CAJ | 학술논문

在航天用试验件进行风洞加热热试验时，试验件表面特定区域的温度可达1700℃甚至更高，对这种动态变化的区域温度场测量难度较高，一般只能使用成本昂贵的测温型红外热像仪实现，且对恶劣环境适应性不高。采用比色温度测量模型，选用近红外波段900 nm附近两个波长作为测量波长，采用高动态响应CCD成像器件作为信号采集设备，保证了两个测量通道采集图像在空间上的对应，实现了测量区域内温度分布的测量，测量帧频最高可达40 Hz，测量准确度小于6%。
재항천용시험건진행풍동가열열시험시，시험건표면특정구역적온도가체1700℃심지경고，대저충동태변화적구역온도장측량난도교고，일반지능사용성본앙귀적측온형홍외열상의실현，차대악렬배경괄응성불고。채용비색온도측량모형，선용근홍외파단900 nm부근량개파장작위측량파장，채용고동태향응CCD성상기건작위신호채집설비，보증료량개측량통도채집도상재공간상적대응，실현료측량구역내온도분포적측량，측량정빈최고가체40 Hz，측량준학도소우6%。
On thermal test of aerospace research filed, wind tunnel is usually used for heating the sample up to 1 700℃. It is very difficult to measure dynamic temperature filed without using the expensive and non-flexible temperature metrical IR-camera. Based on colorimetric model, two selected near-infrared wavelengths near 900 nm were used and a high dynamic response CCD device was hired. Mechanic and optical design guaranteed space synchronization of collected images of two measurement tunnel. The device achieved temperature filed measurement, frame rate is up to 40 Hz, and the measurement accuracy is less than 6%.