Landing gear strut damper, and landing gear with independent struts comprising same
US7426983B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 29, 2003 |
| Grant date | Sep 23, 2008 |
| Priority date | — |
| Expiry date | Jan 7, 2025 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64C2025/125
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A damper for an airplane landing gear leg comprises a main strut (11) and a rod piston (13) co-operating with the strut (11) to define a main chamber (15) and annular chamber (16) for hydraulic fluid, and presenting internally two adjacent chambers (19, 20) that are isolated from each other by a separator piston (21). The damper (10) further comprises a first secondary strut (26) telescopically Slidable on the above-mentioned rod piston (13), and a second secondary strut (37) telescopically slidable on the other end of the first secondary strut (26). The two second annular chambers (31, 40) as defined in this way are respectively connected to associated control circuits thus enabling the total length of the damper to be shortened or lengthened respectively for the purpose of causing the landing gear to contract or to be extended.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.