An aircraft landing gear structure according to the present disclosure includes a retract actuator and a shrink mechanism. The retract actuator is configured to transition a strut assembly of the aircraft landing gear structure between an extended configuration and a retracted configuration via the shrink mechanism, thereby reducing the overall longitudinal length of the strut assembly. The retract actuator is also configured to retract the aircraft landing gear into a stowage area of the aircraft during flight, via a retraction mechanism. In some examples, the retraction mechanism is a walking beam that rotates about a retraction axis to retract the aircraft landing gear structure, while simultaneously actuating the shrink mechanism, such as via a drive link coupling the retraction mechanism and the shrink mechanism. In some examples, the shrink mechanism is mechanically slaved to the retraction mechanism. The shrink mechanism is a locking link assembly in some examples.
AIRCRAFT LANDING GEAR, AIRCRAFT, AND RELATED METHODS
2018-08-30
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
Aircraft landing gear shock absorber, aircraft landing gear, aircraft and related methods
European Patent Office | 2022
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