微小型飞行器姿态快速机动控制方法  

Fast attitude maneuver control method of micro flight vehicle

作　　者：刘成国[1] 余翔[2] 刘昆[2] 刘佳琪[1] LIU Chengguo;YUXiang;LIUKun;LIUJiaqi(Beijing Institute of Space Long March Vehicle,Beijing 100076,China)

机构地区：[1]北京航天长征飞行器研究所,北京100076 [2]国防科技大学空天科学学院,湖南长沙410073

出　　处：《国防科技大学学报》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)

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.

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 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]