EP2242639A2 - Fiber composite part for an aircraft or spacecraft - Google Patents

Fiber composite part for an aircraft or spacecraft

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Withdrawn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)
French (fr)
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/en
Withdrawn legal-status Critical Current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)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace 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

Disclosed is a fiber composite part (1) for an aircraft or spacecraft, comprising electrically conductive fibers (6) in at least some sections. The fibers (6) are coupled to an electric power source to apply electricity in order to heat the fibers (6) and/or measure the electric resistance of the fibers (6).

Description

Faserverbundbauteil für ein Luft- oder Raumfahrzeug Fiber composite component for an aircraft or spacecraft
Die vorliegende Erfindung bezieht sich auf ein Faserverbundbauteil für ein Luft- oder Raumfahrzeug.The present invention relates to a fiber composite component for an aircraft or spacecraft.
Obwohl auf beliebige Faserverbundbauteile anwendbar, werden die vorliegende Erfindung sowie die ihr zugrunde liegende Problematik nachfolgend mit Bezug auf Kohlefaserkunststoff (CFK) -Bauteile (auch als Faserverbundbauteile bezeichnet), beispielsweise Rumpf, Flügel, Seitenleitwerk eines Flugzeugs, näher erläutert.Although applicable to any fiber composite component, the present invention and the problem underlying it will be explained in more detail below with reference to carbon fiber plastic (CFRP) components (also referred to as fiber composite components), for example, fuselage, wing, fin of an aircraft.
Die Verwendung von Faserverbundbauteilen ist im Flugzeugbau weit verbreitet. Sie werden zum Beispiel durch Vakuuminfusionsverfahren zum Einbringen einer Matrix, beispielsweise eines Epoxidharzes, in Faserhalbzeuge und nachfolgendem Härten hergestellt. Infusionsverfahren können gegenüber anderen bekannten Verfahren zur Herstellung von Faserverbundbauteilen, wie beispielsweise dem Prepreg-Verfahren, kostengünstig sein, weil dies die Verwendung von kostengünstigeren Faserhalbzeugen erlaubt.The use of fiber composite components is 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.
Bestimmte Bereiche, wie beispielsweise Profilnasen bzw. Flügelvorderkanten und/oder Oberflächen der Flügel, können bei bestimmten Umgebungsbedingungen vereisen und den Auftrieb und das Gewicht des Luftfahrzeugs erheblich verändern. Maßnahmen gegen Vereisung sind zum Beispiel unter anderem Systeme, die eine Profilnase mit aufblasbaren Bereichen zum Absprengen von Vereisungen besitzen. Andere Vorrichtungen verwenden elektrische Heizelemente, die entweder direkt oder indirekt (induktiv) mit elektrischer Energie versorgt werden. Noch weitere Lösungen bestehen darin, Warmluft durch eine Vielzahl von Öffnungen in dem Bauteil auf die Oberfläche auszublasen. All diesen Lösungen ist gemein, dass sie einerseits zusätzliches Gewicht durch Zuleitungen und Vorrichtungen dem Luftfahrzeug zufügen und/oder andererseits Zusatzkosten bei der Herstellung verursachen.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.
Vor diesem Hintergrund liegt der vorliegenden Erfindung die Aufgabe zugrunde, ein Faserverbundbauteil bereitzustellen, um die oben genannten Nachteile zu beheben bzw. erheblich zu reduzieren.Against this background, the object of the present invention is to provide a fiber composite component in order to remedy or substantially reduce the abovementioned disadvantages.
Erfindungsgemäß wird diese Aufgabe durch ein Faserverbundbauteil mit den Merkmalen des Patentanspruchs 1 gelöst.According to the invention, this object is achieved by a fiber composite component having the features of patent claim 1.
Demgemäß wird ein Faserverbundbauteil für ein Luft- oder Raumfahrzeug mit zumindest abschnittsweise angeordneten elektrisch leitfähigen Fasern bereitgestellt. Die elektrisch leitfähigen Fasern können für eine Strombeaufschlagung zur Erwärmung der Fasern und/oder zur Messung des elektrischen Widerstands der Fasern mit einer elektrischen Energiequelle gekoppelt sein.Accordingly, 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.
In den Unteransprüchen finden sich vorteilhafte Ausgestaltungen und Verbesserungen der vorliegenden Erfindung.In the dependent claims are advantageous embodiments and improvements of the present invention.
Eine grundlegende Idee der Erfindung besteht darin, Kohlenstofffasern, Naturfasern, Borfasern und/oder Glasfasern, die mit einer metallischen Schicht überzogen sind, als leitfähiges Material in Prepreg- oder Infusionsbauteilen einzusetzen. Auf Grund der Metallisierung weisen die Fasern gute elektrische Leitfähigkeit auf. Das Material kann in Tapelegeprozes- sen (ATL, AFP) verarbeitet werden, die auch mit anderem Material für das Faserverbundbauteil Verwendung finden.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.
Somit weist die vorliegende Erfindung gegenüber den eingangs genannten Ansätzen unter anderem den Vorteil auf, dass der extrem dünne metallische Überzug Gewichtsvorteile bietet. Die elektrische Energiequelle kann zur Bereitstellung einer vorher festlegbaren elektrischen Leistung zur Erwärmung der zumindest abschnittsweise elektrisch leitfähigen Fasern ausgelegt sein. Zum Beispiel kann die elektrische Energie der Bordenergieversorgung des Luft- oder Raumfahrzeugs entnommen werden. Auch eine indirekte Kopplung der elektrischen Energiequelle mit den zumindest abschnittsweise elektrisch leitfähigen Fasern ist mittels einer induktiven Kopplung möglich, welche zum Beispiel Induktionsschleifenleitungen aufweist, die an oder in dem Faserverbundbauteil mit installiert sind..Thus, the present invention over the approaches mentioned above, inter alia, has the advantage that the extremely thin metallic coating offers weight advantages. The electrical energy source can be designed to provide a previously determinable electrical power for heating the at least partially electrically conductive fibers. For example, the electrical energy can be taken from the on-board power supply of the aircraft or spacecraft. Also, 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 ..
Die elektrische Energiequelle kann zur Bereitstellung eines vorher festlegbaren Messstroms und/oder einer vorher festlegbaren MessSpannung ausgebildet und mit einer Messeinrichtung zur Messung von äußeren Krafteinwirkungen bewirkten Längenänderungen der zumindest abschnittsweise elektrisch leitfähigen Fasern gekoppelt sein. So ist es möglich, je nach Anschluss und Anordnung der leitfähigen Fasern in dem Faserverbundbauteil, den Widerstand des Metallüberzugs der leitfähigen Fasern in Abhängigkeit von einer aufgebrachten Kraft bei Betrieb des Luft- oder Raumfahrzeugs in allen Betriebszuständen zu messen und daraus zum Beispiel die Belastung des Bauteils bzw. bestimmter Abschnitte des Bauteils zu beurteilen, dem Luftfahrzeugführen anzuzeigen und/oder automatisch geeignete Maßnahmen zur Beherrschung der jeweiligen Belastungssituation einzuleiten.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. Thus, it is possible, depending on the connection and arrangement of the conductive fibers in the fiber composite component, to measure the resistance of the metal coating of the conductive fibers in response to an applied force during operation of the aircraft or spacecraft in all operating conditions and, for example, the load on the component or to assess certain sections of the component, to indicate to the aircraft operator and / or to automatically initiate suitable measures for controlling the respective load situation.
In einer alternativen Ausführung ist es vorgesehen, dass die zumindest abschnittsweise elektrisch leitfähigen Fasern zur Ankopplung an ein Blitzschutzsystem eines Luft- und Raumfahrzeugs ausgebildet sind.In an alternative embodiment, it is provided that the at least partially electrically conductive fibers are designed for coupling to a lightning protection system of an aircraft and spacecraft.
Nach heutigem Stand der Technik wird zum Blitzschutz bei Luft- oder Raumfahrzeugen mit derartigen Verbundbauteilen ein mit Harz vorimprägniertes Kupfer- oder Bronzemesh oder -folie als erste Lage in das Verbundbauteil eingebracht. EP 0 248 122 Bl gibt dazu Beispiele an. Bei Prepregbauteilen macht sich die Dicke des Materials {im Vergleich zum Kohlefaser- Prepreg) insbesondere bei Überlappungen negativ bemerkbar. Hier kommt es vielfach zur Ausbildung von Falten oder Wellen, die zu Nacharbeiten führen. Hinzu kommt das relativ hohe Gewicht des Mesh. Die Handhabung des Mesh-Materials erfordert besondere Umsicht, da ein Knicken oder Aufrollen größerer Zuschnitte ebenfalls zu massiven Wellen im Bauteil führen kann. Das Material kann bisher nur von Hand verarbeitet werden. Durch die vorliegende Erfindung können diese Nachteile überwunden werden.According to the current state of the art, for lightning protection in aircraft or spacecraft with such composite components, a resin or preimpregnated copper or bronze mesh or foil is introduced as the first layer into the composite component. EP 0 248 122 B1 gives examples of this. When making prepreg components The thickness of the material (in comparison to the carbon fiber prepreg), especially in overlapping negative impact. Here it often comes to the formation of wrinkles or waves that lead to rework. Add to that the relatively high weight of the mesh. The handling of the mesh material requires special care, since a buckling or rolling larger blanks can also lead to massive waves in the component. So far, the material can only be processed by hand. By the present invention, these disadvantages can be overcome.
Ferner ist eine Kombination von Gewebe- oder UD-Prepreg mit metallisierten Fasern auf der Oberfläche des Verbundbauteils denkbar. So kann Strukturfestigkeit über das Langfasermaterial, gute Leitfähigkeit für Erwärmung, gute Verteilung der Blitzschlagenergie im Falle eines Anschlusses an ein Blitzschutzsystem, und durch unterschiedliche Ausrichtung der elektrisch leitfähigen Fasern in Bezug auf Längs- und Querachsen des Faserverbundbauteils eine Belastung desselben über den Widerstand der metallischen Schichten der Fasern in unterschiedlichen Richtungen ermittelt werden.Furthermore, a combination of woven or UD prepreg with metallized fibers on the surface of the composite component is conceivable. Thus, structural strength over the long fiber material, good conductivity for heating, good distribution of lightning impact energy in the case of connection to a lightning protection system, and different orientation of the electrically conductive fibers with respect to longitudinal and transverse axes of the fiber composite component, may stress it over the resistance of the metallic layers the fibers are determined in different directions.
Genauso ist eine Kombination mit Glasgeweben möglich. Das metallisierte Material kann genau wie heutige Prepreg- oder Trockenmaterialien in verschiedenen Flächengewichten angeboten werden.Likewise, a combination with glass fabrics is possible. The metallized material can be offered in different basis weights just like today's prepreg or dry materials.
Die Erfindung wird im Folgenden anhand von Ausführungsbeispielen unter Bezugnahme auf die beiliegenden Figuren der Zeichnung näher erläutert.The invention is explained in more detail below on the basis of exemplary embodiments with reference to the accompanying figures of the drawing.
Von den Figuren zeigen:From the figures show:
Fig. 1 eine perspektivische Ansicht eines Ausführungsbeispiels eines erfindungsgemäßen Faserverbundbauteils als Tragflächenabschnitt eines Luftoder Raumfahrzeugs ; Fig. 2 eine vergrößerte schematisierte Schnittansicht längs Linie A-A nach Fig . 1 ; und1 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 ; and
Fig. 3 eine vergrößerte Querschnittsansicht eines Aus- führυngsbeispiels einer elektrisch leitfähigen Faser mit einer metallischen Schicht.3 shows an enlarged cross-sectional view of an embodiment of an electrically conductive fiber with a metallic layer.
In den Figuren bezeichnen dieselben Bezugszeichen gleiche oder funktionsgleiche Komponenten, soweit nichts Gegenteiliges angegeben ist.In the figures, the same reference numerals designate the same or functionally identical components, unless indicated otherwise.
Fig. 1 zeigt eine perspektivische Ansicht eines Ausführungs- beispiels eines erfindungsgemäßen Faserverbundbauteils 1 als Tragflächenabschnitt eines Luft- oder Raumfahrzeugs (nicht dargestellt) .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).
Der Tragflächenabschnitt weist ein bestimmtes Profil im gezeigten Querschnitt 15 mit einer Vorderkante 1 und einer um den Querschnitt 15 umlaufenden Oberfläche 3 auf. Der Tragflächenabschnitt wird bei Betrieb des Luft- oder Raumfahrzeugs vollständig von Luft umströmt, wobei seine Vorderkante 2 und bestimmte Bereiche seiner Oberfläche 3 bei bestimmten Umgebungsbedingungen vereisen können. In diesen Bereichen, zum Beispiel in einem Anströmbereich 10 der Vorderkante 2 {im Querschnitt schraffiert) , einem oder mehreren Längs- oder Querbereichen 11, 12 oder in Bereichsfeldern 13, weist das Faserverbundbauteil 1 in der zugehörigen Oberfläche 3 elektrisch leitfähige Fasern 6 (siehe Fig. 2) auf, die mit einer elektrischen Energiequelle, zum Beispiel dem elektrischen Bordnetz des Luft- oder Raumfahrzeugs, zur Erzeugung von Wärme in Verbindung stehen.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. In these regions, for example in an approach region 10 of the front edge 2 (hatched in cross-section), one or more longitudinal or transverse regions 11, 12 or in region fields 13, 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.
Diese Verbindung kann in Abhängigkeit von den Umgebungsbedingungen schaltbar sein, wobei zum Beispiel mehrere Parameter {Luftströmungsgeschwindigkeit, Druck und Temperatur) als Ein- flussgrößen verwendet werden.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.
Diese Verbindung kann direkt über nicht gezeigte Anschluss- leitungen oder indirekt über ein Induktionseiement 14 erfolgen, welches innerhalb des Faserverbundbauteils 1 korrespondierend zu den jeweiligen zu erwärmenden Bereichen angeordnet ist.This 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.
Die elektrisch leitfähigen Fasern 6 (siehe Fig. 2) in den jeweiligen Bereichen können auch mit einer elektrischen Energiequelle verbunden bzw. verbindbar sein, die zur Lieferung eines Messstroms ausgebildet ist, mit welchem ein Widerstand elektrisch leitfähiger Fasern 6 messbar ist. Dazu können die elektrisch leitfähigen Fasern 6 in den Längsbereichen 11 in Längsrichtung oder in den Querbereichen 12 in Querrichtung des Faserverbundbauteils 1 angeordnet sein, um korrespondierend zu diesen Richtungen Belastungen zu ermitteln, die durch angreifende Kräfte erzeugt werden. Diese Kräfte verändern durch Veränderung der Länge der elektrisch leitfähigen Fasern 6 deren Widerstand, was in einer geeigneten angeschlossenen Meεseinrichtung mit Verarbeitung der Widerstandswerte zur Belastungsanzeige bestimmter Bereiche benutzt werden kann.The electrically conductive fibers 6 (see FIG. 2) 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. For this purpose, 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.
Es können hierzu auch einzelne Teilbereiche, die hier nur schematisch als Bereichsfelder 13 angedeutet sind, verwendet werden .For this purpose, it is also possible to use individual subregions, which are only schematically indicated here as range arrays 13.
In Fig. 2 ist eine vergrößerte schematisierte Schnittansicht längs Linie A-A nach Fig. 1 des Faserverbundbauteils 1 illustriert .In Fig. 2 is an enlarged schematic sectional view taken along line A-A of FIG. 1 of the fiber composite component 1 is illustrated.
Das Faserverbundbauteil 1 besteht aus mehreren Schichten, die hier schematisch als untere Standardschichten 5 und Oberschichten 4 an der Oberfläche 3 dargestellt sind. Die elektrisch leitfähigen Fasern 6 verlaufen in den Oberschichten in Längsrichtung des Faserverbundbauteils 1, wie in Fig. 1 dargestellt ist. Andere Richtungen sind selbstverständlich mög- lieh.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.
Ein Beispiel einer derartigen elektrisch leitfähigen Faser 6 zeigt Fig. 3 in einem vergrößerten Querschnitt. Eine Faser 7, zum Beispiel aus Kohlenstoff oder Glas, ist mit einer Schicht aus Haftvermittler 8 beschichtet, welcher eine Anhaftung einer metallischen Schicht 9 an dem gesamten Umfang der Faser 7 sicherstellt. Diese metallische Schicht kann in unterschiedlichen Verfahren aufgebracht werden, die hier nicht erläutert werden sollen. Das Material ist vorzugsweise ein Metall oder eine metallische Legierung mit guten elektrischen Leiteigenschaften.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.
Obwohl die vorliegende Erfindung anhand bevorzugter Ausführungsbeispiele vorliegend beschrieben wurde, ist sie darauf nicht beschränkt, sondern auf vielfältige Weise modifizierbar.Although the present invention has been described in terms of preferred embodiments herein, it is not limited thereto, but modifiable in a variety of ways.
Beispielsweise kann anstelle des Induktionselementes auch ein Mikrowellengenerator Verwendung finden.For example, instead of the induction element, a microwave generator can also be used.
Die elektrisch leitfähigen Fasern 6 können sowohl unidirekti- onal (UD~Tape) als auch in Gewebeformation angeordnet sein. Bei einem Gewebe sind Widerstandsmessungen auch in anderen Richtungen relativ zur Längs- und Querachse des Faserverbundbauteils 1 möglich.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.
Eine gute Leitfähigkeit des gesamten korrespondierenden Bereiches, insbesondere im Fall von Ankopplung an ein Blitzschutzsystem, kann dadurch erreicht werden, dass sich die Fasern 6 nebeneinander und übereinander berühren, was auch zum Beispiel bei einem gewebten Band möglich ist.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.
Die elektrisch leitfähigen Fasern 6 können auch zusätzlich oder nur innerhalb der Standardschichten 5 oder an der Innenfläche des Faserverbundbauteils 1 angeordnet sein. Bei Vorflügeln und Klappen bieten den elektrisch leitfähigen Fasern 6 besondere Gewichts- und Raumvorteile.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.
Bei einem Faserverbundbauteil 1 für ein Luft- oder Raumfahrzeug, welches zumindest abschnittsweise elektrisch leitfähige Fasern 6 aufweist, sind die Fasern 6 für eine Strombeauf- schlagung zur Erwärmung der Fasern 6 und/oder zur Messung des elektrischen Widerstands der Fasern 6 mit einer elektrischen Energiequel1e gekoppelt . In 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 ,
B e z u g s z e i c h e n l i s t eC o m p a n c e m e n t i o n s
Faserverbundbauteil Vorderkante Oberfläche Oberschichten Standardschichten Elektrisch leitfähige Fasern Faser Haftvermittler Metallische Schicht Anströmbereich Längsbereich Querbereich Bereichsfeld Induktionselement Querschnitt Fiber composite component Front edge Surface Top layers Standard layers Electrically conductive fibers Fiber Adhesive Metallic layer Inflow area Longitudinal area Transverse area Range field Induction element Cross section

Claims

P a t e n t a n s p r ü c h e Patent claims
1. Faserverbundbauteil (1) für ein Luft- oder Raumfahrzeug, welches elektrisch leitfähige Fasern (6) zumindest abschnittsweise aufweist, die für eine Strombeaufschlagung zur Erwärmung der Fasern (6) und/oder zur Messung des elektrischen Widerstands der Fasern (6) mit einer elektrischen Energiequelle gekoppelt sind.1. fiber composite component (1) for an aircraft or spacecraft, which electrically conductive fibers (6) at least in sections, which for a current application for heating the fibers (6) and / or for measuring the electrical resistance of the fibers (6) with a electrical energy source are coupled.
2. Faserverbundbauteil (1) nach Anspruch 1, dadurch gekennzeichnet , dass die Fasern (6) aus einem elektrisch leitfähigen Material bestehen und/oder mit einer metallischen Schicht (9) überzogen sindSecond fiber composite component (1) according to claim 1, characterized in that the fibers (6) consist of an electrically conductive material and / or with a metallic layer (9) are coated
3. Faserverbundbauteil (1) nach Anspruch 2, dadurch gekennzeichnet , dass die Fasern (6) Kohlenstofffasern, Naturfasern, Borfasern und/oder Glasfasern aufweisen.3. fiber composite component (1) according to claim 2, characterized in that the fibers (6) carbon fibers, natural fibers, boron fibers and / or glass fibers.
4. Faserverbundbauteil (1) nach zumindest einem der vorhergehenden Ansprüche, dadurch gekennzeichnet , dass die elektrische Energiequelle zur Bereitstellung einer vorher festlegbaren elektrischen Leistung zur Erwärmung der zumindest abschnittsweise elektrisch leitfähigen Fasern (6) ausgelegt ist.4. fiber composite component (1) according to at least one of the preceding claims, characterized in that the electrical energy source for providing a previously determinable electrical power for heating the at least partially electrically conductive fibers (6) is designed.
5. Faserverbundbauteil (1) nach Anspruch 4, dadurch gekennzeichnet , dass die indirekte Kopplung der elektrischen Energiequelle mit den zumindest abschnittsweise elektrisch leitfähigen Fasern (6) eine induktive Kopplung ist. 5. fiber composite component (1) according to claim 4, characterized in that the indirect coupling of the electrical energy source with the at least partially electrically conductive fibers (6) is an inductive coupling.
6. Faserverbundbauteil (1) nach zumindest einem der vorhergehenden Ansprüche, dadurch gekennzeichnet , dass die elektrische Energiequelle zur Bereitstellung eines vorher festlegbaren Messstroms und/oder einer vorher festlegbaren Messspannung ausgebildet ist.6. fiber composite component (1) according to at least one of the preceding claims, characterized in that the electrical energy source is designed to provide a previously determinable measuring current and / or a previously definable measuring voltage.
7. Faserverbundbauteil (1) nach Anspruch 6, dadurch gekennzeichnet , dass die elektrische Energiequelle mit einer Messeinrichtung zur Messung von äußeren Krafteinwirkungen bewirkten Längenänderungen der zumindest abschnittsweise elektrisch leitfähigen Fasern (6) gekoppelt ist.7. fiber composite component (1) according to claim 6, characterized in that the electrical energy source with a measuring device for measuring external force effects caused length changes of at least partially electrically conductive fibers (6) is coupled.
8. Faserverbundbauteil (1) nach Anspruch 7, dadurch gekennzeichnet , dass die Messeinrichtung zur Widerstandsmessung der metallischen Schichten (9) der Fasern (6) ausgebildet ist,8. fiber composite component (1) according to claim 7, characterized in that the measuring device for measuring the resistance of the metallic layers (9) of the fibers (6) is formed,
9. Faserverbundbauteil (1) nach zumindest einem der vorhergehenden Ansprüche, dadurch gekennzeichnet , dass die zumindest abschnittsweise elektrisch leitfähigen Fasern (6) zur Ankopplung an ein Blitzschutzsystem eines Luft- und Raumfahrzeugs ausgebildet sind.9. fiber composite component (1) according to at least one of the preceding claims, characterized in that the at least partially electrically conductive fibers (6) are designed for coupling to a lightning protection system of an aircraft and spacecraft.
10. Faserverbundbauteil (1) nach zumindest einem der vorhergehenden Ansprüche, dadurch gekennzeichnet , dass die zumindest abschnittsweise elektrisch leitfähigen Fasern (1) zumindest teilweise in Oberschichten (4) des Faserverbundbauteils (1) angeordnet sind.10. fiber composite component (1) according to at least one of the preceding claims, characterized in that the at least partially electrically conductive fibers (1) at least partially in upper layers (4) of the fiber composite component (1) are arranged.
11. Faserverbundbauteil (1) nach zumindest einem der vorhergehenden Ansprüche, dadurch gekennzeichnet , dass das Faserverbundbauteil (1) aus Prepreg- und/oder Infusionsbauteilen hergestellt ist, die zumindest abschnittsweise elektrisch leitfähigen Fasern (6) als uni- direktionales Band oder/und Gewebeband aufweisen. 11. fiber composite component (1) according to at least one of the preceding claims, characterized in that the fiber composite component (1) of prepreg and / or Infusionsbauteilen is made, at least in sections electrically conductive fibers (6) as a unidirectional tape and / or fabric tape.
EP09705828A 2008-01-29 2009-01-20 Fiber composite part for an aircraft or spacecraft Withdrawn EP2242639A2 (en)

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US2428408P 2008-01-29 2008-01-29
DE102008006523A DE102008006523A1 (en) 2008-01-29 2008-01-29 Fiber composite component for an aircraft or spacecraft
PCT/EP2009/050600 WO2009095335A2 (en) 2008-01-29 2009-01-20 Fiber composite part for an aircraft or spacecraft

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BR (1) BRPI0907617A2 (en)
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JP2011511732A (en) 2011-04-14
DE102008006523A1 (en) 2009-07-30
CN101970217A (en) 2011-02-09
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CA2712374A1 (en) 2009-08-06
RU2010133888A (en) 2012-03-10
WO2009095335A3 (en) 2009-09-24

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