一种测量固体火箭发动机羽焰温度的数据处理方法研究

针对连续测量固体火箭发动机羽焰温度的特点 ,提出了一种新的发射率假设模型 ,并在此基础上提出了一种新的多波长高温计的数据处理方法 ,即通过处理两个不同时刻多波长高温计的测量数据 ,由计算可同时获知两个时刻的真温及光谱发射率 .实验结果表明 ,其真温计算值与火箭发动机设计者提供的理论值之差在± 2 0K以内 ,说明该方法是解决固体火箭发动机羽焰温度测量的可行性方法

RESEARCH ON THE DATA PROCESSING METHOD OF SOLID PROPELLANT ROCKET ENGINE PLUME TEMPERATURE

Considering the characteristics of the plume temperature measurement of solid propellant rocket engine, a new emissivity assumption was presented. Based on the assumption, a new data processing method of the multiwavelength pyrometer was introduced. By processing the measured data of the multiwavelength pyrometer at two different time, the true temperatures and spectral emissivities at two different time can be simultaneously calculated. The experimental results show that the temperature differences between the calculated values and the theoretical ones provided by the rocket engine designer are within ±20K. The above mentioned method is a practical data processing method of solid propellant rocket engine plume temperature.