基于CFD/DSMC羽流仿真的新型运载火箭二级尾舱整体防热方案研究  

Study on Overall Thermal Protection Structure of Second Stage Tail Cabin in New Generation Launch Vehicle Based on CFD/DSMC Simulation of High-Altitude Plume

作　　者：范瑞祥[1] 徐珊姝 宫宇昆 石晓波[3] 梁杰[4] 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)

机构地区：[1]中国运载火箭技术研究院,北京100076 [2]北京宇航系统工程研究所,北京100076 [3]西安航天动力研究所,西安710100 [4]中国空气动力研究与发展中心超高速所,绵阳621000

出　　处：《载人航天》2018年第4期500-504,519,共6页Manned Spaceflight

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.

关 键 词：四喷管 高空羽流 CFD/DSMC 柔性整体防热 

分 类 号：V421.1[航空宇航科学与技术—飞行器设计]