无喷管火箭发动机非定常跨音流场计算

CALCULATION OF UNSTEADY TRANSONIC FLOW FIELD IN A NOZZLELESS ROCKET MOTOR

本文对点火过程进行一定处理,用MacCormark显示预校两步差分格式计算无喷管火箭发动机从点火起整个工作过程的一维非定常跨音速流场。计算并对比了圆柱内孔装药及片形装药两种情况,计算结果规律性好,与现有实验数据符合较好。

After some treatment of the ignition process, the MacCormark explicit prediction-correction schemes can be adapted to predicting the one-dimensional unsteady flow field and interior ballistics in a nozzleless rocket motor from ignition to the end. The interior ballistics of cylindrical proforated and slab charges in the nozzleless rocket motor are calculated and compared with each other. The predicted results are in agreement with the experimental data. Moreover, the computations reveal that the choking position appears somewhat downstream to the geometric throat position and the thrust increases as the angle of divergence decreases and vice versa.