Looking for breakthrough ideas for innovation challenges? Try Patsnap Eureka!

Method for predicting tension-compression fatigue hysteresis loop of metal matrix composite material

A technology of titanium-based composite materials and composite materials, which is applied in the field of prediction of tension-compression fatigue hysteresis loops of metal-based composite materials, and can solve problems such as time-consuming, high cost, and labor consumption

Active Publication Date: 2019-09-03
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
View PDF4 Cites 5 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The technical problem to be solved by the present invention is to provide a method for predicting the tension-compression fatigue hysteresis loop of metal matrix composites to solve the problems of time-consuming, labor-intensive and high-cost existing in the prior art

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Method for predicting tension-compression fatigue hysteresis loop of metal matrix composite material
  • Method for predicting tension-compression fatigue hysteresis loop of metal matrix composite material
  • Method for predicting tension-compression fatigue hysteresis loop of metal matrix composite material

Examples

Experimental program
Comparison scheme
Effect test

Embodiment

[0196] Table 2 Composite material parameters

[0197]

[0198] Given the number of cycles N = 1, 88500, 98500, and the temperature difference ΔT = -279, the matrix crack spacing at this time can be obtained by formula (34), and the current cycle number can be obtained by formula (35). The shear stress of the sliding interface, the reference strength of the fiber under the number of cycles at this time can be obtained by formula (42). According to formula (41), the fiber failure probability under the number of cycles at this time can be obtained by using the loop iteration method. At this point, the following material parameters can be obtained:

[0199] Effective fiber volume fraction:

[0200] V f =V f0 (1-P(T)) (43)

[0201] Composite elastic modulus:

[0202] E. 1 =E m V m +E f V f (44)

[0203] Composite thermal expansion coefficient:

[0204]

[0205] Composite matrix shear modulus:

[0206]

[0207] According to formula (17) (18) (19) (21) (23), t...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

Abstract

The invention discloses a method for predicting a tension-compression fatigue hysteresis loop of a metal matrix composite material. The method specifically comprises the following steps of determiningthe fiber, matrix and shear stress distribution of a one-way silicon carbide fiber reinforced titanium matrix composite material debonding section and a non-debonding section according to a BHE shearhysteresis model; determining the length of the debonding area, the initial debonding stress of the interface and the complete debonding stress of the interface; determining the length of a reverse sliding area and the critical stress of reverse sliding; determining the stress-strain relationship between the stretching loading and unloading stages of the composite material; determining a stress-strain relationship between the compression loading stage and the unloading stage of the composite material; determining a change rule of the crack spacing and the interface shear stress along with thecycle number; determining a fiber breakage fraction of a given cycle number; and giving a cycle number N, and combining the above steps to obtain the fatigue hysteresis loop of the composite materialchanging with the cycle number. According to the method, the stress-strain relationship of the composite material under different matrix crack intervals, different sliding interface shear stresses, different fiber breakage volume fractions and different cycle numbers can be accurately predicted.

Description

technical field [0001] The invention relates to a method for predicting a tension-compression fatigue hysteresis loop of a metal matrix composite material, in particular to a method for predicting a tension-compression fatigue hysteresis loop of a unidirectional silicon carbide fiber reinforced titanium matrix composite material. Background technique [0002] The high specific strength, high specific stiffness, high temperature resistance, structural stability and other excellent properties of silicon carbide fiber reinforced titanium matrix composites make it one of the irreplaceable new structural materials in the aerospace field. It is widely used in aeroengine rotor parts, Structures such as blades and integral leaf rings are of great significance for reducing the weight of aero-engines and improving the thrust-to-weight ratio of engines. [0003] Under service conditions, silicon carbide fiber-reinforced titanium alloy matrix composites need to withstand various complex...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50G06Q10/04
CPCG06Q10/04G06F2119/06G06F30/20
Inventor 孙志刚张帆陈西辉牛序铭许聪宋迎东
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Patsnap Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Patsnap Eureka Blog
Learn More
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic, Popular Technical Reports.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com