GB781892A - Improvements in or relating to landing gear for aircraft - Google Patents

Abstract

781,892. Aircraft undercarriages. SOC. D'INVENTIONS AERONAUTIQUES ET MECANIQUES, S.I.A.M. July 29, 1955 [Sept. 28, 1954], No. 22050/55. Class 4. In an aircraft having a thin wing 1 each land wheel 4 is mounted on its undercarriage leg 5 in a manner which enables it to be housed within the fuselage 2 in an inclined position adjacent a power plant 3. The leg 5 is mounted on the wing 1 by a pivot 6 and it is retracted sideways by a jack 33 connected to the fuselage at 34 and to the leg at 37. The lower end of the leg carries a fitting 8 pivoted thereto on an axis II and having an extension pivot 12 on an axis III for a fitting 9 which has stops 11 co-operating with the member 8 to limit its rotation about axis III. The fitting 9 carries a wheel axle 10 on axis IV and an oppositely directed extension 16 on axis V forming a mounting for a shaft having levers 18 and 22 at its opposite ends. Lever 22 is connected to a spring loaded locking pin 21 which co-operates with a recess 24 in fitting 8 to prevent relative rotation of fitting 9 and lever 18 is connected at 20 to a universal joint on the lower end of a telescopic tie rod 39, said rod having a universal connection 38 at its upper end for attachment to the wing on an axis IX located outboard of the pivot 6. The fitting 9 carries also a lug 30 for the attachment of the lower end of a shock absorber 28. During initial retraction of the leg the tie-rod 39 extends to its limit and subsequent retracting movement first causes levers 18 and 22 to rock about axis V thereby freeing the pin 21 from recess 24 and secondly causes fitting 9 to rock about pivot 12 up to the limit set by stops 11 when the wheel axle 10 lies on axis IVa with the leg and wheel in its fully retracted position. A further embodiment, Figs. 10 and 11 (not shown) concerns a similar arrangement with the shock absorber housed co-axially withiri the main leg.