| Item type |
紀要論文 / Departmental Bulletin Paper(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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タイトル |
A Unique Single Stage Parachute System and Qualification by Balloon Drop Tests |
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言語 |
en |
| 言語 |
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|
言語 |
eng |
| 資源タイプ |
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資源タイプ識別子 |
http://purl.org/coar/resource_type/c_6501 |
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資源タイプ |
departmental bulletin paper |
| アクセス権 |
|
|
アクセス権 |
metadata only access |
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アクセス権URI |
http://purl.org/coar/access_right/c_14cb |
| 著者 |
石井, 信明
平木, 講儒
稲谷, 芳文
本田, 雅久
Ishii, Nobuaki
Hiraki, Koju
Inatani, Yoshifumi
Honda, Masahisa
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| 著者所属 |
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|
宇宙科学研究所 |
| 著者所属 |
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|
宇宙科学研究所 |
| 著者所属 |
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宇宙科学研究所 |
| 著者所属 |
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|
アイ・エイチ・アイ・エアロスペース |
| 著者所属（英） |
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en |
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Institute of Space and Astronautical Science (ISAS) |
| 著者所属（英） |
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en |
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Institute of Space and Astronautical Science (ISAS) |
| 著者所属（英） |
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|
en |
|
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Institute of Space and Astronautical Science (ISAS) |
| 著者所属（英） |
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|
en |
|
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IHI Aerospace Company |
| 出版者 |
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出版者 |
宇宙科学研究所 |
| 出版者（英） |
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出版者 |
Institute of Space and Astronautical Science |
| 書誌情報 |
en : The Institute of Space and Astronautical Science report. S.P. : Aerodynamics, Thermophysics, Thermal Protection, Flight System Analysis and Design of Asteroid Sample Return Capsule
巻 17,
p. 367-378,
発行日 2003-03
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| 抄録（英） |
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内容記述タイプ |
Other |
|
内容記述 |
A simple parachute system for a small space capsule is presented in this paper. The parachute system, proposed here, consists of a main chute and pyrotechnic devices to push up the cover of the parachute container. The parachute is a single stage, which excludes a pilot chute to pull out the main chute. Instead of using a sub-parachute, the hard cover of the parachute container is utilized for the parachute deployment. Therefore, in the proposed system, it is key function for stable deployment of the parachute that qualification of the ejection energy of the pyrotechnic devices and the aerodynamic stability of the rigid cover during jettison. In order to verify the entire functions of a parachute deployment system and to examine the transonic aerodynamics of the capsule with a blunt nose, balloon drop tests were planned and successfully conducted in 1996 and in 1998. In the first balloon test, the parachute deployment strategy using the newly developed pyrotechnic devices was validated as the first priority, together with comparing the fundamental aerodynamics of the capsule and the parachute with the wind tunnel test results. On the other hand, in the second test, structural components of the capsule were upgraded and closely simulated to the actual model of the MUSES-C reentry capsule. Throughout the protomodel demonstration by the balloon drop tests, the parachute deployment method was experimentally validated. Besides, aerodynamic instability during the transonic flight proved to be endurable, and the attitude oscillation was found not to diverge. Namely, the design and strategy of both the deceleration system and the capsule aerodynamics turned out to be applicable for the flight model of the MUSES-C reentry capsule. |
| ISSN |
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収録物識別子タイプ |
ISSN |
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収録物識別子 |
0288-433X |
| 書誌レコードID |
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収録物識別子タイプ |
NCID |
|
収録物識別子 |
AA10455137 |
| 資料番号 |
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内容記述タイプ |
Other |
|
内容記述 |
資料番号: SA0200034000 |
