A Method for Determining Parameters of Structured Notch Filter

A filter parameter and determination method technology, applied in special data processing applications, geometric CAD, design optimization/simulation, etc., can solve problems such as feedback signal phase delay, flight control system bandwidth drop, and adverse effects of aircraft control characteristics. To achieve the effect of improving operating efficiency

Active Publication Date: 2021-09-03
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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  • A Method for Determining Parameters of Structured Notch Filter
  • A Method for Determining Parameters of Structured Notch Filter
  • A Method for Determining Parameters of Structured Notch Filter

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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 object in this embodiment - 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 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 the roll...

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Abstract

The invention relates to a method for determining the parameters of a structural notch filter, comprising: step 1: selecting a design point, and establishing an aerodynamic servoelastic analysis model; Analyze and determine the number of structural notch filters that need to be increased by each feedback input signal channel, and the frequency parameters of the increased structural notch filters in the feedback input signal channel; Step 3: set up a structural notch filter parameter optimization model; step Four: improve the genetic algorithm to solve the parameter optimization model parameters of the structural trap filter established in step three to optimize; step five: calculate the optimal individual of the optimization problem in step three, and select the optimal individual corresponding to the optimal variable value as Structural notch filter parameters. The method for determining the parameters of the structural notch filter of the invention can ensure that the introduction of the structural notch filter has the least influence on the flight mechanics characteristics of the rigid body of the aircraft.

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 structural notch filter parameters 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 filter i...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15G06F30/20
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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