摘要
讨论固体火箭发动机羽焰温度场的特点及测试方法,简要论述了热电偶法的缺点,重点论述红外测温法测试发动机羽焰温度场的可行性及关键技术问题的解决方法。文中针对红外测温法的难点问题,明确提出了发动机羽焰发射率的测试方法及羽焰三维温度场重构的方法,并指出红外测温技术是羽焰测温的发展趋势之一。
It is very important in temperature flow field measurement for solid rocket motor. In this paper, the characteristic of temperature flow field and testing method are discussed. Introducing the - advantage of thermo-couple pyrometer in brief, also described the applicability of infrared spectroscopy and its key technology in detail. Aiming at the difficulty of infrared spectroscopy, the method for testing radiant coefficient of exhaust flame of rocket motor and 3-D reconstruction are introduced. Finally the development tendency of infrared spectroscopy is presented.
出处
《航空兵器》
2006年第6期45-48,共4页
Aero Weaponry
关键词
固体火箭发动机
羽焰温度
温度测量
红外测温法
solid rocket motor
exhaust flame temperature
temperature measurement
infrared spectroscopy
