动态横向过载对固体火箭发动机内弹道的影响

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.