Messier-hispano-bugatti

Messier Hispano

Messier-hispano, S. A.

Messier-hispano-bugatti (sa)

S.e.d.i.c.

Messer-hispano

Messier-hispaono-bugatti (s.a.)

Jean Masclet

Andre Turiot

Jacques Veaux

Roger Papay

Marcel Schott

Claude Marcheron

The nose wheel landing gear has the wheel (23) coupled to the rest of the landing gear by a deformable parallelogram (20, 37, 33, 13) which is located to one side of the wheel (23), the wheel lever (20) which supports the wheel is only slightly longer than the wheel radius. This arrangement enables the landing gear to be shortened when retracted without the wheel itself being offset sideways, thereby occupying less space overall.

Wheel lever landing gear

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.

Dual chamber shock absorbers for aircrafts and the like

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). While primarily for use in connection with landing gear or support bogies of aircraft, the suspension is also suitable for land vehicles or for testing.

Oleopneumatic suspension with variable throttle orifices, especially for

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.

Device for the detection of the displacement of at least one point

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. Each undercarriage further comprises a bush capable of being retained in either of two positions in a bore of the undercarriage leg or a wheel-carrying member and the internal bore of which, through which internal bore passes a shaft on which an assembly for alignment of the wheels are pivoted, has its axis off-set with respect to the axis of the bore in which the bush is retained, and compensates for the angular displacement between the plane of symmetry of the aircraft and the inclined axis of the one or the other undercarriage leg, depending on whether the bush is retained in a first of the two positions or in a second of the two positions which is obtained from the first of the two positions by rotating the bush through 180.degree. about the axis of its bore, whereby the left and right undercarriages are totally interchangeable.

Main undercarriage train for an aircraft

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.

Automatic braking method and apparatus

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.

Fuse device for a wheel equipped with a pneumatic tire

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.

Retractable running gear for vehicle

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.

Operating and bracing jack having an internal locking mechanism

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.

Hydraulic braking device for a load subjected to shocks and vibrations

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.

Landing gear with swing-bar and lateral lifting for aircraft

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.

Shock absorbers and shock absorber struts, notably for aerodyne landing

A mechanical-hydraulic damper for a load which is subject to shocks and vibrations, comprising a co-operating pair of elements, the first of the pair of elements being mounted in a body for relative axial movement in relation to the body and the second of the pair of elements being rotatably mounted in the body and so coupled to the first element that relative axial movement of the first element causes rotation of the second element which is coupled to a hydraulic system which resists sudden or rapid rotation of the second element. The pair of co-operating elements may comprise a screw-nut assembly. The hydraulic system may comprise a reversible pump driven by the rotatable element and pumping hydraulic fluid round a closed circuit including a throttling orifice. Alternatively the hydraulic system may comprise a rotary laminar hydraulic damper filled with high viscosity oil.

Mechanical-hydraulic damper for a load subject to shocks and vibrations

A wing mounted retractable aircraft undercarriage with a trailing wheel or wheels comprising a rigid leg casing, pivotally mounted on the wing about a retraction axis, a rocking lever pivoted on the leg casing, supporting the wheel or wheels and mounting the lower pivot connection of a shock absorber located behind the leg casing, an upper pivot connection of the shock absorber to a lever, which lever is pivotable on the leg casing about an articulation axis which is distinct from the retraction axis, a rod of fixed length pivoted at one end to the lever and at the other end to a fixed position on the wing, so that upon retraction of the undercarriage by the action of a retraction jack, the rod causes rotation of the lever with respect to the leg casing, which rotation, by traction of the expanded shock absorber causes pivoting, with respect to the leg casing, of the rocking lever mounting the wheel or wheels towards the retraction axis, and thus an overall shortening of the undercarriage. Preferably the axis of the pivot connection of the shock absorber to the lever and the articulation axis are aligned with the longitudinal axis of the shock absorber in the undercarriage down position. The rod and the articulation axis are preferably disposed in relation to the retraction axis in such a way that during retraction the extent of rotation of the lever with respect to the leg casing is greater than the extent of the rotation of the leg casing with respect to the wing.

Wing mounted retractable aircraft undercarriages

An apparatus for adjusting the braking force of brakes applied to vehicle wheels in which the brakes are operated under the control of an electromagnet as a function of the deceleration and acceleration of the wheels. For a given braking signal, the braking force is eliminated when the deceleration of the braked wheel exceeds a predetermined threshold value, which may occur, for example, when the wheel starts to freely skid, and the reapplication of the braking force is delayed for a period of time proportional to the magnitude of deceleration of the wheel and inversely proportional to the subsequent magnitude of acceleration of the wheel when it picks up speed only when such acceleration exceeds a threshold which permits the wheel to gain speed irrespective of the frictional adherence of the wheel to the ground.

Growing community of inventors

Paris, France

Jean Masclet