Landing gear actuation control system

Details Landing gear actuation control system Landing gear actuation control system

B - Operations, Transporting

64

C

B64C 25/22 (2006.01)

Patent

CA 2698868

A hydraulic control system for an aircraft landing gear system comprises a hydraulic pressure source connected to a hydraulic fluid pressure transmission line (5), and at least one hydraulic actuator (8,9,10,11,12,13) for extending and/or retracting a landing gear, wherein first and second valves (33,34) are provided in series along the hydraulic fluid pressure transmission line (5), the first (33) and second (34) valves being adjustable to control the hydraulic pressure supplied to the at least one hydraulic actuator (8,9,10,11,12,13). The control system also controls uplock actuators (14,15,16).

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