観測ロケット実験グループ

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

主要な論文

 68
  • 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
  • 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.
  • 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
  • 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