• 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 describes a structural component (1) with a main body (2) formed by a composite fiber material, a plurality of first reinforcing elements (11) and a plurality of second reinforcing elements (12), wherein the main body (2) is configured as a vaulted body with a peripheral edge (3) and a vertex (4), in which the first reinforcing elements (11) are joined to the main body (2) and respectively have a concave curvature facing towards a first plane (e1) and in which the second reinforcement elements (12) are joined to the main body (2) and have respectively also a concave curvature facing a second plane (e2). Furthermore, the invention describes a method for manufacturing the structural component, as well as a pressure fuselage for a vehicle with a structural component. (Machine-translation by Google Translate, not legally binding)
    公开号:ES2651126A2
    申请号:ES201730315
    申请日:2017-03-09
    公开日:2018-01-24
    发明作者:Reinald Pfau；Jochen SCHOLLER；Bernhard Hoerger；Thomas Drexl
    申请人:Premium Aerotec GmbH；
    IPC主号:
    专利说明:

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    DESCRIPTION
    STRUCTURAL COMPONENT, PROCEDURE FOR THE MANUFACTURE OF A STRUCTURAL COMPONENT, PRESSURE FUSELAGE FOR A VEHICLE WITH
    STRUCTURAL COMPONENT
    The present invention relates to a structural component, a process for the manufacture of a structural component, as well as a pressure fuselage for a vehicle, in particular an aircraft or spacecraft with a structural component.
    The pressure fuselages of vehicles, in particular of aircraft, have a structure as tight as possible to the pressure. An elongated body structure is formed that is tightly closed at at least one end by a structural component.
    Document US 2015/0037541 A1 discloses a pressure frame for an airplane fuselage, the frame being made as an essentially spherical dome with a circumference and presenting reinforcing bands that extend along geodesic lines between two points of the circumference on the dome.
    The objective of the present invention is to provide a structural component, which has a high mechanical load capacity with a low component weight and which can be manufactured in a simple and efficient manner, as well as a process for the realization of such a structural component.
    In addition, the objective of the present invention is to provide a pressure fuselage with such a structural component and to specify a use of such a structural component in a pressure fuselage of a vehicle.
    These objectives are achieved respectively by a structural component with the characteristics of claim 1, by a method with the characteristics of claim 11, a pressure fuselage with the characteristics of claim 16, as well as by the use of the structural component in a Pressure fuselage of a vehicle according to claim 17.
    Advantageous configurations and improvements are specified in the
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    dependent claims referring to independent claims.
    According to a first aspect of the invention, a structural component is provided with a main body formed of a fiber composite material, a plurality of first reinforcement elements and a plurality of second reinforcement elements. The main body is configured as a domed body with a peripheral edge and a vertex. The first reinforcing elements are connected with the main body and extend respectively between two points of a first pair of points located at a distance in the peripheral edge in a peripheral direction of the component along the peripheral edge, so that they present respectively a concave curvature facing a foreground, which extends in a first direction of curvature that occurs at the vertex, as well as through the center of curvature corresponding to it and the vertex. The second reinforcing elements are connected to the main body and extend respectively between two points of a second pair of points located at a distance in the peripheral edge in a peripheral direction of the component along the peripheral edge, so that they have a concave curvature facing a second plane, which extends in a second direction of curvature that occurs at the vertex, as well as through the center of curvature corresponding to it and the vertex.
    An arrangement of the reinforcing elements, so that they extend concavely facing the first or second plane, as described above, has the advantage that, in the case of a given maximum area of the body fields main delimited by reinforcement elements and possibly by the peripheral edge of the main body, fields with large area in the edge area of the main body can also be obtained. This reduces the number of reinforcement elements that are necessary together so that none of the fields exceed the maximum area. Simultaneously in this way the mechanical load is distributed more evenly over the individual reinforcement elements of the plurality of the first reinforcement elements and the plurality of second reinforcement elements. Therefore, the structural component according to the invention has a particularly high mechanically stable weight.
    The fields may generally be delimited by one or more of the following components: first reinforcement elements, second reinforcement elements, peripheral edge of the main body. The vertex reinforcement elements present, which are entered even more precisely below, are formed by first or second
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    reinforcement elements.
    The reinforcing elements or reinforcing strips are generally configured as oblong components, for example, they can have a trapezoidal, rectangular, semicircular, elliptical, V-shaped, T-shaped or similar cross-section.
    The main body is formed by two surfaces that constitute the domed shape of said main body.
    The first surface and the second surface have their normal output vectors, with respect to the interior of the main body, oriented opposite each other. Preferably one of the surfaces is convexly curved and the other respectively concavely, frontally viewed from the outside according to a side elevation view of the main body, so that p. ex. a dome-shaped or generally domed design of the main body is defined.
    The vertex of the main body can be produced, for example, for a case not illustrated, by the centroid of one of the surfaces of the main body that constitute the vaulted shape of the main body. It is also conceivable to define the vertex as that point on one of the surfaces of the main body that constitute the vaulted shape of the main body, which has the shortest distance to the center of mass of the main body. In addition, preferably, the vertex can also be selected as one of those points of the main body surfaces that constitute the vaulted shape of the main body, in which one of these surfaces has a maximum or a minimum curvature. In particular, the vertex can be placed on a cutting line of a plane of symmetry of the main body with one of the surfaces of the main body that constitutes the vaulted shape of the main body. In particular, the vertex can preferably be located at a vertex of two cutting lines of the symmetry planes of the main body with one of the surfaces of the main body constituting the domed shape of the main body.
    The main body may preferably have at least one plane of symmetry. In this case the first and / or the second plane are advantageously identical to one of the symmetry planes. This results in a structure especially favorable for the mechanical stability of the structural component.
    In addition, it may be provided that a first vertex reinforcement element, which is formed
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    by one of the plurality of first reinforcing elements, it extends through the vertex of the main body and a second vertex reinforcing element, which is formed by one of the plurality of the second reinforcing elements, extends through the vertex of the main body. In this way an especially high mechanical stability of the structural component is obtained.
    The first direction of curvature may be the first principal direction of curvature that occurs at the vertex and the second direction of curvature the second principal direction of curvature that occurs at the vertex.
    In particular, it can be provided that each of the first and second reinforcement elements have a concave curvature facing the first and second planes, so that each of two of a plurality of fields of the structural component, each of the which is delimited by two seconds and two first reinforcement elements, present areas that deviate from each other by a maximum of 15 percent, preferably at most 10 percent and in particular preferably at most 5 percent. In the case of small similar deviations of the areas from each other, a minimum number of reinforcement elements can be used in the case of a given size of the structural component and in the case of a given maximum allowed area of the fields, whereby gets an extraordinarily low component weight.
    The first and second reinforcing elements are preferably formed respectively by at least one strip of the fiber composite. In particular, it may be provided that a first or second reinforcement element of the plurality of first and second reinforcement elements is constituted by a plurality of strips of the composite of superimposed fibers, so-called tows. For example, up to 80 tows can be stacked. The tows typically have a width in a range between 1.5 mm and 20 mm, preferably in a range between 5 mm and 18 mm and in particular preferably between 10 mm and 15 mm. The structural component may have in the area of a reinforcing element, for example, a thickness in a range between 2 mm and 8 mm, in an area without reinforcement element, for example between 1.5 mm and 5 mm. In the areas mentioned above, an especially light structural component with good mechanical properties is produced.
    The main body preferably has at least two layers of fiber composite material. The strips of the fiber composite of a first layer of fiber composite material can be arranged with their oblique or perpendicular longitudinal direction, in general
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    transversely with respect to the longitudinal direction of the strips of the fiber composite of an adjacent layer of the fiber compound.
    In addition, it may be provided that the reinforcing elements are embedded at least partially between two layers of the fiber composite. Alternatively, the reinforcing elements may be arranged on a first and / or a second surface of the main body. The first surface and the second surface have their normal output vectors, with respect to the interior of the main body, oriented opposite each other. Preferably one of the surfaces is convexly curved and the other respectively concavely, frontally viewed from the outside according to a side elevation view of the main body, so that p. ex. a dome-shaped or generally domed design of the main body is defined.
    The structural component may in particular have a peripheral closure element, which extends along the peripheral edge of the main body and is connected with it, so that the peripheral edge is located within the peripheral closure element with respect to a width thereof , so that the peripheral closure element configures an edge of the structural component.
    When the peripheral edge of the main body is located within the peripheral closure element, the structural component can advantageously be configured with a constant thickness in the area of the peripheral closure element. In this way, by means of the peripheral closure element, different thicknesses of the structural component are compensated, which are produced in the area of the reinforcement elements and in the areas without reinforcement elements. In this way the structural component can be suitably mounted in a fuselage structure, in particular in a pressure fuselage.
    Furthermore, according to the invention, a process for manufacturing a structural component is provided. The procedure presents in particular the following stages:
    form a semi-finished product arrangement through the following steps:
    - arranging a semi-finished product of fiber composite material, comprising a pre-impregnated fiber layer with a matrix material, on a contour surface of a tool that has a surface development such that it forms the semi-finished product of fiber composite material in a domed main body arrangement with a
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    peripheral edge and a vertex,
    - arranging a plurality of first reinforcing elements on the fiber composite material, so that they extend respectively between two points of a first pair of points located at a distance in the peripheral edge in a peripheral direction of the component along the edge peripheral, so that the reinforcing elements respectively have a concave curvature facing a foreground, which extends in a first direction of curvature that occurs at the vertex, as well as through the center of curvature corresponding thereto, and
    - arranging a plurality of second reinforcing elements on the fiber composite material so that they extend between two points of a second pair of points located at a distance on the peripheral edge in a peripheral direction of the component along the peripheral edge, so that the reinforcement elements have a concave curvature facing a second plane, which extends in a second direction of curvature that occurs at the vertex, as well as through the center of curvature corresponding thereto, and
    heating the semi-finished product arrangement, by exerting a pressure, and thereby hardening the matrix material to form a main body from the semi-finished product of fiber composite material, as well as to connect the first and second reinforcing elements with the main body.
    Furthermore, in the process it can be provided that, by forming the semi-finished product arrangement after the second reinforcement elements are arranged, an arrangement is made thereon of another semi-finished product of fiber composite material.
    In addition, it may be provided that the application of the semi-finished product of fiber composite material is carried out by successive arrangement of at least two layers of fiber composite material on the contour surface of the tool. In this case the arrangement of the layers of fiber composite material is advantageously performed by forming a first layer of fiber composite material by unwinding a plurality of strips of the fiber composite in a longitudinal strip direction and on this first layer of composite material. of fibers, at least one other layer of fiber composite material is disposed by unwinding a plurality of strips of the fiber composite, so that the strips of the fiber composite of the other layer of the fiber composite material respectively extend in a longitudinal direction oblique, angled or generally transversely to the longitudinal direction of the strips of the fiber composite of the layer of
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    fiber composite material arranged adjacent.
    In general, in the process it can also be provided that the arrangement of the plurality of first reinforcement elements and the arrangement of the plurality of second reinforcement elements is carried out by unwinding at least one strip of the fiber composite over the semi-finished product of material fiber composite
    The strips of the fiber compound mentioned in reference to the process can be constructed in general in an identical manner to the strips of the fiber compound disclosed in reference to the structural component, in this case in particular in reference to the reinforcing elements.
    Furthermore, according to the invention, a pressure fuselage with a structural component according to one of the embodiments described above is provided. The pressure fuselage may in particular be the pressure fuselage of a vehicle, in particular of an aircraft, of a spaceship, of a vessel, in particular of a submarine, or of a road, rail or amphibious vehicle. The pressure fuselage can also be mounted on a stationary device, such as in a building or a construction. In general, the pressure fuselage defines an interior space in which a constant pressure can be adjusted, the pressure prevailing in the interior space of an environment surrounding the pressure fuselage.
    In this respect, the structural compound can be joined thanks to union components with the structure of the fuselage of a vehicle. Especially preferably, the structural component may be mounted as so-called pressure frame in a pressure fuselage of an aircraft.
    Here under a "fiber composite material" is generally understood a material that has at least one layer of reinforcing fibers preferably in the form of yarn, such as, for example, carbon, glass, ceramic, aramid, boron, mineral, natural or of plastic or mixtures of these, the at least one layer of reinforcing fibers being embedded in a matrix material, such as an elastomeric, thermoplastic, duroplastic resin or in general a natural or plastic resin or the like.
    Here under a "vaulted body" is generally understood a body or a component that has at least a first surface and a second surface with its normal vectors
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    of exit, with respect to the interior of the main body, oriented in opposite direction to each other, extending the first and / or the second surface respectively curved in at least one direction, where a central line of the body or component has a curvature whose center line, in a cross section perpendicular to one of the surfaces and in a direction of curvature thereof, is formed by the set of points that in the cross section have the same distance from respectively a point on the first surface and a point on the second surface, the corresponding points on the first surface and the second surface being points that are separated from each other by the smallest possible distance. For example, under a vaulted body, a body at least partially domed, spherical, parabolic or shell-shaped is understood here.
    Under a "center of curvature" it is generally understood here a center of a circle that has a radius that best approximates the curvature of a surface in a direction of curvature at a given point on the surface or the curvature of a curve at a point determined from the curve.
    With reference to the directions of direction and axes, in particular to the indications of direction and axes that refer to the development of physical structures, it is understood herein under a development of an axis, a direction or a structure "transversely" to another axis, direction or structure, that these, in particular the tangents that occur at a corresponding point of the structures, extend respectively with an angle greater than or equal to 45 degrees, preferably greater than or equal to 60 degrees and in particular preferably of perpendicular to each other.
    The invention will now be explained in reference to the figures in the drawings. The figures show:
    Figure 1 a perspective view of a structural component according to a preferred embodiment of the present invention;
    Figure 2 a plan view of a first surface of the structural component shown in Figure 1;
    Figure 3 a plan view of a second surface of the structural component shown in Figure 1, oriented in the opposite direction to the first surface;
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    Figure 4 a detailed view of the area characterized by the letter Z of the structural component shown in Figure 3;
    Figure 5 a sectional view of the embodiment of the structural component according to the invention, which is produced with a section along the line A-A drawn in Figure 4;
    Figure 6 a sectional view of the embodiment of the structural component according to the invention, which is produced with a section along the line B-B drawn in Figure 4;
    Figure 7 a schematic view of the layers of composite material of superimposed fibers by way of example of a main body of the structural component;
    Figure 8 an exemplary embodiment of a vehicle with a pressure fuselage according to the present invention;
    Figure 9 a schematic representation of the sequence of the steps of the process according to the invention.
    In the figures the same references designate the same or functionally identical components, as long as the contrary is not indicated.
    Figure 1 shows a preferred embodiment of a structural component 1 according to the present invention. The structural component 1 has a main body 2 that is formed of a fiber composite material. The main body 2 is generally configured as a domed body with a peripheral edge 3 and a vertex 4 and in particular has a first surface 2a and a second surface 2b with its normal exit vectors, with respect to the interior of the main body 2, oriented opposite each other. In the exemplary embodiment shown in Figure 1, the first surface 2a is convexly curved and the surface 2b concavely viewed from the main body 2.
    Figures 1 to 3 show by way of example a main body 2 that has a symmetrical dome-like shape. Such a conformation offers in particular great mechanical stability when applying pressure on the second surface 2b. However, in general, non-symmetrical shaped main bodies 2 are also conceivable.
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    The vertex 4 of the main body 2 can be defined, for example, by the centroid of the first or second surface 2a, 2b of the main body 2. It is also conceivable to define the vertex 4 as that point of the first or second surface 2a, 2b of the main body that has the shortest distance to the center of mass of the main body. In addition, vertex 4 can also be selected as one of those points of the first or second surface 2a, 2b of the main body 2 in which the first or second surface 2a, 2b has a maximum or a minimum curvature. In particular the vertex 4 can be placed on a cutting line of a plane of symmetry of the main body 2 with the first or second surface 2a, 2b of the main body 2 and in particular preferably on a cutting point of second cutting lines of symmetry planes of the main body 2 with the first or second surface 2a, 2b of the main body 2.
    At vertex 4 the first or second surface 2a, 2b of the main body 2, preferably the first and second surface 2a, 2b of the main body 2, can be curved at least in a direction of curvature. The curvature can also be zero at the vertex. In general, a first direction of curvature K1 and a second direction of curvature K2 that are produced from the curvature of the first or second surface 2a, 2b can be defined at the vertex.
    If the first and / or the second surface 2a, 2b of the main body 2 is curved at vertex 4 in at least two directions, a first direction of curvature K1 can be selected extending in one of the directions in which one of the curves is curved. surfaces 2a, 2b at the vertex. A second direction of curvature K2 can be selected extending at an angle to the first direction of curvature K1.
    If the first and second surfaces 2a, 2b of the main body 2 only extend in a curved way in one direction at vertex 4, the first direction of curvature K1 can be given in this direction. A second direction of curvature K2 can be selected by extending at an angle preferably perpendicular to the first direction of curvature K1.
    If at the vertex 4 the curvature of the first and second surface 2a, 2b of the main body 2 is equal to zero, the first direction of curvature K1 can be selected basically at will, however, preferably extending along a line of symmetry or axis of symmetry. The second direction of curvature K2 can be selected extending at an angle, preferably perpendicular to the first direction of curvature K1.
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    The first direction of curvature 1 may in general be the first principal direction of curvature that occurs at vertex 4 and the second direction of curvature K2 the second principal direction of curvature that occurs at vertex 4. In this case the first and Second direction of curvature K1 and K2 extend perpendicularly to each other.
    In general, the first direction of curvature K1 may be transverse and in particular perpendicular to a principal direction of mechanical loading.
    As shown in Figures 1 to 3, the structural component 1 has a plurality of first reinforcement elements 11 and a plurality of second reinforcement elements 12, the reinforcement elements 11, 12 being connected respectively with the main body 2. In general the First reinforcement elements 11 extend transversely or obliquely to the second reinforcement elements 12. In particular it may be provided that a corresponding first reinforcement element 11 and a corresponding second reinforcement element 12 only intersect respectively at one point.
    As seen in particular in Figure 3, the first reinforcing elements 11 extend respectively between two points PA1, PE1 of a first pair of points located at a distance at the peripheral edge 3 of the main body 2 in a peripheral direction of the component U1 along the peripheral edge 3. The first reinforcing elements 11 extend between points PA1, PE1 so that they respectively have a concave curvature facing a first plane E1. The first plane E1 extends in the first direction of curvature K1 that occurs at vertex 4, as well as through the center of curvature M1 corresponding to it and to vertex 4.
    In addition, the second reinforcing elements 12 also extend respectively between two points PA2, PE2 of a second pair of points located remotely at the peripheral edge 3 in the peripheral direction of the component U1. The second reinforcement elements 12 extend between points PA2, PE2, so that they have a concave curvature facing this second plane E2. The second plane E2 extends in the second direction of curvature K2 that occurs at vertex 4, as well as through the center of curvature M2 corresponding to it and the vertex.
    The plane E1 is defined in particular by the first direction of curvature K1 at vertex 4 and a first radius vector, whose direction is defined by vertex 4 and the center of curvature M1
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    corresponding to vertex 4 and the first direction of curvature K1. The plane E2 is defined in particular by the second direction of curvature K2 at vertex 4 and a second radius vector, whose direction is defined by vertex 4 and the center of curvature M2 corresponding to vertex 4 and the second direction of curvature K2 .
    By concave curvature of the reinforcing elements 11, 12 towards the planes E1, E2 it can be understood, for example, that in a line of sight in the plane E1, E2, that is, in the direction of the first or second radius vector , and perpendicularly to the corresponding direction of curvature K1, K2, the first and second reinforcement elements 11, 12 extend concavely facing the planes E1, E2, as this is particularly clarified in Figures 2 and 3.
    By concave curvature of the reinforcing elements 11, 12 towards the planes E1, E2 it can also be understood, for example, that the reinforcing elements 11, 12 extend, in a viewing direction in the plane E1, E2, at along a curved line, where for each point of this curved line its respective center of curvature is located on one side of the curved line that is opposite the side of the line on which the plane E1 or E2 is located. In other words, the center of curvature of a point of the curved line and the corresponding plane E1, E2 are located on opposite sides of the curved line, as this is particularly clarified by Figures 2 and 3.
    Furthermore, by concave curvature of the reinforcing elements 11, 12 towards the planes E1, E2 it can also be understood that the reinforcing elements 11, 12 have, at each point that is located within the peripheral edge 3 of the main body, a distance normal smaller to the plane E1 or E2 than a connection line that extends geodesically between points PA1, PE1 or between points PA2, PE2.
    Preferably it may be provided that the reinforcing elements 11, 12 in the main body 2 extend along cutting lines that occur when the main body 2 is cut with a cylinder with an elliptical cross section. In this case, the central axis of the elliptical cylinder is preferably located outside the main body 2 and can extend in particular in parallel to the direction of the first or second radius vector. In the exemplary embodiment shown in Figures 1 to 6 of the structural component 1, the reinforcement elements 11, 12 extend respectively along similar cut lines, decreasing according to this example the radius of the elliptical cylinder as it increases the distance between the respective reinforcing elements 11, 12 and the plane E1 or E2, and
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    the cylinder axis extending parallel to the first and second radius vector.
    Points PA1, PE1 of the first pair of points are both respectively located on the same side of the plane E1 and preferably on respectively on different sides of the plane E2. Points PA2, PE2 of the second pair of points are both respectively located on the same side of the plane E2 and preferably respectively on different sides of the plane E1. This is shown by way of example in Figure 3.
    An arrangement of the reinforcing elements 11, 12, so that they extend with respect to the corresponding E1 or E2 plane concave, as described above, has the advantage that, in the case of a given maximum area of the Fields 15, 16 of the main body 2 delimited by the reinforcing elements 11, 12 and possibly by the peripheral edge 3 of the main body, fields 15, 16 with large surface area can also be obtained in the edge area of the main body 2. In this way, therefore, the number of reinforcement elements 11, 12, which are needed together so that none of the fields 15, 16 exceeds the maximum area, is reduced. Simultaneously in this way the mechanical load is distributed more evenly over the individual reinforcement elements of the plurality of the first reinforcement elements 11 and the plurality of the second reinforcement elements 12. Accordingly, the structural component 1 according to the invention It has a particularly high mechanical stability with low weight.
    Due to the concave curvature facing the planes E1, E2 of the first and second individual reinforcing elements 11, 12 described above, their radius of curvature is relatively large. The reinforcing elements 11, 12 are therefore slightly curved, which is favorable, on the one hand, in terms of mechanical stability and in particular in terms of manufacturing the structural component. Next, more detail is given in the last mentioned aspect.
    As shown in Figures 1 to 3, the structural component 1 may have a first vertex reinforcement element 13, which extends through the vertex 4 of the main body 2 and a second reinforcement element 14 which also extends through of vertex 4 of main body 2. The first vertex reinforcement element 13 is formed by one of the plurality of first reinforcement elements 11, the second vertex reinforcement element 14 is formed by one of the plurality of second reinforcement elements 12. In particular, it may be provided that the first reinforcing element 13 extends in the first plane E1 and
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    the second vertex reinforcement element 14 in the second plane E2.
    It is especially preferable that the first and second reinforcement elements 11, 12 respectively have a concave curvature facing the first and second planes E1, E2, so that respectively two of a plurality of fields 15 of the structural component 1 they present respectively areas that deviate from each other at most by a predetermined value, for example at most 15 percent, preferably at most 10 percent and in particular preferably at most 5 percent. The fields 15 are delimited in this case for respectively two seconds and two first reinforcement elements. Thus, in the case of a given size of the structural component 1 and in the case of a given maximum allowed area of the fields 15, a minimum number of reinforcement elements 11, 12 can be used, whereby a weight of extraordinarily low component.
    The first and second reinforcing elements 11, 12 may be formed, as shown by way of example in Figures 5 and 6, respectively, by at least one strip of the fiber compound 7, a so-called bast. Preferably a reinforcing element 11, 12 is formed by a plurality of strips of the fiber composite 7 superimposed with respectively extraordinarily small thickness, as shown in Figure 6. A strip of the individual fiber compound 7 respectively has a fiber layer that It is surrounded by a matrix material.
    The main body 2 can also be constituted by at least two layers of fiber composite material 8. In this case it may be provided in particular that the layers of fiber composite material 8 of the main body 2 are respectively formed by a plurality of strips of the fiber composite 7, as shown by way of example in figures 5 to 7. As schematically shown in figure 7, in this case it may be provided in particular that the strips of the fiber compound 7 of a first layer of material Fiber composite 18 extends in a first longitudinal direction of strip L18 and the strips of the fiber composite of a layer of fiber composite material 19 located adjacent to the first layer of fiber composite material 18 extend in a second longitudinal direction of band L19, extending the first and second longitudinal direction of strip L18, L19 obliquely to each other. In this way, especially stable flat components can be easily manufactured.
    The reinforcing elements 11, 12 may be embedded in particular at least partially
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    between two layers of the fiber composite 8, 18, 19. In particular the strips of the individual fiber composite 8 may be located in reference to a thickness direction of component T1 within the cross section of the main body 2 defined by the layers of the composed of fibers 8, 18, 19, as shown by way of example in Figure 6. In the example shown in Figure 6, the reinforcing element 12 extends to a depth d12 within the main body 2.
    In this way an especially good connection of the main body 2 with the reinforcement elements 11, 12 is obtained, whereby the structural component 1 receives an especially high mechanical stability.
    Alternatively, the reinforcing elements 11, 12 can be arranged on one of the surfaces 2a, 2b of the main body 2. In this way the structural component 1 can be manufactured in a particularly simple way.
    The reinforcing elements 11, 12 may have, for example, a rectangular, a semicircular, a T-shaped, a triangular or a trapezoidal cross section. Figures 4 and 6 show by way of example a second reinforcing element 12 with a trapezoidal cross section.
    Furthermore, it can be provided that the structural component 1 has a peripheral closure element 5. This extends along the peripheral edge 3 of the main body 2 and is connected to it. As shown in particular in Figure 4, the peripheral edge 3 of the main body is located within the peripheral closure element 5 with respect to a width b5 thereof, so that the peripheral closure element configures an edge 6 of the structural component
    I. Since the peripheral edge 3 of the main body is located within the peripheral closure element 5, the structural component 1 is configured in the area of the peripheral closure element 5 advantageously with a constant thickness t5, as shown by way of example in Fig. 5. In this way, by means of the peripheral closure element 5, different thicknesses t12 are compensated, which are produced in the area of the reinforcing elements.
    II, 12, and thicknesses t2 of the structural component that are produced in areas without reinforcement elements 11, 12. In this way the structural compound 1 can be suitably mounted in a fuselage structure, in particular in a pressure fuselage 50.
    The peripheral closure element 5 may be constructed as the reinforcing elements from a plurality of strips of the composite fiber 7 superimposed and joined.
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    Figure 8 shows by way of example a pressure fuselage 50 for a vehicle 60, in this example an airplane 61, according to the present invention. The pressure fuselage 60 has a structural component 1 that is configured in one of the ways described above.
    Figure 8 also shows by way of example a use according to the invention of a structural component 1, which is configured in one of the ways described above. Therefore, the use of the structural component 1 is provided in a pressure fuselage 50 of a vehicle 60, in particular in a pressure fuselage 60 of an aircraft 61, arranged as illustrated in Figure 8, with the surface 2a following the inner contour of the tubular wall of the pressure fuselage 50.
    Figure 9 shows by way of example the development of a process for the manufacture of a structural component 1. The process in particular presents a step S1 for the formation of a semi-finished product arrangement. This step S1 may have S1 in particular the following sub-stages:
    A first sub-stage S1a comprises an application of a semi-finished product of fiber composite material, which has a pre-impregnated fiber layer with a matrix material, on a contour surface of a tool, which has a surface development such that it forms the semi-finished product. of fiber composite material in a vaulted arrangement of the main body with a peripheral edge and a vertex.
    A second sub-stage S1b comprises an application of a plurality of first reinforcing elements on the fiber composite material so that they extend respectively between two points of a first pair of points located at a distance in the peripheral edge in a peripheral direction of the component , so that they respectively have a concave curvature facing a first plane, which extends in a first direction of curvature that occurs at the vertex, as well as through the center of curvature corresponding thereto.
    Another sub-stage S1c comprises an application of a plurality of second reinforcing elements on the fiber composite material, so that they extend respectively between two points of a second pair of points located at a distance in the peripheral edge in a peripheral direction of the component , so that these have a concave curvature facing a second plane that extends in a second
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    direction of curvature that occurs at the vertex, as well as through the center of curvature belonging to it.
    The process also has a second stage S2, in which a pressure is produced by heating S2 of the semi-finished product arrangement configured in step S1 and thus hardening the matrix material for the configuration of a main body of the product semi-finished fiber composite material, as well as for the connection of the first and second reinforcement elements with the main body.
    The step S1 may have another sub-stage S1d, which is carried out after the application of the second reinforcing elements and in which an application of another semi-finished product of fiber composite material is made. In this way the reinforcing elements 11, 12 can be partially or totally embedded in the cross section of the main body, in particular between two layers of fiber composite material 18, 19 located adjacent to the main body 2.
    Preferably the application of the semi-finished product of fiber composite material is carried out in step S1 by the successive arrangement of at least two layers of fiber composite material on the contour surface of the tool.
    In this case it may be provided in particular that the arrangement of the layers of fiber composite material 8, 18, 19 is carried out because a first layer of fiber composite material 18 is formed by unwinding a plurality of strips of the fiber composite 7 in a longitudinal direction of strip L18 and on this first layer of fiber composite material 18 at least one other layer of fiber composite material 7 is made by unwinding a plurality of strips of the fiber composite 7, so that the compound strips of fibers 7 of the other layer of the fiber compound 19 with its longitudinal strip direction L19 respectively extend obliquely with respect to the longitudinal direction of strip L18 of the strips of the fiber composite 7 of the fiber composite layer 18 located adjacent.
    In particular, it can be provided that the application S1b of the plurality of first reinforcement elements and the application S1c of the plurality of second reinforcement elements is carried out by unwinding at least one strip of the fiber composite 7 onto the semi-finished composite product of fibers. In this way, strips of the identical fiber composite can be used both for the configuration of the semi-finished product of
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    composite material, from which the main body 2 is formed, as well as for the configuration of the reinforcement elements 11, 12. In this way the procedure can be carried out especially efficiently.
    Due to the described concave curvature of the reinforcement elements 11, 12, the strips of the fiber composite 7 can be laid with relatively large radii for the formation of the reinforcement elements 11, 12. Consequently, strips or tows can be used more wide without folds forming. When using wider tows increases, on the one hand, the amount of material deposited per unit of time and simultaneously due to the higher resistance of the wide tows only a smaller number of tows per reinforcing element 11, 12 is required for the formation of the reinforcing elements 11, 12. Therefore, on the one hand, the manufacturing time of the structural component 1 is reduced and simultaneously a high strength of the low weight component is obtained.
    Reference List
    1 Structural component
    2 Main body
    3 Peripheral edge of the main body
    4 Main body vertex
    5 Peripheral closure element
    6 Edge of the structural component
    7 Strip of fiber composite, bast
    8 Layer of composite material of main body fibers
    11 First reinforcement elements
    12 Second reinforcement elements
    13 First vertex reinforcement element
    14 Second vertex reinforcement element
    15 Fields delimited for each time two first and two second elements of
    reinforcement
    16 Fields delimited by first and second reinforcement elements and the peripheral edge
    18 First layer of fiber composite material of the main body
    19 Adjacent fiber composite layer of the main body
    50 Pressure fuselage
    60 Vehicle
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    61 Aircraft
    d12 Depth of penetration of the reinforcement elements in the main body t2 Thickness of the structural component in areas without reinforcement elements t12 Thickness of the structural component in the area of the reinforcement elements E1 Foreground E2 Second plane
    L18, L19 Longitudinal strip directions of the fiber composite layers
    K1 First direction of curvature K2 Second direction of curvature
    M1 Center of curvature of the first direction of curvature M2 Center of curvature of the second direction of curvature PA1, PE1 Points of the first pair of points PA2, PE2 Points of the second pair of points T1 Direction of thickness of the component U1 Peripheral direction of the component
    权利要求:
    Claims (16)
    [1]
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    1. Structural component (1), comprising a main body (2), a plurality of first reinforcement elements (11) and a plurality of second reinforcement elements (12), in which the main body (2) is configured as a domed body with a peripheral edge (3) and a vertex (4), and in which the main body (2) is formed by a first surface (2a) and a second surface (2b) that constitute the vaulted shape thereof ;
    characterized in that:
    said main body (2) is formed by a fiber composite material;
    the first reinforcing elements (11) are connected to the main body (2) and extend respectively between two points (PA1, PE1) of a first pair of points located at a distance in the peripheral edge (3) in a peripheral direction of the component (U1) along the peripheral edge (3), so that said elements respectively have a concave curvature facing a foreground (E1), which extends in a first direction of curvature (K1) that occurs in the vertex (4), as well as through the center of curvature (M1) corresponding to this and the vertex (4); Y
    the second reinforcing elements (12) are connected to the main body (2) and extend respectively between two points (PA2, PE2) of a second pair of points located at a distance in the peripheral edge (3) in a peripheral direction of the component (U1) along the peripheral edge (3), so that they have a concave curvature facing a second plane (E2), which extends in a second direction of curvature (K2) that occurs at the vertex ( 4), as well as through the center of curvature (M2) corresponding to this and the vertex (4).
    [2]
    2. Structural component (1) according to claim 1, wherein a first vertex reinforcement element (13), which is formed by one of the plurality of first reinforcement elements (11), extends through the vertex ( 4) of the main body (2), and a second vertex reinforcement element (14), which is formed by one of the plurality of second reinforcement elements (12), extends through the vertex (4) of the main body (2).
    [3]
    3. Structural component (1) according to claim 1 or 2, wherein the first direction of curvature (K1) is the first principal direction of curvature that occurs at the vertex (4) and
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    The second direction of curvature (K2) is the second principal direction of curvature that occurs at the vertex (4).
    [4]
    4. Structural component (1) according to any one of the preceding claims, wherein each of the first and second reinforcement elements (11, 12) have a concave curvature facing the first and second planes (E1, E2 ), so that each of two of a plurality of fields (15) of the structural component (1), each of which is delimited by two seconds and two first reinforcement elements, has surface areas that deviate from each other at a maximum of 15 percent, preferably at most 10 percent and in particular preferably at most 5 percent.
    [5]
    5. Structural component (1) according to any one of the preceding claims, wherein each of the first and second reinforcing elements (11, 12) is formed by at least one strip of the fiber composite (7).
    [6]
    6. Structural component (1) according to any one of the preceding claims, wherein the main body (2) has at least two layers of fiber composite material (8).
    [7]
    7. Structural component (1) according to claim 6, wherein each of the layers of fiber composite material (8) of the main body (2) are formed by a plurality of strips of the fiber composite (7) which is they extend according to respective longitudinal directions, in which the longitudinal direction (L18) of the strips of the fiber composite (7) of a first layer of fiber composite material (18) extends obliquely with respect to the longitudinal direction (L19) of the strips of the fiber composite of an adjacent layer (19) of the fiber compound.
    [8]
    8. Structural component (1) according to claim 6 or 7, wherein the reinforcing elements (11, 12) are embedded at least partially between two layers of the fiber composite (8, 18, 19).
    [9]
    9. Structural component (1) according to any one of claims 1 to 7, wherein the reinforcing elements (11, 12) are arranged on a surface (2a, 2b) of the main body (2).
    [10]
    10. Structural component (1) according to any one of the preceding claims, in the
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    that the structural component has a peripheral closure element (5), which extends along the peripheral edge (3) of the main body (2) and is connected with it, so that the peripheral edge (3) of the main body is located within the same peripheral closure element (5) with respect to a width (b5) thereof, so that the peripheral closure element forms an edge (6) of the structural component (1).
    [11]
    11. Procedure for the production of a structural component (1), the procedure presenting the following steps:
    form (S1) a semi-finished product arrangement through the following steps:
    disposing (S1a) a semi-finished product of fiber composite material, comprising a pre-impregnated fiber layer with a matrix material, on a contour surface of a tool, where said contour surface has a surface development such that it forms the product semi-finished fiber composite material in a vaulted main body arrangement with a peripheral edge and a vertex,
    arranging (S1b) a plurality of first reinforcing elements on the fiber composite material, so that said reinforcing elements extend respectively between two points of a first pair of points located at a distance in the peripheral edge in a peripheral direction of the component along the peripheral edge, so that said reinforcing elements respectively have a concave curvature facing a first plane, which extends in a first direction of curvature that occurs at the vertex, as well as through the corresponding center of curvature to this one, and
    arranging (S1c) a plurality of second reinforcing elements on the fiber composite material so that said reinforcing elements extend respectively between two points of a second pair of points located remotely at the peripheral edge in a peripheral direction of the component a along the peripheral edge, so that said reinforcing elements have a concave curvature facing a second plane, which extends in a second direction of curvature that occurs at the vertex, as well as through the center of curvature corresponding thereto. , Y
    heating (S2) the arrangement of semi-finished product, by exerting a pressure, and thus hardening the matrix material to form a main body from the semi-finished product of the fiber composite, as well as to connect the first and second
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    reinforcement elements with the main body.
    [12]
    12. The method according to claim 11, wherein, upon forming the semi-finished product arrangement, after arranging the second reinforcing elements, an arrangement is made thereon of another semi-finished product of fiber composite material.
    [13]
    13. A method according to claim 11 or 12, wherein the arrangement of the semi-finished product of fiber composite material is carried out by successive arrangement of at least two layers of fiber composite material on the contour surface of the tool.
    [14]
    14. The method according to claim 13, wherein the arrangement of the layers of fiber composite material is carried out by forming a first layer of fiber composite material by unwinding a plurality of strips of the fiber composite according to a longitudinal direction and arranging at least one other layer of fiber composite material on the first layer of fiber composite material by unwinding a plurality of strips of the fiber composite such that the strips of the fiber composite of the other layer of the fiber composite respectively extend according to an oblique longitudinal direction with respect to the longitudinal direction of the strips of the fiber composite of the adjacent layer of fiber composite material.
    [15]
    15. A method according to one of claims 11 to 14, wherein the arrangement (S1b) of the plurality of first reinforcement elements and the arrangement (S1c) of the plurality of second reinforcement elements is carried out by unwinding of at least one strip the fiber composite over the semi-finished product of fiber composite material.
    [16]
    16. Pressure fuselage (50) for a vehicle (60) comprising a structural component (1) according to any one of claims 1 to 10.
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    同族专利:
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    US20170259511A1|2017-09-14|
    ES2651126B2|2019-01-17|
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    ES2651126R1|2018-03-05|
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