小推力速度闭环交会制导律设计

Fast Closed-loop Guidance Law with Finite Thrust Amplitude Jets for Rendezvous

在空间飞行器交会对接的近程导引阶段,以小推力喷气发动机作为执行机构,同时完成轨道控制和姿态稳定。基于C-W方程提出了速度闭环交会制导方案,依据转动惯量是否为对角占优阵,姿态与轨道协调控制采用分时控制方案或同时控制方案,轨控推力和姿控力矩指令由同一套小推力发动机来执行。分析了此方案的制导误差,并提出了分步多推力弧段的小推力交会制导方法以提高制导精度。基于MATLAB/Simulink仿真平台实现了两个空间飞行器的分步多推力弧段近程交会导引仿真,仿真结果证实了所采用方法的有效性。

Fast closed-loop guidance law for the short-range-guidance stage of rendezvous and docking based on the C-W equation was present. Jets with finite thrust amplitude were adopted as actuator for orbital and attitude coupling control. Attitude and orbit simul- taneous control scheme and time-shared control scheme were adopted to coordinate the attitude and orbital control during the coupling phase. The guidance error induced by the fast closed-loop guidance law was analyzed. Further, a step-by-step muti-thrust-arcs guidance law with finite thrust amplitude for rendezvous was given. Finally, we implemented the short-range-guidance scenarios simulation of ren-dezvous via MATLAB/ Simulink platform. Simulation results confirm the validity of the methods used.