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.
AUTOPILOT CONTROL ARRANGEMENT AND METHODS
AUTOPILOTSTEUERANORDNUNG UND VERFAHREN
AGENCEMENT ET PROCÉDÉS DE COMMANDE DE PILOTE AUTOMATIQUE
2019-12-11
Patent
Electronic Resource
English
Rotorcraft advanced autopilot control arrangement and methods
European Patent Office | 2020
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