火箭弹发射过程冲击流场压力和温度实验测量

Measurement of pressure and temperature in exhaust jet during launching stage of rocket

关键词:  火箭发动机  燃气流  冲击影响  压力测量  温度测量

Key words:  Rocket engine  Gas flow  Shock effect  Pressure measurement  Temperature measurement

摘要:

考虑燃气流场的冲击效应,根据冲击特点对燃气作用区域的装置结构和强度进行合理的设计,以获得有效的导流和防护效果。实验对火箭发射阶段管后冲击流场在平面斜钢板上的流动参数进行了测量。得到了火箭燃气射流对倾斜钢板热冲击的最大滞止压力和温度,以及冲击流场的压力与温度分布,并确定了管后燃气冲击流场的危险区域。

Abstract:

Impinging effect of rocket exhaust jet should be considered comprehensively in overall design of rocket weapon system. Rational design for structure and strength of the equipment in shock-affect zone according to exhaust jet characteristics can help to achieve effective flow bypass and protection function. Flow parameters of exhaust jet on a lean steel platform were measured in the experiment during a practical launching. The maximum stagnation pressure and temperature, and distribution of pressure and temperature exhaust jet on the platform were obtained. The dangerous zone behind launch tube is determined from these data.