The invention refers to an aircraft an hydraulic system for an aircraft, wherein the hydraulic system comprises: a hydraulic energy generator, at least one actuator, and at least one pressure hydraulic line fluidly communicated with the hydraulic energy generator and with the actuator for applying hydraulic energy to the actuator, and at least one return hydraulic line fluidly communicated with the hydraulic energy generator and with the actuator for the return of the hydraulic energy to the hydraulic energy generator. The hydraulic system further comprises at least one double-walled pipe (1) having an outer pipe (2) and an inner pipe (3) running inside the outer pipe, and wherein the outer pipe is part of the return hydraulic line, and wherein the inner pipe is part of the pressure hydraulic line. The invention reduce the number and routing of the hydraulic lines (piping) of an aircraft.
HYDRAULIC SYSTEM FOR AN AIRCRAFT
HYDRAULIKSYSTEM FÜR EIN FLUGZEUG
SYSTÈME HYDRAULIQUE POUR AÉRONEF
2019-08-21
Patent
Elektronische Ressource
Englisch
Europäisches Patentamt | 2022
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