EP2242639A2 - Élément composite renforcé par fibres pour aéronef ou vaisseau spatial - Google Patents

Élément composite renforcé par fibres pour aéronef ou vaisseau spatial

Info

Publication number
EP2242639A2
EP2242639A2 EP09705828A EP09705828A EP2242639A2 EP 2242639 A2 EP2242639 A2 EP 2242639A2 EP 09705828 A EP09705828 A EP 09705828A EP 09705828 A EP09705828 A EP 09705828A EP 2242639 A2 EP2242639 A2 EP 2242639A2
Authority
EP
European Patent Office
Prior art keywords
fiber composite
fibers
composite component
electrically conductive
conductive fibers
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP09705828A
Other languages
German (de)
English (en)
Inventor
Hauke Lengsfeld
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations GmbH
Original Assignee
Airbus Operations GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Operations GmbH filed Critical Airbus Operations GmbH
Publication of EP2242639A2 publication Critical patent/EP2242639A2/fr
Withdrawn legal-status Critical Current

Links

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
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/88—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
    • B29C70/882—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 partly or totally electrically conductive, e.g. for EMI shielding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/88—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
    • B29C70/882—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 partly or totally electrically conductive, e.g. for EMI shielding
    • B29C70/885—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 partly or totally electrically conductive, e.g. for EMI shielding with incorporated metallic wires, nets, films or plates
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
    • 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
    • B64D43/00—Arrangements or adaptations of instruments
    • 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
    • Y02T50/40—Weight reduction

Definitions

  • Fiber composite component for an aircraft or spacecraft
  • the present invention relates to a fiber composite component for an aircraft or spacecraft.
  • CFRP carbon fiber plastic
  • fiber composite components are widely used in aircraft construction. They are produced, for example, by vacuum infusion processes for introducing a matrix, for example an epoxy resin, into semi-finished fiber products and subsequent curing. Infusion methods may be cost effective over other known methods of making fiber composite components, such as the prepreg method, because this allows for the use of less expensive semi-finished fiber products.
  • a matrix for example an epoxy resin
  • Certain areas such as tread lobes or wing leading edges and / or surfaces of the wings, may freeze under certain environmental conditions and significantly alter the buoyancy and weight of the aircraft.
  • Measures against icing are, for example, systems that have a profile nose with inflatable areas for breaking off icing.
  • Other devices use electrical heating elements that are powered either directly or indirectly (inductively) with electrical energy.
  • Still other solutions are to heat air through a variety of Blow openings in the component onto the surface. All these solutions have in common that they add on the one hand additional weight through cables and devices to the aircraft and / or on the other hand cause additional costs in the production.
  • the object of the present invention is to provide a fiber composite component in order to remedy or substantially reduce the abovementioned disadvantages.
  • a fiber composite component for an aircraft or spacecraft is provided with at least partially arranged electrically conductive fibers.
  • the electrically conductive fibers may be coupled to an electrical energy source for current application to heat the fibers and / or to measure the electrical resistance of the fibers.
  • a basic idea of the invention is to use carbon fibers, natural fibers, boron fibers and / or glass fibers, which are coated with a metallic layer, as conductive material in prepreg or infusion components. Due to the metallization, the fibers have good electrical conductivity.
  • the material can be processed in tape laying processes (ATL, AFP), which are also used with other materials for the fiber composite component.
  • the electrical energy source can be designed to provide a previously determinable electrical power for heating the at least partially electrically conductive fibers.
  • the electrical energy can be taken from the on-board power supply of the aircraft or spacecraft.
  • an indirect coupling of the electrical energy source with the at least partially electrically conductive fibers is possible by means of an inductive coupling having, for example, induction loop lines, which are installed on or in the fiber composite component with ..
  • the electrical energy source can be designed to provide a previously determinable measurement current and / or a previously determinable measurement voltage and be coupled to a measuring device for measuring external force effects caused length changes of at least partially electrically conductive fibers.
  • a measuring device for measuring external force effects caused length changes of at least partially electrically conductive fibers.
  • the at least partially electrically conductive fibers are designed for coupling to a lightning protection system of an aircraft and spacecraft.
  • the metallized material can be offered in different basis weights just like today's prepreg or dry materials.
  • FIG. 1 is a perspective view of an embodiment of a fiber composite component according to the invention as a wing section of an aircraft or spacecraft.
  • 2 is an enlarged schematic sectional view taken along line AA of FIG. 1 ;
  • FIG 3 shows an enlarged cross-sectional view of an embodiment of an electrically conductive fiber with a metallic layer.
  • FIG. 1 shows a perspective view of an exemplary embodiment of a fiber composite component 1 according to the invention as the wing section of an aircraft or spacecraft (not shown).
  • the airfoil section has a specific profile in the illustrated cross-section 15 with a front edge 1 and a surface 3 surrounding the cross-section 15.
  • the wing section is completely surrounded by air during operation of the aircraft or spacecraft, with its front edge 2 and certain areas of its surface 3 can freeze under certain environmental conditions.
  • the fiber composite component 1 has in the associated surface 3 electrically conductive fibers 6 (see FIG 2), which are connected to an electrical energy source, for example the electrical system of the aircraft or spacecraft, for generating heat.
  • This connection can be switchable depending on the environmental conditions, for example, several parameters ⁇ air flow velocity, pressure and temperature) as an input. flow sizes are used.
  • connection can be made directly via connecting lines, not shown, or indirectly via an induction element 14, which is arranged within the fiber composite component 1 corresponding to the respective areas to be heated.
  • the electrically conductive fibers 6 in the respective regions can also be connected or connectable to an electrical energy source which is designed to supply a measuring current with which a resistance of electrically conductive fibers 6 can be measured.
  • the electrically conductive fibers 6 may be arranged in the longitudinal regions 11 in the longitudinal direction or in the transverse regions 12 in the transverse direction of the fiber composite component 1, in order to determine loads corresponding to these directions, which are generated by acting forces. These forces change their resistance by changing the length of the electrically conductive fibers 6, which can be used in a suitable connected measuring device with processing of the resistance values for the load indication of specific areas.
  • Fig. 2 is an enlarged schematic sectional view taken along line A-A of FIG. 1 of the fiber composite component 1 is illustrated.
  • the fiber composite component 1 consists of several layers, which are shown here schematically as lower standard layers 5 and upper layers 4 on the surface 3.
  • the electrically conductive fibers 6 extend in the upper layers in the longitudinal direction of the fiber composite component 1, as shown in Fig. 1. Other directions are of course possible. borrowed.
  • FIG. 3 An example of such an electrically conductive fiber 6 is shown in FIG. 3 in an enlarged cross section.
  • a fiber 7, for example made of carbon or glass, is coated with a layer of adhesion promoter 8, which ensures adhesion of a metallic layer 9 to the entire circumference of the fiber 7.
  • This metallic layer can be applied in different methods, which will not be explained here.
  • the material is preferably a metal or a metallic alloy with good electrical conductivity.
  • a microwave generator can also be used.
  • the electrically conductive fibers 6 can be arranged both unidirectional (UD tape) and in tissue formation. In a tissue resistance measurements are also possible in other directions relative to the longitudinal and transverse axis of the fiber composite component 1.
  • a good conductivity of the entire corresponding region in particular in the case of coupling to a lightning protection system, can be achieved in that the fibers 6 adjacent to each other and touching each other, which is also possible for example in a woven tape.
  • the electrically conductive fibers 6 can also be arranged additionally or only within the standard layers 5 or on the inner surface of the fiber composite component 1. In slats and flaps offer the electrically conductive fibers 6 special weight and space advantages.
  • a fiber composite component 1 for an aircraft or spacecraft which at least partially has electrically conductive fibers 6, the fibers 6 are coupled to an electrical energy source for a current supply for heating the fibers 6 and / or for measuring the electrical resistance of the fibers 6 ,

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Laminated Bodies (AREA)
  • Reinforced Plastic Materials (AREA)
  • Woven Fabrics (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

L'invention concerne un élément composite renforcé par fibres (1) pour aéronef ou vaisseau spatial, qui présente des fibres électroconductrices (6), au moins par sections. Lesdites fibres (6) sont couplées à une source d'énergie électrique pour assurer une sollicitation en courant afin de chauffer les fibres (6) et/ou pour mesurer la résistance électrique des fibres (6).
EP09705828A 2008-01-29 2009-01-20 Élément composite renforcé par fibres pour aéronef ou vaisseau spatial Withdrawn EP2242639A2 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US2428408P 2008-01-29 2008-01-29
DE102008006523A DE102008006523A1 (de) 2008-01-29 2008-01-29 Faserverbundbauteil für ein Luft- oder Raumfahrzeug
PCT/EP2009/050600 WO2009095335A2 (fr) 2008-01-29 2009-01-20 Élément composite renforcé par fibres pour aéronef ou vaisseau spatial

Publications (1)

Publication Number Publication Date
EP2242639A2 true EP2242639A2 (fr) 2010-10-27

Family

ID=40794520

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09705828A Withdrawn EP2242639A2 (fr) 2008-01-29 2009-01-20 Élément composite renforcé par fibres pour aéronef ou vaisseau spatial

Country Status (9)

Country Link
US (1) US9669937B2 (fr)
EP (1) EP2242639A2 (fr)
JP (1) JP2011511732A (fr)
CN (1) CN101970217A (fr)
BR (1) BRPI0907617A2 (fr)
CA (1) CA2712374A1 (fr)
DE (1) DE102008006523A1 (fr)
RU (1) RU2010133888A (fr)
WO (1) WO2009095335A2 (fr)

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US9004407B2 (en) * 2008-12-24 2015-04-14 Middle River Aircraft Systems Anti-icing system and method for preventing ice accumulation
US8231080B2 (en) 2009-02-26 2012-07-31 The Boeing Company Distributing power in systems having a composite structure
DE102011119844A1 (de) 2011-05-26 2012-12-13 Eads Deutschland Gmbh Verbundstruktur mit Eisschutzvorrichtung sowie Herstellverfahren
DE102012002132A1 (de) 2012-02-03 2013-08-08 Airbus Operations Gmbh Vereisungsschutzsystem für ein Flugzeug und Verfahren zum Betreiben eines Vereisungsschutzsystems
FR2988639B1 (fr) 2012-04-02 2014-06-13 Hexcel Reinforcements Materiau aux proprietes de conductivite ameliorees pour la realisation de pieces composites en association avec une resine
US9072184B2 (en) 2012-10-24 2015-06-30 The Boeing Company Carbon fiber spacecraft panel with integral metallic foil power return
GB2513652A (en) * 2013-05-03 2014-11-05 Rolls Royce Plc Vehicle composite structure
US9463879B2 (en) * 2014-03-03 2016-10-11 The Boeing Company Systems and methods for predicting and controlling ice formation
GB2531522B (en) * 2014-10-20 2018-05-09 Bae Systems Plc Strain sensing in composite materials
FR3028205B1 (fr) * 2014-11-10 2018-01-05 Airbus Operations Procede de fabrication d'un panneau en materiau composite integrant une protection contre la foudre et panneau en materiau composite fabrique selon ledit procede
DE102015112302A1 (de) 2015-07-28 2017-02-02 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Verfahren und Vorrichtung zur Herstellung eines Halbzeugs
CN107323648A (zh) * 2017-06-22 2017-11-07 中国航空工业集团公司沈阳飞机设计研究所 复合材料飞机的传导金属网络
FR3081367A1 (fr) * 2018-05-24 2019-11-29 Airbus Operations Procede d'assemblage par soudage d'au moins deux pieces en materiau composite et assemblage de pieces en materiau composite ainsi obtenu
CN111731485B (zh) * 2020-07-03 2021-09-03 中国空气动力研究与发展中心低速空气动力研究所 一种自主间歇式除冰装置及其安装方法和除冰方法

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Also Published As

Publication number Publication date
WO2009095335A2 (fr) 2009-08-06
US20110114895A1 (en) 2011-05-19
BRPI0907617A2 (pt) 2015-07-21
RU2010133888A (ru) 2012-03-10
US9669937B2 (en) 2017-06-06
CN101970217A (zh) 2011-02-09
WO2009095335A4 (fr) 2009-11-19
CA2712374A1 (fr) 2009-08-06
DE102008006523A1 (de) 2009-07-30
JP2011511732A (ja) 2011-04-14
WO2009095335A3 (fr) 2009-09-24

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