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高超声速飞行器瞬态热试验
引用本文:侯玉柱,郑京良,董威.高超声速飞行器瞬态热试验[J].航空动力学报,2010,25(2):343-347.
作者姓名:侯玉柱  郑京良  董威
作者单位:上海交通大学机械与动力工程学院,上海,200240
摘    要:为了进行高超声速飞行器热防护系统的初步设计和数值计算的验证,设计开发了高超声速飞行器瞬态气动加热地面试验系统及其控制软件.试验系统能够根据飞行器的飞行轨迹和外形参数加载瞬态热流,实时测出结构表面的热流值和温度,得到飞行器的表面试验热流曲线和温度曲线.试验系统采用真空舱模拟飞行环境,并为此设计了冷却床,在真空环境下能比较真实的模拟热防护系统的下表面热环境,使瞬态热试验的原理更加合理,精度进一步提高.

关 键 词:高超声速飞行器  气动加热  瞬态试验  金属热防护系统
收稿时间:1/13/2009 2:21:36 PM
修稿时间:2009/4/21 0:00:00

Transient test of aerodynamic heating for hypersonic vehicle
HOU Yu-zhu,ZHENG Jing-liang and DONG Wei.Transient test of aerodynamic heating for hypersonic vehicle[J].Journal of Aerospace Power,2010,25(2):343-347.
Authors:HOU Yu-zhu  ZHENG Jing-liang and DONG Wei
Institution:Shanghai Jiaotong University,Shanghai Jiaotong University,Shanghai Jiaotong University
Abstract:To design a thermal protection system of the hypersonic vehicle and verify the numerical computations,an aerodynamic heating transient test system together with its control software was designed and developed.The test system can measure the real-time heat flux and temperature on the surface,directly produce heat flow and temperature curve,according to hypersonic vehicle's trajectory.To simulate the heat transfer conditions at different altitudes and understand the effecting of the pressure,the test system used a vacuum chamber.To ensure that the conditions of the lower side of the thermal protection system could be simulated in a vacuum environment,a cooling bed was used,making the transient test method more reasonable and accurate.
Keywords:hypersonic vehicle  aerodynamic heating  transient test  metallic thermal protection system
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