研究者業績

羽生 宏人

ハブ ヒロト  (Hiroto HABU)

基本情報

所属
国立研究開発法人宇宙航空研究開発機構 宇宙科学研究所 学際科学研究系 教授
東京大学 大学院工学系研究科 化学システム工学専攻 教授
横浜国立大学 総合学術高等研究院 リスク共生社会創造センター 客員教授
相模女子大学 客員教授
学位
博士(工学)(東京大学)

J-GLOBAL ID
200901019157833600
researchmap会員ID
5000019460

外部リンク

論文

 68
  • Hiroki Matsunaga, Hiroto Habu, Atsumi Miyake
    JOURNAL OF THERMAL ANALYSIS AND CALORIMETRY 113(3) 1387-1394 2013年9月  査読有り
    Ammonium dinitramide (ADN) is one of the several promising new solid propellant oxidizers. ADN is of interest because its oxygen balance and energy content are high, and it also halogen-free. One of the most important characteristics of a propellant oxidizer, however, is stability and ADN is known to degrade to ammonium nitrate (AN) during storage, which will affect its performance. This study focused on the effects of aging on the thermal decomposition mechanism of ADN. The thermal behaviors of ADN and ADN/AN mixtures were studied, as were the gases evolved during their decomposition, using differential scanning calorimetry (DSC), thermogravimetry-differential thermal analysis-infrared spectrometry (TG-DTA-IR), and thermogravimetry-differential thermal analysis-mass spectrometry (TG-DTA-MS). The results of these analyses demonstrated that the decomposition of ADN occurs via a series of distinct stages in the condensed phase. The gases evolved from ADN decomposition were N2O, NO2, N-2, and H2O. In contrast, ADN mixed with AN (to simulate aging) did not exhibit the same initial reaction. We conclude that aging inhibits early stage, low temperature decomposition reactions of ADN. Two possible reasons were proposed, these being either a decrease in the acidity of the material due to the presence of AN, or inhibition of the acidic dissociation of dinitramic acid by NO (3) (-) .
  • Yoshihiro Kakinami, Masayuki Yamamoto, Chia-Hung Chen, Shigeto Watanabe, Charles Lin, Jenn-Yanq Liu, Hiroto Habu
    JOURNAL OF GEOPHYSICAL RESEARCH-SPACE PHYSICS 118(8) 5184-5189 2013年8月  査読有り
    Ionospheric disturbances caused by a missile launched from North Korea on 12 December 2012 were investigated by using the GPS total electron content (TEC). The spatial characteristic of the front edge of V-shaped disturbances produced by missiles and rockets was first determined. Considering the launch direction and the height of estimated ionospheric points at which GPS radio signal pierces the ionosphere, the missile passed through the ionosphere at heights of 391, 425, and 435km at 0056:30, 0057:00, and 0057:30 UT, respectively. The observed velocities of the missile were 2.8 and 3.2km/s at that time, which was estimated from the traveling speed of the front edge of V-shaped disturbances. Westward and eastward V-shaped disturbances propagated at 1.8-2.6km/s. The phase velocities of the westward and eastward V-shaped disturbances were much faster than the speed of acoustic waves reported in previous studies, suggesting that sources other than acoustic waves may have played an important role. Furthermore, the plasma density depletion that is often observed following missile and rocket launches was not found. This suggests that the depletion resulting from the missile's exhaust was not strong enough to be observed in the TEC distribution in the topside ionosphere.
  • Hiroki Matsunaga, Hiroto Habu, Atsumi Miyake
    JOURNAL OF THERMAL ANALYSIS AND CALORIMETRY 111(2) 1183-1188 2013年2月  査読有り
    Ammonium dinitramide (ADN) is a promising new oxidizer for solid propellants because of its high oxygen balance and high energy content, and halogen-free combustion products. One of the characteristics needed for solid propellants is stability. Heat, light, and moisture are factors affecting stability during storage, manufacture, and use. For practical use of ADN as a solid propellant, clarification of the mechanism of decomposition by these factors is needed to be able to predict lifetime. This study focused on thermal decomposition of ADN. Exothermal behavior of ADN decomposition was measured by isothermal tests using high-sensitive calorimetry (TAM) and non-isothermal tests using differential scanning calorimetry (DSC). Based on these results, analysis of the decomposition kinetics was conducted. The activation energy determined by TAM tests was lower than that from DSC tests. Thus, the decomposition path in TAM tests was different from that in DSC tests. The amount of ADN decomposition predicted from TAM tests was closer to that found under real storage conditions than the amount of decomposition predicted from DSC tests. Non-isothermal tests may not be able to precisely predict the lifetime of materials with a decomposition mechanism that changes with temperature, such as ADN. The lifetime predicted from DSC results was much longer than that from TAM tests especially at low temperature. It is necessary to use isothermal tests to predict the long-term stability at low temperature.
  • 羽生 宏人, 岡田 実, 伊藤 正則, 野副 克彦, 川野 達也, 松本 伸二, 吉田 裕二
    Science and Technology of Energetic Materials : journal of the Japan Explosive Society 73(5) 147-152 2012年12月31日  査読有り筆頭著者
  • Fujisato Koji, Habu Hiroto, Shibamoto Hidefumi, Yu Xiuchao, Miyake Atsumi, Hori Keiichi
    宇宙航空研究開発機構研究開発報告 11 1-7 2012年3月  
    Ammonium perchrolate (AP) is the most useful oxidizer for the solid rocket motors (SRMs) under the present situation, however it is also the source of the environmental pollution close to the launch site. It is well known that HCl is exhausted through the firing of SRMs and its concentration reaches approximately 10 to 20 mole percent of the total exhaust.`Environmentally friendly' and `High performance' are required for the next-generation SRMs. In this study, ammonium dinitramide (ADN), which has recently attracted attentions as a halogen-free oxidizer was employed for a substitution of AP and the combustion properties of the composite propellants were investigated. Thermoplastic elastomer (TP) and hydroxyl-terminated butadiene polymer (HTPB) were used as a binder for this research. Pyrotechnic sensitivity analysis was conducted to estimate the safety of TP/ADN propellants. Strand burning tests were also carried out for all samples and the burning rate and temperature profile were obtained through these experiments. It was found that the burning rate characteristics of ADN-based propellants were influenced by the binders.
  • 松永 浩貴, 吉野 悟, 熊崎 美枝子, 羽生 宏人, 三宅 淳巳
    Science and Technology of Energetic Materials : journal of the Japan Explosive Society 72(5) 131-135 2011年12月31日  査読有り
  • Jean-Francois Guery, I-Shih Chang, Toru Shimada, Marilyn Glick, Didier Boury, Eric Robert, John Napior, Robert Wardle, Christian Perut, Max Calabro, Robert Glick, Hiroto Habu, Nobuhiro Sekino, Gilles Vigier, Bruno d'Andrea
    ACTA ASTRONAUTICA 66(1-2) 201-219 2010年1月  査読有り
    For the last 50 years solid propulsion has successfully created a multitude of small launchers and many first stages or boosters for heavy launchers with low risk, high performance. competitive cost, superb storability, and "instant" readiness in many countries. Technical Support for these successes arose from simple designs, very high thrust levels, and low development and operation costs/risks. The first solid propulsion roadmap based on these foundations and rational projections was published in 2000 [A. Davenas, D. Boury, M. Calabro, B. D'Andrea, A. McDonald, Solid propulsion for space applications: a roadmap, in: 51st International Astronautical Congress, paper IAA-00-IAA.3.3.02, October 2000]. Moreover, subsequent information Supports its enabling technologies (high strength composite cases. energetic material processing based on continuous mixing, low density insulation, reduced actuator energy requirements, and advanced detailed simulations) and applications (first stages, strap-on, add-ons, small launchers, and niche space applications). Missions currently devoted to solid propulsion and plans for present and future launchers and exploration mission developments in the USA, Japan, and Europe are sketched and targeted improvements, and potential breakthroughs are discussed. (C) 2009 Elsevier Ltd. All rights reserved.
  • 羽生宏人, 和田英一, 丹羽崇博, 近藤靖雄, 川村尚史, 丸山信也, 岡村彩乃, 山科早英良, 永井康仁, 中道達也, 上道茜, 田中成明, 小林直樹, 笠原次郎, 森田泰弘
    航空宇宙技術(Web) 9 15-21 2010年  査読有り筆頭著者
    The educational hybrid-rocket was successfully launched and it also landed within the predicted area. Aerodynamic characteristics of the rocket designed by students of Tsukuba University were evaluated by the wind tunnel testing with the support of Tokai University. The flight path affected by the environmental condition, especially wind direction and velocity, was simulated with the original calculation program. The altitude of the rocket was measured with the optical equipment and the apex was 123 m although the calculation indicated 198 m. We expected that the insufficient filling or the volatilization of Nitrous oxide as an oxidizer led to this result. And then, the apex was verified with a function of the oxidizer filling ratio. The results showed that 81.2 % of the oxidizer volume in comparison with the firing test condition was accumulated in the tank at the launch.
  • Akihito Itoh, Masashi Watanabe, Hiroto Habu, Shin-Ichiro Tokudome, Keiichi Hori, Hirobumi Saito, Kazuyuki Kondo, Shuji Tanaka, Masayoshi Esashi
    International Journal of Energetic Materials and Chemical Propulsion 8(4) 321-327 2009年  査読有り
    A micro solid propellant thruster for simple attitude control of a 10 kg class small spacecraft is currently under development. The prototype has 0.8 mm micro rocket elements, arrayed at a pitch of 1.2 mm on a 22 × 22 mm substance. Initially, solid propellants were used, obtaining only 20% ignition probability with a very long ignition delay (e.g. 1000 ms) as well as very high ignition energy. While observing the tested prototype sample, it became apparent that the main cause of these problems was a gap between the solid propellants and ignition heater. So, the thruster system was improved so that the propellants adhered to the heater. In addition, an ignition charge was used that starts to burn at 210°C, which was acetone having the form of slurry. As a result, a better ignition probability of over 80% in vacuum and half thrust of expectation were gained.
  • Shuji Tanaka, Kazuyuki Kondo, Hiroto Habu, Akihito Itoh, Masashi Watanabe, Keiichi Hori, Masayoshi Esashi
    SENSORS AND ACTUATORS A-PHYSICAL 144(2) 361-366 2008年6月  査読有り
    In this study, reactive B/Ti multilayer igniters were investigated for the noncontact ignition of a micro solid rocket array thruster in vacuum. When current is supplied to the B/Ti multilayer igniter, the chemical reaction: 2B + Ti -> TiB2 + 1320 cal/g occurs, and sparkles are spread to a distance of several millimeters or more. The B/Ti multilayer igniters with three sizes were fabricated, and tested in six configurations of solid propellant. Although one rocket with ignition charge was ignited successfully, the noncontact ignition of the solid propellant was not achieved. However, the B/Ti multilayer igniters themselves generated small impulses of 10(-6) Ns order, suggesting the possibility of self-propulsion. (C) 2008 Elsevier B.V All rights reserved.
  • 羽生 宏人
    軽金属 58(4) 162-166 2008年4月30日  筆頭著者
  • MAYUMI Atsushi, OHTSUKA Hirohito, YAGI Kazuhiro, MORITA Yasuhiro, HABU Hiroto
    The Journal of space technology and science : a publication of Japanese Rocket Society 24(1) 7-12 2008年3月1日  査読有り
  • Yasuhiro Morita, Takayuki Imoto, Hiroto Habu, Hirohito Ohtsuka, Keiichi Hori, Takemasa Koreki, Apollo Fukuchi, Yasuyuki Uekusa, Ryojiro Akiba
    24(1) 1-6 2008年  査読有り
  • Toru Shimada, Hiroto Habu, Yoshio Seike, Seiji Ooya, Hideo Miyachi, Masaaki Ishikawa
    FLOW MEASUREMENT AND INSTRUMENTATION 18(5-6) 235-240 2007年10月  査読有り
    Simulated solid propellant slurry containing lead sphere tracers is experimentally cast into a double-circular cylindrical container. During the casting, the temperature and the pressure environment has been mimicked to an actual composite solid propellant casting of solid rocket motors. X-rays are projected on to the slurry flow from two directions and penetration images are recorded by a flat-panel detector and an X-ray image intensifier. By suppressing the mutual interference of the X-rays, the two-directional X-ray photography has been successfully conducted. Using the time series data of the X-ray images from the two directions, the identification of each tracer particle in space and time has been done and their three-dimensional paths have been computed. From these procedures, the flow field or the velocity field inside the slurry flow, which is usually invisible, has been estimated. (c) 2007 Elsevier Ltd. All fights reserved.
  • 羽生 宏人, 堀 恵一
    Science and Technology of Energetic Materials : journal of the Japan Explosive Society 67(6) 187-192 2006年12月31日  査読有り筆頭著者
  • 石川 正明, 宮地 英生, 嶋田 徹, 羽生 宏人, 大矢 清司, 清家 誉志男
    可視化情報学会誌 26(2) 197-198 2006年  査読有り
    A lot of slurry fluids have an opaque substance. It is difficult to visualize using previous photograph system with a visible ray. Therefore, we use the X-ray photograph to visualize inside a slurry fluid. And also to capture three-dimensional flow structure of the slurry flow, we use two X-ray sources and detectors. Time-serial data of the particle position are obtained by particle tracking and stereo-pair matching techniques. 3-Dimensional velocity vectors inside the slurry fluid are obtained
  • Kazuyuki Kondo, Shuji Tanaka, Hiroto Habu, Shin-ichiro Tokudome, Keiichi Hori, Hirobumi Saito, Akihito Itoh, Masashi Watanabe, Masayoshi Esashi
    IEICE Electron. Express 1(8) 222-227 2004年  査読有り
    A Ф0.8mm micro-solid propellant rocket array thruster for simple attitude control of a 10 kg class micro-spacecraft was tested in vacuum. The micro-thruster uses boron/potassium nitrate propellant (NAB), because NAB has ignition temperature as low as 500°C, and easily start to burn in vacuum. For a half of the rockets, an ignition aid (RK) was also loaded. Ignition was succeeded in vacuum with NAB + RK and NAB. The maximum impulse thrust of 4.6ˣ10-4 Ns, which is approximately a half of our requirement, was obtained with NAB. Compared to NAB, NAB + RK generated lower impulse thrust. The success rate of ignition was as low as 30%, although RK was used. These results suggest that RK has no benefit for the ignition of NAB, and other kinds of ignition aid should be found. © 2004, The Institute of Electronics, Information and Communication Engineers. All rights reserved.
  • 羽生 宏人, 野副 克彦, 霜田 正隆, 山谷 寿夫, 堀 恵一, 齋藤 猛男
    火薬学会誌 = Journal of the Japan Explosives Society : explosion, explosives and pyrotechnics 60(2) 83-90 1999年4月30日  査読有り筆頭著者

MISC

 128

講演・口頭発表等

 241
  • 中尾達郎, 山田和彦, 秋元雄希, 羽森仁志, 森みなみ, 満野真里絵, 平田耕志郎, 高澤秀人, 永田靖典, 石丸貴博, 今井駿, 前田佳穂, 前原健次, 羽生宏人, 鈴木宏二郎
    宇宙科学技術連合講演会講演集(CD-ROM) 2021年
  • 松永浩貴, 羽生宏人, 羽生宏人, 野田賢, 三宅淳巳
    火薬学会春季研究発表会講演要旨集 2021年
  • K. Wakamatsu, D. Hagiwara, H. Adachi, K. Ashigaki, A. Iwasaki, Y. Yamada, H. Habu, T. Nakamura
    Proceedings of the 2020 IEEE/SICE International Symposium on System Integration, SII 2020 2020年1月
    © 2020 IEEE. In recent years, expectations for low-cost and high-frequency rocket launches for space exploration have increased. Solid fuel rockets are small, inexpensive, and easy to handle. However, in the production of solid fuel, the mixing process and the transportation process are separate batch processes, leading to an increase in maintenance costs and disposal costs. In addition, being a manual process, it is difficult to manufacture large amounts simultaneously in a safe method. The authors have developed a mixing and transportation device that simulates the movement of the intestinal tract by using an elastic duct and a low pneumatic drive. In addition, actual fuel production has been carried out in a mixing and transporting experiment using this device. The effectiveness of this device has been exhibited from the combustion test of the produced fuel. In this paper, we present a high-quality and efficient method of mixing and transporting solid propellant material. This is a mixing of solid and liquid achieved by peristaltic movement done in real-time by adjusting the mixing degree of the mixture inside the device. The degree of mixing is determined by the solid propellant's volume and viscosity change. Therefore, we first investigate whether the content volume can be detected when the rigid bodies with different volumes are inserted. Next, we focus on the change in the viscosity of the mixture that occurs during the mixing process. We also examine the viscosity of the contents when fluids having different viscosities are inserted.
  • Asato Wada, Hiroto Habu
    AIAA Scitech 2020 Forum 2020年
    © 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. Low toxicity ionic liquid monopropellant thrusters, such as hydroxylammonium-nitrate-based and ammonium-dinitramide-based monopropellant thruster, have been continuously developed and researched as replacement for conventional hydrazine thrusters. In this study, for the attitude and orbit control thruster of spacecraft, a chemical plasma space propulsion with ammonium dinitramide based ionic liquid has been proposed. The ignition systems have been used the discharge plasma of arc or non-equilibrium, and the generation methods of discharge plasma have been researched for decomposition and combustion of ionic liquid monopropellant. This paper presents the results of open-cup firing tests with discharge plasma for an ionic liquid monopropellant. This liquid monopropellant is a eutectic mixture of ammonium dinitramide, monomethylamine nitrate, and urea. In addition, the effects of ambient pressure on the characteristics of electric and ignition were evaluated. As a result, the breakdown and ignition of the ionic liquid were confirmed under sea-level condition and vacuum condition. After breakdown and ignition, exhaust flame was observed from downstream of reaction system at sea-level condition. In a range of ambient pressure from 10 Pa to 30 Pa, the plasma plume of decomposition gas was observed. In addition, at the each condition, the pulse discharge of unsteady state was observed from discharge waveforms after breakdown of the ionic liquid.
  • 若松康太, 足立遼, 松井大育, 萩原大輝, 岩崎祥大, 山田泰之, 羽生宏人, 中村太郎
    日本機械学会ロボティクス・メカトロニクス講演会講演論文集(CD-ROM) 2020年

担当経験のある科目(授業)

 2

Works(作品等)

 3

共同研究・競争的資金等の研究課題

 11

産業財産権

 22