A method for assisting the piloting of a rotorcraft comprising a first engine and a second engine, each capable, in the absence of a failure, of transmitting engine torque to at least one rotor providing at least lift keeping the rotorcraft in the air. The rotorcraft has aerodynamic members for piloting the rotorcraft. The method has these steps: controlling the first engine and the second engine asymmetrically, the first engine alone providing driving power to the rotor(s), the second engine operating at a standby speed; identifying an engine failure in the first engine by a failure monitor; and in the event of failure in the first engine, accelerating the second engine to a synchronization speed.
A method for simulating an autorotation phase of a simulated rotorcraft. This method comprises a training phase carried out with a training rotorcraft comprising a single training combustion engine for rotating a training lift rotor. The training phase comprises assigning of a stored training value to a regulation limit, by a regulator, and regulation of the training combustion engine, by the regulator, keeping the torque parameter of the training rotorcraft less than or equal to the regulation limit, the training value being less than a nominal value, so that the training combustion engine produces a power equal to a reference power produced by a simulated electric motor.
G09B 9/46 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer the aircraft being a helicopter
3.
POWER PLANT PROVIDED WITH A TURBOSHAFT ENGINE AND AN ADAPTIVE STARTING CIRCUIT AND ADAPTIVE STARTING METHOD FOR A TURBOSHAFT ENGINE
An adaptive starting method for a turboshaft engine comprising a gas generator, an electric machine connected mechanically to the gas generator and electrically to one or more electrical energy sources. A maximum electrical intensity of an electric current that can be delivered by the electrical energy hgsource or sources is determined as a function of at least one characteristic of each electrical energy source, a maximum engine torque supplied by the electric machine powered by each electrical energy source with the maximum electrical intensity is determined. The maximum engine torque is compared with a required engine torque envelope permitted by the gas generator. The maximum electrical intensity of the electric current supplied by the electrical energy source or sources is adapted in order to comply with the required envelope in order to start the gas generator.
A monitoring system for monitoring a hybrid power plant of a rotorcraft comprising at least one rotor. The hybrid power plant has an electric motor comprising a first drive shaft, a heat engine comprising a second drive shaft and a gearbox. The monitoring system includes at least one first sensing device measuring a first item of torque information representative of a first engine torque C1 transmitted by the first drive shaft to a first input shaft of the gearbox and a controller comparing the first engine torque C1 with a first limit value VL1.
B64D 31/18 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants for hybrid-electric power plants
B64D 35/022 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants of hybrid-electric type
5.
ACTUATOR PROVIDED WITH TWO PRESSURE SENSORS AND A VIRTUAL PRESSURE SENSING DEVICE; A BRAKING SYSTEM AND AN AIRCRAFT PROVIDED WITH SUCH AN ACTUATOR, AND THE METHOD APPLIED
An actuator provided with a pump connected to a first hydraulic connection connected to a reservoir and to a second hydraulic connection. A command controller communicates with a first pressure sensor arranged on the second hydraulic connection and measuring a first supply pressure. A monitoring controller communicates with the command controller and a second pressure sensor arranged on the second hydraulic connection and measuring a second supply pressure. A virtual pressure sensing device is provided with a verification instrument transmitting at least one verification signal carrying an operating parameter of the pump to the command controller and to the monitoring controller in order to identify a failure of the actuator and consequently apply a degraded operating mode.
A measurement apparatus for determining a bending moment acting on a rotor shaft of a rotary-wing aircraft as well as to a method of operating such a measurement apparatus. The measurement apparatus includes a processing system and a sensor arrangement that is mounted to a rotor blade which is attached to the rotor shaft. The sensor arrangement includes a sensor that generates a signal in response to a force or moment acting on the rotor blade. A cable transmits the signal from the sensor to the processing system, and the processing system determines the bending moment acting on the rotor shaft based on the signal from the sensor.
G01M 5/00 - Investigating the elasticity of structures, e.g. deflection of bridges or aircraft wings
G01D 5/353 - Mechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using optical means, i.e. using infrared, visible or ultraviolet light with attenuation or whole or partial obturation of beams of light the beams of light being detected by photocells influencing the transmission properties of an optical fibre
A method for controlling a rotorcraft, the rotorcraft comprising at least two combustion engines, at least one regulation system and one transmission system, the at least two engines being mechanically connected to the transmission system respectively by at least two couplings. Such a control method comprises at least identifying an N2-regulated engine, identifying a non-N2′-regulated engine and generating a control setpoint limit for at least one first regulation system of the N2-regulated engine and depending on the speed of rotation N2 of at least one first output shaft of the N2-regulated engine.
B64C 27/57 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
A measurement system for measuring a dynamic deformation of an object, the measurement system comprising an optical fiber, the optical fiber extending at least partially into a tube that is configured to be secured to the object, the optical fiber having a measurement sector that is able to move inside the tube, the measurement sector comprising at least one Bragg grating. The measurement system comprises a non-Newtonian fluid filling at least one chamber delimited by the tube, the measurement sector extending into the at least one chamber, the non-Newtonian fluid being in contact with the tube and the measurement sector.
G01L 1/24 - Measuring force or stress, in general by measuring variations of optical properties of material when it is stressed, e.g. by photoelastic stress analysis
G01L 11/02 - Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by means not provided for in group or by optical means
9.
GROUND SERVICE DEVICE FOR SECURING ROTOR BLADES OF A ROTARY-WING AIRCRAFT
A ground service system that includes a ground service device and a connecting interface. The ground service device secures rotor blades of a multi-blade rotor of a rotary-wing aircraft in a non-operational mode of the rotary-wing aircraft, when the ground service device is attached to the connecting interface on the rotary-wing aircraft. The ground service device includes a rack with three struts and an attachment device that are releasably attachable to four receiver mounts of the connecting interface. The ground service device further includes clamps for releasably connecting the rotor blades with the four receiver mounts to secure the rotor blades in the non-operational mode of the rotary-wing aircraft.
La présente invention concerne un système mécanique muni d’une enveloppe délimitant un volume interne contenant de l’huile. Le système mécanique comporte un dispositif de prélèvement pour prélever au moins une partie de l’huile. Le dispositif de prélèvement comprend au moins une tuyauterie solidaire de l’enveloppe, la tuyauterie s’étendant d’une extrémité interne située dans le volume interne jusqu’à un col comprenant une extrémité externe ouverte sur un milieu extérieur situé à l’extérieur du système mécanique. Le dispositif de prélèvement comprend un obturateur manœuvrable par un opérateur pour obturer le col. Le dispositif de prélèvement comprend dans le col une barrière anti-polluant ménageant un passage restreint apte à être traversé par un tuyau de prélèvement.
12.
SYSTEM HAVING A MECHANICAL CONNECTION DEVICE WITH TWO MECHANICAL TORQUE TRANSMISSION PATHS
A system comprising a connection device having a first shaft and a second shaft, the connection device comprising a free-wheel interposed between the first shaft and the second shaft that can only transmit engine torque from the first shaft to the second shaft when a motor mode is activated. The connection device comprises a coupler, the coupler being provided with a fusible section, the connection device comprising a dog clutch connection that can only transmit engine torque from the coupler to the first shaft when an electrical power generation mode is activated.
B64D 35/022 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants of hybrid-electric type
F16D 3/06 - Yielding couplings, i.e. with means permitting movement between the connected parts during the drive adapted to specific functions specially adapted to allow axial displacement
F16D 9/06 - Couplings with safety member for disconnecting by breaking due to shear stress
F16D 11/14 - Clutches in which the members have interengaging parts with clutching members movable only axially
F16D 48/06 - Control by electric or electronic means, e.g. of fluid pressure
The transmission system, including a drive shaft, a driven shaft and a connecting device enabling the drive shaft to transmit mechanical torque to the driven shaft, and guide devices guiding the drive shaft in rotation about a drive axis and guiding the driven shaft in rotation about a driven axis. When the transmission system is at a standstill, the drive axis and the driven axis are misaligned, and they move closer to one another when the transmission system transmits torque from the drive shaft to the driven shaft.
12 - Land, air and water vehicles; parts of land vehicles
37 - Construction and mining; installation and repair services
Goods & Services
Helicopters and rotorcraft and structural parts and fittings therefor, included in class 12. Installation, upgrading, maintenance, repair and overhaul of helicopters and rotorcraft, parts, fittings and equipment therefor; Customization [installation services] of helicopters and rotorcraft; Custom installation of helicopter and rotorcraft interiors; Painting for helicopters and rotorcraft; Information and consultancy relating to all the above-mentioned services.
12 - Land, air and water vehicles; parts of land vehicles
37 - Construction and mining; installation and repair services
41 - Education, entertainment, sporting and cultural services
Goods & Services
Air vehicles; apparatus for locomotion by air; Helicopters and rotorcraft and structural parts, fittings, dynamic components, and equipment therefor, included in class 12. Installation, upgrading, maintenance, repair and overhaul of helicopters and rotorcraft, structural parts, fittings, dynamic components, and equipment thereof; inspection of helicopters and rotorcraft prior to maintenance and repair; installation, upgrading, maintenance and repair of helicopter and rotorcraft flight simulators; technical support services, namely, technical advice in the field of helicopter and rotorcraft maintenance, repair and overhaul; information services relating to the repair, maintenance and overhaul of helicopters and rotorcraft. Providing of training; Training of helicopter and rotorcraft pilots; Training of mechanics, technicians and engineers in the field of helicopters and rotorcraft; Training provided through helicopter and rotorcraft flight simulators; Conducting courses, conferences, seminars, workshops in the field of helicopters and rotorcraft, and distribution of training material in connection therewith; Provision of information relating to training services in the field of helicopters and rotorcraft; Publication of books, manuals, magazines, journals, newspapers, periodicals, catalogs, brochures, all relating to helicopters and rotorcraft; Providing online electronic publications (not downloadable) relating to helicopters and rotorcraft.
16.
METHOD FOR ANTICORROSION TREATMENT OF A MAGNESIUM ALLOY PART, ASSOCIATED ANTICORROSION AQUEOUS SOLUTION AND PART
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventor
Le Pottier, Nathalie
Cotinot, Jérémie
Frayret, Jérôme
Castetbon, Alain
Pettier, Sophie
Gurt Santanach, Julien
Pommiers Belin, Sébastien
Thielleux, Delphine
Potin Gautier, Martine
Vialas, Nadia
Zoccali, Sandra
Abstract
The invention relates to a method for anticorrosion treatment of a magnesium alloy part, in which the part is immersed for a given duration in an anticorrosion aqueous solution having a given temperature and containing permanganate ions MnO4- and dihydrogen phosphate ions H2PO4-. According to the invention, the anticorrosion aqueous solution contains, prior to immersion of the part, a molar ion concentrate of permanganate ions [MnO4-] of greater than or equal to 0.18 mol/L and less than or equal to 0.32 mol/L, the pH of the anticorrosion aqueous solution is maintained for the given duration at a value of greater than or equal to 3.2 and less than or equal to 4.2, preferably greater than or equal to 3.4 and less than or equal to 4.0, by addition of phosphoric acid, and, after the given duration, the part is removed from the solution and rinsed with water.
C23C 22/73 - Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals characterised by the process
17.
PIVOTING LANDING GEAR PROVIDED WITH AN IMMOBILIZATION SYSTEM
A landing gear provided with a stand and a pivoting assembly carrying a contact member and able to rotate about a pivot axis in relation to the stand. An immobilization system comprises a movable pin and a passage provided in a base secured to the pivoting assembly. An elastic locking system tends to push the pin into the passage in a locked mode. An elastic unlocking system is configured to move the pin out of the passage when activation of an unlocked mode is commanded by a control, the elastic unlocking system being calibrated to allow the pin to be extracted from the passage only when there is a shearing force less than a threshold between the base and the pin.
A method for assisting the piloting of an aircraft comprising a head-up display and an automatic flight control system that comprises a human-machine selection interface for choosing an operating mode from among several predetermined operating modes comprising a disengaged mode and an engaged mode, the automatic flight control system being configured, in the engaged mode, to control at least one actuator in order to bring a current value of a controlled parameter towards a setpoint value. The method comprises: i) detecting, with a control system, an applied current mode from among the several predetermined operating modes; and ii) controlling and displaying, on the head-up display, a symbol carrying the current value according to a graphic charter specific to the current mode, a first graphic charter applied during the disengaged mode being different from a second graphic charter applied during the engaged mode.
A method for determining a current fuel consumption margin of a functional engine of an aircraft in relation to a theoretical fuel consumption of a reference engine. This method comprises: a) when in flight, performing at least one engine health check comprising at least measuring a current value of a monitoring temperature and a control value of a power parameter of said functional engine; b) determining, as a function at least of the control value, with a consumption model applied by a controller, said current fuel consumption margin in relation to the theoretical fuel consumption; and c) transmitting said current fuel consumption margin to a receiver.
An aircraft provided with at least one electric machine accommodated in a compartment separated from an outside environment by a cowling, the aircraft comprising a ventilation system for conveying air from the outside environment to the electric machine. The ventilation system comprises a duct connected to the electric machine and extending up to a free section, the free section being situated in the outside environment, the duct passing through a passage in the cowling, the duct extending partially into the compartment and partially into the outside environment, a free space surrounding the duct in the passage and separating the duct from the cowling, the ventilation system comprising a scoop that faces the free section without closing it off according to a vertical axis when the aircraft is on horizontal ground.
A rotorcraft flight training method for a rotorcraft comprising at least two engines and at least one rotor providing lift helping to keep the rotorcraft in the air. The method comprises at least the following steps: flying the rotorcraft in a mode wherein each engine supplies driving power to the rotor; and activating a first command to start a training phase simulating asymmetric flight, the training phase comprising a first flight phase comprising a first control operation, with a controller, controlling the at least two engines and a first display operation for displaying, with a display, information carrying at least two simulated powers.
G09B 9/46 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer the aircraft being a helicopter
The present disclosure relates to a method (20) for determining an absolute pose of a camera (11), in a reference coordinate system, said camera (11) being located on board a craft (10) that is able to move with respect to a scene, said method comprising: - obtaining (S20) a sequence of images of said scene, said images being acquired by the camera at various respective times, said sequence being able to be considered to be a video stream, - determining (S21), from the sequence of images, a local 3D model in a coordinate system of the camera, said local 3D model representing part of the scene at the time of acquisition of one image, called the target image, among the sequence of images, - determining (S22) the absolute pose of the camera at the time of acquisition of the target image, by aligning the position and attitude of the local 3D model in the coordinate system of the camera with a predetermined 3D reference model corresponding to said scene represented in three dimensions in the reference coordinate system.
G06T 7/70 - Determining position or orientation of objects or cameras
23.
METHOD AND DEVICE FOR MONITORING THE HEALTH OF A MECHANICAL SYSTEM OF A VEHICLE BY USING THRESHOLDS THAT VARY DEPENDING ON OPERATING PARAMETERS OF THE SYSTEM
A method for monitoring a mechanical system for a vehicle. During an initial phase, measurements are taken of vibration values from vibration sensors and context parameters from context sensors in order to determine several values of a health indicator CI relating to the mechanical system and a variation model of a threshold relating to this health indicator CI and variable as a function of the context parameters. Next, during a monitoring phase, measurements are taken once more of vibration values and context parameters in order to determine an operational value of the health indicator CI and a threshold specific to this health indicator CI by means of the threshold variation model and the measured context parameters. A fault presence alarm may then be triggered if there is a risk of presence of a fault in the mechanical system.
A method for controlling an economy operating mode for an aircraft comprising two heat engines, only one of the heat engines being active and supplying mechanical power to the rotor in the economy operating mode. Operating parameters of the aircraft are measured and then compared with functional and safety limitations relating to the economy operating mode. When the aircraft is in the economy operating mode, if a functional limitation is not being respected by one of the parameters, an alert indicating the proximity of the functional limitations is issued in order to inform the pilot, and, if one of the safety limitations is not being respected, the economy operating mode is disengaged, each heat engine not supplying mechanical power to the at least one rotor being started.
A method of processing engine monitoring parameters in a rotorcraft that comprises at least one rotor and at least two engines for powering the at least one rotor in one of an All Engines Operative mode and a Single Engine Operation mode, wherein the engine monitoring parameters are at least indicative of power margins of one engine of the at least two engines of the rotorcraft, wherein the method comprises displaying an engine monitoring indicator for the one engine of the at least two engines of the rotorcraft for visualizing a current performance state of the one engine; and, if the rotorcraft is operated in the Single Engine Operation mode, displaying a first graphical representation of a Single Engine Operation mode indicator with the engine monitoring indicator for visualizing that the rotorcraft is operated in the Single Engine Operation mode.
A method for simulating an engine failure on a rotorcraft comprising several engines for setting a rotary wing in motion. The method comprises a training mode that comprises controlling each engine with a controller in order to simulate an engine failure, this control comprising limiting the power of each engine to a respective control restriction value. The training mode comprises the following steps: i) determining, with the controller, a maximum mass at least as a function of external conditions, and an initial mass of the rotorcraft at least as a function of an unladen mass of the rotorcraft, a mass of a crew present in the rotorcraft, and an estimated mass of fuel on-board; ii) comparing, with the controller, the initial mass with the maximum mass; and iii) determining, with the controller, each control restriction value as a function of the comparison.
A method for controlling an aircraft having at least two engines burning fuel and a transmission system connected to a rotary wing, each engine having a power shaft connected to the transmission system. An energy-saving phase comprises at least one energy-saving period comprising controlling, at an active rating, with a control system, one active engine from the at least two engines, and using the control system to stop or control, at an inactive rating, each inactive engine from the at least two engines that is not the active engine.
A method for testing a hybrid power plant equipping a rotary-wing aircraft comprising at least one lift rotor, the hybrid power plant being configured to rotate the at least one lift rotor, the hybrid power plant comprising at least one heat engine configured to rotate the at least one lift rotor; and at least one electric motor supplied with electrical energy by at least one electrical power source, the at least one electric motor being configured to rotate the at least one lift rotor at least when at least one of the at least one heat engine fails.
A rotorcraft provided with a rotary wing and a skid landing gear, the landing gear being provided with a first skid and a second skid and with a first cross-member and a second cross-member. The first cross-member is connected to an airframe of the rotorcraft only by two fastenings. The second cross-member is only carried during flight by two supports fastened to the airframe and traversed by the second cross-member. Each support comprises a hole delimited by a stop surface, the second cross-member always being separated from each stop surface by a clearance. A median supporting member is arranged transversely between the two supports and above the second cross-member.
The present disclosure relates to a method for detecting a hard landing comprising: i) determining three ground components of a ground reaction force, and determining, for each connector of a landing gear, three attachment components of a force applied to this connector, ii) determining whether a ground stress point defined by the three ground components lies within or outside a ground dimensioning envelope, and, for each connector, whether an attachment stress point defined by the three corresponding attachment components lies within or outside an attachment dimensioning envelope, iii) determining that a hard landing has been made when at least the ground stress point lies outside the ground dimensioning envelope or at least one attachment stress point lies outside the corresponding attachment dimensioning envelope.
A window for a vehicle with a main window pane having a vent window opening, and a vent window assembly mounted to the main window pane. The vent window assembly comprises: a movable vent window pane adapted for closing the vent window opening in closed state of the vent window assembly; a first vent window frame assembly comprising a first support frame arranged on a first surface of the main window pane; and a second vent window frame assembly comprising a second support frame arranged on a second surface of the main window pane, wherein the second vent window frame assembly is rigidly attached to the first vent window frame assembly at the vent window opening such that the first and second vent window frame assemblies fasten each other at the main window pane.
B64D 13/00 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
32.
METHODS FOR DETERMINING THE CYCLOSTATIONNARITY OF A VIBRATION SIGNAL RELATING TO A MECHANICAL SYSTEM, FOR ARRANGING VIBRATION SENSORS FOR MONITORING SUCH A SYSTEM, AND FOR MONITORING IT
A method for determining the cyclostationarity of a vibration signal transmitted by a vibration sensor arranged on a mechanical system and allowing a cyclostationarity indicator Iα to be calculated. The present disclosure also relates to a method for arranging vibration sensors, using the method for determining cyclostationarity applied to the signals transmitted by these vibration sensors at different positions and orientations. A position of a vibration sensor is validated as a function of this cyclostationarity indicator Iα. The present disclosure finally relates to a method for monitoring a mechanical system 10 using the method for determining cyclostationarity to determine the cyclostationarity of the vibration signals relating to the mechanical system before calculating the monitoring indicators of the mechanical system.
A method and a device for detecting a fault in a mechanical system comprising a rotating member and a vibration sensor transmitting a temporal vibration signal. The method comprises processing the temporal vibration signals transmitted over a predetermined period in order to transform the temporal vibration signals firstly into angular vibration signals, then into frequency vibration signals. Next, series of amplitudes are generated, each series being associated with a specific frequency channel and comprising the amplitudes of the frequency vibration signals for this frequency channel. The frequency channels displaying an increasing trend consistent with the fault of interest are then identified. The frequency channels that display an increasing trend are then compared with characteristic frequencies of a known fault of interest in order to check for the possible presence of such a fault in the mechanical system.
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
37 - Construction and mining; installation and repair services
Goods & Services
Downloadable computer software for the configuration, control, operation and maintenance of drones and unmanned aerial vehicles (UAVs); computer hardware; ground control stations for the remote control of drones and unmanned aerial vehicles (UAVs) consisting of computer hardware, video monitors, controllers and aerials Drones, unmanned aerial vehicles (UAVs), and parts and fittings therefor. Maintenance and repair of drones; maintenance and repair of unmanned aerial vehicles (UAVs).
35.
METHOD AND SYSTEM FOR DETECTING OBSTACLES WITH AN OBSTACLE SENSOR FOR A ROTARY-WING AIRCRAFT
A method for signaling obstacles present in a space surrounding an aircraft. This method comprises: acquiring, with at least one LiDAR obstacle sensor, positioning data in a reference frame of the obstacle sensor, constructing, during said flight, a three-dimensional map of the surrounding space in a mapping reference frame and positioning the aircraft in the map by applying a simultaneous localization and mapping process based at least on the positioning data, and displaying, during the flight, on a display, an aircraft symbol and a two-dimensional representation of at least a part of the map, each point displayed in the representation being displayed according to a graphic charter taking the associated level of risk into consideration.
An exhaust duct configured to be arranged around an exhaust nozzle of an engine, the exhaust duct having a plurality of sections. The sections are circular between an inlet section and an outlet section, with the exception of the sections of a deformed segment, each section of the deformed segment extending from a bottom sector to a top sector, the bottom sector having a non-circular shape so that at least a volume of liquid that is not able to reach, by force of gravity, the inlet section and the outlet section, is less than a volume threshold when the pitch and roll angles respectively lie within predetermined pitch and roll angle ranges.
A retractable landing gear for an aircraft. The landing gear comprises a rocker arm hinged to a structure of the aircraft and carrying at least one wheel that is able to move between a deployed position and a retracted position, a shock-absorber hinged to the structure, a connecting rod connecting the rocker arm and the shock-absorber, a strut provided with two connecting links that are hinged to each other and respectively hinged to shock-absorber and connected to an actuator fastened to the structure. The connecting rod is out of alignment with the shock-absorber when a force applied to the shock-absorber is less than a predetermined force, and the landing gear comprises a locking device provided with an elastic return member and a stop device for locking the strut when the wheel is in the deployed position, and then for securing the wheel in the deployed position.
A non-retractable wheel-type landing gear for a rotorcraft, comprising: at least one wheel; a shock absorber with a circumferential direction, which is connected to the at least one wheel and comprises a shock absorber tube and a shock absorber rod telescopically mounted to the shock absorber tube; a mounting arm extending laterally from the shock absorber tube, the mounting arm being integrally formed with the shock absorber tube and adapted for attachment to a first fitting of a rotorcraft; and a link fixation extending laterally from the shock absorber tube, the link fixation being arranged in the circumferential direction of the shock absorber at an angle in a range from 45° to 120° with respect to the mounting arm and adapted for connection to a second fitting of the rotorcraft.
A rotorcraft with at least one non-retractable wheel-type landing gear and a fuselage comprising a lower shell, an inner floor, and at least one lower fuselage compartment arranged between the inner floor and the lower shell, wherein the at least one non-retractable wheel-type landing gear is rigidly attached in the at least one lower fuselage compartment and comprises: at least one wheel; a shock absorber connected to the at least one wheel and comprising a shock absorber tube and a shock absorber rod telescopically mounted to the shock absorber tube; at least two mounting arms extending laterally from the shock absorber tube; and a mounting pin extending from the shock absorber tube toward a floor fitting provided at the inner floor, wherein the mounting pin is connected to the floor fitting.
A rotorcraft with at least one non-retractable wheel-type landing gear and a fuselage comprising a lower shell, an inner floor, and at least one lower fuselage compartment arranged between the inner floor and the lower shell, wherein the at least one non-retractable wheel-type landing gear is rigidly attached in the at least one lower fuselage compartment and comprises: at least one wheel; a shock absorber connected to the at least one wheel and comprising a shock absorber tube and a shock absorber rod telescopically mounted to the shock absorber tube; at least two mounting arms extending laterally from the shock absorber tube; and a mounting pin device extending laterally from the shock absorber tube and comprising a mounting pin connected to a floor fitting provided at the inner floor.
A method for setting, in an aircraft, a calculation mass relative to a load to be transported by a hooking system of the aircraft. The method comprises: detecting whether a current state of the aircraft is a flight state with the load to be transported attached to the hooking system and, if so, displaying a proposed mass on a display, validating the proposed mass using a validation interface in order to assign the proposed mass to the calculation mass, or, if the proposed mass is not validated at the end of a predetermined condition, assigning a predetermined mass to the calculation mass.
G01G 19/07 - Weighing apparatus or methods adapted for special purposes not provided for in groups for weighing wheeled or rolling bodies, e.g. vehicles for weighing aircraft
G01G 19/14 - Weighing apparatus or methods adapted for special purposes not provided for in groups for weighing suspended loads
42.
Method for authorizing the flight of an aircraft having a hybrid power plant provided with at least one electric motor and at least one heat engine
A method for authorizing the flight of an aircraft provided with a hybrid power plant having at least one heat engine and at least one electric motor electrically connected to an electrical energy source comprising several electrical accumulators. The method comprises extracting (STP1), while on the ground, an electrical energy or an electrical power to be extracted from the electrical energy source during a predetermined time period and determining (STP2) for the electrical accumulators, respective initial values of an operating parameter, calculating (STP3) an average value from the initial values, determining (STP4) a minimum value from the measured initial values, issuing an authorization when a difference between the average value and the minimum value is less than a threshold and a prohibition when said difference between the average value and the minimum value is greater than or equal to the threshold.
An aircraft provided with at least one exhaust duct for discharging gases from an engine. The exhaust duct is partly accommodated in an internal housing of the aircraft, the housing being separated from an external environment situated outside the aircraft by at least one cowl that is able to move in relation to a load-bearing structure of the aircraft. The exhaust duct comprises an exhaust segment passing through a passage of the cowl without touching the cowl. A space separates the exhaust segment from the cowl. The aircraft comprises at least one stabilization system coupled to the exhaust duct, the stabilization system comprising a stiffening ring secured to the exhaust duct and at least one fastening connecting the exhaust duct to the cowl.
A blade comprising a blade root extended by an aerodynamic intermediate part that extends up to a free end. The blade root comprises a one-piece attachment body made from composite materials, that is hollow and has a casing that defines an empty internal space, the attachment body incorporating: a pitch attachment configured to be traversed by a pitch link rod connected to a pitch lever, the attachment body incorporating a leading edge attachment configured to be traversed by a leading edge link rod connected to a first drag damper, a trailing edge attachment configured to be traversed by a trailing edge link rod configured to be connected to a second drag damper, and a connection attachment configured to be traversed by at least one connecting rod connected to a first reinforcement of a stratified spherical stop.
An aircraft provided with a power plant provided with at least one combustion engine mechanically connected to a drive system, the drive system comprising two electric machines each connected to the combustion engine by a kinematic chain, the two electric machines being electrically connected to at least one electrical power source. The aircraft comprises a management system controlling at least a mechanical power or an engine torque delivered by each of the two electric machines as a function of a current operating mode, the management system being configured, during a superior operating mode, to control the two electric machines in order for the two electric machines to deliver different and non-zero mechanical powers or engine torques.
An aircraft provided with an engine compartment, the aircraft comprising an engine at least partially housed in the engine compartment, the engine comprising an exhaust nozzle for at least discharging gases, the aircraft comprising an exhaust duct arranged around the exhaust nozzle, the exhaust duct having an open end opening into the engine compartment. The aircraft comprises a drainage device comprising a guide cooperating with the exhaust duct for collecting liquid flowing along the exhaust duct and exiting the exhaust duct through the end.
B64D 33/04 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
A62C 3/06 - Fire prevention, containment or extinguishing specially adapted for particular objects or places of highly inflammable material, e.g. light metals, petroleum products
A62C 3/08 - Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles in aircraft
47.
METHOD OF OPTIMIZING THE NOISE GENERATED IN FLIGHT BY A ROTORCRAFT
A method of optimizing the noise generated by a hybrid power plant of a rotorcraft in flight, the hybrid power plant driving a main rotor of the rotorcraft in rotation and being provided with at least one engine, with at least one electric machine, and with at least one electrical energy source that electrically powers the electric machine. The method includes a determination step for determining a required power delivered by the hybrid power plant and that is required for the flight phase, and a distribution step for distributing the required power between the at least one engine and the electric machine as a function of a target noise level and of the required power for the flight phase, as well as of a model for the noise generated by the at least one engine as a function of one of its parameters.
An aircraft door with an inner door space; a door opening system arranged at least partly in the inner door space. The door opening system comprises: at least one locking device for locking the aircraft door in a locked state, actuation kinematics for actuating the at least one locking device, and at least one transmission rod coupling the actuation kinematics with the at least one locking device; wherein the at least one transmission rod is displaceable in the inner door space by means of the actuation kinematics for actuating the at least one locking device; and an anti-vibration device mounted in the inner door space to the at least one transmission rod for absorbing vibrations of the at least one transmission rod, wherein the anti-vibration device is displaceable in the inner door space together with the at least one transmission rod.
E05B 77/38 - Cushion elements, elastic guiding elements or holding elements, e.g. for cushioning or damping the impact of the bolt against the striker during closing of the wing
B64C 1/14 - WindowsDoorsHatch covers or access panelsSurrounding frame structuresCanopiesWindscreens
49.
Aircraft comprising at least two turboshaft engines and device configured to be connected to one of the turboshaft engines and method for controlling such an aircraft
An aircraft and a method for controlling such an aircraft comprising two turboshaft engines, an electric machine, an electrical power source and a rotor rotated by one of the two turboshaft engines and/or by the electric machine. The aircraft comprises at least one controller configured to implement, at all times, a current operating mode of the electric machine and the electrical power source, selected from seven operating modes, allowing standard start-up or fast start-up respectively of a turboshaft engine in a switched-off state or in a standby state. The electric machine can also provide first or second levels of power assistance to a turboshaft engine in order to transmit engine torque to the gas generator of that turboshaft engine, apply mechanical resistance to a turboshaft engine or help ventilate a turboshaft engine in a switched-off state.
A method of determining a trajectory for a rotorcraft, comprising: receiving an initial trajectory defining a planned flight path of the rotorcraft between a starting point and a target point; performing iterations of a loop comprising adding the initial trajectory to a set of selectable trajectories, evaluating a noise indicator of the rotorcraft for the initial trajectory on the basis of a noise-related acoustic footprint and a noise exposure level-related acoustic footprint, adding the evaluated noise indicator to a set of evaluated noise indicators, determining an alternative trajectory defining an alternative flight path of the rotorcraft between the starting point and the target point on the basis of the evaluated noise indicator, and setting the alternative trajectory as initial trajectory; and outputting a trajectory of the set of selectable trajectories associated with a selected noise indicator fulfilling predetermined noise indicator conditions.
La présente invention concerne un atterrisseur muni d'au moins une roue coopérant avec un dispositif amortisseur. Ledit dispositif amortisseur comporte un premier sous-ensemble amortisseur muni d'une première chambre remplie par un premier gaz, la première chambre étant délimitée par un premier corps et un premier piston mobile par rapport au premier corps, ledit dispositif amortisseur comportant un deuxième sous-ensemble amortisseur muni d'une deuxième chambre remplie par un deuxième gaz, la deuxième chambre étant délimitée par un deuxième corps et par un deuxième piston mobile par rapport au deuxième corps, la première chambre présentant une première pression qui est maximale dans une position de repos de l'atterrisseur précédent un atterrissage, la deuxième chambre présentant une deuxième pression qui est minimale dans la position de repos.
B64C 25/58 - Arrangements or adaptations of shock-absorbers or springs
F16F 9/02 - Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium using gas only
52.
DOUBLE-LOCKING HOOKING SYSTEM INTENDED FOR TRANSPORTING A LOAD OUTSIDE AN AIRCRAFT
A double-locking hooking system comprising a structure, a hook that is able to move in relation to the structure between a closed position and an open position, and an immobilization system for immobilizing the hook in the closed position (18). The immobilization system comprises two immobilization devices each provided with at least one movable stop. The stops are in contact with the hook when the hook is in the closed position in order to immobilize the hook in the closed position. The two immobilization devices therefore each allow the hook to be immobilized in the closed position, by means of the stops, independently of each other. In order to position the hook in the open position, the two immobilization devices need to be activated in order for the stops to be moved to release the hook.
A method for training at least one artificial intelligence model for estimating the weight of an aircraft during flight based on use data, the at least one artificial intelligence model being developed in order to be implemented during at least one predetermined flight phase of at least one aircraft of the same type. The method comprises carrying out a plurality of flights and, for at least one of the plurality of flights, the method comprises acquiring, during flight, at least one set of flight data, carrying out at least one consistency test in order to check that a reliable reference weight is calculated or capable of being calculated, calculating at least one calculated weight of the aircraft and storing the at least one set of flight data and the at least one calculated weight.
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
G01G 19/414 - Weighing apparatus or methods adapted for special purposes not provided for in groups with provisions for indicating, recording, or computing price or other quantities dependent on the weight using electromechanical or electronic computing means using electronic computing means only
G01G 19/07 - Weighing apparatus or methods adapted for special purposes not provided for in groups for weighing wheeled or rolling bodies, e.g. vehicles for weighing aircraft
The disclosure relates to a door locking assembly for locking a door of an aircraft, comprising a locking hook adapted for blocking in a locking position a lockable arm of a door of an aircraft; a release lever connected to the locking hook for moving the locking hook from a releasing position into the locking position in response to being actuated by a lockable arm of a door of an aircraft; an operating handle connected at least to the release lever and rotatable for moving the locking hook from the locking position to the releasing position; and a locking indicator connected to the locking hook for indicating positioning of the locking hook in one of the locking position or the releasing position.
E05C 3/04 - Fastening devices with bolts moving pivotally or rotatively without latching action with operating handle or equivalent member rigid with the bolt
E05C 3/00 - Fastening devices with bolts moving pivotally or rotatively
The invention relates to a door locking assembly (6) for locking a door (4) of an aircraft, comprising a locking hook (6a) adapted for blocking in a locking position a lockable arm (4e) of a door (4) of an aircraft; a release lever (6i) connected to the locking hook (6a) for moving the locking hook (6a) from a releasing position into the locking position in response to being actuated by a lockable arm (4e) of a door (4) of an aircraft; an operating handle (6d) connected at least to the release lever (6i) and rotatable for moving the locking hook (6a) from the locking position to the releasing position; and a locking indicator (6b) connected to the locking hook (6a) for indicating positioning of the locking hook (6a) in one of the locking position or the releasing position.
B64C 1/14 - WindowsDoorsHatch covers or access panelsSurrounding frame structuresCanopiesWindscreens
E05B 83/04 - Locks for railway freight-cars, freight containers or the likeLocks for the cargo compartments of commercial lorries, trucks or vans for sliding wings
E05B 83/40 - Locks for passenger or like doors for sliding doors
E05B 85/00 - Details of vehicle locks not provided for in groups
E05C 17/60 - Devices for holding wings openDevices for limiting opening of wings or for holding wings open by a movable member extending between frame and wingBraking devices, stops or buffers, combined therewith holding sliding wings open
A landing gear provided with at least two first rollers mounted on two first free-wheels respectively connected to a first skid and configured, during a landing phase, to lock in the elastic return direction when the first skid moves in a first direction from the first skid towards a second skid and to be free in the sink direction during movement in a second direction, at least two second rollers being mounted on two respective second free-wheels connected to a second skid and configured, during a landing phase, to lock when the second skid moves in the second direction and to be free during movement in the first direction.
An automatic diagnostic method for monitoring a state of health of at least one engine equipping an aircraft, the method comprising the periodic in-flight acquisition of a plurality of flight data, with sensors, the plurality of flight data being representative of a plurality of physico-chemical parameters, the identification, with a controller, from the plurality of flight data, of at least one predetermined engine health check phase and the isolation, with the controller, of a sequence of significant data from the plurality of flight data produced during the at least one engine health check phase.
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.
A method for continuous in-flight management of a beam generator on board an aircraft, the aircraft comprising the beam generator, sensors, a calculator and a display device. After continuously acquiring a value of at least one parameter of the beam generator and a value of at least one parameter of the aircraft by means of the sensors, a step of continuously estimating a piece of information relating to the reliability of the beam generator over a predetermined time period is carried out using the calculator, as a function, at the very least, of the successive values of the parameters of the beam generator and the aircraft as well as data from a history of the beam generator. Finally, at least one indication relating to the beam generator and depending on the piece of information is displayed on the display device.
La présente invention concerne une articulation deformable élastiquement comportant une portion deformable et une portion interne cylindrique agencée en tout ou partie à l'intérieur d'une portion externe cylindrique, ladite portion deformable étant solidaire de ladite portion interne cylindrique et de ladite portion externe cylindrique, ladite portion interne cylindrique étant mobile par rapport à ladite portion externe cylindrique, ladite articulation deformable comportant une interface de liaison agencée en tout ou partie à l'intérieur d'un alésage de ladite portion interne cylindrique, ladite interface de liaison comportant un arbre connecté à ladite portion interne cylindrique, ledit arbre s'étendant suivant une direction longitudinale traversant ledit alésage.
F16C 7/00 - Connecting-rods or like links pivoted at both endsConstruction of connecting-rod heads
F16F 1/48 - Springs made of plastics, e.g. rubberSprings made of material having high internal friction characterised by the mode of stressing loaded mainly in torsion
G01L 3/04 - Rotary-transmission dynamometers wherein the torque-transmitting element comprises a torsionally-flexible shaft
61.
SKID-TYPE LANDING GEAR EQUIPPED WITH ANTI-SINK SKIDS
La présente invention concerne un train d'atterrissage muni d'un premier patin pourvu d'une première partie longitudinale d'appui et d'un deuxième patin pourvu d'une deuxième partie longitudinale d'appui, chacune desdites première partie longitudinale d'appui et deuxième partie longitudinale d'appui s'étendant longitudinalement selon un sens arrière d'un axe longitudinal propre d'une extrémité avant a une extrémité arrière. La première partie longitudinale d'appui et la deuxième partie longitudinale d'appui sont respectivement prolongées selon le sens arrière associé par une première patinette et une deuxième patinette, chaque patinette présentant une face inferieure en vis-a-vis d'un sol lorsque le train d'atterrissage repose sur le sol, chaque face inferieure étant courbée longitudinalement et transversalement vers le sol, chaque face inferieure ayant une forme convexe au regard dudit sol.
A method for helping to keep a drone within an authorized airspace. This method involves displaying several symbols on a display of a path estimator comprising: i) displaying an aircraft symbol showing a current position of the drone in relation to the authorized airspace; ii) displaying a boundary symbol showing a boundary of the authorized airspace in a position in relation to the aircraft symbol representative of a position of the boundary in relation to the current position of the drone; and iii) determining a geometry and displaying a path symbol showing a predicted path of the drone without changing values of an item of speed data and an item of navigation data, the geometry of the path symbol being based at least on the value of the item of speed data and the value of the item of navigation data.
G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraftCombined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
63.
METHOD AND SYSTEM FOR ASSISTING THE PILOTING OF AN AIRCRAFT, AIRCRAFT EQUIPPED WITH SUCH A SYSTEM
The present disclosure relates to a system and a method for assisting the piloting of an aircraft, said method comprising, during a flight phase of said aircraft, at least two steps of measuring at least two current values of at least two respective operating parameters of said aircraft. The method comprises, for each of said at least two operating parameters, the following steps: generating an item of digital data representative of a current value of this operating parameter; identifying a current range within which an index lies, each range from said at least two ranges of indices being associated with a specific display configuration of said item of digital data; and displaying said item of digital data on at least one page of symbologies according to said specific display configuration corresponding to said current range.
B64D 43/00 - Arrangements or adaptations of instruments
G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraftCombined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
64.
Mechanical system provided with a sump receiving, above components to be lubricated or cooled, a tank of a lubricating fluid system
A mechanical system comprising a sump and at least one component to be lubricated or cooled arranged in the sump, the mechanical system comprising a lubricating fluid system provided with a lubricating fluid and a tank arranged in the sump. The tank is a leaking tank and is situated above said at least one component to be lubricated or cooled, the lubricating fluid flowing out of the tank by force of gravity, so as to reach said at least one component to be lubricated or cooled. The lubricating fluid system has at least one lift flow generator connected by at least one filling line to the tank and to at least one suction point present in a bottom of the sump. The lift flow generator fills the tank with the lubricating fluid present in said bottom at least during a starting phase.
F16H 57/04 - Features relating to lubrication or cooling
F16N 7/02 - Arrangements for supplying oil or unspecified lubricant from a stationary reservoir or the equivalent in or on the machine or member to be lubricated with gravity feed or drip lubrication
F16N 7/38 - Arrangements for supplying oil or unspecified lubricant from a stationary reservoir or the equivalent in or on the machine or member to be lubricated with a separate pumpCentral lubrication systems
A method for supplying air to an engine of an aircraft via an air supply system of the aircraft. A dynamic air intake vent of the system can be closed by a closure member that is movable between a closed position and an open position. A static air intake vent is equipped with a filter medium. During flight, the method comprises an unfiltered operating mode that comprises the following steps: positioning of the closure member in the open position, and, during a phase of forward travel of the aircraft, dynamic intake of a flow of air, then transfer of a first portion of the flow of air to the engine and a second portion of the flow of air to the filter medium in order to clean the filter medium.
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
F02C 7/052 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with dust-separation devices
A propeller provided with interchangeable blades, and to a method of mounting such interchangeable blades on the propeller. The propeller comprises a hub, fastening fittings, rotation guide devices for guiding the fastening fittings in rotation relative to the hub, locking parts, and blades. The fastening fittings are configured to be assembled into the hub from the inside of the hub, and the locking parts lock respective ones of the fastening fittings onto the hub. The blades are fastened to respective ones of the fastening fittings outside the hub and can thus easily be replaced with other blades without removing the propeller.
La présente invention concerne un simulateur (20) de balourd d'un rotor. Le simulateur (20) comporte un porteur (30) configuré pour effectuer un mouvement rotatif autour d'un axe de rotation (AX1), le simulateur (20) ayant une masselotte (40) mobile par rapport au porteur (30) entre une position initiale (POS1) et une position finale (POS2)õ le simulateur (20) ayant un bloqueur (50) commandé immobilisant sur requête la masselotte (40) par rapport au porteur (30) dans une position initiale (POS1), ledit simulateur (20) ayant une butée (60) ) bloquant la masselotte (40) dans la position finale (POS2) suite à un déplacement de la masselotte (40)).
A rotary wing aircraft that extends along a roll axis between a nose region and an aft region, comprising: at least one first single-blade rotor and at least one second single-blade rotor which are spaced apart from each other along the roll axis; at least one first electric machine and at least one second electric machine which are at least configured to drive in motor mode the at least one first single-blade rotor and the at least one second single-blade rotor for generating lift in hover condition of the rotary wing aircraft; at least one propulsion device that is at least configured to generate forward thrust in forward flight condition of the rotary wing aircraft; and a fixed-wing arrangement that is at least configured to provide lift in the forward flight condition.
B64C 27/30 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with provision for reducing drag of inoperative rotor
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 35/024 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants of hybrid-electric type of series type
H01M 10/46 - Accumulators structurally combined with charging apparatus
H02K 7/14 - Structural association with mechanical loads, e.g. with hand-held machine tools or fans
69.
Lubricating liquid manifold for a crankpin of an epicyclic gear train, gearbox and aircraft
A lubricating liquid manifold for a crankpin of an epicyclic gear train. The epicyclic gear train is lubricated by a lubrication system conveying a first flow of a lubricating liquid towards the manifold and a second flow of the lubricating liquid towards a member to be lubricated. The manifold comprises a hollow body provided with an inlet port intended to receive the first flow and an outlet port designed such that the first flow is conveyed towards a guide device connected to the crankpin. The manifold comprises a barrier comprising a shoulder connected to the body and a deflector protruding radially outwards from the body so as to form, with the shoulder, a diversion space for diverting the second flow and preventing it from penetrating into the manifold.
A height indicator for an aircraft, the height indicator being provided with a controller controlling a display means to display a height scale and a pointer. The height scale is able to move in relation to the pointer along an axis on the display means, the height scale being a piecewise linear scale comprising several graduated sections, each graduated section having its own linear scale, each graduated section having a scale factor different from a scale factor of another graduated section, each scale factor representing the quotient between a distance on the graduated section along axis and a corresponding actual height.
G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraftCombined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
B64D 43/00 - Arrangements or adaptations of instruments
71.
Multifunction display system for an aircraft, associated aircraft and display method
A two-pilot multifunction display system and an aircraft equipped with the system, the system comprising: at least three screens, at least two of the at least three screens being suitable for displaying a page of symbologies referred to as the “FND page” comprising predetermined symbols and information relating to the flight and to the navigation of the aircraft; and detectors for detecting at least one failed screen among the at least three screens.
The invention relates to an aircraft (1) equipped with a fuel battery (5) and a tailboom (4) bearing a shrouded rotor (10). The aircraft (1) comprises a cooling system (35) for said fuel battery (5). The cooling system (35) is equipped with a cooling circuit (40) in which heat transfer fluid (45) circulates. The cooling circuit (40) comprises a catchment duct (42) leading into or beside the fuel battery (5) and a heat exchanger (41) in fluid communication with said catchment duct (42). A ventilation system is equipped with at least an outlet opening (60) fitted in the shrouded rotor (10) to ventilate said heat exchanger (41) at least by aspiration depending on the direction of air flow (101).
A display system for an aircraft, comprising at least one first display unit; at least one second display unit; a control unit that is configured to control the at least one first display unit and the at least one second display unit; and a storage unit with a main memory that is configured to store at least one configuration file, wherein the at least one configuration file is useable by the control unit for configuration of the at least one first display unit and the at least one second display unit, and wherein the at least one configuration file defines at least one displayable parameter for the at least one first display unit and the at least one second display unit.
G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraftCombined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
A gearbox including an angular contact ball bearing comprising a first row of balls provided with a plurality of balls, a second row of balls provided with another plurality of balls, at least one inner ring and at least one outer ring. According to the invention, in a degraded operating mode of the bearing, the first row of balls is configured to transmit at least one first axial force oriented along a first axis and at least one second axial force oriented along a second axis opposite the first axis, the second row of balls transmitting no axial force.
F16C 19/18 - Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load with two or more rows of balls
B64C 27/59 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
F16C 19/52 - Bearings with rolling contact, for exclusively rotary movement with devices affected by abnormal or undesired conditions
F16C 19/54 - Systems consisting of a plurality of bearings with rolling friction
An anchor for an aircraft. The anchor comprises a jack comprising a housing and a head that is able to move in translation in relation to the housing along an elevation axis, the head having three degrees of rotational freedom respectively about a longitudinal axis as well as a transverse axis and the elevation axis, the anchor comprising a member for taking up forces surrounding the jack and provided with a fastening suitable for being secured to the aircraft.
A blade, for a rotor of an aircraft, comprising a hollow cylindrical sleeve, a stop fastened to the cylindrical sleeve, a profiled portion, and an anchoring device, a blade body and a hollow torsion box secured to the profiled portion. The anchoring device and the blade body are positioned inside the cylindrical sleeve. The anchoring device surrounds the stop in order to form a stop for the profiled portion parallel to a longitudinal axis of the blade. The hollow torsion box is secured to the profiled portion, and comprises a bearing zone in contact with an inner wall of the cylindrical sleeve, taking up the bending loads on the blade.
A method for hovering an aircraft having at least one wing and at least one rotary wing and at least one propeller, the aircraft comprising an autopilot system. The method comprises keeping the aircraft hovering, with the autopilot system, in the setpoint position, keeping the aircraft hovering in this way comprising controlling, with the autopilot system, a pitch of blades of the at least one propeller irrespective of the setpoint pitch angle and controlling, with the autopilot system, a pitch of blades of the at least one rotary wing as a function at least of the setpoint pitch angle.
G05D 1/00 - Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
G05D 1/08 - Control of attitude, i.e. control of roll, pitch, or yaw
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64C 27/82 - RotorcraftRotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
A test bench configured to test a drag damper. The test bench comprises a first support that can be rotated about a first axis by a motor, the test bench comprising a second support that can rotate about a second axis, the second axis being axially offset from the first axis, the test bench comprising a first connector secured to the first support and a second connector secured to the second support, the first connector and the second connector being offset from the first axis and the second axis, the first connector and the second connector being opposite each other along an arrangement axis and being configured to carry the damper in line with the arrangement axis.
A method and a system for identifying tools intended for tools comprising a marking provided with at least one optically readable symbol. The system comprises, in particular, one or more image capture devices covering a checking area and a calculator. Several tools are positioned by an operator in the checking area, then an image of the checking area is captured by each image capture device. Next, at least one complete symbol is detected in at least one image by an image processing operation carried out by the calculator, and one or more detected tools corresponding respectively to a detected complete symbol are identified. Finally, a list comprising each detected tool is determined.
G06K 7/14 - Methods or arrangements for sensing record carriers by electromagnetic radiation, e.g. optical sensingMethods or arrangements for sensing record carriers by corpuscular radiation using light without selection of wavelength, e.g. sensing reflected white light
80.
METHOD AND DEVICE FOR CONTROLLING A THERMAL AND ELECTRICAL POWER PLANT FOR A ROTORCRAFT
A method for controlling a thermal and electrical power plant for setting in motion at least one rotary member of a rotorcraft, the power plant comprising at least one heat engine and an electrical system provided with at least one electric machine. The method comprises: selecting, with a selector, an operating mode chosen from several operating modes; determining a density altitude and comparing, with a controller, the current density altitude and a threshold density altitude; and controlling, with the controller, the at least one electric machine depending on at least the chosen operating mode as well as the comparison and a necessary power to be supplied to the power transmission system.
A method and a system for controlling a plurality of control stations of an aircraft. The control method comprises determining a current position of a portable electronic terminal in relation to the aircraft, identifying a current control station, determining at least one current image of the aircraft representative of the current control station, displaying, on a screen of the portable electronic terminal, the at least one current image, displaying at least one graphic interface component in overlay on the at least one current image, selecting a result relating to an inspection of at least one component on the portable electronic terminal and storing it in a memory, the result corresponding to a validated state or a non-validated state of the at least one inspected component.
A method and a device for assisting the piloting of a propeller rotorcraft having a rotary wing and at least one propeller. The piloting assistance device comprises a computer configured to display the following on a display: (i) a first scale representing a power consumed by the at least one propeller and carrying a minimum power mark and a maximum power mark, (ii) a second scale graduated in forward speed of the propeller rotorcraft, (iii) an index comprising a power section representing a current power consumed by the at least one propeller, the index comprising a speed section indicating a current forward speed on the second scale.
B64C 27/57 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64D 31/12 - Initiating means actuated automatically for equalising or synchronising power plants
B64D 35/04 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
83.
METHOD OF QUANTIFYING A LOSS OF VISIBILITY THROUGH A TRANSPARENT OBJECT
A method, comprising: providing a light source, a high contrast providing object, and an image acquisition device; emitting a light beam from the light source through the high contrast providing object, a transparent object and a surface of the transparent object toward the image acquisition device; exposing the surface of the transparent object to icing conditions such that a layer of ice is formed by ice accretion on the surface, wherein the light beam traverses the layer of ice after having traversed the transparent object; acquiring a series of images over time of the high contrast providing object using the image acquisition device; determining blur occurring in the series of images over the time; and quantifying the loss of visibility over the time through the transparent object on the basis of the determined blur.
A failure detection apparatus for a hydraulic system, to a hydraulic, failure detection-capable system, and to a method of operating a failure detection apparatus. The failure detection apparatus comprises a monitoring and failure detection unit that receives first and second pressure values from first and second pressure sensors and comprises a failure detection unit that detects a failure of at least one hydraulically operated device when a 2-tuple of a plurality of 2-tuples is within a first and outside a second predetermined tolerance range of relative pressure values, and wherein the failure detection unit 260 detects a failure of the pump when a 2-tuple of the plurality of 2-tuples is outside the first predetermined tolerance range of relative pressure values.
An arrangement provided with a partition at least partially delimiting an emergency exit, the arrangement having a movable panel that closes the emergency exit in an inactive operating mode, the arrangement comprising an evacuation system provided with a lifeline. The lifeline comprises a deployment section passing through a passage in the partition and secured to a handle, the panel together with the partition delimiting a recess in which the handle is arranged in the inactive operating mode.
The invention concerns an arrangement (1) equipped with a bulkhead (3) at least partially demarcating an emergency exit (10), said arrangement (1) having a movable panel (15) closing said emergency exit (10) in an inactive operating mode (INACMOD), said arrangement (1) comprising an evacuation system (20) equipped with a lifeline (30). Said lifeline (30) comprises a deployment section (42) crossing a passageway (300) of the bulkhead (3) and connected to a handle (60), said panel (15) demarcating with the bulkhead (3) a housing (19) in which is arranged said handle (60) in the inactive operating mode (INACMOD).
A method for assisting the piloting of a rotorcraft including at least two engines capable of transmitting engine torque to at least one main rotor, the assistance method comprising the following steps: periodically determining a current position of the rotorcraft; making a first periodic comparison between the current position and a decision point; identifying an engine failure; making a second periodic comparison between the current position of the rotorcraft and a touchdown point; periodically determining an emergency landing profile, the emergency landing profile being generated at least depending on a result of the second periodic comparison; and periodically generating control orders to pilot the rotorcraft according to the emergency landing profile.
B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
B64D 35/08 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions characterised by the transmission being driven by a plurality of power plants
An aircraft comprising two half-wings extending to either side of an airframe. The aircraft comprises at least one propeller arranged in the rear part of the airframe. The aircraft comprises a rotary wing provided with two synchronized counter-rotating rotors carried respectively by the half-wings. The aircraft comprises a power plant comprising at least one engine and a mechanical interconnection system connecting the power plant permanently to the rotors except in the event of failure and during training, and to the at least one propeller.
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64C 11/00 - Propellers, e.g. of ducted typeFeatures common to propellers and rotors for rotorcraft
B64C 27/59 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
B64D 35/06 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors the propellers or rotors being counter-rotating
89.
Method for assisting the piloting of a rotorcraft at high altitudes by supplying mechanical power from an electrical power plant
A method for assisting piloting beyond an altitude that can be reached with only the capabilities of a thermal power plant of a rotorcraft, by supplying power from an electrical power plant. After defining a take-off point of the rotorcraft and a target point, and their respective altitudes, a determination of a first maximum altitude that can be reached by the rotorcraft using only the thermal power plant is carried out according to a first altitude law. Then, an estimate of a second maximum altitude that can be reached by the rotorcraft using the thermal power plant and the electrical power plant jointly driving each rotor of the rotorcraft is made according to a second altitude law. If the second maximum altitude is higher than the altitude of the target point, the rotorcraft can fly to the target point.
A modular power plant for a rotorcraft comprising at least one lift rotor, the power plant comprising: at least one combustion or electric engine; a main gearbox, comprising a gearbox housing and a toothed wheel arranged in an internal space at least partially delimited by the gearbox housing, the toothed wheel having a degree of rotational freedom about a primary axis of rotation relative to the gearbox housing, the toothed wheel mechanically transmitting an engine torque generated by the at least one engine to the at least one lift rotor; and at least two mechanical connection interfaces, a first mechanical connection interface mechanically connecting the main gearbox to a first engine, and a second mechanical connection interface being left free or mechanically connecting the main gearbox to a second engine.
B64D 35/08 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions characterised by the transmission being driven by a plurality of power plants
91.
METHOD FOR AIDING THE STEERING OF A ROTORCRAFT COMPRISING AT LEAST TWO ENGINES
The present invention relates to a method (10) for aiding the steering of a rotorcraft comprising at least two engines capable of transferring an engine torque to at least one main rotor, said method (10) comprising the following steps: = periodic determination (12) of a current position of said rotorcraft (1), = first periodic comparison (13) between said current position and a decision point, = identification of an engine fault (14), = second periodic comparison (15) between said current position of said rotorcraft and a touchdown point, = periodic determination (16) of an emergency landing profile, said emergency landing profile being generated at least based on a result of said second periodic comparison (15), and = periodic generation (17) of control instructions for steering said rotorcraft according to said emergency landing profile.
The invention relates to a method for aiding the steering of a rotorcraft (1) beyond an altitude reachable through the capabilities of a thermal power plant alone through supplying power from an electric power plant. After defining a take-off point (PtD) for said rotorcraft (1) and an objective point (PtO), and their respective altitudes, a first maximum altitude (AM1) reachable by said rotorcraft (1) with the aid of only said thermal power plant is determined according to a first law of altitude. A second maximum altitude (AM2) reachable by said rotorcraft (1) with the aid of said thermal power plant and said electric power plant driving each rotor of said rotorcraft (1) is then achieved according to a second law of altitude. If said second maximum altitude (AM2) is greater than the altitude of said objective point (PtO), the rotorcraft can fly up to said objective point (PtO).
B60L 50/16 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by engine-driven generators, e.g. generators driven by combustion engines with provision for separate direct mechanical propulsion
B64D 27/02 - Aircraft characterised by the type or position of power plants
B64D 31/18 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants for hybrid-electric power plants
A linear electromechanical servocontrol comprising a power rod that is able to move in translation. The servocontrol comprises a single linear electrical actuator provided with at least one electric motor connected by a mechanical link to the power rod, the servocontrol comprising an anchor secured to the electrical actuator, the at least one electric motor being controlled by a computer, the anchor having an anchoring rod that is able to move in translation, the anchor having an anchoring brake that is configured to immobilize the anchoring rod with respect to the electrical actuator in a normal operating mode or to allow the electrical actuator to move in relation to the anchoring rod in a safe operating mode at the request of the computer.
B64C 27/605 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including swash plate, spider or cam mechanisms
B64C 11/44 - Blade pitch-changing mechanisms electric
B64C 13/50 - Transmitting means with power amplification using electrical energy
B64C 27/68 - Transmitting means, e.g. interrelated with initiating means or means acting on blades using electrical energy, e.g. having electrical power amplification
A protective assembly provided with a hollow first cap with a first cavity configured to house a first connector and a second cap. The second cap has a hollow portion delimiting a second cavity configured to house a second connector to be connected to the first connector. The first cavity is shaped to match an outer casing of the hollow portion. The second cap penetrates into the first cavity in a sealed manner, in a connected mode, isolating the first cavity and the second cavity from an external environment.
H01R 13/44 - Means for preventing access to live contacts
B60L 53/16 - Connectors, e.g. plugs or sockets, specially adapted for charging electric vehicles
B60R 16/02 - Electric or fluid circuits specially adapted for vehicles and not otherwise provided forArrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for electric
B60R 16/08 - Electric or fluid circuits specially adapted for vehicles and not otherwise provided forArrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for fluid
G02B 6/38 - Mechanical coupling means having fibre to fibre mating means
H01R 13/52 - Dustproof, splashproof, drip-proof, waterproof, or flameproof cases
F16L 57/00 - Protection of pipes or objects of similar shape against external or internal damage or wear
H01R 13/623 - Casing or ring with helicoidal groove
H01R 13/625 - Casing or ring with bayonet engagement
96.
Rotorcraft provided with a yaw motion control system having a ducted rotor and an ice protection system
A rotorcraft provided with a yaw motion control system comprising a fairing and a rotor provided with blades, the blades being arranged in the fairing and able to rotate about an axis of rotation of the rotor, the fairing comprising a casing defining an air stream, the air stream extending in a direction of flow of the air within the fairing from an intake section towards an outlet section. The rotorcraft comprises an ice protection system comprising at least one grille arranged upstream of the air stream in the air flow direction, the grille facing the intake section parallel to the axis of rotation and the casing, no grille facing at least one unprotected section of the intake section in a direction parallel to the axis of rotation.
B64C 27/82 - RotorcraftRotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
97.
Assembly provided with a disconnectable coupling system having a mechanical fuse and a friction brake
An assembly comprising a first part and a second part, the assembly comprising a disconnectable coupling system provided with a mechanical fuse for securing the first part and the second part according to an axis of movement up to a breaking threshold. The assembly comprises at least one single-use friction brake interposed between the first part and the second part, the friction brake braking a movement of the first part with respect to the second part after the mechanical fuse has broken.
The present invention relates to a piloting assistance system and method associated with a vehicle, the system comprising several displays and a plurality of sensors, each measuring a value of the same parameter, each display being configured to display a symbol carrying this value, and the plurality of sensors comprising sensors with a redundancy of order three or more. The system comprises a display controller configured to select, according to a stored logic, a sensor selected from among the plurality of sensors, each display using the value of said parameter measured with the sensor selected to display the symbol, where the plurality of sensors comprises two groups or more, each group comprising at least one of said sensors, the groups having an order ranging from highest to lowest ranked, the controller selecting a sensor from the first group deemed integrated from the high-ranked group, the order being a function of the accuracy level of the sensors.
A piloting assistance system for assisting the piloting of a vehicle, the piloting assistance system comprising at least one display and a plurality of sensors for each measuring a value of a given parameter, the at least one display being configured to display a symbol carrying the value, the plurality of sensors comprising redundant sensors with a redundancy of order three or higher. The piloting assistance system comprises a display controller configured to select, according to stored logic, a selected sensor from the plurality of sensors, the at least one display using the value of the parameter measured with the selected sensor to display the symbol.
