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.
出处
《飞行力学》
CSCD
北大核心
2005年第4期63-66,共4页
Flight Dynamics
关键词
姿态控制
退步控制
飞轮
电机模型
attitude control
backstepping control
flywheel
motor model
