Helicopter flight stability control induced oscillation suppression
US4330829A · kind A · utility
17Cited by
2References
4Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 7, 1980 |
| Grant date | May 18, 1982 |
| Priority date | — |
| Expiry date | Jul 7, 2000 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG05D1/0858
- WIPO fieldControl
- WIPO sectorInstruments
Abstract
Oscillations in helicopter attitude sustained by the aerodynamic response of the helicopter to an automatic flight control system which is responsive to an attitude sensor, are eliminated by band reject (notch) filtering of a control system stability command to the aircraft, derived from rate of changes of such attitude at a frequency related to the aircraft attitude oscillations induced by the rate-controlled stability compensation.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.