The dynamic equation of the spacecraft with extensional flexible appendages system is time variable and nonlinear, so it is very difficult to solve this kind of equation with traditional methods.
带伸展柔性附件航天器的动力学方程是刚-柔耦合的时变非线性动力学方程，用传统方法求解其动力学响应时会遇到很大的困难。
Researches on the dynamic and control for the flexible spacecraft usually use the modal of the flexible appendages.
研究柔性航天器的动力学与控制问题时，通常需要利用柔性附件的模态信息。
The attitude dynamic equations of a spacecraft with flexible appendages are obtained by using the momentum theorem.
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。
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