飞行器层板式前缘热管防热结构等效热分析

针对高超声速飞行器前缘尖锐部件所面临的严重气动热,提出层板式前缘热管防热结构。为避免前缘热管内复杂的两相传热传质计算,对高温热管蒸汽腔的传热进行了等效导热分析,讨论了蒸汽腔的等效导热系数的计算方法,与常规高温热管试验对比验证了计算方法的准确性。对该结构热防护效果的计算表明,当飞行器在34 km高度以7Ma速度飞行时,以IN718为管壁材料、Na为工质的层板式热管对头部半径为15 mm的前缘结构具有良好的热防护效果。

The Effective Thermal Analysis of Platelet Heat-pipe-cooled Leading Edge

A new structure, the platelet heat-pipe-cooled leading edge, is proposed fro hypersonic vehicle thermal protection. In order to avoid the challenge of modeling two-phase conjugate heat and mass transfer, an approach of modeling the vapor core as a solid thermal conductor with high conductivity is adopted and the effective vapor thermal conductivity is deduced mathematically, and its effectiveness is validated by comparing the wall temperature against experimental date for a conventional heat pipe. The prediction indicate that the nickel based alloy IN718, with sodium as the working fluid, is a feasible combination fro Mach 7 with a 15 mm leading edge radius.