带挠性附件的航天器系统动力学特性研究

本文研究了带挠性附件的航天器系统动力学特性。带挠性附件的航天器系统建模为刚性主体带挠性附件（挠性附件的末端带有刚性质量），根据拟坐标下的Ｌａｇｒａｎｇｅ定理建立了主刚体姿态运动与挠性附件振动相互耦合的动力学状态方程。针对一类带挠性附件的航天器系统编制了有关计算软件，利用该软件以ＳＣＯＬＥ模型（ＳＣＯＬＥ是ＳｐａｃｅｃｒａｆｔＣｏｎｔｒｏｌＬａｂｏｒａｔｏ－ｒｙＥｘｐｅｒｉｍｅｎｔ的缩写，其系统构形可参见文献［２］［３］）为例进行动力学分析，我们得到了与ＮＡＳＡ有关报告几乎完全一样的结果。本项研究为一类带挠性附件的航天器控制系统设计提供了一种合适的动力学理论模型。

DYNAMICS OF SPACECRAFT WITH FLEXIBLE APPENDAGES

The dynamics of spacecraft with flexible appendages is investigated The set of dynamical equations which are derived by means of a Lagrangian approach in terms of quasicoordinates incorporate rigid body attitude dynamics and three dimensional vibrations of the complete assembly comprising the rigid shuttle,the flexible beams,and the reflectors with offset masses at the ends The final set of dynamical equations obtained are nonlinear and coupled in terms of the flexible modes and the rigid body modes The equations are further linearized and evaluated numerically to include the first eighteen flexible modes The computer program written by us could calculate natural frequencies and three dimensional mode shapes and the rotation couple coefficient matrix of the state equations of the system It is shown that the dynamical modes(of the SCOLE model) derived from our computer program are the same as the NASA's reports This research yields a model for designing control systems to perform three axis stabilized spacecraft with appendages