Research On Rapid Attitude Maneuver And Stabilization Control Method For Statellites

The complexity of space missions requires higher agile performance of satellites; especially, the satellite’s large angle maneuver and rapid stabilization is of great significance for a satellite in orbit. As an excellent and effective device of angular momentum exchange, Single Gimbal Control Momentum Gyroscope(SGCMGs) has the ability to provide larger torque with the same weight of reaction wheel; meanwhile, its electricity consumption also extends the life span of the satellite in orbit compared with thrusters. Therefore, SGCMGs has drawn more and more attention nowadays. Focusing on the rapid attitude maneuver and stabilization control method of satellites, this paper selects SGCMGs as the satellite attitude adjustment actuator, plans its guidance law, designs a sliding mode variable structure attitude control law to track the guidance law and finally sets up the simulation to verify the system.The main contents of this dissertation are summarized as follows:Firstly, this paper reviewed the development of agile satellite at home and abroad and introduced some examples, analyzed the performance of the current mainstream satellite attitude adjustment actuator and summarized the control algorithm. This paper established the satellite attitude kinematics mod el on Euler angles and quaternion, and then established the satellite dynamics model on rig id satellite.Secondly, this study probed the issue of inherent singularity and steering strategies. The present paper introduced the basic working principle and common structure of SGCMGs, analyzed the inherent singularity problem and realized the singularity visualization to make the problem clearer. SGCMGs singularity measure was determined. Based upon gimbal angular velocity, several singularity avoidance and escape steering strategies were designed and testified to make sure that SGCMGs can provide the desired torque even in singular gimbal angle configuration.Third, this paper investigated the issue of satellite’s large angle maneuver and rapid stabilization, i.e. the satellites attitude guidance law. Taking consideration of multiple constraints of satellite attitude adjust, this paper transform ed the problem into optimal control, discretized and transcribed the optimal control problem to a nonlinear programming(NLP). The attitude guidance law was gotten by Hp pseudospectal method. This path significantly reduced the possibility of SGCMGs reaching singular state and realized the maneuver task that the initial and final velocities are nonzero.Finally, this study researched on large angle maneuver and rapid stabilization control scheme. The study put forward control process with path planning, built a nonlinear satellites model based on error quarnions and error velocities, design the PD control law the siding mode variable structure law to track the desired guidance law, and then set up the simulation to verify the system.