某型发动机尾流场热环境测量及数值模拟研究  

Experimental and Numerical Investigations of the Thermal Circumstance of a Rocket Engine's Tail's Fields

作　　者：罗天培[1] 朱子勇[1] 王石磊[1] 刘瑞敏[1] Luo Tian-pei;Zhu Zi-yong;Wang Shi-lei;Liu Rui-min(Beijing institute of Aerospace Testing Technology, Beijing, 100074)

机构地区：[1]北京航天试验技术研究所,北京100074

出　　处：《导弹与航天运载技术》2017年第1期38-41,共4页Missiles and Space Vehicles

摘　　要：对某型液体火箭发动机的尾流温度场及辐射场进行测量,采用计算流体力学技术对尾流场进行数值模拟,仿真结果同试验结果进行对比分析。结果表明:加载辐射模型后尾流温度场的预测更准确,发动机前部辐射场由喷管外壁的固体辐射及燃气的气体辐射构成,而远离发动机的区域主要气体辐射构成,P1模型可以有效预测液体火箭发动机尾流辐射场。Experimental and numerical investigations of a liquid rocket engine’s tail field are conducted.The simulation isevaluated by comparison with the experimental results.The results show that the prediction accuracy of temperature field can beimproved by using radiation model,the solid radiation of engine’s wall and gas radiation constitute the front part of engine’s radiationfield,while the gas radiation plays the important role far from the engine,and P1model can predict the tail’s radiation fields of therocket engine effectively.

关 键 词：热环境 测量 数值模拟 辐射 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]