摘要
热成像法测量航天飞行器防热材料在电弧风洞内烧蚀时的表面温度是一种有效的方法,它能快速地测量大量的数据点。为了能透过红外光线,在电弧风洞上安装特殊的窗口。防热材料的发射率、窗口的透射率要事先测定并要分析风洞背景热辐射和电弧射流热辐射的影响。实验表明。热成像法测量真实温度分布的准确度高于热电偶测量的结果。
The thermal imaging method is used to measure the surface temperature of aerospace heat-resistant material during ablation in the arc wind tunnel. It is an effective and quantitative method with fast response time to measure a large number of data points. A special window for infrared beam transmission was designed and mounted in the are wind tunnel. The material surface emissivity, the window transmittance was measured and the effect of background radiation and arc-jet radiation was analyzed. The test showed that the measurement accuracy of the true temperature distribution by the thermal imaging method is higher than that by thermocouples
出处
《宇航计测技术》
CSCD
1997年第4期37-41,共5页
Journal of Astronautic Metrology and Measurement
基金
航天科学基金
关键词
热成像法
耐热材料
烧蚀试验
航天器
温度分布
Thermal imaging method
Heat-resistant material
Ablation
Temperature distribution
