One embodiment is an aircraft comprising a fuselage; a rotor system connected to the fuselage and comprising at least one rotor blade; a pilot input device; a single hydraulic servo actuator in mechanical communication with the pilot input device and the rotor system for providing force assistance in connection with the pilot input device; and a magnetorheological (MR) actuator in mechanical communication with the pilot input device and the rotor system for providing auto pilot assistance in connection with the pilot input device; wherein subsequent to detection of a failure of the single hydraulic servo actuator, the MR actuator is caused to provide force assistance to the pilot input device.
SINGLE BOOST HYDRAULIC CONTROL SYSTEM WITH MAGNETORHEOLOGICAL ACTUATOR
03.10.2024
Patent
Elektronische Ressource
Englisch
IMECE2003-43315 Magnetorheological Hydraulic Actuator Driven by a Piezopump
British Library Online Contents | 2003
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