An aircraft landing gear assembly (50) comprising: a first structural member (52); a second structural member (54) pivotally coupled to the first structural member at an apex pivot point so as to be movable between a first angular condition and a second angular condition; a down-lock spring having a first end region pivotally coupled to a mounting structure and being arranged under tension to bias the first and second structural members to assume the first angular condition; and a linkage assembly, the linkage assembly comprising: an arm member (58) pivotally coupled to one of the first and second structural members at an arm pivot point, the arm having an first end region pivotally coupled to a second end region of the down-lock spring; and a control link (56) pivotally coupled to one of the first and second structural members at a first control link pivot point and pivotally coupled to the arm member at a second control link pivot point the such that, as the first and second structural members move relative to one another from the first angular condition towards the second angular condition, the first control link pivot point moves over centre, though an axis or plane bisecting the apex pivot point and the second control link pivot point.
AIRCRAFT LANDING GEAR ASSEMBLY
FLUGZEUGFAHRWERKSBAUGRUPPE
ENSEMBLE TRAIN D'ATTERRISSAGE D'AÉRONEF
2023-03-01
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |