低功率电弧加热发动机喷管扩张段内壁面温度测量  

Inner Nozzle Surface Temperature Measurement in a Low Power Arcjet Thruster

作　　者：黄河激[1] 潘文霞[1] 吴承康[1] 

机构地区：[1]中国科学院力学研究所,北京100190

出　　处：《工程热物理学报》2011年第7期1185-1187,共3页Journal of Engineering Thermophysics

基　　金：国家自然科学基金(No.50836007;No.10921062)

摘　　要：采用滤光成像,摒弃电弧及羽流干扰,实验获得了采用纯氮、纯氢以及氢-氮混合气为推进剂时,低功率电弧加热发动机喷管内壁面的热辐射强度分布。通过辐射强度-温度标定以及图像分析,导出了相应的温度分布。实验结果表明,喷管扩张段内壁面温度最高处位于喉道出口附近。采用不同推进剂时,喷管内壁面温度分布情况有显著区别。Using an interference filter,thermal radiation images of the inner nozzle surface were obtained for a low power arcjet thruster.The interference filter was selected to cut off disturbance from arc and plume emissions when pure nitrogen,pure hydrogen and their mixtures were used as the propellant.Relationship between the radiation intensity and the temperature was calibrated and the corresponding temperature distribution was calculated based on the radiation intensity distribution obtained by image analysis.Results show that the highest temperature zone locates downstream close to the throat exit and the temperature distributions for different propellants vary a lot.

关 键 词：电弧加热发动机 热辐射 喷管内壁 温度测量 

分 类 号：V439[航空宇航科学与技术—航空宇航推进理论与工程]