Active vibration control system for helicopter with improved actustor placement
US6467723B1 · kind B1 · utility
25Cited by
28References
16Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 10, 2000 |
| Grant date | Oct 22, 2002 |
| Priority date | — |
| Expiry date | Oct 10, 2020 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64C2027/004
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An aircraft has a fuselage that defines an interior cabin and an exterior; a first housing located along one side of the fuselage exterior; a second housing located along the second side of the fuselage exterior; and an active vibration control system for limiting fuselage vibration, the vibration control system comprising a plurality of sensors located in the cabin; a controller in signal receiving relation with the sensor means; first actuator means located in the first housing and second actuator means located in the second housing and wherein the actuator means are in signal receiving relation with the controller.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.