基于等离子喷涂法的火箭弹尾翼热障涂层试验研究  

Thermal Barrier Coating Test in Empennage of Rocket Projectile Based on Method of Plasma Spray

作　　者：霍文娟 李龙飞 孔为民 刘巍浩 HUO Wen-juan;LI Long-fei;KONG Wei-min;LIU Wei-hao(Jinxi Industries Group Co. Ltd. , Taiyuan 030027, China;Engineering Training Center, North University of China, Taiyuan 030051, China)

机构地区：[1]晋西工业集团有限责任公司,山西太原030027 [2]中北大学工程训练中心,山西太原030051

出　　处：《中北大学学报（自然科学版）》2018年第2期200-205,共6页Journal of North University of China(Natural Science Edition)

摘　　要：针对火箭弹飞行中尾翼遭受气动加热损伤而造成飞行失效的问题,通过分析其尾翼结构特征,设计了适应尾翼工况的热障涂层结构和等离子喷涂制备方法,分析了预处理对热障涂层与基体结合力的影响,以及等离子喷涂工艺参数对热障涂层沉积率的影响,并进行了热障涂层静态和动态测试试验.试验结果表明,该热障涂层与基体的结合强度由10MPa提高至20MPa,风洞试验中,热障涂层可以在1 800℃高温和20s时间内,克服气动热而不产生剥落.The empennage suffers from damage for aerodynamic heating at rocket projectile flying,and the flying can be failed.Through analyzing the structure of empennage,the thermal barrier coating（TBC）structure and preparation method of plasma spray were designed,which suited for the working conditions of empennage.The influence of pretreatment on binding force of matrix and TBC were analyzed,and the influence of plasma spraying process parameters on deposition rate of TBC was analyzed.The static and dynamic test of TBC was made.Test results show that the bonding strength of the modified TBC with the matrix is increased from 10 MPa to 20 MPa,and TBC can overcome aerodynamic heat without peeling at 1 800 ℃ and in 20 sby the wind tunnel test.

关 键 词：热障涂层 尾翼 火箭弹 等离子喷涂 

分 类 号：TG156.99[金属学及工艺—热处理]