Method for verifying damage mechanisms of high-temperature resistant composite-material structure under multiple failure modes

A composite material and verification method technology, which is applied in the field of multi-failure mode damage mechanism verification of high temperature resistant composite material structures, can solve the problems of high cost, low simulation verification accuracy, can not truly reflect the structural design level, etc., to reduce the verification period and cost, the effect of improving the verification accuracy

Active Publication Date: 2017-06-13
CHINA ACAD OF LAUNCH VEHICLE TECH
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Problems solved by technology

Traditional verification methods include physical verification and simulation verification. The physical verification cycle is long an

Method used

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  • Method for verifying damage mechanisms of high-temperature resistant composite-material structure under multiple failure modes
  • Method for verifying damage mechanisms of high-temperature resistant composite-material structure under multiple failure modes
  • Method for verifying damage mechanisms of high-temperature resistant composite-material structure under multiple failure modes

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Embodiment

[0123] with [0] 16 Taking the life test of the fabric one-way plate under the tension-tension fatigue load as an example, the implementation process of the present invention is briefly described.

[0124] Select 85% loading as [0] 16 Fixed values ​​of fatigue loads for strength and stiffness degradation tests of fabric unidirectional plates. Adopt the component damage analysis method that the present invention provides to analyze component damage response, obtain [0] 16 The strength degradation curve of fabric unidirectional plate is as follows: figure 2 As shown, the change trend of residual stiffness under different cycle times is as follows image 3 shown. in figure 2 The middle ordinate is [0] 16 The ratio of the residual tensile strength of the fabric unidirectional panel to the static load tensile strength under the specified number of cycles X T (n,σ,R) / X T , and the abscissa is the ratio of loading times to fatigue life (n / N). image 3 The middle ordinate is...

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Abstract

Provided is a method for verifying damage mechanisms of a high-temperature resistant composite-material structure under multiple failure modes. Firstly, damage mechanism models of a high-temperature resistant composite material under various failure modes are established; then, according to the damage mechanism models, a high-temperature resistant composite-material component damage analyzing method is established, component damage responses are analyzed, the component damage analyzing method is corrected by real-object tests, then, a component damage response law is obtained, through the combination of ideal connection relations among components, a finite element method is adopted to analyze structural-component damage responses under different load working conditions, the connection relations among the components are corrected by real-object tests, the finite element method is adopted to analyze damage responses of assemblies, segments and flying machines according to corrected connection relations among the components and the component damage response law, and virtual-test verification is finished. According to the method for verifying the damage mechanisms of the high-temperature resistant composite-material structure under the multiple failure modes, a multi-grade multi-correction virtual-test verification method of a composite-material structural component is achieved, the verification cycle and the cost are reduced, and the verification accuracy is improved.

Description

technical field [0001] The invention relates to a multi-failure mode damage mechanism verification method for a high-temperature-resistant composite material structure, belonging to the field of structural design. Background technique [0002] Composite structures are more and more widely used in aircraft structures due to their light weight, relatively low cost and the development of manufacturing technology. The loading environment of aircraft structural parts is complex and the weight requirements are strict, so verification is required to ensure the reliability of the design. Traditional verification methods include physical verification and simulation verification. The physical verification period is long and the cost is high. The accuracy of traditional simulation verification is low and cannot truly reflect the level of structural design. Contents of the invention [0003] The technical problem of the present invention is: to overcome the deficiencies of the prior ...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/23G06F30/333
Inventor 苏玲王悦刘维玮吴迪王月郭爱民姚宇地陈飞曾亮邓云飞陈亦冬徐喆李丹圆张涛
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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