原子发射光谱双谱线法测量固体火箭发动机内燃气温度

Combustion Gas Temperature Measurement in the Chamber of Solid Rocket Motor by Double Line of Atomic Emission Spectroscopy

发展了一种利用原子发射双谱线法 ,测试固体火箭发动机燃烧室内燃气温度的方法 ,设计了相应的测试系统。该方法利用石英光学纤维 ,将固体火箭发动机内高温高压燃气的光谱辐射信号传入测量系统 ;选用了两条波长间隔小的谱线 ,大大减少了光谱辐射率、光谱透射率等对光谱测量的影响 ;设计使用了耐压测量探头 ,保证在高压、强腐蚀实验条件下 ,系统的密封性和光的透过率。对装填有SQ 2推进剂的固体火箭发动机燃烧室内的气流温度进行了在线检测。测量时间分辨率可高达 0 5 μs。

A method was developed to measure the gas temperature in the chamber of solid rocket motor by using the double line of atomic emission spectroscopy. The measurement system had been designed. In this method. the spectral signal of the bun-ling gas with high pressure and high temperature in the solid rocket motor chamber was transfer into the spectroscopic system by using a quartz optic fiber. The effect of the spectral radiance and spectral transmissivity on the spectral measurement was decreased extremely by using two spectral lines that the interval was very small. A pressure-resistant probe was designed and applied, which guarantee the sealing ability and the spectral transmissivity of measurement system under the high-pressure and erosion experimental condition, The distributions of gas temperatures vs. time in the chambers of solid rocket motor that charged in the SQ-2 propellants were measured in situ and real time. The time resolution can highly reach 0.5 Vs.