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为使飞机以足够高的准确度保持在预定飞行轨迹上,飞机俯仰角位移?的控制性能及稳态精度至关重要。为改进飞机俯仰角位移控制系统的控制性能,运用根轨迹法对飞机俯仰角位移控制系统的积分式控制规律进行了分析和设计,为提高?的稳态精度,基于SISO Design Tool设计工具,对俯仰角位移控制系统的零极点进行校正配置,实现了对飞机俯仰角位移控制系统积分式控制规律的改进设计。仿真结果表明,改进后的积分式控制规律使?控制系统的控制性能得以改善,所设计的改进型积分式控制规律是可行的和有效的。
In order to keep the aircraft on a predetermined trajectory with sufficient accuracy, the control performance and steady-state accuracy of the aircraft’s pitch-angle displacement are crucial. In order to improve the control performance of aircraft pitch angle displacement control system, the integral control law of aircraft pitch angle displacement control system is analyzed and designed by using root locus method. In order to improve the steady state accuracy, based on SISO Design Tool design tool, Pitch angle displacement control system of the zero-pole calibration configuration, to achieve the aircraft pitch angle displacement control system integral control law of the improved design. The simulation results show that the improved integral control law can improve the control performance of the control system. The improved integral control law is feasible and effective.