Messier-bugatti-dowty

Messier-dowty Sa

Safran Landing Systems

Dominique Ducos

Jean-François Locufier

Richard Masson

Philippe Henrion

Edouard Campbell

Ian Robert Bennett

Thierry Blanpain

Nicolas Nguyen

Nicolas Keller

Sebastien Dubois

David Smart

Albert De Pindray

Maud Courtois

Pascal Martin

Jean-Francois Locufier

The invention relates to an aircraft undercarriage having a leg () pivotally mounted on a structure of the aircraft to pivot about a pivot axis (X) between a deployed position and a retracted position, the undercarriage including a foldable brace () comprising two hinged-together elements, one of which is hinged to the leg and the other of which is hinged to the structure of the aircraft, in such a manner that when the leg is in the deployed position, the two brace elements are locked together in a substantially aligned position, the undercarriage also being provided with a rotary drive actuator () having an outlet shaft acting on one of the elements of the foldable brace in order to cause the leg to pivot between its two positions. The drive actuator is pivotally mounted on the structure of the aircraft to pivot about an axis of rotation (X) of the outlet shaft, the drive actuator having a casing () connected by a reaction rod () to the leg in order to take up the torque developed by the drive actuator when driving the undercarriage.

Aircraft undercarriage with a rotary drive actuator

Aircraft landing gear having a leg () for hinging to a structure of the aircraft so as to be movable between a deployed position and a retracted position, a main brace (), a secondary brace (), and a double-acting type unlocking actuator () having a first end coupled to the secondary brace and controllable for causing its links to move out of alignment against the action of the resilient member during retraction or deployment of the landing gear. The landing gear includes couplers () for coupling to a second end of the unlocking actuator, which couplers ensure movement of said second end relative to the leg so that, for a given action, the unlocking actuator tends to break the alignment of the links when the landing gear is in one of its positions and tends to confirm said alignment when the landing gear is in its other position.

Landing gear with realigning lock link assembly

A device for coupling an actuator for operating an aircraft undercarriage to an aircraft structure. The device comprises a lever having a first end for hinging to the structure of the aircraft, and a second end to which the actuator is hinged, a pre-loading structure acting on the lever to urge it towards a stable rest position that is occupied by the lever in the absence of any force transiting through the actuator; and an abutment structure defining at least one working position for the lever when the actuator is activated.

Device for coupling an actuator for controlling the landing gear of an aircraft

An anti-lofting deflector for landing gear having two wheels on an axle. The deflector comprises a stationary support () for being fastened in service to a portion of the landing gear that carries the axle in order to extend between the wheels and present a distal end behind the wheels. It also has a first flap () hinged to the support via its distal end about a first hinge axis (X) substantially parallel to the axle and a second flap () hinged to the first flap about a second hinge axis (X) substantially parallel to the first hinge axis. Finally, there is a a return member () arranged so as to urge the second flap against an abutment of the first flap that prevents the second flap from becoming aligned with the first flap, and to urge the first flap against an abutment of the stationary support that prevents the first flap from folding against the support.

Anti-lofting deflector for aircraft landing gear

A simple device for blocking and unblocking the locking member of an undercarriage having a breaker strut and including an unlocking device. The device comprises a rotary actuator of axis parallel to the hinge axis of the links of the stabilizing member; a crank connected to a shaft of the actuator; a pawl hinged to the end of the crank and including a step; a pin secured to and at a distance from one of the links of the stabilizing member; and return means for urging the pawl towards the pin. The actuator is actuatable between a first angular position in which the pin is in contact with the pawl facing the step while the links are substantially in alignment, and a second angular position that the crank reaches when the step of the pawl has pushed back the pin, taking the links of the stabilizer member out of alignment.

Device for unlocking an undercarriage in a deployed position, and an undercarriage fitted with such a device

An aircraft undercarriage comprising two rocker beams () carrying wheels and mounted to pivot on a common pivot (Y), the undercarriage including a shock-absorber device comprising two connecting rods (), each rod () being coupled to a respective rocker beam, at least one connecting rod being telescopic and forming a shock absorber. The two connecting rods also are coupled to a rocker () pivotally mounted on a central pivot (), wherein the common pivot of the rocker beams is secured to a structure of an aircraft to which the undercarriage is fastened and is mounted in a fixed position on the structure. The central pivot of the rocker is movable between a first position (rocker beams in a landing position) and a second position in which a rocker has pulled on the connecting rods to cause the rocker beams to pivot towards a retracted position of the undercarriage.

Main landing gear of an aircraft, comprising two walking beams joined to the structure of the aircraft in an articulated manner

The invention relates to an aircraft landing gear of deformable-parallelogram type, including: According to the invention, one of the panels () is hinged on the leg while being connected to the casing by a pin on one end of the pivot () of the rocker arm.

Aircraft landing gear of the rocker-arm and deformable-parallelogram type

A method of operating an aircraft landing gear between a deployed position and a retracted position. The landing gear comprises a leg hinged to the aircraft, the leg being stabilized in the deployed position by a folding strut comprising two hinged-together links, the strut being held in an aligned position by a stabilizer member comprising two hinged-together links themselves held in alignment by a locking member. The method comprises the steps of arranging the strut () and the stabilizer member () in such a manner that at least one of the links () of the stabilizer member moves continuously during a movement of the leg from the deployed position to the retracted position, and of attaching an operating actuator () to the link in order to cause the link to pivot against the locking member and to exert thereon a force tending to move the leg.

Method for operating a landing gear assembly with a breaker strut

A process for manufacturing a metal part reinforced with ceramic fibers, in which: a housing is formed for an insert in a main metal body having an upper face; an insert formed from a bundle of fibers with a metal matrix is placed in the housing; a metal cover is placed on the main body so as to cover the insert; the cover is welded onto the metal body; a hot isostatic pressing operation is carried out; and the part obtained is machined to the desired shape. The housing has the shape of a notch of L-shaped cross section with a face perpendicular to the upper face and a face parallel to the upper face, the cover having an internal notch of L-shaped cross section, this having a shape complementary to that of the metal body with said insert, the cover being shaped on the outside so that the pressure forces are exerted perpendicular to said faces of the notch.

Process for manufacturing a metal part reinforced with ceramic fibres

A process for manufacturing a metal part reinforced with ceramic fibers, in which: a housing for an insert is machined in a metal body having an upper face; an insert formed from a fiber bundle having a metal matrix is placed in the housing; a metal cover is placed on the metal body so as to cover the insert; the cover is welded onto the metal body; the assembly including the metal body with the cover undergoes a hot isostatic compression treatment; and the treated assembly is machined to obtain the part. The insert is a rectilinear insert and the housing forms a rectilinear groove that extends beyond the insert and is open at each end, the groove being filled by a tab when the cover is placed on the metal body.

A damper for an airplane landing gear leg comprises a main strut () and a rod piston () co-operating with the strut () to define a main chamber () and annular chamber () for hydraulic fluid, and presenting internally two adjacent chambers () that are isolated from each other by a separator piston (). The damper () further comprises a first secondary strut () telescopically Slidable on the above-mentioned rod piston (), and a second secondary strut () telescopically slidable on the other end of the first secondary strut (). The two second annular chambers () as defined in this way are respectively connected to associated control circuits thus enabling the total length of the damper to be shortened or lengthened respectively for the purpose of causing the landing gear to contract or to be extended.

Landing gear strut damper, and landing gear with independent struts comprising same

Retractable landing gear for an aircraft, the landing gear being of the type that is raised vertically, and comprising a plurality of independent legs, each leg comprising a structural part rigidly secured to a structure of the aircraft, a pivoting rocker beam supporting a pair of wheels, and a shock absorber. In accordance with the invention, the shock absorber of each leg is extended by a positioning portion enabling the total length of the extended shock absorber to be shortened in order to collapse the leg, and each leg further comprises a positioning actuator connected in hinged manner to the extended shock absorber and arranged to lengthen relative to a normal use position in order to lengthen the corresponding leg. This makes it possible to shorten and/or lengthen one or another of the legs of the landing gear while the aircraft is stationary or taxiing slowly.

Retractable landing gear for aircraft

The invention relates to an aircraft landing gear having a retractable leg, in which the leg comprises a strut with a telescopic rod, the strut being hinged to a structure of the aircraft in order to pivot between a gear-up position and a gear-down position, said strut also being connected to the structure of the aircraft via hinged brace elements. According to an essential aspect of the invention, the landing gear includes an independent low-noise fairing system that serves, when the leg is in the gear-down position, to cover the front of at least a portion of the hinge between the brace elements, said low-noise fairing system comprising a hinged fairing of two complementary portions connected to each other via a hinge whose axis is parallel to the axis of the corresponding hinge portion of said brace elements.

Growing community of inventors

Savigny sur Orge, France

Dominique Ducos