Abstract: 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.

Abstract: A method and a system for detecting wire or wire-like obstacles, which method and system are designed for an aircraft. The system for detecting wire or wire-like obstacles comprises a detection device, such as a video camera or a LIDAR device, a computer and a display device. The method includes a step of detecting at least one pylon in the surrounding environment of the aircraft via a detection device, a step of identifying a family of pylons to which each detected pylon corresponds, a step of characterizing at least one cable supported by the at least one detected pylon, and a step of determining a prohibited zone that can potentially contain each pylon and each cable and a safe zone not containing either a pylon or a cable. The prohibited zone and the safe zone may be displayed on the display device.

Abstract: 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.

Abstract: A method and a system for detecting and avoiding obstacles with several obstacle detection spaces for an aircraft. The aircraft comprises a control system, a plurality of sensors for detecting obstacles in three detection spaces and a calculator. The method comprises a step of detecting at least one obstacle present in at least one detection space, a step of analyzing the at least one detected obstacle in order to determine at least one characteristic of the at least one obstacle, a step of determining at least one avoidance trajectory enabling the aircraft to avoid the at least one detected obstacle depending on at least one characteristic of the obstacle and a step of controlling the control system in order for the aircraft to automatically undertake an avoidance trajectory to avoid the detected obstacle.

Abstract: A method and a system for detecting wire or wire-like obstacles, which method and system are designed for an aircraft. The system for detecting wire or wire-like obstacles comprises a detection device, such as a video camera or a LIDAR device, a computer and a display device. The method includes a step of detecting at least one pylon in the surrounding environment of the aircraft via a detection device, a step of identifying a family of pylons to which each detected pylon corresponds, a step of characterizing at least one cable supported by the at least one detected pylon, and a step of determining a prohibited zone that can potentially contain each pylon and each cable and a safe zone not containing either a pylon or a cable. The prohibited zone and the safe zone may be displayed on the display device.

Abstract: 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.

Abstract: 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.

Abstract: 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 (R2) lying orthogonally between each face tooth and its axis of rotation, the small radius (R2) being smaller than the large radius (R1).

Abstract: 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.

Abstract: 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 (R2) lying orthogonally between each face tooth and its axis of rotation, the small radius (R2) being smaller than the large radius (R1).

Abstract: A method of piloting an aircraft (1) provided with at least one rotary wing (2) and a tail rotor (10) suitable for swiveling to pass reversibly from an anti-torque mode of operation to a propulsion mode of operation, said tail rotor (10) having a plurality of second blades (12) having a second variable pitch and rotating about an axis of rotation (AX), said axis of rotation presenting a first variable salient angle (?) relative to a first plane (P1). Thus, in the anti-torque mode of operation, said second pitch is controlled using first control means (31). Furthermore, in the propulsion mode of operation, said first salient angle (?) is controlled using first control means (31) and said second pitch is controlled using second control means (32) for controlling thrust.

Abstract: An aircraft (1) having an airframe (4) extending from a rear end (4?) to a front end (4?), a rotary wing (2), and a tail rotor (10). The aircraft (1) also includes a power plant (20) driving said rotary wing (2) via a main power gearbox (30) secured to a mast (31) of said rotary wing (2), said power plant (20) driving said tail rotor (10) via a tail power gearbox (40). The aircraft possesses pivot means (43) for causing the tail rotor (10) to swivel in a reversible manner from a stationary first position (POS1) towards a second position (POS2). The aircraft also includes tilt means (50) for tilting said mast (31) in a reversible manner.

Abstract: A drive device (D) for driving first and second lift rotors (2, 3) of a twin-rotor rotorcraft, includes link elements provided with first and second transmission shafts (5, 6) for synchronizing the first and second transmission members (74, 84) of first and second main gearboxes (7, 8), the first main gearbox (7) being provided with first power combiner element (73) firstly meshing with the first transmission member (74) and secondly mechanically linked with the first transmission shaft (5) and with the second transmission shaft (6), and the second main gearbox (8) being provided with second power combiner element (83) firstly meshing with the second transmission member (84), and secondly mechanically linked with the first transmission shaft (5) and with the second transmission shaft (6).

Abstract: An aircraft (1) having an airframe (4) extending from a rear end (4?) to a front end (4?), a rotary wing (2), and a tail rotor (10). The aircraft (1) also includes a power plant (20) driving said rotary wing (2) via a main power gearbox (30) secured to a mast (31) of said rotary wing (2), said power plant (20) driving said tail rotor (10) via a tail power gearbox (40). The aircraft possesses pivot means (43) for causing the tail rotor (10) to swivel in a reversible manner from a stationary first position (POS1) towards a second position (POS2). The aircraft also includes tilt means (50) for tilting said mast (31) in a reversible manner.

Abstract: A method of piloting an aircraft (1) provided with at least one rotary wing (2) and a tail rotor (10) suitable for swiveling to pass reversibly from an anti-torque mode of operation to a propulsion mode of operation, said tail rotor (10) having a plurality of second blades (12) having a second variable pitch and rotating about an axis of rotation (AX), said axis of rotation presenting a first variable salient angle (?) relative to a first plane (P1). Thus, in the anti-torque mode of operation, said second pitch is controlled using first control means (31). Furthermore, in the propulsion mode of operation, said first salient angle (?) is controlled using first control means (31) and said second pitch is controlled using second control means (32) for controlling thrust.

Abstract: A drive device (D) for driving first and second lift rotors (2, 3) of a twin-rotor rotorcraft, includes link elements provided with first and second transmission shafts (5, 6) for synchronizing the first and second transmission members (74, 84) of first and second main gearboxes (7, 8), the first main gearbox (7) being provided with first power combiner element (73) firstly meshing with the first transmission member (74) and secondly mechanically linked with the first transmission shaft (5) and with the second transmission shaft (6), and the second main gearbox (8) being provided with second power combiner element (83) firstly meshing with the second transmission member (84), and secondly mechanically linked with the first transmission shaft (5) and with the second transmission shaft (6).

Abstract: 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.

Abstract: A transmission gearbox (1) has a casing (2) that tilts around a tilting axis (B—B) via two bearings (19). Each of the bearings includes: a fixed part (20) having a sleeve (20a); and a trunnion (21a) which belongs to a pivoting part (21) and which pivots around the sleeve, the pivoting part being solidly connected to the casing (2). A shouldered wear ring (22) is disposed between the sleeve (20a) and the trunnion (21a) of each bearing (19). The invention is suitable for use in the pivot mounting of a power transmission gearbox (1) that is used to rotate the tilting rotor (14) of a convertible aircraft.

Abstract: 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.

Abstract: 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.