Device for damping the vibrations of a rotary-wing aircraft rotor
US4255084A · kind A · utility
40Cited by
9References
14Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 5, 1979 |
| Grant date | Mar 10, 1981 |
| Priority date | — |
| Expiry date | Feb 5, 1999 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10S416/50
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
The invention relates to a device for damping the vibrations of the rotor of a rotary-wing aircraft. This device comprises a flapping weight concentrated near the rotor axis and at least three resiliently deformable elements, such as helical springs. The deformable elements are radially biassed in directions regularly distributed around the rotor axis. The inner ends of the deformable elements directly bear on the flapping weight. Their outer ends directly bear on rigid structure elements, rigidly secured to the rotor hub, so that the biassed deformable elements apply statically balanced centripetal thrusts to the flapping weight.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.