Rendezvous Guidance Method Of Spacecraft

With the rapid development of space technology, spacecraft technique using for implement multifarious operation in the space has become more and more mature. Many countries including China have been participating in this field to different degree. The problem on orbital rendezvous of spacecraft is a crucial technology for human space exploration. It is one of the most difficult problems in theory and application of spacecraft control. In this thesis, we study the short-range rendezvous of spacecraft and complete some analysis on several kinds of guidance methods, the effectiveness of them are verified by simulation.First, this thesis gives the definition of reference frame describing the rendezvous process and dynamic equation (Hill equation) of relative motion between two spacecrafts. We also give the dynamic model of actuator. These models are the foundation of designing the orbital rendezvous guidance method of spacecraft.Second, we introduce the principles of Hill guidance and Hohmann transfer, design line-of-sight (LOS) control method based on LOS-angle and LOS angular rate, then analyse the factors affecting these guidance methods. According to characteristic of these guidance methods and the affecting factors, we design three approaching control methods in the automatic homing phase of rendezvous. With simulation, we compare the accuracy and fuel consumption of these guidance methods.In the last approaching phase, we take care of the accuracy and safety, because the tracker is very close to the target. In this phase, we use sliding mode to certify the system robustness.Finally, we integrate the methods in the former two phases to make a simulation for the whole rendezvous process. The simulation results satisfy the accuracy requirement.