基于有限体积法的液体火箭发动机燃气红外特性仿真

摘要

Using method of finite volume, we simulate infrared radiation properties of the attitude and orbit control engine gas flow field. First for the engine gas flow field is calculated by Fluent in typical working conditions. Used the latest spectrum database for the major components of radiation absorption coefficient to calculate. Finally, the gas infrared radiation characteristic is calculated. Analyzed infrared radiation intensity distribution in different wavelengths, different zenith angle, different wave band. The results show that the proposed method of calculation is reliable and calculation results of infrared characteristics is accurate, conducive to liquid rocket engineers further grasp the infrared radiation characteristics calculation and analysis methods.%运用有限体积法对某轨姿控发动机典型工况燃气流场红外辐射特性进行仿真计算.首先通过Fluent软件对发动机典型工况燃气流场进行计算,再利用最新的光谱数据库对主要辐射组分吸收系数进行计算,最后对燃气红外辐射特性进行计算;重点分析不同波长、不同天顶角、不同波段下燃气红外辐射强度分布规律.研究结果表明:所提计算方法可靠,红外特性计算结果准确,有利于掌握液体火箭发动机红外辐射特性计算和分析方法.