动态横向过载对固体火箭发动机内弹道的影响

为研究动态横向过载下固体火箭发动机（SRM）的内弹道特性，进行了某三组元复合推进剂在-50g～50g过载加速度下的燃速测量，结合Greatrix多参数模型建立了该推进剂的过载燃速模型；基于此模型，对管型内孔燃烧装药进行了横向过载下的燃面退移模拟，建立了动态横向过载下大长径比发动机的内弹道计算模型。结果表明：过载对该推进剂燃速影响存在一个角度阈值，负角度过载影响很小；瞬间一个横向过载会使燃烧室压强发生跃迁，在100g过载下，压强增加8%左右，过载消失，压强骤降；若受横向过载时间间隔一定，100g过载下导弹后作机动飞行（t=12～15 s）比先机动飞行（t=3～6 s）压强变化幅值小1%，对飞行更有利。

Influence of dynamic lateral overload on internal ballistics of solid rocket motor

In order to study the internal ballistic characteristics of the solid rocket motor（SRM） under dynamic lateral overload, the burning rate measurement of a three-component composite propellant under ?50g?50g overload acceleration was carried out, and the overload burning rate model of the propellant was established by combining with the Greatrix multi-parameter model; based on this model, the combustion surface retreat of tubular inner hole combustion grain under lateral overload was carried out, and the internal ballistic calculation model of large aspect ratio SRM under dynamic lateral overload was established. Results showed that there was an angular threshold for the influence of overload on the burning rate, and the influence of negative angular overload was small; an instantaneous lateral overload made the combustion chamber pressure jump, under 100g overload, the pressure increased by about 8%, the overload disappeared and the pressure dropped suddenly; if the time interval of lateral overload was fixed, the pressure change amplitude of maneuvering flight after 100g overload （t=12?15 s） was 1% smaller than that of maneuvering flight first （t=3?6 s）, which was more favorable for flight.