Experimental Study On The Attitude Control Of Spacecraft With Flexible Solar Arrays

Large area flexible solar panel is common for large spacecraft installed components, under the conditions of structural damping coefficient is smaller. The lower modal vibration of the flexible solar panel will have an important impact on the attitude motion of stars. How to considering panels for low frequency mode under the condition of spacecraft attitude controller design is a very important precondition to realize the accurate control of the satellite attitude. The for a single flexible solar array of a class of spacecraft attitude control problem of the theoretical model and control strategy research, and the establishment of the single axis attitude control system simulation, by using the physical simulation experiment on the design of the controller for the experimental study.First, with flexible solar panels of the spacecraft considered as a rigid flexible combination system, under the integrated system to consider the attitude of a rigid body motion and flexible mode of using Lagrangian modeling method, establish the rigid flexible coupling attitude dynamics model; in order to reduce the dimensionality of the model and ensure the precision of the model, the modal truncation method of rigid flexible coupling dynamic model is simplified. Based on completed the analysis of the coupling relationship between rigid motion system and movement mode, laid the foundation for the further development of the design of the controller.Secondly, combined with the attitude stabilization of flexible spacecraft attitude maneuver control problem, a PD controller is designed for the commonly used, and in MATLAB to establish the corresponding closed-loop numerical simulation model and the numerical simulation is completed. According to the simulation results and then successively designed variable structure controller, quasi sliding mode variable structure controller and based on the exponential approach law of variable structure controller. Through the comparison of several kinds of controllers, the advantages and disadvantages of the controllers are analyzed, and the chattering phenomenon in the structure control is analyzed.Again, in order to improve the system dynamics model is not deterministic and variable structure control the chattering problem of process, the fuz-zy control and variable structure control the combination method are designed flexible spacecraft conventional fuzzy variable structure controller and based on reaching law of the fuzzy variable structure controller. Theoretical analysis and numerical simulation show that the controller combines the fuzzy and variable structure controller has the advantages, can effectively solve the kinetic model of uncertainty and change the chattering problem of structure control and maneuver time short, for each mode has very good inhibitory effect.For the validation of the proposed control method is effective, is designed in this paper and build the with flexible solar panel of single axis air bearing and the attitude experimental system, combined with the proposed controller mathematical model, completed the development of single axis air bearing table gesture to the experiment system of control software. Finally, the semi physical real-time simulation experiments of the proposed control method are carried out under the conditions of different simulation parameters. The experimental results show that the PID, sliding mode variable structure, fuzzy variable structure controller can effectively on the attitude and has higher control accuracy and reasonable response velocity, and numerical simulation results have good consistency. With the higher control precision and reasonable response speed, the results of numerical simulation analysis have good agreement.