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Method for judging fatigue dangerous part of lug hole edge

A technology of dangerous parts and discrimination methods, applied in geometric CAD, design optimization/simulation, etc., can solve problems such as no longer applicable, and achieve the effect of simple and reliable judgment methods and easy promotion and calculation

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

[0003] At present, the damage tolerance analysis of lugs often focuses on the analysis of straight lugs and symmetrical oblique lugs under straight loads. It has certain applicability to use the maximum Mises stress as the cracking criterion to determine the most likely cracking position, but When the straight lugs are subjected to oblique loads, and the oblique lugs with other bevel angles are subjected to straight and oblique loads, it is no longer applicable to use the maximum Mises stress as the cracking criterion. Therefore, how to determine a suitable method for different lugs? The cracking criterion for determining the cracking position of the lug under loads in different directions is the core of solving this problem

Method used

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  • Method for judging fatigue dangerous part of lug hole edge
  • Method for judging fatigue dangerous part of lug hole edge
  • Method for judging fatigue dangerous part of lug hole edge

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Embodiment Construction

[0018] Referring to the accompanying drawings, the method for discriminating fatigue risk parts at the edge of the ear hole of the present application, the structural parameters of the ear are known, is characterized in that it comprises the following steps: 1) carrying out the above-mentioned ear structure 1 in the finite element analysis software. Grid division, set up finite element model, this finite element model is divided into not less than 360 mesh units by lug hole edge in implementation, establishes local cylindrical coordinate system in the center of lug hole 2; 2) in finite element analysis software Boundary conditions and loads are applied to the lug structure 1, and the stress value of the lug structure 1 in the global coordinate system under the load is obtained. The tangential stress of each grid unit on the edge of the lug hole is the stress on the hole wall 3) Transform the stress value of the lug structure 1 in the global coordinate system into the tangential...

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Abstract

A method for judging a fatigue dangerous part of a lug hole edge comprises the following steps: knowing structural parameters of a lug, and establishing a finite element model and a local cylindrical coordinate system for the lug structure; converting the stress value of the lug structure in the global coordinate system into a tangential stress value under a cylindrical coordinate system, and obtaining the tangential stress of each grid unit on the edge of a lug hole through finite element analysis; and according to the tangential stress value, selecting the position where the lug hole is most likely to crack, wherein the position is the fatigue dangerous part of the edge of the lug hole under the load condition.

Description

technical field [0001] The invention belongs to the field of aircraft structure strength design, and relates to a method for judging dangerous parts around ear piece holes in the field of aircraft structure strength design. Background technique [0002] As a connection joint, the lug structure is a commonly used connection structure in aircraft structures, and it is also a key component for fatigue and damage tolerance of aircraft structures. The key factors for crack growth analysis of sheet structures. The location of the crack at the edge of the ear hole depends on the maximum stress at the edge of the hole, and which criterion is used to calculate the stress at the edge of the hole directly determines the location of the maximum stress at the edge of the hole of the ear, thus determining the location of the initiation of the ear crack. [0003] At present, the damage tolerance analysis of lugs often focuses on the analysis of straight lugs and symmetrical oblique lugs u...

Claims

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Application Information

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IPC IPC(8): G06F30/23G06F30/15
Inventor 彭航张彦军赵天娇王锋
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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