航天器姿态控制系统的退步控制设计方法  

Spacecraft Attitude Control System Design via Backstepping Method

作　　者：郑敏捷[1] 徐世杰[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《飞行力学》2005年第4期63-66,共4页Flight Dynamics

摘　　要：研究了航天器的姿态控制问题。考虑了飞轮作为执行机构的姿态动力学模型,应用退步控制理论设计了姿态控制算法。该算法克服了飞轮的电机滞后带来的影响,保证了姿态控制系统对指令信号的跟随。对所设计的控制律进行了数值仿真。仿真结果说明了所设计的控制律的有效性。The spacecraft attitude control system is designed via a backstepping method, considering the attitude dynamic model on conditions that flywheels are adapted as actuatoss. The derived algorithm overcomes the negative effects brought by the sluggish motors of flywheels and guarantees excellent tracking character of the attitude control system. Numerical simulation is performed to show the effectiveness of the proposed controller.

关 键 词：姿态控制 退步控制 飞轮 电机模型 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]