Method for manufacturing a fiber composite component of arched configuration and preform

Abstract

The invention provides a method for producing a fiber-composite component which is arched in design. A preform is designed with a planar fiber-layer arrangement which is formed along an arched structure, the planar fiber-layer arrangement having an outer edge which is assigned to a convex outer side of the arched structure. The outer edge is designed with a recess which extends into the planar fiber-layer arrangement in such a way that the contour of the recess approximates at least section-wise the target contour of a recess which is to be provided in the fiber-composite component. The preform is deformed in such a way that at least one first region of the planar fiber-layer arrangement which adjoins the outer edge extends essentially in the direction of the arched structure is curved or bent relative to a second region of the planar fiber-layer arrangement which adjoins the first region on the outer side of the arched structure. The recess which the preform had before the deformation transitions into the recess of the deformed preform and remains open when the deformed preform is formed. Furthermore, a preform for producing an arched fiber-composite component by means of such a method is proposed. The invention can in particular contribute to saving material and working steps and avoiding waste material when producing fiber-composite components.

Description

Technical Field

[0001] This invention relates to the manufacture of fiber composite components, and more particularly to the manufacture of arched fiber composite components and preforms for manufacturing such fiber composite components. Background Technology

[0002] Curved profiles made of fiber-reinforced composite plastics are described, for example, in DE 10 2016 109 284 B3. According to the processing method proposed in DE 10 2016 109 284 B3, the curved profile is manufactured using an arched preform. The inner region of the preform has a wave-shaped relief structure formed along the arched structure, while the outer region of the preform has radially oriented wedge-shaped recesses. The outer region, as an upsetting region, abuts against the side of a deformation tool, where the wedge-shaped recesses are closed.

[0003] In traditional manufacturing processes, additional steps are required to machine the wedge-shaped recess into a flat preform during preparation for deformation. This can also incur costs due to scrap and material loss. To obtain the final profile of the workpiece, it may be necessary to machine the desired additional geometry into the workpiece in another process, such as by milling, at the cost of additional scrap or milling waste.

[0004] Therefore, it is expected that material consumption and waste generation will be reduced compared to the conventional processing methods, and the number of working steps will be further reduced, so as to enable more efficient and cost-effective manufacturing of fiber composite components. Summary of the Invention

[0005] In this context, the objective of the present invention is to propose an improved method that enables, particularly with at least partial automation, more efficient manufacture of arched fiber composite components, thereby additionally saving materials and processing steps and better avoiding waste.

[0006] According to the present invention, this task is accomplished by a method having the features of claim 1 and / or by a preform having the features of claim 15.

[0007] Therefore, a method for manufacturing fiber composite components for arched ground structures is proposed, the method comprising:

[0008] - Construct a preform having a planar fiber layer arrangement along an arched structure, the fiber layer arrangement having an outer edge with a convex outer side corresponding to the arched structure, wherein the outer edge is constructed with recesses extending into the planar fiber layer arrangement such that the contours of the recesses are respectively constructed at least segmentally near the target contour of the gaps to be correspondingly disposed in the fiber composite member. Here, the contours of the recesses can be constructed, particularly at least segmentally, except for the protrusions, which can be processed by removing material in a subsequent step after further processing of the preform to precisely achieve the target contour. Furthermore:

[0009] - The preform is deformed such that at least one first region of the planar fiber layer arrangement, adjacent to the outer edge and extending substantially in the direction of the arched structure, is bent or folded relative to a second region of the planar fiber layer arrangement that is opposite to the outer side of the arched structure and adjacent to the first region. Here, during the formation of the deformed preform, a recess that the preform had before deformation transitions into a recess in the deformed preform and remains open.

[0010] Furthermore, the preform is configured to manufacture an arched fiber composite component by means of this method under deformation of the preform. The preform has a planar arrangement of fiber layers forming along the arched structure, the planar arrangement of fiber layers having an outer edge corresponding to the convex outer side of the arched structure. The outer edge is configured with recesses extending into the planar arrangement of fiber layers. Here, the contours of the recesses at least segmentally approximate the target contours of the openings to be provided in the fiber composite component to be manufactured, and in particular at least segmentally except for the protrusions, which are processed by removing material in a subsequent step after further processing of the preform to precisely achieve the target contours.

[0011] According to another approach, a method for manufacturing fiber composite components, particularly those with an arched structure, is proposed. This method includes constructing a preform having a fiber layer arrangement structure, particularly along an arched planar shape, deforming the previously formed preform, and further processing the deformed preform. In this other method, the formation and / or deformation and / or further processing of the preform, particularly through age hardening of the matrix material, is specified such that the workpiece produced from the deformed preform, particularly the age-hardened workpiece, prior to its material removal process, possesses a geometry that is intentionally deviated from the target geometry of the fiber composite component in such a way that the geometry of the workpiece substantially corresponds to the target geometry after material removal, particularly in the case of releasing internal stress within the workpiece.

[0012] According to another aspect, a further method is proposed for manufacturing fiber composite components, particularly those with an arched structure. This method includes forming a preform having a planar arrangement of fiber layers, particularly along an arched structure; deforming the previously formed preform; and further processing the deformed preform, particularly by age hardening of a matrix material. Here, the preform is formed on the mounting surface of a mounting tool; the deformation of the preform is carried out using a deformation tool; and the further processing of the deformed preform, particularly age hardening, is carried out using a further processing tool, particularly an age hardening tool. The shape of the mounting surface and / or its base surface and / or the deformation tool and / or the further processing tool, preferably in combination with the shape of the mounting surface and its base surface, and the deformation tool and the further processing tool, is intentionally deviated from the target geometry of the fiber composite component, so as to account for shape deviations during further processing (e.g., shape deviations due to shrinkage) and shape deviations during material removal (e.g., shape deviations due to the release of internal stress), such that the finished fiber composite component substantially corresponds to the target geometry. In particular, deformation tools can be set up separately from further processing tools or used in or together with further processing tools, such as in the aging hardening step.

[0013] The basic concept of this invention is to achieve length compensation in the direction of the arched structure in a first region by means of a recess during the deformation of the preform, wherein the recess in the preform, before deformation, is already set close to the target contour. In this way, the precursor of the geometric features required for the void configuration in the final geometry of the completed fiber composite component can be used for area compensation on the convex outer side of the arched structure during deformation, which generally undergoes upsetting during deformation. Additional cuts or similar structures that result in additional work consumption and waste are avoided. Simultaneously, since less material must be removed, the reprocessing costs for creating the precise target contour of the void are reduced, resulting in very little waste. Therefore, this invention advantageously reduces additional material consumption due to manufacturing, as well as scrap and waste. This invention facilitates the efficient, automated, and economical creation of preforms.

[0014] According to another aspect of the concept, the desired shape deviation of the fiber composite component during manufacturing has been compensated during one or more manufacturing steps in order to achieve the target geometry in the finished fiber composite component as accurately and effectively as possible.

[0015] Advantageous design options and improvements are derived from the other dependent claims and from the description with reference to the accompanying drawings.

[0016] In one design, the recess extends through a first region of the planar fiber layer arrangement and further extends segmentally into a second region of the planar fiber layer arrangement. This can be advantageous because the geometry of the finished fiber composite component has already been largely taken into account in the alternative, thereby avoiding reprocessing costs and scrap. Thus, the recess has been able to accommodate the required final size of the clearance as much as possible.

[0017] In one improved embodiment, the recesses are arranged along the arched structure at at least irregular, segmental intervals. Therefore, the recesses can already be incorporated into the preform before deformation, according to the specifications and intended use of the finished fiber composite component. However, alternatively or in combination with this, the recesses can also be arranged along the arched structure at regular or at least regularly, segmental intervals. Segments with regular and irregular arrangements of recesses can be combined.

[0018] In particular, in one design scheme, the outline of the entire outer edge of the fiber layer arrangement structure can be constructed to approximate the target outline.

[0019] According to one design, the voids in the fiber composite component each have rounded bottoms according to their target contours. In particular, the recesses of the preform may each have at least approximately rounded boundaries in their bottom regions, which approximate the target contour of the void within their rounded bottom regions. Rounded bottoms may be mechanically advantageous, for example, and help to avoid peak mechanical stresses.

[0020] In one design, the outer edge is additionally constructed with at least one retracted portion extending into the planar fiber layer arrangement and ending before reaching the second region. In this way, the preform can further accommodate the target geometry of the fiber composite component, for example, and also serves to further reduce component weight. However, in other equally useful and advantageous designs of the invention, this additional retracted portion can be omitted.

[0021] In one improved embodiment, a fiber layer arrangement structure is formed on a mounting surface during the formation of the preform. This mounting surface has a region with a series of successive recesses and / or protrusions relative to the base surface of the mounting surface in the direction of the arched structure. Here, the planar fiber layer arrangement structure is constructed with an inner edge corresponding to the concave inner side of the arched structure, and a third region of the planar fiber layer arrangement structure, adjacent to this inner edge and extending substantially in the direction of the arched structure, is at least partially formed on the region of the mounting surface with the recesses and / or protrusions. In this way, during the deformation of the preform, when the third region bends or flexes relative to the second region, the length variation in the third region can be pre-maintained by the recesses and / or protrusions of the corresponding spatial structure of the preform generated in the third region during the formation of the fiber layer arrangement structure. Therefore, forming the fiber layer arrangement structure in this way allows for the provision of the additional surface required in the third region in the deformed preform, thereby enabling problem-free deformation.

[0022] According to one design, the first and second regions of the planar fiber layer arrangement structure of the preform are formed on a substantially flat or only slightly arched surface portion of the mounting surface before its deformation, particularly on a substantially flat portion of the mounting surface or a portion only slightly arched compared to a region of the mounting surface with recesses and / or protrusions. In the first region adjacent to the outer edge, considering the convexity of the outer side, excess material present in this region can be compensated by recesses during the deformation of the preform from a substantially planar initial shape. Here, the recesses can be constructed in the first region and, if extending to the second region, also in the second region in an effective and efficient manner close to the target contour.

[0023] In one improved embodiment, the mounting surface with recesses and / or protrusions has a wavy shape when viewed in a cross-section parallel to the direction of the arch structure. For example, the wavy shape can be sinusoidal when viewed in at least one cross-section. However, other waveforms different from sinusoidal shapes can also be considered.

[0024] Fiber composite components are particularly constructed to extend longitudinally. Such components can be advantageously used, for example, to reinforce other components, such as skin components.

[0025] In a preferred design, the fiber composite member is profiled with an outer flange and a connecting piece for connection to the outer flange, wherein the outer flange is formed using a first region of a planar fiber layer arrangement structure, and the connecting piece is formed using a second region of a planar fiber layer arrangement structure.

[0026] In another design, the fiber composite component is constructed in a profile-like manner, comprising an outer flange, an inner flange, and a connecting piece between the outer and inner flanges. Here, the outer flange is formed using a first region of a planar fiber layer arrangement structure, the connecting piece using a second region of a planar fiber layer arrangement structure, and the inner flange using a third region of a planar fiber layer arrangement structure.

[0027] The profile shape of fiber composite components can be constructed as a C-profile in its cross section.

[0028] Here, the height of the splice, and therefore its dimension between the outer and inner flanges, is either constant or variable along the arched structure in other design schemes. For example, the height of the splice, viewed along the arched structure, is smaller in the middle section of the fiber composite member than at the ends. In this way, different requirements regarding the weight and space of the fiber composite member can be met, and the load-bearing capacity of the fiber composite member can be further improved.

[0029] In other improvements, the preform can have locally different thicknesses before and after deformation. This allows for further improvements in weight reduction while simultaneously meeting the load requirements of the fiber composite component. Different local thicknesses can be achieved, for example, by locally varying the number of fiber layers in the fiber layer arrangement. For instance, fewer fiber layers can be provided at the ends of the preform, allowing it to be constructed thinner than in the middle region, where it can be constructed with more fiber layers and thus thicker.

[0030] In a preferred improvement, a planar fiber layer arrangement is constructed, particularly by automating the placement of fiber materials, especially fiber bundles. In this way, the arrangement, orientation, and direction of the reinforcing fibers can be selectively influenced to meet requirements for the fiber composite component, such as strength, stiffness, and weight. Automated placement contributes to an efficient and cost-effective manufacturing process.

[0031] For example, the automated placement of fiber bundles can be performed using automated, computer-controlled placement devices. For instance, the placement device could be a placement robot.

[0032] In particular, considering the recesses of the preform in this way when placing the fiber bundles ensures that only a small amount of scrap is generated during subsequent material removal to achieve the target profile. The placement of the fiber bundles can be particularly carried out such that the edges of the placed and formed fiber layers by means of the fiber bundles approximate a profile that extends close to the target profile extension of the fiber composite member, especially in the recessed areas.

[0033] Furthermore, in the third region of the planar fiber layer arrangement, the fiber bundles are at least partially disposed on areas of the placement surface that have recesses and / or protrusions. Thus, an additional surface for deforming the fiber layer arrangement structure in the third region is provided in a simple and effective manner.

[0034] In one improved embodiment, the fiber layer arrangement structure comprises reinforcing fibers pre-impregnated with a matrix material. Fiber bundles, in particular, may have reinforcing fibers pre-impregnated with a matrix material. Pre-impregnation of the fibers as a prepreg can further facilitate the efficient manufacture of fiber composite components.

[0035] In one design, the fiber composite component can be constructed using a plastic matrix of a thermosetting plastic material. Preferably, the matrix material is a plastic material that can age-cur under heat, such as a synthetic resin.

[0036] Alternatively, fiber composite components can be constructed using thermoplastic materials in another design scheme. The matrix material here is thermoplastic.

[0037] Not only in the case of thermoplastic matrix materials, but also in the case of thermosetting matrix materials, the reinforcing fibers are preferably pre-impregnated with the matrix material as described above.

[0038] In the improved design, the fiber layer arrangement can have fiber layers with different fiber orientations. The fiber layers can particularly include 0-degree layers with fiber orientations following the direction of the arch structure and / or layers with fiber orientations extending at an angle to the direction of the arch structure, such as 30-degree layers and / or 45-degree layers and / or 90-degree layers. Other angles between the fiber orientation and the direction of the arch structure (deviations from 0, 30, 45, or 90 degrees) are possible and can be equally useful and advantageous. In particular, the fiber orientations and combinations of fiber orientations in the preform can be arbitrarily selected according to the requirements of the fiber composite component.

[0039] In other design options, different fiber types can be considered to form the fiber layer arrangement structure. For example, the fiber layer arrangement structure can have carbon fiber or glass fiber, or a combination thereof, as reinforcing fibers. Other fiber types can also be considered.

[0040] In one design, fiber composite components are specifically designed as structural members for aircraft or spacecraft, such as airplanes. Fiber composite components can be very useful as structural members in the aerospace field because the reduced component weight can be combined with mechanical characteristics that are particularly well matched to the expected load. This invention can help to manufacture such advantageous components in a more efficient and economical manner.

[0041] In one improvement, the fiber composite component can be constructed as a bulkhead or section of a bulkhead for an aircraft or spacecraft. In particular, the fiber composite component can be constructed, for example, as a bulkhead for the fuselage shell of an aircraft or spacecraft, such as an airplane, or as a section of such a bulkhead. For bulkheads as structural components, which often have relatively complex, integrally curved, or curvature geometries, the present invention can advantageously contribute to a significant improvement in the manufacturing process in terms of efficiency, economy, and waste avoidance.

[0042] In other design schemes, fiber composite components can be constructed as upper shell bulkheads or side shell bulkheads, or as sections of upper shell bulkheads or side shell bulkheads. Upper shell bulkheads or side shell bulkheads here, for example, reinforce the upper or side shell of an aircraft or spacecraft, such as an aircraft fuselage section.

[0043] In a preferred design, the fiber composite component is constructed as a monolithic bulkhead. Monolithic bulkheads help avoid the separate manufacture of multiple bulkhead components and their assembly and fastening to each other, thus contributing to reduced labor costs and weight. The aforementioned advantages of the invention are particularly advantageous in the case of monolithically formed bulkheads, which are manufactured as a single piece as complex components.

[0044] In one improved embodiment, at least one or more, or all, of the openings in the fiber composite member are respectively configured as channels for at least one longitudinal beam to pass through. Therefore, on the one hand, it is possible to effectively provide, for example, multiple such openings required in the bulkhead. On the other hand, by means of multiple recesses provided in the preform as precursors for the openings, effective area compensation can be advantageously achieved in the first region.

[0045] In particular, at least one or more or all of the open spaces may be constructed in a mouse hole-like shape in the fiber composite component.

[0046] In one design scheme, the deformation of the preform is performed as thermal deformation under the action of heat.

[0047] In one design, the thermosetting matrix material undergoes aging hardening after deformation of the preform, for example, under heat, particularly under additional pressure, such as in a high-pressure heater. Aging hardening can be performed in an aging hardening tool specifically constructed for this purpose.

[0048] In another design, the workpiece is demolded after age hardening and then machined, particularly by milling, to achieve the target contour. Here, trimming of the workpiece is especially performed in areas corresponding to the recesses of the preform to achieve the target contour of the empty portion. This helps to accurately achieve the target geometry. In particular, it can be specified that the entire edge area of ​​the age-hardened workpiece is machined for trimming.

[0049] In the design scheme, after the material removal process, other method steps can be set, including inspecting the dimensional accuracy and / or defect-free nature of the fiber composite component and / or sealing the edges of the fiber composite component and / or performing final quality control.

[0050] In another design, the formation and / or deformation and / or further processing of the preform, particularly through age curing of the matrix material, can be carried out such that the workpiece produced by the deformed preform, particularly the age-cured workpiece, prior to its material removal process, has a geometry that is intentionally deviated from the target geometry of the fiber composite component, such that the geometry of the workpiece substantially corresponds to the target geometry after material removal, particularly after the release of internal stresses in the workpiece. This pre-holding of deformation, for example, the so-called "spring-in" characteristic of the workpiece, and other deformations if necessary, can further reduce the deviation of the finished fiber composite component's shape from the desired target geometry. This deviation from the desired target geometry may stem from the release of internal stresses during the mechanical material removal process, as already mentioned, and additionally from the shrinkage of the matrix material during further processing, such as resin shrinkage during age curing and crosslinking of the matrix material. This deviation occurs in the finished component during the manufacturing process without pre-holding, and hereby particularly during the formation of the preform and / or its deformation and / or further processing through age curing.

[0051] In another design, the preform can be formed on the mounting surface, the deformation of the preform is performed by means of a deformation tool, and further processing (especially age hardening) of the deformed preform is performed by means of a further processing tool (especially an age hardening tool). The shape of the mounting surface and / or its base surface and / or the deformation tool and / or the further processing tool is preferably deliberately deviated from the target geometry of the fiber composite member in combination with the shape of the mounting surface and its base surface and the deformation tool and the further processing tool, so as to take into account shape deviations during further processing (e.g., shape deviations due to shrinkage) and shape deviations during material removal (e.g., shape deviations due to the release of internal stress), so that the finished fiber composite member substantially corresponds to the target geometry.

[0052] Wherever meaningful, the above-described design schemes and improvements can be combined arbitrarily. Other possible design schemes, improvements, and implementations of the present invention also include combinations of features not explicitly mentioned in the foregoing or following descriptions of the embodiments. Here, those skilled in the art will also add individual aspects as improvements or supplements to the corresponding basic forms of the present invention.

[0053] In particular, all the design schemes, improvements and modifications mentioned above can be applied in a similar manner to methods, preforms and fiber composite components manufactured by means of methods, especially when using preforms. Attached Figure Description

[0054] The invention will now be described in detail with reference to embodiments shown in the schematic diagrams. Here are:

[0055] Figure 1 An exemplary monolithic bulkhead formed of fiber-reinforced plastic material is shown in perspective view. This monolithic bulkhead is exemplaryly constructed as a side shell bulkhead for the fuselage of an aircraft or spacecraft.

[0056] Figure 2 The image shows a preform according to an embodiment before deformation, wherein a fiber layer with reinforcing fibers oriented at 0 degrees is shown in a top view.

[0057] Figure 3 Showing the preform before deformation Figure 2 The preform, wherein another fiber layer with reinforcing fibers oriented at 45 degrees is shown in a top view;

[0058] Figure 4 Showing the basis for forming Figure 2 and Figure 3 A schematic top view of the mounting surface of the preform in an embodiment;

[0059] Figure 5 Show along Figure 4 The cross-sectional view shown along line AA is used to illustrate the surface shape of the mounting surface;

[0060] Figure 6 The fiber composite component is shown as a workpiece according to Figure 2 and Figure 3 The preform of the embodiment is obtained after deformation and after age hardening and reprocessing;

[0061] Figure 7 Shown in Figure 2 The leftmost preform around the recess Figure 2 Details;

[0062] Figure 8A schematic diagram is shown to illustrate the deformation characteristics of a workpiece caused by internal stress and resin shrinkage in a variation of an embodiment, and taking into account these deformation characteristics; and

[0063] Figure 9 Another exemplary monolithic bulkhead formed of fiber-reinforced plastic material is shown in a side view. This monolithic bulkhead is exemplaryly constructed as an upper shell bulkhead for the fuselage of an aircraft or spacecraft. Detailed Implementation

[0064] The accompanying drawings should facilitate a further understanding of embodiments of the invention. The drawings illustrate embodiments and, in conjunction with the description, serve to explain the principles and aspects of the invention. Many other embodiments and advantages, among those mentioned, arise with respect to the drawings. Elements in the drawings are not necessarily shown to scale relative to each other.

[0065] In the accompanying drawings, identical, functionally identical, and identically acting elements, features, and components (unless otherwise stated) are given the same reference numerals.

[0066] Figure 1 An integral bulkhead 100 for the fuselage shell of an aircraft or spacecraft (e.g., an airplane) is shown as an example, wherein Figure 1 The integral bulkhead 100 is constructed as a side shell bulkhead and is thus disposed within a fuselage shell constructed as a side shell. The integral bulkhead 100 is constructed as a structural fiber composite component of an aircraft or spacecraft and is made, for example, of a carbon fiber reinforced plastic (CFK) material.

[0067] Figure 1 The integral bulkhead 100 is constructed in the form of a profile and has an elongated, arched, and curved shape. Figure 1 The integral bulkhead 100 has a basically C-shaped cross-section, and includes a joint 101, an inner flange 102, and an outer flange 103. Regarding... Figure 1 The bulkhead 100, not shown in detail, follows an arched structure. The outer flange 103 is fitted to the convex outer side of the arched structure, and the inner flange 102 is fitted to the concave inner side of the arched structure. The inner flange 102 and the outer flange 103 are integrally connected to the connecting piece 101 arranged between the flanges 102 and 103.

[0068] The integral bulkhead 100 has a plurality of openings 36 that extend through the outer flange 103 and into the tab 101. One or more openings 36 may be provided, for example, to allow additional reinforcing elements, particularly longitudinal beams, to pass through the airframe of an aircraft or spacecraft. These reinforcing elements are arranged on the inner side of the airframe surface for additional reinforcement. Figure 1In the bulkhead 100, multiple openings in the openings 36 are formed in a mouse-hole-like shape, and can therefore be called "mouse holes" or, in English terminology, "mouseholes." Some openings in the openings 36 within the intermediate region 109 of the integral bulkhead (in...) Figure 1 The outer flange 103 (included in 36') is constructed to be smaller, but it also extends into the joint 101. The outer flange 103 is divided into multiple sections by multiple gaps 36, 36'.

[0069] The height h of the splice 101 is Figure 1 The height h is not constant, but varies along the arched structure. Here, h is smaller at the middle 109 of the integral bulkhead 100 than at its end 110. Alternatively, a constant height h can be considered.

[0070] Figure 9 Another exemplary integral bulkhead 300 is shown as an upper shell bulkhead for an aircraft or spacecraft, particularly an airplane, configured as an upper shell. The integral bulkhead 300 is also configured as a structural fiber composite component of the aircraft or spacecraft and is made, for example, of a carbon fiber reinforced plastic material. Figure 9 The bulkhead 300 also has multiple gaps 36'. The above description of the bulkhead 100 can be similarly applied to the bulkhead 300, except for the differences that will be described below, and except that in the bulkhead 300, the height h of the joint is substantially constant and there are no smaller gaps 36.

[0071] The following reference Figures 2 to 7 To illustrate, according to one embodiment, the method for manufacturing, for example, with Figure 1 The bulkhead 100 in the middle is similar to or the same as Figure 9 The method is similar to that of the bulkhead 300 in the middle. Figure 2 , Figure 3 and Figure 7 Fiber composite plastic preform 1 is shown here, while Figure 6 Shown as from the basis Figure 2 , Figure 3 and Figure 7 A specific example is the fiber composite component 200 of the workpiece obtained from the preform 1. The preform 1 and the workpiece 200 can, for example, correspond to a fiber composite component 200 similar to... Figure 1 The bulkhead 100 is a section of an integral bulkhead, but in a variant, it can be constructed, for example, to correspond to a similar Figure 9 The section of the 300mm integral bulkhead. It can be understood here that... Figure 2-7The detailed design of the exemplary preform 1 and exemplary workpiece 200 varies depending on the requirements for the fiber composite component, such as bulkhead 100 or 300, and in particular, the position and arrangement of the voids 36, 36' can be modified along the arched structure 3. For Figure 6 Regarding the blank space 36 in the middle, the above is about Figure 1 and Figure 9 The same applies to the situations described. The same applies to flange 201, inner flange 202, and outer flange 203. Figure 6 The image shows workpiece 200.

[0072] Figure 2 The diagram illustrates the planar fiber layer arrangement structure 6 of a fiber composite preform 1, which is constructed substantially planar as a whole. In the specific case of the exemplary workpiece 200, this fiber composite preform is used to manufacture an arched fiber composite component, such as a bulkhead 100 or 300. The fiber layer arrangement structure 6 substantially follows an arched structure 3 having a convex outer side 10 and a concave inner side 11. Regarding the curvature of the arched structure 3, the preform 1 has an outer edge 15 on the outer side and an inner edge 16 on the inner side.

[0073] To form the fiber layer arrangement structure 6, pre-impregnated fiber material in the form of fiber bundles formed of continuous reinforcing fibers is automatically, layer by layer or in layers, placed on the placement surface 78 of a placement tool or table having a body 77 constituting the placement surface 78, using a so-called AFP method. The fiber bundles are thus placed in layers using a computer-controlled placement device, such as a placement robot, to form fiber layers in the fiber layer arrangement structure 6, which have a desired arrangement and orientation of continuous reinforcing fibers in a desired sequence. The placement is performed according to the specifications of the fiber composite members 100, 200, or 300 to achieve a fiber orientation that allows for meeting the requirements for the fiber composite members 100, 200, or 300 in terms of mechanical properties and weight, etc.

[0074] When arranging fiber bundles to construct preform 1, planar fiber layer arrangement structures 6 can be constructed by locally utilizing different numbers of fiber layers, thereby giving fiber composite components 100, 200, and 300 locally different material thicknesses. For example, Figure 1 The end 110 can be constructed to be thinner than the middle 109. Similarly, a constant thickness and therefore a constant number of fiber layers can be considered throughout the fiber layer arrangement structure 6.

[0075] The reinforcing fibers that are pre-impregnated with a preferred thermosetting resin to form a thermosetting plastic matrix in the fiber bundle provided as a prepreg can be, for example, carbon fiber or glass fiber or other suitable fibers, wherein, in principle, combinations of different fiber types can also be considered.

[0076] In a variant, a fiber bundle for placing the preform 1 can also be used, the fiber bundle having, for example, one or more reinforcing fibers of the aforementioned type, which are pre-impregnated with a thermoplastic material to form a matrix.

[0077] exist Figure 2 The top view shows a fiber layer in which fibers extend at 0 degrees as unended or continuous fibers, that is, these fibers extend along the direction of the arch structure 3, in other words, follow the arch structure 3 or extend in a direction parallel to the arch structure 3.

[0078] To illustrate, Figure 3 An exemplary illustration shows a fiber layer of preform 1 with a 45-degree fiber orientation.

[0079] The fiber layer arrangement structure 6 can include fiber layers with different fiber orientations according to different combinations and sequences in the illustrated embodiment, especially as... Figure 2 The fiber layer with 0-degree fiber orientation and / or such Figure 3 The fiber layers have a 45-degree fiber orientation and / or a 90-degree fiber orientation and / or a 30-degree fiber orientation and / or layers with fibers oriented in other ways. The fiber orientation in terms of angle is observed relative to the direction of the arch structure 3.

[0080] When forming the preform 1, the outer edge 15 is constructed with a recess 21 extending into the planar fiber layer arrangement structure 6. Reference numeral 22 indicates the contour produced in the region of the outer edge 15 for the fiber layers shown in the figures when the fiber bundles are placed, while reference numeral 25 indicates the contour produced in the region of the outer edge 15 for the fiber layers shown in the figures. Figure 7 The target outline of preform 1 is shown in dashed lines to illustrate this.

[0081] Here, the contour 22 is constructed in the region of each recess 21 such that the contour 22 is at least segmentally defined. Figure 2 , Figure 7 In the example, a large portion of the recess 21, which extends in a tongue-like shape into the fiber layer arrangement structure 6, extends close to the target contour 45 of the void 36 or 36' to be formed in the fiber composite member 100, 200, or 300. For the preform 1, the target contour of the void 36 is, for example, in... Figure 7 The enlarged view is indicated by reference numeral 28. Figure 7 Shown in Figure 2 Details around the leftmost recess 21. Figure 7 This describes the formation of the approximate component outline of the fiber composite plastic preform 1.

[0082] Figure 2 As shown, the planar fiber layer arrangement structure 6 has a first region 55, a second region 56, and a third region 57. The first region 55 is defined by an outer edge 15 on the concave outer side 10 of the arched structure 3. On the inner side, that is, away from the outer side 10, the second region 56 is adjacent to the first region 55. Further inward, that is, away from the outer side 10, the third region 57 is adjacent to the second region 56. Therefore, the inner edge 16 defines the third region 57 on the concave inner side 11. The first, second, and third regions 55, 56, and 57 extend in the form of strips along the direction of the arched structure 3. In the illustrated embodiment, the substantially arched imaginary line 61 shows the boundary between the first and second regions 55 and 56 in this case, while the curved imaginary line 62, also in this embodiment, shows the boundary between the second and third regions 56 and 57.

[0083] In the region 55 of the outer flanges 103, 203 that subsequently form the fiber composite components 100, 200, or 300—as will be described in detail below—the preform 1 is thus positioned in a manner close to the component profile, as previously described. Prior to deformation, all the substantially geometric features of the outer flanges 103, 203, especially the gaps 36, 36' in length, and particularly the "mouse hole" 36, are already positioned in region 55. Therefore, the preform 1 can be referred to as a preform 1 conforming to the component profile.

[0084] Figure 7 As shown, contour 22 is configured such that preform 1 has a protrusion 29 relative to target contour 28. The protrusion 29 enables, in later method steps, after deformation of preform 1 (to be further explained) and after subsequent age-hardening steps, the material can be removed by machining, such as milling, to achieve a precise, desired target contour 28 as target contour 45 in the finished fiber composite components 100, 200, 300. Therefore, contour 28 can also be considered as a milling line shown in preform 1 after age-hardening.

[0085] When constructing the preform 1 by automatically placing the fiber bundles, the recess 21 has been taken into account; that is, the individual fiber bundles are placed and cut along their length in such a way that the edges of the arranged fiber bundles form a profile 22. In the example shown, since the ends of the fiber bundles are cut straight to the respective required lengths, the profile 22 is not precisely smooth, but rather approximates a smooth profile 22 close to the target profile 28. This produces very little scrap. Therefore, it is possible to avoid subsequently processing the profile 22 into a full-face fiber arrangement in the area of ​​the recess 21, for example, by cutting it into a full-face fiber arrangement before deformation of the preform 1.

[0086] Figure 2 and Figure 7 For example, it is also shown that the minimum placement length of the fiber bundle, which is necessary to limit on the device side, can cause the protrusion 30 of the actually placed profile 22 to be subsequently removed, for example, along with the protrusion 29, in the region of the outer edge 15 via the target profile 25 of the preform 1. This is particularly likely to be the case in the regions of the preform 1 where the placed bundle is relatively short for a given fiber orientation. Preferably, optimization is sought to make the profile 22 as close as possible to the target profile 25 of the preform 1 with only a small protrusion 30. Figure 3 In the fiber layer exemplarily shown, protrusions 31 are generated during placement to replace the fiber layer according to the fiber layer. Figure 2 and Figure 7 The protruding part 30.

[0087] exist Figure 2 Recesses 21 are machined into the preform 1 using irregularly spaced sections. Figure 2 In the left-hand region of the preform 1, the distance from the center of the recess 21 to the center of the recess 21 is, for example, d1. Figure 2 The two recesses 21 in the middle have a larger distance d2 between them on the right side. Here, the arrangement of the recesses 21 is component-specific and is chosen such that the recesses 21 can form a suitable precursor for the desired voids 36 in the fiber composite components 100, 200, and 300. Segmental or generally regular spacing of the recesses 21 is also conceivable and can be useful, especially when the voids 36 are later intended to serve as, for example, "mouse holes". Such regular spacing of the voids 36 is, for example, in the fiber composite component 300... Figure 9 As shown in the image.

[0088] The recess 21 extends through the first region 55 in the preform 1 and extends segmentally into the second region 56, thereby a portion of the empty portion 36 subsequently exists in the tabs 101, 201, see [reference]. Figure 2 and Figure 7 In the region of the bottom 23 of the recess 21, which in the illustrated embodiment, for example, faces the inner side 11 of the arched structure 3, the contour 22 approximates the rounded target contour 25 of the preform 1. Therefore, the recess 21 has a substantially rounded boundary in the region of its bottom 23, which extends near the contours 28, 45 of the similarly rounded bottom 46 of the empty portion 36 in the fiber composite members 100, 200, 300.

[0089] Furthermore, the preform 1 has retracted portions 66a and 66b on its outer edge 15 that correspond to the target contour 25 indicated by its dashed lines, and these retracted portions do not extend into the second region 56. In this way, protruding tab-like segments 104 and 204 are formed, for example, on the edges of the outer flanges 103 and 203 of the completed fiber composite components 100, 200, and 300, see also... Figure 1 and Figure 6 .exist Figure 2 and Figure 7 In the figure, reference numeral 68 indicates the precursors of the protruding segments 104 and 204, respectively.

[0090] like Figure 4 and Figure 5 As shown, the mounting surface 78 has an area in which a series of recesses 79 and protrusions 81 are formed relative to the base surface 80. The recesses 79 and protrusions 81 follow each other in a, for example, regular order along the arched structure 3.

[0091] When forming a planar fiber layer arrangement structure 6, the fiber bundles are placed in the third region 57, or the segments of the fiber bundles to be placed in the third region 57 are placed on the partial area of ​​the placement surface 78 with recesses 79 and protrusions 81. The fiber layer arrangement structure 6 thus placed obtains a wavy three-dimensional structure in the third region 57 and provides an additional surface in the third region 57.

[0092] The mounting surface 78 is located in the area equipped with recesses 79 and protrusions 81 along the... Figure 5 The arched structural section is shown in detail in section AA. Here, the base surface 80 may extend continuously into portion 85 of the mounting surface 78, that is, in this case, the recess 79 or protrusion 81 is constructed recessed or protruding relative to the mounting surface 78 in portion 85. At section AA, the wavy surface shape of the mounting surface 78 corresponds to a sine wave, wherein, by means of... Figure 4 It is understandable that, for example, at other sections parallel to section AA, and further, for example, in the direction of portion 85, the wave shape changes because the recess 79 becomes narrower and less deep in the direction away from the inner side 11 of the arch structure 3. In this sense, Figure 5 This illustrates a central cross-section of a region formed by the corrugation of surface 78. Other wavy shapes in the central cross-section can also be considered in variations. Furthermore, it goes without saying that... Figure 4 The image first shows a section of the mounting surface 78, on which the fiber bundle rests during mounting and forms Figure 2 , Figure 3The fiber layer arrangement structure 6. However, the mounting surface 78 can also suitably protrude beyond the edge of the fiber layer arrangement structure 6, for example, to form a larger preform. Recesses 79 and / or protrusions 81 can also extend beyond the mounting surface 78. Figure 4 The portion shown in the image.

[0093] Unlike the region belonging to the third region 57, the mounting surface 78 does not have any depressions or protrusions in another portion 85, but is substantially flat or only slightly arched compared to the aforementioned depressions 79 and protrusions 81. The first region 55 and the second region 56 are formed by placing the fiber bundle on the portion 85 of the mounting surface 78, and are thus constructed to be substantially flat or only slightly arched corresponding to that portion 85 of the mounting surface 78.

[0094] After the preform 1 is completed, it undergoes thermal deformation. For this purpose, the preform 1 can be removed from the mounting surface 78 first.

[0095] Thermal deformation can be performed using a deformation tool not shown in detail in the accompanying drawings. This deformation tool may include, for example, a surface for placing the second region 56 and a surface for abutting the first and third regions 55, 57 against the curved longitudinal sides of these curved surfaces.

[0096] During the deformation of the preform 1, in this example, the second region 56 remains substantially undeformed. In particular, the second region 56 remains flat or only slightly curved. However, the second region 56 may also have a slight arching from its flat-positioned configuration during the deformation step.

[0097] During deformation, the first region 55 is relative to the second region 56. Figure 2 The first region 55 bends or folds upward or downward along the arched line 61 in the drawing plane, such that after the aging hardening and material removal trimming described herein, the first region 55 forms the outer flange 103 or 203 of the fiber composite member 100 or 200 or 300.

[0098] The third region 57, when deformed relative to the second region 56, is exemplarily located on the same side as the first region 55, i.e. Figure 2 The curve or bends upward or downward from the drawing along the arched line 62. This is achieved in such a way that the inner flange 102 or 202 of the fiber composite member 100 or 200 or 300 is formed in the third region 57 after age hardening and material removal processing.

[0099] The splice 101 or 201 of the fiber composite component 100, 200 or 300 is formed through the middle second region 56 after age hardening and trimming.

[0100] During deformation, the surface excess is compensated for by the recess 21, which exists in the first region 55 relative to its substantially flat shape before the deformation process. Here, the recess 21 absorbs the length variation along the direction of the arched structure 3, but does not close. The recess 21 of the preform 1 transitions into the recess of the deformed preform 1 and remains open as a precursor to the empty portions 36, 36'.

[0101] Therefore, while the middle second region 56 remains "flat" or at most undergoes slight arching during thermal deformation, and subsequently forms a flat tab 101 or 201 according to the final geometry, the first region 55 then forms an arched outer flange 103 or 203, wherein the length is compensated for during deformation by means of the recess 21.

[0102] Furthermore, when the inner flanges 102, 202 are bent or flexed in the third region 57 to form an arched bend, the corrugated structure described above provides the required area in the third region 57 so that deformation can be achieved without problems and without damaging or undesirably altering the fiber arrangement.

[0103] The deformed preform, not shown in detail, can be age-cured in a suitable age-curing tool, also not shown in detail, under increased pressure and temperature, especially after the application of a vacuum film and, for example, in a high-pressure heater. For age-curing the matrix material and forming a thermosetting matrix, a temperature of, for example, 180°C can be used.

[0104] Here, the aging curing tool can be matched to the shape of the formed recess 21 to hold the material forming the matrix in place during the aging curing process. For example, an insertable core can be provided, having a negative structure that corresponds to the arrangement of the recess 21 and generally to the shape of the outer edge 15.

[0105] When aging hardening is complete, the workpiece is demolded; that is, the vacuum bag is removed and the workpiece is taken out of the aging hardening tool. The workpiece is then machined by material removal. In this machining, a precise target profile 45 is achieved by milling, as shown in... Figure 2 The state of the preform 1 is shown with the aid of line 28. After the recess 21 has been formed in the preform 1 in a manner close to the component outline, in the reprocessing step of material removal, only a small amount of material is removed by milling to obtain the final geometry. Therefore, a small amount of scrap and a small amount of waste are generated.

[0106] Reduced material usage leads to lower costs in an economically advantageous manner. Therefore, the recess 36 does not require complete post-processing; instead, its precursor, formed by the recess 21, only needs a trimming after age hardening to achieve the precise target geometry. Trimming can be performed along the entire outer and inner edges 15, 16 of the workpiece, as well as the edge of the end face.

[0107] After milling, it is preferable to inspect the dimensional accuracy and defect-free nature of the obtained fiber composite components 100, 200 or 300, seal the edges of the fiber composite components 100, 200 or 300, and perform final quality control on the fiber composite components 100, 200 or 300.

[0108] For fiber composite components, such as an integral bulkhead 100 with a length of several meters, for example, between 4 and 5 meters, or an integral bulkhead 300 with an exemplary length between 3 and 4 meters, high profile accuracy is often desired. However, during the milling process described above, the internal stresses present in the material are released in the age-hardened workpiece, which leads to deformation of the workpiece and thus deviation from the given profile. Furthermore, shrinkage may occur in the workpiece due to cross-linking of the matrix material during its prior age hardening. Both the shrinkage of the matrix and the release of internal stresses result in geometric changes in the finally obtained fiber composite components 100, 200, and 300, and together they lead to deviations from their theoretical geometry.

[0109] In an advantageous variation of the method for manufacturing fiber composite components, such as integral bulkheads 100 or 300, according to one embodiment described above, the deformation of the preform 1 and the age hardening of the deformed preform are performed using a deformation tool and an age hardening tool separately disposed from the deformation tool. The geometry of the age hardening tool, and preferably also the deformation tool, comprises deformation relative to the theoretical geometry of the finished fiber composite component, which is "pre-preserved" due to deformation caused by internal stress and shrinkage, and especially the so-called "spring-in" characteristic of the workpiece. This means that the geometry of the deformation and / or age hardening tool deviates from a precise target geometry of the fiber composite component 100, 200, 300, more precisely, such a deviation is such that the workpiece obtained from the deformed preform, after age hardening and before the milling process, has a geometry that is specifically deviated from the target geometry of the fiber composite component 100, 200, 300. This deviation is chosen such that the geometry of the workpiece after milling corresponds as precisely as possible to the predetermined target geometry. The release of internal stress within the workpiece during milling causes deformation. By pre-treating these geometric changes in a targeted manner as described above, fiber composite components 100, 200, and 300 can more accurately correspond to a pre-given target geometry after milling.

[0110] Figure 8 This illustrates the pre-holding of deformation in, for example, fiber composite components 100, 200, or 300, which exists after the milling process without this pre-holding. For clarity, the deformation or shape deviation is... Figure 8 The figures are exaggerated. As explained, these shape deviations may stem from the aforementioned internal stress release, resin shrinkage, or a combination of both effects.

[0111] The optimized geometry of an age-hardening tool is illustrated by reference numeral 91. The nominal, theoretical, or target geometry of the fiber composite components 100, 200, and 300 is indicated by reference numeral 92. The compensated shape deviation of the workpiece having the theoretical geometry 92 after milling is shown as 93. Reference numerals 94a-e indicate different types of deformations that constitute the deviations from the theoretical geometry indicated by 93, such as thrust 94a, expansion 94b, torsion 94c, bending 94d, and “bounce” 94e.

[0112] As mentioned above, the shrinkage properties of thermosetting resins can contribute to deformation 94a-e. At the outer or inner flange and the connecting piece (in Figure 8Resin shrinkage in the area of ​​the connection radius (not shown in detail) contributes to the "bounce-in" 94e. The further contribution by shrinkage is particularly evident in the variations along the longitudinal directions of the members 100, 200, 300 94b, in bending 94d, and especially in the torsion 94c of the inner and outer flanges in different size designs.

[0113] Using the age-hardening tool's geometry, which differs from 92, according to 91, Figure 8 This deformation is predicted and compensated for. For example, joints 101 and 201 can be slightly arched after age hardening but before milling, as indicated by geometry 91. Figure 8 As shown, the outer and inner flanges can also be slightly "outward" inclined in geometry 91, that is, inclined away from the inner area of ​​the profile, in order to compensate for "bounce-in" 94e.

[0114] The geometric deviations of the completed fiber composite components 100, 200, and 300 from the target geometry can be exemplarily considered and pre-held only in the age-curing tool. Alternatively, they can be additionally considered and "pre-held" when designing the geometry of the deformation tool.

[0115] However, preferably, the aforementioned expected geometric deviations between the completed fiber composite components 100, 200, 300 and the target geometry 92 have been considered and "pre-maintained" during the formation of the preform 1 and its deformation and age hardening.

[0116] For example, a placement tool having a placement surface 78 and a placement tool body 77, a deformation tool disposed separately from the placement tool, and an age-curing tool disposed separately from the deformation tool are used to form and prepare the preform 1 and manufacture fiber composite components 100, 200, or 300. However, in a variant, it is also possible to integrate the deformation tool into the curing process, for example, as part of the age-curing tool.

[0117] In the preferred processing method for pre-maintaining geometric changes through internal stress and resin shrinkage, shape deviations have been considered when designing the placement tool and therefore when forming the preform 1, and also in the geometric design of the deformation tool and the age-hardening tool respectively.

[0118] Accordingly, the base surface 80 of the mounting surface 78 can be complexly shaped, for example by introducing arching and / or bending along the arch structure 3, for example as a global radius, and / or twisting around the arch structure direction 3. However, as explained, the arching and / or bending and / or twisting and / or global radius used to pre-hold the deformation 93 can also be introduced only during the deformation or age hardening of the preform 1, wherein the tools used are designed accordingly.

[0119] The fabrication of fiber composite components 100, 200, and 300 has been described above, wherein reinforcing fibers are embedded in a thermosetting plastic matrix, which is formed by age curing of the resin. As already mentioned, thermoplastic materials can also be considered for use as the matrix. In this case, the matrix is ​​not age-cured, but can be subjected to elevated temperatures, for example, exceeding the glass transition temperature of the thermoplastic matrix, after heat deformation to fix the final configuration.

[0120] Although the present invention has been fully described above with reference to embodiments, the present invention is not limited thereto, but can be modified in various ways and methods.

[0121] This invention is not limited to bulkheads used in fuselage shells as fiber composite components. It can also be used to manufacture other profiled and curved fiber composite components.

[0122] List of reference numerals

[0123] 1 Preform

[0124] 3. Arched structure

[0125] 6. Fiber layer arrangement structure

[0126] 10 Outer side

[0127] 11. Inner side

[0128] 15 Outer edge

[0129] 16 Inner Edges

[0130] 21 recess

[0131] 22. Profile (Preform)

[0132] 23 Bottom

[0133] 25. Target Profile (Preform)

[0134] 28. Target profile (fiber composite component; shown as a preform)

[0135] 29. Protrusion

[0136] 30. Protrusion

[0137] 31. Protrusion

[0138] 36, 36” blank space

[0139] 45 Target outline

[0140] 46 Bottom

[0141] 55 First District

[0142] 56 Second Region

[0143] 57 Third District

[0144] Line 61

[0145] Line 62

[0146] 66a, 66b Retraction section

[0147] 68. Precursor for plate-like segments

[0148] 77. Main body of the installation tool

[0149] 78. Surface placement

[0150] 79. Depression (surface)

[0151] 80 Base surface (mounting surface)

[0152] 81. Raised surface (mounting surface)

[0153] 85. Part (Surface to be installed)

[0154] 91 Geometry of age-hardening tools

[0155] 92 Target geometry of fiber composite components

[0156] 93 Compensated Deformation of Fiber Composite Components

[0157] 94a-e Deformation

[0158] 100 integral bulkhead

[0159] 101 stitching

[0160] 102 Inner Flange

[0161] 103 Outer Flange

[0162] 104 plate-like segments

[0163] 109 in the middle

[0164] 110 End side end

[0165] 200 Fiber Composite Components

[0166] 201 stitching

[0167] 202 Inner Flange

[0168] 203 Outer Flange

[0169] 204. Plate-like segment

[0170] 300 integral bulkhead

[0171] Spacing between d1 and d2

[0172] h Height (for splicing)

Claims

1. A method for manufacturing fiber composite components for arched ground structures, comprising: Construct a preform (1) having a planar fiber layer arrangement structure (6) formed along an arched structure (3), the fiber layer arrangement structure having an outer edge (15) corresponding to a convex outer side (10) of the arched structure (3), wherein, The outer edge (15) is constructed with a recess (21) extending into the planar fiber layer arrangement structure (6) such that the outline (22) of the recess (21) at least segmentally approaches the target outline of the vacancy to be provided in the fiber composite member, and has a protrusion (29) protruding toward the inner side at the bottom of the recess (21) facing the inner side opposite to the outer side of the arch structure (3), the protrusion being able to remove material in a subsequent step after further processing of the preform (1) in order to accurately achieve the target outline, wherein the outline of the recess is formed by cutting the ends of each fiber bundle to a predetermined length; The preform (1) is deformed such that at least one first region (55) of the adjacent outer edge (15) of the planar fiber layer arrangement structure (6) extends substantially in the direction of the arch structure (3) and a second region (56) of the planar fiber layer arrangement structure (6) adjacent to the first region (55) is bent or folded relative to the outer side (10) of the planar fiber layer arrangement structure (6) away from the arch structure (3), wherein, when forming the deformed preform, the recess (21) that the preform (1) had before deformation transitions into the recess of the deformed preform and remains open; Age hardening of deformed preforms; and The age-cured preform undergoes a material removal process, in which the target contour is achieved.

2. The method according to claim 1, characterized in that, The recess (21) extends through a first region (55) of the planar fiber layer arrangement structure (6) and also extends segmentally into a second region (56) of the planar fiber layer arrangement structure (6).

3. The method according to claim 1 or 2, characterized in that, The recesses (21) are arranged at least in a segmental, irregular interval along the arched structure (3).

4. The method according to claim 1 or 2, characterized in that, The void portion in the fiber composite component has a rounded bottom (46) according to its target profile.

5. The method according to claim 1 or 2, characterized in that, The outer edge (15) is additionally constructed with at least one retraction portion extending into the planar fiber layer arrangement (6) and ending before reaching the second region (56).

6. The method according to claim 1 or 2, characterized in that, When forming the preform (1), the fiber layer arrangement structure (6) is formed on the mounting surface (78), the mounting surface having a series of recesses (79) and / or protrusions (81) that are successively arranged relative to the base surface (80) of the mounting surface (78) in the direction of the arch structure (3), wherein the planar fiber layer arrangement structure (6) is configured with an inner edge (16) corresponding to the concave inner side (11) of the arch structure (3), and a third region (57) of the planar fiber layer arrangement structure (6) is formed at least partially on the region of the mounting surface (78) provided with the recesses (79) and / or protrusions (81), the third region extending substantially in the direction of the arch structure (3) adjacent to the inner edge (16).

7. The method according to claim 1 or 2, characterized in that, The first region (55) and the second region (56) of the planar fiber layer arrangement structure (6) of the preform (1) are formed on a substantially flat or only slightly arched surface portion of the placement surface (78) before its deformation.

8. The method according to claim 7, characterized in that, The first region (55) and the second region (56) of the planar fiber layer arrangement structure (6) of the preform (1) are formed on a substantially flat portion (85) of the mounting surface (78) or only slightly arched compared to the recessed and / or raised portion of the mounting surface (78) before its deformation.

9. The method according to claim 1 or 2, characterized in that, The fiber composite component is constructed in a profile shape with an outer flange, an inner flange, and a connecting piece located between the outer flange and the inner flange, wherein the outer flange is formed using a first region (55) of the planar fiber layer arrangement structure (6), the connecting piece is formed using a second region (56) of the planar fiber layer arrangement structure (6), and the inner flange is formed using a third region (57) of the planar fiber layer arrangement structure (6).

10. The method according to claim 1 or 2, characterized in that, The planar fiber layer arrangement structure (6) is formed by automatically placing fiber bundles.

11. The method according to claim 1 or 2, characterized in that, The fiber layer arrangement structure (6) is composed of reinforcing fibers pre-impregnated with a matrix material.

12. The method according to claim 1 or 2, characterized in that, The preform (1) is formed and / or deformed and / or further processed in such a way that the workpiece obtained from the deformed preform has a geometry that is selectively deviated from the target geometry (92) of the fiber composite component before material removal processing, such that the geometry of the workpiece substantially corresponds to the target geometry (92) after material removal processing; and / or A preform (1) is formed on a mounting surface (78), the preform (1) is deformed by means of a deformation tool, and the deformed preform is further processed by means of a further processing tool, wherein the shape of the mounting surface (78) and / or its base surface (80) and / or the deformation tool and / or the further processing tool is intentionally deviated from the target geometry (92) of the fiber composite component, so as to take into account the shape deviations during the further processing and the shape deviations during the material removal process, so that the finished fiber composite component substantially corresponds to the target geometry (92).

13. The method according to claim 12, characterized in that, The age-hardened workpiece obtained from the deformed preform has a geometry that is intentionally deviated from the target geometry (92) of the fiber composite component before the material removal process, such that the geometry of the workpiece substantially corresponds to the target geometry (92) after the material removal process.

14. The method according to claim 12, characterized in that, The further treatment of the deformed preform is age hardening, which is carried out by means of an age hardening tool.

15. The method according to claim 1 or 2, characterized in that, The fiber composite component is constructed as a bulkhead or section of a bulkhead for an aircraft or spacecraft.

16. The method according to claim 1 or 2, characterized in that, At least one or all of the open sections in the fiber composite member are configured as channels for at least one longitudinal beam to pass through.

17. The method according to claim 1 or 2, characterized in that, At least one or all of the voids (36) in the fiber composite member are constructed in a mouse hole shape.

18. A preform (1) for manufacturing an arched fiber composite component by means of the method according to any one of the preceding claims, wherein the preform (1) is deformed, having a planar fiber layer arrangement structure (6) formed along the arched structure (3), the fiber layer arrangement structure having an outer edge (15) corresponding to a convex outer side (10) of the arched structure (3), the outer edge having a recess (21) extending into the planar fiber layer arrangement structure (6), wherein, The contour (22) of the recess (21) is at least segmentally close to the target contour structure of the vacant portion provided in the fiber composite component to be manufactured, and has a protrusion (29) protruding toward the inner side at the bottom of the recess (21) toward the inner side opposite to the outer side of the arch structure (3), which can be processed by material removal in a subsequent step after further processing of the preform (1) to accurately achieve the target contour (45). The contour therein approximates the target contour; and The preform is configured such that after age hardening the deformed preform and removing material from the age hardened preform, the final geometry of the target profile can be achieved.

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