書誌事項
- タイトル別名
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- Minimum Energy Maneuver of Satellites by Two Wheels
- 2 ホイール ニ ヨル ジンコウ エイセイ ノ サイショウ エネルギマヌーバ キドウ
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抄録
This paper discusses on the minimum energy maneuver of a satellite using two reaction wheels. The problem is a rest-to-rest maneuver around the axis, which is perpendicular to each wheel axes. The attitude of satellite is described using the parameters that are presented by Tsiotras et al. The parameters are useful for the description of maneuvers by two wheels. The relation between the optimal maneuver and the moment of inertia is shown analytically and numerically. The results show that the symmetry satellite whose all moments of inertia are same does not have a unique optimal solution. A group of minimum energy trajectories exists. On the other hand, the asymmetry satellite has a unique optimal solution. The numerical solutions show that the wheel on the axis of smaller moment of inertia consumes more energy than the other wheel.
収録刊行物
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- 日本航空宇宙学会論文集
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日本航空宇宙学会論文集 51 (598), 613-620, 2003
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
- 1390282679447501184
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- NII論文ID
- 10012565808
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- NII書誌ID
- AA11307372
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- ISSN
- 24323691
- 13446460
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- NDL書誌ID
- 6767542
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- 本文言語コード
- ja
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- データソース種別
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- JaLC
- NDL
- Crossref
- CiNii Articles
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- 抄録ライセンスフラグ
- 使用不可