Vibration damper, in particular for a helicopter rotor
US5979618A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Dec 4, 1996 |
| Grant date | Nov 9, 1999 |
| Priority date | — |
| Expiry date | Dec 4, 2016 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF16F13/08
- WIPO fieldMechanical elements
- WIPO sectorMechanical engineering
Abstract
The present invention relates to a vibration damper, in particular for a helicopter rotor, the damper comprising a driving element having a "main" axis and a rigid element, and including a damping assembly functionally interconnecting the driving element and the rigid element to damp vibrations in at least one direction perpendicular to said main axis. The damper includes a hydraulic damper device having first and second sets of plane laminations each having its plane perpendicular to the main axis, the laminations of the first and second sets being interleaved and narrowly spaced apart so as to present viscous damping zones each situated between one of the laminations of the first set and one of the laminations of the second set. The damper includes an elastic element having low stiffness parallel to the main axis so as to decouple compression excitation between the driving element and the rigid element.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.