Separation Experiment for OMOTENASHI Moon Lander at Extremely High Spin Rates
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- MORISHITA Naoki
- Research and Development Directorate, JAXA
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- KIKUCHI Junji
- Research and Development Directorate, JAXA
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- TORII Wataru
- Institute of Space and Astronautical Science, JAXA
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- KAWANO Taro
- Research and Development Directorate, JAXA
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- KUHARA Takahiro
- Technosolver Corporation
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- NAKAMURA Kazuyuki
- Technosolver Corporation
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- MIYOSHI Kota
- Research and Development Directorate, JAXA
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- TOKUNAGA Kakeru
- Institute of Space and Astronautical Science, JAXA
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- ISHIGE Yasuo
- Institute of Space and Astronautical Science, JAXA
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- OTSUKI Masatsugu
- Institute of Space and Astronautical Science, JAXA
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- HASHIMOTO Tatsuaki
- Institute of Space and Astronautical Science, JAXA
Description
<p>This paper describes a separation experiment conducted at extremely high spin rates for OMOTENASHI, being developed as the world's smallest Moon lander. The experiment validated the separation method used in the landing sequence and the tipoff impulse was estimated from the motion of the separated object. The study showed that the tipoff impulse increases superlinearly in the high spin rate region. This information is indispensable in determining the operational spin rate of OMOTENASHI in orbit. The method described in this paper can be applied widely to separation experiments for small spinning satellites and rocket stages.</p>
Journal
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- TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 19 (4), 453-460, 2021
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
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Details 詳細情報について
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- CRID
- 1390851553098923264
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- NII Article ID
- 130008062309
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- ISSN
- 18840485
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- Text Lang
- en
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- Data Source
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- JaLC
- Crossref
- CiNii Articles
- OpenAIRE
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- Abstract License Flag
- Disallowed
