Abstract: The invention relates to a shock absorber for a landing gear leg, the shock absorber being of the type comprising a cylinder and a sliding rod, and including a disk that delimits a lower hydraulic fluid chamber which communicates via a diaphragm with an upper hydraulic fluid chamber adjacent to a pressurized gas chamber formed in the top portion of the cylinder. According to the invention, the sliding rod 102 is implemented in telescopic form, having an outer rod 131 and an inner rod 132 which bears directly against an intermediate partition 112 constituting the above-mentioned disk when the shock absorber is relaxed or under static load. The shock absorber also includes a linear actuator 150.1 received in the inner rod 132, and which, when triggered, serves to extend the landing gear providing the airplane is stationary or is moving slowly on the ground. Two scissors linkages 124 and 127 are also provided for conveying structural twisting forces.

Abstract: The locking device of the invention comprises a locking device mounted to pivot relative to a beam and having ends associated with an axle to lock the axle in a first position of the locking device and to release the axle by the locking device pivoting towards a second position, together with a control actuator and a set of two links for controlling the position of the locking device.

Abstract: A device for steering the wheels fitted to the bottom end of the leg (1) of the nose landing gear of an aircraft, the wheels being steered about the axis of the leg, the leg (1) comprising a strut (2) hinged to the structure of the aircraft, a tube (4) mounted to rotate inside the strut (2) and projecting outside the strut, a rod (5) slidably mounted inside the tube (4) and carrying the wheels at its free end, and a scissor linkage (6) for constraining the tube (4) and the rod (5) to rotate together.

Abstract: Landing gear comprising a pivoting strut (1) receiving the rod of a shock absorber (2) which projects downwardly from the strut and is movable in an axial direction (3) relative thereto, a rocking beam (4) mounted to tilt at the bottom end of the shock absorber rod (2) and supporting leading and trailing wheel sets (6), a torque linkage comprising a top branch (7) and a bottom branch (8) which are hinged to each other, the top branch (7) being hinged to the strut (1) and the bottom branch (8) being hinged to the rocking beam, and locking means (9, 15) for limiting a downwards pivot movement of the top branch (7) of the torque linkage while the shock absorber rod (2) is not fully extended.

Abstract: The present invention relates to shock absorbers including a rod slidable in a cylinder and a piston for determining at least two variable volume chambers, one of the two chambers including a first resilient member at a first pressure, and the other chamber containing a second resilient member at a second determined pressure, the second resilient member being suitable for being displaced in translation en bloc by an actuator chamber.

Abstract: The present invention is concerned with tilting-beam undercarriages.The undercarriage is characterized in that the shock absorber means (7) comprise a hollow cylinder (11) entered by a plunger stem (14) at its first end (12) and by a piston (18) at its second end, while the hollow cylinder (11) has a hinge member (22) onto which the beam (8) is hinged at a point C differing from the center of it and the piston (18) is connected to the beam at a point D differing from the point of hinge C.

Abstract: Each rocking arm (9, 10) hinged to a shock absorber (7, 8) has a lateral extension (13, 14) extending at an acute angle a to one side of the shock absorber (7, 8). This extension (13, 14) is connected by a telescopic strut (15, 16) to the opposite end (7A, 8A) of the same shock absorber (7, 8) in order to shorten said shock absorber when the landing gear is raised, thereby reducing the space it occupies in the raised position.

Abstract: The landing gear comprises: a rod including nested first and second tubes between which there slides a cylinder whose outer end supports a running gear; a strut surrounding the top of the rod and including a steering mechanism cooperating with a rotary tube disposed between the rod and the strut; and a fluid actuator constituted by at least one chamber between the strut and the rod and having a feed inlet only. The landing gear is particularly applicable to helicopters that are required to "kneel down" camel fashion, e.g., for storage in the hold of an aircraft carrier or a cargo plane.

Abstract: On a shaft (2) which carries a wheel there are mounted: firstly a toothed sector (3) which meshes with a rack (4) on a piston rod (5) which is a part of a double-acting hydraulic actuator (8); and secondly a cam (12) which acts on two rocking levers (13, 14) to apply a bolt (13B, 14B) against a stop face (10A, 10B) of the rod (5) when, by directly swivelling the wheel, the toothed sector (3) is disengaged from the rack (4).

Abstract: The low portion (9) of a landing gear strut (3) carrying running means such as a wheel (8) is capable of swivelling together with the running means relative to the strut. A system of cranks (17) receives the necessary force for swivelling the wheel during retraction and extension of the landing gear from a rod (13) which is fixed to the aircraft structure (2) at a point different from the point at which the strut (3) is fixed. The rod (13) is of variable length (piston and cylinder arrangement 31), and the crank system has a stop (33) against excessive swivelling. The arrangement is such that swivelling is restricted to a selected portion of the landing gear's travel, e.g. to ensure that the wheel enters the aircraft body at a particular degree of swivel.

Abstract: The present invention relates to landing gear. The landing gear has a strut (2) having one end pivotally mounted about a first axis (4) suitable for connection to the structure (1) of an aircraft. A lower portion (6) for supporting running gear (10) is pivotally mounted relative to said strut (2) to pivot about a second axis. A collapsible side brace (20) has one end suitable for connection to a first point (27) of the aircraft structure (1) for pivoting about a third axis (29) and a fourth axis (30) providing rotation with two degrees of freedom about said third and fourth axes respectively. The third axis (29) passes through said first point (27) being situated on a line which is not colinear with the first axis but which intersects said first axis at a second point (40). A pivot pin (33) is rotatable about a fifth axis (35), the fifth axis not being colinear with said first (4), third (29) and fourth (30) axes and being situated on a line which passes through said second point (40).

Abstract: The landing gear comprises a shock absorber (4) having a rod (6) slidable in a cylinder (6), a wheel (12) linked to the cylinder, a guide sheath (14) surrounding the shock absorber (4), releasably engageable means (17) for fixing the cylinder at least in rotation relative to the guide sheath (14), and a strut (21) surrounding the sheath. When the strut is retracted under the control of an actuator (42) a rod (80) draws the sheath (14) into the strut (21) thereby compacting the landing gear lengthwise, at the same time a helical groove (38) cooperates with a groove follower (40) to turn the sheath, and hence the shock absorber cylinder (6) and the nose wheel (12) so that the wheel lies flat inside the aircraft when retracted.

Abstract: A shock absorber including a cylinder (501), a rod (502) slidably mounted in the cylinder, and a piston (506) fixed to the rod and slidable inside the cylinder. The piston divides the cylinder into two oil-filled chambers (508, 514) and there is a third chamber (518) in the rod and including air to act as a hydraulic spring. Shocks tend to move the piston along the rod away from its equilibrium position therein, and the hydraulic spring tends to return the piston to its equilibrium position. Damping is provided by variable aperture channels between the first chamber (508) and the other two chambers (514 and 518). The channels comprise orifices (509 and 510) in a cylindrical wall of the first chamber (508) which overlap orifices in a movable cylindrical valve plate (527). A control shaft (540) leading out along the axis of the shock absorber serves to rotate the valve plate and to move it in axial translation.

Abstract: The shock absorber is characterized by the fact that it comprises a rod (1) sliding in a cylinder (2) through a piston (3) to determine at least two variable-volume chambers (4,6), ports (40,41) for placing the two chambers in communication, one of the two chambers (4) comprising first elastic fluid (44) at a first given pressure, the other chamber (6) comprising second elastic fluid (10) at a second given pressure, controllable according to at least one parameter, corresponding to a force to be absorbed.

Abstract: Devices for detecting the displacement of an element relative to a referential. A first end of a recopying bar is connected with the element and the other end is capable of cooperating with a mechanism for determining the displacement of this second end relative to the referential. The device is particularly useful for determining the deformation on landing gears of aerodynes.

Abstract: A bracing jack comprising a cylinder and a jack bar slidable in the cylinder from a bar extended position to a bar retracted position, the jack having an internal locking mechanism including a hydraulic and a mechanical actuator for unlocking under load.

Abstract: Shock absorbers and shock absorber jacks each of which comprises a shaft containing a low-pressure chamber and sliding in a first chamber of a first cylinder which is separated from another or second chamber which contains a high-pressure chamber, by means of a partition which is traversed by a grooved shaft borne by a separator piston in the other chamber and guided in a sleeve borne by the partition. In the event of the penetration of the shaft into the first cylinder at a rate of very much higher than normal, then the two grooves in the shaft communicate with each other and permit the flow of oil from the first chamber towards the second chamber and towards the low-pressure chamber because of a radial passage through the sleeve near the partition.

Abstract: A shock-absorber of the piston-and-cylinder kind for use in the landing gear of an aircraft and comprising a cylinder, a piston-rod and a shock-absorbing rod which encloses a chamber for compressed gas and is provided with a valve having a throttling orifice, in which the shock-absorbing rod is mounted to slide, in a fluid-tight manner, in a first chamber, filled with hydraulic fluid, of the cylinder or of the piston-rod, to form a oleopneumatic shock-absorber; the piston-rod is mounted to slide, in a fluid-tight manner, in the cylinder and is solidly connected to a piston-head which, with the cylinder, defines a descent chamber to control lowering of the landing gear when hydraulic fluid is admitted to the descent chamber; the shock-absorber also comprises a lifting piston to load the shock-absorber and mounted to slide within a second chamber of the cylinder or of the piston-rod, so defining a lifting chamber to control lifting of the landing gear when hydraulic fluid is admitted to the lifting chamber thro

Abstract: An oleo-pneumatic damper comprises a hollow rod slidable within a cylinder, and a low-pressure gas chamber defined within the cylinder adjacent to a first variable volume of hydraulic fluid, which volume is essentially provided in the hollow rod. A second variable volume of hydraulic fluid in the rod is separated from the first fluid volume by a valve device, and a separating piston separates the second fluid volume from a high-pressure gas chamber, also in the hollow rod. A spring in the first fluid volume urges the hollow rod into the cylinder, thereby to form an anti-threshold spring to reduce the threshold or minimum loading on the damper, at which the damper will commence a compression stroke movement for damping purposes.