Abstract:
A component for connecting structures to intersection regions of said component is disclosed, particularly for an aircraft or spacecraft, including a coupling element, including a first fiber which wraps around the coupling element so that the first fiber extends in a first plane in front of the coupling element and in a second plane behind the coupling element, the first and second planes intersecting, and including a second fiber which wraps around the coupling element so that the second fiber extends in a third plane in front of the coupling element and in a fourth plane behind the coupling element, the third and fourth planes intersecting, and with the first fiber portions of the first and second fibers crossing over in a first region and the second fiber portions of the first and second fibers crossing over in a second region.

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
     This application claims the benefit of and priority to U.S. Provisional Application No. 61/546,754, filed on Oct. 13, 2011, and German patent application No. 10 2011 084 433.3, filed Oct. 13, 2011, the entire disclosures of which are incorporated herein by reference. 
    
    
     FIELD OF THE INVENTION 
     The present invention relates to a component, a reinforcement member, a structural arrangement, an aircraft or spacecraft and a method for producing a component. 
     BACKGROUND OF THE INVENTION 
       FIG. 1  shows a detail of an aircraft which is generally denoted by reference numeral  100 . The aircraft  100  comprises a landing flap  102 .  FIG. 1  shows the landing flap  102  when viewed in the direction opposite to the flight direction of the aircraft  100 . The landing flap  102  is shown once by a dashed line, this view corresponding to the unloaded state of the landing flap. The landing flap  102  is also shown by way of a solid line, this corresponding to the deformed state of the landing flap owing to air loads  104 , which is shown in a much exaggerated manner. The landing flap  102  is connected by means of two flap carriages  106 ,  108  to a wing  110 , which is indicated merely schematically. The flap carriages  106 ,  108  make it possible to adjust the landing flap  102  in relation to the wing  110  from a flight position into a take-off or landing position, the take-off and landing position serving to increase the lift. In the span direction, that is to say from left to right in  FIG. 1 , one flap carriage  106  is designed as a fixed bearing and the other flap carriage  108  is designed as a loose bearing. The flap carriages  106 ,  108  are each connected to the landing flap  102  via an eye-bolt connection  112 . 
     It is known to design the eye of a respective eye-bolt connection  112  as a fitting which is made of metal and connected, in particular riveted, to the landing flap  102 . For example, DE  10   2007   011   613  Al shows a metal fitting for load introduction. 
     There is an increasing need even to produce load introduction elements, for example the above-described eye of the eye-bolt connection  112 , from fibre composite materials, for example carbon-fibre-reinforced plastics material (CFRP), in order to reduce further weight and assembly costs. U.S. 2010/0148008 A1 describes a load introduction element of this type made of fibre composite material. 
     SUMMARY OF THE INVENTION 
     An idea of the invention is to provide an improved, fibre-compatible approach to introducing loads, in particular into box-like structures, for example landing flaps. 
     Accordingly, a component for connecting structures to intersection regions of said component, in particular for an aircraft or spacecraft, is provided, comprising a coupling element, comprising a first fibre which wraps around the coupling element in such a way that the first fibre extends, with a first fibre portion, in a first plane in front of the coupling element and, with a second fibre portion, in a second plane behind the coupling element, the first and second planes intersecting, and comprising a second fibre which wraps around the coupling element in such a way that the second fibre extends, with a first fibre portion, in a third plane in front of the coupling element and, with a second fibre portion, in a fourth plane behind the coupling element, the third and fourth planes intersecting, the first fibre portions of the first and second fibres crossing over in a first region and the second fibre portions of the first and second fibres crossing over in a second region. 
     Furthermore, a reinforcement member for connecting structures to intersection regions of said member, in particular for an aircraft or spacecraft, is provided, comprising an embedding part and the component according to the invention which is embedded into the embedding part. 
     Yet further, a structural arrangement, in particular for an aircraft or spacecraft, is provided, comprising a first structure, comprising a second structure which forms an intersection region together with the first structure, and comprising the component according to the invention, which interconnects the first and second structures in the intersection region, or comprising the reinforcement member according to the invention, which interconnects the first and second structures in the intersection region. 
     Yet further, an aircraft or spacecraft comprising the structural arrangement according to the invention is provided. 
     Yet further, a method for producing a component, in particular the component according to the invention, is provided having the following steps: placing a first fibre around a first coupling element in such a way that the first fibre extends, with a first fibre portion, in a first plane in front of the coupling element and, with a second fibre portion, in a second plane behind the coupling element, the first and second planes intersecting, placing a second fibre around a second coupling element in such a way that the second fibre extends, with a first fibre portion, in a third plane in front of the coupling element and, with a second fibre portion, in a fourth plane behind the coupling element, the third and fourth planes intersecting, removing the first and second coupling elements, superposing the first fibre with the second fibre in such a way that the first fibre portions of the first and second fibres intersect in a first region and the second fibre portions of the first and second fibres intersect in a second region and therefore form a closed passage for a third coupling element, and inserting the third coupling element through the closed passage. 
     The idea on which the present invention is based consists in that two fibres are coupled in the component by means of a coupling element in such a way that the fibres can transfer loads between at least two different planes which are arranged obliquely, in particular perpendicularly, to one another. In this way, a fitting made of fibre composite material, which is connected to a landing flap by means of a coupling element of this type, can be prevented from peeling off, for example. 
     The use of the component is not limited to the aviation or aerospace industry. For example, this can also be used in lightweight construction or in bridges, high-rise buildings, pylons, roofs or other load-bearing structures. 
     In the present case, a “closed passage” should be understood to mean a passage which, viewed in a direction perpendicular to a plane in which the first or second fibre wraps around the coupling element, is completely delimited by the first and second fibres. 
     Advantageous configurations of the invention are provided in the dependent claims. 
     A multitude of first and second fibres may of course be provided. 
     According to one configuration of the component according to the invention, it is provided that the first and second planes are arranged substantially perpendicular to one another and/or the third and fourth planes are arranged substantially perpendicular to one another. In this way, the component is well suited to reinforcing structures which intersect at an angle of approximately 90 degrees. 
     According to one configuration of the component according to the invention, it is provided that the coupling element comprises one or more fibres which are in particular interwoven, the one or more fibres preferably extending in a direction perpendicular to a plane in which the first or second fibre wraps around the coupling element. In this way, a lightweight and at the same time stable coupling element can be provided. 
     According to one configuration of the component according to the invention, it is provided that the one or more fibres comprise glass or carbon and/or are provided with a thermoplastic and/or thermosetting matrix. The thermoplastic and/or thermosetting matrix is preferably cured before the first and second fibres are placed around the coupling element thus formed. 
     According to one configuration of the component according to the invention, it is provided that the coupling element is formed, preferably in the shape of a rod, from a monolithic material, in particular aluminium or titanium. In this way, the coupling element can be produced in a simple manner. It is also conceivable for the coupling element to be formed from a mixture of fibres and metal. 
     According to one configuration of the component according to the invention, it is provided that the coupling element has a rounded, in particular circular, cross-section in a plane in which the first or second fibre wraps around the coupling element. In this way, the coupling element can be produced in a simple manner, in particular extruded. 
     According to one configuration of the component according to the invention, it is provided that a multitude of first fibres which form a plurality of first fibre strands and a multitude or second fibres are provided which form a plurality of second fibre strands which are arranged so as to alternate with the first fibre strands in a direction perpendicular to a plane in which the first or second fibre wraps around the coupling element. In this way, the component can be produced in a simple manner because entire fibre strands can be more efficiently processed, in particular placed around a respective coupling element, than individual fibres. 
     According to one configuration of the component according to the invention, it is provided that the first fibre strands are interwoven with third fibre strands and the second fibre strands are interwoven with fourth fibre strands, for example, fifth fibre strands further being interwoven with the third fibre strands and forming a first closed passage together with the first fibre strands and/or sixth fibre strands being interwoven with the fourth fibre strands and forming a second closed passage together with the second fibre strands, the coupling element extending through the first and second passages. A particularly stable construction is achieved by interweaving the fibres. 
     According to one configuration of the structural arrangement according to the invention, it is provided that the first structure is formed as a box structure, in particular as a box structure of an aerofoil or control surface or a control flap, the first fibre portion of the first fibre of the component being connected to a first wall portion of the box structure and/or the second fibre portion of the second fibre being connected to a second wall portion of the box structure, the second structure preferably being configured as an internal web inside and an external web outside the box structure, the first fibre portion of the second fibre of the component being connected to the internal web and/or the second fibre portion of the first fibre of the component being connected to the external web, the external web preferably comprising an eye for attaching an adjusting member, in particular a flap carriage, a lever and/or a coupling rod. It is therefore possible in a simple manner to use the component for connecting structures. 
     According to one configuration of the structural arrangement according to the invention, it is provided that an adjusting member arranged on an aerofoil or control surface engages in the eye of the structural arrangement, the adjusting member preferably being configured as a flap carriage which is displaceably arranged on the aerofoil or control surface and is in engagement with the eye. A connection capable of being loaded is therefore produced, for example of a landing flap on an aerofoil. 
     According to one configuration of the method according to the invention, it is provided that a first woven fabric having a multitude of first fibres and a second woven fabric having a multitude of second fibres are provided, the first coupling element being pushed into a compartment instead of the weft thread when weaving the first woven fabric and the second coupling element being pushed into a compartment when weaving the second woven fabric. The first and second fibres form corresponding warp threads of the first and second woven fabrics respectively. The third and fourth fibres form corresponding weft threads of the first and second woven fabrics respectively. In this way, a simple production process is achieved. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The invention is explained in greater detail in the following by way of embodiments, with reference to the appended figures of the drawings, in which: 
         FIG. 1  is a detail of an aircraft; 
         FIG. 2A  is a schematic representation of a component according to one embodiment of the present invention; 
         FIG. 2B  is a perspective view of the component of  FIG. 2A  according to a variation; 
         FIG. 2C  is a perspective view of the component of  FIG. 2B  according to a variation; 
         FIG. 3  is a perspective view of a reinforcement member comprising a component of  FIG. 2A to 2C  according to one embodiment of the present invention; 
         FIG. 4A  is a partial section through a structural arrangement according to one embodiment of the present invention; 
         FIG. 4B  is a partial section through a structural arrangement according to a variation on  FIG. 4A ; 
         FIG. 4C  is a partial section through a structural arrangement  400  according to a variation on  FIG. 4B ; 
         FIG. 4D  is a partial section through a structural arrangement together with the reinforcement member of  FIG. 3  according to a further embodiment of the present invention; 
         FIG. 5A  is a perspective view of a structural arrangement according to a further embodiment of the present invention; 
         FIG. 5B  is a sectional view along line I-I from  FIG. 5A ; 
         FIG. 5C  is a sectional view along line II-II from  FIG. 5B ; 
         FIG. 5D  is a view III from  FIG. 5A ; 
         FIG. 6  is a schematic view of a component according to a further embodiment of the present invention; 
         FIG. 7  is a schematic view of a component according to yet another embodiment of the present invention; 
         FIG. 7A  is a basic view of a structural arrangement together with the component  200  of  FIG. 7 ; 
         FIG. 8  is a perspective view of a component according to yet another embodiment of the present invention; 
         FIG. 9A  is a perspective view of a woven fabric according to a variant on  FIG. 8 ; and 
         FIG. 9B  is a perspective view of a component according to yet another embodiment of the present invention. 
     
    
    
     In the figures, like reference numerals denote like or functionally like components, unless indicated otherwise. 
     DETAILED DESCRIPTION OF THE INVENTION 
       FIG. 2A  is a schematic representation of a component  200  according to one embodiment, kept comparatively general, of the present invention. 
     The component  200  is for example part of the landing flap  102  shown in  FIG. 1  and therefore part of the aircraft  100 . 
     In the present case, the three mutually orthogonal spatial directions are referred to as the longitudinal direction L, the transverse direction Q and the vertical direction H. Denoting the three directions serves merely to provide a better understanding of the spatial arrangement of the various elements relative to one another and is not to be taken as limiting. In the installation position of the component  200  in the landing flap  102 , the transverse direction Q corresponds to the flow direction X, the longitudinal direction L corresponds to the span direction Y and the vertical direction H corresponds to the vertical direction Z of the landing flap. 
     The component  200  comprises two fibres  202 ,  204  which are each placed around a coupling element  206 . 
     The first fibre  202  comprises a first fibre portion  208  in front of the coupling element  206  and a second fibre portion  210  behind the coupling element  206 . “In front of” and “behind” in this case relate to a contact region  212  in which the first fibre  202  contacts the outer circumference  214  of the coupling element  206  and therefore wraps around said element in portions. The first fibre portion  208  extends in a first plane  216 . The second fibre portion  210  extends in a second plane  218 . The first and second planes  216 ,  218  intersect, for example as shown, at an angle of 90 degrees. 
     The second fibre  204  also comprises a first fibre portion  220  in front of the coupling element  206  and a second fibre portion  222  behind the coupling element  206 . Here, too, “in front of” and “behind” relate to a contact region  224  in which the second fibre  204  contacts the outer circumference  214  of the coupling element  206  and therefore wraps around said element in portions. The first fibre portion  220  extends in a third plane  226 . The second fibre portion  222  extends in a fourth plane  228 . The third and fourth planes  226 ,  228  intersect, for example as shown, at an angle of 90 degrees. 
     Furthermore, the first fibre portions  208 ,  220  of the first and second fibres  202 ,  204  intersect in a first region  230 . The second fibre portions  210 ,  222  of the first and second fibres  202 ,  204  intersect in a second region  232 . The first and second regions  230 ,  232  are at a distance from one another and, for example as shown, are opposite one another relative to the coupling element  206 . In addition, the first and third planes  216 ,  226  preferably intersect at an angle of 90 degrees. Correspondingly, the second and fourth planes  218 ,  228  preferably also intersect at an angle of 90 degrees. As a result, the first fibre portion  208  of the first fibre  202  and the second fibre portion  222  of the second fibre  204  extend in the longitudinal direction L on both sides of the coupling element  206 , but in different planes  216 ,  228 . However, the first fibre portion  220  of the second fibre  204  and the second fibre portion  210  of the first fibre  202  extend in the vertical direction H on both sides of the coupling element  206 , but in different planes  218 ,  226 . The coupling element  206  extends in the transverse direction Q. 
     Typically, a multitude of first and second fibres  202 ,  204  are provided which each form a strand. The fibres  202 ,  204  are for example made of carbon, aramid or glass and are infiltrated with a thermosetting or thermoplastic matrix. 
     The coupling element  206  can be formed in various ways, but should have a high shear strength in planes  234  (paper plane and planes parallel thereto) in which a respective fibre  202 ,  204  wraps around the coupling element  206 . 
     For example, the coupling element  206  can comprise a multitude of fibres (not shown), in particular made of glass or carbon. The fibres extend exclusively or predominantly in the transverse direction Q, that is to say perpendicular to the respective planes  234 . The fibres can be interwoven. The fibres are preferably provided with a thermosetting or thermoplastic matrix which is cured once the component  200  is, for example, installed in the landing flap. 
     Alternatively, the coupling element  206  is formed from a monolithic material, in particular aluminium or titanium. The coupling element  206  is preferably formed as a rod. 
     The component  200  can for example be produced in that the first fibre  202  is placed around a first coupling element (not shown) in such a way that the first fibre  202  extends, with the first fibre portion  208 , in the first plane  216  in front of the first coupling element and, with the second fibre portion  210 , in the second plane  218  behind the coupling element. Hereafter, prior thereto or simultaneously, the second fibre  204  is placed around a second coupling element (not shown) in such a way that the second fibre  204  extends, with the first fibre portion  220 , in the third plane  226  in front of the second coupling element and, with the second fibre portion  222 , in the fourth plane  228  behind the second coupling element. Subsequently, the first and second coupling elements are removed. In a further step, the first fibre  202  is superposed with the second fibre  204  in such a way that the first fibre portions  208 ,  220  cross over in a first region  230  and the second fibre portions  210 ,  222  cross over in a second region  232  and thereby form a closed passage  235 , viewed in the transverse direction Q. In this case, the fibres  202  and  204  are in two different planes  234  which are at a distance from one another but are parallel. The third coupling element  206  is inserted through this passage  235 , whereby the first and second fibres  202 ,  204  are interconnected in an interlocking manner. 
       FIG. 2A  shows the coupling element  206  having a circular cross-section. Alternatively, the cross-section of the coupling element  206  is also merely rounded, for example oval, or is triangular or square having rounded corners. The cross-section is preferably constant in the transverse direction Q. 
       FIG. 2B  is a perspective view of the component  200  of  FIG. 2A  according to a variation. 
     First fibre portions  208  of first fibres  202 ,  202 ′ together form a first arm  236 , second fibre portions  210  of the first fibres  202 ,  202 ′ together form a second arm  238 , first fibre portions  220  of second fibres  204 ,  204 ′ together form a third arm  240  and second fibre portions  222  of the second fibres  204 ,  204 ′ together form a fourth arm  242 . The first and fourth arms  236 ,  242  are for example mutually offset in the vertical direction H and the second and third arms  238 ,  240  in the longitudinal direction L. For the purposes of better understanding, the fibres  202 ,  202 ′,  204 ,  204 ′ are merely indicated schematically. 
     For example, three arms  236 ,  240 ,  242  can each taper away from the coupling element  206 , and this is achieved by correspondingly cutting back the fibres  202 ,  202 ′,  204 ,  204 ′. The arm  238  has a constant thickness D. 
     The arm  238  is further provided with an eye  244 . This is suitable for attaching a flap carriage  106 ,  108 . The multitude of second fibre portions  210  (indicated by dashed lines) adjoin the eye  244  and correspondingly receive loads acting on the eye  244 . This load is then conducted into the arm  240  via the coupling element  106 . In response, the fibres in the arms  236  and  242  receive reaction forces via the coupling element  206 . By means of the coupling element  206 , the loads are transmitted from a respective first fibre  202  to a respective second fibre  204  and are then transmitted into the arms  240  and  242  by means of the first and second fibre portions  220 ,  222 . 
       FIG. 2C  is a perspective view of the component  200  of  FIG. 2B  according to a variation. 
     In the embodiment according to  FIG. 2C , the arm  238  is also configured in such a way that it tapers away from the coupling element  206 . In addition, the arm  238  does not comprise an eye. 
       FIG. 3  is a perspective view of a reinforcement member  300  comprising a component  200  of one of  FIG. 2A to 2C . The multitude of fibres  202 ,  204  is embedded into an embedding part  301 . The embedding part  301  has a cruciform cross-section comprising a first, a second, a third and a fourth arm  302 ,  304 ,  306 ,  308 . The embedding part  301  preferably comprises a fibre composite material. A fibre portion  208 ,  210 ,  220  or  222  is received in an integrated manner in each of the arms  302 ,  304 ,  306 ,  308 . The coupling element  206  is in the centre of the cross  310 . Owing to the embedding material  301 , the reinforcement member  300  can be configured such that the arms  304 ,  308  are in the same plane QL, that is to say not mutually offset, and the arms  302 ,  306  are in the same plane HQ, that is to say also not mutually offset. 
     For example, three of the arms  304 ,  306 ,  308  can taper away from the centre of the cross  310  while one arm  302  has a constant thickness D. The tapering of each arm  304 ,  306 ,  308  can be provided in the form of a plurality of steps  311 . 
     The arm  302  comprises an eye  312  for fastening, for example, a flap carriage  106 ,  108  of  FIG. 1 . The multitude of the second fibre portions  210  (indicated by dashed lines) adjoin the eye  312  and correspondingly receive loads acting on the eye  312 , as already explained above in conjunction with  FIG. 2B . These loads are then directly conducted into the arm  304  inside a respective first fibre  202  by means of a respective first fibre portion  208 . By means of the coupling element  206 , the loads are transmitted from a respective first fibre  202  to a respective second fibre  204  and are then transmitted into the arms  306  and  308  by means of the first and second fibre portions  220 ,  222 . 
       FIG. 4A  is a partial section through a structural arrangement  400  according to one embodiment of the present invention. 
     The structural arrangement  400  comprises a substantially closed box structure  402  (only shown in part). In the present case, “substantially closed” includes a box structure having a completely closed outer contour and a box structure having comparatively small openings in the outer contour. 
     The box structure  402  comprises in particular a lower outer wall  404 . The lower outer wall  404  forms an intersection region  406  comprising an internal and an external web  408 ,  410  of the structural arrangement  400 . The internal web  408  is arranged inside the box structure  402 , that is to say in an internal space  411  thereof, and the external web  410  is arranged outside the box structure  402 . 
     The component  200  according to the embodiment described in conjunction with  FIG. 2B  is arranged in the intersection region  406 . The second portions  210  of the first fibres  202 ,  202 ′ extend inside the external web  410 , the first portions  220  of the second fibres  204 ,  204 ′ extend inside the internal web  408 , the first portions  208  of the first fibres  202 ,  202 ′ extend inside a first portion  414  of the outer wall  404  and the second portions  222  of the second fibres  204 ,  204 ′ extend inside a portion  416  of the outer wall  404  which is opposite the first portion  414 . The portions  220 ,  210  are rigidly connected to the respective webs  408 ,  410  thereof and the portions  208 ,  222  are rigidly connected, in particular adhered, to the respective portions  414 ,  416  thereof. For the sake of clarity, a corresponding resin matrix  412  is only shown in part. 
     The component  200  can be glued into the box structure  402  and into the webs  408 ,  410  in various ways. The completely or partly cured component  200  can be cured together with the wet box structure  402  (prepreg) and the wet webs  408 ,  410  (prepreg). Furthermore, the completely or partly cured component  200  can be structurally adhered to the completely or partly cured box structure  402  and the completely or partly cured webs  408 ,  410 . Yet further, the dry component  200  and the dry box structure  402  and dry webs  408 ,  410  can be infiltrated and cured together. Furthermore, the wet component  200  and the wet box structure  402  and wet webs  408 ,  410  can be adhered to one another. 
     The internal web  408  can be configured as a rib or spar which is connected in particular to an upper outer wall  418  of the box structure  402 . 
       FIG. 4B  is a partial section through a structural arrangement  400  according to a variation on  FIG. 4A . 
     In the structural arrangement  400  according to  FIG. 4B , the component  200  of  FIG. 2B  is integrated into the structural arrangement  400  of  FIG. 4A . While for example, as indicated in  FIG. 4A , the fibre portions  208 ,  222  can extend in the longitudinal direction L inside the lower wall  404  over the entire extension thereof, the tapering arms  236 ,  242  of the component  200  are configured to be comparatively short in  FIG. 4B  and extend in the longitudinal direction L inside the lower wall  404  only over part of the entire extension of said lower wall  404 . The same applies to the upper tapering arm  240  in the internal web  408 . 
     The eye  244  in the component  200  forms an eye  420  together with corresponding passages  418 ,  419  in the external web  410 . This is suitable for attaching a flap carriage  106 ,  108 . 
       FIG. 4C  is a partial section through a structural arrangement  400  according to a variation on  FIG. 4B . 
     In the structural arrangement  400  according to  FIG. 4C , the component  200  of  FIG. 2C  is integrated into the structural arrangement  400  of  FIG. 4B . In contrast to  FIG. 4B , the lower tapering arm  238  extends in the vertical direction H inside the external web  410  only over part of the entire extension of said external web  410 . The external web  410  can comprise an eye  420  which the arm  238  does not penetrate by said eye being arranged at a distance therefrom in the vertical direction. 
       FIG. 4D  is a partial section through a structural arrangement  400  according to a further embodiment of the present invention. 
     Instead of the component  200 , as in the embodiments according to  FIG. 4A to 4C , the reinforcement member  300  of  FIG. 3  is arranged in the intersection region  406 . The first arm  302  extends inside the external web  410 , the third arm  306  extends inside the internal web  408 , the second arm  304  extends inside the first portion  414  and the fourth arm  308  extends inside the portion  416 . The arms  302 ,  306  are rigidly connected to the respective web  408 ,  410  thereof and the arms  304 ,  308  are rigidly connected, in particular adhered, to the respective portion  414 ,  416  thereof, in particular adhered. For the sake of clarity, a corresponding resin matrix  412  is only shown in part. 
     The reinforcement member  300  can be glued into the box structure  402  and into the webs  408 ,  410  for example in the way which is described for the component  200  in conjunction with the embodiment according to  FIG. 4A . 
     The eye  312  in the reinforcement member  300  forms an eye  420  together with corresponding passages  418 ,  419  in the external web  410 . 
       FIG. 5A  is a perspective view of a structural arrangement  400  according to a further embodiment of the invention. The structural arrangement  400  forms part of a landing flap  102 . 
     The structural arrangement  400  comprises a substantially closed box structure  402  which forms the outer wall of the aerodynamic profile of the landing flap  102 . In the Y direction, that is to say the span direction, the box structure  402  is preferably open. Internal webs  408  in the form of transverse ribs and transverse webs  500  extend inside the box structure  402 . 
     A reinforcement member  300  is integrated into the box structure  402  and a transverse rib  408 , as described with reference to  FIG. 3 , in such a way that the arm  302  of said rib extends downwards in the Z direction. The arm  306  points into the inner space  411  of the box structure  402  and is preferably integrated into the transverse rib  408 . The arms  304 ,  308  are integrated into the lower outer wall  404 . The external web  410  extends downwards from the lower outer wall  404  and forms the eye  420 . The eye  420  is therefore arranged below the box structure  402  and is thus well suited to being connected to a flap carriage  106 ,  108  (not shown). 
     As can be seen from the sectional view along line I-I from  FIG. 5A  which is shown in  FIG. 5B  and shows a more specific configuration compared with  FIG. 5A , the arm  306  is inside the transverse rib  408 , which is preferably connected over the entire circumference thereof to the box structure  402 . The left-hand and right-hand ends of the arm  306  in  FIG. 5B  are indicated by a dot-dash line. With reference to  FIG. 5B , it is to be noted in particular that the transverse rib  408  and preferably the arm  306  attach at the top to the upper outer wall  418  of the box structure  402 , that is to say are fastened thereto. 
     The external web  410  can comprise bevels  502  in order to additionally save material. 
       FIG. 5C  is a sectional view along line II-II from  FIG. 5B . With a view to a more simplified representation,  FIG. 5C  does not differentiate between the material of the reinforcement member  300  and the material of the box structure  402  and the webs  408 ,  410 . 
     With reference to  FIG. 5C , it is shown that the structural arrangement  400  can further comprise a pair of angular parts  504 , for example made of fibre composite material or metal, which are arranged on both sides of the external web  410  and reinforce the eye  420 . The angular parts  504  each comprise webs  506  together with eyes  508 , which correspond to the eye  420 . The angular parts  504  each further comprise a foot  510  with which they contact the lower outer wall  404 . The feet  510  are each fastened by four bolts  512  to the box structure  402 . The bolts  512  can comprise a head  514 , with which they engage behind the upper outer wall  418 , and the shaft  516  thereof can extend through the reinforcement member  300 . The end  518  of each shaft  516  is screwed to the corresponding foot  510 . 
     As is to be noted with reference to  FIG. 5D , which is a view III from below from  FIG. 5A , eight bolts  512  can be provided per reinforcement member  300  which penetrate said member or are arranged contiguously thereto. For the sake of clarity, in  FIG. 5D  the angular parts  504  and also the external web  410  are not shown. 
     Instead of the reinforcement member  300 , a component  200  according to one of the embodiments described herein could equally be used. 
       FIG. 6  is a schematic view of a component  200  according to a further embodiment of the present invention. 
     In contrast to the embodiment according to  FIG. 2A , the component  200  according to  FIG. 6  comprises a plurality of first fibres  202 ,  202 ′ which are arranged so as to alternate with a plurality of second fibres  204 ,  204 ′ in the transverse direction Q. 
       FIG. 7  is a schematic view of a component  200  according to yet another embodiment of the present invention. 
     In contrast to the embodiment according to  FIG. 6 , the component  200  according to  FIG. 7  additionally comprises a plurality of third fibres  702 ,  702 ′ and fourth fibres  704 ,  704 ′. 
     Each third fibre  702 ,  702 ′ comprises a first fibre portion  708  in front of the coupling element  206  and a second fibre portion  710  behind the coupling element  206 . In the present case, “in front of” and “behind” refer to a contact region  712  in which the third fibre  702  (in this instance, “fibre” always means “each” fibre, unless otherwise stated) contacts the outer circumference  214  of the coupling element  206  and therefore wraps around said element in portions. The first fibre portion  708  extends in a fifth plane  716 . The second fibre portion  710  extends in a sixth plane  718 . The fifth and sixth planes  716 ,  718  intersect, for example as shown, at an angle of 90 degrees. 
     Each fourth fibre  704  also comprises a first fibre portion  720  in front of the coupling element  206  and a second fibre portion  722  behind the coupling element  206 . Here, too, “in front of” and “behind” refer to a contact region  724  in which the fourth fibre  704  contacts the outer circumference  214  of the coupling element  206  and therefore wraps around said element in portions. The first fibre portion  720  extends in a seventh plane  726 . The second fibre portion  722  extends in an eighth plane  728 . The seventh and eighth planes  726 ,  728  intersect, for example as shown, at an angle of 90 degrees. 
     Furthermore, the first fibre portions  708 ,  720  of the third and fourth fibres  702 ,  702 ′,  704 ,  704 ′ intersect in a third region  730 . The second fibre portions  710 ,  722  of the third and fourth fibres  702 ,  702 ′,  704 ,  704 ′ intersect in a fourth region  732 . The third and fourth regions  730 ,  732  are at a distance from one another and, for example as shown, are opposite one another relative to the coupling element  206 , in such a way that the intersection regions  230 ,  232 ,  730 ,  732  are at the corners of a rectangle. In addition, the fifth and seventh planes  716 ,  726  preferably intersect at an angle of 90 degrees. Correspondingly, the sixth and eighth planes  718 ,  728  also preferably intersect at an angle of 90 degrees. As a result, the first fibre portion  708  of the third fibre  702  and the second fibre portion  722  of the fourth fibre  704  extend in the longitudinal direction L on both sides of the coupling element  206  in different planes. However, the first fibre portion  720  of the fourth fibre  704  and the second fibre portion  710  of the third fibre  702  extend in the vertical direction H on both sides of the coupling element  206 . The planes  216 ,  728 , the planes  226 ,  726 , the planes  228 ,  716  and the planes  218 ,  718  are each in the same plane. The planes  216 ,  728  are arranged so as to be offset to the planes  228 ,  716  in a parallel manner in the vertical direction. The planes  226 ,  726  are arranged so as to be offset to the planes  218 ,  718  in a parallel manner in the longitudinal direction L. 
     By means of the component  200  shown in  FIG. 7 , during installation thereof in a box structure  402  and webs  408 ,  410  (see one of  FIG. 4A to 4C ), it is achieved that the wall portions  414 ,  416  can be arranged in the same plane and the webs  408 ,  410  can be arranged in the same plane, and not in different planes (as is the case in  FIG. 4A to 4C ). 
       FIG. 7A  is a basic view of a structural arrangement  400  together with the component  200  of  FIG. 7 . 
     Additional layers  734  are introduced, in particular glued, into intermediate spaces respectively formed between the fibres  202 ,  702 , the fibres  202 ,  704 , the fibres  204 ,  702  and the fibres  204 ,  704 . Together with these layers  734 , the component  200  is surrounded in this case by external fibres  404 ,  408  via which said component is inserted into the box structure  402 . 
       FIG. 8  is a perspective view of a component  200  according to yet another embodiment of the present invention. 
     The component  200  comprises first fibres  202  which form a plurality of first fibre strands  800 . Furthermore, the component  200  comprises second fibres  204  which form a plurality of second fibre strands  802 . The fibre strands  800 ,  802  wrap around the coupling element  206  in such a way that they alternate in the transverse direction Q. 
     The first fibre strands  800  are interwoven with third fibre strands  804  which extend in the transverse direction Q. Correspondingly, fourth fibre strands  806  are interwoven with the second fibre strands  802 . 
     The two separate woven fabrics  805 ,  807  thus formed can be easily glued into an intersection region  406  of a structural arrangement  400  or connected thereto in another way. A first woven fabric portion  808  of the woven fabric  805  is preferably glued into an external web  410 , see for example  FIG. 4A , a second woven fabric portion  810  of the woven fabric  805  is glued into a first portion  414  of a box structure  402 , a first woven fabric portion  812  of the woven fabric  807  is glued into an internal web  408  and a second woven fabric portion  814  of the woven fabric  807  is glued into a second portion  416  of the box structure  402 , or they are connected to said webs or portions in another way. 
     The necessary clearance for pushing the coupling element through the woven fabric  805 ,  807  is for example created in that a fibre strand  804  is omitted in a first woven fabric  805  and a fibre strand  806  is omitted in a second woven fabric  807 . Subsequently, the woven fabrics  805 ,  807  are each bent in the region of the omitted fibre strand  804 ,  806  and are arranged in such a way that the first and second fibre strands  800 ,  802  overlap. Hereafter, the coupling element is pushed through the closed passage  816  which is formed. 
       FIG. 9A  is a perspective view of a woven fabric  805  according to a variant on the embodiment according to  FIG. 8 . In this case, the angular woven fabric  805  points away from the observer. 
     The woven fabric  805  comprises five fibre strands  900  which form the closed passage  816  together with the first fibre strands  800  in the LH plane and also preferably extend parallel to the first fibre strands  800 . In addition, the fifth fibre strands  900  are arranged so as to alternate together with the first fibre strands  800  in the transverse direction Q and are interwoven with the third fibre strands  804 . 
     Correspondingly, the woven fabric  807  shown in  FIG. 9B  comprises sixth fibre strands  902  (corresponding fibres are shown in a partially transparent view) which are interwoven with the fourth fibre strands  806  and form second closed passages  816 ′ together with the second fibre strands  802 . 
       FIG. 9B  is a perspective view of a component  200  according to a further embodiment of the present invention. 
     The component  200  comprises two woven fabrics  805 ,  807  which are each formed according to the model in  FIG. 9A . The woven fabrics  805 ,  807  are overlapped at the respective passages  816 ,  816 ′ thereof. The coupling element  206  is inserted through the passages  816 ,  816 ′. 
     The component  200  can for example be produced in that, when weaving the first woven fabric  805 , a first coupling element is pushed into a formed compartment (not shown) instead of the weft thread. When weaving the second woven fabric  807 , a second coupling element is pushed into a formed compartment (not shown) instead of the weft thread. Subsequently, the first and second coupling elements are pulled out, which then overlaps the formed passages  816 ,  816 ′ and a (third) coupling element  206  is inserted through said passages. Hereafter, the first and second woven fabrics  805 ,  807  are rigidly interconnected by means of the third coupling element  206 . The first and second coupling elements can each be provided as the shown coupling element  206 . 
     The components  200  of  FIGS. 8 and 9B  can be used in the same way as described above for the components  200  of the previous embodiments. 
     The fibres  202 ,  204 ,  702 ,  704  and the fibres which are not referred to in detail of the above-mentioned fibre-strands  804 ,  806 ,  900 ,  902  can for example be made of carbon, glass and/or aramid. 
     Although the present invention has been disclosed by way of preferred embodiments, it is not in any way limited thereto, but can be modified in various ways. In particular, the embodiments and configurations which are mentioned for the component according to the invention can be used correspondingly for the reinforcement member according to the invention, the structural arrangement according to the invention, the vehicle according to the invention and the method according to the invention, and vice versa. Furthermore, “a” or “one” does not exclude a plurality in the present case. In particular, the structural arrangement according to the invention can not only be used for landing flaps, but also for complete box structures such as control flaps.