论文部分内容阅读
上面级在多星部署过程中将涉及大角度姿态机动问题,卫星释放所引起的质心横移将给上面级姿态控制带来困难。根据系统质心的横移情况,在上面级体坐标系中确定矢量喷管的平衡位置,进而确定出矢量喷管指向指令方向时的上面级姿态。调制姿态四元数可以得到描述上面级姿态偏差的拟欧拉角及相应的拟欧拉角速度,在拟欧拉角描述的上面级姿态运动模型的基础上,选择合适的滑模面,构造变结构控制律。仿真结果表明,该控制律可对上面级姿态进行控制,进而实现对矢量喷管指向的间接控制,喷管摆角的限幅不会影响姿态控制的过程。
In the multi-satellite deployment process, the upper stage will involve large-angle attitude maneuvering problems. Centroid shifting caused by satellite release will cause difficulties in attitude control at the upper level. According to the traverse of the system center of mass, the equilibrium position of the vector nozzle is determined in the upper body coordinate system, and the upper stage attitude of the vector nozzle in the direction of the command is determined. Modulation quaternions can be obtained to describe the upper-class posture Euler angles and the corresponding Euler angle Euler angular velocity quasi Euler angle based on the top-level attitude motion model, select the appropriate sliding surface, the structure of variable Structure control law. The simulation results show that the control law can control the attitude of the upper stage, and then realize the indirect control of the vector nozzle. The limit of nozzle swing angle will not affect the process of attitude control.