An aircraft landing gear structure (18, 152) according to the present disclosure includes a retract actuator (32) and a shrink mechanism (22). The retract actuator (32) is configured to transition a strut assembly (100, 154) of the aircraft landing gear structure (18, 152) between an extended configuration (74) and a retracted configuration (72) via the shrink mechanism (22), thereby reducing the overall longitudinal length of the strut assembly. The retract actuator (32) 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 (22), such as via a drive link coupling the retraction mechanism (32) and the shrink mechanism (22). In some examples, the shrink mechanism (22) is mechanically slaved to the retraction mechanism. The shrink mechanism (22) is a locking link assembly in some examples.
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2019-07-22
Patent
Electronic Resource
Russian
IPC: | B64C AEROPLANES , Flugzeuge |
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