2.5D机织C_f/Al复合材料高温拉伸力学行为数值模拟与实验研究

Numerical and experimental study of tensile mechanical behavior of 2.5D woven C_f/Al composites at high temperature

摘要

2.5D机织复合材料因高比强度、高比模量和良好的抗分层性能而在航空航天领域极具应用前景，目前尚缺乏其高温力学性能与破坏行为的研究。针对2.5D机织C_f/Al复合材料，开展高温400 ℃下准静态拉伸力学响应与失效行为的数值模拟与实验研究。基于纱线内部组织和纱线的周期性分布特征，构建微观和细观尺度的代表性单胞模型，结合与温度相关的基体和界面性能参数，建立微观和细观尺度的有限元模型，分析高温环境下复合材料热应力分布以及拉伸载荷下的宏细观力学行为。高温环境下复合材料内部热应力分布不均，基体主要承受压应力作用而纱线则处于拉应力状态；高温拉伸模量、拉伸强度和伸长率的实验值分别为63.7 GPa、238 MPa和0.72%，高温拉伸曲线的数值模拟结果与实验结果基本一致，二者误差小于10%；高温拉伸过程中热应力导致的基体与界面损伤逐渐累积和扩展，拉伸前期出现明显的界面失效与脱粘现象，随着拉伸应变增加，复合材料先后发生纬纱的横向开裂和经纱的局部失效，拉伸后期严重的经纱轴向断裂导致复合材料失去承载能力而发生破坏。

Abstract

2.5D woven composites show great promise for aerospace applications owing to their high specific strength, high specific modulus and good delamination resistance. However, there is a dearth of research on their mechanical properties and failure behaviour at high temperature environment. This paper presents numerical simulation and experimental study on the quasi-static tensile mechanical response and failure behaviour of 2.5D woven C_f/Al composites at high temperature (400 ℃). Representative unit-cell models at the micro- and meso-scale are constructed based on the microstructure and periodic arrangement characteristics of the yarn. Based on the temperature-related material parameters of the matrix and interface, a multiscale finite element model is established to numerically analyse the thermal stress distribution as well as macroscopic and mesoscopic mechanical behaviour of the composites at high-temperature environment. The high temperature induces inhomogeneous thermal stress distribution in the composites, where the matrix and yarns are subjected to compressive and tensile stress, respectively. The experimental results show that the tensile modulus, ultimate strength and elongation of the composites are 63.7 GPa, 238 MPa and 0.72%, respectively. The numerical tensile stress-strain curve is generally consistent with the experimental results. Numerical simulation results show that the matrix and interface damage that induced by the thermal stresses accumulates and expands gradually during the tensile process. This results in the emergence of local interface debonding at the initial tensile stage. As the tensile strain increases, the composites successively experience the local failure of warp yarns and transverse cracking of weft yarns. At the final stage, the severe axial fracture of warp yarns leads to catastrophic fracture of the composite, resulting in a dramatic drop of the tensile stress curve. The fractured warp yarn exhibits a rough fracture surface with the characteristics of fibre pull-out and matrix alloy tearing.

关键词

铝基复合材料 / 2.5D织物 / 高模量碳纤维 / 高温力学性能 / 失效机制 / 数值模拟

Key words

aluminium matrix composite / 2.5D fabric / high-modulus carbon fiber / high temperature mechanical property / failure mechanism / numerical simulation

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基金资助

国家自然科学基金(52165018)

国家自然科学基金(52261031)

江西省主要学科学术和技术带头人-领军人才计划(20225BCJ22002)

航空科学基金(2019ZF056013)

江西省自然科学基金(20242BAB20164)

江西省自然科学基金(20212BAB214035)

江西省自然科学基金(20232ACB204003)