高超声速飞行器热载荷计算及影响因素分析  

Calculation of thermal load and impact factor analysis for hypersonic vehicle

作　　者：张利珍[1] 王晓明[2] 董素君[1] 王浚[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191 [2]成都飞机设计研究所,成都610041

出　　处：《北京航空航天大学学报》2009年第3期308-312,共5页Journal of Beijing University of Aeronautics and Astronautics

基　　金：航空科学基金资助项目(2006ZC5135)

摘　　要：对吸热式热防护系统和液氮为冷源的高超声速飞行器热控系统,分别采用辐射热平衡法和双层集总参数法,建立了隔热层和舱内温度场的热力学模型,实现了气动加热、隔热层导热及舱内温度场等各传热环节的解耦.在此基础上,按照X-34验证机的飞行剖面对高超声速飞行器电子设备舱热载荷进行了计算,并分析了隔热层厚度、舱内冷却气体流速及液氮量对舱内温度和电子设备温度的影响.结果表明,该方法对热传递过程各环节响应特性能够较准确的分析,在工程方案初步设计阶段具有重要的应用价值.Endothermal thermal protection system （TPS） and liquid N2 heat sink were chosen to calculate the characteristics of thermal control system （TCS） in hypersonic vehicle. The methods of radiation balance and double lumped parameter were adopted to obtain the thermodynamic model of adiabatic layer and cabin air temperature. Therefore, aeroheating, adiabatic layer heat transfer and cabin air temperature were decoupled. On the basis of flight profile of X-34 hypersonic vehicle, the thermal load of avionics bay was calculated. Besides, the influence of adiabatic layer, cooling gas velocity and liquid N2 amount on cabin air as well as the equipment temperature were analyzed. The results show that this method could get the response characteristics of heat transfer sections, which played an important part in the primary stage of hypersonic vehicle design.

关 键 词：高超声速 飞行器 热控系统 热防护系统 热载荷 

分 类 号：V245[航空宇航科学与技术—飞行器设计]