国防科技大学学报2018，Vol.40Issue(3)：42-48,7.DOI:10.11887/j.cn.201803007
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
摘要
Abstract
In order to fulfill the attitude control mission of micro flight vehicle delivered from a certain kind of ballistic missile , a fast attitude maneuver control approach based on the GPM ( Gauss pseudospectral method) was proposed.Firstly, the accurate attitude control model was established 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 controller was designed to track the optimal trajectories.Numerical simulation results demonstrate the optimality of the attitude maneuver trajectories obtained by using the GPM , the good performances of the quasi-sliding mode controller in tracking the optimal 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Key words
attitude control/Gauss pseudospectral method/reaction wheel/time-optimal control/sliding mode controller分类
航空航天引用本文复制引用
刘成国,余翔,刘昆,刘佳琪..微小型飞行器姿态快速机动控制方法[J].国防科技大学学报,2018,40(3):42-48,7.基金项目
国家自然科学基金资助项目(61603405) （61603405）
