Abstract: The invention provides a telescopic member that includes a cylinder in which a rod carrying a piston is mounted to slide telescopically, the telescopic member including internal abutment mechanisms that are overridable over a predetermined force when the rod comes into abutment inside the cylinder in the shortening direction. The internal abutment mechanisms include an abutment piece extending in an open bore within the rod and projecting therefrom, the abutment piece being held to the rod via a pin.

Abstract: The invention relates to a shock absorber for an aircraft undercarriage, the shock absorber comprising a main cylinder in which a rod is mounted to slide telescopically, the shock absorber having one or more pneumatic chambers filled with gas, a supply of hydraulic fluid, and throttle means for throttling the hydraulic fluid such that when the shock absorber is shortened, the gas in the pneumatic chamber(s) is compressed and the hydraulic fluid is throttled, in which the pneumatic chamber(s) is/are fully contained in one or more auxiliary cylinders external to the main cylinder, and in each of which a sealed piston is slidably mounted to separate a pneumatic chamber contained in said external auxiliary cylinder from a fluid chamber in fluid flow communication with the main cylinder. According to the invention, the throttle means are disposed at the inlet of a fluid flow connection between the main cylinder and the auxiliary cylinder(s).

Abstract: The invention relates to a telescopic shock absorber for an aircraft undercarriage, the shock absorber comprising a strut (1) in which a rod (2) is mounted to slide, the shock absorber including controlled retraction means (41 . . . 43) for retracting the rod into the strut to a retracted position. The shock absorber includes positive retention means (27, 29) for retaining the rod in the strut and adapted to retain the rod in the retracted position when the rod is moved thereto by the retraction means, the positive retention means being arranged, at least in the event of a severe landing of the aircraft, to allow the rod to be pushed into the strut beyond the retracted position.