A stability and control augmentation system (SCAS) actuator is operable for actuating a flight control surface of an aircraft. The SCAS actuator includes an actuator housing having a first aperture, a second aperture and a hydraulic chamber therebetween. A piston extends through the actuator housing. Fluid inlets are in fluid communication with regions of the hydraulic chamber. A first end portion of the piston is arranged to slide through the first aperture without a seal between the first end portion and the first aperture. A second end portion of the piston is arranged to slide through the second aperture without a seal between the second end portion and the second aperture. An intermediate portion of the piston is arranged to slide in the hydraulic chamber without a seal between the intermediate portion and the hydraulic chamber.
STABILITY AND CONTROL AUGMENTATION SYSTEM ACTUATOR
15.06.2023
Patent
Elektronische Ressource
Englisch
SERVO-ACTUATOR ARCHITECTURE WITH ELECTROMECHANICAL-STABILITY AND CONTROL AUGMENTATION SYSTEM
Europäisches Patentamt | 2023
|Servo-actuator architecture with electromechanical-stability and control augmentation system
Europäisches Patentamt | 2023
|SERVO-ACTUATOR ARCHITECTURE WITH ELECTROMECHANICAL-STABILITY AND CONTROL AUGMENTATION SYSTEM
Europäisches Patentamt | 2021
|