Joint for connecting an aircraft wing to the main body of the aircraft

Abstract

The present disclosure relates to a joint connecting an aircraft wing to an aircraft body, the joint employing a joint panel that is joined in surface engagement with a skin panel on a side of the aircraft body and in surface engagement with a post panel that extends upward from the aircraft wing. A plurality of fasteners extend through the joint panel and the post panel and extend through the joint panel and the skin panel. The plurality of fasteners attach the joint panel to the skin panel and attach the joint panel to the post panel, thereby attaching the skin panel to the post panel. After the fastener holes are drilled through the joint panel and the post panel to attach the joint panel to the post panel, the joint panel can be removed from the post panel. This facilitates access to the fastener holes drilled through the post panel to remove burrs from the fastener holes.

Description

Technical Field

[0001] This disclosure relates to the construction of joints that connect various parts of an aircraft. More specifically, this disclosure relates to the construction of a joint that serves as one of the main connecting components between the aircraft wing and the fuselage of the aircraft body. Background Technology

[0002] In the construction of modern aircraft, it is often necessary to attach structural panels made of different materials together. For example, it is often necessary to attach composite material structural panels to metallic material structural panels (such as aluminum or titanium).

[0003] When attaching large structural components of an aircraft together, such as attaching an aircraft wing to the aircraft body, one or more interlocking joints may serve as part of the construction for attaching the aircraft wing to the aircraft body. In one example of attaching an aircraft wing to the aircraft body, an upright column panel or column panel extending upwards from the aircraft wing overlaps with a skin panel on the side of the aircraft body. Holes are then drilled through the overlapping column panel and skin panel to prepare holes for inserting fasteners to secure the column panel to the skin panel. In this example, an upright column panel of the wing's upper T-chord, typically made of metal, overlaps with a skin panel of the fuselage, typically made of composite materials or aluminum. Fastener holes for attaching the column panel to the skin panel are drilled at the overlap location of the column panel and skin panel.

[0004] Drilling fastener holes in the metal of a post panel typically results in burrs at both the entrance and exit edges of the hole. One or more burrs are usually present at the exit edge of the hole. Burrs are small, raised, or protruding edges or tips of the metal material at the hole's exit edge.

[0005] The burrs formed at the exit edge of the fastener hole act as a cut at that edge. These cuts, created by the burrs at the exit edge of the fastener hole, can become the starting point for cracks in the metal material of the column panel. Therefore, the cuts formed by burrs at the exit edge of the fastener hole create a fatigue critical zone at the joint, and thus must be removed.

[0006] To remove burrs from the exit edge of the fastener holes passing through the column panel, and possibly from the entrance edge, a deburring tool must be used to access the edge of the fastener hole. The deburring tool processes around the edge of the fastener hole, essentially forming a chamfered or beveled edge surface around the opening of the fastener hole. This eliminates potential cracks in the metal material of the column panel at the edge of the fastener hole. However, it is typically difficult to access the exit edge of the fastener hole with a deburring tool.

[0007] In aircraft assembly, particularly during the connection of the wings to the fuselage body, the overlapping wing strut panels and fuselage skin panels often require prying apart. Wedges, levers, or similar tools are used to pry apart the overlapping panels to create a passage between them and access the exit edges of the fastener holes. Prying apart the overlapping strut and skin panels to access the exit edges of the fastener holes is a time-consuming process. Because numerous fastener holes are drilled in the strut and skin panels, prying them apart at these locations significantly increases aircraft construction time and costs. Summary of the Invention

[0008] The joint disclosed herein for connecting an aircraft wing to the aircraft body avoids the increased production time and costs associated with deburring from the exit edge of a fastener hole drilled through a metal panel. This is achieved by simplifying access to the exit edge of the fastener hole. This reduces the time required to access the exit edge of the fastener hole to deburr it, thereby reducing production time and costs.

[0009] The connector disclosed herein is constructed to connect the skin panel on the side of the aircraft body to the column panel extending upward from the aircraft wing.

[0010] The skin panel is the external fuselage skin panel located on the side of the aircraft body. The skin panel is made of composite materials or metal. The skin panel has an outer surface facing outwards from the aircraft body and an opposing inner surface facing inwards from the aircraft body. The skin panel has a lower edge surface extending between the outer and inner surfaces of the skin panel.

[0011] An aircraft wing has an upper surface and an opposing lower surface. The aircraft wing is formed by an upper T-chord located on the fuselage side rib on the upper surface of the wing. The upright column panels of the T-chord extend upward from the T-chord.

[0012] The pillar panel extends upward from the upper surface of the aircraft wing. The pillar panel is made of a metallic material, such as titanium, aluminum, or other equivalent material. The pillar panel has an outer surface facing outwards from the aircraft body and an opposing inner surface facing inwards from the aircraft body. The pillar panel has an upper edge surface extending between the outer and inner surfaces of the pillar panel.

[0013] The connector panel is used to attach the aircraft wing to the aircraft body. The connector panel is made of composite materials or metallic materials (such as aluminum or titanium). The connector panel has an outer surface and opposing inner surfaces. The inner surface of the connector panel is surface-mounted to the outer surface of the pillar panel and also surface-mounted to the outer surface of the skin panel. When attaching the aircraft wing to the aircraft body, the skin panel and pillar panel lie on a single vertically oriented plane. The lower edge surface of the skin panel is directly opposite the upper edge surface of the pillar panel, and a gap is left between the lower and upper edge surfaces. The connector panel is then attached to the pillar panel and the skin panel.

[0014] When attaching the connector panel to the post panel and the skin panel, before placing the skin panel above the post panel, the lower half of the inner surface of the connector panel is configured to surface-fit with the outer surface of the post panel.

[0015] Then, drill pairs of vertically spaced fastener holes on the connector panel and the post panel. The pairs of vertically spaced fastener holes are drilled through the connector panel and the post panel at longitudinally spaced locations along the longitudinal length of the connector panel and the post panel.

[0016] Remove the connector panel from the post panel. Once the connector panel is removed from the post panel, the drill hole through the post panel can be easily accessed.

[0017] Then, deburr the drilled holes through the column panel using a deburring tool. The inlet edge of the hole is deburred, and the outlet edge of the hole is deburred. The outlet hole of the connector panel, if made of a metal material such as aluminum or titanium, can also be deburred.

[0018] Next, position the connector panel to surface-fit the post panel, aligning the holes previously drilled through both panels. Then, insert threaded fasteners into the aligned holes in the connector panel and post panel. Tighten the threaded fasteners to attach the connector panel to the post panel.

[0019] Then, the aircraft fuselage skin panel is positioned above the pillar panel. As previously described, the skin panel has an outer surface, an opposing inner surface, and a lower edge surface. The lower edge surface of the skin panel is positioned above the upper edge surface of the pillar panel, thereby maintaining a gap between the lower edge of the skin panel and the upper edge of the pillar panel, and the outer surface of the skin panel is configured to engage with the upper half of the inner surface of the pillar panel.

[0020] Then, pairs of vertically spaced fastener holes are drilled on the joint panel and the skin panel. The pairs of vertically spaced fastener holes pass through the post panel and the skin panel at longitudinally spaced positions and are vertically aligned with the pairs of vertically spaced fasteners that attach the joint panel to the post panel.

[0021] Then insert the threaded fasteners into the alignment holes on the connector panel and the skin panel. Tighten the threaded fasteners to attach the connector panel to the skin panel.

[0022] Multiple fasteners extending through the joint panel and the post panel, and extending through the joint panel and the skin panel, attach the joint panel to the post panel and attach the joint panel to the skin panel, thereby attaching the post panel to the skin panel.

[0023] The features, functions, and advantages already discussed can be implemented independently in various embodiments or combined in other embodiments, further details of which can be found in the following description and figures. Attached Figure Description

[0024] Figure 1 It is a perspective view of the aircraft and a representation of the position of the joints of this disclosure on the main body and wings of the aircraft.

[0025] Figure 2 This is the publicly disclosed contact. Figure 1 Side view of the main body and wings of the aircraft.

[0026] Figure 3 It is along Figure 2 The plane passing through the 3-3 line Figure 2 A schematic diagram of the cross-section of the connector.

[0027] Figure 4 It is along Figure 2 Passing through the plane of line 4-4 Figure 2 A schematic diagram of the cross-section of the connector.

[0028] Figure 5 yes Figure 1 A perspective view of the connector. Detailed Implementation

[0029] Figure 1 This is a perspective view of the aircraft body 12 and the aircraft wings 14, 16 connected to the opposite sides of the aircraft body 12. The joints of this disclosure connecting the aircraft wings 14, 16 to the aircraft body 12 are located on the left side relative to the aircraft body 12, or on the port side of the aircraft wing 14. Figure 1 The area shown is within rectangle 2. It should be understood that the connector of this disclosure also connects the right-side or starboard aircraft wing 16 to the aircraft body 12. The connector of this disclosure connecting the port-side or left-side aircraft wing 14 to the aircraft body 12 will also be disclosed herein. It should be understood that the connector of this disclosure also connects the right-side or starboard aircraft wing 16 to the aircraft body 12.

[0030] Figure 2This is a partial front view representation of connector 18, which connects aircraft wing 14 to aircraft body 12. Figure 2 Only a small portion of the entire longitudinal length of the aircraft body 12 is shown. Furthermore, in Figure 2 The image only shows the longitudinal length of the wing box attached to the root of the aircraft wing of the main body 12. Figure 3 It is along Figure 2 A schematic diagram of the cross-section of the 3-3 line passing through the connector 18 on the plane. Figure 4 It is along Figure 2 A schematic diagram of the cross-section of the 4-4 line passing through connector 18 on the plane. (Refer to...) Figure 1 and Figure 2 The connector 18 is constructed to connect the aircraft wing 14 to the aircraft body 12. More specifically, the connector 18 connects the skin panel 22 on the side of the aircraft body 12 to the upright column panel 24 extending upward from the aircraft wing 14.

[0031] Reference Figure 3 and Figure 4 The diagram schematically illustrates skin panel 22. Skin panel 22 is the external fuselage skin panel located on the side of the aircraft body 12. The construction of skin panel 22 is conventional. For example, skin panel 22 is composed of multiple layers of composite material sheets, such as carbon fiber reinforced composite fabric, carbon fiber reinforced composite strips, or combinations of these composite materials. Skin panel 22 may also be made of metallic materials such as aluminum or titanium. Skin panel 22 may have other equivalent constructions. Figure 3 and Figure 4 The skin panel 22 shown has an outer surface 26 facing the exterior of the aircraft body 12 and the external environment of the aircraft body 12. The skin panel 22 has an inner surface 28 opposite to the outer surface 26. The inner surface 28 of the skin panel 22 faces the interior of the aircraft body 12. The inner surface 28 does not necessarily face the interior of the aircraft cabin inside the aircraft body 12, but rather faces the interior of the fuselage structure of the aircraft body 12. The skin panel 22 has a lower edge defined by a lower edge surface 32 extending between the outer surface 26 and the inner surface 28 of the skin panel. The lower edge surface 32... Figure 3 and 4 The middle part is represented as a flat plane. However, the lower edge surface 32 can be a chipping surface or other equivalent surface configuration.

[0032] The aircraft wing 14 has an upper wing skin joint panel 34. The upper wing skin joint panel 34 has a conventional construction. For example, the upper wing skin joint panel 34 is made of a metallic material such as aluminum or titanium, or an equivalent material. A metallic layer 36 defines the upper surface 38 of the aircraft wing 14. Figure 2As shown, the aircraft wing 14 also has a lower surface 42 opposite to the upper surface 38. The lower surface 42 may also have a skin structure similar to that of the lower surface 38 of the aircraft wing.

[0033] like Figure 3 and 4 As shown, the aircraft wing 14 is formed by the over wing Tchord 44 on the upper surface 38 of the aircraft wing. Figure 3 and Figure 4 The upper wing T-chord 44 is schematically shown. The upper wing T-chord 44 extends along a portion of the longitudinal length of the aircraft wing 14. The upper wing T-chord 44 may extend along the entire longitudinal length of the aircraft wing 14. The upper wing T-chord 44 has a lower flange 46 that is secured to the upper surface 38 of the aircraft wing 14. The upper wing T-chord 44 also includes an upstanding leg panel 24 that extends upward from the lower flange 46 of the T-chord 44 and upward from the aircraft wing 14. Figure 2 As shown, the leg panel 24 has a longitudinal length extending from the front edge 52 of the leg panel to the rear edge 54 of the leg panel. The overwing T-chord 44, including the lower flange 46 and the leg panel 24, is made of a metallic material, such as titanium, aluminum, or other equivalent materials. The leg panel 24 has an outer surface 56 facing outwards from the aircraft body 12 and towards the external environment of the aircraft body 12, and an opposing inner surface 58 facing inwards from the aircraft body 12. The inner surface 58 of the leg panel 24 does not necessarily face inwards towards the interior of the aircraft cabin inside the aircraft body 12, but rather towards the interior of the fuselage structure of the aircraft body 12. The leg panel 24 also has an upper edge defined by an upper edge surface 62, which extends between the front edge 52 and the rear edge 54 of the leg panel 24, and between the outer surface 56 and the inner surface 58 of the leg panel 24. The upper edge surface 62... Figure 3 and 4 The upper edge surface 62 is represented as a flat plane. However, the upper edge surface 62 can be a curved surface or other equivalent surface configuration.

[0034] The connector panel 64 is used to form a connector 18 for connecting the aircraft wing 14 to the aircraft body 12. (See reference...) Figure 3 and Figure 4 The diagram schematically illustrates a connector panel 64. The connector panel 64 is made of a composite material or a metallic material (e.g., aluminum or titanium). For example, the connector panel 64 is made of multiple layers of composite material sheets, such as carbon fiber reinforced composite fabric, carbon fiber reinforced composite tape, or a combination of these composite materials.

[0035] Figure 3 and Figure 4The connector panel 64 shown has an outer surface 66 facing the exterior of the aircraft body 12 and its external environment. The connector panel 64 has an inner surface 68 opposite the outer surface 66. The inner surface 68 of the connector panel 64 faces the interior of the aircraft body 12. The inner surface 68 does not necessarily face the interior of the aircraft cabin inside the aircraft body 12, but rather faces the interior of the fuselage structure of the aircraft body 12. The peripheral edge surface 72 of the connector panel 64 extends completely around the connector panel and extends between the outer surface 66 and the inner surface 68 of the connector panel. When constructing the connector connecting the pillar panel 24 to the skin panel 22, the inner surface 68 of the connector panel 64 is configured to engage with the outer surface 56 of the connector panel 24 and the outer surface 26 of the skin panel 22 in a surface-mount manner.

[0036] The connector panel 64 is used to construct a connector 18 for connecting the aircraft wing 14 to the aircraft body 12. In the construction of the connector 18 for connecting the aircraft wing 14 to the aircraft body 12, a pillar panel 24 extending upward from the upper surface 38 of the aircraft wing 14 is vertically positioned near the skin panel 22 on the fuselage of the aircraft body 12. The lower edge surface 32 of the skin panel 22 is directly opposite and above the upper edge surface 62 of the pillar panel 24, thereby maintaining a gap between the lower edge surface 32 and the upper edge surface 62 of the pillar panel 24. The connector panel 64 is attached to the pillar panel 24 and the skin panel 22 by a plurality of fasteners, wherein the plurality of fasteners attach the connector panel 64 to the pillar panel 24 and attach the connector panel 64 to the skin panel 22, thereby attaching the pillar panel 24 to the skin panel 22.

[0037] When attaching the connector panel 64 to the post panel 24, before arranging the skin panel 22 and the post panel 24 in a single vertically oriented plane such that the skin panel 22 is directly above the post panel 24, the lower half of the inner surface 68 of the connector panel 64 is configured to engage with the outer surface 56 of the post panel 24. The connector panel 64 is held in this position relative to the post panel 24 by a mechanical clamp or other equivalent tool.

[0038] Then, drill pairs of vertically spaced fastener holes 74 at the bottom through the connector panel 64 and the post panel 24. Figure 3 and 4The diagram schematically illustrates these lower pairs of vertically spaced fastener holes 74. Lower pairs of vertically spaced fastener holes 74 are drilled through the joint panel 64 and the post panel 24 at longitudinally spaced locations along the longitudinal length of the joint panel 64 and the post panel 24. When the pairs of vertically spaced fastener holes 74 are drilled along the longitudinal length of the joint panel 64 and the post panel 24, fasteners (such as bolts and nuts 76, or other equivalent fasteners) can be inserted through the drilled holes and tightened in them to further hold the joint panel 64 onto the post panel 24.

[0039] After drilling the lower paired vertically spaced fastener holes 74 through the connector panel 64 and the post panel 24, remove all fasteners 76 secured by the drilled holes, and remove the mechanical clamps holding the connector panel 64 and the post panel 24 together. Remove the connector panel 64 from the post panel 24. After removing the connector panel 64 from the post panel 24, it is easy to access the lower paired vertically spaced fastener holes 74 through the post panel 24.

[0040] After removing the connector panel 64 from the post panel 24, a deburring tool is used to deburr the lower paired, vertically spaced fastener holes 74 drilled through the post panel 24. The inlet edges of the lower paired, vertically spaced fastener holes 74 are deburred, and the outlet edges are also deburred. The burr-forming cuts, especially at the outlet edges of the lower paired, vertically spaced fastener holes 74 drilled through the post panel 24, are removed by the deburring tool. This eliminates any potential starting point for cracks to form in the metallic material of the post panel 24. If the connector panel 64 is made of a metallic material such as aluminum or titanium, the outlet holes of the fastener holes 74 drilled through the connector panel 64 can also be deburred.

[0041] The lower half of the inner surface 68 of the connector panel 64 is then configured to engage with the outer surface 56 of the post panel 24, such that the lower paired vertically spaced fastener holes 74 passing through the two panels are aligned. Lower paired threaded fasteners 76 are then inserted through the aligned lower paired vertically spaced fastener holes 74 of the connector panel 64 and the post panel 24. The lower paired fasteners 76 are tightened to attach the connector panel 64 to the post panel 24.

[0042] Then, the skin panel 22 on the fuselage side of the aircraft body 12 is positioned above the pillar panel 24. For example... Figure 3 and Figure 4As shown, the lower edge surface 32 of the skin panel 22 is positioned directly opposite and above the upper edge surface 62 of the column panel 24. A portion of the outer surface 26 of the skin panel 22 is configured to engage with the upper half of the inner surface 68 of the joint panel 64. The joint panel 64 and the skin panel 22 are then held together by a mechanical clamp or other equivalent tool.

[0043] Then, drill pairs of vertically spaced fastener holes 78 through the joint panel 64 and the skin panel 22. Figure 3 and 4 The diagram schematically illustrates a pair of vertically spaced upper fastener holes 78. These upper pairs of vertically spaced fastener holes 78 are drilled through the joint panel 64 and skin panel 22 at longitudinally spaced locations. These fastener holes 78 are vertically aligned with a pair of lower vertically spaced fastener holes 74 and a pair of lower fasteners 76 that attach the joint panel 64 to the post panel 24. When the upper pairs of vertically spaced fastener holes 78 are drilled at longitudinally spaced locations, the upper pairs of fasteners 82 (e.g., bolts and nuts) can be inserted into and tightened to further retain the joint panel 64 on the skin panel 22.

[0044] After drilling the upper paired vertically spaced fastener holes 78 into the joint panel 64 and the skin panel 22, the upper paired threaded fasteners 82 are inserted through the alignment holes in the joint panel 64 and the skin panel 22. The upper paired threaded fasteners 82 are tightened to attach the joint panel 64 to the skin panel 22. A plurality of fasteners 76 extending through the joint panel 64 and the post panel 24, and a plurality of fasteners 82 extending through the joint panel 64 and the skin panel 22, attach the joint panel 64 to the post panel 24 and the skin panel 22, thereby attaching the skin panel 22 to the post panel 24.

[0045] Then, the mechanical clamps that hold the joint panel 64 and the skin panel 22 together are removed, thereby attaching the skin panel 22 to the column panel 24 via the joint panel 64.

[0046] refer to Figure 4 The schematic diagram shows that the lower paired vertically spaced fastener holes 74 drilled through the joint panel 64 and the column panel 24, and the upper paired vertically spaced fastener holes 78 drilled through the joint panel 64 and the skin panel 22, can also extend into the vertically oriented struts 84 of the fuselage frame. The lower paired fasteners 76 and the upper paired fasteners 82 that secure the joint panel 64 to the column panel 24 and the skin panel 22 also secure the joint panel 64 to the struts of the fuselage frame 84. The struts of the fuselage frame 84 are constructed of composite materials or metals such as aluminum or titanium.

[0047] As an alternative to the above-described sequence of attaching the connector panel 64 to the post panel 24 and the skin panel 22, the connector panel 64 can first be attached to the skin panel 22 in the manner described above, and then the connector panel 64 can be attached to the post panel 24, thereby attaching the skin panel 22 to the post panel 24. Other equivalent sequences of attaching the skin panel 22 to the post panel 24 using the connector panel 64 can also be used to attach the post panel 24 to the skin panel 22.

[0048] Reference Figure 2 and Figure 5 The connector panel 64 that secures the pillar panel 24 to the skin panel 22 is the first connector panel. A second connector panel 86 may also be provided, which is attached to the pillar panel 24 and the skin panel 22 in the same manner as the first connector panel 64. The first connector panel 64 and the second connector panel 86 together serve to connect the aircraft wing 14 to the aircraft body 12. A third or more connector panels may also be provided in the connector 18 that connects the aircraft wing 14 to the aircraft body 12.

[0049] exist Figure 3 and Figure 4 The diagram also schematically shows the outer upper wing skin 92, the inner upper wing skin 94, and the fuselage side ribs 96.

[0050] Various modifications may be made to the construction and usage of the joint for connecting an aircraft wing to the aircraft body described and illustrated herein without departing from the scope of this disclosure. Therefore, all matters contained in the foregoing description or shown in the accompanying drawings should be interpreted as illustrative rather than restrictive. Consequently, the breadth and scope of this disclosure should not be limited by any of the exemplary embodiments described above, but should be defined solely by the following claims appended herein and their equivalents.

Claims

1. A connector for connecting an aircraft wing to the aircraft body, the connector comprising: Skin panels on the sides of the aircraft body; A pillar panel extends upward from the lower flange of the upper wing T-chord, wherein the upper wing T-chord includes the pillar panel and the lower flange, and the aircraft wing includes the upper wing T-chord; The connector panel is attached to the column panel and also to the skin panel; and Multiple fasteners extend through the joint panel and the post panel, and further through the joint panel and the skin panel, the multiple fasteners attaching the joint panel to the post panel and the skin panel. Wherein, the column panel and the skin panel are located in a single vertically oriented plane, and in, The column panel has an upper edge; The skin panel has a lower edge; and The lower edge of the skin panel is located directly opposite and above the upper edge of the column panel.

2. The connector according to claim 1, further comprising: The connector panel is surface-mounted to the column panel and surface-mounted to the skin panel.

3. The connector according to claim 1, further comprising: The connector panel is a first connector panel that engages with the column panel and the skin panel; The second connector panel is engaged with the column panel and also with the skin panel; The plurality of fasteners extend through the first joint panel and the post panel and extend through the first joint panel and the skin panel; as well as The plurality of fasteners extend through the second joint panel and the post panel and extend through the second joint panel and the skin panel, the plurality of fasteners attaching the first joint panel to the post panel and attaching the first joint panel to the skin panel, and the plurality of fasteners attaching the second joint panel to the post panel and attaching the second joint panel to the skin panel, thereby attaching the skin panel to the post panel.

4. The connector according to claim 1, further comprising: The plurality of fasteners are removable from the joint panel and the post panel, and from the joint panel and the skin panel, to remove the joint panel from the post panel and the skin panel.

5. The connector according to claim 1, further comprising: The column panel is made of either a metal material or a composite material; The skin panel is made of either a metallic material or a composite material; as well as The connector panel is made of either a metallic material or a composite material.

6. The connector according to claim 1, further comprising: The skin panel is the outer fuselage skin panel.

7. The connector according to claim 1, further comprising: The plurality of fasteners includes a pair of vertically spaced upper fasteners extending through the joint panel and the skin panel, and a pair of vertically spaced lower fasteners extending through the joint panel and the post panel.

8. The connector according to claim 7, further comprising: The paired vertically spaced upper fasteners and the paired vertically spaced lower fasteners are located in a single vertically oriented plane.

9. A connector for connecting an aircraft wing to the aircraft body, the connector comprising: Aircraft body; An aircraft wing has an upper surface and a corresponding lower surface; A skin panel, located on the side of the aircraft body, having an outer surface facing outwards from the aircraft body and opposing inner surfaces facing inwards from the aircraft body; A pillar panel extends upward from the lower flange of the upper wing T-chord, wherein the upper wing T-chord includes the pillar panel and the lower flange, the aircraft wing includes the upper wing T-chord, and the pillar panel has an outer surface facing outward of the aircraft body and opposing inner surfaces facing inward of the aircraft body. A connector panel having an outer surface and an opposing inner surface, the inner surface of the connector panel engaging with the outer surface of the column panel and also engaging with the outer surface of the skin panel; and Multiple fasteners extend through the joint panel and the post panel, and further through the joint panel and the skin panel, the multiple fasteners attaching the joint panel to the post panel and the joint panel to the skin panel, thereby attaching the skin panel to the post panel. The skin panel and the column panel are located in a single vertically oriented plane. And among them, The column panel has an upper edge defined by an upper edge surface that extends between the outer surface of the column panel and the inner surface of the column panel. The skin panel has a lower edge defined by a lower edge surface extending between the outer surface and the inner surface of the skin panel; and The lower edge surface of the skin panel is located directly opposite and above the upper edge surface of the column panel.

10. The connector according to claim 9, further comprising: The inner surface of the connector panel is joined to the outer surface of the column panel by a surface bonding manner, and the inner surface of the connector panel is joined to the outer surface of the skin panel by a surface bonding manner.

11. The connector according to claim 9, further comprising: The connector panel is a first connector panel, which has an outer surface away from the aircraft body and an opposing inner surface. The inner surface of the first connector panel engages with the outer surface of the pillar panel and with the outer surface of the skin panel. The second connector panel has an outer surface away from the aircraft body and an opposing inner surface, the inner surface of the second connector panel engaging with the outer surface of the pillar panel and engaging with the outer surface of the skin panel. as well as The plurality of fasteners extend through the first joint panel and the post panel and extend through the first joint panel and the skin panel, the plurality of fasteners extend through the second joint panel and the post panel and extend through the second joint panel and the skin panel, the plurality of fasteners attach the first joint panel and the second joint panel to the post panel and the skin panel, thereby attaching the skin panel to the post panel.

12. The connector according to claim 9, further comprising: The plurality of fasteners are removable from the joint panel and the post panel, and from the joint panel and the skin panel, to remove the joint panel from the post panel and the skin panel.

13. The connector according to claim 9, further comprising: The column panel is made of either a metal material or a composite material; The skin panel is made of either a metallic material or a composite material; and The connector panel is made of either a metallic material or a composite material.

14. The connector according to claim 9, further comprising: The skin panel is the outer fuselage skin panel.

15. A method for attaching an aircraft wing to the body of an aircraft, the method comprising: The skin panel is positioned on the side of the aircraft body directly opposite and above the pillar panel extending upward from the lower flange of the upper wing T-chord, wherein the upper wing T-chord includes the pillar panel and the lower flange, and the aircraft wing includes the upper wing T-chord. The connector panel is configured to engage with both the column panel and the skin panel; and Multiple fasteners are configured to extend through the joint panel and the post panel, and further through the joint panel and the skin panel, such that the multiple fasteners attach the joint panel to the post panel and the skin panel. The column panel and the skin panel are located in a single vertically oriented plane. Furthermore, the method further includes: The lower edge surface of the skin panel is positioned directly opposite and above the upper edge surface of the column panel.

16. The method of claim 15, further comprising: The joint panel, which engages with the column panel and the skin panel, is positioned above the lower edge of the skin panel and above the upper edge of the column panel. as well as The plurality of fasteners are configured to extend through the joint panel and the post panel and extend through the joint panel and the skin panel, such that the plurality of fasteners attach the joint panel to the post panel and the joint panel to the skin panel above the lower edge of the skin panel and above the upper edge of the post panel.

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