A docking connection structure for docking a composite material wall panel of an aircraft

Abstract

The present invention provides a docking connection structure for docking composite panels of an aircraft, the composite panels comprising a plurality of first composite panels arranged along a direction of travel, each first composite panel comprising a plurality of second composite panels arranged along a circumferential direction, the docking connection structure comprising a first connection strap spanning a gap between adjacent first composite panels, secured to the adjacent first composite panels by fasteners; a second connection strap spanning a gap between adjacent second composite panels, secured to the adjacent second composite panels by fasteners; and a connection joint arranged at an intersection of the first connection strap and the second connection strap, secured to the first connection strap, the second connection strap and the second composite panels at the intersection by fasteners respectively.

Description

Technical Field

[0001] This invention relates to the field of mechanical manufacturing and assembly, mainly to the field of aircraft manufacturing and assembly, and particularly to a docking connection structure for composite material panels used in docking aircraft. Background Technology

[0002] In medium and large composite material fuselage structures for aircraft, due to limitations in manufacturing capabilities, maintainability, and economic efficiency, it is often impossible to manufacture the entire fuselage structure directly. Therefore, it is frequently necessary to use a splicing method, connecting multiple composite material panels to form the target fuselage structure. The aforementioned multiple composite material panels, such as... Figure 1 As shown, it generally includes multiple first composite material panels 1 (i.e. fuselage sections) distributed along the heading direction of the aircraft, and each first composite material panel includes multiple second composite material panels 2 distributed along the circumferential direction.

[0003] The process of splicing and connecting multiple composite material wall panels to form the fuselage structure includes: sequentially splicing and connecting multiple second composite material wall panels 2 to form a first composite material wall panel 1, and then sequentially splicing and connecting the formed multiple first composite material wall panels 1 to form the fuselage structure. In practice, the composite material wall panels of the fuselage structure mostly have cap-shaped stringers 21. At this time, the fuselage sections are mainly connected by butt joints with plates combined with stringer joints. At the same time, the second composite material wall panels are connected separately using a simple lap joint method.

[0004] As can be seen from the above, existing butt joint structures typically only connect the second composite material wall panel 2 or the first composite material wall panel 1 individually, and their structural forms are relatively simple. For the intersection area of ​​the gaps between the second composite material wall panels 2 and the gaps between the first composite material panels 1, due to limitations imposed by various requirements such as assembly, load transfer, and sealing, the design of its butt joint structure is more complex, and there is currently no publicly available information on this. Summary of the Invention

[0005] Therefore, the technical problem to be solved by the present invention is to overcome the problem that the existing docking connection structure for composite material panels for docking aircraft only targets the individual connection of the first composite material panel or the second composite material panel, and it is difficult to achieve accurate and reliable connection between the second composite material and the first composite material and / or the intersection area of ​​the second composite material. A new docking connection structure for composite material panels for docking aircraft is proposed.

[0006] The present invention solves the above-mentioned technical problems through the following technical solution:

[0007] Specifically, the present invention provides a docking connection structure for composite material panels used in docking aircraft. The composite material panels include a plurality of first composite material panels arranged along the heading direction of the aircraft, and each of the plurality of first composite material panels includes a plurality of second composite material panels arranged along the circumferential direction of the aircraft. The docking connection structure is characterized in that it includes:

[0008] A first connecting strip spans the gap between adjacent first composite material wall panels and can be fixed to the adjacent first composite material wall panels by fasteners.

[0009] A second connecting strip spans the gap between adjacent second composite wall panels and can be secured to the adjacent second composite wall panels by fasteners; and

[0010] A connecting joint is arranged at the intersection of the first connecting strip plate and the second connecting strip plate, and can be fixed to the first connecting strip plate, the second connecting strip plate and the second composite material wall panel located at the intersection by fasteners.

[0011] The docking connection structure for composite material panels used in docking aircraft provided by this invention can not only achieve independent connection of the first composite material panel and the second composite material panel, but also comprehensively consider the limitations of various requirements such as assembly, load transfer and sealing at the junction of the second composite material panel and the first composite material panel. By connecting the first connecting strip plate, the second connecting strip plate and the second composite material panel through the connecting joint, the effective connection of the first composite material panel and the second composite material panel at the junction is achieved, the continuous load transfer and the sealing performance are significantly improved.

[0012] Meanwhile, for composite panel walls with cap-shaped stringers, the adjacent second composite material junction area lacks stringers, resulting in greater assembly space and weaker load transfer capacity. Therefore, the application of connecting joints not only enables the connection of the various panel structures at the junction, improving the connection margin at the aforementioned junction and the second composite material junction area through double shearing, but also effectively reduces stress concentration at the stringers caused by complex stress environments.

[0013] According to one embodiment of the present invention, the second composite material panel, the first connecting strip plate, the second connecting strip plate, and the connecting joint all have curved profiles, and their curvatures are all the same along the circumferential direction. By adopting a structure in which each panel, connecting strip plate, and connecting joint has the same curvature along the circumferential direction, good contact between the components can be ensured, thereby achieving uniform stress distribution on the fuselage structure and effectively avoiding fuselage tearing caused by uneven stress distribution during flight.

[0014] According to one embodiment of the present invention, the second composite material wall panel and the second connecting strip plate have the same length along the flight direction. Using a second connecting strip plate with the same length as the second composite material wall panel effectively improves the connection margin and connection strength between the second composite material wall panels, thereby compensating for the strength of the intersection area where the second composite material wall panels lack stringers, and effectively and uniformly transferring stress and load between the second composite material wall panels.

[0015] According to one embodiment of the present invention, the connecting joint includes a web and side plates located on opposite sides of the web in the circumferential direction, thereby enabling the connecting joint to be connected to the first connecting strip plate, the second connecting strip plate, and the second composite material wall panel respectively through the web, and to contact the stringer on the inner side of the second composite material wall panel through the side plates. Using the web to connect to the connecting strip plate and the second composite material wall panel improves the connection margin and connection stiffness, and ensures the airtightness requirements at the intersection of the directional and circumferential directions. Simultaneously, contact between the side plates and the stringer facilitates the transfer of directional loads and uniform stress distribution at the stringer, alleviating stress concentration at the connecting joint location.

[0016] According to one embodiment of the present invention, the first connecting strip plate includes a plurality of sub-strip plates arranged in a circumferential direction, and the intersection of adjacent sub-strip plates has a certain distance between the gap between it and the second composite material wall panel in the circumferential direction.

[0017] According to one embodiment of the present invention, the docking connection structure further includes an H-shaped connecting joint with an H-shaped web, the H-shaped connecting joint being arranged at the intersection of adjacent sub-strip plates, thereby enabling the H-shaped connecting joint to connect adjacent sub-strip plates through the H-shaped web and to accommodate the stringers on the inner side of the second composite material wall panel.

[0018] By including multiple sub-strips in the first connecting strip plate, manufacturing difficulty can be reduced. Furthermore, setting the intersection of adjacent sub-strips at a certain distance from the aforementioned gap ensures sufficient available connection space and connection margin in the first connecting strip plate, thereby guaranteeing that the sub-strips can be connected via an H-shaped connector. Moreover, the web of the sub-strip plate connector is H-shaped, allowing the long stringer inside the second composite material wall panel to be accommodated through through holes in the web along the flight direction, thus avoiding interference with the long stringer.

[0019] According to one embodiment of the present invention, the length of the middle portion of the H-shaped web along the yaw direction is equal to that of the first connecting strip. Through the aforementioned shape and size settings, the load transfer in the yaw direction can be maximized, and the continuity of the yaw load transfer can be guaranteed.

[0020] According to one embodiment of the present invention, adjacent sub-strip plates have overlapping areas along the circumferential direction and are connected at the overlapping positions by an H-shaped connector.

[0021] According to one embodiment of the present invention, the butt joint structure further includes a gasket, which is elongated and located between the web of the H-shaped joint and the second composite material wall panel and connected to both. The gasket can compensate for the thickness difference between the first connecting strip plate and the inner wall of the second composite material wall panel, as well as the thickness difference between the first connecting strip plate and the stringer on the inner side of the second composite material wall panel, thereby alleviating stress and load concentration at the fasteners on the H-shaped joint.

[0022] According to one embodiment of the present invention, the first connecting strip, the second connecting strip, and the connecting joint are formed of carbon fiber composite material. Carbon fiber composite material possesses advantages such as high strength, heat resistance, excellent thermal shock resistance, low specific gravity, and excellent corrosion and radiation resistance, ensuring the strength and impact resistance of the formed fuselage structure. Furthermore, the materials forming the connecting strip and the connecting joint are designed to be similar to those used in the composite material wall panels, facilitating uniform load transfer and matching the elongation and deformation of the fuselage wall panels.

[0023] Based on common knowledge in the field, the above-mentioned preferred embodiments can be combined arbitrarily to obtain various preferred embodiments of the present invention.

[0024] The positive and progressive effects of the above-described embodiments of the present invention are as follows:

[0025] 1. This docking connection structure can effectively connect the first composite material gap, the second composite material gap and the intersection of their connecting strip plates, ensuring connection margin and load transfer, and improving the airtightness of the resulting fuselage structure;

[0026] 2. The connecting joints in this docking structure can contact the stringer through the side plates, improving the load transfer efficiency at the stringer. Furthermore, by covering the joints, connecting strips, and composite material wall panels with adhesives or other materials, the airtightness of the fuselage structure can be ensured.

[0027] 3. The sub-strip plates of the first connecting strip plate are connected by an H-shaped connecting joint, which reduces the manufacturing difficulty of the first connecting strip plate. Furthermore, the web shape of the H-shaped connecting joint can accommodate the stringers on the inner side of the second composite material without relying on the stringers for connection, thereby avoiding stress concentration at the stringers. Attached Figure Description

[0028] Figure 1 A schematic diagram illustrating an exemplary distribution of composite material panels of a spacecraft to be docked according to a preferred embodiment of the present invention is shown.

[0029] Figure 2 A partial perspective view of the structure formed after connection using a docking connection structure for a composite material panel for docking aircraft according to a preferred embodiment of the present invention is shown schematically.

[0030] Figure 3 schematically shown Figure 2 The structure in the image is enlarged at point A.

[0031] Figure 4 schematically shown Figure 2 The structure in the image is magnified from another perspective at point A.

[0032] Figure 5 schematically shown Figure 3 A cross-sectional view of the structure at point B along the circumferential direction.

[0033] Figure 6 An exploded view schematically illustrates a portion of the junction structure after connection using a docking connection structure for a docking aircraft made of composite material panels according to a preferred embodiment of the present invention.

[0034] Figure 7 A perspective view of an exemplary connection joint in a mating connection structure is schematically shown.

[0035] Figure 8 A perspective view of an exemplary H-shaped connector in a mating connection structure is schematically shown. Detailed Implementation

[0036] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be clearly and completely described below in conjunction with the accompanying drawings showing multiple embodiments according to this application. It should be understood that all other embodiments obtained by those skilled in the art based on the embodiments described in this application without creative effort will fall within the scope of protection of this application.

[0037] Unless otherwise defined, all technical and scientific terms used in this application have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains; the terms "comprising," "having," etc., in the specification, claims, and foregoing description of the drawings are open-ended terms. Thus, "comprising" or "having" means, for example, one or more steps, having one or more steps, but not limited to having only these one or more steps.

[0038] In the aerospace field, medium and large composite material fuselage structures are typically formed by connecting multiple first composite material panels 1 arranged along the flight direction. Each first composite material panel 1 is further connected by connecting multiple second composite material panels 2 arranged circumferentially. Existing connection structures for composite material panels can usually only connect the gaps between the first composite material panels 1 or the gaps between the second composite material panels 2, but cannot connect the areas where the gaps between the first composite material panels 1 and the second composite material panels 2 intersect.

[0039] Furthermore, for the first composite material wall panel 1 formed by the second composite material wall panel 2 with a cap-shaped girder 21, a butt connection structure including a butt joint plate and a girder joint is usually used for connection. According to engineering practice experience, this butt connection structure, because the connection is achieved through a girder, often causes stress concentration at the joint of the girder 21, and also results in defects such as discontinuous load transfer between composite material wall panels.

[0040] Therefore, at least to address the aforementioned problems and deficiencies, the present invention provides a docking connection structure for composite material panels of docking aircraft. This docking connection structure can not only achieve connection between second composite material panels 2 or between first composite material panels 1, but also achieve connection at the intersection of second composite material panels 2 and first composite material panels 1. This docking connection structure, by combining connecting strips with a special type of joint, can meet the requirements of connection assembly, continuous load transfer, and sealing at the intersection. Moreover, through the unique design of the joint shape, load transfer or continuous load transfer can be achieved between the stringer 21 and the composite material panels at the connection position, thereby effectively preventing tearing of the structure during flight due to uneven load transfer or distribution.

[0041] like Figures 2 to 6 As shown, the docking connection structure includes at least a first connecting strip plate 3, a second connecting strip plate 4, and a connecting joint 5. The first connecting strip plate 3, the second connecting strip plate 4, the connecting joint 5, and the second composite material wall panel 2 all have curved contours and the curvature along the circumferential direction is the same, thereby ensuring good contact between the connecting strip plate, the connecting joint, and the wall panel.

[0042] like Figure 3 As shown, the second connecting strip 4 spans the gap between adjacent second composite material wall panels 2 and is fixed to the adjacent sides of the adjacent second composite material wall panels 2 by fasteners, thereby achieving the connection of the adjacent second composite material wall panels 2. Preferably, the second connecting strip 4 achieves the connection of adjacent second composite material wall panels 2 by one or more of the following methods: multi-row threaded fasteners, welding, and adhesive bonding. It is understood that the second connecting strip 4 can also achieve the connection of adjacent second composite material wall panels 2 by other similar methods.

[0043] The second connecting strip 4 can be arranged on the inner or outer side of the second composite material wall panel 2 for butt joint connection. Furthermore, the length of the second connecting strip 4 along the flight direction can be the same as that of the second composite material wall panel 2, extending to the starting position of the gap formed by it in the first composite material wall panel 1, thereby ensuring continuous load transmission along the circumferential direction on the second composite material wall panel 1. Preferably, the length of the second connecting strip 4 along the flight direction is greater than its length along the circumferential direction.

[0044] like Figure 4 As shown, the first connecting strip 3 spans the gap between adjacent first composite material wall panels 3 and is fixed to the adjacent sides of the adjacent first composite material wall panels 3 by fasteners, thereby achieving the connection of adjacent first composite material wall panels 3. The connection method of the first connecting strip 3 is similar to the connection method of the second connecting strip 4. Exemplarily, both the first connecting strip 3 and the second connecting strip 4 are connected by threaded fasteners. Preferably, the length of the first connecting strip 3 in the circumferential direction is greater than its length in the azimuth direction, that is, the first connecting strip 3 is ring-shaped or ring segment-shaped.

[0045] The first connecting strip 3 can be arranged inside the first composite material wall panel 1, and connected to the sides of adjacent first composite material wall panels 1 distributed along the flight direction by multiple rows of threaded fasteners. Alternatively, to reduce manufacturing difficulty, the first connecting strip 3 may include multiple sub-strips 31 arranged in the circumferential direction, and the intersection of adjacent sub-strips 31 in the circumferential direction has a certain distance from the gap between the second composite material wall panel 2. Moreover, through the aforementioned positional design between the sub-strips 31, interference between the connection of the sub-strips 31 and the connection between the first connecting strip 3 and the second connecting strip 4 can be avoided, thereby facilitating assembly.

[0046] like Figures 3 to 6 As shown, the connecting joint 5 is arranged at the intersection of the first connecting strip plate 3 and the second connecting strip plate 4 (i.e., the intersection of the gap between adjacent first composite material wall panels 1 and the gap between adjacent second composite material wall panels 2), and can be fixed to the first connecting strip plate 3, the second connecting strip plate 4 and the second composite material wall panel 2 located at the intersection by fasteners, thereby completing the bridging at the intersection of the gap between the second composite material wall panel 2 and the gap between the first composite material wall panel 1, and thus realizing the load transfer at the intersection position.

[0047] Specifically, the connecting connector 5 may include, for example, Figure 7 The U-shaped connector 8 shown includes a web 81 and two side plates 82 and 83 located on opposite sides of the web 81 in the circumferential direction. The web 81 and the side plates 82 and 83 are of equal or slightly shorter length. The U-shaped connector 8 can be connected to the second connecting strip 4, the first connecting strip 3, and the second composite material wall panel 2 respectively through the web 81. Furthermore, the length of the U-shaped connector 8 in the circumferential direction is equal to the length of the opposite sides of the adjacent stringers 21 in that direction, so that the U-shaped connector contacts the stringers 21 on the inner side of the second composite material wall panel through the side plates 82 and 83, in order to transfer the yaw load on the stringers 21 at this location, alleviate stress concentration at this location, and ensure the airtightness requirements at the junction.

[0048] The connection method of the U-shaped connector 8 is similar to that of the second connecting plate 4. For example, the U-shaped connector 8 is connected to both the first connecting plate 3 and the second connecting plate 4 using fasteners. At the intersection, if the space is limited, the U-shaped connector 8 and the first connecting plate 3, and the U-shaped connector 8 and the second connecting plate 4, can be connected in a staggered arrangement of fasteners in the wall panel area. Simultaneously, the first and second connecting plates and the U-shaped connector connection areas use common fasteners. The dimension of the web plate 81 of the U-shaped connector 8 along the flight direction can be determined based on the number of fasteners and the edge distance, and can be slightly shorter than the two side plates 82 and 83.

[0049] When the first connecting strip 3 includes multiple sub-strips 31, the connecting joint 5 also includes, for example, Figure 8 The H-shaped connector 9 shown includes a web 91 and two side plates 92 and 93 located on opposite sides of the web 91 in the circumferential direction, wherein the web is H-shaped. The H-shaped connector 9 is arranged at the intersection of adjacent sub-strip plates 31, so that the H-shaped connector 9 can connect adjacent sub-strip plates 31 through the H-shaped web 91 and accommodate the stringer 21 on the inner side of the second composite material wall panel 2.

[0050] Preferably, the middle portion of the H-shaped web 91 has a length in the directional direction consistent with that of the first connecting strip 3, used to transfer the directional load between the sub-strips 31 of the first connecting strip 3. Alternatively, adjacent sub-strips 31 overlap in the circumferential direction by a length of a stringer along that direction, and are connected at the overlap position by an H-shaped connecting joint, thereby ensuring continuous circumferential load transfer on the first connecting strip 3. Furthermore, the length of the H-shaped connecting joint 9 in the directional direction is equal to the length of the opposite side of the adjacent stringer 21, so that the side plate of the H-shaped connecting joint 9 can contact the stringer 21, thereby transferring the directional and circumferential loads on the stringer 21 at that position.

[0051] like Figure 3As shown, the docking connection structure according to a preferred embodiment of the present invention includes the following docking connection method: a second connecting strip plate 4 is arranged on the outer side of the second composite material wall panel 2, and adjacent second composite material wall panels 2 are connected by four rows of fasteners along the circumferential direction. The second connecting strip plate 4 extends to both sides of the second composite material wall panel 2 along the flight direction, and the fasteners on it are determined according to actual needs; a first connecting strip plate 3 is arranged on the inner side of the first composite material wall panel 1, and adjacent first composite material wall panels 1 are connected by six rows of fasteners along the circumferential direction; a U-shaped connecting joint 8 is used to connect the first connecting strip plate 3, the second connecting strip plate 4, and the second composite material wall panel 2 at the intersection of the gap between adjacent second composite material wall panels 2 and the gap between adjacent first composite material wall panels 1, and the connection is performed by the aforementioned staggered arrangement of fasteners; adjacent sub-strip plates 31 of the first connecting strip plate 3 have overlapping areas along the circumferential direction, and adjacent sub-strip plates 31 are connected from the overlapping position by an H-shaped connecting joint 9, wherein the middle part of the web of the H-shaped connecting joint 9 has the same length along the flight direction as the first connecting strip plate 3, and the connection is performed by common fasteners.

[0052] like Figures 3 to 8 As shown, the docking connection structure also includes a gasket 6, which is elongated and located between the H-shaped connector 9 and the second composite material wall panel 2. The length of the gasket 6 along the flight direction is equal to or slightly longer than the connection area between the H-shaped connector 9 and the second composite material wall panel 2, to compensate for the thickness difference between the first connecting strip 3 and the stringers 21 on the second composite material wall panel 2 in the first composite material wall panel 1, thereby alleviating load concentration at fasteners such as head studs on the H-shaped connector 9. Alternatively, in the connection areas of the U-shaped connector 8 and the H-shaped connector 9 with the second composite material wall panel 2, the gasket 6 is used for thickness compensation based on the thickness step difference of the stringers 21 on the first connecting strip 3 and the second composite material wall panel 2. Preferably, the gasket 6 extends forward of the U-shaped connector 8 and the H-shaped connector 9 along the flight direction by the length required for the connection of one fastener.

[0053] Preferably, the first connecting strip 3, the second connecting strip 4, and the connecting joint 5 are all formed of carbon fiber composite material or glass fiber composite material.

[0054] This invention achieves butt joint connection of composite material wall panels at the intersection of the azimuth and circumferential directions using a U-shaped connector 8, while simultaneously reducing stress concentration at the fasteners on the H-shaped connector 9 caused by complex stress environments. Furthermore, it improves the connection margin at the intersection through a double-shear method. Through the H-shaped connector 9, efficient circumferential load transfer is achieved at the separation position between the sub-plates 31 of the first connecting strip 3 without altering the load-transfer function of the stringer 21. Additionally, the gasket 6 reduces stress concentration and provides thickness compensation. This butt joint has the advantages of simple structural design and connection relationships, and high assembly feasibility.

[0055] Furthermore, it should be understood that the first connecting plate 3, the second connecting plate 4, the connecting joint 5, and the gasket 6 in this invention are not limited to using carbon fiber composite materials or glass fiber composite materials, and the number of threaded fasteners is not limited to two rows, three rows, or six rows, but can be adapted to actual needs.

[0056] While specific embodiments of the present invention have been described above, those skilled in the art should understand that these are merely illustrative examples, and the scope of protection of the present invention is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but all such changes and modifications fall within the scope of protection of the present invention.

Claims

1. A docking connection structure for a composite material panel for docking an aircraft, the composite material panel comprising a plurality of first composite material panels arranged along the heading direction of the aircraft, each of the plurality of first composite material panels comprising a plurality of second composite material panels arranged along the circumferential direction of the aircraft, characterized in that, The docking connection structure includes: A first connecting strip spans the gap between adjacent first composite material wall panels and can be fixed to the adjacent first composite material wall panels by fasteners. A second connecting strip spans the gap between adjacent second composite wall panels and can be secured to the adjacent second composite wall panels by fasteners; and A connecting joint is provided at the intersection of the first connecting strip plate and the second connecting strip plate, and can be correspondingly fixed to the first connecting strip plate, the second connecting strip plate, and the second composite material wall panel located at the intersection by fasteners. The first connecting strip plate includes a plurality of sub-strip plates arranged along the circumferential direction. The connecting joint includes an H-shaped connecting joint with an H-shaped web. The H-shaped connecting joint is arranged at the intersection of adjacent sub-strip plates, so that the H-shaped connecting joint can connect adjacent sub-strip plates through the H-shaped web and accommodate the stringers on the inner side of the second composite material wall panel.

2. The docking connection structure according to claim 1, characterized in that, The second composite material wall panel, the first connecting strip plate, the second connecting strip plate, and the connecting joint all have curved contours, and the curvature along the circumferential direction is the same.

3. The docking connection structure according to claim 2, characterized in that, The second composite material wall panel and the second connecting strip plate have the same length along the heading direction.

4. The docking connection structure according to claim 3, characterized in that, The connecting joint further includes a U-shaped connecting joint, which includes a web and side plates located on opposite sides of the web along the circumferential direction, so that the connecting joint can be connected to the first connecting strip plate, the second connecting strip plate and the second composite material wall panel respectively through the web, and contact the stringer on the inner side of the second composite material wall panel through the side plates.

5. The docking connection structure according to claim 4, characterized in that, The intersection of adjacent sub-strip plates is at a certain distance from the gap between the second composite material wall panel along the circumferential direction.

6. The docking connection structure according to claim 1, characterized in that, The length of the middle portion of the H-shaped web along the heading direction is equal to that of the first connecting strip.

7. The docking connection structure according to claim 6, characterized in that, The adjacent sub-strip plates have overlapping areas along the circumferential direction and are connected at the overlapping positions by the H-shaped connector.

8. The docking connection structure according to claim 6, characterized in that, The docking connection structure also includes a gasket, which is elongated and located between the web of the H-shaped connection joint and the second composite material wall panel and connected to both.

9. The docking connection structure according to any one of claims 1 to 8, characterized in that, The first connecting strip, the second connecting strip, and the connecting joint are formed of carbon fiber composite material.

Images