Researcher basic information

• Ph. D March 1999, Hokkaido University

• https://researchmap.jp/TsuyoshiTotani_HKD?lang=en

• https://jglobal.jst.go.jp/detail?JGLOBAL_ID=200901030771919809

• 200901030771919809

• Thermal Management
• Thermal Design of Satellites
• Wavelength Control of Radiation
• 液滴ラジエータ
• 微小重力
• 表面微細周期構造
• マイクロナノデバイス
• マランゴニ対流
• Liquid Droplet Radiator
• 宇宙インフラ
• Thermal Engineering
• Space Engineering
• Fluid Mechanics

• Manufacturing Technology (Mechanical Engineering, Electrical and Electronic Engineering, Chemical Engineering), Thermal engineering
• Frontier Technology (Aerospace Engineering, Marine and Maritime Engineering), Aerospace engineering

• Bachelor's degree program, School of Engineering
• Master's degree program, Graduate School of Engineering
• Doctoral (PhD) degree program, Graduate School of Engineering

Research activity information

• Relaxation enhancement from intra- to intermolecular vibrations in water continuously excited by wavelength-selective infrared radiation
  Yoshitaka TANADA; Tsuyoshi TOTANI; Satoru ODASHIMA; Kazumichi KOBAYASHI; Yoshio KONDO
  Journal of Thermal Science and Technology, 20, 25-00209, Dec. 2025, [Peer-reviewed], [Corresponding author]
  English, Scientific journal, 45294852
• A Novel System for Crystal Polymorph Discovery via Selective-Wavelength Infrared Irradiation Using Metamaterials
  Yoshio Kondo; Tsuyoshi Totani; Satoru Odashima; Daiki Kato; Norimitsu Tohnai
  Crystals, 15, 8, 741, MDPI AG, 20 Aug. 2025, [Peer-reviewed]
  English, Scientific journal, The control of crystal polymorphs is central to the design of pharmaceuticals and functional materials. Conventionally, crystal polymorph production has been controlled primarily by adjusting chemical and thermodynamic parameters. In this study, we developed a device capable of emitting infrared radiation at selected wavelengths using a novel material having a “MIM structure” which is a type of metamaterial. With this device, we propose a new approach to crystal polymorph control through the irradiation of narrow-band infrared radiation that coincides with the infrared absorption band of specific functional groups. In this paper, we present the design and operating principle of a new crystallization system, and as an application example, we report the experimental results of controlling the crystal polymorphs of Ritonavir, an active pharmaceutical ingredient.
• Thermal design exploration of flexible and lightweight antenna structures through design of experiments
  Delburg Mitchao; Tsuyoshi Totani; Hiraku Sakamoto
  Applied Thermal Engineering, 264, 125323, 125323, Elsevier BV, Apr. 2025, [Peer-reviewed]
  English, Scientific journal
• Verification of Thermal Design for Small Satellite Izanagi with Synthetic Aperture Radar using Measured Flight Data
  Masaki Aoi; Tsuyoshi Totani; Hiroki Kitamura; Shunsuke Onishi; Yuji Sakamoto
  Journal of Evolving Space Activities, 2, Article No.210, 2024, [Peer-reviewed], [Corresponding author]
  English, Scientific journal
• Thermal Effects of Aluminum-Copper-Aluminum Clad Material for the Utilization of the Entire Heat Capacity of Microsatellites
  Kei Yoshii; Tsuyoshi Totani
  Journal of Evolving Space Activities, 1, Article No.84, Dec. 2023, [Peer-reviewed], [Last author, Corresponding author]
  English, Scientific journal
• Molecular dynamics study of evaporation induced by locally heated argon liquid
  Hirofumi Tabe; Kiryu Hiramatsu; Kazumichi Kobayashi; Hiroyuki Fujii; Masao Watanabe; Tsuyoshi Totani
  Applied Thermal Engineering, 212, 118472, Jul. 2022, [Peer-reviewed], [Last author]
  English, Scientific journal
• Manufacturing method of the heat-storable carbon fiber reinforced plastics with applying trans-1,4-polybutadiene by using cellulose nanofibers and electrodeposition solution
  Kazuaki Katagiri; Tsuyoshi Totani; Takuya Isono; Ryohei Goto; Shimpei Yamaguchi; Sonomi Kawakita; Tomoatsu Ozaki; Hirosuke Sonomura; Sayaka Minami; Shinya Honda; Katsuhiko Sasaki
  Journal of Energy Storage, 31, 101636, Elsevier BV, Oct. 2020, [Peer-reviewed]
  English, Scientific journal
• Thermal Design of Upper Boost Stage with Hybrid Kick Motor for Microspacecraft
  Tabata Kenichi; Totani Tsuyoshi; Matsushima Kohei; Nagata Harunori
  Proceedings of 2020 International Conference on Environmental Systems, ICES-2020-342, Jul. 2020, [Peer-reviewed], [Corresponding author], [International Magazine]
  English, International conference proceedings
• Applying the Thermal Design Method Based on Overall Heat Capacity to Microsatellites
  Hajime Ota; Kei Yoshii; Tsuyoshi Totani
  Proceedings of 2020 International Conference on Environmental Systems, ICES-2020-292, Jul. 2020, [Peer-reviewed], [Last author, Corresponding author], [International Magazine]
  English, International conference proceedings
• Fabrication of heat-storable CFRP by incorporating trans-1,4-polybutadiene with the application of the electrodeposition resin molding method
  Kazuaki Katagiri; Ryohei Gotoh; Tsuyoshi Totani; Takuya Isono; Shimpei Yamaguchi; Takuya Ehiro; Hirosuke Sonomura; Tomoatsu Ozaki; Sonomi Kawakita; Yayoi Yoshioka; Sayaka Minami; Shinya Honda; Katsuhiko Sasaki
  Journal of Energy Storage, 26, 100980-1, 100980-6, Dec. 2019, [Peer-reviewed], [International Magazine]
  English, 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]
  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]
  Japanese, Scientific journal, 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.
• 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, Oct. 2018
  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．

• Control of Heat Release Energy during Heating from Solid-solid Phase Change Material
  Ryohei Gotoh; Tsuyoshi Totani; Masashi Wakita; Harunori Nagata
  Proceedings of the 16th International Heat Transfer Conference, IHTC16-24007, 4425, 4432, Aug. 2018, [Peer-reviewed]
  English, International conference proceedings
• Application of the Wavelength Selective Emitter with the Metamaterial of a Metal-insulator-metal to an Infrared Ray Drying Furnace
  Tsuyoshi Totani; Atsushi Sakurai; Thang D. Dao; Tadaaki Nagao; Yoshio Kondo
  Proceedings of the 16th International Heat Transfer Conference, IHTC16-24220, 5901, 5908, Aug. 2018, [Peer-reviewed]
  English, International conference proceedings
• 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]
  English, Scientific journal
• 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]
  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, 2018, [Peer-reviewed]
• 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]
  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]
  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
• 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 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, 2017, [Peer-reviewed]
  English, Scientific journal
• 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, 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]
  Japanese, Scientific journal, 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.
• 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, Sep. 2016, [Peer-reviewed]
  English, Scientific journal
• 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, International conference proceedings
• 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]
  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]
  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]
  English, Scientific journal
• Influence of Degradation on Storage of Heat of Heat Storage Material with Crystal Transformation
  Takuya KUNI; Tsuyoshi TOTANI; Toshifumi SATOH; Takuya ISONO; Masashi WAKITA; Harunori NAGATA
  Japan Journal of Thermophysical Properties, 29, 4, 173, 178, Nov. 2015, [Peer-reviewed]
  Japanese, Scientific journal
• 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]
  English, Scientific journal

  
  Preprint
• 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, International conference proceedings
• New Procedure for Thermal Design of Micro- and Nano-satellites Pointing to Earth
  Tsuyoshi TOTANI; Ryota INOUE; Hiroto OGAWA; Tilok Kumar DAS; Masashi WAKITA; Harunori NAGATA
  Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan, 12, ists29, Pf_11, Pf_20, Aug. 2014, [Peer-reviewed]
  English, Scientific journal
• Heat Storage Material without Phase-change for Micro and Nano Satellite
  Tsuyoshi TOTANI; Toshifumi SATOH; Masashi WAKITA; Harunori NAGATA
  Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan, 12, ists29, Po_4_1, Po_4_5, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, Jul. 2014, [Peer-reviewed]
  English, Scientific journal, 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.
• 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, Techno Press, 01 Jul. 2014, [Peer-reviewed]
  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]
  English, Scientific journal
• Development and Flight Demonstration of 5 kN Thrust Class CAMUI Type Hybrid Rocket
  Harunori NAGATA; Masashi WAKITA; Tsuyoshi TOTANI; Tsutomu UEMATSU
  TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 12, ists29, Ta_1, Ta_4, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, Apr. 2014, [Peer-reviewed]
  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 fuel. By the new fuel grain design, the combustion gas repeatedly impinges on fuel surfaces to accelerate the heat transfer to the fuel. 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. Basic technologies for the sea recovery are staged braking by parachutes, suspending the fuselage on the ocean, and locating the fuselage by an electric beacon and sea marker. Test results were successful and all of the fuselage was recovered. A typical drag coefficient profile around the sonic speed was obtained.
• 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]
  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.
• 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, 1, 12, 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]
  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.
• 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, Scientific journal
• 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, International conference proceedings
• 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, International conference proceedings
• 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]
  Japanese
• Development of Pulse Detonation Engine Initiator using Reflector for Large Bore Combustor
  Masashi Wakita; Masayosi 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, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, Mar. 2012, [Peer-reviewed]
  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.
• 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, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, Mar. 2012, [Peer-reviewed]
  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, 185/186, 212, 220, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, Jan. 2012, [Peer-reviewed]
  English, Scientific journal, The effects of heating or cooling of the supersonic flow in a Laval nozzle have been investigated numerically. We focus on the exhaust velocity and the area ratio at given expansion ratios, which are ranged from 30 to 16,000. This range is equivalent to the area ratio from 4 to 400 at the specific heat ratio of 1.3 under isentropic expansion. Two types of heat profile are considered: pulsed heat transfer (PHT) and distributed heat transfer (DHT). The relations of Rayleigh flow and isentropic expansion are used for PHT. The exhaust velocity is higher than the isentropic value for the case where heat is provided near the throat. In other cases, the exhaust velocity is less than the isentropic value. The equivalent point of heat transfer is introduced for DHT. Using this equivalent point, the results for DHT exhibit the same trend as the results for PHT. This indicates that the effects of DHT can be predicted directly from results for PHT without numerical analyses.
• 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, International conference proceedings
• 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]
  English, Scientific journal
• 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, 586, 589, Dec. 2010, [Peer-reviewed]
  English, International conference proceedings
• 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, The Japan Society of Mechanical Engineers, Nov. 2010, [Peer-reviewed]
  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, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, Jul. 2010, [Peer-reviewed]
  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.
• 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]
  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.
• 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, 社団法人 日本航空宇宙学会, Jun. 2010, [Peer-reviewed]
  Japanese, Scientific journal, 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.
• Status of VNIR hyperspectral sensor HSC development: Optical and data handling sub-system
  Y. Aoyanagi; T. Totani; K. Yamaguchi; A. Nakamura; N. Takeyama; Y. Kanai; Shin Satori
  61st International Astronautical Congress 2010, IAC 2010, 6, 4624, 4628, 2010
  English, International conference proceedings
• Development of Spaceborne Small Hyperspectral sensor HSC-III for Micro Satellite
  Yoshihide Aoyanagi; Shin Satori; Tsuyoshi Totani; Toshihiko Yasunaka; Akihiro Nakamura; Yusuke Takeuchi
  SMALL SATELLITE MISSIONS FOR EARTH OBSERVATION, 331, +, 2010, [Peer-reviewed]
  English, International conference proceedings
• EFFECT OF JET VELOCITY ON SCALE EFFECT IN OXIDIZER IMPINGING REGION
  Yudai Kaneko; Mitsunori Itoh; Massasi Wakita; Tsuyoshi Totani; Harunori Nagata
  APPLICATIONS OF SPACE TECHNOLOGY FOR HUMANITY, 138, 629, +, 2010, [Peer-reviewed]
  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
  APPLICATIONS OF SPACE TECHNOLOGY FOR HUMANITY, 138, 611, +, 2010, [Peer-reviewed]
  English, International conference proceedings
• Design of a Spaceborne Small Hyperspectral Sensor
  AOYANAGI YOSHIHIDE; NISHIZATO SHIN'YA; SATORI SHIN; TOTANI TSUYOSHI; HARA URUMI; YASUNAKA TOSHIHIKO; NAKAMURA AKIHIRO; TAKEUCHI YUSUKE
  Memoirs of the Hokkaido Institute of Technology, 37, 37, 205, 211, 北海道工業大学, Mar. 2009, [Peer-reviewed]
  Japanese, Research institution
• 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, 2009
  English, International conference proceedings
• Orbital Experiment of Nano-satellite "HIT-SAT" as a Sub-payload of M-V Rocket
  Tatsuhiro SATO; Ryuichi MITSUHASHI; Shin SATORI; Kosei ISHIMURA; Tsuyoshi TOTANI; Akihiro NAKAMURA; Kotaro HORI; Toshihiko YASUNAKA; HIT-SAT Development; Team
  TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN, 7, ists26, Tu_47, Tu_50, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2009, [Peer-reviewed]
  English, Scientific journal, A small satellite named Hokkaido Satellite "TAIKI" has been designed by NPO Frontier Incubation center for space applications and intellectual activities in Hokkaido. The missions of TAIKI are an agricultural remote sensing using a hyper-spectral sensor and a hi-vision video image filming. As the first step of the Hokkaido satellite project, a space experiment using a 2.7kg nano-satellite was executed. To demonstrate the performance of the bus system of the small satellite, a cube-sat "HIT-SAT" was developed as a scale model of the Hokkaido Satellite. This paper describes the development and results of launch and operation. The HIT-SAT is 2.7 kg in weight and 12cm cubed sizes. The bus system of the satellite consists of five subsystems; power generation system, structure system, data handling system, communication system and attitude control system. The HIT-SAT was launched successfully on Sep. 23, 2006 (JST) as a sub-payload of M-V-7 rocket. The CW telemetry has been received around the world by many radio amateurs.
• 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, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2009, [Peer-reviewed]
  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 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, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2009, [Peer-reviewed]
  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.
• Development of 90 kgf Class CAMUI Hybrid Rocket for a CanSat Experiment
  Harunori NAGATA; Tsutomu UEMATSU; Mitsunori ITO; Akihito KAKIKURA; Yudai KANEKO; Kazuhiro MORI; Norikazu MURAI; Tatsuhiro SATO; Ryuichi MITSUHASHI; Tsuyoshi TOTANI
  TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN, 7, ists26, Tu_1, Tu_5, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2009, [Peer-reviewed]
  English, Scientific journal, 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.
• Data analysis results of electrical power subsystem of the micro satellite "HIT-SAT"
  NISHIDATE JUN; SATO TATSUHIRO; AOYANAGI YOSHIHIDE; ONO TSUTOMU; TANAKA YOSHINORI; TAKENAMI KYOHEI; SATORI SHIN; MITSUHASHI RYUICHI; HIROTA NORIHISA; ISHIMURA KOSEI; SUGIMOTO KOICHIRO; MATSUSHIMA KOTA; TOTANI TSUYOSHI; SAKAKIBARA TAKAHIRO; HORI KOTARO; ERA SATOSHI; NAKAMURA AKIHIRO; YASUNAKA TOSHIHIKO; UEMATSU TSUTOMU
  Memoirs of the Hokkaido Institute of Technology, 36, 36, 191, 195, 北海道工業大学, Mar. 2008, [Peer-reviewed]
  Japanese, Research institution
• Development of hyperspectral sensor for Hokkaido satellite "Taiki"
  S. Satori; Y. Aoyanagi; S. Nishizato; T. Totani; U. Hara; T. Yasunaka; A. Nakamura; Y. Takeuchi
  International Astronautical Federation - 59th International Astronautical Congress 2008, IAC 2008, 6, 3966, 3972, 2008
  English, International conference proceedings
• Fuel Regression Characteristics of Cascaded Multistage Impinging-Jet (CAMUI) Type Hybrid Rocket
  Mitsunori Itoh; Takenori Maeda; Akihito Kakikura; Yudai Kaneko; Kazuhiro Mori; Takushi Nakajima; Masashi Wakita; Tsutomu Uematsu; Tsuyoshi Totani; Nobuyuki Ohshima; Harunori Nagata
  Journal of the Japan Society for Aeronautical and Space Sciences, 55, 646, 516, 526, 社団法人 日本航空宇宙学会, Nov. 2007, [Peer-reviewed]
  Japanese, Scientific journal, 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 contribute as burning surfaces. Polyethylene and LOX were used as a propellant, and the tests were conducted at the chamber pressure of 0.5–2MPa and the mass flux of 50–200kg/m²s. Main results obtained in this study are in the followings: The regression rate of each surface was obtained as a function of the propellant mass flux and local equivalent ratio of the combustion gas. At back-end surfaces the regression rate has a high sensitivity on the gap height of neighboring fuel blocks. These fuel regression characteristics will contribute as fundamental data to improve the optimum design of the fuel grain.
• Thermal and Structural design of subminiature satellite "HIT- SAT"
  Satori Shin; Totani Tsuyoshi; Sakakibara Takahiro; Yasunaka Tosihiko; Uematsu Tsutomu; Ishimura Kousei; Sugimoto Kouichirou; Matsushima Kouta; Mitsuhashi Ryuichi; Nishidate Jun; Sato Tatsuhiro; Aoyanagi Yosihide; Ohno Tsutomu; Tanaka Yoshinori; Takenami Kyouhei; Nakamura Akihiro; Hori Koutaraou; Era Satoshi; Hirota Naohisa
  Memoirs of the Hokkaido Institute of Technology, 35, 105, 111, 北海道工業大学, Mar. 2007, [Peer-reviewed]
  Japanese, Research institution, HIT-SAT has been designed and developed in order to examine functions of the bus system. It was launched by M-V-7 into a sun-synchronous orbit of the altitude of 279-660 [km] and the inclination of 98.32 [deg]. The volume and weight of HIT-SAT are about 12×13×12[cm3] and 2.7[kg], respectively. HIT-SAT has a flame-panel structure that consists of 6 panels, 4 columns and 2 shelves made of the aluminum alloy that has a high conductivity. The load pass at the launch is their panels and columns. The passive thermal control is adopted. Random vibration tests and impact tests were carried out. It ...
• Development of data handling unit for Pico-Satellite "HIT-SAT"
  Tamayama Yuta; Ohno Tsutomu; Aoyanagi Yoshihide; Sato Tatsuhiro; Nishidate Jun; Tanaka Yoshinori; Mitsuhashi Ryuichi; Satori Shin; Ishimura Kosei; Matsushima Kota; Sugimoto Koichiro; Totani Tsuyoshi; Sakakibara Takahiro; Yasunaka Toshihiko; Nakamura Akihiro; Hori Kotaro; Era Satoshi; Hirota Naohisa
  Memoirs of the Hokkaido Institute of Technology, 35, 281, 283, 北海道工業大学, Mar. 2007, [Peer-reviewed]
  Japanese, Research institution, "Hokkaido satellite" is a 50kg small satellite, and the main mission is a remote sensing. The HIT-SAT had been developed by Hokkaido in order to demonstrate the performance of the attitude control system for "Hokkaido Satellite". The HIT-SAT is size 12cm cubed and weight 2.7kg. Attitude Control is an object of keeping satellite attitude by spin stabilization. The HIT-SAT was launched successfully on September, 23, 2006(JST) as a sub-payload of the M-V-7 Rocket. In this paper, we described a design of data handling unit for the HIT-SAT and the result in orbit.
• Development of Attitude Control System for Pico-Satellite "HIT-SAT"
  Tamayama Yuta; Aoyanagi Yoshihide; Sato Tatsuhiro; Nishidate Jun; Ohno Tsutomu; Tanaka Yoshinori; Mitsuhashi Ryuichi; Satori Shin; Ishimura Kosei; Matsushima Kota; Sugimoto Koichiro; Totani Tsuyoshi; Sakakibara Takahiro; Yasunaka Toshihiko; Nakamura Akihiro; Hori Kotaro; Era Satoshi; Hirota Naohisa
  Memoirs of the Hokkaido Institute of Technology, 35, 275, 280, 北海道工業大学, Mar. 2007, [Peer-reviewed]
  Japanese, Research institution, The HIT-SAT had been developed by Hokkaido in order to demonstrate the performance of the attitude control system for "Hokkaido Satellite". "Hokkaido satellite" is a 50kg small satellite, and the main mission is a remote sensing. The HIT-SAT is size 12cm cubed and weight 2.7kg. Attitude Control is an object of keeping satellite attitude by spin stabilization. It has three parts as de-spin, spin-up and sun acquisition. As an Attitude sensor, we adopt Sun sensor, Magnetometer, and GYRO. Actuator is 3-axis Magnetic Torquer. The HIT-SAT was launched successfully on September, 23, 2006(JST) as a...
• 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]
  English, Scientific journal
• Research on tracking control operation system of "HIT-SAT"
  Sato Tatsuhiro; Takeoka Kazuhiko; Nishidate Jun; Aoyanagi Yoshihide; Ohno Tsutomu; Takenami Kyohei; Tanaka Yoshinori; Nishizato Shinya; Mitsuhashi Ryuichi; Satori Shin; Ishimura Kosei; Matsushima Kota; Totani Tsuyoshi; Sakakibara Takahiro; Era Satoshi; Nakamura Akihiro; Hori Kotaro; Yasunaka Toshihiko; Uematsu Tsutomu; Kase Satoshi; Sasaki Issei
  Memoirs of the Hokkaido Institute of Technology, 35, 403, 407, 北海道工業大学, Mar. 2007, [Peer-reviewed]
  Japanese, Research institution, HIT-SAT was launched as a sub-payload of the M-V-7 rocket on September 23, 2006. The orbit of HIT-SAT is the elliptic one with 98 deg inclination. Altitude at apogee is 648km and perigee 279km.The satellite is operated by the ground station set up by Hokkaido Institute of Technology. The mission of HIT-SAT is to demonstrate the commercial-off-the-shelf component on the orbit. HIT-SAT is an amateur satellite where the amateur radio machine was installed. Operation is being done well on the orbit as for HIT-SAT now. This paper describes the system of the ground control station of HIT-SAT.
• Experiment on flight model of HIT-SAT on development and orbit
  Sato Tatsuhiro; Takeoka Kazuhiko; Nishidate Jun; Aoyanagi Yoshihide; Ohno Tsutomu; Takenami Kyohei; Tanaka Yoshinori; Nishizato Shinya; Mitsuhashi Ryuichi; Satori Shin; Ishimura Kosei; Matsushima Kota; Totani Tsuyoshi; Sakakibara Takahiro; Era Satoshi; Nakamura Akihiro; Hori Kotaro; Yasunaka Toshihiko; Uematsu Tsutomu; Sasaki Issei
  Memoirs of the Hokkaido Institute of Technology, 35, 397, 401, 北海道工業大学, Mar. 2007, [Peer-reviewed]
  Japanese, Research institution, For earth observation thorough hyper-spectral camera, a small satellite "Hokkaido Satellite : TAIKI" has been designed in Hokkaido. To demonstrate the performance of the bus system, a cube-sat "HIT-SAT" was developed as a scale model of the Hokkaido Satellite This paper describes the development and results of launch and operation. The HIT-SAT is 2.7kg and 12cm cubed. The bus system of the satellite consists of five subsystem; power generation system, structure system, data handling system, communication system and attitude control system. The HIT-SAT was launched successfully on Sep. 23, 2...
• Electrical power subsystem design of subminiature satellite "HIT-SAT"
  Nishidate Jun; Sato Tatsuhiro; Aoyanagi Yosihide; Ohno Tsutomu; Tanaka Yoshinori; Takenami Kyouhei; Satori Shin; Mitsuhashi Ryuichi; Hirota Naohisa; Ishimura Kousei; Sugimoto Kouichirou; Matsushima Kouta; Totani Tsuyoshi; Sakakibara Takahiro; Hori Koutarou; Era Satoshi; Nakamura Akihiro; Yasunaka Toshihiko; Uematsu Tsutomu
  Memoirs of the Hokkaido Institute of Technology, 35, 285, 290, 北海道工業大学, Mar. 2007, [Peer-reviewed]
  Japanese, Research institution, A CubeSat size class "HIT-SAT" is a micro satellite that developed by Hokkaido CubeSat development team. Its volume and weight is 2.7kg and 12cm cubed. It was fixed in the sub payload space of M-V-7, and was ejected after main satellite separation on September 23, 2006. The orbit is sun-synchronous orbit of the altitude of 279-660 [km] and the inclination of 98.32 [deg]. The purpose is to examine some functions of the bus system. This research report describes an electric al power subsystem design. The major difficulty of Electrical Power System is surely OFF and ON. The OFF needs to be gua...
• 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
  Ryusuke Numakura; Masashi Wakita; Yusuke Sugata; Shigetoshi Sugata; Harunori Nagata; Tsuyoshi Totani; Isao Kudo
  Journal of the Combustion Society of Japan, 48, 145, 265, 272, 日本燃焼学会, Aug. 2006, [Peer-reviewed]
  Japanese, Scientific journal
• 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]
  English, Scientific journal
• HOKKAIDO SATELLITE PROJECT: STRUCTURAL AND THERMAL DESIGN OF ENGINEERING TEST CUBESAT
  T. Totani; T. Sakakibara; T. Yasunaka; K. Ishimura; S. Satori; K. Sugimoto; D. Igarashi; H. Hoshika; T. Uematsu; S. Era; A. Nakamura; K. Hori; R. Mitsuhashi; J. Nishidate; T. Sato; T. Yoneya; Y. Aoyanagi; T. Iwamoto
  PROCEEDINGS OF THE TWENTY-FIFTH INTERNATIONAL SYMPOSIUM ON SPACE TECHNOLOGY AND SCIENCE, 1271, 1276, 2006, [Peer-reviewed]
  English, International conference proceedings
• Hokkaido Satellite Project : System Design of a Engineering Test CubeSat
  K. Ishimura; T. Totani; K. Sugimoto; D. Igarashi; T. Sakakibara; H. Hoshika; K. Matsushima; S. Era; A. Nakamura; T. Yasunaka; T. Uematsu; K. Hori; N. Hirota; R. Mitsuhashi; J. Nishidate; T. Sato; T. Yoneya; Y. Aoyanagi; T. Iwamoto; R. Miura; T. Sugawara; S. Satori
  Proceedings of the 25th International Symposium on Space Technology and Science, 1265, 1270, 2006, [Peer-reviewed]
  English, International conference proceedings
• 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, 社団法人 日本航空宇宙学会, Sep. 2005, [Peer-reviewed]
  Japanese, Scientific journal, 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, 社団法人 日本航空宇宙学会, Jul. 2005, [Peer-reviewed]
  Japanese, Scientific journal, 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, [Peer-reviewed]
  English, Scientific journal
• 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, [Peer-reviewed]
  English, Scientific journal
• 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]
  English, Scientific journal
• 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, [Peer-reviewed]
  English, Scientific journal
• 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, [Peer-reviewed]
  English, Scientific journal
• Hokkaido Satellite Project : Satellite System Design
  Kosei ISHIMURA; Sang-Wook KIM; Yasumasa ITOH; Tsuyoshi TOTANI; Kouichiro SUGIMOTO; Akihiro NAKAMURA; Mitsuru FUKUSHIMA; Ryuichi MITSUHASHI; Shin SATORI
  Proceedings of the 24th International Symposium on Space Technology and Science, 2004-n-12, 896, 901, 2004, [Peer-reviewed]
  English, International conference proceedings
• 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, Scientific journal
• Evaluation of the usage of the VSRL and an example at an educational project
  Shigeo Yoshikawa; Tsuyoshi Totani; Harunori Nagata; Isao Kudo
  Journal of Japan Distane Learing Association, 4, 13, 20, 日本ディスタンスラーニング学会, Mar. 2003, [Peer-reviewed]
  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
• 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, [Peer-reviewed]
  Japanese, 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, 日本マイクログラビティ応用学会, Apr. 2002, [Peer-reviewed]
  Japanese, Scientific journal
• Construction and operation of collaborated research support environment using Internet
  Shigeo Yoshikawa; Tsuyoshi Totani; Harunori Nagata; Isao Kudo
  Journal of Japan Distance Learing Association, 3, 19, 25, 日本ディスタンスラーニング学会, Mar. 2002, [Peer-reviewed]
  Japanese, Scientific journal
• 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, [Peer-reviewed]
  English, Scientific journal
• 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, [Peer-reviewed]
  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, [Peer-reviewed]
  Japanese, Scientific journal
• 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, 一般社団法人日本機械学会, 2001, [Peer-reviewed]
  English, Scientific journal
• Three-Dimensional Numerical Analysis on Transient Marangoni Convection in a Liquid Droplet Using Spherical Harmonic Spectral Method
  TOTANI Tsuyoshi; KURODA Akiyoshi; KUDO Kazuhiko
  Transactions of the Japan Society of Mechanical Engineers. B, 65, 629, 267, 274, 一般社団法人日本機械学会, Jan. 1999, [Peer-reviewed]
  Japanese, Scientific journal, A method is developed to analyze the three-dimensional transient Marangoni convection in a liquid droplet heated by a concentric warm rigid sphere set in the center and cooled uniformly from its surroundings. As the system is unstable and the convection is very sensitive to the temperature gradients along the surface, it is required for the scheme to be highly accurate and be free from the effects of the polar singularities. For the purpose, a spherical harmonic spectral method is developed to analyze the flow and temperature fields in the droplet on the three-dimensional spherical coordina...
• Heat Storage Material without Phase-change for Micro and Nano Satellite
  戸谷 剛
  [Peer-reviewed]
  English, Scientific journal

• 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
• 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
• Trial fabrication of the morphing wing for UAV by CFRP with applying the electrodeposition resin molding method and evaluation of the aerodynamic properties
  片桐一彰; 山口真平; 川北園美; 本田真也; 戸谷剛; 佐々木克彦; 小木曽望; 玉山雅人, 飛行機シンポジウム講演集(CD-ROM), 57th, 2019
• 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
• Addition of Heat Storage Properties to CFRP by Using Electoro-activated Resin Molding
  片桐一彰; 山口真平; 永廣卓哉; 尾崎友厚; 園村浩介; 吉岡弥生; 垣辻篤; 後藤凌平; 戸谷剛; 南沙也加; 本田真也; 佐々木克彦, 宇宙科学技術連合講演会講演集(CD-ROM), 61st, 2017
• 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
  清谷優理香; 平井翔大; 平井翔大; KAMPS Landon; 山口亮; 櫻井和人; 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), 2017, 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
• 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
• 端面燃焼式ハイブリッドロケットの推力制御特性に関する研究—Investigation of the Throttling Characteristics of Axial-injection End-burning Type Hybrid Rockets
  齋藤 勇士; 横井 俊希; 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, 60, 6p, Sep. 2016
  日本航空宇宙学会, Japanese
• 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, 01 Jan. 2016
• 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
• 液滴ラジエータにおける平行液滴流からの 熱放射に関する数値解析—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, 宇宙科学技術連合講演会講演集, 58, 3p, Nov. 2014
  日本航空宇宙学会, Japanese
• 推力15kN級CAMUI型ハイブリッドロケットモーターの開発—Development of 15 kN thrust class CAMUI-type Hybrid Rocket Motor
  川端 良輔; 永田 晴紀; 戸谷 剛, 宇宙科学技術連合講演会講演集, 58, 4p, Nov. 2014
  日本航空宇宙学会, 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
• 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, 2014
  Japanese
• 超小型衛星の熱設計手順の提案—Propose of Procedure of Thermal Design of Micro and Nano Satellite
  戸谷 剛; Tilok Kumar Das; 脇田 督司, 宇宙科学技術連合講演会講演集, 57, 5p, Oct. 2013
  東京 : 日本航空宇宙学会, 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 Izumo; Masashi Wakita; Tsuyoshi Totani; Harunori Nagata, Advances in the Astronautical Sciences, 146, 79, 84, 24 Apr. 2013
• 北海道学生会の活動(学生会だより)
  戸谷 剛, 日本機械学會誌, 115, 1123, 05 Jun. 2012
  一般社団法人日本機械学会, Japanese
• 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
• 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
• CAMUI型固体燃料後退速度式の導出方法に関する検討
  野原正寛; 出雲弘一; 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, 2011 (CD-ROM), ROMBUNNO.S192013, 10 Sep. 2011
  Japanese
• 太陽同期軌道を周回する超小型衛星の熱設計に関する研究
  小川洋人; 井上遼太; 戸谷剛; 脇田督司; 永田晴紀, 日本機械学会年次大会講演論文集, 2011 (CD-ROM), ROMBUNNO.S192022, 10 Sep. 2011
  Japanese
• H3 Development of VNIR Hyperspectral Camera HSC for small/ micro satellites
  Satori Shin; Aoyanagi Yoshihide; Totani Tsuyoshi; Nakamura Akihiro; Yasunaka Toshihiko; Ishikawa Tomohiro; Takeyama Norihide; Ueyama Yoshihiro, スペース・エンジニアリング・コンファレンス講演論文集 : Space Engineering Conference, 2010, 19, "H3, 1"-"H3-5", 27 Jan. 2011
  Hyper Spectral Camera (HSC) is a VNIR (visible and near-infrared) hyperspectral sensor for micro satellites. The objective of the HSC is to provide high-quality hyperspectral images and to utilize for agricultural area. The HSC acquires GSD (ground sampling distance) of 15m over a swath width of 15km. The spectrometer is equipped with a direct vision prism and covers wavelength range from 450nm to 1000nm. The result of the optical design indicated that high imaging quality at each wavelength is achieved. The HSC also has data handling subsystem. High-general versatility for data handling an..., The Japan Society of Mechanical Engineers, Japanese
• 超小型衛星搭載のための可視・近赤外帯ハイパースペクトルカメラHSCの開発
  佐鳥新; 青柳賢英; 戸谷剛; 中村明弘; 安中俊彦; 石川智浩; 武山芸英; 上山善弘, 日本機械学会スペース・エンジニアリング・コンファレンス(CD−ROM), 19th, ROMBUNNO.H3, 2011
  Japanese
• 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
• ほどよし1号機の開発状況
  宮下直己; 中村友哉; 中須賀真一; 岩崎晃; 戸谷剛; 佐原宏典; 江野口章人; 武山芸英; 早川義彰; 山口耕司, 宇宙科学技術連合講演会講演集(CD−ROM), 55th, ROMBUNNO.3S18, 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
• 小型ハイパースペクトルセンサHSCに搭載するデータ処理装置の開発
  上山善弘; 佐鳥新; 青柳賢英; 戸谷剛; 石川智浩; 中村明広, 宇宙科学技術連合講演会講演集(CD−ROM), 55th, ROMBUNNO.3D11, 2011
  Japanese
• 超小型衛星搭載用ハイパースペクトルセンサHSCの開発
  青柳賢英; 上山善弘; 佐鳥新; 戸谷剛; 山口耕司; 武山芸英; 中村明広, 宇宙科学技術連合講演会講演集(CD−ROM), 55th, ROMBUNNO.3D10, 2011
  Japanese
• 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
• 紫外線硬化樹脂に金属膜を設けた表面微細周期構造の光学特性
  石川直幸; 戸谷剛; 脇田督司; 永田晴紀, Thermophys Prop, 31st, 118-120, 17 Nov. 2010
  Japanese
• 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, 17 Nov. 2010
  Japanese
• 拡大する環状流路を伝播する円環デトネーション波に流路幅が与える影響
  寺坂昭宏; 田村正佳; 脇田督司; 戸谷剛; 永田晴紀, 日本機械学会北海道支部講演会講演概要集, 49th, 163-164, 07 Nov. 2010
  Japanese
• 樹脂製表面微細周期構造の分光特性
  石川直幸; 戸谷剛; 永田晴紀; 脇田督司, 日本機械学会北海道支部講演会講演概要集, 49th, 133-134, 07 Nov. 2010
  Japanese
• 遺伝的アルゴリズムを用いたCAMUI型燃料グレインの最適設計
  野原正寛; 金子雄大; 萩原俊輔; 脇田督司; 戸谷剛; 永田晴紀, 日本機械学会北海道支部講演会講演概要集, 49th, 161-162, 07 Nov. 2010
  Japanese
• 512 Spectroscopic Characteristics of Resinous Microstructure Surface
  ISHIKAWA Naoyuki; TOTANI Tsuyoshi; NAGATA Harunori; WAKITA Masashi, 北海道支部講演会講演概要集, 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, 北海道支部講演会講演概要集, 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, 北海道支部講演会講演概要集, 2010, 49, 163, 164, 07 Nov. 2010
  The Japan Society of Mechanical Engineers, Japanese
• 小型CAMUI式ハイブリッドロケットの開発と運用
  竹腰卓博; 佐藤峻哉; 田村正佳; 萩原俊輔; 脇田督司; 戸谷剛; 永田晴紀; 植松努, 日本機械学会年次大会講演論文集, 2010, Vol.5, 361-362, 04 Sep. 2010
  Japanese
• 超小型宇宙機UNITEC‐1の熱設計と軌道上温度
  戸谷剛; 脇田督司; 永田晴紀, 日本機械学会年次大会講演論文集, 2010, Vol.5, 359-360, 04 Sep. 2010
  Japanese
• ラバールノズルの超音速域における伝熱が推力および比推力に与える影響
  岩城裕樹; 戸谷剛; 脇田督司; 永田晴紀, 日本機械学会年次大会講演論文集, 2010, Vol.5, 407-408, 04 Sep. 2010
  Japanese
• CAMUI型固体燃料の燃料後退予測式取得方法に関する検討
  萩原俊輔; 金子雄大; 野原正寛; 永田晴紀; 戸谷剛; 脇田督司; 松岡常吉; 植嶋健太; 植松努, 日本機械学会年次大会講演論文集, 2010, Vol.5, 367-368, 04 Sep. 2010
  Japanese
• Report on the 47th National Heat Transfer Symposium of Japan
  CHIKAHISA Takemi; OSONE Yasuo; KURODA Akiyoshi; KUWAHARA Fujio; SAKASHITA Hiroto; TOTANI Tsuyoshi; NAKAMURA Yuji; YAMADA Masahiko; TABE Yutaka, Journal of the Heat Transfar Society of Japan, 49, 208, 19, 28, 01 Jul. 2010
  日本伝熱学会, 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, 2010
  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
• 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
• Investigation of an Evaluation Method on the Improvement of Thrust and Specific Impulse by Nozzle Heating
  NAGANUMA Tetsushi; IWAKI Yuuki; SATO Shunya; TOTANI Tsuyoshi; WAKITA Masashi; NAGATA Harunori, JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 58, 677, 171, 177, 2010
  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., THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, Japanese
• CAMUI式ハイブリッドロケットの小型化および繰り返し運用
  佐藤峻哉; 竹腰卓博; 田村正佳; 萩原俊輔; 脇田督司; 戸谷剛; 永田晴紀, 日本機械学会北海道支部講演会講演概要集, 48th, 211-212, 28 Nov. 2009
  Japanese
• 小型ハイブリッドロケットにおける能動的ロール制御システムの構築
  田村正佳; 佐藤俊哉; 竹腰卓博; 萩原俊輔; 脇田督司; 戸谷剛; 永田晴紀, 日本機械学会北海道支部講演会講演概要集, 48th, 213-214, 28 Nov. 2009
  Japanese
• 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, 北海道支部講演会講演概要集, 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, 北海道支部講演会講演概要集, 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
• Improvement of thrust and specific impulse by convective heat transfer in Laval nozzle
  IWAKI YUKI; NAGANUMA TETSUSHI; SATO SHUN'YA; TOTANI TSUYOSHI; WAKITA MASASHI; NAGATA HARUNORI, 日本機械学会年次大会講演論文集, 2009, Vol.5, 297-298, 12 Sep. 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
• 超小型人工衛星HIT‐SATの実験結果
  三橋龍一; 佐藤立博; 竹浪恭平; 中尾明弘; 羽鳥翼; 戸谷剛; 加瀬誠志; 佐鳥新, 電子情報通信学会大会講演論文集, 2009, 317, 04 Mar. 2009
  Japanese
• B-2-60 Experiment result of nano-satellite HIT-SAT
  Mitsuhashi Ryuichi; Sato Tatsuhiro; Takenami Kyohei; Nakao Akihiro; Hatori Tsubasa; Totani Tsuyoshi; Kase Satoshi; Satori Shin, Proceedings of the IEICE General Conference, 2009, 1, 317, 317, 04 Mar. 2009
  The Institute of Electronics, Information and Communication Engineers, 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
• 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
• 超小型人工衛星HIT‐SATの運用結果
  三橋龍一; 佐藤立博; 竹浪恭平; 安部潤一郎; 中尾明弘; 羽鳥翼; 戸谷剛; 佐鳥新, 電気・情報関係学会北海道支部連合大会講演論文集(CD−ROM), 2008, ROMBUNNO.0001, 25 Oct. 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後退速度の粒径依存性
  羽柴健太; 堺裕哉; 戸谷剛; 永田晴紀, 日本機械学会北海道支部講演会講演概要集, 47th, 149-150, 27 Sep. 2008
  Japanese
• 反射板を用いたPDEイニシエーターにおける反射板径の最適化に関する研究
  浅田隆利; 脇田督司; 戸谷剛; 永田晴紀, 日本機械学会北海道支部講演会講演概要集, 47th, 151-152, 27 Sep. 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, 北海道支部講演会講演概要集, 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, 北海道支部講演会講演概要集, 2008, 47, 151, 152, 27 Sep. 2008
  The Japan Society of Mechanical Engineers, Japanese
• Improvement of the thrust and specific impulse by elongating and heating the Laval nozzle
  IWAKI YUKI; NAGANUMA TETSUSHI; TOTANI TSUYOSHI; NAGATA HARUNORI, 日本機械学会年次大会講演論文集, 2008, Vol.5, 395-396, 02 Aug. 2008
  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
• 90・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, 電子情報通信学会大会講演論文集, 2008, 266, 05 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
• 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
• Design and Experiments of a small Hyperspectral sensor
  AOYAGI YOSHIHIDE; NISHIZATO SHIN'YA; SATORI SHIN; TOTANI TSUYOSHI; HARA URUMI; YASUNAKA TOSHIHIKO; NAKAMURA AKIHIRO, 宇宙科学技術連合講演会講演集(CD−ROM), 52nd, ROMBUNNO.1H18, 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
• 二段燃焼式ハイブリッドロケット一次燃焼室における粒状燃料のガス化履歴
  片野光; 羽柴健太; 堺裕哉; 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, 129-134, 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
• 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
• 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
• 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
• 二段燃焼式ハイブリッドロケット一次燃焼室における粒状燃料のガス化履歴
  片野光; 羽柴健太; 永田晴紀; 戸谷剛, 燃焼シンポジウム講演論文集, 45th, 506-507, 20 Nov. 2007
  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
• 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
• 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, 北海道支部講演会講演概要集, 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, 北海道支部講演会講演概要集, 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, 北海道支部講演会講演概要集, 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, 北海道支部講演会講演概要集, 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, 北海道支部講演会講演概要集, 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, 北海道支部講演会講演概要集, 2007, 46, 127, 128, 29 Sep. 2007
  The Japan Society of Mechanical Engineers, Japanese
• CAMUI方式を用いたハイブリッドロケット燃料の燃焼速度に及ぼすスケールの効果
  森一大; 伊藤光紀; 柿倉彰仁; 金子雄大; 植嶋健太; 室井典和; 戸谷剛; 植松努; 永田晴紀, 日本機械学会北海道支部講演会講演概要集, 46th, 137-138, 25 Sep. 2007
  Japanese
• CAMUIハイブリッドロケット燃料グレインの形状履歴の予測
  柿倉彰仁; 伊藤光紀; 金子雄大; 森一大; 植嶋健太; 室井典和; 植松努; 戸谷剛; 永田晴紀, 日本機械学会北海道支部講演会講演概要集, 46th, 127-128, 25 Sep. 2007
  Japanese
• 傾斜壁面に衝突する液滴流の飛散と捕集を分ける閾値に関する研究
  川上哲史; 由利泰史; 戸谷剛; 永田晴紀, 日本機械学会北海道支部講演会講演概要集, 46th, 133-134, 25 Sep. 2007
  Japanese
• 液滴ラジエータの作動流体循環流量の自動制御に関する研究
  由利泰史; 川上哲史; 戸谷剛; 永田晴紀, 日本機械学会北海道支部講演会講演概要集, 46th, 129-130, 25 Sep. 2007
  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粒状燃料のガス化履歴
  片野光; 羽柴健太; 戸谷剛; 永田晴紀, 日本機械学会北海道支部講演会講演概要集, 46th, 135-136, 25 Sep. 2007
  Japanese
• 水を推進剤とした太陽熱推進軌道変換機によるペイロード輸送ミッションの設計
  岩城裕樹; 戸谷剛; 永田晴紀, 日本機械学会北海道支部講演会講演概要集, 46th, 131-132, 25 Sep. 2007
  Japanese
• The Attitude Control Experiments of "HIT-SAT" and the Future Development Satellite
  MATSUSHIMA KOTA; ISHIMURA KOSEI; IGARASHI DAIGAKU; TOTANI TSUYOSHI; SAKAKIBARA TAKAHIRO; SATORI SHIN; MITSUHASHI RYUICHI; AOYANAGI YOSHIHIDE; TANAKA YOSHINORI; SATO TATSUHIRO; NAKAMURA AKIHIRO; YASUNAKA TOSHIHIKO; HORI KOTARO; HIROTA NORIHISA, 日本機械学会年次大会講演論文集, 2007, Vol.5, 391-392, 07 Sep. 2007
  Japanese
• Electrical power subsystem design of Pico satellite "HIT-SAT"
  NISHIDATE JUN; SATO TATSUHIRO; AOYANAGI YOSHIHIDE; ONO TSUTOMU; TAKENAMI KYOHEI; SATORI SHIN; MITSUHASHI RYUICHI; HIROTA NAOHISA; ISHIMURA KOSEI; MATSUSHIMA KOTA; TOTANI TSUYOSHI; SAKAKIBARA TAKAHIRO; HORI KOTARO; ERA SATOSHI; NAKAMURA AKIHIRO; UEMATSU TSUTOMU; YASUNAKA TOSHIHIKO, 日本機械学会年次大会講演論文集, 2007, Vol.5, 347-348, 07 Sep. 2007
  Japanese
• On-orbit Thermal Data and Review of the Thermal Analytical Model of HIT-SAT
  SAKAKIBARA TAKAHIRO; TOTANI TSUYOSHI; ABE RYO; YASUNAKA TOSHIHIKO; ISHIMURA KOSEI; MATSUSHIMA KOTA; SATORI SHIN; MITSUHASHI RYUICHI; SATO TATSUHIRO; NISHIDATE JUN; AOYANAGI YOSHIHIDE; ONO TSUTOMU; TANAKA YOSHINORI; NAKAMURA AKIHIRO; HORI KOTARO, 日本機械学会年次大会講演論文集, 2007, Vol.5, 389-390, 07 Sep. 2007
  Japanese
• 4123 The Attitude Control Experiments of "HIT-SAT" and the Future Development Satellite
  MATSUSHIMA Kouta; ISHIMURA Kosei; IGARASHI Daigaku; TOTANI Tsuyoshi; SAKAKIBARA Takahiro; SATORI Shin; MITSUHASHI Ryuichi; AOYANAGI Yoshihide; TANAKA Yoshinori; SATO Tatsuhiro; NAKAMURA Akihiro; YASUNAKA Toshihiko; HORI Koutaro; HIROTA Norihisa, The proceedings of the JSME annual meeting, 2007, 5, 391, 392, 07 Sep. 2007
  "HIT-SAT" is a small satellite to demonstrate performance of the bus systems of "Hokkaido Satellite". The main purpose of the attitude control system of "HIT-SAT" is to get basis data for the attitude control and determination system of "Hokkaido Satellite". "HIT-SAT" was launched on Sep. 23, 2006 by M-V-7. Attitude control system of "HIT-SAT" could get magnetometer data and gyro data on orbit. This paper describes the attitude determination from magnetometer data obtained on orbit., The Japan Society of Mechanical Engineers, Japanese
• 4122 On-orbit Thermal Data and Review of the Thermal Analytical Model of HIT-SAT
  SAKAKIBARA Takahiro; TOTANI Tsuyoshi; ABE Ryo; YASUNAKA Toshihiko; ISHIMURA Kosei; MATSUSHIMA Kouta; SATORI Shin; MITSUHASHI Ryuichi; SATO Tatsuhiro; NISHIDATE Jun; AOYANAGI Yoshihide; Ono Tsutomu; TANAKA Yoshinori; NAKAMURA Akihiro; HOR Kotaro, The proceedings of the JSME annual meeting, 2007, 5, 389, 390, 07 Sep. 2007
  HIT-SAT has been designed and developed in order to examine functions of the bus system. It was successfully launched by M-V rocket #7 on 23rd September 2006. The volume and weight of HIT-SAT are about 12[cm^3] and 2.7[kg], respectively. HIT-SAT has a flame-panel structure that consists of 6 panels, 4 columns and 2 shelves made of the aluminum alloy that has a high conductivity. The passive thermal control is adopted. Thermal analysis was conducted using Thermal Desktop/SINDA/FLUINT before launch. However, the result of thermal analysis is quite different from on-orbit thermal data of HIT-S..., The Japan Society of Mechanical Engineers, Japanese
• 4101 Electrical power subsystem design of Pico satellite "HIT-SAT"
  西舘 純; 佐藤 立博; 青柳 賢英; 大野 努; 竹浪 恭平; 佐鳥 新; 三橋 龍一; 廣田 尚久; 石村 康生; 松島 幸太; 戸谷 剛; 榊原 隆浩; 堀 耕太郎; 江良 聡; 中村 明広; 植松 努; 安中 俊彦, The proceedings of the JSME annual meeting, 2007, 5, 347, 348, 07 Sep. 2007
  A CubeSat size class "HIT-SAT" is a micro satellite that developed by Hokkaido CubeSat development team. Its volume and weight is 2.7kg and 12cm cubed. It was fixed in the sub payload space of M-V-7, and was ejected after main satellite separation on September 23,2006. The orbit is sun-synchronous orbit of the altitude of 279-660[km] and the inclination of 98.32[deg]. The purpose is to examine some functions of the bus system. This research report describes an electric al power subsystem design. The major difficulty of Electrical Power System is surely OFF and ON. The OFF needs to be guaran..., The Japan Society of Mechanical Engineers, Japanese
• B-2-51 Satellite Communication System for the HIT-SAT
  Mitsuhashi Ryuichi; Sato Tatsuhiro; Takeoka Kazuhiko; Nishidate Jun; Takenami Kyohei; Totani Tsuyoshi; Ishimura Kosei; Kase Satoshi; Satori Shin, Proceedings of the IEICE General Conference, 2007, 1, 299, 299, 07 Mar. 2007
  The Institute of Electronics, Information and Communication Engineers, Japanese
• In-plane deformation of the multi-cellular inflatable structure-contact between cell and partition-
  ISHIMURA KOSEI; HASHIBA KENTA; KATO RYUZO; TOTANI TSUYOSHI; HIGUCHI KEN, 構造強度に関する講演会講演集, 49th, 187, 189, 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
• Thermal and Structural Design of Subminiature Satellite "HIT-SAT"
  Memoirs of the Hokkaido Institute of Technology, 35, 105, 111, 2007
• 119 Rigidity of Multi-Cellular Inflatable Structures
  KATO Ryuzo; TOTANI Tsuyoshi; ISHIMURA Kosei; NAGATA Harunori, 北海道支部講演会講演概要集, 2006, 45, 37, 38, 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, 北海道支部講演会講演概要集, 2006, 45, 31, 32, 25 Sep. 2006
  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, 北海道支部講演会講演概要集, 2006, 45, 33, 34, 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, 北海道支部講演会講演概要集, 2006, 45, 35, 36, 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, 北海道支部講演会講演概要集, 2006, 45, 39, 40, 25 Sep. 2006
  The Japan Society of Mechanical Engineers, Japanese
• Application of a multi-cellular inflatable structure to large space systems
  ISHIMURA KOSEI; HIGUCHI KEN; TOTANI TSUYOSHI; KATO RYUZO, 宇宙科学技術連合講演会講演集(CD-ROM), 50th, 3E11, 2006
  Japanese
• 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
• 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, 北海道支部講演会講演概要集, 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, 北海道支部講演会講演概要集, 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, 北海道支部講演会講演概要集, 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, 北海道支部講演会講演概要集, 2005, 44, 76, 77, 08 Oct. 2005
  The Japan Society of Mechanical Engineers, Japanese
• Creation of a Market for Small Rocket Experiment through CAMUI Hybrid Rocket
  NAGATA Harunori; WATANABE Mikio; ITO Mitsunori; MAEDA Takenori; TOTANI Tsuyoshi; KUDO Isao, スペース・エンジニアリング・コンファレンス講演論文集 : 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
• 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
• 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
• 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
  English
• Preliminary Design of Fully Reusable CAMUI Hybrid Rocket for Upper-layers Stratosphere Observations
  MIURA Takashi; WATANABE Mikio; NAGATA Harunori; TOTANI Tsuyosi; KUDO Isao, 北海道支部講演会講演概要集, 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, 北海道支部講演会講演概要集, 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, 北海道支部講演会講演概要集, 2003, 43, 162, 163, 28 Sep. 2003
  The Japan Society of Mechanical Engineers, Japanese
• 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, 31 Jan. 2003
  日本マイクログラビティ応用学会, Japanese
• TED-AJ03-270 NUMERICAL ANALYSIS OF SURFACE TENSION DRIVEN CONVECTION IN A LIQUID DROPLET USING A SPECTRAL METHOD :
  KURODA Akiyoshi; TOTANI Tsuyoshi; KUDO Kazuhiko, Proceedings of the ... ASME/JSME Thermal Engineering Joint Conference, 2003, 6, 376, 376, 2003
  A three-dimensional numerical analysis is performed to study the Marangoni convection in a spherical liquid droplet cooled uniformly from its surroundings. Like the Benard cells observed on flat liquid surfaces cooled from the surface, the convection occurs even for curved liquid surfaces under appropriate conditions. The essential physical features of the phenomenon come from the fact that surface tension is a monotonous decreasing function of temperature in most fluids. Consider a hot liquid droplet cooling from its surface. When the free surface of a fluid layer is not under a uniform temperature, surface traction from the hot areas to cold areas causes a motion within the fluid. At the hot spot on the surface, warm fluid is drawn towards the surface from the inside of the droplet, which keeps the spot being hot. And this hot fluid spreads across the surface, cooling as it goes. The decrease in temperature across the surface is accompanied by an increase in surface tension that tends to maintain the convection. This phenomenon of the surface-tension-driven convection may affect the heat and mass transport within a small droplet in spray combustion or spray drying. And it may also play an important roll within a droplet under micro-gravity condition, a droplet radiator for example, which may be used as a compact heat-releasing device for space stations. In out study, a method is developed to analyze the three-dimensional transient Marangoni convection in a spherical liquid droplet that is cooled uniformly from its surroundings. As the field is unstable and is very sensitive to the temperature gradients along the surface, it is required for the numerical scheme to be highly accurate and be free from the effects of the polar and central singularities. For the purpose, a spherical harmonic spectral method was adopted to analyze the flow and temperature fields in the droplet on the spherical coordinates. And the transports equation of rƒ (r : radius coordinate, ƒ : velocity components, pressure, temperature) is numerically solved to avoid the singularity at the center of the droplet. The validity of the numerical method is checked at first. And some calculations are carried out to study the effects of parameters, i.e., Marangoni number, Prandt1 number, on the numerical results and it is found that the net heat transport rate within the droplet is affected by the surface tension driven convection when Ma>1000.[figure], 日本機械学会, English
• 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
• 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, 北海道支部講演会講演概要集, 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, 北海道支部講演会講演概要集, 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, 北海道支部講演会講演概要集, 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
• 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
• 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
• 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
• 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, 北海道支部講演会講演概要集, 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, 北海道支部講演会講演概要集, 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
• 720 Static Test Firings of Jet-Impinging Hybrid Rocket for Flight Model Design
  NAKAYAMA Hisahiro; WATANABE Mikio; NAGATA Harunori; KUDO Isao; TOTANI Tsuyoshi, 北海道支部講演会講演概要集, 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
• 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
• 506 Construction of Virtual Space Research Laboratory and Application to Engineering support
  YOSHIKAWA Shigeo; TOTANI Tsuyoshi; NAGATA Harunori; KUDO Isao, 北海道支部講演会講演概要集, 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, 北海道支部講演会講演概要集, 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
• 514 Response Time of the Hydrogen Concentration Probe for a Supersonic Flow
  SASAKI Masahiro; NAKAMURA Daisuke; NAGATA Harunori; TOTANI Tsuyosi; KUDO Isao, 北海道支部講演会講演概要集, 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, 北海道支部講演会講演概要集, 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, 北海道支部講演会講演概要集, 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
• 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
• Totani, T., Itami, M., Nagata, H., Kudo, I., Iwasaki, A. and Hosokawa, S.:"Performance of Droplet Generator and Droplet Collector in Liquid Droplet Radiator Under Microgravity", Drop Tower Days 2000 in Bremen, Extended Abstracts:28-30(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
• 「微小重力下における液滴ラジエータ要素の性能確認」
  『日本マイクログラビティ応用学会誌』, 16 Supplement, 114, 115, 1999
• KURODA, A., TOTANI, T., and KUDO, K.:"Three-dimensional Numerical Analysis on Transient Marangoni Convection in a Liquid Droplet Using Spherical Harmonic Spectral Method", Proceedings of the 5th ASME/JSME Joint Thermal Engineering Conference, 【1/1(CD-R・・・
  1999
  KURODA, A., TOTANI, T., and KUDO, K.:"Three-dimensional Numerical Analysis on Transient Marangoni Convection in a Liquid Droplet Using Spherical Harmonic Spectral Method", Proceedings of the 5th ASME/JSME Joint Thermal Engineering Conference, 【1/1(CD-ROM) AJTE99-6372】(1999)
• 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

• 次世代自動車の熱マネジメント
  戸谷 剛, 固相ー固相の相変化で蓄熱する蓄熱材
  株式会社技術情報センター, 25 Dec. 2020, 9784861048197, 326-332, Japanese, Scholarly book, [Contributor]
• 応用数理ハンドブック
  戸谷 剛, 衛星の熱解析
  朝倉書店, Nov. 2013, 9784254111415, Japanese, Dictionary or encycropedia, [Contributor]
• Small Satellite Missions for Earth Observation
  Yoshihide Aoyanagi; Shin Satori; Tsuyoshi Totani; Toshihiko Yasunaka; Akihiro Nakamura; Yusuke Takeuchi, Development of Spaceborne Small Hyperspectral sensor HSC-III for Micro Satellite
  Springer Berlin Heidelberg, 2010, 9783642035005, English, Scholarly book, [Contributor]

• Development and Flight Demostration of 5000 N Thrust Class CAMUI Type Hybrid Rocket
  Harunori Nagata; Masashi Wakita; Tsuyoshi Totani; Tsutomu Uematsu; Yuki Yasumoto; Ryuichi Mitsuhashi
  56th Space Sciences and Technology Conference, 22 Nov. 2012, The Japan Society for Aeronautical and Space Sciences, Japanese, Oral presentation
  Beppu, [Domestic Conference]
• Thermal design of micro satellite using simple nodal and multi nodal analyses for short development period
  Hiroto Ogawa; Ryota Inoue; Tsuyoshi Totani; Masashi Wakita; Harunori Nagata
  56th Space Sciences and Technology Conference, 21 Nov. 2012, The Japan Society for Aeronautical and Space Sciences, Japanese, Oral presentation
  Beppu, [Domestic Conference]
• Development of Heat Storage Material with Crystal Structure Transformation for Micro Satellite
  Tsuyoshi Totani; Toshifumi Satoh; Masashi Wakita; Harunori Nagata
  56th Space Sciences and Technology Conference, 20 Nov. 2012, The Japan Society for Aeronautical and Space Sciences, Japanese, Oral presentation
  Beppu, [Domestic Conference]
• Wave Length Selective Radiator with Microcavity
  Tsuyoshi Totani; Masashi Wakita; Harunori Nagata
  Thermal Engineering Conference 2012, 18 Nov. 2012, Thermal Engineering Division, The Japan Society of Mechanical Engineers, Japanese, Oral presentation
  Kumamoto, [Domestic Conference]
• Optical Properties of Wavelength-selective Radiator with Periodic Microcavities
  Tsuyoshi Totani; Naoyuki Ishikawa; Minoru Iwata; Masashi Wakita; Harunori Nagata
  The 3rd International Forum on Heat Transfer, 13 Nov. 2012, Heat Transfer Society of Japan, English, Poster presentation
  Nagasaki, [International presentation]
• Thermal Analyses and Guideline for Thermal Design of Nano and Micro Satellites on Sun-synchronous Orbits
  Ryota Inoue; Tsuyoshi Totani; Hiroto Ogawa; Masashi Wakita; Harunori Nagata
  UN/Japan Nano-Satellite Symposium, 10 Oct. 2012, United Nations, The University of Tokyo, English, Poster presentation
  Nagoya, [International presentation]
• Heat Storage Performance of Heat Storage Material with crystal Transformation
  Tsuyoshi Totani; Toshifumi Satoh; Masashi Wakita; Harunori Nagata
  The 33rd Japan Symposium on Thermophysical Properties, 05 Oct. 2012, Japan Society of Thermophysical Properties, Japanese, Oral presentation
  Osaka, [Domestic Conference]
• Performance of Wave Length Selective Radiator with Microgravity
  Tsuyoshi Totani; Masashi Wakita; Harunori Nagata
  The 33rd Japan Symposium on Thermophysical Properties, 04 Oct. 2012, Japan Society of Thermophysical Properties, Japanese, Oral presentation
  Osaka, [Domestic Conference]
• Thermal Analyses and Thermal Design of Nano and Micro Satellites on Sun-synchronous Orbits
  Ryota Inoue; Hiroto Ogawa; Tsuyoshi Totani; Masashi Wakita; Harunori Nagata
  Mechanical Engineering Congress, 2012 Japan, 10 Sep. 2012, The Japan Society of Mechanical Engineers, Japanese, Oral presentation
  Kanazawa, [Domestic Conference]
• 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
  Tsunetaro Himono; Kazuya Sajiki; Masashi Wakita; Tsuyoshi Totani; Harunori Nagata
  44th Fluid Dynamic Conference/Aerospace Numerical Simulation Symposium 2012, 05 Jul. 2012, The Japan Society for Aeronautical and Space Sciences, Japan Aerospace Exploration Agency, Japanese, Oral presentation
  Toyama, [Domestic Conference]
• Characteristics of Normal Emissivity of Periodic Microstructure with Metal Layer
  Tsuyoshi Totani; Naoyuki Ishikawa; Masashi Wakita; Harunori Nagata
  The 49th National Heat Transfer Symposium, 30 May 2012, Heat Transfer Society of Japan, Japanese, Oral presentation
  Toyama, [Domestic Conference]
• Thermal Design Method of Nano and Micro Satellites on Sun-synchronous Orbits by Using One-nodal and Two-nodal Analyses
  Ryota Inoue; Hiroto Ogawa; Tsuyoshi Totani; Masashi Wakita; Harunori Nagata
  The 2012 Annual Meeting of the Northern Branch of the Japan Society for Aeronaoutical and Space Sciences, 15 Mar. 2012, Northern Branch of The Japan Society for Aeronautical and Space Sciences, Japanese, Oral presentation
  Muroran, [Domestic Conference]
• Thermal Analyses of Nano and Micro Satellites on Sun-synchronous Orbits
  Ryota Inoue; Hiroto Ogawa; Tsuyoshi Totani; Masashi Wakita; Harunori Nagata
  日本機械学会北海道学生会第41回学生員卒業研究発表講演会, 03 Mar. 2012, Hokkaido Students Branch, Japan Society of Mechanical Engineers, Japanese, Oral presentation
  Sapporo, [Domestic Conference]
• Cylindrical exploding detonation wave propagating in large-bore plate combustor
  Kazuya Sajiki; Akihiro Terasaka; Masashi Wakita; Tsuyoshi Totani; Harunori Nagata
  43rd Fluid Dynamic Conference/Aerospace Numerical Simulation Symposium 2011, 07 Jul. 2011, The Japan Society for Aeronautical and Space Sciences, Japan Aerospace Exploration Agency, The Japan Society of Fluid Mechanics, Japanese, Oral presentation
  Tokyo, [Domestic Conference]
• Performance Evaluation of a Liquid Droplet Radiator Under Microgravity
  伊丹 雅洋; 戸谷 剛; 永田 晴紀; 工藤 勲; 岩崎 晃; 細川 俊介
• 「微小重力下における液滴ラジエータ要素の性能確認」
• KURODA, A., TOTANI, T., and KUDO, K.:"Three-dimensional Numerical Analysis on Transient Marangoni Convection in a Liquid Droplet Using Spherical Harmonic Spectral Method", Proceedings of the 5th ASME/JSME Joint Thermal Engineering Conference, 【1/1(CD-R・・・
• Performance Test of Liquid Droplet Radiator Elements Under Microgravity
  伊丹 雅洋; 戸谷 剛; 永田 晴紀; 工藤 勲; 岩崎 晃; 細川 俊介
• Totani, T., Itami, M., Nagata, H., Kudo, I., Iwasaki, A. and Hosokawa, S.:"Performance of Droplet Generator and Droplet Collector in Liquid Droplet Radiator Under Microgravity", Drop Tower Days 2000 in Bremen, Extended Abstracts:28-30(2000)
• 506 Construction of Virtual Space Research Laboratory and Application to Engineering support
  吉川 茂雄; 戸谷 剛; 永田 晴紀; 工藤 勲
• 510 Ignition Characteristic and Combustion Stability of a Jet-impinging Hybrid Rocket
  渡辺 三樹生; 中山 久広; 永田 晴紀; 戸谷 剛; 工藤 勲; 大和田 陽一
• 511 Combustion stability of End-Burning Hybrid Rocket
  橋本 望; 永田 晴紀; 戸谷 剛; 工藤 勲
• 514 Response Time of the Hydrogen Concentration Probe for a Supersonic Flow
  笹木 正裕; 中村 大輔; 永田 晴紀; 戸谷 剛; 工藤 勲
• 516 Experiments of Liquid Droplet Radiator Elements Under Microgravity
  薮田 茂; 戸谷 剛; 永田 晴紀; 工藤 勲; 伊丹 雅洋; 岩崎 晃; 細川 俊介
• 517 A Study on the Ignition of a cluster of Coal particles under Microgravity
  丹羽 由樹子; 永田 晴紀; 戸谷 剛; 工藤 勲
• Performance of Liquid Droplet Radiator Elements (collector and gear pump) Under Microgravity
  戸谷 剛; 藪田 茂; 永田 晴紀; 工藤 勲; 岩崎 晃; 細川 俊介
• 707 A Performance Test on Circulation of Working Fluid in Liquid Droplet Radiator Under Microgravity
  薮田 茂; 宮本 拓哉; 戸谷 剛; 永田 晴紀; 工藤 勲; 岩崎 晃; 細川 俊介
• 709 Measurement of Catalytic Heat Release Rate of Hydrogen-Air Premixture Gas on Platinum Wire at the Unsteady Field behind a Shock Wave
  中村 大輔; 永田 晴紀; 戸谷 剛; 工藤 勲
• 720 Static Test Firings of Jet-Impinging Hybrid Rocket for Flight Model Design
  中山 久広; 渡辺 三樹生; 永田 晴紀; 工藤 勲; 戸谷 剛
• An Experimental Test on Circulation of the Working Fluid in Liquid Droplet Radiator under Microgravity
  戸谷 剛; 薮田 茂; 宮本 拓哉; 永田 晴紀; 工藤 勲
• Development and Launch Test of a Jet Impinging Type Hybrid Rocket Engine
  永田 晴紀; 中山 久広; 渡辺 三樹生; 佐鳥 新; 高田 毅; 芝 邦明; 豊田 国昭; 中須賀 真一; 宮村 典秀; 戸谷 剛; 工藤 勲; 伊藤 献一; 大和田 陽一
• Ignition of Fuel Particle Cluster in High Temperature Environment under Microgravity Condition
  永田 晴紀; 藤井 篤之; 伊藤 献一; 戸谷 剛; 工藤 勲
• Promotion of Detonation Wave Propagation by a Reflecting Board : Effect of the Distance between the Shock-tube Exit and the Reflecting Board
  脇田 督司; 沼倉 龍介; 永田 晴紀; 戸谷 剛; 工藤 勲
• Fuel Regression Characteristics of Porous Solid Fuels for End-Burning Hybrid Rocket
  渡辺 賢; 橋本 望; 永田 晴紀; 戸谷 剛; 工藤 勲
• Gasification of solid fuel pellets in a pressurized combustion chamber
  藤井 篤之; 栗田 慎一郎; 永田 晴紀; 戸谷 剛; 工藤 勲
• Conceptual design of Jupiter probe using TOPAZ reactor
  加藤 健太郎; 永田 晴紀; 戸谷 剛; 工藤 勲
• Verification Tests on the Functions of the Liquid Droplet Radiator Elements under the short-Duration Microgravity Environment
  戸谷 剛; 永田 晴紀; 工藤 勲
• Ballistic Flight and Recovery Demonstration of Fully Reusable CAMUI Hybrid Rocket
  渡辺 三樹生; 三浦 崇志; 伊藤 光紀; 村木 祐介; 永田 晴紀; 戸谷 剛; 工藤 勲; 芝 邦明; 下岡 彩子; 久保田 勲
• Preliminary Design of Fully Reusable CAMUI Hybrid Rocket for Upper-layers Stratosphere Observations
  三浦 崇志; 渡辺 三樹生; 永田 晴紀; 戸谷 剛; 工藤 勲
• Conceptual Design of Mars Probe with Micro Rover
  増田 紀昭; 戸谷 剛; 永田 晴紀; 工藤 勲
• The Re-ignition Mechanism of Detonation Wave around a Reflecting Board
  沼倉 龍介; 脇田 督司; 永田 晴紀; 戸谷 剛; 工藤 勲
• Behavior of Concentration and Collision of Droplet Streams under Microgravity
  戸谷 剛; 児玉 拓也; 渡辺 健介; 永田 晴紀; 工藤 勲
• Creation of a Market for Small Rocket Experiment through CAMUI Hybrid Rocket
  永田 晴紀; 渡辺 三樹生; 伊藤 光範; 前田 剛典; 戸谷 剛; 工藤 勲
• 3329 Thermal Analysis and Performance Characteristics on Solar Thermal Thruster
  高野 千尋; 村木 祐介; 戸谷 剛; 永田 晴紀; 工藤 勲
• 3332 Fuel Design of 70kgf Thrust Class CAMUI type Rocket Motor
  伊藤 光紀; 前田 剛典; 永田 晴紀; 戸谷 剛; 工藤 勲; 植松 務
• 3422 Characteristics on Circulation of Working Fluid in Liquid Droplet Radiator
  戸谷 剛; 児玉 拓也; 渡辺 健介; 南部 航太; 永田 晴紀; 工藤 勲
• 216 The Effect of Incidence Shock Strength on the Performance Characteristic of PDE with a Reflecting Board
  伊藤 雄介; 脇田 督司; 沼倉 龍介; 菅田 成俊; 永田 晴紀; 戸谷 剛; 工藤 勲
• 217 Thermal-design of Staged Combustion Hybrid Rocket
  譜久山 尚; 坂本 将司; 永田 晴紀; 戸谷 剛; 工藤 勲
• 218 Transient characteristics after the change of circulation flow in Liquid Droplet Radiator
  渡辺 健介; 南部 航太; 戸谷 剛; 永田 晴紀; 工藤 勲
• 219 Concept Design of Biological Experiments for Mouse in a Reentry Space System
  飯田 恭平; 戸谷 剛; 永田 晴紀; 工藤 勲; 矢野 昭起
• 1024 Development of 400kgf thrust class CAMUI type sounding rocket
  前田 剛典; 伊藤 光紀; 柿倉 彰仁; 難波江 亮; 永田 晴紀; 戸谷 剛; 工藤 勲; 植松 努
• 119 Rigidity of Multi-Cellular Inflatable Structures
  加藤 隆造; 戸谷 剛; 石村 康生; 永田 晴紀
• 116 Deposition and Splash of Liquid Droplet Stream at Liquid Droplet Collector
  南部 航太; 川上 哲史; 由利 泰史; 戸谷 剛; 永田 晴紀
• 117 Structural Design and Mechanical Tests of HIT-SAT Flight Model
  榊原 隆浩; 戸谷 剛; 安中 俊彦; 佐鳥 新; 永田 晴紀
• 118 Engineering Model Design of Staged-Combustion Hybrid Rocket
  坂本 将司; 片野 光; 戸谷 剛; 永田 晴紀
• 120 Influence of Amount of Driver Gas Mixture on Promotion of Detonation Wave Propagation
  菅田 成俊; 脇田 督司; 沼倉 龍介; 永田 晴紀; 戸谷 剛
• B-2-51 Satellite Communication System for the HIT-SAT
  三橋 龍一; 佐藤 立博; 武岡 和彦; 西舘 純; 竹浪 恭平; 戸谷 剛; 石村 康生; 加瀬 誠志; 佐鳥 新
• The Attitude Control Experiments of "HIT-SAT" and the Future Development Satellite
  松島幸太; 石村康生; 戸谷剛; 榊原隆浩; 佐鳥新; 三橋龍一; 青柳賢英; 田中喜規; 佐藤立博; 中村明広; 安中俊彦; 堀耕太郎; 廣田尚久
• Electrical power subsystem design of Pico satellite "HIT-SAT"
  西舘純; 佐藤立博; 青柳賢英; 大野努; 竹浪恭平; 佐鳥新; 三橋龍一; 廣田尚久; 石村康生; 松島幸太; 戸谷剛; 榊原隆浩; 堀耕太郎; 江良聡; 中村明広; 植松努; 安中俊彦
• On-orbit Thermal Data and Review of the Thermal Analytical Model of HIT-SAT
  榊原隆浩; 戸谷剛; 安部良; 安中俊彦; 石村康生; 松島幸太; 佐鳥新; 三橋龍一; 佐藤立博; 西舘純; 青柳賢英; 大野努; 田中喜規; 中村明広; 堀耕太郎
• 4131 Ultrasonic Pulse-echo Measurement of Hybrid Rocket Fuel Regression
  金子 雄大; 伊藤 光紀; 柿倉 彰仁; 森 一大; 植嶋 健太; 戸谷 剛; 永田 晴紀
• 4130 Scale Effect on Fuel Regression Characteristics of CAMUI Hybrid Rocket
  伊藤 光紀; 前田 剛典; 柿倉 彰仁; 金子 雄大; 森 一大; 植松 努; 戸谷 剛; 永田 晴紀
• 4123 The Attitude Control Experiments of "HIT-SAT" and the Future Development Satellite
  松島 幸太; 石村 康生; 戸谷 剛; 榊原 隆浩; 佐鳥 新; 三橋 龍一; 青柳 賢英; 田中 喜規; 佐藤 立博; 中村 明広; 安中 俊彦; 堀 耕太郎; 廣田 尚久
• 4122 On-orbit Thermal Data and Review of the Thermal Analytical Model of HIT-SAT
  榊原 隆浩; 戸谷 剛; 安部 良; 安中 俊彦; 石村 康生; 松島 幸太; 佐鳥 新; 三橋 龍一; 佐藤 立博; 西舘 純; 青柳 賢英; 大野 努; 田中 喜規; 中村 明広; 堀 耕太郎
• 4101 Electrical power subsystem design of Pico satellite "HIT-SAT"
  西舘 純; 佐藤 立博; 青柳 賢英; 大野 努; 竹浪 恭平; 佐鳥 新; 三橋 龍一; 廣田 尚久; 石村 康生; 松島 幸太; 戸谷 剛; 榊原 隆浩; 堀 耕太郎; 江良 聡; 中村 明広; 植松 努; 安中 俊彦
• CAMUI方式を用いたハイブリッドロケット燃料の燃焼速度に及ぼすスケールの効果
  森一大; 伊藤光紀; 柿倉彰仁; 金子雄大; 植嶋健太; 室井典和; 戸谷剛; 植松努; 永田晴紀
• CAMUIハイブリッドロケット燃料グレインの形状履歴の予測
  柿倉彰仁; 伊藤光紀; 金子雄大; 森一大; 植嶋健太; 室井典和; 植松努; 戸谷剛; 永田晴紀
• 傾斜壁面に衝突する液滴流の飛散と捕集を分ける閾値に関する研究
  川上哲史; 由利泰史; 戸谷剛; 永田晴紀
• 液滴ラジエータの作動流体循環流量の自動制御に関する研究
  由利泰史; 川上哲史; 戸谷剛; 永田晴紀
• 水を推進剤とした太陽熱推進軌道変換機によるペイロード輸送ミッションの設計
  岩城裕樹; 戸谷剛; 永田晴紀
• 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
• 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
• 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
• 506 Gasification History of Pellet Fuels in the Primary Combustion Chamber of Staged Combustion Hybrid Rocket
  片野 光; 羽柴 健太; 戸谷 剛; 永田 晴紀
• 507 Scale Effects on the Regression Rate of CAMUI Hybrid Rocket Fuel
  森 一大; 伊藤 光紀; 柿倉 彰仁; 金子 雄大; 植嶋 健太; 室井 典和; 戸谷 剛; 植松 努; 永田 晴紀
• 205 Prediction of geometric history of CAMUI hybrid rocket fuel grain
  柿倉 彰仁; 伊藤 光紀; 金子 雄大; 森 一大; 植嶋 健太; 室井 典和; 植松 努; 戸谷 剛; 永田 晴紀
• 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
• 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
• 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
• 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
• 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
• Design and Experiments of a small Hyperspectral sensor
  青柳賢英; 西里真哉; 佐鳥新; 戸谷剛; 原潤海; 安中俊彦; 中村明広
• 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
• 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
• 二段燃焼式ハイブリッドロケット一次燃焼室における粒状燃料のガス化履歴
  片野光; 羽柴健太; 堺裕哉; 戸谷剛; 永田晴紀
• 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
• 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
• 90・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
• B-2-24 Experiment equipped with micro model satellite to 90&250kgf class CAMUI hybrid rocket
  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
• 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
• Designing the Fuel Grain of CAMUI Hybrid Rocket Using the Prediction Model of Performance History
  植嶋健太; 伊藤光紀; 柿倉彰仁; 金子雄大; 森一大; 飯島直純; 室井典和; 植松努; 戸谷剛; 永田晴紀
• Ultrasonic Pulse-echo Measurement of Hybrid Rocket Fuel Regression
  金子雄大; 伊藤光紀; 植嶋健太; 戸谷剛; 永田晴紀
• Improvement of the thrust and specific impulse by elongating and heating the Laval nozzle
  岩城裕樹; 長沼哲史; 戸谷剛; 永田晴紀
• 4037 Improvement of the thrust and specific impulse by elongating and heating the Laval nozzle
  岩城 裕樹; 長沼 哲史; 戸谷 剛; 永田 晴紀
• 4040 Designing the Fuel Grain of CAMUI Hybrid Rocket Using the Prediction Model of Performance History
  植嶋 健太; 伊藤 光紀; 柿倉 彰仁; 金子 雄大; 森 一大; 飯島 直純; 室井 典和; 植松 努; 戸谷 剛; 永田 晴紀
• 4041 Ultrasonic Pulse-echo Measurement of Hybrid Rocket Fuel Regression
  金子 雄大; 伊藤 光紀; 植嶋 健太; 戸谷 剛; 永田 晴紀
• 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後退速度の粒径依存性
  羽柴健太; 堺裕哉; 戸谷剛; 永田晴紀
• 反射板を用いたPDEイニシエーターにおける反射板径の最適化に関する研究
  浅田隆利; 脇田督司; 戸谷剛; 永田晴紀
• 605 Dependence of the Regression Rate on the Grain Diameter in the Primary Combustion Chamber of Staged Combustion Hybrid Rocket
  羽柴 健太; 堺 裕哉; 戸谷 剛; 永田 晴紀
• 606 Optimal design of the Reflecting Board Diameter in a PDE Initiator with a Reflecting Board
  浅田 隆利; 脇田 督司; 戸谷 剛; 永田 晴紀
• 超小型人工衛星HIT‐SATの運用結果
  三橋龍一; 佐藤立博; 竹浪恭平; 安部潤一郎; 中尾明弘; 羽鳥翼; 戸谷剛; 佐鳥新
• 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
• 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
• 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
• 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
• 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
• 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
• 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
• 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
• 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
• 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
• 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
• 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
• 超小型人工衛星HIT‐SATの実験結果
  三橋龍一; 佐藤立博; 竹浪恭平; 中尾明弘; 羽鳥翼; 戸谷剛; 加瀬誠志; 佐鳥新
• B-2-60 Experiment result of nano-satellite HIT-SAT
  三橋 龍一; 佐藤 立博; 竹浪 恭平; 中尾 明弘; 羽鳥 翼; 戸谷 剛; 加瀬 誠志; 佐鳥 新
• 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
• 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
• Improvement of thrust and specific impulse by convective heat transfer in Laval nozzle
  岩城裕樹; 長沼哲史; 佐藤峻哉; 戸谷剛; 脇田督司; 永田晴紀
• S1904-2-2 Improvement of thrust and specific impulse by convective heat transfer in Laval nozzle
  岩城 裕樹; 長沼 哲史; 佐藤 峻哉; 戸谷 剛; 脇田 督司; 永田 晴紀
• 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
• 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
• 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
• CAMUI式ハイブリッドロケットの小型化および繰り返し運用
  佐藤峻哉; 竹腰卓博; 田村正佳; 萩原俊輔; 脇田督司; 戸谷剛; 永田晴紀
• 小型ハイブリッドロケットにおける能動的ロール制御システムの構築
  田村正佳; 佐藤俊哉; 竹腰卓博; 萩原俊輔; 脇田督司; 戸谷剛; 永田晴紀
• 619 Downsizing and operating more than once of CAMUI type hybrid rocket
  佐藤 峻哉; 竹腰 卓博; 田村 正佳; 萩原 俊輔; 脇田 督司; 戸谷 剛; 永田 晴紀
• 620 Construction of Active Roll Control System for Hybrid Rocket CAMUI
  田村 正佳; 佐藤 俊哉; 竹腰 卓博; 萩原 俊輔; 脇田 督司; 戸谷 剛; 永田 晴紀
• 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
• 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
• 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
• 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
• 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
• 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
• Report on the 47th National Heat Transfer Symposium of Japan
  近久 武美; 大曽根 靖夫; 黒田 明慈; 桑原 不二朗; 坂下 弘人; 戸谷 剛; 中村 祐二; 山田 雅彦; 田部 豊
• 小型CAMUI式ハイブリッドロケットの開発と運用
  竹腰卓博; 佐藤峻哉; 田村正佳; 萩原俊輔; 脇田督司; 戸谷剛; 永田晴紀; 植松努
• 超小型宇宙機UNITEC‐1の熱設計と軌道上温度
  戸谷剛; 脇田督司; 永田晴紀
• ラバールノズルの超音速域における伝熱が推力および比推力に与える影響
  岩城裕樹; 戸谷剛; 脇田督司; 永田晴紀
• CAMUI型固体燃料の燃料後退予測式取得方法に関する検討
  萩原俊輔; 金子雄大; 野原正寛; 永田晴紀; 戸谷剛; 脇田督司; 松岡常吉; 植嶋健太; 植松努
• S1901-1-1 Thermal Design and Temperature on Orbit of Micro Spacecraft UNITEC-1
  戸谷 剛; 脇田 督司; 永田 晴紀; UNITEC; 開発チーム
• S1901-1-2 Development and Operation of Small-Scale CAMUI Hybrid Rocket
  竹腰 卓博; 佐藤 峻哉; 田村 正佳; 萩原 俊輔; 脇田 督司; 戸谷 剛; 永田 晴紀; 植松 努
• S1901-1-5 Improvement of Method to Obtain Regression Formulae of CAMUI Type Fuel Grain
  萩原 俊輔; 金子 雄大; 野原 正寛; 永田 晴紀; 戸谷 剛; 脇田 督司; 松岡 常吉; 植嶋 健太; 植松 努
• G1900-1-3 Effect of heat transfer in supersonic region of Laval nozzle on thrust and specific impulse
  岩城 裕樹; 戸谷 剛; 脇田 督司; 永田 晴紀
• 拡大する環状流路を伝播する円環デトネーション波に流路幅が与える影響
  寺坂昭宏; 田村正佳; 脇田督司; 戸谷剛; 永田晴紀
• 樹脂製表面微細周期構造の分光特性
  石川直幸; 戸谷剛; 永田晴紀; 脇田督司
• 遺伝的アルゴリズムを用いたCAMUI型燃料グレインの最適設計
  野原正寛; 金子雄大; 萩原俊輔; 脇田督司; 戸谷剛; 永田晴紀
• 512 Spectroscopic Characteristics of Resinous Microstructure Surface
  石川 直幸; 戸谷 剛; 永田 晴紀; 脇田 督司
• 612 Optimum design CAMUI type fuel grain shape using genetic algorithm
  野原 正寛; 金子 雄大; 萩原 俊輔; 脇田 督司; 戸谷 剛; 永田 晴紀
• 613 Effect of channel width on toroidal detonation wave propagating through expanding annular channel
  寺坂 昭宏; 田村 正佳; 脇田 督司; 戸谷 剛; 永田 晴紀
• Optical Properties of Periodic Microscopic Structures on Ultra Violet Solidification Plastic with Metal Layer
  石川 直幸; 戸谷 剛; 脇田 督司; 永田 晴紀
• 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
• 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
• 超小型衛星搭載のための可視・近赤外帯ハイパースペクトルカメラHSCの開発
  佐鳥新; 青柳賢英; 戸谷剛; 中村明弘; 安中俊彦; 石川智浩; 武山芸英; 上山善弘
• 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
• ほどよし1号機の開発状況
  宮下直己; 中村友哉; 中須賀真一; 岩崎晃; 戸谷剛; 佐原宏典; 江野口章人; 武山芸英; 早川義彰; 山口耕司
• 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
• 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
• 小型ハイパースペクトルセンサHSCに搭載するデータ処理装置の開発
  上山善弘; 佐鳥新; 青柳賢英; 戸谷剛; 石川智浩; 中村明広
• 超小型衛星搭載用ハイパースペクトルセンサHSCの開発
  青柳賢英; 上山善弘; 佐鳥新; 戸谷剛; 山口耕司; 武山芸英; 中村明広
• H3 Development of VNIR Hyperspectral Camera HSC for small/ micro satellites
  佐鳥 新; 青柳 賢英; 戸谷 剛; 中村 明弘; 安中 俊彦; 石川 智浩; 武山 芸英; 上山 善弘
• CAMUI型固体燃料後退速度式の導出方法に関する検討
  野原正寛; 出雲弘一; 脇田督司; 戸谷剛; 永田晴紀
• 太陽同期軌道を周回する超小型衛星の熱設計に関する研究
  小川洋人; 井上遼太; 戸谷剛; 脇田督司; 永田晴紀
• 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
• 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
• 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

• 人工衛星設計特論, 2024年, 修士課程, 工学院
• 大学院共通授業科目（一般科目）：自然科学・応用科学, 2024年, 修士課程, 大学院共通科目
• 人工衛星設計特論, 2024年, 博士後期課程, 工学院
• コンピュータ演習, 2024年, 学士課程, 工学部
• 熱力学Ⅰ, 2024年, 学士課程, 工学部
• 英語演習, 2024年, 学士課程, 全学教育
• 熱流体力学演習Ⅰ, 2024年, 学士課程, 工学部
• 航空宇宙工学, 2024年, 学士課程, 工学部

• 日本熱物性学会
• 日本航空宇宙学会 北部支部
• アメリカ航空宇宙学会（American Institute of Aeronautics and Astronautics）
• 日本燃焼学会
• 日本機械学会
• 日本伝熱学会
• 日本マイクログラビティ応用学会
• 日本航空宇宙学会
• The Japan Society for Aeronautical and Space Sciences

• 日本伝熱学会 北海道支部 伝熱セミナーでの招待講演
  2012
• JAXA 宇宙教育指導者セミナー での招待講演
  2011
• 日本熱物性学会「宇宙材料の熱物性とシステムデザイン」研究会 第11回研究会での招待講演
  2011
• Chittagong University of Engineering and Technology, Bangladeshでの招待講演
  2010
• 国際学会での学術講演
  2008
• 国際学会での学術講演
  2007
• 北海道支部講演会での招待講演
  2007

• Development of additive manufacturing method for CFRP using resin impregnation method by electrodeposition and imparting impact resistance and heat absorption properties
  Grants-in-Aid for Scientific Research
  01 Apr. 2024 - 31 Mar. 2028
  片桐 一彰; 戸谷 剛; 奥村 俊彦; 岸本 直子; 磯野 拓也; 本田 真也
  Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (B), Hiroshima University, 24K00763
• Relaxation of intramolecular vibration of solvents by infrared excitation and clarification of effective infrared absorption wavelength band for solvent drying
  Grants-in-Aid for Scientific Research
  01 Apr. 2022 - 31 Mar. 2025
  戸谷 剛; 小林 一道
  2023年度は、下記の2項目を行った。(2023-1)溶剤(水)の蒸発に最も効果的な分子内振動(赤外線吸収波長帯)の解明実験、(2023-2)緩和挙動を組み込んだ平均場分子運動論解析・分子動力学解析法の開発と溶剤の蒸発量を計算する計算手法の確立
  (2023-1)では、計画通り、波長制御エミッタから放射されたふく射をポンプ光として、プローブ光と同じ溶剤の下方から当て、溶剤の分子内振動を励起する実験系を構築した。この実験系でも、反射スペクトルを取得する溶剤表面を、熱伝導で加熱するよりも、波長制御エミッタで加熱した方が、溶剤の表面温度は同じにも関わらず、蒸発につながる分子間振動が促進される緩和挙動が確認された。 しかし、昨年度確認された反射スペクトルの差より小さく、観測しにくかったため、今年度は、実験系を昨年度の系に戻して、実験を行うことにした。波長3.03 μmに単色放射能のピークを持つ波長制御エミッタと波長6.10 μmに単色放射能のピークを持つ波長制御エミッタを用いた加熱実験を、単色放射能のピークが同じになるようにそれぞれ行った結果、蒸発につながる分子間振動の励起には有意な差が出ないことが確認された。
  (2023-2)では、昨年度に引き続き平均場分子運動論を用いて温度の異なる二液膜問題について研究を行った。その結果、過去の分子動力学解析結果と同様の傾向で蒸発界面の速度分布関数が非等方性を持つことを確認した。この結果より、本解析の平均場分子運動論への有用性を確認することができた。また、凝縮界面についても，蒸発界面とは異なる傾向で速度分布関数が非等方性を持つことがわかった。さらに、本計算を大規模分子動力学解析で行うための予備調査も行った。
  Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (B), Hokkaido University, 23K22678
• Relaxation of intramolecular vibrations of solvents by infrared excitation and elucidation of effective infrared absorption wavelength band for drying solvent
  Grants-in-Aid for Scientific Research
  01 Apr. 2022 - 31 Mar. 2025
  戸谷 剛; 小林 一道
  Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (B), Hokkaido University, 22H01407
• Development of the manufacturing method of CFRP lattice structure by using electrodeposition resin impregnation method and its application technology
  Grants-in-Aid for Scientific Research
  01 Apr. 2020 - 31 Mar. 2023
  片桐 一彰; 戸谷 剛; 陶山 剛; 奥村 俊彦; 磯野 拓也; 本田 真也
  下記の研究を推進した。
  （A) 電着樹脂含浸法を用いたラティス構造の製造法を開発、部材曲線化の効果の実証：これまでに、独自の炭素繊維強化樹脂（Carbon Fiber Reinfroced Plastic, 以下、CFRP)の製造方法である、電着樹脂含浸法の開発を進めてきた。今年度、この方法を適用したCFRP製ラティス構造の製作方法を確立するため、いくつかのラティス構造の試作試験を行った。電着樹脂含浸法は、ラティス構造を構成する部材が曲線状であっても容易に製作できることが大きな特長である。そのため、曲線部材を使った変形性が最大限に活用され、将来、有用と想定されるラティス構造として、航空機の主翼の骨組構造に着目し、検討した。
  （B) セルロースナノファイバーによるCFRPの衝撃強度の向上とラティス構造への適用：CFRPの衝撃強度を向上させるため、まずは、添加するセルロースナノファイバーの長さや直径を変化させて、炭素繊維間に侵入させる試験を開始した。従来から言われているが、セルロースナノファイバーの長さや直径は、セルロースナノファイバーの分散評価とも関連性が大きい。そのため、現用のレーザー回折式の粒度分布分析装置を用いてセルロースナノファイバーの直径、長さを評価し、衝撃強度の評価に向けた基礎データを取得した。
  （C）蓄熱性の計測手法、評価手法についての検討：蓄熱性CFRPの蓄熱量を向上させるためには、蓄熱性のみならず、熱伝導性を向上させ、蓄熱性CFRPの面内において、極力の広い範囲で蓄熱させる必要がある。そのため、表面の熱分布を精密に確認でき、かつ、断熱性を十分に確保する方法について検討を行った。
  Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (B), Osaka Research Institute of Industrial Science and Technology, 20H02039
• Relaxation of intramolecular vibration generated by continuous infrared radiation at the gas-liquid interface and effective absorption band for solvent drying
  Grants-in-Aid for Scientific Research
  01 Apr. 2019 - 31 Mar. 2022
  Totani Tsuyoshi
  In this study, (1) the relaxation behavior of a solvent when continuously irradiated with infrared light at the absorption wavelength of the solvent and (2) the evaporation behavior of the solvent by molecular dynamics and Boltzmann equation analysis were investigated.
  In (1), it was found that continuous irradiation of infrared light, which causes angular vibration of water, may accelerate evaporation by about 5% compared to heating by thermal conduction in the wavelength range of bound rotational vibration, which is involved in water evaporation. In (2), It was found that for evaporating molecules by local heating, the normal direction temperature is almost equal to the local heating temperature, and the tangential direction temperature is anisotropic taking a temperature close to that of the bulk liquid in the non-heated state. Further, the larger the number of non-condensable gases in the gas, the more isotropic the distribution becomes due to molecular collisions.
  Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (B), Hokkaido University, 19H02074
• Method for Determining Nozzle-Throat-Erosion History in Hybrid Rockets and Elucidation of the Mechanism
  Grants-in-Aid for Scientific Research
  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, 15H04197
• Fuel Regression Characteristics of CAMUI-type hybrid rockets under high Reynolds numbers
  Grants-in-Aid for Scientific Research
  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, 24246135
• Radiative Characteristics of Liquid Droplet Radiator for Large Space Structures
  Grants-in-Aid for Scientific Research
  2012 - 2012
  TOTANI Tsuyoshi
  One of the candidates to solve the waste heat problem of large space systems such as space solar power systems is a liquid droplet radiator. The data of the effective emissivity of the radiating surface formed by the droplet stream is essential in order to design the liquid droplet radiator. In this study, a technique for obtaining the effective emissivity by a radiative heat transfer experiment and numerical analysis using Monte Carlo method has been established. It is clarified from this approach that the effective emissivities of three kinds of a single droplet flow (droplet diameter: 0.118, 0.106, 0.090 mm, droplet spacing: 0.630, 0.435, 0.212 mm) are 0.073, 0.087, and 0.12, respectively.
  Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (B), Hokkaido University, Principal investigator, Competitive research funding, 24360346
• Technology for Preventing Global Warming using Periodic Micro-structure
  Grants-in-Aid for Scientific Research
  2009 - 2011
  TOTANI Tsuyoshi
  A periodic microstructure is built on a ultra violet curable resin by the UV nanoimprint method. A gold film is sputtered on the periodic microstructure. Assuming Kirchhoff's law, the maximum normal emissivity of the periodic microstructure is 0.6 near 10gm in the case of the gold film 200 nm thick the surface facing a sputter source. The periodic microstructure with the gold film contributes to the prevention of global warming.
  Japan Society for the Promotion of Science, Grant-in-Aid for Challenging Exploratory Research, Hokkaido University, Principal investigator, Competitive research funding, 21651026
• Optimal Design Method of CAMUI-type Fuel Grain
  Grants-in-Aid for Scientific Research
  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, Coinvestigator not use grants, Competitive research funding, 21360410
• 表面微細周期構造を用いた地球温暖化防止技術の研究
  科学研究費補助金
  2009
  Competitive research funding
• Wavelength-selective radiator with periodic microstructure
  Grant-in-Aid for Scientific Research
  2009
  Competitive research funding
• Regression Mechanism of a Solid Fuel around Oxidizer Jet Stagnation Region
  Grants-in-Aid for Scientific Research(基盤研究(B))
  2006 - 2008
  Harunori NAGATA; Tsuyoshi TOTANI; Nobuyuki OSHIMA
  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.
  Ministry of Education, Culture, Sports, Science and Technology, 基盤研究(B), 北海道大学, Coinvestigator not use grants, Competitive research funding, 18360402
• 液滴ラジエータにおける作動流体循環の自動化に関する研究
  科学研究費補助金(若手研究(A))
  2006 - 2007
  戸谷 剛
  ラジエータは、構造物内の廃熱量の変動に、作動流体の循環量を変化させて対応する.宇宙構造物内の廃熱量は分オーダーで変動するため作動流体の循環制御を自動化する必要がある.一方、液滴ラジエータで使用する液滴回収器とベローズ式圧カレギュレータは装置内の流体量が変化するため、ポンプの回転数を制御するだけでは循環は成立しない.ベローズ式圧カレギュレータにかける圧力、液滴回収器とギアポンプの回転数を制御する必要がある.平成19年度(予算を繰越し、平成20年度も含む)は流量制御装置を構築し、作動流体の循環量を自動的に制御することが目標である.実験は、廃熱量変動を模擬するために、演算部に作動流体の循環量を変更する命令(例えば、100ml/minから500ml/min、500ml/minから100ml/min)を送り、作動流体循環量の変化・応答性等を調べた.平成19年度に発生した作動流体循環プログラムの処理速度の遅さと装置自身の不具合を解決し、平成20年度にまず、設定した流量に応じて作動流体循環プログラムを通して各コンポーネント(液滴生成器にかける圧力、液滴回収器とギアポンプの回転数)をそれぞれ単体で制御することに成功した.次に、各コンポーネントを接続し、液滴ラジエータ全体の作動流体循環実験を行った結果、循環量が大きく変動し、設定した循環量で一定にならなかった.原因を調べたところ、ベローズ式圧カ...
  文部科学省, 若手研究(A), 北海道大学, Principal investigator, Competitive research funding, 18686068
• 宇宙空間での液滴流の捕集と飛散を分ける閾値の特定
  科学研究費補助金(若手研究(A))
  2004 - 2005
  戸谷 剛
  平成16年度は親油性表面での、平成17年度は疎油性表面での、液滴の飛散と捕集を分ける閾値について調べた。作動流体には、液滴ラジエータでの使用が考えられているシリコンオイル(信越化学工業株式会社KF96-50cSt)を用いた。シリコンオイルと親油性を持つ表面はアルミ面をもちいることで、疎油性を持つ表面はアルミ面に撥油剤(信越化学工業株式会杜KP-801)を塗布することで実現した。宇宙空間(微小重力,真空環境)での液滴の捕集と飛散を模擬するために、液滴の衝突は真空チャンバー内で行い、航空機(ダイヤモンドエアサービス株式会社MU-300)を用いて微小重力実験を行った。その結果、以下の知見を得た。1.通常重力下での液滴の飛散と捕集を分ける閾値(K=We×Oh^<-0.4>)は、親油性表面で○○○、疎油性表面で○○○であることが分かった。2.宇宙空間と通常重力下での液滴の捕集と飛散の結果を比較したところ、微小重力下と地上重力下での結果に違いがないことが分かった。3.宇宙空間での液滴の飛散と捕集を分ける閾値は、微小重力実験の回数が少ないことから、はっきり特定することはできなかったが,1,2の結果より、通常重力下での閾値の値と違いがないことを推測することができた。4.親油性表面と疎油性表面で液滴の捕集と飛散を分ける閾値に大きな違いがないことから、液滴回収器の表面は親油性でも疎油性でも良いこ...
  文部科学省, 若手研究(A), 北海道大学, Principal investigator, Competitive research funding, 16686048
• 超小型衛星の熱設計
  2005
  Competitive research funding
• Thermal Design of Micro Satellite
  2005
  Competitive research funding
• Development Study of High-response Hydrogen Concentration Probe for Supersonic Flows
  Grants-in-Aid for Scientific Research(基盤研究(B))
  2000 - 2002
  Harunori NAGATA; 新井 隆景; 戸谷 剛; 工藤 勲
  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 c...
  Ministry of Education, Culture, Sports, Science and Technology, 基盤研究(B), 北海道大学, Coinvestigator not use grants, Competitive research funding, 12450390
• 微小重力下で発生する液滴内3次元マランゴニ対流の解析
  科学研究費補助金(奨励研究(A))
  2000 - 2001
  戸谷 剛
  微小重力下で対流熱伝達によって冷却される液滴において発生する3次元マランゴニ対流の解析を行った.今年度は,平成12年度のマランゴニ数5,000からマランゴニ数10,000に増やし,解析を行った.その結果,マランゴニ数5,000では発生しなかった計算が途中で発散するという予期しなかった問題に直面した.プログラムの再チェックを行ったが,プログラミング上の不具合は見つからなかった.また,初期温度外乱の大きさやパターンを変えても,スペクトル数(計算格子数に対応)を増やしても,流れが発達すると計算が発散するため,マランゴニ数10,000以上の液滴内3次元マランゴニ対流を解析する場合には,現在よりさらに精度の良い手法が必要であると結論付けられた.現在は,半径方向速度,渦度,圧力,温度を変数として用いているが,流れ場を記述する変数に,さらに精度を上げることのできるポロイダルベクトルやトロイダルベクトルを用いる手法を採用するなどの対策が必要になると考えられる.計算が発散するという予期しなかった事態に直面し,原因が手法によるものであると結論付けられたため,本年度並行して行うことを予定していた温度境界条件を対流熱伝達からふく射熱伝達に変更した計算プログラムの開発は断念した.計算が発散したため定常状態までの計算は行うことができなかったが,計算が発散するまでの結果から表面張力対流の以下の過渡的現象が...
  文部科学省, 奨励研究(A), 北海道大学, Principal investigator, Competitive research funding, 12750807
• Generation and Collection of Droplets under microgravity
  Grants-in-Aid for Scientific Research(基盤研究(B))
  1998 - 2000
  Isao KUDO; 戸谷 剛; 永田 晴紀
  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...
  Ministry of Education, Culture, Sports, Science and Technology, 基盤研究(B), 北海道大学, Coinvestigator not use grants, Competitive research funding, 10450369
• 大型宇宙構造物用ラジエータ「液滴ラジエータ」の研究開発
  1998
  Competitive research funding
• Liquid Droplet Radiator for Large Space Structure
  1998
  Competitive research funding

• 蓄熱性炭素繊維強化プラスチック
  Patent right, 片桐一彰; 山口真平; 永廣卓哉; 川北園美; 尾崎友厚; 園村浩介; 武村 守; 吉岡弥生; 垣辻 篤; 佐々木克彦; 戸谷 剛, 地方独立行政法人大阪産業技術研究所, 国立大学法人北海道大学
  特願2017-205236, 24 Oct. 2017
  特許7173477
• Infrared Heater
  Patent right, Tsuyoshi Totani; Atsushi Sakurai; Yoshio Kondo, Hokkaido University; Niigata University;
  特願2015-175068, 04 Sep. 2015
  特開2017-50254, 09 Mar. 2017
  特許6692046
  13 May 2020, NGK INSULATORS, LTD.