Research on Tracking Guidance Method for On-orbit Service Autonomous Homing Based on Proportional Guidance and Trajectory Planning

摘要

It is a trend that the high orbit and high performance satellites are applied to on-orbit service. There are some advantages for tracking spacecraft to use proportional navigation timely in autonomous homing phase of rendezvous docking. In this paper, proportional navigation is derived from inertial coordinate system using optimal control method. The approximate treatment of C-W equation shows that proportional navigation is suitable for high orbit. The simulation results of proportional navigation and trajectory planning show that the fuel optimal effect of proportional navigation is good. There is no accumulated error in proportional navigation, which results in a good accuracy of reaching the target point. Because the terminal velocity cannot be effectively controlled, it is suitable for long-distance autonomous homing phase. Timely use of proportional navigation has certain advantages.