A method of determining at a given time at least one position of a mobile structure by determining at least one speed of the mobile structure at the given time, comparing the speed determined with listed speeds each associated with a listed position, and determining the position of the mobile structure at the given time that corresponds to the listed position associated with the listed speed equal to or closest to the speed determined at the given time. Also, a device for executing the method and an aircraft including at least one such device.
An aircraft galley system comprising a temperature adjusting loop, in which a heat exchanger fluid is circulated; a temperature adjusting unit configured to cool the fluid in the temperature adjusting loop, and compartments configured to be cooled by heat exchangers supplied with the fluid from the temperature adjusting loop. Also an aircraft with an aircraft galley comprising the galley system.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
An aircraft galley compartment comprising: at least one port accessible from the inside of the compartment and configured to connect to a compartment temperature adjusting unit. Also an aircraft galley system with an aircraft galley, such a compartment; a compartment temperature adjusting unit for cooling the inside of the compartment and being connected to the at least one port of the compartment; and a waste heat conduct configured to distribute the waste heat from the compartment temperature adjusting unit to at least one specific location of the aircraft galley that is different from the compartment. Also an aircraft with such a galley system or galley compartment.
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
5.
SYSTEM AND METHOD FOR REPAIRING AIRCRAFT STRUCTURES
A system for repairing aircraft structures comprises a frame that is divided into two portions, and one or more straps that attach both portions of the frame to each other. A method of repairing includes the step of making a cutout in the skin of the structure to be repaired; dividing the frame into two portions; placing the two portions of the frame on the internal side of the skin through the cutout; and attaching the two portions of the frame to each other by one or more straps.
ABCABCBCC) connecting with the secondary platform. The secondary mirror is positioned beyond these top ends in a volume delimited by straight lines extending the bars, at least in the deployed configuration.
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 23/16 - HousingsCapsMountingsSupports, e.g. with counterweight
B64G 1/22 - Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
7.
METHOD AND SPACE SYSTEM FOR EJECTING AT LEAST TWO SATELLITES FROM A LAUNCHER
Disclosed is a method for ejecting at least two satellites (2; 2a, 2b) from a launcher (3), said at least two satellites (2; 2a, 2b) being oriented along a central axis coinciding with a longitudinal axis (A) of the launcher and secured together side by side, the method comprising: a. an initial orientation of the direction of the longitudinal axis (A) of the launcher, so as to form a predetermined angle (θ) with an orbital speed axis (X), the predetermined angle (θ) being between 20° and 60°, b. a first separation comprising the simultaneous separation from the launcher (3) of said satellites (2; 2a, 2b) along the longitudinal axis (A) with a first predetermined differential speed (dV1) relative to the launcher (3), said at least two satellites (2; 2a, 2b) remaining secured together, then c. a second separation comprising the separation of said satellites (2; 2a, 2b) from each other along an axis perpendicular to the central axis and included in the orbital plane, with a second predetermined differential speed (dV2).
A threat estimation system arranged to provide a first artificial neural network (ANN) that operates in accordance with a first set of weight values, and an engagement planner. The threat estimation system is arranged to receive a source of sensor data; estimate from the sensor data, using the first ANN, a threat result for a threat indicated by the sensor data; and determine from the threat result, using the engagement planner, a threat action to be performed. The threat estimation system is further arranged to receive an updated first set of weight values for the first ANN, and update the first ANN to operate in accordance with the updated first set of weight values.
G06N 3/044 - Recurrent networks, e.g. Hopfield networks
G01S 7/41 - Details of systems according to groups , , of systems according to group using analysis of echo signal for target characterisationTarget signatureTarget cross-section
G08B 31/00 - Predictive alarm systems characterised by extrapolation or other computation using updated historic data
9.
METHOD FOR DETERMINING AT LEAST ONE CHARACTERISTIC OF A MOVEMENT OF A MOBILE STRUCTURE OF AN AIRCRAFT AND AIRCRAFT COMPRISING A DEVICE FOR ITS IMPLEMENTATION
A method for determining, at a given moment in time, at least one characteristic of a movement of a mobile structure of an aircraft. The method includes determining a pair of coordinates in a reference plane corresponding to a projection of a reference feature forming part of the mobile structure in the reference plane, determining the characteristic of the movement of the mobile structure by comparing the pair of coordinates previously determined with reference coordinate pairs, at least one characteristic of the movement of the mobile structure being associated with each pair of reference coordinates. Also an aircraft having a device for implementing the method.
An aircraft cabin trolley, including: a body with a top, a bottom, a front and a rear, wherein a door for accessing the inside of the trolley is provided at the front, which is the operator side of the trolley; an electrical cooling unit, including a compressor, an evaporator and a condenser, configured to actively cool the inside of the trolley; and a power transfer unit configured to transfer electrical power from a power source outside the trolley to the cooling unit. An aircraft galley arrangement including the aircraft cabin trolley, wherein the power transfer unit is configured to dock with a galley power transfer unit on a galley wall. An aircraft with at least one of the aforementioned.
A water tank, including: a dry ice compartment arranged inside the tank to be brought in contact with water to be cooled inside the tank. The compartment is provided with a hole for discharging evaporated gas from the compartment into a space that is closer to a top wall of the tank than a bottom wall of the tank. A side wall of the tank connects the top and the bottom walls of the tank, and extends above the water volume within the tank. A water outlet extends from the bottom wall of the tank. An aircraft cabin trolley, an aircraft galley and an aircraft with such a water tank are also provided.
A system for making a finished component having a three-dimensional (3D) reinforcement integrally formed within a cured additive manufacturing fluid via an additive manufacturing process. The system includes a transport having the 3D reinforcement attached thereto, the transport being used to at least partially immerse the 3D reinforcement within the additive manufacturing fluid in an uncured state; an energy source that emits energy, which changes the additive manufacturing fluid from an uncured state to a cured state, to a focal point; and a controller that controls a position of the focal point to pass over at least a portion of an outer surface of the 3D reinforcement according to a curing pattern, changing the additive manufacturing fluid from the uncured state to the cured state on the portion of the outer surface of the 3D reinforcement defined by the curing pattern as the curing pattern is executed by the controller.
B29C 64/165 - Processes of additive manufacturing using a combination of solid and fluid materials, e.g. a powder selectively bound by a liquid binder, catalyst, inhibitor or energy absorber
A decompression panel includes a frame provided with an opening and a flap connected to the frame by a connecting system comprising at least one elastomer part provided with a plurality of fixing elements fixing together the elastomer part, the frame, and the flap. The flap is moved from a closed position in which it completely closes the opening to an open position in which it partially frees the opening because of the effect of a pressure difference between the two sides of the decompression panel in the event of rapid decompression.
An assistance system and method for assisting with the restart of at least one engine of an aircraft includes determining that at least one engine of the aircraft has flamed out and controlling an automated descent of the aircraft down to a predefined target altitude below which the altitude of the aircraft is conducive to at least one attempt to restart the at least one stopped engine.
An engine mounting system comprising an engine with a center of thrust, a first engine mount having a longitudinal axis that intersects with the center of thrust, a second engine mount having a longitudinal axis that intersects with the center of thrust, the longitudinal axis of the first engine mount intersecting the longitudinal axis of the second engine mount at the center of thrust, wherein the engine includes a first connection point at a first point on the engine, the first engine mount to couple the first connection point to a pylon, a second connection point at a second point on the engine, the second engine mount to couple the second connection point to the pylon, and a third connection point at a third point on the engine symmetrical to the second point across a centerline, the second engine mount to couple the third connection point to the pylon.
This invention relates to an engine mounting assembly comprising a forward engine mount coupled to a pylon of the aircraft and an engine, the engine having a propeller with a center of thrust, the forward engine mount having a longitudinal axis that intersects with the center of thrust, an intermediate engine mount including at least two thrust links coupled to the pylon and the engine aft of the forward engine mount, the intermediate engine mount having a longitudinal axis that intersects with the center of thrust, wherein the longitudinal axis of the forward engine mount and the longitudinal axis of the intermediate engine mount intersect at the center of thrust, and a rear engine mount coupled to the pylon and the engine aft of the intermediate engine mount.
A rig for testing thermomechanical loads comprises grip portions for gripping a test specimen, and a frame that join the grip portions to each other, the thermal expansion coefficient of the grip portions being greater than the thermal expansion coefficient of the frame. The frame may be made from metal.
09 - Scientific and electric apparatus and instruments
16 - Paper, cardboard and goods made from these materials
35 - Advertising and business services
38 - Telecommunications services
42 - Scientific, technological and industrial services, research and design
45 - Legal and security services; personal services for individuals.
Goods & Services
Airborne data acquisition instruments; Observation instruments, especially, cameras, radar sensors, ultraviolet sensors, infrared sensors; Computer software for the airborne surveillance and monitoring of the environments, especially, natural environments, urban environments, agricultural environments, maritime environments, and forests; Computer software for the airborne surveillance and monitoring of the infrastructure, especially, buildings, roads, power supplies, movement of vehicles and people; Computer software for the airborne surveillance and monitoring of emergency situations; Computer software for airborne surveillance and monitoring for military missions; Computer software for airborne surveillance and monitoring of the environment for supporting military missions; Computer software for airborne surveillance and monitoring of the infrastructure for supporting military missions; Computer software for the provision of geographical information for supporting military missions. Printed matter; Satellite photographs; Plastic foils, films and bags of plastic for packaging and wrapping. Data processing, systematization, analysis and management services, especially, in the fields of geographical data, environmental data, infrastructural data, agricultural data, maritime data, and forestry data; Data processing, systematization, analysis and management services, especially, in the fields of geographical data, environmental data, infrastructural data, maritime data, and forestry data for supporting military missions. Providing access to computer databases and data in computer networks; Telecommunication services via satellites; Satellite transmission services; Communications by computer terminals in the field of satellite data and imagery; Provision of access to a global computer network; Computer-assisted transmission of messages and images in the field of satellite data and imagery; Satellite television broadcasting services; Transmission of data and information by satellite; Transmission of signals by satellite; Sound and image transmission by satellite; Broadcasting and transmission of television and radio programs by satellite; Transmission of audio and video content via satellite; Digital transmission services by satellite; Transmission of sound and images by interactive multimedia network; Satellite transmission of messages and data for air navigation. Data warehousing services, especially, for geographical data, environmental data, infrastructural data, agricultural data, maritime data, and forestry data; Data warehousing services, especially, for geographical data, environmental data, infrastructural data, maritime data, and forestry data for supporting military missions; Software development for the airborne surveillance and monitoring of the environments, especially, natural environments, urban environments, agricultural environments, maritime environments, and forests; Software development for the airborne surveillance and monitoring of infrastructure, especially, buildings, roads, power supplies, and movement of vehicles and people; Software development for the airborne surveillance and monitoring of emergency situations; Airborne surveillance and monitoring services for environmental purposes, especially, natural environments, urban environments, agricultural environments, maritime environments, and forests; Airborne surveillance and monitoring services for infrastructure, especially, buildings, roads, power supplies, movement of vehicles and people; Airborne surveillance and monitoring services for emergency situations; Provision of geographical information services; Scientific and technological evaluation, estimation, research and reports in the field of satellite data and imagery; Expertise services of engineers in the scientific and technological fields; Industrial analysis and research services in the field of satellite data and imagery; Consultancy on environmental protection; Technical project studies; Oil-field surveys; Geological surveys; Geological research; Analysis for oil-field exploitation; Land surveys; Oil prospecting; Urban planning services; Geological prospecting; Recovery of computer data; Software design and development in the field of satellite data and imagery; Surveying services (engineering). Intellectual property licensing services; Airborne surveillance and monitoring services for military missions; Airborne surveillance and monitoring services of the environment for supporting military missions; Airborne surveillance and monitoring services of the infrastructure for supporting military missions; Provision of geographical information services for supporting military missions.
19.
METHOD FOR TRANSMITTING CONTENT WITH THE AID OF A QUANTUM KEY DISTRIBUTION NETWORK
A method for transmitting content in a communication network comprising a quantum key distribution network of quantum keys, the communication network comprising a key manager device connected to transmission nodes and connected to the quantum key distribution network, the transmission nodes communicating in the communication network and transmitting and receiving quantum keys in the quantum key distribution network, the method comprising sending and receiving control messages to and from the control plane manager to organize the transfer of the content in the communication network. The control messages comprise hash values to identify quantum keys. Also a control plane manager device, a transmission node, and a computer program.
H04L 9/32 - Arrangements for secret or secure communicationsNetwork security protocols including means for verifying the identity or authority of a user of the system
A semantic routing method for time varying networks, wherein the method is configured to provide a congestion-aware source-based routing for satellites, preferably LEO constellations, with a distributed name resolution system, comprising a multitude of routers, a multitude of border routers, and a service provider. Wherein the method comprises an announcement phase and a forwarding phase executed in a proactive mode or a reactive mode.
A propulsion assembly comprising a cowling delimiting an internal zone, an engine which operates on hydrogen, a hydrogen conduit which is connected to the engine and which is positioned in the internal zone, a zone for ejecting debris and an inert gas container which is positioned around or in the vicinity of the hydrogen conduit and which is configured to be perforated or ruptured when it is struck by debris originating from the engine. Also an aircraft comprising at least one such propulsion assembly.
B64D 37/32 - Safety measures not otherwise provided for, e.g. preventing explosive conditions
22.
ACOUSTIC ABSORPTION STRUCTURE COMPRISING A CELLULAR STRUCTURE AND AT LEAST ONE PARTITION TUBE WHICH HAS AT LEAST TWO FLAT SIDES WHICH ARE CONNECTED TO THE WALLS OF THE CELLULAR STRUCTURE
An acoustic absorption structure includes at least one cellular structure interposed between an acoustically resistive layer and a reflective layer, which includes cells and at least one partition tube positioned in one of the cells and configured to delimit in the cell two cavities forming two resonators. The partition tube includes at least two flat sides, the walls which delimit the cell into which the partition tube is inserted including at least first and second planar fixing walls against which the flat sides of the partition tube are placed and fixed, and at least two remote walls which are spaced apart from the lateral wall of the partition tube.
A thermal assembly including a heat exchanger including a central matrix including a first assembly, an inlet module configured to cause a first fluid to enter the central matrix, and an outlet module configured to evacuate the first fluid from the central matrix, and a support including a base to be fixed to the propulsion system and rails rigidly fastened to the base including a second assembly cooperating with the first assembly to form a sliding connection. Also an aircraft with such a heat exchanger.
A structural arrangement for an elongated nose region of a rotary-wing aircraft, including a nose structure that comprises an outer shell with a first shell section and a second shell section arranged diametrically opposed thereto; a first frame; a second frame that is longitudinally spaced apart from the first frame; at least two longitudinal beams which extend on the second shell section between the first frame and the second frame; at least one nose structure floor supported by the at least two longitudinal beams inside of the nose structure; and a center wall that is arranged between the nose structure floor 360 and the first shell section and that extends from the first frame to the second frame.
A restraining device for restraining a wheelchair in a cabin area on board of an aircraft. The device comprises a beam-like base structure being elongate in a beam extension direction, at least two floor connectors attached to the base structure and at least one restraining connector attached to the base structure. The floor connectors are spaced apart from each other in the beam extension direction. The floor connectors are configured to temporarily mount the base structure to a seat rail floor support in an aircraft cabin. The restraining connectors are configured to be temporarily connected to a structural part of the wheelchair to hold the wheelchair in place with a passenger seated therein.
An assembly for reinforcing a fuselage of an aircraft, the aircraft including a fuselage including an opening and a removable panel received in the opening. The assembly including a first support fixed to an exterior face of the fuselage around and outside an opening in the fixed fuselage. A sub-assembly is to an exterior face of the removable panel and housed inside the first support. The first support is fixed to the fuselage. The sub-assembly is fixed to the removable panel.
An inerting system for an aircraft and a method of inerting fuel cell systems. The inerting system injects inert gas into a casing around the fuel cells in a distributed manner to ensure a correct dissolution of flammable agents like oxygen and hydrogen that could be present inside the casing around the fuel cells.
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 controlling a hybrid power plant of a vehicle provided with a heat engine and at least one electrical unit comprising an electric machine, an electrical energy source, and a power management unit, the heat engine and the at least one electric machine being mechanically connected to input shafts of a gearbox. After acquiring parameters of the at least one electrical unit, and receiving a mechanical power requirement of the vehicle, a usable electrical power that can be used by the electrical unit and at least one operating setpoint of the electrical unit are determined as a function of the parameters and the mechanical power requirement. Finally, the heat engine and the electrical unit are controlled as a function of the at least one operating setpoint in order to meet the mechanical power requirement.
B64D 31/18 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants for hybrid-electric power plants
An air/particle separation device which comprises a container and a rotary filter positioned in the container, between a laden-air inlet and a treated-air outlet, the container is configured to channel air laden with particles through the rotary filter, the rotary filter comprises at least one block of cellular material configured to be passed through by the laden air and to promote the separation of the particles from the laden air and the ejection of the particles from the rotary filter which migrate, by virtue of the centrifugal effect, toward the periphery of the rotary filter.
A connection interface for mounting a building component to a support structure. The connection interface comprises at least one connector and at least one aligner. The connector comprises: a primary fastening region at a first end configured to be fastened to one of a first plurality of mounting points at the support structure and a secondary fastening region at a second end configured to be fastened to one of a second plurality of mounting points at the building component. The aligner is arranged between the first end and the second end; and wherein the aligner is configured to align the connector in an oriented manner according to an alignment value for bringing the building component and the support structure in an alignment arrangement. The aligner provides an adjustment in at least two spatial directions.
F16M 13/02 - Other supports for positioning apparatus or articlesMeans for steadying hand-held apparatus or articles for supporting on, or attaching to, an object, e.g. tree, gate, window-frame, cycle
A method for monitoring the operation of a power plant of a rotorcraft and a rotorcraft comprising at least one lift rotor rotated by the power plant comprising at least one engine. Such a rotorcraft comprises a monitoring system comprising at least one failure sensor detecting a regulation failure affecting a regulation system of the at least one engine, a speed sensor measuring a current speed of rotation of the at least one lift rotor and a controller determining whether there is a condition of compatibility or a condition of incompatibility between a current flight phase and the speed of rotation.
A method for monitoring an energy level of an electrical energy source capable of delivering a reference electrical power PRef for a reference time period DTRef for a reference charge level NRef. Said source comprises at least one electrical energy storage device and several sensors. Said method comprises using the sensors to acquire parameters of the electrical energy source, then calculating a main consumption time period DTprin wherein the source is able to supply an electric current carrying the reference electrical power PRef, as a function of the parameters of the source. Next, a main display of main symbols indicating the main consumption time period DTprin is displayed in order to indicate to an operator how long the source can supply the reference electrical power PRef.
A data network for aircraft cabin devices including a network controller, and a plurality of cabin device modules connected to the network controller via a plurality of Single-Pair Ethernet, SPE, communication links. Each of the plurality of cabin device modules comprises an SPE switch coupled to the network controller via one of the plurality of SPE communication links, and at least two module nodes coupled in daisy-chain topology to the SPE switch.
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
An assessment method, a corresponding assessment program, a computer-readable data-carrier having stored thereon the assessment program, a computing device configured to carry out the assessment program and/or comprising the computer-readable data-carrier, and an assessment arrangement for a computer assisted assessment of at least one property parameter. Generally, the method includes obtaining a molecular structure of the chemical substance; obtaining at least one reference structure of at least one reference substance having at least one reference parameter, comparing the molecular structure to the at least one reference structure; and deriving the at least one property parameter from the comparison based on the at least one reference parameter.
Disclosed is a method of exchanging cryptographic parameters in a network of tire monitoring devices, the method including broadcasting, from each tire monitoring device to a plurality of other tire monitoring devices, a message comprising a cryptographic parameter generated by that respective tire monitoring device.
A method for controlling a superconducting electrical supply line that is carried out in a control circuit obtains a piece of information representative of a first electric current in the superconducting electrical supply line, then, when the piece of information representative of a first electric current is greater than or equal to a first predetermined threshold value, generates a current, referred to as the second current, in a superconducting coil arranged in the vicinity of the supply line, the value of the second current being determined on the basis of the piece of information representative of the first current. A control circuit is configured to implement the method. Current limiter functions are reversibly performed by initiating a quench phenomenon in the superconducting electrical supply line.
H02H 7/00 - Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions
40.
ENERGY CONVERSION ARRANGEMENT, ENERGY SYSTEM AND AIRCRAFT COMPRISING SAME
An energy conversion arrangement for an aircraft, an energy system and an aircraft including 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, for converting at least one fuel to electrical and/or mechanical energy, and an exhaust outlet for letting out exhausts produced in the fuel conversion device by the fuel conversion. At least one heating device is arranged in a flow path of the exhausts before the exhaust outlet which is configured to heat up the exhausts.
B60L 50/70 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by fuel cells
B60L 1/02 - Supplying electric power to auxiliary equipment of electrically-propelled vehicles to electric heating circuits
B60L 50/90 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by specific means not covered by groups , e.g. by direct conversion of thermal nuclear energy into electricity
B64D 33/04 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
An energy conversion arrangement for an aircraft, an energy system and an aircraft including 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, for converting at least one fuel to electrical and/or mechanical energy; an expansion device arranged in a flow path of exhausts produced in the fuel conversion device and configured to decompress the exhausts; an exhaust outlet for letting out exhausts produced in the fuel conversion device by the fuel conversion; and at least one bypass duct configured to allow the exhausts to bypass the expansion device on their way from the fuel conversion device to the exhaust outlet.
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
42.
ASSEMBLY OF AN ENGINE MOUNTING PYLON WITH AN AIRCRAFT ENGINE
A front engine mount system for an aircraft comprising an assembly secured, on the one hand, to the engine mounting pylon and, on the other hand, to a set of front fittings of an engine; the assembly being situated at the front of the engine/engine mounting pylon assembly and having, on the one hand, a central articulation system articulated to the clevis block of the engine and two lateral articulation systems connected to the engine.
A method for controlling the position of an end effector of a multi-axis robot, in particular used to drill aeronautical-equipment parts in a first direction. The method regulates the clamping force of the tool against a workpiece in the first direction while automatically controlling the position of the end effector in two other directions that are perpendicular to each other and each perpendicular to the first direction, based on pieces of information representative of forces oriented in the first direction and obtained from three separate sensors. A control device is configured to execute the method for positioning the end effector. Reducing or preventing slippage of a tool over a workpiece improves the quality of machining operations carried out by the tool-bearing end effector.
METHOD TO PRODUCE A RECYCLED MATERIAL WITH PREFERRED ORIENTATION OF FIBRES FROM THE MULTILAYER UNCURED PREPREG SCRAP GENERATED IN THE MANUFACTURING OF AERONAUTICAL PARTS WITH PREPREG MATERIAL
A method to produce a recycled material with preferred orientation of fibers from the multilayer uncured prepreg scrap generated in the manufacturing of aeronautical parts with prepreg material, comprising: collection of the unused scrap from the manufacturing of aeronautical parts; removal of materials other than the prepreg material of the scrap; transfer of the scrap free of additional materials to a cutting station; cutting the scrap in strips parallel to the predominant orientation of the fibers in the cutting station; transfer of the strips to a station of several successive stages of rollers, and the strips pass through each successive stage of rollers in the station, such that the thickness of the strips is progressively reduced after passing through each successive stage of rollers in the station.
B29B 17/00 - Recovery of plastics or other constituents of waste material containing plastics
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
An image projector to be installed in a space used for placing a dead mass to mitigate aeroelastic vibrations suffered by the horizontal stabilizer of an aircraft. The image projector replaces the dead mass. The image projector may be connectable to the surface of a closed rib of the horizontal stabilizer. The image projector may include a structural features configured to mitigate at least the same aeroelastic vibrations as the dead mass. The image projector is configured to project at least one image.
An aircraft fuselage section extending along a longitudinal direction including: a fuselage structure comprising a plurality of frames; a floor connected to the fuselage structure; a cushioning element arranged on the floor, and a crash absorption assembly between the fuselage structure and the floor, wherein the crash absorption assembly includes first absorption elements and second absorption elements distributed along the longitudinal direction, wherein the first absorption elements and the second absorption elements are configured to dissipate and distribute energy; and wherein the first absorption elements are each arranged at a position corresponding to a frame of the fuselage structure and the second absorption elements are each arranged at a position between successive frames of the fuselage structure.
A wing for an aircraft, including a main wing and a slat assembly including a slat and at least one connection assembly movably connecting the slat to the main wing, such that the slat is movable between a retracted position and at least one extended position, such that the connection assembly has an elongate slat track, and the front end of the slat track is mounted to the slat, such that the rear end and/or the intermediate portion of the slat track are mounted to the main wing by a roller or slide bearing such that the slat track is movable along the track longitudinal axis, such that the connection assembly has a drive unit configured for driving the slat track, such that the drive unit includes a rotary actuator having at least one drive arm rotatably driven about a rotation axis and drivingly engaging the slat track.
An energy conversion arrangement for an aircraft, an energy system and an aircraft including 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, for converting at least one fuel to electrical and/or mechanical energy, and an exhaust outlet for letting out exhausts produced in the fuel conversion device by the fuel conversion. At least one mixing assembly is arranged in a flow path of the exhausts before and/or after the exhaust outlet and is configured to mix the exhausts with further exhausts from the energy conversion arrangement.
B60L 50/70 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by fuel cells
B60L 50/90 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by specific means not covered by groups , e.g. by direct conversion of thermal nuclear energy into electricity
B64D 33/04 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
A method to load sub-modules into a aerostructure of an aircraft including: providing each sub-module with a connecting element wherein first holes are drilled in each of connecting element; drilling a second holes in the aerostructure a pattern corresponding to the first set of holes; assembling the at least one module assembly and the connecting elements by matching the second holes in the at least one structural part with corresponding ones of the first holes in the connecting elements and securing the sub-modules to the aerostructure by aligning the first holes to the second holes and attaching fasteners to the aligned holes, and attaching a connection between the sub-modules in the aerostructure.
Disclosed is a brake component (151) comprising a composite material (200), the composite material comprising a matrix (202) and reinforcements (201) embedded in and supported by the matrix, wherein the matrix is a glass-ceramic matrix. Also disclosed is a braking system, an aircraft braking system, an aircraft and a method of operating an aircraft.
F16D 65/18 - Actuating mechanisms for brakesMeans for initiating operation at a predetermined position arranged in or on the brake adapted for drawing members together
An aircraft including a wing with a fixed wing portion and a wing tip device rotatably hingedly attached at a fixed wing portion outboard end. The wing includes a wing fold mechanism configured to actuate the wing tip device to rotate relative to the fixed wing portion to at least three commanded and predetermined wing fold angles and to restrain rotational movement of the wing tip device at each commanded position. A first position corresponds to high-speed flying, a second position to ground-based operations and a third position to low-speed flying. The flying positions rotate the wing tip to a position where upper and lower wing tip surfaces are continuations of the upper and lower surfaces of the fixed wing, with a low-speed incidence angle being less than a high-speed incidence angle. The ground-based position reduces the wing span to the greatest degree of the three positions.
Metamaterials, and associated methods and apparatuses An apparatus 150 comprising a control system 200 and a metamaterial 201 electronically controlled by the control system 200, the control system including an electrical network 224 and a plurality of independently controllable impedance elements 223a, 223b, 223c, 223d, wherein each of the plurality of independently controllable impedance elements 223a, 223b, 223c, 223d is arranged to be switched between a first state in which at least one of the plurality of independently controllable impedance elements 223a, 223b, 223c, 223d is electrically connected to the electrical network 224 and a second state in which at least one of the plurality of independently controllable impedance elements 223a, 223b, 223c, 223d is electrically disconnected. This provides a plurality of discrete impedance values in the metamaterial 201 according to the combination of impedance elements in the first or second state. Also disclosed are related control systems, methods of control and vehicles.
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
38 - Telecommunications services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Appareils et instruments de communication en rapport avec les véhicules aériens; Appareils et instruments électriques et électroniques de contrôle en rapport avec véhicules aériens; Appareils et instruments de navigation en rapport avec véhicules aériens; Appareils et instruments de mesure en rapport avec véhicules aériens; Appareils et instruments utilisés pour la commande et la surveillance de véhicules aériens; Appareils et instruments pour la communication de données; Logiciels; Logiciels d'applications; Simulateur de vol; Plateformes logicielles, enregistrées ou téléchargeables; Logiciels de stockage, de gestion et de traitement de données; Equipement et système de traitement de données; Bases de données; Programmes informatiques pour l'accès, la navigation et la recherche dans des bases de données en ligne; Logiciels de gestion de bases de données dans le domaine de l’aviation; Logiciel interactif pour ordinateur et appareils mobiles fournissant des informations de navigation et de voyage en relation avec les véhicules aériens. Véhicules aériens; Aéronefs; Avions; Pièces, composants et parties constitutives pour véhicules aériens. Services de télécommunications; Transmission de données; Fourniture d'accès à des bases de données; Services de communication informatique et accès à internet; Services de communication par satellite; Communications via un réseau informatique mondial ou Internet; Services de fourniture d'accès à Internet. Service de développement (conception), installation, maintenance, mise à jour et location de logiciels; Logiciel-service [SaaS]; Développement de plateformes informatiques; Plateforme informatique en tant que service [PaaS]; Services d'analyse de données techniques; Sécurisation de données.
55.
ELECTRONIC CONNECTORS FOR USE ON BOARD A SPACECRAFT
An electronic device (1) suitable for use on board a spacecraft, including a motherboard (2) electrically connected to daughterboards (3a, 3b, 3c), the motherboard and the daughterboards each include a support plate (4a, 4b, 4c, 5) in order to form a printed circuit board, each support plate extending in a respective main plane, wherein each daughterboard includes a first electrical connector (6a, 6b, 6c, 6d) fixed to its support plate and the motherboard includes a corresponding number of second connectors (7a, 7b, 7c, 7d) fixed to the support plate of the motherboard, each first electrical connector engages with one of the second connectors, the first electrical connector of each daughterboard is arranged on a portion of the support plate forming a tab (8a, 8b, 8c, 8d) configured for deflection relative to the main plane of the printed circuit board.
H01R 12/73 - Coupling devices for rigid printing circuits or like structures coupling with the edge of the rigid printed circuits or like structures connecting to other rigid printed circuits or like structures
A method for a soft-start strategy of a fuel cell includes: providing a fuel cell, wherein the fuel cell is connected to load, providing a capacitor, wherein the capacitor is connected in between the fuel cell and the load, wherein the fuel cell includes an anode and a cathode and the anode and the cathode are in a preconditioned state, the method further including filling the cathode with a mass rate derived from a proportion of an input gas and a used gas, and a predefined current, such that the predefined current does not exceed a maximum current during a precharge of the capacitor.
A transmission welding apparatus for welding thermoplastic resin material parts includes at least one heat source emitting thermal radiation, and at least one pressure device adapted to apply a welding pressure on the material parts. The at least one pressure device includes at least one pressure generator for supplying a pressure force, at least one pressure plate which is permeable to the thermal radiation and which is adapted to introduce the pressure force into the material parts, and at least one pressure transmission system for transferring the pressure force to the pressure plate, such that the at least one pressure plate is segmented into a plurality of plate segments which are arranged movable relative to one another.
B29C 65/20 - Joining of preformed partsApparatus therefor by heating, with or without pressure using heated tool with direct contact, e.g. using "mirror"
B29C 65/00 - Joining of preformed partsApparatus therefor
A fuel line, terminating in a refuel connector, is used to fuel/defuel an aircraft, for example with liquid hydrogen. A barrier is disposed around the area where the refuel connector connects to an aircraft fuel port, and is sealed against the aircraft wing with a seal. A gas line runs generally parallel to the aircraft fuel line, and supplies inert gas, for example nitrogen, into the volume defined by the barrier. The inert gas flushes out air present around the refuel connector such that the oxygen concentration in that area is significantly lowered. This prevents ignition of fuel in the event of a fuel leak from the fuel line structure.
The disclosure is directed to a fuel line terminating in a refuel connector is used to fuel (or defuel) an aircraft, for example with liquid hydrogen. A barrier is deployed around the area where the refuel connector connects to an aircraft fuel port. A gas line supplies inert gas from a supply of gas, for example nitrogen, into the area defined by the barrier. The inert gas flushes out air present around the refuel connector such that the oxygen concentration in that volume is significantly lowered. This prevents ignition of fuel in the event of a fuel leak from the refuel connector. The barrier, the gas supply, and/or the outlets for the inert gas to be supplied through are provided by a part of the aircraft.
A cabin air ventilation system for an aircraft cabin comprising a riser duct configured to conduct fresh air to the aircraft cabin, and an air outlet connected to the riser duct. The air outlet includes an inlet fluidly connected to the riser duct, a main body having an outlet opening, and a plurality of vanes arranged in the outlet opening, wherein a first number of vanes is oriented in a first direction and a second number of vanes is oriented in a second direction forming an angle with the first direction. An aircraft section and an aircraft having such cabin air ventilation system are also provided.
A fixation interface includes primary connection studs and secondary attachment interface components. Each connection stud includes a longitudinal axis, a mounting foot, and an interface head arranged along the longitudinal axis. The mounting foot form-fittingly fastens to a floor fastening point. On opposite lateral sides, the interface head includes protrusions extending traverse to the longitudinal axis. Each secondary attachment interface component mounts to an interface head by form-fittingly engaging the protrusions in a longitudinal direction. Each secondary attachment interface component is positionable to the interface head region in a positioning movement and is lockable in a locking movement. Each secondary attachment interface component includes first and second types of interface components. The first type are positionable and lockable in first positioning and first locking movements, and the second type are positionable and lockable in second positioning and second locking movements, the first and second locking movements being different.
An engine protection cover device for airtight sealing an engine of an aircraft or spacecraft includes an air intake cover being inflatable to correspond to the internal dimension of the air intake for airtight sealing the same, wherein the air intake cover includes an airtight sealable access opening for attaching or passing through an air dryer for drying the air inside the engine. An aircraft or spacecraft is disclosed with such an engine protection cover device.
B64F 1/00 - Ground or aircraft-carrier-deck installations
F02C 7/055 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with intake grids, screens or guards
63.
DEVICE FOR ABSORBING ENERGY BY COMPRESSION, AIRCRAFT COMPRISING AT LEAST ONE SUCH DEVICE
A device for absorbing energy by compression including several first conduits spaced apart from one another and oriented in a compression direction and joining walls which are parallel to the compression direction and connect the first conduits so as to delimit, with the latter, at least one second conduit. This solution makes it possible to absorb a greater quantity of energy. An aircraft including at least one such device for absorbing energy is also disclosed.
An aircraft including first and second elements spaced apart from one another and at least one device for absorbing energy by compression, positioned between the first and second elements, including at least one module for absorbing energy by compression and at least one attachment system removably connecting each module for absorbing energy by compression to at least one of the first and second elements, at least one module for absorbing energy by compression including several first conduits oriented in a compression direction and being independent of the first and second elements.
An aircraft propulsion assembly has an engine casing, an attachment pylon, a first front engine attachment with a pin and a blade fitted on the pin and fastened in an articulated manner on either side of a median plane to the casing and a second front engine attachment with a central rod in the median plane fastened in an articulated manner to a lower wall of the attachment pylon and to a fitting of the casing. The central rod is generally parallel to a longitudinal axis. In this arrangement, the casing is brought closer to the attachment pylon for a saving in terms of height.
A propeller includes a hub, blades each provided with a shank, a pivoting connection connecting the shank of the blade and the hub and having a pivot axis and at least one holding system for holding the blade connected to the hub. The holding system is reinforced and includes at least one main stop integral with the hub and configured to be at least partially housed in a transverse groove, provided in a surface integral with the shank of the blade, which extends over at least a part of the circumference of the shank. This solution reduces the risk of blades or blade debris being ejected. An aircraft propulsion assembly includes at least one such propeller.
Fittings and joints to be attached to a removable aircraft panel and/or to a fuselage section of an aircraft. The joint includes a fitting having a body comprising: a first end, a second end, a first supporting portion and a protruding first contact portion, both the first supporting portion and the first contact portion extending between the ends. The first supporting portion is for attaching to the aircraft or fuselage section. The first contact portion contacts a complementary portion of a second fitting of the structural joint in an assembled position with the second fitting. The first contact portion comprises first main contact portion, and two first lateral contact portions, each joined to the first main contact portion, wherein the first lateral contact portions are arranged laterally with respect to the first main contact portion and are inclined with respect to the first main contact portion.
A method for encoding data defining an image is disclosed. The image is segmented into image blocks, each having a uniform block size. A frequency-based transform is applied to each providing transformed image data in which the image data is represented as coefficients defining a linear combination of predetermined basis functions having different spatial frequencies. Each block of transformed image data comprises one coefficient for a zero frequency basis function, and a plurality of coefficients for higher frequency basis functions which are grouped into one or more sub-bands. The blocks of transformed image data are grouped into slices. The coefficients of a first sub-band of each block in a slice are concatenated, and converted into binary code using binary arithmetic coding, and an end-of-slice codeword is inserted at the end of the sub-band. The concatenation/conversion is repeated for all the sub-bands in the slice, and then for all slices.
H04N 19/645 - Methods or arrangements for coding, decoding, compressing or decompressing digital video signals using transform coding using sub-band based transform, e.g. wavelets characterised by ordering of coefficients or of bits for transmission by grouping of coefficients into blocks after the transform
H04N 19/174 - Methods or arrangements for coding, decoding, compressing or decompressing digital video signals using adaptive coding characterised by the coding unit, i.e. the structural portion or semantic portion of the video signal being the object or the subject of the adaptive coding the unit being an image region, e.g. an object the region being a slice, e.g. a line of blocks or a group of blocks
H04N 19/176 - Methods or arrangements for coding, decoding, compressing or decompressing digital video signals using adaptive coding characterised by the coding unit, i.e. the structural portion or semantic portion of the video signal being the object or the subject of the adaptive coding the unit being an image region, e.g. an object the region being a block, e.g. a macroblock
69.
AIRCRAFT LIFTING SURFACE AND AIRCRAFT COMPRISING SUCH LIFTING SURFACE
A method for assisting the piloting of a rotorcraft comprising a first engine and a second engine, each capable, in the absence of a failure, of transmitting engine torque to at least one rotor providing at least lift keeping the rotorcraft in the air. The rotorcraft has aerodynamic members for piloting the rotorcraft. The method has these steps: controlling the first engine and the second engine asymmetrically, the first engine alone providing driving power to the rotor(s), the second engine operating at a standby speed; identifying an engine failure in the first engine by a failure monitor; and in the event of failure in the first engine, accelerating the second engine to a synchronization speed.
B64D 31/09 - Initiating means actuated automatically in response to power plant failure
72.
PROPULSION ASSEMBLY FOR AN AIRCRAFT COMPRISING A FLUID-COOLING CIRCUIT WITH QUICK-FIT NACELLE/ENGINE COUPLINGS AND AIRCRAFT PROVIDED WITH SUCH AN ASSEMBLY
A propulsion assembly for an aircraft with an engine; an inner structure formed by two half-shells, each half-shell articulated to a pylon and comprising a semi-cylindrical part movable between a closed position, in which the half-shell is closely fitted around the engine, and an open position, in which the half-shell is away from the engine; and, a fluid circuit. At least one half-shell has a cooling circuit connected to the fluid circuit. A detachable hydraulic interface between the fluid circuit and the cooling circuit is provided having at least two quick-fit couplings, wherein each of the quick-fit couplings comprises a pair of male/female elements configured for axial fitting of one in the other, with one element of the pair being fixed on the half-shell and the other element of the pair being integral with the engine.
A method for monitoring the coherence of an atmospheric pressure value to be used for configuring flight instruments of an aircraft includes: interrogating a database to obtain an altitude value of a selected airport; obtaining a static pressure value, a static temperature value, and a geometric altitude value, corresponding to a current situation of the aircraft; deducing therefrom an estimate of a static pressure value at the selected airport; evaluating a coherence level between the estimate and the atmospheric pressure value to be used for configuring the flight instruments of the aircraft; and generating a warning if the coherence level is below a predefined threshold.
A drive system for a lift control device of an aircraft. The drive system has first and second connection assemblies. The first connection assembly comprises a first track comprising a first end coupled to the lift control device and a track curvature having a radius of curvature; a first guiding element to absorb side loads from the first track; a first drive device to drive the first track, and a second guiding element to sense spanwise movement of the first track. The second connection assembly comprises a second track comprising a first end coupled to the lift control device; a third guiding element to absorb side loads from the second track, and a second drive device to drive the second track. The first and second drives are mechanically coupled by a transmission shaft. When the spanwise movement exceeds a threshold value, the drive system is stopped.
A hydraulic actuator for an aircraft. The hydraulic actuator comprises: a housing to accommodate hydraulic fluid; an extension chamber and a retraction chamber each defined by the housing; and a bypass line in fluid communication with the extension chamber and the retraction chamber, wherein the bypass line comprises a flow restrictor and a bypass valve, wherein the flow restrictor restricts a rate of fluid flow through the bypass line, wherein the bypass valve has material defining a port that is openable to allow the hydraulic fluid to flow through the bypass line, and wherein the material is configured to change shape, as a temperature of the material reduces to below a predetermined temperature, to thereby open the port. Also disclosed is a hydraulic actuation system, in the form of a landing gear system, comprising the hydraulic actuator, and an aircraft comprising the hydraulic actuation system.
F15B 15/14 - Fluid-actuated devices for displacing a member from one position to anotherGearing associated therewith characterised by the construction of the motor unit of the straight-cylinder type
A hydraulic actuation system for an aircraft. The system comprises: a hydraulic actuator comprising: a housing to accommodate hydraulic fluid; an extension chamber and a retraction chamber each defined by the housing; and a bypass line in fluid communication with the extension chamber and the retraction chamber, the bypass line comprising a flow restrictor and a bypass valve, the flow restrictor configured to restrict a rate of fluid flow through the bypass line; and a controller configured to receive a signal indicative that the aircraft is in a take-off or a landing procedure, to determine that the aircraft is performing the take-off or the landing procedure based on the signal, and to perform an operation to cause the bypass valve to open to allow the hydraulic fluid to flow through the bypass line only when the controller determines that the aircraft is performing the take-off or the landing procedure.
F15B 15/14 - Fluid-actuated devices for displacing a member from one position to anotherGearing associated therewith characterised by the construction of the motor unit of the straight-cylinder type
The present invention relates to a conditioning system for an aircraft. In particular, the present invention belongs to a conditioning system having a pressure accumulator connected to the heat recovery circuit and to the fuel conduct. The present invention also relates to an aircraft comprising said conditioning system.
The present invention relates to a heat exchanger for an aircraft. In particular, the present invention belongs to the field of heat exchangers configured for being mounted at the combustion gases outlet of a power unit of an aircraft. The present invention also refers to the power unit and the aircraft thereof.
B64D 33/00 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
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
The present invention relates to a conditioning system for an aircraft. In particular, the present invention belongs to a conditioning system having a new architecture including a power unit and a heat exchanger located at the output of the power unit. The present invention also relates to an aircraft comprising said conditioning system and to a method for conditioning fuel by means of the conditioning system of the invention.
12 - Land, air and water vehicles; parts of land vehicles
20 - Furniture and decorative products
Goods & Services
Lighting; electric lighting; lighting apparatus Aircraft; vehicle seats; headrests for vehicle seats; fitted seat covers for vehicles Furniture for aircraft; seats and couches and holders in the nature of seats and couches sold with cup holders therefor; seats and couches containing audio and video apparatus; beds; bedding except linen, namely, pillows; convertible seats; non-metallic trays, namely, corrugated plastic trays, computer keyboard trays, rigid plastic trays, plastic trays for use when manually counting pills, and tool and tool accessory trays not made of metal sold empty and parts and fittings therefor; cabinets; footrests; overhead bins
81.
ENGINE FAILURE TRAINING METHOD FOR A HYBRID ROTORCRAFT
A method for simulating an autorotation phase of a simulated rotorcraft. This method comprises a training phase carried out with a training rotorcraft comprising a single training combustion engine for rotating a training lift rotor. The training phase comprises assigning of a stored training value to a regulation limit, by a regulator, and regulation of the training combustion engine, by the regulator, keeping the torque parameter of the training rotorcraft less than or equal to the regulation limit, the training value being less than a nominal value, so that the training combustion engine produces a power equal to a reference power produced by a simulated electric motor.
G09B 9/46 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer the aircraft being a helicopter
A method of training a machine-learning model to identify image features is disclosed including: a. receiving a set of predicted feature regions from the machine-learning model, each predicted feature region comprising a prediction of a feature in training image data; b. generating a set of similarity coefficients, each similarity coefficient indicative of a similarity between a predicted feature region and a corresponding groundtruth region which overlaps with the predicted feature region; c. determining a loss value based on the similarity coefficients and a threshold; and d. training the machine-learning model on a basis of the loss value, wherein a.-d. are repeated, each repeat comprising a respective training epoch; in one or more of the training epochs, the set of similarity coefficients comprises one or more similarity coefficients less than the threshold, and the loss value is based on a difference between the threshold and each similarity coefficient less than the threshold.
A system for performing a laser peening application on a workpiece. A purge system is included with the system to provide a compartment housing combustion sources with compressed air so that the compartment has an increased air pressure. Also, a method of operating the system in which power is provided to the system, but only the purge system operates initially. Only after the purge system has bene operating, are the other subsystems and components of the systems, like the laser, provided with operational power.
C21D 10/00 - Modifying the physical properties by methods other than heat treatment or deformation
B23K 26/12 - Working by laser beam, e.g. welding, cutting or boring in a special environment or atmosphere, e.g. in an enclosure
B23K 26/14 - Working by laser beam, e.g. welding, cutting or boring using a fluid stream, e.g. a jet of gas, in conjunction with the laser beamNozzles therefor
B23K 26/356 - Working by laser beam, e.g. welding, cutting or boring for surface treatment by shock processing
84.
METHOD FOR ASSESSING ELECTROMAGNETIC COMPATIBILITY OF CABIN CONFIGURATIONS
A method for assessing electromagnetic compatibility (EMC) of an assembly of electronic components includes checking electronic components of the assembly as to which of the components are compliant within the framework of the overall assembly EMC; finding, for each electronic component that has been found to be non-compliant, one or more replacement electronic components of a respective analogous component type that would be considered to be acceptable within the framework of the overall assembly EMC; testing an analogous assembly of the plurality of electronic components in which at least one of the electronic components found to be non-compliant has been virtually replaced by the respectively found replacement electronic component for overall assembly EMC of the analogous assembly; and assessing the assembly of the plurality of electronic components to be overall assembly EM compatible when the analogous assembly has been found to be overall assembly EM compatible in the testing step.
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
85.
AIR ASSISTED PREPREG APPLICATION APPARATUS AND SYSTEM
A prepreg application apparatus, comprising an air supply duct having a lumen configured to guide an air stream, a prepreg compacting body configured to set a position of a prepreg, the prepreg compacting body having a porous surface in fluid communication with the lumen of the air supply duct, and configured to release air of the air stream to an area ambient to the prepreg compacting body, and an air conveying device configured to control a power of the air stream ensuring that the air emanates from the prepreg compacting body at the porous surface when being on or close to the prepreg.
B29C 70/50 - Shaping or impregnating by compression for producing articles of indefinite length, e.g. prepregs, sheet moulding compounds [SMC] or cross moulding compounds [XMC]
A joining system, between a first anterior element and a second posterior element, comprising a through hole. The joining system has a threaded bolt for passing through the through hole of the first element and the second element, a shank configured to be located concentrically to the threaded bolt in at least the anterior longitudinal zone of the threaded bolt and to move together with the threaded bolt, the shank comprising an outer face comprising at least one tapered longitudinal section, a housing attached to the second posterior element and comprising a conical inner face for housing the shank, and a clamping element configured for the threading of the posterior longitudinal zone of the threaded bolt for fastening the joining system.
An aircraft landing gear has a suspension mechanism which has a four-bar linkage that comprises four links rigidly extending between a corresponding four pivots. A lower link of the four-bar linkage supports front and rear wheels, and is movable relative to an upper link between lengthened and shortened positions. A shock absorber urges the four-bar linkage towards the lengthened position. A length of the upper link of the four-bar linkage is adjustable.
An adaptive starting method for a turboshaft engine comprising a gas generator, an electric machine connected mechanically to the gas generator and electrically to one or more electrical energy sources. A maximum electrical intensity of an electric current that can be delivered by the electrical energy hgsource or sources is determined as a function of at least one characteristic of each electrical energy source, a maximum engine torque supplied by the electric machine powered by each electrical energy source with the maximum electrical intensity is determined. The maximum engine torque is compared with a required engine torque envelope permitted by the gas generator. The maximum electrical intensity of the electric current supplied by the electrical energy source or sources is adapted in order to comply with the required envelope in order to start the gas generator.
A computer-implemented method of determining a maintenance schedule or maintenance plan for a fuel tank of an aircraft. In a training phase, a predictive model is trained with training data. The training data is associated with fuel tanks of plural aircraft. The training data comprises environmental data indicative of an environmental parameter at locations of the plural aircraft, and test data which is indicative of a level of microbial contamination of fuel in fuel tanks of the plural aircraft. In a prediction phase, input data is received and the predictive model is operated, along with an optimisation algorithm, to determine a maintenance schedule or maintenance plan. One or more microbial contamination maintenance tasks are performed on the fuel tank based on the maintenance schedule or maintenance plan.
A method of training a machine learning model to identify image features is disclosed including: a. providing training image data, the training image data comprising a plurality of pixels; b. assigning a groundtruth annotation to each pixel, each groundtruth annotation relates to a respective one of the pixels and each groundtruth annotation indicates whether or not that the pixel corresponds with an image feature; c. providing an ignore mask comprising a set of ignore flags; each ignore flag relates to a respective one of the pixels and each ignore flag provides an indication that the pixel should be ignored; d. receiving a prediction value from the machine learning model, each prediction value provides an indication of a probability of the pixel corresponding with an image feature; e. for each pixel which has no ignore flag, determining a loss value based on the prediction value and groundtruth annotation for that pixel.
G06V 20/70 - Labelling scene content, e.g. deriving syntactic or semantic representations
G06V 10/98 - Detection or correction of errors, e.g. by rescanning the pattern or by human interventionEvaluation of the quality of the acquired patterns
A method of training a machine-learning model to identify image features is disclosed including: a. providing a set of groundtruth regions, each groundtruth region comprising an annotation of a feature in training image data; b. providing a set of ignore regions; c. receiving a set of predicted feature regions from the machine-learning model, each predicted feature region comprising a prediction of a feature in the training image data; d. for each predicted feature region which overlaps with a corresponding groundtruth region, generating a similarity coefficient indicative of a similarity between the predicted feature region and the corresponding groundtruth region; e. determining a loss value based on the similarity coefficients; f. training the machine-learning model on a basis of the loss value; g. for each predicted feature region which does not overlap with any of the ignore regions and does not overlap with any of the groundtruth regions.
G06V 20/70 - Labelling scene content, e.g. deriving syntactic or semantic representations
G06V 10/74 - Image or video pattern matchingProximity measures in feature spaces
G06V 10/82 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using neural networks
G06V 10/98 - Detection or correction of errors, e.g. by rescanning the pattern or by human interventionEvaluation of the quality of the acquired patterns
92.
5G-COMPATIBLE LDPC DECODER FOR SATELLITE COMMUNICATIONS
The invention relates to a decoder (30) for decoding low-density parity-check (LDPC) codewords. The decoder includes at least one core (10) and a memory (20) in which a number NC of predefined configurations is stored. The core is suitable for being dynamically configured with any one of the NC predefined configurations stored in the memory in order to decode an LDPC codeword using this configuration. The NC predefined configurations form a sub-group, in the strict sense, of 5G LDPC configurations defined in the 3GPP TS 38.212 standard. Each configuration corresponds to a triplet of three parameters {K, R, Z}, and to a parity matrix constructed according to at least a portion of these parameters. K is a message size encoded by the LDPC code, Z is an expansion factor of the parity matrix, and R is a code rate of the LDPC code. Advantageously, the NC predefined configurations include different values of the parameter Z.
H03M 13/11 - Error detection or forward error correction by redundancy in data representation, i.e. code words containing more digits than the source words using block codes, i.e. a predetermined number of check bits joined to a predetermined number of information bits using multiple parity bits
H03M 13/00 - Coding, decoding or code conversion, for error detection or error correctionCoding theory basic assumptionsCoding boundsError probability evaluation methodsChannel modelsSimulation or testing of codes
The invention relates to a multicore decoder (31) for decoding low-density parity-check (LDPC) codewords. The multicore decoder includes at least one group of a plurality of cores (10), a plurality of these cores (10) being capable of each simultaneously decoding a different LDPC codeword. The at least one group includes a memory (20) shared between the various cores (10) in which a number NC of predefined configurations is stored. Each predefined configuration includes a binary parity matrix corresponding to an LDPC code. Each core is suitable for being dynamically configured with any one of the NC predefined configurations stored in the shared memory (20) in order to decode an LDPC codeword using this configuration.
H03M 13/11 - Error detection or forward error correction by redundancy in data representation, i.e. code words containing more digits than the source words using block codes, i.e. a predetermined number of check bits joined to a predetermined number of information bits using multiple parity bits
H03M 13/00 - Coding, decoding or code conversion, for error detection or error correctionCoding theory basic assumptionsCoding boundsError probability evaluation methodsChannel modelsSimulation or testing of codes
H04L 1/00 - Arrangements for detecting or preventing errors in the information received
94.
MONITORING SYSTEM FOR MONITORING A HYBRID POWER PLANT OF A ROTORCRAFT, ASSOCIATED ROTORCRAFT AND METHOD
A monitoring system for monitoring a hybrid power plant of a rotorcraft comprising at least one rotor. The hybrid power plant has an electric motor comprising a first drive shaft, a heat engine comprising a second drive shaft and a gearbox. The monitoring system includes at least one first sensing device measuring a first item of torque information representative of a first engine torque C1 transmitted by the first drive shaft to a first input shaft of the gearbox and a controller comparing the first engine torque C1 with a first limit value VL1.
B64D 31/18 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants for hybrid-electric power plants
B64D 35/022 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants of hybrid-electric type
An attachment system for installing a landing gear into a landing gear bay of an aircraft. The attachment system comprises an attachment element configured to be attachable to the landing gear; and a receiving element configured to receive the attachment element and secure the landing gear within the landing gear bay. The receiving element is configured such that the attachment element is insertable into the receiving element from an installation direction, and the attachment element is configured to receive, in the installation direction, a fastener to fasten the attachment element to the receiving element.
An elongate aircraft structural component for an aircraft, the structural component comprising a web and a flange, wherein the flange extends from the web, comprises layers of composite material, and has a length in a direction of a length of the elongate aircraft structural component, a width perpendicular to the length of the flange and a thickness smaller than, and perpendicular to, both the width and the length of the flange, wherein the width of the flange varies along the length of the flange, whereby the flange comprises a wide flange region and a narrow flange region, the narrow flange region having a smaller width than the wide flange region, and wherein the wide flange region comprises stitching interconnecting the layers of composite material, the stitching extending along a path in a direction with at least a component parallel to the width of the flange.
A demosaicing method is disclosed as being applied to an initial image in order to obtain a demosaiced image, enabling an improved demosaicing due to the fact that it includes a noise variance stabilization transformation, for each reference patch: a determination of a set of similar patches, a determination of a covariance matrix for said set of similar patches, and for each similar patch, a calculation of estimates of the interpolated spectral bands according to a block-based deconstruction of the covariance matrix as a function of the phasing, a determination of the interpolated spectral bands by an aggregation of estimates of the interpolated spectral bands, and an inverse transformation of the stabilization transformation.
An optical terminal for quantum communication, comprising a first terminal unit configured to receive and/or transmit a first signal beam from or to a first target terminal and having a first optical axis, a second terminal unit configured to receive and/or transmit a second signal beam from and/or to a second target terminal and having a second optical axis, and a connecting part to communicate with the terminal units, wherein each terminal units comprises: a telescope provided on an optical axis to collimate the respective signal beams, a beam corrector placed on the respective optical axis and configured to correct the respective optical signals beam over a predetermined field of view of the telescope, a steering system to adjust a propagation direction of the signal beams to the respective optical axis, and a coupling portion coupling the respective signal beams to the connecting part. Also a method for quantum communication.
G02B 26/08 - Optical devices or arrangements for the control of light using movable or deformable optical elements for controlling the direction of light
A method for pipelining data processing includes a data processing step taking an a priori indeterminable amount of processing time. The method involves generating a unique ID and associating it with the input data, feeding the input data and UID to a pipeline module including a data processing module and processing delay module, delaying outputting the UID by the processing delay module for a delay time corresponding to processing time required by the data processing module for a single iteration, wherein, in response to the branching part determining the condition is met or not met, the pipeline module re-inputs the UID into the processing delay module. In response to the branching part determining that the condition is another of met or not met, the processing delay module outputs the UID unblocking transmission of further input data to the processing module, and the processing module outputs processed data as output data.
H04L 9/32 - Arrangements for secret or secure communicationsNetwork security protocols including means for verifying the identity or authority of a user of the system
A monitoring system comprising multiple portable camera units may be formed by aircraft safety cones each housing a video camera for locally viewing under-wing turnaround activities of an aircraft at the stand. Each portable camera unit has a processor for relaying or processing data, images and the like captured by the unit. Data is sent wirelessly to a separate computer/or to other systems or personnel at the airport, or both.
G08G 5/06 - Traffic control systems for aircraft for control when on the ground
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
