Retraction of a landing gear assembly (4, fig 3) on an aircraft (1, fig 3) is actuated by a hydraulic actuator 12. The actuator 12 includes a piston 28 that travels within a cylinder 26 along a stroke length between a first position corresponding to the landing gear assembly when extended and a second position corresponding to the landing gear assembly when retracted. Movement of the piston 28 along its stroke length is snubbed at different levels, for example by use of a snubbing spear 40 having one or more fluid channels 46, 48 formed herein. Differential snubbing is thus provided, which enables the landing gear to retract faster.
Aircraft landing gear system
2021-03-24
Patent
Elektronische Ressource
Englisch
Landing gear of aircraft and aircraft comprising landing gear
Europäisches Patentamt | 2021
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