The CFRP/Ti6Al4V composite has excellent properties of CFRP and Ti6Al4V. Therefore, they are widely used in aerospace and some military fields. The laminated structure of CFRP/Ti6Al4V composite is different from the traditional homogeneous workpiece, and the properties of each layer are diverse, so the processing performance is poor. The experimental research cost of CFRP/Ti6Al4V composites is relatively high and has certain limitations. The finite element method is a promising alternative. In the research, a finite element model combining the macro and micro with the fiber orientation of 90° was established. By combining the mechanism of exit burr formation in the cutting direction of Ti6Al4V and the delamination mechanism of CFRP composites, a new mechanical model was proposed for CFRP/Ti6Al4V composites during this study, and it was found that there is not a linear relationship between the rake angle and the delamination of CFRP/Ti6Al4V composites during the cutting process. The results show that the delamination damage of CFRP/Ti6Al4V composites is serious when the rake angle is 4° ~ 10°. The delamination damage is light when the rake angle is 0° ~ 4°. And the delamination damage is the smallest when the rake angle is 10° ~ 20°. In the cutting process, the tremor of the Ti6Al4V phase is also an important factor for delamination. During the extrusion of Ti6Al4V relative to the CFRP phase, the fragmentation of the epoxy matrix leads to brittle fracture of the carbon fibers and shear damage can occur. The brittle fracture height is minimum when the rake angle is 16°. The shear damage height is minimum when the rake angle is 10°. The tremor of Ti6Al4V phase is also an important factor for delamination damage. The fracture of the epoxy resin matrix leads to brittle fracture and shear damage of carbon fiber. The brittle fracture height has a linear relationship with the fracture height of epoxy resin. When the cutting sequence is CFRP → Ti6Al4V, a better surface quality can be obtained, effectively avoiding carbon fiber brittle fracture. Therefore, the rake angle and cutting sequence are of great importance for processing CFRP/Ti6Al4V composites. Therefore, it is of reference significance for the machining of 90° fiber orientation.

CFRP/Ti6Al4V复合材料具有CFRP和Ti6Al4V的优良性能。因此，它们被广泛应用于航空航天和一些军事领域。CFRP/Ti6Al4V复合材料的层状结构不同于传统的均质工件，每一层的性能多种多样，因此加工性能较差。CFRP/Ti6Al4V复合材料的实验研究成本较高，具有一定的局限性。有限元方法是一种很有前景的替代方法。在研究中，建立了纤维取向为90°的宏观与微观相结合的有限元模型。本研究结合 Ti6Al4V 切削方向出口毛刺形成机理和 CFRP 复合材料的分层机理，提出了一种新的 CFRP/Ti6Al4V 复合材料力学模型，发现切削过程中CFRP/Ti6Al4V复合材料的前角与分层之间不存在线性关系。结果表明，当前角为4°～10°时，CFRP/Ti6Al4V复合材料的分层损伤严重。前角0°～4°时分层损伤较轻。且前角为10°～20°时分层损伤最小。在切割过程中，Ti6Al4V相的震颤也是造成分层的重要因素。在 Ti6Al4V 相对于 CFRP 相的挤压过程中，环氧树脂基体的碎裂导致碳纤维脆性断裂并可能发生剪切损伤。前角为16°时脆性断裂高度最小。前角为10°时剪切损伤高度最小。Ti6Al4V相的震颤也是造成分层破坏的重要因素。环氧树脂基体的断裂导致碳纤维脆性断裂和剪切破坏。脆性断裂高度与环氧树脂的断裂高度呈线性关系。当切削顺序为CFRP→Ti6Al4V时，可获得较好的表面质量，有效避免碳纤维脆性断裂。因此，前角和切削顺序对于加工CFRP/Ti6Al4V复合材料非常重要。因此，对90°纤维取向的加工具有参考意义。当切削顺序为CFRP→Ti6Al4V时，可获得较好的表面质量，有效避免碳纤维脆性断裂。因此，前角和切削顺序对于加工CFRP/Ti6Al4V复合材料非常重要。因此，对90°纤维取向的加工具有参考意义。当切削顺序为CFRP→Ti6Al4V时，可获得较好的表面质量，有效避免碳纤维脆性断裂。因此，前角和切削顺序对于加工CFRP/Ti6Al4V复合材料非常重要。因此，对90°纤维取向的加工具有参考意义。