摘要
针对某弹道导弹释放的微小型飞行器的姿态控制任务需求,提出一种基于Gauss伪谱法的姿态快速机动控制方法。建立精确的姿态控制模型,并考虑反作用飞轮的耦合力矩项;采用Gauss伪谱法获取最优姿态轨迹,设计准滑模跟踪控制器以跟踪该最优轨迹。数字仿真结果表明,Gauss伪谱法计算得到的轨迹是最优的,准滑模跟踪控制器能实现对最优轨迹的良好跟踪,且对干扰力矩有较好的抑制作用。
In order to fulfill the attitude control mission of micro flight vehicle dlivered from maneuver control approach based on the GPM （ Gauss pseudospectral method） was proposed. Firstly, the accurate attitude control model wasestablished and the coupling torque term of the reaction wheels was taken into account. Secondly , the GPM was adopted to obtain the optimal attitude trajectories. Moreover , a quasi-sliding mode contoller was designed to track the optimal trajectories. Numerical simulation results demonstrate the optimality of the attitude maneuver trajectories obtained by using the GPM , the gcontroller in tracking the optmal trajectories , and the good effect in rejecting the external disturbance torque.
作者
刘成国
余翔
刘昆
刘佳琪
LIU Chengguo;YUXiang;LIUKun;LIUJiaqi(Beijing Institute of Space Long March Vehicle,Beijing 100076,China)
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2018年第3期42-48,共7页
Journal of National University of Defense Technology
基金
国家自然科学基金资助项目(61603405)
关键词
姿态控制
GAUSS伪谱法
反作用飞轮
时间最优控制
滑模控制器
attitude control
Gauss pseudospectral method
reaction wheel
time-optimal control
sliding mode controller
