Joint for connecting a central wing box and a compartment in an aircraft

Abstract

A joint for connecting a center wing box and a bulkhead of an aircraft. The joint includes a curved corner member having a first portion shaped to abut against and connect to the center wing box, a second portion shaped to abut against and connect to a first side of a deck of the bulkhead, and an intermediate rounded corner portion between the first and second portions. A first support member is attached to the center wing box at a first pin and supports a first side of the second portion of the curved corner member. A second support member is attached to a web of the bulkhead at a second pin and supports a second side of the second portion of the curved corner member. The first support member is positioned on the first side of the deck of the bulkhead and the second support member is positioned on the second, opposing side of the deck.

Description

TECHNICAL FIELD

[0001] The present invention relates generally to the field of aircraft, and in particular to connections between portions of an aircraft. BACKGROUND

[0002] An aircraft can include a central wing box located between and connected to the wings. The central wing box is subjected to stresses such as tension, compression, shear, and torsion due to aerodynamic forces from the wings when in flight, and due to the weight of the wings themselves and fuel contained within the wings when the aircraft is on the ground. In addition, the central wing box transmits forces from the wings to the fuselage.

[0003] An aircraft can be manufactured in a modular fashion. Different portions of the aircraft can be manufactured separately and then brought together for assembly. For example, a wing assembly can be manufactured separately from the fuselage. During assembly, a substantially complete fuselage is lowered onto a complete wing, and they are then connected together. This can enable high production rates and save on factory space and assembly costs. This modular approach requires a secure connection of the central wing box to the fuselage. SUMMARY

[0004] One aspect relates to a joint for an aircraft for connecting a central wing box and a bulkhead, the bulkhead including a web and a deck. The joint includes a curved corner member including a first portion shaped to abut against and connect to one of the central wing box and the bulkhead, a second portion shaped to abut against and connect to a first side of the deck of the bulkhead, and an intermediate rounded corner portion between the first portion and the second portion. A first support member is attached to the central wing box at a first pin. A second support member is attached to the web of the bulkhead at a second pin. One of the first support member and the second support member supports the second portion of the curved corner member. The first support member is positioned on the first side of the deck of the bulkhead and the second support member is positioned on a second, opposite side of the deck.

[0005] In another aspect, the first support member supports the second portion of the curved corner member, and the first pin coincides with a center of a radius of the intermediate rounded corner portion of the curved corner member.

[0006] In another aspect, the second support member supports the second portion of the curved corner member, and the second pin is positioned at a point that coincides with a center of a radius of the rounded corner portion at an intersection of the web and the deck of the bulkhead.

[0007] In another aspect, a support fitting is attached to the central wing box, wherein the first support member is mounted to the support fitting by the first pin; and a stiffener is mounted to the web of the bulkhead, wherein the second support member is mounted to the stiffener by the second pin.

[0008] In another aspect, the first and second support members comprise a brace having opposing U-shaped clips, and the support fitting and the stiffener are located between the U-shaped clips.

[0009] In another aspect, the curved corner member is comprised of one of a fiber reinforced composite material and a metallic material.

[0010] In another aspect, the corner fitting is laterally offset from the curved corner member, and the corner fitting comprises a first portion and a second portion oriented at an angle to fit at the intersection of the central wing box and the bulkhead, wherein the corner fitting comprises a different structure than the curved corner member and is less flexible than the curved corner member.

[0011] In another aspect, the curved corner member is a first curved corner member, and the first curved corner member abuts against and is connected to the central wing box, and further comprising a second curved corner member that abuts against and is connected to the deck of the bulkhead.

[0012] In another aspect, the first and second support members are oriented in pairs, with the first and second support members of each pair overlapping on opposite sides of the horizontal deck.

[0013] One aspect relates to an aircraft, comprising: a fuselage; a wing assembly comprising a central wing box located in the fuselage and wings extending outward from opposite sides of the fuselage; a bulkhead located within the fuselage and comprising a deck and a web; and a joint connecting the central wing box to the bulkhead. The joint comprises: a curved corner member comprising a first portion connected to one of the central wing box and the bulkhead, a second portion extending over the deck of the bulkhead, and an intermediate corner located between the first portion and the second portion; a first support member spaced apart across a width of the fuselage on a first side of the deck; and a second support member spaced apart across the width of the fuselage on an opposite second side of the deck, and one of the first and second support members contacts against the second portion of the curved corner member.

[0014] In another aspect, the first support member supports the second portion, and the first support member is attached to the central wing box by a pin located at a center of a radius of the corner.

[0015] In another aspect, the second support member supports the second portion and is attached to the web by a pin located at a center of a radius of the corner.

[0016] In another aspect, the first and second support members are oriented in pairs along the width of the fuselage, wherein the first and second support members of each pair overlap on opposite sides of the deck.

[0017] In another aspect, the curved corner member is a first curved corner member attached to the central wing box and further comprising a second curved corner member having a first portion attached to the web, a second portion positioned on the deck, and an intermediate rounded corner portion.

[0018] In another aspect, the curved corner member is positioned along a central portion of the fuselage and further comprises angled corner portion fittings laterally offset from the curved corner member and on opposite sides of the curved corner member, the angled corner portion fittings having an angled shape to contact against the central wing box and the deck of the compartment and comprising a different structure than the curved corner member and less flexible than the curved corner member.

[0019] In another aspect, the curved corner member is a first curved corner member attached to the central wing box and further comprising one or more additional curved corner members comprising a first portion attached to the central wing box, a second portion extending outward from the central wing box and extending on the deck of the compartment, and an intermediate corner portion.

[0020] One aspect relates to a method of connecting a central wing box and a compartment of an aircraft. The method comprises positioning an intermediate rounded corner portion of a curved corner member at an intersection of the central wing box and the compartment; connecting a first portion of the curved corner member to the central wing box; connecting a second portion of the curved corner member to the compartment; connecting a first support member to the central wing box and contacting a first side of the second portion of the curved corner member; and connecting a second support member to the compartment and overlapping the first support member and the second support member on opposite sides of the compartment.

[0021] In another aspect, the method comprises connecting the first support member to the central wing box with a first pin located at a center of a radius of the rounded corner portion.

[0022] In another aspect, the curved corner member is a first curved corner member and further comprising connecting a first portion of a second curved corner member to a first portion of the compartment; connecting a second portion of the second curved corner member to a second portion of the compartment; positioning a rounded corner portion of the second curved corner member at an intersection of the first portion and the second portion of the compartment, the rounded corner portion being between the first portion and the second portion; and connecting a second support member to the compartment with a pin coinciding with a center of a radius of the rounded corner portion.

[0023] In another aspect, the method comprises attaching a first corner portion fitting to the central wing box on a first lateral side of the curved corner member and attaching a second corner portion fitting to the central wing box on a second lateral side of the curved corner member, wherein the first corner portion fitting and the second corner portion fitting abut against the curved corner member.

[0024] The features, functions, and benefits discussed can be implemented independently in various examples or combinations thereof, further details of which can be seen with reference to the following description and drawings. BRIEF DESCRIPTION OF DRAWINGS

[0025] Figure 1 is a perspective view of an aircraft.

[0026] Figure 2 is a schematic side view of an aircraft fuselage.

[0027] Figure 3 is a partial perspective view of a central wing box attached to a compartment at a joint within an aircraft fuselage.

[0028] Figure 4A is a partial perspective view of a joint connecting a central wing box and a compartment.

[0029] Figure 4B is a side view of a joint connecting a central wing box and a compartment.

[0030] Figure 5 is a schematic side view of a forward curved corner member.

[0031] Figure 6 is a partial perspective view of a joint connecting a central wing box and a compartment.

[0032] Figure 7A is a schematic side view of a forward curved corner member.

[0033] Figure 7B is a perspective view of an aft curved corner member.

[0034] Figure 8 is a partial perspective view of a joint connecting a central wing box and a compartment.

[0035] Figure 9 is a schematic view of a connection of a support member and a reinforcement or support fitting.

[0036] Figure 10 is a flowchart of a method of connecting a central wing box of an aircraft with a compartment. DETAILED DESCRIPTION

[0037] As shown in Figure 1 , the aircraft 100 includes a fuselage 101 having a nose 109 and a tail 108. A wing assembly 102 includes a central wing box 20 positioned between and supporting opposing wings 103. Engines 105 are connected to the wings 103 to provide power to the aircraft during flight. The central wing box 20 is positioned in the fuselage 101 and operatively joins the wing assembly 102 with the fuselage 101.

[0038] Figure 2A schematic side view of the fuselage 101 is shown, with the wings 103 removed for clarity. The fuselage 101 includes an elongated shape having a length L extending between a tail 108 and a nose 109. In one example as shown, the fuselage 101 is divided into an upper portion 110 and a lower portion 111. The upper portion 110 includes a cabin area 106 having a floor 104. The upper portion 110 includes various components for transporting passengers, such as but not limited to seats, overhead stowage bins, lavatories, and various other amenities. Figure 2

[0039] The lower portion 111 is located below the floor 104 of the upper portion 110. The lower portion 111 includes a forward cargo deck 112 for holding cargo on either the right or left side of the fuselage 101. A center wing box 20 is located aft of the forward cargo deck 112. The center wing box 20 is connected to the compartment 30 at a joint 40 located aft of the forward cargo deck 112. A main landing gear wheel well 113 is located immediately aft of the center wing box 20. A lower aft cargo hold 114, including an aft cargo deck, is located aft of the main landing gear wheel well 113.

[0040] When the aircraft 100 is manufactured in separate components, the aircraft is designed with the compartment 30 offset from the center wing box 20 to facilitate the assembly process. This offset positioning facilitates quick wing-to-fuselage engagement when the substantially complete fuselage 101 is lowered onto the fully complete wing assembly 102. This supports higher production rates than other designs. In the embodiment shown, the aircraft 100 is a commercial aircraft with the upper portion 110 configured for passengers and crew, and the lower portion 111 configured for cargo storage and aircraft equipment. The joint 40 connecting the center wing box 20 and the compartment 30 is also applicable to various other aircraft, including but not limited to various commercial and non-commercial aircraft. These aircraft 100 can include the same or different configurations for storing cargo and / or passengers.

[0041] Figure 3 A front portion of the center wing box 20 is shown. The outer skin of the fuselage 101 is removed for clarity. The center wing box 20 includes crossbeams extending across the width W of the fuselage 101, including a front beam 21. Overwing beams 23 are spaced apart across the width W and are oriented substantially perpendicular to the front beam 21. The center wing box 20 also includes upper and lower skins (not shown). Longitudinal beams (not pictured) can be connected to the skins to provide additional mechanical support.

[0042] The compartment 30 is positioned across the width W of the fuselage 101. In one example as shown, the compartment 30 is located aft of the center wing box 20. The compartment 30 is connected to the center wing box 20 at a joint 40. The joint 40 is located at the aft end of the compartment 30. The joint 40 is configured to allow the compartment 30 to move relative to the center wing box 20. In one example, the joint 40 is configured to allow the compartment 30 to move vertically relative to the center wing box 20. In another example, the joint 40 is configured to allow the compartment 30 to move vertically and laterally relative to the center wing box 20. Figure 3 ​In one example shown, the compartment 30 is located at the bottom 115 of the fuselage 101. Other examples can include compartments 30 having different heights relative to the bottom 115 of the fuselage 101. The center wing box 20 can also include various sizes and be positioned at various locations within the fuselage 101. In one example, both the center wing box 20 and the compartment 30 are contained within the lower portion 111 of the fuselage 101. As Figure 3 In the example shown, the compartment 30 has a limited height with the top 116 of the compartment 30 located below the top of the center wing box 20. This orients the top 116 of the compartment 30 along the front spar 21.

[0043] The compartment 30 includes a stringer 32 having a curved shape that conforms to the generally circular cross-sectional shape of the fuselage 101. A horizontal deck 31 is formed on the stringer 32 and attached to a chord plate extending on opposite sides of the width W. The compartment 30 also includes a vertical wall including a web 33 extending between the horizontal deck 31 and the lower stringer 32. In one example, the stringer 32 is oriented substantially vertically within the fuselage 101. A horizontal stiffener 34 is attached to the stringer 32 and provides additional strength to the stringer.

[0044] As Figure 4A , Figure 4B and Figure 5 shown, a front curved corner member 85 is located at the compartment 30. The front curved corner member 85 includes a first portion 86, a second portion 87, and an intermediate circular corner portion 38. The corner portion 38 includes a circular shape having a radius R1. In one example as Figure 5 shown, the front curved corner member 85 is separate from the compartment 30 and includes a first portion 86 that is substantially flat to be positioned above the horizontal deck 31, a second portion 87 that is substantially flat to be positioned above the web 33, and includes the circular corner portion 38. The front curved corner member 85 can be a single piece or formed from two or more pieces that are integrally connected together. In other examples, one or both of the first portion 86 and the second portion 87 are formed from portions of the compartment 30 including, but not limited to, the first portion being formed from the horizontal deck 31 and the second portion being formed from the web 33.

[0045] The corner portion 38 of the front curved corner member 85 includes a radius R1 extending from a center point C. The circular corner portion 38 positions the first portion 86 and the second portion 87 at an angle β in a range between about 85° and about 95°. In one example, the angle β is 90°.

[0046] The compartment 30 also includes vertical stiffeners 36 attached to and providing support for the web 33. The stiffeners 36 are attached to the web 33 in various ways including, but not limited to, mechanical fasteners, adhesives, and combinations thereof. The vertical stiffeners 36 can be constructed from various materials including, but not limited to, aluminum and titanium.

[0047] The support members 60 are attached to the compartment 30 and provide support for the horizontal deck 31. Each support member 60 is attached to the vertical stiffener 36 at a pin 62. The pin 62 coincides with the center point C of the radius Rl of the rounded corner 38. The support member 60 also includes a contact edge 61 that contacts against and supports the underside of the horizontal deck 31. In one example, the contact edge 61 is flat. In other examples, the contact edge 61 includes a different shape.

[0048] In one example as shown in FIG. 1, the support members 60 are formed as a single piece that extends across the width of the compartment 30. In other examples, the support members 60 are formed as two separate pieces that are attached to the vertical stiffeners 36 at the pins 62. Figure 9 In one example as shown in FIG. 2, the support members 60 are formed as a brace 79 having a pair of spaced apart U-shaped clips 77, 78 sized to receive the end of the vertical stiffener 36. A pin extends through each U-shaped clip 77, 78 and through the vertical stiffener 36. In another example, the support members 60 include a single piece that abuts against and is connected to one side of the vertical stiffener 36. As shown in FIG. 3, the vertical stiffener 36 and the support member 60 extend across the width of the compartment 30. In one example as shown in FIG. 4, the support members 60 are formed as a single piece that extends across the width of the compartment 30. Figure 6 Figure 6 In one example as shown in FIG. 5, the support members 60 are spaced equally across the width of the compartment 30.

[0049] The second curved corner member 50 is attached to and extends outwardly from the front spar 21. Figure 7A Figure 7B The curved corner member 50 is shown schematically as including a first portion 51, a second portion 52, and an intermediate rounded corner 53. The first and second portions 51, 52 are substantially flat and the rounded corner 53 has a radius R2. The first and second portions 51, 52 are oriented at an angle a that can be in a range between about 85°-95°. The curved corner member 50 includes a length LI measured between opposite ends 54, 55. In one example as shown in FIG. 6, the length LI is sized to extend across the width W of the lower portion of the fuselage 101. In one example as shown in FIG. 7, the curved corner member 50 is separate from the central wing box 20. The curved corner member 50 includes the first portion 51 positioned against the central wing box 20, the second portion 52 positioned on the horizontal deck 31, and the rounded corner 53 positioned at the intersection of the front spar 21 and the horizontal deck 31 of the central wing box 20. The front curved corner member 85 can be a single piece or formed from two or more pieces that are integrally connected together. In other examples, one or both of the first and second portions 51, 52 are formed from these components, including but not limited to the first portion 51 formed from the front spar 21 and the second portion 52 formed from the horizontal deck 31. Figure 3 Figure 4B In one example as shown in FIG. 8, the curved corner member 50 is formed as a single piece that extends across the width of the compartment 30. In other examples, the curved corner member 50 is formed as two separate pieces that are attached to the vertical stiffeners 36 at the pins 62.

[0050] ​​​In one example, the curved corner members 50 include first and second portions and a corner portion 53 that are comprised of a single piece. In other examples, the curved corner members 50 are comprised of two or more different pieces that are connected together.

[0051] In one example, one or both of the curved corner members 50, 85 are comprised of a fiber-reinforced composite material or a metallic material, such as a carbon fiber reinforced polymer (CFRP) material. The fiber-reinforced composite material can additionally or alternatively be described or referred to as a fiber-reinforced polymer or plastic. As used herein, fiber-reinforced composite material is understood to include at least an epoxy or other polymer or binding material with fibers, such as (but not limited to) carbon fibers, boron fibers, para-aramid (e.g., Kevlar® fibers), and / or other fibers. In other examples, the curved corner members 50 are comprised of a metal and / or metal alloy. ) In one example, the curved corner members 50 are comprised of a carbon fiber reinforced polymer (CFRP) material. In other examples, the curved corner members 50 are comprised of a metal and / or metal alloy.

[0052] The carbon fiber material used in one or both of the curved corner members 50, 85 provides for lower corrosion and fatigue cracking as compared to metallic materials. In one example, the aircraft design includes a fuselage 101 that is wide enough to accommodate a large cabin area 106 in the upper portion 110. In one example, the cabin area 106 has a width that accommodates a double aisle and three sets of seats in each row. The relatively wide fuselage cross section results in a significantly higher relative lateral displacement of the wings 103 with respect to the fuselage 101, which presents a challenge to designs that include metallic curved corner members 50 due to the high strain levels introduced to the curved corner members. The carbon fiber material is also able to be exposed to moisture that can accumulate in this area of the aircraft 100 and cause corrosion of other materials. Additionally, the carbon fiber is better able to handle the significant cyclic loads that are generated during operation of the aircraft 100. Carbon fiber is less prone to fatigue cracking. Furthermore, the location of the joints 40 makes it difficult to access after assembly of the aircraft 100, so design considerations that minimize these issues are of interest.

[0053] Figure 8 The curved corner members 50 are shown installed at the joints 40. For each curved corner member 50, the first portion 51 is positioned against and attached to the front spar 21. The second portion 52 is located on and overlaps the horizontal deck 31 of the bulkhead 30. The first and second portions 51, 52 are attached with one or more mechanical fasteners and adhesive. In one example, the second portion 52 overlaps the first portion 87 of the forward curved corner member 85.

[0054] A support fitting 56 extends over the front spar 21 and the first portion 51 of the curved corner member 50 and is secured to them with adhesive and / or mechanical fasteners. In one example, the support fitting 56 is T-shaped and has a top member that contacts against the front spar 21 and the first portion 51 and has a brace that extends outwardly. A support member 70 is attached to the support fitting 56.

[0055] A support member 70 is positioned and attached to the second portion 52 of the curved angle member 50. The support member 70 includes a contact edge 71 that contacts the second portion 52 and the horizontal deck 31 or the first portion 87. This attachment may be formed by one or more mechanical fasteners and adhesives. The support member 70 has a length extending outward beyond the second portion 52 and extending onto the horizontal deck 31. Figure 9 In one example shown, the support member 70 includes a support 79 with U-shaped clips 77 and 78, which are spaced apart and receive a support fitting 56. Figure 7A As shown, pin 72 coincides with the center C of radius R2 of the circular corner portion 53 of the curved corner member 50.

[0056] The position of pin 72 at corner 53 minimizes the bending of the bending corner member 50. This reduces the interlaminar stress and lamination bending stress in radius R2 to an acceptable level for carbon fiber structures.

[0057] A stiffener 80 is attached to the first portion 87 of the horizontal deck 31 and / or the bend angle member 85. The stiffener 80 is oriented substantially perpendicular to the support member 70. The stiffener 80 provides support to prevent buckling of the horizontal deck 31. One or more additional stiffeners 80 are attached to the underside of the horizontal deck 31 (see [link to documentation]). Figure 4B ).

[0058] like Figure 4A and Figure 4B As shown, the support members 60 and 70 are oriented in pairs along the lengths of the bend members 50 and 85. Each pair includes a support member 70 on a first side of the horizontal deck 31 of the compartment 30 and a support member 60 on a second side opposite to the horizontal deck 31. These pairs may be spaced apart at various intervals on the bend members 50 and 85. The lengths of the support members 60 and 70 also cause them to overlap each other. That is, the distal portions of each support member 60 and 70 overlap on opposite sides of the horizontal deck 31 of the compartment 30. This provides additional support for the compartment 30.

[0059] The joint 40, formed by the bending angle member 50 and the support members 60, 70, is configured to provide a pressure seal that seals the pressure difference between the center wing box 20 and the forward cargo deck 112. In one example, the center wing box 20 communicates with the landing gear wheel well 113 and experiences a first pressure level, while the forward cargo deck 112 has a different second pressure level. In one example, the forward cargo deck 112 is pressurized during flight. The joint 40 is also configured to provide a shear continuous load path to accommodate movement of the center wing box 20 relative to the bulkhead 30 and / or the fuselage 101. Furthermore, the joint 40 allows the wing assembly 102 to bend relative to the fuselage 101. The flexible nature of the joint 40 makes it lighter than other rigid structures that would resist movement and increase the weight of the aircraft 100.

[0060] In one example, the bent corner member 50 is a single part extending across the width. In other examples, the bent corner member 50 consists of two or more separate parts, each extending across a finite portion of the width. When assembled, the separate parts extend across the entire width to form a joint 40.

[0061] In one example, connector 40 includes a rear bend corner member 50 and a front bend corner member 85. In another example, connector includes only a single bend corner member (i.e., either only the rear bend corner member 50 or only the front bend corner member 85).

[0062] like Figure 3 As shown, the bend angle member 50 is located in the central portion of the fuselage 101. In one example, the bend angle member 50 is centered along the width W. A corner fitting 90 is located on the lateral side of the bend angle member 50. The corner fitting 90 provides further support for the bend angle member 50. The corner fitting 90 provides a substantial shear connection between the central wing box 20 and the horizontal deck 31.

[0063] like Figure 8 As shown, the corner fitting 90 is an angled shape comprising a first portion 91 that contacts and abuts against the front beam 21 and a second portion 92 that contacts and abuts against the slats 32 of the compartment 30. A corner portion 93 is located between the first portion 91 and the second portion 92, and at the intersection of the front beam 21 and the slats 32. The corner fitting 90 is angled, with the first portion 91 and the second portion 92 oriented at an angle in the range of approximately 85°–95°. The corner fitting 90 includes a different structure from the bent corner member 50 and is less flexible than the bent corner member 50. In one example, the corner fitting 90 is made of titanium or aluminum. The corner fitting 90 is attached to other structures by one or more of mechanical fasteners and adhesives.

[0064] One or more support members 70 are connected to the front beam 21 and positioned on the corner fitting 90. The support member 70 is connected to the support fitting 56 by a pin 72, and has a length extending over and connecting to each of the second section 92 and the horizontal deck 31. Similarly, one or more support members 60 are connected to the web 33 of the compartment 30 by a pin 62. The support member 60 extends outward from the web 33 on the second side of the horizontal deck 31. In one example, the support members 60, 70 aligned with the corner fitting 90 are oriented in pairs.

[0065] In one instance, the corner fitting 90 is also positioned against the compartment 30 to support the curved corner member 85.

[0066] Figure 10 A method for connecting a center wing box 20 to a compartment 30 of an aircraft 100 is shown. The method includes positioning a central rounded corner 53 of a curved corner member 50 at the junction of the center wing box 20 and the compartment (frame 160). The method includes connecting a first portion 51 of the curved corner member 50 to the center wing box 20 (frame 161) and a second portion 52 of the curved corner member 50 to the compartment 30 (frame 162). A first support member 70 is connected to the center wing box 20 (frame 163). The first support member 70 supports a first side of the second portion 52 of the curved corner member 50. A second support member 60 is connected to the compartment 30 (frame 164). The second support member 60 supports a second side of the second portion 52 opposite to its original position.

[0067] The design disclosed above, featuring a connector 40 that connects the center wing box 20 to the lower compartment 30, allows for rapid engagement of the wing and fuselage, with the substantially complete fuselage 101 being lowered onto the fully complete wing assembly 102. This enables higher productivity and saves factory space and assembly costs. This design also decouples the wing and fuselage loads, allowing them to deform independently at the front spars 21. Furthermore, this design offers cost and weight improvements because it eliminates structures that force the wing and fuselage to move simultaneously, structures that are expensive and potentially have maintenance issues.

[0068] Device 10 can be used on various aircraft 100. Aircraft 100 includes, but is not limited to, manned aircraft, unmanned aircraft, manned spacecraft, unmanned spacecraft, manned rotorcraft, unmanned rotorcraft, satellites, rockets, missiles, and combinations thereof.

[0069] The term "substantially" in relation to a quantity or measurement means that the feature, parameter, or value does not need to be precisely achieved. Rather, deviations or variations may occur on the order of magnitude, including, for example, tolerances, measurement errors, measurement accuracy limitations, and other factors known to those skilled in the art, which may not preclude the effect that the feature is intended to provide.

[0070] The invention may be practiced in ways other than those specifically set forth herein without departing from its essential characteristics. These embodiments are to be considered illustrative rather than restrictive in all respects, and all variations within the meaning and equivalence of the appended claims are intended to be included therein.

Claims

1. An aircraft connector for connecting a center wing box and a compartment, the compartment including a web and a deck, the connector comprising: The curved corner member includes a first portion formed to abut and connect to one of the central wing box and the compartment, a second portion formed to abut and connect to a first side of the deck of the compartment, and includes an intermediate rounded corner located between the first portion and the second portion; The first support member is attached to the central wing box at the first pin; as well as The second support member is attached to the web of the compartment at the second pin; One of the first support member and the second support member supports the second portion of the bending angle member; and The first support member is positioned on the first side of the deck of the compartment, and the second support member is positioned on the second side opposite to the deck.

2. The connector according to claim 1, wherein, The first support member supports the second portion of the curved corner member, and the first pin coincides with the radius center of the intermediate circular corner portion of the curved corner member.

3. The connector according to claim 2, wherein, The second support member supports the second portion of the curved corner member, and the second pin is positioned at a point coinciding with the radius center of the intermediate circular corner, which is located at the junction of the web and the deck of the compartment.

4. The connector according to claim 1, further comprising: A support fitting is attached to the central wing box, wherein the first support member is mounted to the support fitting via the first pin; and A reinforcing member is mounted on the web of the compartment, wherein the second support member is mounted to the reinforcing member via the second pin.

5. The connector according to claim 4, wherein, The first support member and the second support member include supports with opposing U-shaped clamps, and the support fitting and the reinforcement are located between the U-shaped clamps.

6. The connector according to claim 1, wherein, The curved corner member is made of either a fiber-reinforced composite material or a metallic material.

7. The connector of claim 6 further includes a corner fitting laterally offset from the curved corner member, and the curved corner member includes a first portion and a second portion oriented at an angle for fitting at the junction of the central wing box and the compartment, the corner fitting having a different structure from the curved corner member, and the corner fitting being less flexible than the curved corner member.

8. The connector according to claim 1, wherein, The curved corner member is a first curved corner member, which abuts against and is connected to the central wing box, and also includes a second curved corner member, which abuts against and is connected to the web of the deck and the compartment.

9. The connector according to claim 1, wherein, The first support member and the second support member are oriented in pairs, with the first support member and the second support member in each pair overlapping on opposite sides of the horizontal deck.

10. An aircraft comprising: body; The wing assembly includes a central wing box located in the fuselage and wings extending outward from opposite sides of the fuselage; A compartment, located within the fuselage, includes the belly and deck; as well as A connector, which connects the central wing box to the compartment, the connector comprising: The curved corner member includes a first portion connected to one of the central wing box and the compartment, a second portion extending on the deck of the compartment, and includes an intermediate corner portion located between the first portion and the second portion; The first supporting member is spaced apart on the first side of the deck across the width of the fuselage; and The second support member is spaced apart from the fuselage on the second side opposite to the deck. One of the first support member and the second support member contacts and abuts against the second portion of the bending angle member.

11. The aircraft according to claim 10, wherein, The first support member supports the second part, and the first support member is attached to the central wing box by a pin located at the radial center of the intermediate corner.

12. The aircraft according to claim 11, wherein, The second support member supports the second portion, and the second support member is attached to the web by the pin located at the radial center of the intermediate corner.

13. The aircraft according to claim 10, wherein, The first support member and the second support member are oriented in pairs along the width of the fuselage, wherein the first support member and the second support member in each pair overlap on opposite sides of the deck.

14. The aircraft according to claim 10, wherein, The curved corner member is a first curved corner member attached to the central wing box, and also includes a second curved corner member having a first portion attached to the web, a second portion positioned on the deck, and having a central rounded corner portion.

15. The aircraft according to claim 10, wherein, The curved corner member is positioned along the central portion of the fuselage and includes angled corner fittings that are laterally offset from the curved corner member and located on opposite sides of the curved corner member. The angled corner fittings have angled shapes to contact and abut the deck of the central wing box and the compartment, and the angled corner fittings have a different structure from the curved corner member and are less flexible than the curved corner member.

16. The aircraft according to claim 10, wherein, The curved corner member is a first curved corner member connected to the central wing box, and also includes one or more additional curved corner members, the additional curved corner members including a first portion connected to the central wing box, a second portion extending outward from the central wing box and extending on the deck of the compartment, and a middle corner portion.

17. A method for connecting a center wing box of an aircraft to a compartment, the method comprising: Position the middle circular corner of the curved corner component at the intersection of the central wing box and the compartment; Connect the first portion of the curved corner member to the central wing box; Connect the second part of the curved corner member to the compartment; The first support member is connected to the central wing box and contacts the first side of the second part of the curved corner member; as well as The second support member is connected to the compartment, and the first support member and the second support member overlap on opposite sides of the compartment.

18. The method of claim 17, further comprising connecting the first support member to the central wing box using a first pin located at the radius center of the intermediate circular corner portion.

19. The method according to claim 18, wherein, The bending angle member is a first bending angle member, and also includes: Connect the first part of the second curved corner member to the first part of the compartment; Connect the second part of the second curved angle member to the second part of the compartment; Position the rounded corner portion of the second curved corner member located between the first and second portions at the intersection of the first and second portions of the compartment; and The second support member is connected to the compartment by a pin whose radius center coincides with the circular corner portion of the second curved corner member.

20. The method of claim 17, further comprising attaching a first corner fitting to the central wing box on a first lateral side of the curved corner member, and attaching a second corner fitting to the central wing box on a second lateral side of the curved corner member, wherein, The first corner fitting and the second corner fitting abut against the curved corner member.

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