Maneuver feel system for a rotary wing aircraft
US5213282A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Aug 28, 1991 |
| Grant date | May 25, 1993 |
| Priority date | — |
| Expiry date | Aug 28, 2011 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG05D1/0061
- WIPO fieldControl
- WIPO sectorInstruments
Abstract
A helicopter fly-by-wire flight control system (21) includes a model following control system architecture which provides the pilot with maneuvering feel. Maneuvering feel is generated by varying the gain of a rate model (52) in the control system to schedule a constant sidearm controller force per g of load factor currently on the helicopter main rotor. This gain variation works in conjunction with control logic which requires the pilot to apply a nose up pitch command during steep banked turns in order to offset a control system induced downward (pitch) bias of the aircraft nose. The control system induced bias is generated only during steep banked turns, thus allowing the pilot to fly shallow banked coordinated turns without having to apply a nose up pitch command.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.