导弹垂直发射系统排烟道燃气流的等离子体测温法研究

TEMPERATURE MEASUREMENTS IN ROCKET LAUNCHING SYSTEM USING LANGMUIR PROBE

导弹垂直发射系统排烟道出口燃气流直接接触飞出发射箱的导弹。所以排烟道进出口温度分布，对系统设计十分重要。本文采用等离子体测温法，测得了温度分布。发现由于导弹发射位置的变化，排烟道内温度分布是很不均匀的。

The launching system for the rocket lobe launched vertically is composed ofa launching box for carrying the rocket,a pressure room and a exhaust channel. To achievethe reasonable design of the launching syetsn, the profiles of temperature, velocity andpressure in the flow fields inside the system need to be known. Since the temperature isvery high and the velocity is large,the measurement for the temperature is quite difficult, acalibrational method for measuring the temperature of high pressure plasma is suitable forthis purpose. Choosing fiVe points in the exhaust channel,a temperature profile is obtainedand compared with other experimetal and theoretical results.