Finite Time Control Of Rendezvous And Docking Of Rigidbody Spacecraft Considering Actuator Failure

Extreme outer space environment and spacecraft itself hardware components used by the life of the restrictions,will greatly increase the risk of the stability of the orbiting spacecraft into space,the risk often comes from the spacecraft actuator failure,and actuator failure problems due to the particularity of orbiting spacecrafts and is almost inevitable,will directly affect the overall stability of the control system of spacecraft performance and even lead to serious consequences such as failure directly.Among all the causes of spacecraft control system failure,at least 44% are caused by factors related to the failure of spacecraft actuators.At the same time,in the process of spacecraft rendezvous and docking,the requirements for the stability of the spacecraft are more stringent than that of a single spacecraft in normal orbit.In other words,the fault-tolerant control system of spacecraft rendezvous and docking requires shorter stability time and less fluctuation compared with the general fault-tolerant control system of spacecraft.Therefore,when studying the controller of spacecraft rendezvous and docking process,it is necessary to fully consider the possible failure of the actuator in advance.Similarly,this has great academic and engineering significance for improving the operational stability and mission completion efficiency of on-orbit spacecraft in the complex and changeable outer space environment.Based on the analysis of the above situation,two sliding mode surfaces,linear sliding mode surface and terminal sliding mode surface,are adopted in this paper.The fault tolerant controllers of spacecraft rendezvous and docking attitude and orbit based on linear sliding mode surface and finite time stable fault tolerant controllers of spacecraft rendezvous and docking attitude and orbit based on terminal sliding mode surface with actuator fault are designed respectively,and their stability is verified.The attitude and orbit control problems of rendezvous and docking of rigid spacecraft under the condition of failure of the actuator are solved perfectly.At last,the stability of the spacecraft attitude and orbit control system under the condition of the actuator’s complete health and partial failure is analyzed in detail.