Flexbeam for a helicopter bearingless main rotor assembly

Fluid reaction surfaces (i.e. – impellers) – Articulated – resiliently mounted or self-shifting impeller... – Nonmetallic resilient mounting

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Details

416230, B64C 2733

Patent

active

053724798

ABSTRACT:
A flexbeam for a soft inplane bearingless main rotor assembly has six spanwise regions: a hub attachment region; a first tapered region; a second tapered region; a pitch region; a tapered outboard transition region; and a main rotor blade, torque tube attachment region. One described embodiment of the flexbeam is fabricated from continuous unidirectional fiberglass plies having a 0.degree. fiber orientation, unidirectional fiberglass plies of varying lengths having a 0.degree. fiber orientation, and graphite cross plies having .+-.45.degree. fiber orientations. The pitch region is formed solely by the continuous fiberglass plies which define a rectangular cross section therefor. The second tapered region is formed solely by the continuous fiberglass plies and the fiberglass plies of varying lengths. The ends of the fiberglass plies terminate in a distributed arrangement in the second tapered region to define the taper thereof. The remaining regions of the flexbeam are formed by interleaved combinations of the continuous fiberglass plies, the fiberglass plies of varying length, and the graphite cross plies of varying length. Ends of the graphite cross plies terminate in a distributed arrangement in the first tapered region to partially define the taper thereof. Ends of the fiberglass plies and the graphite cross plies terminate in a distributed arrangement in the tapered outboard transition region to define the taper thereof. The distributed arrangements of ply endings cause kick loads in the flexbeam to be distributed relatively uniformly into the ply buildups.

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