用于固体火箭燃烧室的超声温度测量系统。

Ultrasonic thermometric measurement system for solid rocket combustion chambers.

作者信息

Wei Yanlong, Liang Haijian, Wang Gao, Xingqi Wang, Yang Lu, Zhou Hanchang, Yang Luxia, Mu Xiaofang, Yin Guimei

机构信息

Science and Technology on Sensor Test & Intelligent Information Processing Laboratory, Department of Computer Science, Taiyuan Normal University, Taiyuan 030619, China.

Department of Electronic Engineering, Taiyuan Institute of Technology, Taiyuan 030008, China.

出版信息

Ultrasonics. 2021 May;113:106361. doi: 10.1016/j.ultras.2021.106361. Epub 2021 Jan 19.

DOI:10.1016/j.ultras.2021.106361

PMID:33548757

Abstract

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.

摘要

固体火箭发动机（SRM）温度是一个重要的物理参数，除了热电偶外，在如此高温的环境中没有可靠的原位测量装置。在本研究中，设计了一种采用铱铑40%合金波导的超声温度测量系统。实验室实验表明，该装置在高达1800°C的温度下能获得超声信号，且具有从室温到1800°C的温度拟合曲线。该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%。获得了置信度为95%的误差带。在高于1000°C的温度下，灵敏度逐渐增加，最高可达0.0035 µs/°C。在对传感器进行温度测试实验之前，为固体火箭发动机建立了相应的应用结构。获得的温度-时间曲线检测到峰值温度为1744°C。