固液混合火箭发动机喷焰红外辐射特性分析  

Analysis of infrared radiation of hybrid rocket motor exhaust plume

作　　者：申文涛[1] 董超[1] 朱定强[1] 蔡国飙[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《航空动力学报》2012年第8期1874-1880,共7页Journal of Aerospace Power

摘　　要：为了研究固液混合火箭发动机喷焰在不同飞行状态的红外辐射特性,建立了固液两相状态下喷焰的红外辐射计算模型,获得了喷焰在2～12μm波段的红外辐射.将喷焰的温度、压力、摩尔组分等作为输入条件,米氏散射(Mie)模型计算颗粒相的散射,采用有限体积法(FVM)离散辐射传递方程,利用中分辨率大气辐射传输(MODTRAN)模型计算不同观测距离的大气透过率,编程计算得到不同飞行高度,不同观测方向下喷焰的红外辐射.结果表明喷焰红外辐射亮度与温度分布类似,在2.7～3.0μm和4.2～4.5μm波段范围内的辐射较强,高温粒子在近红外比远红外对总辐射的贡献大,太空与地面观测不同飞行高度的发动机喷焰辐射率因大气衰减的不同而有所差异,可为目标跟踪与发动机设计提供参考.Infrared properties of hybrid rocket engine plume were studied by establishing a theoretical model of infrared radiation in 2-12μm wavelength. The pressure, temperature and concentration of each component of flow field were considered as the input parameters. The spectral radiation parameters of the particle were calculated by the Mie scattering model. The thermal radioactive transfer equation was discredited by using the finite volume method （FVM）. Finally, the moderate resolution atmospheric transmission （MODTRAN） model was used to calculate the infrared radiation attenuation in the atmosphere. The results indicate that the transmission conditions, height, angle and particle size exert important effect on the distribution of spectrum radiance. The results contribute to providing reference for further research of target tracking and hybrid rocket motors design.

关 键 词：固液混合发动机 喷焰 红外辐射 数值计算 大气衰减 

分 类 号：V436[航空宇航科学与技术—航空宇航推进理论与工程]