长征7号火箭发射台用耐高温涂层的研制  

Development of a High Temperature Resistant Coating for CZ-7 Launch Pad

作　　者：张巍[1] 马磊[1] 王晓东[1] 张涛[1] ZHANG Wei;MA Lei;WANG Xiaodong;ZHANG Tao(Laboratory of Catalysts and New Materials for Aerospace, Dalian Institute of Chemical and Physics, Chinese Academy of Science, Liaoning Dalian 116023, China)

机构地区：[1]中国科学院大连化学物理研究所航天催化与新材料研究室,辽宁大连116023

出　　处：《弹箭与制导学报》2017年第5期77-80,共4页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：中国科学院知识创新工程重要方向项目(YYYJ-1106-3)资助

摘　　要：为了研制用于火箭发射台的耐高温涂层,文中提出了双层涂层结构,底层以环氧树脂为基体材料;表层以焦宝石、堇青石和高铝水泥等为原料。试验结果表明:底层附着力达18.87 MPa;表层耐火度为1 660℃,常温耐压强度达48.7 MPa,导热系数为0.692 W/(m·K),热膨胀系数在200℃时为8.73×10^(-6)℃^(-1);耐高温涂层线烧蚀率为0.277 mm/s,背温不超过80℃。将所研制的耐高温涂层在长征7号火箭发射台上使用,结果表明:耐高温涂层能够承受长征7号火箭发射时的燃气流冲刷,满足使用要求。In order to develop a high temperature resistant coating for launch pad, double layer coating material structure was proposed in this paper. Epoxy resin was the bottom substrate material and surface material was composed of calcined flint clay, cordierite and calcium aluminate cement. The results show that adhesion of bottom material is 18. 87 MPa, refractoriness of surface material is 1 660℃, cold crushing strength after cuing one day of surface material is 48. 7 MPa, thermal conductivity of surface material is 0. 692 W/（ m · K）, ther- mal expansion coefficient（200 ℃ ） of surface material is 8.73 × 10^（ -6）℃ -1. Linear ablation rate of the high temperature resistant coating is 0. 277 mm/s, temperature of the back side is less than 80 ℃. The developed high temperature resistant coating is used on the launch pad of CZ-7, and the results show that the heat-resistant coating could bear the combustion-gas stream when the rocket of CZ-7 launched, which meet the requirements.

关 键 词：火箭发射台 耐高温 涂层 

分 类 号：V553.1[航空宇航科学与技术—人机与环境工程] TQ637.6[化学工程—精细化工]