空间飞行器柔性附件动力学建模方法研究

Study on Dynamics Modeling of a Flexible Appendage of Spacecraft

论述了采用传统动力学建模方法建立空间飞行器柔性附件动力学方程时过早线性化的问题，揭示了这种方法建立动力学方程的缺陷，即失去了一些重要的刚柔耦合项。采用Ｋａｎｅ方法建立动力学方程的一般公式，并确定了采用传统动力学方法建立动力学方程所失去的项。进一步探讨了基于构件小变形的空间飞行器柔性附件动力学的建模方法，并进行了仿真和实验研究，证明了理论分析的正确性。

The premature linearization in modeling dynamics of a spacecraft flexible appendage is discussed by using the conventional modeling method, and the method defects are demonstrated that some coupling terms between large overall motion and small deformation are lost. A general formulation is developed by using Kane′s method, and the missed terms are determined. Furthermore, dynamics modeling methods of flexible appendages for spacecraft based on small deformations are analyzed. The dynamic simulation and experimental study of a flexible beam are completed, and simulation results are verified by the experimental ones.