低温下复合材料层合板就位效应的细观力学分析  

Micromechanical analysis of in-situ effect of composite laminates at cryogenic temperatures

作　　者：贺丹[1] 张在强 常鑫 HE Dan;ZHANG Zaiqiang;CHANG Xin(Key Laboratory of Liaoning Province for Composite Structural Analysis of Aerocraft and Simulation,Shenyang Aerospace University,Shenyang 110136,China;Light Alloy Research Institute,Central South University,Changsha 410083,China;State Key Laboratory of Precision Manufacturing for Extreme Service Performance,Central South University,Changsha 410083,China)

机构地区：[1]沈阳航空航天大学辽宁省飞行器复合材料结构分析与仿真重点实验室,沈阳110136 [2]中南大学轻合金研究院,长沙410083 [3]极端服役性能精准制造全国重点实验室,长沙410083

出　　处：《沈阳航空航天大学学报》2025年第1期14-24,共11页Journal of Shenyang Aerospace University

基　　金：国家重点研发计划项目(项目编号:2020YFA0711104);XX行动项目(项目编号:933A2AB1)。

摘　　要：在低温状态下,复合材料贮箱容易产生微裂纹。准确地预测低温状态下结构微裂纹起始与演化规律对于贮箱结构设计及优化至关重要。为此,建立了嵌入式多纤维代表性体积单元模型,研究低温状态对考虑就位效应的复合材料层合板微裂纹起始及扩展规律的影响,该模型由两个0°相邻约束层和90°中间层组成。在横向拉伸载荷及低温条件下,获得了结构中微裂纹起始应变及拉应力,并对微裂纹起始与演化的规律进行了研究。结果表明,低温条件显著影响了结构微裂纹起始位置及扩展路径,且温度越低,结构越容易萌生微裂纹。在纤维排列较为紧密的区域,低温条件下更容易发生界面脱粘现象。热应力的存在还导致了常温和低温状态下模型微裂纹起始位置存在差异。在常温和低温状态下,中间层的结构损伤演化规律基本一致。Composite material tanks are prone to microcracks at cryogenic temperature conditions.Accurately predicting the initiation and evolution of structural microcracks at cryogenic temperatures is crucial for the design and optimization of tank structures.An embedded multi-fiber representative volume element model was established to study the influence of cryogenic temperature conditions on the initiation and evolution of microcracks in composite laminates that considered the in-situ effect.This model was consisted of two 0°adjacent constraint layers and a 90°intermediate layer.Under transverse tensile loads and cryogenic temperature conditions,the microcrack initiation strain and tensile stress in the structure were obtained,and the initiation and evolution of microcracks were studied.The results show that cryogenic temperatures significantly influence the initiation location and evolution path of microcracks in structures.Microcracks are prone to occur in structures at cryogenic temperatures.The interface debonding is more likely to occur in regions with denser fiber arrangements at cryogenic temperatures.The thermal stress results in variations in microcrack initiation location between ordinary temperature and cryogenic temperature conditions.Notably,the structural damage evolution pattern in the intermediate layer remains consistent under both ordinary and cryogenic temperatures.

关 键 词：复合材料层合板 代表性体积单元 细观力学 就位效应 微裂纹 

分 类 号：V414.8[航空宇航科学与技术—航空宇航推进理论与工程]