An aircraft landing gear actuation system which uses two separate actuation forces to retract aircraft landing gear is disclosed. One of the actuation forces may be provided by an actuator, such as a hydraulic actuator. Another of these actuation forces may be provided by a pressurized fluid that is directed into the actuator through a conduit (232) that extends into a hollow interior of an actuator rod (206, 206') of the actuator. The pressurized fluid may be provided from a pressurized fluid source (230, 230') that contains a fixed volume of pressurized fluid. This pressurized fluid may exert a force on an actuator piston of the actuator or the actuator rod (206, 206'). The pressurized fluid may also be used to dampen the deployment of the landing gear.
COUNTERBALANCED RETRACT ACTUATOR FOR LANDING GEAR
AUSGEGLICHENER EINZUGAKTUATOR FÜR FAHRWERK
ACTIONNEUR DE RÉTRACTION À CONTREPOIDS POUR TRAIN D'ATTERRISSAGE
23.08.2023
Patent
Elektronische Ressource
Englisch
Europäisches Patentamt | 2025
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