用于固体火箭羽焰真温测量的宽量程多光谱高温计

现有的多光谱高温计的测量下限均大于1 173 K(900 ℃)，不适用于新型火箭羽焰真温测量范围的要求(900~2 700 K)。为了解决现有的多光谱高温计无法测量1 173 K以下羽焰真温的问题，研制了用于固体火箭发动机羽焰真温测量的宽量程多光谱高温计。该多光谱高温计采用了并联光电探测器阵列相邻像元的方法，并且创建了基于对数函数的900~1 173 K温区的温度标定方法，从而拓宽了高温计的温度测量范围。针对某型号固体火箭发动机羽焰的三个目标点进行了现场测量，实验结果验证了该高温计的有效性。

A Wide-Range Multi-Spectral Pyrometer for True Temperature Measurement of Solid Rocket Engine Plume

The lower limit of the existing multi-spectral pyrometer is higher than 1 173 K (900 ℃), which is not suitable for the measurement of the true temperature range of a new rocket plume (900~2 700 K). A wide-range multi-spectral pyrometer for true temperature measurement of the solid rocket engine plume is developed to solve the problem that existing multi-spectral pyrometers cannot measure the plume true temperature when the temperature is lower than 1 173 K. The pyrometer uses a parallel connection method of the photoelectric detectors adjacent pixels, and proposes a temperature calibration method for 900~1 173 K region on the basis of the logarithmic function, so as to broaden the range of the measuring temperature pyrometer. The field measurement is carried out on the three targets of a solid rocket engine plume and the experimental results verify the validity of the pyrometer.