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针对高超声速飞行器巡航段姿态稳定控制问题,提出了一种新的预测控制器设计方法。基于飞行器数学模型,引入参考模型,建立了飞行器姿态控制模型。应用预测控制理论,同时结合非线性干扰观测器实时观测外界干扰,设计了飞行器姿态预测控制器,使飞行器姿态角响应具有良好的动态特性与鲁棒性,并利用Lyapunov稳定性理论证明了整个系统的稳定性。最后,在高超声速飞行条件下进行了飞行器巡航飞行的数字仿真。仿真结果表明,所设计的姿态控制器可以满足高超声速飞行器巡航段的稳定飞行要求。
Aiming at the problem of attitude stability control of the hypersonic vehicle cruise segment, a new design method of predictive controller is proposed. Based on the aircraft mathematical model, the reference model is introduced and the attitude control model of the aircraft is established. Based on the theory of predictive control and the real-time observing of external disturbances by non-linear disturbance observer, the aircraft attitude predictive controller is designed so that the aircraft attitude response has good dynamic characteristics and robustness. The Lyapunov stability theory is used to prove that the whole system Stability. Finally, the digital simulation of aircraft cruise flight was conducted under hypersonic flight conditions. The simulation results show that the designed attitude controller can meet the stable flight requirements of the hypersonic vehicle cruise section.