A flexbeam for a helicopter bearingless main rotor assembly

Details A flexbeam for a helicopter bearingless main rotor assembly A flexbeam for a helicopter bearingless main rotor assembly

B - Operations, Transporting

64

C

B64C 27/33 (2006.01)

Patent

CA 2161529

A flexbeam (10) for a soft inplane bearingless main rotor assembly (100) has six spanwise regions: a hub attachment region (12); a first tapered region (14); a second tapered region (16); a pitch region (18); a tapered outboard transition region (20); and a main rotor blade, torque tube attachment region (22). One described embodiment of the flexbeam is fabricated from continuous unidirectional fiber-glass plies having a 0° fiber orientation, unidirectional fiberglass plies of varying lengths having a 0° fiber orientation, and graphite cross plies having 45° fiber orientation. The distributed arrangements of ply endings cause kick loads in the flexbeam to be distributed relatively uniformly into the ply buildups.

Une poutre de flexion (10) pour ensemble à rotor principal souple sans paliers (100) présente six zones en envergure: une zone de fixation du moyeu (12); une première zone conique (14); une deuxième zone conique (16); une zone de pente longitudinale (18); une zone de transition extérieure conique (20); et une pale de rotor principal ainsi qu'une zone de fixation du tube de torsion (22). Dans un mode réalisation, ladite poutre de flexion est constituée de nappes de fibres de verre continues unidirectionnelles présentant une orientation des fibres de 0 DEG , de nappes de fibres de verre unidirectionnelles de longueurs variables présentant une orientation de 0 DEG , et des nappes transversales de graphite présentant des orientations de +/- 45 DEG . De par la répartition des extrémités des nappes, les charges de battement dans la poutre de flexion sont réparties uniformément dans l'assemblage des nappes.

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