Damping device and aircraft rotor system incorporating it
US8177202B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 5, 2009 |
| Grant date | May 15, 2012 |
| Priority date | — |
| Expiry date | Sep 30, 2030 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF16F13/18
- WIPO fieldMechanical elements
- WIPO sectorMechanical engineering
Abstract
The damping device is intended to form a drag-mode damper for a helicopter blade, and is incorporated in an aircraft rotor system. This damping device comprises: an external frame intended to be coupled to a first rotating element, and a radially internal element mounted coaxially to the frame and intended to be coupled to a second rotating element; at least one elastomer damper of annular cross section mounted fixedly to the frame and to the internal element; and a working chamber bounded by the frame and by the damper and communicating with a compensation chamber bounded by a highly deformable flexible member mounted coaxially to the internal element. The working chamber is formed at a first end of the device and communicates with the compensation chamber via a porous structure surmounting an end opening of the flexible member, which member is mounted in the internal element.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.