Calculation method of ultimate load of composite laminates based on maximum stress criterion

A composite material layer, maximum stress technology, applied in the direction of calculation, design optimization/simulation, special data processing applications, etc., can solve the problem of reducing the calculation efficiency, unable to reflect the stress of the laminate, and unable to directly obtain the ultimate strength of the composite laminate. value and other problems, to achieve the effect of simplifying the tedious process, reducing the error rate and high precision

Active Publication Date: 2018-12-28
WEIHAI GUANGWEI COMPOSITES
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  • Application Information

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Problems solved by technology

However, most of the finite element software is currently oriented towards the general finite element analysis of large and complex structures. For this kind of composite laminates with simple loads, many parameters in the finite element software requirements are not involved in the calculation process. , the operation process is also carried out in accordance with the process of complex large-scale structural analysis, so the redundancy in many processes reduces the computational efficiency
Moreover, the calculation results obtained by the finite element method cannot reflect the overall stress of the laminate, and its inherent properties also limit the calculated value to an approximate solution of the actual value, and it is impossible to directly obtain the composite laminate under a simple load. The ultimate strength value of

Method used

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  • Calculation method of ultimate load of composite laminates based on maximum stress criterion
  • Calculation method of ultimate load of composite laminates based on maximum stress criterion
  • Calculation method of ultimate load of composite laminates based on maximum stress criterion

Examples

Experimental program
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Effect test

Embodiment 1

[0048] A method for calculating the ultimate load of composite laminates based on the maximum stress criterion, including an information input module, an operation module, and an information output module. Response calculation module and strength and failure mode calculation module. After the data is input and run, the calculation program will first calculate the stiffness matrix of each single layer according to the data input in the information input module, and then integrate the laminate stiffness matrix and flexibility matrix according to the ply information. Then, according to the laminate flexibility matrix and the basic load information (tension, compression, shear, bending, torsion is related to the shape of the loaded section, so it is not considered), the overall strain and deflection rate of the laminate can be calculated, and further can be obtained for each The stress-strain information in the main direction of a single layer and the stress-strain information und...

Embodiment 2

[0088] On the basis described in Example 1, in order to analyze the performance of multi-material composite laminates, such as foam sandwich composites, honeycomb sandwich composites, etc., increase the multi-material performance input in the information input module part, in the layer information The module adds a material selection section.

Embodiment 3

[0090] On the basis described in Example 2, in order to facilitate the calculation of the equivalent modulus of the composite laminate, the output equivalent modulus and its stiffness matrix data are increased:

[0091] According to the obtained matrices A, D, and B, there is no tension-bend coupling for symmetrically balanced ply composite laminates, so the B matrix is ​​empty; because A 16 、A 26 、D 16 、D 26There are positive and negative alternating items in the term, so its value is much smaller than other stiffness coefficients, and the calculation can be simplified.

[0092] a. For the case of pure in-plane load, there is no bending and torsional load M, so the relationship between the internal force and strain of the laminate is

[0093] N=Aε 0 (3-1)

[0094] Therefore, the equivalent modulus parameter E of the laminate can be obtained through the calculation of the A matrix 1 ,E 2 , μ 12 , G 12 And the equivalent stiffness matrix Q.

[0095] b. For the pure b...

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Abstract

The invention relates to the field of composite material design, in particular to a composite material laminate ultimate load calculation method based on a maximum stress criterion. The invention comprises an information input module, an operation module and an information output module. Material performance information, ply information and load data information are input in the information inputmodule, the calculation program will calculate three stiffness matrices A, D, B of composite laminates according to the input data, and calculate the corresponding flexibility matrices A ', D', B ', and then the overall strain and deflection of the laminated plate are calculated according to the flexibility matrix and the foundation load information, furthermore, the stress-strain information in the principal direction of each layer and the stress-strain information in the global coordinates can be obtained, and the maximum value of the ratio of stress to ultimate strength under the action offoundation load can be obtained by using the maximum stress or maximum strain failure criterion. As the relationship between load and stress-strain is linear, the minimum failure load of composite laminates can be obtain according to the maximum value of the ratio.

Description

technical field [0001] The invention relates to the field of structural design of composite materials, in particular to a method for calculating the ultimate load of composite material laminates based on the maximum stress criterion. Background technique [0002] As we all know, there are generally two analysis methods for the stress-strain response analysis of composite laminates under simple loads (tension, compression, shear, and bending uniformly distributed along the cross-section): [0003] One is to perform complex and lengthy performance calculations of composite laminates through mechanical calculations or simple programming based on the basic mechanics knowledge in "Composite Mechanics" and other materials. Due to the lack of systematicness and continuity in the calculation process, it is often prone to confusion when transferring or inputting a large amount of data, and a large amount of repetitive work is required, especially for laminates with more complex layer...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/17G06F2113/24G06F30/23Y02T90/00
Inventor 丛庆隋显航殷飞王鹏远
Owner WEIHAI GUANGWEI COMPOSITES
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