Minimum Energy Maneuver of Satellites by Two Wheels

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  • Endo Tatsuya
    横浜国立大学大学院環境情報学府環境システム学専攻
  • Ueno Seiya
    横浜国立大学大学院環境情報研究院

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  • ２ホイールによる人工衛星の最小エネルギマヌーバ軌道
  • 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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Abstract

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.

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