【摘要】 推进剂的羽焰温度是固体推进剂火箭发动机的重要参数,对于研究发动机内的燃烧过程具有重要价值．使用多波长高温计实现对固体推进剂火箭发动机羽焰温度的测量．根据多光谱辐射测温的参考温度数学模型和测量得到的数据,判断羽焰的发射率与波长的关系．并对二者的关系进行非线性拟合,采用遗传算法进行优化计算得到羽焰温度和发射率．实验结果表明,羽焰温度计算值与火箭发动机设计者提供的理论值之差在±20 K以内,说明该方法是解决固体推进剂火箭发动机羽焰温度测量的可行性方法．更多还原

【Abstract】 The plume temperature is an important parameter, for solid propellant rocket engines and it is useful for determining the combustion process of the engine. Plume temperatures of a mounted solid propellant rocket engine were measured by multi-wavelength pyrometer. According to the reference temperature model of multi-spectral thermometry and the obtained experimental data, the relationship between the emissivity and wavelength of the plume was predicted. The relationship was nonlinearly fitted and optimized by genetic algorithm to calculate plume temperatures and emissivities. The experimental results show that the temperature differences between the calculated values and the theoretical ones provided by the rocket engine designer are within 20 K. Therefore, this method is applicable to measure the plume temperatures of solid propellant rocket engines.更多还原