Landing gear strut damper, and landing gear with independent...

B - Operations – Transporting – 64 – C

Patent

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Details

B64C 25/58 (2006.01) B64C 25/60 (2006.01)

Patent

CA 2512623

The invention concerns an aircraft landing gear strut damper of the type comprising a main strut assembly (11) and a piston rod (13) delimiting with the strut assembly (11) a main chamber (14) and an annular chamber (15) of hydraulic fluid, and having internally two adjacent chambers (19, 20) isolated from each other by a separating piston (21). The invention is characterized in that the damper (10) further comprises a first auxiliary strut assembly (26) sliding telescopically on said piston-rod (13), as well as a second auxiliary strut assembly (37) sliding telescopically on the other end of the first auxiliary strut assembly (26). The two auxiliary annular chambers (31, 40) thus delimited are connected each to an associated control circuit thereby enabling the total length of the damper to be shortened or lengthened for respectively collapsing or extending the landing gear strut.

L~invention concerne un amortisseur de jambe de train d~atterrissage d~aéronef du type comportant un caisson principal (11) et une tige-piston (13) délimitant avec le caisson (11) une chambre principale (14) et une chambre annulaire (15) de fluide hydraulique, et présentant intérieurement deux chambres adjacentes (19, 20) isolées l~une de l~autre par un piston séparateur (21). Conformément à l~invention, l~amortisseur (10) comporte en outre un premier caisson secondaire (26) coulissant télescopiquement sur la tige-piston précipitée (13), ainsi qu~un deuxième caisson secondaire (37) coulissant télescopiquement sur l~autre extrémité du premier caisson secondaire (26). Les deux chambres secondaires annulaires (31, 40) ainsi délimitées sont reliées chacune à un circuit de commande associé permettant ainsi de raccourcir ou de rallonger la longueur totale de l~amortisseur en vue respectivement d~un affaissement ou d~un rehaussement de la jambe de train.

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