Design method of longitudinal flight model cluster man-machine closed-loop PID (proportion integration differentiation) robust controller

Abstract

The invention provides a design method of a longitudinal flight model cluster man-machine closed-loop PID (proportion integration differentiation) robust controller. The design method includes: directly determining and acquiring a model cluster constituted according to amplitude-frequency and phase-frequency characteristics within the full envelop through sweep flight tests on set conditions of different heights and different Mach numbers; directly determining open-loop cutoff frequency range according to amplitude frequency characteristics within the flight envelop; directly determining a phase margin range corresponding to the cutoff frequency range according to phase frequency characteristics within the flight envelope; determining number of levels and parameter values of a multi-level PID robust controller by a model identification method applied to system identification according to requirements of the phase margin index within the full envelope of an aircraft after adding the multi-level PID controller; verifying effect of the controller on the condition of the given decibels of the amplitude margin index within the full envelop of the aircraft; designing the small-overshoot stable low-altitude flight controller capable of avoiding pilot induced oscillation and meeting requirement of the flight full envelop from the concepts of the phase margin and the amplitude margin.

Description

technical field [0001] The invention relates to a design method of an aircraft controller, in particular to a design method of a longitudinal flight model cluster man-machine closed-loop PID robust controller, which belongs to the categories of measurement and control technology and flight mechanics. Background technique [0002] The control of the take-off and landing process of the aircraft plays an important role in flight safety; due to the large change in flight speed during the take-off and landing process of the aircraft, even according to the longitudinal model, it will face strong nonlinear problems; on the other hand, the control rudder of the aircraft has saturation, dead zones, etc. Phenomenon; From the perspective of flight safety, when flying at ultra-low altitudes (such as aircraft takeoff / landing), the controller must ensure that the system has a certain stability margin, no overshoot and stability, which makes the design of ultra-low-altitude flight controlle...

AI Technical Summary

Problems solved by technology

[0010] In order to overcome the fact that the existing method cannot design a stable low-altitude flight controller with no pilot-induced oscillation, small overshoot, and a stable low-altitude flight controller that meets the stability margin index in the full flight envelope when the aircraft model changes greatly in the full flight envelope Due to technical defects, the present invention provides a method for designing a longitudinal flight model cluster man-machine closed-loop PID robust controller. The method directly determines and obtains the full envelope by sweeping flight tests under the conditions of different altitudes and Mach numbers. A model cluster composed of amplitude-frequency and phase-frequency characteristics; directly determine the open-loop cut-off frequency interval according to the amplitude-frequency characteristics within the flight envelope; directly determine the phase margin interval corresponding to the cut-off frequency interval according to the phase-frequency characteristics within the flight envelope ; Determine the number of stages and parameter values ​​of the multi-level PID robust controller by adding the multi-level PID controller and the phase margin index in the full envelope of the aircraft and the model identification method in the system identification; Amplitude Margin Index L * Under the condition of given decibel number, the controller effect verification is carried out; starting from the concept of phase margin and amplitude margin, a robust control for low-altitude flight with no driver-induced oscillation, small overshoot, and stability is designed in line with the full flight envelope device

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