研究者データベース

戸谷 剛(トタニ ツヨシ)
工学研究院 機械・宇宙航空工学部門 宇宙航空システム
教授

基本情報

所属

  • 工学研究院 機械・宇宙航空工学部門 宇宙航空システム

職名

  • 教授

学位

  • 博士(工学)(北海道大学)

J-Global ID

研究キーワード

  • 液滴ラジエータ   液滴   微小重力   液滴回収器   液滴生成器   二酸化炭素削減   地球温暖化ガス排出削減   作動流体   捕集   自動化   表面微細周期構造   圧力損失   オネソルジ数   閾値   廃熱   ベローズ式油圧レギュレータ   マイクロナノデバイス   マランゴニ対流   Liquid Droplet Radiator   飛散   真空   ウェーバー数   作動流体の循環   二酸化炭素   ラジエータ   排熱装置   循環   ロケット   燃焼   宇宙インフラ   流体工学   熱工学   宇宙工学   Fluid Mechanics   Thermal Engineering   Space Engineering   

研究分野

  • ものづくり技術(機械・電気電子・化学工学) / 流体工学
  • ものづくり技術(機械・電気電子・化学工学) / 熱工学
  • フロンティア(航空・船舶) / 航空宇宙工学

職歴

  • 2006年10月 - 2018年03月 北海道大学 工学(系)研究科(研究院) 准教授
  • 1998年04月 - 2006年09月 北海道大学 大学院工学研究科 助手

学歴

  •         - 1999年03月   北海道大学   大学院工学研究科   機械工学専攻 博士後期課程 修了
  •         - 1999年   北海道大学
  •         - 1995年03月   北海道大学   大学院工学研究科   機械工学専攻 修士課程 修了
  •         - 1995年   北海道大学
  •         - 1993年03月   北海道大学   工学部   機械工学科 卒業
  •         - 1993年   北海道大学

所属学協会

  • 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   

研究活動情報

論文

  • 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 - 101636 2020年10月 [査読有り][通常論文]
  • Tabata Kenichi, Totani Tsuyoshi, Matsushima Kohei, Nagata Harunori
    Proceedings of 2020 International Conference on Environmental Systems ICES-2020-342 2020年07月 [査読有り][通常論文]
  • Hajime Ota, Kei Yoshii, Tsuyoshi Totani
    Proceedings of 2020 International Conference on Environmental Systems ICES-2020-292 2020年07月 [査読有り][通常論文]
  • 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 2019年12月 [査読有り][通常論文]
     
    © 2019 Elsevier Ltd This work presents a method to fabricate the heat-storable CFRP, a multifunctional composite that combines strength, lightweight and heat storability. For mobile electric devices, thermal management system using phase change material (PCM) has been developed. However, as long as the PCM changes to liquid phase, it is difficult to reduce the weight since the sealed container is indispensable. Hence, the authors have focused trans-1,4-polybutadiene (TPBD), which is crystalline polymer that accumulates heat by crystal structure transition in solid phase. In this study, TPBD was incorporated into CFRP. To avoid exposing TPBD to high-temperature and high-pressure processes, the electrodeposition resin molding (ERM) method was applied. That is, a non-crimp carbon fiber fabric (NCF) was immersed in the electrodeposition solution containing epoxy polymers in which the pulverized TPBD was dispersed. Applying a current, resin was deposited and impregnated between carbon fibers. Simultaneously, TPBD was incorporated to obtain heat-storable CFRP.
  • Ryohei Gotoh, Tsuyoshi Totani, Masashi Wakita, Harunori Nagata
    INTERNATIONAL JOURNAL OF HEAT AND MASS TRANSFER 137 1132 - 1140 2019年07月 [査読有り][通常論文]
     
    The use of phase change materials (PCMs) for heat storage and as a heat source has become an important aspect for energy management. Some PCMs store energy when in a non-equilibrium state (a supercooling state), and supply energy when released from this state. This means PCMs have the ability to sustain heat energy for long periods and select the heat supply timing. 2-amino-2-methyl-1,3-propanediol (AMP), a solid-solid PCM, stores about 264 J/g of heat energy at the crystal transition temperature of about 78 degrees C. AMP has the attractive characteristic of storing heat energy in its solid supercooling state, similar to solid-liquid PCMs. In addition, AMP crystallizes from the supercooling state and releases heat energy of about 140 J/g during the heating process. These positive attributes make AMP a good candidate to assist in heating a system. This study applied this characteristic to methods handling the exoergic heat energy of the crystallization of AMP. First, the thermal properties are studied by DSC measurement and thermal cycle tests in different mass conditions. Second, the crystallization is investigated by observation of crystal growth. The results show that the supercooling state crystallizes with exoergic heat during the heating process. It turns out that the crystal nucleation rate (1/s) highly depends on the temperature and AMP mass. The crystal growth rate (mu m/s) is acquired in this experiment. By using this information, it is possible to handle the exoergic heat of the crystallization from the supercooling state by changing the AMP mass and minimum temperature during cooling. Moreover, the heat energy that is kept in the supercooling state can be also controlled by crystal nucleus addition or impact. (C) 2019 Elsevier Ltd. All rights reserved.
  • TAKANASHI Tomohiro, TOTANI Tsuyoshi, SHIMADA Taizo, RYOMON Kento, WAKITA Masashi, NAGATA Harunori
    日本伝熱学会論文集 27 1 43 - 52 社団法人 日本伝熱学会 2019年 [査読有り][通常論文]
     
    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.
  • 齋藤 勇士, 君野 正弥, 添田 建太郎, 戸谷 剛, 永田 晴紀
    日本航空宇宙学会誌 66 10 291 - 295 一般社団法人 日本航空宇宙学会 2018年10月 

    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.

  • Ryohei Gotoh, Tsuyoshi Totani, Masashi Wakita, Harunori Nagata
    Proceedings of the 16th International Heat Transfer Conference IHTC16-24007 4425 - 4432 2018年08月 [査読有り][通常論文]
     
    © 2018 International Heat Transfer Conference. All rights reserved. The use of phase change materials (PCMs) as a heat source and storage has become an important consideration in energy management. 2-amino-2-methyl-1,3-propanediol (AMP), which is a solid-solid PCM, stores approximately 264 J/g of heat energy at approximately 78 °C. AMP has the attractive characteristic of storing heat energy in its non-equilibrium solid state. This study clarified this characteristic to control the stored heat energy of AMP so that it can be used at when heat energy is needed. The thermal property was measured by differential scanning calorimetry (DSC) in the temperature range of -50 °C to 100 °C, and the structural property was measured through X-ray powder diffraction in the temperature range of -70 °C to 90 °C. The results revealed that the material's initial crystal structure changed from brittle crystalline (phase II) to plastic crystalline (phase I) at 80 °C during heating from room temperature to 90 °C. Phase I remained almost unchanged during cooling from 90 °C to -50 °C, but changed to the non-equilibrium state (phase Ig'). Then, phase Ig' changed to phase II with exoergic heat of 140 J/g in the temperature range between -14 °C and 36 °C during heating. This study clarified that the phase change temperature can be controlled by controlling the sample mass or by applying an external stimulus. In other words, AMP is a rare solid-solid PCM that does not release heat energy during cooling, but rather releases heat energy during heating. Moreover, the heat energy is controllable. This positive attribute makes AMP a good candidate for use in a heating assist system.
  • Tsuyoshi Totani, Atsushi Sakurai, Thang D. Dao, Tadaaki Nagao, Yoshio Kondo
    Proceedings of the 16th International Heat Transfer Conference IHTC16-24220 5901 - 5908 2018年08月 [査読有り][通常論文]
  • Delburg P. Mitchao, Tsuyoshi Totani, Masashi Wakita, Harunori Nagata
    Journal of Thermophysics and Heat Transfer 32 3 789 - 798 2018年07月 [査読有り][通常論文]
     
    A preliminary thermal design was proposed by determining all the possible combinations of solar absorptivity and infrared emissivity on the panel surfaces of Earth-pointing satellites deployed from Japan's experimental module small-satellite orbital deployer. The three most common internal panel configurations in a 50 kg satellite with body-mounted solar cells and dimensions of 550 x 350 x 550 mm were considered. Conductive insulation was applied between the inner and outer structures to decrease the temperature change of inner components. The worst hot-and cold case conditions were estimated based on the beta angle of the orbit and the Earth's distance from the sun. The analyses were carried out using a simple tool created in MATLAB (c). The tool output combinations of optical properties that satisfied the predefined allowable temperature range of structures and components. These optical properties were subsequently verified using Thermal Desktop (c)'s SINDA/FLUINT with the RadCAD module. Using these combinations, the thermal design for microsatellites in a low Earth and non-sun-synchronous orbit may be shortened.
  • Yuji Saito, Toshiki Yokoi, Hiroyuki Yasukochi, Kentaro Soeda, Tsuyoshi Totani, Masashi Wakita, Harunori Nagata
    JOURNAL OF PROPULSION AND POWER 34 1 247 - 259 2018年01月 [査読有り][通常論文]
     
    The regression characteristics of axial-injection end-burning hybrid rocket were experimentally investigated using a laboratory-scale motor. The axial-injection end-burning type fuel grains were made by high-accuracy three-dimensional printing. Firing tests were conducted using gaseous oxygen as the oxidizer at a chamber pressure range of 0.10 to 0.43MPa. Results of 15 static firings tests show that fuel regression rate increases as the chamber pressure rises, and fuel regression rate decreases as the oxidizer port velocity increases. A data reduction method was developed to avoid the difficulty in calculating oxidizer-to-fuel ratio. A simplified fuel regression model based on the granular diffusion flame model is developed to investigate regression characteristics. The trend in results as calculated using the granular diffusion flame model agrees with that in experimentally observe values. However, this does not hold true in tests with varying oxidizer port velocity. A granular diffusion flame model only takes into account simple solid propellant regression. Therefore, modification of the model is needed for calculating the fuel regression rate of an end-burning hybrid rocket.
  • 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年 [査読有り][通常論文]
  • Landon Kamps, Yuji Saito, Ryosuke Kawabata, Masashi Wakita, Tsuyoshi Totani, Yusuke Takahashi, Harunori Nagata
    JOURNAL OF PROPULSION AND POWER 33 6 1369 - 1377 2017年11月 [査読有り][通常論文]
     
    The authors of this paper introduce 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. Nine static-firing tests were carried out on a 2kN-class cascaded multistage impinging-jet-type hybrid-rocket motor under varying oxidizer-flow rates to evaluate the accuracy of reconstructed results. Nozzle-throat-erosion histories calculated by the nozzle-throat reconstruction technique agreed well with measured values for initial nozzle-throat radius, and successfully reconstructed the case, in which no measurable amount of nozzle-throat erosion occurred. For equivalence ratios 0.6-1.4, 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.
  • Harunori Nagata, Hayato Teraki, Yuji Saito, Ryuichiro Kanai, Hiroyuki Yasukochi, Masashi Wakita, Tsuyoshi Totani
    JOURNAL OF PROPULSION AND POWER 33 6 1473 - 1477 2017年11月 [査読有り][通常論文]
     
    The authors have previously proposed the concept of end-burning-type hybrid rockets, which would use cylindrical fuel grains consisting of an array of many small ports running in the axial direction, through which oxidizer gas would flow. Because of difficulty in manufacturing a fuel grain that satisfied requirements such as high volumetric filling rate (above 0.95) and microsized port intervals, the end-burning hybrid rocket had yet to be achieved. This paper reports the results of verification firing tests of a novel end-burning-type hybrid rocket made possible for the first time by recent progress in three-dimensional printing technology. The results clearly distinguish the initial transient and steady periods of the end-burning mode and prove that no oxidizer-to-fuel ratio shift occurs during firing. Because the initial transient is a period for the exit end face to attain a steady-state shape, an initial end-face shape being close to the steady-state shape can shorten this period. A firing test with fuel having tapered ports is shown to attain a steady-state shape in less than 1s, which is much shorter than the nontapered case of about 6 s.
  • Shuntaro Suda, Yasuhiro Kawakatsu, Shujiro Sawai, Harunori Nagata, Tsuyoshi Totani
    Advances in the Astronautical Sciences 160 4027 - 4041 2017年 
    In the modern space development, small-scale deep space mission should be realized to promote frequent and challenging deep space mission. Therefore, the efficient and quick design method to construct Earth escape trajectory with high flexibility in the boundary condition such as escape velocity, direction and timing is strongly demanded. In this paper, the families of Moon-to-Moon transfers with sequential lunar swing-by on a hyperbolic orbit are computed and stored in a database. These families are useful to enhance the Earth escape energy and to change escape direction which could lead a spacecraft to further destinations.
  • Shuntaro Suda, Yasuhiro Kawakatsu, Shujiro Sawai, Harunori Nagata, Tsuyoshi Totani
    SPACEFLIGHT MECHANICS 2017, PTS I - IV 160 4027 - 4041 2017年 [査読有り][通常論文]
     
    In the modern space development, small-scale deep space mission should be realized to promote frequent and challenging deep space mission. Therefore, the efficient and quick design method to construct Earth escape trajectory with high flexibility in the boundary condition such as escape velocity, direction and timing is strongly demanded. In this paper, the families of Moon-to-Moon transfers with sequential lunar swing-by on a hyperbolic orbit are computed and stored in a database. These families are useful to enhance the Earth escape energy and to change escape direction which could lead a spacecraft to further destinations.
  • 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年 [査読有り][通常論文]
  • Delburg Mitchao, Tsuyoshi Totani, Yuji Sakamoto, Masashi Wakita, Harunori Nagata
    Proceedings of 47th International Conference on Environmental Systems ICES-2017-130 2017年 [査読有り][通常論文]
  • 齋藤 勇士, 横井 俊希, 津地 歩, 尾村 和信, 安河内 裕之, 添田 建太郎, 戸谷 剛, 脇田 督司, 永田 晴紀
    日本航空宇宙学会論文集 65 4 157 - 167 一般社団法人 日本航空宇宙学会 2017年 [査読有り][通常論文]
     
    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.
  • Tsuyoshi Totani, Takuya Kuni, Toshifumi Satoh, Takuya Isono, Masashi Wakita, Harunori Nagata
    Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan 14 ists30 Pi_1 - Pi_6 2016年09月 [査読有り][通常論文]
  • Tsuyoshi Totani, Hiroto Ogawa, Masashi Wakita, Harunori Nagata, Yusuke Kuramoto, Naoki Miyashita
    Proceeding of 46th International Conference on Environmental Systems ICES-2016-116 2016年07月 [査読有り][通常論文]
  • 脇田督司
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 14 ists30 67 - 72 一般社団法人 日本航空宇宙学会 2016年 [査読有り][通常論文]
     

    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.

  • 脇田督司
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 14 ists30 39 - 44 一般社団法人 日本航空宇宙学会 2016年 [査読有り][通常論文]
     

    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.

  • 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年 [査読有り][通常論文]
  • 國 拓也, 戸谷 剛, 佐藤敏文, 磯野拓也, 脇田督司, 永田晴紀
    熱物性 29 4 173 - 178 2015年11月 [査読有り][通常論文]
  • 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 2015年03月 [査読有り][通常論文]
  • Tsuyoshi TOTANI, Toshio IROKAWA, Minoru IWATA, Masashi WAKITA, Harunori NAGATA
    Proceedings of the 15th International Heat Transfer Conference, IHTC-15 IHTC15-8771 2014年08月 [査読有り][通常論文]
  • 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 2014年08月 [査読有り][通常論文]
  • 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 2014年07月 [査読有り][通常論文]
     
    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.
  • Harunori Nagata, Hisahiro Nakayama, Mikio Watanabe, Masashi Wakita, Tsuyoshi Totani
    Advances in Aircraft and Spacecraft Science 1 3 273 - 289 2014年07月01日 [査読有り][通常論文]
     
    Accuracy of a reconstruction technique assuming a constant characteristic exhaust velocity (c*) efficiency for reducing hybrid rocket firing test data was examined experimentally. To avoid the difficulty arising from a number of complex chemical equilibrium calculations, a simple approximate expression of theoretical c* as a function of the oxidizer to fuel ratio (ξ ) and the chamber pressure was developed. A series of static firing tests with the same test conditions except burning duration revealed that the error in the calculated fuel consumption decreases with increasing firing duration, showing that the error mainly comes from the ignition and shutdown transients. The present reconstruction technique obtains ξ by solving an equation between theoretical and experimental c* values. A difficulty arises when multiple solutions of ξ exists. In the PMMA-LOX combination, a ξ range of 0.6 to 1.0 corresponds to this case. The definition of c* efficiency necessary to be used in this reconstruction technique is different from a c* efficiency obtained by a general method. Because the c* efficiency obtained by average chamber pressure and ξ includes the c* loss due to the ξ shift, it can be below unity even when the combustion gas keeps complete mixing and chemical equilibrium during the entire period of a firing. Therefore, the c* efficiency obtained in the present reconstruction technique is superior to the c* efficiency obtained by the general method to evaluate the degree of completion of the mixing and chemical reaction in the combustion chamber.
  • Tsuyoshi Totani, Hiroto Ogawa, Ryota Inoue, Tilok K. Das, Masashi Wakita, Harunori Nagata
    JOURNAL OF THERMOPHYSICS AND HEAT TRANSFER 28 3 524 - 533 2014年07月 [査読有り][通常論文]
     
    This paper proposes a thermal design procedure for micro- and nanosatellites that can be completed in one year. Two thermal design concepts keep components within their design temperature range, reducing the temperature change by using the whole structure for heat storage and reducing the temperature change of the inner structure where the most temperature-sensitive components are mounted. One- and two-nodal analysis methods are used for the former and latter concepts, respectively, to clarify the combinations of optical properties for the structures and components to keep within the design temperature range of the components. Finally, multinodal analysis is performed for detail design based on the optical properties clarified from the one- and two-nodal analyses. This thermal design procedure was applied to the Hodoyoshi-1 satellite, which is a cube about 50cm on a side, has two inner plates and has solar cells on the body, is on a sun-synchronous orbit at an altitude of about 500km, and is pointing to Earth. The thermal design of the Hodoyoshi-1 satellite was completed in about 10 months.
  • 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 2014年04月 [査読有り][通常論文]
     
    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.
  • 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 2014年04月 [査読有り][通常論文]
     
    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.
  • 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年 [査読有り][通常論文]
     
    Flame spread and counterflow diffusion flame experiments are widely conducted to investigate the combustibility of solid fuels. Although the use of the gas phase Damkohler number to organize the flame spread rate or regression rate of a solid fuel is effective under constant pressure, some research point out the possibility that the combustion pressure may be an independent factor in determining the regression rate. This research employs a counterflow diffusion flame to investigate the effects of combustion pressure on regression rate, and clarifies the deviation of results using the classical Damkohler number under varying pressures. First, a numerical flow analysis was conducted to determine the oxidizer velocity gradient near the fuel surface, which is an essential factor in evaluating the non-dimensional regression rate. Next, using an enclosed combustion chamber with independently variable oxidizer flux and pressure, experiments with a quasi two-dimensional flame were conducted with polyethylene solid fuel and nitrogen diluted oxygen oxidizer, and the regression rate was measured for two experiment series, constant pressure, and constant oxidizer flux. By comparing the two series, the effect of pressure on non-dimensionalized regression rate is clarified. The results suggest that contrary to the theoretical reaction rate of the gas phase, the non-dimensional regression rate increases when the combustion pressure is decreased, even in the thermal regime. This suggests that the classic method of organizing the regression rate with Damkohler number in thermal regime could not be implemented with varying pressure conditions, possibly due to the change in diffusion rates involved with varying pressures.
  • 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 2013年08月 [査読有り][通常論文]
     
    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.
  • Masashi Wakita, Masayoshi Tamura, Akihiro Terasaka, Kazuya Sajiki, Tsuyoshi Totani, Harunori Nagata
    JOURNAL OF PROPULSION AND POWER 29 4 825 - 831 2013年07月 [査読有り][通常論文]
     
    To achieve reliable transmission of detonation waves to a pulse detonation engine combustor (detonation chamber), the authors propose a pulse detonation engine initiator that uses a cylindrical reflector downstream of a predetonator exit. The detonation wave propagates around the reflector to change the wave shape in three transition stages: from a planar detonation wave in the predetonator to an expanding cylindrical detonation wave, from the cylindrical wave to a planar toroidal detonation wave, and from the toroidal wave to a planar detonation wave in the detonation chamber. The cylindrical wave propagates along a cylindrical path between the reflector and front wall of the detonation chamber, and the toroidal wave propagates along an annular path between the reflector and sidewall of the detonation chamber. The purpose of this study was to examine the influence of the gap width L of the annular path on the transition stages from cylindrical to toroidal and from toroidal to planar. A series of experiments that filled the entire test section with the driver gas mixture (stoichiometric hydrogen oxygen mixture) showed that the expanding cylindrical detonation wave was sufficiently strong to survive the rarefaction waves from the corners of the reflector at all of the investigated annular gap widths (5, 10, 15, and 20 mm) and was transmitted to the planar toroidal wave successfully in all cases. When the strength of the cylindrical detonation wave was under a supercritical condition for diffraction at the reflector corner, the necessary filling distance for the driver gas was predicted well by the Whitham theory. A second series of experiments showed the influence of the annular gap width on the detonation transition from the planar toroidal detonation wave to the planar detonation wave. Two different types of detonation transitions termed "continuous transition" and "temporal quenching" were observed. The threshold value of L/lambda for continuous transition is approximately four.
  • Masashi Wakita, Masayoshi Tamura, Akihiro Terasaka, Kazuya Sajiki, Tsuyoshi Totani, Harunori Nagata
    JOURNAL OF PROPULSION AND POWER 29 4 825 - 831 2013年07月 [査読有り][通常論文]
     
    To achieve reliable transmission of detonation waves to a pulse detonation engine combustor (detonation chamber), the authors propose a pulse detonation engine initiator that uses a cylindrical reflector downstream of a predetonator exit. The detonation wave propagates around the reflector to change the wave shape in three transition stages: from a planar detonation wave in the predetonator to an expanding cylindrical detonation wave, from the cylindrical wave to a planar toroidal detonation wave, and from the toroidal wave to a planar detonation wave in the detonation chamber. The cylindrical wave propagates along a cylindrical path between the reflector and front wall of the detonation chamber, and the toroidal wave propagates along an annular path between the reflector and sidewall of the detonation chamber. The purpose of this study was to examine the influence of the gap width L of the annular path on the transition stages from cylindrical to toroidal and from toroidal to planar. A series of experiments that filled the entire test section with the driver gas mixture (stoichiometric hydrogen oxygen mixture) showed that the expanding cylindrical detonation wave was sufficiently strong to survive the rarefaction waves from the corners of the reflector at all of the investigated annular gap widths (5, 10, 15, and 20 mm) and was transmitted to the planar toroidal wave successfully in all cases. When the strength of the cylindrical detonation wave was under a supercritical condition for diffraction at the reflector corner, the necessary filling distance for the driver gas was predicted well by the Whitham theory. A second series of experiments showed the influence of the annular gap width on the detonation transition from the planar toroidal detonation wave to the planar detonation wave. Two different types of detonation transitions termed "continuous transition" and "temporal quenching" were observed. The threshold value of L/lambda for continuous transition is approximately four.
  • Ryuichiro Kanai, Tatsuya Ishiyama, Masahiro Nohara, Hirokazu Lzumo, Masashi Wakita, Tsuyoshi Totani, Harunori Nagata
    SPACE FOR OUR FUTURE 146 79 - 84 2013年 [査読有り][通常論文]
     
    The authors have been developing fuel regression formulas for CAMUI type hybrid rocket motors. A fuel block in a CAMUI-type fuel grain is a short-axis cylinder having two axial ports. Previous experiments showed that an experimental constant in the regression formula for forward-end faces depends on port length L, mean port diameter D, and the Reynolds number of the flow. In this paper, the authors examined these effects more closely to clarify the basic mechanism of these dependencies.
  • 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  2012年11月 [査読有り][通常論文]
  • 戸谷剛, 脇田督司, 永田晴紀
    Thermophys Prop 33rd 227-229  2012年10月 [査読有り][通常論文]
  • 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 2012年03月 [査読有り][通常論文]
     
    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.
  • 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 2012年03月 [査読有り][通常論文]
     
    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.
  • 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 2012年01月 [査読有り][通常論文]
     
    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  2011年12月 [査読有り][通常論文]
  • Masashi Wakita, Ryusuke Numakura, Takatoshi Asada, Masayoshi Tamura, Tsuyoshi Totani, Harunori Nagata
    JOURNAL OF PROPULSION AND POWER 27 1 162 - 170 2011年01月 [査読有り][通常論文]
     
    To reduce driver gas usage of a pulse detonation engine operating in airbreathing mode, the authors experimentally examined a combination method of a reflecting board and overfilling of the driver gas. This method has the potential to reduce the predetonator diameter by half and shorten the overfilling distance It to the reflecting board position w. Experiments with stoichiometric hydrogen-oxygen and hydrogen-air mixtures as driver and target gases, respectively, showed that the overfilling distance necessary to have a planar detonation wave propagate in a detonation chamber is reduced to 30 mm when a reflecting board is used with a reflecting board clearance of w = 10 mm. With an overfilling distance of 30 mm, the transformation of the detonation wave from cylindrical to toroidal did not occur because of the mixing effect of the driver gas and the target gas around the reflecting board. A 100-mm-thick reflecting board prevents the mixing effect, and a successful transformation from cylindrical to toroidal becomes possible with an overfilling distance as small as 17.2 mm.
  • 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 2010年12月 [査読有り][通常論文]
  • 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 2010年11月 [査読有り][通常論文]
     
    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.
  • 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 2010年07月 [査読有り][通常論文]
     
    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.
  • 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 2010年07月 [査読有り][通常論文]
     
    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.
  • 長沼 哲史, 岩城 裕樹, 佐藤 峻哉, 戸谷 剛, 脇田 督司, 永田 晴紀
    日本航空宇宙学会論文集 = 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 2010年06月 [査読有り][通常論文]
     
    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 efficienc...
  • Yoshihide Aoyanagi, Shin Satori, Tsuyoshi Totani, Toshihiko Yasunaka, Akihiro Nakamura, Yusuke Takeuchi
    SMALL SATELLITE MISSIONS FOR EARTH OBSERVATION 331 - + 2010年 [査読有り][通常論文]
     
    The earth observation micro-satellite "TAIKI" is 50 kg satellite which has low-cost and small bus-subsystem. TAIKI is characterized by a low-cost spaceborne small hyperspectral sensor "HSC-III". HSC-III is targeted at the performances of 30 m ground sampling distance, visible and near infrared wavelength range, 10 mu spectral resolutions, 61 spectral bands and 10 kg weight. HSC-III consists of the telescope, the imaging spectrometer, the electrical system, the on-orbital calibration equipment. The telescope has a pupil diameter of 0.2 m, and has two mirror configuration of Ritchey-Chretien type. The spectrometer has the transmitting grating with the slit and relay lens unit, and array sensor using back-illumination type CMOS image sensor. As a SNR model of HSC-III, we did some calculations and concluded that SNR is approximately 340. Last year, we succeeded to develop the breadboard model of HSC-III optics instrument, and we obtained result of more requirement specification. Also, we have developed the on-orbit spectral calibration equipment. It achieved 0.02 nm of spectral calibration accuracy.
  • Yudai Kaneko, Mitsunori Itoh, Massasi Wakita, Tsuyoshi Totani, Harunori Nagata
    APPLICATIONS OF SPACE TECHNOLOGY FOR HUMANITY 138 629 - + 2010年 [査読有り][通常論文]
     
    Diffusion combustion in a stagnation point boundary layer of a gaseous oxygen jet over a solid fuel was investigated to clarify effects of jet velocity on a similarity condition of fuel regression rates. This combustion field simulates the upstream-end face of the uppermost fuel block of CAMUI type hybrid rocket fuel grain. Increasing the flow velocity from 5.5 m/s to 11.5 m/s caused an increase in the regression rate from 0.22 mm/s to 0.26 mm/s. This result shows that the chemical reaction effect is not negligible in oxidizer impinging region.
  • 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年 [査読有り][通常論文]
     
    Static firing tests clarified how the fuel flow rate varies with the progress of fuel regression in a 'cascaded multistage impinging-jet' (CAMUI) type hybrid rocket motor. The fuel gasification rate decreases with progressing fuel regression because of two causes. One is decreasing gas flow density in ports. The other is decreasing area of end faces. The fuel gasification rate decreases rapidly when end faces disappear. A simple model of the regression progress was proposed. Fuel grains collected after firing tests with various burning duration approved this model. The model serves as a foundation to develop regression formulas applicable to this unconventional type fuel grain.
  • 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, 竹内佑介
    北海道工業大学研究紀要 37 37 205 - 211 北海道工業大学 2009年03月 [査読有り][通常論文]
  • 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年 [査読有り][通常論文]
     
    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.
  • 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年 [査読有り][通常論文]
     
    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.
  • 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年 [査読有り][通常論文]
     
    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.
  • 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年 [査読有り][通常論文]
     
    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.
  • 西舘純, 佐藤立博, 青柳賢英, 大野努, 田中喜規, 竹浪恭平, 佐鳥新, 三橋龍一, 廣田尚久, 石村康生, 杉本康一郎, 松島幸太, 戸谷剛, 榊原隆浩, 堀耕太郎, 江良聡, 中村明広, 安中俊彦, 植松努
    北海道工業大学研究紀要 36 36 191 - 195 北海道工業大学 2008年03月 [査読有り][通常論文]
  • 伊藤 光紀, 前田 剛典, 柿倉 彰仁, 金子 雄大, 森 一大, 中島 卓司, 脇田 督司, 植松 努, 戸谷 剛, 大島 伸行, 永田 晴紀
    日本航空宇宙学会論文集 55 646 516 - 526 社団法人 日本航空宇宙学会 2007年11月 [査読有り][通常論文]
     
    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 ...
  • 佐鳥 新, 戸谷 剛, 榊原 隆浩, 安中 俊彦, 植松 努, 石村 康生, 杉本 康一郎, 松島 幸太, 三橋 龍一, 西舘 純, 佐藤 立博, 青柳 賢英, 大野 努, 田中 喜規, 竹浪 恭平, 中村 明広, 堀 耕太郎, 江良 聡, 廣田 尚久
    北海道工業大学研究紀要 35 105 - 111 北海道工業大学 2007年03月 [査読有り][通常論文]
     
    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 ...
  • 玉山 雄太, 大野 努, 青柳 賢英, 佐藤 立博, 西舘 純, 田中 喜規, 三橋 龍一, 佐鳥 新, 石村 康生, 松島 幸太, 杉本 康一郎, 戸谷 剛, 榊原 隆浩, 安中 俊彦, 中村 明広, 堀 耕太郎, 江良 聡, 廣田 尚久
    北海道工業大学研究紀要 35 281 - 283 北海道工業大学 2007年03月 [査読有り][通常論文]
     
    "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.
  • 玉山 雄太, 青柳 賢英, 佐藤 立博, 西舘 純, 大野 努, 田中 喜規, 三橋 龍一, 佐鳥 新, 石村 康生, 松島 幸太, 杉本 康一郎, 戸谷 剛, 榊原 隆浩, 安中 俊彦, 中村 明広, 堀 耕太郎, 江良 聡, 廣田 尚久
    北海道工業大学研究紀要 35 275 - 280 北海道工業大学 2007年03月 [査読有り][通常論文]
     
    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...
  • Masashi Wakita, Ryusuke Numakura, Yusuke Itoh, Shigetoshi Sugata, Tsuyoshi Totani, Harunori Nagata
    JOURNAL OF PROPULSION AND POWER 23 2 338 - 344 2007年03月 [査読有り][通常論文]
     
    To realize quick initiation of detonation in the combustion chamber of a pulse detonation engine operating in the, air-breathing mode, in which the combustible gas is a fuel-air mixture, the authors have proposed a new pulse detonation engine initiator using a "reflecting board" near the exit of a predetonator tube. In this study, we clarify the transition limit of this new initiator by examining the detonation cell size at the predetonator exit and the mechanism that gives this transition limit. The combustible mixtures are stoichiometric hydrogen-oxygen mixtures diluted with nitrogen or argon. The main results obtained in this study are as follows. When the incident detonation wave interacts with the reflecting board before it completely disappears due to the rarefaction wave from the predetonator exit, the number of cells between the exit and the board defines the transition limit from the planar to cylindrical detonation waves. Even when the cylindrical detonation does not occur, the reflecting board converts a planar detonation wave into a torus-shape pressure wave. This pressure wave encompasses the combustible gas in the detonation chamber and concentrate on the axis, causing a detonation bubble behind the board. The necessary minimum diameter of the predelonator with a reflecting board is expressed by D-c = 6.3 lambda.
  • 佐藤 立博, 武岡 和彦, 西舘 純, 青柳 賢英, 大野 努, 竹浪 恭平, 田中 喜規, 西里 真哉, 三橋 龍一, 佐鳥 新, 石村 康生, 松島 幸太, 戸谷 剛, 榊原 隆浩, 江良 聡, 中村 明広, 堀 耕太郎, 安中 俊彦, 植松 努, 加瀬 誠志, 佐々木 一正
    北海道工業大学研究紀要 35 403 - 407 北海道工業大学 2007年03月 [査読有り][通常論文]
     
    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.
  • 佐藤 立博, 武岡 和彦, 西舘 純, 青柳 賢英, 大野 努, 竹浪 恭平, 田中 喜規, 西里 真哉, 三橋 龍一, 佐鳥 新, 石村 康生, 松島 幸太, 戸谷 剛, 榊原 隆浩, 江良 聡, 中村 明広, 堀 耕太郎, 安中 俊彦, 植松 努, 佐々木 一正
    北海道工業大学研究紀要 35 397 - 401 北海道工業大学 2007年03月 [査読有り][通常論文]
     
    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...
  • 西舘 純, 佐藤 立博, 青柳 賢英, 大野 努, 田中 喜規, 竹浪 恭平, 佐鳥 新, 三橋 龍一, 廣田 尚久, 石村 康生, 杉本 康一郎, 松島 幸太, 戸谷 剛, 榊原 隆浩, 堀 耕太郎, 江良 聡, 中村 明広, 安中 俊彦, 植松 努
    北海道工業大学研究紀要 35 285 - 290 北海道工業大学 2007年03月 [査読有り][通常論文]
     
    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...
  • Nozomu Hashimoto, Harunori Nagata, Tsuyoshi Totani, Isao Kudo
    COMBUSTION AND FLAME 147 3 222 - 232 2006年11月 [査読有り][通常論文]
     
    This study clarified the blowoff mechanism for a flame spreading in an opposed turbulent flow in narrow solid fuel ducts. To clarify this mechanism, two experiments were conducted. The first experiment was to investigate the influence of ambient pressure and fuel duct size on the blowoff limit. The results indicated that the flow velocity at the point when blowoff occurred, V-g,V-t, increased with ambient pressure. This tendency could not be confirmed by a well-known expression for the Damkohler number, which is defined as the ratio of the characteristic flow time to the characteristic chemical time. Subsequently, to clarify the determining factor for the blowoff, the second experiment, which observed the flow field near the flame leading edge, was conducted. The results show that the flow separation in front of the flame leading edge, which provided sufficient residence time of oxidizer and gaseous fuel, is necessary for the flame to spread in an opposed oxidizer flow. From the results, it is found that the oxidizer friction velocity, u(*), which is an indicator of the turbulent momentum transfer, is the determining factor for the flame blowoff limit. When the friction velocity is larger than a critical value, flame blowoff occurs in the fuel duct, due to the absence of flow separation. (c) 2006 The Combustion Institute. Published by Elsevier Inc. All rights reserved.
  • 沼倉 龍介, 脇田 督司, 伊藤 雄介, 菅田 成俊, 永田 晴紀, 戸谷 剛, 工藤 勲
    日本燃焼学会誌 48 145 265 - 272 日本燃焼学会 2006年08月 [査読有り][通常論文]
  • T Totani, T Kodama, K Watanabe, K Nanbu, H Nagata, Kudo, I
    ACTA ASTRONAUTICA 59 1-5 192 - 199 2006年07月 [査読有り][通常論文]
     
    A model of the circulation of the working fluid in a liquid droplet radiator has been developed. The model is based on Bernoulli's law and the loss of the hydraulic head. The behavior of the circulation of the working fluid calculated from the model is compared with that obtained from experiments in the case that the flow rate of the circulating working fluid is changed. In radiators, the flow rate of the circulating working fluid is changed in order to match the change of the waste heat generated in large-space structures. The flow rates of the circulating working fluid calculated from the model correspond to those obtained from the experiments well. The circulation mechanism of the working fluid in the liquid droplet radiator has been clarified. The model developed in the present work will allow us to control the flow rate of the working fluid in the liquid droplet radiator automatically. (C) 2006 Elsevier Ltd. All rights reserved.
  • Harunori Nagata, Mitsunori Ito, Takenori Maeda, Mikio Watanabe, Tsutomu Uematsu, Tsuyoshi Totani, Isao Kudo
    ACTA ASTRONAUTICA 59 1-5 253 - 258 2006年07月 [査読有り][通常論文]
     
    By introducing various innovative ideas, the difficult-to-develop small hybrid-type rocket is successfully developed. The main purpose is to drastically reduce the cost of rocket experiments and thus, attract potential users such as metrological and microgravity researchers. A key idea is a new fuel grain design to accelerate the gasification rate of solid fuel. The new fuel grain design, designated as CAMUI as an abbreviation of "cascaded multistage impinging-jet", is that the gas flow repeatedly collides with the solid fuel surface to accelerate the heat transfer to the fuel. To install a regenerative cooling system using cryogenic liquid oxygen as coolant in a small launcher, the authors devised a valveless supply system (with no valves in the liquid oxygen flow line). Four serial successful launch verification tests by 10kg vehicle equipped with a 50kgf thrust CAMUI motor have shown the feasibility of the motor system. The meteorological observation model of 400kgf class motor is under development and the development of microgravity experiment class of 1.5-2tonf motor will follow subsequently. The authors plan to complete the development of the 400kgf class motor for meteorological observation model by the end of FY2005. (C) 2006 Elsevier Ltd. All rights reserved.
  • 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年 [査読有り][通常論文]
  • 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年 [査読有り][通常論文]
  • 脇田 督司, 沼倉 龍介, 伊藤 雄介, 永田 晴紀, 戸谷 剛, 工藤 勲
    日本航空宇宙学会論文集 53 620 414 - 418 社団法人 日本航空宇宙学会 2005年09月 [査読有り][通常論文]
     
    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...
  • 渡辺 三樹生, 永田 晴紀, 戸谷 剛, 工藤 勲
    日本航空宇宙学会論文集 53 618 337 - 342 社団法人 日本航空宇宙学会 2005年07月 [査読有り][通常論文]
     
    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 ...
  • T Totani, T Kodama, H Nagata, Kudo, I
    JOURNAL OF SPACECRAFT AND ROCKETS 42 3 493 - 499 2005年05月 [査読有り][通常論文]
     
    The waste heat from the space solar-power system, which supplies 5 MW of electricity to a power transmission line on Earth, is estimated, and the liquid droplet radiator for handling the waste heat are examined on the basis of experimental results obtained under microgravity for droplet generation and droplet collection of the liquid droplet radiator. The following results have been obtained. First, an active heat removal system for the power generation unit in the photovoltaic power system is not necessary when the concentration ratio of solar energy is smaller than 1.34, whereas for the liquid droplet radiator, with silicon oil as working fluid, in the solar dynamic power system, the droplet sheet for radiating the waste heat must be 147 m long, 65.1 m wide, and 0.998 m thick. Second, the droplet sheet of the liquid droplet radiator, in which the working fluid is silicon oil, must be 107 m long, 43.2 m wide, and 0.998 m thick to manage the waste heat from the power distribution unit and the power transmission unit in the photovoltaic power system, whereas it must be 107 m long, 65.2 to wide, and 0.998 m thick in the solar dynamic power system.
  • D Nakamura, H Nagata, T Totani, Kudo, I
    JSME INTERNATIONAL JOURNAL SERIES B-FLUIDS AND THERMAL ENGINEERING 48 1 144 - 150 2005年02月 [査読有り][通常論文]
     
    The authors have proposed the use of a hydrogen concentration probe as a new simple method of evaluating hydrogen concentration. We propose a method of evaluating the rate of change of catalytic heat release in order to evaluate hydrogen concentration history for the condition under which the boundary layer is likely to be immature. By using a shock tube, the rate of increase of heat budget of platinum wire was investigated experimentally. Experimental results indicate that the rate of increase of difference due to catalytic heat release is the maximum value when the hydrogen concentration is 30%, which agrees well with a previous result. As a result, this method can be used to evaluate the rate of increase of difference due to catalytic heat release. It is clear that the rate of change due to catalytic heat release is strongly correlated with the rate of change of hydrogen concentration.
  • 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年 [査読有り][通常論文]
  • T Totani, T Kodama, K Watanabe, H Nagata, Kudo, I
    MICROGRAVITY SCIENCE AND TECHNOLOGY 17 3 31 - 38 2005年 [査読有り][通常論文]
     
    Experiments on the convergence of two droplet streams have been carried out under microgravity in order to develop a technique for converging droplet streams under microgravity and to examine the behavior of droplets in a vacuum and under microgravity after the binary droplets collide with each other The working fluid is silicone oil with a low vapor pressure. In this study, a method of orienting the droplet generators toward a con vergence point has been tested. In all of the 68 experiments conducted under microgravity, it is confirmed that droplet streams are converged. It has been concluded that the method of orienting multiple droplet generators to a converging point is effective for converging droplet streams under microgravity. The behaviors of the colliding droplets under microgravity and in a vacuum have been classified into five types. The five types of behavior are mapped on a We (Weber number) - B (impact parameter) diagram. The range of Weber numbers in the experiments is from 200 to more than 3000.
  • T Totani, M Itami, H Nagata, Kudo, I, A Iwasaki
    REVIEW OF SCIENTIFIC INSTRUMENTS 75 2 515 - 523 2004年02月 [査読有り][通常論文]
     
    A measurement technique for obtaining the pumping performance of a centrifugal collector under microgravity has been developed and evaluated through microgravity experiments. These tests have been conducted under conditions such that the pressure sensors cannot easily detect the pressure rise of the liquid working fluid. These conditions have a pressure increase smaller than 400 Pa. The characteristic of the head produced in a centrifugal collector calculated from experimental data agrees well with that predicted theoretically from the velocity and the pressure generated by rotation of the centrifugal collector. It is concluded from this result that the measurement technique can correctly obtain the pumping performance of the centrifugal collector under microgravity. The centrifugal collector has produced the head of 0.041 m at the rotation speed of 223 rpm under microgravity. The working fluid is silicon oil. This head corresponds to the pressure rise of approximately 390 Pa. (C) 2004 American Institute of Physics.
  • 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年 [査読有り][通常論文]
  • Daisuke Nakamura, Harunori Nagata, Tsuyoshi Totani, Isao Kudo
    Heat Transfer - Asian Research 33 1 1 - 11 2004年01月 [査読有り][通常論文]
     
    The authors have proposed a hydrogen concentration probe using a catalytic reaction on the surface of a platinum wire. To use this probe for detecting the concentration change in a supersonic mixing layer, the response of the catalytic heat release rate must depend only on the change of concentration around the probe. The catalytic heat release rate on the surface of the platinum wire in an unsteady state was measured by a constant-temperature hot-wire anemometer and a shock tube to investigate the relationship between the response of the catalytic heat release rate and the temperature of the platinum wire. The catalytic heat release rate began increasing upon the introduction of the shock wave. The rate of increase of catalytic heat release depended on the temperature of the platinum wire when the temperature of the hot wire was low. However, the dependence was very weak when the temperature of the hot wire was above 400 °C. This shows that it is not the catalytic reaction but rather molecular transfer from the flow to the surface of the platinum wire is the controlling step when the temperature of the platinum wire is high. In conclusion, the temperature of the platinum wire must be above 400 °C to use the hydrogen concentration probe in a supersonic mixing layer. © 2003 Wiley Periodicals, Inc.
  • 吉川 茂雄, 戸谷 剛, 永田 晴紀, 工藤 勲
    日本ディスタンスラーニング学会会誌 4 13 - 20 日本ディスタンスラーニング学会 2003年03月 [査読有り][通常論文]
  • N Hashimoto, S Watanabe, H Nagata, T Totani, Kudo, I
    PROCEEDINGS OF THE COMBUSTION INSTITUTE 29 245 - 250 2003年 [査読有り][通常論文]
     
    The influence of channel height on flame spread in a circular duct of the solid fuel in an opposed-flow configuration was examined. Polymethylmethacrylate cylinders with a circular duct (diameter of 1, 2, or 3 mm) were used as fuel specimens, and both flame-spreading and stabilized combustion were observed. In the case of stabilized combustion, the flame cannot spread into the duct because of the high oxygen velocity The flame-traveling velocity is the velocity at which the flame widens the duct by fuel consumption. Therefore, the flame-traveling velocity in stabilized combustion is significantly low compared with flame-spreading combustion. In the case of flame-spreading combustion, the equivalence velocity, which contains channel height information, defines whether the regime is the thermal or the chemical regime. When the equivalent velocity is higher than a certain value, the flame-spread rate is controlled by chemical effects. On the whole, the flame-spread rate decreases with the decrease of channel height in the case of flame-spreading combustion because of the curvature effect. Owing to the curvature effect, the area ratio of the flame to that of the solid surface decreases with decreasing channel height, and this is conspicuous when the channel height is low. The curvature effect is negligible when the channel height is sufficiently large compared with the flame stand-off distance.
  • 中村 大輔, 永田 晴紀, 戸谷 剛, 工藤 勲
    日本機械学會論文集. B編 69 677 126 - 131 一般社団法人日本機械学会 2003年 [査読有り][通常論文]
     
    The authors have proposed a hydrogen concentration probe using catalytic reaction on Pt wire surface. To use this probe to detect a concentration change in a supersonic mixing layer, the response of the catalytic heat release rate must depend only on concentration change around the probe. Catalytic heat release rate on the Pt wire surface in unsteady state is measured using a constant temperature type hotwire anemometer technique and a shock tube to investigate the relation of the response of the catalytic heat release rate and Pt wire temperature. Catalytic heat release rate begins increas...
  • 渡辺 三樹生, 中山 久広, 永田 晴紀, 戸谷 剛, 工藤 勲, 伊藤 献一, 大和田 陽一
    JASMA : Journal of the Japan Society of Microgravity Application 19 2 112 - 116 日本マイクログラビティ応用学会 2002年04月 [査読有り][通常論文]
  • 吉川 茂雄, 戸谷 剛, 永田 晴紀, 工藤 勲
    日本ディスタンスラーニング学会会誌 3 19 - 25 日本ディスタンスラーニング学会 2002年03月 [査読有り][通常論文]
  • T Totani, M Itami, H Nagata, Kudo, I, A Iwasaki, S Hosokawa
    MICROGRAVITY SCIENCE AND TECHNOLOGY 13 2 42 - 45 2002年 [査読有り][通常論文]
     
    The Liquid Droplet Radiator (LDR) has an advantage over comparable conventional radiators in terms of the rejected heat power-weight ratio. Therefore, the LDR has attracted attention as an advanced radiator for high-power space systems that will be prerequisite for large space structures. The performance of the LDR under microgravity condition has been studied from the viewpoint of operational space use of the LDR in the future. In this study, the performances of a droplet generator and a droplet collector in the LDR are investigated using drop shafts in Japan: MGLAB and JAMIC. As a result, it is considered that (I) the droplet generator can produce uniform droplet streams in the droplet diameter range from 200 to 280 [mum] and the spacing range from 400 to 950 [mum] under microgravity condition, (2) the droplet collector with the incidence angle of 35 degrees can prevent a uniform droplet stream, in which droplet diameter is 250 [mum] and the velocity is 16 [m/s], from splashing under microgravity condition, whereas splashes may occur at the surface of the droplet collector in the event that a nonuniform droplet stream collides against it.
  • 戸谷 剛, 伊丹 雅洋, 藪田 茂, 永田 晴紀, 工藤 勲, 岩崎 晃, 細川 俊介
    日本機械学會論文集. B編 68 668 1166 - 1173 一般社団法人日本機械学会 2002年 [査読有り][通常論文]
     
    The Liquid Droplet Radiator (LDR) has an advantage over comparable conventional radiators in terms of the rejected heat power-weight ratio. Therefore, the LDR has attracted as an advanced radiator for high-power space systems that will be prerequisite for large space structures. In this study, the performance of a droplet emittor under microgravity condition has been investigated from the viewpoint of operational space use of the LDR in the future. From experiments, it is considered that the droplet emittor can produce uniform droplet streams under microgravity condition in the non-dimensio...
  • 戸谷 剛, 伊丹 雅洋, 藪田 茂, 永田 晴紀, 工藤 勲, 岩崎 晃, 細川 俊介
    日本機械学會論文集. B編 68 674 2780 - 2787 一般社団法人日本機械学会 2002年 [査読有り][通常論文]
     
    The Liquid Droplet Radiator (LDR) has an advantage over conventional radiators in terms of the rejected heat power-weight ratio. LDR has been taken notice as an advanced radiator for highpower generation systems which will be prerequisite for large space structures. In this study, the performance of a centrifugal droplet collector under microgravity condition has been investigated from the viewpoint of operational space use of LDR in the future. It has been concluded that (1) a centrifugal collector is able to transport working fluid to a recirculating pump under microgravity condition; (2)...
  • 戸谷 剛, 潮 敬之, 永田 晴紀, 工藤 勲
    日本機械学會論文集. C編 67 655 633 - 640 一般社団法人日本機械学会 2001年 [査読有り][通常論文]
     
    Inflatable structures have attracted considerable attention as space structures. In many space experiments, folds occurred during deployments of inflatable structures. They had undesirable influences on the body of space structures. This paper is intended as an investigation of deploying behaviors under microgravity of inflatable tubes that have a plastic fold on the center and a mass block on the tip. During their deployments, spring-back phenomena were happened in some experimental conditions. In order to examine these spring-back phenomena, a numerical simulation was conducted using the ...
  • 戸谷 剛, 黒田 明慈, 工藤 一彦
    日本機械学會論文集. B編 65 629 267 - 274 一般社団法人日本機械学会 1999年01月 [査読有り][通常論文]
     
    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...

書籍

  • 次世代自動車の熱マネジメント
    戸谷 剛 (担当:分担執筆範囲: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 2020年12月 (ISBN: 9784861048197) 326-332
  • 応用数理ハンドブック
    戸谷 剛 (担当:分担執筆範囲:衛星の熱解析)
    朝倉書店 2013年11月 (ISBN: 9784254111415)
  • Small Satellite Missions for Earth Observation
    Yoshihide Aoyanagi, Shin Satori, Tsuyoshi Totani, Toshihiko Yasunaka, Akihiro Nakamura, Yusuke Takeuchi (担当:分担執筆範囲:Development of Spaceborne Small Hyperspectral sensor HSC-III for Micro Satellite)
    Springer Berlin Heidelberg 2010年 (ISBN: 9783642035005)

講演・口頭発表等

  • 推力5000N級CAMUI型ハイブリッドロケットの開発と打上げ実証  [通常講演]
    永田晴紀, 脇田督司, 戸谷剛, 植松努, 安本裕紀, 三橋龍一
    第56回宇宙科学技術連合講演会 2012年11月 口頭発表(一般) 別府市 日本航空宇宙学会
  • 短期開発を実現する少節点解析と多節点解析を併用した超小型衛星の熱設計法  [通常講演]
    小川洋人, 井上遼太, 戸谷剛, 脇田督司, 永田晴紀
    第56回宇宙科学技術連合講演会 2012年11月 口頭発表(一般) 別府市 日本航空宇宙学会
  • 構造転移により蓄熱する超小型衛星用蓄熱材の開発  [通常講演]
    戸谷剛, 佐藤敏文, 脇田督司, 永田晴紀
    第56回宇宙科学技術連合講演会 2012年11月 口頭発表(一般) 別府市 日本航空宇宙学会
  • 表面微細周期構造を用いた波長選択性ラジエータ  [通常講演]
    戸谷剛, 脇田督司, 永田晴紀
    熱工学コンファレンス 2012 2012年11月 口頭発表(一般) 熊本市 日本機械学会 熱工学部門
  • Optical Properties of Wavelength-selective Radiator with Periodic Microcavities  [通常講演]
    Tsuyoshi Totani, Naoyuki Ishikawa, Minoru Iwata, Masashi Wakita, Harunori Nagata
    The 3rd International Forum on Heat Transfer 2012年11月 ポスター発表 長崎市 日本伝熱学会
  • Thermal Analyses and Guideline for Thermal Design of Nano and Micro Satellites on Sun-synchronous Orbits  [通常講演]
    Ryota Inoue, Tsuyoshi Totani, Hiroto Ogawa, Masashi Wakita, Harunori Nagata
    UN/Japan Nano-Satellite Symposium 2012年10月 ポスター発表 名古屋市 国際連合、東京大学
  • 結晶転移する蓄熱材の蓄熱性能  [通常講演]
    戸谷剛, 佐藤敏文, 脇田督司, 永田晴紀
    第33回日本熱物性シンポジウム 2012年10月 口頭発表(一般) 大阪市 日本熱物性学会
  • 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  [通常講演]
    戸谷剛, 脇田督司, 永田晴紀
    第33回日本熱物性シンポジウム 2012年10月 口頭発表(一般) 大阪市 日本熱物性学会
  • 太陽同期軌道を周回する超小型衛星の熱解析と熱設計に関する研究  [通常講演]
    井上遼太, 小川洋人, 戸谷剛, 脇田督司, 永田晴紀
    日本機械学会2012年度年次大会 2012年09月 口頭発表(一般) 金沢市 日本機械学会
  • 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  [通常講演]
    桧物恒太郎, 棧敷和弥, 脇田督司, 戸谷剛, 永田晴紀
    第44回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2012 2012年07月 口頭発表(一般) 富山市 日本航空宇宙学会,宇宙航空研究開発機構
  • 金属膜を付与した表面微細周期構造の垂直放射率特性  [通常講演]
    戸谷剛, 石川直幸, 脇田督司, 永田晴紀
    第49回日本伝熱シンポジウム 2012年05月 口頭発表(一般) 富山市 日本伝熱学会
  • 1節点解析と2節点解析を用いた太陽同期軌道を周回する超小型衛星の熱設計手法  [通常講演]
    井上遼太, 小川洋人, 戸谷剛, 脇田督司, 永田晴紀
    日本航空宇宙学会北部支部2012年講演会 2012年03月 口頭発表(一般) 室蘭市 日本航空宇宙学会北部支部
  • 太陽同期軌道を周回する超小型衛星の熱解析  [通常講演]
    井上遼太, 小川洋人, 戸谷剛, 脇田督司, 永田晴紀
    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 2012年03月 口頭発表(一般) 札幌市 日本機械学会北海道学生会
  • 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  [通常講演]
    棧敷和弥, 寺坂昭宏, 脇田督司, 戸谷剛, 永田晴紀
    第43回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2011 2011年07月 口頭発表(一般) 東京都 日本航空宇宙学会,宇宙航空研究開発機構,日本流体力学会
  • 微小重力における液滴ラジエータの評価  [通常講演]
    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」  [通常講演]
  • 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・・・  [通常講演]
  • 微小重力下における液滴ラジエータ要素の性能試験  [通常講演]
    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)  [通常講演]
  • 506 Virtual Space Research Laboratoryの構築と設計支援への適用(北海道における宇宙活動I)(オーガナイズドセッション(d)北海道における宇宙活動)  [通常講演]
    吉川 茂雄, 戸谷 剛, 永田 晴紀, 工藤 勲
  • 510 衝突噴流式ハイブリッドロケットの点火特性および燃焼安定性(北海道における宇宙活動II)(オーガナイズドセッション(d)北海道における宇宙活動)  [通常講演]
    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 端面燃焼式ハイブリッドロケットの燃焼安定性に関する研究(北海道における宇宙活動II)(オーガナイズドセッション(d)北海道における宇宙活動)  [通常講演]
    橋本 望, 永田 晴紀, 戸谷 剛, 工藤 勲
  • 514 超音速流用水素濃度プローブの応答速度(北海道における宇宙活動III)(オーガナイズドセッション(d)北海道における宇宙活動)  [通常講演]
    笹木 正裕, 中村 大輔, 永田 晴紀, 戸谷 剛, 工藤 勲
  • 516 液滴ラジエータ要素の微小重力実験(北海道における宇宙活動III)(オーガナイズドセッション(d)北海道における宇宙活動)  [通常講演]
    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 微小重力場における模擬石炭粒子群の点火に関する研究(北海道における宇宙活動III)(オーガナイズドセッション(d)北海道における宇宙活動)  [通常講演]
    丹羽 由樹子, 永田 晴紀, 戸谷 剛, 工藤 勲
  • 液滴ラジエータ要素 (液滴回収器,ギアポンプ)の微小重力下での性能  [通常講演]
    戸谷 剛, 藪田 茂, 永田 晴紀, 工藤 勲, 岩崎 晃, 細川 俊介
  • 707 微小重力環境下における液滴ラジエータの作動流体循環試験(OS7-2 マイクログラビティー)(OS7 北海道における航空宇宙工学研究の進展と未来)  [通常講演]
    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 衝撃波後方の非定常場における水素 : 空気混合気の白金触媒燃焼発熱量の測定(OS7-3 計測・地上実験設備)(OS7 北海道における航空宇宙工学研究の進展と未来)  [通常講演]
    中村 大輔, 永田 晴紀, 戸谷 剛, 工藤 勲
  • 720 衝突噴流式ハイブリッドロケットのフライトモデル設計のための地上燃焼試験(OS7-6 航空宇宙推進(流体,燃焼))(OS7 北海道における航空宇宙工学研究の進展と未来)  [通常講演]
    中山 久広, 渡辺 三樹生, 永田 晴紀, 工藤 勲, 戸谷 剛
  • 液滴ラジエータの作動流体循環に関する微小重力実験  [通常講演]
    戸谷 剛, 薮田 茂, 宮本 拓哉, 永田 晴紀, 工藤 勲
  • 3333 噴流衝突型高推力ハイブリッドロケットの開発および打上げ実験  [通常講演]
    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
  • 1502 微小重力場を利用した高温雰囲気における固体燃料粒子群の点火に関する研究  [通常講演]
    永田 晴紀, 藤井 篤之, 伊藤 献一, 戸谷 剛, 工藤 勲
  • 306 反射板によるデトネーション波の伝播促進 : 反射板距離の影響  [通常講演]
    脇田 督司, 沼倉 龍介, 永田 晴紀, 戸谷 剛, 工藤 勲
  • 307 端面燃焼式ハイブリッドロケット用多孔質固体燃料の後退特性  [通常講演]
    渡辺 賢, 橋本 望, 永田 晴紀, 戸谷 剛, 工藤 勲
  • 308 加圧燃焼器内でのペレット状固体燃料のガス化に関する研究  [通常講演]
    藤井 篤之, 栗田 慎一郎, 永田 晴紀, 戸谷 剛, 工藤 勲
  • 401 TOPAZ を用いた木星探査衛星の概念設計  [通常講演]
    加藤 健太郎, 永田 晴紀, 戸谷 剛, 工藤 勲
  • 短時間微小重力実験による液滴ラジエータ要素の機能試験  [通常講演]
    戸谷 剛, 永田 晴紀, 工藤 勲
  • 3316 再使用型 CAMUI ハイブリッドロケットの打上げ・回収試験  [通常講演]
    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
  • 415 高層成層圏観測に用いる完全再使用型 CAMUI ハイブリッドロケットの基本設計  [通常講演]
    三浦 崇志, 渡辺 三樹生, 永田 晴紀, 戸谷 剛, 工藤 勲
  • 416 マイクロローバーを搭載した火星探査機の概念設計  [通常講演]
    増田 紀昭, 戸谷 剛, 永田 晴紀, 工藤 勲
  • 419 反射板まわりにおけるデトネーション波の再点火機構  [通常講演]
    沼倉 龍介, 脇田 督司, 永田 晴紀, 戸谷 剛, 工藤 勲
  • 微小重力下における液滴流の収束および衝突挙動  [通常講演]
    戸谷 剛, 児玉 拓也, 渡辺 健介, 永田 晴紀, 工藤 勲
  • CAMUIハイブリッドロケットによる小型ロケット実験市場の創出  [通常講演]
    永田 晴紀, 渡辺 三樹生, 伊藤 光範, 前田 剛典, 戸谷 剛, 工藤 勲
  • 3329 太陽熱推進用スラスタの伝熱解析と性能特性(S86-2 小型宇宙システム(2),S86 小型宇宙システム)  [通常講演]
    高野 千尋, 村木 祐介, 戸谷 剛, 永田 晴紀, 工藤 勲
  • 3332 CAMUI方式を用いた推力70kgf級ロケットモーターの燃料設計(S86-2 小型宇宙システム(2),S86 小型宇宙システム)  [通常講演]
    伊藤 光紀, 前田 剛典, 永田 晴紀, 戸谷 剛, 工藤 勲, 植松 務
  • 3422 液滴ラジエータにおける作動流体の循環特性(S89-2 微小重力・宇宙環境利用(2),S89 微小重力・宇宙環境利用)  [通常講演]
    戸谷 剛, 児玉 拓也, 渡辺 健介, 南部 航太, 永田 晴紀, 工藤 勲
  • 216 反射板を用いたPDEイニシエータにおいて入射衝撃波強度が動作特性に及ぼす影響(航空宇宙工学)  [通常講演]
    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 二段燃焼式ハイブリッドロケットの熱設計(航空宇宙工学)  [通常講演]
    譜久山 尚, 坂本 将司, 永田 晴紀, 戸谷 剛, 工藤 勲
  • 218 液滴ラジエータの循環流量変化時における作動流体循環の過渡特性(航空宇宙工学)  [通常講演]
    渡辺 健介, 南部 航太, 戸谷 剛, 永田 晴紀, 工藤 勲
  • 219 マウスを用いた回収型動物実験衛星の概念設計検討(航空宇宙工学)  [通常講演]
    飯田 恭平, 戸谷 剛, 永田 晴紀, 工藤 勲, 矢野 昭起
  • 1024 CAMUI方式を用いた推力400kgf級サウンディングロケットの研究開発(S87 小型宇宙システム,S87 小型宇宙システム)  [通常講演]
    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 マルチセルインフレータブル構造の剛性に関する研究(宇宙工学)  [通常講演]
    加藤 隆造, 戸谷 剛, 石村 康生, 永田 晴紀
  • 116 液滴ラジエータにおける液滴流回収時の飛散と捕集に関する研究(宇宙工学)  [通常講演]
    南部 航太, 川上 哲史, 由利 泰史, 戸谷 剛, 永田 晴紀
  • 117 HIT-SATフライトモデルの構造設計と機械環境試験(宇宙工学)  [通常講演]
    榊原 隆浩, 戸谷 剛, 安中 俊彦, 佐鳥 新, 永田 晴紀
  • 118 二段燃焼式ハイブリッドロケットのEMの設計(宇宙工学)  [通常講演]
    坂本 将司, 片野 光, 戸谷 剛, 永田 晴紀
  • 120 デトネーション波の伝播促進に及ぼすドライバーガス供給量の影響(宇宙工学)  [通常講演]
    菅田 成俊, 脇田 督司, 沼倉 龍介, 永田 晴紀, 戸谷 剛
  • B-2-51 超小型人工衛星HIT-SATの衛星通信システム(B-2.宇宙・航行エレクトロニクス,一般講演)  [通常講演]
    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
  • HIT‐SATの姿勢制御結果と北海道衛星への展開  [通常講演]
    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
  • 超小型衛星「HIT‐SAT」の電源系の解析  [通常講演]
    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
  • HIT‐SATの軌道上温度データと熱解析モデルの再検討  [通常講演]
    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 超音波パルス反射法を用いたハイブリッドロケット燃料後退履歴の取得に関する研究(S74-3 小型宇宙システム(3),S74 小型宇宙システム)  [通常講演]
    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 CAMUI方式ハイブリッドロケットの燃料後退特性に及ぼすスケール効果(S74-3 小型宇宙システム(3),S74 小型宇宙システム)  [通常講演]
    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 HIT-SATの姿勢制御結果と北海道衛星への展開(S74-2 小型宇宙システム(2),S74 小型宇宙システム)  [通常講演]
    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 HIT-SATの軌道上温度データと熱解析モデルの再検討(S74-2 小型宇宙システム(2),S74 小型宇宙システム)  [通常講演]
    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 超小型衛星「HIT-SAT」の電源系の解析(G19 宇宙工学に関する基盤研究,G19 宇宙工学)  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    岩城裕樹, 戸谷剛, 永田晴紀
  • 503 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(宇宙工学)  [通常講演]
    由利 泰史, 川上 哲史, 戸谷 剛, 永田 晴紀
  • 504 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(宇宙工学)  [通常講演]
    岩城 裕樹, 戸谷 剛, 永田 晴紀
  • 505 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(宇宙工学)  [通常講演]
    川上 哲史, 由利 泰史, 戸谷 剛, 永田 晴紀
  • 506 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(宇宙工学)  [通常講演]
    片野 光, 羽柴 健太, 戸谷 剛, 永田 晴紀
  • 507 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(宇宙工学)  [通常講演]
    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
  • 502 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(宇宙工学)  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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
  • 宇宙用小型ハイパースペクトルセンサの試作評価  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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 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(B-2. 宇宙・航行エレクトロニクス,一般セッション)  [通常講演]
    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  [通常講演]
    浅田隆利, 脇田督司, 沼倉龍介, 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モデルを用いた燃料グレイン設計  [通常講演]
    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
  • 超音波パルス反射法を用いたハイブリッドロケット燃料の後退履歴の取得  [通常講演]
    金子雄大, 伊藤光紀, 植嶋健太, 戸谷剛, 永田晴紀
  • ラバールノズルの伸長および加熱による推力・比推力の向上  [通常講演]
    岩城裕樹, 長沼哲史, 戸谷剛, 永田晴紀
  • 4037 ラバールノズルの伸長および加熱による推力・比推力の向上(S60-1 小型宇宙システム(1),21世紀地球環境革命の機械工学:人・マイクロナノ・エネルギー・環境)  [通常講演]
    岩城 裕樹, 長沼 哲史, 戸谷 剛, 永田 晴紀
  • 4040 CAMUIハイブリッドロケットの性能履歴予測モデルを用いた燃料グレイン設計(S60-2 小型宇宙システム(2),21世紀地球環境革命の機械工学:人・マイクロナノ・エネルギー・環境)  [通常講演]
    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 超音波パルス反射法を用いたハイブリッドロケット燃料の後退履歴の取得(S60-2 小型宇宙システム(2),21世紀地球環境革命の機械工学:人・マイクロナノ・エネルギー・環境)  [通常講演]
    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  [通常講演]
    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  [通常講演]
    浅田隆利, 脇田督司, 戸谷剛, 永田晴紀
  • 605 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(宇宙工学・環境)  [通常講演]
    羽柴 健太, 堺 裕哉, 戸谷 剛, 永田 晴紀
  • 606 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(宇宙工学・環境)  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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 超小型人工衛星HIT-SATの実験結果(B-2.宇宙・航行エレクトロニクス,一般セッション)  [通常講演]
    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  [通常講演]
    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  [通常講演]
    脇田督司, 浅田隆利, 戸谷剛, 永田晴紀
  • ラバールノズルでの対流熱伝達を利用した推力・比推力の向上  [通常講演]
    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 ラバールノズルでの対流熱伝達を利用した推力・比推力の向上(大気突入・減速技術(2))  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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 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(移動・輸送のメカトロニクス)  [通常講演]
    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 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(移動・輸送のメカトロニクス)  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
  • 第47回日本伝熱シンポジウムの報告  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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 超小型宇宙機UNITEC-1の熱設計と軌道上温度(小型宇宙システム(1),社会変革を技術で廻す機械工学)  [通常講演]
    戸谷 剛, 脇田 督司, 永田 晴紀, UNITEC, 開発チーム
  • S1901-1-2 小型CAMUI式ハイブリッドロケットの開発と運用(小型宇宙システム(1),社会変革を技術で廻す機械工学)  [通常講演]
    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 CAMUI型固体燃料の燃料後退予測式取得方法に関する検討(小型宇宙システム(1),社会変革を技術で廻す機械工学)  [通常講演]
    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 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(宇宙工学部門一般講演,社会変革を技術で廻す機械工学)  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    野原正寛, 金子雄大, 萩原俊輔, 脇田督司, 戸谷剛, 永田晴紀
  • 512 樹脂製表面微細周期構造の分光特性(環境工学)  [通常講演]
    石川 直幸, 戸谷 剛, 永田 晴紀, 脇田 督司
  • 612 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(ロボティクス・メカトロニクス/宇宙工学)  [通常講演]
    野原 正寛, 金子 雄大, 萩原 俊輔, 脇田 督司, 戸谷 剛, 永田 晴紀
  • 613 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(ロボティクス・メカトロニクス/宇宙工学)  [通常講演]
    寺坂 昭宏, 田村 正佳, 脇田 督司, 戸谷 剛, 永田 晴紀
  • 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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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 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(超小型衛星(2))  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    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  [通常講演]
    石川直幸, 戸谷剛, 脇田督司, 永田晴紀

作品等

  • 日本伝熱学会 北海道支部 伝熱セミナーでの招待講演
    2012年
  • JAXA 宇宙教育指導者セミナー での招待講演
    2011年
  • 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年
  • Chittagong University of Engineering and Technology, Bangladeshでの招待講演
    2010年
  • 国際学会での学術講演
    2008年
  • 国際学会での学術講演
    2008年
  • 国際学会での学術講演
    2008年
  • 国際学会での学術講演
    2008年
  • 国際学会での学術講演
    2008年
  • 国際学会での学術講演
    2008年
  • 国際学会での学術講演
    2008年
  • 国際学会での学術講演
    2007年
  • 北海道支部講演会での招待講演
    2007年

その他活動・業績

  • 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年
  • 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 2016年09月06日 [査読無し][通常論文]
  • Yuji Saito, Toshiki Yokoi, Hiroyuki Yasukochi, Kentaro Soeda, Tsuyoshi Totani, Masashi Wakita, Harunori Nagata Proceedings of the International Astronautical Congress, IAC 2016年01月01日 [査読無し][通常論文]
     
    Copyright © 2016 by the International Astronautical Federation (IAF). All rights reserved. The axial-injection end-burning type hybrid rocket originally proposed twenty years ago by Nagata and Hashimoto et al. recently recaptured the attention of researchers for its virtues such as constant ξ (oxidizer to fuel mass ratio) during firing and throttling operations. Previous studies revealed that, for combustion in a single-port fuel grain, the end-face regression rate in the axial direction is proportional to pressure, with a pressure exponent of 0.95. Accordingly, these rockets were expected to display good throttling characteristics. Given that no ξ shift occurs, keeping the oxidizer mass flow rate within 1% of its initial design point ensures specific impulse will remain within 97% of its design point. There are several requirements for realizing this type of hybrid rocket: 1) high fuel filling rate for obtaining an optimal ξ 2) small port intervals for increasing port merging rate; 3) ports arrayed across the entire fuel section. Because common manufacturing methods were unable to produce a fuel that satisfied these requirements, no previous researchers have conducted experiments with this kind of hybrid rocket. Recent advances in high-accuracy 3D printing have enabled such fuels to be produced for the first time. The fuel grains used in this study were produced by a high-precision light polymerized 3D printer. Each grain consisted of an array of 0.3 mm diameter ports for a fuel filling rate of 98%. Last year, the authors reported the results of multiple firing tests of an axial-injection end-burning type hybrid rocket using 3D printed fuel grains and verified that solid fuel regression rate is linearly dependent on pressure. In this study, the authors conducted a unique set of experiments to verify the throttling characteristics of the axial-injection end-burning type hybrid rocket. Oxidizer mass flow rate and chamber pressure were throttled during firings by actuating valves in a fluid circuit consisting of four oxidizer supply lines. Chamber pressure and oxidizer mass flow rate were measured during each firing. These experimental data were analyzed by a reconstruction technique to obtain ξ history. The results show that ξ remains almost constant during firing, even during throttling operations. Therefore, this study verifies that the axial-injection end-burning type hybrid rocket has superb throttling characteristics. Additionally, the study supports findings in previous research that indicate the pressure exponent is close to unity.
  • 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年 [査読無し][通常論文]
  • Tomohiro Takanashi, Tsuyoshi Totani, Yuto Kimura, Harunori Nagata, Masashi Wakita Proceedings of the International Astronautical Congress, IAC 1 519 -522 2014年01月01日 [査読無し][通常論文]
     
    Copyright © 2014 by the International Astronautical Federation. All rights reserved. A high efficiency system for disposing of large quantities of waste heat is needed to realize large structures in space such as solar power satellites, space factories in orbit and bases on the moon. The Liquid Droplet Radiator (LDR) can be the system instead of a conventional radiator with solid plates. In previous studies, the performance tests of a droplet generator, a linear droplet collector, and a gear pump have been conducted under micro-gravity environment. The radiation heat from liquid droplet streams is due to be measured by a part of research of a LDR. It is needed to conduct an experiment to measure the radiation heat from liquid droplet streams under micro-gravity environment to know properties of a LDR. As a first step for the experiment under micro-gravity environment, an experiment for measuring the radiation heat from a liquid droplet stream was conducted under gravitational environment. In order to take the influence of absorption or dispersion into consideration, a numerical analysis of inside an experimental device was also performed. The appropriateness of a result of the experiment ware evaluated by comparing a experimental value with results of numerical analysis. Working fluids are squirt as liquid droplets into a vacuum inside a shroud that is cooled by liquid nitrogen under 79 K. The radiation heat from a liquid droplet stream is measured by using a radiation sensor (Captec RF-100) pasted on inside wall of the shroud. The shroud is 700 mm high and 100 mm in diameter. Silicon oil (Shin-Etsu Chemical Co., Ltd. KF-96 10 cSt) is used as the working fluid. The experimental value are between 0.617 and 0.739 W/m∧2 when the center-to-center distance and diameter of liquid droplets are changed. The more the center-to-center distance and diameter is decreased, the more experimental results are increase. A trend of the results of numerical analysis fitted in the trend of experimental values. A biggest difference is less than 7 between experimental values and the results of numerical analysis when the radiation factor is 0.70 in the numerical analysis. It can be said that the radiation heat from a liquid droplet stream is measured correctly. Additionally the radiation factor of a liquid droplet can be estimated by using a method of this research.
  • 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年 [査読無し][通常論文]
  • Ryuichiro Kanai, Tatsuya Ishiyama, Masahiro Nohara, Hirokazu Izumo, Masashi Wakita, Tsuyoshi Totani, Harunori Nagata Advances in the Astronautical Sciences 146 79 -84 2013年04月24日 [査読無し][通常論文]
     
    The authors have been developing fuel regression formulas for CAMUI type hybrid rocket motors. A fuel block in a CAMUI-type fuel grain is a short-axis cylinder having two axial ports. Previous experiments showed that an experimental constant in the regression formula for forward-end faces depends on port length L, mean port diameter D, and the Reynolds number of the flow. In this paper, the authors examined these effects more closely to clarify the basic mechanism of these dependencies.
  • 戸谷 剛 日本機械学會誌 115 (1123) 2012年06月05日 [査読無し][通常論文]
  • 石川直幸, 戸谷剛, 脇田督司, 永田晴紀 Thermophys Prop 32nd 307-309 2011年11月21日 [査読無し][通常論文]
  • 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 2011年11月20日 [査読無し][通常論文]
  • 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 2011年11月20日 [査読無し][通常論文]
  • 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 2011年09月10日 [査読無し][通常論文]
  • 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 2011年09月10日 [査読無し][通常論文]
  • 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 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" 2011年01月27日 [査読無し][通常論文]
     
    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...
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • H. Nagata, M. Wakita, T. Totani, T. Uematsu, K. Yonemoto 61st International Astronautical Congress 2010, IAC 2010 3 2144 -2148 2010年12月01日 [査読無し][通常論文]
     
    The authors have developed CAMUI type hybrid rockets as a non-toxic propellant sounding rocket system. A main purpose is to drastically downsize the cost and scale of rocket experiments and attract potential users in various research fields. A key idea is a distinctive fuel grain design to accelerate gasification rates of solid fuels. The grain design, designated as CAMUI as an abbreviation of "cascaded multi-stage impinging-jet", makes the combustion gas collide repeatedly with fuel surfaces, resulting in intense heat transfer to the fuel. A 2500 N thrust class CAMUI motor was developed for a small scale winged flight test bed. Static firing tests provided successful thrust performance of the motor. Dividing the total impulse by the total propellant consumption gave mean specific impulse to be 254 sec, achieving the target value of 250 sec. This motor is able to launch a winged vehicle of 50 kg to about 1.7 km apogee altitude. The launch experiment is slated in the next fiscal year. Copyright ©2010 by the International Astronautical Federation. All rights reserved.
  • 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 2010年11月20日 [査読無し][通常論文]
  • 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 2010年11月20日 [査読無し][通常論文]
  • 石川直幸, 戸谷剛, 脇田督司, 永田晴紀 Thermophys Prop 31st 118-120 2010年11月17日 [査読無し][通常論文]
  • 石川 直幸, 戸谷 剛, 脇田 督司, 永田 晴紀 Thermophysical properties 31 (0) 118 -120 2010年11月17日 [査読無し][通常論文]
  • 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 2010年11月07日 [査読無し][通常論文]
  • 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 2010年11月07日 [査読無し][通常論文]
  • 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 2010年11月07日 [査読無し][通常論文]
  • 石川 直幸, 戸谷 剛, 永田 晴紀, 脇田 督司 北海道支部講演会講演概要集 2010 (49) 133 -134 2010年11月07日 [査読無し][通常論文]
  • 野原 正寛, 金子 雄大, 萩原 俊輔, 脇田 督司, 戸谷 剛, 永田 晴紀 北海道支部講演会講演概要集 2010 (49) 161 -162 2010年11月07日 [査読無し][通常論文]
  • 寺坂 昭宏, 田村 正佳, 脇田 督司, 戸谷 剛, 永田 晴紀 北海道支部講演会講演概要集 2010 (49) 163 -164 2010年11月07日 [査読無し][通常論文]
  • 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 2010年09月04日 [査読無し][通常論文]
  • 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 2010年09月04日 [査読無し][通常論文]
  • 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 2010年09月04日 [査読無し][通常論文]
  • 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 2010年09月04日 [査読無し][通常論文]
  • 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 伝熱 : journal of the Heat Transfer Society of Japan 49 (208) 19 -28 2010年07月01日 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 戸谷 剛, 脇田 督司, 永田 晴紀, UNITEC-1開発チーム 年次大会講演論文集 2010 (0) 359 -360 2010年 [査読無し][通常論文]
     
    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.
  • 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 年次大会講演論文集 2010 (0) 361 -362 2010年 [査読無し][通常論文]
     
    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.
  • 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 年次大会講演論文集 2010 (0) 367 -368 2010年 [査読無し][通常論文]
     
    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.
  • 岩城 裕樹, 戸谷 剛, 脇田 督司, 永田 晴紀 年次大会講演論文集 2010 (0) 407 -408 2010年 [査読無し][通常論文]
     
    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.
  • 長沼 哲史, 岩城 裕樹, 佐藤 峻哉, 戸谷 剛, 脇田 督司, 永田 晴紀 日本航空宇宙学会論文集 58 (677) 171 -177 2010年 [査読無し][通常論文]
     
    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.
  • 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 2009年11月28日 [査読無し][通常論文]
  • 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 2009年11月28日 [査読無し][通常論文]
  • 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 北海道支部講演会講演概要集 2009 (48) 211 -212 2009年11月28日 [査読無し][通常論文]
  • 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 北海道支部講演会講演概要集 2009 (48) 213 -214 2009年11月28日 [査読無し][通常論文]
  • 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 2009年11月18日 [査読無し][通常論文]
  • 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 2009年11月18日 [査読無し][通常論文]
  • 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 2009年11月18日 [査読無し][通常論文]
  • 岩城裕樹, 長沼哲史, 佐藤峻哉, 戸谷剛, 脇田督司, 永田晴紀 日本機械学会年次大会講演論文集 2009 (Vol.5) 297-298 2009年09月12日 [査読無し][通常論文]
  • 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 2009年03月17日 [査読無し][通常論文]
  • 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 2009年03月17日 [査読無し][通常論文]
  • 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 2009年03月04日 [査読無し][通常論文]
  • 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 電子情報通信学会総合大会講演論文集 2009 (1) 317 -317 2009年03月04日 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 岩城 裕樹, 長沼 哲史, 佐藤 峻哉, 戸谷 剛, 脇田 督司, 永田 晴紀 年次大会講演論文集 2009 (0) 297 -298 2009年 [査読無し][通常論文]
     
    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.
  • Yuuki Iwaki, Tsuyoshi Totani, Tetsushi Naganuma, Harunori Nagata International Astronautical Federation - 59th International Astronautical Congress 2008, IAC 2008 10 6403 -6410 2008年12月01日 [査読無し][通常論文]
     
    The numerical analysis program for the flow in the Laval nozzle was constructed to research the effect of the heat transfer in the nozzle. The nitrogen is assumed as the propellant and the aluminum alloy is adopted as the material of the nozzle. Supplied heat to the propellant in the nozzle increases with elongating the length of the divergent nozzle. The heat can contribute to the improvement of the specific impulse and the thrust. The effect of the heat supplied in the nozzle appears significantly under the condition of the low enthalpy of the propellant. The elongation of the length of the divergent nozzle from 10 mm to 100 mm changes the thrust from 14.41 mN to 17.02 mN and changes the specific impulse from 84.43 s to 99.69 s in the condition that the diameter of the nozzle throat is 0.1 mm, the inlet pressure is 1 MPa, the inlet temperature of the propellant is 300 K, and the inlet temperature of the nozzle wall is 600 K.
  • 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 2008年11月20日 [査読無し][通常論文]
  • 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 2008年11月20日 [査読無し][通常論文]
  • 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 2008年11月20日 [査読無し][通常論文]
  • 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 2008年10月25日 [査読無し][通常論文]
  • 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 2008年09月27日 [査読無し][通常論文]
  • 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 2008年09月27日 [査読無し][通常論文]
  • 羽柴 健太, 堺 裕哉, 戸谷 剛, 永田 晴紀 北海道支部講演会講演概要集 2008 (47) 149 -150 2008年09月27日 [査読無し][通常論文]
  • 浅田 隆利, 脇田 督司, 戸谷 剛, 永田 晴紀 北海道支部講演会講演概要集 2008 (47) 151 -152 2008年09月27日 [査読無し][通常論文]
  • 岩城裕樹, 長沼哲史, 戸谷剛, 永田晴紀 日本機械学会年次大会講演論文集 2008 (Vol.5) 395-396 2008年08月02日 [査読無し][通常論文]
  • 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 2008年03月17日 [査読無し][通常論文]
  • 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 2008年03月05日 [査読無し][通常論文]
  • 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 電子情報通信学会総合大会講演論文集 2008 (1) 266 -266 2008年03月05日 [査読無し][通常論文]
  • 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 2008年03月 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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 宇宙科学技術連合講演会講演集(CD−ROM) 52nd ROMBUNNO.1H18 2008年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
  • 植嶋 健太, 永田 晴紀, 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 年次大会講演論文集 2008 (0) 401 -402 2008年 [査読無し][通常論文]
     
    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.
  • 金子 雄大, 伊藤 光紀, 植嶋 健太, 戸谷 剛, 永田 晴紀 年次大会講演論文集 2008 (0) 403 -404 2008年 [査読無し][通常論文]
     
    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.
  • 岩城 裕樹, 長沼 哲史, 戸谷 剛, 永田 晴紀 年次大会講演論文集 2008 (0) 395 -396 2008年 [査読無し][通常論文]
     
    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.
  • 植嶋 健太, 永田 晴紀, 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 年次大会講演論文集 2008 (0) 401 -402 2008年 [査読無し][通常論文]
     
    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.
  • 金子 雄大, 伊藤 光紀, 植嶋 健太, 戸谷 剛, 永田 晴紀 年次大会講演論文集 2008 (0) 403 -404 2008年 [査読無し][通常論文]
     
    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.
  • 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 2007年11月20日 [査読無し][通常論文]
  • 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 2007年11月20日 [査読無し][通常論文]
  • 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 2007年10月27日 [査読無し][通常論文]
  • 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 2007年09月29日 [査読無し][通常論文]
  • 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 2007年09月29日 [査読無し][通常論文]
  • 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 2007年09月29日 [査読無し][通常論文]
  • 片野 光, 羽柴 健太, 戸谷 剛, 永田 晴紀 北海道支部講演会講演概要集 2007 (46) 135 -136 2007年09月29日 [査読無し][通常論文]
  • 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 北海道支部講演会講演概要集 2007 (46) 137 -138 2007年09月29日 [査読無し][通常論文]
  • 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 北海道支部講演会講演概要集 2007 (46) 127 -128 2007年09月29日 [査読無し][通常論文]
  • 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 2007年09月25日 [査読無し][通常論文]
  • 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 2007年09月25日 [査読無し][通常論文]
  • 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 2007年09月25日 [査読無し][通常論文]
  • 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 2007年09月25日 [査読無し][通常論文]
  • 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 2007年09月25日 [査読無し][通常論文]
  • 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 2007年09月25日 [査読無し][通常論文]
  • 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 日本機械学会年次大会講演論文集 2007 (Vol.5) 391-392 2007年09月07日 [査読無し][通常論文]
  • 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 日本機械学会年次大会講演論文集 2007 (Vol.5) 347-348 2007年09月07日 [査読無し][通常論文]
  • 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 日本機械学会年次大会講演論文集 2007 (Vol.5) 389-390 2007年09月07日 [査読無し][通常論文]
  • 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 年次大会講演論文集 : JSME annual meeting 2007 (5) 391 -392 2007年09月07日 [査読無し][通常論文]
     
    "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.
  • 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 年次大会講演論文集 : JSME annual meeting 2007 (5) 389 -390 2007年09月07日 [査読無し][通常論文]
     
    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...
  • 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 年次大会講演論文集 : JSME annual meeting 2007 (5) 347 -348 2007年09月07日 [査読無し][通常論文]
     
    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...
  • 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 電子情報通信学会総合大会講演論文集 2007 (1) 299 -299 2007年03月07日 [査読無し][通常論文]
  • 石村康生, 羽柴健太, 加藤隆造, 戸谷剛, 樋口健 構造強度に関する講演会講演集 49th 187 -189 2007年 [査読無し][通常論文]
  • 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 年次大会講演論文集 2007 (0) 407 -408 2007年 [査読無し][通常論文]
     
    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.
  • 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 年次大会講演論文集 2007 (0) 405 -406 2007年 [査読無し][通常論文]
     
    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).
  • Thermal and Structural Design of Subminiature Satellite "HIT-SAT"
    Memoirs of the Hokkaido Institute of Technology (35) 105 -111 2007年 [査読無し][通常論文]
  • 加藤 隆造, 戸谷 剛, 石村 康生, 永田 晴紀 北海道支部講演会講演概要集 2006 (45) 37 -38 2006年09月25日 [査読無し][通常論文]
  • 南部 航太, 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 2006 (45) 31 -32 2006年09月25日 [査読無し][通常論文]
  • 榊原 隆浩, 戸谷 剛, 安中 俊彦, 佐鳥 新, 永田 晴紀 北海道支部講演会講演概要集 2006 (45) 33 -34 2006年09月25日 [査読無し][通常論文]
  • 坂本 将司, 片野 光, 戸谷 剛, 永田 晴紀 北海道支部講演会講演概要集 2006 (45) 35 -36 2006年09月25日 [査読無し][通常論文]
  • 菅田 成俊, 脇田 督司, 沼倉 龍介, 永田 晴紀, 戸谷 剛 北海道支部講演会講演概要集 2006 (45) 39 -40 2006年09月25日 [査読無し][通常論文]
  • 石村康生, 樋口健, 戸谷剛, 加藤隆造 宇宙科学技術連合講演会講演集(CD-ROM) 50th 3E11 2006年 [査読無し][通常論文]
  • 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 年次大会講演論文集 2006 (0) 341 -342 2006年 [査読無し][通常論文]
     
    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.
  • 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 2005年12月01日 [査読無し][通常論文]
     
    By introducing various innovative ideas, the difficult-to-develop small hybrid-type rocket is successfully developed. The main purpose is to drastically reduce the cost of rocket experiments and thus attract potential users such as metrological and microgravity researchers. A key idea is a new fuel grain design to accelerate the gasification rate of solid fuel. The new fuel grain design, designated as CAMUI as an abbreviation of "Cascaded Multistage Impinging-jet", is that the gas flow repeatedly collides with the solid fuel surface to accelerate the heat transfer to the fuel. To install a regenerative cooling system using cryogenic liquid oxygen as coolant in a small launcher, the authors devised a valveless supply system (with no valves in the liquid oxygen flow line). Four serial successful launch verification tests by 10 kg vehicle equipped with a 50 kgf thrust CAMUI motor have shown the feasibility of the motor system. The meteorological observation model of 400 kgf class motor is under development and the development of microgravity experiment class of 1.5 to 2 tonf motor will follow subsequently. The authors plan to complete the development of the 400 kgf class motor for meteorological observation model by the end of FY2005.
  • Tsuyoshi Totani, Takuya Kodama, Kensuke Watanabe, Kota Nanbu, Harunori Nagata, Isao Kudo International Astronautical Federation - 56th International Astronautical Congress 2005 6 3842 -3852 2005年12月01日 [査読無し][通常論文]
     
    A model of the circulation of the working fluid in a liquid droplet radiator has been developed. The model is based on Bernoulli's law and the loss of the hydraulic head. The behavior of the circulation of the working fluid calculated from the model is compared with that obtained from experiments in the case that the flow rate of the circulating working fluid is changed. In radiators, the flow rate of the circulating working fluid is changed in order to match the change of the waste heat generated in large-space structures. The flow rates of the circulating working fluid calculated from the model correspond to those obtained from the experiments well. The circulation mechanism of the working fluid in the liquid droplet radiator has been clarified. The model developed in the present work will allow us to control the flow rate of the working fluid in the liquid droplet radiator automatically.
  • 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 北海道支部講演会講演概要集 2005 (44) 70 -71 2005年10月08日 [査読無し][通常論文]
  • 譜久山 尚, 坂本 将司, 永田 晴紀, 戸谷 剛, 工藤 勲 北海道支部講演会講演概要集 2005 (44) 72 -73 2005年10月08日 [査読無し][通常論文]
  • 渡辺 健介, 南部 航太, 戸谷 剛, 永田 晴紀, 工藤 勲 北海道支部講演会講演概要集 2005 (44) 74 -75 2005年10月08日 [査読無し][通常論文]
  • 飯田 恭平, 戸谷 剛, 永田 晴紀, 工藤 勲, 矢野 昭起 北海道支部講演会講演概要集 2005 (44) 76 -77 2005年10月08日 [査読無し][通常論文]
  • 永田 晴紀, 渡辺 三樹生, 伊藤 光範, 前田 剛典, 戸谷 剛, 工藤 勲 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 2005年01月20日 [査読無し][通常論文]
     
    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...
  • 高野 千尋, 村木 祐介, 戸谷 剛, 永田 晴紀, 工藤 勲 年次大会講演論文集 2005 (0) 385 -386 2005年 [査読無し][通常論文]
     
    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.
  • 伊藤 光紀, 前田 剛典, 永田 晴紀, 戸谷 剛, 工藤 勲, 植松 務 年次大会講演論文集 2005 (0) 391 -392 2005年 [査読無し][通常論文]
     
    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.
  • 戸谷 剛, 児玉 拓也, 渡辺 健介, 南部 航太, 永田 晴紀, 工藤 勲 年次大会講演論文集 2005 (0) 445 -446 2005年 [査読無し][通常論文]
     
    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.
  • 戸谷 剛, 児玉 拓也, 渡辺 健介, 永田 晴紀, 工藤 勲 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 2004年11月04日 [査読無し][通常論文]
  • 三浦 崇志, 渡辺 三樹生, 永田 晴紀, 戸谷 剛, 工藤 勲 北海道支部講演会講演概要集 2003 (43) 154 -155 2003年09月28日 [査読無し][通常論文]
  • 増田 紀昭, 戸谷 剛, 永田 晴紀, 工藤 勲 北海道支部講演会講演概要集 2003 (43) 156 -157 2003年09月28日 [査読無し][通常論文]
  • 沼倉 龍介, 脇田 督司, 永田 晴紀, 戸谷 剛, 工藤 勲 北海道支部講演会講演概要集 2003 (43) 162 -163 2003年09月28日 [査読無し][通常論文]
  • 戸谷 剛, 永田 晴紀, 工藤 勲 JASMA : Journal of the Japan Society of Microgravity Application 20 (1) 22 -29 2003年01月31日 [査読無し][通常論文]
  • KURODA Akiyoshi, TOTANI Tsuyoshi, KUDO Kazuhiko Proceedings of the ... ASME/JSME Thermal Engineering Joint Conference 2003 (6) 376 -376 2003年 
    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]
  • 渡辺 三樹生, 久保田 勲, 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 年次大会講演論文集 2003 (0) 363 -364 2003年 [査読無し][通常論文]
     
    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.
  • 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 2002年11月01日 [査読無し][通常論文]
  • 脇田 督司, 沼倉 龍介, 永田 晴紀, 戸谷 剛, 工藤 勲 北海道支部講演会講演概要集 2002 (42) 82 -83 2002年10月05日 [査読無し][通常論文]
     
    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...
  • 藤井 篤之, 栗田 慎一郎, 永田 晴紀, 戸谷 剛, 工藤 勲 北海道支部講演会講演概要集 2002 (42) 86 -87 2002年10月05日 [査読無し][通常論文]
     
    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...
  • 加藤 健太郎, 永田 晴紀, 戸谷 剛, 工藤 勲 北海道支部講演会講演概要集 2002 (42) 104 -105 2002年10月05日 [査読無し][通常論文]
     
    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.
  • Nozomu Hashimoto, Satoshi Watanabe, Harunori Nagata, Tsuyoshi Totani, Isao Kudo Proceedings of the Combustion Institute 29 (1) 245 -250 2002年 [査読無し][通常論文]
     
    The influence of channel height on flame spread in a circular duct of the solid fuel in an opposed-flow configuration was examined. Polymethylmethacrylate cylinders with a circular duct (diameter of 1, 2, or 3 mm) were used as fuel specimens, and both flame-spreading and stabilized combustion were observed. In the case of stabilized combustion, the flame cannot spread into the duct because of the high oxygen velocity. The flame-traveling velocity is the velocity at which the flame widens the ductby fuel consumption. Therefore, the flame-traveling velocity in stabilized combustion is significantly low compared with flame-spreading combustion. In the case of flame-spreading combustion, the equivalence velocity, which contains channel height information, defines whether the regime is the thermal or the chemical regime. When the equivalent velocity is higher than a certain value, the flame-spread rate is controlled by chemical effects. On the whole, the flame-spread rate decreases with the decrease of channel height in the case of flame-spreading combustion because of the curvature effect. Owing to the curvature effect, the area ratio of the flame to that of the solid surface decreases with decreasing channel height, and this is conspicuous when the channel height is low. The curvature effect is negligible when the channel height is sufficiently large compared with the flame stand-off distance.
  • 永田 晴紀, 戸谷 剛, 工藤 勲, 伊藤 献一, 大和田 陽一, 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 年次大会講演論文集 2002 (0) 345 -346 2002年 [査読無し][通常論文]
     
    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.
  • 永田 晴紀, 藤井 篤之, 伊藤 献一, 戸谷 剛, 工藤 勲 年次大会講演論文集 2002 (0) 3 -4 2002年 [査読無し][通常論文]
     
    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.
  • 渡辺 賢, 橋本 望, 永田 晴紀, 戸谷 剛, 工藤 勲 北海道支部講演会講演概要集 2002 (0) 84 -85 2002年 [査読無し][通常論文]
     
    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.
  • 戸谷 剛, 薮田 茂, 宮本 拓哉, 永田 晴紀, 工藤 勲 JASMA : Journal of the Japan Society of Microgravity Application 18 (0) 87 -87 2001年10月01日 [査読無し][通常論文]
  • 薮田 茂, 宮本 拓哉, 戸谷 剛, 永田 晴紀, 工藤 勲, 岩崎 晃, 細川 俊介 北海道支部講演会講演概要集 2001 (41) 238 -239 2001年09月25日 [査読無し][通常論文]
     
    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...
  • 中村 大輔, 永田 晴紀, 戸谷 剛, 工藤 勲 北海道支部講演会講演概要集 2001 (41) 242 -243 2001年09月25日 [査読無し][通常論文]
     
    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...
  • 中山 久広, 渡辺 三樹生, 永田 晴紀, 工藤 勲, 戸谷 剛 北海道支部講演会講演概要集 2001 (41) 268 -269 2001年09月25日 [査読無し][通常論文]
     
    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...
  • 戸谷 剛, 藪田 茂, 永田 晴紀, 工藤 勲, 岩崎 晃, 細川 俊介 JASMA : Journal of the Japan Society of Microgravity Application 17 (0) 18 -19 2000年10月01日 [査読無し][通常論文]
  • 吉川 茂雄, 戸谷 剛, 永田 晴紀, 工藤 勲 北海道支部講演会講演概要集 2000 (40) 192 -193 2000年09月25日 [査読無し][通常論文]
     
    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.
  • 渡辺 三樹生, 中山 久広, 永田 晴紀, 戸谷 剛, 工藤 勲, 大和田 陽一 北海道支部講演会講演概要集 2000 (40) 200 -201 2000年09月25日 [査読無し][通常論文]
     
    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 ...
  • 笹木 正裕, 中村 大輔, 永田 晴紀, 戸谷 剛, 工藤 勲 北海道支部講演会講演概要集 2000 (40) 208 -209 2000年09月25日 [査読無し][通常論文]
     
    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.
  • 薮田 茂, 戸谷 剛, 永田 晴紀, 工藤 勲, 伊丹 雅洋, 岩崎 晃, 細川 俊介 北海道支部講演会講演概要集 2000 (40) 212 -213 2000年09月25日 [査読無し][通常論文]
     
    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...
  • 丹羽 由樹子, 永田 晴紀, 戸谷 剛, 工藤 勲 北海道支部講演会講演概要集 2000 (40) 214 -215 2000年09月25日 [査読無し][通常論文]
     
    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 ...
  • 橋本 望, 永田 晴紀, 戸谷 剛, 工藤 勲 北海道支部講演会講演概要集 2000 (0) 202 -203 2000年 [査読無し][通常論文]
     
    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.
  • 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年 [査読無し][通常論文]
  • 伊丹 雅洋, 戸谷 剛, 永田 晴紀, 工藤 勲, 岩崎 晃, 細川 俊介 JASMA : Journal of the Japan Society of Microgravity Application 16 (0) 114 -115 1999年10月01日 [査読無し][通常論文]
  • 「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年 [査読無し][通常論文]
  • 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年 [査読無し][通常論文]
     
    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)
  • 伊丹 雅洋, 戸谷 剛, 永田 晴紀, 工藤 勲, 岩崎 晃, 細川 俊介 JASMA : Journal of the Japan Society of Microgravity Application 15 (0) 38 -39 1998年10月01日 [査読無し][通常論文]

特許

  • 特許6692046:赤外線ヒーター    2020年05月13日
    戸谷 剛, 櫻井 篤, 近藤 良夫  国立大学法人北海道大学, 国立大学法人新潟大学, 日本碍子株式会社

共同研究・競争的資金等の研究課題

  • 文部科学省:科学研究費補助金(基盤研究(B))
    研究期間 : 2012年 -2012年 
    代表者 : 戸谷 剛
  • 文部科学省:科学研究費補助金(挑戦的萌芽研究)
    研究期間 : 2009年 -2011年 
    代表者 : 戸谷 剛
     
    本研究は、温室効果ガスの排出量を削減する効果とともに、地表から宇宙へ直接放熱する量を増やす効果で地球温暖化を防止することを目指している。具体的には、高温時には太陽光の当たらない北向きの表面微細周期構造を用いて冷却し、低温時には太陽光の当たる南向きの表面微細周期構造を用いて加熱し、電力使用量を少ない冷暖房機器の開発を目指している。本年度は、UVナノインプリント法で紫外線硬化樹脂上に作成した表面微細周期構造の表面に、ヘリコンスパッタ法で金をスパッタした試料を作成した。作成した表面微細周期構造は、直径10μm、深さ2.5μmの円孔が、ピッチ11μmで周期的に並んでいる。スパッタした金の厚みは、100nmである。この試料の赤外線放射率を半球透過率と半球反射率を測定することで取得した。半球透過率と半球反射率の測定は、九州工業大学の岩田稔助教の協力のもと、積分球を持つFT-IR分光計で行った。その結果、11μm付近で、表面微細周期構造を持たない試料よりも10%赤外線放射率が増加することが分かった。この結果は、金をスパッタした表面微細周期構造は、大気の窓(8~12μm)を利用して、温室効果ガスに吸収されずに、地表から宇宙へ直接、放熱する量を10%増加できることを示している。つまり、電力を用いず、地表から宇宙へ直接、放熱する量を10%増加できるため、地球温暖化を防止する観点から非常に重要な結...
  • 文部科学省:科学研究費補助金(基盤研究(B))
    研究期間 : 2009年 -2011年 
    代表者 : 永田 晴紀, 戸谷 剛, 脇田 督司
     
    (1)燃料後退速度式中の係数αの取得各燃焼面の燃料後退速度式における係数αの値(局所O/Fの関数になる)にスケール効果モデルを組み合わせて、大型モータ用グレイン形状の最適化設計を行うための基礎式を構築した。(2)酸化剤噴流が衝突する燃焼流れ場の解明酸化剤噴流が衝突する燃焼流れ場を異なるスケールで構築し、燃焼場のスケールと燃料後退特性との関係を調べた。レイノルズ数および噴流の速度をスケール間で一致させることにより燃料後退速度がスケール比で相似関係になることが、本実験系においても確認された。また、レイノルズ数を一定のまま圧力を下げ、流量を増加させると、燃料後退速度が増大することが確認された。本結果は実モータにおいても観察されているものである。(3)最適グレイン形状を探索するアルゴリズムの開発CAMUIロケットの燃料グレインにおいては、縦に並べられた6~10個の燃料ブロックが同時に燃え進む。燃料グレインの燃え残りをより少なく、O/Fシフトによる比推力損失をより小さくするような、最適グレイン形状を探索するアルゴリズムを開発する。昨年度は、最適グレイン形状を得るための探索アルゴリズムとして遺伝的アルゴリズムを適用し、良好な探索速度を得た。本年度は、最適解近傍までは遺伝的アルゴリズムを適用し、ある程度良好な解が得られた後は燃え残り燃料を他のブロックに再配分する手法により最適解に至る手法を...
  • 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
    研究期間 : 2009年
  • Wavelength-selective radiator with periodic microstructure
    Grant-in-Aid for Scientific Research
    研究期間 : 2009年
  • 文部科学省:科学研究費補助金(基盤研究(B))
    研究期間 : 2006年 -2008年 
    代表者 : 永田 晴紀, 戸谷 剛, 大島 伸行
     
    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.
  • 文部科学省:科学研究費補助金(若手研究(A))
    研究期間 : 2006年 -2007年 
    代表者 : 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:科学研究費補助金(若手研究(A))
    研究期間 : 2004年 -2005年 
    代表者 : 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...
  • 超小型衛星の熱設計
    研究期間 : 2005年
  • Thermal Design of Micro Satellite
    研究期間 : 2005年
  • 文部科学省:科学研究費補助金(基盤研究(B))
    研究期間 : 2000年 -2002年 
    代表者 : 永田 晴紀, 新井 隆景, 戸谷 剛, 工藤 勲
     
    次世代の極超音速機用エンジンとして注目されているスクラムジェットエンジンの技術的な課題として,極超音速流中でいかに速やかに空気と燃料の混合を行うかということが挙げられる.この課題を解決するためには,超音速混合場の定量的な評価が必要である.研究者らはこれまで,安価かつ簡便な水素濃度評価方法として,触媒反応を利用した水素濃度プローブを提案してきた.これまでの研究では,触媒反応発熱量から定常状態を仮定して水素濃度の推算を行ってきたが,このプローブを乱流混合場に適用し,乱流構造に起因する高速な濃度変動履歴を計測するためには,触媒反応発熱量の非定常な変化量から水素濃度変化量を計測する手法が必要となる.そこで,水素濃度変化量が触媒反応発熱量の変化量(dQ/dt)に与える影響を明らかにすることを目的として,白金線とニッケル線(共に,直径25μm,長さ2mm)をX字型に張ったダブルプローブを用い,触媒反応が起こる条件と起こらない条件の同時測定を行い,触媒反応の応答速度を測定した.衝撃波管により水素濃度が不連続に変化する波面を発生させ,この波面に対するダブルプローブの応答を測定する.実験の結果,プローブの設定温度を概ね680K程度にすれば,発熱量の立ち上がりの勾配(dQ/dt)が設定温度に依存しなくなることが明らかとなった.このとき,(dQ/dt)は主流から白金線表面への化学種の輸送速度が決め...
  • 文部科学省:科学研究費補助金(奨励研究(A))
    研究期間 : 2000年 -2001年 
    代表者 : 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:科学研究費補助金(基盤研究(B))
    研究期間 : 1998年 -2000年 
    代表者 : 工藤 勲, 戸谷 剛, 永田 晴紀
     
    平成10年度から平成12年度にかけて微小重力環境下で液滴の放出と捕集に関する実験を行った。平成10年度は,液滴生成器を作成し,微小重力下で液滴生成器の性能試験を行った。その結果,1.微小重力環境では表面張力が顕在化するため,ノズル出口を塞ぎ,液滴生成ができないことが懸念されていたが,微小重力下でも通常重力下と同様,液滴直径および液滴間隔が均一である均一液滴流が生成されることが確認された。平成11年度は,回収器自体を回転させて遠心流を発生させ,遠心流に直角に当たるように入口を配置した回収管から作動流体を回収する回収器を製作し,微小重力での性能試験を行った。その結果,2.作動流体循環で回収器の下流にあるギアポンプへ作動流体を送り込む能力があることがわかった。また,液滴の捕集については,液滴をアルミ平板に衝突させ,飛散の有無を確認した。その結果,3.液滴直径200μm程度の均一液滴流では飛散発生せず,不均一液滴流の場合,飛散が発生することがわかった。これは,不均一液滴流内に直径の大きい液滴が含まれているためであると推測された。平成12年度は,平成11年度の不均一液滴流内に液滴直径が大きい液滴が含まれていたため飛散したのではないかという推測を裏付けるため,ノズル直径を大きくするとともに,平成11年度の液滴回収装置を改修し,回収面角度を変更できるようにするとともに回収面上に液膜を生成で...
  • 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
    研究期間 : 1998年
  • Liquid Droplet Radiator for Large Space Structure
    研究期間 : 1998年

教育活動情報

主要な担当授業

  • 人工衛星設計特論
    開講年度 : 2021年
    課程区分 : 修士課程
    開講学部 : 工学院
    キーワード : Spacecraft Design, System Engineering, Sub-systems, Orbital Mechanics
  • 人工衛星設計特論
    開講年度 : 2021年
    課程区分 : 博士後期課程
    開講学部 : 工学院
    キーワード : Spacecraft Design, System Engineering, Sub-systems, Orbital Mechanics
  • コンピュータ演習
    開講年度 : 2021年
    課程区分 : 学士課程
    開講学部 : 工学部
    キーワード : コンピュータ、プログラム、数値計算
  • 環境エネルギー工学
    開講年度 : 2021年
    課程区分 : 学士課程
    開講学部 : 工学部
    キーワード : 環境、エネルギー、地球温暖化、原子力発電、燃料電池、高効率発電、風力、エンジン、燃焼、エネルギーキャリア
  • 熱力学Ⅰ
    開講年度 : 2021年
    課程区分 : 学士課程
    開講学部 : 工学部
    キーワード : 内部エネルギー、エンタルピー、エントロピー、エクセルギー、ギブス自由エネルギー、ヘルムホルツ自由エネルギー、エネルギー変換、理想気体、熱力学第一法則、熱力学第二法則,熱力学の一般関係式
  • 英語演習
    開講年度 : 2021年
    課程区分 : 学士課程
    開講学部 : 全学教育
    キーワード : Early History of Rocket Engines, Unmanned Space Flight, Manned Space Flight, Anatomy of a Space Vehicle,Space Flight(Astronautics)
  • 熱流体力学演習Ⅰ
    開講年度 : 2021年
    課程区分 : 学士課程
    開講学部 : 工学部
    キーワード : 各種保存則,有効エネルギー,理想気体,検査体積,運動量理論,ベルヌーイの定理,ポテンシャル流れ
  • 航空宇宙工学
    開講年度 : 2021年
    課程区分 : 学士課程
    開講学部 : 工学部
    キーワード : 航空機原動機、機体、翼、宇宙輸送、宇宙環境利用、人工衛星

大学運営

委員歴

  • 2015年05月 - 現在   日本航空宇宙学会   会誌編集委員会 委員
  • 2015年03月 - 現在   衛星設計コンテスト   実行委員
  • 2015年03月 - 現在   日本航空宇宙学会 宇宙利用部門   部門長
  • 2014年04月 - 現在   第30回宇宙技術および科学の国際シンポジウム組織委員会   プログラム小委員会委員
  • 2014年04月 - 現在   一般社団法人 日本機械学会   熱工学部門 運営委員会 委員
  • 2014年04月 - 現在   一般社団法人 日本機械学会   2015年度年次大会 実行委員会 委員
  • 2012年04月 - 現在   基準認証イノベーション技術研究組合   超小型衛星プロジェクト委員会 委員
  • 2007年03月 - 現在   日本航空宇宙学会 北部支部   幹事   日本航空宇宙学会 北部支部
  • 2014年11月 - 2015年03月   北海道大学 アドミッションセンター   部員
  • 2014年03月 - 2015年02月   日本航空宇宙学会 宇宙利用部門   委員
  • 2010年03月 - 2014年02月   日本航空宇宙学会   宇宙航行部門委員会 委員   日本航空宇宙学会
  • 2013年08月 - 2013年09月   公益社団法人 日本伝熱学会   キッズエネルギーシンポジウム2013 指導員
  • 2012年05月 - 2013年03月   北海道大学 アドミッションセンター   部員
  • 2010年 - 2011年   日本機械学会   北海道支部 学生会担当幹事   日本機械学会
  • 2010年 - 2011年   日本伝熱学会   評議員   日本伝熱学会
  • 2009年 - 2011年   日本熱物性学会   役員(評議員)   日本熱物性学会
  • 2009年 - 2010年   日本機械学会   北海道支部 会計幹事   日本機械学会
  • 2008年 - 2009年   日本機械学会   宇宙工学部門 運営委員   日本機械学会
  • 2007年 - 2008年   日本航空宇宙学会   宇宙利用部門委員会 幹事   日本航空宇宙学会
  • 2002年 - 2006年   日本航空宇宙学会 北部支部   幹事   日本航空宇宙学会 北部支部
  • 日本機械学会   コレスポンデント委員(2000.4-2001.3)   日本機械学会


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