Butt joint structure of aircraft fuselage and aircraft fuselage comprising same
By employing a combination structure of multiple stringer joints and docking frames between aircraft fuselage sections, the problems of precision and load transfer efficiency in the docking of metal and composite material fuselage sections were solved, achieving efficient load transfer and structural strength matching.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- COMMERCIAL AIRCRAFT CORP OF CHINA LTD
- Filing Date
- 2025-05-20
- Publication Date
- 2026-04-17
AI Technical Summary
How to achieve high-precision docking between metal fuselage sections and composite material fuselage sections, and improve load transfer efficiency, while considering the matching requirements of the differences in thermal expansion coefficients and elastic moduli of the two materials.
The structure employs a combination of multiple first stringer joints and second stringer joints, combined with docking frames and docking strips. The metal and composite material fuselage stringers are connected by fasteners to ensure longitudinal axis alignment. 7000 series aluminum alloy and titanium alloy materials are used to match the difference in thermal expansion coefficients, reducing structural weight and improving load transfer efficiency.
It achieves high-precision docking between metal fuselage sections and composite material fuselage sections, uniform load distribution, improves load transfer efficiency and structural fatigue characteristics, and reduces stress concentration.
Smart Images
Figure CN224131293U_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of aircraft design, specifically to the structural design of the fuselage of a civil aircraft, and in particular the docking structure between the various sections of the fuselage. Background Technology
[0002] For aircraft such as civil aircraft, due to requirements and limitations in structure, manufacturing process, manufacturing division of labor, and maintenance, the aircraft fuselage usually needs to be divided into several sections. These sections are manufactured separately and then joined together to form a complete fuselage. The joint structure between the various sections of the aircraft fuselage is an important assembly and separation surface and load transfer area in the fuselage structure, and it is also the part of the aircraft fuselage that is more prone to damage than other parts.
[0003] With the development of composite material technology, composite materials are increasingly being used in aircraft fuselage structures. Consequently, depending on the fuselage materials, the connection scenarios between fuselage sections include docking between metal fuselage sections, between composite material fuselage sections, and between metal and composite material fuselage sections. In aircraft currently in operation, the primary scenarios involve docking between metal fuselage sections and between composite material fuselage sections.
[0004] In aircraft design, achieving the connection between metal fuselage sections and composite fuselage sections is a pressing issue. The connection between these sections is influenced by several factors: First, metal fuselage stringers typically have a "Z"-shaped or similar cross-sectional shape, with only one contact surface, while composite fuselage stringers usually have an "Ω"-shaped or similar cross-sectional shape, with two contact surfaces. Connecting these two different cross-sectional shapes presents a challenge to the design of the connection structure. Second, there is a significant difference in the coefficient of thermal expansion and modulus of elasticity between metal and composite materials. Therefore, the design of the connection structure must meet the matching requirements of the differences in thermal stress and stiffness between the metal and composite fuselage sections.
[0005] Therefore, in the field of aircraft design, there is a need for a docking structure for aircraft fuselage that can achieve docking between metal fuselage sections and composite material fuselage sections with high assembly precision and load transfer efficiency. Utility Model Content
[0006] This application is made to solve the technical problems existing in the prior art. The purpose of this application is to provide a docking structure for an aircraft fuselage that can achieve docking between metal fuselage sections and composite material fuselage sections with high precision, and enable the docked aircraft fuselage to have high load transfer efficiency.
[0007] This application provides a docking structure for an aircraft fuselage, wherein the aircraft fuselage includes a metal fuselage section and a composite material fuselage section. The docking structure includes: a plurality of first stringer joints for connecting to the metal fuselage stringers of the metal fuselage section; and a plurality of second stringer joints for connecting to the composite material fuselage stringers of the composite material fuselage section. The docking structure further includes: a docking frame, comprising a docking frame web, with a first outer edge strip and a second outer edge strip disposed at the bottom of the docking frame web, the first and second outer edge strips respectively located on opposite sides of the docking frame web, and a docking strip plate, the docking frame and the docking strip plate being fixedly connected together. The first stringer joints are fixedly connected to one of the first and second outer edge strips, and the second stringer joints are fixedly connected to the other of the first and second outer edge strips. Each first stringer joint connects to a corresponding metal fuselage stringer on the metal fuselage section, and the second stringer joints are arranged in pairs, with each pair of second stringer joints connecting to a corresponding composite material fuselage stringer on the composite material fuselage section. Each pair of second stringer joints is positioned on both sides relative to the corresponding first stringer joint, and the first stringer joints and the corresponding pair of second stringer joints are configured such that the longitudinal axis of each metal fuselage stringer is aligned with the longitudinal axis of the corresponding composite fuselage stringer.
[0008] The aforementioned docking structure, with joints for the metal fuselage stringers and joints for the composite material fuselage stringers arranged in a one-to-two configuration, allows operators to easily align the longitudinal axes of the metal and composite fuselage stringers. This facilitates precise docking between fuselage sections made of two different materials, preventing eccentricity in the overall force transmission path of the aircraft fuselage. Furthermore, the force transmission path between these docked fuselage sections can be shorter, resulting in more even load distribution, improved load transfer efficiency, and minimized additional stress. Additionally, the paired second stringer joints are preferably arranged symmetrically with respect to their corresponding first stringer joints, further enhancing load transfer efficiency.
[0009] In one specific structure, the first stringer joint includes: a first joint portion connected to the docking frame and having a "T"-shaped cross-section; and a second joint portion for connecting to the metal fuselage stringer and having an "L"-shaped cross-section.
[0010] The first stringer joint may preferably further include: a first thinning region formed on the first joint portion, which mates with one of the first outer edge strip and the second outer edge strip when the first stringer joint is installed on the mating frame; and / or a second thinning region formed on the second joint portion, the second thinning region being used for connection with the metal fuselage stringer.
[0011] For the second stringer joint, one specific structure has an "L"-shaped cross-section, and the second stringer joint includes: a third thinning region that mates with another of the first and second outer edge strips when the second stringer joint is installed on the mating frame; and / or a fourth thinning region for connection with the composite fuselage stringer.
[0012] One specific structure of the docking strip includes: a first width reduction portion formed in the portion of the docking strip between two adjacent first stringer joints; and / or a second width reduction portion formed in the portion between two adjacent pairs of second stringer joints.
[0013] The “T” and “L” shaped designs of the first and second stringer joints, along with the thickness reduction treatment, can reduce the overall structural weight of the docking structure. At the same time, the use of the first and second outer edge strips of the docking frame as force transmission paths can improve the load transfer capacity, efficiency, and fatigue characteristics of the docking structure, thereby meeting the requirements for higher load transfer.
[0014] Preferably, the docking frame is provided with multiple reinforcing ribs, which are connected to the web of the docking frame and extend from at least one of the first and second outer edge ribs toward the top of the web of the docking frame. By providing reinforcing ribs, the web of the docking frame can be made thinner, thereby reducing the overall weight of the docking structure while ensuring the structural strength of the docking frame.
[0015] The docking frame and the first stringer joint are made of 7000 series aluminum alloy. Additionally, the docking strip and the second stringer joint are made of titanium alloy. This material combination provides good thermal compatibility, accommodating the differences in thermal performance between metal and composite fuselage sections due to variations in their coefficients of thermal expansion.
[0016] Preferably, the docking structure further includes a plurality of fasteners for achieving at least one of the following connections: connection between the docking frame and the docking strip plate; connection between the first stringer joint and one of the first and second outer edge strips; connection between the first stringer joint and the metal fuselage stringer; connection between the second stringer joint and the other of the first and second outer edge strips; connection between the second stringer joint and the composite fuselage stringer; connection between the docking strip plate and the skin of the metal fuselage section; and connection between the docking strip plate and the skin of the composite fuselage section.
[0017] Preferably, the fasteners described above are co-riveting fasteners to achieve a reliable and repeatable fixed connection.
[0018] This application also relates to an aircraft fuselage, which includes a metal fuselage section and a composite material fuselage section. The aircraft fuselage includes the docking structure described above for docking the metal fuselage section and the composite material fuselage section. Attached Figure Description
[0019] The preferred embodiments of this utility model are shown in the accompanying drawings. The specific implementation of this utility model can be more clearly understood from the drawings, in which:
[0020] Figure 1 A schematic top view of the overall structure of the docking structure of this application is shown.
[0021] Figure 2 It shows Figure 1 A partial 3D view of the docking frame in the docking structure.
[0022] Figure 3 It shows Figure 1 A three-dimensional view of the first long stringer joint in the docking structure.
[0023] Figure 4 It shows Figure 1 A three-dimensional view of the second stringer joint in the docking structure.
[0024] Figure 5 The use is illustrated schematically. Figure 1 A top view showing the docking structure used to connect the metal fuselage section and the composite fuselage section.
[0025] (Symbol Explanation)
[0026] 11 Metal fuselage sections
[0027] 12 Composite material fuselage sections
[0028] 13 Metal fuselage stringers
[0029] 14 Composite material fuselage stringers
[0030] 100 docking structure
[0031] 110 docking frame
[0032] 111 docking frame web
[0033] 112 First outer edge bar
[0034] 113 Second outer edge strip
[0035] 114 top bar
[0036] 115 Reinforcing Ribs
[0037] 120 mating plate
[0038] 121 First width reduction section
[0039] 122 Second width reduction section
[0040] 130 First Long Truss Joint
[0041] 131 First Connector Section
[0042] 132 Second Connector Section
[0043] 133 First Thinning Zone
[0044] 134 Second Thinning Zone
[0045] 140 Second Long Truss Joint
[0046] 141 Third thinning zone
[0047] 142 Fourth thinning zone
[0048] 150 Fasteners Detailed Implementation
[0049] The specific embodiments of this application will now be described in detail with reference to the accompanying drawings. It should be understood that the embodiments shown in the drawings are merely preferred embodiments of this application and do not constitute a limitation on the scope of this application. Those skilled in the art can make various obvious modifications, variations, and equivalent substitutions to this application based on the embodiments shown in the drawings. Furthermore, without contradiction, the technical features in the different embodiments described below can be arbitrarily combined with each other, all of which fall within the protection scope of this application.
[0050] The terms "top," "bottom," "upper," and "lower" used in this document to indicate direction and orientation are based on the directions and orientations shown in the figures, and are not intended to limit the direction and orientation of the disclosed structures and components in their operational state. Those skilled in the art will understand that the orientation of the structures and components involved may vary depending on the actual operational state.
[0051] Figure 1 A top view of the docking structure 100 for connecting various fuselage sections of an aircraft fuselage, as described in this application, is shown. Figure 1As shown, the docking structure 100 includes a docking frame 110 and a docking strip 120, which are fixedly connected together by fasteners 150 such as screws. The docking structure 100 also includes a plurality of first stringer joints 130 and a plurality of second stringer joints 140, wherein the first stringer joints 130 are disposed on one side of the docking structure 100, and the second stringer joints 140 are disposed on the other side of the docking structure 100 opposite to the first stringer joints 130.
[0052] Specifically, the first stringer joint 130 is used to connect the metal fuselage stringers 13 of the metal fuselage section 11, with each first stringer joint 130 connected to a corresponding metal fuselage stringer 13. The second stringer joint 140 is used to connect the composite material fuselage stringers 14 of the composite material fuselage section 12, and the second stringer joints 140 are arranged in pairs, with each pair of second stringer joints 140 connected to a corresponding composite material fuselage stringer 14. Specific connection methods will be described below. Figure 5 Detailed description.
[0053] Figure 2 A partially enlarged structural view of the docking frame 110 is shown. The docking frame 110 includes a docking frame web 111, which has a generally "J"-shaped cross-section. A first outer edge strip 112 and a second outer edge strip 113 are provided at the bottom of the docking frame web 111, respectively located on both sides of the docking frame web 111. Preferably, the first outer edge strip 112 and the second outer edge strip 113 are formed approximately symmetrically with respect to the docking frame web 111. The first outer edge strip 112 and the second outer edge strip 113 can be connected to the docking strip plate 120 by a plurality of fasteners 150, thereby achieving a fixed connection between the docking frame 110 and the docking strip plate 120.
[0054] Additionally, the first stringer joint 130 is fixedly connected to one side of the first outer edge strip 112 and the second outer edge strip 113, while the second stringer joint 140 is fixedly connected to the other side of the first outer edge strip 112 and the second outer edge strip 113. The connection between the first stringer joint 130 and the second stringer joint 140 and the first outer edge strip 112 and the second outer edge strip 113 can also be achieved by multiple fasteners 150.
[0055] Preferably, the mating frame 110 also includes multiple reinforcing ribs 115. Figure 2The diagram shows a reinforcing rib 115 formed on one side of the first outer edge strip 112. The reinforcing rib 115 is connected to the web of the mating frame 111 and extends upward from the first outer edge strip 112 to the top strip 114 of the web of the mating frame 111, and has a width in the direction from the outside to the inside of the mating frame 110. In an alternative structure, the reinforcing rib 115 may also extend a portion of the distance from the first outer edge strip 112 to the top strip 114, without having to extend it completely from the first outer edge strip 112 to the top strip 114, which is also within the scope of this application.
[0056] By incorporating reinforcing ribs 115, the overall strength of the docking frame 110 can be improved. This allows for a thinner web 111 on the docking frame, reducing its overall weight while maintaining its structural strength.
[0057] As an additional or alternative structure, a reinforcing rib 115 may also be formed on one side of the second outer edge strip 113. In other words, the reinforcing rib 115 may be provided at at least one of the first outer edge strip 112 and the second outer edge strip 113, all of which are within the scope of this application.
[0058] The mating frame 110 may be made of aluminum alloy, such as 7000 series aluminum alloy. More preferably, the mating frame 110 is manufactured by machining a single piece of aluminum alloy.
[0059] Figure 3 A schematic structural perspective view of the first stringer joint 130 is shown. The first stringer joint 130 includes a first joint portion 131 at one end and a second joint portion 132 at the opposite end. Preferably, the first stringer joint 130 is a combined-shape component, with its first joint portion 131 connected to the docking frame 110 and having a "T"-shaped cross-section, and the second joint portion 132 for connecting the metal fuselage stringer 13 of the metal fuselage section 11, having an "L"-shaped cross-section. The connection between the first stringer joint 130 and the docking frame 110 and the metal fuselage stringer 13 can be achieved by means such as fasteners 150.
[0060] Preferably, a first thinning region 133 is formed in the first joint portion 131 of the first stringer joint 130 that connects to the docking frame 110, so as to cooperate with one of the first outer edge strip 112 and the second outer edge strip 113 of the docking frame 110.
[0061] Further preferably, a second thinning zone 134 is formed at the second joint portion 132 of the first stringer joint 130 for connection with the metal fuselage stringer 13.
[0062] Similar to the docking frame 110, the first stringer joint 130 can also be machined from aluminum alloy material, for example, from 7000 series aluminum alloy material.
[0063] Figure 4 A schematic structural perspective view of the second stringer joint 140 is shown. The second stringer joint 140 has an "L"-shaped cross-section. One end of the second stringer joint 140 is connected to the docking frame 110, and the other end is connected to the composite fuselage stringer 14 of the composite fuselage section 12. The connection between the second stringer joint 140 and the docking frame 110 and the composite fuselage stringer 14 can also be achieved by fasteners 150.
[0064] Preferably, a third thinning region 141 is formed in the portion of the first stringer joint 130 that connects to the mating frame 110, and the third thinning region 141 cooperates with another of the first outer edge strip 112 and the second outer edge strip 113.
[0065] Further preferably, a fourth thinning zone 142 is formed at the end of the second stringer joint 140 that is connected to the composite material fuselage stringer 14.
[0066] The second stringer joint 140 is machined from titanium alloy.
[0067] Figure 5 The top view schematically illustrates the structure by which the metal fuselage section 11 and the composite material fuselage section 12 are joined together via the docking structure 100 of this application. The docking strip 120 is connected to the docking frame 110 via connecting components such as fasteners 150. Preferably, as shown, the width of the docking strip 120 is greater than the sum of the widths of the first outer edge strip 112 and the second outer edge strip 113 at the bottom of the docking frame 110. The docking strip 120 can be made of titanium alloy, for example, by bending titanium alloy material, so that the formed docking strip 120 can match the curvature of the aircraft fuselage.
[0068] The first stringer joint 130 for connecting the metal fuselage stringer 13 of the metal fuselage section 11 is provided in a one-to-one correspondence with the metal fuselage stringer 13 on the metal fuselage section 11, so that each first stringer joint 130 is connected to its corresponding metal fuselage stringer 13.
[0069] The second stringer joints 140 for connecting the composite fuselage section 12 and the composite fuselage stringer 14 are arranged in pairs, with each pair of second stringer joints 140 connected to a corresponding composite fuselage stringer 14.
[0070] In the aforementioned docking structure 100, a first stringer joint 130 connects to a metal fuselage stringer 13, and a pair (two) of second stringer joints 140 connect to a composite material fuselage stringer 14. Thus, the first stringer joints 130 and second stringer joints 140 are arranged in a one-to-two configuration. This structural arrangement allows for convenient coaxial arrangement of the metal fuselage stringer 13 and the composite material fuselage stringer 14, i.e., the longitudinal axis of the metal fuselage stringer 13 is aligned with the longitudinal axis of the composite material fuselage stringer 14. Furthermore, each pair of second stringer joints 140 is preferably arranged symmetrically with respect to its corresponding first stringer joint 130. This avoids overall force transmission path eccentricity, shortens the transmission path, improves load transmission efficiency, and consequently improves the stress condition at the connection between the metal fuselage section 11 and the composite material fuselage section 12.
[0071] Preferably, the portion of the mating strip 120 between two adjacent first stringer joints 130 forms a first width reduction 121. Similarly, the portion of the mating strip 120 between two adjacent pairs of second stringer joints 140 forms a second width reduction 122. These width reductions help reduce the overall structural weight, and because the width reductions are located between adjacent first stringer joints 130 and between two adjacent pairs of second stringer joints 140, weight reduction is achieved without compromising the structural connection strength.
[0072] Preferably, the mating strip 120 may also be configured to include a stepped portion or a double-layer structure. This allows the stepped or double-layer design to compensate for the assembly step difference between the metal fuselage section 11 and the composite fuselage section 12 when there is a step difference between their skins. Consequently, the mating strip 120 can better withstand the shear loads between the metal fuselage section 11 and the composite fuselage section 12.
[0073] The process of using the docking structure 100 disclosed above to dock fuselage sections made of different materials (metals and composite materials) will be described in detail below.
[0074] First, fix the docking frame 110 and the docking strip 120 together. Specifically, use two rows of fasteners 150 to fix the docking strip 120 to the first outer edge strip 112 and the second outer edge strip 113 of the docking frame 110 respectively.
[0075] Next, the pair of second stringer joints 140 are connected to one of the first outer edge strips 112 and 113, for example, by securing the second stringer joints 140 with a row of fasteners 150. For example, the third thinning region 141 of the second stringer joint 140 can be fitted onto one of the first outer edge strips 112 and 113, and then the fasteners 150 are used to complete the fixed connection.
[0076] Before, simultaneously with, or after securing the second stringer joint 140, the portion of the mating strip 120 corresponding to the side of the second stringer joint 140 is connected to the skin of the composite fuselage section 12. For example, three rows of fasteners 150 can be used to connect the mating strip 120 to the skin of the composite fuselage section 12. Before, simultaneously with, or after connecting the mating strip 120 to the skin of the composite fuselage section 12, each pair of second stringer joints 140 is connected to the corresponding composite fuselage stringer 14. The connection between the second stringer joint 140 and the composite fuselage stringer 14 can also be achieved using fasteners 150.
[0077] Then, the metal fuselage stringer 13 of the metal fuselage section 11 and the composite material fuselage stringer 14 of the composite material fuselage section 12 are aligned coaxially to determine the assembly position of the metal fuselage section 11 relative to the composite material fuselage section 12.
[0078] After the assembly position of the metal fuselage section 11 is determined, the portion of the mating strip 120 corresponding to the side of the first stringer joint 130 is connected to the skin of the metal fuselage section 11. For example, two rows of fasteners 150 can be used to connect the mating strip 120 to the skin of the metal fuselage section 11.
[0079] Before, simultaneously with, or after connecting the mating strip 120 to the skin of the metal fuselage section 11, the second stringer joint 140 is connected to the other of the first outer edge strip 112 and the second outer edge strip 113. For example, the first thinned section 133 of the first stringer joint 130 can be fitted onto the other of the first outer edge strip 112 and the second outer edge strip 113, and then fasteners 150 are used to complete the fixed connection.
[0080] Before, simultaneously with, or after connecting the second stringer joint 140 to the other of the first outer edge strip 112 and the second outer edge strip 113, the first stringer joint 130 is connected to its corresponding metal fuselage stringer 13, for example by means of fastener 150.
[0081] At this point, the process of using the docking structure 100 to dock the metal fuselage section 11 and the composite material fuselage section 12 is basically complete. It should be noted that the above sequence of operations can be adjusted according to actual needs and operating habits.
[0082] Preferably, the fastener 150 described above for fixed connection is a co-riveting fastener to achieve reliable connection and fixation.
[0083] The exemplary preferred structure and corresponding operation method of this application have been described above. However, the disclosed structure is not intended to limit the scope of this application. Those skilled in the art can make various obvious modifications and variations to this application based on the disclosed structure without departing from the scope of this application.
Claims
1. A butt joint structure of an aircraft fuselage, the aircraft fuselage comprising a metallic fuselage section and a composite material fuselage section, the butt joint structure comprising: Multiple first stringer joints, the first stringer joints being used to connect to the metal fuselage stringers of the metal fuselage section; And multiple second stringer joints, the second stringer joints being used to connect to the composite fuselage stringers of the composite fuselage section; The docking structure is characterized in that it further includes: A docking frame, comprising a web, with a first outer edge strip and a second outer edge strip disposed at the bottom of the web, the first and second outer edge strips being located on opposite sides of the web. A docking strip plate, wherein the docking frame is fixedly connected to the docking strip plate; The first stringer joint is fixedly connected to one of the first outer edge strip and the second outer edge strip, and the second stringer joint is fixedly connected to the other of the first outer edge strip and the second outer edge strip. Each of the first stringer joints is connected to a corresponding metal fuselage stringer on the metal fuselage section; the second stringer joints are arranged in pairs, and each pair of second stringer joints is connected to a corresponding composite material fuselage stringer on the composite material fuselage section. Each pair of second stringer joints is positioned on both sides relative to the corresponding first stringer joint, and the first stringer joint and the corresponding pair of second stringer joints are configured such that the longitudinal axis of each metal fuselage stringer is aligned with the longitudinal axis of the corresponding composite material fuselage stringer.
2. The docking structure of claim 1, wherein, The first stringer joint includes: The first joint portion is connected to the docking frame and has a "T" shaped cross-section; The second joint portion is used to connect with the metal fuselage stringer, and the second joint portion has an "L" shaped cross-section.
3. The docking structure of claim 2, wherein, The first stringer joint includes: A first thinning region is formed on the first joint portion, and when the first stringer joint is installed onto the mating frame, the first thinning region mates with one of the first outer edge strip and the second outer edge strip; and / or A second thinning zone is formed on the second joint portion, the second thinning zone being used to connect with the metal fuselage stringer.
4. The docking structure of claim 1, wherein, The docking frame is provided with a plurality of reinforcing ribs, which are connected to the web of the docking frame and extend from at least one of the first outer edge strip and the second outer edge strip toward the top of the web of the docking frame.
5. The docking structure of claim 1, wherein, The docking frame and the first stringer joint are made of 7000 series aluminum alloy.
6. The docking structure of claim 1, wherein, The second stringer joint has an "L"-shaped cross-section, and the second stringer joint includes: The third thinning zone, when the second stringer joint is installed onto the mating frame, mates with the other of the first and second outer edge strips; and / or The fourth thinning zone is used to connect with the composite material fuselage stringer.
7. The docking structure of claim 1, wherein, The docking strip includes: A first width reduction portion is formed at the portion of the mating strip plate between two adjacent first stringer joints; and / or The second width reduction section is formed in the portion between two adjacent pairs of second stringer joints.
8. The docking structure of claim 1, wherein, The docking strip and the second stringer joint are made of titanium alloy.
9. The docking structure of claim 1, wherein, The docking structure also includes a plurality of fasteners, which are used to achieve at least one of the following connections: The connection between the docking frame and the docking strip plate; The first stringer joint is connected to one of the first outer edge strip and the second outer edge strip; The connection between the first stringer joint and the metal fuselage stringer; The second stringer joint is connected to the other of the first outer edge strip and the second outer edge strip; The connection between the second stringer joint and the composite material fuselage stringer; The connection between the docking strip and the skin of the metal fuselage section; and The connection between the docking strip and the skin of the composite material fuselage section.
10. The docking structure of claim 9, wherein, The fastener is a co-riveting fastener.
11. An aircraft fuselage comprising a metallic fuselage section and a composite material fuselage section, characterized in that The aircraft fuselage includes a docking structure as described in any one of claims 1-10, the docking structure connecting the metal fuselage section to the composite material fuselage section.