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本文首次讨论并给出了利用星上GPS输出反馈,来实现卫星大角度姿态机动的自主非线性状态跟踪控制系统的设计。其中包括非线性状态反馈控制器的设计以及利用星上GPS伪距测量输出信息,采用修改的罗格里德参数描述姿态状态方程,实现星上实时状态跟踪控制的非线性估计器的设计。文中以EO-1/LandSat7卫星编队飞行为背景,给出了姿态测量信息的获取、姿态状态估计和实时跟踪控制的数学仿真结果,验证了控制系统设计的可行性和正确性,精度指标满足要求。
This paper discusses for the first time and presents the design of an autonomous nonlinear state tracking control system that uses the satellite GPS output feedback to realize maneuvering of large-angle attitude satellite. Including the design of nonlinear state feedback controller and the design of nonlinear estimator which uses the pseudo-range of satellite to measure the output information, uses the modified Logge parameter to describe the attitude equation and realizes the real-time state tracking control on the satellite. In this paper, based on the EO-1 / LandSat7 satellite formation flight, the mathematical simulation results of attitude measurement information acquisition, attitude state estimation and real-time tracking control are given. The feasibility and correctness of the control system design are verified. The accuracy index meets the requirements .