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Method for determining ultimate load of composite laminated plate after patching and repairing

A composite material layer, ultimate load technology, applied in special data processing applications, instruments, electrical digital data processing, etc., to achieve the effect of high computational efficiency and computational accuracy

Pending Publication Date: 2021-07-23
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS +1
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Design and certification of repair methods also become more challenging as new aircraft programs drive the use of composite materials into safety-critical primary structures

Method used

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  • Method for determining ultimate load of composite laminated plate after patching and repairing
  • Method for determining ultimate load of composite laminated plate after patching and repairing
  • Method for determining ultimate load of composite laminated plate after patching and repairing

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Embodiment Construction

[0094] The present invention will be further described below in conjunction with the accompanying drawings. The following examples are only used to illustrate the technical solution of the present invention more clearly, but not to limit the protection scope of the present invention.

[0095] The present invention will be further described in detail below in conjunction with the embodiments and the accompanying drawings, but the embodiments of the present invention are not limited thereto.

[0096] The finite element model is established in ABAQUS. Build a geometric model such as image 3 As shown, where: W=20mm is the width of the laminate, L=120mm is the length of the laminate, T=2mm is the thickness of the laminate, t=0.1mm is the thickness of the adhesive layer, a=20mm is the length of the reinforcing sheet, D is the diameter of the damaged hole, and B is the diameter of the patch. The parameter values ​​of D and B are shown in Table 1, and the material properties are s...

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Abstract

The invention discloses a method for determining the ultimate load of a composite material laminated plate after patching and repairing. The method comprises the following steps: establishing a finite element model of a composite material laminated plate trepanning piece; building a composite material damage constitutive model; building a constitutive model of the composite material adhesive layer; based on an ABAQUS-UMAT finite element user dynamic subprogram module, writing a user-defined subprogram by using an FORTRAN language to realize a proposed damage constitutive model, and solving stress, strain and damage; and calculating the finite element model, and predicting the limit load of the composite laminated plate after the composite laminated plate is pasted and repaired. According to the invention, an ABAQUS-UMAT user-defined subprogram is used for achieving the established three-dimensional damage constitutive model in a numerical value mode, the model considers the influence of material performance degradation caused by shear nonlinearity and damage accumulation at the same time, and the limit load of the composite laminate after pasting and repairing can be predicted in a criterion mode.

Description

technical field [0001] The invention relates to a method for determining the ultimate load after patching and repairing composite laminated boards, and belongs to the technical field of mechanical performance analysis of composite materials. Background technique [0002] In the field of aviation, the application of composite materials in the structure of aircraft is very common. Fiber-reinforced resin-based composites have high specific modulus and specific strength, excellent energy absorption performance, especially the designability of isotropic stiffness and strength, and are widely used in aerospace, military, marine, civil and mechanical engineering fields . Although composite materials have various advantages over metal materials, they also have their disadvantages. In practical applications, it is found that due to the structural characteristics of composite materials, the damage of materials after low-speed impact is often hidden inside the structure and is not ea...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/23G06F113/26G06F119/14
CPCG06F30/23G06F2113/26G06F2119/14
Inventor 吴志荣杨鑫雷航朱康康宋迎东
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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