Eurocopter

Airbus Helicopters

Avio S.p.a.

Lionel Thomassey

Thierry Sandrart

Glacomo Orsini

Eric Magre

Maurice Blanc

Antoine Guillemin

Natacha Laborde

Giacomo Orsini

Nadine Laborde

A mechanical device comprising an input pinion, an intermediate shaft and a terminal pinion that are coaxial and are able to rotate about a rotation axis, as well as a torquemeter with a phonic wheel provided with a reference shaft connected by a distal end to the intermediate shaft, measuring indexes arranged at a proximal end of the intermediate shaft and reference indexes arranged at a proximal end of the reference shaft. A first mechanical connection connects the input pinion and the intermediate shaft. A second mechanical connection connects a first distal end of the intermediate shaft and the terminal pinion and comprises series of first teeth arranged on the distal end and second teeth arranged on the terminal pinion, and a drive ring comprising a series of connecting teeth cooperating with the first and second teeth.

Mechanical drive device provided with a torquemeter with a phonic wheel, gearbox provided with such a mechanical drive device and aircraft

A safe control method and a safe control system for performing control relative to an authorized flight envelope of an aircraft. The aircraft includes a digital main measurement system for measuring flight characteristics of the aircraft, a flight control system for automatically piloting the aircraft, and said safe control system. The safe control system includes an analog backup measurement system that delivers at least one analog signal that is a function of the at least one flight characteristic, and a switch-over device that is configured so that the flight control system uses the at least one analog signal delivered by the backup measurement system for automatically piloting the aircraft whenever at least one flight characteristic of the aircraft exceeds a predetermined limit of the authorized flight envelope.

Safe method and a safe system for controlling a position of an aircraft relative to the authorized flight envelope

A drone comprising a carrier structure, at least three lift propulsion rotors and a control system delivering at least one electrical power supply to at least three electric motors driving said at least three rotors, said at least three rotors being spaced apart longitudinally and transversely beside one another, wherein said drone includes a wing carrying two half-wings symmetrically about an anteroposterior plane of symmetry P of said drone, serving at least to increase the lift of said drone, each of said two half-wings including at least one movable portion suitable for moving relative to said carrier structure of said drone with at least a first degree of freedom to move in rotation about a first pivot axis parallel to a longitudinal direction X of said drone; and two first electric actuators respectively enabling each of said movable portions of one of said two half-wings.

Drone having at least three lift and propulsion rotors

A power transmission gearbox having at least one driving gear with spur teeth presenting a large radius. The gearbox includes at least one mechanical outlet drive system suitable for driving an accessory, the mechanical outlet drive system having a gear with face teeth referred to as an 'accessory pinion', the accessory pinion presenting a 'small' radius (R) lying orthogonally between each face tooth and its axis of rotation, the small radius (R) being smaller than the large radius (R).

Power transmission gearbox and an aircraft

A method of piloting an aircraft () provided with at least one rotary wing () and a tail rotor () suitable for swiveling to pass reversibly from an anti-torque mode of operation to a propulsion mode of operation, said tail rotor () having a plurality of second blades () having a second variable pitch and rotating about an axis of rotation (AX), said axis of rotation presenting a first variable salient angle (&#x3b8;) relative to a first plane (P). Thus, in the anti-torque mode of operation, said second pitch is controlled using first control means (). Furthermore, in the propulsion mode of operation, said first salient angle (&#x3b8;) is controlled using first control means () and said second pitch is controlled using second control means () for controlling thrust.

Method and an aircraft provided with a swiveling tail rotor

An aircraft () having an airframe () extending from a rear end (&#x2033;) to a front end ('), a rotary wing (), and a tail rotor (). The aircraft () also includes a power plant () driving said rotary wing () via a main power gearbox () secured to a mast () of said rotary wing (), said power plant () driving said tail rotor () via a tail power gearbox (). The aircraft possesses pivot means () for causing the tail rotor () to swivel in a reversible manner from a stationary first position (POS) towards a second position (POS). The aircraft also includes tilt means () for tilting said mast () in a reversible manner.

Aircraft provided with a swiveling tail rotor, and an associated method

A drive device (D) for driving first and second lift rotors () of a twin-rotor rotorcraft, includes link elements provided with first and second transmission shafts () for synchronizing the first and second transmission members () of first and second main gearboxes (), the first main gearbox () being provided with first power combiner element () firstly meshing with the first transmission member () and secondly mechanically linked with the first transmission shaft () and with the second transmission shaft (), and the second main gearbox () being provided with second power combiner element () firstly meshing with the second transmission member (), and secondly mechanically linked with the first transmission shaft () and with the second transmission shaft ().

Drive device for driving first and second lift rotors of a rotorcraft having twin rotors in tandem

An installation includes at least a pressurized lubricating circuit for elements housed in the rocking crankcase, each circuit including a radial transfer bearing between two opposite cylindrical journals coaxial about the rocking axis, one fixed journal on a fixed part and one pivoting journal on a pivoting part integral with the pivoting crankcase. Each transfer bearing has two U-shaped annular gaskets facing each other and spaced apart along the rocking axis so as to define between them an annular pressurized liquid lubricant chamber. The annular chamber is supplied with pressurized liquid lubricant by at least a supply duct integrated in the fixed part and whose upstream part is connected to a pressurized lubricant source, and feeds the rocking crankcase with pressurized lubricant through a dispensing duct emerging into the rocking crankcase. The invention is useful for lubricating rocking power transmission boxes for convertible aircraft tilt rotors.

Lubricating installation for rocking power transmission box

A transmission gearbox () has a casing () that tilts around a tilting axis (B&#x2014;B) via two bearings (). Each of the bearings includes: a fixed part () having a sleeve (); and a trunnion () which belongs to a pivoting part () and which pivots around the sleeve, the pivoting part being solidly connected to the casing (). A shouldered wear ring () is disposed between the sleeve () and the trunnion () of each bearing (). The invention is suitable for use in the pivot mounting of a power transmission gearbox () that is used to rotate the tilting rotor () of a convertible aircraft.

Tilting transmission gearbox comprising a pivoting connection with plain bearings

A pivoting power transmission unit is provided for driving a tiltable rotor of a convertible aircraft. The casing of the pivoting transmission unit comprises a lower casing, by which the casing is able to pivot on a support by two bearings each having a stationary part integral with the support and a swivelling part. The lower casing is assembled to an upper casing in which a drive shaft connected in rotation to gears housed in the casing is mounted so as to rotate about an axis of rotation perpendicular to the pivot axis of the casing. The upper casing is supported by an arrangement configured to transfer to the support via said bearings load/thrust forces experienced by the drive shaft during use.

Pivoting power transmission unit with load transfer via the casing

A pivoting power transmission unit is provided for transmitting rotational drive to a rotor configured to revolve about an axis of rotation and configured to be swivelled about a pivot axis substantially perpendicular to said rotation axis. The unit comprises a casing mounted between two parts of a support by two bearings co-axial with the pivot axis. Each bearing includes a stationary part attached to the support, swivelling part attached to the casing and a wear take-up ring disposed therebetween. The unit further comprises a device to take up axial play between the casing and the support. The device includes an annular piston, sliding axially in a chamber fed with fluid under pressure, and bearing against an axial end of the wear take-up ring.

Pivoting transmission unit with a device to take up play along the pivot axis

A device for lubricating a power gearbox having a variable orientation and a closed space has a lubricating unit that supplies lubricant to at least one element of the gearbox, which needs to be lubricated. A collecting reservoir collects lubricant from the closed space. A drain screw chamber, within the closed space, has a number of orifices disposed between different zones of the closed space and the drain screw chamber for passing lubricant there between. At least one rotary drain screw, which is produced in the form of an Archimedean screw, is disposed in the drain screw chamber to convey the lubricant from the drain screw chamber to the collecting reservoir. A drive unit drives the drain screw in rotation for conveying the lubricant. The orifices open respectively different zones of the closed space to the drain screw chamber such that the drain screw chamber can always collect lubricant from the different zones regardless of the orientation of the gearbox.

Device for lubricating a power gearbox with a variable orientation, particularly for a convertible tilt-rotor aircraft

A pivoting power transmission unit is provided for transmitting rotational drive from a power source to a rotor configured to revolve about a first axis and configured to swivel about a second axis perpendicular thereto. The transmission unit comprises: input pinion driven in rotation by the power source; two contra-rotating gearwheels which mesh with the input pinion and are co-axially mounted along the second axis; two cylindrical intermediate pinions, each joined to rotate co-axially with a respective one of the two gearwheels; and a further gearwheel in meshing engagement with the intermediate pinions. The further gearwheel drives in rotation an output shaft linked to the rotor.

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Fos sur Mer, France

Lionel Thomassey