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Method for designing aircraft multi-loop model cluster composite root locus compensating controller

A technology of compensating controllers and design methods, applied in the direction of adaptive control, general control system, control/regulation system, etc., which can solve the problem of designing overshoot and so on

Active Publication Date: 2014-05-28
XIAN FEISIDA AUTOMATION ENG
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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 composite root locus compensation controller for a multi-loop model cluster of an aircraft. This method directly determines and obtains the amplitude-frequency and phase-frequency characteristics within the full envelope through frequency-sweeping flight tests under the conditions of different altitudes and Mach numbers. According to the military standard requirements of amplitude-frequency margin and phase margin within the flight envelope, the closed-loop pole distribution limit index under the description of the corresponding root locus is given. By adding a multi-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 the system identification determine the series and parameter values ​​of the multi-level series lag-lead compensation controller; the concept of the closed-loop pole distribution limit under the description of the root locus is designed. Small overshoot and stable low-altitude flight controller in line with the full flight envelope

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  • Method for designing aircraft multi-loop model cluster composite root locus compensating controller
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  • Method for designing aircraft multi-loop model cluster composite root locus compensating controller

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Embodiment Construction

[0038] Step 1. Use a linear frequency sweep signal at different altitudes and Mach numbers (f 0 is the starting frequency, f 1 is the cut-off frequency, r=(f 1 -f 0 ) / T, T is sweep time) or logarithmic sweep signal f(t)=A(t)sin{2πf 0 / r·[exp(rt)-1]} (f 0 is the starting frequency, f 1 is the cut-off frequency, r=ln(f 1 / f 0 ) / T, T is the frequency sweep time) to excite the aircraft, the amplitude-frequency and phase-frequency characteristics in the full envelope of the allowed flight can be directly obtained, and the flutter frequency of the aircraft can be obtained across the flight envelope to obtain the corresponding aircraft control The open-loop transfer function model cluster matrix between the rudder surface and the flight height is:

[0039]

[0040] Among them, G is an m×m square matrix, m>1 is a positive integer, s is the independent variable of Laplace transform, h is the flying height of the aircraft, M is the Mach number, P is the m×m single-mode squar...

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Abstract

The invention provides a method for designing an aircraft multi-loop model cluster composite root locus compensating controller. According to the method for designing the aircraft multi-loop model cluster composite root locus compensating 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 controller are determined by adding the multi-level series lag-lead compensating 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 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 for an aircraft controller, in particular to a design method for an aircraft multi-loop model cluster composite root trajectory compensation controller, which belongs to the categories of measurement and control technology, flight mechanics and the like. 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...

Claims

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Application Information

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IPC IPC(8): G05B13/04
Inventor 史忠科
Owner XIAN FEISIDA AUTOMATION ENG
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