Bulkhead connector assembly

Abstract

Bulkhead joint assembly. A bulkhead joint assembly includes a carrier tape segment configured to be secured to a rear section of a fuselage and a forward section of the fuselage and extending through a bulkhead of the fuselage. The bulkhead joint assembly also includes a chord engaged and secured to the carrier tape segment, wherein the chord is configured to extend along the bulkhead to transfer forces from the bulkhead in shear between the chord and the carrier tape segment.

Description

Technical Field

[0001] Embodiments of the present disclosure relate generally to aircraft fuselages, and more particularly to a bulkhead for a fuselage. Background Art

[0002] The fuselage is the main body of the aircraft. Within the fuselage a bulkhead is provided to couple to the horizontal tail of the aircraft and to transfer loads from the horizontal tail through the bulkhead and to the structural components of the fuselage.

[0003] Extra care is taken to ensure that the bulkhead is installed correctly and transfers forces through the fuselage components without damaging the fuselage. The fuselage consists of many sections. With respect to the bulkhead, the sections surrounding the bulkhead are considered to be the aft section and the forward section, with the bulkhead spanning both sections. The bulkhead joint assembly connects and secures these components of the fuselage to facilitate the transfer of forces from the bulkhead to the structural elements of the aft section and the forward section.

[0004] Known examples of bulkhead joint assemblies include attaching opposing bulkheads of different sized split ring chords that are secured on opposite sides of the bulkhead. In one example, bathtub fittings are aligned and placed against the chords on opposite sides of the bulkhead and secured to corresponding aft and forward sections of the fuselage to form a tension joint between the bathtub fittings to resist movement of the bulkhead.

[0005] However, such tension-based bulkhead joint assemblies are inefficient in transmitting forces and require an intensive installation process. Additionally, such bulkhead joint assemblies of the fuselage include many components that need to be spliced, which also causes difficulty and complexity during manufacturing. In order to handle the bulkhead forces, for example, many of the components include metals such as aluminum that may corrode. Such metals are also expensive, increase manufacturing processes such as deburring, and require a high level of coordinated assembly processes for final installation and are generally difficult to function during installation. Additionally, often in order to reduce the effects of corrosion on such metals, corrosion resistant sealants are utilized, further increasing costs. Summary of the invention

[0006] There is a need for a bulkhead joint assembly for a fuselage that couples to the interior of the fuselage while effectively transferring forces on the bulkhead to other components of the fuselage. Additionally, there is a need for a bulkhead joint assembly design that minimizes the effects of corrosion on the fuselage and that minimizes spliced ​​parts, simplifies the manufacturing process, and reduces costs. Additionally, there is a need to simplify bulkhead joints to reduce the cost and complexity associated with the installation of bulkhead assemblies.

[0007] In view of those needs, certain embodiments of the present disclosure provide a bulkhead joint assembly including a carrier tape segment configured to be secured to a rear section of a fuselage and a front section of the fuselage and extending through a bulkhead of the fuselage. The bulkhead joint assembly also includes a chord engaged and secured to the carrier tape segment, wherein the chord is configured to extend along the bulkhead to transfer forces from the bulkhead in shear between the chord and the carrier tape segment.

[0008] In at least one embodiment, a fuselage is provided, comprising a rear section and a front section that cooperatively receives the rear section at a bulkhead joint. A bulkhead extends around an interior of the rear section and an interior of the front section adjacent to the bulkhead joint. A bulkhead joint assembly secures the rear section to the front section and comprises a carrier tape segment secured to the rear section and extending to and secured to the front section. The carrier tape segment extends between the bulkhead and the bulkhead joint. The bulkhead joint assembly also includes a chord engaged and secured to the carrier tape segment, wherein the chord is configured to extend along the bulkhead to transfer forces from the bulkhead in shear between the chord and the carrier tape segment.

[0009] In at least one embodiment, a bulkhead joint assembly is provided, the bulkhead joint assembly including a carrier tape segment configured to be secured to a rear section and a front section and extending through a bulkhead. The bulkhead joint assembly also includes: a chord that engages and is secured to the carrier tape segment and is configured to extend along the bulkhead to transfer forces from the bulkhead in shear between the chord and the carrier tape segment; a rear stringer end fitting that is secured to the carrier tape segment and extends to the rear section and is configured to be secured to the rear section; and a front stringer end fitting that is secured to the carrier tape segment and extends to the front section and is configured to be secured to the front section. The bulkhead joint assembly also includes a T-shaped chord segment that is adjacent to the carrier tape segment. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 is a partial side plan view of a fuselage according to an embodiment of the present disclosure.

[0011] Figure 2 is a partially exploded perspective view of a body according to an embodiment of the present disclosure.

[0012] Figure 3 is a front perspective view of a bulkhead joint assembly according to an embodiment of the present disclosure.

[0013] Figure 4 is a rear perspective view of a bulkhead joint assembly according to an embodiment of the present disclosure.

[0014] Figure 5is a side cross-sectional view of a bulkhead joint assembly according to an embodiment of the present disclosure.

[0015] Figure 6 is a partial side cross-sectional view of a bulkhead joint assembly according to an embodiment of the present disclosure.

[0016] Figure 7 is a side perspective view of a strap section of a bulkhead joint assembly according to an embodiment of the present disclosure.

[0017] Figure 8 is a side perspective view of a stringer end fitting of a bulkhead joint assembly according to an embodiment of the present disclosure.

[0018] Fig. 9 is a side perspective view of a chord of a bulkhead joint assembly according to an embodiment of the present disclosure.

[0019] Fig.10 is a side perspective view of a T-chord of a bulkhead joint assembly according to an embodiment of the present disclosure. DETAILED DESCRIPTION

[0020] When read in conjunction with the accompanying drawings, the following detailed description of the preceding summary of the invention and certain embodiments will be better understood. As used herein, an element or step recorded in the singular and followed by the word "one" or "an" should be understood to not necessarily exclude multiple elements or steps. In addition, reference to "an embodiment" is not intended to be interpreted as excluding the existence of additional embodiments that also incorporate the described features. In addition, unless explicitly stated to the contrary, an embodiment that "contains" or "has" an element or multiple elements with a specific condition may include additional elements that do not have the condition.

[0021] Certain embodiments of the present disclosure provide a bulkhead joint assembly including a carrier tape segment configured to taper and extend below the bulkhead and receive stringer end fittings on both the front side of the bulkhead and the rear side of the bulkhead. The bulkhead joint assembly also includes a chord member secured to and extending along the bulkhead and also secured to and extending along the carrier tape segment. The chord receives forces transmitted from the bulkhead by being generally positioned between the bulkhead and the carrier tape segment and transmits the forces as shear forces to the carrier tape segment.

[0022] Figure 1 A partial side view of a fuselage 100 of an aircraft is illustrated. Figure 2 A partially exploded perspective view of the body 100 is shown. Figure 1 and 2 As shown, the fuselage 100 includes a rear section 102, a bulkhead 104 ( Figure 2 )、Bulkhead joint 106( Figure 1 )、pivot fitting 108( Figure 2 ), horizontal tail 110 and front section 112.

[0023] The rear section 102 of the fuselage includes an end point 114 of the aircraft and includes an outer shell 116 or skin having an interior or internal cavity 118 ( Figure 2 The housing 116 also includes a perimeter 120 that receives the front section 112 of the fuselage.

[0024] The bulkhead 104 includes a web body 122 including a front side 124, a rear side 126, a crown perimeter 128, a first side perimeter 130, a second side perimeter 132, and a keel perimeter 134. The web body 122 includes a plurality of horizontal support members 136 and vertical support members 138 around a bulkhead opening 140 at the front side 124, which is generally rectangular in shape in one example. The horizontal support members 136 and the vertical support members 138 are interconnected to each other to generally form a cross-hatched pattern around the bulkhead opening 140. In this manner, the bulkhead 104 is configured to receive and absorb forces from the horizontal tail 110 via the pivot fittings 108 secured to the web body 122. While the diaphragm 104 of this exemplary embodiment includes horizontal support members 136 and vertical support members 138 that are generally cross-hatched relative to one another, in other embodiments, support member positioning and shapes are utilized on the web body 122 to provide structural support for the diaphragm 104. Similarly, in other embodiments, only the horizontal support members 136 are on the front side 124 or the rear side 126. In another embodiment, only the vertical support members 138 are on the front side 124 or the rear side 126.

[0025] Pivot fitting 108 is secured to forward side 124 of web body 122 and pivotably engages horizontal stabilizer 110. In this manner horizontal stabilizer 110 is able to pivot relative to rear section 102 and forward section 112 of fuselage 100 in order to operate the aircraft.

[0026] The horizontal tail 110 includes a pivot pin 142 pivotally connected to the pivot fitting 108. This connection allows for pivotal movement between the horizontal tail 110 and the aft section 102. The horizontal tail 110 places a load on the bulkhead 104, which must absorb the load and transfer it to the rest of the fuselage structure.

[0027] Front section 112 is configured to matingly receive horizontal tailplane 110 to allow horizontal tailplane 110 to move relative to front section 112. Front section 112 also has a perimeter 144 configured to receive perimeter 120 of rear section 102.

[0028] A rear crown stringer end fitting 146 and a rear keel stringer end fitting 148 are also provided for coupling the rear section 102 to the bulkhead 104. Similarly, the front keel stringer end fitting 150 is also provided with a front crown stringer end fitting (not shown) for coupling the front section 112 to the bulkhead 104.

[0029] Figure 3 The illustrated separator 300 includes a partial view of a web body 302 disposed within the front section 308 viewed from within the front section 308 such that a front side 310 of the web body 302 is illustrated. Figure 4 A partial view of the bulkhead 300 including the web body 302 within the rear section 304 is illustrated such that the rear side 306 of the web body 302 is illustrated. Figure 5 A partial perspective view is illustrated with the rear section 304 and the front section 308 of the bulkhead 300 and the web body 302 removed. Figure 3 , Figure 4 and Figure 5 The bulkhead joint assembly 312 is collectively illustrated. Figure 3 , Figure 4 and Figure 5 The keel or bottom section of the bulkhead 300 is illustrated throughout, but the bulkhead joint assembly 312 can similarly be disposed on the crown or top section of the bulkhead 300 in the same manner as illustrated. Figure 1 and Figure 2 The partition 104, the rear section 304 is Figure 1 and Figure 2 The rear section 102 and the front section 308 are Figure 1 and Figure 2 The first part 112.

[0030] like Figure 5 As illustrated, the bulkhead joint assembly 312 couples and secures the rear section 304 and the front section 308 and is configured to also couple and secure the rear section 304 and the front section 308 to the bulkhead 300. The bulkhead joint assembly 312 includes a carrier band section 314, a stringer end fitting 316, a chord or chord section 318, and a T-shaped chord section 320 ( Figure 3 and Figure 5 ). The bulkhead joint assembly 312 is typically secured around the bulkhead perimeter 322.

[0031] The carrier tape segments 314 extend from the rear side 324 of the bulkhead 300, which is fixed to the rear section 304, to the front side 326 of the bulkhead 300, which is fixed to the front section 308. Specifically, the shape of each carrier tape segment 314 is generally arcuate to cooperatively engage both the rear section 304 and the front section 308. Each carrier tape segment 314 additionally extends under the bulkhead 300. In one example, the carrier tape segments 314 are fixed to the rear section 304 and the front section 308 by fasteners. In other embodiments, rivets, bolts, screws, bonding, welding, other fasteners, etc. are used. Although illustrated as multiple segments in the exemplary embodiment, the carrier tape segments 314 can be a single-piece construction depending on manufacturing requirements. In one example, a spliced ​​carrier tape is provided to be fixed to the bulkhead 300 or the corresponding chord segment 318 to provide additional strength to the bulkhead joint assembly 312. In one embodiment, the carrier tape segments 314 are made of composite fiber reinforced plastic (CFRP). By being made from CFRP, corrosion of the joint assembly 312 is minimized while manufacturing speed is increased because manufacturing steps including drilling, removal, and deburring of metal parts (such as bathtub fittings) are eliminated.

[0032] The stringer end fittings 316 are positioned in spaced relation to each other on both the rear side 324 and the front side 326 of the bulkhead 300 along the bulkhead perimeter 322 of the bulkhead 300. The stringer end fittings 316 each extend from a carrier end 328 to a fuselage section end 330. At the carrier end 328, the stringer end fittings 316 are secured to the corresponding carrier section 314, whereas at the fuselage section end 330, the stringer end fittings 316 are secured to the stringers of the rear section 304 or the front section 308. The stringer end fittings 316 thus provide a moment to the bulkhead 300. Because the stringer end fittings 316 do not provide a tensile force, the stringer end fittings 316 do not necessarily have to be aligned with each other on opposite sides of the bulkhead 300. Alternatively, the stringer end fittings 316 may be offset from each other on opposite sides of the bulkhead. Additionally, fewer stringer end fittings 316 are required due to the increased efficiency of load transfer through the bulkhead joint assembly 312. Therefore, costs are saved, installation time is reduced, and manufacturing time is minimized.

[0033] In one example, the stringer end fittings 316 are secured to the rear section 304, the front section 308, and the carrier strip section 314 by fasteners. In other embodiments, rivets, bolts, screws, bonding, welding, other fasteners, etc. are utilized. Each stringer end fitting 316 is shaped to matingly engage a corresponding stringer of the rear section 304 or the front section 308. In one example, each rear section 304 and the front section 308 are generally L-shaped to ensure that the surface of the stringer end fitting 316 secured to the corresponding carrier strip section 314 is flat, or is continuously engaged along the surface of the carrier strip section 314. At the same time, the surface of the stringer end fitting 316 is secured to the corresponding stringer of the rear section 304 or the front section 308 and is therefore considered to be the rear stringer end fitting 316 or the front stringer end fitting 316. Additionally, in embodiments where the stringer end fitting 316 is generally L-shaped, the section of the stringer end fitting 316 extends away from the fixed section to provide additional structural support. In alternative embodiments, other sizes and shapes of stringer end fittings 316 are utilized, including T-shaped stringer end fittings 316. In one embodiment, the carrier strap segment 314 is made of composite fiber reinforced plastic (CFRP). By being made of CFRP, corrosion of the joint assembly 312 is minimized while manufacturing speed is increased because manufacturing steps including drilling, disassembly, and deburring of metal parts (such as bathtub fittings) are eliminated.

[0034] The chord 318 is generally L-shaped in an exemplary embodiment, wherein each chord includes a horizontal section 332 and a vertical section 334 extending at a certain angle to the horizontal section 332. The angle can be an obtuse angle, an acute angle, or a right angle. Alternatively, the chord 318 can be generally T-shaped. Although illustrated as a plurality of chords 318, a single chord 318 is provided in another embodiment. The horizontal section 332 is joined and fixed to the carrier section 314 in the front section 308. The vertical section 334 is simultaneously joined and fixed to the web body 302 of the bulkhead 300. In one example, the chord 318 is fixed to other components by fasteners. In other embodiments, rivets, bolts, screws, bonding, welding, etc. are used. In one example, the chord 318 is fixed to the carrier section 314 and the bulkhead 300 with fasteners on a single side of the bulkhead 300 to provide load transfer through the chord 318 on a single side of the bulkhead 300. In another example each chord 318 includes at least one rat-hole opening 336 therein to facilitate visual inspection of the corresponding carrier tape segment 314. Specifically, each rat-hole opening 336 is generally arcuate and extends from partially within the vertical segment 334 to partially within the horizontal segment 332 and terminates in the horizontal segment 332. Additionally, the rat-hole opening 336 facilitates part production and assists in installation by making the chord 318 more compliant. In one embodiment the chord 318 is made of composite fiber reinforced plastic (CFRP). By being made of CFRP, corrosion of the joint assembly 312 is minimized while manufacturing speed is increased because manufacturing steps including drilling, disassembly, and deburring of metal parts (such as bathtub fittings) are eliminated.

[0035] Thus, a bulkhead joint assembly 312 is provided that transfers the load from the bulkhead 300 to the chord 318 and through the corresponding carrier tape segment 314 to provide efficient transfer of the load. The chord 318 only needs to be placed on one side of the bulkhead 300 (the front side 326 in this example), thereby reducing the number of chords required. Additionally, due to the efficiency of the transfer of loads, the components of the bulkhead joint assembly 312, including the carrier tape segment 314, the stringer end fitting 316, the chord segment 318, and the T-shaped chord segment 320, can be made of a material that minimizes corrosion, such as titanium or a composite material such as CFRP, rather than a more corrosive metal material such as aluminum. Therefore, costs are reduced, the manufacturing process is simplified, corrosion is minimized, and the components are more flexible, thereby facilitating installation. Additionally, the number of spliced ​​parts is reduced, thereby simplifying the manufacturing process again. Finally, the simplified design facilitates replacement and repair of the bulkhead 300 and other fuselage components because it is no longer necessary to disassemble layers of components to access such components.

[0036] Figure 6A partial side cross-sectional view of a bulkhead joint assembly 600 is illustrated that couples a rear section 602, a front section 604, and a bulkhead 606. In one example, the bulkhead joint assembly 600 is Figure 3 , Figure 4 and Figure 5 The bulkhead joint assembly 600 includes a carrier band section 614, a first stringer end fitting 616A, a second stringer end fitting 616B, a chord section 618, and a T-shaped chord (at Figure 6 not shown). Figure 7 , Figure 8 , Fig. 9 and Fig.10 Each illustrates individual components of the bulkhead connector assembly 600, including the carrier tape segment 614 ( Figure 7 )、First beam end fitting 616A( Figure 8 ), chord section 618 ( Fig. 9 ) and T-shaped chord section 1000 ( Fig.10 ).

[0037] The carrier tape segments 614 are configured to mate with the rear section 602 and the front section 604. Specifically, the carrier tape segments 614 include a bottom surface 620 that extends from a first end 622 along an interior or inner surface 624 of the rear section 602, along an interior or inner surface 626 or skin of the front section 604, and to a second end 628. A gap is formed between the first end 622 of each carrier tape segment 614 and the adjacent stringer for tolerance during installation and as a drainage path for liquids present in this area of ​​the aircraft. Similarly, a gap is again formed between the second end 628 and the adjacent stringer for tolerance during installation and as a drainage path for liquids present in this area of ​​the aircraft.

[0038] The carrier tape segment 614 also includes a top surface 630, which in one example faces toward the first end 622 and the second end 628 ( Figure 6 Alternatively, in another exemplary embodiment, the top surface 630 extends parallel to the bottom surface 620 at the first end 622 until it tapers toward the bottom surface at a taper point 632 to form a constant gage section 634 and a taper section 636 ( Figure 7 ) until. Figure 7 In one example of an exemplary embodiment of the present invention, the constant gauge section 634 has a thickness of approximately thirty-two (32) piles and the tapered section 636 extends from a thickness of thirty-two (32) piles at the tapered point 632 to sixteen (16) piles at the second end 628. Due to the constant gauge section 634 and the tapered section 636, the need for additional shims is greatly reduced and minimized. In this manner, a shim-free carrier tape section 614 is provided. Figure 7 As shown, the bottom surface 620 additionally extends in an arcuate shape (to Figure 6 Thus, the bottom surface 620 matingly engages the arcuate interior surface 624 or skin of the rear section 602 and the interior surface 626 or skin of the front section 604.

[0039] First beam end fitting 616A ( Figure 8 ) is engaged and secured to the aft section 602 at a first end 638 and matingly engages the carrier strap section 614 at a second end 640. Similarly, the second stringer end fitting 616B is engaged and secured to the forward section 604 at a first end 642 and matingly engages the carrier strap section 614 at a second end 644. In this manner, forces (including axial forces) of the bulkhead joint assembly 600 are provided with an effective load path for fore-aft load transfer between the first stringer end fitting 616A and the carrier strap section 614 and between the second stringer end fitting 616B and the carrier strap section 614.

[0040] The chord 618 is generally L-shaped in an exemplary embodiment and includes a horizontal section 646 having a bottom surface 648 that joins and extends along the top surface 630 of the carrier tape section 614. Alternatively, the chord 618 can be generally T-shaped. The horizontal section 646 extends into a vertical section 649 having a side surface 650 that joins and extends along the front surface 652 of the web body 654 of the bulkhead 606. In one example, the chord 618 is fastened to the carrier tape section 614 and the bulkhead 606 with fasteners on a single side of the bulkhead 606 to provide load transfer through the chord 618 on a single side of the bulkhead 606. Disposed in the horizontal section 646 and the vertical section 649 is a rat hole opening 655. The rat hole opening 655 facilitates visual inspection of the corresponding carrier tape section 614. Additionally, the rathole opening 655 facilitates part production and aids installation by making the chord 618 more compliant.

[0041] As illustrated, the chord 618 of this embodiment is not at right angles but instead has an obtuse angle. Specifically, because the bottom surface 648 of the horizontal segment 646 is joined and extended along the top surface 630 of the carrier segment 614, and because the side surface 650 of the vertical segment 649 is joined and extended along the front surface 652 of the web body 654, the chord 618 converts the load from the bulkhead 606 into a shear force between the chord 618 and the carrier segment 614. Because the load presented in the joint assembly 600 is effectively transmitted, the joint assembly 600 can be made of CFRP, thereby improving manufacturing efficiency and cost. In addition, this also reduces the amount of splicing joints required and reduces part number count. The joint assembly 600 is also easy to install and replace. Additionally, if additional support is desired, the splicing carrier is easily added.

[0042] Fig.10An exemplary T-shaped chord segment 1000 of a bulkhead joint assembly is illustrated, which in one embodiment is Figure 3 , Figure 4 and Figure 5 The T-shaped chord segment 320 of the bulkhead joint assembly 312 of the embodiment of the present invention is a T-shaped chord segment. The T-shaped chord segment 1000 includes a body 1002, a flange 1004 extending from the body 1002, a top edge 1006, an opposite bottom edge 1008, a rear side edge 1010, a front side edge 1012, and a flange edge 1014. In one example, the flange 1004 extends at a right angle from the body. In another embodiment, the flange 1004 extends to form an acute angle and an obtuse angle with the body. The T-shaped chord segment 1000 in the fuselage spans from the rear section under the web body of the bulkhead to the front section. The T-shaped chord segment 1000 is joined between the carrier segment and the chord segment at the keel of the bulkhead and the carrier segment and the chord segment at the crown of the bulkhead and is fixed to the web body, the rear section and the front section of the bulkhead. In this way, the T-shaped chord provides a transition from the keel of the bulkhead joint to the crown. Specifically, at the keel end, the bottom edge 1008 abuts or engages the keel chord and abuts or engages the keel carrier band segment on the front section, and abuts or engages the keel carrier band segment on the rear section. Meanwhile, at the crown end, the top edge 1006 abuts or engages the crown chord and abuts or engages the crown carrier band segment on the front section, and abuts or engages the crown carrier band segment on the rear section. In one example, the T-chord 1000 is fixed to the web body, rear section and front section of the bulkhead by fasteners. In other embodiments, rivets, bolts, screws, bonding, welding, other fasteners, etc. are used. In one embodiment, the T-chord 1000 is made of titanium. In another embodiment, CFRP is used to make the T-chord 1000 in an integral process. In yet another embodiment, the T-chord is made by combining a CFRP chord and a spliced ​​carrier band. By being made of CFRP, corrosion of the joint assembly is minimized while manufacturing speed is increased because deburring of metal connectors (such as bathtub fittings) is eliminated.

[0043] The body 1002 includes a rear section 1016 extending from the rear side edge 1010 to the flange 1004. The rear section 1016 also extends within and engages the inner wall of the rear section. The rear side edge 1010 extends in an arcuate shape from the rear top edge section 1018 to the rear bottom edge section 1020. Specifically, the rear side edge 1010 tapers inwardly from the rear top edge section 1018 and tapers inwardly from the rear bottom edge section 1020.

[0044] The body 1002 also includes a front section 1022 extending from the front side edge 1012 to the flange 1004. The front section 1022 also extends within and engages the inner wall of the front section. The front side edge 1012 extends from the front top edge section 1023 to an inner arcuate section 1024 that tapers inwardly and outwardly back to the front bottom edge section 1025. Specifically, the front section 1022 thus has an outer width 1026 and an inner width 1028, wherein the inner width 1028 is less than the outer width 1026. The arcuate section 1024 facilitates part production and assists installation by making the T-chord 1000 more compliant.

[0045] The flange 1004 includes a flange top surface section 1030 that tapers downwardly to fit snugly against the crown band section. Although the flange top surface section 1030 is illustrated as fittingly snugly against the crown band section in this and other exemplary embodiments, in other embodiments, the chord forms an overlap with the T-shaped chord section 1000, thereby overlapping the T-shaped chord section 1000 rather than snugly against the crown band section. The flange top surface section 1030 extends outwardly into a first flange arcuate section 1032 and then inwardly to a flange inner arcuate section 1034. The flange edge 1014 at the flange inner arcuate section 1036 extends outwardly to a second flange arcuate section 1038. The flange inner arcuate section 1036 facilitates part production and assists installation by making the T-shaped chord more compliant. The second flange arcuate section 1038 then tapers to a flange floor section 1040 which tapers downwardly to matingly abut the keel carrier strap section.

[0046] Thus, in one exemplary embodiment, the T-chord segment 1000 extends between and abuts the keel carrier strap segment and keel chord and the crown carrier strap segment and crown chord. Alternatively, one or more lap joints are provided between the T-chord segment 1000 and the keel carrier strap segment and crown carrier strap segment, such that the T-chord segment 1000 overlaps any one or both of the keel carrier strap segment and / or the crown carrier strap segment as desired. Thus, the T-chord is provided to effectively distribute forces at the bulkhead joint. Additionally, the T-chord segment is formed to facilitate mounting and accommodate corresponding pivot fittings secured to the web body of the bulkhead.

[0047] Furthermore, the present disclosure includes implementations according to the following clauses:

[0048] Clause 1. A bulkhead (104, 300, 606) joint assembly (312, 600), the bulkhead (104, 300, 606) joint assembly (312, 600) comprising:

[0049] a carrier tape section (314, 614) configured to be secured to a rear section (314, 614) (102, 304, 602, 1016) of a fuselage (100) and a front section (314, 614) (112, 308, 604, 1022) of the fuselage (100) and to extend through a bulkhead (104, 300, 606) of the fuselage (100); and

[0050] A chord (318, 618) is engaged and secured to the carrier tape segment (314, 614), wherein the chord (318, 618) is configured to extend along the bulkhead (104, 300, 606) to transfer loads from the bulkhead (104, 300, 606) in shear between the chord (318, 618) and the carrier tape segment (314, 614).

[0051] Clause 2. The bulkhead (104, 300, 606) joint assembly (312, 600) according to clause 1, further comprising:

[0052] an aft stringer end (328) fitting secured to the carrier tape section (314, 614) and extending to and configured to be secured to the aft section (314, 614) (102, 304, 602, 1016);

[0053] A front stringer end (328) fitting is secured to the carrier tape section (314, 614) and extends to and is configured to be secured to the front section (314, 614) (112, 308, 604, 1022).

[0054] Clause 3. The bulkhead (104, 300, 606) joint assembly (312, 600) of clause 2, wherein the carrier tape segment (314, 614), the chord (318, 618), the rear stringer end (328) fitting, and the front stringer end (328) fitting are made of composite fiber reinforced plastic.

[0055] Clause 4. The bulkhead (104, 300, 606) joint assembly (312, 600) of clauses 1, 2, or 3, wherein the carrier tape segment (314, 614) comprises a constant gauge segment (314, 614) (634) and a tapered segment (636) (314, 614).

[0056] Clause 5. The bulkhead (104, 300, 606) joint assembly (312, 600) of any one of clauses 1 to 4, wherein the chord (318, 618) includes a rat-hole opening (336) extending in an arcuate manner in a vertical section (334, 649) (314, 614) of the chord (318, 618).

[0057] Clause 6. A bulkhead (104, 300, 606) joint assembly (312, 600) according to any one of clauses 1 to 5, wherein the chord (318, 618) includes a horizontal segment (314, 614) (332, 646) joined and extending along the carrier segment (314, 614) and a vertical segment (334, 649) (314, 614) constructed to join and extend along the bulkhead (104, 300, 606).

[0058] Clause 7. The bulkhead (104, 300, 606) joint assembly (312, 600) of clause 6, wherein an obtuse angle is formed between the horizontal section (314, 614) (332, 646) of the chord (318, 618) and the vertical section (334, 649) (314, 614) of the chord (318, 618).

[0059] Clause 8. The bulkhead (104, 300, 606) joint assembly (312, 600) of any one of clauses 1 to 7, further comprising:

[0060] A T-shaped chord (318, 618) section (314, 614) is adjacent to the carrier tape section (314, 614).

[0061] Clause 9. The bulkhead (104, 300, 606) joint assembly (312, 600) of any one of clauses 1 to 8, further comprising:

[0062] A T-shaped chord (318, 618) segment (314, 614) overlaps the carrier tape segment (314, 614).

[0063] Clause 10. The bulkhead (104, 300, 606) joint assembly (312, 600) of clause 8 or 9, wherein the T-chord (318, 618) segment (314, 614) includes a body (1002) and a flange (1004) extending from the body (1002).

[0064] Clause 11. The bulkhead (104, 300, 606) joint assembly (312, 600) of clause 10, wherein the flange (1004) of the T-chord (318, 618) segment (314, 614) comprises an arcuate segment (314, 614) (1024) (1024) inside the flange (1004).

[0065] Clause 12. A fuselage (100), the fuselage (100) comprising:

[0066] Rear section (314,614)(102,304,602,1016);

[0067] a front section (314,614) (112,308,604,1022) that matingly receives the rear section (314,614) (102,304,602,1016) at a joint of the bulkhead (104,300,606);

[0068] a baffle (104,300,606) extending around the interior of the rear section (314,614) (102,304,602,1016) and the interior of the front section (314,614) (112,308,604,1022) adjacent to the baffle (104,300,606) joint; and

[0069] A bulkhead (104, 300, 606) joint assembly (312, 600) that secures the rear section (314, 614) (102, 304, 602, 1016) to the front section (314, 614) (112, 308, 604, 1022) includes:

[0070] The carrier tape section (314, 614) is fixed to the rear section (314, 614) (102,

[0071] 304,602,1016) and extends to and is fixed to the front section (314,614) (112,308,604,1022), the carrier tape section (314,614) being connected to the partition (104,300,606) and the partition (104,300,606)

[0072] extending between the joints; and

[0073] A chord (318, 618) includes a horizontal segment (314, 614) (332, 646) joined and extending along the carrier tape segment (314, 614) and a vertical segment (334, 649) (314, 614) joined and extending along the diaphragm (104, 300, 606) to provide a shear force between the diaphragm (104, 300, 606) and the carrier tape segment (314, 614).

[0074] Clause 13. The fuselage (100) of clause 12, wherein the bulkhead (104, 300, 606) joint assembly (312, 600) further comprises:

[0075] a rear stringer end (328) fitting secured to the carrier tape section (314, 614) and extending to and secured to the rear section (314, 614) (102, 304, 602, 1016);

[0076] A front stringer end (328) fitting is secured to the carrier strap section (314, 614) and extends to and is secured to the front section (314, 614) (112, 308, 604, 1022).

[0077] Clause 14. The fuselage (100) of clause 13, wherein the carrier tape segment (314, 614), the chord (318, 618), the rear stringer end (328) fitting, and the front stringer end (328) fitting are made of composite fiber reinforced plastic.

[0078] Clause 15. The fuselage (100) of clauses 12, 13, or 14, wherein the bulkhead (104, 300, 606) joint assembly (312, 600) further comprises:

[0079] A T-shaped chord (318, 618) section (314, 614) is adjacent to the carrier tape section (314, 614).

[0080] Clause 16. The fuselage (100) according to clause 15, further comprising:

[0081] A pivot fitting pivotably receives the horizontal tail (110) and is secured to the bulkhead (104, 300, 606) adjacent the T-shaped chord (318, 618).

[0082] Clause 17. The fuselage (100) of any one of clauses 12 to 16, wherein the chord (318, 618) includes a rathole opening (336).

[0083] Clause 18. The fuselage (100) of any one of clauses 12 to 17, wherein the chord (318, 618) is secured to the carrier tape segment (314, 614) and the bulkhead (104, 300, 606) with fasteners on a single side of the bulkhead (104, 300, 606).

[0084] Clause 19. A bulkhead (104, 300, 606) joint assembly (312, 600), the bulkhead (104, 300, 606) joint assembly (312, 600) comprising:

[0085] a carrier tape section (314, 614) configured to be secured to a rear section (314, 614) (102, 304, 602, 1016) of a fuselage (100) and a front section (314, 614) (112, 308, 604, 1022) of the fuselage (100) and to extend through a bulkhead (104, 300, 606) of the fuselage (100);

[0086] a chord (318, 618) engaged and secured to the carrier tape segment (314, 614), wherein the chord (318, 618) is configured to extend along the bulkhead (104, 300, 606) to transfer loads from the bulkhead (104, 300, 606) in shear between the chord (318, 618) and the carrier tape segment (314, 614);

[0087] an aft stringer end (328) fitting secured to the carrier tape section (314, 614) and extending to and configured to be secured to the aft section (314, 614) (102, 304, 602, 1016);

[0088] a front stringer end (328) fitting secured to the carrier tape section (314, 614) and extending to and configured to be secured to the front section (314, 614) (112, 308, 604, 1022); and

[0089] A T-shaped chord (318, 618) section (314, 614) is adjacent to the carrier tape section (314, 614).

[0090] Clause 20. The bulkhead (104, 300, 606) joint assembly (312, 600) of Clause 19, wherein the carrier tape segment (314, 614) is one of a plurality of carrier tape segments (314) of the bulkhead (104, 300, 606) joint assembly (312, 600).

[0091] Although various spatial and directional terms (such as top, bottom, lower, middle, lateral, horizontal, vertical, front, etc.) may be used to describe embodiments of the present disclosure, it should be understood that such terms are used only with respect to the orientation shown in the drawings. The orientation may be inverted, rotated, or otherwise changed so that up is down and vice versa, horizontal becomes vertical, and so on.

[0092] The above-mentioned changes and modifications are within the scope of the present disclosure. It should be understood that the embodiments disclosed and defined herein extend to all alternative combinations of two or more of the individual features mentioned or apparent from the text and / or the accompanying drawings. All these different combinations constitute various alternative aspects of the present disclosure. The embodiments described herein illustrate the best mode known for practicing the present disclosure and will enable other persons skilled in the art to utilize the present disclosure. The claims will be interpreted as including alternative embodiments within the scope permitted by the prior art.

[0093] As used in the appended claims, the terms "including" and "in which" are used as the plain-language equivalents of the respective terms "comprising" and "wherein." Furthermore, as used in the appended claims, the terms "first," "second," and "third," etc. are used merely as labels and are not intended to impose numerical requirements on their objects. Furthermore, the limitations of the appended claims are not drafted in means-plus-function form unless and until the claim limitation expressly uses the phrase "means for..." followed by a statement of function without further structure.

[0094] Various features of the disclosure are set out in the following claims.

Claims

1. A bulkhead joint assembly (312, 600) for a bulkhead (104, 300, 606), the bulkhead (104, 300, 606) having a web body (122), the web body (122) including a front side (124), a rear side (126), a crown perimeter (128), a first side perimeter (130), a second side perimeter (132), and a keel perimeter (134), the bulkhead joint assembly (312, 600) comprising: a carrier tape segment (314, 614) configured to be secured to a rear section (304, 602) of a fuselage (100) and a front section (308, 604) of the fuselage (100) and to extend through a bulkhead (104, 300, 606) of the fuselage (100); a chord (318, 618) engaged and secured to the carrier tape segment (314, 614), wherein the chord (318, 618) is configured to extend along the crown perimeter and the keel perimeter of the diaphragm (104, 300, 606) to transfer loads from the diaphragm (104, 300, 606) in shear between the chord (318, 618) and the carrier tape segment (314, 614); and A T-shaped chord segment (320, 1000) is constructed to be joined and fixed to the web body (122), the rear segment (304, 602) and the front segment (308, 604) of the bulkhead between a carrier segment (314, 614) and a chord (318, 618) located at the keel of the bulkhead and a carrier segment (314, 614) and a chord (318, 618) located at the crown of the bulkhead.

2. The bulkhead joint assembly (312, 600) of claim 1, further comprising: an aft stringer end fitting (316, 616A) secured to the carrier strap section (314, 614) and extending to and configured to be secured to the aft section (304, 602); A front stringer end fitting (316, 616B) is secured to the carrier strap section (314, 614) and extends to and is configured to be secured to the front section (308, 604).

3. The bulkhead joint assembly (312, 600) of claim 2, wherein: The carrier belt segment (314, 614), the chord (318, 618), the rear stringer end fitting (316, 616A) and the front stringer end fitting (316, 616B) are made of composite fiber reinforced plastic.

4. The bulkhead joint assembly (312, 600) of claim 1 or 2, wherein: The carrier tape section (314, 614) includes a constant gauge section (634) and a tapered section (636).

5. The bulkhead joint assembly (312, 600) of claim 1 or 2, wherein: The chord (318, 618) includes a mousehole opening (336) extending arcuately in a vertical section (334, 649) of the chord (318, 618).

6. The bulkhead joint assembly (312, 600) of claim 1 or 2, wherein: The chord (318, 618) includes a horizontal segment (332, 646) joined and extending along the carrier tape segment (314, 614) and a vertical segment (334, 649) configured to join and extend along the bulkhead (104, 300, 606).

7. The bulkhead joint assembly (312, 600) of claim 6, wherein: An obtuse angle is formed between the horizontal section (332, 646) of the chord (318, 618) and the vertical section (334, 649) of the chord (318, 618).

8. The bulkhead joint assembly (312, 600) of claim 1 or 2, wherein: The T-shaped chord section is adjacent to the carrier tape section (314, 614).

9. The bulkhead joint assembly (312, 600) of claim 1 or 2, wherein: The T-shaped chord segment overlaps the carrier tape segment (314, 614).

10. The bulkhead joint assembly (312, 600) of claim 8, wherein: The T-shaped chord segment (320, 1000) includes a body (1002) and a flange (1004) extending from the body (1002).

11. The bulkhead joint assembly (312, 600) of claim 10, wherein: The flange (1004) of the T-shaped chord segment (320, 1000) includes a flange inner arcuate segment (1024).

12. A fuselage (100), the fuselage (100) comprising: rear section (304,602); a front section (308, 604) that matingly receives the rear section (304, 602) at a bulkhead joint; a bulkhead (104, 300, 606) extending around the interior of the rear section (304, 602) and the interior of the front section (308, 604) adjacent the bulkhead joint, the bulkhead having a web body (122) including a front side (124), a rear side (126), a crown perimeter (128), a first side perimeter (130), a second side perimeter (132), and a keel perimeter (134); and The bulkhead joint assembly (312, 600) of claim 1, the bulkhead joint assembly (312, 600) securing the rear section (304, 602) to the front section (308, 604).

13. The fuselage (100) according to claim 12, wherein: The bulkhead joint assembly (312,600) further includes: a rear stringer end fitting (316, 616A) secured to the carrier strap section (314, 614) and extending to and secured to the rear section (304, 602); A front stringer end fitting (316, 616B) is secured to the carrier strap section (314, 614) and extends to and is secured to the front section (308, 604).

14. The fuselage (100) according to claim 13, wherein: The carrier belt segment (314, 614), the chord (318, 618), the rear stringer end fitting (316, 616A) and the front stringer end fitting (316, 616B) are made of composite fiber reinforced plastic.

15. The fuselage (100) according to claim 12 or 13, wherein: The T-shaped chord section is adjacent to the carrier tape section (314, 614).

16. The fuselage (100) according to claim 15, further comprising: A pivot fitting pivotally receives the horizontal tail (110) and is secured to the bulkhead (104, 300, 606) adjacent the T-shaped chord segment.

17. The fuselage (100) according to claim 12 or 13, wherein: The chord (318, 618) includes a mousehole opening (336).

18. The fuselage (100) according to claim 12 or 13, wherein: The chord (318, 618) is fastened to the carrier tape segment (314, 614) and the bulkhead (104, 300, 606) with fasteners on a single side of the bulkhead (104, 300, 606).

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