Research On Trajectory Design And Attitude Control Method Of Non-cooperative

The rendezvous and docking technology of non-cooperative targets has great potential value in space environment cleaning,improving the efficiency of satellite utilization and military strategy.In recent years,it has been concerned and studied by a large number of scholars.In this paper,the approach orbit design and attitude control technology of non-cooperative target in space are studied.The design method of each segment is given and the corresponding calculation examples and simulation analysis are given.Firstly,the relative coordinate system and the corresponding transformation relationship are defined,the flight dynamics model and the perturbation model are established,and the relative orbit dynamics model of spacecraft is derived,which provides the theoretical basis for the later algorithm design.In the short-range guidance section,considering the inaccurate measurement of non-cooperative target orbit information,the short-range guidance section is divided into two stages according to the relative distance.When the relative distance is relatively long,the pulse guidance based on C-W state equation is used for preliminary approach,and the design method of double pulse and multi pulse orbit transfer is derived and given;when the relative distance is relatively short,the line of sight guidance is used,the line of sight rotation coordinate system is established and the APN guidance rate is designed,and the design of the speed in the line of sight direction is added on the basis of the traditional proportional guidance,so as to track the spacecraft Approach the target spacecraft with controllable speed and high precision.Several kinds of coplanar flying around configurations are designed,and the trajectory functions of each flying around configuration are derived.In order to ensure better observation effect,the performance of each configuration is compared from the angle of relative distance change and energy consumption.Finally,the performance of each flying around configuration is summarized.In the approach phase,considering the possible rotation of the target spacecraft,a reasonable approach scheme is designed.Based on the relative position and attitude control model,the auto disturbance rejection control rate is designed.By controlling the moment and overload,the tracking spacecraft can keep approaching the capture point of the target spacecraft,while the docking port always points to the capture point direction of the target spacecraft(the docking port axis).Finally,the approximation scheme is verified by simulation.