Reactive active propulsion

Abstract

A new interior ballistic concept of reactive active projectile propulsion is analyzed. During acceleration in a rocket launcher the projectile is separated from the rocket engine chamber by the action of active granular propellant charge located behind the projectile stabilizer. The projectile is then additionally accelerated with corresponding deceleration of the rocket engine chamber. The active propellant charge is initiated by the pyrotechnic delay during the rocket engine function. The interior ballistic cycle terminates near the front of the rocket launcher by the extraction completion of the projectile stabilizer from the launching tube. A theoretical model for reactive active propulsion is presented. The model includes simultaneous function of rocket engine and active propellant charge in the launcher. The computer code RAP (Reactive Active Propulsion) for interior ballistic cycle of reactive active projectiles is developed. The parametric study is carried out based on the RAP code calculations. The moment of active charge initiation by the pyrotechnic train is found to be very important parameter for regular function of the system. Computational results show possibilities of reactive active propulsion interior ballistic concept to significantly increase projectile performance.