论文部分内容阅读
介绍了可用于激波风洞等高超声速脉冲设备复杂外形模型表面热流分布显示与测量的温敏热图技术。该技术利用温敏材料发光特性随温度变化的特点实现对模型表面的温度测量,进而分析获得其表面热流分布。由于有效运行时间一般只有10ms左右,在激波风洞中采用温敏热图技术在材料温敏响应、图像采集等方面均存在困难,导致此技术还很不成熟。介绍了近期在CARDC 0.6m激波风洞中开展温敏发光热图技术研究的情况,包括发光材料的研制、材料喷涂、图像处理及标定等方面的研究工作。验证试验采用了平板加钝舵模型,获得了与理论分析及传感器测量结果较一致的平板干扰区热图结果。热图与薄膜传感器测量数据差异大致在5%~25%之间。
The thermosensitive heat map technique, which can be used to display and measure the heat flow distribution on the surface of shock wave wind tunnel hypersonic pulse equipment, is introduced. The technology uses temperature characteristics of the light-emitting characteristics of the temperature-sensitive material to achieve the temperature measurement of the model surface, and then analyze the surface heat flow distribution. Due to the fact that the effective operation time is only about 10ms, the use of temperature-sensitive heat-map technique in shock wind tunnel has difficulties in material temperature-sensitive response and image acquisition, which leads to this technology is still immature. This paper introduces the recent research on the thermosensitive luminescence thermography in the CARDC 0.6m shock wind tunnel, including research on luminescent materials, material spraying, image processing and calibration. The validation test uses the model of flat plate and blunt rudder, and obtains the result of plate interference region heat map that is more consistent with the theoretical analysis and sensor measurement results. Heat map and thin film sensor measurement data about 5% ~ 25% difference between.