• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The present invention provides a method for the manufacture of a thermoplastic fiber composite component, in particular for an aircraft or spacecraft, with the following process steps: material removal machining of a first side of a first platinum, wherein the first platine has a thermoplastic fiber composite material and by material removal machining of the first side a local reduction of a thickness of the first platine is carried out, - positioning of a second platine with respect to the first platinum such that the first side of the first platinum. the first platinum is brought into coverage with a third side of the second platine; and combining the first platine with the second platine into a common component, the surface of the first side of the first platine with the surface of. the third side of. the second platine is dust-tightly connected. The invention further provides a thermoplastic fiber composite component for an air or spacecraft manufactured according to such a method.
    公开号:NL2018506A
    申请号:NL2018506
    申请日:2017-03-13
    公开日:2017-09-20
    发明作者:Neitzel Tim；Bahnsen Jens；Miaris Angelos；Edelmann Klaus
    申请人:Premium Aerotec Gmbh；
    IPC主号:
    专利说明:

    Method for the manufacture of a thermoplastic fiber composite component and thermoplastic fiber composite component
    Description
    The present invention relates to a method for the manufacture of a thermoplastic fiber composite component as well as a thermoplastic fiber composite component.
    Although they can be applied to any thermoplastic fiber composite components, the present invention as well as the problems underlying it with regard to thermoplastic fiber composite components of an aircraft or spacecraft are further explained.
    Thermoplastic fiber composite components are usually manufactured during finishing by the fact that semi-finished products, so-called platins, present in the form of sheet material are transformed or compressed. The compression of thermoplastic laminates is described, for example, in US 8 771 575 B2.
    A platinum 100 usable for the manufacture of an aircraft or spacecraft component is schematically shown in FIG. IA. The platine 100 in each case has a glass layer 101, 102 on its surface, which serves for the corrosion protection of adjacent metal parts, for example the aluminum parts. The platine 100 has various fiber layers 103, for example of carbon fibers, and a thermoplastic matrix 104. The carbon fibers 103 are thereby arranged symmetrically in an original state of the semi-finished product with respect to a diameter 105.
    For the manufacture of a thermoplastic fiber composite component, the thickness 106 of the platinum 100 and / or the number of fiber layers 103 of the platinum are usually chosen such that they satisfy the requirements of the usually loaded component parts. A local reduction of the thickness 106 or of the number of fiber layers 103 can be carried out either at the platinum 100 or after a forming process at the already converted component by machining on the outside. A component 200 machined accordingly on the outside is shown in FIG. 18 is shown schematically.
    A further approach provides for the manufacture of a thermoplastic fiber composite component in a construction of the thermoplastic fiber composite component from a plurality of semi-finished products, meeting the requirements, called tapes. This method of manufacture, which is also referred to as the laying of tape, is described, for example, in DE 10 2013 202046 A1.
    Moreover, according to an additional approach, there are also so-called thickness-adaptive semi-finished products, which have intermediate layers of non-reinforced thermoplastic material which can be deformed into the thickness and, therefore, transformable into the thickness of the semi-finished product. Such a semi-finished product is described, for example, in DE 197 38 388 A1.
    Against this background, it is an object of the present invention to provide an improved process for the manufacture of a thermoplastic fiber composite component as well as an improved thermoplastic fiber composite component.
    According to the invention achieved for this purpose by a method with the features of patent claim 1 and / or by a thermal fiber composite component with the features of claim 12.
    It is therefore provided:
    A method for manufacturing a thermoplastic fiber composite component, in particular for an air or spacecraft, with the following process steps: material removal machining of a first side of a first platinum, the first platine having a thermoplastic fiber composite material and by material removal processing of the first side a local reduction of a thickness of the first platine is performed; positioning a second platine with respect to the first platine such that the first side of the first platine is brought into coverage with a third side of the second platine; and joining the first platine with the second platine into a common component, the surface of the first side of the first platine being dust-tightly connected to the surface of the third side of the second platine. a thermoplastic fiber composite component for an air or spacecraft, manufactured according to a method according to the invention.
    The underlying idea of the present invention is to merge two platins for the manufacture of a fiber composite component, with at least one of the platins prior to joining on the side to be joined to adjust the thickness of the later component to remove material is being edited. Consequently, a thickness change according to the invention is taken into account with the mounted inner surface of the platins.
    In this way, a material-removing operation of the outer surfaces of the later component, which is necessary for example during the machining operation on the outside of a platinum or a component, is advantageously avoided. This is structurally favorable from the point of view of the fact that fiber layers lying on the outside remain undamaged, which improves the mechanical material properties in many applications.
    Furthermore, according to the invention, the manufacturing process is advantageously simplified, since no milling edges or the like come into direct contact with a (hot) pressing tool, but lie only in the interior of the component. For example, such an unwanted sudden change of individual layers is avoided.
    Furthermore, despite the thickness adjustment, an optically appealing, uniform outer surface of the component is produced with comparatively low manufacturing input, in particular without intermediate consolidation.
    Moreover, according to the invention, any outer layers, for example glass layers, which have already been provided with the semi-finished product advantageously remain undamaged, which contributes to an improved corrosion protection of neighboring metal components.
    In addition, the present invention simplifies organization deployment in manufacture, since family formation and component changes are made easier by the simple adjustment of local thicknesses.
    In addition, the invention can be applied to an extremely large component spectrum in an air or spacecraft, so that a high potential for saving weight is made accessible by the simplified thickness adjustment.
    The platinum in particular concerns consolidated semi-finished products.
    The material removal processing can for example be a machining operation. In particular, it can be a machining operation by milling. For material-removing processing, alternatively or additionally also grounded separation processes are conceivable, for example different types of beam cutting such as laser beam or electron beam cutting, or the like.
    The joining is preferably a flat joining, in particular over a complete component surface of the fiber composite component. It is furthermore possible to lay a connecting part, a so-called patch, for reinforcing the dust-sealing connection between the two platins prior to joining, which is then embedded in the dust-sealing connection when joining.
    Advantageous designs and improvements of the invention can be found in the sub-claims.
    According to a preferred further development of the method, the first platinum has at least a first fiber layer, which is partially removed in the material removal operation. Consequently, different types of layer structure can be realized within the component which are adapted to the desired thickness change of the component. The second platinum can either be maintained with its constant thickness or can be machined in the same way as the first platine on the third side to remove material or to cut it, whereby an originally continuous fiber layer is also partially removed.
    According to an embodiment, the first platinum has a first covering layer which is provided on a second side opposite to the first side and which remains undamaged during the material-removing operation and / or during the joining together. The cover layer is, for example, a glass layer which serves for the corrosion protection of neighboring components of metal, for example of aluminum. Therefore, the original corrosion protection of the platinum, which would for example be no longer present on the outside of a component by removing the cover layer, is favorably maintained.
    According to an embodiment, the second platinum has a thermoplastic fiber composite material and a second covering layer, which is provided on a fourth side opposite the third side. Advantageously, therefore, a formation of the second platinum with respect to the first platinum and consequently a symmetrical structure of the fiber layers and / or of the cover layers of the component manufactured with the platins is made possible with respect to the center line of a component contour. In addition, a second outer layer of the component also provides, by means of the second cover layer, for example, corrosion protection of adjacent metal components with supporting layer, in particular a glass layer.
    According to an embodiment, the step of combining the platins into a common component comprises the step of compressing. Depending on the choice of material of the thermoplastic matrix of the platins, the compression may also comprise a heat treatment adapted to the material. Advantageously, hollow spaces which are created by the material-removing operation of the first side (and possibly from the third side), in particular by a transformation of the first and / or second platinum, are closed by compressing.
    According to a further development, the material-removing part of the first platine is transformed during compression and connected to the third side of the second platine in a dust-tight manner. A fully connected fiber composite component is advantageously produced in this way. In the same way as with the first platine, if the second platine is also removed with a material removal action, the material removal-processed part of the second platinum can be converted during compression. In this case, the material-removing machined part of the second platinum is connected with the material-removal machined part of the first platinum or with another part of the first side of the first platine in a dust-tight manner. Furthermore, if no material-removing machined part is provided with the second platine, it is also possible to co-convert the second platine into a part of the first platinum covered-machining part. The cover layer of the respective transformed platinum is always partly transformed and preferably remains undamaged.
    According to an embodiment, the first platinum and the second platine are each provided with a plurality of fiber layers. Therefore, with the method according to the invention, a large variation width of the layer structure is made possible. For example, this may involve differently oriented fiber layers.
    According to an embodiment, the second platine is provided with a constant thickness. The thickness is particularly constant throughout. In this case, the second platinum on the third side is not or not removed with material removal. Therefore, only one processing step is advantageously required. During compression, the first platinum is then dust-tightly connected to its first side and its material-removing machined part to the unprocessed third side of the second platine. With regard to the arrangement in the tool, the upper side of a lower plate or the lower side of an upper plate can represent the machined first side.
    According to an embodiment, the third side of the second platine is processed to remove material prior to positioning for the local reduction of a thickness of the second platine. Consequently, a symmetry of the layer structure of the first and the second platinum can be obtained. A design other than symmetrical is also possible. The second cover layer preferably remains undamaged during the material-removing operation on the third side.
    According to an embodiment, the reduction in the thickness of the second platinum is provided symmetrically with respect to the first platinum. The reduction of the thickness of the second platinum is therefore preferably mirror-mirrored for the reduction of the thickness of the first platine, i.e. symmetrical with respect to a diameter between the first and the second platinum. As a result, a layer structure can be obtained in the component to be manufactured which is symmetrical with respect to a centerline of the component contour. A component contour symmetrical on the centerline would also be conceivable.
    According to an embodiment, the fiber layers and the cover layers of the platins are compressed during compression into an arrangement which is at least predominantly symmetrical with respect to the centerline of a component contour. An at least predominantly symmetrical shaping is to be understood to mean a symmetry for at least those parts where no transition of a thickness change is provided. Parts constant and evenly changed and unchanged with respect to the thickness therefore have a symmetry with respect to a centerline. In parts with a changing thickness, on the other hand, a non-symmetrical shape may be provided. Preferably, however, symmetry must also be provided for these parts with a varying thickness, in particular if the two platins are processed symmetrically in advance.
    According to a preferred embodiment of a fiber composite component, a first cover layer is provided on a first outside of the fiber composite component. A second cover layer is provided on a second outside of the fiber composite component. A partially continuous fiber layer is furthermore arranged between the first and the second cover layer. Consequently, a local thickness change and also a local change in the layer structure of the component can advantageously be provided.
    According to an embodiment, the thermoplastic fiber composite component has at least a first continuous fiber layer and a second continuous fiber layer. The partial continuous fiber layer is preferably arranged between the first continuous fiber layer and the second continuous fiber layer. Therefore, continuous fiber layers are provided despite the change in thickness and the change in the number of layers in an outer region of the component, which is structurally favorable.
    According to a further development, the first continuous fiber layer and the second continuous fiber layer as well as the first cover layer and the second cover layer are at least predominantly symmetrical with respect to a centerline of the component contour. A at least predominantly symmetrical course is to be understood here to mean a symmetry at least for those parts where no change in the course of the thickness occurs. Advantageously, such a symmetrical or at least predominantly symmetrical shape is structurally and favorably structured.
    The above designs and further developments can, as far as it is useful, be combined randomly. In particular, all the features of the method for manufacturing a thermoplastic fiber composite component can be applied to a thermoplastic fiber composite component, and vice versa.
    Further possible designs, further developments and implementations of the invention also comprise combinations of characteristics of the invention described earlier or hereinafter with reference to the exemplary embodiments. In particular, those skilled in the art will also add individual aspects such as improvements or additions to the relevant basic form of the present invention.
    The invention is explained in more detail below with reference to exemplary embodiments with reference to the accompanying figures of the drawing. The elements of the drawings are not necessarily shown to scale with respect to each other.
    From the figures show:
    Fig. 1A is a schematic representation of a platine;
    FIG. 1B a schematic representation of a machined machined component;
    FIG. 2A a schematic representation of two platins;
    FIG. 2B the platins according to FIG. 2A after a machining operation;
    FIG. 2C the platins according to FIG. 2B after a positioning;
    FIG. 2D one from the platins according to FIG. 2C a fiber composite component assembled by compression;
    FIG. 3 is a side view of a fiber composite component of an aircraft or spacecraft; and
    FIG. 4 is a perspective view of the fiber composite component of FIG. 3.
    In the figures, the same reference signs indicate identical or functionally identical components, unless otherwise indicated.
    FIG. 1A shows a schematic representation of a platinum, which in each case has a glass layer 101, 102 on its surfaces. The platine 100 has a plurality of fiber layers 103, for example of carbon fibers, and a thermoplastic matrix 104. The carbon fibers 103 are arranged symmetrically with respect to a component diameter 105.
    FIG. 1B shows a schematic representation of a machined machined component 200. It is a fiber composite component made from the platinum 100.
    For the production, a local reduction of the thickness 106 and the number of fiber layers 103 is carried out by machining on the outside. As a result, material is removed on one of the outer edges, here as an example at the top. The material removal can for instance take place by means of milling.
    In this way, the thickness and the number of the fiber layers of the component 200 are locally reduced. However, a glass layer 101 on the machined surface of the component 200 is thereby partly removed.
    The fiber profile is thereby retained in its original form. Fiber layers 103 located near the surface are only partially removed. The course of the fiber layers 103 and the glass layer 101, 102 is therefore asymmetrical in the machined part 107 with respect to a center line 105 of the component contour.
    FIG. 2A shows a schematic representation of two platinum 2, 3.
    A first plate 2 has a first side 4 and a second side 10. A thickness 6 of the first plate 2 is first constantly constant.
    The first plate 2 has a first cover layer 9 on its second side 10, which can be formed as a corrosive protective glass layer. Furthermore, the first platine 2 has a fiber composite material 5, which is also present on the first side 4 without a cover layer. Such platins are sold, for example, by the company TenCate under the name "Cetex®".
    The fiber composite material 5 comprises fiber layers 8, 8 ', 8' 'and a thermoplastic matrix in which the fiber layers 8, 8', 8 '' are embedded. The representation of the fiber layers 8, 8 ', 8' 'must be understood as purely explanatory. This preferably involves a plurality of differently oriented fiber layers, for example a -45 °, a + 45 °, a 90 ° and a 0 ° oriented fiber layer. A different number and / or different orientation of fiber layers may also be provided.
    The second plate 3 has a third side 7 and a fourth side 12. It is formed with a thickness 14, which is also constantly constant.
    The second plate 3 has a second cover layer 11 on the fourth side 12, which can be formed, for example, as a corrosion-resistant glass layer. Otherwise, the second platinum 3 also has a fiber composite material 5, which has fiber layers 16, 16 ', 16' 'embedded in a thermoplastic matrix in the same way as the first platine 2.
    In the embodiment shown, the first platinum 2 and the second platinum 3 are, by way of example, identically shaped and arranged in reverse relation to each other. In additional embodiments, however, second platinum 3 can also have a shape different from the first platinum 1, for example a different, in particular greater or smaller, thickness 14, a different number of fiber layers 16, 16 ', 16' ', ..., none or have a different type of cover layer 12, a larger or smaller length or other difference characteristics, whereby combinations of difference characteristics are also possible.
    The platinum 2, 3 are consolidated semi-finished products.
    FIG. 2B shows the platins according to FIG. 2A after a machining operation. The machining operation involves material removal, so that a material removal machined part 13, 13 'is produced.
    The material-removing part 13 extends at the first platinum 2 in the fiber-composite material 5 so far that a first fiber layer 8 lying near the first side 4 is partly removed as well. The additional fiber layers 8 ', 8' 'and the first coating 9 remain undamaged.
    For this purpose, the material-removing part 13 'at the second platinum 3 in the fiber-composite material 5 extends in such a symmetrical manner that a fiber layer 16 lying near the third side 7 is partially removed, the remaining fiber layers 16', 16 '' as well as the second cover layer 11 remain undamaged.
    FIG. 2C shows the platins according to FIG. 2B after a positioning. When positioning, the platins 2, 3 are arranged such that the first side 4 is in coverage with the third side 7.
    In the embodiment shown, in which the platins are symmetrically shaped and symmetrically machined to remove material, unprocessed parts of the first side 4 and the third side 7 lie directly on top of each other.
    In addition, in the embodiment shown, the parts 13, 13 'of the first platinum 2 and of the second platinum 3 which have been removed with material are arranged in coverage with respect to each other, so that in total a symmetrical arrangement of a drawn fictitious centerline 15' of the platinum 2, 3 is present.
    In other embodiments, in which the platins are not formed symmetrically or are not processed symmetrically, this arrangement may be different with respect to symmetry. However, also with differently shaped or machined platins after positioning, coverage of the first side 4 with the third side 7 is provided.
    FIG. 2D shows one from the platins 2, 3 according to FIG. 2C component assembled by compression.
    In the compression step, which can also include a pre-existing, post-occurring or simultaneous heat treatment adapted to the thermoplastic material of the matrix used, the first side 4 and the third side 7 of the platins 2, 3 become dust-tight with each other connected. furthermore, the material-removing part 13 of the first platinum 2 is transformed during compression and connected to the third side 7 of the second platinum 3 in a dust-tight manner.
    In the embodiment shown here, the material removing machined part 13 of the first platinum 2 in the region of the oppositely arranged material removing machined part 13 'of the second platine 3 is connected to the third side 7 with a dust-tight connection, so that the two material removal machined parts 13 13 'are properly merged.
    The component 1 formed in this way then has a fiber pattern of the fiber layers 8, 8 ', 8' 'and 16, 16', 16 '', which, in a first region 19, in which no change in the thickness of the platins was observed and in a second region 20, in which a constant change in the thickness of the platins was performed, runs symmetrically with respect to a centerline 15 of the component contour.
    Also in a transition part 21, in which the thickness changes during its course, the fiber course has a symmetry with respect to the centerline 15.
    In the case of additional embodiments, it can be determined that prior to compression, the thickness 6, 14 of the respective platinum 2, 3 for the adaptation between a part changed with respect to the thickness due to the material removal and a part not changed with respect to the thickness also have an asymmetry. In total, however, the fiber profile is always at least to a large extent symmetrical with respect to the centerline of the component contour.
    Consequently, a first exterior 17 of the component 1 has a transition area 21 visible from the outside, where the thickness of the component changes. A second exterior 18, on the other hand, is flat.
    In an additional embodiment, however, it would also be conceivable to deform the material-removing parts 13, 13 'of the first platinum 2 and of the second platinum 3 in the same manner so that they form in a component center or on a center line 15 of the component contour, respectively. be connected to each other dust-tightly. In this case, an ideal symmetry of the fiber layers with respect to a centerline 15 would have been made possible.
    In a still further embodiment, in which only the first platinum 2 is provided with a material-removing machined part 13 and the second platinum 3 is not machined in a material-removing manner, the fiber course is provided in a similar manner, but all fiber layers 16, 16 ', 16 of the second platinum 3 are continuously maintained and therefore the first fiber layer 8 and the additional fiber layers 8 ', 8' 'and those of the cover layer 9 of the first platinum 2 are unwound to a lesser extent.
    Here too, the difference in thickness can be compensated for either only by a transformation of the material-removing part 13 of the first platinum 2 or, moreover, also by a simultaneously opposite transformation of the area of the second platinum 3 which is thus covered.
    FIG. 3 shows a side view of a fiber composite component 1 'of an air or spacecraft. This is an L-shaped clip, which serves, for example, for connecting a truss to the skin.
    The L-shaped clip has a longer arm 22 and a shorter arm 23. In the area of the longer arm 22, the clip has a transition part 21, where the thickness of the component contour changes.
    For the manufacture of such a clip, two platins are applied in the manner described with respect to Figures 2A to 2D, machined in a material-removing manner, positioned with respect to each other and compressed and joined together to form the clip. Moreover, in the compression process, prior to the joining of the first and second platinum, a conversion for deflecting the shorter arms 23 with respect to the longer arm 22 is also carried out, so that the L-shape is produced.
    Accordingly, an L-shaped clip is provided which, with respect to its course, has a thickness change and has fully continuous undamaged outer cover layers, in particular adjacent metal components prior to corrosion protection glass layers.
    FIG. 4 shows a perspective view of the fiber composite component 1 'of FIG. 3.
    Dotted lines here indicate a contour change on the surface. This relates to the contour change on an outer side 17 opposite the deflection of the shorter arm 23, which is completely covered with a cover layer 9.
    Although the present invention has been described here with reference to preferred embodiments, it is not limited thereto, but can be modified in many ways.
    For example, the material removal processing of platins does not necessarily have to take place by a machining operation. In addition, conceivable optionally or additionally adequately matched separation processes would also be conceivable, for example by means of laser beam, electron beam or water jet cutting or the like.
    Moreover, the method can also be applied to platinum without a coating. Further, grounded layers may also be provided, for example cover layers formed as a fiber layer.
    Instead of an L-shaped clamp, any other fiber composite components, in particular also more complex components, can be manufactured with the method according to the invention.
    List of reference characters 1.1 'fiber composite component 2 first platinum 3 second platinum 4 first side 5 fiber composite material 6 thickness 7 third side 8 first fiber layer 8', 8 '' additional fiber layers 9 cover layer 10 second side 11 cover layer 12 fourth side 13, 13 'material removal machined part 14 thickness 15, 15 'diameter 16 fiber layer 16', 16 '' additional fiber layers 17 first exterior 18 second exterior 19 first region 20 second region 21 transition part 22 longer arm 23 shorter arm 100 platinum 101, 102 glass layer 103 fiber layers 104 matrix 105 diameter 106 thickness 107 machining machined part 200 component
    权利要求:
    Claims (15)
    [1]
    A method for manufacturing a thermoplastic fiber composite component (1; 1 '), in particular for an air or spacecraft, with the following process steps: Material removal machining of a first side (4) of a first platinum (2), wherein the first platinum (2) has a thermoplastic fiber composite material (5) and a local reduction of a thickness (6) of the first platinum (2) is effected by material-removing machining of the first edge (4); second platine (3) with respect to a first platine (2), covering the first side (4) of the first platine (2) with a third side (7) of the second platine (3); and combining the first platinum (2) with the second platinum (3) into a common component (1; 1 '), the surface of the first side (4) of the first platine (2) with the surface of the the third side (7) of the second platinum (3) is dust-tightly connected.
    [2]
    Method according to claim 1, characterized in that the first platinum (2) has at least one first fiber layer (8}, which is partially removed during material removal processing.
    [3]
    Method according to claim 1 or 2, characterized in that the first platinum (2) has a first cover layer (9) which is provided on a second side (10) opposite the first side (4) and provided with the material removal processing and / or remains undamaged when joining.
    [4]
    Method according to at least one of the preceding claims, characterized in that the second platinum (3) has a thermoplastic fiber composite material (5) and a second cover layer (11) which is on a fourth side opposite the third side (7) (12) is provided.
    [5]
    Method according to at least one of the preceding claims, characterized in that the step of combining the platins (2, 3) into a common component (1, - 1 ') comprises the step of compressing.
    [6]
    Method according to claim 5, characterized in that a material-removing machined part (13) of the first platine (2) is transformed during compression and is dust-tightly connected to the third side (7) of the second platine (3) .
    [7]
    Method according to at least one of the preceding claims, characterized in that the first platinum (2) and the second platinum (3) are each provided with a plurality of fiber layers (8, 8 ', 8' ').
    [8]
    Method according to at least one of the preceding claims, characterized in that the second platinum (3) with a constant thickness (14) is provided.
    [9]
    Method according to claim 7, characterized in that the third side (7) of the second platinum (3) is machined to remove material prior to positioning for the local reduction of a thickness (14) of the second platinum (3) .
    [10]
    Method according to claim 9, characterized in that the reduction in the thickness (14) of the second platinum (3) is provided symmetrically with respect to the first platinum (2).
    [11]
    A method according to claim 10, characterized in that the fiber layers (8, 8 ', 8' ') and the cover layers (9, 11) of the platins (2, 3) when compressed in a relative to a center line ( 15) of a component contour are at least predominantly symmetrical arranged.
    [12]
    A thermoplastic fiber composite component (1; 1 ') for an air or spacecraft manufactured according to a method according to any one of the preceding claims.
    [13]
    A fiber composite component according to claim 12, characterized in that a first outer layer (9) is provided on a first outside (17) of the fiber composite component (1; 1 '), on a second outside (18) of the fiber composite component (1) 1; 1 ') a second cover layer (11) is provided, and a partially continuous fiber layer (8; 16) is arranged between the first and the second cover layer (9; 11).
    [14]
    Fiber composite component according to claim 13, characterized in that the thermoplastic fiber composite component (1; 1 ') has at least a first continuous fiber layer (8'; 8 '') and a second continuous fiber layer (16 '; 16' '), wherein the partially continuous fiber layer (8-16) is disposed between the first continuous fiber layer (8 '; 8' ') and the second continuous fiber layer (16'; 16 '').
    [15]
    Fiber composite component according to claim 14, characterized in that the first continuous fiber layer (8 '; 8' ') and the second continuous fiber layer (16'; 16 '') as well as the first cover layer (9) and the second cover layer (11) ) extend at least predominantly symmetrically with respect to a centerline (15) of the component contour.
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    同族专利:
    公开号 | 公开日
    US10384397B2|2019-08-20|
    FR3048916A1|2017-09-22|
    DE102016003109A1|2017-09-21|
    NL2018506B1|2018-01-12|
    US20170266867A1|2017-09-21|
    FR3048916B1|2020-09-11|
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    法律状态:
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    申请号 | 申请日 | 专利标题
    DE102016003109.3A|DE102016003109A1|2016-03-15|2016-03-15|Process for producing a thermoplastic fiber composite component and thermoplastic fiber composite component|
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