气密条件下水下热发射流场数值研究

Numerical simulation of complex flow field for missile launched under-water under gas proof conditions

针对气密条件下导弹水下热发射伴随的复杂多相流动,采用混合多相流模型求解燃气、水介质与水蒸气的耦合流动、传热及相变过程;利用动网格技术模拟导弹发射初期的计算域变化。计算结果表明,受多相耦合流动影响,发动机喷管出口参数经历了压强峰值、压强次峰值、压强阶梯上升、压强波动及压强震荡等不同状态,对发动机推力产生重要影响。此外,计算过程还揭示了发射筒口燃气泡发展、导弹表面温度变化等过程的基本规律。

To research the complex flow field for missile launched under water under gas proof condition,the multi-phase mixing model was used to simulate the coupled flow,heat transfer and phase changing process between combustion gas,liquid water and water steam.The dynamic mesh method was used to update the flow field following with the missile movement.The calculated results indicat that the pressure at the nozzle exit,which is influenced by the coupled flow,experienced different status,such as pressure peak value,second peak value,step increase,pressure vibration and so on.Furthermore,the developing process of the gas cavity and the temperature variation on the missile surface were discovered during the calculating process.