Method for designing flutter-suppression composite root locus compensation robust controller for multi-loop model cluster of aircraft

Abstract

The invention provides a method for designing a flutter-suppression composite root locus compensation robust controller for the multi-loop model cluster of an aircraft. The method comprises the following steps of: directly determining to acquire the model cluster composed of amplitude-frequency and phase-frequency characteristics in a full envelope by virtue of a sweep-frequency flight test in different given heights and Mach number conditions; giving a closed-loop pole distribution limit index under the corresponding root locus description according to standard requirements on an amplitude-frequency margin and a phase margin in a flight envelope, determining the stage number and parameter values of the multi-stage serial lagging-leading compensation robust controller by adding the multi-stage serial lagging-leading compensation controller, and by virtue of the closed-loop pole distribution limit index in the full envelope of the aircraft and a model identification method in system identification; and designing the low-altitude flight robust controller meeting the full flight envelope, capable of suppressing flutter, low in overshoot and stable from the concept of closed-loop pole distribution under the root locus description.

Description

technical field [0001] The invention relates to a design method of an aircraft controller, in particular to a design method of a multi-loop model cluster flutter suppression compound root locus compensation robust controller of an aircraft, and 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-...

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Problems solved by technology

[0006] In order to overcome the fact that the existing method cannot design a stable low-altitude flight controller that meets the stability margin index in the full flight envelope and can suppress flutter when the model of the aircraft changes greatly in the full flight envelope Technical defect, the present invention provides a kind of multi-loop model cluster flutter suppression compound root locus compensation robust controller design method, the method is directly determined by sweeping flight test under the given different altitudes and Mach numbers The model cluster composed of amplitude-frequency and phase-frequency characteristics in the line; according to the military standard requirements of amplitude-frequency margin and phase margin in the flight envelope, the closed-loop pole distribution limit index under the description of the corresponding root locus is given. By adding multiple Stage series lag-lead compensation controller and the closed-loop pole distribution limit index in the full envelope of the aircraft and the model identification method in system identification determine the series and parameter values ​​of the multi-stage series lag-lead compensation robust controller; from the root Based on the concept of the closed-loop pole distribution limit under the trajectory description, a low-altitude flight robust controller that can suppress flutter, have small overshoot, and be stable is designed in line with the full flight envelope

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