No abstract

In the background of a container-type vertical launch missile, the simulation method of adapter separation in different wind speeds is researched. Based on force analysis of the adapters during their separation from the missile, the dynamic and kinematics equations of the adapter separation are established. The adapter’s aerodynamic parameters at different attitudes getting from the numerical wind tunnel are chosen to be the input. Through the dynamic simulation of the separation process of the adapters, the simulation results are in good agreement with the experimental data. The trajectory and placement distribution of adapters are obtained during the analysis of force and motion stance at different wind speeds. Then the relative distances between the adapter and missile or launch facility are determined. At the same time, it can be estimated that the combined calculation will save about two-thirds of time compared with dynamic grid method computing, which provides a significant guidance for the simulation method of adapter separation.

This study attempts to determine the effect of and mechanisms for the suppression of the ignition pressure and back-flowing exhaust during a hot launch process in a W-shaped silo, considering the missile movement via dynamic mesh technology. The mixture model for the multiphase and the turbulent model employed were experimentally proved to be accurate and reliable. The numerical results show that the injection of water into a missile exhaust can effectively suppress the ignition overpressure, thereby reducing the time of oscillation and oscillation amplitude, and reducing the maximum pressure at missile bottom from 3.68 × 105 Pa to 2.39 × 105 Pa. In addition, water injection makes the back-flowing exhaust remain at the bottom of the launch duct instead of filling the duct, and it cools the missile bottom, thus leading to a reduction in the maximum temperature from 3000 K to approximately 500 K.