Patent ID: 8794007

Claim:
A rocket propulsion device comprising: a tubular case of the rocket propulsion device for receiving a propellant; a nozzle at least partially inserted in the case, the nozzle being configured to discharge gas upon burning the propellant and to rotate with respect to a central axis of the nozzle: and a locking unit being configured to be wound on the nozzle, the locking unit in the form of a band having two open ends, wherein a through hole for inserting the locking unit therein is formed at a first region on the circumference of the case, and the both ends of the locking unit are located at a second region symmetrically opposite the first region with respect to the central axis, and wherein the through hole defines a first portion of fragile rigidity and the both ends of the locking unit define a second portion of fragile rigidity, the first portion of fragile rigidity and the second portion of fragile rigidity being symmetrically positioned with respect to the central axis, and wherein the nozzle and the case are fixed to one another through pins.