三维组合药型单室双推力发动机燃面与内弹道计算

BURNING SURFACE AND INTERNAL BALLISTIC CALCULATION OF DUAL-THRUST ROCKET MOTOR WITH THREE DIMENSIONAL ASSEMBLING GRAINS

基于有限容积的思想，构造任意形状的三维药柱燃面退移通用计算方法，并推广应用于嵌金属丝推进剂的燃面计算。计算过程只关心燃面的始态和终态，可完全避开错综复杂的几何燃面变化规律，实现任意药型下多推进剂、变燃速燃面退移的计算机数值模拟。在此基础上，对三维组合药型单室双推力发动机进行了喉部烧蚀条件下的内弹道计算，同时与试验结果进行比较，取得了较好的效果。

ased on finite volume method,a general numerical burning surface calculation methodis derived for arbitrarily shaped three dimensional assembling grains. Suitable for various grain designsuch as multi propellants, dual burning rate grain, or even grains containing metal wire, the numericalprocedure requires only the initial and final grain shape, complex geometric analytical relations are notneeded. Internal ballistic performance of a dual thrust solid rocket motor with 3-D assembling grainsis predicated under the condition of throat ablation. Computational results are in good agreement withexperiments.