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Method for determining parameters of structural notch filters

A filter parameter and determination method technology, applied in the direction of instruments, electrical digital data processing, special data processing applications, etc., can solve problems such as adverse effects of aircraft control characteristics, phase delay of feedback signals, and bandwidth reduction of flight control systems

Active Publication Date: 2018-05-08
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

[0004] The purpose of the present invention is to provide a method for determining the parameters of a structural notch filter, which is used to solve the problem that the current structural notch filter will cause a phase delay of the feedback signal, resulting in a decrease in the bandwidth of the flight control system, which will adversely affect the stability of the aircraft. The problem

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  • Method for determining parameters of structural notch filters

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[0073] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention.

[0074] The method for determining the parameters of the structured notch filter of the present invention will be described in detail below with a set of data.

[0075] Such as Figure 8 Shown is the subject of this example, a large transport class aircraft, with flight control sensors and ailerons for stability augmentation control on it.

[0076] First: choose the roll control loop under the state of flight altitude H=5Km, Ma=0.5 as the design point, and establish the aeroservoelastic system model G ASE (s):

[0077] G ASE (s)=G ACT (s)·[G SAS (s)]·[G s (s)]·[G AR (s)+G AE (s)]

[0078] Second: see Figure 9 , in this embodiment the feedback signals are the roll angle Φ and t...

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Abstract

The invention relates to a method for determining the parameters of structural notch filters. The method includes the steps of firstly, selecting a design point, and building an aeroservoelasticity analysis model; secondly, analyzing the coupling contribution degree of the feedback input signal of a flight control system stability augmentation control link, and determining the number of structuralnotch filters which need to be added to each feedback input signal channel and the frequency parameters of the added structural notch filters of the feedback input signal channels; thirdly, buildinga structural notch filter parameter optimization model; fourthly, improving a genetic algorithm to solve the parameters of the structural notch filter parameter optimization model built in the third step to perform optimization; fifthly, calculating to obtain the optimal individual of the optimization problem in the third step, and selecting the optimized variable values corresponding to the optimal individual to serve as the parameters of the structural notch filters. By the method, the fact that the influence of the introduction of the structural notch filters on the rigid body flight mechanical properties of an airplane is minimum can be ensured.

Description

technical field [0001] The invention belongs to the technical field of aircraft aeroelastic active control, and in particular relates to a method for determining parameters of a structural notch filter in aircraft aerodynamic servoelastic stability. Background technique [0002] Aeroservoelasticity (ASE, Aeroservoelasticity) problem is a multidisciplinary technique involving the interaction of flexible aircraft structure, unsteady aerodynamic force and flight control system. Modern high-gain flight control systems can effectively improve the dynamic performance of the aircraft and improve the pilot's completion rate of complex tasks. At the same time, it is more likely to induce bad ASE coupling, produce cyclic loads that accelerate structural fatigue, and harmful oscillations that affect the normal control of the pilot. Limit cycle oscillations and even destructive chatter can also occur under flight conditions. [0003] In actual engineering, adding a structural notch fil...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20
Inventor 蒲利东严泽洲罗务揆张红波
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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