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

A technology of robust controller and longitudinal flight, applied in the direction of adaptive control, general control system, control/regulation system, etc., can solve the problem of design overshoot and so on

Active Publication Date: 2014-05-21
XIAN FEISIDA AUTOMATION ENG
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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 defects, the present invention provides a method for designing a longitudinal flight model cluster flutter suppression compound root locus multi-stage PID robust controller, which is directly determined by sweeping flight tests at different altitudes and Mach numbers to obtain full A model cluster composed of amplitude-frequency and phase-frequency characteristics within the envelope; according to the military stan

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

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Embodiment Construction

[0027] 1. Using linear frequency sweep signal at different heights 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{2πf0 / 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, which constitutes the model cluster of elevators and flight heights in the full envelope of the aircraft, and can span The flutter frequency of the aircraft is obtained by the flight envelope, and the corresponding open-loop transfer function cluster model between the aircraft elevator and the flight altitude is obtained

[0028] G ( s ) = e - ...

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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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Application Information

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IPC IPC(8): G05B13/04G05D1/10
Inventor 史忠科
Owner XIAN FEISIDA AUTOMATION ENG
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