航天器再入大气层热力分析

以OREX（orbital reentry experiment vehicle）的飞行试验数据和相关的CFD数值模拟结果为基础，采用传热理论及相关公式，分析计算了OREX再入大气层过程中的轨迹，驻点处热流密度非平衡假设和平衡假设下的换热问题.所计算的轨迹、热流密度非平衡假设下计算的驻点温度和热流密度值同试验数据及相关的CFD数值结果取得了很好的一致，相应的计算方法可作为航天器驻点热力分析的通式.然而在平衡假设条件下，尽管计算所得到的驻点热流密度与之前的CFD数值结果差别不大，但这种情况下计算得到的温度与试验数据不符，这应归结于计算的热流密度结果对驻点处温度变化的不敏感.比较非平衡假设和平衡假设下的换热计算结果表明，对于航天器再入过程中的热力探讨不能仅仅满足于热流密度分析，对温度的考察或许更重要. 

Aerothermodynamic analysis of spacecraftduring its atmospheric reentry flight

Based on existing OREX (orbital reentry experiment vehicle) flight experiment data and the CFD numerical results, the OREX reentry trajectory and heat flux at the stagnation point under thermal non-equilibrium and equilibrium conditions were analyzed respectively with heat transfer theory and corresponding formulas. The calculation results of the trajectory and the temperature as well as the heat flux at the stagnation point under the thermal non-equilibrium condition agreed well with the experiment data and CFD numerical results,including that the corresponding calculation method might be used in the thermal analysis of spacecraft''s stagnation point. However under the equilibrium condition, although the calculated heat flux at the stagnation point showed little difference to the former CFD numerical results, the calculated temperature under this condition didn''t match the experiment data, which should be attributed to the insensitivity of the heat flux to the variation of the temperature at the stagnation point. The comparison of calculations under thermal non-equilibrium and equilibrium conditions shows that merely focusing on heat flux of spacecrafts in its reentry flight is risky, paying attention to its temperature might be more important.