LANDING GEAR SHRINK LINK MECHANISM

A landing gear including an outer cylinder rotatably coupled to a frame of an aircraft about a trunnion axis of rotation, a shock strut assembly movably coupled to the outer cylinder so as to reciprocate along a longitudinal axis of the outer cylinder, and a shrink mechanism including a first shrink...

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Bibliographic Details
Main Authors COTTET, Justin D, VERING, Gregory J, CAMPBELL, Leanne M, KNOCK, Aaron P, ALLEY, Christopher M, DEFRANCISCI, Gabriela K, MELLOR, Mitchell
Format Patent
LanguageEnglish
Published 30.01.2020
Subjects
AEROPLANES
AIRCRAFT
AVIATION
COSMONAUTICS
HELICOPTERS
PERFORMING OPERATIONS
TRANSPORTING
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Summary:A landing gear including an outer cylinder rotatably coupled to a frame of an aircraft about a trunnion axis of rotation, a shock strut assembly movably coupled to the outer cylinder so as to reciprocate along a longitudinal axis of the outer cylinder, and a shrink mechanism including a first shrink link member pivotally coupled to the outer cylinder, a second shrink link member coupling the first shrink link member to the shock strut assembly, a crank member pivotally coupled to the outer cylinder, a drive member coupling the crank member to a walking beam (a.k.a. retract actuator beam) of a landing gear retract mechanism, and a driven member coupling the crank member to the first shrink link member.
Bibliography:Application Number: US201816049090