固化残余应力和变形对钛合金损伤构件CFRP单面贴补结构拉伸性能的影响

doi:10.7527/S1000-6893.2025.31997

Abstract

Abstract:

Due to its excellent mechanical properties and strong process feasibility， CFRP is commonly used to repair damaged aerospace metal components. However， the differences in physicochemical properties among the metal， adhesive layer， and patch often induce curing residual stresses and deformation in the bonded area after forming， which can affect the load-bearing performance of the repaired structure. This study investigates the effects of residual stress and curing deformation. Tensile tests were designed for single-sided CFRP patch repairs on damaged titanium alloy components， and a multi-stage numerical analysis method was established， covering the process from co-curing bonding to quasi-static tensile loading. Through comprehensive analysis of experimental and simulation results， the strain evolution behavior of the adhesive layer during the curing stage was clarified， the stress-strain curves and damage failure modes during the tensile stage were compared， and the influence of curing processes on tensile performance was explored. The results show that the strain in the adhesive layer during curing can be divided into five stages， with a simulation error of less than 20% compared to experimental data. The multi-stage simulation method， which accounts for residual stress and curing deformation， yields stress-strain curves that align more closely with experimental results， achieving an error of only 1.39% in ultimate tensile stress. Additionally， the failure modes of different materials observed in the simulation matched those in the experiments. Regarding curing processes， reducing the heating rate and extending the dwell time improved the curing degree and modulus of the patch and adhesive layer. This also reduced tensile stress and increased compressive stress in the titanium alloy substrate along the loading direction， ultimately enhancing the overall tensile performance of the structure.

Key words: composite materials, patch repair, damaged titanium alloy components, curing residual stress and deformation, multi-stage numerical analysis, tensile performance

CLC Number:

V267⁺.45

Chunhao FAN, Junshan HU, Zhiyong YANG, Fusen HOU, Peilin CHEN, Wei TIAN. Effects of curing residual stress and deformation on tensile performance of CFRP single-sided patch-repaired titanium alloy damaged components[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(3): 431997.

Figures/Tables 26

Fig.1

Fig.2

Fig.3

Fig.4

Fig.5

Fig. 6

Table 1

Table 2

Thermo-mechanical model parameters［11，42-44］

参数	纤维	树脂	TC4
弹性模量/MPa	E_lf=138 000	$E r ∞$ =2 910	E_TC4=110 000
弹性模量/MPa	E_tf=9 310	$E r ∞$ =2 910	E_TC4=110 000
剪切模量/MPa	G_23f=5 000
剪切模量/MPa	G_12f=G_13f=4 810
泊松比	ν_23f=0.45	ν_r=0.38	ν_TC4=0.34
泊松比	ν_12f=ν_13f=0.32	ν_r=0.38	ν_TC4=0.34
热膨胀系数/（10^-6 K^-1）	β_11f=-0.9	β_r=81.4	β_TC4=8.6
热膨胀系数/（10^-6 K^-1）	β_22f=β_33f=7.2	β_r=81.4	β_TC4=8.6
化学收缩系数/10^-3		γ_r=6.98

Table 2

Table 3

Fig.7

Table 4

Damage model parameters of resin［18］

参数	数值	参数	数值
黏结力d/MPa	97.6	摩擦角β/（°）	37.7
D-P指数κ	0.8	断裂能G/（J·m^-2）	1
初始损伤应变 $ε ¯$ $p d$	0.25

Table 4

Table 5

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Fig.13

Fig.14

Fig.15

Fig.16

Fig.17

Fig.18

Fig.19

Fig.20

Fig.21

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参数	数值	参数	数值
ρ_c/（kg·m^-3）	1 230	V_f/%	67
c_c/（J·kg^-1·K^-1）	1 580	H_r/（J·g^-1）	401.5
c_a/（J·kg^-1·K^-1）	1 740	A/（10¹⁰s^-1）	1.494
k_x /（W·m^-1·K^-1）	5.43	ΔE/（J·mol^-1）	94 750
k_y， k_z /（W·m^-1·K^-1）	0.41	m	0.45
ρ_a/（kg·m^-3）	1 600	n	1.877
k_TC4/（W·m^-1·K^-1）	7.955	c_TC4/（J·kg^-1·K^-1）	612

参数	数值	参数	数值
初始屈服应力A′	1 040	a₁	-0.09
应变硬化模量B′	1 030	a₂	0.27
应变硬化指数n′	0.757	a₃	-0.48
应变率硬化系数C′	0	a₄	0
温度软化指数m′	0	a₅	0

参数	数值
纤维方向拉伸强度X_T/MPa	2 890
纤维方向压缩强度X_C/MPa	2 065
面内横向拉伸强度Y_T/MPa	92
面内横向压缩强度Y_C/MPa	187
厚度方向拉伸强度Z_T/MPa	92
厚度方向压缩强度Z_C/MPa	187
23面内剪切强度S₂₃/MPa	61
12、23面内剪切强度S₁₂=S₁₃/MPa	107

Effects of curing residual stress and deformation on tensile performance of CFRP single-sided patch-repaired titanium alloy damaged components

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