横向过载下固体火箭发动机内弹道特性研究

The abnormal phenomena of internal ballistics is easy to occur for most of the missiles flying at high altitudes, leading to mission failure under serious cases. In order to understand the influence of lateral overload on the internal ballistic performance of solid rocket motor(SRM)and better predict the internal ballistic performance of SRM under flight overload, a discrete coordinate solution method for non-uniform burning surface regression was established. From the simple inner hole combustion tube grain to the common complex star hole grain, the discrete coordinate solution method was used to simulate the burning surface regression under lateral overload, and the regression law of the burning surface was obtained. At the same time, the areas of different micro units were corresponding to the burning rate, which can predict the internal ballistic characteristics of the SRM under lateral overload. The results show that the lateral overload leads to eccentric combustion, the pressure of the combustion chamber increases, and the insulation is exposed in advance. Under 100 g lateral overload, the combustion chamber pressure increases by 4%, pressure peak occurs at 0.4 s, and exposure time of the insulation increases by 1.6 s. The number of drop sections of the burning surface of star hole grain is equal to the number of star angles N/2+1.The influence of lateral overload on surface regression and interior ballistic performance of SRM is analyzed, which has guiding significance for SRM design.