Regarding a low-temperature gas ejection mechanism

a simplified physical model of the secondary combustion was established

a renormalization group k-ε turbulence model was adopted to simulate the flow-field

and a finite rate/eddy dissipation model was used to simulate the gas phase combustion

meanwhile a dynamic mesh update method was employed to update the missile movement; the launch canister within the load and the interior ballistic properties were obtained through numerical analysis. Results show that: if the interior ballistic design condition is met

the range of the total temperature in the entrance section of the nozzle of gas generator is 0.538-1.231

and the time of secondary reaction and the time out of the barrel decreases with the rise of the total temperature

and the exit velocity increases accordingly. The range of the oxygen mass fraction of the launch canister is 0.07-0.30

and the begin time of secondary reaction and out of the canister of time decreases with the increase of the oxygen mass fraction

and the exit velocity increases with the increase of the oxygen mass fraction. Research results can be used as a reference for the interior ballistic and device structure.