针对航空激光防护技术研究需求, 开展了复合涂层材料的激光烧蚀效应综合研究。采用圆棒固体激光器作为测试光源, 搭建了具有在线温度测量功能的烧蚀实验平台。在此基础上, 对聚碳硅烷(PCS)涂层样品开展了激光烧蚀实验。通过对烧蚀区域形貌和温度数据的对比分析, 证明了PCS复合材料具备显著的激光防护作用。同时, 从理论方面对涂层的激光防护机理进行了研究, 基于材料热传导方程, 建立了激光烧蚀过程的热力学模型, 对温度场变化进行了模拟。研究结果表明, 在复合涂层的保护下, kW级激光仅产生百℃的金属基底升温。

This paper concentrates on the measurement and analysis of laser ablation effect of particularly prepared aerospace material, polycarbosilane (PCS). Laser ablation experiment setup is designed and built, based on a continuous-wave high-power solid-state laser (CWHPSSL). Metal-shell samples with composite PCS are prepared. Then a group of laser ablation experiments are performed on those samples. They are processed by laser beam with thousands of W/cm2. The results, including the ablation morphology and temperature data, are shown and discussed. Temperature data give a good demonstration of the protection effect of composite coating, and in the meanwhile the minor-morphologies in the ablated region hint the principle of PCS laser-proof effect. After that, a theoretical investigation is carried out. Fourier equation of heat conduction is applied to modeling the temperature field during ablation process. The simulation provides a good explanation on the principle of laser-proof effect of PCS composite coating. The results demonstrate that, with the protection of PCS composite coating, kilowatt-level laser only results in hundreds of Celcius temperature increment of steel substrate.