Research of a low toxicity propulsion system for space craft using HAN propellant
| Project/Area Number |
21246127
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| Research Category |
Grant-in-Aid for Scientific Research (A)
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| Allocation Type | Single-year Grants |
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| Section | 一般 |
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| Research Field |
Aerospace engineering
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| Research Institution | Japan Aerospace Exploration Agency |
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Principal Investigator |
HORI Keiichi 独立行政法人宇宙航空研究開発機構, 宇宙科学研究所, 教授 (40202303)
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| Co-Investigator(Kenkyū-buntansha) |
TAKEGAHARA Haruki 首都大学, 東京システムデザイン研究科 (20227010)
AOYAGI Junichiro 首都大学, 東京システムデザイン研究科 (10453036)
TACHIBANA Takeshi 九州工業大学, 工学研究院, 教授 (50179719)
KAKAMI Akira 九州工業大学, 工学研究院, 助教 (80415653)
TAHARA Hirokazu 大阪工業大学, 工学部, 教授 (20207210)
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| Co-Investigator(Renkei-kenkyūsha) |
SAWAI Shujiro 独立行政法人宇宙航空研究開発機構, 宇宙科学研究所, 準教授 (30270440)
NAGATA Taiichi 独立行政法人宇宙航空研究開発機構, 研究開発本部, 開発員 (40421862)
NAKATSUKA Junichi 独立行政法人宇宙航空研究開発機構, 宇宙科学研究所, 開発員 (00462896)
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| Project Period (FY) |
2009 – 2011
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| Project Status |
Completed (Fiscal Year 2011)
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| Budget Amount *help |
¥45,890,000 (Direct Cost: ¥35,300,000、Indirect Cost: ¥10,590,000)
Fiscal Year 2011: ¥9,230,000 (Direct Cost: ¥7,100,000、Indirect Cost: ¥2,130,000)
Fiscal Year 2010: ¥14,300,000 (Direct Cost: ¥11,000,000、Indirect Cost: ¥3,300,000)
Fiscal Year 2009: ¥22,360,000 (Direct Cost: ¥17,200,000、Indirect Cost: ¥5,160,000)
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| Keywords | HAN / 推進 / 低毒性 / 人工衛星 / スラスタ / 触媒 / 電気推進 / 直流アークジェットスラスタ / 惑星探査 / プラズマ支援燃焼 / 推力測定 / 大気圧プラズマ / アークジェットスラスタ / アーク放電 / 放電プラズマ / アークジェット |
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| Research Abstract |
The objective of this study is application of HAN based propellant to thruster of space craft. As compared with the current propellant, Hydrazine, toxicity is low and specific impulse is high. With catalyst ignition, electric ignition, and electric propulsion, HAN based propellant can achieve the thrust and the specific impulse appropriate to maneuver the orbit, to control the attitude, and to keep the orbit As the results of these studies, HAN propellant was able to be ignited in all systems. The obtained characteristics of the ignition and the combustion are useful to design and to test a flight model. In the future, thruster based on these results will be developed, and will be tested on the orbit.
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Report
(4 results)
Research Products
(47 results)
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[Journal Article] Combustion Characteristics of HAN-based Liquid Monopropellant-Combustion mechanism and application to thruster2009
Author(s)
T. Katsumi, H. Kodama, T. Matsuo, J. Nakatsuka, K. Hasegawa, K. Kobayashi, H. Ogawa, N. Tsuboi, S. Sawai, K. Hori
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Journal Title
Combustion, Explosion, and Shock Waves
Volume: Vol.45, No.4
Pages: 442-453
Related Report
Peer Reviewed
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[Journal Article] Combustion Characteristics of HAN-based Liquid Monopropellant -Combustion mechanism and application to thruster-2009
Author(s)
T.Katsumi, H.Kodama, T.Matsuo, J.Nakatsuka, K.Hasegawa, K.Kobayashi, H.Ogawa, N.Tsuboi, S.Sawai, K.Hori
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Journal Title
Combustion, Explosion, and Shock Waves Vol.45, No.4
Pages: 442-453
Related Report
Peer Reviewed
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