B - Operations – Transporting – 64 – C
Patent
B - Operations, Transporting
64
C
B64C 11/06 (2006.01) B64C 11/36 (2006.01)
Patent
CA 2277871
A propeller (3) for aircraft has a tip-to-tip flexbeam spar (9) and torsionally stiff hollow blades (5) bonded to the spar throughout an outer portion of the blades. The spar has two end caps (33) which are separated from each other at the hub and converge in the outer portion. The blades have an inner region which is not bonded to the spar, allowing an inner portion of the spar to twist during pitch changes. A counterweight (27) is mounted to an arm (25) extending from an inner end cuff (7) of each blade. The counterweight is located out of the plane of rotation. The counterweight is also located on a side of a line opposite from the trailing edge, the line passing through the pivot axis perpendicular to the plane of rotation.
L'invention concerne un hélice pour aéronef constituée d'un longeron de type poutre de flexion monté par collage de pointe, et de pales creuses résistant aux déformations de torsion fixées au longeron sur toute la longueur d'une partie externe des pales. Le longeron comporte deux calottes terminales séparées l'une de l'autre au niveau du moyeu et convergeant dans la partie externe. Les pales présentent une partie interne non fixée au longeron, permettant la torsion d'une partie interne du longeron pendant les changements de pas. Un contrepoids est fixé à un bras qui prolonge un manchon de pied de pale interne d'extrémité de chaque pale. Le contrepoids est situé hors du plan de rotation. Il est également situé sur un côté d'une ligne opposée au bord de fuite, ladite ligne passant par l'axe de pivot perpendiculaire au plan de rotation.
Cartercopters L.l.c.
Kirby Eades Gale Baker
LandOfFree
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