关键词: 火箭发动机;燃气流;冲击影响;压力测量;温度测量

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.

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