Time-fuel Optimal Trajectory based Attitude Maneuver Control for Flexible Spacecraft
This paper investigates the attitude maneuver control for flexible spacecraft,in which the torque saturation and unknown parameter uncertainties are considered.Firstly,a timefuel optimal trajectory is developed such that a PD controller based on the trajectory is proposed.Then,in order to suppress the vibration of flexible appendages,a structure filter is designed for the first order elastic mode.Simulation results show that the high-precise attitude control and vibration suppression are achieved successfully.Considering the inertia parameter errors,the effectiveness of the developed optimal trajectory is demonstrated
flexible spacecraft attitude maneuver weighted-time-fuel optimal control structure filter
Pengyu Wang Zongming Liu Chuanjiang Li Yanchao Sun Chao Zhang
Department of Control Science and Engineering, Harbin Institute of Technology, Harbin, China Shanghai Institute of Spaceflight Control Technology, Shanghai, China
国际会议
哈尔滨
英文
197-201
2016-07-21（万方平台首次上网日期，不代表论文的发表时间）