A method for automatically guiding an aircraft includes receiving an ATIS message and decoding the content of the ATIS message. If the decoded content of the ATIS message includes a parameter relating to an active landing runway, the method includes creating a message requesting confirmation of the decoded content and commanding the sending of the message over a communication frequency with air traffic control, receiving a response from air traffic control and decoding the response to determine whether or not the response is a confirmation of the decoded content of the ATIS message. If the response is a confirmation of the decoded content of the ATIS message, the method includes determining a contingency trajectory of the aircraft at least partially in consideration of the decoded content of the ATIS message. The method also includes automatically guiding the aircraft along the determined contingency trajectory.
A module for an aircraft, the module comprising a sealed housing comprising walls delimiting an interior volume, a processing system intended to process dihydrogen fixed on the inside of the sealed housing and filling elements filling at least in part the interior volume around the processing system. The filling elements may be foam or beads. Also an aircraft with such a module.
A nacelle comprising a cowl which has a window, a box structure around the window and containing a conditioning device for conditioning dihydrogen, a door mounted pivotably on the cowl between a closed position and an open position, a maneuvering system for moving the door from the closed position to the open position, a detector for detecting the presence of dihydrogen in the box structure, and a control unit designed to make the maneuvering system open on the basis of information supplied by the detector.
ASSEMBLY COMPRISING AT LEAST ONE CONNECTING ELEMENT AND AT LEAST TWO CONTACT SURFACES PROVIDED WITH ASPERITIES, AIRCRAFT COMPRISING AT LEAST ONE SUCH ASSEMBLY
An assembly comprising at least first and second components, at least one connection element comprising a rod configured to ensure uptake of the traction/compression forces between the first and second components, and at least one pair of first and second contact surfaces provided respectively with first and second bumps and rigidly secured respectively to the first and second components, the first and second bumps having complementary shapes configured to nest in one another and ensure transmission of the shear forces between the first and second components. Also, an aircraft comprising at least one such assembly.
A method for monitoring an engine of an aircraft supplied with dihydrogen, comprising a safety device including a safety valve that is movable between an open position in which the engine is supplied with dihydrogen and a closed position in which the engine is no longer supplied with dihydrogen, an engine fire detection system, a dihydrogen leak detection system and an engine damage detection system, and comprising electronic circuitry adapted to implement the monitoring method. If a locking authorization is given and if one out of three conditions A, B and C is true, then the safety device closes the safety valve, with: the condition A is true if an engine fire detection system detects a fire, the condition B is true if a dihydrogen leak detection system detects a dihydrogen leak, and the condition C is true if an engine damage detection system detects engine damage.
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 2/04 - Removing or cutting-off the supply of inflammable material
A62C 3/08 - Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles in aircraft
A propulsion assembly having a combustion chamber and a turbine, a nacelle with a front cowl facing the turbine, with a window passing through it, and a rear cowl to the rear of the turbine, a fire barrier between the front cowl and the rear cowl, a dihydrogen supply pipe meandering from the inside of the rear cowl, then in a sealed manner through the fire barrier, then through the window as far as the combustion chamber, wherein the supply pipe has an intermediate section between the fire barrier and the window, and a plate fastened in a sealed manner to the intermediate section and fastened in a sealed manner to the front cowl around the window.
A conditioning system for an aircraft having a pressure accumulator connected to the heat recovery circuit and to the fuel conduct. A fluid of the fuel conduct is hydrogen (H2), or the working fluid of the heat recovery circuit comprises Nitrogen (N2), Helium (He), ethylene glycol water (EGW), and mixtures thereof, or both. Also an aircraft comprising such a conditioning system.
The invention relates to a method for ejecting a stack (2) of satellites contained in a launcher (1), wherein each stage of the stack comprises at least two satellites arranged around a central geometric axis (A-A) of the stack, and wherein the satellites of one of the stages, with the exception of the first stage, are stacked on top of the satellites of the preceding stage, so as to simultaneously eject the stack of satellites while minimising the risk of collision, in the long term, between the satellites. The invention also relates to a space system for ejecting a stack of satellites, for implementing this method.
An aircraft ground anti-collision system and method is disclosed including multiple sensors including an on-board sensor and an off-board sensor, and an obstacle detection processing unit, which is configured to: process data received from the multiple sensors to detect an object around the aircraft and/or a trailer for towing the aircraft, and fuse sensing ranges of the multiple sensors and unify information about the object detected by the multiple sensors in a same coordinate system, to generate a view-angle fused view indicating the detected object. Hence, vision blind areas of a pilot and a ground operator during ground movement of the aircraft can be advantageously eliminated, and the cooperation and scene awareness of the pilot and the ground operator can be improved, thereby reducing the accident rate and improving the safety of the ground movement.
G06V 20/58 - Recognition of moving objects or obstacles, e.g. vehicles or pedestriansRecognition of traffic objects, e.g. traffic signs, traffic lights or roads
A cabin lining element for an aircraft cabin which is arranged in the interior of an aircraft fuselage structure, having a fuselage structure side and a cabin side. The cabin lining element comprises an electrically contactable heating lacquer layer at least in regions on its fuselage structure side. A rib is provided for an aircraft fuselage structure, having at least one foot portion on the outer skin facing side and a cabin facing side head portion. The rib comprises an electrically contactable heating lacquer layer at least in regions on a side of the head portion facing the cabin.
H05B 3/14 - Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material the material being non-metallic
A hydraulic actuator comprising a housing, a piston, first to third pressure chambers, and a plurality of arrangements of piezoelectric elements arranged inside one of the plurality of chambers. A computer implemented internal brake for selectively switching between a braking mode and a non-braking mode of the piston comprises the third chamber, and fluid connections between the first to third chambers with flow control elements.
F15B 15/24 - Other details for restricting the stroke
F15B 13/04 - Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with a single servomotor
F15B 13/044 - Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with a single servomotor operated by electrically-controlled means, e.g. solenoids, torque-motors
12.
MODULE FOR AIRCRAFT COMPRISING A DIHYDROGEN PROCESSING SYSTEM
A module for an aircraft, the module comprising a sealed housing comprising walls delimiting an interior volume, a processing system to process dihydrogen and fixed on the inside of the housing, an inlet port connected to the interior volume and equipped with a first shut-off valve, an outlet port connected to the interior volume and equipped with a second shut-off valve and beads filling the interior volume.
A double-wall tank comprising an inner vessel surrounded by an outer jacket. The double-wall tanks comprising arrangements for coupling an inner vessel relative to an outer jacket which include roller bearings between the inner vessel and the outer jacket. Also an aircraft having at least one double-wall tank with the roller bearings.
A heat exchanger configured to be positioned in a tail cone section of a fuselage of an aircraft and including a liner through which passes hot gases from an auxiliary power unit (APU) and plates within the liner, wherein the plates are hollow and receive a second fluid from a first collector and discharge the second fluid from the plates to a second collector.
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
B64D 41/00 - Power installations for auxiliary purposes
15.
METHOD FOR MANAGING AN OPTICAL-LINK SATELLITE TELECOMMUNICATIONS SYSTEM AIDED BY METEOROLOGICAL MODELS FOR CONTINUITY OF SERVICE
The invention describes a method for optical-link communication between at least one satellite (10) and a plurality of transmitting and/or receiving ground stations (20), comprising: - obtaining cloud coverage data from the ground stations, and data relating to an orbit of the satellite, - determining, for each ground station (20), forecasts on the possibility of establishing an uninterrupted optical link between the satellite and the ground station, for at least two given short-term and long-term time horizons, and - selecting at least one of the ground stations (20) to establish an uplink or downlink optical-link communication with the satellite, based on the longest predicted duration for which it is possible to establish an uninterrupted optical link between the station and the satellite.
The present disclosure relates to a detection module, a detection device, a digital detection system, and a detection method. The detection module includes: a scanning unit and a processor. The scanning unit is configured to perform three-dimensional scanning on a detected surface, and includes a laser projecting device and a laser receiving device. The laser projecting device includes a laser source and a MEMS micro scanning mirror. The laser receiving device is configured to receive the laser radiation returning from the detected surface to obtain a laser image of the detected surface. The processor is configured to receive and process the laser image to detect a defect on the detected surface. The scanning unit further includes an RGB image sensor configured to obtain an RGB image of the detected surface. The processor is further configured to obtain the RGB image and detect a defect on the detected surface based on the laser image and the RGB image. The present disclosure can achieve the miniaturization of the detection module and improve the detection accuracy of the detection module.
G01B 11/25 - Measuring arrangements characterised by the use of optical techniques for measuring contours or curvatures by projecting a pattern, e.g. moiré fringes, on the object
G01N 21/88 - Investigating the presence of flaws, defects or contamination
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 process for the acquisition, by a spacecraft in terrestrial orbit, of a useful image of a space object in terrestrial orbit that is gradually approaching the spacecraft from an upstream distal region towards a proximal region is disclosed including controlling the orientation of an array-type detection sensor in order to orient it towards the space object located in the upstream distal region, acquiring, via the array-type detection sensor, a so-called detection image of the space object located in the upstream distal region, determining trajectory-tracking information on the basis of the detection image, controlling the orientation of an array-type acquisition sensor on the basis of trajectory-tracking information, in order to orient it towards the space object located in the proximal region, acquiring, via the array-type acquisition sensor, a useful image of the space object located in the proximal region.
An aircraft wing (3) including a main wing (5), a slat (7), and a connection assembly (9) movably connecting the slat (7) to the main wing (5). The connection assembly (9) includes an elongate slat track (17) extending along a track longitudinal axis (19) having a front end (21) an intermediate portion (25) and a rear end (23). The front end (21) and/or the intermediate portion (25) is mounted to the slat (7). The rear end (23) and/or the intermediate portion (25) is mounted to the main wing (5) by a roller bearing (27). The roller bearing (27) includes a guide rail (29) mounted to the main wing (5) and a first roller unit (31) mounted to the rear end (23) of the slat track (17) and engaging the guide rail (29), and wherein the guide rail (29) includes an upper rail portion (32) and a lower rail portion (34).
A drive assembly for driving a movable flow body of an aircraft, includes: a power drive unit, a flight control computer, a first flex shaft connecting the power drive unit to an inboard drive station, a second flex shaft connecting the inboard drive station to an outboard drive station, a first actuator connected to the inboard drive station and being couplable with the movable flow body, a second actuator connected to the outboard drive station and being couplable with the movable flow body. The second actuator includes a redundant position feedback sensor. The power drive unit includes a power-off brake, wherein the position feedback sensor is configured to send a position feedback signal to the flight control computer, and the flight control computer is configured to control the power drive unit.
A wing for an aircraft, comprising a main wing and a high lift assembly which includes a body, and an assembly connecting the body to the main wing, so the body is movable between a retracted position and an extended position. The assembly comprises a track extending along a longitudinal axis between first and second ends, with an intermediate portion therebetween. A roller bearing ensures that the track moves along the longitudinal axis. The roller bearing comprises bearing units, each mounted to the main wing and having a bearing surface for engaging the elongate track. The units include a first and second end units and an intermediate unit wherein, relative to the longitudinal axis, the intermediate unit is positioned between the first end unit and the second end unit. The elongate track comprises a recessed portion which, in the retracted position, aligns the intermediate unit.
An aircraft wing includes a main wing and a high lift assembly having a high lift body and a connection assembly movably connecting the high lift body to the main wing, such that the high lift body is movable between retracted and extended positions. The connection assembly includes an elongate track extending along a longitudinal axis between first and second ends and has an intermediate portion. The first end is mounted to the high lift body, and the second end is mounted to the main wing by a roller bearing such that the track is movable along the longitudinal axis. The roller bearing includes a roller unit mounted to the main wing and having a circumferential roller surface engaging an engagement surface of the track and an internal elastic bearing allowing the roller surface, in a cross section parallel to the roller rotation axis, to adapt its orientation or form.
An aircraft wing includes a main wing and a high lift assembly having a high lift body, and a connection assembly movably connecting the high lift body to the main wing to be movable between a retracted and an extended position, and having an elongate track extending along a longitudinal axis between a first end and a second end. The first end of the track is mounted to the high lift body. The track is mounted to the main wing via a roller bearing to be movable along the longitudinal axis. The roller bearing includes a first and a second roller mounted to at least one of the main wing and the track via first and second eccentric connector assembly, respectively. The first and second eccentric connector assemblies are configured to be engaged simultaneously by a single alignment member for synchronous rigging of the first and second rollers.
A locking washer includes an annular main component with a ring equipped, on its inner periphery, with flexible tabs which are curved such that their free ends deviate, on the same side, from a plane formed by the ring and substantially define arcs of the same circle, which is referred to as the locking circle, to produce efficient locking and to obtain a robust locking washer, the locking washer also including an annular auxiliary component to interact with the main component to quickly unlock the locking washer.
F16B 39/24 - Locking of screws, bolts, or nuts in which the locking takes place during screwing down or tightening by means of washers, spring washers, or resilient plates that lock against the object
25.
SYSTEM FOR FIXING AN ELEMENT AND AIRCRAFT COMPRISING AT LEAST ONE SUCH SYSTEM
A support for a system for fixing an element comprising a hose clamp having a flexible link and a cage, the support comprising: a base comprising a recess in which the cage is housed and a first channel into which the link is fitted; an inclined upright extending from the base by moving away from the recess such that a free end of the upright is disposed at a distance from and facing an aperture which emerges in the recess. The link is able to penetrate into the first channel, surround the element, then penetrate in succession into the aperture of the recess and into the cage.
F16L 3/233 - Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets specially adapted for supporting a number of parallel pipes at intervals for a bundle of pipes or a plurality of pipes placed side by side in contact with each other by means of a flexible band
B65D 63/10 - Non-metallic straps, tapes, or bandsFilamentary elements, e.g. strings, threads or wiresJoints between ends thereof
26.
POSITION ADJUSTMENT DEVICE HAVING KINEMATIC REDUCTION
The invention relates to a device (1) for adjusting the position of a space apparatus, comprising: an actuator (10) for generating a movement along an axis (X-X), a kinematic reduction stage (20) comprising an interface (201) for being joined to the apparatus, comprising: o two input arms (21) of the reduction stage, which are articulated to one another at a second interface for being joined to the actuator; o two external arms (22) which are articulated to the frame (19) and to the two input arms; o two internal arms (24) which are articulated at the joins between the external arms and the input arms and to an interface arm (23) arranged transversely to the axis, the reduction stage being dimensioned such that a movement of the interface with the actuator along the axis causes a movement of the interface arm, in the same direction and at a reduced amplitude of a reduction ratio which is based on the relative lengths of the arms.
G02B 7/183 - Mountings, adjusting means, or light-tight connections, for optical elements for prismsMountings, adjusting means, or light-tight connections, for optical elements for mirrors for mirrors specially adapted for very large mirrors, e.g. for astronomy
G02B 7/182 - Mountings, adjusting means, or light-tight connections, for optical elements for prismsMountings, adjusting means, or light-tight connections, for optical elements for mirrors for mirrors
B64G 1/22 - Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
B64G 1/66 - Arrangements or adaptations of apparatus or instruments, not otherwise provided for
A wing (3) for an aircraft (1) including a fixed wing (5), a foldable wing tip portion (9) mounted to the fixed wing (5) via a hinge (11) in a manner rotatable about a hinge axis (13) between an extended position and a folded position, an actuation device (24) for actuating the foldable wing tip portion (9) for movement between the extended position and the folded position, and an arresting device (37) for arresting the foldable wing tip portion (9) in the extended position and/or in the folded position. The arresting device (37) includes a clutch device (39) configured for selectively holding the foldable wing tip portion (9) in a fixed position relative to the fixed wing (7) and releasing the foldable wing tip portion (9) for movement relative to the fixed wing (7) about the hinge axis (13).
An assembly of an attachment pylon with an aircraft engine comprising a front engine mount comprising a front tang and a front clevis, a lower tang and a lower clevis connecting the attachment pylon and the engine via a front pin mounted in the front tang and clevis and a lower pin mounted in the lower tang and clevis, and port/starboard links mounted between the attachment pylon and the engine via mounting pins, wherein the front and lower pins are orthogonal to a mid-plane, and wherein the mounting pins of the links are parallel to the mid-plane.
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.
An aircraft with a potable water system enabling the connection of monuments to preinstalled aircraft potable water interfaces by customized piping, which is routed within raceways for example directly along seat rails, and an installation method.
An aircraft with a potable water system to feed potable water from a potable water tank to a consumer equipment of a monument in the aircraft cabin, including potable water interfaces, and at least one monument, with at least one opening in the monument to establish a fluid connection to the consumer equipment, wherein at least one potable water interface is accessible through the at least one opening, and an assembly method for installing a potable water system wherein standard parts of the potable water system are preinstalled and customized parts are installed later on.
A method for detecting and localizing a failure of an input sensor of a flight control computer of an aircraft including comparing a first piece of information representative of a probability of occurrence of the failure, delivered by a neural network, with a second piece of information representative of a probability of occurrence of the failure, delivered by a classifier trained to carry out a detection and a localization of the failure. It is thus possible to optimize a failure diagnosis and a localization of a failure of an input sensor used in the determination of flight controls.
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
33.
PROPULSION UNIT COMPRISING A SUSPENSION SYSTEM OF THE REAR PART OF THE ENGINE, AIRCRAFT COMPRISING AT LEAST ONE SUCH PROPULSION UNIT
A propulsion unit comprising an engine, a pylon, an engine mount system which connects a front part of the engine and the pylon, in addition to a suspension system which connects the pylon and a rear part of the engine which is offset toward the rear end of the engine relative to the engine mount system.
An aircraft propulsion system comprising a turbojet having a fan casing with a rear face, a pylon with a front part and a lower spar with a rear fitting fixed to it, and a front engine attachment fixed between an upper part of the fan casing and the front part, a front arch having two arms, each having a first end fixed to the lower spar and a second end fastened in an articulated manner to the rear face, and two lateral rods, each having a first end fastened in an articulated manner to the rear fitting and a second end fastened in an articulated manner to the rear face.
A painting device including at least one guide system, at least a first movable support configured to move along the guide system, a robotic arm secured to the first movable support, at least a first tool connected to the free end of the robotic arm, and at least a first piece of equipment connected to the first tool by at least one umbilical connection, the first piece of equipment being movable and connected to the first movable support. This configuration makes it possible to reduce the length of the umbilical connection. A painting installation having at least one such painting device is also provided.
A painting system suitable for painting a fuselage of an aircraft, including a paint booth which is positioned on a platform. This paint booth includes at least first and second lateral openings which are configured to permit the wings of the aircraft to pass through the paint booth, in addition to at least two elements, at least one thereof being mobile between an adjacent position corresponding to a closed state of the paint booth in which the two elements are joined together, in addition to a spaced-apart position corresponding to an open state of the paint booth in which the fuselage can be positioned between the two elements.
An aircraft cooling device for cooling a fluid in a fluid supply and/or drainage device of an aircraft in flight, the aircraft cooling device being configured as a skin component for the aircraft, the skin component including an integrated ply of one or more hollow fibers, each hollow fiber being configured for conducting the fluid from one end portion to another end portion of the hollow fiber such that the fluid supply and/or drainage device is enabled to pump the fluid through the one or more hollow fibers when in fluid connection with ply.
A water supply system for an aircraft includes a water supply tank, water consumers, a pressurization unit to convey water from the water supply tank to the water consumers, water consumer supply units, each of the water consumer supply units configured to control water supply from the pressurization unit to one of the water consumers, and a controller. Each of the water consumer supply units is configured to output a consumer signal indicating a water supply of the respective water consumer, wherein the controller is configured to receive the consumer signal of the water consumer supply units and to control a flow rate and/or pressure of the pressurization unit depending on the consumer signal.
A device for sealing a joint between a wall of a wing box and a wall of a central fuselage of an aircraft, the device comprising at least one deformable element clamped between a first and a second rigid end element. The device moreover comprises clamp for moving the first and second rigid end elements closer to one another so as to deform the at least one deformable element by crushing until it is pressed against the walls of the joint.
A polar plate for use in a fuel cell device, the polar plate including an integrated fiber arrangement of one or more hollow fibers, each hollow fiber being configured for conducting a fluid from one end portion to another end portion of the hollow fiber such that the fluid can be pumped through the one or more hollow fibers. Also a fuel cell device, a method for producing the polar plate, an additive manufacturing device, a computer program.
H01M 8/0267 - CollectorsSeparators, e.g. bipolar separatorsInterconnectors having heating or cooling means, e.g. heaters or coolant flow channels
B33Y 80/00 - Products made by additive manufacturing
B60L 58/33 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling fuel cells for controlling the temperature of fuel cells, e.g. by controlling the electric load by cooling
H01M 8/0263 - CollectorsSeparators, e.g. bipolar separatorsInterconnectors characterised by the configuration of channels, e.g. by the flow field of the reactant or coolant having meandering or serpentine paths
41.
HIGH PRESSURE WATER SUPPLY SYSTEM AND AIRCRAFT EQUIPPED WITH SUCH SYSTEM
A high pressure water supply system for an aircraft includes a main water supply tank, water consumers, pressurization units configured to convey water from the main water supply tank to the water consumers, and a controller. One pressurization unit of the pressurization units conveys water to a first subset of water consumers of the water consumers via a corresponding high pressure water supply line, and the controller is configured to control an output pressure of the one pressurization unit depending on a hydraulic resistance length of the high pressure water supply line.
A support device includes a profiled element having at least one passage hole passing transversely through the profiled element, a fastening support, integral with the profiled element, to fasten the support device to a primary structure, at least one clamping element having a clamp to receive at least one cable and at least one fastening element to fasten the clamping element or elements to the profiled element. The device facilitates the fastening of cables to a primary structure.
F16L 3/127 - Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing comprising a member substantially surrounding the pipe, cable or protective tubing and extending away from the attachment surface
F16L 3/123 - Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing comprising a member substantially surrounding the pipe, cable or protective tubing and extending along the attachment surface
43.
METHOD FOR DETERMINING A FUEL CONSUMPTION MARGIN OF AN ENGINE IN RELATION TO A THEORETICAL CONSUMPTION
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 wing is provided having a fixed wing with a gulled wing tip rotatably mounted at the tip thereof, the gulled wing tip extending below a wing plane defined by the end of the fixed wing such that the centre of gravity of the gulled wing tip is located below the wing plane. Lowering the centre of gravity of the gulled wing tip has been found to reduce the onset of flutter. The gulled wing tip may be gulled about a hinge axis where it meets the fixed wing, or may be otherwise folded or curved to lower the centre of gravity of the gulled wing tip.
A reaction transmitting device includes an emission generating compound provided as an elongate transmitting structure having first and second ends, the emission generating compound reaching from the first to the second end. The emission generating compound can be exposed to local thermal energy release at a trigger location between the first and second end along the elongate structure resulting from leaked substance from an enclosure, the enclosure configured to encapsulate a substance from surroundings. The emission generating compound provides an emission reaction upon being triggered by the local thermal energy release and relays the emission reaction from the trigger location along the elongate transmitting structure to the second end which is configured to be exposed to a sensing unit configured to detect a transmitted emission reaction as a signal indicative of the leaked substance.
A high lift assembly (7) including: a high lift body with a high lift structure (8) and an internal volume (22), and a connection assembly (10) extending through an aperture (18) in an outer skin (20) of a leading edge of a main wing (5), the connection assembly (10) includes an elongate track (16) and a first and second connectors (12, 14), the elongate track (16) is mounted to the main wing (5) and moves along a track longitudinal axis (24), and the first and second connectors (12, 14) connect the elongate track (16), the first connector (12) is between the internal volume (22) and the outer skin (20), the second connector (14) has a longitudinal axis transverse to the leading edge of the high lift body and connects to the high lift body and the high lift structure has an opening (40) for the elongate track.
A wing defines a chord which runs from a leading edge to a trailing edge. The wing has a main portion and a flap which is movable relative to the main portion to change the aerodynamics of the wing, for instance to maximize lift, or to reduce drag at the expense of some loss of lift. The wing has a guide mechanism which guides movement of the flap. The guide mechanism uses a pair of runners which run along respective tracks. The tracks are positioned at different locations along the direction of the chord, but overlap one another in the direction of the chord.
A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar, and a complementary front engine attachment fixed between an upper area of the central casing and a lower end of the front wall.
A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the central casing and a lower end of the front wall, and a complementary front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar.
A device for coupling a propulsion system to an engine pylon of an aircraft, the device comprising a baseplate comprising a base suitable for being fastened to the propulsion system, and a first wall extending substantially perpendicularly to the base. The first wall of the baseplate interacts with first and second sleeves, a pair of flanges and a fasteners to the engine pylon. The fasteners comprise two adjacent fastening screws extending parallel to each other.
A command system of an aircraft mobile element actuated by a motor is provided. The command system is electrically connected to a power supply, to the motor and to a current consuming device used to effect de-icing. The system establishes a connection between the motor and the current consuming device and inhibits a first connection between the power supply and the motor and a second connection between the power supply and the current consuming device when a braking command is received. The system enables the first connection and the second connection to be established and inhibits the third connection as long as no braking command has been received or when a command to stop braking is received. Thus the mobile element can be easily braked and the overall size of the system is limited.
H02P 3/06 - Arrangements for stopping or slowing electric motors, generators, or dynamo-electric converters for stopping or slowing an individual dynamo-electric motor or dynamo-electric converter
B64C 13/50 - Transmitting means with power amplification using electrical energy
An aircraft section comprising a first fuel storage tank and a second fuel storage tank arranged in a caudal tandem configuration. The corresponding casings, housing conduits configured for distribution of fuel to and from inside the tanks, are arranged in a common section of the fuselage and spaced between them. Also an aircraft with such a section.
In an aircraft wing structure where space and weight considerations are a principal concern, there may be significant challenges in providing a moveable slat and/or a spoiler, particularly in combination with one another. A control device for an aircraft includes upper and lower flaps pivotably mountable adjacent to a slot in a wing behind a leading edge, wherein the control device is operable in a lift configuration to move the upper and lower flaps towards each other to abut opposing surfaces of the slot, to permit airflow along the slot.
A pipe spacer (50) for separating inner and outer pipes of a double- walled pipe assembly, the pipe spacer comprising: an annular body (60) for positioning in an interspace between inner and outer pipes of a double-walled pipe assembly, wherein the annular body (60) defines an axis of the pipe spacer; a plurality of springs (70) extending radially from the annular body (60), wherein each spring (70) is configured to deform inwardly towards the annular body (60) on contact with one of the inner and outer pipes; and a plurality of projecting stops (80) extending from the annular body (60) which are configured to limit the inward deformation of the springs (70).
F16L 39/00 - Joints or fittings for double-walled or multi-channel pipes or pipe assemblies
F16L 7/00 - Supporting pipes or cables inside other pipes or sleeves, e.g. for enabling pipes or cables to be inserted or withdrawn from under roads or railways without interruption of traffic
A pipe spacer 50 for separating inner and outer pipes of a double-walled pipe assembly, the pipe spacer 50 comprising: an annular body 60 for positioning in an interspace between inner and outer pipes of a double-walled pipe assembly, the annular body 60 formed of a composite material; a plurality of outer arms 70a extending radially outwardly from the annular body 60 for contacting the outer pipe and/or a plurality of inner arms 70b extending radially inwardly from the annular body 60 for contacting the inner pipe; and wherein each of the inner and/or outer arms are springs 71 that extend radially from the annular body 60 and are configured to deform inwardly towards the annular body 70 on contact with the respective outer or inner pipe, the arms formed of a composite material.
F16L 7/00 - Supporting pipes or cables inside other pipes or sleeves, e.g. for enabling pipes or cables to be inserted or withdrawn from under roads or railways without interruption of traffic
F16L 39/00 - Joints or fittings for double-walled or multi-channel pipes or pipe assemblies
F16L 3/01 - Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets for supporting or guiding the pipes, cables or protective tubing, between relatively movable points, e.g. movable channels
A rod with attachment sockets for a truss structure of a vehicle. The rod comprises an elongated body having a plurality of attachment sockets formed on and distributed over an outer side of the body. The plurality of attachment sockets comprises at least a first number of attachment sockets facing in a first direction and a second number of attachment sockets facing in a second direction different from the first direction. The plurality of attachment sockets each comprises a cavity open to the outer side of the body and comprising at least one bearing surface.
An aircraft wing is disclosed having a fixed wing with a tip, and a wing tip device rotatably mounted on a hinge at the tip of the fixed wing, such that the wing tip device is rotatable about the hinge, and an actuation system for rotating the wing tip device about the hinge. The actuation system includes a motor, at least one geared rotary actuator, a reduction gearbox, a clutch for selectively decoupling rotation of the motor from rotation of the geared rotary actuator, the geared rotary actuator is driveable by the motor and arranged to convert rotary motion into a different rotary motion and is arranged to rotate the wing tip device relative to the tip of the fixed wing. The reduction gearbox is positioned between the clutch and the geared rotary actuator along a drive train between the motor and the geared rotary actuator.
A tank comprising a shell having an edge face connecting first and second inner lateral surfaces of first and second portions, at least one end wall, positioned at the first portion of the shell, which has a central part in the shape of a dome, a peripheral sleeve positioned around the central part and a junction zone connecting the central part and the peripheral sleeve and having an edge face, a weld connecting the first portion and the peripheral sleeve, the edge faces of the end wall and of the shell having shapes configured to immobilize the junction zone with respect to the shell in a radial direction. Also a cryogenic reservoir with such a tank.
A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar, and a complementary front engine attachment fixed between an upper area of the central casing and a lower end of the front wall.
A propulsion assembly for an aircraft, the propulsion assembly having a jet engine, an attachment pylon having a rigid structure, and an extinguishing system. The extinguishing system is located in a front position relative to the rigid structure, the extinguishing system being positioned between the rigid structure and the jet engine.
B64D 27/40 - Arrangements for mounting power plants in aircraft
A62C 3/08 - Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles in aircraft
A62C 35/68 - Details, e.g. of pipes or valve systems
61.
AIRCRAFT PROPULSION ASSEMBLY HAVING A JET ENGINE, A PYLON AND MEANS FOR ATTACHING THE JET ENGINE TO THE PYLON
A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the central casing and a lower end of the front wall, and a complementary front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar.
A device for coupling a propulsion system to an engine pylon of an aircraft, the device comprising a baseplate comprising first and second parts of the baseplate placed against each other so as to form a base suitable for being fastened to the propulsion system, and a first wall extending substantially perpendicularly to the base. The first wall of the baseplate interacts with a sleeve, a pair of flanges and fasteners to the engine pylon.
B64D 27/40 - Arrangements for mounting power plants in aircraft
63.
AIRCRAFT NACELLE EQUIPPED WITH AT LEAST ONE THRUST REVERSAL DEVICE COMPRISING AT LEAST ONE LONGITUDINAL DEFLECTOR CONFIGURED TO HOUSE A LONGITUDINAL ACTUATOR
An aircraft nacelle equipped with a thrust reversal device, which comprises: at least one longitudinal actuator for activating or deactivating the thrust reversal device, at least one deflection system configured to deflect an air stream channeled in the nacelle towards a lateral opening in the nacelle, in the activated state, at least one orientation system having: at least one transverse deflector configured to orient the air stream deflected by the deflection system towards the upstream end of the nacelle, for each longitudinal actuator, a hollow longitudinal deflector, which is configured to house the longitudinal actuator and has an aerodynamic profile that has a leading edge oriented towards the deflection system.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
An aircraft wing is disclosed having a fixed wing with a tip, and a wing tip device rotatably mounted on a hinge at the tip of the fixed wing, such that the wing tip device is rotatable about the hinge, and an actuation system for rotating the wing tip device about the hinge. The actuation system includes a motor, at least one geared rotary actuator, a reduction gearbox, a clutch for selectively decoupling rotation of the motor from rotation of the geared rotary actuator, the geared rotary actuator is driveable by the motor and arranged to convert rotary motion into a different rotary motion and is arranged to rotate the wing tip device relative to the tip of the fixed wing. The clutch is coupled to the geared rotary actuator by a shaft and the shaft is fixed in rotation to a mass disposed radially outwardly from the shaft.
A shielded apparatus comprising a device and a shield, and a method of producing a shielded apparatus. The device attenuates x-rays by different amounts in different parts of the device, providing a first span of x-ray attenuations. The shield comprises a layer of x-ray attenuating material that attenuates x-rays by an amount that varies across the shield, providing a second span of attenuations. The second span of attenuations has a magnitude between 20% and 120% of the magnitude of the first span of attenuations.
The invention provides an aircraft fuel supply arrangement for delivering liquid hydrogen to an aircraft engine (19), the arrangement comprising: a fuel tank (2) for the storage of liquid hydrogen; an aircraft engine (19) configured to be powered by liquid hydrogen; a primary pump (3) for delivering liquid hydrogen fuel from the fuel tank (2) to the aircraft engine; one or more fuel delivery conduits (4,5) for carrying fuel from the fuel tank to the primary pump (3), one or more fuel delivery conduits (18) providing a fuel supply volume for carrying fuel; and a secondary pump (6) for delivering liquid hydrogen fuel to the primary pump (3). An aircraft comprising such an aircraft fuel supply arrangement, and a method of supplying liquid hydrogen to an aircraft engine are also provided.
A reinforcing device to provide an alternative improvement in the structural stability of laminated components includes a body structure having an abutment surface and at least one fastening area. The abutment surface extends along a first direction. In a cross-sectional direction, transverse to the first direction, the abutment surface includes a rounded contour section so abutment surface is configured to conform with a concave edge section of a laminated structural member. The at least one fastening area is provided at the body structure opposite to the abutment surface. The at least one fastening area is configured to secure the abutment surface against the concave edge section of the laminated structural member.
There is disclosed a method for determining a location of a platform in a region. The platform comprises an event camera having an array of pixels and a memory store. Each pixel is operable to output events which represent a change in light intensity recorded at that pixel. Before platform motion in the region, a signature library is stored in the memory store. Each of the signatures has an associated patch at a known location, and each signature represents the number of events that would be captured by viewing the associated patch using the event camera whilst moving the sightline of the event camera through each of a predetermined set of intervals on a predetermined trajectory. During platform motion in the region, the platform location is determined by using the event camera to obtain a sensed signature. The sensed signature is compared to the signature library to locate the platform.
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 structural element for a passenger cabin of an aircraft is built using biomimicry methods. The structural element includes a generative structure, and a functional component. The generative structure includes at least one accommodating space. The functional component is arranged within the at least one accommodating space. The generative structure includes a load topology optimized structure based on a bioinspired generative design that is configured to enable the structural integrity of the structural element while simultaneously providing integrated functionalities via the functional component. Further, an interior component for an aircraft is disclosed that includes at least one such structural element, and an aircraft including at least one structural element. For example, an aircraft galley may include a structural component that may therefore, for example, include integrated wiring, plumbing or other functionalities.
The present disclosure relates to an aircraft galley. In order to provide an aircraft galley with improvements for operation and ergonomics, a galley module for an aircraft is provided that comprises a galley support structure providing a plurality of storage compartments and a countertop arranged above lower storage compartments and below upper storage compartments. The countertop is provided as permanent working surface for onboard services. At least one portion of the countertop is an extendable countertop portion that is movable between a retracted position and an extended position.
A passenger seat arrangement for a passenger aircraft includes a passenger seat assembly having at least one passenger seat with a seat supporting frame and a backrest, and a wireless charging system integrated into the backrest. The wireless charging system includes a PED holder having an assembly of permanent magnets embedded within the PED holder configured to a physically hold a PED on the PED holder in place, and a charging pad configured to electromagnetically transfer power to a PED held on the PED holder.
A speed determination system for an aircraft including one or more interfaces arranged to receive first speed data from a first speed measurement system and second speed data from a second speed measurement system. The first speed measurement system provides the first speed data using global positioning system data. The second speed measurement system provides the second speed data based on a second speed measurement. The speed determination system includes a processor arranged to determine whether the data received from the first speed measurement system is reliable. If global positioning data is determined to be reliable, the speed determination system determines a speed from the first speed data and determines correction values for the second speed measurement system. If global positioning data is determined to be unreliable, the speed determination system determines a speed from the second speed data and the correction values.
G01S 19/47 - Determining position by combining measurements of signals from the satellite radio beacon positioning system with a supplementary measurement the supplementary measurement being an inertial measurement, e.g. tightly coupled inertial
G01S 19/48 - Determining position by combining or switching between position solutions derived from the satellite radio beacon positioning system and position solutions derived from a further system
G01S 19/45 - Determining position by combining measurements of signals from the satellite radio beacon positioning system with a supplementary measurement
G01S 19/49 - Determining position by combining or switching between position solutions derived from the satellite radio beacon positioning system and position solutions derived from a further system whereby the further system is an inertial position system, e.g. loosely-coupled
74.
AIR MOBILITY SYSTEM WITH ENHANCED SITUATIONAL AWARENESS
An urban air mobility system includes aerial vehicles, a detection platform, and a fusion platform. The aerial vehicles include one cooperative aerial vehicle and one data consuming aerial vehicle. The detection platform detects a position of flight objects and transmits first data indicative of the position of the detected flight objects to the fusion platform. The cooperative aerial vehicle detects a relative position of flight objects in its surroundings and transmits second data indicative of the relative position of detected flight objects to the fusion platform. The fusion platform fuses the first data and the second data and generates an air traffic scenario. The data consuming aerial vehicle and the cooperative aerial vehicle receive the air traffic scenario from the fusion platform.
A cooling system for aircraft comprises a first loop intended to cool fuel cells and on which there is a ram air heat exchanger, and a second loop intended to cool power electronic equipment items and to supply heat to an evaporator to gasify dihydrogen in order to supply the fuel cells. The first loop and the second loop are interconnected by a flow line starting at the output of the ram air heat exchanger and by a return line. A controller regulates the coolant temperature in the first loop, and in the second loop by controlling the opening of the flow line. Also an aircraft with such a cooling system.
B60L 58/33 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling fuel cells for controlling the temperature of fuel cells, e.g. by controlling the electric load by cooling
B64D 41/00 - Power installations for auxiliary purposes
H01M 8/04007 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
H01M 8/04082 - Arrangements for control of reactant parameters, e.g. pressure or concentration
A method for assisting in designing a technical system by: receiving an input message; processing the input message using a neural network to identify a content of the input message and extract technical system requirements, wherein the technical system requirements include at least a component having at least one parameter and a constraint; generating a proposed system design by determining at least one parameter of the component based on the constraint using the neural network; generating a response message containing the proposed system design using the neural network; and providing the proposed system design, wherein the neural network is configured as a large language model, LLM, and trained with a plurality of template systems and template components in the related technical field.
G06F 30/27 - Design optimisation, verification or simulation using machine learning, e.g. artificial intelligence, neural networks, support vector machines [SVM] or training a model
G06F 111/20 - Configuration CAD, e.g. designing by assembling or positioning modules selected from libraries of predesigned modules
G10L 15/22 - Procedures used during a speech recognition process, e.g. man-machine dialog
77.
METHOD FOR ASSISTING A TRAINEE DURING A PILOT TRAINING ON A PILOT TRAINING SIMULATOR, DATA PROCESSING APPARATUS, A PILOT TRAINING SIMULATOR AND A COMPUTER PROGRAM
A method for assisting a trainee during a pilot training on a pilot training simulator, comprising receiving a vocal input message from the trainee; converting the vocal input message into a text input message; processing the text input message by a neural network configured as a large language model, LLM, to identify the content of the text input message and extract at least a request related to the pilot training simulator; accessing and searching a database based on the request to determine an educational advice using the neural network, wherein the database includes data about an aircraft on which the pilot training is performed; generating a response message containing the educational advice using the neural network; converting the response message into a vocal response message; and providing the vocal response message to the trainee.
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
A water supply system for an aircraft and a method for draining water from or passing air into or out of a buffer tank of a water supply system in an aircraft. The system includes a water buffer tank having a fluid inlet and outlet, a supply arrangement for selective flow from the fluid outlet to a user equipment, and a relief arrangement for permitting fluid flow from the fluid outlet. The relief arrangement includes a relief conduit having a separation element with a separation element inlet positioned above a separation element outlet and separated therefrom by a separation distance such that water flowing in a forwards direction therethrough flows from the inlet to the outlet across the separation distance, and water flowing in a reverse direction therethrough flows into the separation element outlet and is retained therein, and wherein the separation element is defined by the user equipment.
Individual air supply duct for connecting a main air supply duct to a passenger service unit in an aircraft, wherein the duct is an extruded profile with a longitudinal extension direction (x). An individual air supply assembly comprising the duct and a passenger service unit configured to be mounted thereto, wherein the duct comprises individual connection ports, located on the outer surface of the duct, at equal intervals, wherein the passenger service unit comprises a port, located on the outer surface of the passenger service unit, and wherein, when the passenger service unit is mounted to the duct, the port is brought into close proximity and/or into alignment with a corresponding connection port.
A mounting rail interface comprises an elongate body. The body comprises two elongate lateral portions; and an elongate central portion arranged between the two lateral portions. The lateral portions are defined for providing a transition portion to an adjacent surface. The central portion comprises a plurality of openings with a respective circumferential edge flange. The openings are defined as elongate openings configured to allow a range of different orientations of a connector. The edge flange is defined with a concave curved contour on its bottom side. The concave curved contour provides an abutting surface for a connector configured to engage with the edge flange of the opening. The curved contour provides an abutting surface over at least an angular range.
A tank, in particular for a liquid hydrogen reservoir, provided with at least one dome fixed by way of an outer welded joint and having a central portion provided with at least one free end including a first connecting element and at least one dome provided with an open end including a second connecting element, the dome and the central portion being able to be joined together, the first connecting element and the second connecting element being configured to form, when the central portion and the dome are joined together, a protruding tab extending toward the outside of the tank and able to be welded to a protruding end, such a protruding tab making it possible in particular to join together the tank, this being done entirely from the outside of said tank, and to easily mount and dismount the dome, in particular without accessibility issues.
F17C 1/14 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge constructed of aluminiumPressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge constructed of non-magnetic steel
B23K 20/12 - Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by frictionFriction welding
A method for assisting landing of an aircraft on a landing runway of a destination airport facility includes two successive determinations of the position of the aircraft with respect to the landing runway and based on a photographic image taken from the aircraft, respectively according to two different algorithms for determining the position of the aircraft, together with the supply of at least one piece of information representative of a difference between the two determined positions. It is thus possible to verify whether the destination landing runway observed from the photographic image taken from the aircraft is indeed the target destination runway on which a landing of the aircraft is planned, or whether there exists an error in positioning of the aircraft with respect to the destination landing runway.
B64D 45/08 - Landing aidsSafety measures to prevent collision with earth's surface optical
83.
AIRCRAFT PROPULSION ASSEMBLY COMPRISING AT LEAST ONE AERODYNAMIC PANEL WHICH IS SUPPORTED BY AT LEAST ONE INTERMEDIATE RADIAL SUPPORT, AIRCRAFT COMPRISING AT LEAST ONE SUCH PROPULSION ASSEMBLY
A propulsion assembly comprising a fan casing and a nacelle which comprises an air inlet which is connected to the front end of the fan casing, an intermediate portion which is positioned around the fan casing and a rear portion which cooperates with the rear end of the fan casing. The intermediate portion comprises at least one aerodynamic panel which extends from a front edge which is attached to the air inlet as far as a rear edge which is attached to the rear portion and at least one intermediate radial support comprising an internal edge which is connected to the fan casing and an external edge which is connected to the aerodynamic panel, this panel comprising a front edge which is connected to the air inlet by a first connection system. Also an aircraft with such a propulsion assembly.
An enhanced interface for checking an aircraft electrical power supply line, the interface being configured to easily and rapidly check an absence of electrical potential at at least one determined point of an aircraft electrical installation comprising an equipment item of high-voltage type. Also to an aircraft comprising such an enhanced interface and a method for checking and neutralizing an electrical power supply line of an aircraft.
G01R 31/00 - Arrangements for testing electric propertiesArrangements for locating electric faultsArrangements for electrical testing characterised by what is being tested not provided for elsewhere
B64F 5/60 - Testing or inspecting aircraft components or systems
G01R 1/04 - HousingsSupporting membersArrangements of terminals
85.
METHOD FOR ASSISTING WITH LANDING AN AIRCRAFT AND SYSTEM CONFIGURED TO EXECUTE THE METHOD
A method for assisting with landing an aircraft is disclosed and configured to determine a number of probable theoretical positions (POS1, POS2, POS3) of the aircraft equal to the facing plurality of runways of a destination airport facility to reproject the runways into an image (F) obtained by a camera of the aircraft by means of a theoretical camera model (e.g. pinhole camera model), each reprojection being with reference to one of the determined theoretical positions (POS1, POS2, POS3); and to establish, for each of the reprojections, a consistency score making it possible to then deliver an estimated position (POSA) of the aircraft.
G08G 5/02 - Automatic landing aids, i.e. systems in which flight data of incoming planes are processed to provide landing data
G06F 18/2413 - Classification techniques relating to the classification model, e.g. parametric or non-parametric approaches based on distances to training or reference patterns
G06T 7/70 - Determining position or orientation of objects or cameras
G06V 20/17 - Terrestrial scenes taken from planes or by drones
An autonomous energy system for an aircraft with a high voltage network, a main power source, an energy storage, a bidirectional DC-DC converter, and a power control management system connected to: the high voltage network to measure its voltage variations, and to the energy storage and to the DC-DC converter forming an energy buffer module providing/receiving a fixed voltage setpoint to the high voltage network; and being configured so that, when the power control management system detects that the voltage variation (ΔVr_network, ΔVd_network) of the high voltage network is higher than preset voltage discharge/charge activation thresholds during a time higher than preset time discharge/charge activation values, the power control management system provides/receives power from the energy buffer module to the high voltage network until a preconfigured condition is met.
A gas monitoring system for detecting chemical substances in a gas comprising a Raman spectrometer comprising: an excitation source of light, a hollow core optical fiber having a longitudinal axis, a first longitudinal end, a second longitudinal end, an outer surface and an inner hollow core surface, the hollow core optical fiber being configured to: receive in its hollow core the gas to be monitored, receive at its first or its second longitudinal end light emitted by the excitation source of light, and transmit at its first or its second longitudinal end a Raman light when being illuminated by the received light. The system also includes a detector, and a transmission optical fiber coupled to the first longitudinal end and/or to the second longitudinal end of the hollow core optical fiber.
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 invention relates to a deployable sun-protection screen for a piece of space equipment (1) configured to switch from a stored configuration to a deployed configuration and comprising: -- first rods (21); -- second rods (22) for deploying the screen (2) in a radial direction (r, Θ); -- third rods (23) for deploying the screen (2) in an axial direction (z); and -- rotary links (24, 25) joining rods (21, 22, 23) to one another, the rotary links being active (25), storing an amount of energy, or passive (24), the second rods (22) and third rods (23) being folded when the screen (2) is in the stored configuration, the active rotary links (25) being configured to unfold the second and third rods (22, 23) and trigger the transition from the stored configuration to the deployed configuration, by driving the rotation of the passive rotary links (24) and a deployment in an axial direction and in a radial direction.
A device for controlling the angular velocity of an out-of-service spacecraft is disclosed, in which the device makes it possible to facilitate the operations of active removal of the spacecraft as space debris. The device includes a stator and a rotor able to move on a rotation axis with respect to the stator, the stator is configured to be driven by the spacecraft to be stabilized, the rotor is configured to orient itself along the terrestrial magnetic field. The stator includes an electrically conductive non-ferromagnetic body while the rotor includes a magnetized system configured to induce, in the stator, eddy currents for braking a relative movement of the rotor with respect to the stator.
A method for assisting a worker in a production line by: receiving a vocal input message from the worker; converting the vocal input message into a text input message; processing the text input message using a neural network to identify the content of the text input message and extract a request about at least one item related to the production line, wherein the neural network is configured as a large language model, LLM, and trained with information about the items of the production line; generating a response message containing information about the item of the production line using the neural network; converting the response message into a vocal response message; and providing the vocal response message to the worker.
G10L 13/08 - Text analysis or generation of parameters for speech synthesis out of text, e.g. grapheme to phoneme translation, prosody generation or stress or intonation determination
G10L 15/16 - Speech classification or search using artificial neural networks
G10L 15/22 - Procedures used during a speech recognition process, e.g. man-machine dialog
G10L 25/63 - Speech or voice analysis techniques not restricted to a single one of groups specially adapted for particular use for comparison or discrimination for estimating an emotional state
92.
FUEL CELL AND INTERCONNECTION CONCEPTS FOR A FUEL CELL SYSTEM
A fuel cell comprising a tubular body, an inner and outer electrolyte layer disposed on the tubular body, an inner and outer electrically conductive layer disposed on the respective electrolyte layer, and a first electric terminal arranged at an interruption of the outer electrolyte layer and the outer electrically conductive layer. Also fuel cell systems having a plurality of such fuel cells, which are electrically connected in axial direction to form subgroups and in radial direction.
B60L 50/72 - Constructional details of fuel cells specially adapted for electric vehicles
H01M 8/0252 - CollectorsSeparators, e.g. bipolar separatorsInterconnectors characterised by the form tubular
H01M 8/0258 - CollectorsSeparators, e.g. bipolar separatorsInterconnectors characterised by the configuration of channels, e.g. by the flow field of the reactant or coolant
H01M 8/12 - Fuel cells with solid electrolytes operating at high temperature, e.g. with stabilised ZrO2 electrolyte
H01M 8/1226 - Fuel cells with solid electrolytes operating at high temperature, e.g. with stabilised ZrO2 electrolyte characterised by the electrode/electrolyte combination or the supporting material characterised by the supporting layer
H01M 8/243 - Grouping of unit cells of tubular or cylindrical configuration
93.
CRYOGENIC TANK WITH ACCESS OPENING, AND AIRCRAFT EQUIPPED THEREWITH
A cryogenic tank for an aircraft providing a tank access for maintenance and repairing services of equipment inside the tank onboard of the aircraft. An access opening is closed by a removable closure including a multiple wall panel which is vacuum insulated and which is configured and fitted to the multiple tank wall in a manner that the heat ingress into the cryogenic tank is minimized and that no vacuum is impacted by opening and closing the removable closure.
A display device for an aircraft cabin, comprising a first display directed to a first direction, a second display directed to a second direction different from the first direction, a mount for mounting the first display and the second display to a wall of the aircraft cabin, and a controller configured to control a first image displayed on the first display and a second image displayed on the second display, wherein the first direction and the second direction form an angle (γ) of greater than about 90°. Also an aircraft cabin, comprising the display device, and a method for assembling an aircraft cabin.
A leakage sensitive arrangement to improve detection of a leakage of a substance includes an emission generating compound that is applicable on an outside of an enclosure encapsulating a substance from the surroundings. The applied emission generating compound is configured to be exposed to an activation energy resulting from leaking substance from the inside of the enclosure. The activation energy causes a chemical reaction of the emission generating compound. The chemical reaction actively produces an emission detectable by a detector.
An aerodynamic system includes a support structure and an aerodynamic component movably coupled to the support structure via first and second coupling units such that the aerodynamic component can be moved relative to the support structure. The first and second coupling units can transfer a load from the aerodynamic component to the support structure. The system further includes an auxiliary coupling unit coupled between the aerodynamic component and the support structure, and configured to switch from a decoupling state to a coupling state, wherein, in the decoupling state, a load transfer via the at least one auxiliary coupling unit is prevented, and wherein, in the coupling state, a load transfer via the at least one auxiliary coupling unit is enabled.
A simulation of efforts applied to positioners to support the fuselage and the airfoil of an aircraft during operations of assembly is performed. The efforts are defined in a digital model of a load plan of the aircraft in assembly phase. The simulation is performed using the load plan digital model of the aircraft in assembly phase and a digital model of each positioner in the form of a set of three equivalent springs defined by three respective eigenvectors associated with three respective eigenvalues, in which the eigenvalues provide rigidity values and the eigenvectors provide directions on which the respective eigenvalues are applied. Thus, the simulation times are reduced.
G06F 30/20 - Design optimisation, verification or simulation
98.
METHOD FOR ASSEMBLING AN AIRCRAFT CENTRAL WING BOX INVOLVING A STEP OF FASTENING THE EQUIPMENT TO AT LEAST ONE ASSEMBLY SUPPORT SITUATED OUTSIDE THE CENTRAL WING BOX
A method for assembling a central wing box for an aircraft by assembling the upper and lower panels and the front and rear spars in order to obtain a main structure, fastening equipment to at least one assembly support positioned outside the main structure, inserting at least one mounting support inside the main structure, and securing the assembly support to the main structure. Also a central wing box and an aircraft having such a central wing box.
A foldable moveable member for an air vehicle. The moveable member includes a sheet. The sheet has a first portion, a second portion, and a fold region. The first portion is connected to the second portion via the fold region, and the fold region comprises a plurality of holes such that the stiffness of the fold region is lower than the first or second portion. The fold region, the first portion, and the second portion form a continuous surface.
04 - Industrial oils and greases; lubricants; fuels
07 - Machines and machine tools
12 - Land, air and water vehicles; parts of land vehicles
42 - Scientific, technological and industrial services, research and design
Goods & Services
Fuel; Hydrogen fuel. Aircraft engines and air vehicles, parts and components thereof; Aeronautical engines; Hydrogen engines, For use with the following goods: Aircraft and Air vehicles; Combustion engines for aircraft and Combustion engines for aircraft; Hybrid motors, For use with the following goods: Aircraft and Air vehicles; Internal combustion engines For experimental purposes, For use with the following goods: Aircraft and Air vehicles; Propulsion mechanisms for aircraft and propulsion mechanisms for air vehicles. Vehicles; apparatus for transport and locomotion by land, air, water and rail; Air vehicles; Aircraft; Unmanned aerial vehicles (UAVs); Helicopters; Drones; Parts, components, connectors structural parts of aircraft. Engineering services; Engineering research; Engineering design and consultancy; Research in the technological field of superconductivity; Testing services, in relation to the following fields: aviation; Conducting industrial tests, Conducting industrial experiments; Scientific research, Industrial research, in the field of aviation; Technical research, in the field of aviation; Aeronautical research; industrial analisys, Industrial research, in the field of aviation; Design and development services in the field of aviation; Design of prototypes; Design of vehicles.
