中文摘要：

应用CE/SE方法对小型固体火箭发动机内流场进行一维数值模拟。对燃烧室和喷管进行了一体化处理,得到了燃烧室以及喷管处的压力、温度以及马赫数的变化。结果表明,小型固体火箭发动机工作初期通道内压力振荡上升,且振荡次数随着堵盖打开压力的增加而增加;堵盖打开后通道内高温燃气峰逐渐退移至喷管收敛段,发动机头部压力大于其他位置压力,在装药末端存在微弱波动。

英文摘要：

A numerical simulation on one-dimensional internal flow filed of small solid rocket motor was carried out by means of CE/SE method. The change data of the pressure, temperature and mach number of the combustion chamber and the nozzle were obtained with the use of the integrated treatment method. The results showed that the internal pressure increases oscillatorily at the beginning. It will be higher with the rupture of seal diaphragm, which also results a higher oscillation frequency. The peak of the high-temperature gas is gradually moved to the convergent segment of nozzle after the rupture of seal diaphragm. The pressure in the front o f the motor is the highest and that at the end of the charge remains a weak fluctuation.