The compression chord of the fuselage

Abstract

Disclosed is a compression chord of a fuselage. An aircraft fuselage includes a pressure plate assembly extending along the roll axis of the fuselage. The pressure plate assembly includes longitudinal beams and a pressure plate. The longitudinal beams extend along the roll axis of the fuselage for a certain length. The pressure plate extends between the longitudinal beams along the length of the longitudinal beams. The pressure plate has compliance along the pitch axis of the fuselage. The fuselage includes bulkheads extending along the yaw axis of the fuselage. The bulkheads are joined to the pressure plate assembly at the corner joints. The fuselage includes a compression chord extending along the pitch axis of the fuselage for a certain length. The compression chord is joined between the pressure plate assembly and the bulkheads at the corner joints such that the compression chord extends outside of the corner joints.

Description

Technical Field

[0001] The present disclosure generally relates to aircraft fuselages, and more particularly, to a pressure plate assembly for an aircraft fuselage. Background Art

[0002] The fuselage structures of certain aircraft have pressure plate assemblies, sometimes referred to as "pressure plates" or "horizontal pressure plates". The pressure plate assembly forms a partitioning structure that divides the height of the fuselage into different compartments, such as for supporting the floors of compartments (e.g., passenger compartments, cargo compartments, etc.), for separating pressurized compartments (e.g., passenger compartments, cargo compartments, etc.) from non-pressurized compartments (e.g., landing gear compartments, baggage compartments, compartments containing aircraft system components, etc.). The fuselages of certain aircraft are also constructed with internal bulkheads that form a partitioning structure that divides the length of the fuselage into different compartments, such as being part of the landing gear compartment of the aircraft. The pressure plate assembly and the bulkhead are joined together at a corner joint.

[0003] Some aircraft designs generate higher compression loads at the corner joints between the bulkhead and the pressure plate assembly. However, existing corner joint designs have to be heavy in order to withstand the higher pressure loads generated by such aircraft designs. Moreover, assembling existing corner joint designs to join the bulkhead and the pressure plate assembly is time-consuming, expensive, and / or harmful to the operator performing the assembly. Summary of the Invention

[0004] In one aspect, a fuselage for an aircraft is provided. The fuselage includes a pressure plate assembly extending along the roll axis of the fuselage. The pressure plate assembly includes longitudinal beams and a pressure plate. The longitudinal beams extend along the roll axis of the fuselage for a certain length. The pressure plate extends between the longitudinal beams along the length of the longitudinal beams. The pressure plate conforms to the pitch axis of the fuselage. The fuselage includes a bulkhead extending along the yaw axis of the fuselage. The bulkhead is joined to the pressure plate assembly at a corner joint. The fuselage includes a compression chord extending along the pitch axis of the fuselage for a certain length. The compression chord is joined between the pressure plate assembly and the bulkhead at the corner joint such that the compression chord extends outside the corner joint.

[0005] In another aspect, a fuselage for an aircraft is provided. The fuselage includes a pressure plate assembly extending along the roll axis of the fuselage. The pressure plate assembly includes longitudinal beams, corner fittings, and a pressure plate. The longitudinal beams extend along the roll axis of the fuselage for a certain length. The corner fittings are joined to at least one of the longitudinal beams and the pressure plate. The pressure plate extends between the longitudinal beams along the length of the longitudinal beams. The pressure plate conforms to the pitch axis of the fuselage. The fuselage includes a bulkhead extending along the yaw axis of the fuselage. The bulkhead is joined to the pressure plate assembly. The fuselage includes a compression chord extending along the pitch axis of the fuselage for a certain length. The compression chord is joined between the pressure plate assembly and the bulkhead such that the load path of the compression chord passes over the load path of the corner fittings.

[0006] In another aspect, a method for manufacturing a fuselage is provided. The method includes constructing a pressure plate assembly such that longitudinal beams of the pressure plate assembly extend along a roll axis of the fuselage for a certain length and such that compliant pressure plates of the pressure plate assembly extend between the longitudinal beams; constructing bulkheads that extend along a yaw axis of the fuselage; joining the pressure plate assembly and the bulkheads together at corner joints; and joining compression chords at the corner joints between the pressure plate assembly and the bulkheads such that the compression chords extend outside of the corner joints. BRIEF DESCRIPTION OF THE DRAWINGS

[0007] Figure 1 is an exploded perspective view showing a portion of a fuselage of an aircraft according to an embodiment.

[0008] Figure 2 is according to an embodiment Figure 1 sectional view of the fuselage shown.

[0009] Figure 3 is Figure 1 exploded perspective view of a portion of the fuselage shown.

[0010] Figure 4 is a cross-sectional view showing a corner joint between a pressure plate assembly and a bulkhead of the fuselage shown in Figures 1 to 3 according to an embodiment.

[0011] Figure 5 is Figure 1 magnified perspective view of a portion of the fuselage shown.

[0012] Figure 6 is a flowchart showing a method for drilling a workpiece according to an embodiment.

[0013] Figure 7 is a schematic diagram of an embodiment of an aircraft.

[0014] Figure 8 is a block diagram of an embodiment of an aircraft production and service method. DETAILED DESCRIPTION

[0015] The foregoing summary and the following detailed description of certain embodiments and implementations will be better understood when read in conjunction with the accompanying drawings. As used herein, an element or step recited in the singular and preceded by the word "a" or "an" should not be understood as excluding a plurality of elements or steps. Further, a reference to "an embodiment" or "an implementation" is not to be construed as excluding the existence of other embodiments or implementations that also incorporate the recited features. Moreover, unless expressly stated to the contrary, an embodiment that "includes" or "has" one or more elements having a particular property may include additional elements that do not have that property.

[0016] Although various spatial and directional terms, such as "top", "bottom", "upper", "lower", "vertical", etc., are used to describe embodiments and implementations of the present disclosure, it should be understood that these terms are used only with respect to the directions shown in the drawings. The directions can be reversed, rotated, or otherwise changed such that if the structure is flipped 180 degrees, the top side will become the bottom side, and if the structure is rotated 90 degrees, it will become the left or right side, and so on.

[0017] Certain embodiments of the present disclosure provide a fuselage for an aircraft. The fuselage includes a pressure plate assembly extending along the roll axis of the fuselage. The pressure plate assembly includes longitudinal beams and a pressure plate. The longitudinal beams extend a certain length along the roll axis of the fuselage. The pressure plate extends between the longitudinal beams along the length of the longitudinal beams. The pressure plate complies with the pitch axis of the fuselage. The fuselage includes a bulkhead extending along the yaw axis of the fuselage. The bulkhead is joined to the pressure plate assembly at a corner joint. The fuselage includes a compression chord extending a certain length along the pitch axis of the fuselage. The compression chord is joined between the pressure plate assembly and the bulkhead at the corner joint such that the compression chord extends outside the corner joint.

[0018] Certain embodiments of the present disclosure provide a fuselage for an aircraft. The fuselage includes a pressure plate assembly extending along the roll axis of the fuselage. The pressure plate assembly includes longitudinal beams, corner fittings, and a pressure plate. The longitudinal beams extend a certain length along the roll axis of the fuselage. The corner fittings are joined to at least one of the longitudinal beams and the pressure plate. The pressure plate extends between the longitudinal beams along the length of the longitudinal beams. The pressure plate complies with the pitch axis of the fuselage. The fuselage includes a bulkhead extending along the yaw axis of the fuselage. The bulkhead is joined to the pressure plate assembly. The fuselage includes a compression chord extending a certain length along the pitch axis of the fuselage. The compression chord is joined between the pressure plate assembly and the bulkhead such that the load path of the compression chord passes over the load path of the corner fittings.

[0019] Certain embodiments of the present disclosure provide a relatively smooth and / or relatively straight lateral load path through the corner joint between the pressure plate assembly and the bulkhead. Certain embodiments of the present disclosure enable the corner joint between the pressure plate assembly and the bulkhead to withstand higher pressure loads. Certain embodiments of the present disclosure increase the lateral stiffness of the corner joint between the pressure plate assembly and the bulkhead.

[0020] Certain embodiments of the present disclosure reduce or eliminate the drilling operations performed during the assembly of the corner joint between the bulkhead and the pressure plate assembly. Certain embodiments of the present disclosure reduce the number of parts of the corner joint between the bulkhead and the pressure plate assembly. Certain embodiments of the present disclosure reduce the weight of the corner joint between the bulkhead and the pressure plate assembly. Certain embodiments of the present disclosure reduce the time required to assemble the corner joint between the bulkhead and the pressure plate assembly. Certain embodiments of the present disclosure reduce the cost of assembling the corner joint between the bulkhead and the pressure plate assembly, thereby reducing the cost of the fuselage. Certain embodiments of the present disclosure reduce the number of injuries that occur when joining the bulkhead and the pressure plate assembly at the corner joint.

[0021] Now referring to the drawings, there is provided in Figure 1 an exploded perspective view of a portion of the fuselage 100 of an aircraft (e.g., an aircraft 300 as shown in Figure 7 ). The fuselage 100 extends a certain length along the roll axis 102 (i.e., longitudinally) of the fuselage 100 and the aircraft. The fuselage 100 extends a certain width along the pitch axis 104 (e.g., transversely, horizontally, etc.) of the fuselage 100 and the aircraft. The fuselage 100 extends a certain height along the yaw axis 106 (e.g., vertically, etc.) of the fuselage 100 and the aircraft. As Figure 1 shown, the roll axis 102, the pitch axis 104, and the yaw axis 106 extend perpendicular to each other. During flight of the aircraft, the fuselage 100 is configured to roll, pitch, and yaw about the roll axis 102, the pitch axis 104, and the yaw axis 106, respectively. In an exemplary embodiment, the fuselage 100 is a semi-monocoque fuselage, but in other embodiments, the fuselage 100 is any other type of fuselage 100.

[0022] The fuselage 100 includes a pressure plate assembly 108 and a bulkhead 110 joined together at a corner joint 112. The corner joint 112 will be described in more detail below. As Figure 1 shown, the pressure plate assembly 108 extends along the roll axis 102 of the fuselage 100. Specifically, the pressure plate assembly 108 extends a certain length along the roll axis 102. In other words, the length of the pressure plate assembly 108 extends longitudinally along the length of the fuselage 100. The width of the pressure plate assembly 108 extends transversely across the width of the fuselage 100 along the pitch axis 104.

[0023] The pressure plate assembly 108 forms a dividing structure that divides the height of the fuselage 100 into different compartments along at least a portion of the length of the fuselage 100. In some embodiments, the pressure plate assembly 108 is a support structure that supports (or directly forms) the floor of the cargo compartment and / or passenger compartment of the aircraft (e.g., an internal compartment 306 as shown in Figure 7 ). In some embodiments, the pressure plate assembly 108 separates the pressurized compartments (e.g.,Figure 7 The internal cabin 306 shown therein, etc., is separated from one or more non-pressurized cabins of the fuselage 100 (such as the landing gear cabin, etc.).

[0024] In an exemplary embodiment, the length of the pressure plate assembly 108 extends substantially parallel to the roll axis 102 of the fuselage 100, and the width of the pressure plate assembly 108 extends substantially parallel to the pitch axis 104, such that when the fuselage 100 is vertically oriented (e.g., horizontal with respect to the horizontal line, etc.), the pressure plate assembly 108 extends substantially horizontally. In other embodiments, at least a portion of the length of the pressure plate assembly 108 extends at a non-parallel angle (e.g., acute angle, obtuse angle, etc.) with respect to the roll axis 102 of the fuselage 100, and / or at least a portion of the width of the pressure plate assembly 108 extends at a non-parallel angle (e.g., acute angle, obtuse angle, etc.) with respect to the pitch axis 104 of the fuselage 100.

[0025] As Figure 1 shown, the bulkhead 110 extends along the yaw axis 106 of the fuselage 100. Specifically, the bulkhead 110 extends along the yaw axis 106 for a certain length. In other words, the length of the bulkhead 110 extends vertically along the height of the fuselage 100. The width of the bulkhead 110 extends transversely across the width of the fuselage 100 along the pitch axis 104. The bulkhead 110 forms a dividing structure that divides the length of the fuselage 100 into different cabins along at least a portion of the height of the fuselage 100. In some embodiments, the bulkhead 110 is a component (such as forming its support structure, forming its boundary, extending therein, etc.) of the landing gear cabin of the fuselage 100 (such as the landing gear cabin 320 shown, etc.). Figure 7 shown, the landing gear cabin 320, etc.).

[0026] In an exemplary embodiment, the length and width of the bulkhead 110 extend substantially parallel to the yaw axis 106 and pitch axis 104 of the fuselage 100, respectively, such that when the fuselage 100 is vertically oriented (e.g., horizontal with respect to the horizontal line), the bulkhead 110 extends approximately vertically. However, in other embodiments, at least a portion of the length of the bulkhead 110 extends at a non-parallel angle (e.g., acute angle, obtuse angle, etc.) with respect to the yaw axis 106 of the fuselage 100, and / or at least a portion of the width of the bulkhead 110 extends at a non-parallel angle (e.g., acute angle, obtuse angle, etc.) with respect to the pitch axis 104 of the fuselage 100.

[0027] The pressure plate assembly 108 and the bulkhead 110 are joined together at any position along the length of the fuselage 100 (i.e., at any position along the length of the roll axis 102). In other words, the bulkhead 110 is located at any position along the length of the fuselage 100. Figure 7An example of the position of the bulkhead 110 according to an exemplary embodiment is shown. Specifically, the bulkhead 110 is a component of the landing gear bay 320 of the fuselage 304 (e.g., the bulkhead 110 forms the support structure of the landing gear bay 320, the bulkhead 110 forms the boundary of the landing gear bay 320, the bulkhead extends within the landing gear bay 320, etc.). Thus, in Figure 7 the exemplary embodiment of, the bulkhead 110 and the pressure plate assembly 108 are joined together at the landing gear bay 320. However, the bulkhead 110 has any other position along the length of the fuselage 304, whether or not that position is within the landing gear bay of the fuselage 304. For example, in other embodiments, in addition to or alternatively to the landing gear bay, the bulkhead 110 forms the support structure of another component, structure, etc. of the fuselage 304. For clarity, only a part of the length of the pressure plate assembly 108 is shown in Figure 7 .

[0028] Now referring to Figure 2 , the exemplary embodiment of the fuselage 100 includes an elliptical cross-sectional shape that is wider than it is tall at least at the position of the bulkhead 110 (at least when the interior of the fuselage 100 is not pressurized). Specifically, when the interior of the fuselage 100 is not pressurized, the cross-sectional shape of the fuselage 100 at the bulkhead 110 is represented by a dashed line in Figure 2 , and this dashed line is labeled with the reference numeral 100a. In other words, the dashed line 100a shows the unpressurized cross-sectional shape of the exemplary embodiment of the fuselage 100 at the position of the bulkhead 110. Figure 2 The cross-sectional shape of the exemplary embodiment of the fuselage 100 at the bulkhead 110 when the interior of the fuselage 100 is pressurized is shown by a solid line 100b in

[0029] . In other words, the solid line 100b shows the pressurized cross-sectional shape of the exemplary embodiment of the fuselage 100 at the position of the bulkhead 110. Figure 2 As can be seen in

[0030] , the unpressurized cross-sectional shape represented by the dashed line 100a of the fuselage 100 is an ellipse that is wider than it is tall. Specifically, the unpressurized cross-sectional shape represented by the dashed line 100a of the fuselage 100 is an elliptical cross-sectional shape that is greater along the pitch axis 104 than along the yaw axis 106. From the comparison between the dashed line 100a and the solid line 100b, it can be seen that compared with the unpressurized cross-sectional shape of the fuselage 100 represented by the dashed line 100a, the pressurized cross-sectional shape of the fuselage 100 represented by the solid line 100b is smaller along the pitch axis 104 and larger along the yaw axis 106. Thus, the pressurization of the interior of the fuselage 100 applies (e.g., increases, etc.) pressure on the fuselage 100 in the directions of the arrows 114 and 116, and this pressure causes the fuselage 100 to contract along the pitch axis 104 and expand along the yaw axis 106 direction.

[0030] The fuselage 100 is not limited to including an oval cross-sectional shape that is wider than it is tall at the location of the bulkhead 110. Instead, in other embodiments, when the fuselage 100 is not pressurized, the fuselage 100 includes an approximately circular cross-sectional shape at the location of the bulkhead 110. In other embodiments, when the fuselage 100 is not pressurized, the fuselage 100 includes an oval cross-sectional shape that is taller than it is wide at the location of the bulkhead 110.

[0031] Now referring Figure 1 and Figure 3 , the pressure plate assembly 108 includes a plurality of longitudinal beams 118 and a pressure plate 120. Each of the plurality of longitudinal beams 118 extends a certain length along the roll axis 102 of the fuselage 100 from an end 122 to an opposite end (not shown). In other words, the length of each of the plurality of longitudinal beams 118 extends longitudinally along the length of the fuselage 100. In an exemplary embodiment, the length of each of the plurality of longitudinal beams 118 extends generally parallel to the roll axis 102 of the fuselage 100 and is generally perpendicular to each of the pitch axis 104 and the yaw axis 106. However, in other embodiments, the length of one or more of the plurality of longitudinal beams 118 extends along: (1) a non-parallel angle (e.g., acute, obtuse, etc.) relative to the roll axis 102 of the fuselage 100; (2) a non-perpendicular angle relative to the pitch axis 104; and / or (3) a non-perpendicular angle relative to the yaw axis 106.

[0032] Optionally, the pressure plate assembly 108 includes one or more intercostal portions 124 ( Figure 3 not shown in ), which engage between adjacent longitudinal beams of the plurality of longitudinal beams 118, for example to facilitate supporting adjacent longitudinal beams of the plurality of longitudinal beams 118 in the directions shown herein. Each of the plurality of longitudinal beams 118 includes (e.g., is made of, consists of, etc.) any material that enables each of the plurality of longitudinal beams 118 to function as described and / or shown herein, such as but not limited to titanium, aluminum, steel, an alloy of two or more metals, a composite material, etc. Although eight are shown in the exemplary embodiment, the pressure plate assembly 108 includes any number of the plurality of longitudinal beams 118.

[0033] The pressure plate 120 extends between the plurality of longitudinal beams 118 along the length of the plurality of longitudinal beams 118. Specifically, as Figure 1 and Figure 3As shown, a pressure plate 120 along the length of a plurality of longitudinal beams 118 extends laterally between each pair of adjacent longitudinal beams of the plurality of longitudinal beams 118 along a pitch axis 104. In some embodiments, the pressure plate 120 is a continuous plate that continuously spans the plurality of longitudinal beams 118 along the width of the fuselage 100. As used herein, the term "continuously span the plurality of longitudinal beams 118" is intended to mean that the pressure plate 120 extends along the width of the fuselage 100 from the outermost longitudinal beam 118a to the outermost longitudinal beam 118b (not visible in Figure 3 ), while overlapping all of the plurality of longitudinal beams 118 extending between the outermost longitudinal beams 118a and 118b. In other embodiments, the pressure plate 120 is divided into two or more discrete (e.g., separate, individual, etc.) segments, each segment extending between one or more pairs of adjacent longitudinal beams of the plurality of longitudinal beams 118. For example, in some embodiments, the pressure plate 120 is divided into a plurality of discrete segments, each segment extending only between a respective individual pair of adjacent longitudinal beams of the plurality of longitudinal beams 118.

[0034] The pressure plate 120 is a compliant pressure plate. In other words, the pressure plate 120 is a deflectable spring. Specifically, the pressure plate 120 is elastically deflectable along the pitch axis 104 of the fuselage 100. Thus, the pressure plate 120 has compliance along the pitch axis 104 of the fuselage 100. The compliance of the pressure plate 120 along the pitch axis 104 increases the compressive force (e.g., in the directions of arrows 114 and 116, etc.) applied to the angular joint 112 between the pressure plate assembly 108 and the bulkhead 110. In embodiments where the unpressurized cross-sectional shape of the fuselage 100 (such as the cross-sectional shape represented by the dashed line 100a in Figure 2 ) includes an oval with a width greater than its height at the location of the bulkhead 110, the increased compressive force applied to the angular joint 112 is exacerbated (e.g., further increased, etc.).

[0035] The pressure plate 120 includes (e.g., is made of, consists of, etc.) any material that makes the pressure plate 120 compliant along the pitch axis 104 of the fuselage 100, such as but not limited to titanium, aluminum, steel, alloys of two or more metals, composite materials, etc. In an exemplary embodiment, the pressure plate 120 is a catenary web. However, the pressure plate 120 additionally or alternatively includes any type of compliant structure, such as but not limited to parabolic, sinusoidal, arcuate (radius), etc.

[0036] For example, the pressure plate assembly 108 includes a plurality of corner fittings 128 that are joined to the longitudinal beams 118 and / or the pressure plate 120 using bolts, rivets, adhesives, epoxy resins, welding, brazing, etc. Specifically, an exemplary embodiment of each of the plurality of corner fittings 128 includes a block 130 and a strap 132 that is separate from the block 130 (e.g., separated, discrete, etc.). Thus, in an exemplary embodiment, each of the plurality of corner fittings 128 is a two-piece structure. Each block 130 of the plurality of corner fittings 128 is joined to the pressure plate 120 adjacent to the end 122 of a corresponding one of the plurality of longitudinal beams 118 and / or is joined to the end 122 of a corresponding one of the plurality of longitudinal beams 118. In this exemplary embodiment, as Figure 5 shown, each block 130 of the plurality of corner fittings 128 is joined to both the pressure plate 120 and the end 122 of a corresponding longitudinal beam of each of the plurality of longitudinal beams 118. As described below, the straps 132 of the plurality of corner fittings 128 join the blocks 130 of the plurality of corner fittings 128 to the corresponding diaphragm beams 134 of the diaphragm 110.

[0037] Each block 130 of the plurality of corner fittings 128 includes (e.g., is made of, consists of, etc.) any material that enables the plurality of corner fittings 128 to function as described and / or shown herein, such as, but not limited to, titanium, aluminum, steel, an alloy of two or more metals, a composite material, etc. Each strap 132 of the plurality of corner fittings 128 includes (e.g., is made of, consists of, etc.) any material that enables the plurality of corner fittings 128 to function as described and / or shown herein, such as, but not limited to, titanium, aluminum, steel, an alloy of two or more metals, a composite material, etc.

[0038] The diaphragm 110 includes a plurality of diaphragm beams 134 and a web 136. Each diaphragm beam 134 extends along the yaw axis 106 of the fuselage 100 from an end 138 to an opposite end 140 (not visible in Figure 3 ). In other words, the length of the diaphragm beam 134 extends vertically along the height of the fuselage 100. In an exemplary embodiment, the length of each diaphragm beam 134 extends generally parallel to the yaw axis 106 of the fuselage 100 and generally perpendicular to each of the roll axis 102 and the pitch axis 104. However, in other embodiments, the length of one or more diaphragm beams 134 extends along: (1) a non-parallel angle (e.g., acute, obtuse, etc.) relative to the yaw axis 106 of the fuselage 100; (2) a non-perpendicular angle relative to the roll axis 102; and / or (3) a non-perpendicular angle relative to the pitch axis 104.

[0039] Optionally, the bulkhead 110 includes one or more intercostal portions (not shown) that are joined between adjacent bulkhead beams 134 of the bulkhead beam, e.g., to facilitate supporting the bulkhead beam 134 in the direction shown herein. Each bulkhead beam 134 comprises (e.g., is made of, consists of, etc.) any material that enables each bulkhead beam 134 to function as described and / or shown herein, such as but not limited to titanium, aluminum, steel, an alloy of two or more metals, a composite material, etc. Although six are shown in the exemplary embodiment, the bulkhead 110 includes any number of bulkhead beams 134.

[0040] The web 136 extends between the bulkhead beams 134 along the length of the bulkhead beam 134. Specifically, as Figure 1 and Figure 3 shown, the web 136 along the length of the bulkhead beam 134 extends laterally between each pair of adjacent bulkhead beams of the bulkhead beam 134 along the pitch axis 104 of the fuselage 100. In some embodiments, the web 136 is a continuous web that continuously spans the bulkhead beam 134 along the width of the fuselage 100. As used herein, the term "continuously spans the bulkhead beam 134" is intended to mean that the web 136 extends along the width of the fuselage 100 from the outermost bulkhead beam 134a to the outermost bulkhead beam 134b (not visible in Figure 3 ), while overlapping all of the bulkhead beams 134 extending between the outermost bulkhead beams 134a and 134b. In other embodiments, the web 136 is divided into two or more discrete (e.g., separate, individual, etc.) segments, each segment extending between one or more pairs of adjacent bulkhead beams of the bulkhead beam 134. For example, in some embodiments, the web 134 is divided into multiple discrete segments, each discrete segment extending only between a separate respective pair of adjacent bulkhead beams of the bulkhead beam 134.

[0041] The web 136 comprises (e.g., is made of, consists of, etc.) any material that enables the web 136 to function as described and / or shown herein, such as but not limited to titanium, aluminum, steel, an alloy of two or more metals, a composite material, etc. In the exemplary embodiment, the web 136 is a flat web. However, the web 136 additionally or alternatively includes any type of web, such as but not limited to a compliant web, a catenary web, a parabolic web, a sinusoidal web, a radius web, etc.

[0042] For example, the bulkhead 110 includes two or more side fittings 142 (only one is visible in Figure 3 ) that are joined to the web 136 using bolts, rivets, adhesives, epoxy resins, welding, brazing, etc. Optionally, as Figure 5As shown, the side fitting 142 (e.g., using bolts, rivets, adhesives, epoxy resins, welding, brazing, etc.) is joined to the pressure plate 120 of the pressure plate assembly 108. Additionally, as also Figure 5 shown, the side fitting 142 is optionally (e.g., using bolts, rivets, adhesives, epoxy resins, welding, brazing, etc.) joined to a corner fitting 144 corresponding to one of the outermost longitudinal beams 118a and 118b of the pressure plate assembly 108 (only one is visible in Figure 3 ), and / or joined directly thereto. Each side fitting 142 comprises (e.g., is made of, consists of, etc.) any material that enables each side fitting to function as described and / or shown herein, such as but not limited to titanium, aluminum, steel, alloys of two or more metals, composite materials, etc.

[0043] The corner joint 112 between the pressure plate assembly 108 and the bulkhead 110 includes a compression chord 146. The compression chord 146 extends along the pitch axis 104. Specifically, the compression chord 146 extends along the pitch axis 104 of the fuselage 100 from an end 148 to an opposite end 150 (not visible in Figure 3 ). In other words, the length of the compression chord 146 extends transversely across the width of the fuselage 100. In an exemplary embodiment, the length of the compression chord 146 extends generally parallel to the pitch axis 104 of the fuselage 100 and generally perpendicular to each of the roll axis 102 and the yaw axis 106. However, in other embodiments, the length of the compression chord 146 extends along: (1) a non-parallel angle (e.g., acute, obtuse, etc.) relative to the pitch axis 104 of the fuselage 100; (2) a non-perpendicular angle relative to the roll axis 102; and / or (3) a non-perpendicular angle relative to the yaw axis 106. In some examples, each of the ends 148 and 150 is referred to herein as a "first" and / or "second" end.

[0044] In an exemplary embodiment, the length of the compression chord 146 is a continuous structure extending from the end 148 to the end 150. In other words, the length of the compression chord 146 is integrally formed as a single unitary structure from the end 148 to the end 150. Thus, and as described below, the length of the compression chord 146 continuously spans at least three corner fittings (e.g., corner fittings 128 and / or 144, etc.) of the pressure plate assembly 108 along the width of the fuselage 100. As used herein, the term "continuously spans at least three corner fittings" is intended to mean that the length of the compression chord 146 extends from a first corner fitting to a third corner fitting along the width of the fuselage 100 while overlapping a second corner fitting extending between the first corner fitting and the third corner fitting. For example, in an exemplary embodiment, the length of the compression chord 146 continuously spans all of the corner fittings 128 and 144. Specifically, as Figure 1As best shown, the end 148 of the compression chord 146 extends along the width of the fuselage 100 from the corner fitting 144a of the outermost longitudinal beam 118a to the corner fitting 144b of the outermost longitudinal beam 118b (not visible in Figure 3 ). At the same time, the length of the compression chord 146 extending between the ends 148 and 150 completely overlaps with a plurality of corner fittings 128 (extending between the corner fittings 144a and 144b along the pitch axis 104).

[0045] Now referring to Figure 1 , Figure 3 and Figure 4 , an exemplary embodiment of the compression chord 146 includes an L-shape defined by leg segments 152 and 154, and the leg segments 152 and 154 extend at a non-parallel angle α with respect to each other (not labeled in Figure 1 ). In the exemplary embodiment, the angle α between the leg segments 152 and 154 is approximately 90°, such that the leg segments 152 and 154 extend substantially perpendicular to each other. However, in other embodiments, the angle α between the leg segments 152 and 154 is neither a vertical angle nor a parallel angle (e.g., the angle α is an acute angle, the angle α is an obtuse angle, etc.). In some examples, each of the leg segments 152 and / or 154 is referred to herein as the "first" and / or "second" leg segment.

[0046] Figure 1 , Figure 3 and Figure 4 show that the leg segment 152 extends outward from the leg segment 154 along the yaw axis 106 of the fuselage 100, while the leg segment 154 extends outward from the leg segment 152 along the roll axis 102. Specifically, the leg segment 152 extends outward a certain length along the yaw axis 106 from the intersection point 156 of the leg segments 152 and 154 (not labeled in Figure 1 ), and the leg segment 154 extends outward a certain length along the roll axis 102 from the intersection point 156. In the exemplary embodiment, the compression chord 146 is oriented within the corner joint 112 such that: (1) the length of the leg segment 152 extends substantially parallel to the yaw axis 106; (2) the length of the leg segment 154 extends substantially parallel to the roll axis 102. However, in other embodiments: (1) the length of the leg segment 152 extends outward from the intersection point 156 at a non-parallel angle (e.g., an acute angle, an obtuse angle, etc.) with respect to the yaw axis 106 of the fuselage 100; and / or (2) the length of the leg segment 154 extends outward at a non-parallel angle (e.g., an acute angle, an obtuse angle, etc.) with respect to the roll axis 102. The length that each of the leg segments 152 and 154 extends outward from the intersection point 156 has any dimension. In some embodiments, the dimension of the length of the leg segment 152 is different from the dimension of the length of the leg segment 154.

[0047] In some embodiments, the compression chord 146 includes one or more support members 158 that support leg segments 152 and 154 relative to each other ( Figure 4 not shown in Figure 4 ). Additionally, the compression chord 146 optionally includes one or more mounts 160 (

[0048] not shown in Figure 4 ) for engaging the compression chord 146 to the diaphragm beams 134 of the diaphragm 110. The compression chord 146 includes (e.g., is made of, consists of, etc.) any material that enables the compression chord to function as described and / or shown herein, such as but not limited to titanium, aluminum, steel, alloys of two or more metals, composite materials, etc. In some other embodiments, the compression chord 146 does not include the leg segment 154 such that the compression chord 146 includes only the leg segment 152. and Figure 5 , the corner joint 112 between the diaphragm 110 and the pressure plate assembly 108 is assembled at least in part by engaging the compression chord 146 between the pressure plate assembly 108 and the diaphragm 110. For example, the leg segment 152 of the compression chord 146 is engaged to the web 136 of the diaphragm 110 using bolts, rivets, adhesives, epoxy, welding, brazing, etc. As most clearly seen in Figure 4 , for example, the leg segment 154 of the compression chord 146 is engaged to the block 130 of the corner fitting 128 using bolts, rivets, adhesives, epoxy, welding, brazing, etc. As briefly described above, for example, the blocks 130 of the plurality of corner fittings 128 are engaged to the respective diaphragm beams 134 of the diaphragm 110 via (e.g., using etc.) the straps 132 of the plurality of corner fittings 128 using bolts, rivets, adhesives, epoxy, welding, brazing, etc.

[0049] Now referring to Figure 3 and Figure 5 , in some examples, for example, using bolts, rivets, adhesives, epoxy, welding, brazing, etc., the leg segment 154 of the compression chord 146 is also engaged to the corner fittings 144 of the outermost longitudinal beams 118a and 118b respectively located at the ends 148 and 150 of the compression chord 146. The longitudinal beam 118b and the end 150 are not visible in Figure 3 and Figure 5 but are visible in Figure 1is visible. For example, the ends 148 and 150 of the compression chord 146 are joined to the side fitting 142 of the bulkhead 110 via (e.g., using, etc.) corresponding splices 162 using bolts, rivets, adhesives, epoxy, welding, brazing, etc. Each splice 162 comprises (e.g., is made of, consists of, etc.) any material that enables the splice 162 to function as described and / or shown herein, such as but not limited to titanium, aluminum, steel, alloys of two or more metals, composite materials, etc. Optionally, for example, using bolts, rivets, adhesives, epoxy, welding, brazing, etc., the compression chord 146 is joined to the bulkhead beam 134 of the bulkhead 110 at the mounting 160 of the compression chord 146. Additionally, the compression chord 146 is optionally joined to the pressure plate 120 directly and / or via an intermediate structure (not shown) along the pitch axis 104 between adjacent corner fittings 128 and / or 144.

[0050] Now referring to Figure 4 , the compression chord 146 is joined between the pressure plate assembly 108 and the bulkhead 110 at the corner joint 112 such that the compression chord 146 extends over the outside 164 of the corner joint 112. Specifically, the corner joint 112 includes an interior 166 defined by a first space that extends within the angle α1 of the corner joint 112 formed between the pressure plate assembly 108 and the bulkhead 110. The outside 164 of the corner joint 112 is defined by a second space that extends within the angle α2 of the corner joint 112 formed between the pressure plate assembly 108 and the bulkhead 110. The web 136 of the bulkhead 110 includes an outside 168 and an inside 170 that extends opposite the outside 168. As Figure 4 is visible, the outside 168 of the web 136 defines a part of the outside 164 of the corner joint 112. For example, the outside 168 of the web 136 faces in the direction 172 (extending away from the inside 166 of the corner joint 112) along the roll axis 102 of the fuselage 100. Moreover, for example, the direction 172 that the outside 168 of the web 136 faces extends away from the pressure plate 120 along the roll axis 102. Accordingly, the outside 168 of the web 136 defines a part 164a of the outside 164 of the corner joint 112 (extending along the yaw axis 106 of the fuselage 100).

[0051] The pressure plate 120 of the pressure plate assembly 108 includes an outer side 174 and an inner side 176 extending in a direction opposite to the outer side 174. The outer side 174 of the pressure plate 120 defines a part of the outer side 164 of the corner joint 112. For example, the outer side 174 of the pressure plate 120 faces a direction 178 along the yaw axis 106 of the fuselage 100 (which extends away from the interior 166 of the corner joint 112). Also, for example, the direction 178 faced by the outer side 174 of the pressure plate 120 extends along the yaw axis 106 away from the web 136. Therefore, the outer side 174 of the pressure plate 120 defines a part 164b of the outer side 164 of the corner joint 112, and this part extends along the roll axis 102 of the fuselage 100.

[0052] As Figure 4 shown, the compression chord 146 extends on the outer side 168 of the web 136. Therefore, the compression chord 146 extends on the outer side 164 of the corner joint 112, and more specifically, extends on a part 164a of the outer side 164 of the corner joint 112. In an exemplary embodiment, the compression chord 146 is joined to the outer side 168 of the web 136.

[0053] In an exemplary embodiment, the direction 172 faced by the outer side 168 extends rearward along the roll axis 102 of the fuselage 100. In other words, the part 164a of the outer side 164 of the corner joint 112 and the outer side 168 of the web 136 face the tail along the roll axis 102. Therefore, the exemplary embodiment of the compression chord 146 faces the tail along the roll axis 102. However, in other embodiments, the bulkhead 110 and the pressure plate assembly 108 are arranged (e.g., oriented relative to the fuselage 100, etc.) such that the part 164a of the outer side 164 of the corner joint 112 faces forward along the roll axis 102, and thus, when the compression chord 146 extends on the outer side 164 of the corner joint 112, the compression chord 146 faces forward along the roll axis 102.

[0054] The compression chord 146 is joined within the corner joint 112 such that the compression chord 146 extends on the outer side 164 of the corner joint 112, enabling the compression chord 146 to provide a relatively smooth and / or relatively straight lateral (e.g., across the width of the fuselage 100 along the pitch axis 104, etc.) load path through the corner joint 112. For example, the compression chord 146 reduces or eliminates offsets, eccentricities, etc. within the lateral load path through the corner joint 112.

[0055] The compression chord 146 is joined within the corner joint 112 such that the compression chord 146 extends on the outer side 164 of the corner joint 112, enabling the compression chord 146 to carry (e.g., withstand without failure, withstand without fatigue, etc.) higher compression loads (e.g., Figure 1 and Figure 3compressive loads in the directions of arrows 114 and 116 shown in [ID=] and [ID=], etc.). Thus, the compression chord 146 enables the corner joint 112 to withstand higher compressive loads. In other words, the compression chord 146 increases the lateral stiffness of the corner joint 112 (e.g., across the width of the fuselage 100 along the pitch axis 104, etc.).

[0056] Now referring to Figure 1 , Figure 3 and Figure 5 , the compression chord 146 is joined between the pressure plate assembly 108 and the bulkhead 110 such that the load path of the compression chord passes over the load paths of the corner fittings 128 and 144. Specifically, as described above, the length of the compression chord 146 continuously spans all of the corner fittings 128 and 144. In this way, the load path of the compression chord 146 does not break at the corner fittings 128 and 144 along the length of the compression chord 146, but is continuous along the pitch axis 104 between the corner fittings 144a and 144b. In other words, the compression chord 146 provides a continuous lateral (e.g., across the width of the fuselage 100 along the pitch axis 104, etc.) load path spanning the corner fittings 128 and 144. Thus, the load path of the compression chord 146 passes over the corner fittings 128 and 144.

[0057] Passing the compression chord 146 over the corner fittings 128 and 144 enables the compression chord 146 to provide a relatively smooth and / or relatively straight lateral (e.g., across the width of the fuselage 100 along the pitch axis 104, etc.) load path through the corner joint 112. For example, the compression chord 146 reduces or eliminates offsets, eccentricities, etc. within the lateral load path through the corner joint 112.

[0058] Passing the compression chord 146 over the corner fittings 128 and 144 enables the compression chord 146 to carry (e.g., withstand without failure, withstand without fatigue, etc.) higher compressive loads (e.g., Figure 1 and Figure 3 compressive loads in the directions of arrows 114 and 116 shown in [ID=] and [ID=], etc.). Thus, the compression chord 146 enables the corner joint 112 to withstand higher compressive loads. In other words, the compression chord 146 increases the lateral stiffness of the corner joint 112 (e.g., across the width of the fuselage 100 along the pitch axis 104, etc.).

[0059] Passing the compression chord 146 over the corner fittings 128 and 144 can reduce the number of parts of the corner joint 112 and thereby: (1) reduce the weight of the corner joint 112; (2) reduce the time required to assemble the corner joint 112 (e.g., by improving the assembly process of the fuselage 100, etc.); and / or (3) reduce the cost of assembling the corner joint 112, thereby reducing the cost of the fuselage 100.

[0060] In some embodiments, prior to assembling the corner joint 112, the corner fittings 128 and / or 144 are pre - installed (e.g., joined, etc.) to the longitudinal beams 118, as opposed to being installed during the assembly of the corner joint 112. Pre - installing the corner fittings 128 and / or 144 to the longitudinal beams 118 reduces the time required to assemble the corner joint 112 (e.g., by improving the assembly process of the fuselage 100, etc.), thereby reducing the cost of assembling the corner joint 112 and thus reducing the cost of the fuselage 100. Moreover, pre - installing the corner fittings 128 and / or 144 to the longitudinal beams 118 reduces the number of injuries that occur during the assembly of the corner joint 112, e.g., by reducing the number of drilling and / or other operations required to complete the assembly of the corner joint 112.

[0061] In some embodiments, as opposed to drilling during the assembly of the corner joint 112, one or more components of the pressure plate assembly 108, the bulkhead 110, the corner joint 112, and / or the fuselage 100 (e.g., the compression chord 146, the plurality of longitudinal beams 118, the pressure plate 120, the web 136, the bulkhead beam 134, the splice 162, the corner fitting 144, the plurality of corner fittings 128, the block 130, the strap 132, the side fitting 142, etc.) are pre - drilled prior to the assembly of the corner joint 112. Pre - drilling one or more components reduces the time required to assemble the corner joint 112 (e.g., by improving the assembly process of the fuselage 100, etc.), thereby reducing the cost of assembling the corner joint 112 and thus reducing the cost of the fuselage 100. Moreover, pre - drilling one or more components reduces the number of injuries that occur during the assembly of the corner joint 112, e.g., by reducing or eliminating the number of drilling operations required to complete the assembly of the corner joint 112.

[0062] Figure 6 is a flow chart showing a method 200 for manufacturing a fuselage according to an embodiment. The method 200 includes constructing, at 202, a pressure plate assembly 108 such that: (1) the plurality of longitudinal beams 118 of the pressure plate assembly 108 extend along the roll axis 102 of the fuselage 100 for a certain length; (2) the compliant pressure plate (e.g., the pressure plate 120) of the pressure plate assembly 108 extends between the plurality of longitudinal beams 118. At 204, the method 200 includes constructing a bulkhead 110 that extends along the yaw axis 106 of the fuselage 100.

[0063] At 208, method 200 includes joining pressure plate assembly 108 and bulkhead 110 at corner joint 112, including joining compression chord 146 between pressure plate assembly 108 and bulkhead 110 such that compression chord 146 extends on outer side 164 of corner joint 112. Optionally, method 200 includes, at 206, pre-drilling one or more components (e.g., one or more assemblies of pressure plate assembly 108, bulkhead 110, compression chord 146, corner joint 112, airframe 100, etc.), and then joining pressure plate assembly 108 and bulkhead 110 at corner joint 112 at 208.

[0064] In some embodiments, joining compression chord 146 between pressure plate assembly 108 and bulkhead 110 at 208 includes: joining compression chord 145 between pressure plate assembly 108 and bulkhead 110 at 208a such that a portion of outer side 164 of corner joint 112 defined by bulkhead 110 faces the tail along roll axis 102 of airframe 100. Further, in some embodiments of method 200, joining compression chord 146 between pressure plate assembly 108 and bulkhead 110 at 208 includes joining compression chord 146 to a plurality of corner fittings 128 of pressure plate assembly 108 at 208b.

[0065] Now referring Figure 7 , some examples of the present disclosure are described in the context of an aircraft 300 that includes an airframe 302 having a fuselage 304. The fuselage 304 includes an interior 306. The airframe 302 includes a plurality of advanced systems 308. Examples of advanced systems 308 include one or more of a propulsion system 310, an electrical system 312, a hydraulic fluid system 314, a control system 316, and an environmental system 318. Any number of other systems may be included. Although aerospace examples are shown, the principles may be applied to other industries such as, but not limited to, the automotive industry, the marine industry, etc.

[0066] Examples of the present disclosure may be described in the context of an aircraft manufacturing and service method 400 as shown in Figure 8 . During pre-production, illustrative method 400 may include specification and design 402 of an aircraft (e.g., aircraft 300 as shown in Figure 7 ) and material procurement 404. During production, component and sub-component manufacturing 406 of the aircraft and system integration 408 are performed. Thereafter, the aircraft may be certified and delivered 410 for service 412. When used by a customer, the aircraft is scheduled for routine maintenance and servicing 414 (which may also include modifications, reconfigurations, refurbishments, etc.).

[0067] Each process of the illustrative method 400 can be performed or carried out by a system integrator, a third party, and / or an operator (e.g., a customer, etc.). For ease of explanation, the system integrator can include, but is not limited to, any number of aircraft manufacturers and major system subcontractors; the third party can include, but is not limited to, any number of suppliers, subcontractors, and vendors; and the operator can be an airline, a leasing company, a military entity, a service organization, etc.

[0068] It should be noted that the systems described herein can include any number of other systems. Additionally, although an aviation example is shown, the principles can be applied to other industries, such as but not limited to the automotive industry, the marine industry, etc.

[0069] The systems and methods shown or described herein can be employed at any one or more stages of the manufacturing and service method 400. For example, components or sub-components corresponding to component and sub-component manufacturing 406 can be assembled or manufactured in a manner similar to that of components or sub-components generated when an aircraft is in use. Moreover, for example, by substantially accelerating the assembly of an aircraft or reducing the cost of an aircraft, one or more aspects of the system, method, or a combination thereof can be utilized during the production states of sub-component manufacturing 406 and system integration 408. Similarly, for example but not limited to, one or more aspects or a combination thereof implemented by a device or method when an aircraft is in use (e.g., maintenance and servicing 414).

[0070] Various embodiments of the present disclosure provide a relatively smooth and / or relatively straight lateral load path through the corner joint between the pressure plate assembly and the bulkhead. Various embodiments of the present disclosure enable the corner joint between the pressure plate assembly and the bulkhead to withstand higher compression loads. Various embodiments of the present disclosure increase the lateral stiffness of the corner joint between the pressure plate assembly and the bulkhead.

[0071] Various embodiments of the present disclosure reduce or eliminate the drilling operations performed during the assembly of the corner joint between the bulkhead and the pressure plate assembly. Various embodiments of the present disclosure reduce the number of parts of the corner joint between the bulkhead and the pressure plate assembly. Various embodiments of the present disclosure reduce the weight of the corner joint between the bulkhead and the pressure plate assembly. Various embodiments of the present disclosure reduce the time required to assemble the corner joint between the bulkhead and the pressure plate assembly. Various embodiments of the present disclosure reduce the cost of assembling the corner joint between the bulkhead and the pressure plate assembly, thereby reducing the cost of the fuselage. Various embodiments of the present disclosure reduce the number of injuries that occur when joining the bulkhead and the pressure plate assembly at the corner joint.

[0072] The following items describe other aspects:

[0073] Item Group A:

[0074] A1. An airframe for an aircraft, the airframe comprising:

[0075] A pressure plate assembly extends along the roll axis of the fuselage. The pressure plate assembly includes longitudinal beams and a pressure plate. The longitudinal beams extend along the roll axis of the fuselage for a certain length. The pressure plate extends between the longitudinal beams along the length of the longitudinal beams. The pressure plate has compliance along the pitch axis of the fuselage;

[0076] A bulkhead extends along the yaw axis of the fuselage. The bulkhead is joined to the pressure plate assembly at a corner joint; and

[0077] A compression chord extends along the pitch axis of the fuselage for a certain length. Wherein, the compression chord is joined between the pressure plate assembly and the bulkhead at the corner joint such that the compression chord extends outside the corner joint.

[0078] A2. The fuselage according to item A1, wherein a part of the outside of the corner joint defined by the bulkhead faces the tail along the roll axis of the fuselage such that the compression chord faces the tail along the roll axis.

[0079] A3. The fuselage according to item A1, wherein the bulkhead includes bulkhead beams and a web. The bulkhead beams extend along the yaw axis of the fuselage for a certain length. The web extends between the bulkhead beams along the length of the bulkhead beams. The web includes an outside that defines a part of the outside of the corner joint. Wherein, the compression chord extends on the outside of the web.

[0080] A4. The fuselage according to item A1, wherein the bulkhead includes bulkhead beams and a web. The bulkhead beams extend along the yaw axis of the fuselage for a certain length. The web extends between the bulkhead beams along the length of the bulkhead beams. The web includes an outside that defines a part of the outside of the corner joint. Wherein, the compression chord is joined to the outside of the web.

[0081] A5. The fuselage according to item A1, wherein the pressure plate assembly includes corner fittings joined to at least one of the longitudinal beams or the pressure plate. The compression chord is joined to the corner fittings.

[0082] A6. The fuselage according to item A1, wherein the pressure plate assembly includes corner fittings joined to at least one of the longitudinal beams or the pressure plate. The bulkhead includes bulkhead beams extending along the yaw axis of the fuselage for a certain length. The corner fittings include a block and a strap separated from the block. The compression chord is joined to the block of the corner fittings. The block of the corner fittings is joined to the bulkhead beams by the strap.

[0083] A7. The fuselage according to item A1, wherein the compression chord includes an L-shape defined by a first leg segment and a second leg segment extending at non-parallel angles relative to each other.

[0084] A8. The fuselage according to item A1, wherein the compression chord includes an L-shape defined by a first leg section and a second leg section that extend at non-parallel angles relative to each other, the first leg section extending outward from the second leg section along the yaw axis, and the second leg section extending outward from the first leg section along the roll axis.

[0085] A9. The fuselage according to item A1, wherein the bulkhead includes side fittings, the corner joint includes at least one splicing piece, and the compression chord extends a certain length from a first end and a second end, and at least one of the first end or the second end of the compression chord is joined to the side fittings via at least one splicing piece.

[0086] A10. The fuselage according to item A1, wherein the pressure plate includes a catenary web.

[0087] A11. The fuselage according to item A1, wherein the fuselage includes a landing gear bay, and the bulkhead is a component of the landing gear bay.

[0088] A12. The fuselage according to item A1, wherein the fuselage includes an elliptical cross-sectional shape with a width greater than its height.

[0089] A13. The fuselage according to item A1, wherein the pressure plate assembly includes corner fittings joined to at least one of the longitudinal beam or the pressure plate, and the length of the compression chord continuously spans at least three corner fittings.

[0090] A14. The fuselage according to item A1, wherein the fuselage includes a semi-monocoque fuselage.

[0091] Item group B:

[0092] B1. A fuselage for an aircraft, the fuselage comprising:

[0093] A pressure plate assembly extending along the roll axis of the fuselage, the pressure plate assembly including a longitudinal beam, corner fittings, and a pressure plate, the longitudinal beam extending a certain length along the roll axis of the fuselage, the corner fittings being joined to at least one of the longitudinal beam or the pressure plate, the pressure plate extending between the longitudinal beams along the length of the longitudinal beam, and the pressure plate having compliance along the pitch axis of the fuselage;

[0094] A bulkhead extending along the yaw axis of the fuselage, the bulkhead being joined to the pressure plate assembly; and

[0095] A compression chord extending a length along the pitch axis of the fuselage, wherein the compression chord is joined between the pressure plate assembly and the bulkhead such that the load path of the compression chord passes over the load path of the corner fittings.

[0096] B2. The fuselage according to item B1, wherein the bulkhead is joined to the pressure plate assembly at a corner joint, and at the corner joint, the compression chord is joined between the pressure plate assembly and the bulkhead such that the compression chord extends outside the corner joint.

[0097] B3. The fuselage according to item B1, wherein the length of the compression chord continuously spans at least three corner fittings.

[0098] Group of items C:

[0099] C1. A method of manufacturing a fuselage, comprising:

[0100] Constructing a pressure plate assembly such that the longitudinal beams of the pressure plate assembly extend along the roll axis of the fuselage for a certain length, and such that the compliant pressure plates of the pressure plate assembly extend between the longitudinal beams;

[0101] Constructing a bulkhead extending along the yaw axis of the fuselage;

[0102] Joining the pressure plate assembly and the bulkhead together at a corner joint; and

[0103] Joining a compression chord between the pressure plate assembly and the bulkhead at a corner joint such that the compression chord extends outside the corner joint.

[0104] C2. The method according to item C1, wherein joining the compression chord between the pressure plate assembly and the bulkhead includes joining the compression chord between the pressure plate assembly and the bulkhead such that a part of the outside of the corner joint defined by the bulkhead faces the tail along the roll axis of the fuselage.

[0105] C3. The method according to item 1, wherein joining the compression chord between the pressure plate assembly and the bulkhead includes joining the compression chord to a corner fitting of the pressure plate assembly.

[0106] As used herein, a structure, limitation, or element "configured to" perform a task or operation is specifically formed, constructed, or adjusted structurally in a manner corresponding to the task or operation. For clarity and to avoid doubt, an object that can only be modified to perform a task or operation is not "configured to" perform the task or operation as used herein.

[0107] As will be apparent to those skilled in the art, any range or value given herein can be extended or changed without losing the sought-after effect.

[0108] Although the subject matter has been described in language specific to structural features and / or method acts, it should be understood that the subject matter defined in the appended claims need not be limited to the above specific features or acts. Rather, the above specific features and acts are disclosed as example forms for implementing the claims.

[0109] It will be understood that the above benefits and advantages may relate to one embodiment or may relate to several embodiments. Embodiments are not limited to those that solve any or all of the stated problems or have any or all of the stated benefits and advantages. It will also be understood that a reference to "an" item refers to one or more of those items.

[0110] As used in this specification, the term "comprising" means including the features or acts that follow, without excluding the presence of one or more additional features or acts.

[0111] Unless otherwise specified, the order of performance or execution of the operations in the examples of the present disclosure shown and described herein is not required. That is, unless otherwise specified, the operations may be performed in any order, and the examples of the present disclosure may include more or fewer operations than those disclosed herein. For example, it is contemplated that a particular operation may be performed before, concurrently with, or after another operation (e.g., a different step, etc.) within the scope of aspects of the present disclosure.

[0112] When introducing elements of aspects of the present disclosure or examples thereof, the articles "a", "an", "the", and "said" are intended to mean that there is one or more of the elements. The terms "comprising", "including", and "having" are intended to be inclusive and mean that there may be other elements in addition to the listed elements. The term "exemplary" is intended to mean "an example of...". The phrase "one or more of the following: A, B, and C" refers to "at least one of A and / or at least one of B and / or at least one of C".

[0113] Having described the various aspects of the present disclosure in detail, it will be apparent that modifications and variations can be made without departing from the scope of the various aspects of the present disclosure as defined by the appended claims. Since various changes can be made to the above-described structures, products, and methods without departing from the scope of the various aspects of the present disclosure, all of the above-described matter included in the foregoing description and shown in the accompanying drawings is to be construed as illustrative and not restrictive.

[0114] It should be understood that the above description is intended to be illustrative and not restrictive. For example, the above embodiments (and / or aspects thereof) can be used in combination with each other. Additionally, many modifications may be made to adapt a particular situation or material to the teachings of the various embodiments of the present disclosure without departing from its scope. Although the dimensions and types of the materials described herein are intended to define the parameters of the various embodiments of the present disclosure, these embodiments are in no way restrictive but rather exemplary embodiments. After reviewing the above description, many other embodiments will be apparent to a person of ordinary skill in the art. Accordingly, the scope of the various embodiments of the present disclosure should be determined with reference to the appended claims and the full scope of equivalents to which those claims are entitled. In the appended claims, the terms "comprising" and "wherein" are used as the ordinary English equivalents of the respective terms "including" and "wherein". Additionally, 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 following claims are not written in means-plus-function format and are not intended to be interpreted under 35 U.S.C. § 112(f) unless and until such claim limitations expressly use the phrase "means" followed by a recitation of function without further structure.

[0115] This written description uses examples to disclose the various embodiments of the present disclosure, including the best mode, and also enables any person of ordinary skill in the art to practice the various embodiments of the present disclosure, including making and using any device or system, and performing any incorporated method. The patentable scope of the various embodiments of the present disclosure is defined by the claims and may include other examples that occur to a person of ordinary skill in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims or if they include equivalent structural elements that do not differ substantially from the literal language of the claims.

Claims

1. An airframe of an aircraft, the airframe comprising: A pressure plate assembly extending along the roll axis of the airframe, the pressure plate assembly including longitudinal beams and a pressure plate, the longitudinal beams extending a certain length along the roll axis of the airframe, the pressure plate extending between the longitudinal beams along the length of the longitudinal beams, the pressure plate having compliance along the pitch axis of the airframe; A bulkhead extending along the yaw axis of the airframe, the bulkhead being joined to the pressure plate assembly at a corner joint, the bulkhead including bulkhead beams extending a certain length along the yaw axis of the airframe, the bulkhead defining an outer side and an inner side extending opposite to the outer side, the outer side facing away from the corner joint along the roll axis; and A compression chord extending a certain length along the pitch axis of the airframe, wherein at the corner joint the compression chord is joined between the pressure plate assembly and the bulkhead such that the compression chord extends outside the corner joint, wherein the outer side of the bulkhead defines a part of the outer side of the corner joint such that the outer side of the corner joint extends away from the pressure plate in a direction along the roll axis; and A corner fitting joined to the longitudinal beam, the corner fitting including a block and a strap separated from the block; Wherein the compression chord is joined to the block of the corner fitting, and the block of the corner fitting is joined to the bulkhead beam by the strap.

2. The fuselage according to claim 1, wherein, The part of the outer side of the corner joint defined by the bulkhead faces the tail along the roll axis of the airframe such that the compression chord faces the tail along the roll axis.

3. The fuselage according to claim 1, wherein, The bulkhead includes a web extending between the bulkhead beams along the length of the bulkhead beams, the web including an outer side defining a part of the outer side of the corner joint, wherein the compression chord extends on the outer side of the web.

4. The fuselage according to claim 1, wherein, The bulkhead includes a web extending between the bulkhead beams along the length of the bulkhead beams, the web including an outer side defining a part of the outer side of the corner joint, wherein the compression chord is joined to the outer side of the web.

5. The fuselage according to claim 1, wherein, The compression chord includes an L-shape defined by a first leg section and a second leg section extending at non-parallel angles relative to each other.

6. The fuselage according to claim 1, wherein, The compression chord includes an L-shape defined by a first leg section and a second leg section extending at non-parallel angles relative to each other, the first leg section extending outward from the second leg section along the yaw axis, and the second leg section extending outward from the first leg section along the roll axis.

7. The fuselage according to claim 1, wherein, The bulkhead includes side fittings, the corner joint includes at least one splice piece, and the compression chord extends a certain length between a first end and a second end, at least one of the first end and the second end of the compression chord being joined to the side fittings via the at least one splice piece.

8. The fuselage according to claim 1, wherein, The pressure plate includes a catenary web.

9. The fuselage according to claim 1, wherein, The airframe includes a landing gear bay, and the bulkhead is a component of the landing gear bay.

10. The fuselage according to claim 1, wherein, The airframe includes an oval cross-sectional shape with a width greater than the height.

11. The fuselage according to claim 1, wherein, The length of the compression chord continuously spans at least three of the corner fittings.

12. The fuselage according to claim 1, wherein, The fuselage includes a semi-monocoque fuselage.

13. A fuselage of an aircraft, the fuselage comprising: A pressure plate assembly extending along the roll axis of the fuselage, the pressure plate assembly including longitudinal beams, corner fittings, and a pressure plate, the longitudinal beams extending along the roll axis of the fuselage for a certain length, the corner fittings being joined to the longitudinal beams, the pressure plate extending between the longitudinal beams along the length of the longitudinal beams, the pressure plate having compliance along the pitch axis of the fuselage; Bulkheads extending along the yaw axis of the fuselage, the bulkheads being joined to the pressure plate assembly, the bulkheads including bulkhead beams extending along the yaw axis of the fuselage for a certain length, the bulkheads defining an outer side and an inner side extending opposite to the outer side, the outer side facing in a direction away from the corner joints along the roll axis; and Compression chords extending along the pitch axis of the fuselage for a certain length, wherein the compression chords are joined between the pressure plate assembly and the bulkheads such that the load path of the compression chords passes over the load path of the corner fittings, wherein the corner fittings include blocks and straps separated from the blocks; wherein the compression chords are joined to the blocks of the corner fittings, and the blocks of the corner fittings are joined to the bulkhead beams by the straps.

14. The fuselage according to claim 13, wherein, The bulkheads are joined to the pressure plate assembly at the corner joints, and the compression chords are joined between the pressure plate assembly and the bulkheads at the corner joints such that the compression chords extend outside the corner joints.

15. The fuselage according to claim 13, wherein, The length of the compression chord continuously spans at least three corner fittings.

16. A method of manufacturing a fuselage according to any one of claims 1 to 12, comprising: Constructing a pressure plate assembly such that the longitudinal beams of the pressure plate assembly extend along the roll axis of the fuselage for a certain length and such that the compliant pressure plate of the pressure plate assembly extends between the longitudinal beams; Constructing bulkheads extending along the yaw axis of the fuselage; Joining the pressure plate assembly and the bulkheads together at the corner joints; Joining compression chords between the pressure plate assembly and the bulkheads at the corner joints such that the compression chords extend outside the corner joints; and Joining the compression chords to the corner fittings of the pressure plate assembly.

17. The method according to claim 16, wherein Joining the compression chords between the pressure plate assembly and the bulkheads includes: joining the compression chords between the pressure plate assembly and the bulkheads such that a part of the outer side of the corner joint defined by the bulkhead faces the tail along the roll axis of the fuselage.

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