Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
  • B64D27/02—Aircraft characterised by the type or position of power plants
  • B64D27/30—Aircraft characterised by electric power plants
  • B64D27/35—Arrangements for on-board electric energy production, distribution, recovery or storage
  • B64D27/353—Arrangements for on-board electric energy production, distribution, recovery or storage using solar cells
• • H—ELECTRICITY
  • H01—ELECTRIC ELEMENTS
  • H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
  • H01L31/00—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof
  • H01L31/0248—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof characterised by their semiconductor bodies
  • H01L31/036—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof characterised by their semiconductor bodies characterised by their crystalline structure or particular orientation of the crystalline planes
  • H01L31/0392—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof characterised by their semiconductor bodies characterised by their crystalline structure or particular orientation of the crystalline planes including thin films deposited on metallic or insulating substrates ; characterised by specific substrate materials or substrate features or by the presence of intermediate layers, e.g. barrier layers, on the substrate
  • H01L31/03926—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof characterised by their semiconductor bodies characterised by their crystalline structure or particular orientation of the crystalline planes including thin films deposited on metallic or insulating substrates ; characterised by specific substrate materials or substrate features or by the presence of intermediate layers, e.g. barrier layers, on the substrate comprising a flexible substrate
• • H—ELECTRICITY
  • H01—ELECTRIC ELEMENTS
  • H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
  • H01L31/00—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof
  • H01L31/04—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof adapted as photovoltaic [PV] conversion devices
  • H01L31/042—PV modules or arrays of single PV cells
  • H01L31/0445—PV modules or arrays of single PV cells including thin film solar cells, e.g. single thin film a-Si, CIS or CdTe solar cells
• • H—ELECTRICITY
  • H01—ELECTRIC ELEMENTS
  • H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
  • H01L31/00—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof
  • H01L31/04—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof adapted as photovoltaic [PV] conversion devices
  • H01L31/042—PV modules or arrays of single PV cells
  • H01L31/048—Encapsulation of modules
• • H—ELECTRICITY
  • H01—ELECTRIC ELEMENTS
  • H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
  • H01L31/00—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof
  • H01L31/04—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof adapted as photovoltaic [PV] conversion devices
  • H01L31/042—PV modules or arrays of single PV cells
  • H01L31/048—Encapsulation of modules
  • H01L31/049—Protective back sheets
• • H—ELECTRICITY
  • H01—ELECTRIC ELEMENTS
  • H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
  • H01L31/00—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof
  • H01L31/18—Processes or apparatus specially adapted for the manufacture or treatment of these devices or of parts thereof
  • H01L31/1876—Particular processes or apparatus for batch treatment of the devices
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
  • Y02E10/00—Energy generation through renewable energy sources
  • Y02E10/50—Photovoltaic [PV] energy
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/50—On board measures aiming to increase energy efficiency

Definitions

• the present invention relates to the power supply of aircraft. More particularly, it relates to an aircraft structure with solar energy capture capability.
• the invention has a particular advantage for aircraft structures made of composite material.
• bundles of electrical cables are brought from the power source to each system.
• the present invention specifically aims to define an aircraft structure with energy capture capability, with a mass penalty at most equivalent to existing solutions and having performance at least equivalent to existing solutions.
• an aircraft structure with a coating with electrical conductivity property deposited on its outer surface.
• the outer surface is here defined as the surface facing the external environment of the aircraft, ie the surface likely to be subjected to lightning impacts.
• an aircraft structure with solar energy capture capability, wherein at least a portion of the outer surface is coated with a photovoltaic film.
• photovoltaic film is meant a thin layer compared to the other two dimensions (length and width).
• This photovoltaic film is a flexible layer, that is to say a flexible layer.
• This film is composed of photovoltaic cells configured as independent photovoltaic modules for outputting a current and / or a DC voltage when subjected to incident solar radiation.
• the photovoltaic modules are connected together in series or parallel, and arranged next to each other so as to form the photovoltaic film.
• a photovoltaic cell consists of several layers, one of which is an electrode with electrical conduction capability. This electrode advantageously makes it possible to collect and transfer the electric charges. This electrode is preferably a layer of silver, copper or aluminum.
• some systems can be advantageously powered via a source of energy from the capture of solar energy via the aircraft structure according to the invention, placed in proximity to said systems.
• a source of energy from the capture of solar energy via the aircraft structure according to the invention placed in proximity to said systems.
• Such a power supply of these systems for example those farthest from a power source of the aircraft, reduces the electrical wiring.
• a photovoltaic film on an aircraft structure provides a solar energy capture capability serving the needs of the aircraft, without giving rise to mass penalty or complex implementation.
• the photovoltaic film offers the ability to transfer the electrical charges to be dissipated faster and more efficiently than current solutions, during a lightning strike of said aircraft structure.
• the use of a photovoltaic film on the surface of the aircraft structure makes it possible to obtain an effective protection of said aircraft structure against the effects of lightning without giving rise to a degradation of the surface quality, as it does. this is the case for existing aircraft structures requiring metal mesh.
• the photovoltaic film has a homogeneous and constant thickness unlike a wire mesh whose thickness is discontinuous.
• Another advantage of using a photovoltaic film on the surface of the aircraft structure is at the level of production constraints.
• the aircraft structure is also advantageously devoid of decorative paint layer, especially for non-customized areas, such as for example aircraft wings.
• photovoltaic film is suitable for any aircraft structure, whether of metal material or composite material.
• structure of composite material is meant a structure made from mineral or organic fibers, for example glass fibers, aramid fiber or carbon fiber, held in a hard organic matrix, for example epoxy .
• the invention also fulfills the following characteristics, implemented separately or in each of their technically operating combinations. At least some of its features aim to achieve additional objectives of the invention. In particular, the invention aims to ensure that the upper surface of the aircraft structure, that facing the external environment, is as smooth and shiny as in the absence of the standard decoration layer in the current aircraft .
• the aircraft structure comprises a flexible polymer layer between the outer surface and the photovoltaic film.
• the flexible polymer layer is a flexible layer which makes it possible to guarantee the deformation capacity of the assembly under the thermomechanical stress conditions of the aircraft structure.
• a layer is for example formed from elastomer matrices, polysulfone amide matrices (known by the acronym PSA) or so-called hot / melt elastomers advantageously allowing adhesion to the outer surface and to the photovoltaic film while guaranteeing the characteristics viscoelastic sought.
• PSA polysulfone amide matrices
• hot / melt elastomers advantageously allowing adhesion to the outer surface and to the photovoltaic film while guaranteeing the characteristics viscoelastic sought.
• the flexible polymer layer is advantageous from an aerodynamic point of view.
• such a layer is applicable at one time to a plurality of assembled aircraft structures, thus making it possible to overcome the geometrical differences in assemblies, such as, for example, the tolerances of the holes and fastenings, and thus avoiding any parasitic eddies at the same time. desired laminar airflow in a logic of minimum fuel consumption.
• said polymer layer comprises electrically conductive particles.
• the electrically conductive particles are chosen from a group comprising graphene, carbon fibers, metal nanowires or carbon nanotubes, a mixture of these particles or any other conductive pigment (metal, polymer, .. .).
• the polymer layer in order to guarantee durability and resistance to the effects of lightning, has a thickness of between 40 and 10 ⁇ m, preferably 80 ⁇ m. Such a thickness also makes it possible not to penalize en masse the aircraft structure.
• Such a polymer layer also has advantages in terms of: - aerodynamics,
• the aircraft structure comprises a protective layer covering the photovoltaic film.
• the protective layer is a layer capable of guaranteeing the durability of the aircraft structure under the conditions of environmental stresses specific to the aircraft.
• the protective layer covers the photovoltaic film for protection against corrosion, against external damage, etc.
• Such a protective layer is for example formed from polyurethane resins with a high number of functional groups ensuring a high degree of crosslinking.
• the protective layer has gloss and orange peel characteristics in accordance with all the customized zones of the aeronautical liveries. According to an advantageous characteristic of the invention, to allow the photovoltaic film to receive the light radiation and to keep its photovoltaic properties.
• the protective layer is transparent to ultraviolet rays in the useful frequency band.
• the photovoltaic cells have a substantially identical, preferably square, geometric shape.
• the photovoltaic cells have a substantially identical geometric shape, preferably triangular.
• the photovoltaic cells have a substantially identical geometric shape, preferably hexagonal, because this shape improves the acceptance capacity of the photovoltaic film to deformations, in addition to the same capacity of acceptance of the flexible polymer layer.
• each cell has a dimension substantially of the order of 200 * 200 mm.
• the photovoltaic film has a thickness between 300 ⁇ ⁇ ⁇ , preferably about 400 ⁇ .
• This thickness plays a significant role against the protection of the aircraft structure to the impacts of lightning because it allows to increase the transfer of electrical charges during a lightning strike on the aircraft structure.
• the oversizing in thickness of the photovoltaic film is mainly an oversizing in thickness of electrodes with electrical conduction capacity of the photovoltaic cells.
• the thickness of said electrodes is chosen so that the surface impedance is less than 2 ⁇ / ⁇ ⁇ 20%, so as to guarantee the evacuation of the electrical charges related to a lightning impact under the best conditions for the structure of the aircraft.
• the aircraft structure coated on at least a portion of its outer surface with at least one photovoltaic film is a fuselage, a nacelle or a wing of the aircraft.
• the present invention relates to an aircraft comprising an aircraft structure meeting one or more of the above characteristics.
• the present invention relates to a method of manufacturing an aircraft structure, wherein at least a portion of an outer surface of said aircraft structure is applied to one or more of the aircraft structures.
• a photovoltaic film characteristics above, a photovoltaic film. The application of this photovoltaic film requires only a few specific operations, which can be integrated into a more general method of application of conventional coating layers on the outer surface of the body of the aircraft.
• This manufacturing process is easily adapted to the protection of the outer surface against the effects of lightning.
• the application of the photovoltaic film can be carried out by conventional techniques in themselves, for example of the type by laminating.
• a flexible polymer layer is applied to the outer surface of the aircraft structure, and then the photovoltaic film is applied to the flexible polymer layer.
• a protective layer is applied to the photovoltaic film.
• the application of the flexible and protective polymer layers may be carried out by conventional techniques in themselves, for example of the spray or ink jet type, etc., and be followed by a drying step, whether it is a drying in ambient air, controlled drying, temperature and hygrometry, or accelerated drying by ultraviolet lamp.
• the application of the flexible polymer layer, respectively of the protective layer is preceded by a step of preparing the outer surface of the aircraft structure, respectively photovoltaic film.
• the application of the photovoltaic film is preceded by a step of preparing the surface on which it will rest.
• Figure 1 illustrates a cross-sectional view of a multilayer assembly applied to the outer surface of the skin of an aircraft fuselage
• FIG. 2 illustrates a top view of a mosaic of photovoltaic cells having a square geometrical shape
• FIG. 3 illustrates a top view of a mosaic of photovoltaic cells having a triangular geometrical shape
• FIG. 4 illustrates a view from above of a mosaic of photovoltaic cells having a hexagonal geometric shape.
• FIG. Figure 1 shows a locally flat aircraft structure for illustration without this character being limiting of the invention.
• An aircraft structure 10 according to the invention is made of composite material and mainly comprises a structural part 20 comprising inorganic or organic fibers held in an organic hard resin.
• such a structural part 20 comprises stacked plies of glass fibers, Kevlar® or carbon, woven or unidirectional, held in a matrix of a polymeric material such as an aramid.
• the aircraft structure described is for example a fuselage without this choice being limiting of the invention.
• the fuselage comprises, on a surface 21, said outer surface, the structural portion 20 on one side of said fuselage on which electric charges are likely to accumulate and or a lightning strike is likely to occur, a multilayer assembly 345.
• This multilayer assembly 345 is applied instead of the decorative exterior paint.
• This multilayer assembly 345 comprises a plurality of layers 30, 40, 50 for the recovery of solar energy as well as for the protection of the aircraft against the effects of lightning and corrosion.
• the multilayer assembly 345 comprises in particular, arranged one above the other on the outer surface 21 of the structural portion 20 of the fuselage 10, three successive layers.
• a first layer, called flexible polymer layer 30, covers all or part of the outer surface 21 of the structural portion 20.
• This flexible polymer layer has for example a thickness between 40 and 1 10 ⁇ , preferably 80 ⁇ .
• the flexible polymer layer is a specific sealant for aeronautical aeronautical applications, elastomers, PSA acrylic matrices, or even hot melt elastomers.
• a second layer covers a surface 31 of the flexible polymer layer, opposite to a surface covering the outer surface 21 of the structural part.
• the photovoltaic film 40 is flexible and is composed of a plurality of photovoltaic cells 42 connected in series or in parallel.
• the photovoltaic cells 42 used are preferably of the 2 nd or 3 rd generation type.
• the photovoltaic cells 42 have a square, triangular or hexagonal geometrical shape, as illustrated in FIGS. 2 to 4.
• the photovoltaic film 40 has a thickness between 300 and 1000 ⁇ , preferably 400 ⁇ . This thickness is much greater than the thickness of conventional photovoltaic cells in order to increase the transfer of electrical charges during a lightning strike on the aircraft structure.
• the flexible polymer layer 30 positioned between the fuselage and the photovoltaic film 40 advantageously makes it possible to absorb differential expansions between said fuselage and said photovoltaic film which may appear in the condition of use of the aircraft.
• the flexible polymer layer 30 comprises electrically conductive particles, graphene type, carbon nanotubes, etc.
• the protective layer 50 covers a surface 41 of the photovoltaic film 40.
• the photovoltaic film 40 is thus interposed between the flexible polymer layer 30 and the protective layer 50.
• the protective layer 50 advantageously makes it possible to withstand the external aggressions that the aircraft can undergo under conditions of use.
• This protective layer has a thickness between 10 and 80 ⁇ .
• the protective layer is of the varnish type.
• the protective layer is composed for example of polyurethane resins with a high number of functional groups ensuring a high degree of crosslinking.
• said protective layer is transparent and resistant to ultraviolet radiation to allow the photovoltaic film to ensure good absorption of solar radiation.
• said protective layer 50 is a layer ensuring good absorption of solar radiation.
• the outer surface 21 of the structural portion 20 is not necessarily entirely covered by the multilayer assembly 345, some areas not or little exposed to the risk of lightning may not be protected or protected by other means, the description being limited to a portion of the outer surface 21 protected according to the principle of the invention.
• the application of the multilayer stack 345 is performed on the outer surface 21 of the structural portion 20 of the fuselage of the aircraft.
• the three layers 30, 40, 50 are successively applied one on top of the other.
• the application of the flexible polymer layer 30, respectively of the protection layer 40 can be performed by any conventional technique in itself, for example by inkjet, the outer surface 21 of the fuselage, respectively the surface 41 of the photovoltaic film, having previously been subjected to preparation operations surface area required for this purpose.
• the application of the photovoltaic film 40 on the surface 31 of the flexible polymer layer on which it will rest can be carried out by any conventional technique in itself, for example by laminating.
• the proposed invention advantageously makes it possible to make an aircraft structure protected against the effects of lightning, by penalizing little the mass of the aircraft, and without penalizing the external appearance. It also advantageously makes it possible to capture the ambient solar energy for the internal needs of the aircraft.

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• Engineering & Computer Science (AREA)
• Physics & Mathematics (AREA)
• Condensed Matter Physics & Semiconductors (AREA)
• Electromagnetism (AREA)
• General Physics & Mathematics (AREA)
• Computer Hardware Design (AREA)
• Microelectronics & Electronic Packaging (AREA)
• Power Engineering (AREA)
• Aviation & Aerospace Engineering (AREA)
• Life Sciences & Earth Sciences (AREA)
• Sustainable Development (AREA)
• Sustainable Energy (AREA)
• Chemical & Material Sciences (AREA)
• Crystallography & Structural Chemistry (AREA)
• Manufacturing & Machinery (AREA)
• Photovoltaic Devices (AREA)

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• 2013
  • 2013-06-28 FR FR1356246A patent/FR3007734B1/fr not_active Expired - Fee Related
• 2014
  • 2014-06-27 WO PCT/EP2014/063761 patent/WO2014207236A1/fr active Application Filing
  • 2014-06-27 EP EP14735539.0A patent/EP3013690A1/de not_active Withdrawn
  • 2014-06-27 CN CN201480036161.4A patent/CN105392701A/zh active Pending
  • 2014-06-27 US US14/900,282 patent/US20160368613A1/en not_active Abandoned

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