Helicopter hub mounted vibration control and circular force generation systems for canceling vibrations
US8162606B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 7, 2009 |
| Grant date | Apr 24, 2012 |
| Priority date | — |
| Expiry date | Nov 7, 2030 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10S416/50
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A rotary wing aircraft including a vehicle vibration control system. The vehicle vibration control system includes a rotating hub mounted vibration control system, the rotating hub mounted vibration control system mounted to the rotating rotary wing hub with the rotating hub mounted vibration control system rotating with the rotating rotary wing hub. The vehicle vibration control system includes a rotary wing aircraft member sensor for outputting rotary wing aircraft member data correlating to the relative rotation of the rotating rotary wing hub member rotating relative to the nonrotating body, at least a first nonrotating body vibration sensor, the at least first nonrotating body vibration sensor outputting at least first nonrotating body vibration sensor data correlating to vibrations, at least a first nonrotating body circular force generator, the at least a first nonrotating body circular force generator fixedly coupled with the nonrotating body, and a distributed force generation data communications network link.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.