GUIDED MISSILE AND SERVO UNIT FOR IT Russian patent published in 2002 - IPC

FIELD: guided artillery ammunition. SUBSTANCE: the guided missile has a body, cruciform-arranged rotary aerodynamic control surfaces, frame with a high-pressure gas container, gas pressure regulator and four servo units communicating through gas line passages and kinematically linked with the control surface drive shafts. The missile is provided with drives for resetting of the control surfaces to the zero position relative to its longitudinal axis, kinematically linked with the control surface drive shafts. The servo units are made in the form of one-way action gas engines and arranged in pairs on the two sides relative to the axes of the drive shafts that are installed in the frame radial holes and made with journals, in whose end face grooves hinge-mounted are the control surfaces for folding in the body. Each servo unit is coupled to the control surface drive shaft by a linkage, whose one end is rigidly coupled, to the side lever of the drive shaft, and the other is hinge-mounted in the servo unit rod. A gas pressure regulator for a precise regulation is installed in the gas line between the gas container and the gas pressure regulator. The servo unit has a piston gas engine, ball lock engageable with the armature pusher of the plunger electromagnet. The gas engine is made in the form of a one- way action power cylinder and provided with a drive for resetting the piston. This drive is positioned in the cylinder on the side of the piston rod and made in the form of a lock washer secured in the cylinder by a sleeve, spring located in the sleeve and a movable washer located between the spring and the lock washer and engageable with the shoulder of the piston rod. The ball lock is made of successively installed in the power cylinder on the side of the piston working end face and secured by the electromagnet body thrust washer, inlet constrictor, guide bushing with a splined hole in which the ball is installed, and an outlet constrictor. The inlet constrictor is made in the form of a washer with a location for the ball formed by a blind axial hole communicating with the inlet radial holes of the power cylinder through a diametrical hole and through holes parallel to the axis of the inlet constrictor. The outlet constrictor is made in the form of a washer with a location for the ball formed by a through axial hole positioned in which is the pusher of the electromagnet armature, and an outlet cavity formed by the end face undercutting on the side of the electromagnet and communicating with the outlet radial holes of the power cylinder through radial holes. The inlet constrictor, guide bushing and the outlet constrictor are sealed in the power cylinder by sealing collars. The clearance between the piston non-working end face and the lock washer does not exceed the clearance between its working end face and the thrust washer. EFFECT: reduced overall dimensions and mass of the missile control module due to realization of the three-position control law. 2 cl, 5 dwg