CONNECTOR AND METHOD FOR CONNECTING A FRAME AND A STRINGER OF A FUSE STRUCTURE OF AN AIRCRAFT, FUSE STRUCTURE AND AIRCRAFT

Description

[0001] The present invention relates to a connector and a method for connecting a frame and a stringer of a fuselage structure of an aircraft, a fuselage structure for an aircraft and an aircraft.

[0002] An aircraft fuselage typically has a fuselage structure comprising several parallel frames enclosing a longitudinal fuselage axis, and stringers extending along the longitudinal fuselage axis. An outer skin is usually attached to the stringers and frames. Frames come in various cross-sectional shapes, such as Z-profiles or T-profiles. Frames also typically have stringer recesses through which the stringers extend.

[0003] The frames and stringers are typically attached to one another by means of connectors. For example, US Pat. No. 3,600,016 A describes an angled connector that is attached to the frame and the stringer, which are S-shaped, by rivets. Another connector is described in EP 2 212 191 B1, wherein the connector has a base flange connected to a stringer and a frame flange extending transversely thereto, which is connected to a frame. The base flange and frame flange each have bores for the passage of rivets or other connecting elements.

[0004] Another hull structure is described in EP 2 301 840 B1, wherein the hull structure comprises Ω-shaped stringers and annular frames with a C-shaped cross-section which extend beyond the stringers, and wherein L-shaped support elements are provided which are connected by rivets to a foot of the stringer and the frame.

[0005] US 2389767 deals with the attachment of frames and stringers to the outer skin of an aircraft at their intersection point. The frames and stringers are designed as trusses. US 2018 / 162510 A1 describes, according to the translation of the abstract in Espacenet, a body of a mobile vehicle. The body comprises a skin, a stringer, and a frame. The skin includes a first tab and a second tab opposite the first tab. The first tab is fixed directly to the skin, and the second tab is fixed directly to the skin. The frame includes a cutout, a first foot, and a second foot. The second foot is spaced from the first foot by the cutout. The first foot is attached directly to the first tab of the stringer, so that the first tab of the stringer is located directly between the first foot of the frame and the skin.The second foot is attached directly to the skin, so that no part of the frame is attached directly to the second tab of the stringer. US 8480030 B2 describes, according to the translation of the abstract in Espacenet, a structural component for an aircraft or spacecraft with an outer skin and a first reinforcement element running along a first spatial direction on the outer skin. A second reinforcement element runs over the first reinforcement element in a second spatial direction. A foot element supports the second reinforcement element on the outer skin, wherein the foot element has a through opening in which the first reinforcement element is held in a form-fitting manner. From another aspect, a method for reinforcing an outer skin of an aircraft or spacecraft is provided, in which a first reinforcement element is attached to the outer skin along a first spatial direction.A base element with a through-opening is attached above the first reinforcement element, so that the first reinforcement element is held in the through-opening with a form-fitting fit. A second reinforcement element is attached to the base element in a second spatial direction above the first reinforcement element. US 8087621 B2 describes, according to the translation of the abstract in Espacenet, a holder for the hole-free and largely tool-free fastening of all types of components, in particular cables, within a conventional fuselage structure of an aircraft with stringers and annular frames, wherein the frames are each provided with an angle at intersection points, a stringer and an annular frame. The holder is designed in two parts with a lower part and an upper part that can be connected to it, wherein the lower part can be pushed onto an angle.By attaching the upper part to the lower part, the bracket is fixed in position at the intersection point in the upper area of ​​a ring frame. Fixing in its final position is achieved by connecting the bracket to a cross-line bracket as a functional element using an expansion pin or other connecting elements. Other alternative functional elements for fixing the components, such as a longitudinal line bracket, a crossbar, or a longitudinal batten for special installation requirements, can be combined with at least one bracket if required to form a bracket arrangement of any degree of complexity.

[0006] The object of the present invention is to find improved solutions for hull structures with stringers and frames, in particular solutions that simplify assembly of the hull structure.

[0007] This problem is solved by the subject matter of the independent claims. Advantageous embodiments and further developments emerge from the subclaims referring back to the independent claims in conjunction with the description.

[0008] According to a first aspect of the invention, a connector is provided for connecting a frame to a stringer of an aircraft fuselage structure extending transversely thereto. The connector comprises a base support extending in a connector longitudinal direction, a first connecting portion connected to the base support and extending in a first connector transverse direction, which first connecting portion has, in an end region facing away from the base support, a coupling structure for encompassing an end region of a cross section of the stringer, and a second connecting portion connected to the base support and configured for connection to the frame. The first connector transverse direction runs transversely to the connector longitudinal direction.

[0009] According to a second aspect of the invention, a fuselage structure for an aircraft is provided. The fuselage structure comprises a frame, in particular annular, which surrounds a fuselage longitudinal axis and has a stringer recess, a stringer extending along the fuselage longitudinal axis through the stringer recess of the frame, and a connector according to the first aspect of the invention. The first connecting section of the connector, together with the coupling structure, encompasses an end region of a cross-section of the stringer. The second connecting section of the connector is connected to the frame.

[0010] According to a third aspect of the invention, a method for connecting a frame and a stringer of a fuselage structure according to the second aspect of the invention is provided. The method comprises inserting the end region of the cross-section of the stringer into the coupling structure of the first connecting portion of the connector, positioning the second connecting portion of the connector on the frame, and connecting the second connecting portion of the connector to the frame.

[0011] One idea underlying the invention is to fasten a frame and a stringer of a fuselage structure to one another at their intersection point by means of a connector which can be positively connected at least to the stringer. For this purpose, the connector has a first connecting section with a coupling structure which is designed to engage around one end of the cross section of the stringer. The coupling structure can, for example, be hook-shaped and, due to its hook shape, defines a slot which is open on one side, e.g. U-shaped, into which one end of a web of the stringer can be inserted. The coupling structure thus engages around an end region of the cross section of the stringer. The first connecting section extends transversely to a base support of the connector, which base support can, for example, have an X-shaped, an H-shaped or other cross-sectional profile.The coupling structure is provided at an end region of the connecting section facing away from the base support. Furthermore, the coupling structure can also be L-shaped, with a first section and a second section extending transversely thereto, which extends along the longitudinal direction of the connector or along the base support. Thus, in both the L-shaped and the hook-shaped configuration of the coupling structure, a receiving region for receiving the cross section of the stringer can be formed between the coupling structure and the base support. Thus, the end region of the cross section of the stringer can be received in the slot defined by the hook shape of the coupling structure and / or the stringer can be clamped between the coupling structure and the base support.

[0012] One advantage of the connector is that the coupling structure encompassing the end of the stringer's cross-section creates a positive connection between the stringer and the connector. This connection can be easily installed by inserting the end of the stringer's cross-section into the hook-shaped coupling structure. The cross-sectional profile of the stringer can be hooked or clamped into the coupling structure of the connector. This facilitates installation, particularly in the potentially difficult-to-access intersection area between the frame and stringer. In particular, riveting the connector and stringer is no longer necessary.

[0013] According to the invention, the second connecting portion is oriented in a second connector transverse direction.

[0014] The second connector transverse direction runs transversely to the first connector transverse direction and transversely to the connector longitudinal direction. In an assembled state, the first connector transverse direction is thus directed along the frame, and the second connector transverse direction is directed along the stringer or transversely to the frame. The second connecting section can therefore be coupled to the frame in a direction transverse to the frame. This improves the support of the frame by the second connecting section and the load transfer between the frame and stringer by the connector.

[0015] According to the invention, the second connecting section is arranged in a second end region of the base support with respect to the connector longitudinal direction and extends in the second connector transverse direction, and wherein the second connecting section has, for example, an L-shaped or hook-shaped coupling structure for engaging around an end region of a cross-section of the frame in an end region facing away from the base support. For example, the second connecting section can have a transverse web, at the end of which a hook-shaped fold or extension is provided. The hook shape of the coupling structure of the second connecting section defines a slot into which one end of a web of the frame can be inserted. With the L-shaped structure, the end region of the cross-section of the frame can be clamped between the coupling structure and the second end region of the base support.This means that the bulkhead can also be connected to the connector in a form-fitting manner, which further facilitates assembly.

[0016] According to some embodiments of the connector, the second connecting portion may be formed integrally with the base support. In this case, the second connecting portion, if realized with an L-shaped or hook-shaped coupling structure, may be designed to be elastically deformable, so that the coupling structure can be locked to the frame.

[0017] According to some embodiments of the connector, it can be provided that the second connecting section has a guide region which is guided displaceably in a guide of the base support in the longitudinal direction of the connector, and wherein the guide has a first locking structure, in particular an elastic web, which engages in a locking structure formed in the guide region, in particular in the form of teeth. For example, the second connecting section can have a web as a guide region which is guided linearly displaceably between two webs of the base support. A tooth structure can be provided on the web of the second connecting section, which can be locked with an elastic locking pawl of the base support. The coupling structure can thus be displaced in the longitudinal direction of the connector and thereby brought into engagement with the frame.The locking structure can determine the position of the second connecting section.

[0018] According to some embodiments, the connector may comprise a plate-shaped adhesive carrier with a surface oriented in the second transverse direction of the connector, which surface is coated with an adhesive. The adhesive carrier is arranged between the first and second connecting sections with respect to the longitudinal direction of the connector and is connected to the base carrier. The adhesive carrier may, for example, be plate-shaped. The adhesive layer creates an additional, rivet-free connection between the connector and the frame. Furthermore, additional support of the frame is achieved by the adhesive carrier, which further improves the rigidity of the fuselage structure.

[0019] According to some embodiments of the connector, it can be provided that the second connecting section is plate-shaped for contact with a plate-shaped region of the frame. Accordingly, the second connecting section can be designed as a flange, which can be glued to the frame, for example, or connected by connecting elements such as rivets, bolts, screws or the like. This results in a simple design of the connector which can be flexibly combined with a variety of frame cross-sections. The second connecting section can in particular have a flat contact surface which is designed for contact with a plate-shaped region of the frame. The contact surface can in particular be oriented in the second connector transverse direction or in the first connector transverse direction.

[0020] According to some embodiments of the connector, the plate-shaped second connecting portion can be arranged in a second end region of the base support with respect to the longitudinal direction of the connector. This further improves the support of the frame against tilting.

[0021] According to some embodiments of the connector, it can be provided that the first connecting section has a transverse web extending in the first connector transverse direction, which is connected with a first end to the base support, wherein the coupling structure has a longitudinal web extending from a second end of the transverse web along a first end region of the base support, i.e. along the connector longitudinal direction, which longitudinal web is arranged at an end facing away from the transverse web on a

[0022] The U-shaped fold forms a slot with an opening facing the crossbar. The crossbar, the longitudinal web, and the first end region of the base support define a clamping space. This allows for particularly reliable mounting and clamping of the stringer in the first connection section.

[0023] According to one embodiment of the fuselage structure, the stringer can have an S-shaped cross-section, wherein the coupling structure engages behind the end region of the S-shaped cross-section of the stringer with respect to a fuselage radial direction perpendicular to the fuselage longitudinal axis. For example, the coupling structure of the first connecting section can be formed as described with the transverse web, the longitudinal web, and the U-shaped fold at the end of the longitudinal web.

[0024] In an example shown for better technical understanding, a fuselage structure for an aircraft is provided. The fuselage structure comprises a, in particular annular, frame enclosing a longitudinal fuselage axis with a frame base, a frame head which is located opposite the frame base with respect to a fuselage radial direction perpendicular to the longitudinal fuselage axis, and a stringer recess formed in the region of the frame base, a stringer extending along the longitudinal fuselage axis through the stringer recess of the frame, which stringer can have, for example, an Ω-shaped cross-section, a flatly extending outer skin which is fastened to the frame base of the frame and to the stringer, and a frame support.The frame support comprises a support foot which is partially arranged between the outer skin and the frame foot, a support beam which extends from the support foot in the fuselage radial direction, and a connecting portion which is connected to the support beam and has a coupling structure in an end region facing away from the support beam, wherein the coupling structure encompasses an end region of a cross section of the frame head.

[0025] The connecting structure of the frame support is thus designed for a positive connection to the frame, which facilitates the assembly of the frame support. For example, the connecting section can have a crossbar with a hook-shaped fold or extension at the end. The hook shape of the coupling structure of the connecting section defines a slot into which one end of a web of the frame can be inserted. With the L-shaped structure, the end region of the cross-sectional frame can be clamped between the coupling structure and the second end region of the base support. This also allows the frame to be connected to the connector in a positive manner, which further facilitates assembly.

[0026] Optionally, the bulkhead support can have at least one contact plate arranged between the support foot and the connecting section with respect to the fuselage radial direction and connected to the support beam, which contact plate bears against the bulkhead. The contact plate thus has a surface facing the bulkhead, in particular a main web of the bulkhead extending in the fuselage radial direction. This surface can optionally be coated with an adhesive layer that bonds the contact plate and the bulkhead together.

[0027] According to a fourth aspect of the invention, an aircraft having a fuselage structure according to the second aspect of the invention is provided.

[0028] With regard to directions and axes, in particular directions and axes relating to the course of physical structures, the course of an axis, a direction or a structure "along" another axis, direction or structure is understood to mean that these, in particular the tangents resulting at a respective point of the structures, each run at an angle of less than 45 degrees, preferably less than 30 degrees and particularly preferably parallel to one another.

[0029] With regard to directions and axes, in particular directions and axes relating to the course of physical structures, the term "transverse" to another axis, direction or structure is understood herein to mean that these, in particular the tangents resulting at a respective point of the structures, each run at an angle of greater than or equal to 45 degrees, preferably greater than or equal to 60 degrees and particularly preferably perpendicular to one another.

[0030] Herein, "one-piece", "one-piece", "integral" or "in one piece" components are generally understood to mean that these components are present as a single part forming a material unit and, in particular, are manufactured as such, one component not being detachable from the other without disrupting the material cohesion of the other.

[0031] The invention is explained below with reference to the figures of the drawings. The figures show: Fig. 1 is a schematic view of an aircraft according to an embodiment of the present invention; Fig. 2 is a schematic sectional view of a fuselage structure according to an embodiment of the present invention; Fig. 3 is a perspective view of a connector according to an embodiment of the invention; Fig. 4 is a side view of the connector from Fig. 3 , which results when viewed in a first connector transverse direction; Fig. 5 a side view of the connector from Fig. 3, which results when viewed in a second connector transverse direction; Fig. 6 a perspective view of a connector according to a further embodiment of the invention; Fig. 7 a detailed view of an intersection area of ​​a frame and a stringer of a fuselage structure according to an embodiment of the invention; Fig. 8 a sectional view of the Fig. 7 shown fuselage structure, which can be seen in a section along the Fig. 7 drawn line A8-A8; Fig. 9 shows a step of a method according to the invention for connecting a frame and a stringer of the Fig. 7 and 8 shown hull structure; Fig. 10 a further step of the method for connecting a frame and a stringer of the Fig. 7 and 8 shown fuselage structure; Fig. 11 a step of a method according to the invention for connecting a frame and a stringer of the Fig. 7 and 8shown fuselage structure; Fig. 12 a detailed view of an intersection area of ​​a frame and a stringer of a fuselage structure according to a further embodiment of the invention; Fig. 13 a sectional view of the in Fig. 12 shown fuselage structure, which can be seen in a section along the Fig. 12 drawn line A13-A13; Fig. 14 a detailed view of the Fig. 13 by the letter Z; Fig. 15 a detailed view of an intersection area of ​​a frame and a stringer of a fuselage structure according to a further embodiment of the invention; Fig. 16 a detailed view of an intersection area of ​​a frame and a stringer of a fuselage structure according to a further embodiment of the invention; Fig. 17 a sectional view of the Fig. 16 shown fuselage structure, which can be seen in a section along the Fig. 16drawn line A17-A17; Fig. 18 a detailed view of an intersection area of ​​a frame and a stringer of a fuselage structure according to a further embodiment of the invention; Fig. 19 a sectional view of the Fig. 18 shown fuselage structure, which can be seen in a section along the Fig. 18 drawn line A19-A19; Fig. 20 a detailed view of several crossing areas of a frame with stringer of a fuselage structure according to a further embodiment; Fig. 21 a sectional view of the in Fig. 20 shown fuselage structure, which can be seen in a section along the Fig. 20 drawn line A21-A21; and Fig. 22 a step of mounting a frame support on the frame of the Figs. 20 and 21 shown fuselage structure.

[0032] In the figures, the same reference symbols denote identical or functionally identical components, unless otherwise stated.

[0033] Fig. 1shows schematically a plan view of an aircraft 200. The aircraft 200 has a longitudinal fuselage axis L100 extending,

[0034] at least partially substantially cylindrical fuselage 210, from which wings 220, a vertical stabilizer 230 and a horizontal stabilizer 240 extend. The fuselage 210 has a fuselage structure 100 with several frames 110, stringers 220 and an outer skin 130. The frames 110 and stringers 120 are in Fig. 1 only symbolically represented by dashed lines. As in Fig. 1 As can be seen, several frames 110 can be provided and arranged spaced apart along the fuselage longitudinal axis L200 and parallel to one another. The stringers 120 extend transversely to the frames 110 along the fuselage longitudinal axis L100.

[0035] Fig. 2 shows schematically a sectional view of the fuselage structure 100. As in Fig. 2As shown schematically, the frames 110 each form a closed frame, which defines the fuselage cross-section or defines and encloses the fuselage longitudinal axis L100. As shown in Fig. 2 As can also be seen, the frame 110 has at least one stringer recess 115, through which a stringer 120 extends. A stringer 120 thus crosses or penetrates a frame 110 in a respective crossing region or at a crossing point. The outer skin 130 can be attached to the frames 110 and / or the stringers 120, e.g., riveted and / or glued to them.

[0036] The Figs. 7 to 19 show fragmentary views of the intersection area of ​​stringer 120 and frame 110 of fuselage structures 100, in which the frame 110 and the stringer 120 are connected by means of a connector 1. In the Figs. 3 to 6 as well as in the Figs. 7 to 19 various connectors 1 are shown. The Figs. 20 to 22show a hull structure 500 in which frame 110 and stringer 120 are not connected to each other by a connector 1 and the frame 110 is reinforced or supported by a frame support 510. Furthermore, the

[0037] Figs. 20 to 22 shown fuselage structure 500 as shown in the Figs. 1 and 2 explained.

[0038] In the Figs. 3 to 5 As an example, a connector 1 for connecting the frame 110 to the stringer 120 in the crossing area is shown. As in Figs. 3 to 5 As shown by way of example, the connector may comprise a base carrier 2, a first connecting portion 4, and a second connecting portion 6. Optionally, an adhesive carrier 7 may also be present.

[0039] The base support 2 can generally be realized as a profile support extending in a connector longitudinal direction L1. As shown in the Figs. 3 to 5As shown by way of example, the base support 2 can, for example, have a cross-shaped cross-section. In particular, the base support 2 can have a plate-shaped first web 2A and a plate-shaped second web 2B intersecting the first web 2A and extending transversely thereto, as shown in the Figs. 3 to 5 As shown in the Figs. 3 to 5 Furthermore, the first web 2A can optionally have an approximately triangular circumference. However, the second web 2B can also extend from the first web 2A transversely to it, so that a T-shaped cross section is defined, as is shown purely by way of example in Fig. 18 is shown. In general, the base support 2 extends in the connector longitudinal direction L1 and has a first end region 21 and a second end region 22 located opposite thereto with respect to the connector longitudinal direction L1.

[0040] As in the Figs. 3 to 5shown purely by way of example, the first connecting section 4 can, for example, have a crossbar 43 and a coupling structure 40. As shown in particular in Fig. 4 As can be seen, the transverse web 43 can extend in a first connector transverse direction C11 extending transversely to the connector longitudinal direction L1. A first end 43A of the transverse web 43 is connected to the base support 2, e.g., to the first web 2A of the base support 2. A second end 43B of the transverse web 43 is located away from the base support 2 with respect to the first connector transverse direction C11, in particular away from the first web 2A of the base support 2. The second web 2B of the base support 2 can, for example, also extend in the first connector transverse direction C11 and optionally be connected to the transverse web 43, as shown in Fig. 4 The crosspiece 43 can be arranged in the region of the first end region 21 of the base support 2, as shown in the Figs. 3 to 5is shown by way of example. The first end region 21 of the base support 2 can thus extend between the first end 21E of the base support 2 and the crosspiece 43. The crosspiece 43 can in particular be formed integrally with the base support 2; for example, the base support 2 and the crosspiece 43 can be produced using an additive manufacturing process, such as a 3D printing process, or a casting process.

[0041] As in the Figs. 3 to 5 As shown purely by way of example, the coupling structure 40 can have a longitudinal web 44 and, alternatively or in addition to the longitudinal web 44, a hook-shaped or U-shaped fold 44C. The coupling structure 40 is generally designed to encompass an end region of a cross section of the stringer 120, so that the stringer 120 can be held in a form-fitting manner on the first connecting section 4.

[0042] As particularly in Fig. 4As can be seen, the longitudinal web 44 can extend from the second end 43B of the transverse web 43 along the first end region 21 of the base support 2, in particular in the direction of the first end 21E of the base support 2. The longitudinal web 44 thus runs along the connector longitudinal direction L1. In particular, the transverse web 43 can extend along the first web 2A of the base support 2. Between the longitudinal web 44 and the base support 2, in particular the first web 2A of the base support 2, a receiving or clamping space is thus formed, in which the stringer 120 can be received.

[0043] The optional fold 44C can be arranged at an end 44B facing away from the transverse web 43 with respect to the connector longitudinal direction L1. Alternatively, the longitudinal web 44 can also be omitted and the fold 44C can be formed directly at the second end 43B of the transverse web 43. In general, the fold 44C is bent towards the base support 2 or towards a side facing the base support 2. The fold 44C thus defines a hook-shaped structure which is designed to encompass an end region of the cross section of the stringer 120, e.g., an end of a web of the stringer can be inserted into a receiving slot 44S defined by the fold 44C, as can be seen in particular from the Figs. 9 and 10will be explained in more detail below. In general, it can be provided that the coupling structure 40 is designed to encompass an end region of the cross section of the stringer 120 with respect to the first connector transverse direction C11 and / or with respect to the connector longitudinal direction L1.

[0044] The second connecting section 6 is used to connect to the frame 110. As shown in the Figs. 3 to 5 As shown purely by way of example, the second connecting section 6 can be arranged, for example, in the second end region 22 of the base support 2. The second connecting section 6 can, for example, be formed integrally with the base support 2, as shown in the Figs. 3 to 5 is shown as an example. Alternatively, the second connecting section 6 can also be designed as a part separate from the base support 2 and locked to it, as will be shown below with reference to the Figs. 12 to 15will be explained in more detail below. In general, the connecting section 6 is connected to the base support 2.

[0045] The one in the Figs. 3 to 5 The connector 1 shown as an example has a second connecting section 6 with a coupling structure 60, which is designed to encompass an end region of a cross section of the frame 110. As shown in particular in Fig. 5 As can be seen, the connecting section 6 can, for example, have a transverse web 66, which is connected by a first end 66A to the second end region 22 of the base support 2, in particular to the second web 2B of the base support 2. The transverse web 66 extends transversely to the base support 2, in particular to the second web 2B of the base support 2. As shown in the Figs. 3 to 5As shown by way of example, the transverse web 66 can extend in particular in a second connector transverse direction C12, which runs transversely to the connector longitudinal direction L1 and transversely to the first connector transverse direction C11. In general, the second connecting section 6 can thus be oriented in a second connector transverse direction C12.

[0046] The coupling structure 60 of the second connecting section 6 may have a hook-shaped structure 60A, as shown in particular in Fig. 5 shown by way of example. The hook-shaped structure 60A can be arranged at a second end 66B of the crosspiece 66, which is opposite to the first end 66A and thus facing away from the base support 2, as shown in Fig. 5 is shown by way of example. In general, the coupling structure 60 of the second connecting section 6 can thus be located in an end region 62 of the second connecting section 6 facing away from the base support 2. The Fig. 5The hook-shaped coupling structure 60 shown as an example can define a slot 60S which is open towards the base support 2 so that an end region of a cross section of the frame 110 can be received therein, e.g. an end of a web of the frame 110, as shown in Fig. 8 is shown as an example.

[0047] Alternatively or in addition to the hook-shaped structure 60A, the coupling structure 60 of the second connecting section 6 can also have a longitudinal web 67 extending from the second end 66B of the transverse web 66 and along the connector longitudinal direction L1 in the direction of the first end region 21 of the base support 2, as shown in the Figs. 13 and 14 is shown by way of example. Optionally, the hook-shaped structure 60A can additionally be formed at an end of the longitudinal web 67 facing away from the transverse web 66.

[0048] As in the Figs. 3 to 5As further shown, the optional adhesive carrier 7 may generally be formed as a plate with a preferably flat surface 7a. The surface 7a of the adhesive carrier 7 may be coated with an adhesive 70, as shown in Fig. 5 is shown schematically. As particularly in Fig. 5 As can be seen, the adhesive carrier 7 can be arranged, for example, between the first and second connecting sections 4, 6 with respect to the connector longitudinal direction L1. The adhesive carrier 7 is connected to the base carrier 2 and can, for example, be formed integrally therewith. As shown in Fig. 5 As can be seen, the surface 7a coated with adhesive 70 can, for example, be oriented in the second connector transverse direction C12. Generally, the surface 7a can be oriented in the same direction as the second connecting section 6.

[0049] In Fig. 6A further connector 1 is shown purely as an example. This differs from the connector 1 shown in Figures 3 to 5 only in that it additionally has an optional fastening structure 8. The optional fastening structure 8 is used for attaching additional components, such as cable holders or the like. As shown in Fig. 6 As shown by way of example, the fastening structure 8 can be realized as a plate-shaped part having one or more recesses 80, e.g. in the form of through-openings. The fastening structure 8 is connected to the base support 2 and can, for example, be formed integrally therewith. As shown in Fig. 6As shown by way of example, the fastening structure 8 can be arranged in particular between the first and the second end region 21, 22 of the base support 2, e.g. on the first web 2A and extending parallel to the second web 2B. In particular, the fastening structure 8 can be arranged opposite to the second connecting section 6 with respect to the second connector transverse direction C12, as shown in Fig. 6 is shown as an example.

[0050] Fig. 7 shows, by way of example, a detailed view of the fuselage structure 100 in the intersection area of ​​frame 110 and stringer 120 in a viewing direction along the fuselage longitudinal axis L100, wherein frame 110 and stringer 120 are connected to a connector 1, as shown in the Figs. 3 to 6 explained. Fig. 8 shows a sectional view of the Fig. 7 shown fuselage structure 100, which in a section along the Fig. 7 drawn line A8-A8.

[0051] As in Fig. 7 As shown by way of example, the stringer 120 can, for example, have a cross-section that can be described as S- or Z-shaped. The stringer 120 can, for example, have a central web 121 extending along the fuselage radial direction R100, a foot web 122, which is arranged at a first, outer end of the central web 121 with respect to the fuselage radial direction R100 and extends transversely to a first side of the central web 121, and a head web 123, which is arranged at a second, inner end of the central web 121 with respect to the fuselage radial direction R100 and extends to a second side of the central web 121, as shown in Fig. 7 shown as an example. The head web 123 can, for example, be curved so that its end facing away from the central web 121 points towards the first end of the central web 121, as in Fig. 7 shown as an example.

[0052] The frame 110 may, for example, have a C-shaped cross-section, as shown in Fig. 8 is shown by way of example. The frame 110 can, for example, have a plate-shaped central web 111, a web-shaped frame base 112 arranged at a first, outer end of the central web 111 with respect to the fuselage radial direction R100, and a web-shaped frame head 114 arranged at a second, inner end of the central web 111 with respect to the fuselage radial direction R100, wherein the frame head 114 and the frame base 112 each extend parallel to one another on a first side of the central web 111.

[0053] As in Fig. 7As shown by way of example, the first connecting section 4 of the connector 1 with the coupling structure 40 encompasses an end region of a cross section of the stringer 120. Here, the head web 123 and a part of the central web 121 of the stringer 120 are clamped between the longitudinal web 44 and the first web 2A of the base support 2. Furthermore, the end of the head web 123 facing away from the central web 121 is received in the slot 44S defined by the hook-shaped structure 44C. Thus, it can generally be provided that the coupling structure 40 encompasses the end region of the S-shaped cross section of the stringer 120 with respect to the fuselage radial direction R100.

[0054] As in Fig. 8As shown by way of example, the second connecting section 6 of the connector 1 is connected to the frame 110. For example, the transverse web 66 of the second connecting section 6 can be aligned along the fuselage longitudinal axis L100 and extend beyond the frame head 114 with respect to the fuselage radial direction R100, as shown in Fig. 8 shown as an example. The coupling structure 60 of the second connecting section 6, which in Fig. 8 purely exemplary, is realized as a hook-shaped structure 60A, encompasses an end of the frame head 114 facing away from the central web 111 or is received in the slot defined by the hook-shaped structure 60A and the transverse web 66.

[0055] As in Fig. 8 As can also be seen, the optional adhesive carrier 7 lies against a second side of the central web 111 of the frame 110 or is fixed by the adhesive layer 70 (in Fig. 8 not shown) glued to the frame 110.

[0056] As in the Fig. 7 and 8 As shown, the frame 110 and the stringer 120 can be coupled together at their intersection point by the connector 1, by positively connecting the connector to the stringer 120 and optionally also to the frame 110. This enables particularly quick and easy assembly. Figs. 9 to 11 show schematically the sequence of an efficient method for connecting a frame 110 and a stringer 120.

[0057] In a first step, for example, the end region of the cross section of the stringer 120 can be inserted into the coupling structure 40 of the first connecting section 4 of the connector 1. As in Fig. 9As shown by way of example, the insertion of the end region of the cross section of the stringer 120 into the coupling structure 40 of the first connecting section 4 can be carried out, for example, by inserting the end region of the cross section of the stringer 120, e.g. the end of the stringer head 121, between the coupling structure 40 and the first end region 21 of the base support 2. Subsequently, a

[0058] Swiveling of the connector 1 or the base support 2 over the stringer 120. In Fig. 9 This is symbolically indicated by the arrow P9, whereby the second end region 22 of the base support 2 is pivoted from the second side of the stringer 120 towards the first side of the stringer 120 until it reaches the Fig. 10 shown position is reached, in which the coupling structure 40 completely encompasses the end region of the cross section of the stringer 120.

[0059] Furthermore, the second connecting section 6 of the connector 1 is positioned on the frame 110, e.g. by moving the connector 1 along the stringer 120 in the direction of the frame 110 or by moving the stringer 120 along the fuselage longitudinal axis L100 such that the connector 1 is brought closer to the frame 110.

[0060] In a further step, the second connecting section 6 of the connector 1 is connected to the frame 110. If the second connecting section 6 has a hook structure 60A as a coupling structure 60, as shown in the Figures 9 to 11 As shown by way of example, in order to connect the second connecting section 6 to the frame 110, the crosspiece 66 of the second connecting section 6 can be elastically deformed such that the second end 66B of the crosspiece 66 is raised in the connector longitudinal direction L1, as shown in Fig. 11As an example, the hook structure 66A can be pushed along the fuselage longitudinal axis L100 over the frame head 114, as shown in Fig. 11 symbolically indicated by the arrow P11, until the end of the frame head 114 facing away from the central web 111 engages in the hook structure 66A ( Fig. 8 ). In other designs of the second connecting portion 6, the connection of the second connecting portion 6 of the connector 1 to the frame 110 may comprise riveting, screwing, gluing, or welding the second connecting portion 6 to the frame 110.

[0061] Fig. 12 shows, by way of example, a detailed view of a further fuselage structure 100 in the intersection area of ​​frame 110 and stringer 120 in a viewing direction along the fuselage longitudinal axis L100, wherein frame 110 and stringer 120 are connected with a connector 1. Fig. 13 shows a sectional view of the Fig. 12shown fuselage structure 100, which in a section along the Fig. 12 drawn line A13-A13. Fig. 14 shows a detailed view of the Fig. 13 area marked with the letter Z

[0062] As particularly in the Figs. 13 and 14 As can be seen, connector 1 differs from the one shown in the Figs. 3 to 6 shown connector only by the design of the second connecting section 6. This is shown in the Figs. 12 to 14 not formed integrally with the base support 2, but guided along the connector longitudinal direction L1 displaceably on the base support 2. The second connecting section 6 can in particular have a guide region 63, which can be formed, for example, by a substantially plate-shaped guide web 68, as shown in the Figs. 13 and 14shown as an example. A locking or latching structure 63A can optionally be formed on the guide area 63, e.g. in the form of teeth as shown in the Figs. 13 and 14 shown schematically. As particularly in Fig. 14 As further shown, the guide portion 63 may extend from the first end 66A of the crosspiece 66 of the second connecting portion 6 and transversely to the crosspiece 66. In the Figs. 13 and 14 It is shown by way of example that the coupling structure 60 of the second connecting section 6 has a longitudinal web 67 extending from the second end 66B of the transverse web 66 and along the connector longitudinal direction L1 in the direction of the first end region 21 of the base support 2. Alternatively or additionally, a hook-shaped structure 60A could also be provided, as in the Figs. 3 to 6 shown.

[0063] In order to guide the connecting section 6 along the connector longitudinal direction L1, the base support 2 can have a guide 28. As shown in the Figs. 13 and 14 As shown by way of example, the guide 28 can be formed, for example, by a flat end section of the second web 2B of the base support 2, located in the second end section 22 of the base support 2, and a guide web 29, which extends parallel to the end section of the second web 2B of the base support 2. Thus, the end section of the second web 2B of the base support 2 and the guide web 29 form a guide channel, in which the guide section 63 of the second connecting section 6 is received and guided. For example, the web 68 forming the guide section 63 can be arranged between the end section of the second web 2B of the base support 2 and the guide web 29, as shown in the Figs. 13 and 14 is shown as an example.

[0064] The guide 28 of the base support 2 may optionally have a first locking structure 28A. As shown in the Figs. 13 and 14As shown by way of example, the first locking structure 28A can be formed, for example, by an elastic web or projection projecting into the guide channel or from the end section of the second web 2B of the base support 2. The first locking structure 28A engages in the locking structure 63A of the guide region 63 of the second connecting section 6 and thus locks it in a position with respect to the connector longitudinal direction L1. The teeth of the locking structure 63A of the guide region 63 of the second connecting section 6 can in particular be shaped in such a way, and the first locking structure 28A of the base support 2 can in particular be elastically deformable in such a way that it allows a displacement of the guide region 63 of the second connecting section 6 in one direction, e.g. in the direction of the first end region 21 of the base support 2, and blocks it in an opposite direction.

[0065] To connect the connector 1 to the frame 110, the second connecting section 6 can, for example, be subsequently locked to the base support 2 when the base support 2 is already attached to the stringer 120 and positioned relative to the frame 110, e.g. by inserting the guide area 63 into the guide 28 of the base support 2 and moving the second connecting section 6, guided by the guide 28, in the direction of the first end area 21 of the base support 2, so that the frame 110 is inserted between the longitudinal web 67 and the guide area 63.

[0066] Another difference between the Figs. 12 to 14 shown fuselage structure 100 to that shown in the Fig. 7 and 8 shown fuselage structure 100 lies in the design of the frame 110. As shown in the Fig. 12 and 13As shown, the frame 110 may be connected to an edge piece 116 which is L-shaped in cross section. The frame 110 may, for example, have an S- or Z-shaped cross section, in which the frame foot 112 and the frame head 114 protrude to opposite sides from the central web 111 of the frame 110. As shown in Fig. 13 As shown by way of example, the frame head 114 can be bent substantially L-shaped or parallel to the central web 111. The edge piece 116 and the frame head 114 can in particular be arranged on the same side of the central web 111, wherein the edge piece 116 is bent to form the L-shaped cross section towards the same side on which the frame head 114 protrudes from the central web 111.

[0067] As in the Fig. 12 and 13As shown by way of example, the connector 1 can be arranged on the same side of the frame 110 to which the frame head 114 protrudes from the central web 111. An advantage of this design lies in the particularly compact arrangement of the connector 1. Alternatively, the connector 1 can also be arranged on the opposite side of the frame 110 to which the frame head 114 protrudes from the central web 111, as shown in Fig. 15 is shown by way of example. In this case, the base support 2 can be curved or offset in order to bridge the frame foot 112. An advantage of this arrangement is that the first connecting section 4, which is connected to the stringer 120, is arranged at a certain distance from the frame 110. This further improves the supporting effect of the connector 1 against tilting of the frame 110. As shown in Fig. 15As further shown, the guide 28 of the base support 2 can also have two parallel guide webs 29 that define the guide channel. This applies regardless of the design of the frame 110 or the base support 2.

[0068] Fig. 16 shows, by way of example, a detailed view of a further fuselage structure 100 in the intersection area of ​​frame 110 and stringer 120 in a viewing direction along the fuselage longitudinal axis L100, wherein frame 110 and stringer 120 are connected with a connector 1. Fig. 17 shows a sectional view of the Fig. 16 shown fuselage structure 100, which in a section along the Fig. 16 drawn line A17-A17. In the Figs. 16 and 17 the frame 110 is as in the Figs. 12 to 14 S- or Z-shaped and realized with an edge piece 116.

[0069] The Figs. 16 and 17 The fuselage structure 100 shown differs from that shown in the Figs. 12 to 14shown fuselage structure 100 merely by the design of the connector 1 and the attachment of the second connecting portion 6 of the connector 1 to the frame. The design of the connector 1 described below can be realized independently of the design of the frame 110 and is not limited to the combination with a Z-shaped frame 110 with an edge piece 116.

[0070] As in the Figs. 16 and 17As shown by way of example, the second connecting section 6 of the connector 1 can be implemented in a plate-shaped manner, e.g. in the form of a flange 60B. In particular, the connecting section 6 can have a contact surface 60c, which is designed to bear against the frame 110. The contact surface 60c can in particular be flat. The flange 60B can, for example, extend along the first connector transverse direction C11. This means that the contact surface 60c, which can be provided on the flange 60B, is oriented in the second connector transverse direction C12, or a normal vector to the contact surface 60c points in the second connector transverse direction C12. The second connecting section 6 can thus generally be oriented in a second connector transverse direction C12. As shown in the Figs. 16 and 17As further shown by way of example, the flange 60B can be arranged in a second end region 22 of the base support 2 with respect to the connector longitudinal direction L1. For example, the flange 60B can be arranged at one end of the first web 2A of the base support 2 and extend transversely thereto, as shown in the Figs. 16 and 17 is shown as an example.

[0071] As in the Figs. 16 and 17 As shown by way of example, the flange 60B can be connected to the central web 111 of the frame 110. In particular, the contact surface 60c can bear against the central web 111 of the frame 110. In Fig. 16 It is shown purely by way of example that the flange 60B is fastened to the central web 111 of the frame 110 by means of rivets, the rivets being represented merely symbolically by crosses 150. In principle, other connection options are also conceivable, e.g., gluing, welding, screwing, or the like.

[0072] Fig. 18shows, by way of example, a detailed view of a further fuselage structure 100 in the intersection area of ​​frame 110 and stringer 120 in a viewing direction along the fuselage longitudinal axis L100, wherein frame 110 and stringer 120 are connected with a connector 1. Fig. 19 shows a sectional view of the Fig. 18 shown fuselage structure 100, which in a section along the Fig. 18 drawn line A19-A19. In the Figs. 18 and 19 the frame 110 is as in the Figs. 12 to 17 S- or Z-shaped and realized with an edge piece 116.

[0073] The Figs. 18 and 19 The fuselage structure 100 shown differs from that shown in the Figs. 16 and 17 shown fuselage structure 100 only by the design of the connector 1, in particular by the orientation of the plate-shaped second connecting section 6, and by the design of the edge piece 116 in the region of the stringer recess 115.

[0074] As in the Figs. 18 and 19As shown by way of example, the edge piece 116 may have an interruption defining the stringer recess 115. Adjacent to this interruption, the edge piece 116 may have a connecting strap 117 extending along the fuselage longitudinal axis L100 or transversely to the central web 111 of the frame 110 and along the stringer 120. As shown in Fig. 19 As shown by way of example, the connecting tab 117 can be bent from one end of the edge piece 116 and, for example, have a triangular circumference.

[0075] As in Fig. 18 As shown by way of example, the base support 2 of the connector 1 can have the first web 2A and the second web 2B, wherein the first and second webs 2A, 2B define a T-shaped cross section of the base support 2. The first connecting section 4 can be as shown in the Figs. 3 to 6described. The first connecting section 4 is thus oriented in the first connector transverse direction C11, or the transverse web 43 of the first connecting section 4 protrudes to a first side from the first web 2A of the base support 2. The second connecting section 6 is plate-shaped and can be realized, for example, by a second side of the first web 2A of the base support 2, on which the contact surface 60c is provided for contact with the frame 110. Thus, the second connecting section 6 can be oriented in the first connector transverse direction C11.

[0076] As in Fig. 18 As can be seen, the contact surface 60c of the plate-shaped second connecting section 6 provided on the first web 2A of the base support 2 can rest against the tab 117 of the edge piece 116. The second connecting section 6 and the tab 117 of the edge piece 116 can be connected, for example, by rivets 150, as shown in the Figs. 18 and 19is shown by way of example. Of course, it is also conceivable that the tab 117 and the second connecting section 6 are welded, glued, screwed or connected in a similar manner.

[0077] Fig. 20 shows, by way of example, a detailed view of a further fuselage structure 500 in the intersection area of ​​frame 110 and stringer 120 in a viewing direction along the fuselage longitudinal axis L100, wherein frame 110 and stringer 120 are connected with a connector 1. Fig. 21 shows a sectional view of the Fig. 20 shown fuselage structure 500, which can be seen in a section along the Fig. 20 drawn line A21-A21.

[0078] As in the Figs. 20 and 21 As shown by way of example, the fuselage structure 500 may include a frame 110, a stringer 115, an outer skin 130 and a frame support 510.

[0079] The Figs. 20 and 21 The fuselage structure 500 shown basically has the Fig. 2explained structure. In Fig. 2 A Z- or S-shaped stringer 120 is shown as an example. In contrast to this, in the Figs. 20 and 21 a stringer 120 with Ω-shaped cross-section is shown.

[0080] As in Fig. 21 As shown by way of example, the frame 110 can, for example, have a C-shaped cross-section. The frame 110 can, in particular, have a plate-shaped central web 111, a web-shaped frame base 112 arranged at a first, outer end of the central web 111 with respect to the fuselage radial direction R100, and a web-shaped frame head 114 arranged at a second, inner end of the central web 111 with respect to the fuselage radial direction R100, wherein the frame head 114 and the frame base 112 each extend parallel to one another on a first side of the central web 111. The stringer recess 114 is formed in the region of the frame base 112. As shown in the Figs. 20 and 21As shown by way of example, the stringer 120 extends through the stringer recess 115 along the fuselage longitudinal axis L100.

[0081] As in the Figs. 20 and 21 As further shown, the flat outer skin 130 is attached to the frame foot 112 of the frame 110 and the stringer 120.

[0082] The structure of the frame support 510 is particularly Fig. 22 recognizable. As in Fig. 22 As shown by way of example, the frame support 510 may in particular comprise a support foot 512, a support beam 520, a connecting section 530 and one or more optional support plates 540.

[0083] As in Fig. 22 As shown by way of example, the support foot 512 can be realized, for example, as a plate-shaped component which has a flat first section 512A and a second section 512B.

[0084] As in Fig. 22As shown, the support beam 520 extends from the second portion 512B of the support foot 512 and transversely to the first portion 512A of the support foot 512. The support beam 520 may generally be implemented as a profile beam. As shown in Fig. 22 As shown purely by way of example, the support bracket 520 can, for example, have a first web 521 and a second web 522 extending transversely to and penetrating the first web 521, wherein the first and second webs 521, 522 define an X-shaped or cross-shaped cross section of the support bracket 520. However, it is also conceivable for the support bracket 520 to have a different cross-sectional shape, e.g., a T-shaped or an H-shaped cross section. The support bracket 520 and the support foot 512 can, in particular, be formed as a single piece.

[0085] The connecting section 530 can, for example, be arranged in an end region 524 of the support beam 520 facing away from the support plate 512, as shown in Fig. 22is shown by way of example. The connecting section 530 has a coupling structure 534, which is designed to encompass an end region of a cross section of the frame head 114. The connecting section 530 can, for example, be formed integrally with the support beam 520, as shown in Fig. 22 is shown as an example. Alternatively, the connecting section 530 can also be designed as a part separate from the support beam 520 and locked to it, for example as shown in the Figs. 12 to 15 explained in detail. Generally, the connecting portion 530 is connected to the support beam 520.

[0086] As in Fig. 22As shown by way of example, the connecting section 530 can, for example, have a transverse web 536, which is connected with a first end to the end region 524 of the support beam 520, in particular to the first web 521 of the support beam 520. The transverse web 536 extends transversely to the support beam 520, in particular to the first web 521 of the support beam 520. As in Fig. 22 As shown by way of example, the transverse web 536 can in particular extend parallel to the support foot 512 and be arranged opposite the first section 512A of the support foot 512.

[0087] The coupling structure 534 of the connecting portion 530 may, for example, have a hook-shaped structure, as shown in Fig. 22 is shown by way of example. The hook-shaped structure can be arranged on a region of the crossbar 536 facing away from the support beam 520. The Fig. 22The hook-shaped coupling structure 534 shown as an example can define a slot 538 which is open towards the support beam 520 so that an end region of a cross-section of the frame 110 can be received therein, e.g. an end of the web-shaped frame head 114, as shown in Fig. 21 is shown as an example.

[0088] Alternatively or in addition to the hook-shaped structure, the coupling structure 5340 of the connecting portion 530 may also have a longitudinal web (not shown) extending from the end of the transverse web 536 and along the support beam 520 in the direction of the support plate 512, similar to the longitudinal web shown in the Figs. 13 and 14 exemplary design of the second connecting region 6. Optionally, the hook-shaped structure can additionally be formed at an end of the longitudinal web facing away from the transverse web 536.

[0089] The Fig. 22The frame support 510 shown as an example is provided with two optional support plates 540. Of course, only one support plate 540 or more than two support plates 540 can be provided. The support plate 540 has a flat support surface 540a, which can optionally be coated with an adhesive layer (not shown). The support surface 540a extends transversely to the support plate 512. As in Fig. 22 As shown by way of example, a first contact plate 540 can be arranged in a first end region 523 of the support bracket 520 located on the support plate 512, and a second support plate 540 can be arranged in the second end region 524 of the support bracket 520 located remote from the support plate 512. In general, the support plate 540 can be arranged between the support foot 512 and the connecting portion 530. The support plate 540 can, for example, be formed integrally with the support bracket 520 and is generally connected thereto.

[0090] As in Fig. 21 As shown by way of example, the support leg 512 may be partially disposed between the outer skin 130 and the frame foot 112. In particular, the first portion 512A of the support leg 512 may be disposed between the outer skin 130 and the frame foot 112. As shown in Fig. 21 As further shown, the end of the web-shaped frame head 114 is arranged in the slot 538 of the hook-shaped coupling structure 534 of the connecting portion 530. Thus, the coupling structure 534 encompasses an end region of a cross section of the frame head 114.

[0091] Fig. 22schematically shows the assembly of the frame support 510 to the frame 110. First, the frame support 510 is arranged on the second side of the frame, which is opposite the first side of the central web 111 of the frame 110, from which the frame foot 112 and the frame head 114 protrude. The frame support 510 is oriented such that the first section 512A of the frame foot 512, the connecting section 530, and the optional support plates 540 face the frame 110. As symbolically indicated by the arrow P22, the frame support 510 is moved in the direction of the frame 510, wherein the first section 512A of the support foot 512 is pushed overlapping over the frame foot 112 and the connecting section 530 is pushed overlapping over the frame head 114 until the hook-shaped coupling structure 534 is locked to the end of the frame head 114 and the optional support plates rest against the central web 111 of the frame 110, as shown in Fig. 21 is shown as an example.

[0092] Although the present invention has been explained above by way of example using exemplary embodiments, it is not limited thereto but can be modified in many ways. LIST OF REFERENCE SYMBOLS

[0093] 1Connector 2Base support 4First connection section 6Second connection section 7Adhesive support 7aSurface of the adhesive support 8Fastening structure 21First end region of the base support 21EFirst end of the base support 22Second end region of the base support 28Guide 28ALocking structure 29Guide web 40Coupling structure of the first connecting section 42End region of the first connecting section 43Cross web of the first connecting section 43AFirst end of the cross web 43BSecond end of the cross web 44Longitudinal web of the first connecting section 44BEnd of the cross web 44CUmbug 44SGap 60Coupling structure of the second connecting section 60AHook-shaped structure 60BFlange 60CContact surface 62End region of the second connecting section 63Guide region 63ALocking structure 66Cross web of the second connecting section 66AFirst end of the cross web 66BSecond end of the cross web 67Longitudinal web of the second Connecting section 68Guide web 70Adhesive layer 80Recesses 100Fuselage structure 110 Frame 111 Central web of the frame 112 Frame base 114 Frame head 115 Stringer recess 116 Edge piece 117 Tab 120 Stringer 121 Central web 122 Foot web 123 Head web 130 Outer skin 150 Rivets 200Aircraft 210Fuselage 220Wing 230Vertical stabilizer 240Horse tail 500 Hull structure 510 Frame support 512 Support foot 512A First section of the support foot 512B Second section of the support foot 520 Support beam 530 Connecting section 532 End section 534 Coupling structure 536 Cross web 538 Slot C11First connector transverse direction C12Second connector transverse direction L1Connector longitudinal direction L100Fuselage longitudinal axis P9Arrow P11Arrow P22Arrow R100Fuselage radial direction

Claims

1. A connector (1) for connecting a frame (110) to a stringer (120), extending transversely thereto, of a fuselage structure (100) of an aircraft (200), comprising: a base beam (2) extending in a connector longitudinal direction (L1); a first connecting portion (4) connected to the base beam (2) and extending in a first connector transverse direction (C11), which first connecting portion has, in an end region (42) facing away from the base beam (2), a coupling structure (40) for engaging around an end region of a cross section of the stringer (120); and a second connecting portion (6) connected to the base beam (2), which second connecting portion is designed for connection to the frame (110); wherein the second connecting portion (6) is oriented in a second connector transverse direction (C12); and wherein the second connecting portion (6) is arranged in a second end region (22) of the base beam (2) with respect to the connector longitudinal direction (L1) and extends in the second connector transverse direction (C12), and wherein the second connecting portion (6) has, in an end region (62) facing away from the base beam (2), a coupling structure (60) for engaging around an end region of a cross section of the frame (110).

2. The connector (1) according to claim 1, wherein the second connecting portion (6) is formed integrally with the base beam (2).

3. The connector (1) according to claim 1, wherein the second connecting portion (6) has a guide region (63) which is guided displaceably in a guide (28) of the base beam (2) in the connector longitudinal direction (L1), and wherein the guide (28) has a first locking structure (28A), in particular an elastic web, which engages into a locking structure (63A), in particular in the form of teeth, formed in the guide region (63).

4. The connector (1) according to any one of claims 1 to 3, additionally comprising: a plate-shaped adhesive carrier (7) having a surface (7a) oriented in the second connector transverse direction (C12), which surface is coated with an adhesive (70); wherein the adhesive carrier (7) is arranged between the first and the second connecting portion (4; 6) with respect to the connector longitudinal direction (L1) and is connected to the base beam (2).

5. The connector (1) according to claim 1, wherein the second connecting portion (6) is formed in a plate-shaped manner for bearing against a plate-shaped region of the frame (110).

6. The connector (1) according to claim 5, wherein the second connecting portion (6) is arranged in a second end region (22) of the base beam (2) with respect to the connector longitudinal direction (L1).

7. The connector (1) according to any one of the preceding claims, wherein the first connecting portion (4) has a transverse web (43) extending in the first connector transverse direction (C11), which transverse web is connected to the base beam (2) by a first end (43A), wherein the coupling structure (40) has a longitudinal web (44) extending from a second end (43B) of the transverse web (43) along a first end region (21) of the base beam (2), which longitudinal web has a U-shaped bend (44C) on a side facing the base beam (2) at an end (44B) located facing away from the transverse web (43).

8. A fuselage structure (100) for an aircraft (200), comprising an, in particular annular, frame (110) enclosing a fuselage longitudinal axis (L100), which frame has a stringer recess (115); a stringer (120) extending along the fuselage longitudinal axis (L100) through the stringer recess (115) of the frame (110); and a connector (1) according to any one of the preceding claims; wherein the first connecting portion (4) of the connector (1) engages with the coupling structure (40) around an end region of a cross section of the stringer (120); and wherein the second connecting portion (6) of the connector (1) is connected to the frame (110).

9. The fuselage structure (100) according to claim 8, wherein the stringer (120) has an S-shaped cross section, and wherein the coupling structure (40) engages around the end region of the S-shaped cross section of the stringer (120) with respect to a fuselage radial direction (R100) perpendicular to the fuselage longitudinal axis (L100).

10. A method for connecting a frame (110) and a stringer (120) of a fuselage structure (100) according to any one of claims 8 or 9, comprising: introducing the end region of the cross section of the stringer (120) into the coupling structure (40) of the first connecting portion (4) of the connector (1); positioning the second connecting portion (6) of the connector (1) on the frame (110); and connecting the second connecting portion (6) of the connector (1) to the frame (110).

11. An aircraft (200) comprising a fuselage structure (100; 500) according to any one of claims 8 to 9.