斜纹碳布缝合织物结构增强铝基复合材料的高温拉伸及断裂行为

doi:10.11900/0412.1961.2023.00469

金属学报

2025, Vol. 61

Issue (9): 1387-1402 DOI: 10.11900/0412.1961.2023.00469

研究论文

本期目录 | 过刊浏览

斜纹碳布缝合织物结构增强铝基复合材料的高温拉伸及断裂行为

吴志勇¹, 邵徽凡¹, 蔡长春¹, 曾敏¹, 王振军¹(

), 王艳丽², 陈雷², 熊博文¹

1 南昌航空大学航空制造工程学院南昌 330063
2 中航工业江西洪都航空工业集团有限责任公司南昌 330096

Tensile and Fracture Behaviors of Stitched Twill Carbon Fabric Structure Reinforced Aluminum Matrix Composites at Elevated Temperature

WU Zhiyong¹, SHAO Huifan¹, CAI Changchun¹, ZENG Min¹, WANG Zhenjun¹(

), WANG Yanli², CHEN Lei², XIONG Bowen¹

1 School of Aeronautical Manufacturing Engineering, Nanchang Hangkong University, Nanchang 330063, China
2 AVIC Jiangxi Hongdu Aviation Industry Group Co. Ltd., Nanchang 330096, China

引用本文:

吴志勇, 邵徽凡, 蔡长春, 曾敏, 王振军, 王艳丽, 陈雷, 熊博文. 斜纹碳布缝合织物结构增强铝基复合材料的高温拉伸及断裂行为[J]. 金属学报, 2025, 61(9): 1387-1402.
Zhiyong WU, Huifan SHAO, Changchun CAI, Min ZENG, Zhenjun WANG, Yanli WANG, Lei CHEN, Bowen XIONG. Tensile and Fracture Behaviors of Stitched Twill Carbon Fabric Structure Reinforced Aluminum Matrix Composites at Elevated Temperature[J]. Acta Metall Sin, 2025, 61(9): 1387-1402.

全文: PDF(4144 KB) HTML

摘要:

三维织物增强铝基复合材料具有高比强度、高比模量以及优良的耐高温和抗冲击性能，是制造航空航天耐热结构的理想材料，目前尚缺乏其高温环境下力学特性与失效机制的系统性研究。本工作研究了高温(400 ℃)环境下斜纹碳布缝合织物结构增强铝基复合材料的准静态拉伸力学行为与失效机理，并根据其织物结构和纱线微观组织特征建立了基于微观和细观尺度代表性单胞的细观力学有限元模型；采用数值模拟与实验结合的方法分析了复合材料在高温拉伸过程中的宏观力学响应、组元结构损伤演化与渐进失效行为。结果表明，复合材料的高温拉伸模量、强度与断裂应变的实验均值分别为103.20 GPa、621.60 MPa和0.819%，数值模拟得到拉伸应力-应变曲线与复合材料高温拉伸实验曲线总体上吻合较好。高温环境下复合材料内部存在复杂的热应力，基体合金和纱线分别处于压应力和拉应力状态。在拉伸初期阶段，复合材料中缝合纱失效、经/纬纱搭接处基体损伤和经纱局部失效，但表现出了线弹性力学响应。随着拉伸载荷增大，基体的损伤程度加重且沿织物斜纹方向出现严重的基体损伤区和纬纱开裂区，导致随应变增加拉伸应力的增长速率减缓。拉伸变形后期产生显著且互相重叠的基体和纱线失效带，经纱的轴向断裂使得复合材料失去承载能力并且拉伸应力急剧下降。高温拉伸断口中缝合纱和纬纱的断口较为平整，而经纱的断裂拔出长度不一，且呈现大量纤维断裂拔出并伴随基体合金撕裂的微观形貌特征。

关键词 ：斜纹碳布缝合织物, 铝基复合材料, 细观力学, 损伤演化, 高温力学性能, 失效机制

Abstract：

Three-dimensional fabric-reinforced aluminum matrix composites with high specific strength and modulus, excellent high-temperature resistance, and impact resistance are ideal structural materials for fabricating heat-resistant components in aeronautics and aerospace engineering. However, few studies have explored the mechanical properties and fracture behaviors of these composites in high-temperature environments. This study aims to investigate the quasi-static tensile behaviors and failure mechanisms of a stitched twill carbon fabric-reinforced aluminum matrix composite at an elevated temperature of 400 ^oC. Based on the fabric structure and yarn microstructure, a mesoscle finite element model was established using representative unit cells at the microsale and mesoscale. The macroscopic mechanical response, damage evolution, and failure mechanism of the composite during the tensile test at an elevated temperature (400 ^oC) were analyzed through numerical simulations and experiments. Results show that the tested tensile modulus, strength, and fracture strain at 400 ^oC are 103.20 GPa, 621.60 MPa, and 0.819%, respectively. The calculated tensile stress-strain curve aligns with the experimental curves obtained from high-temperature tensile tests. The composites experience complex thermal stress at elevated temperatures, with the matrix pocket under compressive stress and the yarn structure under tensile stress. In the initial tensile stage, the matrix between interlaced weft/warp yarns is damaged, and local failure zones appear in the stitch and warp yarns; however, the composite exhibits a linear elastic response. As the tensile load increases, the degree of damage in the matrix pocket gradually increases, leading to the emergence of serious matrix damage zones and weft yarn cracking along the twill direction of the fabric. Consequently, the growth rate of tensile stress in the tensile curve declines with increasing tensile strain. In the final stage, the matrix failure zone and yarn fracture zone overlap. The axial fracture of warp yarn, in particular, leads to catastrophic fracture of the composite, resulting in a dramatic drop of the tensile stress. The stitch and weft yarns in the composites exhibit a flat fracture morphology, whereas the fractured warp yarn presents rugged fracture surfaces. A mass of fiber pull-out is observed on the microscopic fracture surface of a warp yarn, accompanied by matrix alloy tearing characteristics.

Key words： stitched twill carbon fabric structure aluminum matrix composites micromechanics damage evolution high temperature mechanical property failure mechanism

收稿日期: 2023-12-01

ZTFLH:

TG335.85

基金资助:国家自然科学基金项目(52165018);江西省主要学科学术和技术带头人培养计划项目(20225BCJ22002)

通讯作者: 王振军，wangzhj@nchu.edu.cn，主要从事金属基复合材料设计制备及其结构强度理论研究

Corresponding author: WANG Zhenjun, professor, Tel: 18970951974, E-mail: wangzhj@nchu.edu.cn

作者简介: 吴志勇，男，1998年生，硕士

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https://www.ams.org.cn/CN/10.11900/0412.1961.2023.00469 或 https://www.ams.org.cn/CN/Y2025/V61/I9/1387

图1 斜纹碳布缝合织物结构示意图和表面形貌及铝基复合材料表面形貌

图2 铝基复合材料与铝合金高温拉伸试样尺寸示意图

图3 铝基复合材料中纱线截面形态与显微结构

图4 铝基复合材料细观尺度结构模型建模过程示意图

图5 铝基复合材料细观尺度代表性体积单元(RVE)模型及其离散化处理，及周期性边界条件

图6 基体铝合金的拉伸工程应力-应变曲线

Temperature / ^oC	E^m / GPa	$ε ¯ 0 p l$ / %	$ε ¯ f p l$ / %	α / (10^-6 K^-1)^[34]
25	70.48	0.27	1.2	22.7
100	45.65	0.43	1.5	25.4
200	33.14	0.74	2.0	26.5
300	24.22	2.20	3.2	27.8
400	12.89	3.20	4.5	29.9

表1 基体铝合金的弹-塑性力学性能参数和热膨胀系数[34]

图7 hcp结构纤维分布示意图、微观尺度RVE模型及其离散化处理

Parameter	Symbol	Value	Unit	Ref.
Axial tensile strength	$X t f$	4400	MPa	[41]
Axial compressive strength	$X c f$	2250	MPa	[33]
Axial shear strength	$S 12 f$	340	MPa	[33]
Axial elastic modulus	$E 11 f$	377	GPa	[41]
Axial shear modulus	$G 12 f$	8.9	GPa	[39]
Axial Poisson's ratio	$ν 12 f$	0.26		[33]
Axial thermal expansion coefficient	$α 11 f$	-0.83	10^-6 K^-1	[39]
Transverse tensile strength	$Y t f$	175	MPa	[40]
Transverse compressive strength	$Y c f$	590	MPa	[40]
Transverse shear strength	$S 23 f$	240	MPa	[40]
Transverse elastic modulus	$E 22 f$	19	GPa	[39]
Transverse shear modulus	$G 23 f$	7.3	GPa	[40]
Transverse Poisson's ratio	$ν 23 f$	0.3		[33]
Transverse thermal expansion coefficient	$α 22 f$	8.0	10^-6 K^-1	[39]

表2 纤维材料的弹性常数、极限强度及热膨胀系数[33,39~41]

图8 不同载荷条件下纱线高温(400 ℃)力学行为的微观RVE有限元计算结果

Parameter	Symbol	Value	Unit
Axial tensile modulus	$E 11 t$	262.8	GPa
Axial compression modulus	$E 11 c$	259.4	GPa
Axial shear modulus	$G 12 s$	8.9	GPa
Transverse tensile modulus	$E 22 t$	19.8	GPa
Transverse compression modulus	$E 22 c$	20.3	GPa
Transverse shear modulus	$G 23 s$	7.2	GPa
Axial tensile strength	$X 11 t$	3027.1	MPa
Axial compression strength	$X 11 c$	1577.4	MPa
Axial shear strength	$X 12 s$	39.9	MPa
Transverse tensile strength	$X 22 t$	83.6	MPa
Transverse compression strength	$X 22 c$	86.1	MPa
Transverse shear strength	$X 23 s$	38.9	MPa

表3 纱线的高温弹性常数与强度性能参数

Temperature / ^oC	α₁₁ / (10^-6 K^-1)	α₂₂ / (10^-6 K^-1)	E₁₁ / GPa	E₂₂ / GPa	G₁₂ / GPa	G₂₃ / GPa	$ν$ ₁₂	$ν$ ₂₃
25	3.11	9.94	283.28	23.98	11.03	9.34	0.28	0.41
100	3.03	10.28	282.11	23.50	10.89	8.91
200	2.94	10.39	275.99	22.80	10.54	8.68
300	2.82	10.53	269.96	22.19	9.69	8.06
400	2.68	10.78	268.11	21.86	9.42	7.86

表4 纱线在不同温度下的线性热膨胀系数和弹性常数

图9 细观尺度单胞有限元模型中纱线的局部材料坐标轴示意图

图10 高温(400 ℃)下铝基复合材料的热应力分布状态

图11 400 ℃下铝基复合材料的拉伸应力-应变实验曲线与预测曲线

表5 铝基复合材料高温拉伸力学性能的实验与计算结果

图12 拉伸变形初期复合材料组元的结构损伤与失效状态

图13 拉伸变形中期复合材料组元的结构损伤与失效状态

图14 拉伸变形末期复合材料组元的结构损伤与失效状态

图15 400 ℃拉伸时铝基复合材料的断口形貌

图16 高温拉伸断裂时纱线结构失效模型

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