带柔性部件卫星耦合动力学建模理论及仿真

COUPLED DYNAMICS OF MODELING THEORY AND SIMULATIONS OF SATELLITES WITH FLEXIBLE APPENDAGES

本文利用Jourdain速度变分原理和集中质量有限元法建立了太阳帆板变形运动与星体大范围刚体运动之间相互耦合的程式化动力学方程 ;用数值方法仿真了系统的动力学性能 ,给出了三种卫星动力学模型并比较了三种卫星动力学模型之间的差异 ;指出了目前工程实际中所用动力学模型的不足 。

The paper presents the dynamical equations of satellites coupling between rigid motions of main body and vibration of elastic plates,which are derived by means of Jourdian 's Principle and Finite Element.Through simulating dynamics of three models of satellites,the default of spacecraft model used in present engineering fields is exposed,and a reasonable model is established in this paper.