航空学报 > 1983, Vol. 4 Issue (4): 101-104

火箭冲压发动机喷管的两相流动理论比冲——一种简单估算方法

毕士冠   

  1. 中国精密机械公司北京研究院
  • 收稿日期:1982-02-01 修回日期:1900-01-01 出版日期:1983-12-25 发布日期:1983-12-25

THEORETICAL SPECIFIC IMPULSE FOR TWO-PHASE FLOW IN NOZZLE OF ROCKET-RAMJET ENGINE——A SIMPLE ESTIMATION METHOD

Bi Shiguan   

  1. Beijing Research Institute,China Precision Machinery Co.
  • Received:1982-02-01 Revised:1900-01-01 Online:1983-12-25 Published:1983-12-25

摘要: 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。

Abstract: The theoretical specific impulse formula for two-phase flow in nozzle of rocket-ramjet engine is derived on the basis of similarity to that used for rocket engine.Theoretically,it is proved that for both these engines,the properties of two-phase flow in nozzle can be analysed with a common combined parameter which is equivalent to exhaust velocity.A simple estimation method for specific impulse losses of two-phase flow with variable lag is provided.An approximate solution dealing with the singularity is proposed.