Method and device for joining components

Abstract

A method for joining a first and a second component, at least one of which comprises a fiber-reinforced plastics material. The components are arranged in relation to one another in such a way that a gap region remains between the first and the second component. The gap region is filled, at least in portions, with an uncured plastics material filler in which nanoparticles are dispersed. Energy is introduced locally into the nanoparticles in order to cure the plastics material filler. In another aspect, the invention provides a device for joining two components.

Claims

1. A method for tolerance compensation between a first and a second aircraft fuselage shell segment, at least one of which comprises a fiber-reinforced plastics material, comprising: arranging, after curing of the fiber-reinforced plastics material to a degree sufficient to make a complete aircraft fuselage cell, the aircraft fuselage shell segments in relation to one another while leaving a gap region having a width of at least 0.3 mm between the first and the second aircraft fuselage shell segment; filling the gap region, at least in portions, with an uncured plastics material filler in which nanoparticles are dispersed; and introducing energy locally into the nanoparticles by exciting the nanoparticles in the gap region by sound waves in order to cure the plastics material filler.

2. The method according to claim 1, wherein the width of the gap region is 2 mm or less.

3. The method according to claim 1, comprising heating the plastics material filler by the local introduction of energy in order to cure the plastics material filler is provided.

4. The method according to claim 3, wherein the heating of the plastics material filler is performed up to 40 C. to 90 C. in order to cure the plastics material filler.

5. The method according to claim 1, comprising stimulating, by the local introduction of energy, a chemical reaction in the plastics material filler, which reaction is catalysed by the nanoparticles, in order to cure the plastics material filler is provided.

6. The method according to claim 1, wherein the nanoparticles comprise a material having a higher thermal conductivity than the plastics material filler.

7. The method according to claim 1, wherein the nanoparticles comprise a boehmite.

8. The method according to claim 1, wherein energy is introduced locally by exciting the nanoparticles by ultrasonic waves.

9. A method for tolerance compensation between a first and a second aircraft fuselage section, at least one of which comprises a fiber-reinforced plastics material, comprising: arranging, after curing of the fiber-reinforced plastics material to a degree sufficient to make a complete aircraft fuselage cell, the aircraft fuselage sections in relation to one another while leaving a gap region having a width of at least 0.3 mm between the first and the second aircraft fuselage section; filling the gap region, at least in portions, with an uncured plastics material filler in which nanoparticles are dispersed; and introducing energy locally into the nanoparticles by exciting the nanoparticles in the gap region by sound waves in order to cure the plastics material filler.

10. The method according to claim 9, wherein the width of the gap region is 2 mm or less.

11. The method according to claim 9, comprising heating the plastics material filler by the local introduction of energy in order to cure the plastics material filler is provided.

12. The method according to claim 11, wherein the heating of the plastics material filler is performed up to 40 C. to 90 C. in order to cure the plastics material filler.

13. The method according claim 9, comprising stimulating, by the local introduction of energy, a chemical reaction in the plastics material filler, which reaction is catalysed by the nanoparticles, in order to cure the plastics material filler is provided.

14. The method according to claim 9, wherein energy is introduced locally through the first and/or second aircraft fuselage shell segment.

15. The method according to claim 9, wherein energy is introduced locally through the first and/or second aircraft fuselage section.

16. The method according to claim 9, wherein the nanoparticles comprise a material having a higher thermal conductivity than the plastics material filler.

17. The method according to claim 9, wherein the nanoparticles comprise a boehmite.

18. The method according to claim 9, wherein energy is introduced locally by exciting the nanoparticles by ultrasonic waves.

19. The method according to claim 9, comprising curing the plastics material filler simultaneously in a complete transverse joint region between the aircraft fuselage sections is provided.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) The invention will be described in detail below by way of embodiments with reference to the accompanying figures of the drawings, in which:

(2) FIG. 1 is a schematic view of a device for joining two components according to an embodiment of the invention; and

(3) FIG. 2 is a basic perspective view of a device according to a further embodiment for simultaneously curing a complete transverse joint region between fuselage sections which are to be joined.

DESCRIPTION OF EXEMPLARY EMBODIMENTS

(4) In the figures, like reference numerals denote like or functionally equivalent components, unless indicated otherwise.

(5) FIG. 1 shows the basic construction of a device 1 for joining two components 3, 4, which in this case form, by way of example, part of the outer skin of an aircraft fuselage structure. The two components 3, 4 are basically constructed using a layer 8, 9 which in each case comprises a carbon-fibre-reinforced epoxy resin. Laminations 10, 11, in particular in the form of a copper woven fabric, a copper lamination or a copper net, which are shown by way of example and are not required for the operation of the present device, are used primarily as lightning arrester means for the aircraft. A plastics material 5, for example a sealant or a filler, is introduced at least in regions in a gap region 2 between the components 3, 4.

(6) A plurality of nanoparticles, of which one particle 12 is representatively provided with a reference numeral, are added to the plastics material 5. The nanoparticles have a diameter of from approximately 1 nm to 100 nm. In the present embodiment, particles of an electrically conductive material having good thermal conductivity, for example a ferrite, are used by way of example. The plastics material 5 itself or the matrix comprising the nanoparticles 12 is, for example, formed using heat-curable two-component epoxy resin systems.

(7) An energy introduction means 6 for introducing energy locally into the solid particles 12, which in the present embodiment is configured by way of example as a microwave radiation source, is located above the first component 3. In alternative embodiments, the energy introduction means 6 can be configured for example as an inductor for producing an induction field, as an ultrasonic source, as a light source for visible and/or infrared light, as a source of terahertz radiation or a source of another form of energy-transporting radiation, the type of energy introduction means and the composition of the nanoparticles being matched to one another in each case in such a way that the energy radiated by the energy introduction means during operation can be absorbed locally by the nanoparticles. In addition, the type of energy introduction means 6 is preferably selected with regard to the material and the structure of the components 3, 4, including any laminations 10, 11, in such a way that a sufficient portion of the radiated energy passes at least those portions of the components 3, 4 which are located between the energy introduction means 6 and the gap region 2.

(8) In the present embodiment, the use of electrically conductive nanoparticles 12 under the effect of the microwave radiation 7 emitted during operation by the energy introduction means 6 causes eddy currents to be produced in the nanoparticles dispersed in the plastics material filler, which currents increase the temperature in the plastics material 5 in such a way that the plastics material 5 cures by heating.

(9) The intensity of the energy radiation emitted by the energy introduction means 6 is selectedin the present invention by means of the strength of current I of a supply current used to feed the energy introduction means 6in such a way that a temperature of between 40 C. and 90 C. is set over a period of up to one hour in the plastics material 5 to be cured. The plastics material 5 used is, for example, thermosetting polymers having the following designations: EA 9394 A/B produced by Dexter Hyssol, Redux 870 A/B produced by Hexcel, EA 9394.2 produced by Dexter Hyssol or Epibond 1590-3 A/B produced by Vantico. Alternatively, the plastics material 5 can also be a sealant or sealing agent, for example a two-component polyurethane plastics material. In this configuration, a temperature of approximately 50 C. in the region of the sealing agent is generally sufficient for forced curing.

(10) When using the energy introduction means 6, in particular in the case of a large gap region 2 which is not permeated simultaneously by the radiated energy (in the present case the microwave radiation 7 from the microwave radiation source 6), a positioning means is advantageous, by means of which the energy introduction means 6 can be guided in defined trajectories past the gap region 2 in an automated manner. In this case, a sufficient holding time of the energy introduction means 6 over the gap region 2 is to be provided, in order to effect sufficient thermal curing of the plastics material 5. Alternatively, as shown by the dotted outline in FIG. 1, the energy introduction means 6 can also comprise a handle, for example a grab handle, which makes it possible to use the energy introduction means 6 manually. In this configuration, the energy introduction means 6 preferably has a laser aiming device in order to visualise the spatial sphere of action of the energy radiation 7 produced by the energy introduction means 6 optically on the components 3, 4 for a user in a contact-free manner. As a result, complete curing of the plastics material 5 is ensured.

(11) FIG. 2 shows a variant of a device using which it is possible to cure simultaneously a plastics material filler introduced into a peripheral transverse joint region of a fuselage section.

(12) A further fuselage section (not shown) is connected as a second component to a tail fuselage section 20 as a first component. The device 19 comprises an annular energy introduction means 22, the outer diameter of whichapart from an air gap for tolerance compensationis adapted approximately to the cross-sectional dimensions or the cross-sectional geometry of the fuselage section 20 in the transverse joint region. In the embodiment shown in FIG. 2, the energy introduction means 22 is constructed as an annular microwave radiation source comprising three adjacent 120 segments 23 to 25. In alternative embodiments, the annular energy introduction means 22 can be configured as an annular inductor, an annular source for example for ultrasound, visible light and/or infrared light, for terahertz and/or microwave radiation or another form of energy-transporting radiation, as described with reference to FIG. 1.

(13) Owing to the generally large cross-sectional dimensions of the fuselage sections to be joined, which may have an inner circumference of up to 25 m depending on the aircraft type and which require an annular energy introduction means 22 having an approximately corresponding outer circumference, it may be necessary to divide said energy introduction means into segments such as the three segments 23 to 25 shown by way of example or a higher number.

(14) A higher number of segments also makes it possible to simplify constructionally any necessary water cooling of the individual segments, since a feed line and a discharge line of relatively small diameter are sufficient for each segment. Segmenting the energy introduction means 22 also reduces the supply power required to supply the individual segments and simplifies the sensitive control system of the segments for actuation, for example by power electronics. Segmenting the energy introduction means 22 also makes it possible to adapt to local variations in the degree of curvature of the fuselage sections which adjoin one another in the transverse joint region 21 and also to adapt to different conditions in the modular system. The modular system makes it possible to assemble the annular energy introduction means 22 in a flexible manner by combining a selection of energy introduction segments from a limited supply of standardised segments, it being possible to adapt the energy introduction means in a simple manner to different cross-sectional geometries and cross-sectional dimensions of fuselage sections. The individual segments can be interconnected by means of a plug-in system, it being possible for an optional locking system to be provided. In the transverse joint region 21, devices for arranging, orientating and temporarily fastening the energy introduction segments can be provided inside the fuselage sections 20.

(15) The annular energy introduction means 22 can also comprise an optional central fastening 26, which comprises a total of three struts 28 to 30 which cross in a mid-point 27, in order to facilitate positioning inside the fuselage section 20. A positioning means 31 or a base plate is arranged in the region of the mid-point 27 and is used to orientate and set up the annular energy introduction means 22 inside an inner region 32 of the fuselage section 20.

(16) In preparation for the use of the device 19, in a conceivable variant the liquid plastics material filler is initially mixed with nanoparticles, the material of which is matched to the form of energy emitted by the energy introduction means. In the present case, nanoparticles consisting of a ferrite are used for example, as in the embodiment of FIG. 1. The plastics material filler comprising the nanoparticles dispersed therein is introduced in the transverse joint region 21 of the fuselage section 20 for filling the gaps and/or for tolerance compensation between components to be joined, for example by surface application with subsequent joining or by injection into pilot holes.

(17) The fully assembled annular energy introduction means 22 is then moved by means of the positioning means 31 in the direction of the arrow 33 into the inner region 32, which is still open on one side, of the fuselage section 20, in such a way that the entire transverse joint region 21 is permeated as fully as possible by the radiated energy of the annular energy introduction means 22, that is to say in the present case by the microwave radiation of the microwave radiation source. The fuselage section to be attached is then orientated in relation to the fuselage section 20 or moved towards it and screwed and/or riveted to it, for example by means of a butt joint using a transverse butt strap. Alternatively, a lap joint without a transverse butt strap can also be provided.

(18) Once the joining process is complete, at least in part, that is to say the fuselage sections are provisionally joined at least to fix the position thereof to a sufficient degree, the plastics material introduced beforehand into the gap region between the fuselage section can be cured by means of the annular energy introduction means 22. The annular energy introduction means 22 can then be dismantled into its three segments 23 to 25 again and removed from the joined fuselage sections together with the positioning means 31 and the struts 28 to 30.

(19) In the event that the fuselage sections to be joined need to be moved apart from one another again anyway both before and after the introduction and curing of the plastics material (liquid shim) required for filling the gaps, the energy introduction means 22 can also be assembled in the fuselage sections which have already been positioned and orientated in relation to one another. Since the fuselage sections have at this point already be equipped with the passenger and hold floors, there are options for supporting, assembling and resting the individual segments or the entire annular energy introduction means 22. The central fastening 26 comprising the positioning means 31 and the struts 28 to 30 or the base plate can be dispensed with if the fuselage sections in the transverse joint region 21 have arrangements (for example frame holders for energy introduction means segments) for temporarily fastening the energy introduction means segments.

(20) Although the present invention has been described herein on the basis of preferred embodiments, it is not restricted thereto, but can be modified in many different ways.

(21) For example, nanoparticles of electrically non-conductive materials or nanoparticles composed heterogeneously of a plurality of materials can be used, in accordance with the form of energy introduced locally.

(22) In the following, preferred embodiments of the invention are described.

Embodiment 1

(23) A Method for joining a first and a second component, at least one of which comprises a fibre-reinforced plastics material, comprising the following steps: arranging the components in relation to one another, leaving a gap region between the first and the second component; filling the gap region, at least in portions, with an uncured plastics material filler in which nanoparticles are dispersed; and introducing energy locally into the nanoparticles in order to cure the plastics material filler.

Embodiment 2

(24) The method according to embodiment 1, wherein the gap region has a width of from 0.3 mm to 2 mm.

Embodiment 3

(25) The method according to either embodiment 1 or embodiment 2, wherein a step of heating the plastics material filler by the local introduction of energy, in particular to between 40 C. and 90 C., in order to cure the plastics material filler is provided.

Embodiment 4

(26) The method according to at least one of the preceding embodiments, wherein a step of stimulating, by the local introduction of energy, a chemical reaction in the plastics material filler, which reaction is catalysed by the nanoparticles, in order to cure the plastics material filler is provided.

Embodiment 5

(27) The method according to at least one of the preceding embodiments, wherein energy is introduced locally by exciting the nanoparticles by means of sound waves, in particular ultrasonic waves.

Embodiment 6

(28) The method according to at least one of the preceding embodiments, wherein energy is introduced locally by exciting the nanoparticles by means of electromagnetic radiation, in particular light, infrared and/or microwave radiation.

Embodiment 7

(29) The method according to at least one of the preceding embodiments, wherein energy is introduced locally by exciting the nanoparticles by means of an electromagnetic induction field.

Embodiment 8

(30) The method according to at least one of the preceding embodiments, wherein energy is introduced locally through the first and/or second component.

Embodiment 9

(31) The method according to at least one of the preceding embodiments, wherein the nanoparticles comprise an electrically conductive material.

Embodiment 10

(32) The method according to at least one of the preceding embodiments, wherein the nanoparticles comprise a material having a higher thermal conductivity than the plastics material filler.

Embodiment 11

(33) The method according to at least one of the preceding embodiments, wherein the nanoparticles comprise, for example, a ferrite and/or a boehmite.

Embodiment 12

(34) A device for joining two components, at least one of which comprises a fibre-reinforced plastics material, an uncured plastics material filler in which nanoparticles are dispersed being introduced, at least in regions, in a gap region between the components; comprising an energy introduction means for introducing energy locally into the nanoparticles in order to cure the plastics material filler.

Embodiment 13

(35) The device according to embodiment 12, wherein the energy introduction means comprises a source of electromagnetic radiation, in particular light, infrared and/or microwave radiation.

Embodiment 14

(36) The device according to either embodiment 12 or embodiment 13, wherein the energy introduction means comprises a source of sound, in particular a source of ultrasound.

Embodiment 15

(37) The device according to at least one of embodiments 12 to 14, wherein the energy introduction means comprises an inductor for producing an electromagnetic induction field.

Embodiment 16

(38) The device according to at least one of embodiments 12 to 15, wherein the energy introduction means is constructed using a plurality of segments, in order to make it possible in particular to cure the plastics material filler simultaneously in a transverse joint region between a fuselage section and a further fuselage section to be attached thereto to produce an aircraft fuselage cell.

LIST OF REFERENCE NUMERALS

(39) 1, 19 device 2 gap region 3 first component 4 second component 5 plastics material filler 6, 22 energy introduction means 7 magnetic field 8 layer (CFRP material) 9 layer (CFRP material) 10 lamination 11 lamination 12 nanoparticle 20 fuselage section 21 transverse joint region 23 120 segment 24 120 segment 25 120 segment 26 central fastening 27 mid-point 28 strut 29 strut 30 strut 31 positioning means 32 inner region (fuselage section) 33 arrow