FIELD: engines and pumps.
SUBSTANCE: invention relates to turbojet engine outlet devices, particularly to nozzles that allow varying engine thrust vector and improving aircraft take-off-and-landing performances and maneuverability. Proposed aircraft turbojet engine outlet device comprises nozzle, engine nacelles, outlet part arranged behind the nozzle and pylons rigidly linked with the nozzle and engine immobile housing. Proposed outlet part represents actuated flaps that can vary gas dynamic profile of the outlet device and be arranged at an angle to nozzle axis. Aforesaid flaps are fitted on hinged links to allows the former move to vary aerodynamic profile of outlet device. Hinge links arranged on outlet part flaps and closer to outlet device outlet cross section feature grater length than that of hinge links arranged further from aforesaid cross section. Engine nacelles outer housing, ahead of the outlet part, accommodate additional actuated movable flaps that move in/out over the engine nacelles outer surface, for example on rolls with guides.
EFFECT: expanded engine performances, improved aircraft take-off-and-landing characteristics.
4 dwg
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