基于多CCD同步耦合的动态燃烧场三维辐射测温（特邀）

为满足燃烧场温度参量时空演化特征诊断的需求，提出了基于多CCD同步耦合的动态三维辐射测温方法。在多视线方向测量基础上，通过代数重建技术对燃烧场进行体素分割，根据Plank辐射定律采用标准黑体辐射源对光电信号的映射关系进行标定，利用比色法实现三维温度场表征。进一步在时间序列上控制多CCD相机来同步获取燃烧场不同视线方向的辐射信息，基于R、G通道内的灰度信息，对实验室蜡烛火焰与外场某型号固体火箭发动机试验器尾喷焰的瞬态燃烧场温度参量进行了测试。结果表明，在实验室内，蜡烛火焰温度分布范围为805.4~1280.8 K，使用热电偶进行时空点位验证，平均误差为3.8%，最大误差为4.36%；固体火箭发动机试验器尾喷焰最高温度为2125.7 K，经近红外测温仪验证，测试误差在8%以内。该研究能够在保证时间、空间分辨率的条件下对燃烧场的三维温度参量进行特征诊断，在航天测试领域，对固体火箭发动机的温度参量测量提供了一种有效的方法。

Three-dimensional radiation thermometry for dynamic combustion field based on multi-CCD synchronous coupling (invited)

In order to meet the demands of diagnosing the characteristics of spatiotemporal evolution of temperature parameters in combustion field, a dynamic three-dimensional radiation thermometry method based on multi-CCD synchronous coupling was proposed. On the basis of multiline-of-sight measurements corresponding to different directions, the segmentation of the combustion field in the form of voxel was conducted by the algebraic reconstruction technique. According to Plank’s radiation law, the standard blackbody radiation source was used to calibrate the mapping relationship of optical and electrical signals, and the three-dimensional temperature field was characterized utilizing colorimetric thermometry. The radiation information of the combustion field in different line-of-sight directions was further obtained synchronously by controlling multi-CCD on the time series. On the basis of the grayscale information in R and G channels, the temperature parameter in the transient combustion field of the candle flame in the laboratory and the exhaust plume of a certain solid rocket motor device were tested. The results showed that the temperature distribution range of the candle flame in the laboratory was from 805.4 K to 1280.8 K. Through the spatiotemporal point verification using a thermocouple, the average error was 3.8%, and the maximum error was 4.36%. The maximum temperature of solid rocket motor device exhaust plume was 2125.7 K, the measurement error of which was within 8% by the verification of near infrared thermometer. The characteristic diagnosis of the three-dimensional temperature parameter in the combustion field could be realized with sufficient temporal and spatial resolution, which provides an effective method for the measurement of temperature parameter of solid rocket motors in the field of aerospace testing.