| 高超声速飞行器热载荷计算及影响因素分析 |
| |
| 引用本文： | 张利珍,王晓明,董素君,王浚.高超声速飞行器热载荷计算及影响因素分析[J].北京航空航天大学学报,2009,35(3):308-312. |
| |
| 作者姓名： | 张利珍 王晓明 董素君 王浚 |
| |
| 作者单位： | 北京航空航天大学,航空科学与工程学院,北京,100191;成都飞机设计研究所,成都,610041 |
| |
| 基金项目： | 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.
|
| 关 键 词： | 高超声速 飞行器 热控系统 热防护系统 热载荷 |
| 收稿时间： | 2008-03-19 |
Calculation of thermal load and impact factor analysis for hypersonic vehicle |
| |
| Zhang Lizhen,Wang Xiaoming,Dong Sujan,Wang Jun.Calculation of thermal load and impact factor analysis for hypersonic vehicle[J].Journal of Beijing University of Aeronautics and Astronautics,2009,35(3):308-312. |
| |
| Authors: | Zhang Lizhen Wang Xiaoming Dong Sujan Wang Jun |
| |
| Institution: | 1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
2. Chengdu Aircraft Design & Research Institute, Chengdu 610041, China |
| |
| Abstract: | 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 calcul... |
| |
| Keywords: | hypersonic flow vehicle thermal control system thermal protection system thermal load |
| 本文献已被 CNKI 万方数据 等数据库收录！ |
| 点击此处可从《北京航空航天大学学报》浏览原始摘要信息 |
| 点击此处可从《北京航空航天大学学报》下载免费的PDF全文 |
|
