An aircraft rotor system includes a rotating pitch change shaft which rotates about an axis, a translating element disposed within the rotating pitch change shaft and movable along the axis and a pitch change bearing assembly which transfers movement of the translating element to the pitch change shaft. The pitch change bearing assembly includes a primary bearing and a secondary bearing coupled to the rotating pitch change shaft via the translating element when the primary bearing is in a first mode. A thrust shoulder is coupled to the translating element. The thrust shoulder is movable into engagement with the secondary bearing in response to failure of the primary bearing such that in a second mode, movement of the translating element is primarily transferred to the pitch change shaft via the secondary bearing.
REDUNDANT HELICOPTER PITCH CHANGE BEARING
REDUNDANTES HUBSCHRAUBERSTEIGUNGSWINKELÄNDERUNGSLAGER
PALIER REDONDANT POUR LE RÉGLAGE DU PAS DE L'HÉLICE D'UN HÉLICOPTÈRE
2022-08-03
Patent
Electronic Resource
English
Helicopter rotor wing variable-pitch rod, helicopter automatic inclinator and helicopter
European Patent Office | 2020
|