Fuel dam, aircraft main wing box, aircraft, and method for assembling aircraft main wing

Abstract

To provide fuel dams, an aircraft main wing box, an aircraft, and a method for assembling an aircraft main wing.SOLUTION: A method for assembling an aircraft main wing 12 includes: fastening fuel dams 100 to stringers 18; and fastening the fuel dams to ribs 16. The fuel dam comprises a fuel dam body that defines a channel molded so as to receive one portion of the stringer of the aircraft main wing. The fuel dam body comprises a stringer fastening surface, a rib fastening surface, and a pair of separated flanges 112 that extend from the rib fastening surface and project from the rib fastening surface on both sides of a notch of the rib.SELECTED DRAWING: Figure 3

Description

[Technical Field]

[0001] The present disclosure relates to a fuel dam for an aircraft wing. [Background technology]

[0002] A typical wing structure includes leading and trailing spars, a plurality of spaced-apart ribs extending between the spars, a plurality of stringers spaced-apart and extending across the ribs, and a skin coupled to the stringers. When the wing is used as a fuel tank, a fuel dam may be used at the interface between the stringers and the tank end rib to prevent fuel from passing through the interface, and a fuel dam may be used at the interface between the stringers and the fuel control rib to restrict fuel from passing through the interface. Traditionally, installation of the fuel dam was performed after the wing box was already constructed, requiring engineers to enter the confined spaces of the wing box, making installation difficult and time-consuming. Summary of the Invention

[0003] A fuel dam, an aircraft wing box, an aircraft, and a method for assembling an aircraft wing are disclosed.

[0004] The fuel dam includes a fuel dam body defining a channel shaped to receive a portion of a stringer of an aircraft wing. The fuel dam body includes a stringer attachment surface, a rib attachment surface, and a pair of spaced-apart flanges. The stringer attachment surface defines the channel and is shaped to be attached to a portion of the stringer of the aircraft wing. The rib attachment surface is shaped to be attached to a rib within a cutout in the rib of the aircraft wing. The spaced-apart flanges extend from the rib attachment surface and are positioned to protrude from the rib attachment surface on both sides of the cutout in the rib.

[0005] The aircraft wing box includes spars, ribs, stringers, and fuel dams. The ribs extend between the spars and include cutouts. The stringers extend across the ribs and are partially disposed within the cutouts. The fuel dams are disposed at interfaces between the stringers and the cutouts in at least a subset of the ribs.

[0006] An aircraft comprises a fuselage and wings supported by the fuselage, each wing comprising an aircraft wing box.

[0007] A method for assembling an aircraft wing includes securing a fuel dam to a stringer and securing a fuel dam to a rib. [Brief explanation of the drawings]

[0008] [Figure 1] FIG. 1 is a diagram of an exemplary aircraft. [Figure 2] FIG. 1 is a partial view of an exemplary wing box for an aircraft. [Figure 3] 1 is an isometric view of a portion of an exemplary wing box of an aircraft. [Figure 4] FIG. 1 is an isometric view of an exemplary fuel dam. [Figure 5] FIG. 5 is another isometric view of the fuel dam of FIG. [Figure 6] FIG. 5 is a side view of the fuel dam of FIG. [Figure 7] FIG. 5 is an end view of the fuel dam of FIG. [Figure 8] FIG. 2 is an isometric view of another exemplary fuel dam. [Figure 9] FIG. 9 is another isometric view of the fuel dam of FIG. [Figure 10] FIG. 9 is a side view of the fuel dam of FIG. 8. [Figure 11] FIG. 9 is an end view of the fuel dam of FIG. [Figure 12] 1 is a flow chart that schematically illustrates a method for assembling an aircraft wing. DETAILED DESCRIPTION OF THE INVENTION

[0009] Disclosed herein are an aircraft 10, an aircraft wing box 36 of the aircraft 10, and a method 200 for assembling the aircraft wing 12. As shown schematically in FIG. 1 , the aircraft 10 includes at least a fuselage 11 and wings 12 supported by the fuselage 11. Each wing 12 includes an aircraft wing box 36. As shown schematically in FIG. 2 , the aircraft wing box 36 typically includes leading and trailing spars 14, a plurality of spaced-apart ribs 16 extending between the spars 14, and a plurality of spaced-apart stringers 18 extending across the ribs 16. The ribs 16 include cutouts 22, and the stringers 18 are partially disposed within the cutouts 22 of the ribs 16. The cutouts 22 may also or alternatively be described in the aerospace industry as mouseholes. As shown in Figure 3 and in more detail in Figures 4-11, the aircraft wing box 36 also typically includes fuel dams 100 located at at least a subset of the interfaces 34 between the stringers 18 and the notches 22 in the ribs 16, such as fuel flow control ribs and / or tank end ribs. The fuel dams 100 effectively seal the interfaces 34 to prevent or restrict fuel from passing through the interfaces 34 at the fuel tank boundary or fuel tank baffles.

[0010] Various configurations of stringers 18 may be incorporated into the aircraft wing box 36. Examples include stringers having T-shaped, I-shaped, J-shaped, Z-shaped, and hat-shaped cross sections, as commonly known in the art. In the exemplary assembly of FIG. 3 , an example of a T-shaped stringer 24 and an example of a hat-shaped stringer 30 are shown. However, the present disclosure is not limited to T-shaped and hat-shaped stringers. As shown, the T-shaped stringer 24 includes a base 26 and blades 28 extending from the base 26. Similarly, I-shaped, J-shaped, and Z-shaped stringers may be described as including a base 26. The base 26 is coupled to the skin 20 of the aircraft wing 12. The hat-shaped stringer 30 typically includes two base flanges 32 and a hat portion 35 extending away from and between the base flanges 32. The base flange 32 is coupled to the skin 20 of the aircraft wing 12 .

[0011] Examples of fuel dams 100 are shown in Figures 3-11. Figure 3 shows a portion of an example wing box illustrating an example fuel dam 100 having two different configurations: an example fuel dam used with T-stringers, designated 102, and an example fuel dam used with hat-stringers, designated 120. Figures 4-7 show several views of an example fuel dam 102 used with T-stringers 24, and Figures 8-11 show several views of an example fuel dam 120 used with hat-stringers 30. However, the examples shown in Figures 3-11 are non-exclusive and do not limit the fuel dam 100 to the illustrated embodiments.

[0012] As shown in FIGS. 3-11 , fuel dams 100 according to the present disclosure each include a fuel dam body 104 defining a channel 106 shaped to receive a portion of the stringer 18, such as to fit over the cross-section of the stringer 18. The two exemplary embodiments of the fuel dam 100 shown in FIGS. 3-11 differ primarily with respect to the configuration of the fuel dam body 104 and the channel 106. They are each shaped to accommodate different types of stringers. The fuel dam 102 is configured to accommodate T-shaped stringers, and the fuel dam 120 is shaped to accommodate hat-shaped stringers. In both embodiments, the fuel dam body 104 includes a stringer attachment surface 108, a rib attachment surface 110, and a pair of spaced-apart flanges 112. The stringer attachment surface 108 defines the channel 106 and is shaped to be attached to the portion of the stringer 18 received within the channel 106. The rib bonding surface 110 is shaped to be bonded to the rib 16 within the notch 22 in the rib 16. Spaced flanges 112 extend from the rib bonding surface 110 and are positioned to protrude from the rib bonding surface 110 on either side of the notch 22. The stringers 18 are positioned within the notch 22. As a result, the spaced flanges 112 serve to contain any excess adhesive or sealant squeezed out from between the rib bonding surface 110 and the notch 22 in the rib 16. The fuel dam 100 is installed within the notch 22. In fact, in some embodiments, the containment of any excess adhesive by the spaced flanges 112 may result in no need to remove excess adhesive after installation of the fuel dam 100, resulting in an efficient installation process.

[0013] In some examples, the spaced flanges 112 are generally parallel to one another. In some embodiments, the spaced flanges 112 extend generally perpendicular from the rib attachment surface 110. As used herein, "generally parallel" and "generally perpendicular" mean within 10 degrees of parallel and perpendicular, respectively. The particular orientation of the spaced flanges 112 relative to the remainder of the fuel dam body 104 of a particular fuel dam 100 may be based on the corresponding shapes, dimensions, and configurations of the corresponding ribs 16 and notches 22. When the fuel dam 100 is operably installed, the spaced flanges 112 will be disposed adjacent to the corresponding ribs 16 and notches 22.

[0014] In some embodiments, the fuel dam 100 is monolithic or unitary, i.e., in its final manufactured form, constructed from a single piece of material, as opposed to an assembly of discrete components that are bonded together via fasteners and / or adhesives. For example, the fuel dam 100 may be additively manufactured or molded from a feedstock to form a monolithic body. Alternatively, the fuel dam 100 may be machined from a piece of material to form a monolithic body. Additionally or alternatively, the fuel dam 100 may first be molded or additively manufactured and then machined to finish the final surface of the fuel dam 100. The fuel dam 100 may be constructed from any suitable material depending on the aircraft 10, thereby making the fuel dam 100 compatible with the aircraft fuel. For example, the fuel dam 100 may be constructed from a metal, a plastic material, or a fiber-reinforced plastic material. Similarly, the spars 14, ribs 16, stringers 18, and skin 20 of the aircraft wing 12 may be constructed from a variety of materials, including metal, plastic, and fiber-reinforced plastic, depending on the configuration of the aircraft 10. As one illustrative, non-exclusive example, the fuel dam 100 may be constructed from a nylon material selected to comply with the aircraft's electromagnetic emissions specifications.

[0015] In some embodiments of the fuel dam 100, including the exemplary fuel dam 102 of FIGS. 4-7 , the fuel dam body 104 includes end regions 114 that extend beyond the spaced apart flanges 112 and partially define the channels 106 and the stringer attachment surfaces 108. When present, such end regions 114 provide a larger surface area for the stringer attachment surfaces 108 to be fastened and bonded to the corresponding stringers 18. In some such embodiments, the end regions 114 include fastener holes 116 for operably securing the fuel dam 100 to the corresponding stringers 18. Some such embodiments of the fuel dam 100 may be configured as non-hat fuel dams. Some fuel dams 100 according to the present disclosure lack fastener holes and rely solely on adhesive to be fastened and bonded to the corresponding stringers 18 and corresponding ribs 16.

[0016] 3 and 11 , the fuel dam 100 may include one or more holes 122 extending through the fuel dam body 104. In such an embodiment, the fuel dam 100 may be used as a fuel tank baffle, allowing fuel and / or water to flow or drain from one side of the corresponding rib 16 to the other.

[0017] Referring now to FIG. 12 , a method 200 for assembling an aircraft wing 12 is generally presented. In FIG. 12 , several steps are depicted in dashed boxes, indicating that such steps may be optional or may correspond to optional versions of method 200. That said, not all methods according to the present disclosure need include the steps enclosed in solid lines. The method and steps depicted in FIG. 12 are not limiting, and as will be appreciated from the description herein, other methods and steps are within the scope of the present disclosure, including methods having more or fewer steps than those depicted. Furthermore, the order of steps depicted in FIG. 12 is non-limiting, and the steps of method 200 may be performed in any suitable order.

[0018] As shown generally in FIG. 12 , the method 200 includes securing (202) the fuel dam 100 to the stringer 18 and securing (204) the fuel dam 100 to at least a subset of the ribs 16. In some embodiments of the method 200, securing (202) the fuel dam 100 to the stringer 18 is performed before securing (204) the fuel dam 100 to the ribs 16. In some such embodiments, the stringer 18 may already be coupled to the corresponding skin 20 when the fuel dam 100 is coupled to the stringer 18, or the fuel dam 100 may be secured to the stringer 18, after which the combined stringer 18 and fuel dam 100 may be coupled to the corresponding skin 20. The assembly of the skin 20, stringer 18, and fuel dam 100 may then be coupled to the ribs 16. It includes affixing (204) the fuel dam 100 to the rib 16. Such an embodiment of the method 200 provides for operatively positioning the fuel dam 100 on the stringer 18 in an open environment, which is separated from the remainder of the wing 12 or wing box 36 being assembled, allowing for more ergonomic assembly of the wing 12 than conventional wing assembly methods.

[0019] That is, not all methods 200 require that bonding step 202 be performed before bonding step 204, and in other embodiments of method 200, bonding step 204 is performed before bonding step 202.

[0020] The bonding steps 202 and 204 may utilize any adhesive suitable for the materials of the ribs 16, stringers 18, and fuel dam 100, the corresponding required strength and other specifications of the aircraft wing 12, and that is compatible with aircraft fuel. Exemplary adhesives include two-part, manganese dioxide-cured polysulfide compounds and vulcanizable silicone rubber adhesives. The adhesive may also or alternatively be referred to as a sealant.

[0021] 12 , in some methods 200, the securing step 202 includes securing (206) the fuel dam 100 to the stringer 18 at a predetermined location along the stringer 18. Accordingly, some such methods 200 may further include aligning (228) the fuel dam 100 with respect to the stringer 18 to identify the predetermined location. Proper placement of the fuel dams 100 on the stringer 18 results in the fuel dams 100 being spaced apart from one another by a precise distance relative to the ribs 16.

[0022] Continuing with reference to FIG. 12, in some methods 200, the securing step 204 includes placing 208 the fuel dam 100 within each notch 22 in the rib 16.

[0023] Some methods 200 further include coupling 210 the stringer 18 to the skin 20. In some such methods 200, the coupling step 210 is performed before the securing step 202. As will be explained, such an order of assembly provides for operatively positioning the fuel dam 100 on the stringer 18 in an open environment, which is isolated from the remainder of the wing 12 or wing box 36 being assembled, resulting in a more ergonomic assembly of the wing 12 than conventional wing assembly methods.

[0024] 12 , some methods 200 further include, prior to the bonding step 202, obtaining (212) surface contour data of the stringers 18 and / or obtaining (214) surface contour data of the ribs 16, and then refining (216) a computer model of the fuel dam 100 based on the surface contour data of the stringers 18 and / or the surface contour data of the ribs 16. In some such methods 200, the bonding (210) is performed before the obtaining (212).

[0025] Various techniques may be utilized to acquire the surface contour data. For example, the surface contour data may be acquired from a detailed review of tolerance allocations and / or by reviewing previous manufacturing data to establish statistical boundaries for the fuel dam. Additionally or alternatively, the surface contour data may be acquired by various three-dimensional (3D) scanning techniques, such as time-of-flight laser scanning, triangulation laser scanning, structured light 3D scanning, modulated light 3D scanning, passive stereoscopic 3D imaging, photogrammetric non-contact passive methods, etc. The computer model may be a computer-aided design (CAD) and / or computer-aided manufacturing (CAM) model or file, which may generally be described as a 3D model. The acquiring step 212, the acquiring step 214, and / or the refining step 216 of such method 200 may be described as computer-implemented steps of method 200. Accordingly, such steps of method 200 may be performed or controlled by a controller. The controller is any suitable device or devices configured to perform the recited functions of, i.e., acquiring step 212, acquiring step 214, and / or refining step 216. For example, the controller may include one or more of an electronic controller, a dedicated controller, a special-purpose controller, a personal computer, a special-purpose computer, a display device, a logic device, a memory device, and / or a memory device having a computer-readable medium suitable for storing computer-executable instructions for implementing aspects of the systems and / or methods according to the present disclosure. Additionally or alternatively, the one or more controllers may include or be configured to read non-transitory computer-readable storage, memory, or medium suitable for storing computer-executable instructions, i.e., software, for implementing acquiring step 212, acquiring step 214, and / or refining step 216. Examples of such medium include CD-ROMs, disks, hard drives, flash memory, etc.As used herein, computer-executable instructions and computer-implemented methods and steps according to the present disclosure are deemed to be within the scope of subject matter deemed patentable pursuant to Title 35, Section 101 of the United States Code.

[0026] As one example, the default computer model of the fuel dam 100 may be based on typical final dimensions of the fuel dam 100, or may be based on the largest typical fuel dam 100 for a particular aircraft 10. The refining step 216 manipulates the default computer model based on the obtained surface contour data of the stringer 18 and / or rib 16 to arrive at an updated computer model having desired dimensions for the particular fuel dam 100 based on the particular interface 34 between the particular stringer 18 and the particular rib 16 and based on the desired tolerances. In particular, as shown generally in FIG. 12 , in some methods 200, the refining step 216 includes defining (218) the stringer attachment surface 108 and / or the rib attachment surface 110 of the computer model of the fuel dam 100. That is, the default computer model has corresponding attachment surfaces, but the modeling of one or both of these surfaces is refined based on the obtained surface contour data of the particular stringer 18 and / or the particular rib 16. The particular fuel dam 100 is thereby installed at the corresponding interface 34. In a more particular embodiment, the defining step 218 includes defining (220) the spatial relationship between the stringer attachment surface 108 and the rib attachment surface 110 of the computer model for the particular fuel dam 100.

[0027] 12 , some such methods 200 further include, after the refining step 216, manufacturing 222 the fuel dam 100 based on the computer model. That is, the customized fuel dam 100 is manufactured based on the surface contour data of the stringers 18 and / or ribs 16. The fuel dam 100 thereby meets the appropriate dimensional tolerances of the actual aircraft wing box 36 being assembled.

[0028] In some methods 200, manufacturing 222 includes additively manufacturing the fuel dam 100 based on the computer model. In some methods 200, manufacturing 222 includes subtractively machining the fuel dam 100 based on the computer model. In some such methods 200, the additive manufacturing process may result in a final part having desired dimensions. In other examples, a machining step may be performed after the additive manufacturing step to arrive at the final design dimensions of the fuel dam 100.

[0029] As shown generally in FIG. 12 , in a method 200 that includes positioning (208) a fuel dam 100 within each notch 22 of a rib 16, the positioning step 208 includes positioning (224) a pair of spaced apart flanges 112 of each fuel dam body 104 on either side of the notch 22 of the respective rib 16.

[0030] In some methods 200, securing 204 the fuel dam 100 to the ribs 16 includes containing 226 squeezed adhesive between the pair of spaced apart flanges 112 and each of the ribs 16. That is, as explained, the spaced apart flanges 112 serve to contain any excess adhesive squeezed out from between the rib-securing surface 110 of the fuel dam 100 and the notches 22 in the ribs 16. The fuel dam 100 is installed within the notches 22. Indeed, in some embodiments, the excess adhesive contained by the spaced apart flanges 112 may not need to be removed after installation of the fuel dam 100, resulting in an efficient installation process. Notably, in some methods 200, securing 202 and / or securing 204 do not require removal or cleaning of excess adhesive.

[0031] In embodiments of the method 200 in which the fuel dam 100 includes the end region 114 and the fastener holes 116 extending therethrough, such method 200 may also include securing (230) the fuel dam 100 to the stringer 18 with fasteners extending through the fastener holes 116, as shown schematically in FIG. 12. In other methods 200, no fasteners are used to couple the fuel dam 100 to the stringer 18 and / or the rib 16.

[0032] Illustrative, non-exclusive examples of inventive subject matter according to the present disclosure are described in the following enumerated paragraphs.

[0033] A. A method (200) for assembling an aircraft wing (12), comprising: Securing (202) the fuel dam (100) to the stringer (18); and A method (200) comprising securing (204) the fuel dam (100) to a rib (16).

[0034] A1. The method (200) of paragraph A, wherein securing (202) the fuel dam (100) to the stringer (18) is performed before securing (204) the fuel dam (100) to the rib (16).

[0035] A2. The method (200) of paragraph A, wherein securing (204) the fuel dam (100) to the rib (16) is performed before securing (202) the fuel dam (100) to the stringer (18).

[0036] A3. The method (200) of any one of paragraphs A to A2, wherein securing (202) the fuel dam (100) to the stringer (18) includes securing (206) the fuel dam (100) to the stringer (18) at a predetermined location along the stringer (18).

[0037] A3.1. The method (200) of paragraph A3, further comprising aligning (228) the fuel dam (100) relative to the stringer (18) to identify the predetermined position.

[0038] A4. The method (200) of any one of paragraphs A to A3.1, wherein securing (204) the fuel dam (100) to the ribs (16) includes positioning (208) the fuel dam (100) within each notch (22) of the ribs (16).

[0039] A5. The method (200) of any one of paragraphs A to A4, further comprising coupling (210) the stringer (18) to the skin (20).

[0040] A5.1. The method (200) of paragraph A5, wherein coupling (210) the stringer (18) to the skin (20) is performed before securing (202) the fuel dam (100) to the stringer (18).

[0041] A6. Prior to securing (202) the fuel dam (100) to the stringer (18), obtaining surface contour data of the stringer (18) (212) and / or obtaining surface contour data of the rib (16) (214); and The method (200) of any one of paragraphs A to A5.1, further comprising refining (216) a computer model of the fuel dam (100) based on the surface contour data of the stringer (18) and / or the surface contour data of the rib (16).

[0042] A6.1. The method (200) of paragraph A6, wherein refining (216) the computer model of the fuel dam (100) includes defining (218) a stringer attachment surface (108) and / or a rib attachment surface (110) of the computer model of the fuel dam (100).

[0043] A6.1.1. The method (200) of paragraph A6.1, wherein defining (218) the stringer attachment surface (108) and the rib attachment surface (110) of the computer model of the fuel dam (100) includes defining (220) a spatial relationship between the stringer attachment surface (108) and the rib attachment surface (110).

[0044] A6.2. The method (200) of any one of paragraphs A6 to A6.1.1, further comprising, after refining (216) the computer model of the fuel dam (100), manufacturing (222) the fuel dam (100) based on the computer model.

[0045] A6.2.1. The method (200) of paragraph A6.2, wherein the manufacturing (222) includes additively manufacturing the fuel dam (100) based on the computer model.

[0046] A6.2.2. The method (200) of paragraph A6.2 or 6.2.1, wherein the fabricating (222) includes removing and machining the fuel dam (100) based on the computer model.

[0047] A7. Each fuel dam (100) comprises a fuel dam body (104) defining a channel (106) shaped to receive a portion of a respective stringer (18), the fuel dam body (104) comprising: a stringer attachment surface (108) defining the channel (106) and shaped to be attached to the portion of each stringer (18); a rib attachment surface (110) shaped to be attached to each rib (16) within the notch (22) of each rib (16); and The method (200) of any one of paragraphs A to A6.2.2, comprising a pair of spaced flanges (112) extending from the rib attachment surface (110) and positioned to protrude from the rib attachment surface (110) on either side of the notch (22) of each rib (16).

[0048] A7.1 The method of paragraph A7, wherein the spaced apart flanges (112) are generally parallel to one another.

[0049] A7.2. The method of paragraph A7 or A7.1, wherein the spaced apart flange (112) extends generally perpendicularly from the rib attachment surface (110).

[0050] A7.3. The method of any one of paragraphs A7 to A7.2 when dependent on paragraph A4, wherein positioning (208) the fuel dam (100) includes positioning (224) the pair of spaced apart flanges (112) of each fuel dam body (104) on either side of the notch (22) in the respective rib (16).

[0051] A7.4. The method (200) of any one of paragraphs A to A7.3, wherein securing (204) the fuel dam (100) to the rib (16) includes including (226) an adhesive squeezed between the pair of spaced flanges (112) and the respective rib (16).

[0052] A7.5. The method (200) of any one of paragraphs A7 to A7.4, wherein the fuel dam body (104) has an end region (114) extending beyond the pair of spaced flanges (112), the end region (114) partially defining the channel (106).

[0053] A7.5.1. The method (200) of paragraph A7.5, wherein the end region (114) comprises a fastener hole (116).

[0054] A7.5.1.1. The method (200) of paragraph A7.5.1, further comprising securing (230) the fuel dam (100) to the stringer (18) with a fastener extending through the fastener hole (116).

[0055] A7.6. The method (200) of paragraphs A7 through A7.5.1.1, wherein each fuel dam (100) is a monolithic structure.

[0056] A8. The method (200) of any one of paragraphs A through A7.6, wherein adhering (202) the fuel dam (100) to the stringer (18) does not require removal or cleaning of excess adhesive.

[0057] A9. The method (200) of any one of paragraphs A-A8, wherein adhering (204) the fuel dam (100) to the rib (16) does not require removal or cleaning of excess adhesive.

[0058] A10. The method (200) of any one of paragraphs A through A9 except for paragraph A7.5.1.1, wherein no fasteners are used to couple the fuel dam (100) to the stringer (18).

[0059] A11. The method (200) of any one of paragraphs A-A10, wherein no fasteners are used to couple the fuel dam (100) to the rib (16).

[0060] B. A fuel dam (100) for an aircraft wing (12), comprising: a fuel dam body (104) defining a channel (106) shaped to receive a portion of a stringer (18) of the aircraft wing (12), the fuel dam body (104) comprising: a stringer attachment surface (108) defining the channel (106) and shaped to be attached to the portion of the stringer (18) of the aircraft wing (12); a rib attachment surface (110) shaped to be attached to the rib (16) of the aircraft wing (12) within the notch (22) of the rib (16); and The fuel dam (100) includes a pair of spaced flanges (112) extending from the rib attachment surface (110) and positioned to protrude from the rib attachment surface (110) on either side of the notch (22) in the rib (16).

[0061] B1. The fuel dam (100) of paragraph B, wherein the spaced apart flanges (112) are generally parallel to one another.

[0062] B2. The fuel dam (100) of paragraphs B or B1, wherein the spaced apart flange (112) extends generally perpendicularly from the rib attachment surface (110).

[0063] B3. The fuel dam (100) of any one of paragraphs B to B2, wherein the fuel dam (100) is a monolithic structure.

[0064] B4. The fuel dam (100) of any one of paragraphs B to B3, wherein the fuel dam body (104) has an end region (114) extending beyond the pair of spaced flanges (112), the end region (114) partially defining the channel (106).

[0065] B4.1. The fuel dam (100) of paragraph B4, wherein the end region (114) comprises a fastener hole (116).

[0066] B5. The fuel dam (100) of any one of paragraphs B to B4, wherein the fuel dam (100) is devoid of fastener holes.

[0067] B6. Use of the fuel dam (100) of any one of paragraphs B to B5 to seal the interface between the stringer (18) and the rib (16).

[0068] C. An aircraft wing box (36), comprising: digit(14), a rib (16) extending between the spars (14) and having a notch (22); a stringer (18) extending across the rib (16) and partially disposed within the notch (22); and An aircraft wing box (36) comprising a plurality of fuel dams (100) according to any one of paragraphs B to B5, disposed at interfaces (34) between the stringers (18) and the notches (22) of at least a subset of the ribs (16).

[0069] D. An aircraft (10), fuselage (11), and An aircraft (10) comprising wings (12) supported by said fuselage (11), each wing (12) comprising an aircraft wing box (36) of paragraph C.

[0070] As used herein, the terms "adapted" and "configured" mean that an element, component, or other object is designed and / or intended to perform a given function. Thus, the use of the terms "adapted" and "configured" should not be interpreted to mean that a given element, component, or other inventive subject matter is merely "capable of" performing a given function, but rather that the element, component, and / or other inventive subject matter has been specifically selected, created, implemented, utilized, programmed, and / or designed for the purpose of performing that function. It is within the scope of this disclosure that elements, components, and / or other described subject matter that are described as adapted to perform a particular function may additionally or alternatively be described as being configured to perform that function, and vice versa. Similarly, subject matter that is described as being configured to perform a particular function may additionally or alternatively be described as being operable to perform that function.

[0071] As used herein, the term “and / or” placed between a first entity and a second entity means one of: (1) the first entity, (2) the second entity, and (3) the first entity and the second entity. Multiple items listed with “and / or” should be construed in the same manner, i.e., one or more of the entities so conjoined. Other entities may optionally be present (whether related or unrelated to such specifically identified entities) other than the entity specifically identified by the “and / or” clause. Thus, as a non-limiting example, when used in conjunction with open-ended language such as “comprising,” a reference to “A and / or B” may refer in one embodiment to A only (optionally including entities other than B), in another embodiment to B only (optionally including entities other than A), or in yet another embodiment to both A and B (optionally including other entities). Such entities may be elements, actions, structures, steps, processes, values, and the like.

[0072] The various disclosed elements of the apparatus and steps of the methods disclosed herein are not required for all apparatus and methods according to the present disclosure; the present disclosure includes all novel and inventive combinations and subcombinations of the various elements and steps disclosed herein. Moreover, one or more of the various elements and steps disclosed herein may define independent inventive subject matter that is distinct and separate from the entirety of the disclosed apparatus or method. Thus, such inventive subject matter need not be associated with the particular apparatus and methods explicitly disclosed herein, and may also find utility in apparatus and / or methods not explicitly disclosed herein.

Claims

1. A method (200) for assembling an aircraft wing (12), comprising: Securing (202) the fuel dam (100) to the stringer (18); and A method (200) comprising securing (204) the fuel dam (100) to a rib (16).

2. 2. The method of claim 1, wherein securing the fuel dam to the stringer is performed before securing the fuel dam to the rib.

3. 2. The method of claim 1, wherein securing the fuel dam to the rib is performed before securing the fuel dam to the stringer.

4. 4. The method of claim 1, wherein securing the fuel dam to the stringer comprises securing the fuel dam to the stringer at a predetermined location along the stringer.

5. The method (200) of claim 4, further comprising aligning (228) the fuel dam (100) relative to the stringer (18) to identify the predetermined location.

6. 2. The method of claim 1, wherein securing the fuel dam to the rib includes disposing the fuel dam within a notch in each of the ribs.

7. The method (200) of claim 1, further comprising coupling (210) the stringer (18) to a skin (20).

8. 8. The method of claim 7, wherein coupling the stringer to the skin is performed before affixing the fuel dam to the stringer.

9. Prior to securing (202) the fuel dam (100) to the stringer (18), Obtaining surface contour data of the stringer (18) (212) and / or obtaining surface contour data of the rib (16) (214); and 10. The method of claim 1, further comprising refining a computer model of the fuel dam based on the surface contour data of the stringer and / or the surface contour data of the rib.

10. 10. The method of claim 9, wherein refining the computer model of the fuel dam includes defining a stringer attachment surface and / or a rib attachment surface of the computer model of the fuel dam.

11. 11. The method of claim 10, wherein defining the stringer attachment surface and the rib attachment surface of the computer model of the fuel dam comprises defining a spatial relationship between the stringer attachment surface and the rib attachment surface.

12. 10. The method of claim 9, further comprising, after refining the computer model of the fuel dam, manufacturing the fuel dam based on the computer model.

13. 13. The method of claim 12, wherein the manufacturing comprises additively manufacturing the fuel dam based on the computer model.

14. The method (200) of claim 12, wherein the fabricating (222) comprises subtractively machining the fuel dam (100) based on the computer model.

15. Each fuel dam (100) comprises a fuel dam body (104) defining a channel (106) shaped to receive a portion of a respective stringer (18), said fuel dam body (104) comprising: a stringer attachment surface (108) defining the channel (106) and shaped to be attached to the portion of each stringer (18); a rib attachment surface (110) shaped to be attached to each rib (16) within the notch (22) of each rib (16); and 2. The method (200) of claim 1, further comprising a pair of spaced flanges (112) extending from the rib attachment surface (110) and positioned to protrude from the rib attachment surface (110) on either side of the notch (22) of each rib (16).

16. 16. The method of claim 15, wherein securing the fuel dam to the ribs includes including an adhesive squeezed between the pair of spaced apart flanges and the respective ribs.

17. The method (200) of claim 15, wherein each fuel dam (100) is a monolithic structure.

18. 2. The method of claim 1, wherein no fasteners are used to couple the fuel dam to the stringer and no fasteners are used to couple the fuel dam to the rib.

19. A fuel dam (100) for an aircraft wing (12), comprising: a fuel dam body (104) defining a channel (106) shaped to receive a portion of a stringer (18) of the aircraft wing (12), the fuel dam body (104) comprising: a stringer attachment surface (108) defining the channel (106) and shaped to be attached to the portion of the stringer (18) of the aircraft wing (12); a rib attachment surface (110) shaped to be attached to a rib (16) of the aircraft wing (12) within a notch (22) of the rib (16); and a pair of spaced flanges (112) extending from the rib attachment surface (110) and positioned to protrude from the rib attachment surface (110) on either side of the notch (22) in the rib (16).

20. An aircraft wing box (36), comprising: digit (14), a rib (16) extending between said spars (14) and provided with a notch (22); a stringer (18) extending across the rib (16) and partially disposed within the notch (22); and 20. An aircraft wing box (36) comprising a plurality of fuel dams (100) according to claim 19, disposed at interfaces (34) between the stringers (18) and the notches (22) of at least a subset of the ribs (16).

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