Abstract

The present invention concerns a thermosensitive coating comprising a matrix comprising thermochromic spin transition pigments, said thermochromic pigments comprising a metal centre and at least one ligand, in which said metal centres of the different thermochromic pigments are linked together, thus forming a network, said thermosensitive coating further having at least one temperature threshold of between 50 °C and 180 °C with an accuracy of less than 10 °C. The present invention also relates to a method for producing a thermosensitive material.

IPC Classes  ?

• C09D 5/26 - Thermosensitive paints
• C09B 57/10 - Metal complexes of organic compounds not being dyes in uncomplexed form
• C09D 163/00 - Coating compositions based on epoxy resinsCoating compositions based on derivatives of epoxy resins
• C09D 175/04 - Polyurethanes
• G01K 11/12 - Measuring temperature based on physical or chemical changes not covered by group , , , or using changes in colour, translucency or reflectance

Abstract

A pipe for forming air flow pipelines in a structure that includes a flexible tube made from composite material, the tube having, on the length of same, sections for which the wall of the tube is stiffened by means of structural elements made from a rigid composite material incorporated into the wall of the tube. The structural elements are configured and arranged at the surface of the tube in such a way as to form a lattice framework surrounding the wall of the tube. The pipe further includes electrical conductors, disposed longitudinally on the wall of the pipe, the electrical conductors having a straight path at the stiffened sections of the pipe and a meandering path at certain of the non-stiffened sections of the pipe, the meandering allowing the conductor to tolerate the possible twisting of the pipe when it is installed in the structure.

IPC Classes  ?

• F16L 9/12 - Rigid pipes of plastics with or without reinforcement
• F16L 11/10 - Hoses, i.e. flexible pipes made of rubber or flexible plastics with reinforcements not embedded in the wall
• B64D 13/00 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
• F16L 11/127 - Hoses, i.e. flexible pipes made of rubber or flexible plastics with arrangements for particular purposes, e.g. specially profiled, with protecting layer, heated, electrically conducting electrically conducting
• F16L 11/18 - Articulated hoses, e.g. composed of a series of rings
• F24F 13/02 - Ducting arrangements
• F16L 11/02 - Hoses, i.e. flexible pipes made of fibres or threads, e.g. of textile
• B29D 23/00 - Producing tubular articles
• B29K 75/00 - Use of polyureas or polyurethanes as moulding material
• B29K 83/00 - Use of polymers having silicon, with or without sulfur, nitrogen, oxygen or carbon only, in the main chain, as moulding material
• B29K 309/08 - Glass
• B29L 23/00 - Tubular articles

Abstract

The invention relates to the use of a dialkyl carbonate compound as an anti-soot additive for an aviation fuel for turbine engines, said dialkyl carbonate compound being selected from the group consisting of: (A), (B), (C), (D) and mixtures of same, provided that compound C is not used together with a dialkyl dicarbonate compound.

IPC Classes  ?

• C10L 1/19 - Esters
• C10L 10/02 - Use of additives to fuels or fires for particular purposes for reducing smoke development

Abstract

The invention relates to a device (10; 50; 60) for detecting particles, comprising: - at least two flat matrix sensors (11; 52; 61) arranged in different planes, said matrix sensors each comprising a matrix (13; 54) with at least two dimensions of cells, the state of which is able to be modified when crossed by a particle; - and processing means (18; 58; 64) for processing data supplied by said matrix sensors. Said processing means determine a type, trajectory and energy level of an incident particle (21; 31; 57) having crossed at least one of said matrix sensors and having been responsible for depositing charges in at least one cell of at least two of said matrix sensors, from the analysis (80) of the data supplied by said matrix sensors, with spatial and temporal coincidence between the cells of at least two matrix sensors.

IPC Classes  ?

• G01T 1/24 - Measuring radiation intensity with semiconductor detectors

Abstract

The invention relates to a device (10) for testing an electronic apparatus (100), said device comprising: - a plate (105) comprising a power supply (110) and a means (115) capable of conducting a measure of operation during the test, the plate (105) also comprising at least one encoder (120, 121, 22) that outputs a signal (125, 126, 127) representing a distance 5 covered by the plate (105), - an irradiation means (135) facing the electronic apparatus (100) and configured to subject it to radiation (140), wherein the signal (125, 126, 127) is transmitted to the irradiation means (135) and in that emission of radiation (140) is triggered by reception 10 of a predetermined signal (125, 126, 127). The invention also relates to the method (20) for testing an electronic apparatus (100) implemented by means of the device (10).

IPC Classes  ?

• G01R 31/28 - Testing of electronic circuits, e.g. by signal tracer
• G01R 31/302 - Contactless testing
• G01R 31/305 - Contactless testing using electron beams
• G01R 31/311 - Contactless testing using non-ionising electromagnetic radiation, e.g. optical radiation of integrated circuits

Abstract

The invention relates to a device (100) for the measurement and compliance monitoring of an impact (220) on a structure (200). The device comprises: a support frame (10) including a hollow lower surface (13) to be positioned against a surface (210) of the structure (200) and directed towards the impact, said hollow lower surface defining a positioning plane (14); an optical dimensional measurement means (20) configured to be directed towards the hollow lower surface (13), said optical dimensional measurement means being positioned on the support frame (10) at a distance such that the positioning plane (14) coincides with a reference plane of the optical dimensional measurement means; a management module (30) comprising a unit for processing at least one image obtained by the optical dimensional measurement means (20) and a display screen (31) for providing information relating to the compliance of the impact.

IPC Classes  ?

• G01N 21/88 - Investigating the presence of flaws, defects or contamination
• B64F 5/60 - Testing or inspecting aircraft components or systems
• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for
• G01B 11/16 - Measuring arrangements characterised by the use of optical techniques for measuring the deformation in a solid, e.g. optical strain gauge
• G01B 11/25 - Measuring arrangements characterised by the use of optical techniques for measuring contours or curvatures by projecting a pattern, e.g. moiré fringes, on the object

Abstract

System (1) for correcting a trajectory of at least one robot (5) comprising: - an effector (4) carried by the robot; - a control unit for the robot; - at least one target (3) linked with the effector (4); said system comprises: - at least two cameras (2a, 2b, 2c, 2d) connected to at least one processing unit (6a, 6b, 6c, 6d); and - a central unit (8) configured to receive the two-dimensional coordinates of the targets (3) and to transmit position correction information, to the robot control unit.

IPC Classes  ?

• B25J 9/16 - Programme controls

Abstract

The invention relates to a hybrid power or thrust generator (100) including at least one thermodynamic turbine engine (20) and at least one electric power generator (40). An electric power generator (40) is electrically connected to at least one electric motor (30), mechanically and rotatably coupled to one or more rotating portions (21, 22, 24) of the thermodynamic turbine engine, and the electric power generator operates simultaneously with the thermodynamic turbine engine so as to supply the electric motor(s) to reduce the power drawn from the turbines of the thermodynamic turbine engine in operation. The electric power generator (40) may comprise a thermoacoustic engine (50) driving a linear electric alternator (53). The generator is advantageously implemented in a vehicle, such as an aircraft (15).

IPC Classes  ?

• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
• F02G 1/043 - Hot gas positive-displacement engine plants of closed-cycle type the engine being operated by expansion and contraction of a mass of working gas which is heated and cooled in one of a plurality of constantly communicating expansible chambers, e.g. Stirling cycle type engines

Abstract

The present invention relates to a method for cutting materials for manufacturing parts according to which an image of a cutting line is made recurrently downstream from the cutting head and the images produced in this way are analysed in real time in order to calculate amplitudes of deviations in the quality of the surface profiles of the cutting line as the part is being cut and comparing said calculated amplitudes to at least one predefined threshold value, said cutting being stopped in the event of said at least one threshold value being exceeded. The invention also concerns a device for implementing said method.

IPC Classes  ?

• B26D 5/00 - Arrangements for operating and controlling machines or devices for cutting, cutting-out, stamping-out, punching, perforating, or severing by means other than cutting
• B24C 1/04 - Methods for use of abrasive blasting for producing particular effectsUse of auxiliary equipment in connection with such methods for treating only selected parts of a surface, e.g. for carving stone or glass
• B26F 3/00 - Severing by means other than cuttingApparatus therefor
• B26D 7/24 - Safety devices specially adapted for cutting machines arranged to disable the operating means for the cutting member

Abstract

The invention relates to a method for the automatic calculation of a distance-amplitude correction (DAC) curve for a non-destructive ultrasonic testing system, the system comprising an ultrasound sensor (10) and a reference part (11). The method comprises the following steps: 101 acquisition of a large number of measuring points uniformly distributed over the entire surface of the reference part (11); and 102 unsupervised classification (unsupervised learning) of the acquisition points (time/amplitude couples).

IPC Classes  ?

• G01N 29/44 - Processing the detected response signal

Abstract

The invention relates to an aircraft (100) including a fuselage and at least one wing (10) comprising, on the aerodynamic plane, a plurality of distributed airfoils (20) separated from one another, numbering more than 10, and arranged inside an enclosing space (11) bearing on the airfoils. The shape and dimensions of the enclosing space correspond to the shape and dimensions of a simple wing of conventional structure, which is adapted to the aircraft (100) taking account of the weight and flight speed of the aircraft. Advantageously, the airfoils (20) are arranged such that the cross-section of the enclosing space (11) in a vertical plane XZ of the aircraft matches the shape of the aerodynamic profile of the simple wing of conventional structure. The airfoils (20) are arranged, for example, to produce a V formation in plan view, with the tip pointing forwards.

IPC Classes  ?

• B64C 39/06 - Aircraft not otherwise provided for having disc- or ring-shaped wings
• B64C 39/08 - Aircraft not otherwise provided for having multiple wings

Abstract

The present invention relates to a method for enhanced joint target discovery and detection in a radar through matched illumination, using an adaptive transmit and receive filter, characterized in that, in the absence or weak clutter, the modified adaptive transmit and receive filter is given as Figure (I), where R(f), H(f), X(f) represent the Fourier transform of the receive filter, target spatial spectra and transmitted signal spectra and Φn(f) denotes the PSD of noise. The present invention also concerns a system for enhanced joint target discovery and detection in a radar through matched illumination.

IPC Classes  ?

• G01S 13/524 - Discriminating between fixed and moving objects or between objects moving at different speeds using transmissions of interrupted pulse modulated waves based upon the phase or frequency shift resulting from movement of objects, with reference to the transmitted signals, e.g. coherent MTi
• G01S 7/292 - Extracting wanted echo-signals

Abstract

A thermoacoustic engine (100) comprises an acoustic-wave generator (20), a thermoacoustic cell (10) comprising at least one module (10a, 10b, 10c) and a converter (30) converting the amplified acoustic wave into mechanical power. The thermoacoustic cell (10) comprises, at an inlet of the at least one module of said cell, on the same side as the generator (20), at least one cooling stage (12) to transfer an amount of heat from the working gas to a cold source (14) and at the level of an outlet of the at least one module of said cell, on the same side as the converter (30) comprises at least one reheating stage (11) to transfer a quantity of heat from a hot source (13) to the working gas. The converter (30) mainly comprises a turbine (31) through which the amplified acoustic wave passes, said turbine driving a rotation shaft (32) of axis (33) one end of which passes in gastight manner sealed against the working gas through a wall of the enclosure (40).

IPC Classes  ?

• F01D 1/02 - Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor
• F02G 1/04 - Hot gas positive-displacement engine plants of closed-cycle type
• F02G 1/043 - Hot gas positive-displacement engine plants of closed-cycle type the engine being operated by expansion and contraction of a mass of working gas which is heated and cooled in one of a plurality of constantly communicating expansible chambers, e.g. Stirling cycle type engines
• F02C 1/10 - Closed cycles
• F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
• F03B 13/14 - Adaptations of machines or engines for special useCombinations of machines or engines with driving or driven apparatusPower stations or aggregates characterised by using wave or tide energy using wave energy
• F03B 13/24 - Adaptations of machines or engines for special useCombinations of machines or engines with driving or driven apparatusPower stations or aggregates characterised by using wave or tide energy using wave energy to produce a flow of air, e.g. to drive an air turbine

Abstract

A device (10) for the electric power supply of a load (11), includes at least two energy storage elements (13, 14), elements for determining the power needs of the load (11), elements (16, 17) for monitoring each energy storage element (13, 14), which are able to provide information about a maximum instantaneous power of each energy storage element (13, 14), a calculation body (19) for determining a maximum secured power according to the electromotive force (Ebat(t)) and the resistance (Rbat(t)) of the Thévenin model, a maximum specified current and a maximum specified voltage, and elements (Cbat(t), Csc(t)) for controlling each energy storage element (13, 14), the elements being adjusted over time according to the power needs of the load (11) and the maximum secured power of each energy storage element (13, 14).

IPC Classes  ?

• H02J 1/00 - Circuit arrangements for dc mains or dc distribution networks
• H02J 3/00 - Circuit arrangements for ac mains or ac distribution networks
• H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
• H02J 7/34 - Parallel operation in networks using both storage and other DC sources, e.g. providing buffering

Abstract

The invention relates to a structure (10) comprising at least one electrical line (20) on one surface (11) of the structure, one electrically conductive layer (23) of the line resulting from deposition of an electrically conductive material via a cold spraying method, and the line comprises a protective bonding layer (22) on which the electrically conductive material is deposited via the cold spraying method, the protective bonding layer forming a continuous protective shield between the structure (10) and the cold-sprayed material. An insulating layer (21) is advantageously located between the structure and the protective bonding layer. Achieving an electrical line (20) on a surface (11) of the structure (10) involves implementing a step of oxy-fuel flame spraying of a protective material to form a protective bonding layer (22), followed by a step of cold spraying of the electrically conductive material of the electrically conductive layer (23) onto the protective bonding layer (22).

IPC Classes  ?

• H05K 3/14 - Apparatus or processes for manufacturing printed circuits in which conductive material is applied to the insulating support in such a manner as to form the desired conductive pattern using spraying techniques to apply the conductive material
• C23C 4/12 - Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
• C23C 4/18 - After-treatment
• C23C 24/04 - Impact or kinetic deposition of particles

Abstract

The invention consists of an ultrasonic device for characterising the flow of resin entering and exiting an injection mould (14) during the phase of impregnation, by said resin, of a preform (16) contained in said injection mould. The device comprises two ultrasonic sensors (21, 22) arranged respectively in the vicinity of the inlet port (23) where the resin enters the injection mould (14) and in the vicinity of the outlet port (24) where the resin exits said mould, each sensor emitting an ultrasonic wave towards the end of the mould in the vicinity of which it is positioned, and receiving the ultrasonic wave reflected by the medium. In a preferred embodiment, the device also comprises means for determining the stabilisation of the flow of resin passing through the mould (14) by means of the signals received by the sensors. The invention also consists of a method implementing the device according to the invention in order to determine the completeness of the operation of impregnating, with resin, a preform (16) positioned in an injection mould (14) into which the resin is introduced.

IPC Classes  ?

• G01N 15/08 - Investigating permeability, pore volume, or surface area of porous materials
• 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
• G01N 29/02 - Analysing fluids

Abstract

The invention concerns a method for drilling at a point on the surface of a workpiece, which involves using a drill bushing (15) having a main axis (13). The invention involves carrying out the following steps: a) in an (x, y, z) Cartesian coordinate system linked to said bushing, carrying out a relative movement between said bushing and said workpiece in the (x, y) plane to bring the main axis (13) of said bushing to the vertical of said point on the surface (18) of the workpiece to be drilled, said main axis (13) then being parallel to the z axis, b) said bushing being mobile in rotation about a pivot point positioned on said main axis (13), orienting said main axis (13) such that it is perpendicular to the osculating plane of the workpiece at said point to be drilled, by pivoting said drill bushing (15) relative to said pivot point, said pivot point being fixed in said (x, y) plane, c) moving said drill bushing (15) oriented in this way in translation along said z axis in order to bring said main axis (13) of the bushing to said point to be drilled, said drill bushing (15) being fixed in said (x, y) plane, d) said drill bushing (15) comprising a drilling tool coaxial with said drill bushing (15), drilling said surface (18) of the workpiece at the point to be drilled by moving said tool in translation along said main axis (13).

IPC Classes  ?

• B23B 35/00 - Methods for boring or drilling, or for working essentially requiring the use of boring or drilling machinesUse of auxiliary equipment in connection with such methods
• B23B 49/00 - Measuring or gauging equipment on boring machines for positioning or guiding the drillDevices for indicating failure of drills during boringCentring devices for holes to be bored
• B23Q 17/22 - Arrangements for indicating or measuring on machine tools for indicating or measuring existing or desired position of tool or work

Abstract

The subject of the invention is a device for attenuating sound waves forming the wall of a duct, the sound waves spreading in a stream of air passing along the duct. The device comprises a structure (13) constituting a noise attenuator, bounded by a perforated internal wall and a solid external wall. The device comprises fluid tight piping for transporting a heat-transfer fluid on the internal face of the internal wall, the piping constituting a network of piping running substantially in one and the same direction, and such that each length of piping is situated between rows of orifices and is situated substantially in line with the cell partitions. The piping together with the internal wall forms a surface heat exchanger.

IPC Classes  ?

• G10K 11/172 - Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects
• B64D 15/02 - De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
• B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
• F02K 1/82 - Jet pipe walls, e.g. liners
• F02C 7/045 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression

Abstract

The present invention concerns coatings, for example polymer coatings or sol-gel coatings, comprising at least one layer comprising micrometric, individualised and mesostructured spherical particles, said particles having been created and loaded with at least one element selected from corrosion-inhibiting functional molecules and corrosion-inhibiting functional nano-objects, by a method comprising non-dissociable and continuous steps in a same spray-heating reactor. The purpose of said coatings is to form an anti-corrosion system, having mechanical strength and/or for colouring. The invention is applicable, in particular, in the field of protecting light aeronautical alloys against corrosion.

IPC Classes  ?

• C09D 5/08 - Anti-corrosive paints
• C09D 7/12 - Other additives
• C08K 13/02 - Organic and inorganic ingredients

Abstract

The aircraft (10) includes: at least one electric motor (135); at least one stand-alone electrical power supply (110, 120) supplying power to the electric motor; propulsion elements (130) referred to as “auxiliary propulsion elements”, included in the group including: a stand-alone electrical power supply (130) supplying power to the electric motor, a power supply converting thermal energy into electrical energy and supplying power to the electric motor, and an internal combustion engine; and a structure (100) configured to integrate each electric motor, each stand-alone electrical power supply and the auxiliary propulsion elements, the parameters of the structure being substantially identical regardless of the auxiliary propulsion elements. A method of fitting out such an aircraft is also described.

IPC Classes  ?

• B64D 41/00 - Power installations for auxiliary purposes
• B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
• B64D 37/02 - Tanks
• F02B 61/06 - Combinations of engines with mechanical gearing
• F02B 65/00 - Adaptations of engines for special uses not provided for in groups or Combinations of engines with other devices, e.g. with non-driven apparatus
• B64D 27/02 - Aircraft characterised by the type or position of power plants

Abstract

A method of managing a power demand to assure the operation of a pilotless aircraft. The aircraft includes an internal combustion engine supplying a maximum principal power which can vary. The management method is particularly suitable for a rotary wing pilotless aircraft. It guarantees the storage of an amount of electrical energy at least equal to a recovery energy of the aircraft in the event of failure of the internal combustion engine. This recovery energy enables the control of autorotation and landing of the aircraft.

IPC Classes  ?

• F02B 65/00 - Adaptations of engines for special uses not provided for in groups or Combinations of engines with other devices, e.g. with non-driven apparatus
• B64C 39/02 - Aircraft not otherwise provided for characterised by special use
• F02B 37/00 - Engines characterised by provision of pumps driven at least for part of the time by exhaust
• F02B 33/40 - Engines with pumps other than of reciprocating-piston type with rotary pumps of non-positive-displacement type
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F02C 6/12 - Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
• F02C 6/14 - Gas-turbine plants having means for storing energy, e.g. for meeting peak loads
• F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
• B60K 6/24 - Arrangement or mounting of plural diverse prime-movers for mutual or common propulsion, e.g. hybrid propulsion systems comprising electric motors and internal combustion engines the prime-movers consisting of electric motors and internal combustion engines, e.g. HEVs characterised by apparatus, components or means specially adapted for HEVs characterised by the combustion engines
• B60K 6/38 - Arrangement or mounting of plural diverse prime-movers for mutual or common propulsion, e.g. hybrid propulsion systems comprising electric motors and internal combustion engines the prime-movers consisting of electric motors and internal combustion engines, e.g. HEVs characterised by apparatus, components or means specially adapted for HEVs characterised by the driveline clutches
• B60K 6/40 - Arrangement or mounting of plural diverse prime-movers for mutual or common propulsion, e.g. hybrid propulsion systems comprising electric motors and internal combustion engines the prime-movers consisting of electric motors and internal combustion engines, e.g. HEVs characterised by apparatus, components or means specially adapted for HEVs characterised by the assembly or relative disposition of components
• B60K 6/44 - Series-parallel type
• B60K 6/387 - Actuated clutches, i.e. clutches engaged or disengaged by electric, hydraulic or mechanical actuating means
• B60K 6/442 - Series-parallel switching type
• B64D 27/02 - Aircraft characterised by the type or position of power plants

Abstract

A method for locating electrostatic discharges occurring on an aircraft in flight comprises: - a step of recording, during the flight of the aircraft, electromagnetic signals resulting said electrostatic discharges and received by a plurality of detectors Di arranged at different places on an exterior surface of said aircraft; - a step of analysing the signals recorded during the flight, in which characteristics of each of the signals, received by the various detectors and corresponding to one and the same electrostatic discharge, are processed to identify at least one zone of an exterior surface of the aircraft, determining a structural part in which the electrostatic discharge probably occurred.

IPC Classes  ?

• G01R 31/00 - Arrangements for testing electric propertiesArrangements for locating electric faultsArrangements for electrical testing characterised by what is being tested not provided for elsewhere

Abstract

Disclosed is a method for measuring movement and/or deformation of a study part subjected to an external stress, the method implementing a color digital image acquisition device and image correlation unit. The method includes: acquisition (250) of a plurality of color digital images of the surface of the study part by way of the color digital image acquisition device during the application of an external stress on the study part, and processing (260) of the color digital images acquired in the step of acquisition of a plurality of color digital images so as to highlight contrasting details on variable scales.

IPC Classes  ?

• G06K 9/00 - Methods or arrangements for reading or recognising printed or written characters or for recognising patterns, e.g. fingerprints
• G06T 7/20 - Analysis of motion
• G01B 11/16 - Measuring arrangements characterised by the use of optical techniques for measuring the deformation in a solid, e.g. optical strain gauge
• G01M 5/00 - Investigating the elasticity of structures, e.g. deflection of bridges or aircraft wings
• G01M 11/08 - Testing mechanical properties
• G06T 7/32 - Determination of transform parameters for the alignment of images, i.e. image registration using correlation-based methods
• G06T 7/246 - Analysis of motion using feature-based methods, e.g. the tracking of corners or segments
• G06T 7/90 - Determination of colour characteristics
• H04N 3/36 - Scanning of motion picture films, e.g. for telecine

Abstract

The present invention relates to a device (10, 20) for absorbing kinetic energy caused by an exceptional load, characterized in that it comprises: - an outer casing (100, 200a, 200b) configured to maintain integrity after the exceptional load, - a core (105a, 105b, 205a, 205b, 205c) made of a compactable material at least partially filling the outer casing, the core material becoming compacted under an exceptional load and absorbing some of the kinetic energy caused by the load, - at least one stiffness element (115, 215, 315, 40) incorporated into the core, and - a spreading element (110, 210, 310) comprising each stiffness element. The present invention also relates to an aircraft, a vehicle, an item of equipment and an installation comprising such a device.

IPC Classes  ?

• F16F 7/12 - Vibration-dampersShock-absorbers using plastic deformation of members

Abstract

The subject matter of the invention is a multilayer sealed skin, in particular for an inflatable structure and that comprises a first polymer film (10a or 10b), a reinforcing fabric (20a or 20b) disposed on the first polymer film and a second polymer film (30a or 30b) disposed on the reinforcing fabric and adhered by means of an adhesive to the first polymer film through cavities in the reinforcing fabric. The invention can be applied to the production of an inflatable structural element such as an inflatable beam for which the skin forms an outer wall of the structural element and for which the first film (10a or 10b) of the skin forms an inner face of the outer wall of the structural element, and the second film (30a or 30b) forms an outer face of said wall.

IPC Classes  ?

• B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
• B32B 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
• B32B 27/12 - Layered products essentially comprising synthetic resin next to a fibrous or filamentary layer
• B29D 22/02 - Inflatable articles
• B64G 1/22 - Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
• B64B 1/00 - Lighter-than-air aircraft
• B64C 3/30 - Wings comprising inflatable structural components
• B64C 7/00 - Structures or fairings not otherwise provided for
• B29C 65/48 - Joining of preformed partsApparatus therefor using adhesives
• B29L 9/00 - Layered products
• B29L 22/02 - Inflatable articles
• 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

Abstract

The invention relates to a pipe for forming air flow pipelines in a structure that comprises a flexible tube (10) made from composite material, said tube having, on the length of same, sections (11) for which the wall of the tube (10) is stiffened by means of structural elements (13) made from a rigid composite material incorporated into the wall of the tube (10). Said structural elements are configured and arranged at the surface of the tube in such a way as to form a lattice framework surrounding the wall of the tube. In a particularly advantageous embodiment, the pipe further comprises electrical conductors (21, 22), disposed longitudinally on the wall of the pipe, said electrical conductors having a straight path (21) at the stiffened sections (11) of the pipe and a meandering path (22) at certain of the non-stiffened sections of the pipe (12), said meandering allowing the conductor to tolerate the possible twisting of the pipe when it is installed in the structure.

IPC Classes  ?

• F16L 9/128 - Reinforced pipes
• B64D 13/00 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
• F16L 9/22 - Pipes composed of a plurality of segments
• F16L 11/10 - Hoses, i.e. flexible pipes made of rubber or flexible plastics with reinforcements not embedded in the wall
• F16L 11/127 - Hoses, i.e. flexible pipes made of rubber or flexible plastics with arrangements for particular purposes, e.g. specially profiled, with protecting layer, heated, electrically conducting electrically conducting
• F16L 11/18 - Articulated hoses, e.g. composed of a series of rings
• F24F 13/02 - Ducting arrangements

Abstract

The subject of the invention is a conductive device (11) for forming electrical connections on the surface of a structure (15) made of composite material. The device includes a thin interface layer (13) having a face via which the device is fixed to the surface of the structure (15) made of composite material; a conductive metal element (12) placed on the face of the interface layer (13) opposite the face making contact with the surface of the structure (15), said element being configured so as to be able to undergo without damage tensile and compressive stresses; and a protective layer configured to protect the conductive element (12) from attack from the environment surrounding the structure (15). These various elements are arranged relative to one another in such a way that the length of the conductive element (12) is able to vary as a function of temperature variations independently of the amplitude of the variations undergone by the structure on which the device is mounted.

IPC Classes  ?

• B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
• B64C 1/06 - FramesStringersLongerons
• H01B 7/08 - Flat or ribbon cables
• H01B 5/12 - Braided wires or the like

Abstract

A method for drilling through an assembly forming a stack of at least two different materials uses a drill bit having at least a first cutting edge and a second cutting edge inclined in an axial plane of the drill bit so that the end of the drill bit has a projecting conical shape. The first cutting edge is configured to drill a first material. The second cutting edge is made differently from the first cutting edge, to drill a second material. A first rotational drive axis of the drill bit is laterally offset during the drilling by an offset distance D relative to the axis of the drill bit in a direction opposite the first cutting edge when the drill bit is drilling through the first material, and alternately, in a direction opposite the second cutting edge when the drill bit is drilling through the second material.

IPC Classes  ?

• B23B 1/00 - Methods for turning or working essentially requiring the use of turning-machinesUse of auxiliary equipment in connection with such methods
• B23B 41/00 - Boring or drilling machines or devices specially adapted for particular workAccessories specially adapted therefor
• B23B 35/00 - Methods for boring or drilling, or for working essentially requiring the use of boring or drilling machinesUse of auxiliary equipment in connection with such methods
• B23B 51/00 - Tools for drilling machines

Abstract

The invention relates to a device (1) for transporting a passenger (V) from door to door, characterised in that it comprises: a platform (2) equipped with means for moving along the ground; at least one private seat (3) comprising a power source and connection means, said seat being secured to the platform; and a connected virtual reality unit (4) that can construct a virtual environment for the passenger. The invention also relates to a method for transporting a passenger using the device of the invention.

IPC Classes  ?

• B64F 1/30 - Ground or aircraft-carrier-deck installations for embarking or disembarking passengers

Abstract

An electrical power supply device for electric propulsion aircraft includes first and second electric motors configured to ensure the propulsion of the aircraft. First and second high-voltage electrical circuits are connected respectively to the two electric motors. A low-voltage electrical circuit is connected to at least one control and/or command facility of the aircraft. First and second pack of batteries are connected respectively to the two high-voltage electrical circuits. First and second battery management systems are connected to the low voltage circuit. Two battery management systems are linked respectively to the two packs of batteries. An electrical converter is connected to the first high-voltage electrical circuit and to the low-voltage electrical circuit.

IPC Classes  ?

• H02P 1/00 - Arrangements for starting electric motors or dynamo-electric converters
• B64D 31/02 - Initiating means
• B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
• H02J 1/08 - Three-wire systemsSystems having more than three wires
• H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
• H02J 4/00 - Circuit arrangements for mains or distribution networks not specified as ac or dc
• H02J 1/00 - Circuit arrangements for dc mains or dc distribution networks

Abstract

The invention concerns a device (11) for improving the conduction of a thermal energy flow at the surface and inside a wall (14) made from composite material comprising heat-conductive elements (15) disposed in parallel directions at the surface of the wall (14), the device (11) being configured to be mounted on said wall (14). The device comprises a heat-conductive base at least partially conforming to the surface of the wall (14) at the area of implantation of the device on said wall, and a set of penetrating elements (13) or inserts, attached perpendicular to the heat-conductive base, intended to be inserted into the thickness of the wall (14) in such a way that, after complete insertion, the face of the conductive base (12) carrying the inserts (13) is in contact with the outer face of the wall (14). The dimensional and geometric characteristics of the conductive base (12) and the inserts (13) help constitute heat conduction paths extending into the thickness of the wall (14) from the conductive base (12).

IPC Classes  ?

• B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
• B29C 65/56 - Joining of preformed partsApparatus therefor using mechanical means
• B29C 65/00 - Joining of preformed partsApparatus therefor
• B29C 70/82 - Forcing wires, nets or the like partially or completely into the surface of an article, e.g. by cutting and pressing
• H05K 7/20 - Modifications to facilitate cooling, ventilating, or heating

Abstract

The invention concerns a multilayer thermoformable film (10) for protecting the surface of a workpiece (20), comprising an underlayer made from an adhesive material (11) capable of adhering to the surface of the workpiece by means of a first face (111), and at least one layer of polymer material (12) attached to a second face (112) of the adhesive underlayer. Said layer of polymer material (12) is resistant to erosion by solid particles and to erosion by liquid particles. It is formed from a polymer material chosen from a polyurethane, a polyetheretherketone and a polyethylene having a very high molecular weight, with a Shore D hardness of between 50 and 65 D. A method of surface protection of the workpiece (20) comprises thermoforming the film (10) in a shape adapted to match the shape of at least a portion of the workpiece (20), and applying the film thermoformed in this way onto the surface of the latter.

IPC Classes  ?

• B32B 33/00 - Layered products characterised by particular properties or particular surface features, e.g. particular surface coatingsLayered products designed for particular purposes not covered by another single class
• B29C 63/00 - Lining or sheathing, i.e. applying preformed layers or sheathings of plasticsApparatus therefor
• B29C 63/22 - Lining or sheathing, i.e. applying preformed layers or sheathings of plasticsApparatus therefor using layers or sheathings having a shape adapted to the shape of the article

Abstract

The invention relates to a part (10) made of a fiber-reinforced composite material comprising a structure (11) made from a set of fibers supported in a thermosetting resin and a peel ply (13) across all or part of the outer surface (12) of said structure. The part has a gradient of polymerization at the interface (15) between the structure and the peel ply. The invention also relates to methods for making such a part. The invention further relates to methods for bonding such parts.

IPC Classes  ?

• B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
• B29C 65/00 - Joining of preformed partsApparatus therefor
• B29C 35/02 - Heating or curing, e.g. crosslinking or vulcanising

Abstract

A structure (10) for aircrafts, includes a part (20) including a metal leading edge (30), the leading edge (30) being covered by a coating (40) having a thickness which is less than or equal to ten micrometers and having a hardness higher than six hundred in the Vickers hardness test (HV). According to a mode of embodiment, the coating (40) is a multilayer stainless steel coating consisting of a superposition of layers with a low nitrogen gradient and layers with a high nitrogen gradient, the layers having a thickness essentially equal to a micrometer. An aircraft including such a structure is also described.

IPC Classes  ?

• B64C 27/473 - Constructional features
• C23C 14/06 - Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
• C23C 14/16 - Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
• C23C 28/02 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of metallic material
• C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• B64C 3/24 - Moulded or cast structures
• B64C 3/28 - Leading or trailing edges attached to primary structures, e.g. forming fixed slots
• C23C 14/32 - Vacuum evaporation by explosionVacuum evaporation by evaporation and subsequent ionisation of the vapours
• C23C 14/34 - Sputtering
• C23C 14/35 - Sputtering by application of a magnetic field, e.g. magnetron sputtering

Abstract

A device for absorbing kinetic energy for an aircraft structural element undergoing a dynamic impact. The device includes an outer enclosure made from a braided composite material configured to preserve its integrity after an impact, a foam core, contained in the outer enclosure and to at least partially fill the outer enclosure. The foam core is configured to at least partially absorb the kinetic energy generated by the impact. Reinforcing elements are integrated at least partially into the foam core to dissipate, combined with the form core, the kinetic energy generated by the impact. The reinforcing elements includes discontinuous threads inserted into the foam core by stitching, and each discontinuous thread includes an L- or T-shaped head, folded down outside the outer enclosure.

IPC Classes  ?

• B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
• B64C 7/00 - Structures or fairings not otherwise provided for
• B64C 1/06 - FramesStringersLongerons
• B64C 3/20 - Integral or sandwich constructions
• B64C 11/26 - Fabricated blades
• F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
• B64C 11/20 - Constructional features

Abstract

A method for processing local information acquired by a virtual representation and a device having an inertial unit and an image sensor. At least one image of a real environment of the device is captured. The localization of the device in the virtual representation, corresponding to the localization of the device in the real environment, is obtained by correlating the portions of the captured image and portions of the virtual representation, The inertial unit determines the displacement of the device. The localization of the device in the virtual representation is modified as a function of the displacement so that the real position of the device corresponds, during the displacement, to the localization of the device in the virtual representation.

IPC Classes  ?

• G06T 7/00 - Image analysis
• G06T 19/00 - Manipulating 3D models or images for computer graphics
• G06F 3/00 - Input arrangements for transferring data to be processed into a form capable of being handled by the computerOutput arrangements for transferring data from processing unit to output unit, e.g. interface arrangements
• H04N 5/232 - Devices for controlling television cameras, e.g. remote control
• G06T 7/80 - Analysis of captured images to determine intrinsic or extrinsic camera parameters, i.e. camera calibration
• G06T 7/70 - Determining position or orientation of objects or cameras
• G06T 7/246 - Analysis of motion using feature-based methods, e.g. the tracking of corners or segments

Abstract

The invention relates to a process and installation for producing a composite material part in which plies (12) of continuous and electrically conductive fibres are deposited to form a stack of plies (12) on a substrate (11). According to the invention, at least the face of said substrate (11) bearing said stack is electrically insulating and the following steps are carried out: a) an electrical terminal (13, 18) is inserted between the ends of at least two plies (12) placed directly one on top of the other in said stack, and on at least two opposite sides of these plies (12); b) when said fibres are dry, introducing a resin in order to impregnate said fibres; and c) making a current flow between said electrical terminals (13, 18) through said plies (12) in order to set said resin by resistive heating.

IPC Classes  ?

• B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
• B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
• B29C 70/40 - Shaping or impregnating by compression
• B29C 35/02 - Heating or curing, e.g. crosslinking or vulcanising
• B29C 33/02 - Moulds or coresDetails thereof or accessories therefor with incorporated heating or cooling means

Abstract

An ultrasonic probe for contact measurement of an object and its manufacturing process. The ultrasonic probe has ultrasonic sensors securely fastened to a first face of a substrate. The opposite face of the substrate defines a measurement surface having a shape that is the imprint of the surface of the object to be measured to closely follow the latter when the surface of the object is brought into contact with the measurement surface.

IPC Classes  ?

• C23C 14/34 - Sputtering
• G01H 11/08 - Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by detecting changes in electric or magnetic properties by electric means using piezoelectric devices
• G01N 29/28 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic wavesVisualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object Details providing acoustic coupling

Abstract

The device (100) for welding thermoplastic parts comprises: a matrix (10) for positioning the parts to be assembled, the matrix (10) including an amagnetic insulating insert (12) that defines joining zones (25) in which the welds must be produced; a bladder (11) defining a sealed volume and means for producing a partial vacuum in the sealed volume; and means for moving a magnetic induction head (30) to near the joining zones (25) and without making contact with the bladder (11). The welding process comprises the successive steps of positioning at least one first part (21), then of placing metal inserts (23) on those areas of the first part (21) corresponding to the joining zones (25) that must be welded, and then positioning at least one second part (22). Next, a bladder (11) is put in place covering the parts and a partial vacuum is created in the volume defined by the bladder. The magnetic induction head (30) is moved to produce the weld bead without contact while the partial vacuum is maintained.

IPC Classes  ?

• B29C 65/36 - Joining of preformed partsApparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction

Abstract

A tank for storing liquid configured to withstand overpressures caused by a projectile impact and positioned in a structure. The tank includes an overpressure management device having a layer of polyethylene-based hyperelastic foam. An expansion in a simple, durable and passive manner is sought both for existing tanks and for new tanks.

IPC Classes  ?

• F17C 1/16 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge constructed of plastics materials
• B64D 37/32 - Safety measures not otherwise provided for, e.g. preventing explosive conditions
• F17C 13/02 - Special adaptations of indicating, measuring, or monitoring equipment
• B60K 15/03 - Fuel tanks

Abstract

A method of manufacturing a stiffened panel having a skin and at least one substantially elongate stiffener having a longitudinal groove forming a cavity. At least one storage device for storing and releasing electrical energy. The longitudinal groove is filled with at least one storage device for storing and releasing electrical energy. The storage device is covered with a skin which forms the cavity together with the longitudinal groove of the stiffener. A stiffened ring can be derived from the method.

IPC Classes  ?

• H01G 9/155 - Double-layer capacitors
• B64C 7/00 - Structures or fairings not otherwise provided for
• B64D 41/00 - Power installations for auxiliary purposes
• B64C 1/12 - Construction or attachment of skin panels
• B64C 1/40 - Sound or heat insulation
• H01G 11/58 - Liquid electrolytes
• H01G 11/78 - CasesHousingsEncapsulationsMountings
• B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like

Abstract

A high-impedance passive device to radio-electrically decouple two antennas operating at least partially within a common frequency band and arranged on a surface of the carrier structure. A substrate of the device has a flexible dielectric material layer having a predetermined thickness with patches of conductive material arranged on its surface and a layer to attach the device onto the surface of the carrier structure. The patches having predetermined shape and arrangement. The body of the substrate separates the dielectric layer from the surface of the carrier structure. The substrate thickness is determined based on the size, number, and arrangement of the patches, and further it is based on the aerodynamic constraints imposed on the device. The device having an impedance to cause the desired decoupling in the common frequency band.

IPC Classes  ?

• H01Q 1/52 - Means for reducing coupling between antennas Means for reducing coupling between an antenna and another structure
• H01Q 1/28 - Adaptation for use in or on aircraft, missiles, satellites, or balloons
• H01Q 15/00 - Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices

Abstract

The present invention relates to a mobile device (10) capable of storing digital data, including a storage space (11), characterised by including means for: providing a partial view of said storage space (11) when the content of said storage space is viewed during the connection of said device (10) to a second device (20); and providing an overall view of said storage space (11) when the content of said storage space (11) is viewed during the connection of said device (10) to a second device (20), and when an authorised user of said device (10) performs an authentication with said device (10).

IPC Classes  ?

• G06F 21/62 - Protecting access to data via a platform, e.g. using keys or access control rules

Abstract

The invention relates to an impact detection system for a robotic device. According to the invention, said system comprises: a flexible covering element (10) for enveloping part of said robotic device, said covering element (10) defining an inner air volume; at least one sensor (12) for measuring the differential pressure between the pressure in said inner air volume and the pressure outside said covering element (10); and a detection unit (13) designed to receive the measuring signal of said at least one sensor (12), to carry out an analysis, on the basis of said measuring signal, in order to detect a sudden variation in said pressure, and to emit a stop signal to said robotic device when such a variation is detected.

IPC Classes  ?

• B25J 13/08 - Controls for manipulators by means of sensing devices, e.g. viewing or touching devices
• B25J 19/00 - Accessories fitted to manipulators, e.g. for monitoring, for viewingSafety devices combined with or specially adapted for use in connection with manipulators
• B25J 19/06 - Safety devices

Abstract

The invention relates to a test and simulation system comprising a first level comprising a communication layer in the form of a ring computer network provided with communication nodes consisting of interconnected routing means, a second level around the first level, said second level comprising computational nodes which group together heterogeneous computational means, the computational nodes being associated with communication nodes of the communication layer, and a third level consisting of the real systems being tested.

IPC Classes  ?

• G01R 31/00 - Arrangements for testing electric propertiesArrangements for locating electric faultsArrangements for electrical testing characterised by what is being tested not provided for elsewhere
• G06F 11/36 - Prevention of errors by analysis, debugging or testing of software
• 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

Abstract

The invention consists of a process for marking the real position and real orientation of a tool in relation to the manipulator arm of a robot on which it is mounted, this tool incorporating an acoustic probe (11). The process consists, with the aid of measurements of amplitude of acoustic signals emitted by the acoustic probe (11) and reflected by fixed reference elements (22, 23) and of measurement of flight time of the acoustic waves emitted by the probe (11) and reflected by said fixed reference elements, in determining the position of the centre of reference of the acoustic probe (11) relative to the end of the manipulator arm of the robot and in orienting the axes X and Y defining the plane of the acoustic probe (11) along reference axes X' and Y' of known orientations so that the modification of the position and of the orientation of the acoustic probe in the reference frame can be defined with precision, by the automaton which manages the displacements of the manipulator arm, on the basis of the position of the probe in relation to the manipulator arm and of the reference orientation of the probe which are thus determined.

IPC Classes  ?

• B25J 9/16 - Programme controls
• G01N 29/30 - Arrangements for calibrating or comparing, e.g. with standard objects

Abstract

The present invention relates to a method for determining the thickness of dry textile preforms, characterized in that it comprises a step of generating eddy currents within a dry textile preform (10), a step of calibrating a device (20) able to carry out measurements, a step of acquiring said eddy currents by means of sensors (30, 31), and a step of determining the thickness of said textile preform (10).

IPC Classes  ?

• G01B 7/06 - Measuring arrangements characterised by the use of electric or magnetic techniques for measuring length, width, or thickness for measuring thickness
• G01N 27/02 - Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating impedance

Abstract

The present invention relates to a device (10) for controlling the drilling or countersinking of a workpiece (11) on which the tolerance is less than 50 µm, said device (10) comprising: - a bed (12) for holding said workpiece (11) and - a numerically controlled tool (15) able to perform a machining operation of the boring or countersinking type, - at least one measurement means (25) for the real-time measurement of the strain experienced by said workpiece (11) during machining by the tool (15), and - an analysis means able to calculate the boring or countersinking tolerances using measurements of the strain experienced by said workpiece (11) during the machining, said analysis means being able to perform quality control on the machining of said workpiece (11).

IPC Classes  ?

• G05B 19/4063 - Monitoring general control system

Abstract

A method (100) for production of a part from thermoplastic composite material by deposition (130) of at least one layer (13) of a thermoplastic composite material on a tool (30), comprising a step of depositing (120) a first fold (10) onto the tool. The first hardened fold is deposited on the tool (30) before deposition of the layer of thermoplastic composite material. The first fold is produced beforehand in the shape of the tool (30). It comprises a first material (11) capable of withstanding an attractive force when it is subjected to a magnetic field and/or to an electrical potential difference, and comprising a second material (12) of a thermoplastic resin, chemically compatible with the resin of the thermoplastic composite material layer. The first fold is held on the tool (30) during the step of deposition (120) on the tool by the effect of a magnetic field and/or of an electrical potential difference, created at the tool. In one form of implementation, the first fold (10) is produced on a first-fold mould that is preferably convex in shape.

IPC Classes  ?

• B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
• B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
• B29C 33/16 - Moulds or coresDetails thereof or accessories therefor with incorporated means for positioning inserts, e.g. labels against the mould wall using magnetic means
• B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
• B29K 101/12 - Thermoplastic materials
• B29K 705/00 - Use of metals, their alloys or their compounds, for preformed parts, e.g. for inserts

Abstract

The invention relates to a spacecraft (10) comprising: • a body (20), • a surface of revolution (40), rigidly connected to said body, the spacecraft comprising a heat engine positioned at the centre of the surface of revolution (40), and said surface of revolution comprises a first portion (411) forming a solar concentrator for concentrating solar radiation in the direction of said heat engine and a second portion (412), coaxial with the first portion (411), and such that the first portion (411) and the second portion (412) form, relative to each other, a Cassegrain solar concentrator, of which a focal point is located at the heat engine.

IPC Classes  ?

• B64G 1/22 - Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
• B64G 1/44 - Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
• F24J 2/52 - Arrangement of mountings or supports
• F24J 2/54 - specially adapted for rotary movement
• H01L 31/052 - Cooling means directly associated or integrated with the PV cell, e.g. integrated Peltier elements for active cooling or heat sinks directly associated with the PV cells
• H01L 31/054 - Optical elements directly associated or integrated with the PV cell, e.g. light-reflecting means or light-concentrating means
• H01Q 1/28 - Adaptation for use in or on aircraft, missiles, satellites, or balloons
• H01Q 15/16 - Reflecting surfacesEquivalent structures curved in two dimensions, e.g. paraboloidal

Abstract

The invention is an iterative process for performing iteratively the phase retrieval of an adaptive signal x(t) matching two sets of constraint both concerning the time envelope ue(t) of signal x(t) and magnitude distribution Um(f) of its spectral representation. At each iteration k the process computes an estimate xk(t) of signal x(t) which is obtained from a first projection PA on a first set of constraint in time domain of a computed value Xk(t) of x(t), Xk(t) deriving from an estimate Xk-1(f) of the spectrum of signal x(t), said estimate Xk-1(/) being itself obtained from a second projection PB on a second set of constraints in spectral domain of the Fourier transform Xk(f) of the estimate xk-1(t) of x(t) computed at iteration k-1. Iterative computation of estimate xk(t) is repeated until xk(t) meets a predefined criterion which indicates that estimate xk(t) is close enough to expected signal x(t). The first used spectral estimate X0(f) (first iteration) is computed from an initialization value θo(f) of the phase component of the spectral estimate Xk{f), θo(f) being defined taking into account that the spectral representation of the desired signal has a stationary phase.

IPC Classes  ?

• G01S 7/282 - Transmitters
• G01S 7/35 - Details of non-pulse systems
• G06F 7/544 - Methods or arrangements for performing computations using exclusively denominational number representation, e.g. using binary, ternary, decimal representation using non-contact-making devices, e.g. tube, solid state deviceMethods or arrangements for performing computations using exclusively denominational number representation, e.g. using binary, ternary, decimal representation using unspecified devices for evaluating functions by calculation
• G01S 13/28 - Systems for measuring distance only using transmission of interrupted, pulse modulated waves wherein the transmitted pulses use a frequency- or phase-modulated carrier wave with time compression of received pulses

Abstract

The invention relates to an input/output device (22) for an electric or electronic cabinet grouping together a plurality of devices such as computers (10a,..., 10f), characterised in that it comprises: a plurality of input/output channels (23a, 23b, 23c, 23d), conversion units (25, 26, 28, 29) and at least one computing unit (27), said conversion units being connected to the input/output channels and to the computing unit; a digital network link protocol management unit (27a) connected to the computing unit and to at least one transceiver module (24); and software suitable for the digital transmission of data representative of input/output values from/to network computers (10a,..., 10f) via said at least one transceiver module (24). The invention also relates to an electric cabinet grouping together a plurality of computers, each provided with a transceiver module and comprising an input/output device according to the invention.

IPC Classes  ?

• G06F 13/40 - Bus structure

Abstract

The invention relates to an electric cabinet (2) provided with an interconnection system for devices (10) such as computers received in the cabinet, characterised in that the interconnection system comprises at least one waveguide (4) forming part of the frame of the cabinet. The waveguide is provided with openings (6) disposed facing housings for receiving the aforementioned devices, said openings being dimensioned to form a barrier to the passage of radio-frequency wireless communication waves to be transmitted through the waveguide and to form a barrier to external waves.

IPC Classes  ?

• G06F 1/18 - Packaging or power distribution
• G06F 1/20 - Cooling means
• H05K 7/14 - Mounting supporting structure in casing or on frame or rack
• H05K 7/20 - Modifications to facilitate cooling, ventilating, or heating

Abstract

The subject of the invention is a device (2) for holding a part for an item of ultrasonic measuring equipment (15). This device (2) comprises a hollow, substantially tubular, body (3), a first end (4) of which is able to be pressed against a surface of the part (1), and a second, opposite end (5) of which is able to be connected to a suction means. The hollow body (3) is made of rigid material and the device (2) comprises a peripheral seal (7) joined to the first end (4).

IPC Classes  ?

• G01N 29/22 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic wavesVisualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object Details
• G01N 29/24 - Probes
• G01N 29/28 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic wavesVisualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object Details providing acoustic coupling

Abstract

The invention consists of a system allowing remote wireless transfer of energy from a base station (11) to a moving object (12), in particular a drone, moving in a given zone around the base station. The system comprises means (16) for tracking (13) the moving object (12) so as to determine the position of the moving object (12) relative to the base station (11) at any time, means (13) for transmitting a synthetic acoustic wave (14) focused in the direction of the moving object (12), these two means being located at the base station (11) and powered by said base station, and acoustic reception means (15), located on the moving object (12), for receiving the acoustic wave (14) transmitted by the base station (11) and converting the received acoustic wave into an electrical signal and then into a power supply voltage for a battery.

IPC Classes  ?

• H02J 17/00 - Systems for supplying or distributing electric power by electromagnetic waves
• B64C 39/02 - Aircraft not otherwise provided for characterised by special use

Abstract

The invention relates to a device (100) for visually inspecting the external surfaces (90) of an aircraft, which comprises an inspection area for receiving an aircraft, at least one visual inspection robot (10), and a control center (50). A movable platform (11) of the robot supports a turret (12) having observing means (13). The robot comprises processing means (20) which guide the movable platform (11) and process the data received from the observing means (13). The processing means (22) of the robot are suitable: for autonomously controlling the robot (10) during the visual inspection of the external surfaces of an aircraft (9) parked in the inspection area; for interrupting a visual inspection in the event of a detection of an anomaly on the external surface of the aircraft; for transmitting visual inspection data to the control center; and for receiving instructions from the control center.

IPC Classes  ?

• 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

Abstract

The invention relates to a device (10) for the electric power supply of a load (11), comprising at least two energy storage elements (13, 14), means for determining the power needs of said load (11), means (16, 17) for monitoring each energy storage element (13, 14), which are able to provide information about a maximum instantaneous power of each energy storage element (13, 14), a calculation body (19) for determining a maximum secured power according to the electromotive force (Ebat(t)) and the resistance (Rbat(t)) of the Thévenin model, a maximum specified current and a maximum specified voltage, and means (Cbat(t), Csc(t)) for controlling each energy storage element (13, 14), said means being adjusted over time according to the power needs of said load (11) and the maximum secured power of each energy storage element (13, 14).

IPC Classes  ?

• H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
• H02J 15/00 - Systems for storing electric energy
• H02J 7/34 - Parallel operation in networks using both storage and other DC sources, e.g. providing buffering

Abstract

The invention relates to a method for optimising the architecture of the power supply of a load, comprising the following steps: determination of a mission profile (16) sizing according to the power required by the load over time; definition of the sources of energy storage for hybridisation; association of a characteristic behaviour model with each source of energy storage; determination of the couples of sources of energy storage that can generate the mission profile with a minimum mass; and determination, from the potential couples of sources of energy storage, of the couple with the weakest mass.

IPC Classes  ?

• H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
• H02J 3/00 - Circuit arrangements for ac mains or ac distribution networks
• H01M 10/00 - Secondary cellsManufacture thereof
• H02M 3/00 - Conversion of DC power input into DC power output

Abstract

The invention relates to a method for the non-destructive ultrasonic testing of a part by the analysis of echoes returned by the part in response to the emission of an ultrasonic wave by means of an ultrasonic transducer. The method comprises a step of determining a variable gain curve and a step of correcting the amplitude of the echoes returned by the part according to the variable gain curve and the moments of reception of said echoes. The method comprises steps of: producing a wave function representative of an ultrasonic transducer; producing transfer functions Fm representative of the frequency responses of reference samples Rm of the material forming said part; and calculating reference attenuation values between the wave function and the results of calculations of filtering of said wave function by the respective transfer functions Fm of the reference samples Rm.

IPC Classes  ?

• G01N 29/11 - Analysing solids by measuring attenuation of acoustic waves
• G01N 29/30 - Arrangements for calibrating or comparing, e.g. with standard objects
• G01N 29/44 - Processing the detected response signal
• G01N 29/46 - Processing the detected response signal by spectral analysis, e.g. Fourier analysis

Abstract

The invention relates to a computer-assisted design method for a second three-dimensional object, from a first three-dimensional object known only by its boundary surfaces (through a surface model of the B-Rep type) of the planar, cylindrical, cone, sphere, or toroid type, excluding free forms in defining the boundary of the object, the method comprising the following steps: - breaking the first object down into a set of simple volume primitives, - associating that first object with a construction graph defined from those volume primitives and a set of geometric parameters for using those volume primitives in the specific case of that first object, said construction graph enabling a compact description of all of the construction alternatives of the object through Boolean combinations of those primitives, - creating the second object as an alternative of the first object according to that construction graph, by modifying some of those parameters.

IPC Classes  ?

• G06F 17/50 - Computer-aided design

Abstract

The invention essentially relates to a method for measuring the movement and/or deformation of a study part subjected to an outside stress, said method implementing a device for acquiring colour digital images and image correlating means, characterised in that it comprises the following steps: · acquiring (250) a plurality of colour digital images of the surface of the study part using the colour digital image acquisition device while an outside stress is applied to said study part, · processing (260) the colour digital images acquired during the step for acquiring a plurality of colour digital images so as to show contrasting details on variable scales.

IPC Classes  ?

• G06T 7/20 - Analysis of motion
• G01B 11/16 - Measuring arrangements characterised by the use of optical techniques for measuring the deformation in a solid, e.g. optical strain gauge

Abstract

The invention relates to an aircraft structure (10), in particular the fuselage, nacelles or wings, comprising, over all or part of an outer surface (21) that may undergo lightning impacts, a layer of flexible polymer (30), a photovoltaic film (40) and a protective layer (50) protecting said photovoltaic film. This aircraft structure primarily has a solar energy capture capacity making it possible to meet the needs of an aircraft as well as an ability to protect against the effects of lightning.

IPC Classes  ?

• B64D 33/00 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
• B64D 41/00 - Power installations for auxiliary purposes
• H01L 31/048 - Encapsulation of modules

Abstract

The invention relates to a variable lift device, in particular an airship (10) with a longitudinal axis X, a transverse axis Y and a vertical axis Z. The airship (10) comprises two substantially parallel balloons (20), containing a carrier gas lighter than air, each steered along an axis parallel to the longitudinal axis X, and connected to each other by a beam (30a, 30b) oriented along an axis parallel to the transverse axis Y. The beam (30a, 30b) can be oriented in rotation around said axis in order to define predetermined angular positions to create zero, positive or negative attack angles. The invention also relates to a method for steering such a variable lift device.

IPC Classes  ?

• B64B 1/08 - Framework construction
• B64B 1/12 - Movable control surfaces
• B64B 1/20 - Rigid airshipsSemi-rigid airships provided with wings or stabilising surfaces
• B64B 1/58 - Arrangements or construction of gas-bagsFilling arrangements
• B64C 37/02 - Flying units formed by separate aircraft

Abstract

The device according to the invention consists of associating a laser inspection head (12) comprising a source emitting a laser beam (15) swept along a defined axis (16, 17) and a handling robot (13) seeing to the movement and spatial orientation of parts (14) whose structure requires inspection. The inspection head (12) and the handling robot (13) are configured and arranged across from one another such that, the inspection head (12) occupying a stationary position, the handling robot (13) can move the part to be inspected (14) across from the inspection head (12), such that the sweep of the laser beam (15) combined with the movement of the part in a direction perpendicular to the sweeping direction makes it possible to inspect the entire surface of the part (14). In one particular configuration, the handling robot makes it possible to vary the orientation of the part (14) relative to the direction of the laser beam (15) so as to have optimal lighting of the part.

IPC Classes  ?

• G01B 17/06 - Measuring arrangements characterised by the use of infrasonic, sonic, or ultrasonic vibrations for measuring contours or curvatures
• G01N 29/24 - Probes
• G01N 29/04 - Analysing solids
• G01N 29/275 - Arrangements for orientation or scanning by moving both the sensor and the material

Abstract

A device (100) for moving aircraft along the ground comprises at least one runway (10, 18a, 18b, 18c) and at least one aircraft. The aircraft is secured to a tractor element (30) comprising a magnetic mass (31) formed mainly of type II superconductor material and the runway (10, 18a, 18b, 18c) comprises stator coils (12) arranged in the runway in at least one line of coils which is parallel to an axis (11) of the runway. A command/control system (13) supplies power to the stator coils in such a way as to create a magnetic field that levitates the tractor element (30), magnetized beforehand into a phase II superconducting state, above the runway.

IPC Classes  ?

• B64F 1/04 - Ground or aircraft-carrier-deck installations for launching aircraft

Abstract

The invention relates to an airplane (100) having a device for providing assistance at takeoff (20), which comprises at least one propulsion engine (11) and at least one wheel motor (12) arranged to rotate at least one wheel (13) of a landing gear (10a, 10b) of a landing gear of the airplane. The device for providing assistance at takeoff (20) comprises at least one main command and control computer (22) which monitors the operation of the propulsion engine(s) (10) and of the wheel motor(s) (12) when the airplane is rolling during a takeoff phase, said at least one wheel motor being an electric motor. In a first step E, the airplane is accelerated primarily by the wheel motor(s) (12). In a second step H, the airplane is accelerated by the wheel motor(s) (12) and the propulsion engine(s) (11) jointly. In a third step P, the airplane is accelerated mainly by the propulsion engine(s) (11).

IPC Classes  ?

• B64C 25/40 - Alighting gear characterised by elements which contact the ground or similar surface the elements being rotated before touch-down

Abstract

The invention relates to an electric propulsion assembly for an aircraft, including a nacelle (10) comprising a nacelle cover (10) which defines an inner space in which an electric propulsion unit, which includes a blower (13), of the aircraft is arranged, an electric motor assembly (12) placed after said propulsion unit and connected to the latter in order to supply power to said propulsion unit during the operation thereof and a control system comprising a power electronics system, the space defined between said motor assembly and said nacelle cover (10) defining a pipe in which an air flow generated by said blower (13) during the operation thereof is to flow, in order to supply thrust to said aircraft. According to the invention, said power electronics system comprises at least one heat exchanger making it possible to transfer thermal energy from said system to a work fluid in order to cool said system, and said at least one exchanger is placed such as to project at least partially into said pipe, so that the work fluid consists of said air flow generated by said blower (13) during the operation thereof.

IPC Classes  ?

• B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
• B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
• B64D 33/10 - Radiator arrangement
• B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes

Abstract

The present invention relates to an electrical power supply device (25) for electric propulsion aircraft comprising a first and a second electric motor (20, 21) which are able to ensure the propulsion of the aircraft, a first and a second high-voltage electrical circuit (26, 27) connected respectively to the two electric motors (20, 21), a low-voltage electrical circuit (28) connected to at least one control and/or command facility (49) of the aircraft, a first and a second pack of batteries (31, 32) connected respectively to the two high-voltage electrical circuits (26, 27), a first and a second batteries management system (34, 35) connected to the low-voltage circuit (28), the batteries management systems being linked respectively to the two packs of batteries (31, 32), an electrical converter (37) connected on the one hand to the first high-voltage electrical circuit (26) and on the other hand to the low-voltage electrical circuit (28).

IPC Classes  ?

• B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force

Abstract

The invention relates to an aircraft (10) in which at least a portion of the outer surface (12) of the aircraft body (11), in particular the outer surface of the lower area of the fuselage thereof, is coated with a multilayer paint system (20) comprising at least one layer of a corrosion-inhibiting primer (22) and decorative layers (23), as well as a layer (27) of a material having intumescent properties. Said aircraft (10) has high resistance to the penetration of an external fire into the aircraft body.

IPC Classes  ?

• B64C 1/38 - Constructions adapted to reduce effects of aerodynamic or other external heating
• C09D 5/18 - Fireproof paints

Abstract

The invention relates to a method for analysing the temperature reliability of an electronic component (10) comprising an electronic chip (12) mounted in a housing (11), said electronic chip (12) consisting of a plurality of layers (13-15) of materials. The invention is characterised in that the method comprises the following steps: thermally coupling a thermally conductive coupling body (25) to the electronic chip (12); determining a wavelength according to the layers (13-15) of material to be crossed and the absorption rate of a layer of material to be used; and thermally stressing an area of interest (20) by means of a laser source (32) emitting the pre-determined wavelength.

IPC Classes  ?

• G01R 31/28 - Testing of electronic circuits, e.g. by signal tracer
• G01R 31/311 - Contactless testing using non-ionising electromagnetic radiation, e.g. optical radiation of integrated circuits

Abstract

The invention relates to a structure (10) for aircrafts, characterised in that it comprises a part (20) comprising a metal leading edge (30), said leading edge (30) being covered by a coating (40) having a thickness which is less than or equal to ten micrometres and having a hardness higher than six hundred in the Vickers hardness test (HV). According to a mode of embodiment, said coating (40) is a multilayer stainless steel coating consisting of a superposition of layers with a low nitrogen gradient and layers with a high nitrogen gradient, said layers having a thickness essentially equal to a micrometre. The invention also relates to an aircraft comprising such a structure.

IPC Classes  ?

• C23C 14/06 - Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
• C23C 14/16 - Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
• B64C 11/20 - Constructional features
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
• C23C 28/02 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of metallic material

Abstract

A combined rescue beacon and flight recorder device for an airplane is ejectable, buoyant and/or provided with flotation devices. The combined rescue beacon and flight recorder device comprises a frame provided with at least one outer side surface having a solar panel. The combined rescue beacon and flight recorder device is configured to be placed in a housing created in an airfoil element of the aircraft.

IPC Classes  ?

• G01M 17/00 - Testing of vehicles
• B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
• G01S 5/02 - Position-fixing by co-ordinating two or more direction or position-line determinationsPosition-fixing by co-ordinating two or more distance determinations using radio waves

Abstract

The present invention relates to a method for manufacturing a partially polymerized, preimpregnated material, said method comprising: - a step of impregnation of fibres with thermosetting resin, and - a step of partial polymerization of the resin to a degree of between 10% and 60%. The invention also relates to the production of thermosetting composite parts by drape-forming of the preimpregnated material according to the following steps: - depositing the material in the form of strips, - heating the deposited material, to a temperature above the glass transition temperature of the preimpregnated state, - pressing the deposited material, and - cooling the deposited material, making it possible to return to a temperature below the glass transition temperature of the preimpregnated state under consideration.

IPC Classes  ?

• B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
• B29C 35/02 - Heating or curing, e.g. crosslinking or vulcanising
• B29C 35/16 - Cooling
• B29B 15/10 - Coating or impregnating
• C08J 5/24 - Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
• B23K 101/10 - Pipe-lines
• 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

Abstract

The present invention relates to a method for manufacturing a partially polymerized, preimpregnated material, said method comprising: a step of impregnation of fibres with thermosetting resin, and a step of partial polymerization of the resin to a degree of between 10% and 60%. The invention also relates to the production of thermosetting composite parts by laying of fibres of the preimpregnated material according to the following steps: depositing the material in the form of roves, heating the deposited material to a temperature above the glass transition temperature of the preimpregnated state under consideration, pressing the deposited material, and cooling the deposited material, making it possible to return to a temperature below the glass transition temperature of the preimpregnated state under consideration.

IPC Classes  ?

• B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
• B29C 35/02 - Heating or curing, e.g. crosslinking or vulcanising
• B29C 35/16 - Cooling
• B29B 15/10 - Coating or impregnating
• C08J 5/24 - Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
• B29K 101/10 - Thermosetting resins
• 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

Abstract

The present invention relates to a tank (100, 12, 11) of liquid (2) designed to withstand the overpressures caused by projectile impact and placed within a structure (4), said tank comprising an overpressure management device, said device comprising a layer (3) of polyethylene-based hyperelastic foam. The object of the invention is to obtain simple, durable and passive expansion both on existing tanks and on new tanks.

IPC Classes  ?

• B60K 15/03 - Fuel tanks
• B64D 37/32 - Safety measures not otherwise provided for, e.g. preventing explosive conditions

Abstract

The invention relates to a method of manufacturing a stiffened panel (10) comprising a skin (11) and at least one substantially elongate stiffener (12) said stiffener comprising a longitudinal groove (13) forming a cavity (15), said panel comprising at least one means (19) for storing and releasing electrical energy which means is placed inside the cavity, said method involving a step of filling the groove (13) with at least one means (19) of storing and releasing electrical energy; and a step of covering said means with the skin (11) so that the groove of the stiffener and the skin together form the cavity (15). The invention also relates to a stiffened ring (10) derived from such a method.

IPC Classes  ?

• B64D 41/00 - Power installations for auxiliary purposes

Abstract

The invention relates to a three-dimensional structural framework (10) comprising a plurality of inflatable rings (100), having a T-shaped cross-section along a plane passing through an axis of revolution of the inflatable ring in an inflated state, and a plurality of means (150) for stabilizing the shape of the structural framework in space, two inflatable rings (100) being connected by at least one shape-stabilizing means (150). The structural framework is advantageously intended for producing stratospheric balloons.

IPC Classes  ?

• B64B 1/58 - Arrangements or construction of gas-bagsFilling arrangements
• B64B 1/60 - Gas-bags surrounded by separate containers of inert gas
• B64B 1/62 - Controlling gas pressure, heating, cooling, or discharging gas

Abstract

The invention relates to a device for monitoring the integrity and soundness of a mechanical structure, such as an aircraft. The device comprises a control unit, a radio frequency transmission means, and an electric battery. The control unit recovers data from a set of digital and/or analog sensors. The radio frequency transmission means enables the control unit to transmit the data received from the sensors to a man/machine interface. The electric battery powers the device and is rechargeable. The device further comprises a module for recovering electromagnetic energy capable of converting the recovered electromagnetic energy into electric power so as to recharge the battery and/or directly power the device.

IPC Classes  ?

• G08B 21/00 - Alarms responsive to a single specified undesired or abnormal condition and not otherwise provided for
• G08G 1/123 - Traffic control systems for road vehicles indicating the position of vehicles, e.g. scheduled vehicles
• G08C 19/38 - Electric signal transmission systems using dynamo-electric devices
• G08C 19/12 - Electric signal transmission systems in which the signal transmitted is frequency or phase of AC
• G01N 19/10 - Measuring moisture content, e.g. by measuring change in length of hygroscopic filamentHygrometers
• G01P 15/00 - Measuring accelerationMeasuring decelerationMeasuring shock, i.e. sudden change of acceleration
• G01N 29/00 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic wavesVisualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
• G01L 7/00 - Measuring the steady or quasi-steady pressure of a fluid or a fluent solid material by mechanical or fluid pressure-sensitive elements
• G06F 15/02 - Digital computers in generalData processing equipment in general manually operated with input through keyboard and computation using a built-in program, e.g. pocket calculators
• G01M 5/00 - Investigating the elasticity of structures, e.g. deflection of bridges or aircraft wings
• 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
• G01N 37/00 - Details not covered by any other group of this subclass

Abstract

The invention relates to a process for manufacturing a part (111) made of a composite material, said process comprising the following steps: a step of depositing one or more structural plies (12, 13) impregnated with a thermosetting resin (15) in order to form a structural layer, a step of depositing a surface layer as a stack with the structural plies, said surface layer being formed from an assembly (117) of one or more fibres (118) of thermoplastic resin, said assembly being deformable in at least two directions, said thermoplastic resin having a melting temperature close to a polymerization temperature of said thermosetting resin, then, a step of polymerization of the structural layer at the polymerization temperature, the surface layer then taking the shape of a continuous film that coats the structural layer. Said surface layer may ensure the drainage of air during the polymerization step.

IPC Classes  ?

• B29C 63/02 - Lining or sheathing, i.e. applying preformed layers or sheathings of plasticsApparatus therefor using sheet or web-like material
• B29C 65/02 - Joining of preformed partsApparatus therefor by heating, with or without pressure
• B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
• B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
• B32B 27/04 - Layered products essentially comprising synthetic resin as impregnant, bonding, or embedding substance
• B32B 27/12 - Layered products essentially comprising synthetic resin next to a fibrous or filamentary layer
• B32B 27/38 - Layered products essentially comprising synthetic resin comprising epoxy resins
• B32B 27/42 - Layered products essentially comprising synthetic resin comprising condensation resins of aldehydes, e.g. with phenols, ureas or melamines
• C09D 7/12 - Other additives

Abstract

In order to produce a part (16) from a composite material, which is conductive at least on one of the surfaces thereof, the method consists of: the conductive overstitching (30) of a preform (20) of the part using electrically or thermally conductive threads (31, 32) with substantially parallel stitch lines (34) oriented in at least two intersecting directions. The parts obtained are adapted for the production of aircraft structures that may be subjected to lightning strikes and allow return currents from the electrical or electronic aircraft equipment and/or the discharge of heat by conduction.

IPC Classes  ?

• B29C 45/02 - Transfer moulding, i.e. transferring the required volume of moulding material by a plunger from a "shot" cavity into a mould cavity
• B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
• B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
• B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
• B64C 1/12 - Construction or attachment of skin panels
• B64D 45/02 - Lightning protectorsStatic dischargers
• B64G 1/50 - Arrangements or adaptations of devices for control of environment or living conditions for temperature control
• B32B 5/06 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by a fibrous layer needled to another layer, e.g. of fibres, of paper
• B29K 707/04 - Carbon

Goods & Services

Ultrasonic diagnostic equipment for testing aircraft components; [ blank magnetic data carriers; blank recording disks for use with ultrasonic diagnostic equipment for testing aircraft components; ] data processors for use with ultrasonic diagnostic equipment for testing aircraft components; software for use with ultrasonic diagnostic equipment for testing aircraft components; computer programs for ultrasound cartography [ ; automatic vending machines; cash registers; calculating machines; fire extinguishers ] [ Printed matter, namely, books and pamphlets relating to ultrasonic testing of aircraft components; photographs; stationery; adhesives for stationery and household purposes; paint brushes, typewriters, printed instructional or teaching materials relating to ultrasonic testing of aircraft components, plastic materials for packaging, namely, plastic bags, printer's type, printing blocks ] [ Computer assisted transmission of messages and images; communications via computer terminals; telecommunications, namely, long distance telephone services; and providing multiple user access to a global computer information network ] [ Legal services, scientific and industrial research; computer programming for others; engineering services in the field of ultrasonic testing; professional consulting, namely, technical consulting in the field of ultrasonic testing; consulting services concerning software in the field of ultrasonic testing; materials testing; design of databases; technical and scientific research concerning robotization; technical research and consultation regarding computers and automated technology in an effort to improve productivity in the manufacturing process ]

Abstract

The invention relates to a structure (10) comprising at least one electrical line (20) on one surface (11) of the structure, one electrically conductive layer (23) of the line resulting from deposition of an electrically conductive material via a cold spraying method, and the line comprises a protective bonding layer (22) on which the electrically conductive material is deposited via the cold spraying method, the protective bonding layer forming a continuous protective shield between the structure (10) and the cold-sprayed material. An insulating layer (21) is advantageously located between the structure and the protective bonding layer. Achieving an electrical line (20) on a surface (11) of the structure (10) involves implementing a step of oxy-fuel flame spraying of a protective material to form a protective bonding layer (22), followed by a step of cold spraying of the electrically conductive material of the electrically conductive layer (23) onto the protective bonding layer (22).

IPC Classes  ?

• C23C 4/12 - Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
• C23C 4/18 - After-treatment
• C23C 24/04 - Impact or kinetic deposition of particles
• H05K 3/14 - Apparatus or processes for manufacturing printed circuits in which conductive material is applied to the insulating support in such a manner as to form the desired conductive pattern using spraying techniques to apply the conductive material

Abstract

The present invention relates to a device (10) for cooling at least one autonomous electrical power source (115) of an aircraft characterized in that it comprises: - an air inlet (105) that allows the air to cool a coolant (110), - the coolant (110) is conveyed to the at least one autonomous electrical power source of the aircraft, - a convergent outlet (130) for hot air (120) comprising mobile means (125) for controlling the air flow rate and - supervision means (150) of the aircraft driving the mobile means for controlling the air flow rate according to the cooling needs (145) of the autonomous electrical power source. The present invention also relates to a process for cooling at least one autonomous electrical power source of an aircraft and an aircraft comprising such a device.

IPC Classes  ?

• B64D 33/00 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
• B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems