A Fatigue Life Prediction Method for CFRP-Metal Hybrid Bolted Connections

A technology for fatigue life prediction and connecting structures, applied in geometric CAD, instruments, design optimization/simulation, etc., can solve problems such as competitive fatigue failure, and achieve the effect of reducing test costs

Active Publication Date: 2022-03-25
BEIHANG UNIV
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  • Abstract
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AI Technical Summary

Problems solved by technology

That is, when CFRP and metal materials form a bolted connection structure, there is a competitive fatigue failure between the lap plates in the connection structure

Method used

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  • A Fatigue Life Prediction Method for CFRP-Metal Hybrid Bolted Connections
  • A Fatigue Life Prediction Method for CFRP-Metal Hybrid Bolted Connections
  • A Fatigue Life Prediction Method for CFRP-Metal Hybrid Bolted Connections

Examples

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Comparison scheme
Effect test

Embodiment 1

[0064] Example 1: Prediction of fatigue life of CFRP-aluminum alloy two-nail and double-shear connection structure

[0065] CFRP-aluminum alloy two-nail double-shear bolt connection structure such as figure 2 As shown, the middle plate is a CFRP laminate, the two sides are aluminum alloy plates, the fastener bolts are made of Ti-6Al-4V titanium alloy, and a tightening torque of 5.0 N m is applied to the two fasteners respectively. The steps to achieve fatigue life prediction are as follows:

[0066] 1. According to the structural parameters of the CFRP-aluminum alloy two-nail and double-shear connection, a three-dimensional finite element model of the structure is established in the finite element software ABAQUS, and the free ends of the aluminum plates on both sides are completely constrained. In the 3D finite element model, contact pairs are defined on the contact surfaces of CFRP plate and aluminum plate, CFRP plate and fastener, and aluminum plate and fastener. ...

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Abstract

The present invention establishes a method for predicting the fatigue life of a CFRP-metal mixed bolt connection structure under competitive failure, comprising the following steps: (1) using an improved progressive fatigue damage model to predict the fatigue life of a CFRP plate: establishing a three-dimensional finite element model of the connection structure Stress analysis is carried out to calculate the mechanical properties of composite materials that gradually degrade under fatigue loads, and the extended maximum strain criterion is used to check the failure state of composite materials with damage, and the stiffness of the failed materials is degraded. Finally, according to the residual strength of the structure when it fails, Obtain the fatigue life of the CFRP plate; (2) use the nominal stress method to predict the theoretical value of the fatigue life of the metal plate; (3) compare the predicted fatigue life value of the CFRP laminate with the fatigue life value of the metal plate, and predict the hybrid connection under competitive failure Structural fatigue life and failure modes. The invention is suitable for engineering application, can effectively predict the fatigue life of the CFRP-metal hybrid bolt connection structure, and provides reference for engineering practice.

Description

technical field [0001] The invention relates to the problem of predicting the fatigue life of a CFRP-metal hybrid bolt connection structure under fatigue load, in particular to a method for predicting the fatigue life of a CFRP-metal hybrid bolt connection structure under competitive failure, which is suitable for various systems widely used in aerospace vehicles. A CFRP-metal hybrid bolted connection structure. Background technique [0002] Carbon fiber reinforced composites (CFRP) have been widely used in aircraft main load-bearing structures with high bearing capacity, high efficiency and high reliability requirements due to their good mechanical properties such as high specific strength and high specific stiffness. Although advanced composite materials are widely used in aircraft structures, traditional metal materials are still widely used in aircraft components due to their manufacturing process and cost. Taking the Airbus A350 aircraft as an example, the total consum...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/23G06F30/15G06F119/02G06F119/14
Inventor 赵丽滨张娇蕊刘丰睿
Owner BEIHANG UNIV
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