Nonlinear H∞ Normal Matriz Attitude Control of Spacecraft
The attitude control problem for rigid spacecraft with disturbances is addressed. A feedback control law for rigid spacecraft attitude was proposed by combining the normal matrix design approach for robust control systems, the feedback perturbation description for systems uncertainties, and the Hamilton-Jacobi-Isaacs partial differential inequality for nonlinear H∞ control. The control law is built based on the normal matrix control theory, and the tuning guidelines are established by using the Hamilton-Jacobi-Isaacs inequality. The control law is H∞ solution for the linearized attitude dynamics and nonlinear H∞ solution for the nonlinear attitude motion of attitude tracking problem. Furthermore, no additional assumption about the inertia of spacecraft is needed in the designing process. Computer simulation are performed to demonstrate the effectiveness of the control law proposed.
Spacecraft Attitude control Robustness Hamilton-Jacobi-Isaacs partial differential inequality Normal matriz Feedback perturbation
CUI Ping-Yuan ZHU Hong-Yu
Deep Space Exploration Research Center, Harbin Institute of Technology, Harbin 150080, Heilongjiang, Deep Space Exploration Research Center, Harbin Institute of Technology, Harbin 150080, Heilongjiang,
国际会议
2009年中国控制与决策会议(2009 Chinese Control and Decision Conference)
广西桂林
英文
1404-1409
2009-06-17（万方平台首次上网日期，不代表论文的发表时间）