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
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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

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  • 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

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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...

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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

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Application Information

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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
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