A joint for connecting the center wing box and the bulkhead in an aircraft

Abstract

To provide a quick connection between a center wing box and a fuselage capable of reducing involved space in a factory and assembly cost.SOLUTION: A junction 40 for connecting a center wing box 20 to a partition wall 30 of an aircraft includes a flexible angle member. The flexible angle member comprises: a first section which is formed so as to contact and connect to the center wing box 20; a second section which is formed so as to contact and connect to a first plane of a deck 31 of the partition wall 30; and an intermediate rounded corner arranged between the first and second sections. The center wing box 20 has a first support member attached thereto, and the first plane of the second section of the flexible angle member is supported by the first support member. A web 33 of the partition wall 30 has a second support member attached thereto, the second plane of the second section of the flexible angle member is supported by the second support member.SELECTED DRAWING: Figure 3

Description

[Technical Field]

[0001] The present disclosure relates generally to the field of aircraft, and more particularly to connections between sections of an aircraft. [Background technology]

[0002] An aircraft may include a center wing box located between and connected to the wings. The center wing box is subjected to tension, compression, shear, and torsion stresses due to aerodynamic forces from the wings during flight and due to the weight of the wings and the weight of fuel stored within the wings when the aircraft is on the ground. The center wing box also transmits forces from the wings to the fuselage.

[0003] Aircraft can be manufactured modularly. Different parts of an aircraft are manufactured individually, and then assembled together. For example, the wing assembly can be manufactured separately from the fuselage. During assembly, the nearly complete fuselage is lowered onto the completed wings, and then they are joined together. This increases production speed while reducing factory space and assembly costs. This modular approach requires a secure connection to properly connect the center wing box to the fuselage. Summary of the Invention

[0004] One aspect relates to a joint for connecting a center wing box to a bulkhead in an aircraft, the bulkhead including a web and a deck. The joint includes a flexible angle member having a first section configured to contact and connect to one of the center wing box and the bulkhead, a second section configured to contact and connect to a first side of the deck of the bulkhead, and an intermediate radiused corner disposed between the first and second sections. A first support member is attached to the center wing box with a first pin. A second support member is attached to the web of the bulkhead with a second pin. One of the first support member and the second support member supports the second section of the flexible angle member. The first support member is disposed on a first side of the deck of the bulkhead, and the second support member is disposed on an opposite second side of the deck.

[0005] In another aspect, the first support member supports the second section of the flexible angle member, and the first pin coincides with the center of the radius of the intermediate radiused corner of the flexible angle member.

[0006] In another aspect, the second support member supports the second section of the flexible angle member, and the second pin is positioned at a point coincident with the center of the radius of the rounded corner located at the intersection of the web of the bulkhead and the deck.

[0007] In another aspect, the central wing box has a support fitting attached thereto, and the first support member is attached to the support fitting with the first pin. The bulkhead has a stiffening member attached to the web, and the second support member is attached to the stiffening member with the second pin.

[0008] In another aspect, the first support member and the second support member include lugs with opposing clevises, and the support fitting and the reinforcement member are positioned between the clevises.

[0009] In another aspect, the flexible angle member is made from one of a fiber reinforced composite material and a metallic material.

[0010] In another aspect, a corner fitting is positioned laterally offset from the flexible angle member, the corner fitting including first and second sections oriented at an angle to fit the intersection of the central wing box and the bulkhead, the corner fitting having a different configuration than the flexible angle member and being less flexible than the flexible angle member.

[0011] In another aspect, the flexible angle member is a first flexible angle member that contacts and connects to the center wing box, and the joint further includes a second flexible angle member that contacts and connects to the web and the deck of the bulkhead.

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

[0013] One aspect relates to an aircraft including a fuselage, a wing assembly including a center wing box disposed within the fuselage and wings extending outward from opposite sides of the fuselage, a bulkhead disposed within the fuselage and including a web and a deck, and a joint connecting the center wing box to the bulkhead, the joint including a flexible angle member having a first section connecting to one of the center wing box and the bulkhead, a second section extending across the bulkhead deck, and an intermediate corner disposed between the first and second sections, first support members spaced apart across the width of the fuselage on a first side of the deck, and second support members spaced apart across the width of the fuselage on an opposite second side of the deck, wherein one of the first support member and the second support member contacts the second section of the flexible angle member.

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

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

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

[0017] In another aspect, the flexible angle member is a first flexible angle member attached to the center wing box, and the aircraft further includes a second flexible angle member, the second flexible angle member including a first section attached to the web, a second section disposed across the deck, and radiused intermediate corners.

[0018] In another aspect, the flexible angle member is positioned along the midsection of the fuselage, and the aircraft further includes angled corner fittings laterally offset from the flexible angle member and on either side of the flexible angle member, the angled corner fittings having an angled shape to contact the center wing box and the bulkhead deck, and having a different configuration and less flexibility than the flexible angle member.

[0019] In another aspect, the flexible angle member is a first flexible angle member connected to the center wing box, and the aircraft further includes one or more additional flexible angle members, the additional flexible angle members including a first section connected to the center wing box, a second section extending outward from the center wing box and across the bulkhead deck, and an intermediate corner.

[0020] One aspect relates to a method for connecting a center wing box to a bulkhead of an aircraft, the method including: positioning a middle radiused corner of a flexible angle member at an intersection of the center wing box and the bulkhead, connecting a first section of the flexible angle member to the center wing box, connecting a second section of the flexible angle member to the bulkhead, connecting a first support member to the center wing box and contacting a first face of the second section of the flexible angle member, and connecting a second support member to the bulkhead, overlapping the first and second support members on opposite sides of the bulkhead.

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

[0022] In another aspect, the flexible angle member is a first flexible angle member, and the method further includes connecting a first section of a second flexible angle member to a first section of the partition wall, connecting a second section of the second flexible angle member to a second section of the partition wall, positioning a rounded corner of the second flexible angle member located between the first and second sections at the intersection of the first and second sections of the partition wall, and connecting the second support member to the partition wall with a pin that matches the radius of the rounded corner.

[0023] In another aspect, the method includes attaching a first corner fitting to the central wing box on a first side of the flexible angle member and attaching a second corner fitting to the central wing box on a second side of the flexible angle member, the first corner fitting and the second corner fitting contacting the flexible angle member.

[0024] The above-described features, functions, and advantages can be achieved individually in various embodiments and can also be combined in yet further embodiments, details of which will become apparent with reference to the following description and drawings. [Brief explanation of the drawings]

[0025] [Figure 1] FIG. 1 is a perspective view showing an aircraft. [Figure 2] 1 is a schematic side view of an aircraft fuselage. [Figure 3] FIG. 1 is a partial perspective view of a center wing box attached to a bulkhead at a joint within an aircraft fuselage. [Figure 4] FIG. 10 is a partial perspective view showing the joint connecting the central wing box and the bulkhead. [Figure 4A] FIG. 10 is a side view showing the joint connecting the central wing box and the bulkhead. [Figure 5] FIG. 10 is a schematic side view showing the front flexible angle member. [Figure 6] FIG. 10 is a partial perspective view showing the joint connecting the central wing box and the bulkhead. [Figure 7] FIG. 10 is a perspective schematic view showing a rear flexible angle member. [Figure 7A] FIG. 10 is a schematic side view showing the front flexible angle member. [Figure 8] FIG. 10 is a partial perspective view showing the joint connecting the central wing box and the bulkhead. [Figure 9] 1 is a schematic diagram showing the connection between a support member and a reinforcing member or support fitting. FIG. [Figure 10] FIG. 1 is a flow diagram illustrating a method for connecting a center wing box to a bulkhead of an aircraft. DETAILED DESCRIPTION OF THE INVENTION

[0026] 1, the aircraft 100 includes a fuselage 101 having a nose 109 and a tail 108. A wing assembly 102 includes a center wing box 20 that is positioned between and supports opposing wings 103. The wings 103 carry engines 105 for powering the aircraft during flight. The center wing box 20 is positioned within the fuselage 101 and operatively joins the wing assembly 102 and the fuselage 101.

[0027] 2 is a schematic side view of a fuselage 101 with wings 103 removed for clarity. The fuselage 101 has an elongated shape with a length L extending between a tail 108 and a nose 109. In the example shown in FIG. 2, the fuselage 101 is divided into an upper section 110 and a lower section 111. The upper section 110 includes a cabin area 106 having a floor 104. The upper section 110 includes various components for transporting passengers, such as, but not limited to, seats, overhead storage, restrooms, and various other amenities.

[0028] The lower section 111 is located below the floor 104 of the upper section 110. The lower section 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 bulkhead 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 bay 114, which includes an aft cargo stowage area or aft cargo deck, is located aft of the main landing gear wheel well 113.

[0029] The aircraft design offsets the bulkhead 30 from the center wing box 20 to facilitate the assembly process when the aircraft 100 is manufactured in individual assemblies. This offset arrangement allows for quick joining of the wing and body when the nearly complete fuselage 101 is lowered onto the fully completed wing assembly 102, thereby increasing production rates compared to other designs.

[0030] In the exemplary embodiment, aircraft 100 is a commercial aircraft with upper section 110 configured for passengers and flight crew and lower section 111 configured for cargo stowage and aircraft equipment. Junction 40 connecting center wing box 20 and bulkhead 30 may be used on a variety of other aircraft, including, but not limited to, various commercial and non-commercial aircraft. These aircraft 100 may include the same or different configurations for accommodating cargo and / or passengers.

[0031] 3 shows the forward portion of the center wing box 20. The skin of the fuselage 101 has been removed for clarity. The center wing box 20 includes wing spars, such as a forward spar 21, that extend across the width W of the fuselage 101. Overwing beams 23 are spaced apart across the width W and are aligned substantially perpendicular to the forward spar 21. The center wing box 20 also includes upper and lower skins (not shown). Note that stringers (not shown) may be attached to the skins to provide additional mechanical support.

[0032] The bulkhead 30 is disposed across the entire width W of the fuselage 101. In the example shown in FIG. 3 , the bulkhead 30 is disposed at the bottom 115 of the fuselage 101. In other examples, the bulkhead 30 may be disposed at different heights relative to the bottom 115 of the fuselage 101. The center wing box 20 may be of various sizes and may be disposed at various locations within the fuselage 101. In one example, the center wing box 20 and the bulkhead 30 are both included in the lower portion 111 of the fuselage 101. As shown in the example of FIG. 3 , the height of the bulkhead 30 is limited such that the top 116 of the bulkhead 30 is located below the top of the center wing box 20. This positions the top 116 of the bulkhead 30 along the forward wing spar 21.

[0033] The bulkhead 30 includes panels 32 having a curved shape that matches the substantially rounded cross-sectional shape of the fuselage 101. Horizontal decks 31 form a chord that extends across the entire width W and are attached to either side of the panels 32. The bulkhead 30 also includes vertical walls having webs 33 that extend between the horizontal decks 31 and the underlying panels 32. In one example, the panels 32 are oriented substantially vertically within the fuselage 101. Horizontal stiffeners 34 are attached to the panels 32 to increase their strength.

[0034] As shown in FIGS. 4, 4A, and 5, a front flexible angle member 85 is disposed on the bulkhead 30. The front flexible angle member 85 includes a first section 87, a second section 86, and an intermediate rounded corner 38. The corner 38 has a rounded shape with a radius R1. In the example shown in FIG. 5, the front flexible angle member 85 is separate from the bulkhead 30 and includes a first section 87 that is substantially flat and disposed on the horizontal deck 31, a second section 86 that is substantially flat and disposed on the web 33, and the rounded corner 38. The front flexible angle member 85 may be a single piece or may be formed of two or more pieces integrally attached to each other. In other examples, one or both of the first section 87 and the second section 86 are formed by a portion of the bulkhead 30, for example, but not limited to, the first section being formed by the horizontal deck 31 and the second section being formed by the web 33.

[0035] Corner 38 of front flexible angle member 85 has a radius R1 extending from center point C. Rounded corner 38 positions first section 87 and second section 86 at an angle β in the range of about 85° to about 95°. In one example, angle β is 90°.

[0036] The bulkhead 30 further includes vertical reinforcing members 36 that are attached to and support the web 33. The reinforcing members 36 may be attached to the web 33 in a variety of ways, including, but not limited to, mechanical fasteners, adhesives, and combinations thereof. The vertical reinforcing members 36 may be made from a variety of materials, including, but not limited to, aluminum or titanium.

[0037] Support members 60 are attached to the bulkhead 30 to support the horizontal deck 31. Each support member 60 is attached to the vertical stiffener 36 by a pin 62. The pin 62 coincides with the center point C of the radius R1 of the rounded corner 38. The support members 60 further include a contact edge 61 that contacts and supports the horizontal deck 31 and is located below the horizontal deck. In one example, the contact edge 61 is flat. In other examples, the contact edge 61 has a different shape.

[0038] In the example shown in Figure 9, the support member 60 is formed as a lug 79 having a pair of spaced clevises 77, 78 sized to receive the ends of the vertical reinforcing members 36. The pin passes through each clevis 77, 78 and the vertical reinforcing member 36. In another example, the support member 60 includes a single section that contacts and connects to one side of the vertical reinforcing member 36. As shown in Figure 6, the vertical reinforcing members 36 and support members 60 are interspersed across the width of the bulkhead 30. In the example shown in Figure 6, the spacing is equal across the width of the bulkhead 30.

[0039] A second flexible angle member 50 is attached to the front spar 21 and extends outwardly therefrom. FIGS. 7 and 7A schematically illustrate the flexible angle member 50, which includes a first section 51, a second section 52, and an intermediate rounded corner 53. Both the first section 51 and the second section 52 are substantially flat, and the rounded corner 53 has a radius R2. The first section 51 and the second section 52 are disposed at an angle α ranging from about 85° to about 95°. The flexible angle member 50 has a length L1 measured between opposing ends 54 and 55. In the example shown in FIG. 3, the length L1 extends across the entire width W of the lower portion of the fuselage 101. In the example shown in FIG. 4A, the aft flexible angle member 50 is separate from the center wing box 20. The aft flexible angle member 50 includes a first section 51 positioned relative to the center wing box 20, a second section 52 positioned on the horizontal deck 31, and a radiused corner 53 positioned at the intersection of the forward spar 21 of the center wing box 20 and the horizontal deck 31. The forward flexible angle member 85 may be a single piece or may be formed of two or more pieces integrally attached to one another. In other examples, one or both of the first section 51 and the second section 52 are formed from some of these components, for example, but not limited to, the first section 51 being formed from the forward spar 21 and the second section 52 being formed from the horizontal deck 31.

[0040] In one example, the flexible angle member 50 includes a first section, a second section, and a corner 53 made from a single piece. In another example, the flexible angle member 50 is made from two or more different pieces connected together.

[0041] In one example, one or both of the flexible angle members 50, 85 are made of a fiber-reinforced composite material, such as a carbon fiber reinforced polymer (CFRP) material, or a metal material. Fiber-reinforced composite materials may additionally or alternatively be described or described as fiber-reinforced polymers or fiber-reinforced plastics. As used herein, fiber-reinforced composite materials include fibers, such as (but not limited to) carbon fiber, boron fiber, para-aramid (e.g., Kevlar®) fiber, or other fibers, along with at least an epoxy material, other polymer material, or binder material. In another example, the flexible angle member 50 is made of a metal and / or metal alloy.

[0042] The use of carbon fiber material for one or both of the flexible angle members 50, 85 can reduce corrosion and fatigue cracking compared to metallic materials. In one example, an aircraft design includes a wide fuselage 101 to accommodate a large cabin area 106 in the upper section 110. In one example, the cabin area 106 has a width that accommodates two aisles and three sets of seats per row. The wider fuselage cross-section significantly increases the relative lateral displacement of the wings 103 relative to the fuselage 101. In this case, a design that includes a metallic flexible angle member 50 would be challenging due to the increased strain on the flexible angle member. Carbon fiber material also allows for exposure to moisture that can accumulate in this area of ​​the aircraft 100 and corrode other materials. Furthermore, carbon fiber can better handle the significant cyclic loading experienced during operation of the aircraft 100. Carbon fiber is less susceptible to fatigue cracking. Furthermore, the location of the joint 40 makes access difficult after the aircraft 100 is assembled, requiring design considerations to minimize challenges.

[0043] 8 shows flexible angle members 50 attached at joint 40. Each flexible angle member 50 has its first section 51 positioned on and attached to the forward spar 21. The second section 52 is positioned on and overlaps the horizontal deck 31 of the bulkhead 30. The first and second sections 51, 52 are attached by one or more mechanical fasteners and adhesives. In one example, the second section 52 overlaps the first section 87 of the forward flexible angle member 85.

[0044] The support fitting 56 extends over the first section 51 of the flexible angle member 50 and the leading spar 21 and is secured thereto with adhesive and / or mechanical fasteners. In one example, the support fitting 56 is T-shaped and includes a top member that contacts the leading spar 21 and the first section 51 and a brace that extends outward. Attached to the support fitting 56 is a support member 70.

[0045] The support member 70 is positioned on and attached to the second section 52 of the flexible angle member 50. The support member 70 includes a contact edge 71 that contacts the second section 52 with the horizontal deck 31 or the first section 87. This attachment can be achieved by one or more mechanical fasteners and adhesives. The support member 70 extends outward beyond the second section 52 and onto the horizontal deck 31. In the example shown in FIG. 9, the support member 70 includes a lug 79 with spaced-apart clevises 77 and 78 to receive the support fitting 56. As shown in FIG. 7A, the pin 72 is coincident with the center C of the radius R2 of the rounded corner 53 of the flexible angle member 50.

[0046] By placing the pins 72 at the corners 53, bending of the flexible angle member 50 is minimized, thereby reducing the interlaminar stress and laminate bending strain at radius R2 to levels acceptable for carbon fiber construction.

[0047] A stiffening member 80 is attached to the horizontal deck 31 and / or the first section 87 of the flexible angle member 85. The stiffening member 80 is oriented substantially perpendicular to the support member 70. The stiffening member 80 provides support to prevent buckling of the horizontal deck 31. One or more additional stiffening members 80 are attached to the underside of the horizontal deck 31 (see FIG. 4A).

[0048] As shown in Figures 4 and 4A, the support members 60, 70 are oriented in pairs along the length of the flexible angle members 50, 85. Each pair includes a support member 70 on a first side of the horizontal deck 31 of the bulkhead 30 and a support member 60 on a second, opposite side of the horizontal deck 31. The pairs may be spaced at various intervals along the length of the flexible angle members 50, 85. Additionally, the support members 60, 70 are sized to overlap each other; that is, the distal sections of each support member 60, 70 overlap on both sides of the horizontal deck 31 of the bulkhead 30. This provides additional support to the bulkhead 30.

[0049] The joint 40 formed by the flexible angle member 50 and the support members 60, 70 are both configured to form a pressure seal that seals against pressure differentials between the center wing box 20 and the forward cargo deck 112. In one example, the center wing box 20 is in communication with the main landing gear wheel well 113 and experiences a first level of pressure, while the forward cargo deck 112 has a different second level of pressure. In one example, the forward cargo deck 112 is pressurized during flight. The joint 40 is also configured to provide a continuous load path for shear forces to accommodate movement of the center wing box 20 relative to the bulkhead 30 and / or fuselage 101. Additionally, the joint 40 allows for flexing of the wing assembly 102 relative to the fuselage 101. The flexible joint 40 is lightweight compared to rigid structures that may resist movement and add weight to the aircraft 100.

[0050] In one example, the flexible angle member 50 is a single piece that extends across its entire width. In another example, the flexible angle member 50 is made of two or more separate pieces that each extend across a portion of its width. These separate pieces, when assembled together, extend across the entire width to form the joint 40.

[0051] In one example, the joint 40 includes both a rear flexible angle member 50 and a front flexible angle member 85. In other examples, the joint includes only a single flexible angle member (i.e., only one of the rear flexible angle member 50 or the front flexible angle member 85).

[0052] As shown in Figure 3, the flexible angle member 50 is positioned in the central section of the fuselage 101. In one example, the flexible angle member 50 is centrally positioned along the width W. Corner fittings 90 are positioned on either side of the flexible angle member 50. The corner fittings 90 provide additional support to the flexible angle member 50. The corner fittings 90 provide a substantial shear connection between the central wing box 20 and the horizontal deck 31.

[0053] As best shown in FIG. 8 , the corner fitting 90 has an angled shape including a first section 91 that contacts the forward spar 21 and a second section 92 that contacts the panel 32 of the bulkhead 30. The corner 93 is disposed between the first section 91 and the second section 92 and is located at the intersection of the forward spar 21 and the panel 32. The corner fitting 90 has an angled shape in which the first section 91 and the second section 92 are oriented at an angle between approximately 85° and 95°. The corner fitting 90 has a different configuration than the flexible angle member 50 and is less flexible than the flexible angle member 50. In one example, the corner fitting 90 is made of titanium or aluminum. The corner fitting 90 is attached to another structure using one or more of mechanical fasteners and adhesives.

[0054] One or more support members 70 are connected to the front spar 21 and are positioned at the corner fittings 90. The support members 70 are connected to the support fittings 56 by pins 72 and have lengths that extend to and connect 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 bulkhead 30 by pins 62. The support members 60 extend 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 fittings 90 are arranged in pairs.

[0055] In one example, corner fittings 90 are also positioned against bulkhead 30 to support flexible angle member 85 .

[0056] 10 illustrates a method for connecting the center wing box 20 to the bulkhead 30 of an aircraft 100. The method includes placing a rounded intermediate corner 53 of a flexible angle member 50 at the intersection of the center wing box 20 and the bulkhead (block 160). The method includes connecting a first section 51 of the flexible angle member 50 to the center wing box 20 (block 161) and connecting a second section 52 of the flexible angle member 50 to the bulkhead 30 (block 162). A first support member 70 is connected to the center wing box 20 (block 163). The first support member 70 supports a first face of the second section 52 of the flexible angle member 50. A second support member 60 is connected to the bulkhead 30 (block 164). The second support member 60 supports a second, opposite face of the second section 52.

[0057] The above-described design utilizes a joint 40 connecting the center wing box 20 to the low bulkhead 30, allowing the nearly completed fuselage 101 to be lowered onto the fully completed wing assembly 102 for rapid wing-to-fuselage joining. This increases production speed and reduces factory space and assembly costs. This design also decouples the loads on the wing and fuselage, allowing them to deform independently at the forward spar 21. Furthermore, the above-described design eliminates the cost and weight issues associated with structures that move the wing and fuselage together, which can be expensive and difficult to maintain.

[0058] Apparatus 10 may be used in a variety of aircraft 100, including, but not limited to, a manned aircraft, an unmanned aircraft, a manned spacecraft, an unmanned spacecraft, a manned rotorcraft, an unmanned rotorcraft, a satellite, a rocket, a missile, or a combination thereof.

[0059] The term "substantially" with respect to a quantity or measurement means that the stated characteristic, parameter, or value does not necessarily have to be exactly achieved. Rather, deviations and variations, including, for example, tolerances, measurement errors, measurement accuracy limits, and other factors known to those skilled in the art, may occur to an extent that does not interfere with the effect that is intended to be achieved by the characteristic.

[0060] The present invention may be practiced otherwise than as specifically described herein without departing from its essential characteristics. The embodiments of the present disclosure are to be considered in all respects as illustrative and not restrictive. All changes that come within the meaning and range of equivalency of the claims are embraced within their scope.

Claims

1. 1. In an aircraft, a joint for connecting a center wing box to a bulkhead including a web and a deck, comprising: a flexible angle member including a first section configured to contact and connect to one of the central wing box and the bulkhead, a second section configured to contact and connect to a first surface of the deck of the bulkhead, and an intermediate radiused corner disposed between the first section and the second section; a first support member attached to the central wing box by a first pin; a second support member attached to the web of the bulkhead with a second pin; one of the first support member and the second support member supports the second section of the flexible angle member; A joint, wherein the first support member is disposed on a first side of the deck of the bulkhead and the second support member is disposed on an opposite second side of the deck.

2. 2. The joint of claim 1, wherein the first support member supports the second section of the flexible angle member, and the first pin coincides with a center of radius of the intermediate radiused corner of the flexible angle member.

3. 3. The joint of claim 2, wherein the second support member supports the second section of the flexible angle member, and the second pin is positioned at a point coincident with the center of the radius of the rounded corner located at the intersection of the web of the bulkhead and the deck.

4. further comprising a support fitting and a reinforcement member; the support fitting is attached to the central wing box, and the first support member is attached to the support fitting with the first pin; The joint of any one of claims 1 to 3, wherein the reinforcing member is attached to the web of the bulkhead, and the second support member is attached to the reinforcing member with the second pin.

5. The joint of claim 4 , wherein the first support member and the second support member include lugs having opposing clevises, and the support fitting and the reinforcement member are disposed between the clevises.

6. A joint according to any one of the preceding claims, wherein the flexible angle member is made from one of a fibre reinforced composite material and a metallic material.

7. 7. The joint of claim 6, further comprising a corner fitting, the corner fitting including first and second sections laterally offset from the flexible angle member and oriented at an angle to fit an intersection of the central wing box and the bulkhead, the corner fitting having a different configuration than the flexible angle member and being less flexible than the flexible angle member.

8. 8. The joint of any one of claims 1 to 7, wherein the flexible angle member is a first flexible angle member that contacts and connects to the central wing box, and the joint further comprises a second flexible angle member that contacts and connects to the web and deck of the bulkhead.

9. 9. The joint of claim 1, wherein the first support member and the second support member are oriented in pairs, and the first support member and the second support member of each of the pairs overlap on opposite sides of the horizontal deck.

10. The torso and a wing assembly including a central wing box disposed within the fuselage and wings extending outwardly from opposite sides of the fuselage; a bulkhead disposed within the fuselage and including a web and a deck; a joint connecting the central wing box to the bulkhead, the joint comprising: a flexible angle member including a first section connecting to one of the central wing box and the bulkhead, a second section extending across the deck of the bulkhead, and an intermediate corner disposed between the first section and the second section; first support members spaced apart across the width of the fuselage on a first surface of the deck; second support members spaced apart across the width of the fuselage on an opposite second surface of the deck; One of the first support member and the second support member contacts the second section of the flexible angle member.

11. 11. The aircraft of claim 10, wherein the first support member supports the second section and is attached to the center wing box with a pin located at the center of the corner radius.

12. 12. The aircraft of claim 11, wherein the second support member supports the second section and is attached to the web with a pin located at the center of the corner radius.

13. 13. The aircraft of any one of claims 10 to 12, wherein the first support members and the second support members are oriented in pairs along the width of the fuselage, and the first support member and the second support member of each of the pairs overlap on opposite sides of the deck.

14. 14. The aircraft of any one of claims 10 to 13, wherein the flexible angle member is a first flexible angle member attached to the central wing box, and the aircraft further includes a second flexible angle member, the second flexible angle member including a first section attached to the web, a second section disposed across the deck, and radiused intermediate corners.

15. 15. The aircraft of claim 10, wherein the flexible angle members are positioned along the midsection of the fuselage, and the aircraft further includes angled corner fittings laterally offset from the flexible angle members and on either side of the flexible angle members, the angled corner fittings having an angled shape to contact the deck of the central wing box and the bulkhead, the angled corner fittings having a different configuration and being less flexible than the flexible angle members.

16. 16. The aircraft of any one of claims 10 to 15, wherein the flexible angle member is a first flexible angle member connected to the central wing box, and the aircraft further includes one or more additional flexible angle members, the additional flexible angle members including a first section connected to the central wing box, a second section extending outwardly from the central wing box and across the bulkhead deck, and an intermediate corner.

17. 1. A method for connecting a center wing box to a bulkhead of an aircraft, comprising: disposing intermediate radiused corners of flexible angle members at the intersection of said central wing box and said bulkhead; connecting a first section of the flexible angle member to the central wing box; connecting a second section of the flexible angle member to the bulkhead; a first support member connected to the central wing box and contacting a first surface of the second section of the flexible angle member; connecting a second support member to the bulkhead and overlapping the first and second support members on opposite sides of the bulkhead.

18. 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 center of the radius of the rounded corner.

19. the flexible angle member is a first flexible angle member; connecting a first section of a second flexible angle member to a first section of the bulkhead; connecting a second section of the second flexible angle member to a second section of the bulkhead; disposing a rounded corner of the second flexible angle member located between the first and second sections at an intersection of the first and second sections of the bulkhead; 20. The method of claim 18, further comprising connecting the second support member to the bulkhead with a pin that matches the radius of the rounded corner.

20. 20. The method of any one of claims 17 to 19, comprising attaching a first corner fitting to the central wing box on a first side of the flexible angle member and attaching a second corner fitting to the central wing box on a second side of the flexible angle member, wherein the first corner fitting and the second corner fitting contact the flexible angle member.

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