WO2012084652A1

WO2012084652A1 - A method for the manufacture of a fibre-reinforced composite component, a moulding and a composite component

Info

Publication number: WO2012084652A1
Application number: PCT/EP2011/072799
Authority: WO
Inventors: Mathias Jessrang
Original assignee: Airbus Operations Gmbh
Priority date: 2010-12-23
Filing date: 2011-12-14
Publication date: 2012-06-28
Also published as: DE102010064106A1

Abstract

The method in accordance with the invention allows simplified manufacture of fibre-reinforced composite components, since an initially hardened moulding region (44) further from the tool represents a gas-tight layer (18), which can at least partially replace a conventional vacuum film build. The invention moreover relates to a moulding (10) for the execution of the method wherein the moulding region (44) further from the tool can be hardened faster than the moulding region (42) nearer to the tool, and also to a fibre-reinforced composite component manufactured from the moulding, in particular in accordance with the method.

Description

A method for the manufacture of a fibre-reinforced composite component, a moulding and a composite component

The invention concerns in the first instance a method for the manufacture of a fibre-reinforced composite component from semifinished textile products, which are pre-impregnated with a matrix material .

In addition the invention concerns a moulding, in particular for purposes of executing the method, with a multiplicity of semi^¬ finished textile products pre-impregnated with a matrix material, which form one moulding region nearer to the tool and one moulding region further from the tool.

Furthermore the invention has as its subject a composite

component, in particular one produced with such a moulding.

In modern aeroplane construction components that are manufactured with fibre-reinforced plastic materials are increasingly finding application. In the structural regions of aircraft carbon fibre- reinforced thermoplastic or high-performance thermosetting plastics are primarily deployed. By this means a considerable potential for weight saving ensues, which amongst other factors leads to increased ranges by virtue of a reduced fuel consumption. Moreover, in comparison to metallic materials plastic materials have excellent corrosion and fatigue resistance, as a result of which the servicing and maintenance effort can be significantly reduced in the operation of modern aeroplanes.

The mass production of fibre-reinforced plastic components is still afflicted with significant difficulties. Thus the plastic components often do not possess sufficient dimensional stability, which, moreover, can only be reliably reproduced with a high level of effort. Furthermore in many cases a high level of manual effort must be employed, which makes the automation of the production process difficult. Moreover, the production of large-scale CFRP components demands a high level of production engineering investment, since large moulding tools, autoclaves, vacuum hardening devices, ancillary devices and similar, must be maintained .

In the production of such CFRP components three basic methods of production are in general deployed at the present time. In accordance with one of these methods of prior known art the hardening of the fibre-reinforced component takes place under the action of a force that is created by the ambient air pressure or a fluid. Here the CFRP component that is being produced is placed on an essentially plane tool surface and is then covered with an airtight vacuum bag. Next the vacuum bag is evacuated and the CFRP component is hardened under the action of the increased ambient air pressure.

In another procedure the hardening and/or the earlier moulding of the component takes place under vacuum, such as, for example, in the so-called "OoA" method ("Out of Autoclave") . The method can be used for components made from pre-impregnated arrangements of reinforcing fibres (so-called "pre-pregs " ) , thermoplastic components, and also in the course of the resin infusion method. The two above-mentioned procedures require, however, a vacuum bag, into which the component is introduced - with holding or

supporting devices as necessary. This generation of a vacuum demands an extremely high level of manual effort and as a consequence allows only a small degree of automation. If the vacuum, for purposes of applying pressure and/or temperature in a deviation from the OoA process is generated, for example, in an autoclave, this represents a further limiting factor in the manufacture of large-scale components. The vacuum film must as far as possible cling to the contour of the component over its whole surface and must be free of voids, wherein high mechanical tensile loads act on the film by virtue of the ambient air pressure; tears form in the film and as a consequence leakages. In the case of a further method variant the CFRP component to be produced is manufactured by means of e.g. press hardening in a moulding process in a metallic moulding tool that is closed on all sides and as a rule can be heated, which reproduces the complete spatial form of the component. A disadvantage of this procedure is to be seen in the fact that large-scale components also require correspondingly large moulding tools.

It is thus common to all the methods of prior known art that they require a high level of investment in equipment and/or a

significant proportion of operations that can only be performed manually .

The object of the invention is therefore in the first instance to specify a method for the manufacture of, in particular, large- scale fibre-reinforced composite components.

This object is achieved by means of a method in accordance with Claim 1 with the following steps: a) positioning of the semi-finished products in a tool that is open on one side, to form a moulding reproducing the composite component, with one moulding region nearer to the tool, and with one moulding region further from the tool, b) closure of pores of the moulding region further from the tool to form a gas-tight layer, c) compression of the moulding, d) hardening of the moulding, and e) removal from the mould.

By this means in many cases it is no longer necessary to cover the component positioned on the tool, which is built up from a multiplicity of pre-impregnated textiles or semi-finished products (so-called "pre-preg material"), with a film for purposes of forming a vacuum bag. Laborious sealing and supporting activities internal and/or external to the vacuum bag are eliminated without replacement. The pre-preg material is preferably formed with carbon fibres or with aramide fibres, which are impregnated or infiltrated with a thermosetting matrix material, such as, for example, an epoxy resin, a BMI resin, or similar. At the start of the method the matrix material is in a state in which it is not yet fully hardened, and is still soft and ductile. The carbon fibres can be present in the form of discrete carbon fibre skeins with a multiplicity of parallel filaments (so-called rovings), as a woven fabric, as a multi-layer mat, as a twisted-thread form elastic knitted fabric, as a single-thread sequential loop knitted fabric, or in a combination of at least two of the textile arrangements cited, and embedded into the matrix material.

In step a) of the method the semi-finished products, i.e. the pre- preg materials, are placed in a tool that is open on one side, and form in their entirety a moulding with one moulding region nearer to the tool, and one moulding region further from the tool, which together in the ideal case reproduce exactly the spatial geometry of the later fibre-reinforced composite component. Here a so- called secondary semi-finished product that is used for the moulding region nearer to the tool has physical properties, in particular hardening properties, that differ from those of the moulding region further from the tool, into which a so-called primary semi-finished product is laid (draped) . The phrase

"moulding region nearer to the tool" defines a zone of the moulding in the vicinity of the tool surface, while the phrase "moulding region further from the tool" identifies a zone of the moulding that faces away from the tool surface. In step b) of the method the pores within the moulding region further from the tool are closed, i.e. sealed, so as to form a gas-tight layer, which in the vacuum-based manufacturing method for fibre-reinforced composite components can represent a substitute for the

conventional vacuum bag. The closure of the pores can, for example, be undertaken by the use of a rapid-hardening matrix material in the primary, i.e.

outer, semi-finished products, which in the course of the hardening process passes through the point of minimum viscosity in the related hardening curve more quickly compared with matrix materials that harden more slowly, as a result of which the cavities, or pores, in the moulding further from the tool are completely blocked, i.e. sealed. By comparison, the matrix material deployed in the secondary semi-finished products underlying the primary semi-finished products is still in a highly viscous state, so that the thinner fluid matrix material cannot penetrate further into these regions. This selective hardening process, which is an essential feature of the method, is based in this case on the differing behaviours with time of the hardening processes of the semi-finished products deployed.

Furthermore, matrix materials can find application in the semifinished products that are nearer to and further from the tool, which in each case are hardened in a different manner, i.e. their chemical cross-linking reaction is triggered and maintained by different initial physical mechanisms.

Alternatively the sealing of the pores can take place e.g. by the application of a plastic coating, such as, for example, a paste^¬ like synthetic resin varnish. In the next step c) of the method the moulding is compressed, i.e. compacted, and by this means consolidated. The compression of the moulding preferably takes place by the application of an increased pressure, which can, for example, be generated in an autoclave. Alternatively the

mechanical compressive force necessary for the compression can also be built up by the hydraulic pressure of a fluid, which acts on the already hardened semi-finished products of the moulding further from the tool.

Furthermore a reduced pressure can be applied in the moulding region nearer to the tool so as to exert, by virtue of the action of normal ambient air pressure, a sufficient mechanical force onto the secondary semi-finished products in the moulding. In this case the reduced pressure acts on the secondary semi-finished products that are not yet fully hardened at this stage. In the following step d) of the method the full hardening of the moulding takes place by the application of at least one of the hardening mechanisms described above. In the last step e) of the method the fully hardened moulding is removed from the mould as a finished fibre-reinforced composite component.

In accordance with an advantageous further development of the method provision is made that the moulding region nearer to the tool is hardened by the application of heat.

By this means the conventional thermal-hardening (standard) matrix materials can be deployed for the moulding regions nearer to the tool .

In accordance with a further advantageous embodiment of the method the moulding region further from the tool is hardened by the application of electromagnetic radiation.

By this means the moulding region further from the tool can be selectively hardened for purposes of initial generation of the gas-tight layer required by the method, i.e. the substitute for the vacuum bag, before any hardening of the moulding region nearer to the tool also starts to occur. This is because the

electromagnetic radiation has only a limited depth of penetration, as a function of the particular wavelength in question, and thus cannot trigger the hardening process in the underlying moulding region nearer to the tool, in particular if the materials of the moulding region nearer to the tool are not designed for hardening by means of electromagnetic radiation. In contrast heat, or thermal radiation, has very good depth penetration, so that the moulding regions nearer to the tool, i.e. lying deeper and preferably designed to be reactive to heat, can be hardened without any problems. The electromagnetic radiation preferably takes the form of microwave radiation. Alternatively UV radiation or electron beams can also be used. In this manner selective hardening of the moulding regions nearer to the tool and further from the tool, i.e. of the related semi-finished products, is possible .

In accordance with a further embodiment of the method provision is made that moulding regions that are open to the external

environment, in particular at least one edge region, are covered with a vacuum film, at least in some regions.

By this means it becomes possible to seal effectively edge regions of the moulding, in which it is often impossible for a gas-tight layer to be formed, by virtue of a particular discontinuous geometry, so that, for example, a vacuum can be generated in this zone. For this purpose an edge region that is to be sealed is conventionally covered with peel-off layers {so-called "peel plies") , sealing strips and at least one vacuum film, so as to achieve the necessary edge sealing.

A further advantageous embodiment of the method envisages that the moulding is compressed under pressure and/or increased pressure.

By this means production equipment that is already available, such as, for example, autoclaves, or devices with which a reduced pressure or vacuum can be generated in a limited component volume, can be used in the production of fibre-reinforced composite components for the compression of the semi-finished products placed on the tool.

In accordance with a further embodiment of the method the whole moulding is initially compressed before the hardening of the moulding region further from the tool.

By this means any cavities or air inclusions present in the laminate structure of the semi-finished products nearer to the tool and further from the tool can be reliably eliminated, in comparison to a compression of the moulding region nearer to the tool that is only undertaken during the hardening process.

Moreover the inventive object is achieved by means of a moulding with the identifying features of Claim 7, wherein the moulding region further from the tool has a hardening characteristic that differs from that of the moulding region nearer to the tool.

By this means a selective hardening of the moulding regions becomes possible, in particular so as to form the gas-tight layer as a substitute for the conventional vacuum bag build.

A further design of the moulding envisages that the semi-finished products in the moulding region further from the tool can be hardened faster and can thus pass through a viscosity minimum faster than the semi-finished products in the moulding region nearer to the tool.

By this means the matrix material of the primary semi-finished product liquefies earlier than the matrix material of the secondary semi-finished product - independently of the hardening technology deployed - so that any cavities and pores present in the moulding region further from the tool are closed to form the gas-tight layer quickly and reliably.

In accordance with a further form of embodiment of the moulding the semi-finished products in the moulding region further from the tool are in particular sensitive to electromagnetic radiation.

This enables firstly the primary, outer-lying semi-finished products to be selectively hardened by means of electromagnetic radiation, in particular with microwave radiation or with UV radiation, so as to form the gas-tight layer in the moulding region further from the tool. Here the secondary semi-finished products of the related moulding region nearer to the tool still remain in the non-hardened state. A reduced pressure can then be generated in the region of the secondary semi-finished products of the moulding region nearer to the tool, so as to compress, i.e. compact, the whole structure as a result of the action of ambient air pressure. Finally the secondary semi-finished products can also be hardened, preferably by the application of heat. The tool that is open on one side can be fitted with a heating unit, in particular one that can be heated electrically. Furthermore electrical heating mats can be laid on the moulding, at least in some regions .

A further advantageous embodiment of the moulding provides that the moulding regions further from and nearer to the tool are in each case formed with at least one semi-finished product.

By this means a sufficient material thickness of the gas-tight layer is ensured, so as to achieve the hermetically sealed closure as a replacement for a conventional vacuum film. Here the primary semi-finished products are positioned in the moulding region further from the tool, while for the build-up of the moulding region nearer to the tool the secondary semi-finished products are laid down in layers.

In accordance with a further advantageous embodiment of the moulding provision is made that after removal from the mould the moulding region further from the tool represents a multifunctional outer region of the component, in which, in addition to a structural function, at least one other kind of function is implemented .

By means of this function of the outer component region, which goes beyond the purely structural function of the moulding, the inventively designed moulding can undertake further tasks in a composite component, as a result of which components that would otherwise be provided for these tasks become unnecessary.

A further advantageous embodiment envisages that the outer component region acts as component protection. The outer component region can, for example, have a high erosion resistance, or an insulating action against electrons, and thus acts as component protection integrally embodied into the subsequent fibre-reinforced composite component . As a result of the high erosion resistance the servicing and maintenance effort for the aircraft is minimised and its service life is increased, while the insulating action against electrons in particular provides protection against galvanic corrosion.

In accordance with a further advantageous embodiment of the moulding provision is made that the outer component region acts as an electrical conductor.

By means of the inventively designed moulding this makes it possible to replace, at least partially, electrical conductors within the cabling of an aircraft, which leads to a further reduction in weight. Moreover a moulding that has an outer component region with a high electrical conductivity is

significantly better protected against high voltage discharges, in particular atmospheric lightning strikes or similar. This outer component region is preferably designed within the moulding region further from the tool by means of suitable material properties and composition for the primary semi-finished products.

Moreover the inventive object is achieved by means of a composite component in accordance with Claim 14, according to which the composite component is manufactured with a moulding in accordance with at least one of the Claims 7 to 13.

By this means the manufacture of the fibre-reinforced composite component is simplified, since no vacuum film is required for purposes of creating a traditional vacuum bag build. Moreover the fibre-reinforced composite component can be fitted with an outer, integral component region, which can fulfil additional tasks - as already elucidated above - which go beyond the purely structural functionality . The fibre-reinforced composite component is preferably

manufactured in accordance with the above-described method with the deployment of the moulding.

In the figure:

Fig. 1 shows a schematic representation of the process sequence of the method.

Fig. 1 illustrates the principles of the process sequence of the method .

A moulding 10, which reproduces the spatial shape of a fibre- reinforced composite component to be manufactured, is placed on an essentially plane tool 12 that is open on one side. The moulding 10 is built up from a multiplicity of primary and secondary semifinished products 14, 16, that are laminated one above another. The semi-finished textile products 14, 16 are formed with textile arrangements of reinforcing fibres, which are pre-impregnated or infiltrated with a matrix material (so-called "pre-preg"

material) . Carbon fibres, glass fibres or aramide^® fibres are preferably used as the reinforcing fibres. The matrix material surrounding the reinforcing fibres is preferably formed with a thermosetting plastic material, in particular with an epoxy resin or a BMI resin.

The respective matrix materials of the semi-finished products 14, 16, have different hardening modes, so as to achieve the selective hardening of the secondary and primary semi-finished products 14, 16, and as a result to cause the formation of a gas-tight layer 18 by means of the primary semi-finished products 16.

For example, the primary semi-finished products 16 can be formed with a matrix material that hardens faster compared with a matrix material of the secondary semi-finished products, so that the point of minimum viscosity on the hardening curve of the matrix material of the primary semi-finished product 16 is reached more quickly compared with the matrix material of the secondary semifinished product 14. This means that during the hardening process the matrix material of the primary semi-finished products 16 in the first instance liquefies quickly, closes any pores or cavities within the primary semi-finished products 16, and seals the latter to form the gas-tight layer 18.

The secondary semi-finished products 14 are, for example, impregnated with a matrix material that can essentially be hardened in a purely thermal manner, i.e. by the supply of heat and/or thermal radiation. The supply of the heat necessary for the hardening process can, for example, take place in the form of infrared radiation, or in the form of an electrical heating unit, not represented here, integrated into the tool 12. The necessary infrared radiation can, for example, be generated by means of a large surface array, i.e. by means of an arrangement of a multiplicity of infrared radiators in the form of a matrix, which allows the simultaneous hardening of even large surface areas of semi-finished products. Furthermore it is equally possible to harden the secondary semi-finished products 14 by means of a combination of the action of an electrical heating unit,

integrated into the tool, with the action of a large surface area array of infrared radiators, which irradiate the moulding 10 from above. Since the matrix material of the secondary semi-finished products 14 for purposes of initiation of the hardening process responds primarily to heat that in general operates over a high depth of penetration and activity, the secondary semi-finished products 14 can still be reliably hardened, even if the primary semi-finished products 16 are already fully hardened throughout.

Alternatively, the semi-finished products 14 nearer to the tool and the semi-finished products 16 further from the tool can be pre-impregnated with different matrix materials, which respond in each case to different physical effects for purposes of triggering and maintaining the hardening process (hardening technologies). Thus the primary semi-finished products 16 can be impregnated or infiltrated with a matrix material that is sensitive to electromagnetic radiation. Here microwave radiation or

alternatively even brief periods of UV radiation can be used.

These different hardening modes allow firstly the primary semi^¬ finished products 16 to be selectively hardened by means of the electromagnetic radiation, without thereby triggering any hardening process of the secondary semi-finished products 14 that are located underneath. For the process sequence of the method it is of central importance that the primary semi-finished products 16 are firstly hardened as completely as possible so as to form the gas-tight layer 18, which represents a substitute for the otherwise conventional vacuum film.

For purposes in particular of completing or supplementing the gas- tight layer 18 at its edges, it can be necessary in individual cases to provide an edge region 20 of the moulding 10 with additional edge sealing 22. The edge sealing 22 essentially comprises a peel-off layer 24 (a so-called "peel ply"), on which is arranged a first sealing strip 26. The peel-off layer 24 allows the removal of the sealing strip 26 and the vacuum film 34 from the semi-finished products 14, 16 without any problems, and in particular without any residues, wherein the peel-off layer 24 at the same time ensures a high surface quality, which as a rule makes any mechanical reworking superfluous. A further sealing strip 30 is positioned on an upper face 28 of the tool. The two sealing strips 26, 30, a region of the peel-off layer 24, not identified, the edge region 20, and an edge region 32 of the tool, are covered with a vacuum film 34.

In combination with the at least partially hardened semi-finished products 16 further from the tool, the edge sealing 22 forms a space 38 that is gas-tight, i.e. air-tight, and accordingly can be (partially) evacuated, which can undertake the function of a conventional vacuum bag, if pores 36, which are unavoidable in the course of manufacture of the primary semi-finished products 16 in particular, have been sealed or blocked gas-tight. By means of the evacuation of the space 38, in particular after the pores 36 in the primary semi-finished products 16 have been completely sealed, the moulding 10 can be compressed, i.e. placed under pressure, solely by the action of the ambient air pressure in the direction of the white arrows 40. By means of the compression, i.e. the compaction, of the moulding 10 undesired air inclusions and other cavities within the semi-finished products 14, 16 are to a large extent eliminated. Here the already-hardened primary semi-finished products 16 in the moulding region 44 further from the tool press onto the moulding region 42 nearer to the tool and compress the latter. A moulding 10 hardened to form a fibre-reinforced

composite component can be deployed in particular in space, air, surface water, underwater and land vehicles.

In what follows the process sequence of the inventive method is elucidated. In the first step a) of the method a multiplicity of non-hardened semi-finished products 14, 16 (so-called "pre-preg material") are positioned on the tool 12 for purposes of forming the moulding 10. The moulding 10 forms the spatial shape of the fibre-reinforced composite component to be manufactured, not represented here, in the ideal case with a high level of accuracy. In the laying-up process the secondary semi-finished products 14 are placed in a moulding region 42 nearer to the tool, and correspondingly the primary semi-finished products 16 are placed in a moulding region 44 further from the tool. In step b) of the method the pores 36 within the moulding region 44 further from the tool are firstly closed, i.e. sealed.

This takes place, for example, in that the matrix material of the primary semi-finished products 16 are hardened over a short period of time with a sufficient supply of heat. Accordingly the

hardening curve of the matrix material of the primary semifinished products 16 also reaches the point of minimum viscosity faster compared with the matrix material of the secondary semifinished products 14. Therefore in this stage of the method high- grade fluid matrix material of the primary semi-finished products 16 seals the pores 36 in the moulding region 44 further from the tool gas-tight, and thus forms the gas-tight layer 18 as required by the method. With the conclusion of this step of the method the formation of the gas-tight layer 18 is complete.

In a deviation from the above process the moulding regions 44 further from the tool, i.e. the primary semi-finished products 16, can also be formed with a matrix material that is sensitive to a hardening mechanism that differs from that of the matrix material that is used in the moulding regions nearer to the tool for the secondary semi-finished products 14. For example the moulding regions 44 further from the tool can be hardened by means of electromagnetic radiation, in particular microwave radiation or UV radiation, to which the hardening mechanism of the matrix material of the secondary semi-finished products 14 in the moulding region 42 nearer to the tool does not respond, or only after a very long time delay. In principle the moulding regions 44 further from the tool could also be hardened by means of electron beams.

Fundamentally the selective hardening of the two moulding regions 42, 44 as described above allows the moulding region 44 further from the tool with the primary semi-finished products 16 to be completely hardened to begin with, for purposes of forming the gas-tight layer 18, while the moulding region 42 nearer to the tool, with the secondary semi-finished products 14 therein contained, still remains in a soft state in the first instance, i.e. in a state that is at most only partially hardened.

In step c) of the method the compression, i.e. compaction, of the moulding 10 takes place by the application of mechanical pressure, so as to eliminate in particular undesired air inclusions and cavities in the still soft moulding region 42 nearer to the tool. The compression can, for example, occur by means of the partial evacuation of the evacuable space 38, as a result of which the moulding 10 is compressed, i.e. pressed together, in the direction of the arrows 40 as a consequence of the force generated by the normal ambient air pressure. Here the already hardened moulding region 44 further from the tool presses onto the still ductile moulding region 42 nearer to the tool, with the tool 12 serving as an abutment. Alternatively the necessary pressure onto the moulding 10 can also be generated and maintained during the whole of the hardening process by means of an increased external pressure, or by a hydraulic fluid. In step d) of the method the preferably complete hardening of the moulding 10 takes place. The hardening process can be aided if required by means of an optional, heating unit within the tool 12 that can be electrically heated, and/or by means of an arrangement of infrared radiators in the form of a matrix above the moulding 10. Furthermore electrical heating mats can be placed on the moulding regions 44 further from the tool, at least in some regions, alternatively or additionally to the tool heating and/or the infrared radiators. In the final step e) of the method the moulding 10 is removed from the mould, i.e. the edge sealing 22, consisting of the sealing strips 26, 30, the peel-off layer 24 and the vacuum film 34, is completely removed, and the moulding 10 is lifted off the tool 12.

The moulding region 44 further from the tool and/or the moulding region 42 nearer to the tool can have an outer component region 46, which in addition to the traditional, purely structural function, goes beyond this and fulfils further tasks.

For example the outer component region 46 can have a high electrical conductivity, so that e.g. no additional copper mesh is necessary for purposes of lightning protection, or electrical conductors within the cabling of the aircraft can at least partially be replaced. Moreover the outer component region 46 can also have a high erosion resistance and impact resistance against foreign bodies striking at high velocity. By this means the servicing effort can be reduced and the service lives of

structural components that are constructed with fibre-reinforced composite components manufactured in accordance with the method can be significantly increased.

Furthermore the outer component region 46 can also have a combination of the two above-described properties - on occasion with the incorporation of further functionalities that do not exclusively serve the structure. The outer component region 46 is formed with at least one of the primary or secondary semi-finished products 14, 16, or with another semi-finished product, which makes possible the desired additional functionalities, such as e.g. a high electrical conductivity, a good impact resistance, a high erosion resistance, or a combination of at least two of the properties cited.

Reference symbol list Moulding

Tool

(Secondary) semi-finished products (Primary) semi-finished products

Gas-tight layer

Edge region (moulding)

Edge sealing

Peel-off layer {so-called "peel ply") Sealing strip

Tool upper face

Sealing strip

Tool edge region

Vacuum film

Pore (cavity)

Evacuable space

Arrow

Moulding region nearer to the tool Moulding region further from the tool Outer component region

Claims

Patent Claims

1. A method for the manufacture of a fibre-reinforced composite component from semi-finished textile products (14,16), which are pre-impregnated with a matrix material, with the steps: a) positioning of the semi-finished products (14,16) in a tool (12) that is open on one side, to form a moulding (10) reproducing the composite component, with one moulding region (42) nearer to the tool, and one moulding region (44) further from the tool, b) closure of pores (36) of the moulding region (44) further from the tool to form a gas-tight layer (18), c) compression of the moulding (10), d) hardening of the moulding (10), and e) removal from the mould.

2. The method in accordance with Claim 1, wherein the moulding region (42) nearer to the tool is hardened by means of heat.

3. The method in accordance with Claim 1, wherein the moulding region (44) further from the tool is hardened by means of electromagnetic radiation.

4. The method in accordance with Claim 1, 2 or 3, wherein regions of the moulding (42, 44) that are open to the external

environment, in particular at least one edge region (20), are covered, at least in some regions, with a vacuum film (34).

5. The method in accordance with one of the preceding claims, wherein the moulding (10) is compressed by means of a reduced pressure and/or an increased pressure.

6. The method in accordance with one of the preceding claims, wherein the whole moulding (10) is initially compressed before the hardening of the moulding region (44) further from the tool.

7. A moulding (10) with a multiplicity of semi-finished textile products (14, 16) pre-impregnated with a matrix material, which form one moulding region (42) nearer to the tool and one moulding region (44) further from the tool., in particular for the execution of the method in accordance with one of the Claims 1 to 6, characterised in that the moulding region (44) further from the tool has a hardening characteristic that differs from that of the moulding region (42) nearer to the tool.

8. The moulding (10) in accordance with Claim 7, wherein semifinished products (16) in the moulding region (44) further from the tool can be hardened faster, and pass through a viscosity minimum faster, than semi-finished products (14) in the moulding region (42) nearer to the tool.

9. The moulding (10) in accordance with Claim 7, wherein in particular the semi-finished products (16) in the moulding region (44) further from the tool are sensitive to electromagnetic radiation .

10. The moulding (10) in accordance with one of the preceding claims, wherein the moulding region (44) further from the tool and the moulding region (42) nearer to the tool are in each case formed with at least one semi-finished product (14, 16) .

11. The moulding (10) in accordance with one of the preceding claims, wherein after removal from the mould the moulding region (44) further from the tool represents a multifunctional outer component region (46), in which, in addition to a structural function, at least one other kind of function is integrated.

12. The moulding in accordance with Claim 11, wherein the outer component region (46) acts as component protection.

13. The moulding in accordance with Claim 11 or 12, wherein the outer component region (46) acts as an electrical conductor.

14. A composite component, manufactured from a moulding (10) in accordance with one of the Claims 7 to 13.