摘要
研究气动特性是飞行器姿态稳定性的保证,高超声速飞行器采用姿态控制有助于提高作战效能及生存能力。针对高超声速飞行器作战环境复杂,大气密度偏差大、力/力矩系数不准确造成气动参数偏差较大等特点,采用参数空间方法来设计姿态控制系统。首先建立适用于姿态控制系统的高超声速数学模型,在高超声速气动特性条件下,提出三回路姿态稳定控制系统,根据参数空间方法的原理设计出各回路控制器,最后进行仿真分析验证控制系统的性能。仿真结果表明当气动参数存在较大偏差时,采用基于参数空间法设计的高超声速姿态控制系统可以确保对指令的精确跟踪,并且具有较强的鲁棒稳定性。
Attitude control system of hypersonic vehicle can improve its campaign efficiency and survival capability.In view of the complicated flight conditions and great changes of aerodynamic parameters of hypersonic vehicle,because the density of atmosphere,the coefficient of force and moment great change,parameter space method is used to design the attitude control system.In this method,the mathematic model of attitude control system is built,and an attitude control system is proposed based on the hypersonic aerodynamic characteristics.Then parameter space method is used to caculate the controller parameters.Finally,performance of control system is validated through simulation analysis.The result of simulation shows that the attitude control system of hypersonic vehicle based on the parameter space method ensures that its tracking performance is accurate and robust when great changes of aerodynamic parameters exist.
出处
《计算机仿真》
CSCD
北大核心
2011年第8期33-36,46,共5页
Computer Simulation
