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本文导出了类似于火箭发动机的火箭冲压发动机喷管的两相流动理论比冲公式;从理论上证明:对这两类发动机的两相喷管流动特性可以通过一个共同的组合参数——当量排气速度来进行分析;介绍了一种变滞后两相流动比冲损失的简单估算方法;提出了一种处理奇点问题的近似解法。
In this paper, a theoretical comparison of the two-phase flow theory of rocket ramjet nozzle with rocket engine is derived. It is theoretically proved that the two-phase nozzle flow characteristics of the two types of engine can be expressed by a common combination of parameters Gas velocity. A simple method to estimate the specific impulse loss of two-phase flow after stagnation is introduced. An approximate solution to the singularity problem is proposed.