Damping device for a helicopter rotor blade
US4360337A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Aug 4, 1980 |
| Grant date | Nov 23, 1982 |
| Priority date | — |
| Expiry date | Aug 4, 2000 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64C27/327
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
The wing blades of a helicopter rotor each are connected to the rotor hub a connection, e.g. a spar being .fwdarw..rarw. including a hinge which is at least fictitious to permit lead-lag movements of the blades <yielding relative to torsion to permit the blade angle adjustment>. A rod, which is stiff in the lead-lag direction and yielding against torsion, is connected in parallel to the connection between the blade root and the rotor hub. One connection of the rod is rigid, for example the connection to the blade root. The other connection of the rod is elastically yielding substantially only in the plane of the rotor whereby a substantial damping of blade movements in the lead-lag direction is accomplished.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.