The Study On The Rapid Maneuvre And Stabilization Of Small Satellite Attitude Controlapproaches

In satellite missions of ground observation, such as staring at a specific target for a long time, in-line array camera, the increase can be observed three-dimensional imaging and range, requires that the satellites attitude have the ability of rapid maneuver and rapid stability, known as Attitude agility. Attitude agility includes rapid maneuver, rapid stable, and the stability of the process of rapid maneuver. Different missions require different type of attitude agility. In this paper, these three aspects of how to control law design studies were carried out to study, the contents include:Focusing on the problem of rapid mobility for satellite attitude control, using the feature of great torque the double gimbal control moment gyroscope (DGCMG) can provide, we take DGCMG as the executor of the attitude rapid maneuver. Firstly, according to optimal control theory, we design a control law which contains a lot of constraints it can be desolved by gauss pseudospectral method. Secondly, taking the optimal curve as a foundation resulted in the optimal control law, a tracking control law based on Lyapunov stability theory is designed here.Focusing on the problem of rapid stability for satellite attitude control, three control laws are designed. Owing to attitude precision requirements, reaction flywheels are chosen as the executor. Based on the satellite feture model, an adaptive control law is designed to stabilize the satellite attitude rapidly, which can suppress the vibration of the satellite. The second control law, based on the time scale separation principle and predictive control, separate the satellite attitude control as angle control and angular velocity control. Using boundedness of the hyperbolic tangent function and considering the flywheel output capacity constraints, the third law avoid the flywheel uninstall largely.Focusing on the problem of stability in the process of rapid maneuver, attitude stability in the process of rapid maneuver is defined at first, an expression of attitude stability is given which can be combined with optimal control, making stability as t optimal control objective. Finally, a time scale separation principle is designed here. The outer ring of the desired angular velocity and the tracking control law is obtained in the inner controller. Simulation results show that in satellite large angle attitude maneuver process, the angular rate of change is very small, and it can be achieved by adjusting the control parameter stability and stance balance between rapid mobility and stability。...