Advanced control system for a rotor and/or a compound or rotary wing vehicle
US4025230A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | May 13, 1976 |
| Grant date | May 24, 1977 |
| Priority date | — |
| Expiry date | May 13, 1996 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG05D1/0858
- WIPO fieldControl
- WIPO sectorInstruments
Abstract
The control system includes a sensing mechanism by which a true pure signal from flapping bending activity resulting from an external load force on a rotor blade in a rotor system is generated and fed back to a gyroscope which then precesses to return a correcting feathering motion to the rotor blade through a swashplate. Such generation is developed by the sensing mechanism which comprises a cantilevered beam or spring system secured at its one end to a fixed hub arm about which the blade feathers and having its other end operatively connected to the gyroscope. The gyroscope is positioned outside of a high force blade feathering loop and is independently sized from the rotor to which it is coupled. The system also provides for pilot command input to produce a control feathering motion to a pair of blades independently of the sensing means.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.