摘要
基于跟踪指令轨迹的航天器姿态机动方案,给出了一种余弦过渡角加速度路径规划算法,以抑制机动后挠性附件振动,应用多模态双峰EI输入成型器对规划路径进行优化。该算法简单,易实现。将规划路径与bang-coast-bang(BCB)路径比较,仿真结果表明采用跟踪输入成型器优化的余弦过渡加速度路径法实现姿态机动可有效抑制挠性附件振动,减小残余耦合力矩,提高快速性。
A cosine transition acceleration path planning algorithm to suppress the vibration of the flexible appendix after maneuver was given out based on tracking command path of the attitude maneuver scheme of the spacecraft in this paper, in which the path was optimized by the multi-mode two-hump extra-insensitive shaper. This method was simple and easy to be realized. Comparing the planning path with bang-coast-bang path using the tracking sliding mode controller which designed in the paper, the simulation results showed that using the method of tracking cosine transition acceleration path optimized by input shaper to realize spacecraft＇s attitude maneuver could suppress the flexible appendages＇ vibration effectively, reduce the residual coupling moment and improve the criterion of rapidity.
出处
《上海航天》
2014年第4期41-46,72,共7页
Aerospace Shanghai
关键词
挠性航天器
姿态机动
路径规划
输入成型
振动抑制
余弦过渡加速度路径
Flexible spacecraft
Attitude maneuver
Path planning
Input shaping
Vibration suppressing
Cosine transition acceleration path
