ROCKET Russian patent published in 2009 - IPC F42B15/00 

FIELD: aviation.

SUBSTANCE: invention relates to the field of rocket technology and can be used on rockets with a separate mother missile. The rocket consists of a separate mother missile with engine, sustainer propulsion stage with apparatus control, mechanism for breaking up of stages, including propulsion, gas generator isolated from the mother missile, inner cylinder and nose with circular sections. The nose is attached in the transitional stage. Between them and in the transitional stage a cavity is formed in which an electrical cable is located, on end of which is equipped with a socket with a forked electrical source for the engine ignition, and at the other end a plug. In the window of the nose the anchor for affixing the transitional stage is located using a pin fixing using an angular position the mother missile relative to the nose. Having orientated the nose relative to the engine the key is set in the transitional stage.

EFFECT: reduction of dispersion of the mother missile after separation from the launch engine with increased coefficient for the action of the mechanism for stage separation.

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