A rotor blade assembly of an aircraft. The rotor blade assembly includes a blade attachment assembly rotatable with respect to a rotor hub assembly of the aircraft about a blade fold axis, and a pitch control assembly. The pitch control assembly includes a horn mount attachable to the rotor hub assembly, and a teeter bar hingedly attached to the horn mount at an interface, the interface defining a pitch control fold axis. The pitch control assembly is foldable about the pitch control fold axis when the pitch control fold axis is aligned with the blade fold axis.
FOLDING HORN CONCEPT FOR RIGID ROTOR BLADE FOLD
2020-12-03
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
Dual blade fold bolts and inboard centrifugal bearing in a folding rotor blade assembly
European Patent Office | 2020
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