Thermal radiation model for solid rocket booster plumes
Thermal radiation model for solid rocket booster plumes
复制标题
固体火箭助推器羽流的热辐射模型
DOI：
10.2514/3.27989
复制
发表时间：
1977
影响因子：
1.6
通讯作者：
A. L. Lee
中科院分区：
文献类型：
--
作者：
G. H. Watson;A. L. Lee
采用蒙特卡罗方法模拟了航天飞机发射构型双固体火箭助推器羽流的热辐射场。该模型考虑了羽流辐射特性的轴向和径向变化。羽流被认为是由分散的氧化铝（Al2O3）颗粒浸没在燃烧的气体产物。主要的排放气体是CO、CO2、H2O和HCl。热模型是基于局部热力学平衡。辐射能被Al2O3颗粒散射可被视为各向同性或各向异性。显示了航天飞机底部区域的样品辐射加热率。航天飞机的几何形状被模拟为二次曲面的组合。
The Monte Carlo method is used to model the thermal radiation field of the plumes for the dual solid rocket boosters astride the Space Shuttle launch configuration. The model accounts for axial and radial variations in radiative properties of the plumes. The plumes are considered to be composed of a dispersion of aluminum oxide (Al2O3) particles immersed in the gaseous products of combustion. The principal emitting gases are taken to be CO, CO2, H2O, and HCl. The thermal model is based on local thermodynamic equilibrium. Scattering of radiant energy by Al2O3 particles may be treated as isotropic or anisotropic. Sample radiant heating rates to the base region of the Space Shuttle are shown. Space Shuttle geometries are simulated as combinations of quadric surfaces.