Rotorcraft autopilot and methods
US11591078B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 27, 2021 |
| Grant date | Feb 28, 2023 |
| Priority date | — |
| Expiry date | Jan 27, 2041 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/40
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.