卫星离散动力学模型的建立

Establishment of Discrete Dynamic Model of an Aerospace Satellite

采用部件振型法建立航天卫星离散动力学模型.首先使用有限单元法对挠性部件进行模态分析,得出挠性部件的特征值和特征矢量,然后利用离散参数拟坐标拉格朗日法建立航天卫星的离散动力学模型.该模型既考虑了卫星本体和挠性部件的刚性旋转运动,也考虑了挠性部件本身的振动.

A method is introduced to establish the discrete dynamics model of an Aerospace satellite. The model requires consideration of not only the rigid rotational movement of the satellite body and the flexible components, but also the vibration of the flexible components are considered. First, the eigenvalues and the eigenvectors of vibration mode of the solar panel are calculated by using finite element Method, and then a discrete dynamics model of the aerospace satellite is established with quasi-coordinate Lagrange method.