重型火箭发射平台热防护方法探究  

Research on Thermal Protection Scheme of Heavy Rocket Launching Platform

作　　者：冯超[1] 徐铮[1] 平仕良[1] 吴新跃[1] 毛利民 Feng Chao;Xu Zheng;Ping Shi-liang;Wu Xin-yue;Mao Li-min(Beijing Institute of Space Launch Technology,Beijing,100076;Space System Department Equipment Department,Beijing,100076)

机构地区：[1]北京航天发射技术研究所,北京100076 [2]航天系统部装备部,北京100076

出　　处：《导弹与航天运载技术》2021年第4期93-97,共5页Missiles and Space Vehicles

摘　　要：针对重型火箭发动机推力大,燃气流热流密度大,作用区域大的特点,通过仿真获得热防护的设计需求,据此提出多种热防护方法,并通过缩比发动机烧蚀试验与实际发射搭载试验进行对比。研究结果表明,合理设计热防护方法可以将发射平台表面温度降低至几十度,实现对发射平台的有效防护。In view of the characteristics of heavy rocket engine,such as large thrust,high heat flux of gas flow and large area of action,the design requirements of thermal protection are obtained through simulation,based on which a variety of thermal protection methods are proposed and compared with the actual launching and carrying test by shrinkage engine ablation.The results show that the surface temperature of the launch platform can be reduced to tens of degrees and the effective protection of the launch platform can be realized.

关 键 词：重型火箭发射平台 热防护 烧蚀试验 

分 类 号：V45[一般工业技术—材料科学与工程]