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Method for determining stress concentration coefficient of beveled end of stringer

A technology of stress concentration factor and determination method, which is applied in the direction of design optimization/simulation, etc., can solve the problems of no theoretical solution and difficult analysis of the stress concentration factor at the beveled end of the long truss, and achieve a simple determination method, labor force liberation, and rapid determination Effect

Pending Publication Date: 2021-06-29
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

[0003] The purpose of this application is to provide a method for determining the stress concentration factor of the beveled end of the long truss based on the finite element orthogonal test method according to the requirements of aircraft design, so as to solve the unreasonable solution of the stress concentration factor of the beveled end of the long truss and the analysis is relatively difficult The problem

Method used

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  • Method for determining stress concentration coefficient of beveled end of stringer
  • Method for determining stress concentration coefficient of beveled end of stringer

Examples

Experimental program
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Effect test

Embodiment 1

[0012] Select a beveled end of a long stringer of the overall wall panel of the aircraft, and its bevel angle Bottom corner radius B=5mm, chamfer radius C=2mm, stringer height H=40mm;

[0013] Step 1. Calculate the shape parameter α

[0014] According to the bevel angle A of the basic structural parameter of the beveled end of the long truss of the integral wall plate, according to the formula Calculated shape parameters

[0015] Step 2. Calculate the shape parameter β

[0016] According to the basic structural parameter of the beveled end of the long truss of the integral wall plate, the radius B of the beveled bottom corner is calculated according to the formula β=B / H to obtain the shape parameter β=0.125;

[0017] Step 3. Calculate shape parameters

[0018] According to the chamfering radius C of the basic structural parameters of the oblique end of the long truss of the integral wall plate, according to the formula Calculated shape parameters

[0019] Step 4...

Embodiment 2

[0022] Choose another long truss beveled end of the overall wall panel of the aircraft, and its bevel angle The bottom corner radius is B=8mm, the chamfer radius is C=2mm, and the stringer height H=45mm.

[0023] Step 1. Calculate the shape parameter α

[0024] According to the bevel angle A of the basic structural parameter of the beveled end of the long truss of the integral wall plate, according to the formula Calculated shape parameters

[0025] Step 2. Calculate the shape parameter β

[0026] According to the basic structural parameters of the beveled end of the long truss of the integral wall plate, the radius B of the beveled bottom corner is calculated according to the formula β=B / H

[0027] Step 3. Calculate shape parameters

[0028] According to the chamfering radius C of the basic structural parameters of the oblique end of the long truss of the integral wall plate, according to the formula The calculated shape parameters are

[0029] Step 4. Calcul...

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Abstract

According to the method for determining the stress concentration coefficient of the beveled end of the stringer, correction factors of stress concentration influence factors (the beveled angle, the base angle radius of the beveled root and the chamfer radius of the web root) are determined on the basis of a finite element orthogonal test method, and the method for determining the stress concentration coefficient of the beveled end of the stringer is simple and convenient. The method can be used for quickly determining the stress concentration coefficient of the beveled end of the stringer and liberating the labor force of personnel.

Description

technical field [0001] The invention belongs to the field of aeronautical structure design, and in particular relates to a method for determining a stress concentration factor at a beveled end of a long truss. Background technique [0002] The wing panel stringer is one of the important stress-bearing members in the longitudinal frame. During the flight, the lower wing stringer usually bears high tensile load, which is prone to fatigue failure, which in turn leads to the destruction of the entire aircraft. to a huge loss. The end of the long stringer is generally designed with a bevel. Due to the sudden change of the section, the stress concentration is relatively large, and crack initiation and damage are prone to occur. This structure is the focus and difficulty of the fatigue analysis of the wing structure details. The stress concentration factor is a key parameter that determines the fatigue life, and its specific value must be obtained in aircraft design. At present, ...

Claims

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Application Information

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IPC IPC(8): G06F30/23
Inventor 朱亮张彦军雷晓欣史志俊
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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