An investigation of interfacial fracture modelling of carbon fibre reinforced plastic (CFRP) laminates at the atmosphere similar to the cruise condition of an aircraft has been carried out in this article. The Mode I & Mode II fracture tests are carried out using specimen of aerospace grade composite (AS4/914) at$-{55}^{0}C$. Compliance based methods for estimation of crack growth have been adopted for monitoring during the fracture tests. A new set of thermally influenced interfacial fracture properties are evaluated for AS4/914 laminates. A modified traction – separation law has been derived for Mode-I loadings considering the influence of fibre bridging under influence of extremely cold environmental conditions. This law has been evaluated from the superposition of traditional bilinear law and derived bridging law. A significant reduction in interlaminar fracture toughness has been observed due to the fragile nature of the matrix under cold environment. Experimentally obtained interfacial fracture properties are implemented into the numerical formulation. Extended Isogeometric Analysis augmented with Cohesive Zone Modelling (XIGA-CZM) for unidirectional CFRP laminate has been enhanced and enriched with thermally influenced fracture toughness properties for further investigation. Results obtained from the present XIGA-CZM formulation shows a good agreement with experimentally obtained results. Scanning Electron Microscope (SEM) observation of fractured surfaces are carried out to investigate the nature of crack propagation in CFRP laminate at$-{55}^{0}C$.

本文已经对碳纤维增强塑料（CFRP）层压板在类似于飞机巡航条件的大气环境下的界面断裂建模进行了研究。使用航空级复合材料（AS4 / 914）的样品在I型和II型断裂试验中进行$-{55}^{0}C$。在断裂测试过程中，已经采用基于一致性的方法来估计裂纹扩展。对AS4 / 914层压板评估了一组新的受热影响的界面断裂性能。考虑到极端寒冷环境条件下光纤桥接的影响，已经为I型载荷推导了一种改进的牵引－分离定律。已从传统双线性定律和派生的桥接定律的叠加中对该定律进行了评估。由于基质在寒冷环境下的脆性，已观察到层间断裂韧性的显着降低。将实验获得的界面断裂特性实现为数值公式。对于单向CFRP层压板，通过内聚力区域建模（XIGA-CZM）扩展的扩展等轴测分析得到了增强，并增加了受热影响的断裂韧度特性，以供进一步研究。从目前的XIGA-CZM配方获得的结果与实验获得的结果显示出良好的一致性。扫描电子显微镜（SEM）观察断裂表面，以研究CFRP层压板中裂纹扩展的特性。$-{55}^{0}C$。