Study On The Trajectory Optimization Of Rapid Space Debris Capture Based On Traveling Salesman Problem

Space activities have become more and more frequent,advancing the development of the space industry.At the same time,the space environment has been seriously polluted with a large amount of space debris around our earth.The velocity of space debris is too fast to keep the spacecraft safe,destroying the structure of the spacecraft,penetrating the surface of the spacecraft,changing the flight path of the spacecraft.There have been a number of debris collisions in space.Each hit produces more debris,which makes the spacecraft more dangerous.For the capture of space debris,one fragment in a mission is too expensive,not conducive to the realization of economic goals.For economic reasons,spacecraft often have to capture multiple space debris in limited time.In practical application,the mode of pulse maneuver is more common.Impulse thrust can solve most of the space problems,but usually there is no limit to the time of flight of the spacecraft.For some important spacecraft,especially some spacecraft which have important military roles,they need complete missions in a very short time.In this case,they need to quickly clean up the debris on the track.Impulse thrust maneuver is often difficult to achieve the purpose of the"quick clean".Therefore,based on the "quick clean" background,this paper mainly considers the fast capture problems establishing orbital dynamics under continuous thrust and giving the optimal control equation.Put forward the bi-level optimization model composed of inner optimization and outer optimization.The inner optimization is based on the active-passive rendezvous.Formulate different strategies according to different debris orbit initial parameters and set up different consumption matrix.Outer optimization is based on inner optimization results and Traveling Salesman Problem,taking the path optimization of particle swarm optimization.After the outer optimization the optimal capture path is determined.Then the capture spacecraft begins to capture all the space debris according to the optimal path.Based on this,the effects of the mass of debris on capture order and orbital optimization are preliminarily studied.In the end,the COSMOS debris are studied and then 10 debris are chose randomly from COSMOS.This paper aims to realize the trajectory optimization of fast capture of debris by establishing the computational model,selecting the suitable algorithm and getting the result.Result shows that the use of double-layer optimization model can optimize the fast capture orbit.The optimization result has high stability and credibility.Debris mass has certain influence on fuel consumption.Mass must be considered when the mass of debris is on the same order of magnitude of spacecraft and the mass of each debris varies greatly.