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
2024-10-03
Patent
Electronic Resource
English
IMECE2003-43315 Magnetorheological Hydraulic Actuator Driven by a Piezopump
British Library Online Contents | 2003
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