Research On Fast Approaching And Flyaround Control Of Tracking Satellite

With the continuous progress of space system technology and the increasingly fierce competition in space,the field of space system maintenance and space offensive and defensive confrontation has become the focus of vigorous promotion and development in all countries of the world.Miniature satellites have the characteristics of small size,light weight,strong mobility,high flexibility and strong survivability.Compared with the traditional on-orbit operation of aircraft,autonomous proximity operation of small satellites has the unique advantages of fast response speed,high autonomy,small scale and high safety.The use of micro satellites for autonomous space proximity operations has a very high demand background and advantages in modern space missions.According to the mission requirements of tracking satellite flight process,this paper designs the orbit control strategies of satellite in each maneuvering stage.In the stage of long-distance approach,a guidance law is designed,which can quickly approach the mission requirements in a limited time,and can make the tracking satellite reach the designated position in a limited time and meet the terminal speed requirements The standard particle swarm optimization algorithm is used for multiobjective optimization design,and the optimal fast maneuvering orbit of the tracking satellite with limited thrust is obtained,which meets the task requirement of the tracking satellite reaching the designated position in a limited time.In the short-range guidance stage,the guidance strategy of tracking the short-range guidance stage of the satellite is designed The line-of-sight guidance equation is derived,and the axial control law and lateral control law are designed at this stage Through the combination of linear guidance law and surround guidance law,the rotation rate is reduced by linear guidance law;When the switching condition is reached,the spacecraft switching guidance law is the circling guidance law,and the circling approach is realized only by the lateral engine,which provides the basis for the design of the following fast orbit.In the stage of short-distance flight,a scheme of short-distance controlled flight of tracking satellite is designed by using the existing controlled flight orbit design method and regular polygon controlled orbit,which realizes the task of fast and stable flight observation of tracking satellite for target satellite.Secondly,considering that there is a certain error between the actual thrust and the theoretical thrust of the satellite engine,a sliding mode controller is designed to keep the flight orbit,which effectively controls the actual flight orbit near the ideal flight orbit and meets the task requirements.To sum up,this paper provides a reference scheme for the orbit design of autonomous approaching operation of micro-satellites,which can quickly and stably complete the autonomous approaching and orbiting observation tasks of target satellites.In space missions,it can shorten the maneuvering flight time of spacecraft and speed up the task realization,which has certain practical significance for the future space competition among countries in the world.