基于LQR/PID控制飞机俯仰角的仿真研究

Simulation Research of Aircraft Pitch Angle Control Based on LQR/PID

由于周围环境等诸多因素,飞机会受到干扰和噪声的影响,从而导致系统的振动、稳态误差和响应时间的延长.因此,飞机纵向控制阶段需要将实际俯仰角的值保持在所需设定值附近.在MATLAB仿真环境中建立飞机俯仰角模型,分别设计LQR控制器和PID控制器实现飞机俯仰角控制.LQR控制器通过MATLAB仿真实现参数设置,加入预补偿器后得到最优响应.分别从P控制器、PI控制器、PID控制器3种方式逐步分析,得到相应的响应波形,并加入扰动测试,PID控制器可以得到最佳响应.仿真结果显示:加入LQR和PID控制器后,系统到达稳态的时间缩小,超调量、稳态误差减小,可见LQR和PID控制方法可使俯仰角达到良好的控制效果,为飞行器的平稳运行提供参考.

Because of the influence of environment and other factors,aircraft will be affected by interference and noise,which will lead to the system vibration,steady-state error,and the extension of response time.Therefore,the actual pitch angle should be kept near the desired setting value in the longitudinal control phase.The aircraft pitch angle model is established in the MATLAB simulation environment,and the LQR controller and PID controller are designed to control the aircraft pitch angle,respectively.Firstly,the LQR controller realizes the parameter setting through MATLAB simulation,and the optimal response is obtained by adding the pre-compensator.Secondly,the corresponding response waveform is obtained by analyzing the P controller,PI controller and PID controller step by step,and the optimal response can be obtained by adding the disturbance test to the PID controller.The simulation results show that with the adding of LQR and PID controllers,the time to steady state of the system is reduced,the overshoot amount and the steady-state error are reduced.It can be seen that LQR and PID control methods can achieve good control effect of pitch angle,which provides some references for the smooth operation of aircraft.