固体火箭发动机喷管效率计算

Calculation of nozzle efficiency for solid rocket motor

采用半经验法计算了固体火箭发动机喷管的效率,即用计算流场的方法确定了喷管二维两相流损失和边界层损失,用SPP经验法预示了喷管的化学动力学损失、喷管烧蚀损失和喷管潜入损失。利用该方法对几个实际固体火箭发动机喷管效率进行了计算,计算结果与实际结果比较符合,精度偏差在1%之内。

SRM (Solid Rocket Motor) nozzle efficiency is calculated with the semi-analytical method. In the calculation, the losses of nozzle axisymmetric two-phase flow and boundary layer are determined with the method of numerical simulation of nozzle flow field. The nozzle chemical kinetic loss, throat erosive loss and submergence loss are predicted with SPP empirical method. The efficiency of four actual SRM nozzles is calculated. The computational results are in good agreement with the experimental results, and the deviation is less than 1%.