Speed and collective pitch bias of helicopter longitudinal cyclic pitch
US4168045A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Feb 28, 1978 |
| Grant date | Sep 18, 1979 |
| Priority date | — |
| Expiry date | Feb 28, 1998 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG05D1/0841
- WIPO fieldControl
- WIPO sectorInstruments
Abstract
A bias actuator, such as an extensible link, in the longitudinal cyclic pitch channel of a helicopter is provided with inputs as a function of airspeed multiplied inversely with collective pitch, and as a function of the rate of change of collective pitch stick position, so as to enforce positive angle of attack and speed stability and positive static pitch trim gradient and to decouple collective pitch from the longitudinal cyclic pitch channel at cruise airspeeds, the invention compensates, inter alia, adverse control effects of tail stabilizer surfaces at cruise speeds. A pair of indicators display bias commands and actual bias responses.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.