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
2024-07-02
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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