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.
作者
冯超
徐铮
平仕良
吴新跃
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)
出处
《导弹与航天运载技术》
CSCD
北大核心
2021年第4期93-97,共5页
Missiles and Space Vehicles
关键词
重型火箭发射平台
热防护
烧蚀试验
heavy rocket launch platform
thermal protection
the ablation test
