火箭发动机喷焰红外辐射数值计算方法研究(特邀)  

Progress of Numerical Calculation Methods for Infrared Radiation of Rocket Exhaust Plume(Invited)

作　　者：牛青林 董士奎[2] NIU Qinglin;DONG Shikui(School of Mechanical and Electrical Engineering,North University of China,Taiyuan,China;Key Laboratory of Aerospace Thermophysics ofMIIT,Harbin Institute of Technology,Harbin,China)

机构地区：[1]中北大学机电工程学院,太原 [2]哈尔滨工业大学工信部空天热物理重点实验室,哈尔滨

出　　处：《光电技术应用》2023年第1期1-10,35,共11页Electro-Optic Technology Application

基　　金：国家自然科学基金(52006203,U22B2045);山西省归国留学人员资助项目(2021-113)。

摘　　要：火箭发动机高温尾喷焰因具有显著的红外辐射特征成为天基红外系统探测、跟踪、分类和识别任务重点关注的对象。火箭发动机喷焰辐射信号产生、传递机制的物理建模和数值计算一直是目标探测领域重点关注的问题,也正朝着高精度、高效率的方向发展。针对火箭发动机喷焰红外辐射数值计算研究,围绕喷焰红外辐射计算链路所涉及的各环节,从喷焰反应流场模拟、高温燃气辐射物性参数计算、辐射传输计算和数理模型校验试验等方面的研究情况展开综述。The high-temperature rocket exhaust plume has become the focus of the space-based infrared system detection, tracking, classification and identification tasks due to its prominent infrared radiation signatures. The physical modeling and numerical calculation of the emission and transmission mechanism of the plume radiation signatures has always been a hot issue in the field of target detection, and is also developing towards high accuracy and efficiency. Focusing on the various links involved in the infrared radiation calculation link of the plume, the research situation is summarized from the aspects of reacting flow field simulations, radiative parameters of gas and particles, radiative transfer methods and validation of numerical models.

关 键 词：火箭发动机尾喷焰 红外辐射 辐射传输 

分 类 号：TN211[电子电信—物理电子学]