Patent Publication Number: US-2017355110-A1

Title: Reinforcing component for a structure of an aircraft or spacecraft, aircraft or spacecraft, and method

Description:
FIELD OF THE INVENTION 
     The invention relates to a reinforcing component for a structure of an aircraft or spacecraft and to an aircraft or spacecraft comprising a reinforcing component of this type. The invention further relates to a method for manufacturing a reinforcing component. 
     Although the present invention is applicable to various structural components and in particular to structural reinforcing components in aircraft or spacecraft, the invention and the set of problems on which it is based are to be described in greater detail in the following using the example of a former for reinforcing a skin element for an aeroplane fuselage. 
     BACKGROUND OF THE INVENTION 
     It has previously been proposed to configured formers, for example for the fuselage of an aeroplane, as fibre composite components, for example made of a carbon-fibre-reinforced plastics material. 
     In conventional fuselage structures, additional elements, which are intended to brace the fuselage former for example against tilting, are often additionally connected to the former by riveting or by means of bolts. Thus for example a former can be riveted in a conventional manner during the manufacture of the fuselage structure by means of connecting elements, which are often referred to as “clips” and may comprise a stabilising flange. 
     DE 10 2014 103 438 A1 and WO 2015/007455 A1 disclose manufacturing a primary structure connecting element for fixing an aeroplane skin to an aeroplane primary structure from a fibre-reinforced thermoplastic composition by injection moulding. For example, former-stabilising elements (cleats) are disclosed which are produced from a fibre-reinforced thermoplastic material by injection moulding. In turn, a cleat is connected to a former by means of rivets or bolts. 
     The construction of a fuselage structure using formers to which a plurality of further elements, such as cleats for stabilising, are attached individually by rivets has been found to be expensive. 
     EP 2 746 038 A1 discloses a fibre-reinforced reinforcing element comprising an integrated stabilising portion, the reinforcing element being manufactured starting from a hollow profile made of a fibre-reinforced plastics material using epoxy resin or phenol resin. Although in this way it is already possible to manufacture a reinforcing element of low weight much more simply and efficiently, further simplification of the manufacture of reinforcing elements for the aerospace industry would be desirable. 
     BRIEF SUMMARY OF THE INVENTION 
     One of the ideas of the invention is to provide a reinforcing component which can be manufactured in an even simpler and further improved manner. Additionally, a correspondingly improved method of manufacture is to be provided. 
     Accordingly, a reinforcing component for a structure of an aircraft or spacecraft is proposed which comprises a first component region for reinforcing at least one other element, in particular at least one skin portion, and at least one second component region. In particular, the first component region is elongate. The second component region is permanently connected to the first component region. The reinforcing component is formed using a thermoplastic plastics material in each of the first component region and the second component region. In the first component region, the thermoplastic plastics material forms a matrix in which continuous reinforcing fibres are embedded. Further, in the second component region, the reinforcing component comprises discontinuous reinforcing fibres or is free of reinforcing fibres. 
     Additionally, an aircraft or spacecraft comprising a reinforcing component of this type is proposed. 
     Further, the invention proposes a method for manufacturing a reinforcing component for a structure of an aircraft or spacecraft, a first component region, which is in particular elongate, for reinforcing at least one other element, and at least one second component region being formed and permanently interconnected. The reinforcing component is formed using a thermoplastic plastics material in each of the first component region and the second component region. Further, in the first component region, the thermoplastic plastics material forms a matrix in which continuous reinforcing fibres are embedded. In the second component region, the reinforcing component is formed with discontinuous reinforcing fibres or free of reinforcing fibres. 
     In particular, the reinforcing component according to the invention can be manufactured by the method according to the invention. 
     An idea behind the present invention is to construct the reinforcing component using a hybrid design. Whilst continuous reinforcing fibres are used in the first component region to provide particularly favourable mechanical properties, either a thermoplastic free of reinforcing fibres or a thermoplastic matrix having discontinuous reinforcing fibres embedded therein is used in the second component region, for example depending on the load. As a result, a first component region of a geometrically simpler basic shape can advantageously be formed using the continuous fibres, which require relatively considerable expense for correct embedding in the thermoplastic matrix. However, advantageously, the second component region, which contains discontinuous fibres or is free of reinforcing fibres, can be manufactured by a simpler method and if required in a more complicated geometry. The two component regions together form a hybrid reinforcing component, of which the geometric shape may be relatively complex overall, but which still has the properties of continuous fibres in a component region in which these properties are desired. The reinforcing component according to the invention may advantageously be manufactured at reduced expense. The use of thermoplastic plastics materials in the first and second component regions additionally makes possible permanent connection of the two component regions in a simple and reliable manner without the need for riveting. It is thus possible to produce an integral reinforcing component efficiently. Continuous and discontinuous fibre reinforcement of thermoplastic plastics materials can be combined in one component. 
     Advantageous embodiments and developments of the invention may be derived from the further dependent claims and from the description with reference to the drawings. 
     In an embodiment, the first component region and the second component region are produced by separately providing a first component element and a second component element and by subsequently welding the second component element to the first component element. As a result, the first and second component regions can be reliably connected in a simple manner and without the need for additional connecting elements such as rivets. 
     In a development, the second component element is preferably injection-moulded. By injection moulding, second component elements can be produced expediently and efficiently even in larger numbers and with a relatively complex geometry. 
     In an alternative embodiment, the first component region and the second component region are produced by providing a first component element and subsequently spraying the second component region on by injection moulding. It may in particular be sprayed on by overmoulding, in which the first component element is laid in an injection moulding mould having additional cavities for forming the second component regions and the second component regions are sprayed on by means of the additional cavities. 
     In an embodiment of the method, to produce the first and second component regions, a first component element and a second component element are provided separately and subsequently welded together. In an alternative embodiment, to produce the first and second component regions, a first component element is provided and the second component region is produced by spraying the second component region on in an injection moulding method. 
     In an embodiment, short or long fibres are embedded in the thermoplastic plastics material as discontinuous reinforcing fibres in the second component region. Reinforcing fibres formed as short fibres may in particular be of a length of up to approximately 1 mm, whilst reinforcing fibres formed as long fibres may in particular be of a length of up to approximately 50 mm. Short or long fibres of this type can be processed well by injection moulding, for example for producing the second component element before the welding or for spraying the second component region on by overmoulding. 
     In some embodiments, the reinforcing component is formed as a former or a former element, in particular as a former or former element for a fuselage cell structure of the aircraft or spacecraft. A former element should be understood to mean in particular a sub-piece of a former which extends annularly along the peripheral direction of a fuselage. A former element of this type may for example be used in a fuselage shell for the aircraft or spacecraft. 
     However, it is also conceivable to form other reinforcing components for the structure of the aircraft or spacecraft in a manner according to the invention. 
     For example, in an alternative embodiment, the reinforcing component may be formed as a component of a door frame structure for an aircraft or spacecraft. 
     In an embodiment, the second component region is formed and arranged for reinforcing the first component region at least in portions and/or for stabilising the first component region against tilting at least in portions. Specifically if the reinforcing component is to be stabilised at a plurality of points along the longitudinal extension thereof, the manufacturing outlay can be reduced as a result of the hybrid configuration according to the invention of the reinforcing component, for example by avoiding rivet connections. In particular, even in the case of second component elements which are injection-moulded and subsequently welded to the first component element, a further reduction in the manufacturing outlay can be achieved by standardisation. 
     In some embodiments, the first component region is formed with a web and with a flange connected to the web. The second component region for reinforcing the web is arranged orientated transverse to the web and the flange in the manner of a rib. Effective stabilisation of the reinforcing component is thus achieved. 
     In some embodiments, the first component region further comprises a foot region connected to the web for coupling the reinforcing component to the other element, in particular to a skin portion, the second component region being permanently connected to the foot region and the web and bracing the web against the foot region. This further improves the stabilisation and reinforcement of the web. In particular, the foot region may be a sub-region of a further flange connected to the web or a flange-shaped portion, connected to the web, of the first component. 
     In an embodiment, the second component region is formed as a belt permanently connected to the first component region or formed with a belt of this type. The belt may in particular be provided in addition to a first belt or flange already formed in the first component region. This can greatly simplify the production of a reinforcing component which is for example to have a plurality of belts or flanges so as to perform the mechanical functions thereof. For example, using this embodiment, a first component region may advantageously be shaped into a comparatively simple cross-sectional shape, for example a Z-shape, for example by folding or deformation of a semi-finished product, whilst the additionally desired belt or flange may for example be permanently connected to the first component region as a second component region for example by spraying on or welding on. 
     Additionally, in particular, in further embodiments second component regions for stabilising the web, which extend for example transverse to the web and to the longitudinal direction of the reinforcing component in the manner of ribs, and at least one further second component region in the form of an additional belt may be combined in a reinforcing component. The regions which stabilise the web and the additional belt may also be combined as sub-regions in a shared second component region. 
     In some embodiments, the second component region is provided with at least one means for attaching cabin components and/or systems or forms a holding means for cabin components and/or systems. In this embodiment, the possibility of providing the second component region with relatively complex geometries makes it possible to integrate holding functions, making it possible to omit attaching additional holders and reduce outlay and weight. 
     In particular, in some embodiments, second component regions for stabilising the first component region and second component regions for holding cabin or system components may be present as separate component regions, each permanently connected to the first component region. Advantageously, component regions of this type having different functions are thus combined in a reinforcing component, but can still be manufactured efficiently and expediently, in a manner appropriate to the associated function. 
     In some embodiments, at least one component made of a metal material may be integrated into the second component region at least in regions by injection moulding or spraying. For example, the component made of the metal material may be an element of the means for attaching the cabin components and/or systems, for example a socket, for example with or without an internal thread. By means of the injection moulding, the additional metal component can be integrated into the reinforcing component reliably and rapidly in various ways. 
     In particular, the reinforcing component may have a plurality of second component regions. The second component regions may be formed identically, making possible further reductions in outlay and costs by way of standardisation. 
     The reinforcing fibres in the first and second component region may in each case for example be glass fibres, carbon fibres or other suitable fibres or combinations thereof, it being understood that the reinforcing fibres in the first component region are endless or continuous fibres, whereas reinforcing fibres for the second component region are discontinuous fibres. This makes it possible to manufacture a reinforcing component formed as a hybrid thermoplastic fibre composite component efficiently. 
     In particular, in some embodiments, it may be provided that the reinforcing fibres in the first component region are formed using a material different from the material of the reinforcing fibres in the second component region. 
     For example, in an embodiment, discontinuous glass fibres, for example short glass fibres, may be embedded in the thermoplastic plastics material as a matrix in the second component region, whilst in the first component region continuous carbon fibres are embedded in the thermoplastic plastics matrix thereof. In this way, the first component region can be given particularly good mechanical properties for the reinforcing function thereof, whilst as a result of the use of discontinuous glass fibres in the second component region electrical conductivity can be eliminated or reduced. This can advantageously contribute to preventing or reducing the occurrence of galvanic corrosion if a metal component, for example made of an aluminium material, is connected to the second component region. 
     In other embodiments, however, it may be provided that the reinforcing fibres in the first and second component regions are formed from the same material. For example, carbon fibres may be provided in both component regions. 
     In some embodiments, it may be provided that the thermoplastic plastics material in the first component region is different from the thermoplastic plastics material in the second component region. In particular, the respective thermoplastic plastic materials in the first and second component regions may differ in the respective melting points and/or glass transition temperatures thereof. This may be advantageous for carrying out a welding process to connect the first and second component elements or for spraying on the second component region. For example, in this way it would be possible to influence, in a targeted manner, which of the thermoplastic materials starts to soften and/or melt first during heating. 
     In particular high-grade thermoplastics are possible as thermoplastic plastics materials. For example, in the first and/or second component region, a semi-crystalline thermoplastic may be used as the thermoplastic plastics material in each case, for example a polyaryletherketone (PAEK), a polyetheretherketone (PEEK) or the like. 
     The above embodiments and developments of the invention are applicable analogously to the reinforcing component, the aircraft or spacecraft and the method according to the invention. 
     The above embodiments and developments may be combined with one another in any desired manner within reason. Further possible embodiments, developments and implementations of the invention also include combinations not explicitly mentioned of features of the invention disclosed above or in the following in relation to the embodiments. In particular, a person skilled in the art will also add individual aspects to each basic form of the present invention as improvements or additions. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The present invention is described in greater detail in the following by way of the embodiments set out in the schematic drawings, in which: 
         FIG. 1  is a perspective view of an aeroplane in which reinforcing components in accordance with embodiments of the invention may be used; 
         FIG. 2  is a side view of the aeroplane of  FIG. 1 ; 
         FIG. 3  shows a reinforcing component, formed as a former, in accordance with a first embodiment, together with an example skin element of a fuselage skin; 
         FIG. 4  is a schematic sectional view A-A of the reinforcing component of  FIG. 3 ; 
         FIG. 5  shows a sub-region of the reinforcing component of  FIG. 3 , again in the section A-A, in accordance with a variant of the first embodiment; 
         FIG. 5A  is a perspective view of a sub-region of the reinforcing component of  FIG. 3  in a further variant of the first embodiment; 
         FIG. 6  shows a reinforcing component formed as a former in accordance with a second embodiment of the invention; and 
         FIG. 7  is a schematic sectional view B-B of the reinforcing component of  FIG. 6 . 
     
    
    
     The accompanying drawings are intended to provide a further understanding of the embodiments of the invention. They illustrate embodiments, and are intended to explain principles and concepts of the invention in connection with the description. Other embodiments and many of the stated advantages can be seen from the drawings. The elements of the drawings are not necessarily to scale. 
     In the drawings, unless specified otherwise, like, functionally equivalent and equivalently acting elements, features and components are provided each with like reference numerals. 
     DETAILED DESCRIPTION 
       FIGS. 1 and 2  show an aircraft in the form of a passenger aeroplane  1 , which comprises a fuselage  2 , aerofoils  3  and tail units  5  and  7 . Reinforcing components in accordance with the embodiments of the invention disclosed in the following with reference to  FIGS. 3 to 7  may be used in the aeroplane  1  of  FIGS. 1 and 2 . 
     A first embodiment of a reinforcing component  11  formed as a former for a fuselage structure of the aeroplane  1  of  FIG. 1, 2  is shown schematically in portions in  FIG. 3 . 
     The reinforcing component  11  of  FIG. 3  comprises a first component region  13  and a plurality of second component regions  17 , merely a portion of the reinforcing component  11  comprising two second component regions  17  being shown in  FIG. 3  for reasons of clarity. For illustrative purposes, the two second component regions  17  are each enclosed in a dashed line in  FIG. 3 . The second component regions  17  are formed identically in the first embodiment. 
     The first component region  13  is of an elongate shape curved along a longitudinal direction L of the reinforcing component  11 , and extends in the aeroplane  1  in the peripheral direction U of the fuselage  2 . A function of the first component region  13  is to reinforce a skin portion  19  of a fuselage skin  23  of the fuselage  2 . For this purpose, the first component region  13  comprises a web  14  and a flange  15  integrally connected to the web  14 , the web  14  and the flange  15  extending along the longitudinal direction L of the reinforcing component  11  in the peripheral direction U of the fuselage  2 . The first component region  13  further comprises foot regions  16  integrally connected to the web  14  for coupling the reinforcing component  11  to the skin portion  19 . Further, on the side facing the skin portion  19 , the first component region  13  comprises clearances  29 , for example for passing stringers (not shown in the drawing) through as further reinforcing elements for the skin portion  19 . 
     The second component regions  17  are each formed as a wall-like region having a substantially triangular basic shape, and are each permanently connected to one of the foot regions  16  and to the web  14 . In this way, the two component regions  17  brace the first component region  13 , and in particular the web  14 , against the foot regions  16 , reinforcing and stabilising the web  14 , for example against tilting. For this purpose, the second component regions  17  are orientated transverse to the web  14 , transverse to the foot region  16  and transverse to the flange  15  in the manner of ribs; see also the sectional view of  FIG. 4 . In particular, in the embodiment shown, each of the second component regions  17  extends transverse to the longitudinal direction L of the reinforcing component  11 , and in particular substantially perpendicular to the web  14  and the foot region  16 , as a wall-like element. 
     In the reinforcing component  11  of  FIG. 3 , the first and second component regions  13  and  17  are permanently interconnected.  FIG. 3  shows that each of the two component regions  17  is rigidly connected to the web  14  in a first connection region  18   a  and to the associated foot region  16  in a second connection region  18   b.    
     The reinforcing component  11  of the first embodiment is an integral fibre composite component of a hybrid design, the reinforcing component  11  being formed using a thermoplastic plastics material both in the first component region  13  and in the second component region  17 . The same thermoplastic plastics material may be used for the first and second component regions  13  and  17 , or it may be provided that the thermoplastic plastics material in the first component region  13  is different from the thermoplastic plastics material in the second component regions  17 . 
     In the first component region  13 , the thermoplastic plastics material forms a matrix in which continuous reinforcing fibres are embedded. Some of these reinforcing fibres are denoted by reference numeral  31  in  FIG. 3  by way of example. Continuous reinforcing fibres may also be referred to as “endless” fibres. Continuous fibres of this type are carefully arranged in a targeted manner in such a way that the first component region  13  acquires the desired mechanical properties. The reinforcing fibres  31  may in particular be arranged in such a way that they can absorb the incoming loads as well as possible. It will be appreciated that the fibres  31  schematically illustrated in  FIG. 3  are merely to be understood as an example, and that reinforcing fibres or bundles of reinforcing fibres may be provided in various orientations and arrangements within the first component region  13 , depending on the expected load on the reinforcing component  11 . The continuous fibres  31  have a targeted arrangement and orientation within the first component region  13  for this purpose, and may extend as “endless” fibres for example from one end to the other of the reinforcing component  11 . The reinforcing fibres  31  may for example be carbon fibres, glass fibres or other suitable reinforcing fibres or combinations thereof. 
     The second component regions  17  may be formed free of reinforcing fibres using a thermoplastic plastics material. In advantageous and preferred variants of the first embodiment, however, the thermoplastic plastics material of the second component regions  17  forms a matrix, in which discontinuous reinforcing fibres, shown schematically by way of example in  FIG. 4  and denoted by reference numeral  37 , are embedded. The discontinuous reinforcing fibres  37  are preferably short or long fibres. In particular, reinforcing fibres  37  formed as short fibres may be of a length of up to approximately 1 mm, or reinforcing fibres  37  formed as long fibres may be of a length of up to approximately 50 mm. 
     The reinforcing fibres  37  in the second component regions  17  may also be carbon fibres, glass fibres or other suitable fibres or combinations thereof. 
     The reinforcing fibres  31  in the first component region  13  and the reinforcing fibres  37  in the second component region  17  may be formed using the same material or using different materials. In an advantageous variant of the first embodiment, the second component regions  17  may each have glass fibres as reinforcing fibres  37 , whilst the continuous reinforcing fibres  31  of the first component region  13  are carbon fibres. In another variant, the fibres  31  and the fibres  37  may be carbon fibres in each case. 
     To manufacture the reinforcing component  11  in accordance with the first embodiment, shown in  FIG. 3 , initially a first component element  43  for forming the first component region  13  is provided. The first component element  43  may for example be manufactured by way of a deformation process and optionally a subsequent solidification from a planar semi-finished product, which contains a thermoplastic plastics material as a matrix and a reinforcing fibre arrangement. In cross section, the first component element  43  (see  FIG. 4 ) may for example form a C-shaped profile having limbs of different lengths, the lower leg of the C-shape in  FIG. 4  forming a skin-side flange of the component element  43 . To form the foot regions  16  and the clearances  29 , the component element  43  may for example be processed further after the C-shaped basic shape thereof is produced, or the clearances  19  are provided by corresponding shaping actually during the formation of the first component element  43 . In the embodiment shown, the first component element  43  may be considered a type of “base former” or base part for the former  11 . In  FIG. 3 , the foot portions  16  form flange-like portions of the first component region  13 , which are integrally connected to the web  14 . 
     To produce the second component regions  17 , a plurality of identical second component elements  47  are manufactured by injection moulding, the second component elements  47  initially still being present as separate elements after the injection moulding. The second component elements  47  are thus injection moulded from the thermoplastic plastics material, containing the discontinuous fibres  37 , for the second component region  17 . Standardising the second component elements  47  and the injection moulding thereof makes possible expedient manufacture thereof even for a relatively complex geometry. 
     After the second component elements  47  are manufactured separately, they are welded to the first component element  43  to manufacture the reinforcing component  11  of  FIG. 3 . For this purpose, the first and/or second component element  43 ,  47  may preferably be heated locally to a suitable temperature and the component elements  43 ,  47  subsequently joined together. The welding subsequently takes place in the connection regions  18   a,b . The component elements  43 ,  47  may for example already be positioned relatively to one another by a suitable device prior to heating. Preferably, the component elements  43 ,  47  are held against one another under pressure by regions of the relevant thermoplastic matrix which have melted or at least sufficiently softened during heating until sufficient solidification takes place. 
     Thus, by using thermoplastic plastics materials for the first and second component elements  43 ,  47 , as disclosed above, it is advantageously possible to weld each of the second component elements  47  to the first component element  43 . A reliable, permanent connection of the component elements  43  and  47  is thus achieved, and a unitary reinforcing component  11  comprising the first and second component regions  13  and  17  is formed. Additional connecting elements such as rivets or bolts are not required, and this saves costs and operating time. Instead, the reinforcing component  11  of  FIG. 3  may be produced as an integral former having a relatively complex geometry in an advantageous, simple and cost-effective method. 
     In a variant, the reinforcing component  11  of  FIG. 3  may be manufactured in such a way that initially the first component element  43  is provided as disclosed above and second component regions  17  are subsequently sprayed on by injection moulding. For this purpose, the first component element  43  may be laid in a suitable mould which has additional, suitably shaped cavities for casting the second component regions  17 . Subsequently, the second component regions  17  are cast on by injection moulding, a thermoplastic matrix having discontinuous reinforcing fibres  37  contained therein again being used. In this overmoulding, the second component regions  17  are likewise permanently and reliably connected to the first component region  13 , without rivets or bolts being required as additional connecting elements. 
       FIGS. 3 and 4  further show that the second component regions  17  are each provided with a means  53  for attaching cabin components and/or systems. Thus in an advantageous manner which reduces weight and outlay, a holding function is also integrated into the second component region  17  and thus into the reinforcing component  11  formed as a fuselage former. This may for example facilitate fastening cabin or system components in a manner orientated towards the formers. The means  53  may form a hard point for this purpose. 
       FIG. 3  further schematically shows that in the first embodiment the means may be formed using a sleeve  57 , which may be substantially cylindrical, comprising a through-opening  58 . So as further to facilitate attaching the cabin components or systems, the first component region  13  is formed in the region of the web  14  for example with a through-opening  59  orientated with respect to the through-opening  58 , for example concentric (see  FIG. 4 ). Alternatively, the through-opening  59  may be omitted and the opening  58  may be formed in the manner of a blind hole. 
     In a variant shown schematically in  FIG. 5  of the first embodiment, a metal socket  61  is integrated into the second component region  17 . For this purpose, in the variant of  FIG. 5 , the metal socket  61  is enclosed peripherally with the thermoplastic plastics material comprising added discontinuous fibres by overmoulding it in an injection moulding or spraying process. In this way, the metal socket  61  is enclosed by a sleeve-like portion  67  in the peripheral direction thereof, and thus held securely and reliably in the second component region  17 . The metal socket  61  may for example be used for fastening the cabin components or systems, and thus forms the fastening means  53  or at least part thereof. In variants, the internal thread  62  may be omitted or replaced with other fastening or connection means suitable for air or space travel. 
     Alternatively or additionally, in variants it may be provided that a means  53  without a reinforcing function for the web  14  is permanently connected to the first component region  13  and thus for example to the web  14 , for example by welding or spraying on as disclosed above. In a variant of this type, the second component region  17  may itself form a holding means for cabin components and/or systems. A variant of this type of the first embodiment is shown schematically by way of example in  FIG. 5A , other embodiments being conceivable. 
     In the first embodiment, in which further components can be attached to the former  11  using the means  53 , it may be found to be advantageous to use continuous carbon fibres in the first component region  13  and to use discontinuous glass fibres in the second component regions  17 . The components (not shown in the drawings) attached using the means  53  may for example be made of metal materials, for example aluminium. Whilst the carbon fibres  31  provide the desired mechanical load capacity in the first component region  13 , the glass fibres  37  in the second component region  17  reduce or prevent the electric conductivity of this component region. When metal components are attached using the means  53 , the occurrence of galvanic corrosion is thus advantageously prevented or inhibited. 
     The foot regions  16  are for coupling the reinforcing component  11  to another element, in particular to the skin portion  19  to be reinforced. For this purpose, the foot portions  16  may for example be connected directly or indirectly to an inner face of the skin portion  19 , in particular by riveting or by means of bolts. However, other types of connection of the foot regions  16  to the skin portion  19  are conceivable instead. In a preferred variant, the skin portion  19  may also be formed with a thermoplastic plastics material as a matrix and with reinforcing fibres, such as carbon fibres, embedded in the thermoplastic plastics material, for example with the help of a suitable semi-finished product. On the finished skin portion  19 , which has for example been solidified under pressure by squeeze moulding, made of a thermoplastic fibre composite material, the reinforcing component  11  can be welded onto the inside of the skin portion  19  as a former, the thermoplastic plastics material of the skin portion  19  and/or of the foot region  16  softening or melting and reliable connection of the reinforcing component  11  and the skin portion  19  being achieved by resolidification. 
       FIGS. 6 and 7  schematically show a second embodiment of the invention. The above statements are applicable analogously to the embodiment of  FIGS. 6 and 7 , the differences from the first embodiment being disclosed in the following. 
     In the second embodiment, the second component region  17  is formed as an additional flange or belt  71 , which is permanently connected to the first component region  13  so as to form a reinforcing component  11 . The belt  71  may in particular be welded on or sprayed on, and contains a thermoplastic plastics material which preferably contains discontinuous reinforcing fibres. 
     To manufacture the reinforcing component  11  in accordance with the embodiment of  FIG. 6, 7 , which again is a former for an aeroplane fuselage, a first component element  43  is initially formed from a planar semi-finished product, for which purpose the semi-finished product is brought into a geometry substantially Z-shaped in cross section (see  FIG. 7 ) and comprising a web  14 . Flanges are attached to the two ends of the web  14 , foot regions  16  being formed from the lower flange in  FIG. 7  and it being possible for the flange  15  to be present continuously along the longitudinal direction of the reinforcing component  11  (see  FIG. 6 ). 
     The Z-shaped cross-sectional geometry of the first component element  43 , which forms the first component region  13  in  FIG. 6, 7 , is supplemented with the additional belt  71  as a second component region  17 . The belt  71  is provided in addition to the flange  15 , and contributes to fulfilling the mechanical function of the reinforcing component  11 . Because the belt  71  is formed using discontinuous reinforcing fibres and connected to the first component region  13  by spraying on or welding on in a connection region  18   c , the manufacture of a reinforcing component  11  comprising two belts or flanges  71 ,  15  (see  FIG. 7 ) is greatly simplified. In particular, the first component region  13  can be formed in a simple manner at low outlay using a planar semi-finished product and for example subsequent solidification. In variants of the second embodiment, the belt  71  may alternatively be arranged on the web  14  at a different height from the flange  15  with respect to the foot region  16 . 
     In all above-disclosed embodiments, the thermoplastic plastics material in the first component region  13  may be different from the thermoplastic plastics material in the second component regions  17 , in particular in terms of the associated melting temperature and/or glass transition temperature thereof. In this way, the melting or softening properties of the thermoplastic plastics materials can be influenced in a more targeted manner during the welding or spraying-on process. However, in all above-disclosed embodiments, it is conceivable for the first and second component regions  13 ,  17  to use the same thermoplastic plastics material. 
     In the above-described embodiments, for example high-grade thermoplastics, such as semi-crystalline thermoplastics, are used as the thermoplastic plastics materials in the first and/or second component regions  13 ,  17 , for example a polyaryletherketone (PAEK), a polyetheretherketone (PEEK) or the like. 
     Although the present invention was fully disclosed above by way of preferred embodiments, it is not limited thereto, but can be modified in numerous ways. 
     In particular, the hybrid design for the reinforcing component may be of use not only in formers, but also in other reinforcing components, in particular for aircraft or spacecraft. 
     While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.