A flight control system having primary flight control computers and secondary flight control computers. Each secondary computer is configured to: determine if a situation is confirmed, in which no primary computer is functional, the secondary computer receives valid anemo-inertial information from the aircraft and the secondary computer has not received a piloting command originating from a piloting component, for at least a predetermined duration. When the situation is confirmed, the secondary flight control computer activates a piloting mode and is configured to: determine roll and pitch angles based on anemo-inertial information from the aircraft; compute control commands for control surface actuators connected to the secondary computer in order to keep the aircraft flat and at constant altitude; and control the control surface actuators connected to the secondary computer based on the computed commands. Also a method for flight control of an aircraft.
A clamping device for clamping at least two components of a structure with a predetermined clamping force, particularly in the manufacture of aircraft or spacecraft. Also a method for assembling a structure, particularly in the manufacture of aircraft or spacecraft with such a clamping device. The clamping device utilizes a preloaded force before the components are clamped.
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
B23P 19/04 - Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformationTools or devices therefor so far as not provided for in other classes for assembling or disassembling parts
An aircraft wing assembly, comprising: a stringer, the stringer comprising a first flange, a second flange, and a web extending between, and connecting, the first flange and the second flange; a skin section; and a rib; wherein the first flange is joined to the skin section and the second flange is joined to the rib. Also a method of fabricating the aircraft wing assembly and an aircraft comprising the aircraft wing assembly.
A method for providing connectivity between a personal electronic device, PED, and a networked output device in an aircraft. The method includes providing an encapsulated subnetwork within a wireless network of the aircraft. The subnetwork is dedicated to the networked output device. The method further includes providing, via the networked output device, configuration information configured to provide access to the subnetwork for the PED. The subnetwork is configured to provide connectivity between the networked output device and the PED when the subnetwork is accessed by the PED using the configuration information.
H04W 4/42 - Services specially adapted for particular environments, situations or purposes for vehicles, e.g. vehicle-to-pedestrians [V2P] for mass transport vehicles, e.g. buses, trains or aircraft
A cooling system comprising: a closed main refrigerant circuit which, in the direction of the circuit, includes a compressor, a condenser, an expansion valve, and an evaporator; and a safety arrangement which completely surrounds the main refrigerant circuit and an auxiliary refrigerant and/or neutralizing agent interspersed, such that in the event of a leak in the main refrigerant circuit, any main refrigerant circulating in the main refrigerant circuit must pass through the auxiliary refrigerant and/or neutralizing agent before it reaches an environment outside the safety arrangement. Also, an aircraft with such a cooling system.
F25B 49/02 - Arrangement or mounting of control or safety devices for compression type machines, plants or systems
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
6.
ASSEMBLY FOR AN AIRCRAFT COMPRISING A TURBOMACHINE, A PYLON AND A MOUNTING SYSTEM
An assembly for an aircraft including a turbomachine, a pylon with forward end and a system for mounting the turbomachine to the pylon, the turbomachine extending along a longitudinal axis oriented in a direction of a flow generated by the turbomachine. The turbomachine includes, along the longitudinal axis, a forward casing, an intermediate casing, a turbine casing and an exhaust casing. The mounting system includes a forward mounting including a first suspension to suspend the turbomachine from the pylon fixed at the level of the forward casing and a rear mounting to mount the turbomachine to the pylon fixed at the level of the intermediate casing. The forward mounting includes a second suspension to suspend the turbomachine from the pylon fixed at the level of the intermediate casing. The first and second suspensions are fixed to the pylon in the same plane, perpendicular to the longitudinal axis.
An electrical protection system for an electrical connection of an electrical circuit of an aircraft, for example an aircraft powered by hydrogen, comprising a fuse element made of a material which exhibits superconducting properties in a superconducting state, and non-superconducting properties in a normal state, the transition from the superconducting state to the normal state releasing transition energy, the protection system also comprising a device, called the safety device, designed to open the electrical connection when the fuse element changes from the superconducting state to the normal state.
An aircraft fuselage includes fore and aft sections, a barrier wall separating them and defining an opening therebetween, a rail attached to the barrier wall, a door moveable across the barrier wall between an open position offset from the opening and a closed position covering the opening, first and second rollers each rotatably fixed to the door and moveable on the rail along first and second paths to move the door between positions, the rail including a first ramp engaging the first roller moving along the first path and to direct the first roller towards the barrier wall, and a second ramp engaging the second roller as it moves along the second path and to direct the second roller towards the barrier wall, the first roller is configured to engage the first ramp as the second roller engages the second ramp to move the door towards the barrier wall.
B64C 1/14 - WindowsDoorsHatch covers or access panelsSurrounding frame structuresCanopiesWindscreens
9.
METHOD AND DEVICE FOR AIDING A MAINTENANCE DECISION CONCERNING AN APPARATUS SUCH AS AN AIRCRAFT, AND CORRESPONDING METHOD FOR CONSTRUCTING A MODEL AND MAINTENANCE METHOD
A method for aiding a maintenance decision in relation to an apparatus, such as an aircraft, where a technical failure is detected and entered in a logbook, the resulting entry being referred to as an entry to be processed. The method receives the entry to be processed; queries a model; and provides a user with a result provided by the model and has a list of responses associated with a group of entries selected by the model due to the fact it has entries having a meaning that is identical or similar, in terms of describing a technical failure, to the meaning of the entry to be processed. By virtue of this list, the user is able to quickly and effectively respond to the entry to be processed. A method for constructing the model from data (entries and responses) collected in logbooks of a fleet of apparatuses.
An aircraft propulsion system including a turbomachine including a front casing with a rear face and a rear casing, a mounting pylon with a front portion and to which a rear fitting is attached, an arch attached to the rear fitting and to the rear casing, and on either side of the vertical median plane, and a set of six connecting rods distributed on either side of the vertical median plane, each connecting rod being attached to the rear face of the front casing and to the arch, and the connecting rods converging towards each other at the arch in pairwise fashion.
A lavatory arrangement in a cabin area of a commercial aircraft provides a lavatory arrangement suitable for persons with reduced mobility. The lavatory arrangement includes a lavatory with a toilet and a wall arrangement enclosing the lavatory on at least two sides, with at least a first wall and a second wall, wherein the first wall and the second wall are adjacent to each other and are interconnected via a corner area. A first opening with a first movable closure device is provided in the first wall as a toilet door to allow passengers to access the lavatory. A second opening with a second movable closure device is provided in the second wall as a bi-functional wall segment which, in its open state, releases the second opening in the second wall to allow second access to the lavatory by passengers with reduced mobility.
B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided forHandling, transporting, testing or inspecting aircraft components, not otherwise provided for
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
A method for controlling a pitch angle of a fan or propeller of an aircraft powertrain with the intention of feathering said fan or propeller when an inconsistency of said pitch angle is detected. The invention furthermore relates to an avionics device configured to implement the method. Advantageously, it is thus possible to limit the risks of undesirable aerodynamic effects in the event of malfunctioning of the pitch angle control.
A pipe assembly with first and second tubular pipe sections and fastener system fastening the sections defining a flow path. The first section extends along a common central axis. The second tubular pipe section extends along the common central axis. The fastener system includes a first fastener sub-system having a first component on the first tubular pipe section and a first fastener fastening the first component to a second engagement feature. The first engagement feature is between the first component and second engagement feature restricting movement of the first tubular pipe section. A second fastener sub-system has a second component on the second tubular pipe section and a second fastener fastening the second component to the first engagement feature. The second engagement feature is between the second component and the first engagement feature restricting movement of the first tubular pipe section.
F16L 19/02 - Pipe ends provided with collars or flanges, integral with the pipe or not, pressed together by a screwed member
B64D 37/00 - Arrangements in connection with fuel supply for power plant
F16L 19/025 - Pipe ends provided with collars or flanges, integral with the pipe or not, pressed together by a screwed member the pipe ends having integral collars or flanges
14.
RAMPED COMPOSITE STRUCTURAL MEMBER FOR AIRCRAFT, AND METHOD OF FORMING THE SAME
A composite structural member for an aircraft, the composite structural member having a ramped region and comprising a plurality of composite plies arranged upon one another in a thickness direction; wherein, in the ramped region, the composite plies include at least first and second subsets of composite plies, each subset comprising a plurality of composite plies; and wherein the second subset of composite plies is staggered in a ramp direction relative to the first subset of composite plies, the staggering producing a flat surface region on the second subset of composite plies, suitable for seating a fastener thereon in use. A method of forming such a composite structural member by resin transfer moulding, and a method of designing such a composite structural member, are also provided.
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
B29K 63/00 - Use of epoxy resins as moulding material
A method implemented by a computer device for defining sets of different colors in a color space, each of which consists of spot colors that make it possible to reproduce one or more sensitive colors of the reference pattern to be printed continuously and exactly, and of process colors to be used to produce color combinations, so as to be able to obtain all of the colors of the reference pattern to be printed, other than the one or more sensitive colors, in the livery, and for selecting one of these sets of colors taking into account at least one selection criterion, in order to obtain a set of colors that is optimized in particular in terms of precision and or ink consumption.
An energy conversion arrangement for an apparatus, a corresponding energy system, in particular for powering a propulsion unit for propelling an apparatus, and an apparatus, in particular an aircraft, are provided, including a fuel conversion device, in particular a fuel cell unit, for generating electrical and/or mechanical energy by oxidizing a reductant contained in a fuel gas by an oxidant contained in a reactant gas, with at least one cathode element configured to provide electrons shed by the reductant and to be picked up by the oxidant during fuel conversion, at least one cathode channel configured to lead the reactant gas along the at least one cathode element, and at least one pre-heating duct configured to lead the reactant gas to the cathode channel and to heat up the reactant gas by heat provided by the reactant gas in the cathode channel.
H01M 8/0265 - CollectorsSeparators, e.g. bipolar separatorsInterconnectors characterised by the configuration of channels, e.g. by the flow field of the reactant or coolant the reactant or coolant channels having varying cross sections
H01M 8/04014 - Heat exchange using gaseous fluidsHeat exchange by combustion of reactants
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
H01M 8/1007 - Fuel cells with solid electrolytes with both reactants being gaseous or vaporised
17.
POTABLE WATER CONNECTION FOR AN AIRCRAFT WATER CONSUMER
A potable water connection for a water consumer in an aircraft having a main body with an outer thread, a male fitting configured to be coupled to the water consumer, a connector configured to be coupled to a potable water supply, and a nut plate threaded onto the outer thread. Also an aircraft monument and an aircraft having such potable water connection.
F16L 41/14 - Joining pipes to walls or pipes, the joined pipe axis being perpendicular to the plane of a wall or to the axis of another pipe by screwing an intermediate part against the inside or outside of the wall
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
F16L 41/00 - Branching pipesJoining pipes to walls
18.
HIGH LIFT SYSTEM MONITORING AND CONTROL ARRANGEMENT FOR AIRCRAFT
A high lift system monitoring arrangement (24) includes: a sensor (32), a monitoring unit (34) connected to the sensor (32), wherein the monitoring unit (34) includes: an acquisition module (46), that acquires an analog sensed information (AI) from the sensor (32), a processing module (48) having a first processing circuitry (48A) and a second processing circuitry (48B), different from the first circuitry, wherein the first processing circuitry (48A) processes the analog sensed information (AI) into a first digital sensor data (DD1), the second processing circuitry (48B) processes the analog sensed information (AI) into a second digital sensor data (DD2).
An actuation assembly (10) including a control unit (40), a monitoring unit (50), at least one high voltage power supply (32), a low voltage power supply (34) and power bridges (60a, 60b). The low voltage power supply (34) is connected to a source to provide power to the control unit (40) and to the monitoring unit (50), wherein the control unit (40) and the monitoring unit (50) monitor elements of a sub-system including an electric motor, a brake or a sensor. The high voltage power supply (32) is connected to a source to provide power to each of the power bridges (60a, 60b). The power bridges (60a, 60b) are coupled with an electric motor.
A high lift system architecture is disclosed including a first rotational sensor configured to be installed on a torque transmission arrangement and to measure a first angular position of the torque transmission arrangement, at a first measurement point. A second rotational sensor configured to be installed on the torque transmission arrangement and to measure a second angular position of the torque transmission arrangement at a second measurement point. An actuation control device including an acquisition module configured to acquire the first angular position from the first rotational sensor and the second angular position from the second rotational sensor. A determination module configured to determine a torque applied to the torque transmission arrangement as a function of the acquired first and second angular positions.
A high lift system architecture is disclosed including an actuation arrangement configured to move at least one moveable surface, a sensor configured to generate an analog sensed signal representative of a configuration of the moveable surface, a flight control computer, and an actuation control device. The actuation control device includes an acquisition module for acquiring the analog sensed signal, a processing module for processing the analog sensed signal and for generating an analog controlling signal based on the processed analog sensed signal, a conversion module for converting the analog sensed signal into a digitalized monitoring signal, a control module for controlling the actuation arrangement based on the generated analog controlling signal, and a communication module for communicating the digitalized monitoring signal to the flight control computer.
A method for manufacturing a cellular structure of a sound attenuating panel by manufacturing ducts from a rigid thermoplastic material, placing the ducts on a tool that comprises, for each duct, a core connected to a base, each duct being fitted onto a core, the first end thereof being in contact with the base, placing a flexible layer made from a thermoplastic material against the second ends of the ducts, heating and flat-pressing in order to fuse the flexible layer and the second ends of the ducts so as to form the cellular structure, and demolding the cellular structure. Also a tool for performing the method, a cellular structure and a sound attenuating panel.
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
A method for controlling and limiting a pitch angle of the blades of a fan or propeller of a powertrain of an aircraft aiming to lock said pitch angle of said fan or propeller when an inconsistency in said pitch angle of its blades is detected. The invention further relates to an avionics device configured to implement said method. Advantageously, it is thus possible to limit the risks of undesirable aerodynamic effects in the event of malfunction in the control of the pitch angle of the blades of a propeller or fan of an aircraft powertrain.
An aircraft with a first tank suitable for containing fuel, a second tank suitable for containing a second, different fuel or fuel additive, a first fuel line configured to transport the fuel from the first tank to a mixer, a pump arrangement configured to drive a flow of fuel from the first tank along the first fuel line and a second fuel line configured to transport the second, different fuel or fuel additive from the second tank to the mixer. The mixer is configured to mix the fuel and second, different fuel or fuel additive to form a blended fuel. The aircraft also includes a mixer line configured to transport the blended fuel from the mixer to a combustor.
A path laying method for depositing endless fiber material on a surface of a component, wherein a laying path is divided into a plurality of path portions and each path portion is aligned on a surface portion over which the path portion extends, while complying with at least one technical condition. The technical condition may be a starting point, an end point, a constant fiber angle, a variable fiber angle, a material overlap, a spacing between draped fiber webs, or any combinations thereof.
A method and system for desaturating primary control surfaces towards secondary control surfaces, incorporated in roll kinematics of an aircraft. The method involves: determining a first and a second commanded rolling moment to be applied to primary and, respectively, secondary control surfaces based on a first and, respectively, a second control law order to be realized by the primary and, respectively, secondary control surfaces; determining a first and, respectively, a second deflection angle of the respectively control surfaces based on the respective commanded rolling moments, and based on a non-linear conversion function; deflecting the control surfaces through the respective deflection angles.
A method for estimating the position and speed of an aircraft, by way of a system that includes independent avionic computers receiving inertial measurements supplied by IMUs (IMU1-IMU3) and position measurements supplied by a position sensor. The method includes, for a given independent avionic computer and a current iteration of rank k: upon detection of an IMU fault based on current inertial measurements, transmitting fault information (IP) to a selection sub-module. If a preferred IMU_i is faulty: the selection sub-module (306) selects an IMU_j and transmits, to an estimation sub-module (307), a current inertial measurement nmj(k) of the IMU_j and a previous estimate {circumflex over (b)}j(k−1) of a measurement error model of the IMU_j; the estimation sub-module calculates a current estimate of a state vector based on a previous estimate of the state vector (modified by replacing {circumflex over (b)}i(k−1) with {circumflex over (b)}j(k−1)), nmj(k) and a current position measurement.
G01C 21/16 - NavigationNavigational instruments not provided for in groups by using measurement of speed or acceleration executed aboard the object being navigatedDead reckoning by integrating acceleration or speed, i.e. inertial navigation
28.
COOLING ARRANGMENT, ENERGY STORAGE DEVICE AND APPARATUS COMPRISING SAME
A cooling arrangement, an energy storage device, in particular an electrochemical battery for an apparatus, and an apparatus, in particular a vehicle, such as an aircraft. For cooling down an energy storage device, such as an electrochemical battery in an apparatus, in particular a vehicle, such as an aircraft, the cooling arrangement includes at least one compressing device for providing a cooling medium and/or cooling agent for cooling down the energy storage device and/or quenching exhausts, respectively, which may be produced due to a technical failure of at least one energy storage unit of the energy storage device, wherein the compressing device is configured to be at least partly driven by the exhausts.
An aircraft has an energy storage system including a first battery with first and second battery modules. A venting system includes first and second battery module exhausts and a first battery manifold to connect the first and second battery module exhausts to a first flow path extending to an exhaust port. The first battery manifold includes a first valve with a first flap having a first position wherein fluid flow from one of the first and second battery module exhausts is restricted, a second position wherein fluid flow from the other of the first and second battery module exhausts is restricted, and a neutral position wherein fluid can flow from both first and second battery module exhausts to the first flow path. The first valve is biassed towards the neutral position.
An engine system for an aircraft having an engine with a combustion chamber and a turbine unit, a first injector manifold for the combustion chamber, a second injector manifold arranged downstream of the turbine unit, an auxiliary conduit and a thermal loop with a first heat exchanger on an auxiliary conduit for dihydrogen, a second heat exchanger where the second injector manifold is oriented toward the second heat exchanger and conduits between the heat exchangers so as to heat the dihydrogen circulating in the auxiliary conduit before its arrival at the injector manifolds.
A high lift arrangement for an aircraft wing includes a high lift element arranged to have a deployed position wherein the high lift element extends in front of at least an inboard portion of a leading edge of the wing tip. The high lift element has a sweep angle which is less than the sweep angle of the wing tip, such that a gap is formed between the element and the wing tip. A vortex is generated at the tip of the high lift element to energize the wing tip upper surface boundary layer. The gap accelerates the flow, improving low speed performance of the wing.
A high lift arrangement for a folding aircraft wing having a wing body with a folding wing tip including a high lift element arranged to have a deployed position in front of the leading edge of the folding wing tip, and an actuator for deploying the element. The actuator is mounted to the wing body such that there is no need for electrical or hydraulic cables to cross the wing fold line.
An aircraft fuselage includes fore and aft sections of the aircraft fuselage, a barrier wall separating the fore and aft sections, the barrier wall defining an opening, a door moveable in a straight line across the barrier wall that defines a direction of movement between an open position in which the door is offset from the opening and a closed position in which the door covers the opening, a seal assembly including a first member attached to the barrier wall and extending around a perimeter of the opening, and a second member attached to the door and configured to engage with the first member at respective seal surfaces to form a seal around the perimeter of the opening.
A safety device for an equipment containing potentially flammable and/or potentially explosive media, such as for example a fuel cell. The safety device includes a housing with an internal chamber for encapsulating the equipment. To improve the safety device for use on vehicles, especially aircraft, the safety device includes a flexible membrane separating a gas-tight volume from the chamber wherein the gas-tight volume is filled during operation with a filling gas differing from the media. The flexible membrane can be provided in a form of a balloon filled with the filling gas and located within the chamber, especially in a top portion of the chamber.
A62C 99/00 - Subject matter not provided for in other groups of this subclass
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 3/16 - Fire prevention, containment or extinguishing specially adapted for particular objects or places in electrical installations, e.g. cableways
A62C 35/10 - Containers destroyed or opened by flames or heat
A support frame for an aircraft cabin floor. The support frame has at least two primary frame members and at least two secondary frame members. The primary frame members form vertical load support columns. The secondary frame members form horizontal bar frame members. The primary frame members are arranged parallel to each other, and the secondary frame members are arranged parallel to each other, while the primary frame members are arranged transverse to the secondary frame members. One of the secondary frame members is connected to one end of the respective primary frame members and another of the secondary frame members is connected to the other end of the respective primary frame members. The primary frame members and the secondary frame members are made by cutting and forming from a single sheet.
A method for producing a blank for deformation into a component part. Therein, a first section of a sheet made of a fiber reinforced composite material is designated to after the deformation become a first portion of the component part, and a second section of the sheet is designated to become a second portion of the component part. A slit pattern is generated, within the sheet, whose geometry in the first section is different from its geometry in the second section. Further disclosed are a manufacturing method for manufacturing a component part, and a blank for deformation into a component part.
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B23K 26/38 - Removing material by boring or cutting
B29K 105/00 - Condition, form or state of moulded material
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
09 - Scientific and electric apparatus and instruments
42 - Scientific, technological and industrial services, research and design
45 - Legal and security services; personal services for individuals.
Goods & Services
Computer software for use in real-time collaborative
engagement by a group of vehicles across multiple domains
and environments, especially air, land, sea, space and
submarine; computer software for single vehicle autonomy and
real-time collaborative engagement with other vehicles,
especially for planning, enhancement and execution of
missions for vehicles, especially crewed or uncrewed
aircraft; computer software for enabling communication and
data exchange among vehicles, especially crewed or uncrewed
aircraft; computer software for enabling communication and
data exchange among vehicles, especially for planning,
enhancement and execution of missions for vehicles,
especially crewed and uncrewed aircraft; computer software
for use in facilitating real-time collaboration and
information sharing among vehicles, especially crewed and
uncrewed aircraft; computer software for use in facilitating
real-time collaboration and information sharing among
vehicles, especially for planning, enhancement and execution
of missions for vehicles, especially crewed and uncrewed
aircraft; computer software for planning, enhancement and
execution of missions for vehicles, especially crewed and
uncrewed aircraft. Providing online non-downloadable computer software for use
in real-time collaborative engagement by a group of vehicles
across multiple domains and environments especially air,
land, sea, space and submarine; software as a service (SaaS)
featuring software for enabling communication and data
exchange among diverse vehicles for collaborative purposes;
providing computer software for use in facilitating single
vehicle autonomy and real-time collaboration and information
sharing among vehicles; updating and maintenance of computer
software for use in real-time collaborative engagement by a
group of vehicles across multiple domains and environments,
especially air, land, sea, space and submarine; updating and
maintenance of computer software for single vehicle autonomy
and real-time collaborative engagement with other vehicles,
especially for planning, enhancement and execution of
missions for vehicles, especially crewed or uncrewed
aircraft; updating and maintenance of computer software for
enabling communication and data exchange among vehicles,
especially crewed or uncrewed aircraft; updating and
maintenance of computer software for enabling communication
and data exchange among vehicles, especially for planning,
enhancement and execution of missions for vehicles,
especially crewed and uncrewed aircraft; updating and
maintenance of computer software for use in facilitating
real-time collaboration and information sharing among
vehicles, especially crewed and uncrewed aircraft; updating
and maintenance of computer software for use in facilitating
real-time collaboration and information sharing among
vehicles, especially for planning, enhancement and execution
of missions for vehicles, especially crewed and uncrewed
aircraft; updating and maintenance of computer software for
planning, enhancement and execution of missions for
vehicles, especially crewed and uncrewed aircraft; technical
support services, namely, providing troubleshooting in the
nature of diagnosing problems with computer software for use
in real-time collaborative engagement by a group of vehicles
across multiple domains and environments, especially air,
land, sea, space and submarine; technical support services,
namely, providing troubleshooting in the nature of
diagnosing problems with computer software for single
vehicle autonomy and real-time collaborative engagement with
other vehicles, especially for planning, enhancement and
execution of missions for vehicles, especially crewed or
uncrewed aircraft; technical support services, namely,
providing troubleshooting in the nature of diagnosing
problems with computer software for enabling communication
and data exchange among vehicles, especially crewed or
uncrewed aircraft; technical support services, namely,
providing troubleshooting in the nature of diagnosing
problems with computer software for enabling communication
and data exchange among vehicles, especially for planning,
enhancement and execution of missions for vehicles,
especially crewed and uncrewed aircraft; technical support
services, namely, providing troubleshooting in the nature of
diagnosing problems with computer software for use in
facilitating real-time collaboration and information sharing
among vehicles, especially crewed and uncrewed aircraft;
technical support services, namely, providing
troubleshooting in the nature of diagnosing problems with
computer software for use in facilitating real-time
collaboration and information sharing among vehicles,
especially for planning, enhancement and execution of
missions for vehicles, especially crewed and uncrewed
aircraft; technical support services, namely, providing
troubleshooting in the nature of diagnosing problems with
computer software for planning, enhancement and execution of
missions for vehicles, especially crewed and uncrewed
aircraft. Licensing of computer software for use in real-time
collaborative engagement by a group of vehicles across
multiple domains and environments, especially air, land,
sea, space and submarine; licensing of computer software for
single vehicle autonomy and real-time collaborative
engagement with other vehicles, especially for planning,
enhancement and execution of missions for vehicles,
especially crewed or uncrewed aircraft; licensing of
computer software for enabling communication and data
exchange among vehicles, especially crewed or uncrewed
aircraft; licensing of computer software for enabling
communication and data exchange among vehicles, especially
for planning, enhancement and execution of missions for
vehicles, especially crewed and uncrewed aircraft; licensing
of computer software for use in facilitating real-time
collaboration and information sharing among vehicles,
especially crewed and uncrewed aircraft; licensing of
computer software for use in facilitating real-time
collaboration and information sharing among vehicles,
especially for planning, enhancement and execution of
missions for vehicles, especially crewed and uncrewed
aircraft; licensing of computer software for planning,
enhancement and execution of missions for vehicles,
especially crewed and uncrewed aircraft.
38.
METHOD, CONTROL PROGRAM, COMPUTER-READABLE DATA CARRIER, CONTROL UNIT, COMMUNICATION DEVICE, SYSTEM AND AIRCRAFT COMPRISING SAME FOR USING PUSH MESSAGES
Providing data objects to at least one operating person for operating an aircraft by providing a computing device on the aircraft configured to handle data objects containing status information regarding the aircraft, at least one of an operational unit of the aircraft, a transportation unit to be carried by the aircraft and/or the operating person to be tasked with handling the aircraft and/or a transportation unit transported by and/or supposed to be transported by the aircraft; and providing at least one communication device, such as a mobile device, at least temporarily associated to the operating person or to a further operating person and adapted to send to and/or receive the data objects embedded in and/or in the form of push messages to provide the status information to the operating person and/or to the further operating person.
METHOD, CONTROL PROGRAM, COMPUTER-READABLE DATA CARRIER, CONTROL UNIT, COMMUNICATION DEVICE, SYSTEM AND AIRCRAFT COMPRISING SAME FOR MANAGING WORK TASKS
Managing work tasks to be accomplished within a pre-defined time frame, in particular a turn-around time measured between an expected arrival timepoint and a scheduled departure time point of an aircraft, by providing a computing device on the aircraft configured to handle data objects containing status information regarding the aircraft, at least one of an operational unit of the aircraft, a transportation unit to be carried by the aircraft and/or an operating person to be tasked with handling the aircraft and/or the transportation unit for achieving at least one respective work task; and providing at least one communication device, such as a mobile device, at least temporarily associated to the operating person or to a further operating person and adapted to send to and/or receive the data objects to provide the status information to the operating person and/or to the further operating person.
An on-board computing system for an aircraft. The computing system has a cabin backbone system with system-owned resources configured to provide first computing power. The computing system further includes at least one device interface configured to connect to at least one passenger-owned device which has device-owned resources configured to provide a second computing power to the cabin backbone system. The cabin backbone system is configured to control utilization of the second computing power provided via the device interface to form a resource pool controlled by the cabin backbone system to enhance the first computing power of the cabin backbone system.
A propulsion system for an aircraft comprising an engine mast with a nose, a turbojet engine having a casing, a central shackle articulated to the nose by a first connection point and articulated to the casing by two second connection points, and a lateral shackle articulated between the nose and the casing by a central connection point and two lateral connection points arranged on either side of a vertical median plane.
A method for maintaining pressure in a fuel tank of a fuel consuming system of an aircraft and a fuel distribution system and an aircraft with such a system. The present invention maintains a pressure inside the fuel tank substantially constant by regulating the temperature of a first recirculated fuel mass flow injected back into the fuel tank so that the first recirculated fuel mass flow is mostly stored again in optimal conditions. A heat exchanger may be used to adjust a temperature of the first recirculated fuel mass flow.
A refueling connector has an inner pipe section, for example, defining inner region, for conveying cryogenic hydrogen to an aircraft and an outer pipe section, for example, defining outer region, for holding a vacuum to provide thermal insulation to the inner section. Via one or more suitable valves the connector can, when connected to the aircraft, create a vacuum on the aircraft-side or otherwise convey fluid from/to the aircraft, via the outer pipe section.
A heating installation for an aircraft disposed between a dihydrogen tank and an engine with a first supply line connected to the tank and a second supply line connected to the engine and comprising two branch lines connected parallel to each other between the first supply line and the second supply line. Each branch lines includes a first valve, a heating system and a second valve installed in series, upstream to downstream.
FLOOR INCLUDING AT LEAST ONE CONNECTING DEVICE INCORPORATING AT LEAST ONE GUTTER AND ENABLING COMPENSATION OF RELATIVE MOVEMENT IN AT LEAST A LONGITUDINAL DIRECTION
A floor including at least one connecting device connecting first and second panels spaced in a longitudinal direction and including at least one gutter and at least one threshold bar connected to one another by at least one connecting system and respectively at least partly below and above the first and second panels, at least one of the first and second panels, the gutter and the threshold bar being configured to allow movement in the longitudinal direction of the first panel relative to the second panel. An aircraft including at least one such floor is also disclosed.
An aircraft propulsion system with a turbomachine having a front casing with a rear face and a rear casing, a mounting pylon with a front portion and to which a rear fitting is attached, an arch attached to the rear fitting and to the rear casing, and on each side of the vertical median plane, three port/starboard connecting rods, each connecting rod being attached between the rear face of the front casing and the arch, the three port connecting rods converging towards each other in a port convergence zone at the arch, and the three starboard connecting rods converging towards each other in a starboard convergence zone at the arch.
The invention discloses a sandwich element having a foam core, which has at least one cover layer on each of its mutually opposite large surfaces, wherein recesses are introduced into the one large surface of the foam core, and the at least one cover layer extending over this large surface is provided with openings, which at least partially overlap with the recesses, a production method and a cabin element.
B32B 3/26 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids
B32B 3/30 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids characterised by a layer formed with recesses or projections, e.g. grooved, ribbed
B32B 5/18 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by features of a layer containing foamed or specifically porous material
B32B 27/06 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance
B32B 27/28 - Layered products essentially comprising synthetic resin comprising copolymers of synthetic resins not wholly covered by any one of the following subgroups
48.
AIRCRAFT COMPRISING AT LEAST ONE INFLATABLE AERODYNAMIC STRUCTURE
An aircraft comprising with at least one support, at least one inflatable aerodynamic structure which has at least one aerodynamic surface, and at least one connection system connecting the aerodynamic structure and the support. The aerodynamic structure has at least one flexible wall having an outer face, and at least one inflatable cavity delimited at least partially by the flexible wall and configured to adopt an inflated state in which the cavity has a maximum volume and a deflated state in which the cavity has a volume smaller than the maximum volume, the outer face forming at least part of the aerodynamic surface when the cavity is in the inflated state.
An aircraft propulsion system having a turbomachine with a front casing with a rear face and a rear casing, a mounting pylon with a front portion and to which a rear fitting is attached, an arch attached to the rear fitting and to the rear casing, and on either side of the vertical median plane, two port connecting rods and two starboard connecting rods that are attached between the rear face of the front casing and the arch, the two port, respectively starboard, connecting rods converge towards each other in a starboard convergence zone at the arch, and a central connecting rod lying in the vertical median plane and attached to the rear face and to the arch.
A method for managing network communication between interconnected network devices in a network system by: receiving, from an application of a first network device in the network system, a request for network communication of application data related to a plurality of data objects; classifying, based on a correlation map, the data objects into one or more data sets, each data set including one or more data objects, wherein data objects from different data sets are classified uncorrelated; and establishing, for each data set, a corresponding network connection network communication between the first network device and at least one second network device in the network system, the least one second network device providing application data related to the respective data set, for receiving, by the first network device, the application data from the at least one second network device.
A method and an apparatus for compressing a neural network. Circuitry receives a neural network comprising a set of parameters being in at least one floating-point number format of a first precision. The circuitry also applies at least one mathematical model on the neural network to determine errors introduced by using arithmetic of a second precision lower than the first precision and propagation through network layers of the neural network due to using the arithmetic of the second precision instead of the first precision. The circuitry then applies a solver to an optimization problem formulated based on the errors determined by the at least one mathematical model to determine a set of optimized parameters. Finally, the circuitry compresses the neural network based on the set of optimized parameters to output a compressed neural network.
METHOD AND COMPUTER DEVICE FOR TRANSFORMING A TEXTURED MESH OF A DESIGNED OBJECT INTO A TEXTURED MESH OF A MANUFACTURED OBJECT CORRESPONDING TO SAID DESIGNED OBJECT
A method for determining a transformed textured mesh of a three-dimensional manufactured object on the basis of an initial textured mesh of a three-dimensional designed object, the transformed textured mesh to be used when printing a corresponding two-dimensional texture on the manufactured object by iteratively determining a set of affine transformations with individualized parameters to minimize the value of a target function having at least one term promoting a specific property, the set of affine transformations thus determined being applied to the vertices of the initial textured mesh so as to obtain the transformed textured mesh.
A cryogenic tank includes at least one enclosure, at least one cryogenic element located in the enclosure and at least one connecting system including at least one connecting element connecting first and second anchor points respectively rigidly attached to the enclosure and the cryogenic element directly or indirectly. The connecting element forms a thermal conduction path that has a length greater than a straight line distance separating the first and second anchor points.
A cryogenic tank with at least one enclosure containing a liquid phase and having at least one anti-sloshing structure formed from walls and positioned inside the enclosure and configured to compartmentalize the enclosure and at least one connection system connecting the anti-sloshing structure and the enclosure. Also an aircraft with at least one such tank.
A spark containment cap plate with a base and two or more spark containment caps. Each cap has a cover portion which extends from the base and defines a cavity inside the cap, inside which an end of a fastener is enclosed. Also a fastener joint with a structure; two or more fasteners, each fastener having an end protruding from a surface of the structure; and a spark containment cap plate. The plate has a base and two or more spark containment caps. Each cap has a cover portion extending from the base and defining a cavity inside the spark containment cap inside which the ends of the fasteners. A cured sealing material is provided between the cap plate and the structure which secures the cap plate to the structure in such a position that each end of each fastener is enclosed within a spark containment cap.
H01B 17/38 - Fittings, e.g. capsFastenings therefor
H01B 17/42 - Means for obtaining improved distribution of voltageProtection against arc discharges
56.
OUTER SKIN OF AN AIRCRAFT FUSELAGE OR AIRCRAFT FUSELAGE SECTION AND METHOD FOR MONITORING THE STRUCTURAL INTEGRITY OF THE OUTER SKIN OF AN AIRCRAFT FUSELAGE OR FUSELAGE SECTION
An outer skin of an aircraft fuselage or aircraft fuselage section formed from a fiber reinforced plastic, in particular carbon fiber reinforced plastics in a layered configuration, including at least two layers having electrically conductive fibers, in particular carbon fibers, placed with alternating fiber orientations within the layers and embedded in a polymer matrix material, and a coating consisting of or including magnetically active particles configured to induce a change in physical properties of the coating when exposed to a magnetic field. A method for monitoring the structural integrity of the outer skin of an aircraft fuselage or fuselage section and an aircraft having a fuselage or fuselage section provided with such an outer skin are disclosed.
A water supply system which has two pumping devices which are operated such that the respective value of an operating parameter, such as an operating pressure or an operating time, is different. Pipes connect the pumping devices to water consumers and a valve is provided to connect or disconnect the pumping devices from the piping networks. Also an aircraft with such a water supply system.
A sensor system for monitoring characteristics of a dewar tank having an inner shell and an outer shell. The system includes a sensor arrangement with a magnetic field sensor, and a permanent magnet element, and a controller. The field sensor is connected to the controller and configured to be attached to the outer shell. The magnet element is attached to the inner shell or to the outer shell. The field sensor and the magnet element, in a mounted state on the dewar tank, are located such that the field sensor is capable of detecting a magnetic field created by the magnet element. The controller is configured to measure, via the field sensor, the magnetic field of the magnet element and to infer at least one characteristic of the dewar tank based on the detected magnetic field.
F17C 13/02 - Special adaptations of indicating, measuring, or monitoring equipment
G01F 23/26 - Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water by measuring variations of capacity or inductance of capacitors or inductors arising from the presence of liquid or fluent solid material in the electric or electromagnetic fields
G01K 7/36 - Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat using magnetic elements, e.g. magnets, coils
60.
PROTECTION ARRANGMENT, ENERGY STORAGE DEVICE AND APPARATUS COMPRISING SAME
A protection arrangement, an energy storage device, in particular an electrochemical battery for an apparatus, and an apparatus, in particular, a vehicle, such as an aircraft are disclosed for protecting the energy storage device, such as an electrochemical battery in the event of a technical failure of at least one energy storage unit of the energy storage device. The protecting arrangement includes a discharging circuit with a switching device configured to reduce an electrical charging level of the at least one energy storage unit by electrically closing the discharging circuit upon detection of the technical failure.
H01M 10/42 - Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
H01M 10/48 - Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
A system for cleaning a waste tank in an aircraft, the system comprising a service device, a spray nozzle, and a first adaptor for each spray nozzle. The service device comprises a descaling fluid tank, an outlet, an inlet and a pump in fluid communication with the outlet. The spray nozzle is coupled with the outlet or the pump through a first conduit, wherein spray nozzle ejects a jet of descaling fluid into the waste tank. The inlet is coupled with a second conduit attachable to a waste tank outlet. The first adaptor is couplable with the spray nozzle and has a fastener to attach the first adaptor to an opening of the waste tank in a substantially fluid-tight manner. The service device continuously circulates the descaling fluid through the service device outlet, the first conduit, the spray nozzle, the waste tank outlet, the second conduit and the inlet.
A transmission device having: at least first and second shafts, at least one decoupling system which has at least one first coupling sleeve which is permanently coupled in rotation with the second shaft and movable along the second shaft between a first position in which the first coupling sleeve is coupled in rotation with the first shaft and a second position in which the first coupling sleeve is not coupled in rotation with the first shaft, at least one control which comprises at least one chamber adjoining the first coupling sleeve and supplied with fluid, a variation in the volume of the chamber causing a change in position of the first coupling sleeve.
F16H 63/06 - Final output mechanisms thereforActuating means for the final output mechanisms a single final output mechanism being moved by a single final actuating mechanism the final output mechanism having an indefinite number of positions
B64D 35/021 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants
B64D 35/08 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions characterised by the transmission being driven by a plurality of power plants
An aircraft wing having a fixed wing with a tip, and a wing tip device rotatably mounted on a hinge at the tip of the fixed wing. The wing tip device is rotatable about the hinge. An actuation system rotates the wing tip device about the hinge. The actuation system has a motor, a plurality of geared mechanical actuators, and an angle gearbox coupled between the plurality of geared mechanical actuators and the motor. Each geared mechanical actuator is driveable by the motor and arranged to convert rotary motion into a different rotary motion. Each geared mechanical actuator is arranged along a hinge line of the hinge. The angle gearbox is arranged along the hinge line and between two of the plurality of geared mechanical actuators.
09 - Scientific and electric apparatus and instruments
41 - Education, entertainment, sporting and cultural services
Goods & Services
Downloadable educational materials; Downloadable multimedia content In the fields of science, technology, engineering, arts, and mathematics; downloadable digital materials. Publishing of educational matter In the fields of science, technology, engineering, arts, and mathematics; Providing temporary use of online non-downloadable educational material in the following fields: science, technology, engineering, Art and Mathematics; Publication of interactive educational material in the following fields: science, technology, engineering, Art and Mathematics; Publication of educational material and guides for teaching in the following fields: science, technology, engineering, Art and Mathematics.
65.
Support And Carriage Assemblies For A High Lift Body Arrangement, As Well As Wing And Aircraft Comprising Same
A support assembly for a high lift body configured to be mounted to a spar of a wing of an aircraft includes a track beam configured for supporting the high lift body at the spar movably between a stowed position and a deployed position along a motion path, the track beam having a structural profile portion adapted for transferring operational loads of the high lift body into the spar, and a track profile portion supported at the structural profile portion and adapted for guiding a carriage assembly for carrying the high lift body movably along the motion path and taking up the operational loads. The structural profile portion and/or the track profile portion include a complementing profile portion. The structural profile portion, the track profile portion, and/or the complementing profile portion provide a main load path and a redundant load path configured to transfer and/or take up the operational loads.
A method for draining a water supply system onboard an aircraft which supplies water from a central water tank to consumers. Water is supplied by a supply pump from the central water tank through supply lines of a conduit system to consumers. Each consumer is associated with a supply valve for drawing water from the conduit system. The supply lines have a maximum internal diameter of 8 mm or less. The method includes closing the supply valves of all consumers, subjecting the supply lines of the conduit system at the at the supply pump to a draining pressure and sequentially opening the supply valves of all consumers for removing water from the supply lines of the conduit system. A corresponding water supply system and an aircraft are disclosed.
A method for assisting a pilot navigate an airport while taxiing an aircraft, the method comprising receiving taxi instructions for the aircraft to reach a destination from an origin, generating at least one taxi route for the aircraft to reach the destination from the origin, displaying navigation instructions corresponding to one of the at least one generated taxi route via a display device of the aircraft, and executing the navigation instructions according to the generated taxi route.
A system for detecting a cure and/or flow front in a molding apparatus. The system has a mold portion, a sensor apparatus, and a control unit. The mold portion has a molding surface configured to contact a preform to be infused with resin. The sensor apparatus is arranged within the mold portion and includes a sensor element that extends in a longitudinal direction. The sensor element is arranged to be at least partially below the molding surface into the mold portion such that the sensor element is capable of interaction with resin and/or the preform, for example, via electric fields. The control unit is configured to control the sensor element, so as to detect a cure and/or flow front based on a change in the interaction, such as the electric field, due to the flowing or curing of resin.
G01N 27/60 - Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating electrostatic variables
B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
A system and a method for surface inspection of a composite part of an aircraft with a first illumination unit positioned in front of a surface of a composite part to illuminate that surface with evenly distributed light, and a second illumination unit to illuminate the surface with light hitting the surface at an angle from different sides. Both illumination units are configured to alternately illuminate the surface. A polarization camera unit generates image data of the surface while the surface is alternately illuminated by the illumination units. A processor unit processes the image data, detects defects on the surface of the composite part, and determines the directions of fibers within the composite part from the image data.
A service management system for an aircraft. The service management system is configured to provide a passenger with a service which is closely related to content provided to the passenger on an entertainment system on the aircraft. The service may include an item that is dispensed in the galley of the aircraft, and the system may determine if the item is in stock. Also an aircraft with such a system.
An electrical connection assembly to establish a connection between the terminal elements of electrical conductors which are fitted with terminal rings and including a thermo-deformable element configured to undergo strain as a function of the temperature of the connection assembly, such that an electrical contact between two electrical contact elements is established or interrupted. It is possible to execute detection of conditions for initiation of an electric arc or the presence of a continuous or intermittent electric arc in the connection assembly, by reference to the heat-up of the thermo-deformable element associated with the initiation or the presence of an electric arc.
A power supply module aircraft, including at least an electrical connection to a first AC distribution network, an electrical connection to a second AC distribution network, a synchronization and junction module, and a power converter, the power supply module being external to an aircraft. The power converter is configured to deliver to said aircraft a DC supply voltage obtained by the synchronization and junction module from the first and second AC distribution networks. Advantageously, it is thus possible to supply electrical energy to an aeroplane parked in an area of an airport, without requiring complex logistics and without having to use its auxiliary power unit.
B64F 1/35 - Ground or aircraft-carrier-deck installations for supplying electrical power to stationary aircraft
B60R 16/03 - Electric or fluid circuits specially adapted for vehicles and not otherwise provided forArrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for electric for supply of electrical power to vehicle subsystems
H02J 3/36 - Arrangements for transfer of electric power between ac networks via a high-tension dc link
A propulsion system for an aircraft having: a nacelle which has two cowls that are movable between a closed position and an open position, for each cowl, an actuation system arranged to move that cowl from the open position to the closed position and vice versa, and for each cowl, a holding system arranged to hold that cowl in the open position.
A propulsion assembly of an aircraft comprising a turbojet engine with a front casing extending between a front face and a rear face, a mounting pylon having a primary structure with a front wall, and an engine mount having a first connecting rod and a second connecting rod, where one of the connecting rods is mounted in an articulated manner by a first connecting point on the front wall and by a second connecting point on the front casing, where the other of the connecting rods is mounted in an articulated manner by a third and a fourth connecting point on the front wall and by a fifth connecting point on the front casing, and where the connecting points are in the front third of the front casing.
A propulsion assembly of an aircraft having a longitudinal axis and a vertical median plane and including a front cowling with a rear face perpendicular to the longitudinal axis, a primary structure with a front wall, and an engine attachment including a female yoke member rigidly attached to the front wall, a male yoke member rigidly attached to the rear face and mounted and articulated in the female yolk, a pin rigidly attached to the primary structure and the axis of which is parallel to the longitudinal axis, and a housing in the rear face in which the pin is housed, and wherein the yoke members, the pin and the housing are arranged at the level of the median plane.
An aircraft propulsion assembly having a jet engine with a front casing, a primary structure with a lower spar, two outer rods, wherein each one has a rear end mounted in an articulated manner on the lower spar and a front end mounted in an articulated manner on the front casing, and two inner rods, wherein each one has a rear end mounted in an articulated manner on the lower spar and a front end mounted in an articulated manner on the front casing. Also an aircraft with such an assembly.
Aircraft high-lift device (1) of a lifting surface (2) including an upper skin (3), lower skin (4) and a nose (5), the high-lift device (1) includes: a flexible skin allowing for a morphing high-lift device (1), having a rear upper edge (7.1) and a rear lower edge (7.2), at least the rear upper edge (7.1) sliding along the chordwise direction between a retracted position and an extended position, and a linear actuator (6) connected to the nose (5) and pivotably connected to the lifting surface (2) between the retracted position and the extended position, so that in the extended position the nose (5) is located in a downward location with respect to its location in the retracted position and at least the rear upper edge (7.1) is located in an anterior location with respect to its location in the retracted position.
A method and a system for inspecting the outer skin of an aircraft or a component thereof by scanning a surface of an outer skin of an aircraft with a line scan camera unit while the surface is illuminated with a first light field and with a second light field, and generating image data representing the surface while it is scanned. The image data is processed and defects of the surface and their characteristics and physical locations are automatically determined from the image data representing the surface during its illumination with the first light field and its illumination with the second light field. The defects, characteristics and physical locations are output. The first and second light fields may be formed as alternating bright field illumination and dark field illumination, or as light of a first color and light of a second color.
A method for surface inspection of a cured composite part comprising glass fibers and carbon fibers, in particular of an aircraft, by illuminating a surface of the composite part with infrared light from an IR-light source, and capturing an image of the surface. The IR-light source is arranged so generated infrared light hits the surface at a first angle α to provide a dark field illumination, and the camera is arranged to point at the surface at a second angle β to capture the image of the dark field illuminated surface. The captured image is evaluated with regard to brightness and contrast to detect one or more glass fiber layers on top of one or more carbon fiber layers within the composite part.
G01N 21/88 - Investigating the presence of flaws, defects or contamination
G01N 21/3563 - Investigating relative effect of material at wavelengths characteristic of specific elements or molecules, e.g. atomic absorption spectrometry using infrared light for analysing solidsPreparation of samples therefor
H04N 23/20 - Cameras or camera modules comprising electronic image sensorsControl thereof for generating image signals from infrared radiation only
80.
SUPERCONDUCTING MOTOR COMPRISING COILS INSULATED BY TWO VACUUM LAYERS
A superconducting motor that includes a rotor, a stator and a motor casing. The motor casing has a common chamber which has been evacuated and includes multiple sealed compartments which have also been evacuated, each sealed compartment enclosing one or more coils of the stator, such that the coil(s) in each sealed compartment is/are thermally insulated by two vacuum layers, a first vacuum layer in the sealed compartment in question and a second vacuum layer in the common chamber. Thus, any particles that could become detached from a failed coil do not damage the thermally insulating barrier of any other coil which would be accommodated in another compartment.
H02K 5/10 - Casings or enclosures characterised by the shape, form or construction thereof with arrangements for protection from ingress, e.g. of water or fingers
A load introduction system includes an aerodynamic closed box structure component including an integral closed box having an upper skin section, a lower skin section, a front spar and a rear spar, a load introduction frame, wherein the load introduction frame is arranged at least partly in circumferential direction around the integral closed box, and an attachment unit for coupling the integral closed box to a base system, wherein the attachment unit is coupled to the load introduction frame.
A method of manufacturing a composite part by providing a molding tool comprising a tool base and a tool lid, both configured to form a cavity between the tool base and the tool lid tool when the molding tool is closed. A fiber preform is placed in the tool which is tightly closed so that the fiber preform is within the cavity. A predefined clamping pressure presses the tool lid and the tool base against each other, and a resin is injected into the cavity at an injection pressure to infiltrate the fiber preform with the resin. The size of the cavity is passively increased by allowing an opening movement of the tool lid relative to the tool base and/or an elastic deformation of the tool, when the inner tool pressure is greater than the predefined clamping pressure, while keeping the cavity tightly closed.
B29C 45/14 - Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mouldApparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
A method for manufacturing a stiffened aerodynamic structure component includes: providing an aerodynamic structure component, wherein the aerodynamic structure component includes a plurality of spar elements extending spanwise within the aerodynamic structure component; wherein the plurality of spar elements is integrally formed with an upper skin section and a lower skin section, thereby providing an integrally formed aerodynamic structure component, and generating at least one chordwise reinforcement element by injecting a curable medium, preferably via at least one injection hole, in the upper skin section and/or the lower skin section.
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
B29C 45/14 - Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mouldApparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
84.
ENERGY CONVERSION ARRANGEMENT, ENERGY SYSTEM AND AIRCRAFT COMPRISING SAME
An energy conversion arrangement for an aircraft, an energy system and an aircraft comprising an energy conversion arrangement and/or an energy system are provided. The energy conversion arrangement includes a fuel conversion device, in particular a fuel cell system, configured to convert at least one fuel to electrical and/or mechanical energy, and at least one an exhaust outlet for letting out exhaust produced in the fuel conversion device by the fuel conversion, and at least one mixing assembly configured to merge a stream of further exhaust of the fuel conversion device with at least one stream of the exhaust from the at least one exhaust outlet.
B01F 25/313 - Injector mixers in conduits or tubes through which the main component flows wherein additional components are introduced in the centre of the conduit
An energy conversion arrangement for an aircraft, an energy system, a propulsion unit, and an aircraft comprising an energy conversion arrangement and/or an energy system are provided. The energy conversion arrangement includes at least one exhaust outlet for letting out exhaust produced by a fuel conversion device, in particular a fuel cell system, for converting at least one fuel to electrical and/or mechanical energy in the fuel conversion device; and at least one exhaust assembly configured to admix a stream of the exhaust from the at least one exhaust outlet with ambient air from the ambient surroundings in at least one mixing zone to promote a growth of water droplets through at least partly condensing water vapor contained in the exhaust in the mixing zone.
B64D 27/355 - Arrangements for on-board electric energy production, distribution, recovery or storage using fuel cells
B64D 37/00 - Arrangements in connection with fuel supply for power plant
H01M 8/04119 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyteHumidifying or dehumidifying
86.
METHOD AND DEVICE FOR PROVIDING STRIP MATERIAL FOR MANUFACTURING COMPONENTS FOR VEHICLES, AS WELL AS CORRESPONDING COMPONENT AND VEHICLE WITH SAME
A method and a supply device for providing composite strip material, in particular for the manufacture of components for vehicles, such as aircraft, as well as a corresponding component and vehicle, in particular aircraft, wherein a continuous material feed of the strip material for manufacturing the components includes at least two material portions which are supplied in the course of the continuous material feed.
A leading edge high lift assembly (11) having a slat (13) and a connection assembly (15) movably connecting the slat (13) to a main wing (9). The connection assembly (15) includes an elongate slat track (27) between a first end (31) and a second end (33). The slat track (27) is mounted to the main wing (9) by a roller bearing (37) and mounted to the slat (13) via a link arrangement (39) having a first link element (41) mounted to the slat (13) and to the slat track (27). A recess (59) in the slat track opens to a side of the slat track (27). The first link element (41) extends through the recess (59).
A power supply system, of an aircraft, configured to supply electrical energy to on-board electrical devices including at least an electrical sub-circuit of the high-voltage DC type, an electrical sub-circuit of the low-voltage AC type, and an electrical sub-circuit of the low-voltage DC type. The system additionally including a high-voltage battery switching circuit, the system being such that every power supply line of said low-voltage DC sub-circuit, which power supply line is independent of said switching circuit, has no low-voltage battery. Advantageously, it is thus possible to avoid battery redundancy that is detrimental to the weight of the aircraft and leads to its electrical system being complex.
Aircraft section and aircraft with additional seat belt The present disclosure relates to an aircraft section (100) and an aircraft with an additional seat belt, the belt reel of which is attached to a primary structure assembly and is guided through a side panel element 130 into a passenger cabin of the aircraft section.
A method of indicating a position of a flaw in a part including holding a probe by hand in contact with a surface of the part with a probe; detecting a flaw in the part by emitting ultrasound from the probe into the surface of the part and detecting echoes of the ultrasound from the flaw; providing an indicator on the surface of the part indicating a detection position of the probe; after the indicator has been provided, removing the probe by hand from the surface of the part, leaving the indicator in place; and after the probe has been removed from the surface of the part, providing a flaw marker on the surface of the part indicating an estimated position of the flaw.
An aircraft fuselage for releasing a fuel tank from inside the aircraft fuselage in case of emergency includes an outer structure, a mounting device to releasably secure a fuel tank in an inside of the outer structure, and an openable release door which separates the inside from an outside of the outer structure, wherein the release door is positioned in relation to the mounting device such that the fuel tank is released through the release door when the mounting device releases the fuel tank. A method is disclosed for releasing a fuel tank from inside the aircraft fuselage in case of emergency as well as an aircraft comprising such an aircraft fuselage.
An aircraft section and an aircraft with an additional seat belt, the belt reel of which is attached to a primary structure assembly of frames and stringers for the aircraft section. The seat belt is guided through an opening in a side panel element into a passenger cabin of the aircraft section.
A device for equipping and fitting out fuselage barrels of an aircraft fuselage includes a support structure that carries an assembly platform, the assembly platform including at least one load support and including a frame and at least one actuator rail connected to the frame, wherein at least one actuator carriage can be movably arranged on each of the actuator rails, and wherein the load support is designed to be coupled to a support structure provided on the aircraft fuselage and/or a load introduction point in order to support the assembly platform relative to the aircraft fuselage.
A protective device for aircraft window units includes a frame unit, multi-part and closable protective unit in the frame unit, at least one pretensionable movement unit on the protective unit to transfer the protective unit from at least one open position state into a closed position state, and a triggering unit coupled to the at least one movement unit via at least one coupling region of the at least one movement unit. When the protective device is in an installed state in an aircraft window unit, the triggering unit is between an exterior window unit of the aircraft window unit and the frame unit, such that mechanical forces acting on the exterior window unit can be transmitted to the triggering unit for triggering operation at the at least one movement unit. A protective device system for aircraft, and an aircraft are disclosed.
Protection for an aircraft fuselage being as light as possible and which is easily integrated into the fuselage is provided as a protective insert for an aircraft tail area. The protective insert has a protective panel, an absorption body supporting the protective panel, and a force transmission device holding the absorption body. The protective panel is configured for pressure-loaded sliding contact with a runway during a tail impact. The protective panel transfers compressive force acting during the tail impact to the absorption body. The absorption body is configured to absorb the compressive force in a force-damping manner, wherein part of the energy due to the acting compressive force is convertible into an elastic and/or plastic deformation of at least a part of the absorption body. The force transmission device holds the protective insert on the underside of the tail area of an aircraft via a plurality of fastening areas.
A propulsion system for an aircraft having a jet engine with a front casing with a rear face and a rear casing, a mounting pylon with a front portion and a lower spar to which a rear fitting is attached, a front engine mount attached between the front casing and the front portion, an arch with a base attached to the rear fitting and two arms, each having a first end secured to the base and a second end attached to the rear casing, two upper bars hinged to the rear face and to the arch, and two lower bars hinged to the rear face and to the arch, the two upper bars being rigidly attached to each other.
A method for detecting the presence of ice on an aircraft, including: obtaining, in real time, measurements (provided by sensors) of a set of flight parameters comprising a slope, an incidence, a Mach number, a rotational speed of a low-pressure propulsion engine assembly of the aircraft, a fuel flow, a mass of the aircraft, a position of a trimmable horizontal stabilizer, a static temperature and a static pressure; injecting the obtained measurements into an artificial-intelligence model, trained and configured to calculate a presence of ice indicator based on measurements of the set of flight parameters; and providing the presence of ice indicator calculated by the model. This novel indirect method exhibits good performance because it is based on an artificial-intelligence model using a large number of flight parameters.
A heat transfer device for an aircraft providing heat to the fuel of a fuel conduct, a conditioning system having the heat transfer device, an aircraft including the heat transfer device of the fuel conditioning system, and a method for conditioning fuel of an aircraft. The fuel conduct includes a first end and a second end, in which the first end is connected in fluidic communication to the first inlet of the heat transfer device and the second end is connected in fluidic communication to the first outlet of the heat transfer device.
An aircraft maintenance system, method, and computer-readable storage medium are disclosed. The aircraft maintenance system includes a processor and a storage having a digital twin of at least part of an aircraft and a machine learning classifier. The aircraft maintenance system is configured to obtain aircraft operational data, update the digital twin based on the aircraft operational data, identify an altered operation of the aircraft based on the aircraft operational data, and determine a set of conditions responsible for the altered operation using the machine learning classifier to evaluate the digital twin. Output data indicative of the set of conditions responsible for the altered operation is generated.
B64F 5/60 - Testing or inspecting aircraft components or systems
G06Q 10/20 - Administration of product repair or maintenance
G07C 5/00 - Registering or indicating the working of vehicles
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
An inerting system, for instance an aircraft enclosure inerting system, is configured to separate an inlet air flow into nitrogen enriched air (NEA) and oxygen enriched air (OEA). The inerting system has a vortex tube with a vortex chamber in which the inlet air flow is separated into the NEA and the OEA. The inlet air flow enters the vortex chamber through an inlet passage which intersects the vortex chamber at a chamber inlet aperture. A warming device of the inerting system warms the inlet passage or the inlet air flow before the inlet air flow gets to the chamber inlet aperture.
B01D 53/24 - Separation of gases or vapoursRecovering vapours of volatile solvents from gasesChemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases or aerosols by centrifugal force
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
B64D 37/32 - Safety measures not otherwise provided for, e.g. preventing explosive conditions
