Research On Spacecraft Rendezvous Control Problem Based On Sliding Mode Control Technology

Spacecraft rendezvous is one of the most important tasks during spacecraft operation.In the actual use of spacecraft,spacecraft rendezvous and docking can achieve basic goals such as fuel supply and information communication,providing a solid foundation for the smooth operation of spacecraft in orbit in the future.At present,China’s Tiangong program also extensively applies rendezvous and docking process control methods,providing sufficient accumulation basis for subsequent space station and solar system plans.In this paper,the mathematical model is established for the spacecraft rendezvous phase,and the sliding mode control technology is used to study the Robust control technology for the spacecraft rendezvous process,so that the tracking spacecraft can track the corresponding target spacecraft trajectory when there is interference.At the same time,Matlab is used for simulation and verification.The first chapter introduces the research background,current research status at home and abroad,and the significance of the research topic.In this chapter,the value of spacecraft rendezvous and docking for technology,countries,and individuals is introduced.Our current goal path for spacecraft rendezvous and docking is introduced,and the development history of relevant research abroad is introduced.The structure of the entire article is arranged.Secondly,the definition and classification of spacecraft rendezvous were introduced,and the steps of rendezvous were introduced from a definition perspective.In addition,the relevant theories of sliding mode control technology were introduced,with a focus on several common sliding mode control methods,including terminal sliding mode,fast terminal sliding mode,non singular terminal sliding mode,and integral sliding mode.Once again,a non singular terminal sliding mode control scheme is proposed based on sliding mode control for spacecraft rendezvous control systems with disturbances,fully considering the influence of internal uncertainties.Enable the spacecraft rendezvous system to stabilize in a finite time and improve the fast convergence of the spacecraft rendezvous process.Finally,the effectiveness of the designed method was verified through simulation.Finally,a non Singular integral terminal sliding mode control strategy is designed for the spacecraft rendezvous control system model with external disturbances.Because the traditional terminal sliding mode control has the disadvantages of long convergence time and large error,we introduce the non Singular integral terminal sliding mode control method to deal with this problem,which makes the spacecraft rendezvous process have more superior control effect.Finally,the effectiveness of the designed method was verified through simulation.