Fuselage structure splicing parts

Abstract

A fuselage structural splice may include a panel having an edge and a strip connected to a first panel along the panel edge. A surface of the strip that is not in contact with the panel tapers toward the panel as the distance from the panel edge increases. A stringer is mounted on the panel, extends away from the edge of the panel, and has a flange mounted to the panel. An accessory has a stringer base and a strip base. The stringer base is connected to the stringer flange and extends along a first line extending in a plane orthogonal to the panel edge. The strip base of the accessory is mounted on the strip surface and extends along a second line in the plane. The second line is transverse to the first line, and the strip base of the accessory has a constant thickness along the second line.

Description

Technical Field

[0001] The present disclosure relates to aircraft structures. More specifically, the disclosed examples relate to apparatus and methods for splicing accessories to join fuselage sections of an aircraft. Background Art

[0002] Current fuselage sections are made of carbon fiber reinforced polymer (CFRP) joined by a joint configuration that utilizes at least one strap, a stringer, and a splice fitting to form a splice joint between two skin panels. The splice fitting is connected between a flange on the stringer and the strap. Typically, the splice fitting is flat, and when assembled, the fuselage section requires shims and fillers at many locations to align the splice fitting at the splice joint. Although shims are used as compensators to absorb tolerances between mating components and avoid reworking of parts, the shimming process increases the cost and time of assembling the fuselage section. Summary of the invention

[0003] The present disclosure provides systems, devices and methods related to fuselage structural splices. In some examples, a fuselage structural splice may include a first panel having a first panel main face and a first edge, and a strip connected to the first panel. The strip extends along the first edge of the first panel and has a first strip surface and a second strip surface. The first strip surface contacts the first panel main face, and the second strip surface tapers toward the first panel as the distance from the first edge of the first panel increases. The fuselage structural splice may also include a first stringer mounted on the first panel main face, extending away from the first edge of the first panel, and having a first flange mounted to the first panel main face. The fuselage structural splice may also include a first accessory having a first stringer base and a first strip base. The first stringer base is connected to the first flange of the first stringer and extends along a first line extending in a first plane orthogonal to the first edge of the first panel. The first strip base is mounted on the second strip surface and extends along a second line in the first plane. The second line is transverse to the first line, and the first strip base has a constant thickness along the second line.

[0004] In some examples, a fuselage structural splice may include a first panel having a first panel main face and a first edge, and a strip connected to the first panel. The strip extends along the first edge of the first panel and has a first strip surface in contact with the first panel main face and a second strip surface that tapers toward the first panel as the distance from the first edge of the first panel increases. The fuselage structural splice may also include a stringer mounted on the first panel main face, extending away from the first edge of the first panel, and having a first flange mounted to the first panel main face. An accessory for the fuselage structural splice may include an elongated base having a stringer base and a strip base. The stringer base is configured to be connected to the first flange of the stringer to extend along a first line extending in a first plane orthogonal to the first edge of the first panel. The first strip base is configured to be mounted on a second strip surface to extend along a second line in the first plane. The second line is transverse to the first line, and the first strip base has a constant thickness along the second line.

[0005] In some examples, a method of manufacturing a fuselage structure may include positioning a first panel region of a strip along a first edge of a first panel. The method may include connecting the strip to the first panel. The method may include mounting a first flange of a first stringer to the first panel, wherein the first stringer extends away from the first edge of the first panel. The method may include positioning a first stringer base of a first accessory on the first flange of the first stringer, wherein the first stringer base extends along a first line extending in a first plane orthogonal to the first edge of the first panel. The method may include positioning a first stripe base of the accessory on the strip, wherein the first stripe base extends along a second line extending in the first plane, the second line being transverse to the first line at a first angle, wherein the first stripe base has a constant thickness along the second line. The method may include connecting the first stringer base to the first flange of the first stringer. The method may include connecting the first stripe base to the strip.

[0006] The features, functions, and advantages can be achieved independently in various examples of the present disclosure or may be combined in yet other examples further details of which can be seen with reference to the following description and drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0007] Figure 1 is a perspective simplified view of an illustrative aircraft assembled in accordance with aspects of the present disclosure.

[0008] FIG. 2A to FIG. 2B It shows that Figure 1 A partial isometric view of an example of constructing a splice joint between adjacent fuselage sections of an aircraft.

[0009] Figure 2C yes Figure 2B A magnified view of a portion of .

[0010] Figure 2D It shows that Figure 1 A partial isometric view of an example of constructing a splice joint between adjacent fuselage sections of an aircraft.

[0011] Figure 3 yes Figure 2D An enlarged isometric view of a portion of a splice joint showing the fittings attached to the stringer and strap assembly.

[0012] Figure 4 is attached to Figure 2D Cross-section of the spliced ​​joints for the fittings of stringers and straps.

[0013] Figure 5 is a cross-sectional view of a stringer with attached fittings.

[0014] FIG. 6A to FIG. 6B is a cross-sectional view showing an example of positioning a fitting having a stepped structure on a stringer and a strap.

[0015] Figure 7 is a flow chart depicting an example of steps of a method of assembling a splice joint according to the present teachings.

[0016] Figure 8 is a flow chart depicting another example of steps of a method of positioning an accessory on a strip of a splice joint according to the present teachings. DETAILED DESCRIPTION

[0017] Various aspects and examples of fuselage structural splices and related methods are described below and shown in the relevant drawings. Unless otherwise specified, splicing accessories and / or their various components according to the present teachings may, but not necessarily, include at least one of the structures, components, functions and / or variations described, shown and / or incorporated herein. In addition, unless expressly excluded, the process steps, structures, components, functions and / or variations described, shown and / or incorporated herein in conjunction with the present teachings may be included in other similar devices and methods, including being interchangeable between the disclosed examples. The following description of various examples is merely illustrative in nature and is in no way intended to limit the present disclosure, its application or use. In addition, the advantages provided by the embodiments described below are illustrative in nature, and not all examples provide the same advantages or the same degree of advantages.

[0018] This detailed description includes the following sections, which are followed by the following: (1) Overview; (2) Examples, Components, and Alternatives; (3) Illustrative Combinations and Additional Examples; (4) Advantages, Features, and Benefits; and (5) Conclusion. The Examples, Components, and Alternatives section is further divided into subsections A through D, each of which is labeled accordingly.

[0019] definition

[0020] The following definitions apply herein unless otherwise stated.

[0021] "Substantially" means conforming primarily to a particular size, range, shape, concept, or other aspect modified by the term, such that the feature or component does not need to conform exactly as long as it is suitable for its intended purpose or function. For example, an object that is "substantially cylindrical" means that the object resembles a cylinder, but may have one or more deviations from a true cylinder.

[0022] "Comprising," "including," and "having" (and variations thereof) are used interchangeably to mean including but necessarily limited to, and are open-ended terms that are not intended to exclude additional, unrecited elements or method steps.

[0023] Unless otherwise indicated, the terms "first", "second", "third", etc. are used herein merely as labels and are not intended to impose order, position, or hierarchy requirements on the components to which these terms refer. In addition, for example, reference to a "second" component does not require or preclude the presence of lower-numbered items (e.g., the "first" item) and / or higher-numbered components (e.g., the "third" item).

[0024] “Attached” means a relationship whereby the properties of one affect the properties of the other, and may include permanent or releasable connection or mounting, whether directly or indirectly through intermediate components, and is not necessarily limited to physical connections.

[0025] Overview

[0026] Typically, a complete fuselage structure splice typically includes a plurality of individual accessories distributed along the splice joint. Each individual accessory is configured to be connected between the splice joint strip and the flange of one of the plurality of stringers. The accessory may include a first end connected to a second end. The middle section may extend between the ends. As described below, the accessory preferably has an end attached to the strip and extends at an angle relative to the opposite end attached to the stringer flange. The strip ends of the accessory also preferably have a uniform thickness. In addition, the middle section may extend at an angle between the ends of the accessory relative to one or both of the two ends of the accessory. Such an intermediate section may be oriented and provide a transition between the surface of the accessory end and the surface of the corresponding strip and stringer flange. The different orientations of the two accessory ends accommodate the differences in thickness and orientation of the strips and stringer flanges in the fuselage structure splice, and facilitate the assembly of the entire gasket-free splice joint. The disclosed accessories achieve the versatility and use of standard components for joining multiple pairs of fuselage sections.

[0027] Examples, Components, and Alternatives

[0028] The following sections describe exemplary selected aspects and related systems and / or methods. The examples in these sections are intended to illustrate and should not be construed as limiting the entire scope of the present disclosure. Each section may include one or more different examples, and / or context or related information, functions and / or structures.

[0029] A. Illustrative splicing accessories

[0030] like Figures 1 to 5 As shown, this section describes an illustrative splice fitting 100. The splice fitting 100 is a thermoplastic circumferential splice fitting and is a first example of a splice fitting that may be used in a fitting splice for joining a splice joint of aircraft sections, as described above.

[0031] Figure 1 is a perspective view of an aircraft 101 having a fuselage 102 that may be constructed with a splice joint having a splice fitting, such as splice fitting 100. The fuselage 102 includes a plurality of substantially cylindrical fuselage sections 104 (individually identified as fuselage sections 104a to 104e) that abut one another along joint lines referred to as circumferential splice joints 106 (individually identified as splice joints 106a to 106d). The circumferential joints 106 define a plane 107 (individually identified as splice joints 107a to 107d) that is perpendicular to a longitudinal axis 110 of the fuselage. The joint lines and circumferential joint areas of the splice joints 106 provide strength and transfer forces along the fuselage to withstand the high stresses experienced by the aircraft during flight.

[0032] In one example, fuselage section 104a may be a forward fuselage section, and fuselage section 104b may be a first intermediate fuselage section. Splice joint 106a may represent full fuselage joint sections 41-43 connecting the forward fuselage section to the first intermediate fuselage section. Similarly, fuselage section 104c may be a second intermediate fuselage section, fuselage section 104d may be a third intermediate fuselage section, and fuselage section 104e may be an aft fuselage section. Likewise, splice joint 106b may represent crown joint sections 43-44 connecting the first intermediate fuselage section to the second intermediate fuselage section; splice joint 106c may represent crown joint sections 44-46 connecting the second intermediate fuselage section to the third intermediate fuselage section; and splice joint 106d may represent full fuselage joint sections 46-47 connecting the third intermediate fuselage section to the aft fuselage section.

[0033] Each fuselage section 104a to 104e may include a composite skin 108, shown as a separate skin 108a to 108e, extending circumferentially around the longitudinal axis 110 of the fuselage 102. Throughout this disclosure, for convenience, the term "fuselage section" is used to refer to any aircraft shell structure extending circumferentially around the axis. It will be appreciated by those skilled in the art that the fuselage sections 104a to 104e may not be limited to generally cylindrical structures, but may include structures having circular, elliptical, oval, egg-shaped, rectilinear, conical, or other cross-sectional shapes. In addition, in one example, the fuselage section 104 may be a "single-piece" fuselage section, wherein the composite skin 108 is a "single-piece" skin that extends circumferentially continuously around the longitudinal axis 110. However, in other examples, the skin 108 may be formed by two or more skin sections spliced ​​or otherwise joined together to form a circumferential fuselage section.

[0034] In the present example, each composite skin 108 has a cross-sectional width of at least about 10 feet, such as about 15 feet to about 35 feet. In a specific example, the composite skin 108 may have a cross-sectional width of about 18 feet. The thickness of the skin may also vary for different fuselage sections. In a specific example, the composite skin thickness may range between 18-20 thermoplastic material layers.

[0035] FIG. 2A to FIG. 2D Assembly structures 101a to 101c are shown together, respectively, showing an exemplary assembly sequence for joining a first fuselage section 104a to a second fuselage section 104b according to aspects of the present disclosure. Similar assembly structures can be used to join other fuselage sections 104b to 104c, 104c to 104d, and 104d to 104e, or to join two panels or workpieces.

[0036] First reference Figure 2A , which is the fuselage 102 ( Figure 1 ) is an enlarged isometric view looking inside, which is a portion of the first splice joint 106a. Figure 2A The portion of the first fuselage section 104a shown includes a first panel 112a having a first panel major face 111a and a first edge 113a. Figure 2A The portion of the second fuselage section 104b shown includes a second panel 112b having a second panel major face 111b and a second edge 113b facing the first edge 113a. The second edge 113b of the second panel 112b is aligned or butted against the first edge 113a of the first panel 112a to form a splice joint 106a, wherein the first panel major face is aligned with the second panel major face.

[0037] Those skilled in the art will recognize that in certain embodiments, when the first panel and the second panel are butted together, the first panel and the second panel may not be in full contact along the entire length of the splice joint 106a. Those skilled in the art will also recognize that any gap defined between the butted first panel and the second panel may be filled (e.g., with a gasket, filler, etc.) or otherwise addressed by other known methods.

[0038] In this example, a plurality of stringers 114 (identified as stringers 114a to 114b) can be attached to the first panel main face 111a of the first panel 112a. The plurality of stringers extend away from the splice joint 106a in a first direction D1 and along a straight line parallel to the longitudinal axis 110 of the aircraft 101 and transverse to the first direction D1 of the splice joint and the panel first edge 113a. Each stringer 114 may include a plurality of flanges and a raised portion 124 located between the flanges and extending away from the face of the first panel 112a. In this example, each stringer 114 has a pair of flanges, which are identified as a first flange 126a and a second flange 126b located on opposite sides of the raised portion 124. The flanges 126a and 126b are directly attached to the first panel 112a, and the stringers 114a to 114b are configured to reinforce, strengthen and strengthen the first panel 112a. In the illustrated example, the raised portions of the stringers 114 each have a C-shaped or U-shaped cross-sectional geometry. However, in other examples, the stringers 114 may have other cross-sectional shapes, including a "hat" shape, an "L" shape, an inverted "T" shape, an "I" shape, or other geometric shapes.

[0039] The second panel 112b can be at least roughly similar to the first panel 112a described above in structure and function. Therefore, the second panel 112b can include a plurality of stringers 116 (identified as stringers 116a to 116b) attached to the second panel main face 111b of the second panel 112b. The stringers extend away from the splicing joint 106a in a second direction D2 opposite to D1 and along a line of the second direction D2 and parallel to the longitudinal axis 110 of the aircraft. Each stringer 116 may include a raised portion 125 extending away from the second panel 112b, and a plurality of flanges (identified as first flange 127a and second flange 127b). The flanges are directly attached to the second panel 112b, and the stringers 116a to 116b are configured to reinforce, strengthen and enhance the second panel 112b. In the example shown, each stringer 116 has a C-shaped or U-shaped cross-sectional geometry. However, in other examples, the stringer 116 may have other cross-sectional shapes, including a “hat” shape, an “L” shape, an inverted “T” shape, an “I” shape, or any other suitable geometric shape.

[0040] In this example, a set of stringers 114a to 114b attached to the first panel and a set of stringers 116a to 116b attached to the second panel have the same geometry and are aligned to provide enhanced structural support to the entire fuselage structure. For example, the stringers 114a of the first panel are collinear with the stringers 116a of the second panel along a line parallel to the longitudinal axis 110. The raised portions 124 and 125 are collinear, and their respective flanges 126a to 126b are aligned with the flanges 127a to 127b across the splice joint 106a. In other examples, the set of stringers 114a to 114b attached to the first panel and the set of stringers 116a to 116b attached to the second panel may have different geometries and may be arranged in an alternating or irregular manner.

[0041] Figure 2B Depicted is a structural assembly 101b comprising a Figure 2A An elongated strip 120 of the assembly structure 101A is shown. The strip 120 is attached to the first panel major surface 111a along the first edge 113a and to the second panel major surface 111b along the second edge 113b to cover and bridge the splice joint 106a formed by the first panel 112a and the second panel 112b. The strips 120 are all attached along the splice joint extending around the circumference of the fuselage to bridge the fuselage section 104a to the section 104b.

[0042] The strip may include a strip first surface 121 (or strip bottom surface) and an opposing strip second surface 123 (or strip bottom surface). Figure 2B The strip top surface is shown. The strip first surface 121 contacts the first panel major surface 111a and the second panel major surface 111b. The strip first surface typically has a smooth surface to provide a continuous contact area for attachment to the first panel major surface and the second panel major surface.

[0043] like Figure 2C As shown in the enlarged portion of , the strip second surface 123 may include a first panel region 123a extending longitudinally along the first edge 113a on the first panel major face 111a. In the first panel region, the strip has a thickness orthogonal to the strip first surface 121, and the thickness tapers with the distance from the first edge 113a of the first panel major face and the splice joint 106a along the direction D1. Similarly, the strip second surface 123 includes a second panel region 123b extending longitudinally along the second edge 113b on the second panel major face 111b. In the second panel region, the strip has a thickness orthogonal to the strip first surface 121, and the thickness tapers with the distance from the second edge 113b of the second panel major face and the splice joint 106a along the direction D2.

[0044] In addition, the strip second surface 123 includes a strip middle region 123c between the first panel region 123a and the second panel region 123b. The strip has a constant thickness T1 in the strip middle region 123c. The first panel region 123a extends from a first major edge 123a1 forming an edge of the strip middle region 123c to a first secondary edge 123a2 at a first angle α1 relative to the orientation of the strip middle region of the strip second surface. The first secondary edge 123a2 is spaced apart from the strip first surface 121 by a distance H1, and the strip includes a strip first side face 123f1 connecting the first secondary edge 123a2 to the strip first surface 121. The strip first side face is transverse to the first panel region 123a of the strip second surface and the strip first surface 121, and has a height H1 and a length equal to the length of the strip 120 around the circumferential joint 106a.

[0045] The second panel region extends from the second major edge 123b1 to a second secondary edge 123b2 at a second angle α2 relative to the orientation of the strip intermediate region 123c of the strip second surface along a direction D2. The second secondary edge 123b2 is spaced a distance H2 from the strip first surface 121, and the strip includes a strip second side 123f2 connecting the second secondary edge 123b3 to the strip first surface 121. The strip second side 123f2 is transverse to the second panel region 123b of the strip second surface and the strip first surface 121, and has a height H2 and a length equal to the length of the strip 120 around the circumferential joint 106a.

[0046] In this example, the elongated strip extends along a midline L1 extending along the length of the strip. The midline L1 is Figure 1 The plane 107a shown is parallel to and extends along the circumferential splice joint 106a and is orthogonal to the longitudinal axis 110. The centerline L1 passes through a circular path concentric with the fuselage sections 104a and 104b. The plane 107a represents the plane of symmetry of the strip in which the first panel area and the second panel area are symmetrical to each other. The first major edge and the second major edge of the second surface of the strip are equidistant from the centerline. Likewise, the first secondary edge and the second secondary edge of the second surface of the strip are equidistant from the centerline. The cone angle α1 is equal to the angle α2. The heights H1 and H2 of the first side 123f1 and the second side 123f2 are equal.

[0047] Strips 120 attached to the inner first panel major face of the first panel 112a and the inner second panel major face of the second panel 112b, respectively, join the two panels while maintaining a smooth aerodynamic surface on the exterior of the fuselage 102 .

[0048] In one example, the strip 120 may include a composite material, such as graphite-epoxy or the like. In other examples, the strip 120 may include other materials, including metallic materials such as aluminum, titanium, steel, etc. The strip 120 may be attached to the first panel 112a and the second panel 112b using a plurality of fasteners, similar to Figure 2D The fastener 160 is shown extending through the strip 120 and the first panel 112a and the second panel 112b. In other examples, the strip 120 can be bonded to the first panel 112a and the second panel 112b, or bonded and fastened to the first panel 112a and the second panel 112b. In addition, in one example, the strip 120 can extend continuously or at least approximately continuously around the splice joint 106a. In other examples, the strip 120 can be segmented around the splice joint 106a. For example, the splice joint 106a can include six segments of the strip 120. In other examples, the splice joint 106a can include more (e.g., eight) or fewer segments of the strip 120.

[0049] In the example shown, the strips 120 may be at least approximately as thick as the skin 108, but thicker than the skin 108. Figure 2A and Figure 2D The adjacent flanges 126, 127 of the longerons 114, 116 are thicker than those indicated in FIG.

[0050] Figure 2D A structural assembly 101c is depicted, which includes a plurality of splicing accessories 100 and a plurality of splicing accessories 100 attached to the Figure 2B 140 of the structural assembly 101B shown. For example, the first fitting 100a is positioned relative to the stringer flange 126a of the stringer 114a attached to the first panel 112a and relative to the first panel area 123a of the strip 120. Similarly, the second fitting 100b is positioned relative to the stringer flange 126b of the stringer 114a and relative to the first panel area 123a of the strip 120. In addition, the third fitting 100c is positioned relative to the stringer flange 127b of the stringer 116a attached to the second panel 112b and relative to the second panel area 123b of the strip 120. The fourth fitting 100d is positioned relative to the stringer flange 127a of the stringer 116a and relative to the second panel area 123b of the strip 120. A pair of fittings 100 are similarly positioned relative to the flanges on each stringer 114, 116 and relative to the strip 120.

[0051] Likewise Figure 3 and Figure 4As shown in more detail in FIG. 1 , for accessories 100a and 100b, each accessory 100 may preferably include a base and a projection forming a generally "L" shaped configuration. The base includes a strap base and a stringer base. Thus, accessories 100a to 100d have a respective base with respective strap bases 131a to 131d and stringer bases 132a to 132d, and further, accessories 100a to 100d include respective stringer extensions 136a to 136d extending laterally from respective stringer bases 132a to 132d, and respective strap extensions 135a to 135d extending laterally from respective strap bases 131a to 131d. As shown, strap base 131c of accessory 100c is connected to strap 120. Stringer base 132c of accessory is connected to flange 127b of stringer 116a. In the example shown, the fitting 100c includes a stringer extension 136c extending laterally from the stringer base 132c, and a strap extension 135c extending laterally from the strap base 131c. A plurality of fasteners 160 extend through the strap base 131c and the underlying structure (i.e., the strap 120 and associated panels), and through the stringer base 132c and the underlying structure (i.e., the flange 127b and associated panels). The corresponding fasteners attach each fitting 100 to the underlying structure to form a structural load path through the splice joint 106a.

[0052] The assembly structure 101c may include a frame 140 that extends circumferentially around at least a portion of the splice joint 106a between adjacent fuselage sections 104a and 104b. The frame 140 may be attached to the strap 120 along a strap intermediate region 123C between longitudinally opposing fittings 100. In the example shown, the frame 140 may have a generally Z-shaped cross-sectional configuration with a lower leg 150 secured to the strap 120. The lower leg 150 may be segmented into a plurality of legs, such as Figure 2D Although a Z-shaped frame 140 is shown, those skilled in the art will appreciate that any suitable bending-resistant frame may be used, such as a C-shaped frame, an I-shaped frame, a J-shaped frame, etc. Alternatively, the frame 140 may be omitted.

[0053] The frame 140 may be formed of a composite material, such as CFRP or a similar material, such as the same composite material that forms the strap 120 or the accessory 100. Alternatively, the frame 140 may be formed of a metal or other material, such as aluminum or titanium.

[0054] The accessory 100, the stringers 114 and 116, the strips 120, the frame 140, and the skin 108 can be made of composite materials, including graphite-epoxy resin and / or other suitable composite materials. For example, in one example, the skin 108 can be made of toughened epoxy resin and carbon fiber. In this example, the skin 108 can include fiber tapes pre-impregnated with resin (i.e., "prepregs") and an outer layer of prepreg fabric. In another example, the strips 120 and the accessory 100 can also be made of epoxy resin and carbon fiber. The skin 108, the strips 120, and the accessory 100 can have quasi-isotropic layups, i.e., layups with equal (or approximately equal) numbers of layers oriented at 0°, +45°, -45°, and 90°. The stringer 114 can have an axially dominant fiber orientation. In other examples, the skin 108, the strips 120, the accessory 100, and the stringers 114, 116 can have other fiber orientations.

[0055] One advantage of using composite materials instead of metal is that the fitting 100 and the underlying structure (e.g., skin 108 and stringers 114) will have at least approximately similar coefficients of thermal expansion. Figure 1 ) will not cause disparate thermal expansion between the fitting 100 and the underlying structure, and therefore will not induce significant stresses in the splice joints 106a to 106d. However, in other examples, the fitting 100 may include a metallic material, such as aluminum, titanium, steel, etc. In those cases where the aircraft is not expected to experience wide temperature fluctuations during operation, the use of metal may be appropriate.

[0056] In addition to composite materials and metal materials, in some other examples, the skin 108, strips 120, accessories 100 and stringers 114, 116 and combinations thereof may include other materials, including hybrid materials such as fiber / metal laminates. Such laminates include glass fiber / aluminum laminates and titanium reinforced graphite laminates (Ti / Gr). A hybrid laminate including alternating layers of aluminum and glass fiber is called glass laminated aluminum reinforced epoxy (GLARE). This laminate can provide better fatigue performance than traditional aluminum. Ti / Gr laminates can provide weight advantages over traditional aluminum or graphite-epoxy, but this laminate may also be more expensive.

[0057] Figure 2DThe splice joint 106a shown is characterized in that the fitting 100 overlaps the strip 120. One advantage of this feature is that it provides a fail-safe redundant load path in the unlikely event that a crack or other structural defect propagates through a portion of the strip 120. In this case, the combination of the fitting 100 and the strip can carry the structural loads through the splice joint 106a. In addition, the fitting 100 also provides a redundant load path through the splice joint 106a from the location where the opposing stringers 114, 116 respectively terminate. In addition, if a segmented strip 120 is used, the fitting 100 can also be used as a splice plate for adjacent strip segments. Another feature of the splice joint 106a is that the ends of the stringers 114, 116 remain open. One advantage of this feature is that it allows moisture caused by condensation and other sources to escape the stringers 114, 116.

[0058] Another feature of the fitting 100 of the illustrated example is that the stringer extensions 136a-136d can increase the stiffness of the fitting 100. The extensions also increase the stiffness of the splice between the stringer and the strap, particularly when the fitting is positioned as shown with the extensions proximate the raised portions 124 of the stringers 114, 116. One advantage of this configuration is that it can increase the stability of the splice joint 106A, particularly under compressive loads.

[0059] refer to Figure 2D , Figure 3 and Figure 4 , Figure 3 1 is a close-up front perspective view of fittings 100a and 100b attached to first and second flanges 126a, 126b, respectively, of stringer 114a and to strap 120 (without frame 140) extending along splice joint 106a. Stringer 114a extends along first panel in direction D1 parallel to the longitudinal axis of the aircraft and transverse to edge 113a of panel 112a. Stringer 114a includes second flange 126b spaced from the first flange and mounted on first panel major face 111a. Raised portion 124 between the first and second flanges extends beyond the first and second flanges away from the first panel major face.

[0060] The strip 120 is superimposed over the splice joint 106a to bridge the first panel 112a to the second panel 112b. The strip 120 can be positioned relative to the stringer 114a such that the first panel region 123a of the strip is positioned proximate to the stringer terminal 115c. The strip can include adjacent strip segments S1 and S2 joined by a sealant at a gap 120g. In addition, the gap can include a chamfer feature for accommodating the sealant.

[0061] In this example, the first fitting 100a includes an intermediate base 133a that bridges the first strap base 131a to the first stringer base 132a. The first fitting also includes an intermediate extension 134a that bridges the strap extension 135a to the first stringer extension 136a. The intermediate extension 134a extends laterally from the intermediate base 133a, giving the fitting a generally "L" shape. A rounded first joint 137a joins the first stringer base to the first stringer extension, a rounded second joint 138a joins the first strap base to the first strap extension, and a rounded third joint 139a joins the first intermediate base to the first intermediate extension.

[0062] The first stringer base 132a includes a first fitting surface 141a in contact with the first flange of the first stringer. The first strap base includes a second fitting surface 142a opposite the strap. The intermediate base 133a includes a third fitting surface 143a facing the first panel. The first strap base includes a fourth fitting surface 144a facing the strap and the first panel. The first stringer extension includes a first distal edge 151a at a distal end of the first stringer base. The first strap extension has a second distal edge 152a at a distal end of the first strap base. The intermediate extension includes a third distal edge 153a at a distal end of the first intermediate base.

[0063] The first stringer extension 136a of the fitting 100a is positioned proximate to the raised stringer portion 124, preferably within a distance of 0.09-0.1 inches, to provide stability to the fitting in compression and reduce out-of-plane loads on the stringer 114c and the first panel 112a.

[0064] For ease of illustration, the various bases and extensions are shown as separate parts of the accessory. Preferably, the accessory is made of a single unitary structure, wherein the various parts have the described features. In some instances, the transitions between these parts may not be well defined.

[0065] As described above, the second fitting 100b attached to the flange 126b of the stringer 114a is substantially a mirror image of the fitting 100a. Therefore, corresponding parts are numbered with "b" instead of "a". Figure 3 As shown, the second strap base 131b includes a second fitting surface 142b opposite the strap. The second stringer extension 136b includes a first distal edge 151b distal to the second stringer base. The second strap extension has a second distal edge 152b distal to the second strap base. The intermediate extension 134b includes a third distal edge 153b distal to the second intermediate base.

[0066] The first and second fittings are arranged in a mirrored relationship with respect to a longitudinal rail raised portion 124 disposed between the first and second flanges. As shown, the first and second longitudinal rail extended portions are disposed on opposite sides of the longitudinal rail raised portion 124, with the first and second longitudinal rail bases extending away from the longitudinal rail raised portion 124. A plurality of fasteners 160 secure the fittings 100a and 100b to the flanges 126a and 126b of the longitudinal rail 114a and the strap 120, and to the first panel 112a.

[0067] Again briefly refer to Figure 2D , a third fitting 100c is attached to the second flange 127b of the stringer 116a. The third fitting is substantially similar to the first fitting 100a described above. Accordingly, corresponding components are numbered accordingly. The third stringer base 132c includes a first fitting surface that contacts the second flange 127b of the third stringer 116c. The third strap base 131c includes a second fitting surface 143c (i.e., an exposed surface) opposite the strap. The third stringer extension 136c includes a first distal edge 151c at a distal end of the third stringer base. The third strap raised portion has a second distal edge 152c at a distal end of the third strap base. The third intermediate extension 134c includes a third distal edge 153c at a distal end of the third intermediate base.

[0068] The second and third fittings are arranged in a mirrored relationship relative to the plane 107a of the circumferential splice joint 106a. The second and third fittings are placed on respective opposite sides of the strip 120, with the second and third stringer bases extending in opposite directions from the splice joint 106a. A plurality of fasteners 160 secure the fittings to respective stringers and strips, and to respective panels.

[0069] Figure 4 It is along Figure 3 4-4. This view represents an example of a portion of a spliced ​​joint, showing a side view of the fitting 100b in the fitting splice. This example is an illustration of a fitting for a joint splice.

[0070] In this example, the first fitting surface 141b of the second stringer base 132b contacts the second flange 126b mounted on the first panel 112a and extends along a first line 146 in a first plane P1 orthogonal to the first edge of the first panel. The plane P1 corresponds to Figure 4The second strip base 131b is in contact with the first panel area 123a of the second surface of the strip 120 mounted on the first panel 112a and extends along a second line 147 in the plane P1. The second fitting surface 142b opposite the strip extends along the strip in the first plane P1 parallel to the second line 147. The third fitting surface 143b of the intermediate base 133b facing the panel 112a extends along a third line 148 in the plane P1. The second line 147 is transverse to the first line 146, and the third line 148 is transverse to both the first line 146 and the second line 147.

[0071] like Figure 4 As shown, the second strip base of the accessory includes a fourth accessory surface 144b facing the second strip surface and opposite the second accessory surface 142b. The fourth accessory surface is substantially parallel to the second accessory surface, and thus the first strip base 131b has a constant thickness along the second line 147.

[0072] The second stringer base 132b has a thickness along the second flange that tapers with distance from the strip. In other words, the thickness of the second stringer base tapers with increasing distance from the strip. In one example, the taper may include a slope of 40:1. After traversing a distance of 40 mm in a direction away from the strip along the first line 146, the thickness of the stringer base in a direction orthogonal to the first surface decreases by a ratio corresponding to 1 mm.

[0073] The second distal edge 151b of the first longitudinal beam extension 136b extends along a first edge line 156b and is parallel to the first line 146. The second distal edge 152b of the second strap extension 135b extends along a second edge line 157b parallel to the second line 147. The third distal edge 153b of the intermediate extension 134b extends along a third edge line 158b parallel to the third line 148.

[0074] The second line 147 forms a first acute angle B1 with the first line 146. The third line 148 forms a second acute angle B2 with the first line 146. The second edge line forms the first acute angle B1 with the first edge line. The third edge line forms a second acute angle B2 with the first edge line. In one example, the first acute angle can be less than the second acute angle. The acute angles B1 and B2 are selected so that when the fitting surface 141b of the stringer base is flush with the contact surface of the stringer flange 126B, the fitting surface 144B of the strip base will be flush with the strip second surface. In other examples, the first acute angle can be greater than the second acute angle.

[0075] The above-described relatively angled portions of the fitting are built into the design of the fitting 100b, which allows the fitting to be manipulated relative to the surface of the flange 126b and the first panel area of ​​the strap to obtain mating of the fitting surface with the stringer and strap surfaces. The fitting 100b can be moved from position A1, shown in dashed lines, to position A2 in the direction indicated by arrow AA to obtain continuous mating of the strap base and the first panel area of ​​the strap, eliminating the gap indicated by the distance between arrows B and B'. The intermediate base 133b specifically addresses the differences in thickness, relative position and orientation of the strap and stringer flanges in the fuselage structure splice and facilitates an overall shimless splice joint.

[0076] exist Figure 5 In the example shown, the stringer 114m is attached to the first major face 111a of the first panel 112a. The stringer 114m has a hat-shaped structure including a hat segment 114m1 and first and second side walls 114m2 and 114m3 extending from opposite sides of the hat segment.

[0077] The stringer 114m also includes a first flange 126m extending from the first side wall 114m2, and a second flange 126n extending from the second side wall 114m3. The first flange 126m and the second flange 126n extend away from each other in opposite directions and may be parallel to the cap segment 114m1. For example, the first flange and the second flange may be coplanar and may define a plane parallel to a plane generally defined by the cap segment. As shown, the first flange 126m and the second flange 126n have corresponding bottom surfaces that are attached to the first panel 112a so that the stringer 114m reinforces, strengthens and strengthens the first panel. The exemplary accessory 100a is attached to the flange 126m by a fastener 160 to further secure the stringer to the panel 112a. The fastener may preferably be fastened at a distance 170 within a range of 0.09-0.11 inches from the beginning of the extension 135a of the accessory. The accessory may preferably be mounted at a distance 180 within a range of 0.09-0.11 inches from the second side wall 114m2.

[0078] exist Figure 5In the example shown, the first side wall 114m2 and the second side wall 114m3 extend from the cap segment 114m1 and intersect with the panel to form an acute angle at the joint. In other examples, the first side wall 114m2 and the second side wall 114m3 may form an obtuse angle or a substantially right angle with the panel. The angle between the panel 112a and the first side wall 114m2 at the first joint 114j1 may be equal to or unequal to the angle between the panel 112a and the second side wall 114m3 at the second joint 114j2. In addition, the composite adhesive materials 114c1 and 114c2 extend along the first joint and the second joint between the first panel and the first longitudinal beam, respectively, and are adhesively attached to the first panel and the first longitudinal beam. The composite adhesive material may have a plurality of composite layers to have a shape that substantially conforms to the space between the first panel and the longitudinal beam side wall at the first joint and the second joint.

[0079] B. Illustrative piece with stepped edges

[0080] like Fig. 6A and Figure 6B As shown, this section describes an illustrative splicing accessory 600. Splicing accessory 600 is another example of an accessory that can be used to construct a thermoplastic circumferential splice as described above. Splicing accessory 600 is substantially similar to splicing accessories 100a to 100d described in Example A above. Therefore, corresponding parts are numbered accordingly. Those aspects of accessory 600 that differ from splicing accessories 100a to 100d are described below.

[0081] Fig. 6A A cross-sectional view of a fitting 600 attached to a strip 120 and a stringer flange 126b mounted to a first panel 112a is shown. A first fitting surface 641 of a stringer base 632 contacts the stringer flange 126b. A second fitting surface 642 of the strip base 631 is opposite the first panel region of the strip. A third fitting surface 643 of the intermediate base faces the first panel region of the strip. In addition, the strip base 631 has a constant thickness, and a fourth fitting surface 644 of the strip base 631 is opposite the second fitting surface and faces and is spaced apart from the first panel region of the strip.

[0082] As referenced above Figure 2B As mentioned with reference to the strip 120 described above, the first panel region 123a of the second strip surface 123 terminates at a strip edge 123a2 distal to the first edge of the first panel. The strip edge 123a2 is spaced apart from the first strip surface 121. The strip includes a strip side 123f1 that connects and is transverse to each of the first strip surface and the second strip surface.

[0083] like Fig. 6AAs shown, the strip base has a first thickness T2 transverse to the fourth accessory surface. The intermediate base has a second thickness T3 transverse to the third accessory surface. In this example, the first thickness T2 is less than the second thickness T3. The first thickness T2 is preferably at least one tenth of the second thickness T3.

[0084] The first fitting 600 includes a mating end face 660 connecting the third fitting surface 643 to the fourth fitting surface 644. In other words, the mating end face 660 represents a stepped fitting edge that joins the third fitting surface to the fourth fitting surface, and the mating end face 660 faces the strip side face 123f1. In one example, the mating end face 660 is spaced apart from the strip side face 123f1 by a gap G1. The gap G1 is preferably about 0.25 inches or less.

[0085] The above-described stepped edge of the fitting 600 is built into the design of the fitting 600, which allows the fitting to be manipulated along the surface of the flange 126b and the first panel area of ​​the strip to obtain mating of the fitting surface with the flange and strip surfaces during installation. Figure 6B As shown, gap G1 provides space to allow fitting 600 to move toward the splice joint (to the right as shown) until the surface of the fourth fitting surface contacts the first panel area of ​​the strap. The stepped edge feature specifically addresses the differences in thickness and orientation of straps and stringer flanges in fuselage structure splices and facilitates the construction of an integral shimless splice joint.

[0086] C. Exemplary Method of Manufacturing a Fuselage Structure

[0087] This section describes the steps of an exemplary method 700 for manufacturing a fuselage structure; see Figure 7 Aspects of the aforementioned splice fittings, stringers, straps, and / or any fuselage components may be utilized in the method steps described below. Where appropriate, reference may be made to components and systems that may be used to perform each step. These references are for illustrative purposes only and are not intended to limit the possible manner in which any particular step of the method may be performed.

[0088] Figure 7 700 is a flowchart showing steps performed in an illustrative method and may not list all steps of a complete process or other processes comprising the illustrated method. Although the individual steps of method 700 are described below and in Figure 7 Although depicted in the flowchart, these steps do not necessarily have to be performed in their entirety, and in some cases may be performed simultaneously or in an order different from that shown.

[0089] Step 710 includes positioning a first panel region 123a of a strip 120 along a first edge 113a of a first panel 112a. The strip has a strip first surface 121 in contact with the first panel major surface 111a. The first panel region 123a of the strip second surface 123 tapers toward the first panel as the distance from the first edge 113a of the first panel increases, and extends away from the first edge of the first panel at a first angle relative to the strip first surface. In some examples, step 710 also includes positioning a plurality of strip segments continuously along the first edge of the first panel to form the strip.

[0090] Optional step 712 includes attaching the strip directly to the first panel prior to attachment of the accessory. The strip first surface contacts the first panel major surface and typically has a smooth continuous surface to provide a continuous contact area for attachment. The strip can be attached to the first panel with a plurality of fasteners 160 that extend through the strip and the first panel. In other examples, the strip can be bonded or bonded and fastened to the first panel.

[0091] Step 714 includes mounting a first flange 126a of a first stringer 114a to a first panel, wherein the first stringer extends away from a first edge of the first panel. The first flange of the first stringer can be connected to the first panel using a plurality of fasteners 160 extending through the first flange and the first panel. In some examples, step 714 also includes adhesively attaching the first stringer to the first panel by applying a composite adhesive material. The adhesive material can extend along a joint between the first panel and the first stringer, such as Figure 5 shown.

[0092] Step 716 includes positioning the first stringer base 132b of the first fitting 100b on the first flange 126a of the first stringer 114a. The first stringer base may extend along a first line 146 extending in a first plane P1 orthogonal to the first edge of the first panel, as shown in FIG. Figure 4 As shown. The first stringer base may have a thickness along the first flange that tapers with distance from the strip. The first stringer base may have a first fitting surface 141b in contact with the first flange. The first fitting surface may extend parallel to the first line.

[0093] Step 718 includes positioning a strip base 131b of a fitting 100b on the strip. The first strip base may extend along a second line 147 extending in a first plane P1. The second line may be transverse to the first line at a first angle B1. In one example, the first strip base may have a constant thickness along the second line. The first strip base may have a second fitting surface 142b opposite the strip. The second fitting surface may extend along the strip parallel to the second line. The first strip base may have a third fitting surface 144b facing the strip. In some examples, step 718 also includes moving the first fitting toward or away from the strip so as to obtain continuous contact between the third fitting surface of the strip base and the strip. This feature reduces the need for shims or fillers during the method of manufacturing a fuselage structure by placing a surface of the strip base of the first fitting in continuous contact with the second surface of the strip.

[0094] Step 720 includes connecting the first rail base 132b of the first fitting 100b to the first flange 126b of the first rail 114a. The first rail base may be connected to the first flange by any effective method, including but not limited to fasteners 160 extending through the first rail base and the first flange.

[0095] Step 722 includes connecting the first strap base 131b to the strap 120. The first strap base can be connected to the strap by any effective method, including but not limited to fasteners 160 extending through the first strap base and the strap. In some examples, step 722 can include connecting the first strap base to the panel through the strap, which can also connect the strap to the panel.

[0096] D. Illustrative Method Using a Piece with a Stepped Edge

[0097] This section describes the steps of an illustrative method 800 for positioning an accessory relative to a strap; see Figure 8 Aspects of the aforementioned splice fittings, stringers, straps, and / or any fuselage components may be utilized in the method steps described below. Where appropriate, reference may be made to components and systems that may be used to perform each step. These references are for illustration and are not intended to limit the possible manner in which any particular step of the method may be performed.

[0098] Figure 8 800 is a flowchart showing the steps performed in an illustrative method and may not list the complete process or all steps of the method. Although the various steps of method 800 are described below and in Figure 8 Although depicted in the flowchart, these steps do not necessarily have to be performed in their entirety, and in some cases may be performed simultaneously or in an order different from that shown.

[0099] Method 800 may be an example of steps that may be performed in step 718 of method 700. Step 802 includes positioning the first accessory 600 relative to the strap 120. The first accessory has a first stringer base 632, a first strap base 631, and a stepped accessory edge 660, such as Fig. 6A and Figure 6B As shown. The first accessory surface 641 can be joined to the third accessory surface 644 by a stepped accessory edge. In this example, the strip first surface 121 is connected to the strip second surface 123a by the strip side 123f1. The first accessory is positioned relative to the strip so that the stepped accessory edge faces the strip side.

[0100] Step 804 includes moving the fitting along the longeron flange so that the stepped fitting edge of the fitting moves toward or away from the strip side. The fitting is appropriately moved to place the surface of the strip base of the fitting in continuous contact with the strip second surface. This manipulation of the fitting reduces the need for shims or fillers during the method of manufacturing the fuselage structure because the surface of the strip base is in continuous contact with the strip second surface.

[0101] Illustrative combinations and further examples

[0102] This section describes additional aspects and features of fuselage structural splices, which are presented as a series of paragraphs, some or all of which may be alphanumeric for clarity and effectiveness. Each of these paragraphs may be combined in any suitable manner with one or more other paragraphs and / or with disclosures from elsewhere in this application. Some of the following paragraphs explicitly refer to and further limit other paragraphs, providing examples of some suitable combinations, without limitation.

[0103] A0. A fuselage structure splicing part, comprising:

[0104] a first panel having a first panel major surface and a first edge;

[0105] a strip connected to the first panel, wherein the strip extends along a first edge of the first panel and has a first strip surface in contact with a major surface of the first panel and a second strip surface that tapers toward the first panel with distance from the first edge of the first panel;

[0106] a first longitudinal beam mounted on the first panel main surface, extending away from the first edge of the first panel, and having a first flange mounted to the first panel main surface; and

[0107] A first fitting has a first stringer base and a first strap base, wherein the first stringer base is connected to the first flange of the first stringer and extends along a first line extending in a first plane orthogonal to the first edge of the first panel, the first strap base is mounted on a second strap surface and extends along a second line in the first plane, the second line is transverse to the first line, and the first strap base has a constant thickness along the second line.

[0108] A1. A fuselage structural splice according to paragraph A0, wherein the first stringer base has a first fitting surface that contacts the first flange and extends parallel to the first line, and the first strap base has a second fitting surface opposite the strap, and the second fitting surface extends along the strap in a first plane parallel to the second line.

[0109] A2. The fuselage structural splice of paragraph A0, wherein the first stringer base has a thickness along the first flange that tapers with distance from the strap.

[0110] A3. A fuselage structural splicing piece according to paragraph A0, wherein the first accessory also includes a first longitudinal beam extension portion and a first strip extension portion, the first longitudinal beam extension portion extends laterally from the first longitudinal beam base, the first strip extension portion extends laterally from the first strip base, the first longitudinal beam extension portion has a first distal edge, the first distal edge is at the distal end of the first longitudinal beam base and extends along a first edge line parallel to the first line, the first strip extension portion has a second distal edge, the second distal edge is at the distal end of the first strip base and extends along a second edge line parallel to the second line, and the first distal edge extends laterally to the second distal edge.

[0111] A4. The fuselage structural splice of paragraph A3, wherein the first fitting includes a first rounded joint joining the first stringer base to the first stringer extension, and a second rounded joint joining the first strap base to the first strap extension.

[0112] A5. The fuselage structural splice of paragraph A0, wherein the first stringer includes a second flange spaced apart from the first flange and mounted to the main surface of the first panel, and a raised portion between the first flange and the second flange extending away from the first panel beyond the first flange and the second flange; and the fuselage structural splice further includes:

[0113] A second fitting has a second stringer base and a second strap base, wherein the second stringer base is connected to the second flange of the first stringer and extends along a third line extending in a second plane orthogonal to the first edge of the first panel, the second strap base is mounted on the second strap surface and extends along a fourth line in the second plane, the fourth line is transverse to the third line, and the second strap base has a constant thickness along the fourth line.

[0114] A6. A fuselage structural splice according to paragraph A5, wherein the second longitudinal beam base has a third fitting surface that contacts the second flange and extends parallel to the third line, the second strap base has a fourth fitting surface opposite the strap, and the fourth fitting surface extends along the strap in a second plane parallel to the fourth line.

[0115] A7. A fuselage structural splice according to paragraph A5, wherein the first fitting and the second fitting are arranged in a mirror image relationship relative to a third plane parallel to the first plane and the second plane and disposed between the first plane and the second plane.

[0116] A8. The fuselage structure splice according to paragraph A0, further comprising:

[0117] a second panel having a second panel major face and a second edge, wherein the second edge is positioned to be edgewise aligned with the first edge of the first panel to form a splice joint, wherein the first panel major face is aligned with the second panel major face, wherein the first strip surface of the strip is in contact with the second panel major face;

[0118] a second stringer mounted on the second panel major surface, extending away from the splice joint and having a second flange mounted to the second panel major surface; and

[0119] A second fitting has a second stringer base and a second strip base, wherein the second stringer base is connected to the second flange of the second stringer and extends along a third line extending in a second plane orthogonal to the second edge of the second panel, the second strip base is mounted on the second strip surface and extends along a fourth line in the second plane, the fourth line is transverse to the third line, and the second strip base has a constant thickness along the fourth line.

[0120] A9. A fuselage structural splice according to paragraph A8, wherein the second longitudinal beam base has a third fitting surface that contacts the second flange and extends parallel to the third line, the second strap base has a fourth fitting surface opposite the strap, and the fourth fitting surface extends along the strap in a second plane parallel to the fourth line.

[0121] A10. A fuselage structural splice as described in paragraph A0, wherein the first fitting includes an intermediate base connecting the first stringer base to the first strap base, the intermediate base having a third fitting surface facing the first panel, the third fitting surface extending along a third line extending in the first plane, and the third line is transverse to the first line and the second line.

[0122] A11. The fuselage structure splice of paragraph A10, wherein the second line forms a first acute angle with the first line, the third line forms a second acute angle with the first line, and the first acute angle is smaller than the second acute angle.

[0123] A12. The fuselage structural splice of paragraph A0, wherein a thickness of the first stringer base in a direction transverse to the first fitting surface is greater than a thickness of the first strap base in a direction transverse to the second fitting surface.

[0124] A13. The fuselage structure splice of paragraph A12, wherein the first strap base includes a third fitting surface opposite the second fitting surface, the third fitting surface facing the second strap surface and extending along a third line in the first plane, wherein the third line is parallel to the second line.

[0125] A14. A fuselage structural splice as described in paragraph A12, wherein the first panel region of the second strip surface terminates at a strip edge that is distal to the first edge of the first panel, the strip edge is spaced apart from the first strip surface, the strip includes a strip side connecting the first strip surface to the second strip surface, the first accessory also includes a stepped accessory edge joining the first accessory surface to the third accessory surface, and the stepped accessory edge faces the strip side.

[0126] A15. A fuselage structure splice as described in paragraph A14, wherein the stepped accessory edge is spaced apart from the strip side by a gap.

[0127] A16. A fuselage structural splice as described in paragraph A0, wherein the first fitting also includes a first stringer extension portion extending laterally from the first stringer base, the first stringer includes a second flange spaced apart from the first flange and mounted to the first panel, and a raised stringer portion extending away from the first panel beyond the first flange and the second flange between the first flange and the second flange, and the first stringer extension portion is positioned adjacent to the raised stringer portion.

[0128] A17. A fuselage structural splice as described in paragraph A0, wherein the first longitudinal beam includes a second flange spaced apart from the first flange and mounted to the first panel, and a raised longitudinal beam portion extending away from the first panel beyond the first flange and the second flange between the first flange and the second flange, and the fuselage structural splice further includes a composite adhesive material that extends along a joint between the first panel and the first longitudinal beam and is adhesively attached to the first panel and the first longitudinal beam.

[0129] A18. The fuselage structural splice of paragraph A0, wherein the strap is comprised of a plurality of strap segments positioned continuously along the first edge of the first panel.

[0130] B0. An accessory for a fuselage structural splice, wherein the fuselage structural splice includes: a first panel having a first panel main face and a first edge; a strip connected to the first panel, wherein the strip extends along the first edge of the first panel and has a first strip surface in contact with the first panel main face and a second strip surface that tapers toward the first panel with a distance from the first edge of the first panel; and a stringer mounted on the first panel main face, extending away from the first edge of the first panel and having a first flange mounted to the first panel main face; wherein the accessory includes an elongated base having a stringer base and a strip base, wherein the stringer base is configured to be connected to the first flange of the stringer and extend along a first line extending in a first plane orthogonal to the first edge of the first panel, and the strip base is configured to be mounted on the second strip surface and extend along a second line in the first plane, the second line being transverse to the first line, and the strip base has a constant thickness along the second line.

[0131] B1. A fuselage structural splice according to paragraph B0, wherein the stringer base has a first fitting surface configured to contact the first flange and extend parallel to the first line, the strap base has a second fitting surface extending along the strap and opposite thereto, and the second fitting surface extends along the strap in a first plane parallel to the second line.

[0132] B2. The accessory of paragraph B0, wherein the stringer base has a thickness along the first line that tapers with distance from the strap base.

[0133] B3. The accessory according to paragraph B0 also includes a longitudinal beam extension portion and a strip extension portion, wherein the longitudinal beam extension portion extends laterally from the longitudinal beam base, the strip extension portion extends laterally from the strip base, the longitudinal beam extension portion has a first distal edge, which is at the distal end of the longitudinal beam base and extends along a first edge line parallel to the first line, the strip extension portion has a second distal edge, which is at the distal end of the strip base and extends along a second edge line parallel to the second line, and the first distal edge extends transversely to the second distal edge.

[0134] B4. The accessory of paragraph B3, further comprising a first rounded joint joining the stringer base to the stringer extension, and a second rounded joint joining the strap base to the strap extension.

[0135] B5. The accessory of paragraph B0 further includes an intermediate base connecting the longitudinal beam base to the strip base, the intermediate base having a third accessory surface facing the first panel, the third accessory surface extending along a third line extending in the first plane, and the third line is transverse to the first line and the second line.

[0136] B6. An accessory according to paragraph B5, wherein the second line forms a first acute angle with the first line, the third line forms a second acute angle with the first line, and the first acute angle is smaller than the second acute angle.

[0137] B7. The accessory of paragraph B0, wherein the thickness of the stringer base in the first plane is greater than the thickness of the strap base in the first plane.

[0138] B8. The fuselage structure splice of paragraph B7, wherein the strap base includes a third fitting surface opposite the second fitting surface, the third fitting surface facing the second strap surface and extending along a third line in the first plane, wherein the third line is parallel to the second line.

[0139] B9. The accessory of paragraph B8, further comprising a stepped accessory edge joining the first accessory surface to the third accessory surface and facing away from the stringer base.

[0140] B10. An accessory according to paragraph B0, wherein the longitudinal beam includes a raised longitudinal beam portion extending from the first flange away from the first panel, and the accessory also includes a longitudinal beam extension portion extending laterally from the longitudinal beam base, and the accessory is constructed to be mounted on the flange, wherein the longitudinal beam extension portion is positioned adjacent to the raised longitudinal beam portion.

[0141] C0. A method for manufacturing a fuselage structure, comprising the following steps:

[0142] positioning a first panel region of a strip along a first edge of the first panel, the strip having a strip first surface in contact with a major surface of the first panel and a strip second surface that tapers toward the first panel with distance from the first edge of the first panel and extends away from the first edge of the first panel at a first angle relative to the strip first surface;

[0143] mounting a first flange of a first stringer to the first panel, wherein the first stringer extends away from a first edge of the first panel;

[0144] positioning a first stringer base of a first fitting on a first flange of a first stringer, wherein the first stringer base extends along a first line extending in a first plane orthogonal to a first edge of the first panel;

[0145] positioning a first strip base of a first accessory on the strip, wherein the first strip base extends along a second line extending in a first plane, the second line being transverse to the first line at a first angle, wherein the first strip base has a constant thickness along the second line;

[0146] connecting the first longitudinal beam base to the first flange of the first longitudinal beam; and

[0147] Attach the first strip base to the strip.

[0148] C1. The method of paragraph C0, wherein the first longitudinal beam base has a first fitting surface in contact with the first flange and extending parallel to the first line, the first strip base has a second fitting surface opposite the strip, and the second fitting surface extends along the strip parallel to the second line.

[0149] C2. A fuselage structure splice according to paragraph C1, wherein the first strap base includes a third fitting surface opposite the second fitting surface, the third fitting surface facing the second strap surface and extending along a third line in the first plane, wherein the third line is parallel to the second line.

[0150] C3. The method according to paragraph C0 further includes:

[0151] mounting a second flange of the first stringer to the first panel, wherein the second flange is spaced apart from the first flange, and the raised stringer portion extends between the first flange and the second flange and extends away from the first panel beyond the first flange and the second flange;

[0152] positioning a second stringer base of the second fitting on the second flange of the first stringer, wherein the second stringer base extends along a third line extending in a second plane orthogonal to the first edge of the first panel;

[0153] positioning a second strip base of a second accessory on the strip, wherein the second strip base extends along a fourth line extending in the second plane, the fourth line being transverse to the third line at a first angle, wherein the second strip base has a constant thickness along the fourth line;

[0154] connecting the second longitudinal rail base to the second flange of the first longitudinal rail; and

[0155] Attach the second strip base to the strip.

[0156] C4. The method of paragraph C3, wherein the second longitudinal beam base has a third fitting surface in contact with the second flange and extending parallel to the third line, the first strip base has a fourth fitting surface opposite the strip, and the fourth fitting surface extends along the strip in a second plane parallel to the fourth line.

[0157] C5. A method according to paragraph C3, wherein positioning the second accessory includes positioning the second accessory relative to the first accessory in a mirror relationship relative to a third plane, the third plane being parallel to the first plane and the second plane and disposed between the first plane and the second plane.

[0158] C6. The method according to paragraph C0 further includes:

[0159] positioning a second edge of a second panel having a second panel major face in edgewise alignment with a first edge of a first panel having a first panel major face to form a splice joint wherein the first panel major face is aligned with the second panel major face;

[0160] positioning a second panel region of the strip along a second edge of the second panel, the strip extending along the second edge of the second panel and having a strip first surface in contact with a major surface of the second panel, the strip second surface tapering toward the second panel with distance from the second edge of the second panel and extending away from the second edge of the second panel at a first angle relative to the strip first surface;

[0161] mounting a second flange of a second stringer to the second panel, wherein the second stringer extends away from the splice joint;

[0162] positioning a second stringer base of the second fitting on a second flange of the second stringer, wherein the second stringer base extends along a third line extending in a second plane orthogonal to a second edge of the second panel;

[0163] positioning a second strip base of a second accessory on the strip, wherein the second strip base extends along a fourth line extending in the second plane, the fourth line being transverse to the third line at a first angle, wherein the second strip base has a constant thickness along the fourth line;

[0164] connecting the second longitudinal rail base to the second flange of the second longitudinal rail; and

[0165] Attach the second strip base to the strip.

[0166] C7. The method of paragraph C6, wherein the second longitudinal beam base has a third fitting surface in contact with the second flange and extending parallel to the third line, the first strip base has a fourth fitting surface opposite the strip, and the fourth fitting surface extends along the strip in a second plane parallel to the fourth line.

[0167] C8. A method according to paragraph C2, wherein the first accessory surface is joined to the third accessory surface by a stepped accessory edge, and positioning the first accessory surface includes positioning the first accessory wherein the stepped accessory edge faces a side of the strip connecting the first surface of the strip to the second surface of the strip.

[0168] C9. The method of paragraph C8, wherein positioning the first accessory so that the stepped accessory edge faces the side of the strip includes positioning the first accessory so that the stepped accessory edge is spaced apart from the side of the strip by a gap.

[0169] C10. A method according to paragraph C0, wherein the first accessory also includes a first longitudinal beam extension portion extending laterally from the first longitudinal beam base, the first longitudinal beam includes a second flange spaced apart from the first flange and mounted to the first panel, and a raised longitudinal beam portion extending away from the first panel beyond the first flange and the second flange between the first flange and the second flange, and the method also includes positioning the first longitudinal beam extension portion adjacent to the raised longitudinal beam portion.

[0170] C11. A method according to paragraph C0, wherein the first longitudinal beam includes a second flange spaced apart from the first flange, and a raised longitudinal beam portion between the first flange and the second flange extending away from the first panel beyond the first flange and the second flange, the method further comprising mounting the second flange of the first longitudinal beam to the first panel, and adhesively attaching the first panel to the first longitudinal beam by applying a composite adhesive material extending along a joint between the first panel and the first longitudinal beam.

[0171] C12. The method of paragraph C0, wherein positioning the strip includes positioning a plurality of strip segments continuously along the first edge of the first panel.

[0172] Advantages, Features and Benefits

[0173] The various examples of fittings described herein provide several advantages over known solutions for manufacturing fuselage structural splices. For example, the illustrative examples described herein allow a single fitting to connect two different components and generally need not be limited to a specific size and / or geometry of the components. Furthermore, the illustrative embodiments and examples described herein allow manipulation of a single fitting to obtain matching of a fitting surface to a component surface prior to fastening.

[0174] Additionally, the illustrative examples described herein may reduce or eliminate the need for shims and fillers during fabrication of fuselage structures; may facilitate uniform and standardized joining of multiple fuselage sections; and may provide load transfer continuity across fuselage structure splices, among other benefits.

[0175] No known system or device can perform these functions, particularly with an accessory configuration designed to conform the accessory surface to the surface of the component to which it is attached. Therefore, the illustrative examples described herein are particularly applicable to fuselage structural splices. However, not all examples described herein provide the same advantages or the same degree of advantages.

[0176] Summarize

[0177] The disclosure set forth above may include multiple different examples with independent utility. Although each of these is disclosed in its preferred form, its specific examples as disclosed and shown herein should not be considered restrictive, because many variations are possible. With regard to the section titles used in this disclosure, such titles are only used for organizational purposes. The subject matter of the present disclosure includes all novel and non-obvious combinations and sub-combinations of various elements, features, functions and / or characteristics disclosed herein. The following claims specifically point out certain combinations and sub-combinations that are considered to be novel and non-obvious. Other combinations and sub-combinations of features, functions, elements and / or characteristics may be claimed in applications claiming priority to this application or a related application. Such claims, whether their scope is wider, narrower, the same or different than the original claims, are considered to be included in the subject matter of the present disclosure.

Claims

1. A fuselage structure splicing part, wherein: The fuselage structure splicing parts include: a first panel having a first panel major surface and a first edge; a strip connected to the first panel, wherein the strip extends along the first edge of the first panel and has a first strip surface in contact with a major surface of the first panel and a second strip surface that tapers toward the first panel with distance from the first edge of the first panel; a first longitudinal beam mounted on the first panel main surface, extending away from the first edge of the first panel, and having a first flange mounted to the first panel main surface; and a first fitting having a first stringer base and a first strap base, wherein the first stringer base is connected to the first flange of the first stringer and extends along a first line extending in a first plane orthogonal to the first edge of the first panel, the first strap base is mounted on the second strap surface and extends along a second line in the first plane, the second line being transverse to the first line, and the first strap base has a constant thickness along the second line; wherein the first fitting includes an intermediate base connecting the first stringer base to the first strap base, the intermediate base having a third fitting surface facing the first panel, the third fitting surface extending along a third line extending in the first plane, and the third line being transverse to the first line and the second line; wherein the first stringer base has a first fitting surface that contacts the first flange and extends parallel to the first line, and the first strap base has a second fitting surface that is opposite the strap and extends along the strap in the first plane parallel to the second line; wherein the first panel region of the second strip surface terminates at a strip edge distal to the first edge of the first panel, the strip edge being spaced apart from the first strip surface, the strip comprising a strip side connecting the first strip surface to the second strip surface, the first strip base having a fourth fitting surface opposite the second fitting surface and facing the first panel region and spaced apart from the first panel region and allowing contact with the first panel region, the first fitting further comprising a stepped fitting edge joining the third fitting surface to the fourth fitting surface, the stepped fitting edge facing the strip side; wherein the strip base has a first thickness transverse to the fourth accessory surface, wherein the intermediate base has a second thickness transverse to the third accessory surface, wherein the first thickness is less than the second thickness.

2. The fuselage structure splicing member according to claim 1, wherein: The first stringer includes a second flange spaced apart from the first flange and mounted to the main surface of the first panel, and a raised portion extending away from the first panel and beyond the first flange and the second flange between the first flange and the second flange; and the fuselage structure splice further includes: a second fitting having a second stringer base and a second strap base, wherein the second stringer base is connected to the second flange of the first stringer and extends along a third line extending in a second plane orthogonal to the first edge of the first panel, the second strap base is mounted on the second strap surface and extends along a fourth line in the second plane, the fourth line is transverse to the third line, and the second strap base has a constant thickness along the fourth line.

3. The fuselage structure splicing piece according to claim 1, further comprising: a second panel having a second panel major face and a second edge, wherein the second edge is positioned to be edgewise aligned with the first edge of the first panel to form a splice joint, wherein the first panel major face is aligned with the second panel major face, and wherein the first strip surface of the strip is in contact with the second panel major face; a second stringer mounted on the second panel major surface, extending away from the splice joint and having a second flange mounted to the second panel major surface; and a second fitting having a second stringer base and a second strap base, wherein the second stringer base is connected to the second flange of the second stringer and extends along a third line extending in a second plane orthogonal to the second edge of the second panel, the second strap base is mounted on the second strap surface and extends along a fourth line in the second plane, the fourth line is transverse to the third line, and the second strap base has a constant thickness along the fourth line.

4. The fuselage structure splicing member according to claim 1, wherein: The stepped fitting edge is spaced apart from the strip side by a gap.

5. The fuselage structure splicing member according to claim 1, wherein: The first accessory also includes a first stringer extension extending laterally from the first stringer base, the first stringer including a second flange spaced apart from the first flange and mounted to the first panel, and a raised stringer portion extending beyond the first flange and the second flange away from the first panel between the first flange and the second flange, and the first stringer extension is positioned proximate to the raised stringer portion.

6. The fuselage structure splicing member according to claim 1, wherein: The first stringer includes a second flange spaced apart from the first flange and mounted to the first panel, and a raised stringer portion extending beyond the first flange and the second flange away from the first panel between the first flange and the second flange, and the fuselage structural splice further includes a composite adhesive material extending along a joint between the first panel and the first stringer to be adhesively attached to the first panel and the first stringer.

7. The fuselage structure splicing member according to claim 1, wherein: The strip is comprised of a plurality of strip segments positioned continuously along the first edge of the first panel.

8. A method of manufacturing a fuselage structure, wherein: The method comprises the following steps: a panel region where a strip is positioned along an edge of the panel, the strip having a strip first surface in contact with a major face of the panel and a strip second surface that tapers toward the panel with distance from the edge of the panel and extends away from the edge of the panel at an angle relative to the strip first surface; mounting a first flange of a stringer to the panel, wherein the stringer extends away from the edge of the panel; positioning a first stringer base of a first fitting on the first flange of the stringer, wherein the first stringer base extends along a first line extending in a first plane orthogonal to the edge of the panel; positioning a first strap base of the first accessory on the strap, wherein the first strap base extends along a second line extending in the first plane, the second line being transverse to the first line at the angle, wherein the first strap base has a constant thickness along the second line; wherein the first fitting comprises an intermediate base connecting the first stringer base to the first strip base, the intermediate base having a third fitting surface facing the panel, the third fitting surface extending along a third line extending in the first plane, and the third line being transverse to the first line and the second line; wherein the first stringer base has a first fitting surface, the first fitting surface being in contact with the first flange and extending parallel to the first line, and the first strip base having a second fitting surface opposite the strip, and the second fitting surface extending along the strip in the first plane parallel to the second line; wherein the panel region of the strip second surface terminates at a strip edge distal to the edge of the panel an edge, the strip edge being spaced apart from the first strip surface, the strip comprising a strip side surface connecting the first strip surface to the second strip surface, the first strip base having a fourth fitting surface, the fourth fitting surface being opposite to the second fitting surface and facing the panel area and spaced apart from the panel area and allowing contact with the panel area, the first fitting further comprising a stepped fitting edge joining the third fitting surface to the fourth fitting surface, and the stepped fitting edge facing the strip side surface; wherein the strip base has a first thickness transverse to the fourth fitting surface, wherein the intermediate base has a second thickness transverse to the third fitting surface, wherein the first thickness is less than the second thickness; connecting the first stringer base to the first flange of the stringer; and Connecting the first strap base to the strap.

9. The method according to claim 8, further comprising: mounting a second flange of the stringer to the panel, wherein the second flange is spaced apart from the first flange, and a raised stringer portion extends between the first flange and the second flange and extends away from the panel beyond the first flange and the second flange; positioning a second stringer base of a second fitting on the second flange of the stringer, wherein the second stringer base extends along a third line extending in a second plane orthogonal to the edge of the panel; positioning a second strap base of the second accessory on the strap, wherein the second strap base extends along a fourth line extending in the second plane, the fourth line being transverse to the third line at the angle, wherein the second strap base has a constant thickness along the fourth line; connecting the second stringer base to the second flange of the stringer; as well as Connect the second strap base to the strap.

10. The method according to claim 9, wherein: Positioning the second accessory includes positioning the second accessory relative to the first accessory in a mirrored relationship relative to a third plane disposed between the first plane and the second plane.

11. The method according to claim 8, wherein: The first accessory also includes a first stringer extension extending laterally from the first stringer base, the stringer including a second flange spaced apart from the first flange and mounted to the panel, and a raised stringer portion extending away from the panel beyond the first flange and the second flange between the first flange and the second flange, and the method also includes positioning the first stringer extension proximate to the raised stringer portion.

12. The method according to claim 8, wherein: The stringer includes a second flange spaced apart from the first flange, and a raised stringer portion extending between the first flange and the second flange away from the panel beyond the first flange and the second flange, the method further comprising mounting the second flange of the stringer to the panel and adhesively attaching the panel to the stringer by applying a composite adhesive material extending along a joint between the panel and the stringer.

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