Based on computational fluid dynamic method and homogeneous multiphase theory

vaporization model was adopted to simulate vaporization between gas and cooling water

and missile's motion was simulated by dynamic zone mesh motion method. Three-dimensional unsteady gas-steam ejection gas-liquid two-phase flow field was studied. Compared with the experiment of solid rocket flow field injection with water

this proved that the numerical method was reliable. The flow field structure

secondary flow

load characteristic and internal trajectory in variable depth ejection during ejection were studied. The results show that the evaporation occurs on the wall of the pipe. The gas-steam high temperature region migrates with the increase of tube volume during ejection. Isolation region and secondary flow exist at cross section of the tube and pipe

and form different eddy structures. The maximum impact force occurs on the wall of the pipe between 30° and 60° bend angle at 0.16s. With the ejection depth increasing 10 m

the pressure of monitor is added by 0.25MPa and time of missile motion is delayed 0.01s.