Study On Ground Strategy For Autonomous Orbit Transfer Failure In Space Rendezvous Homing Phase

Since the first rendezvous and docking activity, the rendezvous and docking technology is playing an increasingly important role in the space missions. Rendezvous and docking technology is a key technology for the second step of China's manned spaceflight project. The homing maneuver mission plan is a critical problem of rendezvous orbital design and control. In the normal case, the homing orbit transfer is carried out autonomously by using the device on the spacecraft. However, failure may occur during the autonomous orbit transfer. When the failure occurs, the orbit transfer task has to be accomplished by the engineers on land with the help of grand devices. For the purpose of solving the homing orbital design and control problem, this thesis studies homing phase maneuver after failure and orbital reconfiguring planning problem. The main results achieved in this thesis are summarized as follows:Orbital reconfiguring planning problem after failure of autonomous orbit maneuver during homing phase are studied. 1) The homing trajectory design optimization model is established,and C-W rendezvous equations are given. 2) The ground principles after failure are proposed and a general and systemic ground strategy is given in order to handle all of the failure.3) In view of two typical failure conditions, the simulation results show that all kinds of failure about the former two impulses can be solved by no more than three impulses to drive the chase vehicle to the location required and verifies the ground strategy is correct and feasible.Terminal errors affected by the main errors of C-W guidance are studied. 1) For this study on the specific engineering problems, the results show that the first order linearization error is the major model error in homing phase, and it has a large effect on the motion of tangent and cross directions. Comparing the error of the second order equations to the error of two-body indicates that the third order and the above order items offset some of the error. Considering the impact of J2 Perturbation, the motion of tangent, cross, normal directions are largely affected and the error of normal direction is mainly caused by the J2 perturbation. 2) Considering of initial navigation error based on C-W guidance algorithm, there are some general conclusions. The terminal errors depend mainly on the initial navigation errors and the duration of orbit maneuver, and are not relevant to the impulses and the time when the middle impulses are applied;If the initial navigation errors meet the normal distribution and are independent of each other, then terminal errors of the C-W guidance are a linear combination of the initial navigation errors and still meet the normal distribution. Using the Monte-Carlo simulation method, the results prove that the simulation results are in agreement with theoretical results.This thesis is based on the characteristic of orbital reconfiguring planning problem after failure of autonomous orbit maneuver during homing phase. According to the actual engineering constraints and handle principles, a ground strategy is proposed in order to handle all of the failure and the terminal errors are studied generally and systemically. The research have some theoretical and practical value, and offers a meaningful reference for the practical application.