Design method of longitudinal flight model cluster flutter-suppression composite root-locus multi-level PID (proportion integration differentiation) robust controller

Abstract

The invention provides a design method of a longitudinal flight model cluster flutter-suppression composite root-locus multi-level PID (proportion integration differentiation) robust controller. The design method includes: directly determining and acquiring a model cluster which is 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; according to military standard requirements on amplitude-frequency margin and phase margin, providing the closed-loop pole distribution limit index corresponding to root-locus description, determining number of levels and parameter values of the multi-level PID robust controller by a model identification method applied to system identification according to requirements of the closed-loop pole distribution limit index within the full envelope of an aircraft after adding the multi-level PID controller; designing the small-overshoot stable low-altitude flight controller capable of suppressing flutter and meeting requirement of the flight full envelop from the concept of root-locus description based closed-loop pole distribution limit.

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 flutter suppression compound root locus multi-stage 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-l...

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