Abstract: The present invention relates to shock absorber-actuators.The shock absorber-actuator is characterized essentially by the fact that it comprises at least one cylinder (101), a hollow rod (102) sliding in the cylinder (101), a gas chamber (153) delimited by a separating piston (141), and means (140, 156, 154) for positioning this piston between two stops (145, 147).The shock absorber-actuator finds a particularly advantageous application in aircraft and in particular helicopters.

Abstract: This invention relates to hydraulic pumps. The pump includes essentially a casing (1), a barrel (3) capable of rotating on a slide face (2), the barrel comprising a plurality of pistons (16, 17) sliding in a reciprocating manner in cylinders (9, 10) provided in the casing, the pump being characterized essentially by the fact that it comprises structures (59, 54, 50, 52, 53) for sequentially applying the pressure prevailing in the cylinder on a given portion between a bearing block (26) made in the casing (1) and the part of said barrel (3) cooperating with the bearing block (26). The pump finds a particularly advantageous application in the area of those which must rotate at very high speed, for example in aeronautics.

Abstract: The undercarriage comprises: a leg (1) pivotally mounted about a first pivot axis (14) which is fixed relative to a rigid structure of the aircraft; a main side-brace (30) comprising at least two articulated levers (31 and 32) having first ends pivotally connected to each other about a fourth pivot axis (33), having respective other ends pivotally mounted about a second pivot axis (37) which is fixed relative to the rigid structure, and pivotally mounted about a third pivot axis (36) which is fixed relative to the leg; and a drive (40 to 48) for causing the levers to pivot relative to each other. The first, second, third, and fourth pivot axes are parallel to each other.

Abstract: The present invention relates to landing gears retractable between two positions.The landing gear includes essentially a lever (14 ) mounted rotatably around an axis (5), a rocker beam (7) mounted rotatably on the same axis (5), a strut (21) including two links (22,23) pivoting in relation to each other, the strut being connected to the lever, a shock absorber (18) fixed respectively on the lever (14) and the rocker beam (7), and an actuating cylinder (32) for applying a pivoting force to the lever (14). This landing gear finds a particularly advantageous application in aircraft of the commuter type.CROSS REFERENCE TO RELATED APPLICATIONThe present application relates to application Ser. No. 354,010 filed on Mar. 2, 1982, and entitled "FUSELAGE LANDING GEAR WITH TANDEM WHEELS" by inventors Andre Turiot and Michel Derrien, our reference 4126.

Abstract: This invention relates to landing gears. The described landing gear is characterized essentially by the fact that it comprises a leg (3) at one end of which is fixed a wheel (14 ) for rolling around a pivoting pin (11), a shock absorber (15) of which one end (22) is connected to leg (3), a strut (24) whose end is connected to leg (3) and links (39, 37, 41) connecting the end of strut (24) to the pivoting pin (11) so as to cause the wheel to pivot when the landing gear is retracted. This landing gear finds an advantageous application as a fuselage landing gear of the tripod type.

Abstract: The landing gear for aircraft comprises at least two rocker beams respectively carrying wheels, the rocker beams being connected rigidly and respectively to two points of the rigid structure of the aircraft, each rocker beam being connected to two other rigid points of the aircraft structure by an assembly composed of a lever and a shock absorber mounted rotatably on each other, and a connecting rod of constant length connecting two levers and an actuating cylinder to rotate at least one of the two said levers. The landing gear finds a particularly advantageous application as a fuselage landing gear with tandem mounted wheels.

Abstract: An oleopneumatic suspension with variable throttle orifices, particularly for aircraft landing gear comprising a rod (1) enclosing a pneumatic spring (2) and being fixed with respect to a piston (4) sliding in a cylinder (3), two valves (6) and (7) with permanent throttle orifices, the valve (6), which is of greater cross-section, throttling in the compression phase and the valve (7), which is of lesser cross-section, throttling in the extension phase, the suspension comprising in addition a throttle device, the section of whose orifice varies in dependence on the position and the direction of displacement of the piston (4) in the cylinder (3) so that over a given distance around a predetermined equilibrium position the orifices ensuring throttling in the compression and extension phases are of cross-sections respectively greater than the corresponding orifices over the remainder of the distance covered by the piston (4) in the cylinder (3).

Abstract: The present invention relates to landing gears. The landing gear includes essentially two legs (1, 2) comprising respecitvely two arms (10, 28) and two rocker beams (3, 24), a bar (21) forming with the two arms (10, 28) a deformable parallelogram, a strut (37) consisting of two levers (23, 38) placed on a diagonal of the parallelogram, two locking links (50, 51) cooperating with the strut (37), these two rotatably mounted links being rotated by an actuator (70) and a spring (60). The landing gear finds its application in commuter aircraft fitted with tandem type landing gears.

Abstract: The invention concerns a landing gear. The landing gear is characterized essentially by the fact that it comprises at least one shock absorber (15), this shock absorber being mounted in the leg (1) and casing (2) assembly by means of two convex surfaces (22, 31) made on the cylinder (16) of the shock absorber (15) and cooperating with two concave surfaces (25, 32) integral respectively with the leg (1) and the casing (2). This landing gear finds an application as a nose gear of the rocker-beam type.

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 main undercarriage train for an aircraft which is retractable substantially laterally, the train comprising two undercarriages which comprise identical legs each having a plane of symmetry which passes through its pivot mounting axis which is inclined relative to the plane of symmetry of the aircraft.

Abstract: The invention relates to a device for testing vehicle wheel rims. The device comprises means of positioning and holding the rim, means for applying loads on the rim, and is characterized by the fact that the said means for applying loads on the rim comprise, on the one hand, a set of controllable jacks whose heads are able to cooperate with the rim, and on the other hand, a control member to actuate the jacks successively according to a predetermined cycle. The device is particularly useful for testing the rims of aircraft wheels.

Abstract: An automatic braking method and apparatus for a vehicle, having particular applicability to aircraft, wherein a program deceleration signal is generated according to a preselected deceleration. A signal which is a function of the actual speed of the vehicle is compared with the program signal, and a difference signal is produced. The difference signal controls the actuation of the braking system of the vehicle to result in braking thereof in accordance with the preselected deceleration.

Abstract: The present invention relates to a fuse for a wheel equipped with a pneumatic tire.The fuse is constituted in the form of a screw (1) whereof the head (7) is traversed by an evacuation duct (3) receiving a check valve (8) obturating this duct (3); the fuse being characterized by the fact that it comprises a retainer (17), a part of which is embedded in the head, and another part cooperates with the check valve to hold it.

Abstract: An aircraft landing gear including a leg member supporting at least one wheel, the leg having a first point of attachment around a first axis of rotation about a first point on the aircraft, a strut including a rod and a lever pivotally mounted on one another around a third axis, the rod having a second axis of rotation on a second point of attachment to the aircraft and the lever being pivoted about a fourth axis on the leg, and an operating jack applying at least one rotational torque to the strut and the leg wherein one end of the jack is connected to a third point on the leg and the other end of the jack is connected to a fourth point on the strut, the third and fourth points being located substantially near the first and second points of attachment.

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: A reversible aero-hydraulic generator capable of operating as a turbo-pump or as a motor-compressor, and a heat energy recovery installation including such a generator.The generator comprises a positive displacement pump (5) and an axial turbine (6) tandem connected and coupled by their respective shafts (23 and 11) so that one can drive the other directly and disposed within a single sleeve (1) having end connecting flanges (3 and 4), whereby the sleeve can be directly inserted within a conduit for a first fluid, in the gaseous or vapor phase state, so that the first fluid can pass axially through the sleeve (1), and inlet and outlet conduits (31 and 32) for a second fluid in the liquid or vapor phase, for the pump (5), the conduits (31, 32) passing through the sleeve (1). A heat recovery installation can comprise such a generator for the recovery of heat energy from a drier for printing ink with the pump output used to drive a hydraulic motor to assist in driving the rollers of a printing press.

Abstract: A main landing gear with swing-bar and lateral lifting for aircraft. Two undercarriages are provided which are positioned symmetrically on either side of the longitudinal plane of symmetry of the aircraft, each one having a leg 1 articulated around a lifting axis 5, and a swing bar 16 around a transverse axis 18. The swing bar 16 carries a wheel 21 pivotally mounted around an axis of rotation 19. The maneuvering of the undercarriage and the bracing thereof are insured by a bracing jack 13, and the deflections of swing-bar 16 are damped by a shock absorber 10. The leg 1 of the undercarriage has a first plane of symmetry (X,X) perpendicular to the lifting axis 5 and the longitudinal plane of symmetry of the aircraft and the swing-bar 16 has a second plane of symmetry (Y,Y) defined by the transverse axis 18 of the axis of rotation 19.

Abstract: A hydraulic braking device for a load subjected to shocks and vibrations for the stabilization of loads in thermal or nuclear generating stations.The braking device has a cylinder 1 in which there slides the piston 4 of a rod 7 bearing two flap valves 18 and 19 to brake the passage at high speed of hydraulic fluid from one chamber 15 or 16 to the other. These valves communicate with a reservoir 17, pressurized by springs 31 to 34 and accumulate the expansions of the fluid. A secondary rod 29 which has displacements with respect to rod 7 which are reduced relative to the displacement of piston of reservoir 27 with respect to this rod 7 serves as a leak indicator.Application to the stabilization of loads such as high-temperature steam conduits in thermal or nuclear generating stations.

Abstract: A storage element for use in the recovery of heat originating from the cooling of radioactive wastes including a first element for the storage of radioactive waste having a first closed shell including the wastes, and disposed within a second closed shell, both shells being of generally spherical shape, the second shell bristling with externally projecting radial points or spines, the value between the two shells being filled with a non-contaminatable fluid, promoting the transfer of heat originating from the cooling of the wastes from the first towards the second shell, of which the points or spines serve as radiators in relation to the external medium.