脉冲触发对固体火箭发动机内弹道和瞬态流场特性的影响

The effect of pulse triggering on the internal ballistics and transient flow field characteristics of solid rocket motor (SRM) is studied. An internal ballistic model of pulse triggering,a erosion combustion model and a dynamic flow field simulation model are established by numerical calculation method. The transient flow field of solid rocket motor in the process of pulse triggering is simulated. The results show that,the pressure prediction error is less than 5% compared with the experimental result. The pulse triggering increases the velocity of transverse gas flow in the combustion chamber,and the propellant near the pulse end is burning with erosion,which contributes 44% to the pressure rise. When the pulse is triggered,the closer the propellant is to the pulse inlet,the more aggressive the erosive burning is,and the maximum erosion ratio can reach 7. 32. The simulated results show that the higher the pulse charge is,the greater the peak pressure is,the higher the pressure rise rate is,and the higher the attenuation rate is after the pulse is terminated.