Backstepping based Finite-time Control for the Spacecraft Attitude Tracking Control with uncertainties

摘要：

　　The issue of attitude tracking control with finite-time convergence is investigated based on backstepping method for the spacecraft in presence of external disturbance and uncertain actuator configuration.More specifically,the attitude quaternion can track the demanded command in finite time under the virtual control law by introducing a terminal sliding manifold.Then,the finite-time convergence to the sliding mode of the angular velocity error will be achieved under the proposed novel finite-time control and parameter adjusting law.In addition,the finite-time stabilization/convergence of the sliding surface and the spacecraft attitude tracking error have been proved and analysed using the Lyapunov method theoretically.Finally,numerical simulation results are presented to illustrate the performance of the proposed scheme.

关键词： Spacecraft Finite-time control Backstepping Terminal sliding mode control

作者: YU Yanbo LI Li LI Bo HU Qinglei

作者单位: Department of Control Science and Engineering,Harbin Institute of Technology,Harbin,150001,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: 59-64

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）