来流导致的火箭发动机喷焰红外辐射强度不确定度量化分析  

Quantitative analysis of the uncertainty of infrared radiation signature of rocket exhaust plume caused by incoming flow

作　　者：肖智茹 牛青林 王振华 董士奎[3] Xiao Zhiru;Niu Qinglin;Wang Zhenhua;Dong Shikui(College of Mechatronic Engineering,North University of China,Taiyuan 030051,China;Science and Technology on Optical Radiation Laboratory,Beijing Institute of Environmental Features,Beijing 100854,China;Key Laboratory of Aerospace Thermophysics of MIIT,Harbin Institute of Technology,Harbin 150001,China)

机构地区：[1]中北大学机电工程学院,山西太原030051 [2]北京环境特性研究所光学辐射重点实验室,北京100854 [3]哈尔滨工业大学工信部空天热物理重点实验室,黑龙江哈尔滨150001

出　　处：《红外与激光工程》2023年第4期41-50,共10页Infrared and Laser Engineering

基　　金：国家自然科学基金(52006203,U22B2045);山西省回国留学人员科研资助项目(2021-113);装备预先研究领域基金(80916010304)。

摘　　要：在火箭发动机喷焰红外辐射预测过程中,由于弹道参数的不确定性因素存在,会影响喷焰红外辐射信号计算结果的置信度。文中以Atlas-IIA低空喷焰为研究对象,以来流速度、来流温度、来流压力和飞行攻角为不确定性输入变量,采用拉丁超立方试验设计样本,开展喷焰反应流场与红外辐射特性计算,获得各样本点对应的喷焰红外辐射响应值,利用非嵌入混沌多项式(No-intrusive Polynomial Chaos,NIPC)方法构建代理模型,采用响应面法求解NIPC多项式系数,基于统计参量研究各参量对红外辐射信号的不确定度和敏感性。结果表明来流特性引起的辐射强度不确定度与波段的选取有较高的关联度。来流速度对光谱辐射强度的灵敏程度最高,来流压力和攻角次之,来流温度的影响可忽略不计;来流速度对2.5~3.2、2.8~3.0μm谱带内的辐射强度敏感,主Sobol指数占比均在80%左右,来流压力对4.35~4.65μm波段辐射强度的影响占比为70%;各参数间的耦合作用对喷焰红外辐射的影响不高于4%。该研究可为火箭发动机尾喷焰红外辐射准确预估和置信度评估提供理论支撑。Objective The rocket exhaust plume is one of the key objects of the space-based infrared system(SBIRS)due to its strong infrared radiation characteristics.The infrared radiation signature of the plume is not only related to the motor prototype parameters but also to the flight parameters of the vehicle.In practical applications,the variation characteristics of infrared radiation signature of the rocket exhaust plume can be predicted through numerical methods based on the known motor and flight parameters.However,the flight parameters of non-cooperative targets are often difficult to obtain accurately,which means that there must be some deviation in predicting the infrared radiation signatures of the rocket exhaust plume by numerical methods.Therefore,it is necessary to study the influence of flight parameter disturbance on the infrared radiation of rocket exhaust plumes.For this purpose,the non-intrusive polynomial chaos(NIPC)method is used for the uncertainty quantification and sensitivity analysis of free stream parameters on the infrared radiation signatures of the rocket exhaust plume.Methods The Latin hypercube sampling(LHS)method is used to design the samples of frees tream parameters.The infrared radiation characteristics of the rocket exhaust plume are calculated based on the infrared signature analysis tool(IRSAT),and the corresponding infrared response values of the plume at each sample point are obtained.The regression analysis method is used to solve the polynomial chaotic expansion coefficient and the statistical characteristics of the plume infrared signatures,including the mean value,standard deviation and uncertainty.Based on the Sobol index,the NIPC method can be utilized to quantify the uncertainty and sensitivity of the infrared radiation signature,and analyze the impact of a single variable and multiple variables on the infrared radiation characteristics of the rocket exhaust plume.Results and Discussions The free stream velocity has a high sensitivity to spectral radiation intensity in most s

关 键 词：来流参数 尾喷焰 NIPC 红外辐射 不确定度 

分 类 号：V19[航空宇航科学与技术—人机与环境工程]