MANUFACTURING METHOD FOR THERMOFORMING A FIBER-REINFORCED COMPOSITE LAMINATE

Abstract

A manufacturing method for thermoforming a fiber-reinforced composite laminate with fiber rovings embedded within a thermoplastic matrix includes: mounting fiber rovings to a transport frame, the mounted rovings being arranged to form a support grid layer laterally framed by the transport frame, each roving being mounted on both ends under tension to the transport frame; placing a matrix material layup of thermoplastic material on top of the support grid layer, wherein the tension of the rovings and a density of the support grid layer are configured such that the support grid layer supports the matrix material layup; softening the matrix material layup by heating the support grid layer together with the matrix material layup within a heating station; forming a semi-finished composite laminate by pressing the support grid layer together with the softened matrix material layup; and consolidating the semi-finished composite laminate to form the fiber-reinforced composite laminate.

Claims

1. A manufacturing method for thermoforming a fiber-reinforced composite laminate, the fiber-reinforced composite laminate including fiber rovings embedded within a thermoplastic matrix, the manufacturing method comprising: mounting fiber rovings to a transport frame, wherein the mounted fiber rovings are arranged to form a support grid layer that is laterally framed by the transport frame, each fiber roving being mounted on both ends under tension to the transport frame; placing a matrix material layup of thermoplastic material on top of the support grid layer on the transport frame, wherein the tension of the fiber rovings and a density of the support grid layer are configured such that the support grid layer supports the matrix material layup; softening the matrix material layup by heating the support grid layer together with the matrix material layup within a heating station; forming a semi-finished composite laminate by pressing the support grid layer together with the softened matrix material layup within a press; and consolidating the semi-finished composite laminate to form the fiber-reinforced composite laminate.

2. The method of claim 1, wherein forming the semi-finished composite laminate comprises automatically adjusting at least one of the tension and a position of the fiber rovings.

3. The method of claim 2, wherein at least one of the tension and the position of each fiber roving is adjusted individually.

4. The method of claim 1, wherein each fiber roving is mounted on the transport frame by a mounting device per end.

5. The method of claim 4, wherein the tension of each fiber roving is adjusted by moving one or both of the respective mounting devices relative to the transport frame in a direction defined by the respective fiber roving.

6. The method of claim 4, wherein the position of each fiber roving is adjusted by moving one or both of the respective mounting devices relative to the transport frame.

7. The method of claim 6, wherein the position of each fiber roving is adjusted by moving one or both of the respective mounting devices relative to the transport frame in a direction generally perpendicular to the support grid layer.

8. The method of claim 1, wherein forming the semi-finished composite laminate comprises shaping the semi-finished composite laminate with a shaping tool according to a predetermined shape.

9. The method of claim 8, wherein at least one of the tension and the position of the fiber rovings are automatically adjusted such that the fiber rovings are arranged according to the predetermined shape.

10. The method of claim 1, further comprising: cutting ends of the fiber rovings protruding from the fiber-reinforced composite laminate to separate the fiber-reinforced composite laminate from the transport frame.

11. The method of claim 1, wherein the support grid layer is heated together with the matrix material layup within the heating station by infrared radiation.

12. The method of claim 1, further comprising: welding fiber-reinforced composite laminates together to form a fiber-reinforced composite component.

13. The method of claim 12, wherein the fiber-reinforced composite component is formed as a structural component of an aircraft or spacecraft.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The invention will be explained in greater detail with reference to exemplary embodiments depicted in the drawings as appended.

[0025] The accompanying drawings are included to provide a further understanding of the present invention and are incorporated in and constitute a part of this specification. The drawings illustrate the embodiments of the present invention and together with the description serve to explain the principles of the invention. Other embodiments of the present invention and many of the intended advantages of the present invention will be readily appreciated as they become better understood by reference to the following detailed description. The elements of the drawings are not necessarily to scale relative to each other. In the figures, like reference numerals denote like or functionally like components, unless indicated otherwise.

[0026] FIG. 1 schematically illustrates a structural component of an aircraft including fiber-reinforced composite laminates manufactured with a method according to an embodiment of the invention.

[0027] FIG. 2 schematically illustrates an aircraft being equipped with the structural component of FIG. 1.

[0028] FIG. 3 schematically illustrates a flow diagram of the manufacturing method used for the manufacturing of the structural component of FIG. 1.

[0029] FIGS. 4a and 4b schematically show a cross-sectional view and a top view of a transport frame employed in the manufacturing method of FIG. 3.

[0030] FIG. 5 schematically shows selected manufacturing steps of the method of FIG. 3.

DETAILED DESCRIPTION

[0031] Although specific embodiments are illustrated and described herein, it will be appreciated by those of ordinary skill in the art that a variety of alternate and/or equivalent implementations may be substituted for the specific embodiments shown and described without departing from the scope of the present invention. Generally, this application is intended to cover any adaptations or variations of the specific embodiments discussed herein.

[0032] FIG. 1 schematically illustrates a structural component of an aircraft including fiber-reinforced composite laminates manufactured with a method according to an embodiment of the invention.

[0033] In FIG. 1 reference sign 10 denotes a structural component, which comprises several fiber-reinforced composite laminates 1. Each fiber-reinforced composite laminate 1 comprises a plurality of fiber rovings 2 embedded within a thermoplastic matrix 4. The structural component 10 may be equipped within an aircraft 100 as schematically illustrated in FIG. 2. The structural component 10 may be for example a rudder or similar. The structural component 10 is depicted in FIG. 1 in a very schematic way. FIG. 1 merely illustrates that several fiber-reinforced composite laminates 1 may be welded or fused together to form a larger structural component 10 of an aircraft 100. A possible underlying structure of the structural component 10 of the aircraft 100 is left out in FIG. 1 for reasons of simplicity. Hence, the fiber-reinforced composite laminates 1 in FIG. 1 may cover an underlying framework or construction of the structural component 10, the framework itself not being depicted here. The fiber-reinforced composite laminates 1 in FIG. 1 may thus constitute a cover or skin of the structural component 10.

[0034] FIG. 3 schematically illustrates a flow diagram of the manufacturing method M used for the manufacturing of the structural component 10 of FIG. 1. The manufacturing method M comprises under M1 mounting fiber rovings 2 to a transport frame 5. The mounted fiber rovings 2 are arranged to form a support grid layer 3 that is laterally framed by the transport frame 5. Each fiber roving 2 is mounted on both ends under tension to the transport frame 5. The manufacturing method M further comprises under M2 placing a matrix material layup 7 of thermoplastic material on top of the support grid layer 3 on the transport frame 5. Here, the tension of the fiber rovings 2 and/or a density of the support grid layer 3 are configured such that the support grid layer 3 supports the matrix material layup 7. The manufacturing method M further comprises under M3 softening the matrix material layup 7 by heating the support grid layer 3 together with the matrix material layup 7 within a heating station 8, e.g. by infrared radiation 12 other appropriate means.

[0035] The manufacturing method M further comprises under M4 forming a semi-finished composite laminate 1 by pressing the support grid layer 3 together with the softened matrix material layup 7 within a press 6. This may include under M4 automatically adjusting at least one of the tension and a position of the fiber rovings 2. Each fiber roving 2 may be adjusted individually and/or several or all fiber rovings 2 may be adjusted collectively. This may further include shaping the semi-finished composite laminate 1 with a shaping tool 11 according to a predetermined shape. At least one of the tension and the position of the fiber rovings 2 may be automatically adjusted such that the fiber rovings 2 are arranged according to the predetermined shape.

[0036] Next the method M comprises under M5 consolidating the semi-finished composite laminate 1 to form the fiber-reinforced composite laminate 1. The thermoplastic matrix 4 of the fiber-reinforced composite laminate 1 is thus formed by the first softened and then cured matrix material layup 7. Due to the pressing process the fiber rovings 2 are embedded within the thermoplastic matrix 4. The method M may further comprise under M6 cutting the ends of the fiber rovings 2 protruding from the fiber-reinforced composite laminate 1 to separate the fiber-reinforced composite laminate 1 from the transport frame 5. Finally, the method M may comprise under M7 welding fiber-reinforced composite laminates 1 together to form a fiber-reinforced composite component 10.

[0037] FIGS. 4a and 4b schematically show a cross-sectional view and a top view of a transport frame 5 employed in the manufacturing method M of FIG. 3. The transport frame 5 is configured in the form of a flat hollow square with a plurality of mounting devices 9 attached to all four inner sides. The mounting devices 9 may comprise, without any limitation, pins, clamps, screws, lugs and so on. The four sides of the depicted transport frame 5 are identical, with opposite sides having pairs of mounting devices 9 opposing each other. The fiber rovings 2 are hence arranged in a quadratic grid-like structure, wherein the grid density is chosen to fit the size and weight of the matrix material layup 7 placed upon the support grid layer 3 to be consolidated.

[0038] The person of skill will readily acknowledge that different geometries and configurations of the transport frame 5 may be chosen depending on the specific use case. Furthermore, the arrangement and configuration of the mounting devices 9, and thus of the resulting support grid layer 3, is of purely exemplary nature. A grid according to the invention comprises any pattern of lines that cross each other to form squares or other geometric arrangements within a basically two-dimensional plane. For example, rectangular or lozenge-shaped or other forms may be achieved by arranging the fiber rovings 2 perpendicular or inclined to each other or in other grid arrangements.

[0039] Each fiber roving 2 is mounted on the transport frame 5 by means of two mounting devices 9, i.e. one mounting device 9 per end. The tension of each fiber roving 2 may be adjusted by help of the mounting devices 9. For example, the tension may be adjusted by moving one or both of the respective mounting devices 9 relative to the transport frame 5 in a direction defined by the respective fiber roving 2. For this, the mounting devices 9 may be movably connected to the transport frame 5. Alternatively, the mounting devices 9 may be configured to affect the tension of the fiber rovings 2 directly without any direct movement of the mounting device 9 itself. In a similar way, the position of each fiber roving 2 may be adjusted by moving one or both of the respective mounting devices 9 relative to the transport frame 5. For example, the position of each fiber roving 2 may be adjusted by moving one or both of the respective mounting devices 9 relative to the transport frame 5 in a direction generally perpendicular to the support grid layer 3. Or, the mounting devices 9 may be actively moved in the plane of the transport frame 5. The degrees of freedom of the mounting devices 9 are indicated by arrows in FIGS. 4a and 4b.

[0040] Further, the person of skill will be able to elaborate on basis of the present teachings that there are several alternative strategies on how to mount fiber rovings 2 to the transport frame 5. It is possible to mount a plurality of fiber rovings 2 to the transport frame 5 by mounting individual fiber rovings 2 in between two mounting devices 9 on opposite sides of the transport frame 5. However, an alternative solution would be to mount one single elongated fiber on the transport frame 5 by winding the fiber consecutively from one mounting device 9 to the next until a support grid layer 3 is formed. For example, one could start by fixing the fiber to a first mounting device 9, then stretch it from there to one mounting device 9 on the opposite side of the transport frame 5, fix it there, e.g. by knotting or tying it around a pin or similar, then drag it for example to one adjacent mounting device 9 on the same side or on the other side, mount it there, and so on until a support grid layer 3 is formed that is framed by the transport frame 5.

[0041] FIG. 5 schematically shows selected manufacturing steps of the method M of FIG. 3. The production process runs from right to left in FIG. 5. At M3, the matrix material layup 7 (not shown) that is placed on top of the support grid layer 3 of fiber rovings 2 on the transport frame 5 is softened by heating the support grid layer 3 together with the matrix material layup 7 within a heating station 8 by infrared radiation 12 other suitable means. Next at M4, the transport frame 5 is moved into a press 6 (see arrow in FIG. 5), which includes a shaping tool 11. Here, a semi-finished composite laminate 1 is formed by pressing the support grid layer 3 together with the softened matrix material layup 7. This includes under M4 shaping the semi-finished composite laminate 1 with the shaping tool 11 according to a predetermined shape by automatically adjusting at least one of the tension and a position of the fiber rovings 2 according to the predetermined shape. Each fiber roving 2 may be adjusted individually and/or several or all fiber rovings 2 may be adjusted collectively.

[0042] Next the method M comprises under M5 consolidating the semi-finished composite laminate 1 to form the fiber-reinforced composite laminate 1. Finally, the method M comprise under M6 cutting the ends of the fiber rovings 2 protruding from the fiber-reinforced composite laminate 1 to separate the fiber-reinforced composite laminate 1 from the transport frame 5. The fiber rovings 2 are consequently co-consolidated with the thermoplastic matrix 4 and remain as reinforcements of the fiber-reinforced composite laminate 1.

[0043] In the foregoing detailed description, various features are grouped together in one or more examples or examples with the purpose of streamlining the disclosure. It is to be understood that the above description is intended to be illustrative, and not restrictive. It is intended to cover all alternatives, modifications and equivalents. Many other examples will be apparent to one skilled in the art upon reviewing the above specification.

[0044] The embodiments were chosen and described in order to best explain the principles of the invention and its practical applications, to thereby enable others skilled in the art to best utilize the invention and various embodiments with various modifications as are suited to the particular use contemplated. Many other examples will be apparent to one skilled in the art upon reviewing the above specification.

[0045] 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.