为研究激波起爆脉冲爆震发动机的性能,建立了其性能计算的简化模型和计算方法,计算分析了共振腔直径为90mm时,推力、耗油率等主要性能参数随共振腔进口气流参数条件及飞行条件的变化。计算结果表明,随着共振腔进口气流总压的升高,发动机推力增大,耗油率降低,而随着进口气流总温的升高,发动机推力减小,耗油率降低;随着飞行马赫数的增大,发动机的推力和耗油率增大,而随着飞行高度的升高,发动机的推力和耗油率减小。

Simplified model and performance calculation method were established to investigate performance of shockwave focus pulse detonation engine. Some main parameters were calculated to discuss their variation along with the inlet parameters and flight condition for an engine with a 90mm-diameter resonant cavity. The results indicate that thrust increases, and specific fuel consumption decreases with inlet total pressure increasing. With the increasing inlet total temperature, thrust and specific fuel consumption decrease. The increase in flight Mach number leads to increase in thrust and specific fuel consumption. The thrust and specific fuel consumption decrease with increasing flight altitude.