An aircraft landing gear shock absorber strut (10) including: a casing (11) formed from titanium and including a wall portion defining a first bore (6) which is open at a first axial face of the casing; a non-titanium tubular sleeve (11a) fitted within the first bore, the tubular sleeve having a sleeve wall which defines a second bore that is open at the first axial face of the casing, the sleeve wall being thinner than the wall portion of the casing; a sliding tube (1) having a first end region defining a piston which is slidably housed within the second bore and a second end region which projects from the first axial face of the casing so that the sliding tube (1) can move axially relative to the casing between a compressed shock absorber condition and an extended shock absorber condition, the first end region of the sliding tube (1) defining a first bearing (12) having a first bearing surface arranged in sliding contact with the sleeve; and a second bearing (4) coupled to the casing within the first bore and having a second bearing surface arranged for sliding contact with the sliding tube, the second bearing being situated closer to the first axial face of the casing in comparison to the first bearing.
AIRCRAFT LANDING GEAR SHOCK ABSORBER STRUT
STOSSDÄMPFERSTREBE EINES FLUGZEUGFAHRWERKS
JAMBE D'AMORTISSEUR DE CHOCS DE TRAIN D'ATTERRISSAGE D'AVION
2018-02-07
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |