著者

安平 浩義 小野 航大 平山 和樹 指田 春輝 池田 裕哉 飯島 拓人 吉岡 宙 佐原 宏典 飯塚 俊明 石井 宏宗 岡島 礼奈

出版者

一般社団法人 日本航空宇宙学会

雑誌

航空宇宙技術 (ISSN:18840477)

巻号頁・発行日

vol.22, pp.62-70, 2023 (Released:2023-09-20)

参考文献数

21

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This paper introduces Microsatellite-Friendly Multi-Purpose Propulsion (MFMP-PROP) we proposed as a promising propulsion system using low-toxic propellant for microsatellite, clarifies the development policy and positioning of MFMP-PROP among a variety of propulsion system for microsatellites, and reports the current status of its systemization with the corresponding test results. In addition, the high scalability of MFMP-PROP also makes it suitable for a wide range of missions with microsatellites of 2U to 50kg class. Though the performance of MFMP-PROP is not up to the designed value at present because of too large propellant supply in a prototype of MFMP-1U, this will be solved by optimization of the piping or adding flow adjustment elements. We will continue to further systemize MFMP-PROP and conduct environmental tests to achieve an early space demonstration and utilization.

著者

佐原 宏典 小林 悠也 中村 健二郎 尾又 由佳乃 阿部 圭典 染谷 昴 西尾 勘汰 飯塚 俊明

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会論文集 (ISSN:13446460)

巻号頁・発行日

vol.67, no.6, pp.205-210, 2019 (Released:2019-12-05)

参考文献数

20

被引用文献数

2

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Microsatellites are now in vogue and a lot of and a variety of missions using them are progressed in the world, some of them require propulsion system to realize a highly precise attitude control or orbit transfer. In order to satisfy the requirements, we are developing Microsatellite-Friendly Multi-Purpose Propulsion System, MFMP-PROP, with capabilities of both mono-propellant and bi-propellant modes to provide both of small impulse bit and large delta-V, under the policies of Safety First, Border Free, Effective COTS, and Easy Scalability, based on the techniques of 60wt% Hydrogen Peroxide. We conducted captive tests of a thruster for mono-propellant mode under bi-propellant mode to confirm its stable ignition and continuous operation, and obtained performances under its pre-heating temperature and mixing ratio of hydrogen peroxide and ethanol, of 160 seconds of specific impulse at the highest.

著者

飯塚 俊明 西尾 勘汰 阿部 圭典 川村 壮司 加藤 岳仁 賀来 将大 伴野 眞優 松島 純 小林 悠也 中村 健二郎 佐原 宏典

出版者

独立行政法人 国立高等専門学校機構 小山工業高等専門学校

雑誌

小山工業高等専門学校研究紀要 (ISSN:02882825)

巻号頁・発行日

vol.50, pp.63-68, 2017-12-25 (Released:2019-01-28)

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This paper reports fundamental study on performance degradation, caused by solid catalyst, of 60wt% hydrogen peroxide thruster for small satellites. The chemical in-space propulsion system, with 60wt% hydrogen peroxide, has been proposed and developed based on three policies, safety first, border free, and effective COTS. Platinum based metal honeycomb solid catalyst has been installed to BBM of thruster, and the solid catalyst is one of cause to limit lifetime of the thruster. In this study, to understand degradation, comparison between observation results of solid catalyst surface by FE-SEM/EDS and thruster performance has been conducted. Small cracks have been observed on upstream surface. The evident growth of cracks has not been found; however, instability of response time has been confirmed.