摘要
针对使用大推力发动机的某新型运载火箭二级尾舱防热问题,引入了CFD/DSMC结合的方法用于四喷管并联的高空羽流干扰流场及羽流回流热流的仿真分析,预示了第二级发动机工作时羽流回流在二级尾舱产生热流的分布情况,并以此为基础提出了可有效阻隔四台并联发动机高空羽流回流的新型轻质、柔性整体防热结构,使二级尾舱内热流降低95%以上,改善了火箭二级尾舱的热环境。
To solve the thermal protection problem of the second stage cabin of a new generation launch vehicle with new high thrust engine, a CFD/DSMC coupling simulation method suitable for four nozzle high-altitude plum interactive flow field and heat flow was introduced. Heat flow distribu-tion on the second stage tail cabin from the second stage engine ’ s plume backflow was accurately in-dicated. Based on the result, a new light and flexible overall thermal protection structure was put forward to effectively isolate the high-altitude plum backflow of the four nozzle engine. The thermal protection structure could reduce the heat flow in the second stage tail cabin by 95 % and thus the thermal environment was improved.
作者
范瑞祥
徐珊姝
宫宇昆
石晓波
梁杰
FAN Ruixiang1 , XU Shanshu2 , GONG Yukun2 , SHI Xiaobo3 , LIANG Jie4(1. China Academy of Launch Vehicle Technology, Beijing 100076, China; 2. Beijing Institute of Astronautical System Engineering, Beijing 100076, China; 3. Xi ’ an Aerospace Propulsion Institute, Xi’an 710100, China;4. Hypervelocity Aerodynamics Institute, China Aerodynamic Research and Development Center, Mianyang 621000, Chin)
出处
《载人航天》
CSCD
北大核心
2018年第4期500-504,519,共6页
Manned Spaceflight
关键词
四喷管
高空羽流
CFD/DSMC
柔性整体防热
four nozzle
high-altitude plume
CFD/DSMC
flexible overall thermal protection
