摘要
研究了基于大气阻力实时辨识的Drag-free卫星最优控制。将Drag-free卫星和其内部的验证质量等效为两颗内、外编队卫星并建立动力学方程,推导了基于卫星和验证质量的相对运动状态观测值反演大气阻力的算法。建立了状态最优调节器模型,采用动态规划求解经典的二次型最优控制。对低轨圆轨道Drag-free卫星的仿真计算结果表明方法的求解精度较高,计算消耗较小。
Optimal control for collocation between drag-free satellite and its proof mass based on real time determination was investigated in this paper.The drag-free satellite and its proof mass were equivalent to outer and inner formflying two-satellites,and the dynamic equations were established.The reverse computation method of air drag force based on observing relative states between satellite and its proof mass was derived.The model of state optimal regulator was set up,and the dynamic programming was adopted to solve a linear quadratic optimization control.The simulation results of some drag-free satellite on a low circular orbit showed that the method had high precision and low computation cost.
出处
《上海航天》
2010年第6期6-10,60,共6页
Aerospace Shanghai
关键词
Drag-free卫星
跟踪保持
最优控制
大气阻力
实时辨识
Drag-free satellite
Tracking and collocation
Optimal control
Air drag force
Real time determination
