Abstract: Solid-propellant rocket engine with a combustion chamber, with a thrust nozzle, with one or more grains in the combustion chamber, at least one of which comprises two parts, namely, an inner burner part and an outer burner part, wherein the latter is connected to a support structure, has a cross section changing over its length, is accommodated in the hollow space of identical shape of the inner burner part, and is axially displaceable. A thermal barrier is arranged at the nozzle-side end of the two-part grain. The outer burner part is fitted gap-free into the inner burner part. The contour formed by the contact surfaces of the two grain parts encloses a cross section expanding from the front to the rear. The outer burner part can be moved from a front, inactive position, which is positive-locking with the inner burner part, into a rear, active position with a defined flow gap between the contact surfaces of the grains.

Abstract: A device for ejecting ammunition containers from a war head has transverse to the war head longitudinal axis a bellows, which holds the ammunition containers in a plurality of concave pockets. The bellows is inflated by a gas generator including a gas-permeable tube extending along the longitudinal axis. In order to achieve a wide range of variations in the behavior of the ammunition containers in the process of being ejected, a propellant charge of the gas generator is particulate, with at least one ignition cord extending along the longitudinal axis of the tube around which a particle ignition mixture is arranged, so that the hot particles during burn-down of the ignition mixture are pressed between the particles of the propellant charge. A daming serves for building up the initial pressure required for the burning down of the propellant charge.