Abstract:
Method for manufacturing a composite fibre component ( 1 ) the method comprising the following method steps: forming a moulding core ( 4 ) comprising a hollow profile ( 15 ) made of segments ( 16   a . . . d ) in order to establish an external geometry of the moulding core ( 4 ), wherein the segments ( 16   a . . . d ) of the moulding core ( 4 ) each extend in the direction of the longitudinal axis of the moulding core ( 4 ) and are each constructed so as to be pivotable about an axis running in the longitudinal direction of the moulding core ( 4 ), between a folded position (A). and an unfolded position (B) of the hollow profile ( 15 ) of the moulding core ( 4 ), wherein the segments ( 16   a . . . d ) are constructed so as to be coupled to one another via connections ( 18   a . . . d,    19   a . . . c ) in one piece in order to form the hollow profile ( 15 ); at least one fibre semifinished product ( 3 ) is positioned at least in certain sections on the constructed moulding core ( 4 ) in order to shape at least one moulded section ( 14 ) of the composite fibre component ( 1 ) to be manufactured; and heat and/or pressure is applied to the at least one moulded section ( 14 ) in order to manufacture the composite fibre component ( 1 ).

Description:
FIELD OF THE INVENTION 
       [0001]    The present invention relates to a method for manufacturing a composite fiber component, in particular for aerospace, to a molding core for manufacturing such a composite fiber component and to a composite fiber component having at least one stringer which is manufactured by means of such a molding core and/or such a method. 
       BACKGROUND OF THE INVENTION 
       [0002]    Although the present invention can be applied to any composite fiber components, said present invention and the problem on which it is based are explained in more detail below with reference to planar, stringer-reinforced carbon fiber plastic (CFK) components, for example skin panels of an aircraft. 
         [0003]    It is generally known to reinforce carbon fiber plastic skin panels with carbon fiber plastic stringers in order to withstand the high loads in the field of aircraft together with the lowest possible additional weight. In this context, essentially two types of stringers are distinguished: T and Ω stringers. 
         [0004]    The cross section of T stringers is composed of a base and a web. The base forms the connecting surface to the skin panel. The use of skin panels which are reinforced with T stringers is widespread in aircraft construction. 
         [0005]    Ω stringers have an approximately hat-shaped profile, with the ends of said profile being connected to the skin panel. In the cured state of Ω stringers they can either be adhesively bonded onto the panel which is also cured or they can be cured at the same time as the panel wet on wet. The latter is desirable because it is more favourable in terms of processing technology. However, in order to carry out wet on wet manufacture of skin panels which are reinforced with Ω stringers, supporting cores or molding cores are necessary in order to secure the dimensionally unstable fiber semi-finished products in the desired Ω shape and support them during the manufacturing process. Skin panels with Ω stringers have, compared to T stringers, the advantage of a better infiltration capability during an infusion method in order to introduce a matrix, for example an epoxy resin, into the fiber semi-finished products. Compared to other known methods for manufacturing composite fiber components such as, for example, the prepreg method, infusion methods can be cost-effective because they permit the use of more cost-effective fiber semi-finished products. 
         [0006]    When manufacturing Ω stringers, there is the problem, however, that the material which is used at present for the supporting core or molding core is costly and can be difficult to remove after the Ω stringers have been constructed so that the material which remains in the stringers disadvantageously increases the overall weight of the aircraft. 
       SUMMARY OF THE INVENTION 
       [0007]    It is one of the objects of the present invention to make available a more cost-effective and lightweight composite fiber component, in particular for aerospace. 
         [0008]    Accordingly, a method for manufacturing a composite fiber component, in particular for aerospace, includes the following method steps:
       forming a molding core comprising a hollow profile made of segments in order to establish an external geometry of the molding core, wherein the segments of the molding core each extend in the direction of the longitudinal axis of the molding core and are each constructed so as to be pivotable about an axis running in the longitudinal direction of the molding core, between a folded position and an unfolded position of the hollow profile of the molding core, wherein the segments are constructed so as to be coupled to one another via connections in one piece in order to form the hollow profile;   positioning at least one fiber semi-finished product at least in certain sections on the constructed molding core in order to shape at least one molded section of the composite fiber component to be manufactured; and       
 
         [0011]    applying heat and/or pressure to the at least one molded section in order to manufacture the composite fiber component. 
         [0012]    Furthermore, a molding core for manufacturing a composite fiber component, in particular a stringer on a base component in aerospace, includes a hollow profile which is made in one piece from segments in order to establish an external geometry of the molding core, wherein the segments of the molding core each extend in the direction of the longitudinal axis of the molding core and can each be pivoted about at least one axis running in the longitudinal direction of the molding core, between a folded position and an unfolded position of the hollow profile of the molding core. 
         [0013]    Furthermore, a composite fiber component having at least one stringer, in particular for aerospace, is provided, which is manufactured by means of the molding core according to the invention and/or the method according to the invention. The present invention thus has the advantage over the approaches mentioned at the beginning that the composite fiber component can be manufactured by means of a cost-effective molding core. Instead of costly conventional materials, a molding core is advantageously used which is composed of a hollow profile with segments which can be pivoted with respect to one another, and which core can be easily removed from the mold by pivoting the segments which results in a reduction in the cross section. A further advantage is the re-usability of such a molding core. 
         [0014]    In one embodiment the segments of the molding core are coupled to one another by connections in order to be pivoted with one another between the folded position and the unfolded position of the hollow profile and in order to form a closed hollow profile. These connections permit the segments to be pivoted about the longitudinal axis of the molding core, with the connections being constructed in one piece together with the segments. In this context, the segments and the connections form a closed hollow profile. The latter can easily be manufactured in a cost-effective way from plastic in an extrusion process. 
         [0015]    In an alternative embodiment, the segments of the molding core are constructed together with their pivotable connections as an open profile, for example made of a plastic, which profile is welded in order to form a closed hollow profile. This results in a particular advantage, in that open profiles can generally be manufactured more easily and with tighter tolerances because the inner surfaces can be produced better by means of supporting tools and molds. 
         [0016]    The manufacture of the open profile also provides an advantage in that the connections are embodied in a prestressed fashion such that the hollow profile which is formed from them is provided with a particular position, either the folded position or the unfolded position. 
         [0017]    In one further alternative embodiment, the connections are constructed from a different material from the segments, said material being better suited to the requirements made of a flexible connection and desired prestresses. This other material can be introduced, for example, by means of coextrusion. 
         [0018]    In a further embodiment, at least one segment has at least two subsegments which are pivotably connected in their longitudinal direction by means of a second connection. As a result, the hollow profile can be folded in such a way that only the corner regions have a type of linear contact, in the form of sliding rails, with the interior of the molded section when said hollow profile is removed from the mold, a lower frictional resistance being obtained as it is pulled out. 
         [0019]    It may be particularly advantageous here if a subsegment is extended in its width beyond the second connection as a projection for forming a stop. As a result the unfolded position can be assumed precisely without overshooting of its end position. 
         [0020]    The assumption of the respective position can be implemented by applying an internal pressure to the molding core according to the invention. The internal pressure may be regulated by a set point value in such a way that reproducible positions can be assumed by the hollow profile. 
         [0021]    In a further embodiment, in the folded state the molding core according to the invention is covered by a core sleeve, for example a hose. This hose has such a circumference that it can easily be fitted over in the “folded molding core” state and subsequently extends smoothly around the folding core in the “unfolded molding core” state. Alternatively, a shrink-fit hose which can be fitted by the application of heat can be used. The hose forms a separating and/or sealing layer between the composite fiber component and the molding core. As a result, no undesired exchange of substances during the curing process is brought about and the removal of the molding core from the mold is made easier. 
         [0022]    According to one embodiment of the invention, reinforcement means in the region of junctions of the external geometry which are to be constructed with sharp edges in the molding core which is to be constructed are arranged inside and/or outside the core sleeve. These corner profile parts can also be components of the segment ends or connections. 
         [0023]    The separating layer may be applied to the core sleeve and reduce adherence of the cured composite fiber component. This facilitates removal of the core sleeve after the at least partial curing of the section of the composite fiber component which has been produced by means of the molding core. 
         [0024]    Fiber semi-finished products are to be understood as fabrics, overlays and fiber mats. The latter is provided with a matrix, for example an epoxy resin, and subsequently cured, for example using an autoclave. 
         [0025]    According to a further embodiment of the invention, the molding core is arranged on a base part made of composite fiber semi-finished products and/or at least partly surrounded by fiber semi-finished products in order to construct at least one section of the composite fiber component. As a result, base parts, for example skin panels, pressure domes etc. can be constructed with Ω stringers. As an alternative or in addition to this it is also possible to manufacture separate composite fiber components which are entirely defined in terms of their shape by the molding core. 
         [0026]    When an Ω stringer is manufactured for example, the core sleeve is pulled out of it in the longitudinal direction of the stringer. Consequently, said sleeve, like the core, no longer contributes to the overall weight of the aircraft and the payload of the aircraft can thus be increased. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0027]    The present invention is explained in more detail below using preferred exemplary embodiments and with reference to the attached figures of the drawings, in which: 
           [0028]      FIG. 1  is a schematic perspective view of an exemplary embodiment of a composite fiber component during manufacture in accordance with a method according to the invention; 
           [0029]      FIG. 2  is a schematic sectional illustration of a general molding core of the composite fiber component according to  FIG. 1 ; 
           [0030]      FIG. 3A  is a schematic sectional illustration of an inventive molding core of the composite fiber component according to  FIG. 1  in a folded position; 
           [0031]      FIG. 3B  is a schematic sectional illustration of the inventive molding core according to  FIG. 3A  in an unfolded position; 
           [0032]      FIG. 4A  is a sectional illustration of a first exemplary embodiment of the inventive molding core according to  FIG. 3A  in the folded position; 
           [0033]      FIG. 4B  is a sectional illustration of the first exemplary embodiment of the inventive molding core according to  FIG. 4A  in the unfolded position; 
           [0034]      FIG. 5  is a perspective illustration of the first exemplary embodiment of the inventive molding core according to  FIG. 4A ; 
           [0035]      FIG. 6A  is a sectional illustration of a second exemplary embodiment of the inventive molding core in a first position; 
           [0036]      FIG. 6B  is a sectional illustration of the second exemplary embodiment of the inventive molding core in a second position; and 
           [0037]      FIG. 7  is a schematic perspective view of the composite fiber component according to  FIG. 1  during the removal of an inventive molding core in accordance with the method according to the invention. 
       
    
    
       [0038]    In the figures, the same reference numbers refer to identical or functionally identical components unless otherwise stated. 
       DETAILED DESCRIPTION OF THE INVENTION 
       [0039]      FIG. 1  shows a schematic perspective view of an exemplary embodiment of a composite fiber component  1  during manufacture in accordance with a method according to the invention. 
         [0040]    Two molding cores  4  which have an approximately trapezoidal cross section and whose manufacture will be explained further below are arranged with their base  5  resting on a base part  2 . The base part  2  has at least one layer of a fiber semi-finished product. 
         [0041]    In a further step, further fiber semi-finished products are positioned on the molding cores  4 . The fiber semi-finished products  3  rest here with a central section on the external surface of the molding cores  4  and with their ends on the base part  2 , that is to say for example on the skin of an aircraft. 
         [0042]    It is possible to use various fabrication methods to manufacture the composite fiber component. The infusion method may be selected in order to introduce a matrix, that is to say for example epoxy resin, into the fiber semi-finished products  3 . The prepreg method can be equally well used here. 
         [0043]    In a further step, the base part  2  is cured with the molding cores  4  and the fiber semi-finished products  3  in an oven or autoclave, depending on the method, with the application of heat and pressure. 
         [0044]    The fiber semi-finished products  3  are cured, for example, in a suitable oven or autoclave (not illustrated) to form stringers  20 . The at least partially cured composite fiber component  1  consequently has the two Ω stringers  20  after the curing process. 
         [0045]      FIG. 2  shows a schematic, general sectional illustration of an inventive molding core  4  of the composite fiber component  1  according to  FIG. 1  in a cross section. 
         [0046]    The molding core  4 , details of whose design will be given further below, has a cross section  6  which is formed in a mold  8  and is given the desired shape, here an approximately trapezoidal shape, in said mold in a conventional fashion, for example with the application of heat and pressure. In this example, the molding core  4  is surrounded by a core sleeve  9  which completely encloses the molding core  4 . It prevents direct contact between the molding core  4  and the composite fiber component  1 . Possible undesired exchange of material between 1 and 4 is thus prevented and the later removal of the molding core  4  from the mold is facilitated since it cannot adhere to the composite fiber component  1 . It is important here that the core sleeve  9  should reliably withstand the process temperature and the process pressure. The core sleeve  9  bears with its inner side  11  directly on the surfaces of the molding core  4 , and in this example its outer side  10  is coated with a separating layer (not shown) which can also be composed of an additional sleeve. The separating layer serves for later separating the core sleeve  9  from the composite fiber component  1  if the core sleeve  9  is also to be removed after the removal of the molding core  4  from the mold. 
         [0047]    The molding core  4  according to the invention is composed of individual segments  16   a . . . d  which extend in the longitudinal direction of the molded section  14  ( FIG. 1 ). A cross section through such a molding core  4  is illustrated schematically in  FIGS. 3A and 3B . 
         [0048]    In this context, the dashed outline of the cross section  6  of the unfolded molding core  4  or of a hollow profile  15  is indicated. The side surfaces of this hollow profile  15  are formed by the segments  16   a . . . d . In the folded position A of the molding core  4  which is shown in  FIG. 3A , the segments  16   a . . . d  are connected in an articulated fashion by means of first connections  18   a . . . d  at their corner points or corner joints. Furthermore, the segments  16   a ,  16   b  and  16   d  are each divided into two subsegments  17   a / 17   b ,  17   c / 17   d  and  17   e / 17   f  which are themselves connected in an articulated fashion by means of second connections  19   a . . . c  at central points (central joints) here. In each case one of the respective two subsegments  17   a / 17   b ,  17   c / 17   d  and  17   e / 17   f  is lengthened beyond the respective second connection  19   a . . . c  and forms in each case a projection  21   a . . . c.    
         [0049]    In this folded position A, the second connections  19   a . . . c  are folded towards the centre of the hollow profile  15 . This results in a folded profile which has a smaller cross section than the hollow profile  15 . On the one hand,  FIG. 3  clearly shows that the first connections  18   a  and  18   b  of the molding core  4  each have only linear contact in the form of sliding rails with the interior of the molded section  14 , which can easily be thought of instead of the cross section  6 , and this may be advantageous when removing, that is to say pulling out, the molding core  4  from the molded section  14 . On the other hand,  FIG. 3  clearly shows that in the folded position A the molding core  4  is smaller than the hollow profile  15  and is thus smaller than the cross section of the molded section  14 , so that it can easily be removed from the mold. 
         [0050]    In order to form the unfolded position B, a pressure is applied to the interior  22  formed by the segments  16   a . . . d , which unfolds the segments  16   a . . . d  as shown in  FIG. 3B . In this unfolded position B, the free ends of the projections  21   a . . . c  rest on the respective corresponding subsegment  17   a ,  17   d ,  17   e , and they each form a stop for this position. 
         [0051]    A first exemplary embodiment of an inventive molding core  4  with pivotable segments  16   a . . . d  is illustrated in a way corresponding to the  FIGS. 3A and 3B  in  FIGS. 4A and 4B , with  FIG. 5  showing a perspective illustration of the first exemplary embodiment.  FIG. 4A  shows the folded position A and  FIG. 4B  shows the unfolded position B. 
         [0052]    The segments  16   a . . . d  are manufactured in one piece with the first connections  18   a . . . d  and the subsegments  17   a . . . f  are manufactured in one piece with the second connections  19   a . . . c  from one substance. The connections  18   a . . . d  and  19   a . . . c  are constructed here as film hinges. These film hinges are matched in terms of their geometry (width and thickness) in this example in such a way that sufficient prestress is ensured and movement always takes place in the elastic region of the hinge material. As a result, the properties, in particular the prestress and the necessary folding moment, remain constant over a plurality of folding processes. Consequently, re-use is possible. The film hinges are matched in such a way that the projections  21   a . . . c  all reach their stops simultaneously (with the same internal pressure). The geometry of the molding core  4  is configured in such a way that the projections  21   a . . . c  cannot impede one another. The configuration of the thickness of the connections  18   a . . . d  and  19   a . . . c  permits a prestress to be applied to the segments  16   a . . . d  and subsegments  17   a . . . f  in such a way that a specific sequence is achieved during the folding and unfolding processes. 
         [0053]    In order to construct sharp corners,  FIG. 5  shows two reinforcement means  13  in the form of corner profiles. The latter can be provided subsequently on the respective edges of the hollow profile  15 . It is also possible for the segments  16   a . . . d  and/or the subsegments  17   a . . . f  and/or the connections  18   a . . . d  to be constructed in a lengthened form in order to form such corner profiles. 
         [0054]    The hollow profile  15  which is formed from the segments  16   a . . . d  has a closed cross section and is therefore referred to as a closed hollow profile  15 . The hollow profile  15  can be manufactured, for example, by extrusion. 
         [0055]    An alternative second exemplary embodiment in the form of an open profile  24  is shown by  FIGS. 6A and 6B  in two positions for different prestresses. 
         [0056]    The open profile  24  has, in addition to the abovementioned points, the advantage that during manufacture the individual connections can be embodied precisely in order to generate desired prestresses. Furthermore, the extrusion is possible in different positions, of which  FIGS. 6A and 6B  show two possibilities. 
         [0057]    Furthermore, the open profile  24  can, in contrast to a closed one, be manufactured with tighter tolerances. 
         [0058]    The open profile  24  is processed after its manufacture to form a closed profile  15  by virtue of the fact that in the example shown here two semi-segments  25   a, b  are joined to form one segment, for example the segment  16   c  from  FIGS. 3A ,  3 B,  4 A,  4 B. This can be done, for example, by welding, with third connections  23   a, b  which correspond to one another and are in the form of longitudinal projections being arranged on the free edges of the semi-segments  25   a, b  lying opposite one another in this example. 
         [0059]      FIG. 7  shows a schematic perspective view of the finished composite fiber component  1  according to  FIG. 1  with molded sections  14  which are constructed as stringers  20 . 
         [0060]    On the left-hand side, a molded section  14  is shown in which one end of the hollow profile  15  of the molding core  4  is indicated, said end being connected to a connecting device  26  with a line  27  for the application of the internal pressure p. The other end of the hollow profile  15  is closed off with a closure in the folded state. This is necessary in order to permit removal from the mold in the direction of the lower end of the figure. The junction region with the unfolded state (length of the junction is approximately twice the width of the molding core) cannot be used for molding. Correspondingly, the molding core must project far beyond the end of stringers  20 . 
         [0061]    By varying the internal pressure p, the hollow profile  15  can be unfolded and folded. However, it is also possible to provide it with a further connecting device  26 . The internal pressure p can be measured at a suitable point in order to regulate it. An opening in the core sleeve  12  is also arranged outside the molded section  14 . 
         [0062]    During removal from the mold, an internal pressure (vacuum) which is such that the hollow profile  15  assumes the folded position A is applied to the hollow profile  15  via the connecting device  26 . 
         [0063]    If the removal from the mold is performed, for example, subsequent to curing in a pressure vessel/autoclave within this pressure vessel, it is possible to apply a correspondingly high vacuum of, for example, 10 bar. This can be taken into account if a geometry of a hollow profile  15  is used in which the simple atmospheric vacuum is not sufficient for the folding. Such a process can be automated. 
         [0064]    It is furthermore possible to apply pressure to the outer side of the hollow profile  15  between the inner side of the molded section  14  or inner side of the core sleeve  9  and the outer side of the hollow profile  15  in order to fold the hollow profile  15 . This pressure can also be applied in a way which supports the internal pressure p. 
         [0065]    The molding core  4  which is folded in this way can be pulled out of the cured molded section  14  and used again. The core sleeve  9  is likewise pulled out, which can be done in a particularly simple and easy way if a separating layer is present. The composite fiber component  1  can then be further processed. If reinforcement means  13  are used, they can likewise also be pulled out or remain in the composite fiber component  1 . 
         [0066]    A method for manufacturing a composite fiber component, a corresponding molding core and a corresponding composite fiber component are thus provided which permit a significant reduction in material costs compared to the use of conventional materials for the supporting or molding core. The molding core is removed completely, allowing the weight of the composite fiber component to be reduced compared with the prior art. It is possible to expect that the molding core  4  will be re-used repeatedly and subsequently recycled, permitting a reduction in costs. 
         [0067]    The invention is not restricted to the specific method for manufacturing a composite fiber component in the field of aircraft which is illustrated in the figures. 
         [0068]    For example, the present inventive idea can thus also be applied to composite fiber components in the field of sports equipment or motor sports. 
         [0069]    In addition, the individual sequence of individual method steps of the manufacturing method according to the invention can be varied in a wide variety of ways. The configuration of the individual method steps can also be modified. 
         [0070]    Furthermore, the geometry of the molding core can be modified in a variety of ways. 
         [0071]    In addition, it is also possible to use a plurality of molding cores in order to construct a single molding core which is wrapped with composite fiber matting. This fulfils the aim of providing a more complex geometry by means of the large number of molding cores. Consequently, relatively complex composite fiber components can be manufactured. 
         [0072]    It is thus possible, for example, also to divide the segment  16   c  ( FIGS. 3A ,  3 B,  4 A,  4 B) into two subsegments with a central joint. A plurality of subsegments of one segment are also conceivable.