利用动量矩定理推导出带挠性伸展附件航天器的动力学方程。
The attitude dynamic equations of a spacecraft with flexible appendages are obtained by using the momentum theorem.
建立带附加质量大型挠性航天器大角度快速机动时的动力学模型。
This article presents a dynamic model for a large flexible spacecraft with its end mass undergoing a large Angle, high speed maneuvering.
研究一类构形为中心刚性带挠性梁的航天器平面快速大角度机动的动力学与控制问题。
This paper is concerned with the dynamics and control for planar, large Angle rapid slew maneuvering of a flexible multi body spacecraft, consisting of a rigid central body and a flexible beam.
研究一类构形为中心刚性带挠性梁的航天器平面快速大角度机动的动力学与控制问题。
This paper is concerned with the dynamics and control for planar, large Angle rapid slew maneuvering of a flexible multi body spacecraft, consisting of a rigid central body and a flexible beam.
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