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A Prediction Method for Tension-compression Fatigue Hysteresis Loop of Metal Matrix Composites

A titanium-based composite material and composite material technology, which is applied in the field of tensile-compression fatigue hysteresis loop prediction of metal-based composite materials, can solve the problems of labor consumption, high cost, time-consuming and the like

Active Publication Date: 2020-10-27
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

Method used

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  • A Prediction Method for Tension-compression Fatigue Hysteresis Loop of Metal Matrix Composites
  • A Prediction Method for Tension-compression Fatigue Hysteresis Loop of Metal Matrix Composites
  • A Prediction Method for Tension-compression Fatigue Hysteresis Loop of Metal Matrix Composites

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Experimental program
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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 tension-compression fatigue hysteresis loops of metal matrix composite materials, specifically: determining the fiber and matrix of the debonding section and non-debonding section of the unidirectional silicon carbide fiber reinforced titanium matrix composite material according to the BHE shear lag model , shear stress distribution; determine the length of the debonding zone, the initial debonding stress of the interface and the complete debonding stress of the interface; determine the length of the reverse slip zone and the critical stress of reverse slip; determine the stress and strain of the composite material in the stretching and unloading stages relationship; determine the stress-strain relationship in the compression loading and unloading stages of composite materials; determine the variation law of crack spacing and interface shear stress with the number of cycles; determine the fiber fracture fraction for a given number of cycles; N , combined with the above steps, the fatigue hysteresis loop of the composite material changing with the number of cycles is obtained. The invention can accurately predict the stress-strain relationship of the composite material under different matrix crack distances, different sliding interface shear stresses, different fiber fracture volume fractions and different cycle numbers.

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 Patents(China)
IPC IPC(8): G06F30/17G06Q10/04G06F113/26
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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