HYDRAULIC ACTUATION SYSTEM

Abstract: a hydraulic actuation system for an aircraft. the system comprises: a hydraulic actuator comprising: a housing to accommodate hydraulic fluid; an extension chamber and a retraction chamber each defined by the housing; and a bypass line in fluid communication with the extension chamber and the retraction chamber, the bypass line comprising a flow restrictor and a bypass valve, the flow restrictor configured to restrict a rate of fluid flow through the bypass line; and a controller configured to receive a signal indicative that the aircraft is in a take-off or a landing procedure, to determine that the aircraft is performing the take-off or the landing procedure based on the signal, and to perform an operation to cause the bypass valve to open to allow the hydraulic fluid to flow through the bypass line only when the controller determines that the aircraft is performing the take-off or the landing procedure.

Inventor(s): Sean KERR

CPC Classification: B64C25/22 (fluid)

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