摘要
小发动机是在高温条件(≈1800℃)下进行头部防热材料模拟试验的设备,是为解决导弹弹头再入大气层时的防热问题而研制的。本文叙述了用光学法测量小发动机燃气流火焰温度、燃气流中模型前端的激波温度及不同材料的模型表面温度。实验表明:不同材料的模型,其表面温度不同。文中对测温误差进行了初步分析。
A small rocket engine is a device used to make a analogue test for the material heat-insulation in high temperature(≈1 800℃). It is made for solving the missile head re-entry heat-protection.This paper presents a no-contact temperature measurement for a small rocket engine jet exhaust,for a shock wave on nose cone of a model in a jet exhaust and for a model surface of various materials.Experiment showed that the surface temperature is different when the material is different. The error is analysed in measuring temperature.
出处
《宇航计测技术》
CSCD
北大核心
1990年第4期53-59,共7页
Journal of Astronautic Metrology and Measurement
关键词
火箭发动机
温度测量
燃气流
Rocket engine
Jet exhaust
Jetted flame
Photoelectric pyrometer
Temperature measurement
