抄録
The igniter in the rocket motor is used to give sustained combustion to the propellant. This research paper focused on experimental and numerical investigation of effect of the igniter mass on the maximum pressure rise in single grain solid propellant rocket motor. Experiments are carried out with varying igniter mass by approximately ±15 % of calculated igniter mass. The experimental results are in good agreement and compared with numerical results. A linear relationship between igniter mass and maximum pressure is also established numerically. The present investigation reveals that, the igniter mass contributes in maximum pressure rise along with propellant. The maximum pressure can be retained within required range by optimizing the igniter mass for safe working with rocket motor.
