High speed yaw control system for rotary wing aircraft
US5178307A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Aug 28, 1991 |
| Grant date | Jan 12, 1993 |
| Priority date | — |
| Expiry date | Aug 28, 2011 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG05D1/0061
- WIPO fieldControl
- WIPO sectorInstruments
Abstract
A helicopter flight control system includes a model following control system architecture to control helicopter response about the yaw axis. The control system processes information from a variety of helicopter sensors in order to provide an output command signal to the tail rotor. Yaw control is accomplished by applying a force on a sidearm controller which provides a yaw axis command signal that is used to schedule a desired yaw rate of change. The lateral acceleration and airspeed signals are used to compute a synthesized yaw rate signal which is compared against the desired yaw rate of change, thus allowing the pilot to control lateral acceleration when he applies force on the sidearm controller.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.