Helicopter vibration control system and rotary force generator for canceling vibrations
US7448854B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 30, 2005 |
| Grant date | Nov 11, 2008 |
| Priority date | — |
| Expiry date | May 11, 2026 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64C2027/003
- WIPO fieldMechanical elements
- WIPO sectorMechanical engineering
Abstract
Helicopter rotating hub mounted vibration control system for a rotary wing hub having periodic vibrations while rotating at an operational rotation frequency. The vibration control system includes a housing attachable to the rotary wing hub and rotating with the hub at the operational frequency. The housing is centered about the rotary wing hub axis of rotation and has an electronics housing cavity subsystem and an adjacent rotor housing cavity subsystem. The rotor housing cavity contains a first coaxial ring motor with a first rotor and imbalance mass and a second coaxial ring motor with a second rotor and imbalance mass. The electronics housing cavity contains an electronics control system which receives sensor outputs and electrically controls and drives the first motor and the second motor such that the first imbalance mass and the second imbalance mass are driven at a vibration canceling rotation frequency greater than the operational rotation frequency wherein the helicopter rotary wing hub periodic vibrations are reduced.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.