ROCKET MISSILE CONTROL METHOD Russian patent published in 2013 - IPC F41G7/00 

FIELD: weapons and ammunition.

SUBSTANCE: start of flight of a rocket missile is performed with roll position stabilisation of its front section connected to the rest sections of the missile through a cylindrical hinge. With that, roll position stabilisation of the front rocket missile is performed with an electric torque motor; control action on the electric torque moment is formed with a roll position control unit as per commands supplied from the flight control unit based on the information received from the unit of navigation and orientation system of roll position turning angle (relative to a fixed coordinate system) of a control module. Control action on rocket missile is formed with one pair of aerodynamic rudders fixed on outer surface of the control module at a fixed angle to longitudinal axis of the control module. Increase of flight range is performed at zero turning angle relative to longitudinal axis of the control module due to a partial planning mode. Rocket missile control on the territory is performed by changing direction of ascentional force vector of rudders owing to roll position turning of the control module at angles calculated with the flight control unit.

EFFECT: simplifying a functioning algorithm of a rocket missile control system; improving combat effectiveness of a rocket missile.

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