飞机俯仰角位移控制系统积分式控制规律的改进及仿真

Simulation and Improvement Design on the Integral Control Law of Aero Pitch Angle Control System

摘要:

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。

Abstract:

It is very important for the aero pitch angle control system’s control performance and steady state accuracy, to keep the airplane in scheduled flight track with enough accuracy. In order to improve the lengthways stability, the maneuverability and the mobility of the airplane, taking the airplane’s short period movement as the example, based on MATLAB simulation platform, the design and the simulation research on the control law of integral autopilot were carried on with root-locus method. In addition, adjuster achieved easily in engineering was designed with SISO Design Tool to ameliorate the system by collocating zero pole placements and to improve the control law of integral autopilot. The simulation results indicated that the ameliorated system had obtained the more satisfying capability by the improved control law, also validated the feasibility and advantage of the improved control law.