火箭发动机试验红外测温技术应用  

Application of infrared temperature measurement technology in liquid rocket engine test

作　　者：徐峰[1] 罗军[1] 彭飞[1] 

机构地区：[1]西安航天动力试验技术研究所,陕西西安710100

出　　处：《火箭推进》2017年第1期78-84,共7页Journal of Rocket Propulsion

基　　金：航天支撑技术项目(617010429)

摘　　要：目前发动机试验温度参数主要采用接触式测量方法,测温元件直接与被测对象相接触,优点是测量精度高,缺点是试验过程传感器经常损坏或脱落,且高温和腐蚀性介质影响感温元件的性能和寿命。根据发动机试验任务的要求和液体火箭发动机试验的特点,结合先进的分布式无接触式测量及光纤传输的技术,设计并建立了红外热成像测量系统。该系统采用无损、无线测量及光纤传输方式,提高了发动机热试车恶劣环境条件下关键部位温度参数的获得率,为全面研究发动机工作过程温度场分布情况奠定基础。The temperature measurement during the liquid rocket engine test is currently done with the contact measurement method. It has high accuracy, but the performance and life of temperature sensing elements are influenced by contact of the measured object, high temperature and corrosion propellant. According to the requirements and the characters of the liquid rocket engine test, an infrared temperature measurement system was designed and established in combination of the advanced distributed non-contact measurement and optical fiber transmission technologies. The nondestructive and wireless measurement, and optical fiber transmission are adopted in the system, which improves the pick-up rate of temperature parameters on the key parts of the liquid rocket engine in running test in severe environment. The establishment of the system has laid a firm foundation for the research on temperature field distribution of liquid rocket engine.

关 键 词：发动机试验 红外测温技术 无线测量 红外热成像 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]