Dynamical Sliding Mode Control of Spacecraft Attitude Using SGCMG Systems
To solve the chattering problem in the conventional sliding-mode control, the dynamical sliding-mode control is adopted. Sliding function contains not only the error and high-order differential errors, but also the feedback of the control-output. The expression of the controller’s output is a dynamic differential equation which is about the errors and the controller’s output. In which way the control performance is also improved. This paper deals with the modeling and simulation of attitude maneuver control for spacecraft using Single Gimbal Control Moment Gyroscopes (SGCMG) systems. At first, the dynamical model of SGCMG and the attitude dynamic model of spacecraft were constructed. Based on the pseudo-inverse solution with least square norm, the steering law of SGCMGs was designed. A null motion was added into the control law so that any internal singularity of gimbal configurations was prevented. With virtual prototype technology, solves the conflict between the complex mathematical model and joint simulation. Based on the ADAMS and MATLAB, The united simulation system of attitude control for spacecraft with SGCMG systems is established. The simulation results show the efficiency of the dynamical sliding-mode controller, and validate the feasibility and advantages in improving the design efficiency of attitude control system with this method.
Zhen Chen XiangDong Liu YaPing Dai YongQiang Jin
Department of Automatic Control,Beijing Institute of Technology Beijing,100081,China
国际会议
深圳
英文
512-516
2008-12-10（万方平台首次上网日期，不代表论文的发表时间）