摘要
针对空天飞行器再入段环境变化剧烈、气动参数变化范围大的特点,采用参数空间方法来设计其控制系统;首先建立飞行器控制系统的数学模型,鉴于飞行器再入过程中对攻角有着严格的要求,设计了以攻角反馈为被控信号的三回路自动驾驶仪结构,然后根据参数空间方法求出对应的控制器参数,最后基于Matlab/Simulink的非线性仿真表明,所设计的控制系统在大气密度偏差±30%、气动力/力矩系数各偏差±20%的组合偏差情况下仍具有较好的鲁棒稳定性和跟踪性能。
Parameter space method is adopted to design reentry vehicle control system against the severe changing environment and great changes of aerodynamic parameters. First, the mathematic model is established. In view of reentry vehicle＇s need of strict angle of attack, an attitude control system with angle of attack feedback is proposed. Then parameter space method is used to calculate the controller parame- ters. Finally, the nonlinear simulation performed on the platform of Matlab/Simulink illustrated the excellent robustness and tracking per- formance of the proposed control system.
出处
《计算机测量与控制》
CSCD
北大核心
2012年第8期2187-2189,共3页
Computer Measurement &Control
关键词
空天飞行器
参数空间方法
控制系统
鲁棒性
aerospace vehicle
parameter space method
control system
robustness
