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A finite element method for structural analysis of composite beam with initial defects

A technology of structural analysis and finite element, applied in special data processing applications, instruments, geometric CAD, etc., to achieve the effect of improving calculation accuracy, high calculation efficiency, and eliminating concentration

Active Publication Date: 2020-10-16
HOHAI UNIV +1
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Problems solved by technology

[0003] Aiming at the above-mentioned deficiencies in the prior art, the present invention proposes a finite element method for numerical analysis of composite beams with initial defects, through which the finite element method can be used to solve complex geometric configurations, loading conditions and boundary conditions with Static Mechanics Problems of Composite Beams with Initial Defects

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  • A finite element method for structural analysis of composite beam with initial defects
  • A finite element method for structural analysis of composite beam with initial defects
  • A finite element method for structural analysis of composite beam with initial defects

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Embodiment 1

[0075] Such as figure 1 As shown, this embodiment includes the following steps:

[0076] (a) Input model parameters.

[0077] This embodiment is a static loading simulation of a single leg bending (SLB for short) specimen, such as figure 2 As shown, the length L of the sample is 0.1m, the initial length of the crack is 0.025m, the height of the upper sub-beam ① and the lower sub-beam ② are both 0.002m, and the width is 0.001m. The material parameters of the upper and lower sub-beams are shown in Table 1, and the concentrated load P is 8N.

[0078] Table 1 Material parameters of samples

[0079]

[0080] (b) Discretization of the model.

[0081] First will be as figure 2 The shown embodiment SLB sample is divided into 3 areas, i.e. the cracked area (1), the uncracked area (2) on the left side of the loading point (concentrated load P action point) and the uncracked area (3) on the right side of the loading point; Set a certain number of cells per locale, such as ima...

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Abstract

The invention relates to a finite element method for analyzing a composite beam structure with initial defects. The finite element method comprises the following steps: firstly, dispersing the composite beam structure into continuous elements in a spatial domain; secondly, deducing a rigidity matrix and a load vector of an uncracked part by utilizing a minimum potential energy principle; respectively assembling the solved unit stiffness matrix and load vector with the unit stiffness matrix and load vector of the cracking part to obtain an overall balance equation of the structure; solving theoverall balance equation to obtain the degree of freedom of each node; and finally, performing result post-processing to obtain the stress, strain, energy release rate and the like of each unit, and verifying the convergence of a calculation result. According to the method, the composite beam with the initial defects and with various complex geometric configurations and boundary conditions can beconveniently solved, geometric nonlinearity, material nonlinearity, contact nonlinearity and the like can be conveniently introduced, and the method is an efficient calculation method for analyzing the composite beam with the initial defects based on the first-order shear deformation beam theory.

Description

technical field [0001] The invention relates to a method in the technical field of mechanical numerical simulation, in particular to a finite element method for structural analysis of composite beams with initial defects. Background technique [0002] The finite element method (Finite element method, referred to as FEM) is a mature numerical calculation method, which has been widely used in various engineering fields and has been widely adopted by various engineers. Its advantage is that each parameter has a clear physical meaning, and it can solve structures with various complex boundary conditions and geometric configurations. The combined structure can give full play to the mechanical properties of the component materials, and has been widely used in aerospace, civil engineering, mechanical engineering and other fields. However, due to sudden changes in material properties, the combined structure is prone to debonding at the interface, which affects its mechanical proper...

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Application Information

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IPC IPC(8): G06F30/17G06F30/23G06F111/10G06F119/14
CPCG06F30/17G06F30/23G06F2111/10G06F2119/14Y02T90/00
Inventor 刘庆辉乔丕忠郭兴文蔡新祁洋
Owner HOHAI UNIV
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