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固体火箭发动机装药燃尽后的内弹道下降段对其性能具有重要的作用 .本文首先针对采用含铝推进剂的发动机建立其两相流动的理论模型 ,再用数值方法对其内弹道进行了预估计算 ,同时还与气相计算模型进行对比 .
The internal ballistic descending section of the solid rocket motor burn-out plays an important role in its performance.In this paper, the theoretical model of two-phase flow is established for an engine with aluminum-containing propellant, and then its internal trajectory is numerically calculated Estimated calculation, but also with the gas phase calculation model for comparison.