以某可变流量固冲发动机为研究对象,建立进气道/补燃室一体化流场数值模型,结合地面直连试验,研究了空燃比对固冲发动机性能和流场结构的影响。结果表明:导弹飞行状态不变,减小空燃比可有效提高固冲发动机的推力但比冲减小,导弹射程减小;大空燃比调节时,补燃室内流场结构未发生显著变化,空燃比减小到7时,大量燃气沿补燃室中上部流动;空燃比减小使进气道的结尾激波向上游推移,进气道裕度减小。

The integrated flow field implemented for variable flow ducted rocket. Compared with direct-connected ground test, the influence of air-fuel ratio on the performance and flow field of ducted rocket analyzed. The results show that the rocket thrust has been efficiently enhanced, together with specific impulse descending and range of missile reducing, by keeping missile flight state constant and reducing air-fuel ratio. While air-fuel ratio reduces to 7, the configuration of flow field in combustor changes, then a mass of fuel flows along the middle of combustor. The terminal shock wave of inlet moves toward the intake and the margin of inlet reduce by reduced air-fuel ratio.