Carbon-fiber-reinforced polymer (CFRP) composite is widely used in aerospace industry. The protective paint on the CFRP of aircraft needs to be removed after reaching a certain useful life. Laser cleaning has the advantages of high efficiency and environmental protection. However, the main obstacle to the application of laser cleaning on CFRP is the thermal damage caused by the laser radiation absorbed on the surface or inside of the substrate. In order to understand the interaction between laser and each layer of material, and the influence of laser parameters on the substrate temperature rise. Based on the ‘element death’ technique of the finite element (FE) method, a numerical model of material removal on a heterogeneous fiber–matrix mesh was established, which can accurately simulate the heat transfer process between carbon fiber and resin matrix. The effects of laser energy density, spot overlap rate and adjacent scanning line interval on material removal and the peak temperature of the substrate were investigated. The results show that the pulsed laser paint removal process will produce two high temperature zones on the resin layer and the heterogeneous material, and the superposition of adjacent pulse energy can significantly increase the temperature rise of the substrate.

碳纤维增强聚合物（CFRP）复合材料广泛应用于航空航天工业。飞机碳纤维复合材料上的保护漆在达到一定的使用寿命后需要去除。激光清洗具有高效、环保等优点。然而，在 CFRP 上应用激光清洗的主要障碍是由基板表面或内部吸收的激光辐射引起的热损伤。以了解激光与各层材料的相互作用，以及激光参数对基板温升的影响。基于有限元（FE）方法的“单元死亡”技术，建立了异质纤维矩阵网格上材料去除的数值模型，可准确模拟碳纤维与树脂基体之间的传热过程。研究了激光能量密度、光斑重叠率和相邻扫描线间距对材料去除和衬底峰值温度的影响。结果表明，脉冲激光脱漆工艺会在树脂层和异质材料上产生两个高温区，相邻脉冲能量的叠加可显着提高基材的温升。