A landing gear system for an aircraft is disclosed. In various embodiments, the system includes a truss frame pivotally connected to a frame of the aircraft and configured to rotate about an axis; a retraction actuator configured to rotate the truss frame about the axis; a first truss link pivotally connected to the truss frame; a second truss link 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 configured to pivot the first truss link with respect to the truss frame.
ARTICULATING TRUSS CONFIGURATION FOR AIRCRAFT LANDING GEAR
CONFIGURATION DE CONTREFICHE ARTICULEE POUR UN TRAIN D`ATTERRISSAGE D`AERONEF
06.08.2021
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
ARTICULATING TRUSS CONFIGURATION FOR AIRCRAFT LANDING GEAR
Europäisches Patentamt | 2023
|Articulating truss configuration for aircraft landing gear
Europäisches Patentamt | 2024
|ARTICULATING TRUSS CONFIGURATION FOR AIRCRAFT LANDING GEAR
Europäisches Patentamt | 2024
|ARTICULATING TRUSS CONFIGURATION FOR AIRCRAFT LANDING GEAR
Europäisches Patentamt | 2021
|Vertically retracting side articulating landing gear for aircraft
Europäisches Patentamt | 2015
|