飞行器层板式前缘热管防热结构等效热分析  

Effective thermal analysis of platelet heat-pipe-cooled leading edge of vehicle

作　　者：刘洪鹏[1,2] 刘伟强[1,2] 

机构地区：[1]国防科技大学航天科学与工程学院,湖南长沙410073 [2]国防科技大学高超声速冲压发动机技术重点实验室,湖南长沙410073

出　　处：《国防科技大学学报》2016年第2期19-24,共6页Journal of National University of Defense Technology

基　　金：国家自然科学基金资助项目(90916018);湖南省自然科学基金资助项目(13JJ2002)

摘　　要：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。A new structure, the platelet heat-pipe-cooled leading edge, was proposed for 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 was adopted and the effective vapor thermal conductivity was deduced mathematically. Its effectiveness was validated by comparing the wall temperature against experimental date for a conventional heat pipe. The research result indicates that the nickel based alloy IN718, with sodium as the working fluid, is a feasible combination form Mach 7 with a 15 mm leading edge radius.

关 键 词：热防护 热管 层板 换热系数 

分 类 号：V211.1[航空宇航科学与技术—航空宇航推进理论与工程]