机身 /推进系统一体化高超声速飞行器冷却性能分析  

Cooling Analysis of an Airframe/Propulsion Integrated Hypersonic Vehicle

作　　者：罗世彬[1] 吴先宇[1] 罗文彩[1] 王振国[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《弹箭与制导学报》2004年第1期56-62,共7页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：国家自然科学基金资助(10302031);国家"863"基金资助项目;国防科技大学博士生创新基金资助项目

摘　　要：建立了机身/推进系统一体化高超声速飞行器冷却性能分析模型,分别计算了等高度飞行和等动压飞行条件下的机身/推进系统一体化高超声速飞行器的冷却流量需求,对飞行马赫数、巡航高度和飞行动压对冷却流量的影响进行了分析,得到了满足冷却需求的最大飞行马赫数。结果表明在马赫数6～12的范围内,气动加热部件冷却需要总冷流量的约6%～13%,适当配置燃料喷射方案和提高冷却通道出口冷却剂的温度,再生冷却能够满足机身/推进系统一体化高超声速飞行器的冷却流量需求。Airframe/propulsion integrated cooling analysis model for hypersonic vehicle propelled by scramjet was presented. The coolant rates required for nose, wing/sidewall/cowl leading edges, strut edges and supersonic combustion flowpath were investigated under constant height trajectory and constamt dynamic pressure trajectory respectively. The highest flight Mach number to meet cooling requirement was discussed. The results showed that the coolant flow rate for aeroheaing parts, including nose, wing/sidewall/cowl leading edges and strut edges in this strdy, is abort 6%～13% of total coolan flow rate. It also showed that regenerative cooling can meet airframe/propulsion integrated cooling requirement in the range fo flight Mach numbers from 6 to 12 and dynamic pressure from 30kPa to 120kPa, when fuel injector locaions and injection fuel mass flow were set properly, and hydrogen temperature at the exit of cooling passage was allowed to be a higher value.

关 键 词：高超声速飞行器 冷却 超燃冲压发动机 气动加热 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]