Compressive stress assessment method for honeycomb sandwich panel

A technology of sandwich structure and honeycomb sandwich, which is applied in the field of compressive stress assessment of honeycomb sandwich structure panels, can solve the problems of structural damage and dangerous calculation results.

Active Publication Date: 2019-03-22
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to design a method for evaluating the compressive stress of honeycomb sandwich structure panels, so as to solve the technical problem that the calculation results in the current method will be dangerous, which may lead to early failure of the structure

Method used

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  • Compressive stress assessment method for honeycomb sandwich panel
  • Compressive stress assessment method for honeycomb sandwich panel
  • Compressive stress assessment method for honeycomb sandwich panel

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Embodiment Construction

[0028] Below in conjunction with accompanying drawing and embodiment the present invention will be further described:

[0029] Taking an aircraft sandwich structure panel as an example, the method for evaluating the compression stress of the honeycomb sandwich structure panel of the present invention is calculated and evaluated as follows.

[0030] 1. According to the finite element calculation results, extract the axial force F of the sandwich structural unit N , bending moment M x ;

[0031] 2. Reference figure 1 The section of the sandwich structure shown, using the calculation method of the moment of inertia of the plane figure in the mechanics of materials, can determine the moment of inertia I on the section of the honeycomb sandwich structure z for:

[0032]

[0033] where t 1 is the thickness of panel 1 of the sandwich structure, t 2 is the thickness of panel 2 of the sandwich structure, t c is the thickness of the core of the sandwich structure, and b is the...

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Abstract

The invention belongs to the field of material mechanics, and relates to a compressive stress assessment method for a honeycomb sandwich panel. The method comprises the following steps: extracting theaxial force and bending moment of a sandwich structure unit according to a finite element calculation result; calculating the inertia moment and area of the panel section according to the geometricalparameters of sandwich structure section; calculating the axial stress according to the ratio of the axial force to the section area, calculating the bending stress generated by the bending moment ofa sandwich structure according to a flexure formula, and overlapping the axial stress and the bending stress at the sandwich panel to calculate the maximum compressive stress of the panel. By adopting the method, the maximum working stress of the sandwich panel can be calculated, and damage of the sandwich panel can be accurately predicted.

Description

technical field [0001] The invention belongs to the technical field of material mechanics and relates to a compression stress evaluation method of a honeycomb sandwich structure panel. Background technique [0002] For the honeycomb sandwich structure currently used in aircraft, the compressive stress of the panel under load is required for intercell buckling of the panel, panel wrinkling and shear wrinkling of the panel. At present, the calculation of the compressive stress of the panel at home and abroad is generally carried out by NASTRAN finite element software, and then by selecting the strain value ε on the panel, the compressive stress of the panel is calculated σ=Eε (E is the equivalent elastic modulus of the panel); or The stress value on the panel is directly selected as the working stress of the panel. There is a problem in these methods. The panel stress calculated in this way is the mean stress of the panel, but the stress of the actual panel section in the grad...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N3/20
CPCG01N3/20G01N2203/0023G01N2203/0075G01N2203/0676
Inventor 杜正兴刘洪权殷黎
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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