Attitude Control of Spacecrafts Based on Small-Gain Theorem

摘要：

　　A nonlinear attitude control law for spacecrafts is proposed based on small-gain theorem considering the effects of the control loop dynamics.The attitude angular rate commands,which are aimed at driving the attitude angles to the desired ones,are designed according to input-to-state stability(ISS)theory.Then,the small-gain theorem is iteratively used to propose the final torque input.It is shown that the attitude angles under the control law can robustly track the desired values,and the tracking errors are ISS with respect to disturbances.Simulation results have confirmed the effectiveness of the proposed scheme.

关键词： Attitude control generalized small-gain theorem input-to-state stability robustness

作者: YAN Han

作者单位: Science and Technology on Space Intelligent Control Laboratory,Beijing Institute of Control Engineering,Beijing 100190,China

会议类型: 国际会议

会议名称: The 33th Chinese Control Conference第33届中国控制会议

会议地点: 南京

会议语种:英文

页码: 3494-3499

在线出版日期: 2014-07-28（万方平台首次上网日期，不代表论文的发表时间）