摘要
该文简要介绍了航天器姿态控制的基本理论。利用李雅普诺夫稳定性理论,设计了一种误差受限航天器姿态跟踪控制器。并就跟踪任务进行了数字仿真,通过与基本控制器的对比,验证了误差始终处于给定限制范围内,证明了方案和控制器的可行性。
The paper describes the foundation theory of attitude control briefly. According to the Lyapunov Stability Theory, an error-- constrained controller for attitude tracking is designed herein. The controller is verified by Simulink that the tracking error is constrained within the given limit, in contrast to the basic controller.
出处
《科技创新导报》
2013年第15期54-57,共4页
Science and Technology Innovation Herald
关键词
误差受限
姿态跟踪
控制器
error constrained attitude tracking controller
