Thermal Radiation of Heterogeneous Combustion Products at the Nozzle Exit of the Rocket Microengine

V. A. Kuzmin; E. I. Maratkanova; I. A. ZagraiR. V. Rukavishnikova

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Thermal Radiation of Heterogeneous Combustion Products at the Nozzle Exit of the Rocket Microengine

机译：火箭微发动机喷嘴出口处非均相燃烧产物的热辐射

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The paper describes a technique of the integrated research into thermal radiation of heterogeneous combustion products. We have examined the dependence of optical properties, radiation characteristics, and emission characteristics on the key determinant factors and parameters at the nozzle exit of a model rocket microengine. We have compared the experimental spectrum with the calculated spectrum taking into consideration the radiation scattering from the combustion chamber on the condensate particles (the spotlight effect). The correction value for thermodynamic temperature has been found out.

机译：本文描述了一种非均相燃烧产物热辐射综合研究技术。我们研究了模型火箭微发动机喷嘴出口处的光学特性、辐射特性和发射特性对关键决定因素和参数的依赖性。我们将实验光谱与计算光谱进行了比较，并考虑了燃烧室对冷凝水颗粒的辐射散射（聚光灯效应）。已经找到了热力学温度的校正值。

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来源
《Russian Aeronautics》 |2016年第4期|579-586|共8页
作者
V. A. Kuzmin; E. I. Maratkanova; I. A. ZagraiR. V. Rukavishnikova;
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作者单位

Vyatka State University;

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原文格式 PDF
正文语种英语
中图分类航空;
关键词
Thermal radiation; Heterogeneous combustion products; Nozzle exit; Rocket microengine; Optical properties; Radiation characteristics; Emission characteristics; Computational experiment;

机译：热辐射;非均相燃烧产物;喷嘴出口;火箭微发动机;光学特性;辐射特性;排放特性;计算实验;

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机译：Thermal emission characteristics of combustion products from rocket engines. Part 2. Investigating the influence of various factors for SPRE
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3. Technique for Recording and Analysis of the Amplitude Spectrum of the Strength Oscillations of Magnetic and Electric Fields of Combustion Products in a Model Liquid Rocket Engine Fuel Depending on the Combustion Chamber Pressure [J] . Yagodnikov D. A. High temperature: English translation of teplofizika vysokikh temperatur . 2022,第1期

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5. X-rays from Radio Millisecond Pulsars: Comptonized Thermal Radiation [O] . Bogdanov, Slavko, Grindlay, Jonathan E., Rybicki, George B. 2006

机译：来自Radio millisecond pulsars的X射线：Comptonized Thermal Radiation
6. Boundary Layer Development as a Function of Chamber Pressure in the NASA (National Aeronautics and Space Administration) Lewis 1030:1Area Ratio Rocket Nozzle. [R] . smith, t. a. 1988

机译：作为腔室压力函数的边界层发展在Nasa（美国国家航空航天局）Lewis 1030：1area Ratio Rocket Nozzle。

Thermal Radiation of Heterogeneous Combustion Products at the Nozzle Exit of the Rocket Microengine

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