多喷管液体火箭动力系统尾焰辐射特性研究  

Research on Plume Infrared Radiation of Multi-nozzle Rocket Propulsion System

作　　者：乔野[1] 聂万胜[1] 吴高杨 丰松江[1] Qiao Ye;Nie Wan-sheng;Wu Gao-yang;Feng Song-jiang(Department of Space Equipment, Equipment Academy of PLA, Beijing, 101416)

机构地区：[1]中国人民解放军装备学院航天装备系,北京101416

出　　处：《导弹与航天运载技术》2017年第4期53-58,共6页Missiles and Space Vehicles

基　　金：国家自然科学基金(51206185;91441123)

摘　　要：为研究多喷管液体火箭动力系统尾焰辐射特性,以液氢/液氧和液氧/煤油发动机组成的多喷管动力系统为模型,采用CFD技术对尾焰流场进行计算,利用气体辐射传输方程和大气透过率计算模型对尾焰辐射特性进行计算,结果表明:复燃反应主要发生在尾焰的边界与空气掺混区域,导致尾焰的辐射特性增强;随着飞行高度及观测角的增加,尾焰辐射特性逐渐增强;可视化计算可以有效捕捉到尾焰流场的结构。To take research on the plume infrared radiation of multi-nozzle propulsion system which consisted with LH2/LOX Engines and LOX/Kerosene Engines,the CFD technology is used for the flow-field simulation.The plume infrared radiation is computed with the gas radiation transmission equation and permeation model.The simulation results indicate that the afterburning,which mainly takes place at the boundary of the plume,can enhance the infrared radiation.Increasing with the flight height and the viewing angle,the plume infrared radiation increases.The plume radiation visualization computation can effectively get the structure of the plume.

关 键 词：液体火箭发动机 多喷管 尾焰 红外辐射 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]