航空复合涂层材料的激光烧蚀效应

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。

Laser ablation effect of composite coating applied to aerospace material

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.