittor for liquid droplet radiator under microgravity
Tsuyoshi Totani, Masahiro Itami, Shigeru Yabuta, Harunori Nagata, Isao Kudo, Akira Iwasaki, Shunsuke Hosokawa, Nippon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B, 68, 668, 1166, 1173, 2002
Japan Society of Mechanical Engineers, Japanese

Performance test under microgravity on a centrifugal droplet collector for liquid droplet radiator
Tsuyoshi Totani, Masahiro Itami, Shigeru Yabuta, Harunori Nagata, Isao Kudo, Akira Iwasaki, Shunsuke Hosokawa, Nippon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B, 68, 674, 2780, 2787, 2002
Japan Society of Mechanical Engineers, Japanese

Development of a Winged Vehicle for Fly-back Hybrid-rocket
SHIBA Kuniaki, SHIMOOKA Ayako, TOYODA Kuniaki, OHTAKI Seiichi, SATORI Shin, MITSUHASHI Ryuichi, NAGATA Harunori, The proceedings of the JSME annual meeting, 2002, 0, 339, 340, 2002
The launching project of a hybrid rocket from Taiki Multi-purpose Aerospace Park has been conducted by the research stuffs in the universities in Hokkaido. In this plan, after the flight in outer space, the rocket is taken back using a parafoil-glider with of GPS (Grobal Positioning System). The present study deals with the development of the winged vehicle to obtain the basic materials of the parafoil-glider system., The Japan Society of Mechanical Engineers, Japanese

Preliminary Study of the Staged Combustion Hybrid Rocket with N_2O as Oxidizer
KURITA Shinitirou, TOYODA Kuniaki, Aoki Yosinori, AKIBA Ryojiro, FUJII Atushi, NAGATA Harunori, The proceedings of the JSME annual meeting, 2002, 0, 343, 344, 2002
The basic experiments have been conducted to develop the staged combustion hybrid-rocket engine with two combustion chambers. In the present study, in order to understand the characteristics of the oxidizer (N_2O), the dependency on temperature was measured and the self-pressurizing supply system was tested. Moreover the combustion test was carried out. The results reveal that N_2O is useful as oxidizer of the hybrid-rocket engine., The Japan Society of Mechanical Engineers, Japanese

Development and Launch Test of a Jet Impinging Type Hybrid Rocket Engine
NAGATA Harunori, TOTANI Tsuyoshi, KUDO Isao, ITO Kenichi, OOWADA Yoichi, NAKAYAMA Hisahiro, WATANABE Mikio, SATORI Shin, TAKADA Takeshi, SHIBA Kuniaki, TOYODA Kuniaki, NAKASUKA Shinichi, MIYAMURA Norihide, The proceedings of the JSME annual meeting, 2002, 0, 345, 346, 2002
A joint research team of universities has been organized to develop small-scale reusable launch systems based on new type of hybrid rockets. This paper describes the project outline, development study of a new type of hybrid rocket engine, and the result of a ballistic test launch using this engine. The key design of the new type hybrid rocket engine, designated as Jet Impinging type Hybrid Rocket, is that the gas flow collides with the solid fuel surface to accelerate the heat transfer to the fuel, resulting in improved thrust level. Static firing tests with an engineering model engine with a LOX cooling system showed sufficiently prompt ignition and stable combustion. Based on these results, a flight model engine was developed to conduct a ballistic test launch. The engine worked excellently in the test launch and the result was successful, showing that te engine showed expected performance in the flight condition., The Japan Society of Mechanical Engineers, Japanese

Ignition of Fuel Particle Cluster in High Temperature Environment under Microgravity Condition
NAGATA Harunori, FUJII Atsushi, ITO Kenichi, TOTANI Tsuyoshi, KUDO Isao, The proceedings of the JSME annual meeting, 2002, 0, 3, 4, 2002
Ignition delays of fuel particle clusters that are inserted in a high-temperature environment are measured by changing the ambient temperature and the interval between fuel particles. To eliminate the effect of natural convection on the phenomena, ignition experiments are conducted under microgravity conditions. A qualitative discussion using numerical results about the ignition of a spherical cluster of fuel particles is made also to interpret the experimental results. Main conclusions obtained are in the followings. Ignition delay of a fuel particle cluster quickly immersed into a hot environment has a minimum at a certain interval between particles, and the minimum ignition delay is shorter than that of a single particle. This ignition delay behavior is common to previous results reported for droplet array ignition. The cause of this behavior is the long characteristic reaction time compared to the characteristic fuel mass transfer rate. Depending on the ambient temperature, the following two phenomena occur : (1) The ignition delay becomes minimum for a larger particle interval with increasing the ambient temperature because the volatilization time, which decreases with increasing the particle interval, is more dominant with increasing the ambient temperature. For higher ambient temperatures, the ignition delay is expected to decrease monotonically with increasing the particle interval because the reaction time should be negligible small comparing with the volatilization time. (2) An envelope flame appears for a larger particle interval with decreasing the ambient temperature because more amount of fuel gas is accumulated around the cluster at ignition for lower ambient temperatures., The Japan Society of Mechanical Engineers, Japanese

Fuel Regression Characteristics of Porous Solid Fuels for End-Burning Hybrid Rocket
WATANABE Satoshi, HASHIMOTO Nozomu, NAGATA Harunori, TOTANI Tsuyoshi, KUDO Isao, The Proceedings of Conference of Hokkaido Branch, 2002, 0, 84, 85, 2002
Because of some defects, such as low combustion efficiency and O/F shift, Hybrid Rocket Motors have not been practicable yet. To overcome these defects of conventional Hybrid Rocket Motors, End-Burning Hybrid Rocket Motor has been suggested. In this rocket motor, oxidizer gas is injected from one side of a porous solid fuel grain and combustion occurs on the other side. If the oxidizer flow velocity in the gaps of the porous solid fuel is sufficiently high, the flame cannot spread into these gaps. This type of combustion is called Stabilized Combustion. Understanding of fuel regression characteristics is important to develop the End-Burning Hybrid Rocket Motor. In this paper, the fuel regression characteristics of porous solid fuels are investigated experimentally, and feasible arrangement of the gaps in the porous solid fuel for End Burning Hybrid Rocket Motor is shown., The Japan Society of Mechanical Engineers, Japanese

Hydrogen concentration measurements of supersonic hydrogen-air shear layer using catalytic reaction
Takakage Arai, Jiro Kasahara, Fuminori Sakima, Junji Miura, Takayuki Ami, Harunori Nagata, 10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference, 01 Dec. 2001

Reusable launch vehicle concepts based on hybrid rockets
Kazuhide Mizobataj, Shimon Narita, Jan Nakaya, Hiroshi Yoshida, Takakage Arai, Jiro Kasahara, Harunori Nagata, Ken'ichi Ito, Ryojiro Akiba, Yooichi Oowada, 10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference, 01 Dec. 2001

Baseline Design and Flight Capability Predictions for Reusable Winged Hybrid Rocket System
Mizobata Kazuhide, nakaya Jun, Narita Shimon, Yoshida Hiroshi, Sugiyama Hiromu, Nagata Harunori, Ito Ken'ichi, Akiba Ryojiro, Oowada Yooichi, Memoirs of the Muroran Institute of Technology, 51, 0, 91, 97, 30 Nov. 2001
Hybrid rocket motors, propelled by a combination of a solid fuel and a liquid oxidizer,are best suited to development of small launch systems in university laboratories,becauee af their advantageous characteristics such as Bafety, easy handling. and lawcosts. The performance of hybrid rocket motors of three classes of thrust - 10tonf,1tonf, and 200kgf - is estimated. The feasibility of reusable winged launch systemsbased on the three motors is prelirninarily analyzed for suborbital micro-gravityexperiments. The results tell that a sysbem with a 10tonf-class motor by a coolant bleedcycle wit..., Muroran Institute of Technology, Japanese

固体燃料端面で燃焼するハイブリッドロケットの燃焼特性
橋本望, 渡辺賢, 永田晴紀, 戸谷剛, 工藤勲, 燃焼シンポジウム講演論文集, 39th, 511-512, 01 Nov. 2001
Japanese

713 Development of Aerial Vehicle for Fly-back Hybrid-Rocket : The Avionics of the Winged Vehicle control
TAKADA Tuyoshi, TOYODA Kuniaki, OHTAKI Seiichi, MITSUHASHI Ryuichi, SATORI Sin, NAGATA Harunori, AOKI Yoshinori, 北海道支部講演会講演概要集, 2001, 41, 254, 255, 25 Sep. 2001
The launching project of a hybrid rocket from Taiki Multi-purpose Aerospace Park as an Experimental base is developing by the research stuffs in the Universities in Hokkaido. In this plan, after the flight in outer space, rocket is taken back using a Parafoil-glider Making use of GPS (Global Positioning System). To testify the system, an experiment is Conducted by using Radio-controlled model airplanes equipped GPS system., 一般社団法人日本機械学会, Japanese

707 A Performance Test on Circulation of Working Fluid in Liquid Droplet Radiator Under Microgravity
YABUTA Shigeru, MIYAMOTO Takuya, TOTANI Tsuyoshi, NAGATA Harunori, KUDO Isao, IWASAKI Akira, HOSOKAWA Syunsuke, The Proceedings of Conference of Hokkaido Branch, 2001, 41, 238, 239, 25 Sep. 2001
Liquid Droplet Radiator (LDR) is an advanced and light weight radiator for high power space systems that will be prerequisite for large space structures superseding the traditional heat-pipe radiator. LDR consists of 3 elements that are a droplet generator, a droplet collector and a gear pump. The results of performance tests of 3 elements conducted respectively under microgravity confirm that these devices can function properly under weightless condition. This paper describes performance tests on circulation of working fluid in LDR conducted under microgravity and supplementary experiments..., The Japan Society of Mechanical Engineers, Japanese

709 Measurement of Catalytic Heat Release Rate of Hydrogen-Air Premixture Gas on Platinum Wire at the Unsteady Field behind a Shock Wave
NAKAMURA Daisuke, NAGATA Harunori, TOTANI Tsuyoshi, KUDO Isao, The Proceedings of Conference of Hokkaido Branch, 2001, 41, 242, 243, 25 Sep. 2001
Catalytic combustion is a candidate for an apparatus to stabilize and promote combustion for a Scramjet engine that is a strong candidate for thrusters of space planes and supersonic airplane in the next generation. However, the mechanism of catalytic combustion in the supersonic flow has hardly been clarified because there are little cases of the research on catalytic combustion in the supersonic flow, especially at the unsteady Field. In this research, we tried to measure catalytic heat release rate at the unsteady flow behind a shock wave using Ni or Pt prove and a shock tube. The temper..., The Japan Society of Mechanical Engineers, Japanese

712 A Reusable Hybrid Rocket System : Its Nominal Design and Flight Capability Predictions
YOSHIDA Hiroshi, NAKAYA Jun, MAEDA Naoki, MIZOBATA Kazuhide, SUGIYAMA Hiromu, NAGATA Harunori, ITOH Ken'ichi, AKIBA Ryojiro, OOWADA Yoichi, The Proceedings of Conference of Hokkaido Branch, 2001, 41, 252, 253, 25 Sep. 2001
Hybrid rocket motors, propelled by a combination of a solid fuel and a liquid oxidizer, are best suited to development of small launch systems in university laboratories, because of their advantageous characteristics such as safety, easy handling, and low costs. The performance of hybrid rocket motors of three classes of thrust - 10tonf, 1tonf, and 200kgf- is estimated. The feasibility of reusable winged launch systems based on the three motors is preliminarily analyzed for suborbital micro-gravity experiments. The results tell that a system with a 10tonf-class motor by a coolant bleed cycl..., The Japan Society of Mechanical Engineers, Japanese

714 Development of an Aerial Vehicle for Fly-back Hybrid-rocket : on Parachute and Winged vehicle
SHIBA Kuniaki, SHIMOOKA Ayako, TOYODA Kuniaki, OHTAKI Seiichi, SATORI Sin, AOKI Yoshinori, NAGATA Harunori, 日本機械学会北海道支部講演会講演概要集, 2001, 41, 256, 257, 25 Sep. 2001
The launching project of a hybrid rocket from Taiki Multi-purpose Aerospace Park as an experimental base is conducted by the research stufls in the universities in Hokkaido. In this plan, after the flight in outer space, the rocket is taken back using a parafoil-glider making use of GPS(Grobal Positioning System). The present study deals with the development of the parachute and the winged vehicle to obtain the basic materials of the parafoil-glider system., The Japan Society of Mechanical Engineers, Japanese

715 Development of an Aerial Vehicle for Fly-back Hybrid-rocket : Radio-controlled Experiment Using GPS System
OHTAKI Seiichi, TOYODA Kuniaki, SHIBA Kuniaki, MITSUHASHI Ryuichi, IMAI Noriaki, SASAKI Daisuke, SATORI Sin, AOKI Yoshinori, NAGATA Harunori, 日本機械学会北海道支部講演会講演概要集, 2001, 41, 258, 259, 25 Sep. 2001
The launching project of a hybrid rocket from Taiki Multi-purpose Aerospace Park as an experimental base is conducted by the research stufls in the universities in Hokkaido. In this plan, after the flight in outer space, the rocket is taken back using a parafoil-glider making use of GPS (Grobal Positioning System). To testify the system, an experiment is conducted by using Radio-controlled model airplanes equipped GPS system., The Japan Society of Mechanical Engineers, Japanese

719 Preliminary Study of the Staged Combustion Hybrid Rocket
AOKI Yoshinori, HUJII Atushi, NAGATA Harunori, KAYUTA Seiyu, KURITA Shinichirou, TOYODA Kuniaki, Akiba Ryojiro, SUGIKI Ted Mitsuteru, The Proceedings of Conference of Hokkaido Branch, 2001, 41, 266, 267, 25 Sep. 2001
The staged combustion hybrid rocket is under development by our research group since 1999. This hybrid rocket engine consists of two combustion chambers. The primary combustion chamber is the lower part of the very fuel tank itself filled with granular solid fuels. The fuel rich gas generated by the first stage combustion flows into the secondary combustion chamber, which is located in the bottom core part of the primary combustion chamber. The additional oxidizer is injected to the secondary combustion chamber in order to attain an optimal specific impulse by completing combustion. This ne..., The Japan Society of Mechanical Engineers, Japanese

720 Static Test Firings of Jet-Impinging Hybrid Rocket for Flight Model Design
NAKAYAMA Hisahiro, WATANABE Mikio, NAGATA Harunori, KUDO Isao, TOTANI Tsuyoshi, The Proceedings of Conference of Hokkaido Branch, 2001, 41, 268, 269, 25 Sep. 2001
The authors have proposed a new fuel configuration to overcome defects of conventional hybrid rockets such as low thrust level and low combustion efficiency. This new fuel configuration allows mixing and combustion to occur around jet-impinging points on forward ends of solid fuels. In the previous researches with cylindrical PMMA blocks as fuel, LOx was employed as oxidizer and ignition and combustion characteristics are investigated. As the result, good ignition characteristics and steady combustion with LOx were confirmed. In the present research, the engineering model of jet-impinging h..., The Japan Society of Mechanical Engineers, Japanese

熱工学 : 機械工学年鑑(2000年)
西尾 茂文, 長坂 雄次, 鈴木 雄二, 笹口 健吾, 山田 雅彦, 長崎 孝夫, 太田 淳一, 円山 重直, 松島 均, 前川 透, 大中 逸雄, 伊藤 献一, 小林 成嘉, 長谷 耕志, 小住 敏之, 山下 卓也, 神原 信志, 永田 晴紀, 日本機械学會論文集. B編, 67, 660, 1881, 1890, 25 Aug. 2001
一般社団法人日本機械学会, Japanese

Flight Body Radio Induction Experiment for Hybrid Rocket Collection System
Mitsuhashi Ryuichi, Imai Noriaki, Sasaki Daisuke, Shiba Kuniaki, Ohtaki Seiichi, Satori Shin, Aoki Yoshinori, Nagata Harunori, Proceedings of the IEICE General Conference, 2001, 1, 239, 07 Mar. 2001
The Institute of Electronics, Information and Communication Engineers, Japanese

Space Development Activities in the Field of University Education in Hokkaido Area.
伊藤献一, 永田晴紀, 佐鳥新, 溝端一秀, 日本航空宇宙学会年会講演会講演集, 32nd, 2001

反射板による爆轟波の再点火機構に関する研究
永田晴紀, 平成12年度衝撃波シンポジウム講演論文集, 383, 386, 2001

Hydrogen concentration of 2-D supersonic air-hydrogen mixing layer using platinum catalytic reaction
Takakage Arai, Jiro Kasahara, Junji Miura, Fuminori Sakima, Harunori Nagata, Nihon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B, 67, 656, 934, 939, 2001
Japan Society of Mechanical Engineers, Japanese

大学連合による小型完全再使用打上げシステムの開発
永田 晴紀, 日本機械学会誌, 104, 990, 337, 337, 2001
一般社団法人 日本機械学会, Japanese

高圧環境下における円筒固体燃料内部の燃え広がりに関する研究
橋本望, 永田晴紀, 戸谷剛, 工藤勲, 燃焼シンポジウム講演論文集, 38th, 511-512, 01 Nov. 2000
Japanese

506 Construction of Virtual Space Research Laboratory and Application to Engineering support
YOSHIKAWA Shigeo, TOTANI Tsuyoshi, NAGATA Harunori, KUDO Isao, The Proceedings of Conference of Hokkaido Branch, 2000, 40, 192, 193, 25 Sep. 2000
Engineering changes have been managed by Configuration Management Provision regulated by such a procurement agency as NASDA or USEF. Recently activities of configuration control board which should be established when ECP is issued seem to be neglected because of complicated procedures and pressure of business of CCB members. For revitalizing the activities, we are developing a virtual environment which supports configuration management, especially engineering changes, using functions of Virtual Space Research Laboratory (VSRL) we have been operating these one year and a half., The Japan Society of Mechanical Engineers, Japanese

510 Ignition Characteristic and Combustion Stability of a Jet-impinging Hybrid Rocket
WATANABE Mikio, NAKAYAMA Hisahiro, NAGATA Harunori, TOTANI Tsuyoshi, KUDO Isao, OHWADA Youichi, The Proceedings of Conference of Hokkaido Branch, 2000, 40, 200, 201, 25 Sep. 2000
The authors have proposed a new fuel configuration to overcome defects of conventional hybrid rockets such as low thrust level and low combustion efficiency. This new fuel configuration allows mixing and combustion to occur around jet-impinging points on forward ends of solid fuels. Previous researches with cylindrical PMMA blocks as fuel and gas oxygen as oxidizer revealed that the regression rates of forward ends increase due to the effect of impinging jet. In the present research, LOX was employed as oxidizer and ignition and combustion characteristics are investigated. Additionally, we ..., The Japan Society of Mechanical Engineers, Japanese

512 A Reusable Hybrid Rocket System : Concept Outlines and Feasibility of Winged Flights
NARITA Shimon, MIZOBATA Kazuhide, SUGIYAMA Hiromu, YOSHIDA Hiroshi, NAGATA Harunori, ITOH Ken'ichi, AKIBA Ryojiro, OOWADA Yoichi, The Proceedings of Conference of Hokkaido Branch, 2000, 40, 204, 205, 25 Sep. 2000
Hybrid Rocket systems, propelled by a combination of a solid propellant and liquid oxidizer, have significant advantages such as safety, easy handling and low costs. A joint team has been organized by Hokkaido University, Muroran Institute of Technology, Hokkaido Institute of Technology, Tokai University, Tokyo Metropolitan Institute of Technology, National Space Development Agency, Japan, and some private sectors, so as to investigate the feasibility of suborbital/orbital reuseable hybrid rocket systems. A preliminary analysis of the rocket motor performance and winged flight trajectories ..., The Japan Society of Mechanical Engineers, Japanese

514 Response Time of the Hydrogen Concentration Probe for a Supersonic Flow
SASAKI Masahiro, NAKAMURA Daisuke, NAGATA Harunori, TOTANI Tsuyosi, KUDO Isao, The Proceedings of Conference of Hokkaido Branch, 2000, 40, 208, 209, 25 Sep. 2000
The authors have proposed a new simple method using catalytic reaction on platinum wire to evaluate hydrogen concentrations in a hydrogen-air supersonic flow without the need for costly apparatus. In this research, in order to verify availability of the probe at turbulent mixing field, we attempt to evaluate the response time of the probe in a shock tube. A shock tube generates a shock wave. The response time means a rising time of supplied power when a surface discontinuity of shock wave reaches the probe. Also, we try to examine the relation between response time and hot wire temperature., The Japan Society of Mechanical Engineers, Japanese

516 Experiments of Liquid Droplet Radiator Elements Under Microgravity
YABUTA Shigeru, TOTANI Tsuyoshi, NAGATA Harunori, KUDO Isao, ITAMI Masahiro, IWASAKI Akira, HOSOKAWA Syunsuke, The Proceedings of Conference of Hokkaido Branch, 2000, 40, 212, 213, 25 Sep. 2000
Liquid Droplet Radiator (LDR) is an advanced radiator for high power space systems that will be prerequisite for large space structures (LSS). LDR consists of 3 elements, droplet generator, droplet collector and gear pump. Many studies on performance of LDR have been done at the ground. But LDR must work in space, under weightless condition. Only few performance tests of LDR have been made under microgravity. We have made performance tests of LDR's 2 elements which are droplet generator and droplet collector under microgravity, and have got a certain results. In this year, we will test abou..., The Japan Society of Mechanical Engineers, Japanese

517 A Study on the Ignition of a cluster of Coal particles under Microgravity
NIWA Yukiko, NAGATA Harunori, TOTANI Tsuyoshi, KUDO Isao, The Proceedings of Conference of Hokkaido Branch, 2000, 40, 214, 215, 25 Sep. 2000
The purpose of this study is to investigate mutual influences of fine coal particles in a coal dust cloud on the ignition process. Ignition processes of a cluster of four coal particles in high temperature atmosphere are observed. Spherical active carbons impregnated with salicylic acid are employed as fuel particles. Four fuel particles are arranged on tops of a regular tetrahedron. To remove the influence of the natural convention, experiments are made under microgravity. As a result, a bright luminous flame is observed with a small interval of fuel particles. This is because the density ..., The Japan Society of Mechanical Engineers, Japanese

A NEW ERA OF THE HYBRID ROCKET
AKIBA Ryojiro, NAKAJIMA Takashi, NAGATA Harunori, The Journal of space technology and science : a publication of Japanese Rocket Society, 16, 2, 1, 5, 01 Sep. 2000, [Peer-reviewed], [International Magazine]
English

Simulation for deployment of an inflatable disk in orbit
K Takahashi, H Nagata, Kudo, I, JOURNAL OF SPACECRAFT AND ROCKETS, 37, 5, 707, 708, Sep. 2000
English

B110 EFFECTS OF COAL PARTICLES SEEDING ON BURNING VELOCITY OF METHANE-AIR MIXTURES(Droplet/particle combustion-2) :
NAGATA Harunori, FUJITA Osamu, ITO Kenichi, KUDO Isao, TAKESHITA Yasuhiro, Proceedings of the ... JSME-KSME Thermal Engineering Conference, 1, "1, 151"-"1-155", 2000
This paper describes experimental and numerical studies about effects of coal particles seeding on flame propagation velocity and burning velocity of lean methane-air mixtures. To produce uniform coal dust clouds and to eliminate the buoyancy effect, experiments are carried out under microgravity environment, being obtained with the 500-m drop shaft of Japan Microgravity Center (JAMIC). Experimental and numerical results reveal that seeding of an appropriate amount of coal particles increases flame propagation velocity. In spite of this, the increase of burning velocity is almost zero or very small. Accordingly, the main cause of the enhancement of flame propagation velocity is the gas expansion due to coal combustion behind the methane-air flame. This is because coal combustion is nearly isolated from methane combustion in conditions investigated in this study., 日本機械学会, English

Evaluation of mass transfer coefficient and hydrogen concentration in supersonic flow by using catalytic reaction
H Nagata, M Sasaki, T Arai, T Totani, Kudo, I, PROCEEDINGS OF THE COMBUSTION INSTITUTE, 28, 713, 719, 2000
English

511 Combustion stability of End-Burning Hybrid Rocket
HASHIMOTO Nozomu, NAGATA Harunori, TOTANI Tsuyoshi, KUDO Isao, The Proceedings of Conference of Hokkaido Branch, 2000, 0, 202, 203, 2000
To overcome defects of conventional hybrid rockets such as low combustion efficiency and the O/F shift during the combustion, the authors have proposed a new form of hybrid rocket fuel. The fuel is a fibrous bed in which oxidizer gas flows. Stable diffusion flame appears at the exit surface. Previous researches show that sudden increase of the fuel regression rate occurs with the increase of ambient pressure. This sudden increase is attributed to the flame spreading between fuel fibers. To clarify the limit of fuel gap space the diffusion flame can spread into, experimental study was made. Critical gap space, which means the minimum gap space the diffusion flame can spread into, was obtained experimentally as a function of oxygen gas flow velocity and ambient pressure. Using this result, necessary conditions to realize a stable combustion with this new fuel form are shown., The Japan Society of Mechanical Engineers, Japanese

Kazuhide MIZOBATA, Harunori NAGATA, Kenichi ITO, Ryojiro AKIBA, Isao KUBOTA, "A Reusable Hybrid Rocket System: Concept Outlines and Feasibility of Winged Flights," Proceedings of the 22nd International Symposium on Space Technology and Science, Vol.2, ・・・　　　　　　　　　　　　　　　
2000
Kazuhide MIZOBATA, Harunori NAGATA, Kenichi ITO, Ryojiro AKIBA, Isao KUBOTA, "A Reusable Hybrid Rocket System: Concept Outlines and Feasibility of Winged Flights," Proceedings of the 22nd International Symposium on Space Technology and Science, Vol.2, pp.1334-1340, 2000.

Harunori NAGATA, Mikio WATANABE, Takashi SANDA, Shin SATORI, Yoshinori AOKI, Isao KUDO, Ryojiro AKIBA, Isao KUBOTA, "Improvement of Fuel Regression Rate by Impinging Jet for High Thrust Hybrid Rocket Motors," Proceedings of the 22nd International Sympo・・・　　　　　　　　　　　　　　　
2000
Harunori NAGATA, Mikio WATANABE, Takashi SANDA, Shin SATORI, Yoshinori AOKI, Isao KUDO, Ryojiro AKIBA, Isao KUBOTA, "Improvement of Fuel Regression Rate by Impinging Jet for High Thrust Hybrid Rocket Motors," Proceedings of the 22nd International Symposium on Space Technology and Science, Vol.1, pp.121-126, 2000.

Shin SATORI, Harunori NAGATA, Yoshinori AOKI, Ryojiro AKIBA, Isao KUDO, Isao KUBOTA, "Preliminary Study for Staged Combustion Hybrid Rocket," Proceedings of the 22nd International Symposium on Space Technology and Science, Vol.1, pp.116-120, 2000.　　　　　　　　　　　　　　　
2000

Yoshinori AOKI, Shin SATORI, Kunihiko TAHARA, Hayato MAEDA, Takehisa MURATA, Harunori NAGATA, Ryojiro AKIBA, Isao KUBOTA, "Measuring of the Hybrid Rocket Combustion by Spectrum Mesurement," Proceedings of the 22nd International Symposium on Space Techn・・・　　　　　　　　　　　　　　　
2000
Yoshinori AOKI, Shin SATORI, Kunihiko TAHARA, Hayato MAEDA, Takehisa MURATA, Harunori NAGATA, Ryojiro AKIBA, Isao KUBOTA, "Measuring of the Hybrid Rocket Combustion by Spectrum Mesurement," Proceedings of the 22nd International Symposium on Space Technology and Science, Vol.2, pp.127-132, 2000.

Critical Diameter of Diffusion Flames in Solid Cylindrical Fuels.
KATO TAKAHIRO, HASHIMOTO NOZOMU, NAGATA HARUNORI, KUDO ISAO, 日本機械学会北海道支部講演会講演概要集, 39th, 132-133, 25 Sep. 1999
Japanese

Hydrogen Concentration Measurements in Hydrogen-air Supersonic Mixing Flow using Constant Temperature Type Pt Probe
ARAI Takakage, MIURA Junji, SAKIMA Fuminori, NAGATA Harunori, 年会一般講演, 18, 0, 113, 114, 29 Jul. 1999
Japanese

Evaluation of supersonic turbulent mixing using catalytic combustion of constant temperature Pt wire
T Arai, H Nagata, A Endo, H Sugiyama, S Morita, H Hosokawa, JSME INTERNATIONAL JOURNAL SERIES B-FLUIDS AND THERMAL ENGINEERING, 42, 1, 65, 70, Feb. 1999
English

触媒反応を利用した超音速流中水素濃度プローブに関する研究
永田晴紀, 第9回ラム/スクラムジェットシンポジウム議論集, 239, 244, 1999

Experimental investigation of inclined hydrogen injection into a supersonic flow
Takakage Arai, Hideo Fukuzoe, Junji Miura, Harunori Nagata, Hiroshi Hosokawa, 9th International Space Planes and Hypersonic Systems and Technologies Conference, 1, 7, 01 Jan. 1999

Evaluation of hydrogen concentration of supersonic flow using catalytic reaction on Pt wire
Harunori Nagata, Yasuhiko Sakai, Moto-Omi Iwatsuki, Syuji Morita, Isao Kudo, Nihon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B, 65, 636, 2666, 2671, 1999
Japan Society of Mechanical Engineers, Japanese

Evaluation of supersonic turbulent mixing using catalytic combustion of constant temperature pt wire
Takakage Arm, Harunori Nagata, Akira Endo, Hiromu Sugiyama, Shuji Morita, Hiroshi Hosokawa, Nihon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B, 64, 619, 793, 799, 01 Dec. 1998
The Japan Society of Mechanical Engineers, Japanese

Mixing of H_2 Transverse Injection in Supersonic Flow
ARAI Takakage, MORITA Shuji, FUKUZOE Hideo, NAGATA Harunori, 年会一般講演, 17, 0, 239, 240, Jul. 1998
Japanese

反射板によるデトネーション波の伝播促進に関する研究
永田晴紀, 平成10年度衝撃波シンポジウム, 1998

H2 concentration profile in cold supersonic hydrogen-air mixing layer*
Takakage Arai, Shuji Mortta, Harunori Nagata, Hiromu Sugiyama, 8th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 645, 650, 01 Jan. 1998

Catalytic Combustion in Cold Supersonic Mixing Layer
ARAI Takakage, NAGATA Harunori, SUGIYAMA Hiromu, MORITA Shuji, HOSOKAWA Hiroshi, 年会一般講演, 16, 0, 263, 264, Jul. 1997
Japanese

A Study on Supersonic Combustion of Slot-injected Fuel in a Rectangular Model Combustor.
TOMIOKA Sadatake, TAGUCHI Hideyuki, NAGATA Harunori, TAKAHASHI Shuuhei, UJIIE Yasushige, KONO Michikata, Aeronautical and Space Sciences Japan, 42, 483, 243, 250, 1994
Supersonic combustion in a rectangular duct was investigated experimentally. Hydrogen fuel was injected parallel to an air flow from a two-dimensional slot injector. Two-dimensional flame was established downstream of the injector and so-called precombustion shock was observed. The shock wave originated at separation region in air flow boundary layer upstream of the injector. The relationship between the strength and the position of the shock wave was different from that in perpendicular injection case. In slot injection case, it is supposed that the separation region and reacting region interacted to act as a large wedge and generate the rather strong shock. Combustion without generation of the precombustion shock was achieved with conversion duct. However, the combustion efficiency was low and the ignition delay distance was large in this case. The shock wave was expected to enhance the reaction by rising the static temperature and pressure., THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, Japanese

A Study on Supersonic Combustion Using Methane-Hydrogen Mixture Fuel.
TAGUCHI Hideyuki, TOMIOKA Sadatake, NAGATA Harunori, TAKAHASHI Shuuhei, UJIIE Yasushige, KONO Michikata, Aeronautical and Space Sciences Japan, 42, 483, 224, 231, 1994
In order to attain combustion of methane fuel in supersonic airstreams of relatively low temperature, hydrogen fuel was added to the fuel as a ignition promotor. In experiments, rectangular combustor with backward step was adopted and the methane-hydrogen mixture fuel was injected into supersonic airstreams. The region where the self-ignition occurs was confirmed by high speed direct photographs, and self-ignition characteristics were investigated with parameters of equivalence ratio and fraction of hydrogen in the fuel. The injection form was refined with use of the obtained results to attain self-ignition with low fraction of hydrogen. The combustion of methane-hydrogen mixture fuel was compared with that of hydrogen fuel by using wall static pressure distributions and OH/CH emission images of the flame. As results, it is confirmed that the combustion of methane fuel in the airstreams is obtained by addition of hydrogen fuel, and it is considered that the self-ignition in refined injection form is obtained under same conditions as that of hydrogen fuel, independently of the fraction of hydrogen in total injected fuels. The static pressure distribution and the flame shape in methane-hydrogen mixture fuel case were similar to those in hydrogen fuel case., The Japan Society for Aeronautical and Space Sciences, Japanese

An experimental and numerical investigation on the hot surface ignition of premixed gases under microgravity conditions
H. Nagata, H. M. Kim, J. Sato, M. Kono, Symposium (International) on Combustion, 25, 1, 1719, 1725, 1994
English

微小重力環境を利用した高温白金線による水素-空気予混合気の点火に関する研究
永田晴紀, 第31回燃焼シンポジウム講演集, 319, 321, 1993

へんてこりんな宇宙図鑑 : おもしろくて、役に立たない!?
岩谷, 圭介, 柏原, 昇店, 永田, 晴紀
キノブックス, Nov. 2018, 9784909689177, 143p, Japanese

みんなが知りたい!『宇宙』のことがわかる本 (まなぶっく)
永田 晴紀
メイツ出版, Jun. 2008, 4780404312, 128, [Supervisor]

高速度濃度履歴が取得可能な超音速流用水素濃度プローブに関する研究
永田, 晴紀
[北海道大学], 2003, 31p

冷却によるグラファイトノズルの浸食抑制効果　　　　　　　　　　　　　　　
吉丸 利,永田 晴紀,伊藤 聖司,Landon T. Kamps
第57回燃焼シンポジウム講演論文集, Nov. 2019
Nov. 2019 - Nov. 2019

アブレータ材料によるハイブリッドロケットノズル浸食抑制に関する研究　　　　　　　　　　　　　　　
奥田 晃崇,Landon T. Kamps,櫻井 和人, 井上 卓,Tor Viscor,内山 絵里香,池田 華子, 吉丸 利,脇田 督司,永田 晴紀
第57回燃焼シンポジウム講演論文集, Nov. 2019
Nov. 2019 - Nov. 2019

Using equivalent burn time to improve regression characterization of the CAMUI type hybrid rocket engine
T. Viscor, H. Nagata
53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017, 01 Jan. 2017
01 Jan. 2017 - 01 Jan. 2017, Burn time errors caused by various start-up transient effects have a large effect on the regression simulation model of the Cascaded Multi Impinging Jet hybrid rocket engine. This paper analyses these burn time errors and their effect on the regression simulations for short burn time engines. To address these the equivalent burn time is then defined as the time the engine would burn if it was burning at steady state level throughout the burn time to achieve the measured total impulse. The accuracy of the regression simulation with and without the use of equivalent burn time are then finally compared. Equivalent burn time alone without at the same time addressing other errors is found to be inadequate to clearly address the burn time errors.

Numerical and experimental investigation of nozzle thermochemical erosion in hybrid rockets
Daniele Bianchi, Landon Kamps, Francesco Nasuti, Harunori Nagata
53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017, 01 Jan. 2017
01 Jan. 2017 - 01 Jan. 2017, Despite some inherent disadvantages, hybrid rockets are today considered as having a great potential to become one of the future generation of propulsion systems, partly due to recent emphasis on propulsion safety, reliability, low development cost, reduced environmental pollution, and greater operability. Nevertheless, the hybrid rocket development has not achieved the same level of maturity as solid and liquid traditional systems. An aspect that has not been much dealt with in the open literature is that of nozzle erosion, whose minimization or reduction is one of the challenges in hybrid rocket propulsion. To this goal, a joint numerical and experimental investigation of nozzle throat erosion has been performed using a computational fluid dynamics approach compared to static firing tests carried out on a 2kN-class lab-scale hybrid rocket burning liquid oxygen and highdensity polyethylene. The numerical approach is able to capture the main features of the nozzle throat erosion behavior, fairly reproducing the throat erosion rate values and its dependence upon the oxidizer to fuel mixture ratio and motor chamber pressure.

Investigation of regression characteristics under relatively high-pressure in Axial-injection End-Burning Hybrid Rockets
Yuji Saito, Masaya Kimino, Tsuji Ayumu, Yushi Okutani, Kazunobu Omura, Hiroyuki Yasukochi, Kentaro Soeda, Tsuyoshi Totani, Masashi Wakita, Harunori Nagata
53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017, 01 Jan. 2017
01 Jan. 2017 - 01 Jan. 2017, This study is an investigation of Axial-Inection End-Burning Hybrid Rockets aimed at revealing fuel regression characteristics under relatively high pressure conditions. Firing tests were conducted using gaseous oxygen as oxidizer at chamber pressures and oxidizer port velocities ranging from 0.22 MPa to 1.05 MPa and 31 m/s to 103 m/s, respectively. The results of fifteen static firing tests show that fuel regression rate increases as the chamber pressure increases, and regression rates ranged from approximately 1.1 mm/s at 0.25 MPa to 5.4 mm/s at 0.71 MPa. Furthermore, it is observed that the fuel regression rate is not influenced by oxidizer port velocity. The athours encountered a problem refered to as backfiring in this paper, and developed a calculation model to investigate this problemanalytically. The calculation model explains why the back-firing problem tends to occur in relatively high-pressure conditions, and leads to the conclusion that increasing nozzle throat diameter is an effective means of preventing back-firing from occuring.

Investigation of graphite nozzle-throat-erosion in a laboratory-scale hybrid rocket using GOX and HDPE
Landon Kamps, Shota Hirai, Yassine Ahmimache, Raymond Guan, Harunori Nagata
53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017, 01 Jan. 2017
01 Jan. 2017 - 01 Jan. 2017, The authors of this paper employ a recently developed reconstruction technique titled nozzle-throat reconstruction technique to investigate graphite nozzle-throat-erosion in a laboratory-scale hybrid rocket motor using gaseous oxygen as an oxidizer and high density polyethylene as a fuel. Fifteen static firing tests were conducted under varying experimental conditions to confirm the validity of the reconstruction technique results, and to collect a wide range of nozzle-throat-erosion data. Furthermore, a technique for carrying out classical finite difference calculations for 1D convective and conductive heating based on the time histories of gas properties as determined by the reconstruction technique is introduced and used to estimate nozzle throat wall temperature history and convective heat transfer coefficient history. Results show a distinct trend where nozzle erosion rates increase in the beginning of a firing test, and subsequently decrease for the remainder of the firing test, even though nozzle throat temperatures continue to increase. It is shown that the decreasing nozzle-throat-erosion rates coincide with decreasing mass fluxes and that the erosion rates in this regime may be sensitive to oxidizer to fuel mass ratio.

Thermal Design of 50kg Class Satellites Deployed from JEM Small Satellite Orbital Deployer J-SSOD
PANES Mitchao Delburg, 戸谷剛, 脇田督司, 永田晴紀
宇宙科学技術連合講演会講演集(CD-ROM), 2017, Japanese
2017 - 2017

2‐amino‐2‐methyl‐1,3‐propanediolの固相‐固相結晶転移による潜熱を利用した蓄熱材の開発 過冷却状態の結晶化による発熱とガラス転移点の関係
後藤凌平, 永田晴紀, 戸谷剛, 脇田督司
日本伝熱シンポジウム講演論文集(CD-ROM), 2017, Japanese
2017 - 2017

ふく射センサの低温環境下でのふく射率および単一液滴流からの排熱量
嶋田泰三, 高梨知広, 両門健人, 戸谷剛, 永田晴紀, 脇田督司
日本伝熱シンポジウム講演論文集(CD-ROM), 2017, Japanese
2017 - 2017

The relationship of chamber pressure and combustion efficiency on hybrid rocket using N2O as an oxidizer
清谷優理香, 山口亮, 櫻井和人, KAMPS Landon, 井上卓, 脇田督司, 戸谷剛, 永田晴紀
宇宙科学技術連合講演会講演集(CD-ROM), 2017, Japanese
2017 - 2017

Feasibility of End-Burning Hybrid Rockets with Liquid Oxygen
津地歩, 齋藤勇士, 尾村和信, 君野正弥, 戸谷剛, 脇田督司, 永田晴紀
宇宙科学技術連合講演会講演集(CD-ROM), 2017, Japanese
2017 - 2017

Fuel Regression Characteristics of Axial-Injection End-Burning Hybrid Rockets Using N2O as an Oxidizer
尾村和信, 津地歩, 齋藤勇士, 君野正弥, 奥谷勇士, 小水弘大, 戸谷剛, 脇田督司, 永田晴紀
宇宙科学技術連合講演会講演集(CD-ROM), 2017, Japanese
2017 - 2017

Study on Hysteresis Characteristics of Axial-Injection End-Burning Hybrid Rockets under Throttling Operation
君野正弥, 齋藤勇士, 津地歩, 尾村和信, 安河内裕之, 添田建太郎, 戸谷剛, 脇田督司, 永田晴紀
宇宙科学技術連合講演会講演集(CD-ROM), 2017, Japanese
2017 - 2017

デトネーション波の衝突・反射による遷移促進効果に関する研究
大関敦, 松岡将司, 桧物恒太郎, 脇田督司, 戸谷剛, 永田晴紀
燃焼シンポジウム講演論文集, 26 Nov. 2016, Japanese
26 Nov. 2016 - 26 Nov. 2016

燃料微小管内を燃え拡がる火炎への雰囲気圧力の影響
横井俊希, 齋藤勇士, 尾村和信, 津地歩, 安河内裕之, 添田建太郎, 脇田督司, 戸谷剛, 永田晴紀
燃焼シンポジウム講演論文集, 26 Nov. 2016, Japanese
26 Nov. 2016 - 26 Nov. 2016

端面燃焼式ハイブリッドロケットの燃料後退モデルに関する考察
齋藤勇士, 横井俊希, 津地歩, 尾村和信, 安河内裕之, 添田建太郎, 戸谷剛, 脇田督司, 永田晴紀
燃焼シンポジウム講演論文集, 26 Nov. 2016, Japanese
26 Nov. 2016 - 26 Nov. 2016

液体酸素を用いた固体燃料管内燃え拡がりに関する研究
津地歩, 齋藤勇士, 横井俊希, 尾村和信, 嶋田泰三, 戸谷剛, 脇田督司, 永田晴紀
燃焼シンポジウム講演論文集, 26 Nov. 2016, Japanese
26 Nov. 2016 - 26 Nov. 2016

ハイブリッドロケットにおけるノズルスロートエロージョン抑制材料に関する研究
山口亮, 川端良輔, 川端良輔, 平井翔大, KAMPS Landon, 脇田督司, 戸谷剛, 永田晴紀
日本機械学会年次大会講演論文集(CD-ROM), 10 Sep. 2016, Japanese
10 Sep. 2016 - 10 Sep. 2016

端面燃焼式ハイブリッドロケットの推力制御特性
永田晴紀, 齋藤勇士, 横井俊希, 嶋田泰三, 安河内裕之, 添田建太郎, 戸谷剛, 脇田督司
日本機械学会年次大会講演論文集(CD-ROM), 10 Sep. 2016, Japanese
10 Sep. 2016 - 10 Sep. 2016

Verification of Thermal Design Procedure for Short-term Development of Micro-satellite
戸谷 剛, 毛利 正宏, 脇田 督司, 永田 晴紀
宇宙科学技術連合講演会講演集, 06 Sep. 2016, 日本航空宇宙学会, Japanese
06 Sep. 2016 - 06 Sep. 2016

F117 Heat Storage and Release Tests of Heat Storage Material with Crystal Transformation
Totani Tsuyoshi, Kuni Takuya, Satoh Toshifumi, Wakita Masashi, Nagata Harunori
Procee[d]ings of Thermal Engineering Conference, 08 Nov. 2014, Japanese
It is desirable that the heat storage materials for nano and micro satellites have the characteristic of not phase change but crystal transformation for the heat storage. Trans-1,4-polybutadien has the desirable characteristic of crystal transformation at the heat storage temperature. The heat storage and release tests were conducted on the ground and in orbit. It is clarified that the heat storage and release characteristics do not change in heat storage and release cycle of 300 times and Trans-1,4-polybutadien can storage and release heat in orbit.

E215 Relation between Radiation Peak and Micro-cavities Shape with Metal Film
Totani Tsuyoshi, Irokawa Toshio, Wakita Masashi, Nagata Harunori
Procee[d]ings of Thermal Engineering Conference, 08 Nov. 2014, Japanese
Micro-cavities were made from Zr dispersing liquid on SiO_2 bases and were coated by Au for generating resonance phenomena. The theoretical wavelength of reflectance drop differed 4% from the experiment data. A numerical analysis taking into account the pitch was carried out to find causes of the difference. The wavelength of reflectance drop in the analysis were closer to experiment data than theoretical predictions. On the other hand, the wavelengths of reflectance drop except for the fundamental vibrational mode obtained in the analysis did not accord 7.6 to 8.5 % with experimental data. The reflectance obtained in the analysis was 4 to 11% different from experimental data.

フライトテストベッドとしてのCAMUI型ハイブリッドロケットの進展
永田晴紀, 植松努, 伊藤献一
宇宙科学技術連合講演会講演集(CD-ROM), 2013, Japanese

高レイノルズ数域におけるCAMUI型固体燃料の後退特性におよぼすスケールの影響
石山達也, 稲場康彦, 寺川健, 遠藤瞳, 永田晴紀, 戸谷剛, 脇田督司
宇宙科学技術連合講演会講演集(CD-ROM), 2013, Japanese

缶サット・超小型衛星を用いた創造的科学技術人育成ネットワークの構築
宮崎康行, 永田晴紀, 木村真一, 佐原宏典, 坂本啓, 川島レイ, 安藤恵美子
宇宙科学技術連合講演会講演集(CD-ROM), 2013, Japanese

超小型衛星の熱設計手順の提案
戸谷剛, DAS Tilok Kumar, 脇田督司, 永田晴紀
宇宙科学技術連合講演会講演集(CD-ROM), 2013, Japanese

北海道スペースポート設置の意義と役割
伊藤献一, 工藤勲, 永田晴紀, 秋葉鐐二郎, 植松努, 田口秀之
日本航空宇宙学会年会講演会講演集(CD-ROM), 2013, Japanese

2次元流れ場のよどみ点近傍におけるPMMA燃料の後退特性
斉藤竜也, 松岡常吉, 寺川健, 脇田督司, 戸谷剛, 永田晴紀
宇宙科学技術連合講演会講演集(CD-ROM), 2013, Japanese

環状爆轟波から平面爆轟波への遷移に流路形状が及ぼす影響
菊地敬太, 桧物恒太郎, 脇田督司, 戸谷剛, 永田晴紀
流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM), 2013, Japanese

液滴流からの放射廃熱量を測定するための数値解析
高梨知広, 脇田督司, 永田晴紀, 戸谷剛
宇宙科学技術連合講演会講演集(CD-ROM), 2013, Japanese

CAMUI型ハイブリッドロケットの作動履歴におけるスケール則の構築
稲場康彦, 石山達也, 金井竜一朗, 脇田督司, 戸谷剛, 永田晴紀
宇宙科学技術連合講演会講演集(CD-ROM), 2013, Japanese

表面微細構造を持つ波長選択性ラジエータ
戸谷剛, 脇田督司, 永田晴紀
日本伝熱シンポジウム講演論文集(CD-ROM), 2013, Japanese

相似形状のCAMUI型ハイブリッドロケットの燃焼特性におけるスケール効果
永田晴紀, 脇田督司, 戸谷剛, 植松努
燃焼シンポジウム講演論文集, 20 Nov. 2012, Japanese

一定レイノルズ数のよどみ点近傍における固体燃料の燃焼速度におよぼす酸化剤流速の影響
寺川健, 永田晴紀, 戸谷剛, 脇田督司, 金子雄大
燃焼シンポジウム講演論文集, 20 Nov. 2012, Japanese

細孔内部を燃え拡がる火炎の消炎限界
松岡常吉, 村上翔太, 中村祐二, 永田晴紀
燃焼シンポジウム講演論文集, 20 Nov. 2012, Japanese

固体表面上燃え拡がりの吹き飛び限界に及ぼす流路断面形状の影響
村上翔太, 松岡常吉, 永田晴紀
燃焼シンポジウム講演論文集, 20 Nov. 2012, Japanese

円筒デトネーション波の遷移及び伝播条件に関する研究
棧敷和弥, 桧物恒太郎, 脇田督司, 戸谷剛, 永田晴紀
燃焼シンポジウム講演論文集, 20 Nov. 2012, Japanese

微小重力環境を利用した固体燃焼現象研究(H23研究班WG報告)
藤田修, 中村祐二, 永田晴紀, 菊池政雄, 伊藤昭彦, 鳥飼宏之, 梅村章, 高橋周平, 池田光優, CHUNG Suk Ho, OLSON Sandra L
宇宙利用シンポジウム, Mar. 2012, Japanese

短期開発を実現する少節点解析と多節点解析を併用した超小型衛星の熱設計法
小川洋人, 井上遼太, 戸谷剛, 脇田督司, 永田晴紀
宇宙科学技術連合講演会講演集(CD−ROM), 2012, Japanese

構造転移により蓄熱する超小型衛星用蓄熱材の開発
戸谷剛, 佐藤敏文, 脇田督司, 永田晴紀
宇宙科学技術連合講演会講演集(CD−ROM), 2012, Japanese

サブオービタル機開発に向けての飛行実験と今後の計画
米本浩一, 相良慎一, 松本剛明, 永田晴紀, 越智徳昌, 石本真二, 麥谷高志, 牧野隆, 木元健一
飛行機シンポジウム講演集(CD−ROM), 2012, Japanese

金属膜を付与した表面微細周期構造の垂直放射率特性
戸谷剛, 石川直幸, 脇田督司, 永田晴紀
日本伝熱シンポジウム講演論文集(CD-ROM), 2012, Japanese

固体燃料管内燃え拡がりにおける固相への熱輸送と消炎現象の関係
村上翔太, 松岡常吉, 永田晴紀, 中村祐二
日本伝熱シンポジウム講演論文集(CD-ROM), 2012, Japanese

大口径パルスデトネーションエンジン用イニシエータにおける円筒デトネーション波の伝播に関する研究
桧物恒太郎, 棧敷和弥, 脇田督司, 戸谷剛, 永田晴紀
流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM), 2012, Japanese

液体酸素を用いる端面燃焼式ハイブリッドロケットの実証研究
科学研究費助成事業
01 Apr. 2022 - 31 Mar. 2026
永田 晴紀, 添田 建太郎, KAMPS LANDON, 脇田 督司
日本学術振興会, 基盤研究(A), 北海道大学, 22H00240

Regenerative cooling of graphite nozzle for hybrid rockets using nitrous oxide as oxidant
Grants-in-Aid for Scientific Research
08 Mar. 2023 - 31 Mar. 2025
永田 晴紀, GALLO GIUSEPPE
液体亜酸化窒素を酸化剤とするハイブリッドロケットエンジンにおける再生冷却システムの信頼性と実現可能性を実験的に調べた。昨年度は極低温の液体酸素を用いて再生冷却ノズルの良好な作動を実験的に実証したが、その結果を更に発展させたものである。本年度の研究の新規性は、ロケットノズルで発生する高い熱流束を適切に管理するための冷却剤として、自身の蒸気圧により加圧供給される液体亜酸化窒素を使用することにある。具体的には、燃焼中にグラファイトノズルを目標温度（1500 K程度）以下に保つことにより、ノズル壁面での浸食を完全に抑止することを目指す。
実験においては、直径が異なるオリフィスを通過させることで液体亜酸化窒素にキャビテーションを発生させることで質量流量を適切に制御し、10回の燃焼試験を実施した。燃焼中に、酸化剤流路の複数個所で冷却剤（亜酸化窒素）の圧力と温度の履歴を取得した。グラファイトノズルに埋め込んだ熱電対により、ノズル壁面からグラファイトノズルへの熱流束の履歴も取得した。
燃焼実験においてグラファイトノズル内部の温度は安定しており、燃焼室圧力が5～30 barの範囲において700～1200 Kの範囲内であった。円筒一次元の定常熱伝導を仮定すると、ノズル壁面の温度は1500 Kを充分に下回っていると予想された。実験条件は過去の研究においてはノズル浸食が発生した条件であるが、全ての実験においてノズル浸食は全く観測されなかった。
キャビテーションオリフィスと冷却流路に沿って温度と圧力の分布を取得し、流路に沿って亜酸化窒素の相変化と熱伝達特性の変化の関係を明らかにした。液体酸素と比較して液体亜酸化窒素は高い冷却能力を示した。最後に、キャビテーションオリフィスの位置がシステム全体の流量特性に及ぼす影響を明らかにした。
Japan Society for the Promotion of Science, Grant-in-Aid for JSPS Fellows, Hokkaido University, 22KF0013

Frequent and Flexible Deep Space Exploration by Innovative Nano/Micro-satellites
Grants-in-Aid for Scientific Research
02 Oct. 2020 - 31 Mar. 2023
船瀬 龍, 永田 晴紀, 尾崎 直哉
本研究領域のため総括班として，2021年度は，引き続き研究コミュニティへの研究成果の発信などの広報活動を行いながら，複数の計画研究から構成される研究領域全体の研究を円滑に進行させた．
本研究領域が最終的に目指すキックモーターを有する超小型探査機システムの構築を見据えて，３つの計画研究（通称，推進班，バス班，軌道班）は，システム全体として物理的，機械的，時間的な境界条件を満たしながら全体としての設計を最適化する必要がある．総括班として，各種オンラインコミュニケーションツールを活用して頻度高く研究会合を開催し，各班の検討の整合性をとりながらタイムリーに各班の進む方向性にフィードバックをかけて，領域全体の研究を進めることができた．
2021年11月には，宇宙科学技術連合講演会にてオーガナイズドセッション「超小型探査機を用いた月以遠深宇宙探査」を開催し，超小型衛星による深宇宙探査を目指す関連コミュニティへ本研究領域の成果発信を実施するとともに，超小型探査機による深宇宙探査に必要な技術シーズや技術実証計画に関する発表，超小型探査機で実施したい科学ミッションのニーズに関する発表も実施され，ニーズ側とシーズ側との間で活発な意見交換が行われた．
また，2022年2月には，本研究領域の成果を活用した具体的な深宇宙ミッションを計画しているGEO-X研究グループの研究会に招待され本研究領域の活動内容等を発表し，利用側のユーザーコミュニティとのコミュニケーションも実施した．その他，各種研究会での招待講演等も通じて，本研究領域の目指す世界の認知向上とコミュニティの拡大に向けて大きな成果をあげることができた．
Japan Society for the Promotion of Science, Grant-in-Aid for Transformative Research Areas (B), Japan Aerospace EXploration Agency, 20H05746

小型宇宙機に革新的軌道変換能力を与えるハイブリッドキックモータの開発
科学研究費助成事業 学術変革領域研究(B)
02 Oct. 2020 - 31 Mar. 2023
永田 晴紀, KAMPS LANDON, 脇田 督司
静止トランスファー軌道まで相乗りし、近地点で1 km/s前後の増速を与えて月、火星、金星等へ向かう超小型深宇宙探査機用のキックモータ（軌道変換用上段ロケット）をハイブリッドロケットにより実現するため、高比推力（適切な燃料／酸化剤流量比）を維持する固体燃料形状設計の自在性、ノズルスロート浸食履歴を予測した上での最適ノズル形状設計、およびノズルスロート浸食を抑制する作動条件およびノズル材料、を得るのが本研究の目的である。R3年度はプリフライトモデルモータを開発して高空燃焼実験装置を用いた地上燃焼実験を実施したのが主な実施項目である。概要は以下に説明する通りである。
・高空燃焼実験装置とプリフライトモデルモータとのインタフェース構造を製作した。
・プリフライトモデルモータを製作し、高空燃焼実験装置を用いて0.1気圧程度の低圧力環境雰囲気で点火実験を行った。推力が良好に立ち上がり、真空の宇宙環境での点火シーケンス構築の見通しを得た。併せて、導電性プラスチックを用いて点火する新たな手法を考案し、高い信頼性で点火可能である事を確認した。
・高空燃焼実験装置を用いて10秒間の燃焼実験を実施し、ロケット噴流により低圧力環境が維持されることを確認した。
・プリフライトモデルモータによる60秒の燃焼実験を実施し、設計要求を満たす推力履歴が得られることを確認した。
・亜酸化窒素の蒸気圧を利用したコールドガススラスタを製作し、高空燃焼実験装置を用いて低圧力環境下で推力を計測した結果、設計通りの推力が得られていることを確認した。
日本学術振興会, 学術変革領域研究(B), 北海道大学, 20H05747

Nozzle throat erosion mechanisms in hybrid rockets
Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (B)
01 Apr. 2019 - 31 Mar. 2022
Nagata Harunori
Nozzle erosion study was limited because it is difficult to obtain both nozzle throat area and fuel flow rate histories during combustion in hybrid rockets. This study employed a method developed by this research group to simultaneously acquire both time histories of nozzle throat area and fuel flow rate and obtained the following results.
We obtained nozzle erosion histories using oxygen and nitrous oxide as oxidants and organized the erosion rates unified by using the concentration of oxidizing components in the combustion gas. In collaboration with the numerical research group of D. Bianchi et al. of the University of Rome, we elucidated the physical/chemical mechanism of nozzle erosion and developed a method to predict the erosion rate as a function of combustion chamber pressure and OF ratio.
Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (B), Hokkaido University, 19H02336

Elucidation of Diffusion Flame Mechanism of Liquid Oxygen-Solid Fuel and its Application to End-Burning Hybrid Rocket
Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (C)
01 Apr. 2019 - 31 Mar. 2022
Wakita Masashi
In this study, we clarified the basic combustion characteristics when liquid oxygen is used as an oxidizer instead of gaseous oxygen, aiming at the practical application of "end-burning" hybrid rocket. Combustion experiments were also conducted using single-port and multi-port fuels with high toughness that can withstand the cooling of liquid oxygen, and it was confirmed that "end-burning" combustion is possible even with liquid oxygen supply. Furthermore, the dependence of fuel regression rate on port diameter and pressure was confirmed, and the knowledge necessary to examine the feasibility of "end-burning" hybrid rockets was obtained.
Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (C), Hokkaido University, 19K04832

Practical use study of the Axial-Injection End-Burning Hybrid Rocket Motor
Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (C)
01 Apr. 2017 - 31 Mar. 2020
SOEDA KENTARO
In this study, following result was obtained. 1)Molding of the exact rocket fuel by 3D printer. 2)In the slot ring combustion experiment, I clarified a thrust reply characteristic, 3)By the combustion experiment that changed a kind of the oxidizer and the construction of the combustion model, I clarified combustion mechanism.
Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (C), The University of Tokyo, 17K06943

Development of Ne measurement instrument for ultra-small Mars missions
Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (A)
Apr. 2017 - Mar. 2020
Sugita Seiji
In order to measure the neon isotope ratio in the Mars atmosphere with ultra-small spacecraft, we developed orbitrap-type light-weight high-mass-resolution (m/dm > 10,000) mass spectrometer. We also developed membrane system to separate Ne and Ar before taking Mars air into the mass spectrometer. Using the newly developed system, we obtained gas separation performance as a function of time. We also designed a new mechanism to keep high vacuum condition using getter-type pump with very limited resources, such as size, weight, and electricity.
Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (A), The University of Tokyo, 17H01175

端面燃焼式ハイ ブリッドロケットの実用化研究
基盤研究(C)
Apr. 2017 - Mar. 2020
添田 建太郎
文部科学省, Competitive research funding

Method for Determining Nozzle-Throat-Erosion History in Hybrid Rockets and Elucidation of the Mechanism
Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (B)
01 Apr. 2015 - 31 Mar. 2018
Nagata Harunori
We developed a new reconstruction technique titled nozzle-throat reconstruction technique to estimate nozzle-throat-erosion history and oxidizer-to-fuel-mass-ratio history in hybrid rockets. Static-firing tests were carried out on a 2kN-class hybrid-rocket motor under varying oxidizer-flowrates to evaluate the accuracy of reconstructed results. For equivalence ratios from 0.6 to 1.4, the relationship between nozzle-throat-erosion rate and equivalence ratio of reconstructed results displays a trend consistent with chemical-kinetic-limited heterogeneous-combustion theory, as well as predictions made by previous researchers. Also, we selected some materials which can prevent nozzle erosion and evaluated anti-erosion characteristics by combustion experiments. As an experimental result, graphite coated by silicon carbide showed good anti-erosion characteristics for hybrid rocket nozzles.
Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (B), Hokkaido University, Principal investigator, Competitive research funding, 15H04197

Development study of Hypersonic flight demonstrator for spaceplane technologies
Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (A)
31 May 2013 - 31 Mar. 2018
Sawai Shujiro, Yoshimitsu Tetsuo
In order to obtain various technologies for realization of spaceplanes using airbreathing engines through flight experiments, development study of high-speed flight experiment system based on combination of a high-altitude balloon and a hybrid rocket booster has been conducted. Conceptual studies of the flight experiment system were conducted. Based on the results of the conceptual study, development study of the flight experiment vehicle was conducted. Through the development study, system integration technology had been acquired, and flight dynamics and control studies were conducted. And also, aerodynamic design of spaceplane airframe was studied. Although no flight experiment chance could be obtained, the development of the flight experiment vehicle has been completed. In addition, a flight experiment plan containing an experiment operation was considered so that merits and problems were extracted and arranged for near-future execution of the flight experiment.
Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (A), Japan Aerospace EXploration Agency, 25249125

Development and Verification of End-burning Type Hybrid Rockets Using Optical Modeling Technology
Grants-in-Aid for Scientific Research Grant-in-Aid for Challenging Exploratory Research
01 Apr. 2015 - 31 Mar. 2017
Nagata Harunori
The authors have previously proposed the concept of end burning type hybrid rockets which would use cylindrical fuel grains consisting of an array of many small ports running in the axial direction through which oxidizer gas would flow. Because of difficulty in manufacturing a fuel grain, the end burning hybrid rocket had yet to be achieved. The recent progress in 3D printing technology made novel end burning type hybrid rockets possible. The results of verification firing tests clearly distinguish the initial transient and steady periods of the end burning mode, and prove that no oxidizer to fuel ratio shift occurs during firing. Combustion experiments using single port fuel samples of 0.2 to 0.5 mm in inner diameter show that two combustion modes of flame propagating combustion and stabilized combustion are divided by a critical friction velocity and the flame traveling velocity in the stabilized mode coincides with the regression rate of the end-burning fuel.
Japan Society for the Promotion of Science, Grant-in-Aid for Challenging Exploratory Research, Hokkaido University, Principal investigator, Competitive research funding, 15K14243

Fuel Regression Characteristics of CAMUI-type hybrid rockets under high Reynolds numbers
Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (A)
01 Apr. 2012 - 31 Mar. 2016
Nagata Harunori, OSHIMA NOBUYUKI, TOTANI TSUYOSHI, WAKITA MASASHI
To achieve the practical use of nonhazardous small rockets, We have developed CAMUI type hybrid rockets. CAMUI rockets are free from explosives and liquid fuels, resulting in lower costs for safety management. This research clarifies scale effects on fuel regression characteristics mainly by static firing tests. The firing tests covers Reynolds number range from a few thousands to over a half million. A numerical simulation clarified the mechanism responsible for the effect. By using these results, we can obtain basic design data by static firing tests of a subscale motor. Finally, we developed a 15 kN thrust class motor. Firing tests by this motor show good results, verifying the method developed in this research.
Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (A), Hokkaido University, Principal investigator, Competitive research funding, 24246135

Optimal Design Method of CAMUI-type Fuel Grain
Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (B)
2009 - 2011
NAGATA Harunori, TOTANI Tsuyoshi, WAKITA Masashi
The research team has been developing CAMUI type hybrid rockets. This project is to develop an optimal design method for a CAMUI type fuel grain shape. Main achievements are : 1. New method to obtain regression formulas of all burning surfaces as functions of local O/F by a few static firing tests. 2. A simple combustion experiment successfully reproduced combustion characteristics of the upstream end face of the most upstream fuel block. 3. A search method employing genetic algorithm successfully obtained an optimal design of a CAMUI type fuel grain.
Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (B), Hokkaido University, Principal investigator, Competitive research funding, 21360410

Regression Mechanism of a Solid Fuel around Oxidizer Jet Stagnation Region
Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (B)
2006 - 2008
NAGATA Harunori, TOTANI Tsuyoshi, OSHIMA Nobuyuki
申請者らが開発を進めている無火薬式小型ロケット「CAMUI型ハイブリッドロケット」の特徴的な燃焼特性を実験および数値計算により明らかにし, 以下の成果を得た.
固体燃料のガス化速度を燃料形状, 酸化剤供給量, および燃焼室圧力の関数として予測する手法を確立した.
ロケットモータのスケールが燃焼特性に与える影響を解明し, 小型モータによる燃焼実験で実機モータの燃焼特性を明らかにする手法を開発した.
Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (B), Hokkaido University, Principal investigator, Competitive research funding, 18360402

微小重力燃焼研究に基づく地下空間火災安全に関する基礎研究
Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (C)
2004 - 2004
藤田 修, 永田 晴紀, 伊東 弘行, 梅村 章, 伊藤 昭彦, 菊池 政雄
本企画調査では、地下空間の火災を想定しその抑制に貢献できる研究プロジェクトを立ち上げることを目標として実施したものである。その中で特に、テグの地下鉄火災を一つの例として取り上げその災害を構成する燃焼現象を調査することで、閉鎖空間の火災現象の研究シナリオを構築した。とくに、一連の現象が浮力に強く支配されることに着目して、研究ツールとして微小重力環境利用を取り込み、閉鎖空間特有の境界条件影響を燃焼科学的な側面から明らかにしようとする研究の提案を行った。また、本研究のもう一つの特徴として、国際的な研究ネットワークを構築し、この海外研究者の協力により研究の推進を図る体制について検討した。このため、以下のような項目について調査を進め、最終的に、米国、フランス、韓国の研究者を研究グループに取り込んだ平成17年度発足特定領域研究の提案に至った。
(1)当該研究課題の研究シナリオとアプローチ法に関する検討:研究分担者と5回程度の議論の場を持ったほか、著名な火災研究者による地下空間火災事例に関する講演会を実施し、さらに研究分担者による数値計算・モデリングに関する方向性の考察を加えた研究シナリオを提案した。
(2)当該研究課題への微小重力環境利用有効性の検討:宇宙航空研究開発機構の研究者と当該研究について微小重力利用の有効性について検討した。
(3)海外研究者の研究協力体制:米国、フランス、韓国の研究者と各2回程度の議論の機会を持ち、提案予定の研究への参画見込み、海外研究者の研究資源の調査を行った。また、テグ地下鉄火災に関しては韓国研究者の協力を得て現地調査を実施した。
(4)平成17年発足特定領域研究「微小重力燃焼研究に基づくコンファインメント火災の科学」の提案:本調査研究の具体的成果として本提案を行った。
Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (C), Hokkaido University, Coinvestigator not use grants, Competitive research funding, 16636003

Shock Induced Combustion and Flame Folding in Supersonic Combustion Ramjet Engine
Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (C)
2001 - 2002
ARAI Takakage, KASAHARA Jiro, MIZOBATA Kazuhide, SUGIYAMA Hiromu, MATSUO Akiko, NAGATA Harunori
This research was primarily concerned with flows and combustion phenomena in Scramjet engine model. Hypersonic flow was obtained by using small high enthalpy shock tunnel. At Mach number of about 7, Scramjet engine model was set in the test section. At first, the oblique-shock compression process was studied. Gaseous H2 or He were injected with the injection angle of 70 degrees to the supersonic cross flow from intake wall. We conducted Schlieren-image visualization and wall static pressure measurements, self-emission observation. Schlieren-image visualization and self-emission were observed by using CCD camera and high-speed video camera. We verified the supersonic combustion and shock-induced combustion.
And also, the evaluation of supersonic mixing was conducted by using catalytic reaction on platinum wire surface. This method was applied to evaluate the time variation of hydrogen concentration in the mixing layer. The results showed that the strength of the correlation between the time variations of the hydrogen concentration and velocity in the mixing layer was effected by mixing conditions.
Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (C), MURORAN INSTITUTE OF TECHNOLOGY, Coinvestigator not use grants, Competitive research funding, 13650960

Development Study of High-response Hydrogen Concentration Probe for Supersonic Flows
Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (B)
2000 - 2002
NAGATA Harunori, ARAI Takakage, TOTANI Tsuyoshi, KUDO Isao
Scramjet engine is a strong candidate for use as thrusters for space planes and supersonic civil transporter in the next generation. Supersonic mixing is a key challenge to in realizing scramjet engines. Regarding this, the main purpose of this research is to develop a simple method to evaluate hydrogen concentration in a supersonic mixing layer without the need for costly apparatus. The investigators have proposed a hydrogen concentration probe using catalytic reaction on Pt wire surface. To use this probe to detect a concentration change in a supersonic mixing layer, the response of the catalytic heat release rate must depend only on concentration change around the probe. Catalytic heat release rate on the Pt wire surface in unsteady state is measured using a constant temperature type hotwire anemometer technique and a shock tube to investigate the relation of the response of the catalytic heat release rate and Pt wire temperature. The increasing rate of the catalytic heat release depends on the Pt wire temperature when the wire temperature is low. However, the dependence is very weak when the wire temperature is over about 680 K. This shows that not the catalytic reaction but moleculartransfer from the flow to the Pt wire surface is the controlling step when Pt wire temperature is high enough. As a conclusion, catalytic reaction rate on the Pt wire is high enough comparing with the molecular transfer rate with the temperature over about 680 K, yielding high response frequency as hotwire anemometers(over a hundred kHz).
Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (B), HOKKAIDO UNIVERSITY, Principal investigator, Competitive research funding, 12450390

SUPERSONIC MIXING AND COMBUSTION OF HYDROGEN USING HIGH-ENTHALPY SHOCK TUNNEL
Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (C)
1999 - 2000
ARAI Takakage, KASAHARA Jiro, MIZOBATA Kazuhide, SUGIYAMA Hiromu, NAGATA Harunori
To investigate the flow and combustion in a Scramjet engine model at about Mach 7 flight condition, a small high enthalpy shock tunnel, whose nozzle exit was of 60 mm diameter, was used. Double wedges were set in the test section as a Scramjet engine intake and combustion chamber model. The compression process used the oblique shock systems, which were generated by vehicle forward edge and cowl, was observed. H^2 and/or C_2H_2-air mixture gas was injected normally to supersonic cross flow of Mach 1.7 in the combustion chamber. A self-emission from combustion gas was observed by using a very high-speed video camera (18,000fps) with image intensifier. And also, the wall static pressure in the combustion chamber was measured. It was clarified that the wall pressure increased when the supersonic combustion occurred
Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (C), MURORAN INSTITUTE OF TECHNOLOGY, Coinvestigator not use grants, Competitive research funding, 11650938

Generation and Collection of Droplets under microgravity
Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (B).
1998 - 2000
KUDO Isao, TOTANI Tsuyoshi, NAGATA Harunori
Performances of a droplet generator and a droplet collector in Liquid Droplet Radiator under microgravity were investigated. As a result, it is concluded that
(1) Droplet generator can produce the uniform droplet stream whose diameter and spacing is uniform under microgravity,
(2) Splashes don't occur at the surface of the droplet collector in case that the uniform droplet stream that consists of droplets of 200 [μm] diameter collides against,
(3) Splashes occur in case that the non-uniform droplet stream collides against and the uniform droplet stream that consists of droplets larger than 400 [μm],
(4) Centrifugal collector is effective to carry the working fluid that is collected,
(5) Liquid film that is a few millimeter thick is effective to prevent droplets of 400 [μm] diameter from splashing,
(6) There is small dependency between splashes and angles formed where a droplet stream collides against the surface on the droplet collector.
Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (B)., HOKKAIDO UNIVERSITY, Coinvestigator not use grants, Competitive research funding, 10450369

超音速流中における白金触媒燃焼に関する研究
Grants-in-Aid for Scientific Research Grant-in-Aid for Encouragement of Young Scientists (A)
1998 - 1999
永田 晴紀
超音速流れ場における白金表面での触媒反応の機構を基礎的に理解し、スクラムジェットエンジンでの点火・保炎機構として触媒燃焼を応用することを目指すとともに、触媒燃焼を利用して超音速混合場を評価する手段を確立することを目的とした研究を行った。定温度型熱線風速計の原理を応用し、触媒反応発熱量と白金温度、雰囲気水素濃度の関係を明らかにした。白金線温度が十分に高い条件では、発熱量は白金線温度に依存しないことを実験的に明らかにした。発熱量は水素濃度が理論混合比のときに最大となり、酸素と水素の拡散係数の違いが白金表面への分子輸送の差にほとんど影響を及ぼさないことが判った。ほぼ全域の水素濃度において、熱伝達係数と物質伝達係数の相似性が実験的に示された。これを利用して、熱伝達係数から物質伝達係数を見積る手法が提案され、触媒反応発熱量から高精度で水素濃度を見積ることが可能であることが示された。
Japan Society for the Promotion of Science, Grant-in-Aid for Encouragement of Young Scientists (A), Hokkaido University, Principal investigator, Competitive research funding, 10750654

Catalytic Combustion in Low Temperature Supersonic Mixing Layer on Scramjet Engine Model
Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (C)
1997 - 1998
ARAI Takakge, NAGATA Harunori, SUGUIYAMA Hiromu
It is important for scramjet engine study to understand the mixing process in supersonic mixing layer. So far, many experimental and numerical studies have been conducted to clarify the mixing process in supersonic mixing layer. Most of experimental studies have focused in the velocity distributions concerned with mixing layer, and also evaluated the flow visualization results. Meanwhile, with CPD developing, numerical results have been able to give the spatial data of equivalence ratio of H_2 (distribution of H_2 concentration). There is less data of distribution of equivalence ratio in mixing layer as reason for the difficulty of measuring it. This study proposes a new evaluation technique for the mixing condition of H_2 in hydrogen-air supersonic flow. We have reported the new technique for the evaluation of turbulent supersonic mixing layer using catalytic reaction on constant high temperature Pt wire. This technique has been developed and is applied to measure H_2 concentration in supersonic mixing flow produced by inclined hydrogen injection into a Supersonic flow.
Hydrogen was injected normally to a Mach 1.8 cold air stream with a backward-facing step to investigate mixing flow field in a scramjet combustor. Catalytic reaction on constant temperature Pt wire was used to measure the mixing condition of H_2 and O_2. It was new technique to investigate H_2 mixing condition. The amount of heat release due to the catalytic reaction, which corresponds to the concentration of H_2 and/or O_2 on the surface of the catalyst, was measured spatially so that the local mixing condition of H_2 and O_2 was cleared. The results showed that there were two core regions. which would have good mixing condition for supersonic combustion, in the mixing layer. The development of core regions along flow direction was also clarified It was also clarified that the new teclmique proposed in the present study was very useful and easy to evaluate the hydrogen concentration in supersonic mixing flow field.
Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (C), MURORAN INSTITUTE OF TECHNOLOGY, Coinvestigator not use grants, Competitive research funding, 09651006

新形式ハイブリッドロケットの研究 パルスデトネーションエンジンに関する基礎研究　　　　　　　　　　　　　　　
Competitive research funding

Development of Advanced Hybrid Rockets Development of Pulse Detnation Engine　　　　　　　　　　　　　　　
Competitive research funding

ハイブリッドロケット
Patent right, 秋 葉, 鐐二郎, 長 島, 隆 一, 棚 次, 亘 弘, 永 田, 晴 紀, 佐, 鳥, 新, 山 本, 洋, 一, 秋葉 鐐二郎, 独立行政法人 宇宙航空研究開発機構, 棚次 亘弘, 永田 晴紀, 佐鳥 新, 株式会社IHIエアロスペース
特願平11-174936, 22 Jun. 1999
特開2001-003813, 09 Jan. 2001
特許第4224599号
05 Dec. 2008
200903076540210472

ハイブリッドロケット
Patent right, 永田 晴紀, 独立行政法人科学技術振興機構
特願2003-285514, 04 Aug. 2003
特開2005-054649, 03 Mar. 2005
特許第4205520号
24 Oct. 2008
200903066296453400

バルブレス液体供給装置
Patent right, 永田 晴紀, 金子 雄大, 国立大学法人 北海道大学
特願2007-082739, 27 Mar. 2007
特開2008-240643, 09 Oct. 2008
200903066003720183

ハイブリッドロケットエンジンの固体モータとその燃焼方法
Patent right, 棚次 亘弘, 永田 晴紀, 佐鳥 新, 渡辺 裕之, 株式会社IHIエアロスペース
特願2002-302641, 17 Oct. 2002
特開2004-137956, 13 May 2004
特許第4183475号
12 Sep. 2008
200903017661817971

ガスタービンの燃焼器
Patent right, 藤森 俊郎, 佐藤 公美, 秋葉 鐐二郎, 伊藤 献一, 永田 晴紀, 石川島播磨重工業株式会社
特願2000-317693, 18 Oct. 2000
特開2002-130679, 09 May 2002
200903087204144897

パルスデトネーションエンジン用多孔微細管燃料酸化剤供給プレート
Patent right, 笠原 次郎, 新井 隆景, 永田 晴紀, 松尾 亜紀子, 笠原 次郎, 新井 隆景, 永田 晴紀, 松尾 亜紀子
特願2000-258181, 24 Jul. 2000
特開2002-039012, 06 Feb. 2002
200903098647827840