Aircraft wing structure

Abstract

An aircraft wing includes a central wing section having a continuous structure extending beyond a first side of an aircraft fuselage and beyond a second side of the aircraft fuselage. The aircraft wing also includes a first outboard wing section attached to a first end of the central wing section by a first truss system accessible via a first closure panel. The first end of the central wing section is on a first side of the aircraft fuselage. The aircraft wing also includes a second outboard wing section attached to a second end of the central wing section by a second truss system accessible via a second closure panel. The second end of the central wing section is on a second side of the aircraft fuselage.

Description

Technical Field

[0001] The present disclosure relates generally to aircraft and, more particularly, to wing structures for aircraft. Background Art

[0002] This background section is provided for the purpose of generally presenting the context of the present disclosure. Unless otherwise indicated herein, what is described in this section is neither explicitly nor implicitly admitted to be prior art to the present disclosure or the appended claims.

[0003] A low monoplane typically includes a structural joint (e.g., a wing joint) near one side of the fuselage where a center section of the aircraft wing is connected to an aircraft wing box. The aircraft wing box is typically a load-bearing structure of the aircraft wing that serves as an attachment point for other wing components, such as leading edge flaps, trailing edge flaps, and wingtip devices. Because the aircraft wing box is close to the fuselage, the center section of the aircraft wing may be relatively small. As a result, many internal structures and systems associated with engines and fuel management are located outside of the center section of the aircraft wing, where space is relatively limited. Summary of the invention

[0004] The present application relates to an improved aircraft wing structure. Specifically, according to the technology described herein, the central section of the aircraft wing has a continuous structure, and the wing joint of the aircraft wing is located outside the engine. By constructing the aircraft wing so that the wing joint is located outside the engine, internal structures and systems related to the engine and fuel management can be included in the central section of the aircraft wing. In addition, by constructing the aircraft wing so that the wing joint is located outside the engine, fewer interfaces (e.g., stringers) are required to carry loads through the outer wing sections, so that the number of fasteners can be reduced. In some embodiments, the central section of the aircraft wing can have large openings and closing panels to enable aircraft personnel to access very large portions of the central section.

[0005] An aircraft wing can be attached to an aircraft fuselage using a self-aligning interface. The primary loads of an aircraft wing on the fuselage are vertical (e.g., in an "upward" direction), with maneuvering loads and landing loads acting as the primary driving forces. The opposing maneuvering loads associated with the aircraft fuselage are less than the primary loads of the aircraft wing. Therefore, a self-aligning interface can transfer large loads through features of the interface (e.g., structural design features) rather than relying solely on fasteners.

[0006] In one aspect, the present application discloses an aircraft structure. The aircraft structure includes an aircraft wing. The aircraft wing includes: a central wing section having a continuous structure extending beyond a first side of the aircraft fuselage and extending beyond a second side of the aircraft fuselage. The aircraft wing also includes: a first outboard wing section attached to a first end of the central wing section by a first truss system accessible via a first closure panel. The first end of the central wing section is on the first side of the aircraft fuselage. The aircraft wing also includes: a second outboard wing section attached to a second end of the central wing section by a second truss system accessible via a second closure panel. The second end of the central wing section is on the second side of the aircraft fuselage.

[0007] In another aspect, the present application discloses a method of manufacturing an aircraft structure. The method includes attaching a first outer wing section of an aircraft wing to a first end of a center wing section of the aircraft wing by a first truss system accessible via a first closing panel. The center wing section has a continuous structure extending beyond a first side of the aircraft fuselage and extending beyond a second side of the aircraft fuselage. The first end of the center wing section is on the first side of the aircraft fuselage. The method also includes attaching a second outer wing section of the aircraft wing to a second end of the center wing section by a second truss system accessible via a second closing panel. The second end of the center wing section is on the second side of the aircraft fuselage. The method also includes mounting a first engine to the center wing section and mounting a second engine to the center wing section. The first outer wing section is located outboard of the first engine, and the second outer wing section is located outboard of the second engine.

[0008] In another aspect, the present application discloses an aircraft. The aircraft includes: a fuselage and an aircraft wing. The aircraft wing includes: a central wing section having a continuous structure extending beyond a first side of the fuselage and extending beyond a second side of the fuselage. The aircraft wing also includes: a first outboard wing section attached to a first end of the central wing section by a first truss system accessible via a first closing panel. The first end of the central wing section is on the first side of the aircraft fuselage. The aircraft wing also includes: a second outboard wing section attached to a second end of the central wing section by a second truss system accessible via a second closing panel. The second end of the central wing section is on the second side of the aircraft fuselage. The aircraft also includes a first engine mounted to the central wing section and a second engine mounted to the central wing section. The first outboard wing section is located outboard of the first engine, and the second outboard wing section is located outboard of the second engine.

[0009] The foregoing summary is illustrative only and is not intended to be limiting in any way. In addition to the illustrative aspects, embodiments, and features described above, further aspects, embodiments, and features will become apparent by reference to the drawings and the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] A more complete understanding of embodiments of the present application may be obtained by referring to the detailed description and claims when considered in conjunction with the following drawings, wherein like reference numerals may refer to similar elements throughout the drawings. The drawings are provided to facilitate understanding of the present disclosure and do not limit the breadth, scope, scale, or applicability of the present disclosure. The drawings are not necessarily drawn to scale.

[0011] Figure 1 shows an aircraft including a fuselage and an aircraft wing having a continuous central section extending beyond the fuselage according to an exemplary embodiment;

[0012] Figure 2 shows a portion of an aircraft wing according to an exemplary embodiment;

[0013] Figure 3 showing a bottom portion of an aircraft wing on a first side of a fuselage according to an exemplary embodiment;

[0014] Figure 4 showing a bottom portion of an aircraft wing on a second side of a fuselage according to an exemplary embodiment;

[0015] Figure 5 shows a truss system for attaching a center wing section of an aircraft wing to an outboard wing section of an aircraft wing according to an exemplary embodiment;

[0016] Figure 6 Another truss system for attaching a center wing section of an aircraft wing to an outboard wing section of an aircraft wing is shown in accordance with an exemplary embodiment;

[0017] Figure 7 shows a process of constructing and attaching an aircraft wing to a fuselage according to an exemplary embodiment;

[0018] Figure 8 shows a bottom view of a center wing section of an aircraft wing according to an exemplary embodiment;

[0019] Fig. 9 shows a process for attaching an aircraft wing to a fuselage according to an exemplary embodiment;

[0020] Fig.10 Another process for attaching an aircraft wing to a fuselage is shown in accordance with an exemplary embodiment;

[0021] Fig.11 Another process for attaching an aircraft wing to a fuselage is shown according to an exemplary embodiment; and

[0022] Fig.12A flow chart showing an example of an implementation method according to an exemplary embodiment is shown. DETAILED DESCRIPTION

[0023] The accompanying drawings and the following description illustrate specific exemplary embodiments. It should be understood that, although not explicitly described or shown herein, a person skilled in the art will be able to design a variety of arrangements that embody the principles described herein, and these arrangements are included within the scope of the claims that follow this description. In addition, any embodiments described herein are intended to help understand the principles of the present disclosure and are interpreted as not constituting limitations on the present disclosure. Therefore, the present disclosure is not limited by the specific embodiments or embodiments described below, but by the claims and their equivalents.

[0024] Specific implementations are described herein with reference to the accompanying drawings. In the description, the same feature may be represented by the same reference numeral throughout the drawings. In some drawings, multiple embodiments of a particular type of feature are used. Although the features are physically and / or logically different, the same reference numeral is used for each feature, and different embodiments are distinguished by adding letters to the reference numerals. When features mentioned herein appear as a group or a type (for example, when a specific feature among multiple features is not mentioned), the reference numeral is used without a distinguishing letter. However, when a specific feature among multiple features of the same type is referenced herein, the reference numeral is used with a distinguishing letter. For example, see Figure 1 , an engine is shown and associated with reference numeral 110. When referring to a specific one of the engines, such as engine 110A, a distinguishing letter "A" is used. However, when referring to any one of the engines or the engines as a group, reference numeral 110 may be used without a distinguishing letter.

[0025] As used herein, multiple terms are only used to describe the purpose of specific implementations and are not intended to be restrictive. For example, unless the context clearly indicates otherwise, the singular forms "one", "an" and "the" are intended to also include plural forms. In addition, the terms "including" and "comprising" can be used interchangeably. In addition, the term "wherein" and the term "wherein" can be used interchangeably. As used herein, "exemplary" indicates an embodiment, implementation and / or aspect, and should not be interpreted as limiting or indicating a preference or preferred implementation. As used herein, ordinal terms (e.g., "first", "second", "third", etc.) used to modify elements (such as structures, components, operations, etc.) do not indicate any priority or order of the element relative to another element, but only distinguish the element from another element with the same name (but for the use of ordinal terms). As used herein, the term "set" refers to the grouping of one or more elements, and the term "plurality" refers to multiple elements.

[0026] See also Figure 1 , shows an aircraft 100 according to an exemplary embodiment, comprising a fuselage and an aircraft wing having a continuous central section extending beyond the fuselage. Figure 1 In the embodiment of the invention, the aircraft 100 is a low-wing aircraft. For example, the aircraft 100 has wings below the fuselage.

[0027] For illustration, aircraft 100 includes an aircraft fuselage 102. Aircraft fuselage 102 may correspond to a main body section of aircraft 100. Aircraft fuselage 102 may accommodate crew members, passengers, cargo, etc. Aircraft 100 also includes aircraft wings 104. Figure 1 As shown, the aircraft wing 104 is attached to the aircraft fuselage 102 in such a manner that the aircraft wing 104 is located below the aircraft fuselage 102 .

[0028] The aircraft wing 104 includes a center wing section 106. The center wing section 106 has a continuous structure that extends beyond a first side 120A of the aircraft fuselage 102 and extends beyond a second side 120B of the aircraft fuselage 102. The aircraft wing 104 also includes a first outboard wing section 108A attached to a first end 122A of the center wing section 106 and a second outboard wing section 108B attached to a second end 122B of the center wing section 106. The first end 122A of the center wing section 106 is on the first side 120A of the aircraft fuselage 102, and the second end 122B of the center wing section 106 is on the second side 120B of the aircraft fuselage 102. As described below, the first outboard wing section 108A may be provided by a first truss system (e.g., Figure 7 The first truss system 500A) is attached to the first end 122A of the center wing section 106, which can be connected via a first closing panel (e.g., Figure 3 The closure panel 302A) is close to the first truss system, and the second outboard wing section 108B can be closed by the second truss system (e.g., Figure 7 The second truss system 500B) is attached to the second end 122B of the center wing section 106, which can be connected via a second closing panel (e.g., Figure 4 The closing panel 302B) is close to the second truss system.

[0029] The aircraft 100 also includes a first engine 110A mounted to the center wing section 106 of the aircraft wing 104 and a second engine 110B mounted to the center wing section 106 of the aircraft wing 104. Thus, the first outboard wing section 108A is outboard of the first engine 110A and the second outboard wing section 108B is outboard of the second engine 110B.

[0030] By constructing the aircraft wing 104 so that the outboard wing sections 108 are outboard of the engines 110, internal structures and systems associated with the engines 110 and fuel management may be included within the continuous center wing section 106 of the aircraft wing 104. As described below, the center wing section 106 may have a large opening and a closure panel that enables aircraft personnel to access a very large portion of the center wing section 106 to perform maintenance operations on various aircraft systems. In addition, by using a continuous center wing section 106 that extends beyond the aircraft fuselage 102, fewer interfaces (e.g., stringers) are required to carry loads through the outboard wing sections 108, which may reduce the number of fasteners. For example, due to the continuity of the center wing section 106, the center wing section 106 may carry relatively large loads with a reduced number of fasteners compared to a smaller center wing section that does not extend beyond the aircraft fuselage 102.

[0031] refer to Figure 2 , a portion of an aircraft wing 104 is shown in accordance with an exemplary embodiment. Figure 2 The portion of the aircraft wing 104 in φ may correspond to the portion of the aircraft wing 104 on the first side 120A of the aircraft fuselage 102 or the portion of the aircraft wing 104 on the second side 120B of the aircraft fuselage 102 .

[0032] exist Figure 2 In FIG. 1 , the center wing section 106 of the aircraft wing 104 has a continuous structure extending beyond the aircraft fuselage 102. The outboard wing sections 108 are attached to the ends 122 of the center wing section 106. Figure 5 As depicted, the outboard wing sections 108 may be attached to the end 122 of the center wing section 106 via a truss system 500 .

[0033] By constructing the aircraft wing 104 so that the outboard wing sections 108 are outboard of the engines 110, internal structures and systems associated with the engines 110 and fuel management may be included within the continuous center wing section 106 of the aircraft wing 104. As described below, the center wing section 106 may have a large opening and a closure panel that enables aircraft personnel to access a very large portion of the center wing section 106 to perform maintenance operations on different aircraft systems. In addition, by using a continuous center wing section 106 that extends beyond the aircraft fuselage 102, fewer interfaces (e.g., stringers) are required to carry loads through the outboard wing sections 108, which may reduce the number of fasteners. For example, due to the continuity of the center wing section 106, the center wing section 106 may carry relatively large loads with a reduced number of fasteners compared to a smaller center wing section that does not extend beyond the aircraft fuselage 102.

[0034] refer to Figure 3 , illustrates a bottom portion of aircraft wing 104 at first side 120A of aircraft fuselage 102 according to an exemplary embodiment.

[0035] exist Figure 3 In FIG. 1 , the first end 122A of the center wing section 106 of the aircraft wing 104 is attached to the first outboard wing section 108A of the aircraft wing 104 . Figure 3 A closure panel 302A is also depicted. Closure panel 302A may enable access to a first truss system (such as the first appearance of Figure 5 ), a first truss system attaches the central wing section 106 of the aircraft wing 104 to the first outboard wing section 108A of the aircraft wing 104 .

[0036] Reference Figure 4 , shows a bottom portion of aircraft wing 104 at second side 120B of aircraft fuselage 102 according to an exemplary embodiment.

[0037] exist Figure 4 In FIG. 1 , the second end 122B of the central wing section 106 of the aircraft wing 104 is attached to the second outboard wing section 108B of the aircraft wing 104 . Figure 3 A closure panel 302B is also depicted. Closure panel 302B may enable access to a second truss system (such as a second occurrence). Figure 5 ), the second truss system attaches the central wing section 106 of the aircraft wing 104 to the second outboard wing section 108B of the aircraft wing 104 .

[0038] refer to Figure 5 , shows a truss system 500 for attaching the center wing section 106 of the aircraft wing 104 to the outboard wing section 108 of the aircraft wing 104 according to an exemplary embodiment. The truss system 500 is an arrangement of a plurality of struts configured in a triangular shape. Specifically, the truss system 500 is a triangular system formed by connecting a plurality of straight and interconnected structural elements (e.g., members or struts) at nodes. External forces applied to the truss system 500 and reaction forces at the supports are generally applied at the nodes. When the outboard wing section 108 corresponds to the outboard wing section 108A on the first side 120A of the aircraft fuselage 102, the truss system 500 can be accessed through the closing panel 302A. For example, the truss system 500 can be accessed through the access panel opening 590 associated with the closing panel 302A. Alternatively, the truss system 500 may be accessed through the closure panel 302B when the outboard wing section 108 corresponds to the outboard wing section 108B on the second side 120B of the aircraft fuselage 102. For example, the truss system 500 may be accessed through an access panel opening 590 associated with the closure panel 302B.

[0039] The truss system 500 includes one or more stringers 502 (e.g., a plurality of stringers 502) extending along the aircraft wing 104. The stringers 502, or stiffeners, may correspond to thin strips of material or spars that extend spanwise along the aircraft wing 104 and are attached to the ribs of the aircraft wing 104. Because the center wing section 106 is coupled to the outboard wing sections 108, the center wing section 106 and the outboard wing sections 108 may include a plurality of stringers 502 coupled together by the spars 504, 506 as described below.

[0040] The truss system 500 also includes one or more front spars 504. The front spars 504 are coupled to a plurality of stringers 502 extending along a top portion of the aircraft wing 104 and along a bottom portion of the aircraft wing 104. To couple the center wing section 106 to the outboard wing sections 108, the one or more front spars 504 of the truss system 500 are coupled to a plurality of stringers 502 extending along the center wing section 106 of the aircraft wing 104 and to a plurality of stringers 502 extending along the outboard wing sections 108 of the aircraft wing 104. Figure 5 As shown, the front spar 504 may include components coupled together via fasteners. The components of the spar 504 may be constructed from metal, wood, or composite materials.

[0041] The truss system 500 also includes one or more rear spars 506. The rear spars 506 are coupled to a plurality of stringers 502 extending along a top portion of the aircraft wing 104 and along a bottom portion of the aircraft wing 104. To couple the center wing section 106 to the outboard wing sections 108, the one or more rear spars 506 of the truss system 500 are coupled to a plurality of stringers 502 extending along the center wing section 106 of the aircraft wing 104 and to a plurality of stringers 502 extending along the outboard wing sections 108 of the aircraft wing 104. Figure 5 As shown, the rear spar 506 may include components coupled together via fasteners. The components of the spar 506 may be constructed from metal, wood, or composite materials.

[0042] Loads may be transferred along one or more stringers 502 , one or more front spars 504 , and one or more rear spars 506 of the truss system 500 .

[0043] refer to Figure 6 , shows another truss system 600 for attaching the center wing section 106 of the aircraft wing 104 to the outboard wing sections 108 of the aircraft wing 104 according to an exemplary embodiment. In one embodiment, the truss system 600 may correspond to Figure 5The truss system 600 may be accessed through the closing panel 302A when the outboard wing section 108 corresponds to the outboard wing section 108A of the first side 120A of the aircraft fuselage 102. Alternatively, the truss system 600 may be accessed through the closing panel 302B when the outboard wing section 108 corresponds to the outboard wing section 108B of the second side 120B of the aircraft fuselage 102.

[0044] The truss system 600 includes one or more stringers 502 (eg, a plurality of stringers 502) extending along the aircraft wing 104. The truss system 500 also includes one or more spars 610. The spars 610 in the truss system 600 may correspond to Figure 5 The front spar 504 in the truss system 500, Figure 5 The spar 610 is coupled to the plurality of stringers 502 extending along the top portion of the aircraft wing 104 and to the plurality of stringers 502 extending along the bottom portion of the aircraft wing 104. To couple the center wing section 106 to the outboard wing sections 108, one or more spars 610 of the truss system 600 are coupled to the plurality of stringers 502 extending along the center wing section 106 of the aircraft wing 104 and to the plurality of stringers 502 extending along the outboard wing sections 108 of the aircraft wing 104.

[0045] Loads may be transferred along the one or more stringers 502 and the one or more spars 610 of the truss system 600 .

[0046] refer to Figure 7 , shows a process 700 for constructing and attaching an aircraft wing to a fuselage according to an exemplary embodiment.

[0047] According to the first stage 702 of the process 700, the aircraft wing 104 is constructed (e.g., assembled). For example, during the first stage 702, the center wing section 106 of the aircraft wing 104 is attached to the outboard wing sections 108A via the first truss system 500A. The first truss system 500A is accessible via the first closure panel 302A. Additionally, during the first stage 702, the center wing section 106 of the aircraft wing 104 is attached to the outboard wing sections 108B via the second truss system 500B. The second truss system 500B is accessible via the second closure panel 302B.

[0048] According to the second stage 704 of process 700, aircraft wing 104 is attached to aircraft fuselage 102. Figures 9 to 11 The second stage 704 is described in more detail. Figure 7 As shown, the center wing section closure panel 750 can be used to access the center wing section access panel opening 802, as described with respect to FIG. Figure 8The center wing section closure panel 750 may have external fasteners that align with a plurality of truss members inside the center wing section 106 of the aircraft wing 104. Thus, the center wing section closure panel 750 may be smoothly mated with the center wing section 106 via the external fasteners.

[0049] refer to Figure 8 , shows a bottom view of a center wing section 106 of an aircraft wing 104 according to an exemplary embodiment.

[0050] The center wing section 106 of the aircraft wing 104 includes at least one center wing section access panel opening 802. The center wing section access panel opening 802 is accessible via the center wing section closure panel 750. With respect to the layout and configuration of the aircraft wing 104, the center wing section access panel opening 802 is located between a first access panel opening associated with the first closure panel 302A (e.g., an access panel opening for accessing the truss system 500A) and a second access panel opening associated with the second closure panel 302B (e.g., an access panel opening for accessing the truss system 500B).

[0051] As described above, internal structures and systems associated with the engine 110 and fuel management may be included within the continuous center wing section 106 of the aircraft wing 104. The center wing section access panel opening 802 may provide a relatively large area for personnel to access the internal structures and systems included within the continuous center wing section 106. Specifically, at least one aircraft system may be accessible via at least one center wing section access panel opening 802. As a non-limiting example, the fuel system may be accessible via at least one center wing section access panel opening 802. Therefore, the layout of the center wing section access panel opening 802 may improve the feasibility of maintenance operations for the internal structures and systems.

[0052] See also Fig. 9 , a process 900 for attaching an aircraft wing to a fuselage is shown in accordance with an exemplary embodiment.

[0053] According to process 900, closed-shaped bracket 904 is coupled to center wing section 106 of aircraft wing 104. For example, a plurality of fasteners may be used to couple closed-shaped bracket 904 to rib 910 of center wing section 106 of aircraft wing 104. Fig. 9 As shown, the central portion of the closed-shaped bracket 904 may have a shape of an inverted letter “V.” For example, the central portion of the closed-shaped bracket 904 may have a vertex formed by the meeting of multiple inclined members of the closed-shaped bracket 904 .

[0054] According to process 900, an open-shaped bracket 902 is coupled to a side of aircraft fuselage 102 ( Fig. 9 (not shown). For example, a plurality of fasteners may be used to couple the open-shaped bracket 902 to the aircraft fuselage 102. Fig. 9 As shown, the central portion of the open-shaped bracket 902 may have an opening shaped to fit the central section of the closed-shaped bracket 904. For example, the central portion of the open-shaped bracket 902 may have the shape of an inverted letter "Y".

[0055] To attach an aircraft wing 104 (e.g., a center wing section 106 of the aircraft wing 104) to an aircraft fuselage 102, process 900 attaches an open-shaped bracket 902 to a closed-shaped bracket 904. For example, the apex of the closed-shaped bracket 904 is inserted into an opening of the open-shaped bracket 902. Then, a plurality of fasteners couple the open-shaped bracket 902 to the closed-shaped bracket 904. For example, the fasteners may penetrate the opening of the open-shaped bracket 902, a plurality of members forming the apex of the closed-shaped bracket 904, and the aircraft fuselage 102, such as Fig.10 and Fig.11 shown.

[0056] By inserting the apex of the closed-shaped bracket 904 into the opening of the open-shaped bracket 902, a reduced number of fasteners may be used to attach the aircraft wing 104 to the aircraft fuselage 102. For example, inserting the apex of the closed-shaped bracket 904 into the opening of the open-shaped bracket 902 may provide additional support, which reduces the need to use a larger number of fasteners to ensure that the aircraft wing 104 is adequately attached to the aircraft fuselage 102.

[0057] See also Fig.10 , another process 1000 for attaching an aircraft wing to a fuselage is shown in accordance with an exemplary embodiment.

[0058] According to process 1000, closed-shaped bracket 904 is coupled to center wing section 106 of aircraft wing 104. For example, a plurality of fasteners 1010 may be used to couple closed-shaped bracket 904 to rib 910 of center wing section 106 of aircraft wing 104. According to process 1000, open-shaped bracket 902 is coupled to one side of aircraft fuselage 102 (at Fig.10 For example, a plurality of fasteners ( Fig.10 ) may be used to couple the open-shaped bracket 902 to the aircraft fuselage 102.

[0059] To attach an aircraft wing 104 (e.g., a center wing section 106 of the aircraft wing 104) to an aircraft fuselage 102, the process 1000 attaches an open-shaped bracket 902 to a closed-shaped bracket 904. For example, the apex of the closed-shaped bracket 904 is inserted into an opening of the open-shaped bracket 902. Then, a plurality of fasteners 1020 couple the open-shaped bracket 902 to the closed-shaped bracket 904. For example, the fasteners 1020 may penetrate the opening of the open-shaped bracket 902, a plurality of members forming the apex of the closed-shaped bracket 904, and the aircraft fuselage 102.

[0060] By inserting the apex of the closed-shaped bracket 904 into the opening of the open-shaped bracket 902, a fewer number of fasteners 1020 may be used to attach the aircraft wing 104 to the aircraft fuselage 102. For example, inserting the apex of the closed-shaped bracket 904 into the opening of the open-shaped bracket 902 may provide additional support, which reduces the need to use a larger number of fasteners to ensure that the aircraft wing 104 is adequately attached to the aircraft fuselage 102.

[0061] See also Fig.11 , another process 1100 for attaching an aircraft wing to a fuselage is shown in accordance with an exemplary embodiment.

[0062] According to process 1100, closed-shaped bracket 904 is coupled to center wing section 106 of aircraft wing 104, and open-shaped bracket 902 is coupled to a side of aircraft fuselage 102. To attach aircraft wing 104 (e.g., center wing section 106 of aircraft wing 104) to aircraft fuselage 102, process 1100 attaches open-shaped bracket 902 to closed-shaped bracket 904. For example, the vertex of closed-shaped bracket 904 is inserted into the opening of open-shaped bracket 902. Then, a plurality of fasteners 1020 couple open-shaped bracket 902 to closed-shaped bracket 904. For example, fasteners 1020 may penetrate the opening of open-shaped bracket 902, a plurality of members forming the vertex of closed-shaped bracket 904, and aircraft fuselage 102. Although in Fig.11 , a single fastener 1020 is depicted, but in other embodiments, multiple fasteners 1020 may be used to couple the brackets 902, 904 to the aircraft fuselage 102. As a non-limiting example, in one embodiment, 28 fasteners 1020 (e.g., through bolts) may be used to couple the brackets 902, 904 to the aircraft fuselage 102.

[0063] By inserting the apex of the closed-shaped bracket 904 into the opening of the open-shaped bracket 902, a fewer number of fasteners 1020 may be used to attach the aircraft wing 104 to the aircraft fuselage 102. For example, inserting the apex of the closed-shaped bracket 904 into the opening of the open-shaped bracket 902 may provide additional support, which reduces the need to use a larger number of fasteners to ensure that the aircraft wing 104 is adequately attached to the aircraft fuselage 102.

[0064] Fig.12 A flow chart of a method 1200 is shown according to an exemplary embodiment.

[0065] Method 1200 includes attaching a first outboard wing section of an aircraft wing to a first end of a center wing section of the aircraft wing via a first truss system accessible via a first closure panel (block 1202). The center wing section has a continuous structure extending beyond a first side of the aircraft fuselage and beyond a second side of the aircraft fuselage, and the first end of the center wing section is located on the first side of the aircraft fuselage. For example, referring to Figure 1 and Figure 7 , a first outboard wing section 108A of the aircraft wing 104 is attached to a first end 122A of a center wing section 106 of the aircraft wing 104 by a first truss system 500A accessible via a first closing panel 302A. The center wing section 106 has a continuous structure extending beyond a first side 120A of the aircraft fuselage 102 and beyond a second side 120B of the aircraft fuselage 102, and the first end 122A of the center wing section 106 is located on the first side 120A of the aircraft fuselage 102.

[0066] The method 1200 also includes attaching a second outboard wing section of the aircraft wing to a second end of the center wing section via a second truss system accessible via a second closure panel (block 1204). The second end of the center wing section is located on a second side of the aircraft fuselage. For example, referring to Figure 1 and Figure 7 The second outboard wing section 108B of the aircraft wing 104 is attached to the second end 122B of the center wing section 106 by a second truss system 500B accessible via a second closing panel 302B. The second end 122B of the center wing section 106 is located on the second side 120B of the aircraft fuselage 102.

[0067] Method 1200 also includes mounting a first engine to the center wing section (block 1206). The first outboard wing section is outboard of the first engine. Figure 1 , the first engine 110A is mounted to the center wing section 106. The first outboard wing section 108A is located outboard of the first engine 110A.

[0068] Method 1200 also includes mounting a second engine to the center wing section (block 1208). The second outboard wing section is located outboard of the second engine. Figure 1 , the second engine 110B is mounted to the center wing section 106. The second outer wing section 108B is located outboard of the second engine 110B.

[0069] According to one implementation of the method 1200, the first truss system 500A includes at least one or more stringers 502, one or more front spars 504, and one or more rear spars 506. A first load may be transmitted along the one or more stringers 502, the one or more front spars 504, and the one or more rear spars 506. The first truss system 500A may be accessed through a first access panel opening (e.g., access panel opening 590) associated with the first closure panel 302A.

[0070] According to one implementation of the method 1200, the second truss system 500B includes at least one or more stringers 502, one or more front spars 504, and one or more rear spars 506. The second load can be transmitted along the one or more stringers 502, the one or more front spars 504, and the one or more rear spars 506. The second truss system 500B can be accessed through a second access panel opening (e.g., access panel opening 590) associated with the second closure panel 302B.

[0071] According to one implementation, method 1200 includes coupling a first open-shaped bracket to a first side of an aircraft fuselage and coupling a first closed-shaped bracket to a center wing section at a first location proximate to the first side of the aircraft fuselage. For example, open-shaped bracket 902 may be coupled to first side 120A of aircraft fuselage 102, and closed-shaped bracket 904 may be coupled to center wing section 106 at a first location proximate to first side 120A of aircraft fuselage 102. Method 1200 may also include coupling the first open-shaped bracket to the first closed-shaped bracket. For example, fastener 1020 may couple open-shaped bracket 902 to closed-shaped bracket 904.

[0072] According to one implementation, method 1200 includes coupling a second open-shaped bracket to a second side of the aircraft fuselage and coupling a second closed-shaped bracket to the center wing section. For example, open-shaped bracket 902 may be coupled to second side 120B of aircraft fuselage 102, and closed-shaped bracket 904 may be coupled to center wing section 106 at a second location proximate to second side 120B of aircraft fuselage 102. Method 1200 may also include coupling the second open-shaped bracket to the second closed-shaped bracket. For example, fastener 1020 may couple open-shaped bracket 902 to closed-shaped bracket 904.

[0073] According to one implementation of the method 1200, the center wing section 106 includes at least one center wing section access panel opening 802 accessible via the center wing section closure panel 750. The at least one center wing section access panel opening 802 is between a first access panel opening associated with the first closure panel 302A and a second access panel opening associated with the second closure panel 302B. According to one implementation of the method 1200, at least one aircraft system is accessible via the at least one center wing section access panel opening 802. According to one implementation of the method 1200, a fuel system is accessible via the at least one center wing section access panel opening 802.

[0074] By configuring the aircraft wing 104 so that the outboard wing sections 108 are outboard of the engines 110, internal structures and systems associated with the engines 110 and fuel management may be included within the continuous center wing section 106 of the aircraft wing 104. Additionally, by using a continuous center wing section 106 that extends beyond the aircraft fuselage 102, fewer interfaces (e.g., stringers) are required to carry loads through the outboard wing sections 108, which may reduce the number of fasteners. For example, due to the continuity of the center wing section 106, the center wing section 106 may carry relatively large loads with a reduced number of fasteners compared to a smaller center wing section that does not extend beyond the aircraft fuselage 102.

[0075] Although the system is described herein with specific reference to an aircraft system or an aerospace vehicle, in other embodiments the system may be a vehicle other than an aircraft without departing from the essence of the present disclosure.

[0076] In addition, in this specification, embodiments in which one element is "coupled" to another element may include direct and indirect coupling. Direct coupling may be defined as one element being coupled to another element and contacting the other element to a certain extent. Indirect coupling may be defined as a coupling between two elements that is not in direct contact with each other, but has one or more additional elements between the two coupling elements. In addition, as used herein, fixing an element to another element may include direct fixing and indirect fixing. In addition, as used herein, "adjacent" does not necessarily mean contact. For example, an element may be adjacent to another element without contacting the element.

[0077] As used herein, a system, device, structure, article, element, component or hardware that is "configured to" perform a specific function needs to be able to perform a specific function without any changes, rather than only having the potential to perform a specific function after further modification. In other words, a system, device, structure, article, element, component or hardware that is "configured to" perform a specific function is specially selected, created, implemented, utilized, programmed, and / or designed for the purpose of performing a specific function. As used herein, "configured to" represents the existing characteristics of a system, device, structure, article, element, component or hardware that enables a system, device, structure, article, element, component or hardware to perform a specified function without further modification. For the purposes of this disclosure, a system, device, structure, article, element, component or hardware that is described as "configured to" perform a specific function may be additionally or alternatively described as "suitable for" and / or "operable to" perform the function.

[0078] The flow charts included herein are generally described as logical flow charts. Therefore, the sequence depicted and the numbered steps indicate an embodiment of the method presented. Other steps and methods that are equivalent to one or more steps or parts thereof of the method shown in function, logic or effect can be envisioned. In addition, the format and symbols adopted are provided to explain the logical steps of the method, and should be understood as not limiting the scope of the method. Although multiple arrow types and line types can be adopted in the flow chart, they should be understood as not limiting the scope of the corresponding method. In fact, some arrows or other connecting lines can be used to indicate only the logical flow of the method. For example, an arrow can indicate a waiting period or monitoring period of unspecified duration between multiple steps of the enumeration of the depicted method. In addition, the order in which the specific method occurs may or may not strictly follow the order of the corresponding steps shown.

[0079] Unless otherwise indicated, the terms "first", "second", etc. are used herein only as labels and are not intended to impose ordinal, positional, or hierarchical requirements on the items to which these terms refer. In addition, reference to, for example, a "second" item does not require or exclude the presence of, for example, a "first" item or a lower-numbered item and / or, for example, a "third" item or a higher-numbered item.

[0080] Although the system and method of operation have been described with reference to certain embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted without departing from the scope of the claims. Therefore, the present method and system are not intended to be limited to the specific embodiments disclosed, but rather the disclosed method and system include all implementations falling within the scope of the appended claims.

Claims

1. An aircraft structure comprising: An aircraft wing (104), the aircraft wing comprising: a central wing section (106) having a continuous structure extending beyond a first side (120A) of the aircraft fuselage (102) and extending beyond a second side (120B) of the aircraft fuselage (102); a first outboard wing section (108A) attached to a first end (122A) of the center wing section (106) by a first truss system (500A) accessible via a first closure panel (302A), wherein the first end (122A) of the center wing section (106) is on the first side (120A) of the aircraft fuselage (102); and A second outboard wing section (108B) is attached to a second end (122B) of the center wing section (106) by a second truss system (500B) accessible via a second closing panel (302B), wherein the second end (122B) of the center wing section (106) is on the second side (120B) of the aircraft fuselage (102).

2. The aircraft structure according to claim 1, further comprising: a first engine (110A) mounted to the center wing section (106), wherein the first outboard wing section (108A) is located outboard of the first engine (110A); and A second engine (110B) is mounted to the center wing section (106), wherein the second outboard wing section (108B) is located outboard of the second engine (110B).

3. The aircraft structure according to claim 1, wherein: The first truss system (500A) includes at least one or more stringers (502), one or more front spars (504) and one or more rear spars (506), and wherein a first load is transmitted along the one or more stringers (502), one or more front spars (504) and one or more rear spars (506) of the first truss system.

4. The aircraft structure according to claim 1, wherein: The second truss system (500B) includes at least one or more stringers (502), one or more front spars (504) and one or more rear spars (506), and wherein the second load is transmitted along the one or more stringers (502), one or more front spars (504) and one or more rear spars (506) of the second truss system.

5. The aircraft structure according to claim 1, wherein: The first truss system (500A) is accessible through a first access panel opening (590) associated with the first closure panel (302A), and wherein the second truss system (500B) is accessible through a second access panel opening (590) associated with the second closure panel (302B).

6. The aircraft structure according to claim 1, further comprising: a first open-shaped bracket (902) coupled to the first side (120A) of the aircraft fuselage (102); a first closed-shaped bracket (904) coupled to the center wing section (106) at a first location proximate the first side (120A) of the aircraft fuselage (102), wherein a first vertex of the first closed-shaped bracket (904) is insertable into an opening of the first open-shaped bracket (902); as well as A plurality of first fasteners (1020) connect the first open-shaped support (902) to the first closed-shaped support (904).

7. The aircraft structure according to claim 6, further comprising: a second open-shaped bracket (902) coupled to the second side (120B) of the aircraft fuselage (102); a second closed-shaped bracket (904) coupled to the center wing section (106) at a second location proximate the second side (120B) of the aircraft fuselage (102), wherein a second vertex of the second closed-shaped bracket (904) is insertable into an opening of the second open-shaped bracket (902); as well as A plurality of second fasteners (1020) connect the second open-shaped bracket (902) to the second closed-shaped bracket (904).

8. The aircraft structure according to claim 1, wherein: The center wing section (106) includes at least one center wing section access panel opening (802) accessible via a center wing section closure panel (750), and wherein the at least one center wing section access panel opening (802) is located between a first access panel opening associated with the first closure panel (302A) and a second access panel opening associated with the second closure panel (302B).

9. The aircraft structure according to claim 8, wherein: At least one aircraft system is accessible via the at least one center wing section access panel opening (802).

10. The aircraft structure according to claim 8, wherein: A fuel system is accessible via the at least one center wing section access panel opening (802).

11. A method (1200) of manufacturing an aircraft structure, the method comprising: Attaching (1202) a first outboard wing section (108A) of an aircraft wing (104) to a first end (122A) of a center wing section (106) of the aircraft wing (104) via a first truss system (500A) accessible via a first closure panel (302A), wherein the center wing section (106) has a continuous structure extending beyond a first side (120A) of the aircraft fuselage (102) and beyond a second side (120B) of the aircraft fuselage (102), and wherein the first end (122A) of the center wing section (106) is on the first side (120A) of the aircraft fuselage (102); attaching (1204) a second outboard wing section (108B) of the aircraft wing (104) to a second end (122B) of the center wing section (106) via a second truss system (500B) accessible via a second closure panel (302B), wherein the second end (122B) of the center wing section (106) is on the second side (120B) of the aircraft fuselage (102); mounting (1206) a first engine (110A) to the center wing section (106), wherein the first outboard wing section (108A) is located outboard of the first engine (110A); and A second engine (110B) is mounted (1208) to the center wing section (106), wherein the second outboard wing section (108B) is located outboard of the second engine (110B).

12. The method (1200) of claim 11, wherein: The first truss system (500A) includes at least one or more stringers (502), one or more front spars (504) and one or more rear spars (9506), and wherein a first load is transmitted along the one or more stringers (502), one or more front spars (504) and one or more rear spars (506) of the first truss system.

13. The method (1200) of claim 12, wherein: The second truss system (500B) includes at least one or more stringers (502), one or more front spars (504) and one or more rear spars (506), and wherein the second load is transmitted along the one or more stringers (502), one or more front spars (504) and one or more rear spars (506) of the second truss system.

14. The method (1200) of claim 11, wherein: The first truss system (500A) is accessible through a first access panel opening (590) associated with the first closure panel (302A), and wherein the second truss system (500B) is accessible through a second access panel opening (590) associated with a second closure panel (302B).

15. The method (1200) of claim 11, further comprising: coupling a first open-shaped bracket (902) to the first side (120A) of the aircraft fuselage (102); coupling a first closed-shaped bracket (904) to the center wing section (106) at a first location proximate the first side (120A) of the aircraft fuselage (102), wherein a first vertex of the first closed-shaped bracket (904) is insertable into an opening of the first open-shaped bracket (902); and The first open-shaped support (902) is coupled to the first closed-shaped support (904).

16. The method (1200) of claim 15, further comprising: coupling a second open-shaped bracket (902) to the second side (120B) of the aircraft fuselage (102); coupling a second closed-shaped bracket (904) to the center wing section (106) at a second location proximate the second side (120B) of the aircraft fuselage (102), wherein a second vertex of the second closed-shaped bracket (904) is insertable into an opening of the second open-shaped bracket (902); and The second open-shaped support (902) is coupled to the second closed-shaped support (904).

17. An aircraft (100), comprising: fuselage (102); An aircraft wing (104), the aircraft wing comprising: a central wing section (106) having a continuous structure extending beyond a first side (120A) of the fuselage (102) and extending beyond a second side (120B) of the fuselage (102); a first outboard wing section (108A) attached to a first end (122A) of the center wing section (106) by a first truss system (500A) accessible via a first closure panel (302A), wherein the first end (122A) of the center wing section (106) is on the first side (120A) of the fuselage (102); and a second outboard wing section (108B) attached to a second end (122B) of the center wing section (106) by a second truss system (500B) accessible via a second closure panel (302B), wherein the second end (122B) of the center wing section (106) is on the second side (120B) of the fuselage (102); a first engine (110A) mounted to the center wing section (106), wherein the first outboard wing section (108A) is located outboard of the first engine (110A); and A second engine (110B) is mounted to the center wing section (106), wherein the second outboard wing section (108B) is located outboard of the second engine (110B).

18. The aircraft (100) of claim 17, further comprising: A first open-shaped bracket (902) coupled to the first side (120A) of the fuselage (102); a first closed-shaped bracket (904) coupled to the center wing section (106) at a first location proximate the first side (120A) of the fuselage (102), wherein a first vertex of the first closed-shaped bracket (904) is insertable into an opening of the first open-shaped bracket (902); and A plurality of first fasteners (1020) connect the first open-shaped support (902) to the first closed-shaped support (904).

19. The aircraft (100) of claim 18, further comprising: a second open-shaped bracket (902) coupled to the second side (120B) of the fuselage (102); a second closed-shaped bracket (904) coupled to the center wing section (106) at a second location proximate the second side (120B) of the fuselage (102), wherein a second vertex of the second closed-shaped bracket (904) is insertable into an opening of the second open-shaped bracket (902); as well as A plurality of second fasteners (1020) connect the second open-shaped bracket (902) to the second closed-shaped bracket (904).

20. The aircraft (100) of claim 17, wherein: The center wing section (106) includes at least one center wing section access panel opening (802) accessible via a center wing section closure panel (750), and wherein the at least one center wing section access panel opening (802) is located between a first access panel opening associated with the first closure panel (302A) and a second access panel opening associated with the second closure panel (302B).

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