The Research Of Large Angle Maneuver Attitude Control For Spacecraft

This paper takes a large-angle attitude maneuver teaching experiment of spacecraft based on DSP control experimental platform as a background. According to the feature that large-angle attitude maneuver control is nonlinear, strong coupled and includes uncertain parameters, simulation and experiments are taken for the nonlinear design method of large-angle attitude maneuver control system based on reaction flywheel by using the Lyapunov theory, the variable structure control theory for nonlinear systems and the inverse dynamic decoupled method.Firstly, on the basis of building an attitude maneuver control system model based on reaction flywheel by using error quaternion, the attitude maneuvering is converted into the adjusting of the error quaternion. The paper gives the analysis of the model uncertainty and the proof of the computational relationship characters in the model.Secondly, the scalar gain linear control law and the matrix gain nonlinear control law that are independent of the model are separately designed using the Lyapunov method. The global asymptotic stability of the closed-loop control system at the laws is analyzed and proved in theory. The control laws in different conditions and forms are simulated in Matlab, and it gives the performances of the control system under different laws. The simulation result reveals that the designed control system has better robustness to the model uncertainties and the external disturbances.Thirdly, it gives a research on the methods of designing the control law based on the variable structure and the inverse dynamic decoupled theory. The switching manifold is designed using the quadratic optimal method, and the stability of the sliding mode is proved. Based on the exponential approach law, the paper gives the deducing of the sliding mode control law and its robustness analysis. Considering that the large-angle maneuver has strong coupling, the system is nonlinearly decoupled firstly using the inverse dynamic decoupled method, and then the controller is designed based on the robustness of the variable structure control. Simulation on the designed control system gives the performances of different control law. The result indicates that the law has global asymptotic stability and better robustness.Finally, on the basis of existing large-angle maneuver control experimental platform based on air-jet actuator in laboratory, develop a hardware in the loop simulation experiment of uniaxial large-angle maneuver attitude control based on reaction flywheel. The experiment result proves the feasibility of the theoretical analysis and the system design, and the large-angle attitude maneuver control scheme that takes reaction flywheel as the actuator. Meanwhile, this experiment provides a better experiment platform for the course of attitude control of space vehicle, and makes much contribution to the speciality construction on the development of the DSP experimental platform for large-angle maneuver attitude control.