System Design, Development and Ground Verification of a Separable De-Orbit Mechanism for the Orbital Manoeuvre of Micro-Satellite ALE-1
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- PALA Alperen
- Department of Aerospace Engineering, Tohoku University
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- KUWAHARA Toshinori
- Department of Aerospace Engineering, Tohoku University
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- HONDA Tomoyuki
- Department of Aerospace Engineering, Tohoku University
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- UTO Hiroki
- Nakashimada Engineering Works, Ltd.
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- KANEKO Tetsuya
- Nakashimada Engineering Works, Ltd.
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- POTIER Adrien
- Department of Aerospace Engineering, Tohoku University
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- TANGDHANAKANOND Pasith
- Department of Aerospace Engineering, Tohoku University
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- FUJITA Shinya
- Department of Aerospace Engineering, Tohoku University
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- SHIBUYA Yoshihiko
- Department of Aerospace Engineering, Tohoku University
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- SATO Yuji
- Department of Aerospace Engineering, Tohoku University
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- SHIBUYA Tomomasa
- Department of Aerospace Engineering, Tohoku University
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- KAMACHI Koh
- ALE Co., Ltd.
書誌事項
- 公開日
- 2021
- 資源種別
- journal article
- DOI
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- 10.2322/tastj.19.360
- 公開者
- 一般社団法人 日本航空宇宙学会
この論文をさがす
説明
<p>ALE project is a micro-satellite project with the mission objective of artificial generation of a shooting star. The first satellite of this project (ALE-1) is launched in January of 2019 at an orbit of approximately 500 km of altitude. There are manned missions in the International Space Station at an altitude lower than this, therefore the altitude of ALE-1 needs to be lowered before the actual mission start. There exist mechanical systems that allow a passive lowering of the altitude of satellites by accelerating the natural decay of the orbit with use of a thin polyimide film as a drag sail. Previously such systems were only used to de-orbit completely and decrease space-debris. We propose and design a mechanical system which allows operation of the satellite during de-orbiting, and separation of the drag sail when the desired altitude is reached. We consider sufficient power generation during de-orbiting; passive stabilization of the satellite attitude for shorter de-orbiting time; and mechanical safety and reliability of the system. This paper summarizes the design, development, and ground verification of the proposed module SDOM (Separable De-Orbit Mechanism) along with a projected orbital decay of ALE-1 satellite.</p>
収録刊行物
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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 (3), 360-367, 2021
一般社団法人 日本航空宇宙学会
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詳細情報 詳細情報について
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- CRID
- 1390287907269899264
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- NII論文ID
- 130008034596
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- ISSN
- 18840485
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- HANDLE
- 10097/00132014
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- 本文言語コード
- en
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- 資料種別
- journal article
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- データソース種別
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- JaLC
- IRDB
- Crossref
- CiNii Articles
- OpenAIRE
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- 抄録ライセンスフラグ
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