Numerical Simulation of the Backward Dispensing of a Missile from the Guide Rail Inside the Carrier at Supersonic Flow

Predicting the separation trajectories of both the carrier and the missile is a challenge due to the interdependent rigid motions caused by the guide rail. The rigid motion equations of the carrier and missile during separation are derived, considering the guide rail constraint. Based on overset grid technology, the fluid equations and the derived equations are coupled to simulate the separation. Then, the impact of the carrier's internal structure, as well as flight parameters including to flight altitude, Mach number, angle of attack, sideslip angle, and vertical relative overload on the separation is analyzed. The trajectories and attitude angles of the carrier and missile are obtained. The results indicate that the carrier's internal structure exhibits negligible impact on the separation at supersonic flow; increasing the flight altitude or decreasing the Mach number can facilitate the rapid detachment of the missile from the carrier’s base flow field to improve the safety of separation, where the former is more effective in improving the safety; increasing the angle of attack and sideslip angle enhances the aerodynamic interference between the carrier and the missile, with higher sideslip angles increasing lateral displacement of the missile relative to the carrier; decreasing the vertical relative overload can enhance the safety of separation.