液体火箭发动机喷焰红外辐射信号灵敏度分析  

Sensitivity Analysis of Infrared Radiation Signals from Liquid-Propellant Rocket Engine Exhaust Plumes

作　　者：孙一强 朱檀枭 牛青林 贺志宏[2] 董士奎[1,2] Sun Yiqiang;Zhu Tanxiao;Niu Qinglin;He Zhihong;Dong Shikui(Key Laboratory of Aerospace Thermophysics,Ministry of Industry and Information Technology,School of Energy Science and Engineering,Harbin Institute of Technology,Harbin 150001,Heilongjiang,China;School of Energy Science and Engineering,Harbin Institute of Technology,Harbin 150001,Heilongjiang,China;School of Mechanical and Electrical Engineering,North University of China,Taiyuan 030051,Shanxi,China)

机构地区：[1]哈尔滨工业大学能源科学与工程学院空天热物理工信部重点实验室,黑龙江哈尔滨150001 [2]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001 [3]中北大学机电工程学院,山西太原030051

出　　处：《光学学报》2025年第1期118-128,共11页Acta Optica Sinica

基　　金：国家自然科学基金企业联合基金重点项目(U22B2045);国家自然科学基金青年科学基金(52006203)。

摘　　要：火箭发动机喷焰辐射传递链路上涉及的物理化学机制异常复杂,且信息传递链路上的参量众多,需要量化输入参数的变化对发动机喷焰红外辐射信号的影响程度。以飞行高度为11~61 km的RD-180尾喷焰为研究对象,考虑氧燃比、燃烧室压力、面积比和喷口直径改变对发动机喷口面参数的影响。另外,保持发动机几何外形不变,分析氧燃比、燃烧室压力和飞行速度等工作参数变化对发动机喷焰红外辐射信号的灵敏度。为降低样本数量,采用Smolyak稀疏网格算法进行采样,采用多项式混沌展开结合Sobol指数算法进行灵敏度分析。结果表明:氧燃比主要对喷口出口温度和气体组分产生影响,喷口出口压力、速度、密度和比冲主要受燃烧室压力和面积比的影响,喷口直径仅影响推力。在35 km以下,氧燃比和飞行速度对辐射信号的影响比较微弱,燃烧室压力的影响占据主导地位,55 km以上时二者对应的主Sobol指标Si远大于燃烧室压力的指标,随着高度增加,输入参数之间耦合作用对于喷焰辐射强度的影响随之减弱。Objective The processes involved in the transmission of radiation in rocket engine exhaust plumes—such as thermochemical reactions,propellant combustion,turbulent flow,and gas molecule vibrational transitions—are extremely complex.These processes are characterized by high dimensionality,strong nonlinear behaviors,and intricate propagation mechanisms.The infrared radiation characteristics of the rocket engine plume are influenced by various parameters,including engine parameters(propellant type,propellant formulation,nozzle geometry,engine thrust),flight parameters(flight altitude,flight velocity),and detection parameters(detection angle,detection wavelength).It is crucial to perform a sensitivity analysis of these parameters to the infrared radiation signals emitted by rocket engines.Such an analysis will help classify and identify radiation signal layers from the plume and reverse-engineer of the engine formulation.Methods The sensitivity analysis is performed using a combination of polynomial chaos expansions(PCE) and Sobol'indices.The process begins by defining the input variables' probability space,including their distribution types and sampling range.The sparse grid method is then employed to sample the input variables,with the resulting samples fed into the numerical simulation or experiment to generate the response values.These values,along with the input parameters,are used to solve for the PCE coefficients for variance decomposition.Finally,the main and total Sobol' indices are calculated using the total variance and local variance.The infrared radiation model for the rocket plume consists of three parts:1) A CEA code calculates the engine nozzle exit parameters such as pressure,temperature,velocity,and gas components.2) A k-ε two-equation turbulence model is used to compute the engine plume's flow field,while a finite-rate chemical kinetic model with 10 reactions and 9 components describes the chemical nonequilibrium effects.3) A single-line group(SLG) model with the Curtis-Godson approximation com

关 键 词：灵敏度分析 Sobol指数 液体火箭发动机 尾喷焰 红外辐射 

分 类 号：V19[航空宇航科学与技术—人机与环境工程]