Aircraft landing gear having a retract actuator, aircraft including the same, and related methods
US10766608B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 28, 2017 |
| Grant date | Sep 8, 2020 |
| Priority date | — |
| Expiry date | Apr 8, 2038 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64C2025/125
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An aircraft landing gear structure 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. The retraction mechanism may be 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. The shrink mechanism may be mechanically slaved to the retraction mechanism. The shrink mechanism may be a locking link assembly.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.