A method of managing fire alert signals coming from at least one fire detector configured to generate at least one fire alert signal if overheating is detected, a fault signal being generated if the fire detector is malfunctioning. The management method includes a step of determining a transitory time between the end of the fire alert signal and the start of the fault signal, and a step of emitting an alert signal if the transitory time is less than or equal to an alert threshold time. This solution enables reliable determination if the end of the fire alert signal is the result of extinction of the fire or malfunctioning of the fire detector. A system for executing the method is also provided.
G08B 7/06 - Signalling systems according to more than one of groups Personal calling systems according to more than one of groups using electric transmission
2.
METHOD FOR CONTROLLING FLIGHT COMMANDS OF AN AIRCRAFT, FLIGHT-COMMAND CONTROLLER DEVICE, AND AIRCRAFT
An automated upset-recovery method for recovering an aircraft into a normal flight envelope after detection of one or more flight parameters or one or more flight conditions of the aircraft outside a flight envelope peripheral to the normal flight envelope and on the basis of adapted information coming from sensors and or one or more computers of the aircraft, which are configured to deliver information representative of flight conditions of the aircraft, by carrying out automated control of flight commands.
B64C 13/18 - Initiating means actuated automatically, e.g. responsive to gust detectors using automatic pilot
B64C 13/50 - Transmitting means with power amplification using electrical energy
3.
METHOD FOR SIMULATING AND ANALYSING AT LEAST ONE ELECTRICAL SHORT-CIRCUIT IN AN ELECTRICAL WIRING INTERCONNECTION SYSTEM FOR A VEHICLE, AND METHOD FOR DESIGNING AND MANUFACTURING SUCH A SYSTEM
A method is proposed for simulating and analysing at least one electrical short-circuit in an electrical wiring interconnection system (EWIS) for a vehicle. The result is a report concerning the safety of the EWIS that lists, for a selected modelled pathway (on which at least one short-circuit is simulated), any functional information associated with one or more modelled pathways affected by the at least one simulated short-circuit. A method is also proposed for designing and manufacturing the EWIS that is based on the simulation and analysis method. This assists the manufacturer in confirming the compliance of the EWIS (notably the spaces between the cable paths, in order to avoid any risks of short-circuits thereon) as early as possible in the process for designing and manufacturing this system.
G06F 30/3308 - Design verification, e.g. functional simulation or model checking using simulation
G06F 30/392 - Floor-planning or layout, e.g. partitioning or placement
G06F 119/02 - Reliability analysis or reliability optimisationFailure analysis, e.g. worst case scenario performance, failure mode and effects analysis [FMEA]
4.
AIRCRAFT COMPRISING AT LEAST ONE WING MOUNT SYSTEM, WHICH COMPRISES AT LEAST ONE LATERAL CONNECTING ROD
An aircraft having at least one wing mount system that connects a wing and a primary structure of a pylon and includes at least first and second wing mounts configured to absorb at least some of the forces and moments and positioned at the upper longitudinal member of the primary structure, at least one lateral connecting rod extending between first and second ends connected respectively to the primary structure and to the wing, the second end being spaced apart at least in the horizontal transverse direction and/or the vertical transverse direction with respect to the primary structure.
An air inlet device includes an inlet duct, a valve and at least one helical partition positioned within the inlet duct, the helical partition having an outer edge in contact with the inlet duct and delimiting at least one helical duct within the inlet duct. The helical partition serves to increase the distance travelled by an air flow entering the inlet duct before it reaches the valve in the closed state. An aircraft including at least one air inlet device of this kind is disclosed.
An anti-corrosion sealing washer made of a watertight material, such as a silicone, and having two peripheral tabs configured for gripping the sealing washer, and at least two locating pins. Also a protective assembly with such a sealing washer and a connecting second washer having a groove on its edge face and a protective cap having an inner annular relief with a complementary shape to the groove of the connecting washer.
A method for monitoring performance of an oil filter of an aircraft includes for at least one predetermined measurement time, acquiring a measured temperature value and a measured differential pressure value of oil passing through the oil filter, estimating, for the one or each measurement time, a reference differential pressure value using a prediction model and the measured temperature value, computing, for the one or each measurement time, a comparison value between the measured differential pressure value and the reference differential pressure value, and triggering an alert if a trigger condition, which is dependent on the one or more comparison values computed for the one or more measurement times, is met. Thus, the performance of the filter is monitored using an indicator that is reliable and easy to compute.
ACOUSTIC ABSORPTION STRUCTURE COMPRISING AT LEAST ONE PARTITION SYSTEM POSITIONED IN AT LEAST ONE CELL TO FORM TWO TYPES OF RESONATORS, METHOD OF MANUFACTURING SUCH A STRUCTURE
An acoustic absorption structure including a cellular structure that includes at least one cell delimited by at least one wall and at least one partition system. The system includes at least one subsystem positioned in the cell and adapted to divide it into at least two cavities and at least one tongue connected to the subsystem and having a hook shape straddling one of the first and second edges of the wall. The tongue facilitates installing and retaining each partition system in the cell.
An aircraft propulsive assembly including an engine pylon having a top face, an internal engine part, a possible fixed top cowling of the engine pylon and at least one engine cowl articulated in rotation on an axis of rotation defined by at least two articulation hinges. The axis of rotation of the at least two articulation hinges is positioned above the top face of the engine pylon. It is possible to assemble a nacelle fairing around the internal part of the engine, in the absence of the external part composed of the fan fairing, and without modifying the structure of the engine pylon except with respect to the arrangement of the hinge fittings of the movable engine cowls.
An automated taxi system for an aircraft includes a mapping module configured to generate a collaborative map that identifies traffic within the airport environment, a path trajectory module configured to receive digital taxi clearance from an Air Traffic Control (ATC) identifying a destination within the airport environment, such as a designated take-off runway, and to generate a taxi path trajectory to the destination, a guidance module configured to compute guidance instructions based on the taxi path trajectory, and an aircraft protection module configured to identify obstacles or incursion risks on the collaborative map in the taxi path trajectory and to modify the guidance instructions to avoid the obstacles or incursion risks.
Systems and methods for managing an anti-incursion function of an aircraft taxiing within an airport environment can be implemented by a monitoring equipment embedded in the aircraft. A human-machine interface of the monitoring equipment can be configured to display a guidance tile that presents context-dependent information as the aircraft taxies within the airport environment. In this way, the pilot of the aircraft can be first warned to ensure that the incursion-risk area (such as a runway) is cleared before operating the aircraft to enter into the incursion-risk area, and if the pilot fails to timely make steps to confirm clearance of the incursion-risk area, then the monitoring equipment can trigger automatic braking so as to stop the aircraft, thus preventing the aircraft from unsafely entering the incursion-risk area.
An automated aircraft taxi system for an aircraft taxiing within an airport environment implements a collision-avoidance function. The collision-avoidance function triggers revision of guidance instructions and or alerts the pilots of the aircraft when a predicted trajectory of moving objects intersects a taxi path trajectory of the aircraft. The collision-avoidance function disregards an identified object that is moving on a taxiway in the airport environment when a predicted trajectory of the identified object does not intersect the taxi path trajectory of the aircraft according to the location of the identified object and the layout of taxiways on the airport map.
In order to allow functional integration in a single structure for fluid transport in vehicles, a pipe arrangement is provided that includes at least one multi-walled pipe section that includes a multi-walled pipe for separately transporting each fluid medium or for separately accommodating each solid medium. In one solution, the multi-walled pipe section includes at least two nested pipe layers and the multi-walled pipe section is formed in a location of the pipe arrangement that is disposed in a confined space of the vehicle. In another solution, the multi-walled pipe section includes at least three nested pipe layers, wherein each pipe layer is chosen to transport a fluid medium or to accommodate a solid medium.
A system for supplying hydrogen to hydrogen consumer on an aircraft with a tank storing supercritical hydrogen. Energy is added to the tank to ensure tank pressure maintains supercritical. The system includes a supply pipe fluidly connected between the tank and the hydrogen consumer; a primary heat exchanger arranged on the supply pipe and configured to heat the hydrogen flowing in the supply pipe from the tank to the hydrogen consumer; and a tank heater arranged in the tank and configured to heat the hydrogen in the tank.
a method for mounting, in a nacelle for a hydrogen-powered aircraft, a box containing at least part of the equipment necessary for transporting dihydrogen to an engine of the aircraft, called H2 box, the mounting method comprising a step of positioning the H2 box in the nacelle by virtue of at least one rail secured to a chassis of the nacelle, or to the H2 box, or both.
A fastening system for fastening an object to a support, comprising a first fastening element and a second fastening element placed on either side of the support, and fasteners for fastening the object, the fasteners fastened to one of the fastening elements. The fastening system comprises an element, such as an elastic element, which is integrally fixed to the fastening elements and/or a lock integrally fixed to the fastening elements. Also an aircraft with such a fastening system.
F16L 3/10 - Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing divided, i.e. with two members engaging the pipe, cable or protective tubing
17.
METHOD AND DEVICE FOR DETECTING A DISCONNECTION STATE OF A PIPE FORMING PART OF A PUMPING SYSTEM OF A FUEL COLLECTOR OF AN AIRCRAFT
A method includes a receiving step for receiving a value of the quantity of fuel present in the collector, a processing step including a sub-step for classifying the value received in the receiving step as a normal value, or as an abnormal value, a sub-step for computing the value of a health indicator, based on the received value, as well as on a predetermined number of values received beforehand, and a sub-step for comparing the value of the health indicator with a threshold to be able to detect a disconnection state, as well as a warning step for transmitting a warning in the event of the detection of a disconnection state, the method allowing, by taking into account the quantity of fuel present in the collector, reliable detection of a disconnection state and allowing operators, notably maintenance operators, to be warned.
An aircraft with an energy management system for an electrical energy source in a hybrid electric propulsion architecture with at least one heat engine, an avionics system and components conveying parameters of the aircraft. An energy management module stores functions available for a given mission of the aircraft that are likely to be used by the engine and allowing assistance from the source, as well as the necessary associated charge required for the execution thereof. A controller is provided for authorizing their execution and ensuring the execution of the safety functions, the controller being linked to the components, to the electrical energy source and to an engine activation module in order to send it the authorized functions according to the control that has been completed.
B64D 31/18 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants for hybrid-electric power plants
A hydrogen distribution system for supplying hydrogen to a hydrogen consumer comprising: a tank storing a liquid hydrogen fuel; a conditioning system configured to provide a gaseous hydrogen stream downstream from the tank towards the hydrogen consumer; a compressor downstream of the conditioning system and configured to receive the gaseous hydrogen stream and provide a high-pressure gaseous hydrogen stream; a heater downstream of the compressor and configured to receive the high-pressure gaseous hydrogen stream and provide a high-temperature, high-pressure gaseous hydrogen stream; and, a valve downstream of the heater and configured to adjust a flow of the high-temperature, high-pressure gaseous hydrogen stream; wherein the hydrogen consumer is downstream of the valve and configured to receive the high-temperature, high-pressure gaseous hydrogen stream and provide energy by consuming hydrogen from the high-temperature, high-pressure gaseous hydrogen stream. Also, an aircraft with such a system.
A system for supplying hydrogen to hydrogen consumer on an aircraft with a helium heat transfer circuit. The hydrogen consumer may be a combustion engine or a fuel cell. A supply pipe is fluidly connected between the tank and a hydrogen consumer. A first pump is arranged on the supply pipe and configured to circulate the liquid hydrogen from the tank to the hydrogen consumer.
A flight control system for an aircraft including a first set of primary flight control computers and a second set of secondary flight control computers, where each primary flight control computer implements a first autopilot functionality. The secondary flight control computers jointly take control of control surface actuators when the primary flight control computers fail. The flight control system further includes another computer, to which the secondary flight control computers are connected, which implements a simplified second autopilot functionality, the second autopilot functionality being able to be activated only when the second set of flight control computers has control of the control surface actuators. Thus, an autopilot functionality is widely available, while at the same time ensuring the robustness sought by the installation of the secondary flight control computers.
B64C 13/18 - Initiating means actuated automatically, e.g. responsive to gust detectors using automatic pilot
B64C 13/50 - Transmitting means with power amplification using electrical energy
22.
AIRCRAFT COMPRISING AT LEAST ONE PROPULSION ASSEMBLY COMPRISING AT LEAST ONE MOTORIZATION AND A TRANSMISSION SYSTEM CONNECTED BY AN EXTERNAL COUPLING SYSTEM
An aircraft comprising at least one propulsion assembly comprising: at least one electric motor, a transmission system, at least one coupling module comprising a freewheel inserted between inner and outer shafts coupled by first and second coupling mechanisms to the output and input shafts of the electric motor and of the transmission system, at least one of the first and second coupling mechanisms comprising an angle gearset, at least one hollow intermediate element in which the output shaft of the electric motor, the input shaft of the transmission system and the inner and outer tubes of the coupling module are at least partially positioned.
B64D 35/021 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants
An aircraft control system and method for controlling electrical power distribution in an aircraft are disclosed. The aircraft control system and method obtain state signals from electrical systems in the aircraft, control characteristics of a power source, and control characteristics of the electrical systems. The control characteristics of the electrical systems are dependent on a flight phase status of the aircraft. Output control data is generated, based on the control characteristics and state signals, and used to control electrical power distribution in the aircraft.
B64D 27/35 - Arrangements for on-board electric energy production, distribution, recovery or storage
H02J 4/00 - Circuit arrangements for mains or distribution networks not specified as ac or dc
24.
AIRCRAFT ENGINE ATTACHMENT SYSTEM COMPRISING A TWO-POINT SHACKLE EQUIPPED WITH AT LEAST ONE STOP, AIRCRAFT COMPRISING AT LEAST ONE SUCH ENGINE ATTACHMENT SYSTEM
An engine attachment system connecting an aircraft motive-power unit and a primary structure of an aircraft pylon, and comprising: at least one clevis block secured to the primary structure or to the motive-power unit, at least one two-point shackle which comprises a body, an extension forming just one single component with the body, at least a first stop connected to the extension and facing a first flange of the clevis block and/or at least a second stop connected to the extension and facing a second flange of the clevis block, a connection pin housed in an orifice passing through the body, and a ball-joint connection positioned in the orifice and interposed between the body and the connection pin.
An air intake lip of an aircraft engine nacelle provided with a passive shut-off device for exhaust devices. The passive shut-off device is capable of adopting a shut-off position in which it shuts off the exhaust devices and an open position in which it clears the exhaust devices as a function of the temperature perceived by the passive shut-off device.
A method for repairing a dent situated on a wall includes hammering the dent using at least one ferromagnetic striker, positioned in line with the dent to be repaired, and at least one electromagnetic emitter that generates at least one electromagnetic field configured to animate the ferromagnetic striker according to alternating movements such that it hammers the wall. A repair device makes it possible to implement the method.
A radio altimetry system to be housed on board an aircraft and provide an altitude of the aircraft above ground level, including a first subsystem based on FMCW technology and providing a first altitude value, a second subsystem based on UWB technology and providing a second altitude value, and consolidation electronic circuitry to compare the second value with a predetermined threshold, if the second value is less than or equal to the threshold, determine a consolidated value based on the first and second values, and if the second value is greater than the threshold, determine a consolidated value based on the first value and without taking into account the second value. In this way, the radio altimetry system offers resilience to various interference.
A method for selecting a communication channel, called utilization channel, includes a step of determining, for each channel, one or more items of information representing a transmission quality of a message, with the message being either a “useful” message received by the on-board system, or a probe message, called “ping” message, a step of classifying the communication channels according to indices respectively representing transmission qualities, based on the information, a step of selecting the utilization channel as being the channel exhibiting the best transmission quality based on the indices, a step of determining a buffering time for each received useful message, and, if this time is non-zero, a step of transmitting the useful message, called eligible useful message, instead of a ping message.
A method for obtaining a cascade of vanes of an aircraft thrust reversal device by: manufacturing tubular preforms each having transverse and longitudinal facets that form a single piece, delimit a cell of the cascade of vanes and constitute at least one layer of the vanes, and longitudinal walls of the cascade of vanes situated around the cell; assembling the tubular preforms by connecting the transverse facets of the two tubular preforms so as to form a common vane, and/or the longitudinal facets of two tubular preforms so as to form a segment of a common longitudinal wall. Also a cascade of vanes obtained using such a method.
A triple-walled conduit comprising a main section that has internal, intermediate and external tubes extended by internal, intermediate and external endpieces, respectively, at least one connector that has a through-hole and first and second joining tubes, which surround the through-hole and face at least one surface of the internal, intermediate and external endpieces, at least one first sealing system interposed between the internal endpiece and one of the joining tubes of the connector, at least one second sealing system interposed between the intermediate endpiece and one of the joining tubes of the connector, at least one third sealing system interposed between the external endpiece and one of the joining tubes of the connector.
A method of obtaining a grid of blades of an aircraft thrust reversing device by producing U-shape elements each including an integral central part corresponding to a blade and first and second branches each corresponding to at least a part of a longitudinal wall of the grid of blades and assembling which includes connecting the first branches of the various U-shape elements to one another in such a manner as to form a first longitudinal wall and connecting the second branches of the various U-shape elements to one another in such a manner as to form a second longitudinal wall.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
32.
SYSTEM FOR REMOVABLY FASTENING A SCREEN TO AN INSTRUMENT PANEL OF AN AIRCRAFT, AND VISUALIZATION SYSTEM COMPRISING SUCH A FASTENING SYSTEM
A fastening system comprises a rail, a fastening device to fasten the rail to an instrument panel of a cockpit of an aircraft without modification of the instrument panel, and at least one movable carriage provided with a support device and configured to move in translation along the rail and to be brought into an operation position, the support device being provided with a support bracket to bear the screen and to be raised into the operation position and lowered on the movable carriage during a translational movement of the movable carriage on the rail.
A ring-shaped solid oxide fuel cell assembly, for an aircraft engine, with a ring-shaped inner manifold, a ring-shaped outer manifold arranged coaxially around the inner manifold, wherein one of the manifolds comprises a hydrogen inlet and the other comprise a hydrogen outlet, a plurality of tubular solid oxide fuel cells arranged radially between the manifolds, wherein each fuel cell comprises an anode formed as an inner tube, an inner end fluidly connected to the inner manifold and an outer end fluidly connected to the outer manifold, a cathode formed as an outer porous tube around the anode, and, between, the anode and the cathode, an electrolyte. For each fuel cell, an inner electrical contact electrically connects at the inner end of that fuel cell to the anode or the cathode, and an outer electrical contact electrically connects at the outer end to the other.
H01M 8/12 - Fuel cells with solid electrolytes operating at high temperature, e.g. with stabilised ZrO2 electrolyte
H01M 8/1246 - Fuel cells with solid electrolytes operating at high temperature, e.g. with stabilised ZrO2 electrolyte characterised by the process of manufacturing or by the material of the electrolyte the electrolyte consisting of oxides
H01M 8/2485 - Arrangements for sealing external manifoldsArrangements for mounting external manifolds around a stack
34.
ADJUSTABLE FLOOR MODULE FOR A FUSELAGE PORTION OF AN AIRCRAFT, PARTICULARLY A NOSE CONE, AND METHOD FOR INCORPORATING SUCH A FLOOR MODULE
A floor module includes a forward sub-module and a aft sub-module arranged relative to each other in a longitudinal direction of the floor module, the sub-modules connected together by connecting elements configured to allow relative movement between the sub-modules at least in the longitudinal direction and to allow the transmission of forces between the sub-modules in a vertical direction substantially orthogonal to the floor module without generating relative movement, the sub-modules thus connected by the connecting elements being structurally decoupled, that is, they can be moved slightly relative to each other, which makes it possible to adjust the geometry of the floor module, for example to overcome tolerance defects of the fuselage portion on which it is intended to be installed.
An air inlet of an aircraft propulsion assembly, comprising a lip which includes juxtaposed panels connected by at least one splice plate. This air inlet combines a main de-icing system and at least one secondary de-icing system which includes at least a main layer, which is made of a thermally conductive material and comprises a through-opening for each fixing element passing therethrough, the main layer being interposed at least partially between the splice plate and at least one of the first and second panels.
A method for estimating the air flow through an aircraft air vent, having at least two pressure sensors positioned along a pressure measurement extraction line on or near a lip of the vent, by calibration and correlation steps. The calibration step comprises generating a database associating, for each of at least two air streams applied to the vent, values of at least two known air stream characteristics, and the pressure distribution measurements along the measurement extraction line. The correlation step comprises measuring a pressure distribution along the line when the aircraft is in flight; and correlating the measured pressure distribution, associated with the values of the two characteristics, with the data from the database, in order to estimate the air flow when the aircraft is in flight.
B64D 43/00 - Arrangements or adaptations of instruments
G01F 1/34 - Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow by using mechanical effects by measuring pressure or differential pressure
G01F 25/10 - Testing or calibration of apparatus for measuring volume, volume flow or liquid level or for metering by volume of flowmeters
37.
REDUCED-MASS FLOATING-NUT SYSTEM AND METHOD FOR ASSEMBLING TWO PARTS USING SAID SYSTEM
A floating-nut system for assembling a part and a part, the part including an opening having an axis of revolution, the floating-nut system including at least one elastomer cage device and a nut device, the cage device including a cylinder to be introduced into an opening made in the part and a collar around the cylinder. The nut device includes a cylinder having an axis of revolution and a washer to press the collar against the part when the screw is screwed into the cylinder. The cylinder is deformable as the screw is screwed in so that the axis of revolution and the axis of revolution become substantially coincident. The elastomer cage device makes it possible to reduce the mass of the floating-nut system.
An aircraft including at least one engine attachment system, connecting an engine and a primary structure, which includes a central body and at least first right and left extensions positioned on either side of the central body in a first transverse plane, connected to the latter and stiffened by other right and left extensions and reinforcements. The engine attachment system includes at least three connections each including an anchoring point rigidly secured to the engine, the anchoring points of the various connections being located approximately in the same transverse plane. This solution makes it possible to reduce stresses in the engine, in particular torsional and/or bending stresses, produced as a result of the transfer of the forces between the engine and the primary structure.
An aircraft propulsion assembly that has a nacelle with a front opening and a rear opening, a propeller driven by an electric motor, a fuel cell supplying the electric motor with electric current, an inner channel arranged in the nacelle between the front opening and the rear opening. The electric motor and the fuel cell are disposed in the inner channel. A motorized fan is arranged at the rear part so as to draw in the air present in the inner channel and expel it to the outside through the rear opening. A control unit controls the motorized fan. With such an arrangement, the outside air cools the inside of the nacelle and the dihydrogen is evacuated.
B64D 33/00 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
B64D 27/355 - Arrangements for on-board electric energy production, distribution, recovery or storage using fuel cells
B64D 29/00 - Power-plant nacelles, fairings or cowlings
H01M 8/04014 - Heat exchange using gaseous fluidsHeat exchange by combustion of reactants
H01M 8/04223 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids during start-up or shut-downDepolarisation or activation, e.g. purgingMeans for short-circuiting defective fuel cells
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.
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.
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.
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
45.
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.
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.
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
50.
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
52.
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.
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 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 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.
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
B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
57.
AIRCRAFT COMPRISING AT LEAST ONE REMOVABLE DEVICE FOR ABSORBING ENERGY BY COMPRESSION
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.
B64C 11/06 - Blade mountings for variable-pitch blades
60.
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.
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.
A superconducting motor comprising a rotor, a stator on the outside of the rotor penetrated by an even number of holes, for each pair of holes, a coil comprising a U-shaped base and U-shaped sheets and made from a superconducting material, in which the sheets are fixed to one another and to the base, in which each column of a coil is inserted into one of the holes of the pair of holes.
H02K 55/00 - Dynamo-electric machines having windings operating at cryogenic temperatures
H02K 15/04 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of windings prior to their mounting into the machines
64.
METHOD FOR MONITORING THE TEMPERATURE OF BRAKES OF LANDING GEAR OF AN AIRCRAFT
A device for monitoring a maximum temperature reached during landing by a brake of landing gear of an aircraft. The monitoring device uses a prediction model to estimate a maximum temperature reached by the brake during landing. An error between the estimated maximum temperature and the measured maximum temperature is determined, and if the error is greater than a first predefined threshold, when the measured maximum temperature is greater than the estimated maximum temperature, or a second predefined threshold, when the measured maximum temperature is less than the estimated maximum temperature, and if a total number of errors is greater than a third predefined threshold, then a warning message is generated for attention of the flight crew and/or ground crew. It is thus possible to anticipate maintenance actions on landing-gear components.
A printing method comprising application of an ink on a support, pinning of the ink under UV radiation, capture of an image of the decoration and analysis of the image. In the absence of defects, the method continues with deposition of a varnish and solidification under UV radiation. In the event of a defect, the method includes erasure of the ink in a removal zone surrounding the defect, capture of a second image of the removal zone, analysis of the second image so as to determine the part of the decoration to be redone, the repair of the ink by deposition on the support so as to form the part of the decoration to be redone, and looping back to the analysis step.
B41J 29/26 - Devices, non-fluid media or methods for cancelling, correcting errors, underscoring or ruling
B41J 3/407 - Typewriters or selective printing or marking mechanisms characterised by the purpose for which they are constructed for marking on special material
B41M 7/00 - After-treatment of printed works, e.g. heating, irradiating
A method and a device for analysis of a profile of a real form of a surface of a part. The device determines and divides into subsections a deviation between the real form and the theoretical form. Then, for each subsection, a sinusoidal wave characterized by an amplitude b and a half-length of wave a is identified. When b is smaller than a predetermined value bmin or when a is smaller than a predetermined value amin, then the device stops the analysis, otherwise a new iteration of the analysis is carried out, considering the sinusoidal wave identified as a new profile of a theoretical form of the surface. Upon completion of the analysis phase, an alert message is generated if the values b and/or b/a do not comply with a manufacturing tolerance criterion.
A method of opening a cargo door of an aircraft, the aircraft including a body with an opening into a cargo bay, and a cargo door which covers the opening when it is in a closed position. A cargo door is outwardly rotated with a first actuator from the closed position to a first open position. Then an actuator rod is installed by coupling a first end of an actuator rod to the body and coupling a second end of the actuator rod to the cargo door in the first open position. Then the cargo door is outwardly rotated with the actuator rod from the first open position to a second open position by increasing a distance between the first and second ends of the actuator rod.
B64C 1/14 - WindowsDoorsHatch covers or access panelsSurrounding frame structuresCanopiesWindscreens
E05F 15/60 - Power-operated mechanisms for wings using electrical actuators
68.
METHOD AND SYSTEM FOR DEFINING A DIGITAL TWIN OF AN AIRCRAFT INTENDED TO IMPROVE A DESIGN OF AN AIRCRAFT STRUCTURE IN ORDER TO CONTRIBUTE TO THE FIGHT AGAINST CORROSION OF THE AIRCRAFT STRUCTURE
A method and system for defining a digital twin of an aircraft to improve a design of an aircraft structure to contribute to the fight against corrosion of the aircraft structure includes a step of collecting corrosion incidents on aircrafts, a step of determining zones associated with a corrosion risk level for each part, a definition step for defining a category of corrosion protection for each zone according to the corrosion risk level associated with each of the zones. The method makes it possible to define the corrosion protection treatment requirements of the aircraft structure more precisely.
To detect a measurement error in a pair of right-left static-pressure probes of an aircraft, a system including electronic circuitry is configured to obtain right/left static-pressure measurements from the pair of right-left static-pressure probes, compute a right-left static-pressure differential from the obtained measurements, determine a theoretical right-left static-pressure differential using data from other equipment of the aircraft, compare the difference between the computed right-left differential and the determined theoretical right-left differential with a predetermined threshold, and when the comparison shows that the difference between the computed right-left differential and the determined theoretical right-left differential is greater than the predetermined threshold, generate a static-pressure-measurement error warning. Thus, it is possible to finely detect any errors in static-pressure measurements.
A device comprising a plurality of sensors arranged on an aircraft and configured to measure input data, an avionics computer configured to determine, based on the input data, at least one control command for at least one control surface of the aircraft by using a control law comprising at least one gain value, the control law being configured to obtain a control command making it possible to generate a flutter mode on at least a part of the aircraft, and a control system configured to control the control surface of the aircraft so as to generate the flutter mode by using the control command determined by the avionics computer.
An actuation system for a cargo door of an aircraft. The cargo door covers an opening into a cargo bay when it is in a closed position. The actuation system includes a first actuator configured to outwardly rotate the cargo door from the closed position to a first open position, and a second actuator configured to outwardly rotate the cargo door from the first open position to a second open position.
A method and system for optimizing the maintenance of an aircraft structure against corrosion includes a step of collecting corrosion incidents on aircrafts, a step of determining zones and corrosion incident rates in each of the zones, a step of determining zones at risk, a step of determining a depth of corrosion, a step of determining a rate of corrosion, a step of determining a proposed inspection frequency for each of the zones at risk based on its rate of corrosion and a predetermined limit depth of each of the zones at risk. A proposed inspection frequency can be obtained that is more accurate and suited to the different parts of the aircraft structure.
B64F 5/60 - Testing or inspecting aircraft components or systems
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
73.
METHOD AND SYSTEM USING A NEURAL NETWORK TO PREDICT A TIME OF OCCUPANCY OF A RUNWAY BY AN AIRCRAFT
A prediction system with a unit for generating a current value of a parameter relating to the movement of an aircraft, a selection unit for a crew member of the aircraft to select an exit of the runway used for landing, an avionics computer for computing a value of the time of occupancy of the runway and a unit for transmitting this value to a user system. The avionics computer using an initial ground speed and an exit type and an exit distance of the exit selected, and computes the value of the time of occupancy of the runway, with the data and by using a prediction model comprising a neural network trained on the basis of landing data originating from previous landings.
ATELIERS DE LA HAUTE GARONNE ETS AURIOL ET CIE SAS (France)
Inventor
Laurent, Jean-Noël
Bigot, Julien
Fouladoux, Adrien
Le Henaff, Perig
Maurice, Arnaud
Jehenne, Bertrand
Gutierrez, Lucas
Meric, François
Abstract
A fastening device for keeping at least first and second parts assembled, the fastening device comprising a tubular body passing through the first and second parts, an expansion nut and a screw that is seated in the tubular body and cooperates with the expansion nut. To facilitate the removal of the fastening device, the screw has at least one shape, such as a recess positioned on the transverse face thereof, to prevent it from rotating using a first tool, and the expansion nut has at least one shape, such as a flat, to unscrew it using a second tool. Also an assembly comprising at least one such assembly device as well as a removal method.
A system includes a collecting unit for collecting a current oxygen pressure value of the oxygen bottles, an estimating unit for estimating an average degradation model, an adapting unit for adapting the average degradation model, a generating unit for generating several future degradation scenarios, an estimating unit for estimating, for each of the future degradation scenarios, a remaining useful lifetime, and for generating a remaining useful lifetimes probability distribution, a transmitting unit for transmitting an end-of-lifetime alert signal to an alert device if a remaining useful lifetime of an oxygen bottle is below a predetermined alert threshold.
G01M 3/32 - Investigating fluid tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors for containers, e.g. radiators
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
76.
PROPULSION SYSTEM FOR AN AIRCRAFT COMPRISING A TURBOJET, A PYLON AND ENGINE ATTACHMENT
A propulsion system of an aircraft comprising a turbojet extending around a longitudinal axis and having a vertical median plane passing through the longitudinal axis and having a fan casing with a rear face perpendicular to the longitudinal axis, a pylon presenting a rigid structure with a front wall and a lower spar, and an engine attachment comprising a front ring coaxial with the longitudinal axis and comprising first fixation element for securing the front ring to the rear face of the fan casing and second fixation element for securing the front ring to the front wall of the pylon.
A propulsion assembly having a combustion chamber and a fairing, an exhaust nozzle delimited by a nozzle wall, a dihydrogen tank, and a supply duct between the tank and the combustion chamber with a first portion between the tank and the nozzle wall, a second portion between the nozzle wall and the combustion chamber, and intermediate portions housed in the exhaust nozzle and wherein each intermediate portion has a first end, which is connected to the first portion through the nozzle wall, and a second end, which is connected to the second portion through the nozzle wall.
F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
A propulsion assembly having a propulsion system comprising a fairing, a rotary assembly having a combustion chamber and housed in the fairing, an exhaust nozzle positioned downstream of the combustion chamber and delimited by a nozzle wall, and ensuring the discharge of the combustion gases originating from the combustion of the dihydrogen in the combustion chamber, a dihydrogen tank, a supply duct which connects the tank and the combustion chamber, and at least one vane positioned inside the exhaust nozzle, wherein the supply duct has a duct portion arranged in the vane.
A propulsion assembly having a fairing, a combustion chamber housed in the fairing, an exhaust nozzle delimited by a nozzle wall, a dihydrogen tank, a double-walled supply duct between the tank and the combustion chamber that has an inner wall delimiting an inner volume for the circulation of the dihydrogen and, around it, an outer wall delimiting an outer volume, and a bypass chamber, which is positioned around the nozzle wall and in which is made an upstream orifice for the introduction of the combustion gases and a downstream orifice for the discharge of the combustion gases, and wherein the supply duct has a portion arranged in the bypass chamber.
An aircraft comprising at least one engine attachment system connecting a primary structure of a pylon and a motor, having a right-hand interface connected to the right-hand lateral face of the primary structure, a left-hand interface connected to the left-hand lateral face of the primary structure, first and second shackles connecting the right-hand and left-hand interfaces to the motor by virtue of engine connection pins and interface connection pins, a right-hand emergency connection pin cooperating with the right-hand interface and the motor, and a left-hand emergency connection pin cooperating with the left-hand interface and the motor.
A simplified representation of obstacles in the vicinity of an airport strip is constructed by obtaining information on the elevation of the terrain in the vicinity of the airport strip, applying filtering by following a filtering profile in the shape of a cone the apex of which is placed at one end of the airport strip, the rotation axis of the cone being perpendicular to the airport strip, the cone having an outer surface forming a predetermined angle a with the airport strip, the filtering eliminating the information on the elevation of terrain having an altitude which is lower than the filtering profile. The terrain elevation information remaining after filtering is stored as relevant obstacle information. Thus, the volume of elevation data to be stored and to be processed on take-off or on landing is reduced.
A method for manufacturing an intermediate resistive membrane called “septum” with tubular guides for an acoustic treatment panel with double degree of freedom. The membrane and the tubular guides are manufactured by hot stamping a substrate placed between two parts of a stamping press and an additional layer taking the form of a thermoplastic film of small thickness and pre-perforations. Hot air intake may be used for the hot stamping.
B29C 51/08 - Deep-drawing or matched-mould forming, i.e. using mechanical means only
B29C 51/12 - Shaping by thermoforming, e.g. shaping sheets in matched moulds or by deep-drawingApparatus therefor of articles having inserts or reinforcements
B29C 51/14 - Shaping by thermoforming, e.g. shaping sheets in matched moulds or by deep-drawingApparatus therefor using multilayered preforms or sheets
A method for manufacturing an intermediate resistive membrane, called a “septum”, with tubular guides for a DDOF (double degree of freedom) acoustic treatment panel. The method includes the membrane and the tubular guides being manufactured by the same operation of injecting a resin around a substrate placed between two parts of an injection mold.
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
B29C 45/00 - Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mouldApparatus therefor
An airport installation including a plurality of types of aircraft in which each aircraft of one type includes a tank containing dihydrogen at a saturation pressure in a first range different from the other first ranges, for each type of aircraft a storage tank at a saturation pressure in a second range associated with the type of aircraft, and for each storage tank pumps or other devices fill from the storage tank the tank of the aircraft of the type for which the first range corresponds to the storage tank.
A device for measuring temperature of a fluid flowing over an outer wall of an object including an optical fiber and a flexible jacket surrounding the optical fiber, the optical fiber extending along a longitudinal axis, the measuring device including an elongate insulating part including cork and having at least two opposite faces, an inner face and an outer face, and the jacket surrounding the insulating part, apart from the outer face, and keeping the inner face of the insulating part facing the optical fiber over at least a part of its length along the longitudinal axis, the inner face of the insulating part having a transverse dimension greater at least than the diameter of the fiber.
G01K 11/32 - Measuring temperature based on physical or chemical changes not covered by group , , , or using changes in transmittance, scattering or luminescence in optical fibres
A sealing plug for leaktightly plugging a cavity. The sealing plug comprises an incompressibly deformable envelope delimiting a hollow internal space and provided with at least one orifice, a rod which can slide through the envelope, a first end of the rod that is provided with a head being able to deform the envelope when a second end of the rod is pulled, and a viscous seal arranged in the internal space of the envelope so as to be expelled from the envelope through the orifice when the envelope is deformed.
A method and system for monitoring a safety level of a trajectory followed by a flying aircraft. The system selects, from among a set of integration points, the integration point at the position farthest from the current position of the aircraft on the trajectory. The system checks whether part of the trajectory extending from the current position of the aircraft to the position of the selected integration point is safe if no conflict is detected, and a contingency trajectory exists. These steps are repeated for each integration point, one step at a time until a safe trajectory is found. This results in a safety level dependent on the integration point from which the trajectory is considered to be safe. It is possible to anticipate any conflicts and, if necessary, to seamlessly carry out operations for diverting the aircraft.
A set of pipes comprising two pipes, a sleeve into which the pipes are fitted, for each pipe, a clamping collar arranged around the sleeve and an anchoring element secured to the pipe and comprising a first fastener, for each clamping collar, a retaining element secured to the clamping collar and having a through-passage, and a tie passing through the through-passages and having, at each end, a second fastener cooperating with a first fastener in order to fasten each end of the tie an anchoring element.
F16L 21/06 - Joints with sleeve or socket with a divided sleeve or ring clamping around the pipe ends
89.
Aircraft nacelle provided with at least one thrust reversal device comprising at least one longitudinal deflector, aircraft comprising at least one propulsion assembly composed of such a nacelle
An aircraft nacelle provided with a thrust reversal device which comprises at least one diversion system which is configured to divert, in the activated state, an airflow channeled in the nacelle toward a lateral opening of the nacelle, at least one orientation system comprising at least one transverse deflector which is configured to orientate the airflow diverted by the diversion system in the radial directions and toward the upstream end of the nacelle, and at least one longitudinal deflector which is secant to the transverse deflector(s) and which is oriented in a direction which forms an angle of less than 25° with the longitudinal direction.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
90.
AIRCRAFT COMPRISING A DIHYDROGEN SUPPLY SYSTEM AND A DIHYDROGEN HEAT TREATMENT SYSTEM
An aircraft comprising at least one dihydrogen tank, at least one dihydrogen consumer system, a supply line arranged between a consumer system and a tank, for each consumer system, a loop containing a heat transfer fluid, for each tank and each supply line, a supply heat exchanger which exchanges calories between the heat transfer fluid and the dihydrogen and, for each consumer system, a return heat exchanger which exchanges calories between the heat transfer fluid and the consumer system.
A powerplant for an aircraft, comprising a propulsion system with a core enclosed in a casing and having a combustion chamber, a supply pipe conveying dihydrogen to the combustion chamber by passing through the casing in an injection zone, and a closed enclosure, delimited by first and second walls and containing a downstream pipe, a treatment system for treating the dihydrogen, and the injection zone, wherein the first wall is formed by part of the casing.
A fuel conditioning system for an aerobic hydrogen engine, including: at least one hydrogen pump configured to increase the pressure of the liquid hydrogen delivered at the outlet of a tank, one or several heat exchangers configured to increase the temperature of the pressurized hydrogen, an air supply circuit, at least one combustion device configured to ensure a partial combustion of the hydrogen with air coming from the air supply circuit in order to produce a fuel including a gas mixture including gaseous hydrogen and devoid of oxygen.
An aircraft fuselage includes fore and aft sections, a barrier wall separating the sections and 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, a first roller and a second roller rotatably fixed to the door and moveable on the rail along first and second paths to move the door, the rail including a first ramp engaging the first roller as it moves 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 configured to engage the first ramp as the second roller engages the second ramp to move the door towards the barrier wall.
A joint for aircraft electrical pack or battery pack for attaching the electrical pack to an aircraft component is disclosed. The electrical pack includes a surface having a dovetail dowel integrally formed thereon, and a dovetail rail is attached to the aircraft component. The electrical pack is mounted and assembled to the aircraft component by securing the dovetail dowel to the dovetail rail forming a dovetail joint. The aircraft component may be an engine pylon.
An aircraft including at least one aerodynamic wall against which an airflow flows in a direction of flow when the aircraft is in flight and at least one cavity opening at the aerodynamic wall, the cavity being delimited by a tubular lateral wall and a bottom. The cavity comprises at least one reduction in passage section spaced apart from the bottom and extending only over a part of the circumference of the tubular lateral wall.
An assembly comprising a longitudinal member of an aircraft wing, where the longitudinal member has a contact wall which is penetrated by first bores, each passing through the contact wall parallel to a longitudinal direction, an engine pylon which is arranged at the end of the longitudinal member in the longitudinal direction and having an upper longitudinal member which, for each first bore, is penetrated by a second bore which is aligned with the first bore, and a nut and a screw for each pair of a first bore and a second bore, which are aligned, where the screw is screwed into the nut successively via the first bore and the second bore, sandwiching the upper longitudinal member and the contact wall.
An aircraft pylon comprising an aircraft pylon fairing extending along a longitudinal axis, a primary structure having a peg that is inserted in a through opening of an inner rib of the fairing and four yokes as well as four removable fixing elements that can be inserted from the outside of the fairing. The fixing elements are inserted in a direction perpendicular to said longitudinal axis of the fairing in order to hold in place a fitting of the primary structure that has an oblong through opening and is inserted into one of said yokes of the fairing. Also a method of assembling an aircraft pylon and an aircraft with such a pylon.
A method for managing taxiing paths of an aircraft includes at least one computer system, the method being implemented by the computer system. The method includes the following steps: editing an initial path; displaying a route of the initial path on a screen using a first route symbolism; obtaining a validation of the initial path; displaying a route of the validated initial path on the screen using a second route symbolism; implementing the validated initial path in a taxiing setpoint of the aircraft. The method further includes an editing process and an independent display process.
A seat mounting system having a seat rail and a seat fitting, wherein the seat rail has an upper flange with a plurality of heads thereon. The seat fitting comprises a main body having a void configured to receive the upper flange and at least some of the plurality of heads.
A method for repairing a zone of a metal structural aircraft part having a protection defect in the vicinity of an orifice for receiving a fastener. There is a step of positioning an isolation element on the zone around the orifice, a step of applying a coat of paint to the zone, covering the isolation element, and a step of inserting a metal fastener into an orifice of the isolation element, prior to or following the step of applying the coat of paint. The isolation element makes it possible to avoid direct contact between the metal of the fastener and the metal forming the aircraft structure, and therefore to avoid any risk of galvanic coupling between the damaged zone and the fastening.
