METHOD FOR CONTROL OF MISSILE AND CONTROL ACTUATOR POD (MODIFICATIONS) Russian patent published in 2006 - IPC F42B15/00 F42B10/60 B64C13/40 

FIELD: rocketry, applicable in guided projectiles and missiles of high-accuracy weapon.

SUBSTANCE: the method for control of missile includes formation of a signal to the control actuator by the missile control system and the respective angular deflection of the aerodynamic control surfaces by the control actuator relative to the missile longitudinal axis within two maximum values. At the instant when the aerodynamic control surfaces attain the maximum deflection angle the action of the signal of the control system on the control actuator stops, and an action is formed in it providing angular deflection of the aerodynamic control surfaces to the opposite side. In the first modification the control actuator pod has an actuator with a piston in the form of a rocker fastened on the pivot hinge of the aerodynamic control surfaces, the piston is installed in the body separated by a partition in the axis of the control surfaces into working chambers, whose lateral walls have spherical surfaces. The common real wall is made with holes communicating the working chambers with an air distributing device. An intermediate cavity is formed near the rear wall by undercutting of the lateral walls. The distance from the axis of rotation of the aerodynamic control surfaces to the rear wall and the range of the spherical surfaces from the axis of rotation of the aerodynamic control surfaces in the direction from the rear wall have a value determined from the first mathematical expression. The spread of the spherical surfaces from the axis of rotation of the aerodynamic control surfaces in the direction to the rear wall makes up the value determined from the second mathematical expression. IN the second modification the control actuator pod has series-connected input adder, amplifier, actuator and a feedback transducer. It also has a limiter of voltage of the positive and negative magnitudes of the feedback transducer signal, -two comparators, analog multiplexer and a formed of maximum control commands.

EFFECT: eliminated vibratory load on the on-board devices of the missile control system at execution of the maximum control commands by the control actuator.

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