Electric-powered transfer cylinder for landing gear system
US8556209B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | May 12, 2010 |
| Grant date | Oct 15, 2013 |
| Priority date | — |
| Expiry date | Mar 20, 2032 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64C2025/008
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A shock strut for an aircraft landing gear having a retract actuator that is moveable in length to deploy or retract the landing gear, that includes a shrink strut and a transfer device. The shrink strut may be compressed in length for stowage in the fuselage. The transfer device may be in closed fluid communication with the strut shrink for transferring and receiving hydraulic fluid to and from the strut shrink. When actuated by an aircraft hydraulic or electric system independent of any motion of the retract actuator, the transfer device may drive hydraulic fluid to the strut shrink thereby compressing or shrinking the shrink strut to a partially compressed length.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.