Research On Fast Guidance And High Precision Tracking Control Scheme Of Micro Spacecraft

In recent years,the vigorous development of Chinese space industry has provided an important guarantee for dealing with various complicated and arduous space missions.The key technologies of Chinese space are constantly improving,and the research ideas of spacecraft will focus on "lighter,better,more economical." At the same time,the spacecraft needs to maintain high-precision maneuvering operations at very close distances when implementing tasks such as on-orbit assembly,space debris cleaning,rendezvous and docking.Especially in the face of noncooperative targets,the micro spacecraft need to have very accurate and fast maneuverability,which is also the current research hotspot in various countries.The use of separate control methods that ignore the coupling between orbit and attitude is no longer suitable for the precise modeling and control required to perform very close distances missions,especially for the non-cooperative target spacecraft.which needs large-angle maneuvers and fast tracking and orbital maintenance capabilities.In this context,closely surrounding the whole process of the small spacecraft guidance control scheme,this paper focuses on two key contents,the orbital maneuvering method for short range guidance and flying segment,and the integrated dynamics modeling and control method of attitude and orbit for high-precision tracking segment.For the research content of this topic,the general idea of the research is introduced.Firstly,the research status and progress of the key technology at home and abroad are analyzed.Then the related basic theories such as the attitude description methods,system stability analysis and sliding mode variable structure control of the spacecraft are introduced to.lay a foundation for the subsequent research.For the orbit transfer problem of the short-range guidance and flying segment of the spacecraft,the basic principle of orbital mechanics is used to transform the C-W equation into the expression form of the state transition matrix.Based on the doublepulse transfer maneuver strategy,a multi-pulse deceleration slip orbit transfer algorithm is proposed.Then analyze the form of pulse maneuvering flying and quickly complete the task of observing the target spacecraft.Finally,the correctness of the above method is verified by simulation.For the problem of modeling the attitude and orbit coupling dynamics of micro spacecraft,the mathematical tool of Lie group and Lie algebra is selected as the geometrical mechanics framework to describe the space motion of spacecraft.In the SE(3)space,the poses of the target spacecraft and the tracking spacecraft are respectively configured for the scenario,and the spacecraft dynamic models based on the special European group SE(3)is re-derived.These are the basis for the subsequent chapters of high-precision tracking segment sliding mode controller design.For the high-precision tracking control problem of athe micro spacecraft to the target spacecraft,a terminal sliding mode control scheme based on SE(3)is proposed to realize finite time tracking of target spacecraft under the framework of geometry mechanics.The terminal sliding surface and the adaptive fast terminal sliding surface are designed respectively,and the appropriate Lyapunov function is selected to prove the stability of the system.Finally,in the presence of external interference,the effectiveness of the above control algorithm is verified by numerical simulation,and the simulation results are compared and analyzed.