摘要
建立火箭发动机内流计算模型、尾喷焰反应流场计算模型和红外辐射计算模型,用于分析火箭发动机尾喷焰红外辐射特性。以某型空空导弹为研究对象,分别设计和分析了AP/HTPB/Al、AP/HTPB/RDX/Al和AP/HTPB/Tetryl/Al 3种推进剂配方工况在5 km、10 km和15 km 3个飞行高度下的红外辐射信号差异。结果表明:推进剂中高能炸药成分降低了喷口处的CO_(2)和H_(2)O的含量,提高了H_(2)和CO的含量;Tetryl较RDX在喷口产生含量更多的H_(2)和CO_(2),会引起更广的复燃区域和更高的复燃温度;高能炸药成分增强了复燃现象,会引起喷焰辐射光谱强度、谱带内积分强度的升高以及辐射强度分布范围的增大。
A comprehensive calculation model was established to analyze the infrared radiation characteristics of the plume including rocket internal flow module,reacting plume flow field module and infrared radiation module.Taking a certain type of air-to-air missile as the research object,the three propellant formulas,including AP/HTPB/Al,AP/HTPB/RDX/Al and AP/HTPB/Tetryl/Al,were designed at flight altitudes of 5 km,10 km and 15 km.The difference of infrared radiation signatures was analyzed.The results show that the composition of high explosive in propellant reduces the content of CO_(2)and H_(2)O,and increases the content of H_(2)and CO in the exit plane of nozzle.Tetryl produces more H_(2)and CO_(2)at the nozzle than RDX,resulting in a wider range of after-burning and higher temperature.Due to the increase of after-burning of high explosive components,the radiant spectrum intensity,the in-band radiance and the distribution range of radiation brightness of rocket exhaust plume increase.
作者
牛青林
高文强
孙一强
董士奎
NIU Qinglin;GAO Wenqiang;SUN Yiqiang;DONG Shikui(School of Mechanical and Electrical Engineering,North University of China,Taiyuan 030051,China;Key Laboratory of Aerospace Thermophysics,Harbin Institute of Technology,Harbin 150001,China)
出处
《兵器装备工程学报》
CSCD
北大核心
2021年第8期1-7,共7页
Journal of Ordnance Equipment Engineering
基金
国家自然科学基金项目(52006203)
山西省回国留学人员科研资助项目(2021-113)。
关键词
固体火箭发动机
尾喷焰
红外辐射
高能炸药
solid rocket motor
rocket exhaust plume
infrared radiation
high-energy explosive
