MISSILE AND DRIVE OF MISSILE STAGE SEPARATION MECHANISM Russian patent published in 2006 - IPC F42B15/00 

FIELD: armament.

SUBSTANCE: the missile has a sustainer stage, separating zero stage with an engine, stage separation mechanism including a drive, prechamber with a pyrocomposition and a primer cap, adapter frame. The prechamber is positioned with obturation in a probe fastened with the aid of catches on the end face of the aft compartment of the sustainer stage and squeezed out by a spacer nut up to the stop of the catches against the adapter frame. The prechamber is isolated from the blocks of the sustainer stage aft compartment by a partition. A drive provided with a striker pin positioned opposite the primer cap is installed on the bottom of the prechamber. The missile stage separation mechanism has a piston and locks. The piston is loaded by an adjusting spring and retained from longitudinal motion by locks. The adjusting spring is tightened by the flange of a stop sleeve rigidly fastened in the drive body and provided with a stricker pin positioned in the same axis with the primer cap, the striker pin is tightened by the mainspring and retained by ball locks placed in the stop sleeve by embracing by the piston skirt.

EFFECT: enhanced reliability of operation of the guided missile.

2 cl, 4 dwg