Solid rocket motor (SRM) temperature is an important physical parameter for which there is no reliable in situ measurement device, apart from a thermocouple, for such a high temperature environment apart. In this study, an ultrasonic temperature measurement system was designed with an iridium-rhodium-40% alloy waveguide. Laboratory experiments showed that the device obtained ultrasonic signals up to 1800 °C with a temperature fitting curve from room temperature to 1800 °C. The thermometer also operated stably under high temperature and produced a repeatable calibration curve, at 97% repeatability. An error band was obtained with 95% confidence. At temperatures above 1000 °C, sensitivity gradually increased to a maximum of 0.0035 µs/°C. A corresponding application structure was established for an SRM before subjecting the sensor to a temperature test experiment. The temperature–time curve obtained detected a peak temperature at 1744 °C.

固体火箭发动机（SRM）温度是一个重要的物理参数，对于该参数没有可靠的就地检测测量设备，除了热电偶以外，还适用于这种高温环境。在这项研究中，超声温度测量系统是用铱铑40％合金波导设计的。实验室实验表明，该设备获得了高达1800°C的超声波信号，并具有从室温到1800°C的温度拟合曲线。温度计在高温下也能稳定运行，并产生可重复的校准曲线，重复性为97％。以95％的置信度获得了误差带。在高于1000°C的温度下，灵敏度逐渐提高到最大0.0035 µs /°C。在对传感器进行温度测试实验之前，为SRM建立了相应的应用程序结构。获得的温度时间曲线检测到1744°C的峰值温度。