TURBOJET ENGINE NOZZLE FLAPS SYNCHRONIZING SYSTEM Russian patent published in 2008 - IPC F02K1/12 

FIELD: aircraft industry.

SUBSTANCE: proposed synchronizing system of turbojet vectored thrust engine nozzle flaps contains subsonic flaps. Flaps are hinge-secured on body and are mechanically intercoupled by intermediate members to form closed multilink mechanism. Symmetrical projections are made on side surfaces of each flap. Holes are made on end of projections for intermediate members, lying on one axis parallel to axis of flap hinge joint. Plane passing through said axes is located at angle α to plane of flap defining angle of deflection of flap to either side from plane perpendicular to axis of nozzle which is equal to half of angle β of flap turning relative to its hinge joint. Intermediate members are made in form of V-shaped joints consisting of two cylindrical rods arranged at angle of γ relative to each other, equal to angle between two adjacent flaps.

EFFECT: increased rigidity of structure, preservation of round form of nozzle throat section at deflection of thrust vector.

6 dwg