The present invention relates to a electrical power distribution network for an electrically powered aircraft comprising: at least one electrical power source; at least one essential power user; at least one non-essential power user; a busbar arrangement comprising a plurality of busbars, wherein each busbar is connected to at least one of the at least one electrical power source, at least one of the at least one essential power user and at least one of the at least one non-essential power user; a controller arrangement arranged to: control electrical power delivery via the busbar arrangement from the at least one electrical power source, detect an operating failure state; detect essential power usage; and, detect non-essential power usage wherein the busbar arrangement is arranged to provide a different connection route for each busbar to at least one essential power user and at least one non-essential power user.
The present invention relates to a power management system for an electrically powered aircraft, the system comprising: at least one electrical power source; at least one propulsion source arranged to generate propulsion from electrical power; a busbar arrangement comprising a plurality of busbars, wherein each busbar is connected to at least one electrical power source and at least one propulsion source and wherein each busbar has a connection to at least one other busbar; a re-configuration element arranged to controllably re-configure connections between the plurality of busbars; a controller arrangement arranged to: control electrical power delivery via the busbar arrangement from the at least one electrical power source to the at least one propulsion source; detect an operating failure state; detect propulsive power requirement; and, provide a signal to the re-configuration element based on the operating failure state and the propulsive power requirement.
The present invention relates to a thermal energy transfer device for use in transferring thermal energy from a coil of an electrically drivable motor, the device comprising: a plurality of elongate thermally conductive members each arranged to thermally communicate with at least a portion of a coil of an electrically drivable motor; at least one thermally conductive portion arranged to thermally communicate with a plurality of elongate thermally conductive members, wherein each of the plurality of elongate thermally conductive members is electrically insulated from any other of the plurality of thermally conductive members, and wherein the first plurality of elongate thermally conductive members are arranged to have a longitudinal axis in a first axis, and wherein the at least one thermally conductive portion is arranged to have a longitudinal axis in a second axis, wherein the first axis and the second axis are arranged between 45 degrees and 135 degrees apart, and wherein the at least one thermally conductive portion has a thermal conductivity of at least 100 Wm-1K-1 and an electrical conductivity of less than 10-14 Sm-1.
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
H02K 9/22 - Arrangements for cooling or ventilating by solid heat conducting material embedded in, or arranged in contact with, the stator or rotor, e.g. heat bridges
H02K 55/00 - Dynamo-electric machines having windings operating at cryogenic temperatures
The present invention relates to an electrical aircraft propulsion arrangement comprising: at least one fuel cell arranged to generated electrical power for use in propelling an aircraft; a fluid source arranged to provide fluid to at least one fuel cell for use in generating electrical power; at least one centrifugal compressor arranged to compress a fluid prior to provision to at least one fuel cell; at least one axial compressor arranged to compress a fluid prior to provision to at least one fuel cell, wherein at least one axial compressor is upstream of at least one centrifugal compressor.
B64D 27/355 - Arrangements for on-board electric energy production, distribution, recovery or storage using fuel cells
H01M 8/04089 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
The present invention relates to a thermal energy management system for use in an electrically powered aircraft, the system comprising: a passive cooling system (110); an active cooling system (120); and, a controller (130) arranged to control the active cooling system based on detected characteristics of flight, wherein the passive cooling system operates at all stage of flight; and wherein the active cooling system is controllably operable by the controller for all stages of flight.
The present invention relates to a repeatable unit for a segmented stator for an electric machine, the unit comprising: a back-iron stator segment; a stator tooth segment comprising a top portion, a main body portion and a base portion; and a connection portion for connecting the back-iron stator segment to the stator tooth segment, wherein the base portion of the stator tooth segment has a width that is greater than a width of the top portion and the width of the main body portion, wherein, in use, a furthest radial distance of the back-iron stator segment is broadly the same as a furthest radial distance for the stator tooth segment.
H02K 1/18 - Means for mounting or fastening magnetic stationary parts on to, or to, the stator structures
H02K 15/02 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies
H02K 5/20 - Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
H02K 55/00 - Dynamo-electric machines having windings operating at cryogenic temperatures
A component can be formed from a non-crimp fibre material, by using a forming tool over which a layer of non-crimp fibre is to be drawn, wherein the layer of non-crimp material is drawn over the tool by forming boards extending around all or part of the periphery of the tool using an elastic material.
B29C 70/56 - Tensioning reinforcements before or during shaping
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 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
The present invention relates to an aircraft propulsion arrangement comprising a cryogenic source, there is presented an aircraft propulsion arrangement comprising: a cryogenic source comprising a cryogenic resource, wherein the cryogenic resource is arranged to, initially, provide a heat exchanger function and to, subsequently, function as a fuel for a fuel cell; at least one heat exchanger, arranged in use to exchange thermal energy between generators of thermal energy and the cryogenic resource; at least one fuel cell, arranged to generate electrical power from the cryogenic resource for motive power, wherein the cryogenic resource is arranged to flow from the cryogenic source to the at least one heat exchanger and from the at least one heat exchanger to the at least one fuel cell.
The present invention relates to a thermal energy transfer device for use in transferring thermal energy from a coil of an electrically drivable motor, the device comprising: a first plurality of elongate thermally conductive members each arranged to thermally communicate with at least a portion of a coil of an electrically drivable motor; a second plurality of elongate thermally conductive members each arranged to thermally communicate with at least a portion of a coil of the electrically drivable motor, wherein each of the first and second plurality of elongate thermally conductive members is directly electrically insulated from any other of the plurality of thermally conductive members, and wherein the first plurality of elongate thermally conductive members are arranged to have a longitudinal axis in a first axis, and wherein the second plurality of elongate thermally conductive members are arranged to have a longitudinal axis in a second axis, wherein the first axis and the second axis are arranged between 45 degrees and 135 degrees apart.
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
H02K 9/22 - Arrangements for cooling or ventilating by solid heat conducting material embedded in, or arranged in contact with, the stator or rotor, e.g. heat bridges
H02K 55/00 - Dynamo-electric machines having windings operating at cryogenic temperatures
A cryocooled electric motor (500) comprising: a stator (510) comprising a magnetic core (510,510a), a rotor (520), an armature arrangement (550) and a cryogen source arranged to provide a cryonic fluid (544) to the armature arrangement (550), in order to cool the armature arrangement (550) below a temperature of 77 K, wherein the armature arrangement (550) comprises a plurality of Litz wires (552) and wherein the armature arrangement (550) is able to provide during operation of the motor a current density of more than 25 A/mm2.
H02K 3/14 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors arranged in slots with transposed conductors, e.g. twisted conductors
H02K 55/02 - Dynamo-electric machines having windings operating at cryogenic temperatures of the synchronous type
H02K 5/20 - Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
The present invention is concerned with an aircraft comprising an elongate fuselage for containing cargo or passengers. The fuselage comprises a lower floor and an upper ceiling and opposing fuselage sides extending between the ceiling and floor. The fuselage sides each comprise at least one door which can be selectively opened and closed. The fuselage is divided into multiple zones between the fore and aft of the aircraft, each zone being associated with one of said doors adjacent to said zone and wherein the doors alternate in position between sides of the aircraft such that adjacent zones from fore to aft of the aircraft are associated with a door on an opposing side of the aircraft.
The present invention relates to a power unit suitable for use in an aircraft comprising: at least one fuel cell; at least two fuel sources for providing fuel to the at least one fuel cell; wherein a first fuel source is a hydrogen supply arranged to provide hydrogen to a first fuel cell of the at least one fuel cell, and wherein a second fuel source is an air gas supply arranged to provide air gas to a first fuel cell of the at least one fuel cell.
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
H01M 8/04082 - Arrangements for control of reactant parameters, e.g. pressure or concentration
H01M 8/249 - Grouping of fuel cells, e.g. stacking of fuel cells comprising two or more groupings of fuel cells, e.g. modular assemblies
The present invention relates to an electrical transmission comprising: an electrical conductor; and, a cryogen carrying portion arranged so that, in use, cryogen is carried in the cryogen carrying portion to maintain the conductor in a hyperconductive state.
The present invention relates to a propulsion system for providing controllable propulsion comprising: a fuel cell arrangement (210) for generating electrical energy; a gas generator (250) comprising a compressor (256), a combustor (254) and a turbine (252), wherein the output from turbine is arranged to provide propulsion from rotational movement; a hydrogen source (212) for providing hydrogen to the fuel cell arrangement and the gas generator; an oxygen source (214) for providing oxygen to the gas generator (250), wherein, in use, the gas generator is used selectively to provide electrical energy for additional propulsion.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 41/00 - Power installations for auxiliary purposes
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
B64D 27/02 - Aircraft characterised by the type or position of power plants
The present invention relates to electrical network comprising an electrical conductor and, a cryogen source configured to hold cryogen, the cryogen source arranged so that, in use, cryogen is provided to the conductor to maintain the conductor in a hyperconductive state.
The present invention relates to an aircraft propulsion system (100) comprising: a fuel cell arrangement comprising at least one fuel cell (110); an air source (130) for providing air to the fuel cell arrangement; a compressor arrangement comprising a first compressor (120) in fluid communication with the air source and a fuel cell of the fuel cell arrangement; and, a turbine arrangement comprising a first turbine (124) mechanically coupled to the first compressor, wherein the first turbine is in fluid communication with the at least one fuel cell (110), the system being arranged so that, in use, air from the air source (130) flows in turn to the first compressor (120), the fuel cell arrangement and the first turbine (124).
B64D 41/00 - Power installations for auxiliary purposes
F02C 6/10 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
The present invention relates to a thermal energy transfer device for use in transferring thermal energy from a coil of an electrically drivable motor, the device comprising: a plurality of thermally conductive members arranged to thermally communicate with at least one coil of an electrically drivable motor; and, a thermally conductive portion connected to the plurality of thermally conductive members, wherein each of the plurality of thermally conductive members is directly electrically insulated from any other of the plurality of thermally conductive members.
H02K 9/22 - Arrangements for cooling or ventilating by solid heat conducting material embedded in, or arranged in contact with, the stator or rotor, e.g. heat bridges
H02K 55/00 - Dynamo-electric machines having windings operating at cryogenic temperatures
The present disclosure relates to a motor drive system comprising: a fuel cell; a motor, electrically connected to the fuel cell; and, a cryogenic system arranged to contain a cryogen, wherein the fuel cell is arranged to output current to the motor, and wherein the cryogenic system is arranged to communicate a cryogen from the cryogenic system to the fuel cell.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
H02K 55/00 - Dynamo-electric machines having windings operating at cryogenic temperatures
H02K 7/14 - Structural association with mechanical loads, e.g. with hand-held machine tools or fans
B60L 50/71 - Arrangement of fuel cells within vehicles specially adapted for electric vehicles
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B60L 58/33 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling fuel cells for controlling the temperature of fuel cells, e.g. by controlling the electric load by cooling
Disclosed are polyurethane-polysiloxane hybrid coating compositions (PUPSHCC) and their uses, processes for their preparation, and substrates incorporating the coating compositions.
C09D 4/00 - Coating compositions, e.g. paints, varnishes or lacquers, based on organic non-macromolecular compounds having at least one polymerisable carbon-to-carbon unsaturated bond
In manufacturing an electrothermal heater mat, there is provided a preform which comprises a laminated stack of dielectric layers which are made of thermoplastic material and include a central layer or group of layers which include(s) reinforcement and first and second outer groups of layers which do not include reinforcement. The preform includes a heater element and the preform has a first configuration. The preform is then heated to a temperature (e.g. 180° C.) between the glass-transition temperature of the thermoplastic material and the melting point of the thermoplastic material, and the heated preform is formed into a second configuration which is different to the first configuration so as to produce the heater mat.
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/88 - 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
H05B 3/36 - Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs heating conductor embedded in insulating material
A method of forming a component from a non-crimp fibre material, the method comprising a forming tool (6) over which a layer (10, 8) of non-crimp fibre is to be drawn, wherein the layer (8) of non-crimp material is drawn over the tool by forming boards (9A, 9B) extending around all or part of the periphery of the tool using an elastic material (10).
B29C 70/20 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in a single direction, e.g. roving or other parallel fibres
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 70/44 - 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 70/56 - Tensioning reinforcements before or during shaping
B29D 99/00 - Subject matter not provided for in other groups of this subclass
A method of forming a component from a non-crimp fibre material, the method comprising a forming tool (6) over which a layer (10, 8) of non-crimp fibre is to be drawn, wherein the layer (8) of non-crimp material is drawn over the tool by forming boards (9A, 9B) extending around all or part of the periphery of the tool using an elastic material (10).
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 70/56 - Tensioning reinforcements before or during shaping
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 70/20 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in a single direction, e.g. roving or other parallel fibres
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
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
An aircraft, such as an unmanned aerial vehicle or single-seat aircraft, including a main body and a pair of wing sections, each wing section including a front wing and a rear wing, wherein the front wing and the rear wing each include a first end that is connected to the main body, and a second end, wherein the second end of the front wing is connected to the second end of the rear wing. The main body is located between the pair of wing sections, and each wing section includes a propulsion unit located between the front wing and the rear wing of the wing section. Each propulsion unit may include a first rotor and a second rotor, which may be pivotable with respect to the rest of the aircraft.
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
A multi-source aircraft propulsion arrangement comprises a cryogenic propulsion source and a combustion propulsion source wherein the cryogenic propulsion source and the combustion propulsion source may be selectively and independently operated to generate propulsive force for an aircraft.
The present invention relates to a motor drive system comprising: a fuel cell; a motor, electrically connected to the fuel cell; and, a cryogenic system arranged, in use, to contain a cryogen, wherein the fuel cell is arranged to output current to the motor, and wherein the cryogenic system is arranged in use to communicate a cryogen from the cryogenic system to the fuel cell.
H02K 55/00 - Dynamo-electric machines having windings operating at cryogenic temperatures
B60L 15/00 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train
B60L 50/71 - Arrangement of fuel cells within vehicles specially adapted for electric vehicles
B60L 50/72 - Constructional details of fuel cells specially adapted for electric vehicles
B60L 58/33 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling fuel cells for controlling the temperature of fuel cells, e.g. by controlling the electric load by cooling
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
An electrical coupling for aerospace applications comprises an interposer arranged in use to electrically connect an electrical connector to an electrical circuit, the electrical connector comprising a plurality of electrical contacts and the electrical circuit comprising a plurality of electrical conductors. The interposer comprises a body arranged to surround each electrical contact within the connector.
Disclosed are polyurethane-polysiloxane hybrid coating compositions (PUPSHCC) and their uses, processes for their preparation, and substrates incorporating the coating compositions.
C08G 18/10 - Prepolymer processes involving reaction of isocyanates or isothiocyanates with compounds having active hydrogen in a first reaction step
C08G 18/24 - Catalysts containing metal compounds of tin
C08G 18/28 - Polymeric products of isocyanates or isothiocyanates with compounds having active hydrogen characterised by the compounds used containing active hydrogen
C08G 18/42 - Polycondensates having carboxylic or carbonic ester groups in the main chain
C08G 18/75 - Polyisocyanates or polyisothiocyanates cyclic cycloaliphatic
C08G 77/18 - Polysiloxanes containing silicon bound to oxygen-containing groups to alkoxy or aryloxy groups
An ice removal apparatus for an aircraft is provided comprising a laminate structure encapsulating an electrically operable heater. The laminate structure comprises a plurality of layers and at least two layers are configured to be selectively movable relative to each other to increase the separation of the two layers, thereby removing ice.
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
B32B 27/08 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance of synthetic resin of a different kind
B32B 27/28 - Layered products essentially comprising synthetic resin comprising copolymers of synthetic resins not wholly covered by any one of the following subgroups
B64D 15/16 - De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface
H05B 3/36 - Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs heating conductor embedded in insulating material
The present invention relates to a fluid release system for a fuel cell, the system comprising: a conduit for communicating water from the fuel cell to one or more outlets; and, a water discharge arrangement arranged to selectively release water from the one or more outlets, wherein the water discharge arrangement is arranged to controllably open the one or more outlets to selectively release water from the one or more outlets.
H01M 8/04119 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyteHumidifying or dehumidifying
01 - Chemical and biological materials for industrial, scientific and agricultural use
12 - Land, air and water vehicles; parts of land vehicles
Goods & Services
Chemical preparations having water repellant properties for repelling water from aircraft windows Component feature of an aircraft window, namely, a water repellant coating
01 - Chemical and biological materials for industrial, scientific and agricultural use
12 - Land, air and water vehicles; parts of land vehicles
Goods & Services
Coatings for glass [chemicals]; chemical treatment kits for glass; Coating preparations [chemicals] for applying a water repellent coating to a glass article; coating preparations [chemicals] having water repellent properties; chemical preparations included in a kit useful in the application of a water repellent coating to an article, especially a glass article. Aircraft windows; aircraft windows pre-coated with a hydrophobic coating.
01 - Chemical and biological materials for industrial, scientific and agricultural use
Goods & Services
Coatings for glass [chemicals]; chemical treatment kits for glass; coating preparations [chemicals] for applying a water repellent coating to a glass article; coating preparations [chemicals] having water repellent properties; chemical preparations included in a kit useful in the application of a water repellent coating to an article, especially a glass article.
An aerospace surface heating apparatus includes opposing layers formed from a thermoplastic containing in excess of 20% by volume of an inorganic filler material, and at least one electrically powered heating element located between the opposing layers. A method for making a heater for an aerospace component includes forming an electrical heating element on a layer of glass fiber reinforced thermoplastic film substrate, applying two opposing thermoplastic layers on opposing sides of the intermediate layer, and applying heat and pressure to the layers to join the layers together, in which the thermoplastic material contains an inorganic filler material.
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
B32B 27/08 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance of synthetic resin of a different kind
B32B 27/20 - Layered products essentially comprising synthetic resin characterised by the use of special additives using fillers, pigments, thixotroping agents
B32B 27/28 - Layered products essentially comprising synthetic resin comprising copolymers of synthetic resins not wholly covered by any one of the following subgroups
B32B 37/20 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with all layers existing as coherent layers before laminating involving the assembly of continuous webs only
B32B 38/00 - Ancillary operations in connection with laminating processes
H05B 3/18 - Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor the conductor being embedded in an insulating material
The invention concerns a curing apparatus in which individual parts which are to be cured are detected. The apparatus may determine the type of part being cured and display information to an operative based on the cure requirements for the given part and the curing time that has elapsed. Other determinations may additionally be made from these determinations.
An aircraft, such as an unmanned aerial vehicle or single-seat aircraft, comprising a main body and a pair of wing sections, each wing section comprising a front wing and a rear wing, wherein the front wing and the rear wing each comprise a first end that is connected to the main body, and a second end, wherein the second end of the front wing is connected to the second end of the rear wing. The main body is located between the pair of wing sections, and each wing section comprises a propulsion unit located between the front wing and the rear wing of the wing section. Each propulsion unit may comprise a first rotor and a second rotor, which may be pivotable with respect to the rest of the aircraft.
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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
An electrothermal heater for an ice protection system includes a laminated heater mat which comprises a primary heater element layer, a secondary heater element layer, and at least one dielectric layer interposed between the primary and secondary heater element layers, and control apparatus which comprises power supply apparatus and a current detector. The control apparatus is configured to have (i) a first mode in which the power supply apparatus supplies a heater current to the primary heater element layer and does not supply a heater current to the secondary heater element layer and the current detector monitors the secondary heater element layer for detecting a leakage current of the heater current of the primary heater element layer indicative of burn-out of the primary heater element layer and (ii) a second mode in which the power supply apparatus supplies a heater current to the secondary heater element layer and does not supply a heater current to the primary heater element layer. The control apparatus is configured to switch from the first mode to the second mode in response to detection of said leakage current by the current detector.
The invention concerns a deformable aerospace structure comprising a first layer and a second layer spaced from the first layer and defining a space therebetween. The space comprises one or more reinforcement elements extending between the first layer and the second layer. The ends or portions of the reinforcement element(s) proximate to the first layer are connected thereto and ends or portions of the reinforcement element(s) proximate to the second layer are moveable with respect to ends or portions of adjacent reinforcement element(s) proximate to the second layer.
12 - Land, air and water vehicles; parts of land vehicles
21 - HouseHold or kitchen utensils, containers and materials; glassware; porcelain; earthenware
Goods & Services
Windscreens and windows for aircraft, watercraft and land vehicles; toughened glass for incorporation in windscreens and windows for aircraft, watercraft and land vehicles in the nature of toughened glass windows for aircraft, watercraft and land vehicles Unfinished toughened glass for vehicle windows for incorporation in windscreens and windows for aircraft, watercraft and land vehicles
In manufacturing an electrothermal heater mat, there is provided a preform which comprises a laminated stack of dielectric layers which are made of thermoplastic material and include a central layer or group of layers which include(s) reinforcement and first and second outer groups of layers which do not include reinforcement. The preform includes a heater element and the preform has a first configuration. The preform is then heated to a temperature (e.g. 180° C.) between the glass-transition temperature of the thermoplastic material and the melting point of the thermoplastic material, and the heated preform is formed into a second configuration which is different to the first configuration so as to produce the heater mat.
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/88 - 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
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
H05B 3/36 - Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs heating conductor embedded in insulating material
An additive manufacturing metallic powder recovery apparatus comprising a powder removal chamber in communication with one or more powder recover modules. Each of the modules is arranged in use to recover metallic powder from an airflow passing through the module(s) in a variety of different ways and to weigh the contents of the module.
The present invention relates to a multi-source aircraft propulsion arrangement comprising a cryogenic propulsion source and a combustion propulsion source wherein the cryogenic propulsion source and the combustion propulsion source may be selectively and independently operated to generate propulsive force for an aircraft.
F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
B60L 50/15 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by engine-driven generators, e.g. generators driven by combustion engines with additional electric power supply
B64D 27/20 - Aircraft characterised by the type or position of power plants of jet type within, or attached to, fuselages
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F02K 5/00 - Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan
A method of forming a component by applying a forming load to a blank of material against a mandrel, wherein the mandrel defines the shape of the component to be formed and applying a forming load as a combination of a localised force and localised friction heating.
In a method of manufacturing an electrothermal heater mat, a heater element is deposited on a first one of the dielectric layers of the heater mat by using a laser blown powder process.
B22F 10/25 - Direct deposition of metal particles, e.g. direct metal deposition [DMD] or laser engineered net shaping [LENS]
B22F 7/02 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite layers
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
B23K 26/144 - Working by laser beam, e.g. welding, cutting or boring using a fluid stream, e.g. a jet of gas, in conjunction with the laser beamNozzles therefor the fluid stream containing particles, e.g. powder
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
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
B22F 12/55 - Two or more means for feeding material
B32B 27/28 - Layered products essentially comprising synthetic resin comprising copolymers of synthetic resins not wholly covered by any one of the following subgroups
B32B 37/18 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with all layers existing as coherent layers before laminating involving the assembly of discrete sheets or panels only
B22F 12/50 - Means for feeding of material, e.g. heads
The invention concerns an electrical coupling for aerospace applications comprising an interposer arranged in use to electrically connect an electrical connector to an electrical circuit, the electrical connector comprising a plurality of electrical contacts and the electrical circuit comprising a plurality of electrical conductors. The interposer comprises a body arranged to surround each electrical contact within the connector.
An ice accretion apparatus comprises a column having a longitudinal axis, a side wall, and a central chamber having top and bottom ends. It also comprises a top unit which closes the top end of the chamber and includes a droplet discharge device for producing water droplets, a bottom unit which closes the bottom end of the chamber and includes a target, and chamber cooling means configured to cool the chamber during a test and thereby to cool the water droplets, whereby, in use during the test, a layer of accreted ice is built up on the target.
An aerospace surface heating apparatus and method for use on wing leading edges and the like. The apparatus comprising at least one electrically powered heating element located between opposing layers of a thermoplastic material. The thermoplastic material comprises an inorganic filler material blended with the thermoplastic.
H05B 3/26 - Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater non-flexible heating conductor mounted on insulating base
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
An ice removal apparatus for an aircraft comprising a laminate structure encapsulated an electrically operable heater. The laminate structure comprises a plurality of layers and at least two layers are configured to be selectively movable relative to each other to increase the separation of the two layers.
B64D 15/08 - Liquid application exuded from surface
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
B64D 15/16 - De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface
An ice removal apparatus for an aircraft comprising a laminate structure encapsulated an electrically operable heater. The laminate structure comprises a plurality of layers and at least two layers are configured to be selectively movable relative to each other to increase the separation of the two layers.
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
B64D 15/16 - De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface
B64D 15/08 - Liquid application exuded from surface
53.
DEFECT DETECTION AND CORRECTION IN ADDITIVE MANUFACTURING
Disclosed is a method for identifying, in a near-infrared or infrared image of a layer of an object being manufactured by additive manufacturing, at least one pixel representing at least part of a first defect in the object, the method comprising: removing from the image any pixels that are identified as representing at least part of the boundary of the object and any pixels that are outside the border of the second image; identifying any pixel having a difference in brightness from the average brightness in the region around it above a threshold value as representing at least part of a defect. Also disclosed is a method of correcting a defect.
B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
B29C 64/393 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
Ice test devices include an ice adhesion test device. The ice adhesion test device comprises an ice adhesion test target in the form of a well in which, in use, a layer of accreted ice is built up. The target comprises a sample plate at the bottom of the well and an ice-engagement element positioned circumferentially around the sample plate and providing a side wall of the well, and wherein the sample plate is rotatable relative to the ice-engagement element. The ice adhesion test device also comprises torque means for applying a rotational torque between the sample plate and the ice-engagement element. The ice adhesion test device also comprises transducer means for, at least at a point at which the layer of accreted ice separates from the sample plate, measuring the rotational torque and/or the stress on the ice.
The present invention relates to a method of manufacturing a rib wherein the rib comprises two opposing outer skins and a plurality of internal reinforcement members connecting the skins together.
In a method of manufacturing an electrothermal heater mat (3), there is provided a preform (7) which comprises a laminated stack of dielectric layers (51-56) which are made of thermoplastic material and include a central layer or group of layers (501) which include(s) reinforcement and first and second outer groups of layers (502, 503) which do not include reinforcement. The preform (7) includes a heater element and the preform has a first configuration. The preform (7) is then heated to a temperature (e.g. 180°C) between the glass- transition temperature of the thermoplastic material and the melting point of the thermoplastic material, and the heated preform (7) is formed into a second configuration which is different to the first configuration so as to produce the heater mat (3).
B29C 35/02 - Heating or curing, e.g. crosslinking or vulcanising
B29C 65/00 - Joining of preformed partsApparatus therefor
B29C 70/78 - Moulding material on one side only of the preformed part
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
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
H05B 3/36 - Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs heating conductor embedded in insulating material
57.
ELECTROTHERMAL HEATER MAT AND METHOD OF MANUFACTURE THEREOF
In a method of manufacturing an electrothermal heater mat (3), there is provided a preform (7) which comprises a laminated stack of dielectric layers (51-56) which are made of thermoplastic material and include a central layer or group of layers (501) which include(s) reinforcement and first and second outer groups of layers (502, 503) which do not include reinforcement. The preform (7) includes a heater element and the preform has a first configuration. The preform (7) is then heated to a temperature (e.g. 180°C) between the glass- transition temperature of the thermoplastic material and the melting point of the thermoplastic material, and the heated preform (7) is formed into a second configuration which is different to the first configuration so as to produce the heater mat (3).
B29C 70/78 - Moulding material on one side only of the preformed part
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 35/02 - Heating or curing, e.g. crosslinking or vulcanising
B29C 65/00 - Joining of preformed partsApparatus therefor
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
H05B 3/36 - Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs heating conductor embedded in insulating material
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
58.
Acoustic honeycomb panel with integrated electrical heater
A noise attenuation panel comprises a sound absorbing honeycomb layer disposed between a perforated surface layer on an airflow facing side of the panel and a composite support layer on a second opposing side of said panel. The composite material support layer comprises an electrical heat source.
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B32B 3/26 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids
B32B 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
B32B 15/04 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance
H05B 3/48 - Heating elements having the shape of rods or tubes non-flexible heating conductor embedded in insulating material
The invention is concerned with a method of forming a component (1) by applying a forming load to a blank (13) of material against a mandrel (9), wherein the mandrel (9) defines the shape of the component (1) to be formed, and applying a forming load (15) as a combination of a localised force and localised friction heating.
The invention is concerned with a method of monitoring the performance of a cathode of an electron beam melting machine wherein detection means such as a near infrared (NIR) camera is used in combination with the electron beam of the machine to detect changes in performance over time the machine.
An electrothermal heater (2) for an ice protection system includes a laminated heater mat (3) which comprises a primary heater element layer (36), a secondary heater element layer (37), and at least one dielectric layer (34) interposed between the primary and secondary heater element layers, and control apparatus (5) which comprises power supply apparatus (51, 52) and a current detector (56). The control apparatus (5) is configured to have (i) a first mode in which the power supply apparatus (51, 52) supplies a heater current to the primary heater element layer (36) and does not supply a heater current to the secondary heater element layer (37) and the current detector (56) monitors the secondary heater element layer (37) for detecting a leakage current of the heater current of the primary heater element layer (36) indicative of burn-out of the primary heater element layer and (ii) a second mode in which the power supply apparatus (51, 52) supplies a heater current to the secondary heater element layer (37) and does not supply a heater current to the primary heater element layer (36). The control apparatus (5) is configured to switch from the first mode to the second mode in response to detection of said leakage current by the current detector (56).
In a method of manufacturing an electrothermal heater mat (3), a heater element (6) is deposited on a first one (51) of the dielectric layers (51, 52) of the heater mat (3) by using a laser blown powder process.
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 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
B32B 3/18 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by an internal layer formed of separate pieces of material
Ice test devices are disclosed. One such ice test device is an ice adhesion test device. The ice adhesion test device comprises an ice adhesion test target in the form of a well in which, in use, a layer of accreted ice is built up. The target comprises a sample plate at the bottom of the well and an ice-engagement element positioned circumferentially around the sample plate and providing a side wall of the well, and wherein the sample plate is rotatable relative to the ice-engagement element. The ice adhesion test device also comprises torque means for applying a rotational torque between the sample plate and the ice-engagement element. The ice adhesion test device also comprises transducer means for, at least at a point at which the layer of accreted ice separates from the sample plate, measuring the rotational torque and/or the stress on the ice.
An ice accretion apparatus is disclosed. The ice accretion apparatus comprises a column having a longitudinal axis, a side wall, and a central chamber having top and bottom ends. It also comprises a top unit which closes the top end of the chamber and includes a droplet discharge device for producing water droplets, a bottom unit which closes the bottom end of the chamber and includes a target, and chamber cooling means configured to cool the chamber during a test and thereby to cool the water droplets, whereby, in use during the test, a layer of accreted ice is built up on the target.
G01N 25/14 - Investigating or analysing materials by the use of thermal means by using distillation, extraction, sublimation, condensation, freezing, or crystallisation
G01N 19/04 - Measuring adhesive force between materials, e.g. of sealing tape, of coating
The invention concerns a noise attenuation panel comprising a sound absorbing honeycomb layer disposed between a perforated surface layer on an airflow facing side of the panel and a composite support layer on a second opposing side of said panel. The composite material support layer comprises an electrical heat source.
There is described a method of designing a composite component for manufacture using a pre-impregnated uni-directional or woven material; the method comprising: creating a design for a composite component comprising multiple layers of pre-impregnated uni- directional or woven material; defining within the design a division of the design into a plurality of macroscale elements; for each macroscale element, defining a microscale relative volume element, determining model parameters for the microscale representative volume element, and upscalin9the microscale representative volume element to provide a set of model parameters describing the macroscale element; using the set of model parameters for each macroscale element to analyse the design to identify the presence or absence of regions where structures likely to be detrimental to the integrity of the component would be expected to occur when manufacturing a component according to the design; if regions where structures likely to be detrimental to the integrity of the component would be expected to occur are identified, making data describing these regions available to a redesign process.
B64C 1/12 - Construction or attachment of skin panels
B29C 65/54 - Applying the adhesive between pre-assembled parts
B29C 65/56 - Joining of preformed partsApparatus therefor using mechanical means
B29C 65/72 - Joining of preformed partsApparatus therefor by combined operations, e.g. welding and stitching
B29C 65/00 - Joining of preformed partsApparatus therefor
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
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B29C 65/48 - Joining of preformed partsApparatus therefor using adhesives
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels
B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
B29K 63/00 - Use of epoxy resins as moulding material
Method for producing a structural component (1), comprising at least the following steps: a) providing a base carrier (2) with a surface (3), comprising a nonmetallic composite material (4), b) forming an imparting layer (5) on the surface (3), comprising a metallic material (6), c) forming a metallic top layer (7) on the imparting layer (5). Furthermore, a structural component (1) is proposed, having a base carrier (2) made of a nonmetallic composite material (4), an imparting layer (5) made of a matrix material (11) with a metallic material (6) integrated therein, and a metallic top layer (7), wherein the imparting layer (5) is arranged between the base carrier (2) and the top layer (7).
B32B 15/08 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance of synthetic resin
B05D 1/18 - Processes for applying liquids or other fluent materials performed by dipping
C23C 16/06 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the deposition of metallic material
An ice-protection system suitable for use in an aircraft (1) comprises first de-icing apparatus (5) operable to de-ice a first zone (61); a first ice-detection sensor (2) positioned in the first zone (61) and arranged to detect ice accreted on the first zone (61); and a control system (71) responsive to the first ice-detection sensor (2) and arranged to control the operation of the first de-icing apparatus (5).
A detection apparatus measures liquid water content and/or ice crystal particle concentration in an airstream (4) such as the airstream (4) around an aircraft (1). A light source (3) emits a beam of light (31) along an emission path (32), and the emission path (32) is located in a detection volume (42) which is arranged to receive the airstream (4). A first optical sensor (5) receives scattered light along a first viewing path (53) from the detection volume (42) and produces a first detection output (54). A processor (6) analyses the first detection output (54) of the first optical sensor (5) and produces a status output (61) indicative of measured liquid water content and/or ice crystal particle concentration. The first viewing path (53) is at a first oblique angle θ to the emission path (32).
An apparatus for detecting ice accretion on a surface (2020) comprises an electromagnetic radiation source (2014) configured in use to be positioned adjacent the surface (2020) and a detector (2012) spaced apart from the electromagnetic radiation source. The electromagnetic radiation source (2014) is operable to project electromagnetic radiation (2018) across a portion of the surface (2020) and on to the detector (2012) such that ice accretion on the surface produces a shadow in the projected electromagnetic radiation impinging on the detector (2012).
Method for bonding a T-section stiffener (100) to a surface (106) comprising the steps of: arranging an isolation layer (120) between two adjacent upright portions (102,104) of a T-section stiffener (100), arranging the stiffener (100) on the surface (106) and bonding the stiffener (100) to the surface (106).
Method forming a composite structure (9) comprising a main body and a flange. The composite structure is manufactured by laying-up a preform (7) on a mold (6). The preform (7) does not have the first and second bends and comprises a first part which corresponds to the main body of the composite structure and a second part which corresponds to the flange of the composite structure. The second part of the (preform (7) has a proximal portion which corresponds to the wall portion of the flange and a distal portion which corresponds to the lip portion of the flange. The preform (7) comprises a plurality of plies and uni-directional ply material extends from the first part of the preform (7) to the distal portion of the second part of the preform (7). The flange is formed by advancing movable portion(s) (62) of the mold 6 to form the proximal portion of the second part of the preform (7) to create the first bend (81) and by forming the distal portion of the second part of the preform (7) around the advancing movable portion(s) (62) of the mold (6) to create the second bend (83). The presence of the two bends (81, 83) ensures that the ply material (78) is kept in tension during the forming operation.
B32B 37/02 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by a sequence of laminating steps, e.g. by adding new layers at consecutive laminating stations
B29C 53/04 - Bending or folding of plates or sheets
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
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
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
B29C 57/00 - Shaping of tube ends, e.g. flanging, belling or closingApparatus therefor
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
A method of forming a composite component in which the component comprises a series of sub-layers and in which the sub-layers are offset with respect to one or all of the other sub-layers forming the composite component.
B29C 70/00 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
B29C 70/02 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements and fillers incorporated in matrix material, forming one or more layers, with or without non-reinforced or non-filled layers
B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
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
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
75.
Method of manufacturing a composite structure and composite structure obtained thereby
An example of a composite structure is a containment case 2 for a gas turbine engine 1 which comprises an annular housing 3 and an annular flange 4 which is integral with and is positioned at an end of the housing 3. The housing 3 comprises composite material which includes tape 9 laid in the circumferential direction of the housing. The flange 4 comprises composite material which includes tape 8 laid at an oblique angle to the circumferential direction of the flange 4 and/or tape 7 laid at a perpendicular angle to the circumferential direction. The flange 4 does not include tape 9 laid in the circumferential direction of the flange, because such tape would impede the forming of the flange material to form the flange.
B32B 37/18 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with all layers existing as coherent layers before laminating involving the assembly of discrete sheets or panels only
B32B 38/00 - Ancillary operations in connection with laminating processes
B29C 33/00 - Moulds or coresDetails thereof or accessories therefor
B29C 33/48 - Moulds or coresDetails thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
A structure such as a containment case (2) for a gas turbine engine (1) comprises an annular housing (3) made of composite material. A sleeve-like flange unit (4) is fitted onto an end of the housing (3) and is mechanically joined thereto by a first portion (31, 32, 33) of the composite material of the housing which projects into a recess (411) of the flange unit (4). This reduces or eliminates the need to use mechanical fasteners to connect the housing (3) to the flange unit (4).
B29C 70/56 - Tensioning reinforcements before or during shaping
B29C 44/00 - Shaping by internal pressure generated in the material, e.g. swelling or foaming
B29C 37/00 - Component parts, details, accessories or auxiliary operations, not covered by group or
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 70/76 - Moulding on edges or extremities of the preformed part
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
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
The invention relates to a method of manufacturing a composite acoustic panel employed in an inlet passage of a gas turbine engine (1). The acoustic panel comprises a permeable face-layer (8), an impermeable backing sheet (9) and a sound absorbing layer (10) disposed therebetween. The method comprises a double polymerisation process for the face-layer and the remainder of the acoustic panel and finally a perforation step to perforate the face-layer according to a pre-determined perforation distribution (11.1, 11.2, 11.3, 11.4, 11.5).
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
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 70/86 - Incorporating in coherent impregnated reinforcing layers
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
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
F02C 7/045 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
G10K 11/172 - Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects
B26D 3/08 - Making a superficial cut in the surface of the work without removal of material, e.g. scoring, incising
B23B 39/16 - Drilling machines with a plurality of working-spindlesDrilling automatons
B29C 70/32 - 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 on a rotating mould, former or core
B29K 105/04 - Condition, form or state of moulded material cellular or porous
B29K 105/24 - Condition, form or state of moulded material cross-linked or vulcanised
B29L 31/60 - Multitubular or multicompartmented articles, e.g. honeycomb
An electrothermal heater mat (3) is provided for an ice protection system for an aircraft (1) or the like. The heater mat (3) is a laminated heater mat and comprises dielectric layers (50-58), a heater element (501) and a conductive ground plane (71-74) for detecting a fault with the heater element (501). The dielectric layers (50-58) are made of thermoplastic material, and the ground plane (71-74) is formed by spraying metal such as copper onto the thermoplastic material of one of the dielectric layers.
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
H05B 3/36 - Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs heating conductor embedded in insulating material
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
An electrothermal heater mat (3) is provided for an ice protection system for an aircraft (1) or the like. The heater mat (3) is a laminated heater mat and comprises dielectric layers (50-58), a heater element (501) and a temperature sensor (507). Each dielectric layer (50-58) comprises thermoplastic material, and the temperature sensor (507) comprises a sprayed metal track (5010, 5012) deposited on a substrate (50, 5019) comprising thermoplastic material. The substrate may be one of the dielectric layers (50) or a separate carrier (5019) which is smaller than the dielectric layers (50-58). The substrate (50, 5019) is laminated to at least a first one of the dielectric layers (53, 58) and the thermoplastic material of the substrate is (i) the same as the thermoplastic material of the first dielectric layer such that the thermoplastic material of the substrate is dispersed or merged into the thermoplastic material of the first dielectric layer or (ii) compatible with the thermoplastic material of the first dielectric layer such that the thermoplastic material of the substrate is fused to the thermoplastic material of the first dielectric layer. Thus, the formation of an undesirable discontinuity at the interface between the substrate (50, 5019) and the first dielectric layer (53, 58) is substantially prevented or minimized.
A dielectric component with electrical connection is provided for a laminated heater mat (3) for an ice protection system for an aircraft (1). The dielectric component with electrical connection comprises at least one dielectric layer (50, 55) comprising thermoplastic material, and the dielectric layer (50) or a stack of the dielectric layers (50, 55) has first and second main surfaces and a hole (505) extending between the first and second main surfaces. A first sprayed metal coating (501) comprises a first portion (503) deposited on the first main surface (502) adjacent to the hole (505) and a second portion (5014) which projects into the hole. A second sprayed metal coating (5013, 5513) comprises a third portion deposited on the second main surface (506, 552) adjacent to the hole (505) and a fourth portion (5015) which projects into the hole (505). The second portion (5014) overlaps the fourth portion (5015) to form a continuous conductive path between the first main surface and the second main surface. This provides a cheap, neat and thin connection through the dielectric layer or the stack of dielectric layers.
H05B 3/18 - Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor the conductor being embedded in an insulating material
H05B 3/36 - Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs heating conductor embedded in insulating material
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
Electrical apparatus such as a heater (2) for an ice protection system for an aircraft (1) comprises a laminate such as a heater mat (3) and a connector (41-49). The laminate (3) comprises dielectric layers (50-58) and an electrical element such as a heater element (501), and each dielectric layer of the laminate comprises thermoplastic material. The connector (41-49) comprises a ribbon having first and second ends and a metal conductor (413, 423, 433). The ribbon comprises thermoplastic material and its first end (415, 425, 435, 445, 455, 465, 475, 485) is embedded in the laminate and is laminated to adjacent first and second ones of the dielectric layers (50-58) of the laminate. Because the thermoplastic material of the ribbon is the same as or is compatible with the thermoplastic material of the first and second dielectric layers, the formation of an undesirable discontinuity at the interfaces between the first end of the ribbon and the first and second dielectric layers is prevented. Thus, cracks are less likely to be initiated at the interfaces during the use of the electrical apparatus, and de-lamination is less likely to occur.
H05B 3/18 - Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor the conductor being embedded in an insulating material
H05B 3/36 - Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs heating conductor embedded in insulating material
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
82.
METHOD OF FORMING A COMPOSITE STRUCTURE COMPRISING A FLANGE
Method forming a composite structure ( 9 ) comprising a main body and a flange. The composite structure is manufactured by laying -up a preform (7) on a mould (6). The preform (7) does not have the first and second bends and comprises a first part which corresponds to the main body of the composite structure and a second part which corresponds to the flange of the composite structure. The second part of the (preform (7) has a proximal portion which corresponds to the wall portion of the flange and a distal portion which corresponds to the lip portion of the flange. The preform (7) comprises a plurality of plies and uni - directional ply material extends from the first part of the preform (7) to the distal portion of the second part of the preform (7). The flange is formed by advancing movable portion (s) (62) of the mould 6 to form the proximal portion of the second part of the preform (7) to create the first bend (81) and by forming the distal portion of the second part of the preform (7) around the advancing movable portion (s) (62) of the mould (6) to create the second bend (83). The presence of the two bends (81, 83) ensures that the ply material (78) is kept in tension during the forming operation.
B29C 53/04 - Bending or folding of plates or sheets
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
A fire-protected composite structure (2, 6) comprises a composite component (32, 62) having a first surface (34, 64) and a hot sprayed metallic layer (36, 66) is deposited on the first surface ((34), (64). In the event of a malfunction which generates a flame, the outer surface( 34, 64) is offered some fire protection by the hot sprayed metallic layer (36, 66). The layer (36, 66) acts as a physical barrier stopping the flame from directly acting on the composite material and also, because the metal or metal alloy of the layer (36, 66) has good thermal conductivity, the layer (36, 66) conducts the heat of the flame away from the point of impingement of the flame on the composite material, thus stopping or slowing the thermal degradation of the matrix (resin) of the composite material.
E04B 1/04 - Structures consisting primarily of load-supporting, block-shaped or slab-shaped elements the elements consisting of concrete, e.g. reinforced concrete, or other stone-like material
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
Method forming a composite structure ( 9 ) comprising a main body and a flange. The composite structure is manufactured by laying -up a preform (7) on a mould (6). The preform (7) does not have the first and second bends and comprises a first part which corresponds to the main body of the composite structure and a second part which corresponds to the flange of the composite structure. The second part of the (preform (7) has a proximal portion which corresponds to the wall portion of the flange and a distal portion which corresponds to the lip portion of the flange. The preform (7) comprises a plurality of plies and uni - directional ply material extends from the first part of the preform (7) to the distal portion of the second part of the preform (7). The flange is formed by advancing movable portion (s) (62) of the mould 6 to form the proximal portion of the second part of the preform (7) to create the first bend (81) and by forming the distal portion of the second part of the preform (7) around the advancing movable portion (s) (62) of the mould (6) to create the second bend (83). The presence of the two bends (81, 83) ensures that the ply material (78) is kept in tension during the forming operation.
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29C 53/04 - Bending or folding of plates or sheets
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
A method of forming a composite component in which the component comprises a series of sub -layers and in which the sub -layers are offset with respect to one or all of the other sub -layers forming the composite component.
B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
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
A method of forming a composite component in which the component comprises a series of sub -layers and in which the sub -layers are offset with respect to one or all of the other sub -layers forming the composite component.
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
87.
METHOD OF MANUFACTURING A COMPOSITE STRUCTURE AND COMPOSITE STRUCTURE OBTAINED THEREBY
An example of a composite structure is a containment case 2 for a gas turbine engine 1 which comprises an annular housing 3 and an annular flange 4 which is integral with and is positioned at an end of the housing 3. The housing 3 comprises composite material which includes tape 9 laid in the circumferential direction of the housing. The flange 4 comprises composite material which includes tape 8 laid at an oblique angle to the circumferential direction of the flange 4 and/or tape 7 laid at a perpendicular angle to the circumferential direction. The flange 4 does not include tape 9 laid in the circumferential direction of the flange, because such tape would impede the forming of the flange material to form the flange.
A structure such as a containment case (2) for a gas turbine engine (1) comprises an annular housing (3) made of composite material. A sleeve-like flange unit (4) is fitted onto an end of the housing (3) and is mechanically joined thereto by a first portion (31, 32, 33) of the composite material of the housing which projects into a recess (411) of the flange unit (4). This reduces or eliminates the need to use mechanical fasteners to connect the housing (3) to the flange unit (4).
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
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 70/76 - Moulding on edges or extremities of the preformed part
89.
METHOD OF MANUFACTURING A COMPOSITE STRUCTURE AND COMPOSITE STRUCTURE OBTAINED THEREBY
An example of a composite structure is a containment case 2 for a gas turbine engine 1 which comprises an annular housing 3 and an annular flange 4 which is integral with and is positioned at an end of the housing 3. The housing 3 comprises composite material which includes tape 9 laid in the circumferential direction of the housing. The flange 4 comprises composite material which includes tape 8 laid at an oblique angle to the circumferential direction of the flange 4 and/or tape 7 laid at a perpendicular angle to the circumferential direction. The flange 4 does not include tape 9 laid in the circumferential direction of the flange, because such tape would impede the forming of the flange material to form the flange.
A composite structure such as a containment case (2) is manufactured with an inwardly projecting flange (93, 94) by using modular moulds (81, 82) so that the composite material of the containment case may be machine laid including machine laying the inwardly projecting flange (93, 94).
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/84 - Moulding material on preformed parts to be joined
B29C 70/46 - 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
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
B29D 99/00 - Subject matter not provided for in other groups of this subclass
An apparatus and method for forming a composite component comprising a flange. The flange may be employed to couple the composite component to another component such as a structural part of an engine or the like.
B29C 70/20 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in a single direction, e.g. roving or other parallel fibres
B29C 70/32 - 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 on a rotating mould, former or core
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
An apparatus and method for forming elongate composite components using an advance fibre placement (AFP) technique, such as a fan case for a gas turbine engine or the like, with an integral flange.
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
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 70/32 - 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 on a rotating mould, former or core
B29C 70/20 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in a single direction, e.g. roving or other parallel fibres
A method which improves manufacturing efficiencies and reduces the finishing process steps required for a given composite component. A frangible path ( 5 ) is created in cured stack of a composite material ( 2 ) which can be conveniently fractured to provide a component with an improved edge surface finish.
A flange (1) made of composite material, a method of making the flange (1) and a mandrel (3) upon which the flange (1) is formed are provided. The flange (1) is a curved hollow member that has a substantially triangular cross-section. The method of making the flange (1) includes applying composite material to external surfaces of a curved mandrel (3). The mandrel (3) is curved and comprises a solid triangular cross-section. The method also includes curing the composite material to produce a flange (1) that is a curved hollow member that is substantially triangular in cross-section.
The invention relates to a method of manufacturing a composite acoustic panel employed in an inlet passage of a gas turbine engine (1). The acoustic panel comprises a permeable face-layer (8), an impermeable backing sheet (9) and a sound absorbing layer (10) disposed therebetween. The method comprises a double polymerisation process for the face- layer and the remainder of the acoustic panel and finally a perforation step to perforate the face -layer according to a pre - determined perforation distribution (11.1, 11.2, 11.3, 11.4, 11.5).
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 70/86 - Incorporating in coherent impregnated reinforcing layers
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
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
F02C 7/045 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
G10K 11/172 - Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects
96.
Manufacturing method for components made of fiber-reinforced composite materials by using microwaves
A method for manufacturing a component comprising at least one layer having a fiber-reinforced composite material that absorbs microwaves is disclosed. The method comprises at least the following steps: a) arranging the at least one layer in a shape, b) treating a first surface section of the at least one layer with microwaves, wherein a temperature limiting mechanism of the at least one layer cooperate with at least one adjacent second surface section, at least part of the time. The method may be carried out in such that steps a) and b) are carried out for a plurality of components and that the components are further treated according to at least the following steps: c) positioning a plurality of components with respect to one another such that each second surface section forms at least one overlapping area at least partially, d) treating the at least one overlapping area with microwaves.
B29C 65/14 - Joining of preformed partsApparatus therefor by heating, with or without pressure using wave energy or particle radiation
B29C 35/02 - Heating or curing, e.g. crosslinking or vulcanising
B29C 35/08 - Heating or curing, e.g. crosslinking or vulcanising by wave energy or particle radiation
B29C 65/00 - Joining of preformed partsApparatus therefor
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 105/24 - Condition, form or state of moulded material cross-linked or vulcanised
B29K 105/06 - Condition, form or state of moulded material containing reinforcements, fillers or inserts
B29K 307/00 - Use of elements other than metals as reinforcement
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
97.
ELECTRICAL APPARATUS FOR AN ELECTROTHERMAL ICE PROTECTION SYSTEM
Electrical apparatus such as a heater (2) for an ice protection system for an aircraft (1) comprises a laminate such as a heater mat (3) and a connector (41-49). The laminate (3) comprises dielectric layers (50-58) and an electrical element such as a heater element (501), and each dielectric layer of the laminate comprises thermoplastic material. The connector (41-49) comprises a ribbon having first and second ends and a metal conductor (413, 423, 433). The ribbon comprises thermoplastic material and its first end (415, 425, 435, 445, 455, 465, 475, 485) is embedded in the laminate and is laminated to adjacent first and second ones of the dielectric layers (50-58) of the laminate. Because the thermoplastic material of the ribbon is the same as or is compatible with the thermoplastic material of the first and second dielectric layers, the formation of an undesirable discontinuity at the interfaces between the first end of the ribbon and the first and second dielectric layers is prevented. Thus, cracks are less likely to be initiated at the interfaces during the use of the electrical apparatus, and de- lamination is less likely to occur.
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
H05B 3/36 - Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs heating conductor embedded in insulating material
An electrothermal heater (2) for an ice protection system for an aircraft (1) or the like is provided with improved protection against lightning strikes. The heater (2) comprises a laminated heater mat (3) formed from dielectric layers (51-54) and a heater element (501). A first connector (41) has a first end (415) which is embedded in the heater mat (3) and is electrically connected to the heater element (501) and a second end which extends away from the heater mat for connection to a heater control unit (6). The heater mat (3) further includes first and second conductive ground planes (71, 72) and the first end (415) of the first connector (41) is positioned between the first and second ground planes so as to be shielded thereby and so as to reduce the current induced therein during a lightning strike.
An electrothermal heater mat (3) is provided for an ice protection system for an aircraft (1) or the like. The heater mat (3) is a laminated heater mat and comprises dielectric layers (50-58), a heater element (501) and a conductive ground plane (71-74) for detecting a fault with the heater element (501). The dielectric layers (50-58) are made of thermoplastic material, and the ground plane (71-74) is formed by spraying metal such as copper onto the thermoplastic material of one of the dielectric layers.
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
H05B 3/36 - Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs heating conductor embedded in insulating material
An electrothermal heater mat (3) is provided for an ice protection system for an aircraft (1) or the like. The heater mat (3) is a laminated heater mat and comprises dielectric layers (50-58), a heater element (501) and a temperature sensor (507). Each dielectric layer (50-58) comprises thermoplastic material, and the temperature sensor (507) comprises a sprayed metal track (5010, 5012) deposited on a substrate (50, 5019) comprising thermoplastic material. The substrate may be one of the dielectric layers (50) or a separate carrier (5019) which is smaller than the dielectric layers (50-58). The substrate (50, 5019) is laminated to at least a first one of the dielectric layers (53, 58) and the thermoplastic material of the substrate is (i) the same as the thermoplastic material of the first dielectric layer such that the thermoplastic material of the substrate is dispersed or merged into the thermoplastic material of the first dielectric layer or (ii) compatible with the thermoplastic material of the first dielectric layer such that the thermoplastic material of the substrate is fused to the thermoplastic material of the first dielectric layer. Thus, the formation of an undesirable discontinuity at the interface between the substrate (50, 5019) and the first dielectric layer (53, 58) is substantially prevented or minimised.
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
H05B 3/36 - Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs heating conductor embedded in insulating material
