摘要
在再入过程中高超声速飞行器存在着多约束,包括角度,角速度,力矩约束,提出一种约束非线性控制方法.基于奇异摄动理论设计内外环解耦控制方案,控制系统的外环基于近似连续非线性预测控制和滑模预测实现角度跟踪,满足角速度约束和闭环稳定.强耦合的内环采用动态逆跟踪角速度指令,期望动力学采用PI形式抑制干扰,采用抗饱和技术在线调整控制参数,减少力矩饱和,提高内环的跟踪性能.最后,通过仿真验证了所提算法的有效性.
A nonlinear control method is presented for nonlinear attitude dynamics of a reentry hypersonic vehicle with constraints,including attitude angle,attitude angular velocity,moment constraints.The dynamics is separated into fast and slow loops as attitude angular velocity and attitude angle based on the singular perturbation theory.In the out-loop,continuous nonlinear predictive control and sliding mode predictive control laws are used to implement the attitude to meet angular velocity constraint and closed-loop stability.In the in-loop system with strongly coupling aerodynamic coefficient,control vector is solved explicitly by nonlinear dynamic inversion,the desired dynamics is designed by using the proportional plus integral controller,and the adaptive anti-saturation is used to reduce moment saturation.Finally,the effectiveness of the proposed algorithm is verified by simulation.
出处
《空间控制技术与应用》
2011年第3期35-40,共6页
Aerospace Control and Application
基金
江苏大学高级专业人才科研启动基金资助项目(10JDG074)
关键词
高超声速飞行器
姿态控制
预测控制
动态逆
hypersonic vehicle
attitude control
predictive control
dynamic inversion
