高超声速飞行器热管冷却前缘结构一体化建模分析  

Investigation on integral model of heat-pipe-cooled leading edge of hypersonic vehicle

作　　者：孙健[1] 刘伟强[1] 

机构地区：[1]国防科技大学高超声速冲压发动机技术重点实验室,长沙410073

出　　处：《物理学报》2013年第7期231-238,共8页Acta Physica Sinica

基　　金：国家自然科学基金(批准号:90916018);高等学校博士学科点专项科研基金(批准号:200899980006)资助的课题~~

摘　　要：针对高超声速飞行器工作时前缘恶劣的气动加热环境,为了保证飞行器前缘的尖锐外形,提出内嵌高温热管前缘结构.针对热管内部复杂流动与换热情况,对内嵌高温热管前缘结构进行一体化建模,将模型的核心部件液态金属热管工作状况的计算与实验进行对比以验证模型的可靠性.本文还分析了给定工况下内嵌高温热管前缘结构的热防护效果,其中壁面最高温度下降了11.6%,最低温度上升了8%,高温区和低温区均被封闭在前缘外层区域,内层温度更加均匀,实现了热流由高温区向低温区的转移,削弱了高温区的热负荷.本文还分析了接触热阻对热管冷却前缘结构效果的影响.The structure of leading edge embedded high temperature heat-pipe （HTHP） is considered as thermal protection system to prevent hypersonic vehicle＇s leading edge that requires sharp figure during hypersonic flying from the serious aerodynamic heating. Under the complex flow and heat transfer condition of the heat pipe, the model of leading edge embedded HTHP is established. In contrast with experimental results, the model of heat pipe which is a core component of leading edge embedded HTHP has good accuracy. Using a numerical method, we analyze the thermal protection effect of leading edge embedded HTHP under the given condition. The maximum temperature of leading edge can be decreased by 11.6% and the minimum temperature of the leading edge increases by 8%. Both high temperature areas and low temperature areas are closed in the outer zone of the leading edge. While the temperature distribution of the inner zone is almost uniform, the heat transfer from high temperature areas to low areas is achieved. Thus the thermal load in high temperature areas is reduced. The influence of contact thermal resistance on the thermal protection effect of heat-pipe cooled leading edge is also studied.

关 键 词：热管 前缘 疏导式热防护 气动热 

分 类 号：V228.3[航空宇航科学与技术—飞行器设计]