脉冲触发对固体火箭发动机内弹道压强抬升的影响

In order to understand the working performance of solid rocket motors under pulse trigger excitation, a pulse trigger experimental system was designed and experiments were carried out, and a pulse trigger internal ballistics model was established. The results show that the pressure rise response time of the experimental system is within 25 ms. Compared with the extended section position, the pressure disturbance at the motor head is greater, and the disturbance propagation speed is 1259 m / s. The prediction errors between pulse trigger peak pressure and motor pressure rise are both less than 6%. The longer the extension section, the smaller the pressure rise caused by pulse triggering; the greater the pulse charge, the higher the pressure rise. The relationship between pulse charge and pressure rise is near linear, the increase of pulse charge from 3 g to 8 g, the motor pressure rise rate from 8.142% to 31.594%; the motor pressure rise increases significantly with the increase of throttling aperture of pulse trigger, the aperture increases from 1 mm to 4 mm, and the pressure rise rate increases from 1.656% to 27.448%. The choke effect causes that the throttling aperture of 1 mm cannot achieve the pulse trigger effect. The motor pressure rise decreases with the increase of the throat diameter, the throat diameter increases from 12. 50 mm to 14. 00 mm, and the pressure rise rate decreases from 19.204% to 14.771%. For the experimental system, the trigger time has little effect on the motor pressure rise.