激波风洞温敏热图技术初步试验研究

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。

Preliminary experimental study on temperature sensitive thermography used in shock tunnel

The temperature sensitive thermography technique can be used to measure the heat transfer distribution of a complex shaped model in hypervelocity impulse facilities,such as shock tunnels.This technique depends on the luminescent characteristics of the temperature sensitive material to obtain the surface temperature of the model,and also the heat transfer distribution.However,the application of this technique in shock tunnels is still immature,because under the short effective running time of about 10ms,it is difficult for the material to respond fast enough to catch up with the temperature variation,and difficult to acquire image data and so on.In this paper,the recent development of the temperature sensitive thermography technique in CARDC 0.6mshock tunnel is presented,including the research on luminescent material,spraying,data processing and calibration etc.In the verification experiment,a flat plate with blunt rudder is used as model.The result from thermography fits well with theoretical analysis and the result from thin film gauge.The difference between thermography result and heat flux gauge measurement is about 5%~25%.