The present invention includes a rotorcraft drive system (200) comprising: an engine positioned at an end of a wing (202) between a mid-wing spar (204) and an aft-wing spar (208); a spindle (216) positioned forward from the engine, the spindle (216) capable of rotation between a hover and forward flight position, wherein the spindle (216) rotates about a rotation bearing (218a, 218b) on an inboard split rib (212) and an outboard tip rib (214) or in a cantilevered spindle configuration supported by the inboard tip rib; and a tilt axis driveshaft (230) connected to the engine, wherein the tilt axis driveshaft (230) connects to a plurality of gears (234, 236, 238, 240, 244, 248, 250) and shafts (232, 246) that transmit power from the engine to a proprotor gear box when the spindle (216) is in: a forward position, a hover position, and during a transition between the forward position and the hover position without loss of power to the proprotor gear box.
FIXED OUTBOARD ENGINE TILTROTOR WITH LEADING EDGE DRIVE SYSTEM AND ANGLED ROTATION SPINDLE CONFIGURATION
KIPPROTOR MIT FESTSTEHENDEM MOTOREINBAU AM FLÜGELENDE MIT IN DER FLÜGELVORDERKANTE EINGEBAUTEM ANTRIEBSSTRANG UND ABGEWINKELTER ROTATIONSSPINDELKONFIGURATION
ROTOR BASCULANT AVEC MOTEUR FIXE INSTALLÉ DANS LA PARTIE EXTÉRIEURE DE L'AILE ET COMPORTANT UN SYSTÈME D'ENTRAÎNEMENT INSTALLÉ DANS LE BORD D'ATTAQUE ET AYANT UNE BROCHE DE ROTATION ANGULAIRE
2020-06-10
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Europäisches Patentamt | 2020
|Europäisches Patentamt | 2019
|Europäisches Patentamt | 2018
|Europäisches Patentamt | 2020
|Europäisches Patentamt | 2020
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