Study On Control Technology For Satellite With Rapid Maneuver Missions

With the development of the aerospace technology, the requirement for satellite attitude control is getting stricter. At the same time with the development of space technology, requirements for spacecrafts with rapid maneuver ability become more and more intense.The design problem of variable structure control method for spacecraft attitude control systems is studied in the thesis. In the first place, the sliding mode control law of the system described by Euler angles is designed. The sliding mode variable structure is able to response quickly, invariant to systemic parameters and external disturbance, and able to keep the system asymptotic a stable state. Then the thesis deals with the sliding mode control law design of the systems described by quaternion mathematical models.In order to study new methods used in satellite attitude control, a satellite with rapid maneuver missions is discussed in this thesis. In the first place, in a classical control system a PD attitude maneuver controller based on reaction flywheel by using error quaternion is designed. Then the thesis deals with the sliding mode control law design of the systems described by quaternion mathematical models based on reaction flywheel and air-jet actuator. For both control laws, numerical simulation and a hardware in the loop simulation experiment is conducted with satisfactory result, which justifies the validity and the feasibility of the proposed method.Firstly, at the beginning of the thesis, several widely used reference coordinate systems and transformations among then are introduced according to the knowledge of the satellite. Methods to describe satellite attitude angles are introduced, by which attitude kinematics equations described by quaternion is given. Then the corresponding dynamic equations are given, which, together with the kinematics equations, constitute the whole mathematical model of flight attitude system.Secondly, considering complex project reality condition, by using attitude quaternion feedback control, a PD attitude maneuver controller based on reaction flywheel as actuator is designed. Based on Lyapunov stability theory and focusing directly at the error between reference quaternion and real attitude quaternion, switching functions of the variable structure controller based on reaction flywheel and air-jet actuator are designed to guarantee the stability of sliding modes. VSC law is designed by given switching functions to ensure that system state reach switching surface in finite time and keep within it thereafter. At the end of the paper, numerical simulation under a set of parameters is conducted to verify the feasibility of the proposed method.Finally, on the control experimental platform in laboratory, develop a hardware in the loop simulation experiment of uniaxial rapid maneuver attitude control based on1、reaction flywheel,2reaction flywheel and air-jet actuator.The experiment result proves the feasibility of the theoretical analysis and the system design, and the attitude maneuver control scheme that takes reaction flywheel and air-jet actuator as the actuator. Meanwhile, this experiment makes much contribution to the construction on the development of the laboratory.