大角速度柔性航天器动力学模型修正

Dynamic Model Modification of Flexible Spacecraft with Large Angular Velocity

将拉格朗日方程及其准坐标形式用于中心刚体加柔性附件航天器的拉格朗日函数,推导了中心刚体加柔性附件航天器动力学模型。针对航天器大角速度,分析中心刚体角速度对角动量方程的影响,对传统动力学模型进行修正。航天器绕惯量主轴大角速度自旋仿真结果验证了修正后的动力学模型对于大角速度航天器的有效性。

The Lagrange equation and its quasi-coordinate form were applied into the Lagrange function of dynamic model of spacecraft with and central rigid body and flexible appendages, the dynamic model for spacecraft with relatively large angular velocity was derived in this paper. Aim to the spacecrafts with large angular velocity, the impact of the central rigid body＇s angular velocity on the flexible appendages＇ angular momentum was analyzed, and the conventional dynamic model was modified. The numerical simulation and theoretical analysis showed that the modified dynamic model was valid for spacecrafts with relatively big angular velocity.