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研究了高超声速飞行器大跨度飞行条件下的俯仰通道姿态控制问题。首先,建立了高超声速飞行器俯仰通道姿态运动模型。然后,针对高超声速飞行器俯仰通道模型非线性、不确定性等特点,应用模糊控制和模型参考自适应控制方法,设计了俯仰通道的模糊模型参考自适应控制器:以参考模型和实际系统的误差及其变化率作为模糊控制器的输入,以PID控制参数的修正量作为模糊控制器的输出,通过在线调节PID参数实现自适应控制。最后,对俯仰通道姿态控制方法进行了数值仿真。当模型发生切换时,俯仰角发生变化,能够在2s内精确跟踪参考模型,且稳态误差趋于0,验证了控制方法的有效性。
The attitude control of pitch channel under the condition of long-span flight of hypersonic vehicle is studied. First, the model of hypersonic vehicle pitch channel attitude movement is established. Then, based on the nonlinearity and uncertainty of hypersonic vehicle’s elevation channel model, a fuzzy model reference adaptive controller of pitch channel was designed by using fuzzy control and model reference adaptive control method. The reference model and actual system error And its rate of change as a fuzzy controller input to the PID control parameter correction as the output of the fuzzy controller through the online adjustment of PID parameters to achieve adaptive control. Finally, numerical simulation of pitch channel attitude control method is carried out. When the model is switched, the pitch angle changes, the reference model can be accurately tracked within 2s, and the steady-state error tends to 0, which verifies the effectiveness of the control method.