The application of carbon fiber reinforced polymer (CFRP) Multidirectional (MD) laminates in aircraft structure have motivated the manufacturers to tailor the mechanical strength in desired directions. The complex stress field owing to multiple orientations with the loading direction increases the intricacy of failure analysis. Hence, the macroscopic and microscopic fracture behaviour of MD CFRP laminates under static loading needs to be explored further. In this study, four different MD CFRP laminates were fabricated using IMA/M21 prepregs by the autoclaving technique. Effect of fiber orientation on static strength i.e. tensile and compressive strength was studied. The strength decreased with the increase in orientation angle. Scanning electron micrographs revealed that irrespective of the lay-up sequence individual layers failed parallel to the fiber direction. Fiber breakage and delamination were the major failure modes in tensile specimens while kinking, matrix failure, in-plane shear, stepped fracture, and fiber-matrix debonding were dominated in compression specimens. The theoretical and experimental data was in good agreement with the Weibull distribution model.

碳纤维增强聚合物（CFRP）多向（MD）层压板在飞机结构中的应用促使制造商在所需方向上调整机械强度。由于载荷方向有多个方向而导致的复杂应力场增加了失效分析的复杂性。因此，需要进一步研究MD CFRP层压板在静态载荷下的宏观和微观断裂行为。在这项研究中，使用IMA / M21预浸料通过高压灭菌技术制造了四种不同的MD CFRP层压板。研究了纤维取向对静态强度（即拉伸强度和压缩强度）的影响。强度随着取向角的增加而降低。扫描电子显微照片显示，不管层叠顺序如何，各层平行于纤维方向均失效。纤维断裂和分层是拉伸试样的主要破坏方式，而压缩试样则主要是扭结，基体破坏，面内剪切，阶梯状断裂和纤维-基体脱胶。理论和实验数据与威布尔分布模型吻合良好。