09 - Scientific and electric apparatus and instruments
42 - Scientific, technological and industrial services, research and design
45 - Legal and security services; personal services for individuals.
Goods & Services
Computer software for use in real-time collaborative
engagement by a group of vehicles across multiple domains
and environments, especially air, land, sea, space and
submarine; computer software for single vehicle autonomy and
real-time collaborative engagement with other vehicles,
especially for planning, enhancement and execution of
missions for vehicles, especially crewed or uncrewed
aircraft; computer software for enabling communication and
data exchange among vehicles, especially crewed or uncrewed
aircraft; computer software for enabling communication and
data exchange among vehicles, especially for planning,
enhancement and execution of missions for vehicles,
especially crewed and uncrewed aircraft; computer software
for use in facilitating real-time collaboration and
information sharing among vehicles, especially crewed and
uncrewed aircraft; computer software for use in facilitating
real-time collaboration and information sharing among
vehicles, especially for planning, enhancement and execution
of missions for vehicles, especially crewed and uncrewed
aircraft; computer software for planning, enhancement and
execution of missions for vehicles, especially crewed and
uncrewed aircraft. Providing online non-downloadable computer software for use
in real-time collaborative engagement by a group of vehicles
across multiple domains and environments especially air,
land, sea, space and submarine; software as a service (SaaS)
featuring software for enabling communication and data
exchange among diverse vehicles for collaborative purposes;
providing computer software for use in facilitating single
vehicle autonomy and real-time collaboration and information
sharing among vehicles; updating and maintenance of computer
software for use in real-time collaborative engagement by a
group of vehicles across multiple domains and environments,
especially air, land, sea, space and submarine; updating and
maintenance of computer software for single vehicle autonomy
and real-time collaborative engagement with other vehicles,
especially for planning, enhancement and execution of
missions for vehicles, especially crewed or uncrewed
aircraft; updating and maintenance of computer software for
enabling communication and data exchange among vehicles,
especially crewed or uncrewed aircraft; updating and
maintenance of computer software for enabling communication
and data exchange among vehicles, especially for planning,
enhancement and execution of missions for vehicles,
especially crewed and uncrewed aircraft; updating and
maintenance of computer software for use in facilitating
real-time collaboration and information sharing among
vehicles, especially crewed and uncrewed aircraft; updating
and maintenance of computer software for use in facilitating
real-time collaboration and information sharing among
vehicles, especially for planning, enhancement and execution
of missions for vehicles, especially crewed and uncrewed
aircraft; updating and maintenance of computer software for
planning, enhancement and execution of missions for
vehicles, especially crewed and uncrewed aircraft; technical
support services, namely, providing troubleshooting in the
nature of diagnosing problems with computer software for use
in real-time collaborative engagement by a group of vehicles
across multiple domains and environments, especially air,
land, sea, space and submarine; technical support services,
namely, providing troubleshooting in the nature of
diagnosing problems with computer software for single
vehicle autonomy and real-time collaborative engagement with
other vehicles, especially for planning, enhancement and
execution of missions for vehicles, especially crewed or
uncrewed aircraft; technical support services, namely,
providing troubleshooting in the nature of diagnosing
problems with computer software for enabling communication
and data exchange among vehicles, especially crewed or
uncrewed aircraft; technical support services, namely,
providing troubleshooting in the nature of diagnosing
problems with computer software for enabling communication
and data exchange among vehicles, especially for planning,
enhancement and execution of missions for vehicles,
especially crewed and uncrewed aircraft; technical support
services, namely, providing troubleshooting in the nature of
diagnosing problems with computer software for use in
facilitating real-time collaboration and information sharing
among vehicles, especially crewed and uncrewed aircraft;
technical support services, namely, providing
troubleshooting in the nature of diagnosing problems with
computer software for use in facilitating real-time
collaboration and information sharing among vehicles,
especially for planning, enhancement and execution of
missions for vehicles, especially crewed and uncrewed
aircraft; technical support services, namely, providing
troubleshooting in the nature of diagnosing problems with
computer software for planning, enhancement and execution of
missions for vehicles, especially crewed and uncrewed
aircraft. Licensing of computer software for use in real-time
collaborative engagement by a group of vehicles across
multiple domains and environments, especially air, land,
sea, space and submarine; licensing of computer software for
single vehicle autonomy and real-time collaborative
engagement with other vehicles, especially for planning,
enhancement and execution of missions for vehicles,
especially crewed or uncrewed aircraft; licensing of
computer software for enabling communication and data
exchange among vehicles, especially crewed or uncrewed
aircraft; licensing of computer software for enabling
communication and data exchange among vehicles, especially
for planning, enhancement and execution of missions for
vehicles, especially crewed and uncrewed aircraft; licensing
of computer software for use in facilitating real-time
collaboration and information sharing among vehicles,
especially crewed and uncrewed aircraft; licensing of
computer software for use in facilitating real-time
collaboration and information sharing among vehicles,
especially for planning, enhancement and execution of
missions for vehicles, especially crewed and uncrewed
aircraft; licensing of computer software for planning,
enhancement and execution of missions for vehicles,
especially crewed and uncrewed aircraft.
2.
HEATING INSTALLATION FOR AN AIRCRAFT COMPRISING A DIHYDROGEN TANK, AN ENGINE AND DIHYDROGEN HEATING SYSTEMS
A heating installation for an aircraft disposed between a dihydrogen tank and an engine with a first supply line connected to the tank and a second supply line connected to the engine and comprising two branch lines connected parallel to each other between the first supply line and the second supply line. Each branch lines includes a first valve, a heating system and a second valve installed in series, upstream to downstream.
FLOOR INCLUDING AT LEAST ONE CONNECTING DEVICE INCORPORATING AT LEAST ONE GUTTER AND ENABLING COMPENSATION OF RELATIVE MOVEMENT IN AT LEAST A LONGITUDINAL DIRECTION
A floor including at least one connecting device connecting first and second panels spaced in a longitudinal direction and including at least one gutter and at least one threshold bar connected to one another by at least one connecting system and respectively at least partly below and above the first and second panels, at least one of the first and second panels, the gutter and the threshold bar being configured to allow movement in the longitudinal direction of the first panel relative to the second panel. An aircraft including at least one such floor is also disclosed.
An aircraft propulsion system with a turbomachine having a front casing with a rear face and a rear casing, a mounting pylon with a front portion and to which a rear fitting is attached, an arch attached to the rear fitting and to the rear casing, and on each side of the vertical median plane, three port/starboard connecting rods, each connecting rod being attached between the rear face of the front casing and the arch, the three port connecting rods converging towards each other in a port convergence zone at the arch, and the three starboard connecting rods converging towards each other in a starboard convergence zone at the arch.
The present invention relates to a method and a system (1) for assisting in the piloting of an aircraft (100), which system comprises a display (10), a computer (20), and at least one item of equipment (30). The computer (20) comprises a memory (25) storing display configurations containing the features of at least one image (11) to be displayed. Each item of equipment (30) is connected to the computer (20) by a bidirectional primary data link (70) and by an at least unidirectional secondary link (80) for an external video stream (V31, V32) from the item of equipment (30) to the computer (20). The computer (20) is configured to transfer the external video stream (V31, V32), via a video link (90), to the display (10), without modification or transformation, in order to display at least one external image (12, 14) generated by the item of equipment (30) in accordance with a display configuration selected from the display configurations.
G06F 3/147 - Digital output to display device using display panels
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
6.
SANDWICH ELEMENT, MANUFACTURING METHOD AND CABIN ELEMENT
The invention discloses a sandwich element having a foam core, which has at least one cover layer on each of its mutually opposite large surfaces, wherein recesses are introduced into the one large surface of the foam core, and the at least one cover layer extending over this large surface is provided with openings, which at least partially overlap with the recesses, a production method and a cabin element.
B32B 3/26 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids
B32B 3/30 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids characterised by a layer formed with recesses or projections, e.g. grooved, ribbed
B32B 5/18 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by features of a layer containing foamed or specifically porous material
B32B 27/06 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance
B32B 27/28 - Layered products essentially comprising synthetic resin comprising copolymers of synthetic resins not wholly covered by any one of the following subgroups
7.
AIRCRAFT PROPULSION SYSTEM COMPRISING A TURBOMACHINE, A MOUNTING PYLON AND MEANS FOR ATTACHING THE TURBOMACHINE TO THE MOUNTING PYLON
An aircraft propulsion system having a turbomachine with a front casing with a rear face and a rear casing, a mounting pylon with a front portion and to which a rear fitting is attached, an arch attached to the rear fitting and to the rear casing, and on either side of the vertical median plane, two port connecting rods and two starboard connecting rods that are attached between the rear face of the front casing and the arch, the two port, respectively starboard, connecting rods converge towards each other in a starboard convergence zone at the arch, and a central connecting rod lying in the vertical median plane and attached to the rear face and to the arch.
An aircraft comprising with at least one support, at least one inflatable aerodynamic structure which has at least one aerodynamic surface, and at least one connection system connecting the aerodynamic structure and the support. The aerodynamic structure has at least one flexible wall having an outer face, and at least one inflatable cavity delimited at least partially by the flexible wall and configured to adopt an inflated state in which the cavity has a maximum volume and a deflated state in which the cavity has a volume smaller than the maximum volume, the outer face forming at least part of the aerodynamic surface when the cavity is in the inflated state.
The present invention relates to a piloting assistance method for detecting obstacles. The method comprises the following steps carried out iteratively: - for each cell of a corridor covering a space located along a current track or a current heading of the aircraft (1), the corridor being materialized by a two-dimensional grid forming cells, each cell representing a volume of space that is unlimited in altitude, determining, using an obstacle database (15), a selected point corresponding to the highest point in the obstacle database for the cell, - transmitting an altitude of each selected point and position information relating to a position of the associated cell.
A method for managing network communication between interconnected network devices in a network system by: receiving, from an application of a first network device in the network system, a request for network communication of application data related to a plurality of data objects; classifying, based on a correlation map, the data objects into one or more data sets, each data set including one or more data objects, wherein data objects from different data sets are classified uncorrelated; and establishing, for each data set, a corresponding network connection network communication between the first network device and at least one second network device in the network system, the least one second network device providing application data related to the respective data set, for receiving, by the first network device, the application data from the at least one second network device.
A method and an apparatus for compressing a neural network. Circuitry receives a neural network comprising a set of parameters being in at least one floating-point number format of a first precision. The circuitry also applies at least one mathematical model on the neural network to determine errors introduced by using arithmetic of a second precision lower than the first precision and propagation through network layers of the neural network due to using the arithmetic of the second precision instead of the first precision. The circuitry then applies a solver to an optimization problem formulated based on the errors determined by the at least one mathematical model to determine a set of optimized parameters. Finally, the circuitry compresses the neural network based on the set of optimized parameters to output a compressed neural network.
METHOD AND COMPUTER DEVICE FOR TRANSFORMING A TEXTURED MESH OF A DESIGNED OBJECT INTO A TEXTURED MESH OF A MANUFACTURED OBJECT CORRESPONDING TO SAID DESIGNED OBJECT
A method for determining a transformed textured mesh of a three-dimensional manufactured object on the basis of an initial textured mesh of a three-dimensional designed object, the transformed textured mesh to be used when printing a corresponding two-dimensional texture on the manufactured object by iteratively determining a set of affine transformations with individualized parameters to minimize the value of a target function having at least one term promoting a specific property, the set of affine transformations thus determined being applied to the vertices of the initial textured mesh so as to obtain the transformed textured mesh.
A cryogenic tank includes at least one enclosure, at least one cryogenic element located in the enclosure and at least one connecting system including at least one connecting element connecting first and second anchor points respectively rigidly attached to the enclosure and the cryogenic element directly or indirectly. The connecting element forms a thermal conduction path that has a length greater than a straight line distance separating the first and second anchor points.
A cryogenic tank with at least one enclosure containing a liquid phase and having at least one anti-sloshing structure formed from walls and positioned inside the enclosure and configured to compartmentalize the enclosure and at least one connection system connecting the anti-sloshing structure and the enclosure. Also an aircraft with at least one such tank.
A spark containment cap plate with a base and two or more spark containment caps. Each cap has a cover portion which extends from the base and defines a cavity inside the cap, inside which an end of a fastener is enclosed. Also a fastener joint with a structure; two or more fasteners, each fastener having an end protruding from a surface of the structure; and a spark containment cap plate. The plate has a base and two or more spark containment caps. Each cap has a cover portion extending from the base and defining a cavity inside the spark containment cap inside which the ends of the fasteners. A cured sealing material is provided between the cap plate and the structure which secures the cap plate to the structure in such a position that each end of each fastener is enclosed within a spark containment cap.
H01B 17/38 - Fittings, e.g. capsFastenings therefor
H01B 17/42 - Means for obtaining improved distribution of voltageProtection against arc discharges
16.
OUTER SKIN OF AN AIRCRAFT FUSELAGE OR AIRCRAFT FUSELAGE SECTION AND METHOD FOR MONITORING THE STRUCTURAL INTEGRITY OF THE OUTER SKIN OF AN AIRCRAFT FUSELAGE OR FUSELAGE SECTION
An outer skin of an aircraft fuselage or aircraft fuselage section formed from a fiber reinforced plastic, in particular carbon fiber reinforced plastics in a layered configuration, including at least two layers having electrically conductive fibers, in particular carbon fibers, placed with alternating fiber orientations within the layers and embedded in a polymer matrix material, and a coating consisting of or including magnetically active particles configured to induce a change in physical properties of the coating when exposed to a magnetic field. A method for monitoring the structural integrity of the outer skin of an aircraft fuselage or fuselage section and an aircraft having a fuselage or fuselage section provided with such an outer skin are disclosed.
A water supply system which has two pumping devices which are operated such that the respective value of an operating parameter, such as an operating pressure or an operating time, is different. Pipes connect the pumping devices to water consumers and a valve is provided to connect or disconnect the pumping devices from the piping networks. Also an aircraft with such a water supply system.
A sensor system for monitoring characteristics of a dewar tank having an inner shell and an outer shell. The system includes a sensor arrangement with a magnetic field sensor, and a permanent magnet element, and a controller. The field sensor is connected to the controller and configured to be attached to the outer shell. The magnet element is attached to the inner shell or to the outer shell. The field sensor and the magnet element, in a mounted state on the dewar tank, are located such that the field sensor is capable of detecting a magnetic field created by the magnet element. The controller is configured to measure, via the field sensor, the magnetic field of the magnet element and to infer at least one characteristic of the dewar tank based on the detected magnetic field.
F17C 13/02 - Special adaptations of indicating, measuring, or monitoring equipment
G01F 23/26 - Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water by measuring variations of capacity or inductance of capacitors or inductors arising from the presence of liquid or fluent solid material in the electric or electromagnetic fields
G01K 7/36 - Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat using magnetic elements, e.g. magnets, coils
20.
PROTECTION ARRANGMENT, ENERGY STORAGE DEVICE AND APPARATUS COMPRISING SAME
A protection arrangement, an energy storage device, in particular an electrochemical battery for an apparatus, and an apparatus, in particular, a vehicle, such as an aircraft are disclosed for protecting the energy storage device, such as an electrochemical battery in the event of a technical failure of at least one energy storage unit of the energy storage device. The protecting arrangement includes a discharging circuit with a switching device configured to reduce an electrical charging level of the at least one energy storage unit by electrically closing the discharging circuit upon detection of the technical failure.
H01M 10/42 - Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
H01M 10/48 - Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
09 - Scientific and electric apparatus and instruments
13 - Firearms; explosives
Goods & Services
Data processing apparatus, data processing systems, electronic systems, electronic apparatus, optoelectronic apparatus, software, all the aforesaid goods being for use in control and command of missiles, detection, identification, tracking and disposal of military targets. Missiles and corresponding weapon systems; missiles for naval and ground based air defence.
22.
SYSTEM AND METHOD FOR CLEANING A WASTE TANK IN AN AIRCRAFT
A system for cleaning a waste tank in an aircraft, the system comprising a service device, a spray nozzle, and a first adaptor for each spray nozzle. The service device comprises a descaling fluid tank, an outlet, an inlet and a pump in fluid communication with the outlet. The spray nozzle is coupled with the outlet or the pump through a first conduit, wherein spray nozzle ejects a jet of descaling fluid into the waste tank. The inlet is coupled with a second conduit attachable to a waste tank outlet. The first adaptor is couplable with the spray nozzle and has a fastener to attach the first adaptor to an opening of the waste tank in a substantially fluid-tight manner. The service device continuously circulates the descaling fluid through the service device outlet, the first conduit, the spray nozzle, the waste tank outlet, the second conduit and the inlet.
A transmission device having: at least first and second shafts, at least one decoupling system which has at least one first coupling sleeve which is permanently coupled in rotation with the second shaft and movable along the second shaft between a first position in which the first coupling sleeve is coupled in rotation with the first shaft and a second position in which the first coupling sleeve is not coupled in rotation with the first shaft, at least one control which comprises at least one chamber adjoining the first coupling sleeve and supplied with fluid, a variation in the volume of the chamber causing a change in position of the first coupling sleeve.
F16H 63/06 - Final output mechanisms thereforActuating means for the final output mechanisms a single final output mechanism being moved by a single final actuating mechanism the final output mechanism having an indefinite number of positions
B64D 35/021 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants
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 wing having a fixed wing with a tip, and a wing tip device rotatably mounted on a hinge at the tip of the fixed wing. The wing tip device is rotatable about the hinge. An actuation system rotates the wing tip device about the hinge. The actuation system has a motor, a plurality of geared mechanical actuators, and an angle gearbox coupled between the plurality of geared mechanical actuators and the motor. Each geared mechanical actuator is driveable by the motor and arranged to convert rotary motion into a different rotary motion. Each geared mechanical actuator is arranged along a hinge line of the hinge. The angle gearbox is arranged along the hinge line and between two of the plurality of geared mechanical actuators.
The collected information is distributed (306) between input data and output data with a view to training (308) a machine learning model in order to obtain predictions identifying which peers are most likely to transmit missing blocks and at what time. The machine learning model thus trained enables each peer to determine a scheduling of demands made by said peer on the other peers in the consensus process for the elaboration of the blockchain, according to the predictions obtained. The consensus process is therefore more efficient.
H04L 9/00 - Arrangements for secret or secure communicationsNetwork security protocols
G06N 3/006 - Artificial life, i.e. computing arrangements simulating life based on simulated virtual individual or collective life forms, e.g. social simulations or particle swarm optimisation [PSO]
09 - Scientific and electric apparatus and instruments
41 - Education, entertainment, sporting and cultural services
Goods & Services
Matériels éducatifs téléchargeables; contenus multimédias téléchargeables dans les domaines des sciences, de la technologie, de l'ingénierie, des arts et des mathématiques; contenus numériques téléchargeables. Publication de matériel éducatif dans les domaines des sciences, de la technologie, de l'ingénierie, des arts et des mathématiques; mise à disposition temporaire de matériels éducatifs en ligne non téléchargeables dans les domaines des sciences, technologie, ingénierie, arts et mathématiques; publication de matériel d'éducation interactif dans les domaines des sciences, technologie, ingénierie, arts et mathématiques; services de publication de matériel et guides pédagogiques pour l’enseignement dans les domaines des sciences, technologie, ingénierie, arts et mathématiques.
09 - Scientific and electric apparatus and instruments
35 - Advertising and business services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Software for technical and administrative support services
for operation and maintenance of satellites and their
components on the ground. Providing administrative support services to satellite
operators with regard to the operation and maintenance of
satellites and their components on the ground. Hosting of a platform comprising software for
administration, operation and maintenance of satellites and
their components on the ground; providing technical support
services to satellite operators with regard to the operation
and maintenance of satellites and their components on the
ground.
28.
Support And Carriage Assemblies For A High Lift Body Arrangement, As Well As Wing And Aircraft Comprising Same
A support assembly for a high lift body configured to be mounted to a spar of a wing of an aircraft includes a track beam configured for supporting the high lift body at the spar movably between a stowed position and a deployed position along a motion path, the track beam having a structural profile portion adapted for transferring operational loads of the high lift body into the spar, and a track profile portion supported at the structural profile portion and adapted for guiding a carriage assembly for carrying the high lift body movably along the motion path and taking up the operational loads. The structural profile portion and/or the track profile portion include a complementing profile portion. The structural profile portion, the track profile portion, and/or the complementing profile portion provide a main load path and a redundant load path configured to transfer and/or take up the operational loads.
A method for draining a water supply system onboard an aircraft which supplies water from a central water tank to consumers. Water is supplied by a supply pump from the central water tank through supply lines of a conduit system to consumers. Each consumer is associated with a supply valve for drawing water from the conduit system. The supply lines have a maximum internal diameter of 8 mm or less. The method includes closing the supply valves of all consumers, subjecting the supply lines of the conduit system at the at the supply pump to a draining pressure and sequentially opening the supply valves of all consumers for removing water from the supply lines of the conduit system. A corresponding water supply system and an aircraft are disclosed.
A method for assisting a pilot navigate an airport while taxiing an aircraft, the method comprising receiving taxi instructions for the aircraft to reach a destination from an origin, generating at least one taxi route for the aircraft to reach the destination from the origin, displaying navigation instructions corresponding to one of the at least one generated taxi route via a display device of the aircraft, and executing the navigation instructions according to the generated taxi route.
A system for detecting a cure and/or flow front in a molding apparatus. The system has a mold portion, a sensor apparatus, and a control unit. The mold portion has a molding surface configured to contact a preform to be infused with resin. The sensor apparatus is arranged within the mold portion and includes a sensor element that extends in a longitudinal direction. The sensor element is arranged to be at least partially below the molding surface into the mold portion such that the sensor element is capable of interaction with resin and/or the preform, for example, via electric fields. The control unit is configured to control the sensor element, so as to detect a cure and/or flow front based on a change in the interaction, such as the electric field, due to the flowing or curing of resin.
G01N 27/60 - Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating electrostatic variables
B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
A system and a method for surface inspection of a composite part of an aircraft with a first illumination unit positioned in front of a surface of a composite part to illuminate that surface with evenly distributed light, and a second illumination unit to illuminate the surface with light hitting the surface at an angle from different sides. Both illumination units are configured to alternately illuminate the surface. A polarization camera unit generates image data of the surface while the surface is alternately illuminated by the illumination units. A processor unit processes the image data, detects defects on the surface of the composite part, and determines the directions of fibers within the composite part from the image data.
A service management system for an aircraft. The service management system is configured to provide a passenger with a service which is closely related to content provided to the passenger on an entertainment system on the aircraft. The service may include an item that is dispensed in the galley of the aircraft, and the system may determine if the item is in stock. Also an aircraft with such a system.
An electrical connection assembly to establish a connection between the terminal elements of electrical conductors which are fitted with terminal rings and including a thermo-deformable element configured to undergo strain as a function of the temperature of the connection assembly, such that an electrical contact between two electrical contact elements is established or interrupted. It is possible to execute detection of conditions for initiation of an electric arc or the presence of a continuous or intermittent electric arc in the connection assembly, by reference to the heat-up of the thermo-deformable element associated with the initiation or the presence of an electric arc.
A power supply module aircraft, including at least an electrical connection to a first AC distribution network, an electrical connection to a second AC distribution network, a synchronization and junction module, and a power converter, the power supply module being external to an aircraft. The power converter is configured to deliver to said aircraft a DC supply voltage obtained by the synchronization and junction module from the first and second AC distribution networks. Advantageously, it is thus possible to supply electrical energy to an aeroplane parked in an area of an airport, without requiring complex logistics and without having to use its auxiliary power unit.
B64F 1/35 - Ground or aircraft-carrier-deck installations for supplying electrical power to stationary aircraft
B60R 16/03 - 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 for supply of electrical power to vehicle subsystems
H02J 3/36 - Arrangements for transfer of electric power between ac networks via a high-tension dc link
A propulsion system for an aircraft having: a nacelle which has two cowls that are movable between a closed position and an open position, for each cowl, an actuation system arranged to move that cowl from the open position to the closed position and vice versa, and for each cowl, a holding system arranged to hold that cowl in the open position.
A propulsion assembly of an aircraft comprising a turbojet engine with a front casing extending between a front face and a rear face, a mounting pylon having a primary structure with a front wall, and an engine mount having a first connecting rod and a second connecting rod, where one of the connecting rods is mounted in an articulated manner by a first connecting point on the front wall and by a second connecting point on the front casing, where the other of the connecting rods is mounted in an articulated manner by a third and a fourth connecting point on the front wall and by a fifth connecting point on the front casing, and where the connecting points are in the front third of the front casing.
A propulsion assembly of an aircraft having a longitudinal axis and a vertical median plane and including a front cowling with a rear face perpendicular to the longitudinal axis, a primary structure with a front wall, and an engine attachment including a female yoke member rigidly attached to the front wall, a male yoke member rigidly attached to the rear face and mounted and articulated in the female yolk, a pin rigidly attached to the primary structure and the axis of which is parallel to the longitudinal axis, and a housing in the rear face in which the pin is housed, and wherein the yoke members, the pin and the housing are arranged at the level of the median plane.
An aircraft propulsion assembly having a jet engine with a front casing, a primary structure with a lower spar, two outer rods, wherein each one has a rear end mounted in an articulated manner on the lower spar and a front end mounted in an articulated manner on the front casing, and two inner rods, wherein each one has a rear end mounted in an articulated manner on the lower spar and a front end mounted in an articulated manner on the front casing. Also an aircraft with such an assembly.
Aircraft high-lift device (1) of a lifting surface (2) including an upper skin (3), lower skin (4) and a nose (5), the high-lift device (1) includes: a flexible skin allowing for a morphing high-lift device (1), having a rear upper edge (7.1) and a rear lower edge (7.2), at least the rear upper edge (7.1) sliding along the chordwise direction between a retracted position and an extended position, and a linear actuator (6) connected to the nose (5) and pivotably connected to the lifting surface (2) between the retracted position and the extended position, so that in the extended position the nose (5) is located in a downward location with respect to its location in the retracted position and at least the rear upper edge (7.1) is located in an anterior location with respect to its location in the retracted position.
The invention relates to a method for transmitting data streams through a communication network, the method comprising the steps, carried out iteratively, of: - i) the control system obtaining an updated list of streams awaiting transmission; - ii) the control system obtaining at least the operational state of each node and the available bandwidth on each unidirectional link; - iii) the control system admitting streams to be transmitted according to a routing calculation, the routing calculation being triggered at least periodically or upon receipt of a stream whose priority level exceeds a determined priority level, the routing calculation favoring the highest priority streams; - iv) transmitting the streams admitted by the control system through the network.
A method and a system for inspecting the outer skin of an aircraft or a component thereof by scanning a surface of an outer skin of an aircraft with a line scan camera unit while the surface is illuminated with a first light field and with a second light field, and generating image data representing the surface while it is scanned. The image data is processed and defects of the surface and their characteristics and physical locations are automatically determined from the image data representing the surface during its illumination with the first light field and its illumination with the second light field. The defects, characteristics and physical locations are output. The first and second light fields may be formed as alternating bright field illumination and dark field illumination, or as light of a first color and light of a second color.
A method for surface inspection of a cured composite part comprising glass fibers and carbon fibers, in particular of an aircraft, by illuminating a surface of the composite part with infrared light from an IR-light source, and capturing an image of the surface. The IR-light source is arranged so generated infrared light hits the surface at a first angle α to provide a dark field illumination, and the camera is arranged to point at the surface at a second angle β to capture the image of the dark field illuminated surface. The captured image is evaluated with regard to brightness and contrast to detect one or more glass fiber layers on top of one or more carbon fiber layers within the composite part.
G01N 21/88 - Investigating the presence of flaws, defects or contamination
G01N 21/3563 - Investigating relative effect of material at wavelengths characteristic of specific elements or molecules, e.g. atomic absorption spectrometry using infrared light for analysing solidsPreparation of samples therefor
H04N 23/20 - Cameras or camera modules comprising electronic image sensorsControl thereof for generating image signals from infrared radiation only
44.
SUPERCONDUCTING MOTOR COMPRISING COILS INSULATED BY TWO VACUUM LAYERS
A superconducting motor that includes a rotor, a stator and a motor casing. The motor casing has a common chamber which has been evacuated and includes multiple sealed compartments which have also been evacuated, each sealed compartment enclosing one or more coils of the stator, such that the coil(s) in each sealed compartment is/are thermally insulated by two vacuum layers, a first vacuum layer in the sealed compartment in question and a second vacuum layer in the common chamber. Thus, any particles that could become detached from a failed coil do not damage the thermally insulating barrier of any other coil which would be accommodated in another compartment.
H02K 5/10 - Casings or enclosures characterised by the shape, form or construction thereof with arrangements for protection from ingress, e.g. of water or fingers
A load introduction system includes an aerodynamic closed box structure component including an integral closed box having an upper skin section, a lower skin section, a front spar and a rear spar, a load introduction frame, wherein the load introduction frame is arranged at least partly in circumferential direction around the integral closed box, and an attachment unit for coupling the integral closed box to a base system, wherein the attachment unit is coupled to the load introduction frame.
A method of manufacturing a composite part by providing a molding tool comprising a tool base and a tool lid, both configured to form a cavity between the tool base and the tool lid tool when the molding tool is closed. A fiber preform is placed in the tool which is tightly closed so that the fiber preform is within the cavity. A predefined clamping pressure presses the tool lid and the tool base against each other, and a resin is injected into the cavity at an injection pressure to infiltrate the fiber preform with the resin. The size of the cavity is passively increased by allowing an opening movement of the tool lid relative to the tool base and/or an elastic deformation of the tool, when the inner tool pressure is greater than the predefined clamping pressure, while keeping the cavity tightly closed.
B29C 45/14 - Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mouldApparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
A method for manufacturing a stiffened aerodynamic structure component includes: providing an aerodynamic structure component, wherein the aerodynamic structure component includes a plurality of spar elements extending spanwise within the aerodynamic structure component; wherein the plurality of spar elements is integrally formed with an upper skin section and a lower skin section, thereby providing an integrally formed aerodynamic structure component, and generating at least one chordwise reinforcement element by injecting a curable medium, preferably via at least one injection hole, in the upper skin section and/or the lower skin section.
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
B29C 45/14 - Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mouldApparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
48.
ENERGY CONVERSION ARRANGEMENT, ENERGY SYSTEM AND AIRCRAFT COMPRISING SAME
An energy conversion arrangement for an aircraft, an energy system and an aircraft comprising an energy conversion arrangement and/or an energy system are provided. The energy conversion arrangement includes a fuel conversion device, in particular a fuel cell system, configured to convert at least one fuel to electrical and/or mechanical energy, and at least one an exhaust outlet for letting out exhaust produced in the fuel conversion device by the fuel conversion, and at least one mixing assembly configured to merge a stream of further exhaust of the fuel conversion device with at least one stream of the exhaust from the at least one exhaust outlet.
B01F 25/313 - Injector mixers in conduits or tubes through which the main component flows wherein additional components are introduced in the centre of the conduit
An energy conversion arrangement for an aircraft, an energy system, a propulsion unit, and an aircraft comprising an energy conversion arrangement and/or an energy system are provided. The energy conversion arrangement includes at least one exhaust outlet for letting out exhaust produced by a fuel conversion device, in particular a fuel cell system, for converting at least one fuel to electrical and/or mechanical energy in the fuel conversion device; and at least one exhaust assembly configured to admix a stream of the exhaust from the at least one exhaust outlet with ambient air from the ambient surroundings in at least one mixing zone to promote a growth of water droplets through at least partly condensing water vapor contained in the exhaust in the mixing zone.
B64D 27/355 - Arrangements for on-board electric energy production, distribution, recovery or storage using fuel cells
B64D 37/00 - Arrangements in connection with fuel supply for power plant
H01M 8/04119 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyteHumidifying or dehumidifying
50.
METHOD AND DEVICE FOR PROVIDING STRIP MATERIAL FOR MANUFACTURING COMPONENTS FOR VEHICLES, AS WELL AS CORRESPONDING COMPONENT AND VEHICLE WITH SAME
A method and a supply device for providing composite strip material, in particular for the manufacture of components for vehicles, such as aircraft, as well as a corresponding component and vehicle, in particular aircraft, wherein a continuous material feed of the strip material for manufacturing the components includes at least two material portions which are supplied in the course of the continuous material feed.
A leading edge high lift assembly (11) having a slat (13) and a connection assembly (15) movably connecting the slat (13) to a main wing (9). The connection assembly (15) includes an elongate slat track (27) between a first end (31) and a second end (33). The slat track (27) is mounted to the main wing (9) by a roller bearing (37) and mounted to the slat (13) via a link arrangement (39) having a first link element (41) mounted to the slat (13) and to the slat track (27). A recess (59) in the slat track opens to a side of the slat track (27). The first link element (41) extends through the recess (59).
A power supply system, of an aircraft, configured to supply electrical energy to on-board electrical devices including at least an electrical sub-circuit of the high-voltage DC type, an electrical sub-circuit of the low-voltage AC type, and an electrical sub-circuit of the low-voltage DC type. The system additionally including a high-voltage battery switching circuit, the system being such that every power supply line of said low-voltage DC sub-circuit, which power supply line is independent of said switching circuit, has no low-voltage battery. Advantageously, it is thus possible to avoid battery redundancy that is detrimental to the weight of the aircraft and leads to its electrical system being complex.
Aircraft section and aircraft with additional seat belt The present disclosure relates to an aircraft section (100) and an aircraft with an additional seat belt, the belt reel of which is attached to a primary structure assembly and is guided through a side panel element 130 into a passenger cabin of the aircraft section.
The invention relates to an electric flight control system (5) for controlling an aircraft (1). The flight control system (5) comprises a plurality of functional subassemblies (95), each having at least one primary computer (35) 5 and at least one secondary computer (36), which are dissimilar; at least one functional subassembly (95) being a simplex/duplex subassembly (96) comprising at least three identical simplex primary computers (41, 42, 43) and at least one duplex secondary computer (44, 45), each duplex secondary computer 10 (44, 45) in a simplex/duplex subassembly (96) comprising a computer-controlled flight control mode (46) and a monitoring mode (47), which are independent and synchronized, each simplex primary computer (41, 42, 43) in a simplex/duplex subassembly (96) having a single computation mode, and inasmuch as, 15 barring a breakdown, the three primary computers (41, 42, 43) in a simplex/duplex subassembly (96) form two virtual pseudo-duplex computers.
The invention relates to a fly-by-wire flight control system (10) comprising an actuating subassembly (C) having three external duplex calculators (21, 24, 27) for controlling an electrical actuator (40). The electrical actuator (40) has three stators (42, 43, 44) electrically connected to three respective tilting assemblies (50) being electrically connected to a same internal simplex calculator (80) of the electrical actuator (40), each tilting assembly (50) being connected to one of the respective external duplex calculators (21, 24, 27), each tilting assembly (50) being configured to connect to the associated stator (42, 43, 44), the internal simplex calculator (80) or the respective external duplex calculator (21, 24, 27), the internal simplex calculator (80) being self-monitored and communicating with the three external duplex calculators (21, 24, 27).
B64C 13/50 - Transmitting means with power amplification using electrical energy
B64C 27/58 - Transmitting means, e.g. interrelated with initiating means or means acting on blades
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
B64D 31/00 - Power plant control systemsArrangement of power plant control systems in aircraft
56.
PROCEDE D’ENTRAINEMENT À LA PANNE MOTEUR SUR UN GIRAVION MONOMOTEUR
La présente invention concerne un procédé de simulation d'une panne d'un moteur à combustion d'un giravion monomoteur, le giravion comprenant un contrôleur pilotant le moteur à combustion. Le procédé comporte : i) l'armement d'un mode école en manœuvrant un bouton d'armement en communication avec le contrôleur, le mode école ne pouvant pas être activé en l'absence dudit armement du mode école, ii) sous réserve dudit armement, activation du mode école en manœuvrant un bouton d'activation qui est en communication avec le contrôleur, le contrôleur pilotant en conséquence une décélération du moteur à combustion pour atteindre le régime de ralenti, iii) désactivation du mode école en manœuvrant à nouveau le bouton d'activation, le contrôleur pilotant en conséquence une accélération du moteur à combustion pour atteindre un régime de vol, le mode école ne pouvant être réinitialisé que lors d'une nouvelle phase de simulation.
B64D 31/09 - Initiating means actuated automatically in response to power plant failure
G09B 9/08 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
G09B 9/44 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer providing simulation in a real aircraft flying through the atmosphere without restriction of its path
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
57.
FLIGHT CONTROL SYSTEM HAVING AN ELECTRIC ACTUATOR FOR CONTROLLING A HYDRAULIC SERVO CONTROL
An electric flight control system comprising an actuation subassembly, having three external duplex computers for controlling an electric actuator. The electric actuator has three stators electrically connected to three respective switching devices, the switching devices being electrically connected to a same internal simplex computer of the electric actuator, each switching device being connected to a respective external duplex computers, each switching device being configured to connect the internal simplex computer or respective external duplex computer to the associated stator, the internal simplex computer being self-monitored and communicating with the three external duplex computers.
An electrical flight control system for controlling an aircraft. The flight control system comprises a plurality of functional subassemblies each having at least one primary computer and at least one dissimilar secondary computer, at least one functional subassembly being a simplex/duplex subassembly comprising at least three identical simplex primary computers and at least one duplex secondary computer, each duplex secondary computer of a simplex/duplex subassembly comprising an independent and synchronized control calculation channel and a monitoring calculation channel, each simplex primary computer of a simplex/duplex subassembly having a single calculation channel, and wherein, except in the event of failure, the three primary computers of a simplex/duplex subassembly form two virtual pseudo-duplex computers.
A method of indicating a position of a flaw in a part including holding a probe by hand in contact with a surface of the part with a probe; detecting a flaw in the part by emitting ultrasound from the probe into the surface of the part and detecting echoes of the ultrasound from the flaw; providing an indicator on the surface of the part indicating a detection position of the probe; after the indicator has been provided, removing the probe by hand from the surface of the part, leaving the indicator in place; and after the probe has been removed from the surface of the part, providing a flaw marker on the surface of the part indicating an estimated position of the flaw.
An aircraft fuselage for releasing a fuel tank from inside the aircraft fuselage in case of emergency includes an outer structure, a mounting device to releasably secure a fuel tank in an inside of the outer structure, and an openable release door which separates the inside from an outside of the outer structure, wherein the release door is positioned in relation to the mounting device such that the fuel tank is released through the release door when the mounting device releases the fuel tank. A method is disclosed for releasing a fuel tank from inside the aircraft fuselage in case of emergency as well as an aircraft comprising such an aircraft fuselage.
A device for equipping and fitting out fuselage barrels of an aircraft fuselage includes a support structure that carries an assembly platform, the assembly platform including at least one load support and including a frame and at least one actuator rail connected to the frame, wherein at least one actuator carriage can be movably arranged on each of the actuator rails, and wherein the load support is designed to be coupled to a support structure provided on the aircraft fuselage and/or a load introduction point in order to support the assembly platform relative to the aircraft fuselage.
A protective device for aircraft window units includes a frame unit, multi-part and closable protective unit in the frame unit, at least one pretensionable movement unit on the protective unit to transfer the protective unit from at least one open position state into a closed position state, and a triggering unit coupled to the at least one movement unit via at least one coupling region of the at least one movement unit. When the protective device is in an installed state in an aircraft window unit, the triggering unit is between an exterior window unit of the aircraft window unit and the frame unit, such that mechanical forces acting on the exterior window unit can be transmitted to the triggering unit for triggering operation at the at least one movement unit. A protective device system for aircraft, and an aircraft are disclosed.
Protection for an aircraft fuselage being as light as possible and which is easily integrated into the fuselage is provided as a protective insert for an aircraft tail area. The protective insert has a protective panel, an absorption body supporting the protective panel, and a force transmission device holding the absorption body. The protective panel is configured for pressure-loaded sliding contact with a runway during a tail impact. The protective panel transfers compressive force acting during the tail impact to the absorption body. The absorption body is configured to absorb the compressive force in a force-damping manner, wherein part of the energy due to the acting compressive force is convertible into an elastic and/or plastic deformation of at least a part of the absorption body. The force transmission device holds the protective insert on the underside of the tail area of an aircraft via a plurality of fastening areas.
An aircraft section and an aircraft with an additional seat belt, the belt reel of which is attached to a primary structure assembly of frames and stringers for the aircraft section. The seat belt is guided through an opening in a side panel element into a passenger cabin of the aircraft section.
A propulsion system for an aircraft having a jet engine with a front casing with a rear face and a rear casing, a mounting pylon with a front portion and a lower spar to which a rear fitting is attached, a front engine mount attached between the front casing and the front portion, an arch with a base attached to the rear fitting and two arms, each having a first end secured to the base and a second end attached to the rear casing, two upper bars hinged to the rear face and to the arch, and two lower bars hinged to the rear face and to the arch, the two upper bars being rigidly attached to each other.
A method for detecting the presence of ice on an aircraft, including: obtaining, in real time, measurements (provided by sensors) of a set of flight parameters comprising a slope, an incidence, a Mach number, a rotational speed of a low-pressure propulsion engine assembly of the aircraft, a fuel flow, a mass of the aircraft, a position of a trimmable horizontal stabilizer, a static temperature and a static pressure; injecting the obtained measurements into an artificial-intelligence model, trained and configured to calculate a presence of ice indicator based on measurements of the set of flight parameters; and providing the presence of ice indicator calculated by the model. This novel indirect method exhibits good performance because it is based on an artificial-intelligence model using a large number of flight parameters.
A heat transfer device for an aircraft providing heat to the fuel of a fuel conduct, a conditioning system having the heat transfer device, an aircraft including the heat transfer device of the fuel conditioning system, and a method for conditioning fuel of an aircraft. The fuel conduct includes a first end and a second end, in which the first end is connected in fluidic communication to the first inlet of the heat transfer device and the second end is connected in fluidic communication to the first outlet of the heat transfer device.
An inerting system, for instance an aircraft enclosure inerting system, is configured to separate an inlet air flow into nitrogen enriched air (NEA) and oxygen enriched air (OEA). The inerting system has a vortex tube with a vortex chamber in which the inlet air flow is separated into the NEA and the OEA. The inlet air flow enters the vortex chamber through an inlet passage which intersects the vortex chamber at a chamber inlet aperture. A warming device of the inerting system warms the inlet passage or the inlet air flow before the inlet air flow gets to the chamber inlet aperture.
B01D 53/24 - Separation of gases or vapoursRecovering vapours of volatile solvents from gasesChemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases or aerosols by centrifugal force
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
B64D 37/32 - Safety measures not otherwise provided for, e.g. preventing explosive conditions
A fuel mixing assembly is disclosed including a fuel vessel, such as a pipe for conveying flow of a first fuel, and a second-fuel conduit for conveying flow of, for example an additive, into the fuel vessel. The fuel mixing assembly further includes a vortex generator, the vortex generator is configured to generate vortices to mix the first fuel and the additive. The additive may be released from an outlet in the vortex generator.
B64D 37/00 - Arrangements in connection with fuel supply for power plant
B01F 23/40 - Mixing liquids with liquidsEmulsifying
B01F 23/451 - Mixing liquids with liquidsEmulsifying using flow mixing by injecting one liquid into another
B01F 25/10 - Mixing by creating a vortex flow, e.g. by tangential introduction of flow components
B01F 25/313 - Injector mixers in conduits or tubes through which the main component flows wherein additional components are introduced in the centre of the conduit
An aircraft maintenance system, method, and computer-readable storage medium are disclosed. The aircraft maintenance system includes a processor and a storage having a digital twin of at least part of an aircraft and a machine learning classifier. The aircraft maintenance system is configured to obtain aircraft operational data, update the digital twin based on the aircraft operational data, identify an altered operation of the aircraft based on the aircraft operational data, and determine a set of conditions responsible for the altered operation using the machine learning classifier to evaluate the digital twin. Output data indicative of the set of conditions responsible for the altered operation is generated.
B64F 5/60 - Testing or inspecting aircraft components or systems
G06Q 10/20 - Administration of product repair or maintenance
G07C 5/00 - Registering or indicating the working of vehicles
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
A method of securing a first structure to a second structure is disclosed including providing a jig assembly having spark containment caps carried by a jig; mounting the jig assembly on a structure so that the spark containment caps and the jig contact the first structure; securing the spark containment caps to the first structure by injecting adhesive material into contact with the first structure and the spark containment caps and then curing the adhesive material; removing the jig after the adhesive material has cured; and securing the first structure to the second structure with fasteners, each fastener having a tail which is inserted through the first and second structures and into a respective one of the spark containment caps.
A method for simulating a failure of a combustion engine of a single-engine rotorcraft, the rotorcraft comprising a controller controlling the combustion engine. The method comprises: i) arming a training mode by operating an arming button in communication with the controller, the training mode not being able to be activated in the absence of the arming of the training mode; ii) subject to the arming, activating the training mode by operating an activation button that is in communication with the controller, the controller consequently controlling a deceleration of the combustion engine to reach the idling speed; iii) deactivating the training mode by operating the activation button again, the controller consequently controlling an acceleration of the combustion engine to reach a flight speed, the training mode being able to be reset only during a new simulation phase.
G09B 9/08 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
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
73.
ELECTRICAL FLIGHT CONTROL SYSTEM FOR CONTROLLING AN AIRCRAFT AND ASSOCIATED AIRCRAFT
An electrical flight control system for controlling an aircraft, the flight control system comprising at least one subassembly for acquiring a piloting command in order to acquire the piloting command from an operation of an associated piloting member that can be operated by a pilot of the aircraft along at least one piloting axis, the flight control system comprising at least three position sensors per piloting axis generating position information of the piloting member and being in communication with the at least one acquisition subassembly. Each acquisition subassembly comprises at least three simplex computers each having a single calculation channel connected to one of the at least three position sensors.
A kinematics assembly for a high lift body, in particular a droop nose or leading-edge-slat, configured to be mounted to a main body of a wing of an aircraft, a corresponding support station for supporting the high lift body, and a high lift body arrangement includes an actuation organ providing a drive mounting point configured to mount the kinematics assembly to a drive organ for moving the high lift body with respect to the main body between a stowed position and a deployed position, and a deflection organ configured to be connected to the actuation organ and providing a central hinge point for hinging the high lift body at the main body movably between the stowed position and the deployed position; wherein, at least in the stowed position, the drive mounting point is located aft of the central hinge point with respect to a travel direction of the aircraft.
An electric power generation system for an aircraft and its emergency power solutions are disclosed. The electric power network includes the electric power generation system, and an aircraft including the electric power generation system.
H02J 9/06 - Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over
An enclosure device configured to enclose a concave surface portion of an aerodynamic component of an aircraft wing is disclosed including an aerodynamic component having an enclosure device, and an aircraft wing and aircraft including one or more enclosure devices. Also disclosed is a method of counteracting unwanted airflow circulation in a concave surface portion of an aerodynamic component of an aircraft wing.
A hinge arrangement for an aircraft wing is provided, for providing a folding wingtip. The hinge arrangement comprises a first mount for securing in a first wing section and a second mount for securing to a second relatively foldable wing section, each having a plurality of hinge elements arranged along a hinge axis. The arrangement comprises a latching arrangement for securing the mounts against folding movement, the latch arrangement having a latch axis being spaced from the hinge axis in a substantially spanwise direction for example so as to extend into the wing box. This can provide an efficient arrangement which may be contained within the outer mould line of the wing which can reduce the need for a fairing.
A rotorcraft having a main rotor with at least one main rotor actuator; a series actuator arranged upstream of the main rotor actuator; engines for powering the main rotor; and a flight control system for controlling flight operation in an AEO mode or in an AFR mode, comprising: a control logic for pre-conditioning the series actuator upon entering the AFR mode for enabling rotorcraft control upon occurrence of an IFSD, wherein pre-conditioning of the series actuator comprises shifting a reduced nominal stroke range authorized for the series actuator stroke of the series actuator in the AEO mode into a reduced shifted stroke range authorized for the series actuator stroke of the series actuator in the AFR mode to enable authorization of an increased stroke range upon occurrence of an IFSD to provide sufficient control authority for a recovery maneuver.
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 27/58 - Transmitting means, e.g. interrelated with initiating means or means acting on blades
37 - Construction and mining; installation and repair services
40 - Treatment of materials; recycling, air and water treatment,
Goods & Services
Paints; varnishes; lacquers; primers; coatings [paints];
paints for vehicles; dyes, colorants, pigments; printing
inks; pigments for printing; lacquers for printing ink;
anti-corrosive coatings [paints]; coatings (paints) for
exterior surfaces of motor vehicles; products for treating
metal surfaces to make them resistant to tarnishing;
products used as waterproofing coatings for structural
surfaces [paints]; protective coatings for spraying on
metals [paints]. Painting services; decorative painting services; painting of
aircraft; painting of vehicles; paint spraying services;
consultant services in relation to painting of vehicles;
sand cleaning services; buffing and polishing services;
repair, maintenance, overhaul, dismantling, reconditioning,
cleaning and varnishing of vehicles and their parts;
application of base coat on vehicles; inspection of aircraft
and parts thereof prior to maintenance and repair; repair
and finishing of air vehicle bodies for third parties. Inkjet printing services; printing services; digital
printing; digital printing services; direct-to-shape
printing services.
80.
METHOD AND SYSTEM FOR CONTROLLING AN AIRCRAFT DISPLAY
A control system for controlling a display, comprising a palm rest provided with a support face configured to receive a palm of a hand of an operator, two lateral faces situated on either side of the palm rest, and a front face. The control system also comprises four controls, namely a wheel projecting from one of the lateral faces, moveable relative to the palm rest along three non-coplanar axes, a push-button, a rotary ring positioned on the front face and able to rotate relative to the palm rest, a trackball, arranged at the center of the rotary ring and able to rotate relative to the palm rest about two complementary axes. Finally, the control system comprises a computer configured to generate control commands to control the display as a function of the actions on the four controls.
B64D 43/00 - Arrangements or adaptations of instruments
G06F 3/01 - Input arrangements or combined input and output arrangements for interaction between user and computer
G06F 3/02 - Input arrangements using manually operated switches, e.g. using keyboards or dials
G06F 3/03 - Arrangements for converting the position or the displacement of a member into a coded form
G06F 3/0354 - Pointing devices displaced or positioned by the userAccessories therefor with detection of 2D relative movements between the device, or an operating part thereof, and a plane or surface, e.g. 2D mice, trackballs, pens or pucks
G06F 3/04842 - Selection of displayed objects or displayed text elements
G06F 3/04845 - Interaction techniques based on graphical user interfaces [GUI] for the control of specific functions or operations, e.g. selecting or manipulating an object, an image or a displayed text element, setting a parameter value or selecting a range for image manipulation, e.g. dragging, rotation, expansion or change of colour
81.
METHOD FOR DETECTING OBSTACLES WITH A LIDAR OBSTACLE SENSOR SYSTEM FOR A ROTARY-WING AIRCRAFT
A method of detecting obstacles with an aircraft having at least one rotary wing. Said method comprises: i) acquiring a point cloud detected using at least one LIDAR obstacle sensing device; ii) positioning each detected point in an orthonormal reference frame attached to the aircraft having a first axis coincident with an axis of rotation of the rotary wing; iii) dividing the surrounding space into volumetric units, the detected point or points present in the same volumetric unit being all replaced by a representative point; iv) segmenting the ground; v) determining the presence or absence of at least one obstacle based on the distinct representative points of the ground; and displaying, on a display, a symbology illustrating said obstacle with respect to the aircraft.
An air supply module for a system for producing electrical energy comprising a fuel cell, including a housing which has an inlet orifice and an outlet orifice and through which an air flow flows. The module includes, accommodated in the housing, a first filter and a first heat exchanger which are in direct fluidic communication with one another.
A system includes a flight management system and anticollision system installed on board an aircraft, and a transponder installed in a predefined position at an airport and linked to a computer of an air traffic control center. The transponder is configured to receive environmental information transmitted by the computer. The anticollision system is configured to interrogate the transponder, to receive, in response, the environmental information and to determine a position of the transponder. One of the anticollision system or the flight management system is configured to compare the position of the transponder determined by the anticollision system with a theoretical position saved on board the aircraft to authenticate the environmental information received only if the determined position corresponds to the theoretical position. The flight management system is configured to order an aircraft flight trajectory as a function of the environmental information received when it is authenticated.
A curved pipe segment for transporting a cryogenic fluid is elongated along a curved axial direction and comprises: an outer curved tube, comprising a first outer end and a second outer end; an inner curved tube comprising a first inner end and a second inner end; a first end portion, connected to the first outer end; and a second end portion, connected to the second outer end. The curved pipe segment comprises: a first connection element guiding the first inner end along the axial direction; a second connection element guiding the second inner end along the axial direction; and an intermediate guiding element blocking axial movement of the inner curved tube relative to the outer curved tube.
F16L 59/22 - Arrangements specially adapted to local requirements at flanges, junctions, valves, or the like adapted for bends
F17D 1/08 - Pipe-line systems for liquids or viscous products
85.
METHOD, CONTROL PROGRAM, COMPUTER-READABLE DATA CARRIER AND CONTROL DEVICE FOR CONTROLLING A FUEL CELL ARRANGEMENT, AS WELL AS FUEL CELL ARRANGEMENT AND VEHICLE COMPRISING SAME
A method for operating a fuel cell arrangement of a fuel cell system of a vehicle, such as an aircraft, a control program for controlling a fuel cell arrangement, a fuel cell arrangement and a vehicle, in particular aircraft, including a fuel cell arrangement, are disclosed. The method includes acquiring at least one reaction temperature value representing a reaction temperature at which a conversion of fuel, such as hydrogen, takes place within the fuel cell arrangement, acquiring at least one system temperature value representing a system temperature of the fuel cell arrangement, monitoring a temperature difference between the at least one reaction temperature value and the at least one system temperature value, and initiating at least one fuel starvation damage counter measure for avoiding a local fuel starvation state of the fuel cell arrangement if the temperature difference indicates a fuel starvation probability.
A slat cove filling device for a slat of an aircraft is disclosed including a sheltering panel extending along a spanwise direction (Y) and comprising a proximal edge (50), configured for being fastened to a slat body of the slat, and a distal edge, configured for being slidable relative to the slat body. The sheltering panel includes guiding passages, each guiding passage being configured for cooperating with a guiding element of the slat body for guiding the distal edge along a sliding direction (S) relative to the slat body.
A cable holder including a first disk which has first seats each configured to receive a first cable, at least one second disk which can pivot relative to the first disk between first and second angular positions, this second disk being configured to allow the first cables to be inserted into the first seats in the first angular position and to prevent the first cables from coming out of the first seats in the second angular position. An electrical installation including at least one such cable holder and an aircraft including at least one such electrical installation are also provided.
A method and system for automatic determination of a real relative mechanical play between at least two actuators of a control surface of an aircraft includes executing a position control loop to control position of the at least two actuators, during at least one predetermined measurement period collecting first data and second data, determining from the first data a theoretical relative movement with no mechanical play between the at least two actuators, and determining from the second data and the theoretical relative movement a real relative mechanical play between the at least two actuators, and if the real relative mechanical play is above or equal to a predetermined threshold, sending an alert message. The disclosure enables a considerable reduction in the time taken to diagnose real mechanical play in control surfaces of the aircraft.
An assembly of an engine mounting pylon with an aircraft engine, by virtue of a front engine mount rigidly secured to an aircraft primary structure, including a body partially fitted into the primary structure. The body includes, on its front face, a first and second pair of branches. The branches of the two pairs all extend forwards and parallel to the median vertical plane. The body includes a lower face facing the engine and a stud located in the vertical median plane and articulated to the engine, a two-point straight shackle, inserted between the branches of the first pair of branches, being articulated, at one location, to the body via a first pivot pin and, at another location, to the engine via a second pivot pin. Each of the branches of the second pair of branches are articulated to the engine via the second pivot pin.
A method for surveillance of an estimate of the gross mass of an aircraft includes: obtaining or calculating a first estimate of the gross mass resulting from an addition of an estimate of a fuel onboard mass of the aircraft and a zero fuel mass estimate and an estimate of a fuel onboard mass of the aircraft; obtaining or calculating a second estimate of the gross mass of the aircraft using a first digital (aerodynamic) model of the aircraft; calculating for a calculation cycle of rank of a plurality of successive calculation cycles executed during a phase of acceleration of the aircraft when it takes off a third estimate of the gross mass using a second digital model of a different aircraft; and when a difference between the first and second estimates above a predetermined difference threshold validating one and invaliding the other as a function of the third estimate.
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
A composite part for a vehicle is provided. The composite part has a first surface and an opposing second surface, wherein at least part of the first surface forms an outer aerodynamic surface of a vehicle. A region of the composite part has a curvature in two orthogonal directions. The composite part has an undulation defining a channel in one of the first surface or the second surface, and a corresponding ridge in the other of the first surface and the second surface.
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
A method for assisting in the operational decision-making of an aircraft is executed by three computers during a current mission. The first computer automatically determines, as a function of fault information, a technical status of the aircraft and of a minimum equipment list, one or more affected MEL items and, for each item, one or more applicable dispatch conditions. The second computer automatically determines, as a function of the previous items provided by the first computer and of a set of future missions to be distributed among a fleet of aircraft, a proposed scenario (including, in the case of dispatch under one or more MEL items, a selection of dispatch conditions for each affected MEL item). The third computer receives a decision from the pilot to accept or refuse the proposed scenario and, in the event of acceptance, triggers completion of some tasks in the aircraft and updates the logbook.
G06Q 10/20 - Administration of product repair or maintenance
G07C 5/00 - Registering or indicating the working of vehicles
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
93.
HEATED LEADING EDGE STRUCTURE FOR AN AIRCRAFT, ASSOCIATED SLAT, WING AND AIRCRAFT
A heated leading edge structure (14) for an aircraft (10) including a leading edge panel (20) having an outer surface (32) configured to contact an ambient flow (A), and an inner surface (34) opposite the outer surface (32); a reinforcing member (22) connected to the inner surface (34) of the leading edge panel (20), and a heating arrangement (24) configured to heat the leading edge panel (20); wherein the heating arrangement (24) includes an indirect heating device (44) mounted on the reinforcing member (22) and configured to heat the leading edge panel (20) by conduction through the reinforcing member (22).
A device for protecting a hydrogen tank, in particular for an aircraft, comprising an external envelope delimiting an internal volume, and an extinguishing agent, preferably in the gas phase, in the internal volume, the external envelope being provided with at least one pressure relief valve, to release the at least one extinguishing agent when a pressure prevailing in the internal volume is greater than a threshold value, and the external envelope being shaped to be installed in a fuselage of the aircraft.
A method for automatically inspecting a surface of a solid object such as, for example, a surface of an aircraft; the method employs a step of detecting a defect in said surface represented in the form of an image that is also a depth map, analyses of successive depth profiles aiming to determine a depth for each of said depth profiles, then determines a “final” depth of a defect based on all the depths of said profiles. The invention further relates to a system configured to execute the method. Advantageously, it is thus possible to automatically determine the depth of non-planarities in a surface of an aircraft with a level of accuracy not previously reached.
An aircraft that includes a floor, a tank and a connection between the tank to the floor. The connection include guide rails fixed to the floor, a cradle with guide grooves cooperating with the guide rails, two rear links articulated between the cradle and the tank, two front links fixed to the cradle and articulated on the tank, a lateral link articulated between the cradle and a lower part of the tank, and two intermediate links articulated between the cradle and the tank.
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29K 105/00 - Condition, form or state of moulded material
Described is a method for controlling a cluster of gyroscopic actuators of a satellite, the cluster being divided into two coplanar subsets, the method comprising: - receiving a setpoint angular momentum; - determining an angular momentum to be provided by each coplanar subset (Formula I) on the basis of a distribution parameter for distributing, between the two subsets, a component of the setpoint angular momentum along an axis (Formula II) common to both planes, r being a scalar between the lowest allowable value and the highest allowable value of the contribution of one of the coplanar subsets to the component of the setpoint angular momentum along the axis common to both planes; - determining an inclination angle value of each gyroscopic actuator of a subset, on the basis of the angular momentum to be provided by the subset; and - issuing a command for each gyroscopic actuator comprising the respective determined inclination angle value.
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
41 - Education, entertainment, sporting and cultural services
Goods & Services
Avionic instruments, equipment and systems related thereto for unmanned aerial vehicles (UAVs); measuring apparatus and instruments for unmanned aerial vehicles (UAVs); apparatus and instruments for recording, transmitting, reproducing or processing sound, images or data for unmanned aerial vehicles (UAVs); sensors for unmanned aerial vehicles (UAVs); computer hardware for unmanned aerial vehicles (UAVs); data processing equipment for unmanned aerial vehicles (UAVs); electronic data recorders for unmanned aerial vehicles (UAVs); telecommunications apparatus for unmanned aerial vehicles (UAVs); aerials for unmanned aerial vehicles (UAVs); optical apparatus and instruments for unmanned aerial vehicles (UAVs); cameras for unmanned aerial vehicles (UAVs); batteries, electric, for unmanned aerial vehicles (UAVs); computer software for operating, piloting and managing unmanned aerial vehicles (UAVs); remote control apparatus for operating and piloting unmanned aerial vehicles (UAVs); head-mounted video displays for use with unmanned aerial vehicles (UAVs); ground control stations for the remote operation and control of unmanned aerial vehicles (UAVs); ground control stations for the remote operation and control of unmanned aerial vehicles (UAVs) consisting of computer hardware, video screens, controllers, modems and aerials; simulation software for the operation and piloting of unmanned aerial vehicles (UAVs); training simulators for the operation and piloting of unmanned aerial vehicles (UAVs); electronic downloadable publications, namely, manuals for the operation, piloting, maintenance and repair of unmanned aerial vehicles (UAVs); electronic publications, namely, manuals for the operation, piloting, maintenance and repair of unmanned aerial vehicles (UAVs), recorded on computer media. Unmanned aerial vehicles (UAVs); structural parts for unmanned aerial vehicles (UAVs). Maintenance and repair of unmanned aerial vehicles (UAVs). Training services relating to the operation, piloting, maintenance and repair of unmanned aerial vehicles (UAVs).
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
41 - Education, entertainment, sporting and cultural services
Goods & Services
Avionic instruments, equipment and systems related thereto for unmanned aerial vehicles (UAVs); measuring apparatus and instruments for unmanned aerial vehicles (UAVs); apparatus and instruments for recording, transmitting, reproducing or processing sound, images or data for unmanned aerial vehicles (UAVs); sensors for unmanned aerial vehicles (UAVs); computer hardware for unmanned aerial vehicles (UAVs); data processing equipment for unmanned aerial vehicles (UAVs); electronic data recorders for unmanned aerial vehicles (UAVs); telecommunications apparatus for unmanned aerial vehicles (UAVs); aerials for unmanned aerial vehicles (UAVs); optical apparatus and instruments for unmanned aerial vehicles (UAVs); cameras for unmanned aerial vehicles (UAVs); batteries, electric, for unmanned aerial vehicles (UAVs); computer software for operating, piloting and managing unmanned aerial vehicles (UAVs); remote control apparatus for operating and piloting unmanned aerial vehicles (UAVs); head-mounted video displays for use with unmanned aerial vehicles (UAVs); ground control stations for the remote operation and control of unmanned aerial vehicles (UAVs); ground control stations for the remote operation and control of unmanned aerial vehicles (UAVs) consisting of computer hardware, video screens, controllers, modems and aerials; simulation software for the operation and piloting of unmanned aerial vehicles (UAVs); training simulators for the operation and piloting of unmanned aerial vehicles (UAVs); electronic downloadable publications, namely, manuals for the operation, piloting, maintenance and repair of unmanned aerial vehicles (UAVs); electronic publications, namely, manuals for the operation, piloting, maintenance and repair of unmanned aerial vehicles (UAVs), recorded on computer media. Unmanned aerial vehicles (UAVs); structural parts for unmanned aerial vehicles (UAVs). Maintenance and repair of unmanned aerial vehicles (UAVs). Training services relating to the operation, piloting, maintenance and repair of unmanned aerial vehicles (UAVs).
