Attitude synchronization for model following control systems
US5169090A · kind A · utility
16Cited by
12References
12Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 28, 1991 |
| Grant date | Dec 8, 1992 |
| 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 having provisions to compensate for Euler singularities which occur when the pitch attitude of the helicopter starts to approach ninety degrees. The control system processes information from a variety of helicopter sensors in order to provide the control commands to the helicopter main and tail rotors. The present invention synchronizes a sensed attitude signal, and a desired attitude signal as the pitch attitude of the helicopter approaches ninety degrees to compensate for the Euler singularities.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.