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A failure analysis method for multi-nail connection structures of all-sic composite materials

A composite material and connection structure technology, applied in the direction of instrumentation, design optimization/simulation, calculation, etc., can solve the problems of staying, C/SiC composite material joints are rare, etc., and achieve the effect of reducing the test cost and simplifying the model form.

Active Publication Date: 2021-03-02
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

[0005] However, most of the current analysis of the mechanical connection structure of C / SiC composites is still in the experimental means, and there are few studies on the use of numerical methods to predict the failure of C / SiC composite joints.

Method used

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  • A failure analysis method for multi-nail connection structures of all-sic composite materials
  • A failure analysis method for multi-nail connection structures of all-sic composite materials
  • A failure analysis method for multi-nail connection structures of all-sic composite materials

Examples

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Embodiment 1

[0080] Example 1: Failure analysis of C / SiC composite multi-nail connection structure

[0081] Such as image 3 As shown in (a), the C / SiC composite multi-nail connection structure connects the upper plate and the lower plate through bolts, and the composite plate and bolts used are both made of C / SiC material. Firstly, the C / SiC substrate was fabricated by the CVI process, and the connecting plate and bolts were cut out from the substrate, and the bolts and the connecting plate were manually tightened and installed, and the tightening torque was about 0.3N·m. Such as image 3 As shown in (b), the bolt weaving plane is parallel to the direction of the bolt shank.

[0082] 1. According to the structural parameters of C / SiC composite multi-nail connection joints, a three-dimensional finite element model of the structure was established in the finite element software ABAQUS, and the free end of the upper laminate was completely constrained, and a displacement load in the x dire...

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Abstract

The invention relates to a failure analysis method for a multi-nail connection structure of a full C / SiC composite material based on a progressive damage model, comprising the following steps: (1) establishing a bilinear model of the material on the basis of the mechanical performance test of the C / SiC composite material (2) According to the geometric parameters of C / SiC composite multi-nail connection structure, a three-dimensional finite element model of composite material structure is established; (3) Stress analysis is performed based on the three-dimensional finite element model of composite material structure; (4) The application is suitable for C / SiC composite material failure criterion predicts the failure state of the composite material; (5) degrades the material stiffness of the failed material according to the degradation model; (6) judges whether the damage in the composite material structure leads to structural damage, if the structure does not fail Continue loading until the material fails. The invention is suitable for engineering application, can effectively analyze and predict the failure of the multi-nail connection structure of the full C / SiC composite material, can significantly reduce the test cost, and provides reference for engineering practice.

Description

technical field [0001] The invention relates to the technical field of failure analysis of full-SiC composite material structures, in particular to a method for failure analysis of full-SiC composite multi-nail connection structures based on an asymptotic damage model, which is applicable to full-SiC composite multi-nail joints used in hypersonic aircraft connection structure. Background technique [0002] Carbon fiber reinforced silicon carbide ceramic matrix composites (carbon fiber reinforced silicon carbide, C / SiC) has a series of excellent properties such as high strength, high hardness, high temperature resistance, ablation resistance and low density, and has become a promising prospect in the aerospace field. A new generation of high temperature thermal structure. [0003] The various parts in the aircraft need to be connected to form a whole. Due to the weaving process of C / SiC composite materials, it is difficult and expensive to manufacture large and complex struc...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/23G06F113/26G06F119/14
CPCG06F30/23
Inventor 赵丽滨杨文曹天成陈奎儒
Owner BEIHANG UNIV
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