Composite structure failure prediction analytical method

A composite material and failure prediction technology, applied in the direction of applying stable tension/pressure to test the strength of materials, can solve the problems of weakening the mechanical properties of the matrix and fibers, complex failure process and degradation behavior of composite materials, etc., to achieve the effect of accurate performance

Inactive Publication Date: 2016-02-24
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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Problems solved by technology

In general, high temperature and humid environments will significantly weaken the mechanical properties of t

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  • Composite structure failure prediction analytical method
  • Composite structure failure prediction analytical method
  • Composite structure failure prediction analytical method

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Embodiment 1

[0065] Example 1: Tensile failure analysis of a typical composite orifice structure A typical composite orifice is made of T300 grade carbon fiber reinforced epoxy resin composite material, and the layup sequence is [45 / -45 / 0 / -45 / 0 / 45 / 0 / 45 / -45 / 0 / -45 / 45 / 90 / 45 / -45 / 0 / 45 / -45 / 90 / 0]s, single layer thickness is 0.12mm. Material fiber volume fraction V f It is about 63%, the glass transition temperature is about 260°C, the thermal expansion coefficients are α1=0.25×10-6 / K, α2=32.6×10-6 / K, and the wet expansion coefficients are β1=0, β2=0.6 ×10-6, γ is set to 10-6, and, based on the existing material degradation coefficient calculation method, the calculation of each degradation coefficient is as follows:

[0066] d ft = 0.00874; d fc = 0.0693; d fm1 = 0.061; d fm2 =0.18

[0067] 1. According to the geometric parameters of the composite orifice plate structure, a three-dimensional finite element model of the structure is established in the finite element software ABAQUS, and one...

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Abstract

The invention provides a composite structure failure prediction analytical method. The constitutive equation expressing the stress-strain relation of an anisotropic composite under the influences of damp-heat environments is established through the combination of influences of damp-heat strain. Meanwhile, through the combination with an asymptotic damage analysis method, the influences of damp-heat effects on parameters such as rigidity and strength of materials are introduced to the three aspects of a stress analysis mode, a failure criterion and a material degradation model, a UMAT subprogram is complied, packaged and embedded in finite element software, and finally a more perfect asymptotic damage model capable of being used for composite failure analysis under the damp-heat environments is established. Compared with an existing failure asymptotic damage analysis method for various composite structures, the influences of damp-heat effects on failure behaviors of anisotropic composites are considered, the damage process of materials under damp-heat environments can be accurately expressed, and the composite structure failure prediction analytical method is suitable for prediction of simulation and strength of the composite structure damage process under the condition that temperature, humidity and other conditions are more complex.

Description

technical field [0001] The invention relates to the technical field of composite material structure failure analysis, in particular to a composite material structure failure prediction analysis method considering the influence of hygrothermal effect factors, which is applicable to various complex fiber-reinforced resin-based composite material structures widely used at present. Background technique [0002] Advanced composite materials have many excellent characteristics such as high specific strength and specific modulus, tailorable design and easy overall forming, which can significantly reduce the weight of aircraft structures and improve the safety, economy, comfort and environmental protection of aircraft. The scope of application has been expanded from the original non-bearing structure, secondary load-bearing structure to the main load-bearing structure. At present, the amount and application position of advanced composite materials in the aircraft body structure has ...

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Application Information

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IPC IPC(8): G01N3/18
CPCG01N3/18
Inventor 洪海铭王佳莹赵丽滨
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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