A landing gear system (100) for an aircraft includes a truss frame (102) pivotally connectable to a frame of the aircraft and configured to rotate about an axis; a retraction actuator (104) configured to rotate the truss frame about the axis; a first truss link (106) pivotally connected to the truss frame; a second truss link (110) pivotally connected to the first truss link; a truss locking link pivotally connected to the truss frame and to the second truss link; and an articulation actuator (128) configured to pivot the first truss link with respect to the truss frame.
ARTICULATING TRUSS CONFIGURATION FOR AIRCRAFT LANDING GEAR
GELENKTRÄGERKONFIGURATION FÜR EIN FLUGZEUGFAHRWERK
CONFIGURATION DE TREILLIS ARTICULÉ POUR TRAIN D'ATTERRISSAGE D'AÉRONEF
2023-08-23
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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