Design method of robust controller with compound root locus compensation for multi-loop models of aircraft

Abstract

The invention provides a method for designing an aircraft multi-loop model cluster composite root locus compensating robust controller. According to the method for designing the aircraft multi-loop model cluster composite root locus compensating robust controller, under the conditions of different given heights and different given Mach numbers, a model cluster formed by amplitude-frequency characteristics and phase-frequency characteristics in a full envelope curve is determined and acquired directly through frequency sweeping flight tests; according to requirements of military standards for amplitude-frequency margins and phase margins in a flight envelope curve, closed-loop pole distribution limiting indexes under corresponding root locus descriptions are given, the series and the parameter values of a multi-level series lag-lead compensating robust controller are determined by adding the multi-level series lag-lead compensating robust controller and through the closed-loop pole distribution limiting indexes in the full envelope curve of an aircraft and a model recognition method in system recognition, and the low-attitude flight robust controller which accords with the full flight envelope curve and is small in overshoot and stable is designed from the concept of closed-loop pole distribution limiting under the root locus descriptions.

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 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-low-altitude flight ...

AI Technical Summary

Problems solved by technology

[0006] In order to overcome the technical defect that the existing method cannot design a small overshoot and stable low-altitude flight controller that meets the stability margin index in the full flight envelope when the model of the aircraft varies greatly in the full flight envelope, the present invention Provides a method for designing a robust controller with complex root locus compensation for multi-loop model clusters of an aircraft. This method directly determines and obtains the amplitude frequency and phase frequency in the full envelope through frequency sweep flight tests under the conditions of given different altitudes and Mach numbers A model cluster composed of characteristics; according to the requirements of the military standard for amplitude-frequency margin and phase margin within the flight envelope, the closed-loop pole distribution limit index under the corresponding root locus description is given. By adding a multi-stage series lag-lead compensation controller And determine the series and parameter values ​​of the multi-stage series lag-lead compensation robust controller within the closed-loop pole distribution limit index and system identification in the full envelope of the aircraft; from the closed-loop pole distribution limit described by the root locus Design a robust controller for low-altitude flight with small overshoot and smoothness in line with the full flight envelope

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