Stiffened wallboard damage tolerance analysis method based on finite element analysis solving

A technique of stiffening siding, analytical methods, applied in special data processing applications, instruments, electrical digital data processing, etc.

Active Publication Date: 2017-01-25
AVIC SAC COMML AIRCRAFT
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  • Claims
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AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to provide a more accurate damage tolerance evaluation method for reinforced wall panels in view of the deficiencies of the existing damage tolerance analysis methods for reinforced wall panels

Method used

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  • Stiffened wallboard damage tolerance analysis method based on finite element analysis solving
  • Stiffened wallboard damage tolerance analysis method based on finite element analysis solving
  • Stiffened wallboard damage tolerance analysis method based on finite element analysis solving

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Embodiment Construction

[0060] The specific implementation process of the present invention will be described in detail below in conjunction with the accompanying drawings. The specific steps are described by taking the damage tolerance analysis of longitudinal cracks at a certain position of the aircraft fuselage panel as an example. Its basic implementation process is as follows:

[0061] Step 1: Determine the crack propagation direction according to the structural form of the aircraft panel and the load condition; set the limit crack length to be twice the frame spacing, and determine the model scale;

[0062] figure 1 , figure 2 The position marked in the center is the crack analysis area of ​​the fuselage wall, and the longitudinal crack of the fuselage is located at the center line of the skin between the left and right No. 1 stringers of the lower wall of the straight barrel section of the fuselage. In the analysis, it is considered that the fuselage skin can not fail under the action of c...

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Abstract

The invention relates to a stiffened wallboard damage tolerance analysis method based on finite element analysis solving, comprising the steps of first, determining a crack growth direction according to aircraft wallboard structural form and load-bearing condition; setting limit crack length to determine model scale; second, establishing a crack-free stiffened wallboard details finite element model; third, applying total load to the model to solve wallboard stress distribution; fourth, simulating cracks different in length in the finite element model, and extracting note balance force and displacement of a crack tip unit; fifth, solving stress strength factor K for tips with different crack lengths of a stiffened wallboard in fourth step by applying virtual crack closure technique VCCT; sixth, subjecting the stiffened wallboard to crack growth life and structural residual strength analysis. The method can provide real simulation for stiffened wallboard different-size cracks, crack tip stress and strain condition, stiffened wallboard different-size crack stiffener stress level, and fastener load; crack growth analysis is performed on stiffened wallboard skin based on analysis results.

Description

technical field [0001] The invention relates to a damage tolerance analysis method for a main structure of a large transport aircraft body and belongs to the field of damage tolerance design of a main structure of the body. Background technique [0002] In the field of aeronautical design, based on economic and safety requirements, the main structure of modern large transport aircraft is mostly designed using the concept of damage tolerance design. The fuselage and wings of large transport aircraft are mostly designed with reinforced panels, so the damage tolerance analysis of reinforced panels plays an extremely important role in the design of large transport aircraft. In China, the damage tolerance analysis methods for reinforced panels of large transport aircraft are developed relatively late. Most of the damage tolerance analysis methods for reinforced panels are based on the original damage tolerance design manual, and can only perform basic damage tolerance analysis fo...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/23
Inventor 刘旭孟维宇贾大炜支晗周龙超
Owner AVIC SAC COMML AIRCRAFT
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