Reinforcing device, reinforcing arrangement and method for introducing load to laminated structural component while maintaining structural integrity of laminated structural component

Abstract

The invention relates to a reinforcing device, a reinforcing arrangement and a method for introducing a load to a laminated structural member while maintaining the structural integrity of the laminated structural member. In order to provide an alternative improvement in the structural stability of a laminated component, a reinforcing device (10) is provided. The reinforcement device comprises a body structure (12) having an abutment surface (14) and at least one fastening area (16). The abutment surface extends along a first direction. In a cross-sectional direction transverse to the first direction, the abutment surface comprises a rounded profile section (18) such that the abutment surface is configured to coincide with a concave edge section (20) of the laminated structural member (22). At least one fastening region is provided at the body structure opposite the abutment surface. The at least one fastening region is configured to fasten the abutment surface against the concave edge section of the laminated structural member.

Description

Technical Field

[0001] The present invention relates to the stability of curved sections of laminated materials; more particularly, the present invention relates to reinforcement devices, reinforcement arrangements, and methods for introducing loads into laminated structural members while maintaining the structural integrity of the laminated structural members. Background Art

[0002] Components of vehicles such as aircraft may include laminated layers. These components may be given structural integrity by integral manufacture of the laminated layers to provide stability. Certain portions of the integrally manufactured components may be exposed to forces acting on the vehicle and therefore on the laminated layers.

[0003] Therefore, alternative improvements in the structural stability of laminate components may be needed. Summary of the invention

[0004] The objects of the invention are solved by the subject matter of the main aspects; further embodiments are incorporated in the additional aspects. It should be noted that the aspects of the invention described below also apply to the reinforcement device, the reinforcement arrangement and the method for introducing loads into a laminated structural member.

[0005] According to the present invention, a reinforcement device is provided, which comprises a body structure. The body structure comprises an abutment surface and at least one fastening region. The abutment surface extends along a first direction. In a cross-sectional direction transverse to the first direction, the abutment surface comprises a rounded contour section, so that the abutment surface is configured to conform to a concave edge section of a laminated structural member. At least one fastening region is arranged at the body structure opposite to the abutment surface. At least one fastening region is configured to fasten the abutment surface against the concave edge section of the laminated structural member.

[0006] As an effect, the abutment surface acts as a convergence to maintain the structural integrity of the concave edge section.

[0007] As an advantage, more precise forces can be introduced in a targeted manner into the concave edge sections of the laminated structural component in order to prevent delamination.

[0008] By placing the reinforcement, ie corner fitting, into the corner, ie concave edge section, for example between the spar and the skin of a laminated structural member in direct contact with the radius of the concave edge section, the peeling or deployment forces will be directly counteracted by the corner fitting.

[0009] As an advantage, the reinforcement device provides increased safety against structural failure, since it increases the strength of the concave edge section, ie the radius of the CFRP (Carbon Fiber Reinforced Polymer), to prevent the ability to deploy.

[0010] As a further advantage, the load required for expansion to occur in the radius may be significantly increased, or the optimum orientation of the bolt at the tightening area may be avoided altogether.

[0011] According to the invention, there is also provided a reinforcement arrangement comprising at least one reinforcement device according to the aforementioned example and at least one fastening device. The at least one fastening device is configured to fasten the at least one reinforcement device against a concave edge section of a laminate structural member.

[0012] As an effect, the open end of a laminated structural member, such as an integrally manufactured composite material box-like element, can be accessed for the assembly process of the reinforcement device.

[0013] As an advantage, a laminated structural component, such as a closed CFRP box, does not have to be opened by milling a huge cutout in the laminated structural component, its corresponding skin, which would significantly weaken the structure of the box, since the cover of the cutout is a structural load-bearing cover with a large number of double-row fasteners.

[0014] As a further advantage, the reinforcement means only requires smaller holes for bolts or rivets that join the internal reinforcement means to the external fitting at the laminate structure.

[0015] According to an example, two reinforcement devices are provided and the bolt arrangement comprises two bolts. At least one fastening element is configured as a common fastening element. The two reinforcement devices are configured to be fastened against each other on both sides of the abutting convex edge section forming the spar. The reinforcement device is fastened to the common fastening element by two bolts to abut against the laminated structural member. The two bolts protrude from any one of the reinforcement devices so that their bolt hole axes intersect at an intersection point. Preferably, the intersection point is at the vertex area.

[0016] As an advantage, the reinforcement means may act synergistically to concentrate the retaining forces on the concave edge sections of the spar.

[0017] As an advantage, the forces or loads are more evenly distributed at the spar.

[0018] According to an example, two reinforcement devices are provided and the bolt structure comprises a U-bolt structure. At least one fastening element is configured as a main fastening element. The two reinforcement devices are configured to be fastened against each other on both sides of the abutting convex edge section forming the spar. The U-bolt structure comprises fastening arms. The fastening arms extend from each of the reinforcement devices in a direction opposite to the spar and engage at their intersection point at the vertex region. The U-bolt structure is configured to be fastened at the intersection point by the main fastening element at the laminated structural member, thereby exerting a holding force on the two reinforcement devices.

[0019] As an advantage, only a single main fastening element is required.

[0020] As a further advantage, only a single primary fastening element needs to be fastened at the laminated structural member.

[0021] As another advantage, more of the structural integrity of the laminated structural member is maintained.

[0022] According to an example, the body structure comprises at least one flange. The at least one flange is arranged at the body structure distal to the rounded profile section. The at least one flange is configured to hold the reinforcement device indirectly against the concave edge section using the at least one shear rivet.

[0023] According to an example, at least two reinforcing devices are provided. Each of the at least two reinforcing devices is provided with a fastening area formed to receive a support rod. The fastening device comprises at least one support rod, a bolt structure and a fastening element. The at least one support rod is fastened to the laminated structural member by the bolt structure and the fastening element. The at least one support rod is configured to hold one of the at least two reinforcing devices to the concave edge section via another of the at least two reinforcing devices abutting against the opposite concave edge section.

[0024] According to the present invention, there is also provided a method for introducing load into a laminated structural member while maintaining the structural integrity of the laminated structural member. The method comprises the following steps:

[0025] providing at least one laminate structural member having a concave edge section;

[0026] attaching a reinforcement device of the reinforcement arrangement to the concave edge section;

[0027] Fastening the reinforcing device and generating a force by means of the fastening device; and

[0028] The reinforcement arrangement concentrates forces on the abutment surface of the reinforcement device to counteract delamination forces at the concave edge section.

[0029] According to one aspect, the laminated structure is provided with retaining portions which are placed in abutment with rounded corner portions of the laminated structure which are subject to delamination forces. The retaining portions counteract these forces. To apply the retaining forces, the retaining portions are clamped in their position.

[0030] According to one aspect, strip elements, i.e. reinforcement devices, are provided, which are preferably arranged in pairs on both sides of the spar in the inner corner / edge, i.e., the concave edge section, between the spar and the skin of the integrally manufactured multi-spar box-shaped member, i.e., the laminated structural member. Optionally, only one strip element is provided on one side. The strip element is called a "corner fitting". The internal corner fitting is used as a counterpart to the external load introduction fitting located on the outside of the integrally manufactured multi-spar box-shaped member. The internal corner fitting and the external load introduction fitting are structurally joined by bolts and / or rivets extending through the openings on the skin of the box-shaped member. The internal fitting, the "corner fitting", accordingly offsets the peeling force, i.e., the deployment force. Different orientations of the bolts connecting the internal fitting to the external fitting are possible. This orientation affects the strength of the reinforcement device related to the failure caused by deployment.

[0031] These and other aspects of the invention will be apparent from and elucidated with reference to the embodiments described hereinafter. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Hereinafter, exemplary embodiments of the present invention will be described with reference to the following drawings:

[0033] Figure 1 The overall concept of a cross section of an example of a reinforcement device is schematically shown.

[0034] Figure 2 An example of a reinforcement device is schematically shown in cross section.

[0035] Figure 3A and Figure 3B The cross section through an example of a reinforcement device having a holding section designed as a rod is schematically shown.

[0036] Figure 4 The general scheme of a cross section of an example of a reinforcement arrangement is schematically shown.

[0037] Figure 5 An example of a reinforcement arrangement with cross bolts and a common fastening element as fastening means is schematically shown in cross section.

[0038] Fig. 6A The general scheme of a cross section of an example of a reinforcement arrangement with a U-bolt structure is schematically shown.

[0039] Figure 6B , Figure 6C , Fig.6D , Fig. 6E , Fig. 6F , Figure 6G , Figure 6H A cross section of an example of a reinforcement arrangement having a U-bolt structure configured as a flexible belt structure 126 is schematically shown.

[0040] Fig.6I A cross section of an example of a reinforcement arrangement having an inverted U-shaped bolt structure is schematically shown.

[0041] Figure 6J A cross section of an example of a reinforcement arrangement with a U-bolt structure configured as a U-bracket is schematically shown.

[0042] Figure 6K and Figure 6L An example of a reinforcement arrangement is schematically shown in cross-section in different directions, wherein a U-shaped bolt structure comprises a plate, and the end of the plate protrudes into another U-shaped piece.

[0043] Figure 6M A cross section of an example of a reinforcement arrangement is schematically shown, wherein the U-bolt arrangement comprises a Y-bolt.

[0044] Figure 6N An example of a Y-bolt is schematically shown.

[0045] Fig. 7A An example of a reinforcement device with a flange is schematically shown.

[0046] Figure 7B An example of a reinforcement arrangement with a reinforcement device with a flange and a shear rivet is schematically shown.

[0047] Figure 7C An example of a reinforcement arrangement with a vertical flange abutting the spar is schematically shown.

[0048] Fig. 8A An example of a reinforcement arrangement with at least one supporting rod is schematically shown.

[0049] Figure 8B An example of a reinforcement arrangement with support rods and magnetic reinforcement means is schematically shown.

[0050] Fig. 9 The basic steps of an example of a method for introducing loads into a laminated structural member while maintaining the structural integrity of the laminated structural member are shown. DETAILED DESCRIPTION

[0051] Certain embodiments will now be described in more detail with reference to the accompanying drawings. In the following description, the same reference numerals are used for the same elements even in different drawings. The contents defined in the specification, such as detailed construction and elements, are provided to help fully understand the exemplary embodiments. In addition, well-known functions or structures are not described in detail because these functions or structures make the embodiments unclear due to unnecessary details. In addition, expressions such as "at least one of..." when appearing before a list of elements modify the entire list of elements rather than modifying the individual elements in the list.

[0052] In the example, the important part of the CFRP multi-spar box-shaped member manufactured in one piece is the CFRP radius between the spar of the multi-spar box-shaped member and the upper skin and the lower skin respectively. The example application of the reinforcement arrangement structure described in this article is in the context of a beam-shaped structure such as an aircraft flap, aileron or a rudder that is bent due to external loads. These structures are mounted to a supporting structure. At the joint of the supporting structure and the structure, the span force generated by the bending intersects with the reaction force generated in the vertical direction. If this joint between the supporting structure and the structure should be designed as an integral composite material accessory with a conventional 2D fabric or NCF, it is complicated to achieve the required strength because the load introduction area will be loaded out of the plane by the peeling force generated by the cross-shaped arrangement structure of the force flux plane at the structure. Due to the low out-of-plane strength of the composite material, the peeling force may cause the composite material accessory of the structure to fail. The radius at the composite material accessory may be affected by a mechanism called "unfolding": if the radius formed by the CFRP layer, such as the radius in the L-angle structure, is subjected to a load, the radius will be effectively bent. The curvature of the curved structure, i.e. the radius, may also induce out-of-plane stresses or peeling stresses in the radius, which may lead to delamination of the CFRP layer in the radius area. Loads applied to the radius area, such as tension, lateral forces, bending moments, can lead to delamination caused by deployment. In multi-spar box structures, high-load radii, especially in the load introduction area, are susceptible to deployment.

[0053] Figure 1 The general scheme of a cross section of an example of a reinforcing device 10 is schematically shown. The reinforcing device 10 comprises a body structure 12 having an abutment surface 14 and at least one fastening area 16. The abutment surface 14 extends along a first direction. In a cross-sectional direction transverse to the first direction, the abutment surface 14 comprises a rounded contour section 18, so that the abutment surface 14 is configured to conform to a concave edge section 20 of a laminated structural member 22. The at least one fastening area 16 is arranged at the body structure 12 opposite to the abutment surface 14. The at least one fastening area 16 is configured to fasten the abutment surface 14 against the concave section 20 of the laminated structural member 22 - indicated by arrow 24.

[0054] exist Figure 1 In the present invention, the term "reinforcement device" refers to providing a holding force shown by arrow 24 to reinforce the laminated structural member 22. The reinforcement device 10 may also be referred to as a force transmission device or a force introduction device or a load introduction device.

[0055] In the example, the reinforcing device 10 is configured to transmit or conduct the force from point A to point B, for example. Figure 1 Not shown in the figure - and the force is transmitted or conducted from point B to point A to provide mechanical force to hold the laminated structural member 22 to prevent delamination.

[0056] The term "body structure" refers to an object structure used as a structural part. The body structure 12 can be configured as a frame or a 3D grid-like structure or a beam-like structure or a rack or can also be configured as a solid structure, for example, forming a volume filled with material and having a three-dimensional shape. Figure 1 The main body structure 12 can also be understood as a structural unit or a structural component.

[0057] In an example, the body structure 12 is a frame, a track, a rack, a strap, a border, a ridge, a bracket, a strip, a corner, or a fitting or a corner fitting.

[0058] In an example, the body structure 12 provides a constriction.

[0059] In the example, in addition to at least one fastening area 16, the body structure 12 also includes Figure 1 Recesses, deepenings, depressions and cavities not shown in the drawing are provided to reduce weight.

[0060] In an example, the body structure 12 may include a gradual change in its stiffness, thermal conductivity, or other material parameters.

[0061] In an example, the body structure 12 is made of at least one of the group of aluminum, titanium, polymers, resins, fiber materials, CFRP materials, or composite materials.

[0062] The term "abutment surface" refers to the surface of an object that can be pushed against another object - also referred to as Figure 1 The arrow 24 in FIG. 1 shows - or against another object to hit the face of another object. The abutment surface 14 is configured to exchange forces with another object.

[0063] In an example, the abutment surface 14 is configured to be attached to another object.

[0064] In the example, the abutment surface 14 encloses the recess.

[0065] In the example, the abutment surface 14 encloses the body structure 12 .

[0066] In the example, the rigidity of the material of the abutment surface 14 varies along the abutment surface 14. Figure 1 Not shown.

[0067] The fastening region 16 may also be referred to as a fastening point, a fastening point, an attachment point or attachment point, a fixing point, a mounting point or mounting portion or mounting part or a fastening device.

[0068] The term "fastening area" relates to a point that is capable of receiving a force in order to secure the body structure 12 at a predetermined position.

[0069] In the example, at least one fastening region 16 is located at the laminate structural member 22 .

[0070] In the example, at least one fastening region 16 is located at a surface of the body structure 12 and is configured to receive a fastening member as described below. Fig. 8A and Figure 8B A support rod is further shown in order to maintain the body structure 12 at a predetermined position.

[0071] exist Figure 1 In the example shown, the at least one fastening area 16 may cover the entire surface 26 of the body structure 12 . The surface of the body structure 12 is opposite to the abutment surface 14 .

[0072] In the example, at least one fastening region 16 comprises a hole through the body structure 12 to receive a support rod or bolt 33 or wire. Figure 1 Not shown.

[0073] In an example, at least one fastening region 16 is configured to generate a preload force or a biased retaining force or clamping force.

[0074] The term "first direction" may refer to the y direction in a Cartesian coordinate system. The term "cross-sectional direction" may refer to the x direction in a Cartesian coordinate system that is perpendicular to the y direction. The term "cross-sectional direction" refers to a cut through the body structure 12 transverse to the first direction, which reveals Figure 1 A “cross-section” view on a circular profile of the abutment surface 14 at the body structure 12 is shown.

[0075] The rounded contour section 18 may also be referred to as a rounded contour or a smooth contour.

[0076] The term “section” refers to an area at, on a surface of, or in a volume of the body structure 12 .

[0077] In the example, the rounded profile has a curvature. The curvature is the amount by which the profile deviates from a straight line or the amount by which the abutment surface 14 deviates from a plane.

[0078] In the example, the rounded contour is described by a radius, which is Figure 1 Not shown.

[0079] In the example, the radius is inversely proportional to the curvature of the rounded contour.

[0080] The concave edge section 20 may also be referred to as an edge section or edge. The concave edge section describes the inner side of an edge or curve that can hold a volume. The term "convex edge section" refers to the inner side of a convex edge section. Figure 1 The outer part on the right side cannot maintain the volume part.

[0081] In the example, Figure 1 The concave edge section 20 is obtained by bending or folding a plane away from the plane.

[0082] In the example, the concave edge section 20 is obtained by attaching an edge of a plate to the surface of another plate.

[0083] In the example, the concave edge section 20 is obtained by laminating layers to each other in a curved form.

[0084] In the example, the concave edge section 20 is obtained by connecting layers of different structural components via lamination.

[0085] In the example, the concave edge section 20 is a CFRP radius at the connection between different CFRP-based components. Figure 1 Not shown.

[0086] In the example, the concave edge section 20 is the CFRP radius between the upper and lower skins and the spar of the CFRP multi-spar box, which is Figure 1 Not shown.

[0087] In the example, the concave edge section 20 is a CFRP radius at a structural component of the aircraft, which is Figure 1 Not shown.

[0088] In the example, the concave edge section 20 is part of an integrally manufactured laminate structural member 22 .

[0089] In the example, the concave edge section 20 is part of an integrally manufactured CFRP multi-spar box. Figure 1 Not shown.

[0090] In an example, the concave edge section 20 is part of a 2D fabric or comprises an NCF.

[0091] In an example, the body structure 12 and the concave edge section 20 are made of the same material.

[0092] The term "conform" describes the use of the abutment surface 14. Figure 1The geometric state in which the interface contact surface between the abutment surface 14 and the concave edge section 20 is maximized.

[0093] In the example, the abutment surface 14 is made to match or cooperate with the concave edge section 20 .

[0094] In an example, the abutment surface 14 comprises a layer of elastic material to match the edge section.

[0095] In the example, the abutment surface 14 fits snugly into the concave edge section 20 .

[0096] The term "laminated structural member" refers to a component made of interconnected layers.

[0097] In examples, the layers are interconnected by resin, polymer or any other bonding substance.

[0098] In examples, each layer includes any organic and / or inorganic fiber material.

[0099] In the example, the laminated structural member 22 is a CFRP panel.

[0100] In an example, the laminate structural member 22 includes NCF and / or 2D fabric material.

[0101] The term "fastening" means to Figure 1 The orientation of the abutment surface 14 in the embodiment is fixed, preserved, maintained or anchored towards the concave edge section 20 .

[0102] In an example, the body structure 12 comprises more than at least one fastening area 16 , for example two or three or at most five fastening areas.

[0103] In the example, the at least one fastening region 16 is configured to fasten the abutment surface 14 against the concave edge section 20 by connecting the at least one fastening region 16 to a laminate structural member 22 or another structural component.

[0104] Figure 2 Schematically shown is a cross section of an example of a reinforcement device 10. At least one fastening region 16 of the device comprises a bolt hole 28 along a bolt hole axis 30 and a retaining section 32 for abutting a portion of the bolt. The bolt hole axis 30 extends through the abutment surface 14. A bolt 33 can be inserted into the bolt hole 28 to apply a retaining force to the retaining section 32, thereby securing the position of the abutment surface 14.

[0105] The term "bolt hole axis" may be used to describe the orientation of the bolt 33 toward the body structure 12. However, this means that the orientation of the bolt 33 may vary along the bolt hole axis 30. The bolt hole axis 30 only describes a rough trend of how the bolt 33 is oriented relative to the body structure 12 or the concave edge section 20, not an exact one.

[0106] In the example, the bolt holes 28 are configured as recesses in the body structure 12 .

[0107] In the example, the bolt hole 28 is configured to enter from the abutment surface 14 into the body structure 12, wherein the bolt hole 28 terminates at Figure 2 The main body structure 12.

[0108] In the example shown, the bolt hole 28 traverses the entire body structure 12 .

[0109] In the example, the bolt holes 28 are provided with threads for mounting screws.

[0110] In the example, the inner surface of the bolt hole 28 is configured to enhance friction with the bolt 33 .

[0111] In the example, the bolt holes 28 are provided with Figure 2 The bolt 33 provides a positive locking connection.

[0112] The holding section 32 may also be referred to as a screw connection portion.

[0113] In the example, the retaining section 32 is a nut or a hook in the body structure 12 .

[0114] In the example, the retaining section 32 is configured to Figure 2 A preload force is applied to the bolt 33.

[0115] In the example, the retaining section 32 is formed in the body structure 12 to achieve a form-locking connection with a portion of the bolt.

[0116] In the example shown, the bolt 33 is a straight bolt.

[0117] In the example, the bolt 33 is configured to generate a preload force.

[0118] The bolt 33 can be fixed to the laminated structural member 22. For example, the bolt 33 is provided with a head on one end, and a nut can be mounted on the other end.

[0119] In the example, the nut is a barrel nut.

[0120] In the example, the bolt 33 does not tighten or hold the abutment surface 14 directly against the concave edge section 20. Figure 2 Not shown, but in the following Figure 7BFurther indicated in.

[0121] exist Figure 2 In the example of FIG. 2 , the bolt hole 28 is formed so that the bolt hole axis 30 of the bolt hole 28 is aligned with the bisecting diagonal 34 of the concave edge section 20. The bisecting diagonal 34 passes through the vertex area 36 of the concave edge section 20 and divides the concave edge section 20 into two parts 38a, 38b. The retaining section 32 applies a retaining force along the bisecting diagonal 34 via the bolt 33 in the bolt hole 28.

[0122] In the example, the opposing clamping force from the concave edge section 20 is generated by applying a retaining force to the concave edge section 20. Figure 2 The two parts of the concave edge section 20 clamp the body structure 12 via the abutment surface 14 .

[0123] In the example, a bisector, corresponding to the bolt hole 28 , divides the body structure 12 into two parts.

[0124] In the example, the apex region 36 is the point of concentration of compressive forces in the concave edge section 20 .

[0125] The term "apex region" does not necessarily describe the mathematical vertex of the geometry of the concave edge segment 20. The apex region refers to the region at the edge segment.

[0126] In the example, the body structure 12 and the abutment surface 14 are formed so that the holding force is directly concentrated on the apex region 36. Then, the abutment surface 14 is configured to counteract the delamination force of the laminated structural member 22 with the holding force, which is at the apex region 36. Figure 2 Not shown.

[0127] In the example, all parts of the reinforcement device 10 are configured so that the holding force is concentrated on the apex region 36 of the concave edge section 20 .

[0128] The term "delamination force" may also be referred to as peel force.

[0129] In the example, the concave edge section 20 comprises a plurality of layers interconnected by lamination. Figure 2 The layers tend to delaminate at the concave edge section 20. The layers have a tendency or inclination to delaminate at the apex region 36. The apex region 36 exerts a delamination force in a direction from the convex edge section toward the concave edge section 20. The delamination separates the layers that are held together by the connecting substance. The delamination forms cavities in the material at the apex region 36, which Figure 2 The cavity results in a weakening of the material at the concave edge section 20. The abutment surface 14 prevents the creation of cavities by applying a reaction force from the retaining section 32 via the abutment surface 14 towards the apex region 36, thereby inhibiting delamination.

[0130] In an example, the tendency to form delamination and the type of delamination depend on the type of laminated structural member 22 .

[0131] In an example, the reinforcement device 10 is configured to facilitate scalability of its dimensions to counteract peel forces defined by the type of laminated structural member 22 .

[0132] exist Figure 2 In the example of FIG. 4 , the transition and edge 40 of the body structure 12 distal to the rounded contour section 18 is beveled and / or rounded to disperse the force transmission—indicated by arrows 42 .

[0133] In an example, when a load is introduced to the reinforcement device 10 , the sharp edges and the sudden reduction in rigidity at the abutment surface 14 may damage the laminate structural member 22 .

[0134] In the example, the additional degree of freedom of the bolt 33 in the bolt hole prevents an imposed bending moment from acting on the bolt.

[0135] In the example, due to local defects, the abutment surface 14 cannot be matched exactly with the concave edge section 20. In order to make the abutment surface 14 match, a larger tolerance is allowed in the orientation of the bolt by providing, for example, a tapered bolt hole, which is Figure 2 Not shown.

[0136] exist Figure 2 In an example not shown in FIG. 3 , the retaining section 32 for abutting against a portion of the bolt comprises a rotatable bolt suspension in the body structure.

[0137] In the example, to compensate for the imperfections along the concave edge section 20 , the bolts are allowed to change their orientation within the body structure 12 by means of a rotatable bolt suspension.

[0138] As an advantage, the additional degree of freedom prevents imposed bending moments from acting on the bolt.

[0139] As a further advantage, the matching of the abutment surface 14 with the concave edge section 20 is improved.

[0140] exist Figure 2 In the example of FIG. 1 , the retaining section 32 for abutting against a portion of the bolt in the body structure 12 is formed to receive the barrel nut 44. The retaining section 32 is configured to generate a preload force at the bolt 33 using the barrel nut 44.

[0141] In the example, the fastening means comprises a plate or a nut or a barrel nut 44 .

[0142] In the example, the fastening elements are arranged at the bolts 33 and / or in the bolt holes 28 and / or at the body structure 12 and / or at the concave edge section 20 and / or at the laminated structural member 22 .

[0143] In the example, at least one bolt 33 abuts in the retaining section 32 in at least one reinforcement device 10 and passes through the abutment surface 14 and the bolt hole 28 in the concave edge section 20 to the convex edge section, where it is fastened by means of at least one fastening element, which is fastened in the convex edge section. Figure 2 Not shown.

[0144] Figure 3A and Figure 3B A cross section through an example of a reinforcement device 10 with holding sections designed as rods 46 , 47 is schematically shown.

[0145] exist Figure 3A In the example shown, the retaining section 32 is formed as a rod 46, wherein the rod 46 has a rotatable mounting 48 relative to the body structure 12 of the at least one reinforcement device 10 at a first end 50. The rod 46 is configured to receive the barrel nut 44 to retain the second end 52 of the rod 46 away from the first end 50 - indicated by the arrow 51 - to the concave edge section 20 by a preload force.

[0146] exist Figure 3B In the example shown, the rod 47 is mounted to the body structure 12 via a rotatable mount 48 and is formed to be retained with the second end 52 abutting against the concave edge section 20, indicated by arrow 51, and the area of ​​the laminate structural member 22 opposite the concave edge section 20, indicated by arrow 53.

[0147] Figure 4 Schematically shown is a general scheme of a cross section of an example of a reinforcement arrangement 100. The reinforcement arrangement 100 comprises at least one reinforcement device 10 according to one of the aforementioned aspects and at least one fastening device 102. The at least one fastening device 102 is configured to fasten the at least one reinforcement device 10 against a concave edge section 20 of a laminated structural member 22.

[0148] In an example, more than one fastening device 102 is deployed, such as two, three, or five or more fastening devices 102 .

[0149] Figure 5A cross section of an example of a reinforcement arrangement 100 with crossed bolts and a common fastening element 112 as fastening means 102 is schematically shown. At least one fastening means 102 comprises a bolt structure 104 having at least one bolt 106 extending at least partially through the body structure 12 of the reinforcement device 10, and a fastening structure having at least one fastening element 108. The bolt structure 104 is configured to extend through a portion of the laminated structural member 22 and to be fastened at the laminated structural member 22 by means of the at least one fastening element 108 in order to hold the reinforcement device 10 against the concave edge section 20 of the laminated structural member 22.

[0150] In an example, variations of the reinforcement arrangement 100 are provided. As an example, these variations may have in common an elongated opening aligned with the long axis of the corner fitting. The opening accommodates a barrel nut 44 that transfers the tensioning load of the tensioning bolt into the corner fitting. Some variations differ in the manner in which the corner fitting engages the box and the outer fitting.

[0151] In an example, a so-called "X-bolt concept" variant is provided. The bolt axis is aligned with the bisector between the spar and the lower skin. Thus, the contact force of the corner fitting is preferably directed to counteract the peeling forces in the radius between the spar and the lower skin.

[0152] exist Figure 5 In the example of FIG. 1 , at least one bolt 106 extends through the body structure 12 along the bisecting diagonal 34 that abuts the concave edge section 20 .

[0153] exist Figure 5 In the example of , two reinforcing devices 110a, 110b are provided. The bolt structure 104 includes two bolts 106a, 106b. At least one fastening element 108 is configured as a common fastening element 112. The two reinforcing devices 110a, 110b are configured to be fastened against each other on both sides of the abutting convex edge section 114 forming the spar 116. The reinforcing devices 110a, 110b are fastened to the common fastening element 112 by two bolts 106a, 106b to abut the laminated structural member 22. The two bolts 106a, 106b protrude from either of the reinforcing devices 110a, 110b so that their bolt hole axes intersect at the intersection point 118.

[0154] exist Figure 5 In the example option, preferably, the intersection point 118 is at the vertex area 36.

[0155] In the example, Figure 5 As shown, the two reinforcement devices 110a, 110b are configured to complement each other.

[0156] The term “complementary” means that the first reinforcing means 110 a and the second reinforcing means 110 b complete each other in their functions, force flows, structures and shapes to produce a consistent and synergistic effect in abutting the convex edge section 114 .

[0157] In the example, the first reinforcement means 110a is form-fitted to the concave edge section 20 of the high-angle side of the inclined spar, and the second reinforcement means 110b is form-fitted to the low-angle side of the corresponding spar. Figure 5 In the embodiment, the first reinforcing means 110a and the second reinforcing means 110b are shaped to abut against each other to fill a full angle of 180°.

[0158] In the example, when the L-shaped concave edge section 20 is mirrored relative to itself, an inverted T-shaped section is obtained from the laminated structural member 22. The upper right part of the T-shaped section may also be referred to as a spar. The horizontal section may also be referred to as a skin.

[0159] In the example, mirroring does not necessarily mean mirror symmetry of the mirrored part. It simply means the operation of duplicating and aligning the copies. This means that the upper right part or the spar can also be tilted, such as Figure 5 shown.

[0160] In the example, the apex region 36 is located at the point where the upper right portion and the horizontal segment meet.

[0161] In the example, the stiffening means 110a, 110b are located on both sides of the spar where the spar meets the skin.

[0162] Fig. 6A The overall scheme of a cross section of an example of a reinforcement arrangement 100 with a U-bolt arrangement 120 is schematically shown. The arrangement is provided with two reinforcement devices 110a, 110b. The bolt arrangement 104 comprises a U-bolt arrangement 120. At least one fastening element 108 is configured as a main fastening element 122. The two reinforcement devices 110a, 110b are configured to be fastened against each other on both sides of an abutting convex edge section 114 forming a spar 116. The U-bolt arrangement 120 comprises fastening arms 124a, 124b. The fastening arms 124a, 124b extend from each of the reinforcement devices 110a, 110b in a direction opposite to the spar 116 and meet at their intersection 118 at the vertex region 36. The U-bolt structure 120 is configured to be fastened at the intersection 118 via a primary fastening element 122 at the laminate structural member 22, thereby exerting a retaining force on both reinforcement devices 110a, 110b.

[0163] Figure 6B , Figure 6C , Fig.6D , Fig. 6E , Fig. 6F , Figure 6G and Figure 6H A cross section of an example of a reinforcement arrangement 100 having a U-bolt structure 120 configured as a flexible belt structure 126 is schematically shown.

[0164] exist Figure 6B In the example shown, the U-bolt structure 120 is a flexible band structure 126. The fastening arms 124a, 124b are configured as the flexible band structure 126 extending from each of the stiffening devices 110a, 110b to join at the intersection 118. The main fastening element 122 is configured for tensioning the flexible band structure 126. This tensioning fastens the two stiffening devices 110a, 110b against each other on both sides of the abutting convex edge section 114 forming the spar 116.

[0165] exist Figure 6B In the example shown, the flexible belt structure 126 is a steel belt 128 .

[0166] exist Figure 6B In the example shown, the main fastening element 122 is an eccentric 130 which tensions the steel belt 128 .

[0167] exist Figure 6C In the example shown, the primary fastening element 122 is a tensioning bolt 132 that tensions the flexible belt structure 126. Fig.6D The tensioning bolt 132 is shown in FIG.

[0168] exist Fig. 6E In the example shown, the primary fastening element 122 is a wedge 134 that tensions the flexible strap structure 126 .

[0169] exist Fig. 6F In the example shown, the belt structure is a CFRP ring 136 .

[0170] In an example, the elasticity of the CFRP ring 136 is affected by curing with resin.

[0171] exist Fig. 6F In the example shown, the fixing screw 137 of the main fastening element 122 and the main fastening element 122 can be introduced by removing the region 138 of the concave edge section 20 .

[0172] exist Figure 6G In the example shown, the main fastening element 122 comprises a fixing bolt 137 .

[0173] exist Figure 6H In the example shown, the fastening arms 124 a , 124 b of the U-bolt structure 120 are joined at the reinforcement means 110 a , 110 b to form a closed O-bolt structure 140 .

[0174] Fig.6I Schematically shown is a cross section of an example of a reinforcement arrangement 100 with an inverted U-bolt structure 120. The fastening arms 124a, 124b of the U-bolt structure 120 engage at an intersection 118a at the spar 116 opposite the apex region 36, and the main fastening element 122 comprises an inverted bolt 142a, 142b, which fastens the intersection 118 against the laminate structural member 22. The inverted bolts 142a, 142b extend vertically through the laminate structural member 22. The intersection 118a fastens the two reinforcement devices 110a, 110b against each other on both sides of the abutting convex edge section 114 forming the spar 116.

[0175] Figure 6J A cross section of an example of a reinforcement arrangement 100 having a U-bolt structure 120 configured as a U-bracket 144 is schematically shown.

[0176] Figure 6K and Figure 6L Schematically shows a cross section of an example of a reinforcement arrangement 100 in different directions, wherein the U-bolt structure 120 is formed as a plate 146 and the fastening arms 124a, 124b are formed as fastening points 148a, 148b. The reinforcement devices 110a, 110b extend from any of the fastening points 148a, 148b to the concave edge section 20. The main fastening element 122 is configured to fasten the plate 146 at the end of the plate 150 opposite to the spar 116 at the laminated structural member 22 to fasten the two reinforcement devices 110a, 110b against each other on both sides of the abutting convex edge section 114 forming the spar 116.

[0177] exist Figure 6L Shown relative to Figure 6K In the example of the rotation of the spar 116 in the embodiment of the present invention, the end of the plate 150 protrudes in the direction of the spar 116 in a transverse U-shaped shape 152 transverse to the U-bolt structure 120. The end of the plate includes adjacent fastening points 154a, 154b. The adjacent fastening points 154a, 154b are configured to be attached to another pair of adjacent stiffening devices 110c, 110d at the same abutting convex edge section 114 forming the spar 116.

[0178] Figure 6M A cross section of an example of a reinforcement arrangement 100 is schematically shown, wherein a U-bolt arrangement 120 comprises a Y-bolt 160. Two reinforcement means 110a, 110b are provided. The U-bolt arrangement 120 comprises Figure 6NThe Y-bolt 160 is shown. The at least one fastening element 108 is configured as a main fastening element 122 and the two reinforcement means 110a, 110b are configured to be fastened against each other on both sides of an abutting convex edge section 114 forming a spar 116.

[0179] Figure 6N An example of a Y-bolt 160 is schematically shown.

[0180] The Y-shaped bolt 160 includes bolt arms 162a, 162b and a main bolt 164. Figure 6M At the reinforcement arrangement 100 shown, bolt arms 162a, 162b extend from each of the reinforcement devices 110a, 110b along the bisecting diagonal 34 abutting the concave edge section 20 and join at their intersection 118 at the vertex region 36, where the bolt arms 162a, 162b have a rotatable connection 165 relative to a main bolt 164. The main bolt 164 protrudes through a portion of the laminate structural member 22 in a direction opposite to the spar 116. The main bolt is configured as part of the main fastening element 122 at the laminate structural member 22, thereby exerting a holding force on the two reinforcement devices 110a, 110b, which is illustrated by the branching arrow 166.

[0181] In the example, the Y-bolt is provided as a so-called "Y-bolt concept", which essentially comprises three fittings joined together by a central bolt, the main bolt 164. The central bolt allows the fittings to rotate relative to each other. This additional degree of freedom prevents the forced bending moment from being applied to the inclined bolts of the "X-bolt concept". In addition, the bolts joining the outer fitting, the main fastening element 122, to the Y-bolt can be oriented perpendicular to the lower skin abutting the convex edge section 114, thereby facilitating manual drilling.

[0182] As an advantage, the rotatable connection 165 at the intersection 118 of the Y-bolts prevents bending moments from acting on the tilt bolt arms 162a, 162b.

[0183] As an advantage, the rotatable connection 165 at the intersection 118 of the Y-bolts prevents bending moments from acting on the tilt bolt arms 162a, 162b.

[0184] In the example, the bolt holes 28 are formed such that their engaging bolt holes are aligned with the mirror image axis of the abutting convex edge section 114 .

[0185] In the example, the engaging bolt hole 28 is formed for the main bolt.

[0186] In the example, the bolt holes 28 are formed such that their engaging bolt holes are aligned with the spar 116 .

[0187] In the example, the bolt hole 28 is configured to support a Y-bolt 160 .

[0188] In the example, the main fastening element 122 further comprises at least one bearing structure 167 and at least one nut as part of the main fastening element 122. The axis of the main bolt 164 is inclined relative to the bearing structure 167, and the main bolt 164 is aligned with the inclined spar. The main bolt 164 is fixed to the fixing area of ​​the bearing structure 167 by means of at least one nut. Figure 6M The bearing structure 167 in the embodiment comprises a recess 168 in the fixing region, which provides a flat and inclined abutment surface for at least one nut oriented obliquely relative to the surface of the bearing structure 167 .

[0189] Fig. 7A An example of a reinforcement device 10 having a flange 174 is schematically shown. The body structure 12 comprises at least one flange 174. The at least one flange 174 is arranged at the body structure 12 at the distal end of the rounded contour section 18. Figure 7B In the embodiment of the present invention, at least one flange 174 is configured to indirectly hold the reinforcement device 10 against the concave edge section 20 using at least one shear rivet 170 .

[0190] Figure 7B An example of a reinforcement arrangement 100 comprising reinforcement devices 110a, 110b with flanges 174a, 174b and shear rivets is schematically shown. Figure 7B The bolt structure 104 in the embodiment further includes at least one shear rivet 170. The at least one bolt 33 and the at least one shear rivet 170 protrude from the abutment surface 14 of the body structure 12 and are configured to protrude through a common abutment surface 172 of the concave edge section 20 to hold the reinforcement device 10 at the concave edge section 20 of the laminated structural member 22.

[0191] In the example, the bolt axis of at least one bolt 33 is relative to Figure 7B The orientation of the spar in FIG. 1 is inclined at an angle α to hold the reinforcement device 10 at the concave edge section 20 of the laminate structural member 22 .

[0192] In an example, the angle α is greater than or equal to 5°.

[0193] In the example, at least one bolt 33 and at least one shear rivet 170 protrude vertically from the abutment surface 14 of the body structure 12. Figure 7B Not shown.

[0194] In the example, at least one shear rivet 170 protrudes vertically from the abutment surface 14 of the body structure 12, and the bolt axis of at least one bolt 33 is inclined relative to the spar 116 at an angle α greater than or equal to 5°. Figure 7B As shown, the at least one flange 174a is configured to provide a shear-resistant fixation between the abutment surface 14 and the concave edge section 20 .

[0195] In the example, the retention is provided in an indirect manner. The term “indirect” means that the bolts and shear rivets do not generate a retention force that is applied directly to the apex region 36 of the concave edge section 20 via the bisecting diagonal 34 .

[0196] In the example, Figure 7B The force flow in FIG. 1 is further characterized by the fact that the bolts and shear rivets hold the reinforcements 110 a , 110 b against the spar 116 , rather than pressing the reinforcements 110 a , 110 b against the spar 116 .

[0197] In the example, the force flow is more characterized in that it is a friction force flow rather than a preload force flow.

[0198] In the example, the holes for the bolts and shear rivets through the abutting convex edge section 114 are in the direction of the spar 166 and perpendicular to the abutting convex edge section 114 .

[0199] As an advantage, the reinforcement arrangement 100 with the attached shear rivets facilitates drilling holes for fastening the reinforcement arrangement 100 at the laminate structural member 22 .

[0200] In the example, the additional bolts provide additional friction to tighten the abutment surface 14 against the concave edge section 20 .

[0201] In the example, the additional bolts are shear rivets.

[0202] In the example, at least one straight bolt and at least one shear rivet 170 are fastened at the laminate structure portion by fastening elements to hold the reinforcement device 10 indirectly against the concave edge section 20 .

[0203] In an example, the arrangement comprises:

[0204] At least two straight bolts;

[0205] At least two shear rivets;

[0206] at least two fastening elements;

[0207] at least two additional fastening elements; and

[0208] at least two of the reinforcement devices 110a, 110b;

[0209] The at least two reinforcement means 110a, 110b are configured to complement each other. The reinforcement means 110a, 110b are configured to be indirectly retained on the abutting convex edge section 114 forming the spar 116 by:

[0210] at least two bolts fastened to the at least two fastening elements; and

[0211] At least two shear rivets, which are additionally fastened to the at least two additional fastening elements. The reinforcement means 110a, 110b are mirrored at the spar 116.

[0212] In another example, the two reinforcement devices 110a, 110b further include flanges.

[0213] The reinforcement means are configured to be indirectly fastened at the abutting convex edge section 114 forming the spar 116 by:

[0214] at least two bolts, the at least two bolts being fastened to the at least two fastening elements; and

[0215] At least two shear rivets at the flange, the at least two shear rivets being fastened to at least two additional fastening elements.

[0216] In an example, an aircraft comprising a fuselage and a frame structure with a propulsion system is provided. At least one of the fuselage and the frame structure comprises a structural component comprising a laminated structural member 22 having a concave edge section 20. At least one reinforcement arrangement 100 according to one of the aforementioned examples is provided with abutment surfaces 14 of a reinforcement device 10 against the concave edge section 20. The frame structure is attached to the fuselage, and both the frame structure and the fuselage are configured to operate the aircraft. At least one laminated structural member 22 is mounted to a functional unit of the fuselage and / or the frame structure via its concave edge section 20 by at least one reinforcement system. The functional unit is configured to present the state of at least one laminated structural member 22 via at least one reinforcement system to allow the operation of the aircraft. The at least one laminated structural member 22 is configured as one of the groups comprising flaps, ailerons, rudders and doors.

[0217] As an advantage, a more robust aircraft is obtained.As an advantage, the forces are applied more precisely to the components of the aircraft.

[0218] In examples, two, three or five laminated structural members and reinforcement arrangements are provided.

[0219] The term "reinforcement arrangement" may also be referred to as reinforcement system or reinforcement system.

[0220] In the example, a variant of a so-called "straight bolt corner fitting" is provided. This variant has straight bolts that are oriented more or less perpendicular to the lower skin abutting against the convex edge section 114. Therefore, the straight bolts cannot directly counteract the peeling forces. In order to avoid that the corner fitting will be pushed sideways, additional flanges for additional shear rivets are added to the corner fitting.

[0221] Figure 7C An example of a reinforcement arrangement 100 having vertical flanges 176, 178 abutting against an example of a spar 116 is schematically shown. The vertical flange 176 is formed to extend along the spar 116 abutting one of the convex edge sections 114a. The vertical flange 176 is configured to be connected to another vertical flange 178 formed to extend along the spar 116 abutting the other convex edge section 114b. Both flanges are connected to the spar 116 by a plurality of shear rivets 170.

[0222] exist Figure 7C In the example of , a wedge-shaped recess is provided between the abutment surface 14 and the laminated structural member 22, opposite to the spar 116, the wedge-shaped recess being indicated by the angle wr. The wedge-shaped recess wr tapers toward the concave edge section 20. Both the wedge-shaped recess wr and the distance d indicated by the arrow d are configured to direct the orientation of the force indicated by the arrows 177a, 177b that tightens the reinforcement means 110a, 110b against the concave edge section 20.

[0223] Fig. 8A An example of a reinforcement arrangement 100 with at least one support rod 182 is schematically shown. The reinforcement arrangement 100 comprises at least two reinforcement devices 110a, 110b. Each of the at least two reinforcement devices 110a, 110b is provided with a fastening region formed to receive the support rod 180a, 180b. The reinforcement arrangement 100 comprises a fastening device 102, which comprises at least one support rod 182, a bolt structure 104 and a fastening element 108. The at least one support rod 182 is fastened to the laminated structural member 22 by the bolt structure 104 and the fastening element 108. The at least one support rod 182 is configured to hold one of the at least two reinforcement devices 110a to the concave edge section 20a through the other reinforcement device 110b of the at least two reinforcement devices abutting against the opposite concave edge section 20b.

[0224] In an example, at least one support rod 182 is a dovetail joint.

[0225] Figure 8BAn example of a reinforcement arrangement 100 with a support rod 182 and magnetic reinforcement means 194a, 194b is schematically shown. The fastening means 102 also comprises magnetic primary fastening elements 190a, 190b. The magnetic primary fastening elements 190a, 190b are provided with fastening areas 192a, 192b for the support rod. The magnetic reinforcement means 194a, 194b comprise a magnetic element 196. The magnetic reinforcement means 194a, 194b are configured to be fastened against each other by their magnetic attraction force and the magnetic attraction force of the magnetic primary fastening element 190a on both sides of the abutting convex edge section 114a forming the first spar 116a to form a magnetic triangle 198a. The support rod is configured to abut against another magnetic primary fastening element 190b of another magnetic triangle 198b at the second spar 116b abutting against the convex edge section 114b, holding the magnetic triangle at the first spar 116a by the magnetic primary fastening element 190a.

[0226] As an advantage, the magnetic attraction force eliminates the need to drill bolt holes in the laminated structural member 22 for tightening bolts by a preload force.

[0227] Fig. 9 The basic steps of an example of a method 200 for introducing a load into a laminated structural member while maintaining the structural integrity of the laminated structural member are shown. The method 200 includes the following steps:

[0228] In a first step 202, at least one laminate structural component having a concave edge section is provided.

[0229] In a second step 204 , a reinforcement device of the reinforcement arrangement is attached to the concave edge section.

[0230] In a third step 206 , the reinforcing device is fastened by the fastening device and a force is generated.

[0231] In a fourth step 208 , forces are concentrated on the abutment surface of the reinforcement means by the reinforcement arrangement to counteract delamination forces at the concave edge section.

[0232] It must be noted that embodiments of the present invention are described with reference to different subject matters. In particular, some embodiments are described with reference to method type claims, while other embodiments are described with reference to device type claims. However, it will be understood by those skilled in the art from the above description and the following description that, unless otherwise indicated, any combination of features related to different subject matters, in addition to any combination of features belonging to one type of subject matter, is also considered to be disclosed by the present application. However, all features can be combined to provide synergistic effects that exceed the simple superposition of features.

[0233] Although the present invention is illustrated and described in detail in the drawings and the foregoing description, such illustration and description are to be considered illustrative or exemplary rather than restrictive. The present invention is not limited to the disclosed embodiments. Other variations of the disclosed embodiments may be understood and effected by those skilled in the art in practicing the claimed invention by studying the drawings, the disclosure, and the dependent claims.

[0234] In the claims, the word "comprising" does not exclude other elements or steps, and the indefinite article "a" or "an" does not exclude a plurality. A single processor or other unit may fulfill the functions of several items recited in the claims. The mere fact that certain measures are recited in mutually different dependent claims does not indicate that a combination of these measures cannot be used to advantage. Any reference signs in the claims should not be construed as limiting the scope.

Claims

1. A reinforcing device (10), comprising a main body structure (12), wherein the main body structure (12) has: an abutment surface (14); and at least one fastening region (16); in, The abutment surface extends along a first direction; wherein, in a cross-sectional direction transverse to the first direction, the abutment surface comprises a rounded contour section (18) such that the abutment surface is configured to conform to a concave edge section (20) of a laminated structural member (22); wherein the at least one fastening region is disposed at the body structure opposite to the abutment surface; and Wherein, the at least one fastening region is configured to fasten the abutment surface against the concave edge section of the laminate structural member.

2. The reinforcing device according to claim 1, wherein: The at least one fastening region includes a bolt hole (28) along a bolt hole axis (30) and a retaining section (32) for abutting against a portion of the bolt; wherein the bolt hole axis extends through the abutment surface; and A bolt (33) can be inserted into the bolt hole to apply a retaining force to the retaining section, thereby securing the position of the abutment surface.

3. The reinforcing device according to claim 2, wherein: The bolt hole is formed such that the bolt hole axis of the bolt hole is aligned with a bisecting diagonal line (34) of the concave edge section; wherein the bisecting diagonal line passes through the vertex region (36) of the concave edge segment to divide the concave edge segment into two parts (38a, 38b); and The holding section applies the holding force along the bisecting diagonal line via the bolt in the bolt hole.

4. Reinforcement device according to one of the preceding claims, wherein The transition and edge (40) of the body structure distal to the rounded contour section is beveled and / or rounded to distribute force transmission.

5. Reinforcement device according to one of the preceding claims, wherein The retaining section for abutting a portion of the bolt includes a rotatable bolt hanger in the body structure.

6. Reinforcement device according to one of the preceding claims, wherein The retaining section for abutting a portion of the bolt is formed to receive a barrel nut (44); and The retaining section is configured to generate a preload force on the bolt by using the barrel nut.

7. A reinforcement arrangement structure (100), comprising: at least one reinforcing device (10) according to one of the preceding claims; as well as at least one fastening device (102); Therein, the at least one fastening device is configured to fasten the at least one reinforcement device against a concave edge section of the laminate structural member.

8. The reinforcement arrangement according to claim 7, wherein: The at least one fastening device comprises: a bolt structure (104) having at least one bolt (106) extending at least partially through the body structure of the reinforcement device; and a fastening structure having at least one fastening element (108); Therein, the bolt structure is configured to extend through a portion of the laminate structural member and is configured to be fastened at the laminate structural member by the at least one fastening element to hold the reinforcement device against the concave edge section of the laminate structural member.

9. The reinforcement arrangement according to claim 8, wherein: The at least one bolt extends through the body structure along a diagonal bisecting the abutting concave edge section.

10. The reinforcement arrangement according to claim 8, wherein: Two reinforcing devices (110a, 110b) are provided; Wherein, the bolt structure comprises two bolts (106a, 106b); wherein the at least one fastening element is configured as a common fastening element (112); wherein the two reinforcement means are configured to be fastened against each other on both sides of an abutting convex edge section (114) forming a spar (116); wherein the reinforcing device is fastened to the common fastening element by the two bolts to abut against the laminated structural member; wherein the two bolts protrude from any one of the reinforcement devices such that the bolt hole axes of the two bolts intersect at an intersection point (118); and Wherein, the intersection point is in the vertex area.

11. The reinforcement arrangement according to claim 9, wherein: Two reinforcement devices are provided; Wherein, the bolt structure comprises a U-shaped bolt structure (120); wherein the at least one fastening element is configured as a main fastening element (122); and wherein the two reinforcement means are configured to be fastened against each other on either side of an abutting convex edge section forming the spar; Wherein, the U-shaped bolt structure includes a fastening arm (124a, 124b); wherein the fastening arms extend from each of the stiffening means in a direction opposite to the spar and join at an intersection of the fastening arms at the apex region; and Therein, the U-bolt structure is configured to be fastened at the intersection point by the main fastening element at the laminated structural member, thereby exerting a retaining force on the two reinforcement devices.

12. The reinforcement arrangement of claim 8, wherein: The bolt structure also includes at least one shear rivet (170); wherein the at least one bolt and the at least one shear rivet protrude from the abutment surface of the body structure, and the at least one bolt and the at least one shear rivet are configured to protrude through a common abutment surface (172) of the concave edge section to retain the reinforcement device at the concave edge section of the laminated structural member.

13. The reinforcement arrangement according to claim 12, wherein: The body structure includes at least one flange (174); wherein the at least one flange is disposed at the body structure at a distal end of the rounded contour segment; and Therein, the at least one flange is configured to hold the reinforcement device indirectly against the concave edge section using the at least one shear rivet.

14. The reinforcement arrangement of claim 7, wherein: At least two reinforcement devices are provided; wherein each of the at least two reinforcing means is provided with a fastening region formed to receive a support rod (180a, 180b); Wherein, the fastening device comprises: at least one support rod (182); Bolted structures; and Fastening elements; wherein the at least one support rod is fastened to the laminated structural member by means of the bolt structure and the fastening element; and Therein, the at least one support rod is configured to hold one of the at least two reinforcement devices to the concave edge section via the other of the at least two reinforcement devices abutting against the opposite concave edge section.

15. A method (200) for introducing a load into a laminated structural member while maintaining the structural integrity of the laminated structural member, the method (200) comprising the steps of: providing (202) at least one laminate structural member having a concave edge section; attaching (204) a reinforcement device of a reinforcement arrangement to the concave edge section; Fastening (206) the reinforcing device and generating a force by means of a fastening device; as well as The force is concentrated (208) by the reinforcement arrangement on an abutment surface of the reinforcement device to counteract delamination forces at the concave edge section.

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