METHOD FOR ADJUSTMENT OF FLIGHT VEHICLE CONTROL ACTUATOR AND CONTROL ACTUATOR ELECTROMAGNETIC UNIT FOR ITS REALIZATION Russian patent published in 2007 - IPC F42B15/01 F15B19/00 

FIELD: armament.

SUBSTANCE: the method consists in adjustment of the value of the working stroke of the primary member for provision of the extreme levers of the actuator output co-ordinate. The maximum levers of deflection of the actuator to either side are set, they should correspond to the excess of the maximum levers of actuator defections by 5 to 10 %. An input signal of the operating frequency is applied to the control actuator input, and at a functioning actuator an additional fine adjustment within the above limits is performed, trying to obtain the minimum amplitude of its recoil. The electromagnetic unit of the flight vehicle control actuator realized in the method has a body with two plunger electromagnets positioned on it, their armatures are coupled to one another and kinematically linked with the actuator. Each armature has a rod. The rods are turned off in the armatures with a lock-nut. The armature coupling is effected by kinematic linkage of the rods with a link rigidly fastened on the control surface shaft and positioned between the body and the plate installed on the body, the plate has two screws with lock-nuts that can be engaged with the link when turned to both sides.

EFFECT: improved quality of flight vehicle control.

3 dwg