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。
The coupled dynamic equations of a spacecraft with tip mass attached flexible appendage which is deployable are obtained by using the momentum theorem.
结构复杂的航天器带有几十米、上百米大型挠性附件，附件末端还带有大质量刚体。
This article presents a dynamic model for a large flexible spacecraft with its end mass undergoing a large Angle, high speed maneuvering.
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。
The dynamic equations of flexible spacecraft are derived by introducing a moving coordinate frame.
首先建立了采用任意浮动参考系时的柔性航天器动力学方程；
The dynamic equations of flexible spacecraft are derived by introducing a moving coordinate frame.
首先建立了采用任意浮动参考系时的柔性航天器动力学方程；
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