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针对高超声速飞行器存在模型参数不确定和外部干扰的特点,提出了一种自适应滑模变结构控制律设计方法。首先,结合高超声速飞行器数学模型,在引入参考模型的基础上,建立了跟踪误差模型;然后,基于该控制模型设计自适应滑模变结构控制律;最后,对该控制算法的有效性进行了仿真验证。仿真结果表明,所设计的滑模变结构控制系统对高超声速飞行器具有良好的控制效果,可以满足速度和高度精确跟踪控制的要求,并具有较强的鲁棒性。
Aimed at the uncertainties of model parameters and external disturbances of hypersonic vehicles, a design method of adaptive sliding mode variable structure control law is proposed. Firstly, based on the introduction of the reference model, the tracking error model is established based on the mathematical model of the hypersonic vehicle. Then, an adaptive sliding mode variable structure control law is designed based on the control model. Finally, the effectiveness of the control algorithm Simulation. The simulation results show that the designed sliding mode variable structure control system has good control effect on hypersonic vehicle, which can meet the requirements of speed and highly accurate tracking control and has strong robustness.