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采用空气与水作为二次流工质,进行流体喉部的冷流实验,研究了固体火箭发动机流体喉部的推力调节特性.分析了不同二次流工质、注射方式,注射流量下的推力响应时间、扼流性能、推力偏角和推力效率.实验结果表明:注射液态二次流推力响应时间更短;扼流性能、推力偏角与二次流的注射位置及注射角度有关,且随流量比的增大而增大;相同的流量比下,气态二次流的推力性能要比液态二次流的效果更好,但提供相同的流量比,液态二次流需要压比更小,且流量比的调节范围更大.
The air and water were used as secondary working fluid, and the cold flow experiment of fluid throat was carried out to study the thrust regulating characteristics of fluid throat of solid rocket motor.The thrust of different working fluid, injection mode and injection flow rate Response time, throttling performance, thrust angle and thrust efficiency.The experimental results show that the thrust response time of injection liquid second-order flow is shorter, the choke performance and thrust declination are related to injection position and injection angle of secondary flow, The flow rate ratio increases and increases; under the same flow ratio, the thrust performance of the gaseous secondary flow is better than the liquid secondary flow, but to provide the same flow ratio, the liquid secondary flow needs a smaller pressure ratio, And the flow rate adjustment range greater.