Trajectory Design And Optimization For Space Debris Recycling

With the expansion of human’s space activities in space, the space environment isgetting more and more deteriorated due to the increase of space debris. Space debris areposing serious threat to in-orbit spacecrafts, that would greatly restrict further humanspace exploration. On one hand, the study of space debris recycling can directly help toreduce space debris. On the other hand, this study can predict the distribution model ofthe space debris and analyze the debris impact effect on human being activities on earth,forming the foundation of the risk assessment and guidelines for optimal structure designof the spacecraft. Therefore, the space debris recycling has significance. This objective ofthis article is to study space debris recycling trajectory optimal design methods. Thespace debris recycling trajectory includes the capture orbit and the reentry trajectory. Thecapture orbit is the obit for collector rendezvous the space debris. The paper is organizedas follows:First, we introduced the relevant background knowledge, including the spacedebris, genetic algorithm, space rendezvous. We illustrated the advantages of geneticalgorithm in solving the complex problem of space debris recycling trajectoryoptimization. Lambert rendezvous problem has been discussed in detail, iterativemethods and genetic algorithm was provided to solve this computing model.Second, based on Lambert rendezvous, the single-target rendezvous computingmodel has been established. Using genetic algorithms, the waiting time and transfer timeof the collector are viewed as independent variables. The necessary energy and time ofspacecraft to maneuver as comprehensive weight are the performance indicators foroptimize of the rendezvous. Single target intersection model based on single-targetrendezvous, the computational models and optimization methods of the multi-target arerendezvous established. The simulation results for the optimization of single-target rendezvous and multi-target rendezvous has been given.Finally, we gave a brief introduction to the kinematic model, constraints andoptimization method for the collector reentry orbit.This paper mainly used the genetic algorithm to optimize the capture orbit of thespace debris recycling trajectory, respectively. Single-target recycling and multi-targetrecycling are obtained computing model and optimization methods was given. Theoptimization results were computed. The simulation results showed that the multi-targetrendezvous optimal problem can be solved accurately and effectively by our method.