多根管型装药固体火箭发动机初始压强峰影响因素研究

In order to understand the problem of excessive initial pressure peaks appearing in the test of multiple tubular solid rocket motors, the combination of experimental research and theoretical analysis is used to study the effects of the ignition dose, the number of charges and the area of the limited of burning on the initial pressure peak. The results show that for multiple tubular solid rocket motor, it is found that the ignition dose has little effect on the initial pressure peak, and the reduction of the ignition dose can not effectively reduce the initial pressure peak. The number of charges and the limited burning area have a greater influence on the burn-through ratio and the initial pressure peak, when the number of charges is reduced from 7 to 6, the initial pressure peak is reduced by 57%, when the burning-limiting area is 0.22 times the outer surface area of the charges, the initial pressure peak disappears. At the same time, an erosion function of this type of charge was obtained with a critical burn-through ratio of 50. 10.