多根管型装药固体火箭发动机初始压强峰影响因素研究

Study on Factors Affecting Initial Pressure Peak in Solid Rocket Motor with Multiple Tubular Charges

关键词:  装药  固体火箭发动机  初始压强峰  燃通比  推进剂

摘要:

为了解多根管型装药固体火箭发动机实验时出现的过高的初始压强峰的问题，采用实验研究和理论分析相结合的方法，对点火药量、药柱数量、限燃面积对初始压强峰的影响进行了研究。结果表明：对于多根管型装药固体火箭发动机，发现点火药量对初始压强峰影响较小，减少点火药量不能有效降低初始压强峰；药柱数量和限燃面积对燃通比和初始压强峰影响较大，装药数量从7根减少为6根时，初始压强峰减小了57%；限燃面积为装药外表面面积的0.22倍时，初始压强峰消失。同时，得到了该类型装药的侵蚀函数，其临界燃通比为50.10。

Abstract:

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.