METHOD FOR BONDING TWO FIBER COMPOSITE COMPONENTS WITH EACH OTHER TO FORM A FIBER COMPOSITE STRUCTURE

Abstract

A method for bonding two fiber composite components with each other to form a fiber composite structure includes integrating conductive fibers underneath a bonding surface of at least one of the two fiber composite components, each conductive fiber comprising a carbon fiber coated with an electrically insulating coating, the conductive fibers running along the bonding surface and protruding at least at their ends from the respective fiber composite component; arranging the two fiber composite components against each other at their respective bonding surfaces; passing an electric current through the conductive fibers by electrically contacting the conductive fibers at their protruding ends so that the respective fiber composite component is heated at the bonding surface to a curing temperature; and joining the two fiber composite components with each other at their bonding surfaces via secondary bonding, co-bonding and/or co-curing at the curing temperature, thereby forming the fiber composite structure.

Claims

1. A method for bonding two fiber composite components with each other to form a fiber composite structure of an aircraft, comprising: integrating conductive fibers underneath a bonding surface of at least one of the two fiber composite components, each conductive fiber comprising a carbon fiber coated with an electrically insulating coating, the conductive fibers running along the bonding surface and protruding at least at their ends from the respective fiber composite component; arranging the two fiber composite components against each other at their respective bonding surfaces; passing an electric current through the conductive fibers by electrically contacting the conductive fibers at their protruding ends so that the respective fiber composite component is heated at the bonding surface to a curing temperature; and joining the two fiber composite components with each other at their bonding surfaces via secondary bonding, co-bonding and/or co-curing at the curing temperature, thereby forming the fiber composite structure.

2. The method according to claim 1, wherein the electrically insulating coating is a polymer electrolyte coating.

3. The method according to claim 1, wherein joining comprises pressing the two fiber composite components against each other at the bonding surfaces.

4. The method according to claim 1, wherein arranging comprises providing an adhesive between the bonding surfaces.

5. The method according to claim 1, wherein the conductive fibers are arranged in a form of at least one of single fibers, bundles, tapes, scrims, mats, woven fabrics and fleece.

6. The method according to claim 1, further comprising: measuring the curing temperature; and controlling the electric current based on the measured curing temperature.

7. The method according to claim 6, wherein the curing temperature is measured with at least one of a thermographic camera and a temperature sensor integrated in at least one of the fiber composite components.

8. The method according to claim 1, wherein the curing temperature is below 150° C.

9. A fiber composite structure manufactured with a method according to claim 1.

10. An aircraft comprising a fiber composite structure according to claim 9.

11. A fiber composite component for use in a method according to claim 1, comprising: a plurality of conductive fibers integrated underneath a bonding surface of the fiber composite component, each conductive fiber comprising a carbon fiber coated with an electrically insulating coating, the conductive fibers running along the bonding surface and protruding at least at their ends from the fiber composite component, wherein the fiber composite component is formed with a matrix material at least at the bonding surface curable under application of a curing temperature.

12. The fiber composite component according to claim 11, wherein the electrically insulating coating is a polymer electrolyte coating.

13. The fiber composite component according to claim 11, wherein the conductive fibers are arranged in a form of at least one of single fibers, bundles, tapes, scrims, mats, woven fabrics and fleece.

14. The fiber composite component according to claim 11, further comprising an integrated temperature sensor configured to measure the curing temperature.

15. The fiber composite component according to claim 11, wherein the curing temperature is below 150° C.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0033] The invention will be explained in greater detail with reference to exemplary embodiments depicted in the drawings as appended.

[0034] The accompanying drawings are included to provide a further understanding of the present invention and are incorporated in and constitute a part of this specification. The drawings illustrate the embodiments of the present invention and together with the description serve to explain the principles of the invention. Other embodiments of the present invention and many of the intended advantages of the present invention will be readily appreciated as they become better understood by reference to the following detailed description. The elements of the drawings are not necessarily to scale relative to each other. In the figures, like reference numerals denote like or functionally like components, unless indicated otherwise.

[0035] FIG. 1 schematically depicts a cross-sectional view of a conductive fiber for use in a method for bonding two fiber composite components with each other according to an embodiment of the invention.

[0036] FIG. 2 shows two fiber composite components with integrated conductive fibers as shown in FIG. 1.

[0037] FIG. 3 is a schematic flow diagram of a method for bonding two fiber composite components with each other according to an embodiment of the invention.

[0038] FIG. 4 schematically shows a passenger aircraft having a fiber composite structure formed with the method of FIG. 3.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0039] Although specific embodiments are illustrated and described herein, it will be appreciated by those of ordinary skill in the art that a variety of alternate and/or equivalent implementations may be substituted for the specific embodiments shown and described without departing from the scope of the present invention. Generally, this application is intended to cover any adaptations or variations of the specific embodiments discussed herein.

[0040] FIG. 1 schematically depicts a cross-sectional view of a conductive fiber 2 for use in a method M for bonding two fiber composite components 1 with each other according to an embodiment of the invention.

[0041] The conductive fiber 2 comprises a carbon fiber 3, which is provided with an electrically insulating coating 4. The electrically insulating coating 4 of this embodiment is a solid polymer electrolyte coating. Such an electrochemical coating can be produced, for example, by immersing the carbon fiber 3 in a suitable electrochemical bath. In a specific example, the coating may be achieved by a polymerization of methoxypolyethylene glycol monomethacrylate. For example, the carbon fiber 3 may have a diameter between 6 and 7 microns. Such a solid polymer-electrolyte coating can be formed very thinly, for example, with a thickness of 0.5 micrometers, resulting in a total diameter of the conductive fiber 2 of about 7 to 8 micrometers. Furthermore, such a coating can withstand temperatures of several hundred degrees Celsius, making it suitable for providing in-situ thermal energy for curing adhesives and partially/semi-cured and/or uncured fiber composites in an out-of-autoclave process.

[0042] This configuration of the conductive fiber 2 offers several advantages for use in the manufacture of fiber composite structures by bonding. On the one hand, the conductive fiber 2 exhibits similar properties to an ordinary carbon fiber in structural terms as well as in terms of its compatibility with fiber composite material. For this reason, it can be readily used as a reinforcing fiber in fiber composite components or integrated into them without causing undesirable reactions. On the other hand, the solid polymer electrolyte coating is designed as an electrical insulator, which can electrically insulate a conductive fiber 2 from further conductive fibers 2 without leakage currents and/or short circuits occurring between several current-carrying and adjacent conductive fibers 2. Furthermore, such a conductive fiber 2 is sufficiently temperature resistant for the typical curing temperatures required to harden the materials typically used in out-of-autoclave bonding processes, in particular thermosetting polymers and the corresponding adhesives. In the following, with reference to the further figures, advantageous applications are explained that employ such conductive fibers 2 in a method M for bonding two fiber composite components 1 with each other to form a fiber composite structure 10.

[0043] FIG. 2 shows a schematic perspective view of two fiber composite components 1 with the conductive fibers 2 from FIG. 1. FIG. 3 depicts a schematic flow chart of a corresponding method M for bonding the two fiber composite components 1.

[0044] The two fiber composite components 1 may be formed from a matrix material, e.g., a thermosetting polymer like a thermoset epoxy, which embeds a plurality of reinforcement fibers, e.g., carbon fibers. The two fiber composite components 1 are shown in FIG. 2 purely schematically as identical rectangular blocks. In a specific application, the fiber composite components 1 may be, for example, structural components or parts of such components for the fuselage of an aircraft 100, e.g., a passenger aircraft (cf. FIG. 4). For example, one of the two components 1 may be a stringer, frame or other stiffening member, while the other component 1 may be an aircraft skin section. Both components 1 may be joined together in the form described herein to form a stiffened member-skin assembly, e.g., a stringer-skin assembly.

[0045] The fiber composite components 1 may be fully cured components, which means that the matrix material may be fully hardened. However, the fiber composite components 1 may also be partially cured, semi-cured and/or uncured, which means that the matrix material is not yet (fully) hardened and needs to undergo a curing process before the components 1 can be used in an aircraft assembly. In one example, one or both of the components 1 may be a laminate or pre-preg made from pre-impregnated fibers and a partially cured polymer matrix, such as epoxy or phenolic resin.

[0046] Besides the usual reinforcing fibers, both fiber composite components 1 include conductive fibers 2 as shown in FIG. 1, which are integrated underneath a respective bonding surface 6 of the fiber composite components 1. The conductive fibers 2 are oriented along the respective bonding surface 6 and protrude at both ends laterally from the respective fiber composite component 1 with respect to the bonding surface 6. This arrangement of the fiber composite components 1 and the conductive fibers 2 is to be understood purely as an example. In principle, it is left to the skilled person to introduce conductive fibers 2 as individual fibers, bundles, tapes, scrims, mats, woven fabrics and/or nonwovens or the like in a planar or other arrangement, depending on the application.

[0047] As can be seen in FIG. 2, the two fiber composite components 1 are arranged against each other at their respective bonding surfaces 6, wherein an adhesive, e.g., a temperature curable paste adhesive, is applied to at least one of the bonding surfaces 6 beforehand By contacting the laterals ends of the conductive fibers 2 with electrical cables from a current source, electric current may now be introduced in the conductive fibers, whereby the fiber composite components 1 may be heated up in a curing portion around the conductive fibers 2 by means of the Joule effect. By suitable control of the current, the curing temperature can be regulated precisely to heat-up the respective portions of the components 1 to the required temperature in a uniform way.

[0048] Depending on the type of component 1, various bonding processes may thus be realized. For example, in case both components are formed from fully hardened fiber-reinforced material, then they can be joined together at the bonding surfaces 6 by pressing them together and curing the adhesive 9 in between them (secondary bonding) Similarly, an uncured component 1 may be joined with a fully cured component 1 by means of an adhesive 9 and curing of both the adhesive 9 and the matrix material of the uncured component 1 (co-bonding). Finally, also two partially and/or uncured components 1 may be joined to each other, either with or without an additional adhesive, by heating up both components 1 to their respective curing temperature (co-curing).

[0049] Accordingly, the method M comprises under M1 (cf. FIG. 3) integrating conductive fibers 2 underneath a bonding surface 6 of at least one of the two fiber composite components 1, under M2 arranging the two fiber composite components 1 against each other at their respective bonding surfaces 6, under M3 passing an electric current through the conductive fibers 2 by electrically contacting the conductive fibers 2 at their protruding ends so that the respective fiber composite component 1 is heated at the bonding surface 6 to a curing temperature, and under M4 joining the two fiber composite components 1 with each other at their bonding surfaces 6 via secondary bonding, co-bonding and/or co-curing at the curing temperature, thereby forming the fiber composite structure 10.

[0050] For this purpose, for example, a power source can be connected to the conductive fibers 2 from outside the curing portion 5. The two fiber composite components 1 can additionally be pressed against each other with a force and/or pressure to support the bonding of the components and to achieve the most uniform temperature distribution possible or to guarantee that the fiber composite components 1 are in close contact over the entire joining area 6.

[0051] The method M can further comprise, under M5, measuring of the curing temperature and, under M4, controlling the electric current on the basis of the detected curing temperature. For this purpose, in this exemplary embodiment, a thermographic camera 7 is provided, e.g., a thermal imaging camera, which continuously detects the curing temperature so that the electric current can be adjusted locally or globally, if necessary, if there are deviations of the curing temperature from the desired temperature. Care must be taken to ensure that the curing temperature at least exceeds the minimal required temperature to harden the respectively used materials (adhesives and/or matrix materials). It is of course possible to set different curing temperatures, one after the other, or different temperatures in different portions of the components 1.

[0052] Alternatively, or additionally, the curing temperature can also be measured, for example, with temperature sensors 8, which are integrated in the fiber composite components 1 close to the conductive fibers 2 so that they can determine the temperature directly in the joining portions 5 close to the bonding surfaces 6.

[0053] As soon as the components 1 are joined to a fully cured composite structure 10, the projecting ends of the conductive fibers 2 may be cut off Such a fiber composite structure 10 can be, for example, a higher-level structural component for an aircraft 100. FIG. 4 shows an example of such an aircraft 100 in which a fiber composite structure 10 produced by the present method M is incorporated, e.g., a bulkhead, a stringer, a cross member, an outer skin section, a ceiling panel, a floor panel, and/or a wall panel, or the like.

[0054] With the aid of the method M described, it is thus possible to produce a fiber composite structure 10 from two fiber composite components 1 using an energy efficient and uncomplicated bonding process. The conductive fibers 2, which have a core of carbon fibers 3, serve here as current conductors (i.e., as resistance carriers for generating the curing heat), the individual conductive fibers 2 being insulated from one another due to the electrically insulating coating 4. This prevents leakage currents and undesirable heat losses. Carbon fibers 3 with a well-tolerated coating are used, which can be incorporated into the fiber composite components 1 without any unfavorable effects and, moreover, can be used to reinforce them.

[0055] In the foregoing detailed description, various features are grouped together in one or more examples or examples with the purpose of streamlining the disclosure. It is to be understood that the above description is intended to be illustrative, and not restrictive. It is intended to cover all alternatives, modifications and equivalents. Many other examples will be apparent to one skilled in the art upon reviewing the above specification. The embodiments were chosen and described in order to best explain the principles of the invention and its practical applications, to thereby enable others skilled in the art to best utilize the invention and various embodiments with various modifications as are suited to the particular use contemplated.

[0056] While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.

LIST OF REFERENCE SIGNS

[0057] 1 fiber composite component [0058] 2 conductive fiber [0059] 3 carbon fiber [0060] 4 electrically insulating coating [0061] 5 curing portion [0062] 6 bonding surface [0063] 7 thermographic camera [0064] 8 temperature sensor [0065] 9 adhesive [0066] 10 fiber composite structure [0067] 100 aircraft [0068] M method [0069] M1-M6 method steps