AIR RADIATION ANALYSIS OF A SUPERORBITAL REENTRY VEHICLE
AIR RADIATION ANALYSIS OF A SUPERORBITAL REENTRY VEHICLE
复制标题
超轨道再入飞行器的空气辐射分析
DOI：
10.2514/6.1997-2561
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发表时间：
1997
期刊：
影响因子：
--
通讯作者：
Kojiro Suzuki
中科院分区：
文献类型：
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作者：
K. Fujita;T. Abe;Kojiro Suzuki
为了估算高超声速飞行器再入地球大气层或进入有大气层的行星时的辐射加热率，开发了一个数值代码。利用该代码，对一种超轨道再入飞行器（MUSES - C）进行了辐射分析。所开发的辐射数据库适用于高达100,000 K的温度范围，包括11种空气成分和6种碳质烧蚀产物。采用非耦合方式，利用具有非平衡化学的单温度和双温度模型计算出的流场，计算了驻点处的辐射热通量。讨论了烧蚀产物对辐射热通量的影响。在激波层上进行辐射积分时引入了无限平板和球冠近似。还讨论了辐射热通量对这些近似的依赖性。
A numerical code is developed in order to estimate the radiative heating rate of hypersonic vehicles reentering the earth atmosphere or entering the atmospheric planets. Using this code, radiation analysis of a superorbital reentry vehicle (MUSES-C) is conducted. The developed radiation database is applicable to the temperature range up to 100,000 K, including both the 11species air components and 6-species carbonic ablation products. The radiative heat flux at the stagnation point is calculated in the non-coupled manner, using the flow fields calculated by the one-temperature and twotemperature models with nonequilibrium chemistry. Effects of the ablation products on the radiative heat flux are discussed. The infinite-slab and spherical-cap approximations are introduced to radiation integration over the shock layer. Dependence of the radiative heat flux on these approximations is also discussed.