With Flexible Solar Panels, Three-axis Stabilized Satellite Attitude Control System Analysis And Design Studies

The paper deals with three-axe stabilized satellite with flexible solar arrays. The main objective is to apply robust control method to attitude control of three-axe stabilized satellite. In addition, the study of how to suppress attitude vibration caused by flexible solar arrays is another aim.Initially, the rigid body dynamics of three-axe stabilized satellite and flexure dynamics are introduced. The classical PD control law and Linear Quadratic Regulator then are respectively designed to stabilize rigid body attitudes. In order to compare control effect with subsequently obtained H∞ robust control law, there gives acertain degree of simulation analyses of the classical control law. Under a good many of supposed uncertainties and exterior disturbs, H∞ robust control laws to pitch axe and coupled roll and yaw axes are respectivelyobtained. Because arithmetic of H∞ robust control law is very difficult, control law will be obtained only when control object meet some premises, and it is also very difficult to choose appropriate weighting functions, there use a way in the paper to meet all those premises through enlarging control object. In comparison with choosing weighting functions, the way steers clear of abstraction and experience. Its metric can be especially embodied in multivariate control system. At last, there gives an overall comparison between classical control law and robust control method. The conclusion is that the H∞ robust control law are more superior in overcoming influence ofuncertainties especially exterior disturbs exist in control system to classical control law.It should be pointed out that uncertainties exist in control system stand in contradiction with system's stability and performance, though the H∞ robust control laws meet the need of robust stability , it weaken the system's dynamic performance. In addition, the orders of H∞ robust control laws are universally high, it need to be further studied.To flexible satellite, the paper lays stress on analyzing influence of solar arrays' anti-symmetry bend on satellite attitude. The simulation results are that under body control law, the flexible solar arrays cause serious vibration and overshoot of attitude. In order to weaken the vibration and overshoot, classical PD control in company with filter is applied. The method can diminish attitudes vibration and overshoot to a certain degree. In addition, there designed robust control law in the paper to flexible satellite through choosing weighting sensitivity function. Simulation effects indicate that robust control law is superior to classical control law preconditioned appropriate weighting functions must be chosen. But its control effect is not better than that of PD control law with filter. At last, there gives simple analyses about why weighting sensitivity function was modeled like that.There are two parts mainly involved in the paper:1. H∞ control theory and its application in attitude control of three-axe stabilized satellite;2. Analysis of flexure dynamics and study of its control method.