Design method for longitudinal flight model cluster composite root-locus compensation controller
A technology of compensation controller and design method, applied in the direction of adaptive control, general control system, control/regulation system, etc., can solve the problem of designing overshoot and other issues
Active Publication Date: 2014-05-28
XIAN FEISIDA AUTOMATION ENG
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[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 A method for designing a composite root trajectory compensation controller for longitudinal flight model clusters is provided, which directly determines and obtains the amplitude-frequency and phase-frequency characteristics in the full envelope through frequency-sweeping flight tests under the conditions of different altitudes and Mach numbers. Model cluster; 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. The closed-loop pole distribution limit index in the full envelope and the model identification method in system identification determine the series and parameter values of the multi-level series lag-lead compensation controller; design a design that meets the concept of the closed-loop pole distribution limit under the root locus description Small overshoot of the full flight envelope, stable low-altitude flight controller
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[0026] 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{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 allowed to fly can be directly obtained, which constitutes the model cluster of elevators and flight heights in the full-envelope of the aircraft, and the corresponding aircraft The open-loop transfer function family between the elevator and the flight height is described as:
[0027] Where: A(h,M,s)=s m +a m-1 (h,M)s m-1 +a m-2 (h,M)s m-2 +…+a 1 (h,M)s+a 0 (h,M),
[0028] B(h,M,s)=s n +b n-1 (h,M)s n-1 +b n-2 (h,M)s n-2 +…+b 1 (h,M)s+b 0 (h, M) is a polynomial, s is the variable after the Laplace chang...
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The invention provides a design method for a longitudinal flight model cluster composite root-locus compensation controller. According to the design method, a model cluster composed of amplitude-frequency characteristics and phase-frequency characteristics in a whole envelope is determined directly through frequency sweep flight tests with different heights and different Mach numbers given; a closed-loop pole distribution limiting index described by a corresponding root locus is given according to military standard requirements for amplitude-frequency margin and phase margin in a flight envelope, a multi-stage tandem lag-lead compensation controller is additionally arranged, and therefore the number of stages and parameter values of the multi-stage tandem lag-lead compensation controller are determined through a model identification method in a closed-loop pole distribution limiting index and system identification process in the whole envelope of an air vehicle; a low-altitude flight robust controller which is small in overshoot and steady and accords with a whole flight envelope is designed from the conception of closed-loop pole distribution limiting described by a root locus.
Description
technical field [0001] The invention relates to a design method of an aircraft controller, in particular to a design method of a composite root trajectory compensation controller of a longitudinal flight model cluster, and 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...
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IPC IPC(8): G05B13/00
Inventor 史忠科
Owner XIAN FEISIDA AUTOMATION ENG