METHOD FOR CONTROL OF SPIN-STABILIZED MISSILE AND GUIDED MISSILE Russian patent published in 2001 - IPC

FIELD: rocketry. SUBSTANCE: the method consists in variation of the quantity of control fins, that is effected by successive pair- wise opening and actuation of control fins opposite relative to the missile longitudinal axis as soon as the missile attains a definite flight speed. At supersonic flight speeds the missile control is accomplished by one pair of fins, and at subsonic flight speeds in the terminal trajectory leg - by two pairs of fins. The missile has a body, whose frame carriers actuators kinematically linked with the aerodynamic control surfaces. The fin opening and lock mechanisms are combined in pairs, opposite relative to the missile longitudinal axis. They are positioned on shafts installed on the frame and kinematically linked by levers with the actuators, and made in the form of axles rigidly coupling the shafts in pairs installed in which are pyrotechnical cartridges, and pistons positioned in the central holes of the shafts between the axle ends and the trailing edges of the fins. The axles have ducts communicating the chambers of the pyrotechnical cartridges with the piston chambers. The fins are installed on the folding axles. The folding axles are positioned eccentrically relative to the axis of the shafts, and the trailing edges of the fins are positioned relative to the axis of the shafts at an angle exceeding the fin aperture angle. EFFECT: enhanced stability of missile flight at different speeds and enhanced accuracy of fire. 2 cl, 2 dwg