Stringer joints for pressure deck components

Abstract

The present invention relates to a stringer joint for a pressure deck assembly. A pressure deck assembly for a fuselage includes a stringer extending a length along a roll axis of the fuselage. The stringer includes a center member and opposing first and second flanges extending from the center member. The first flange includes a first upper side and a first lower side. The second flange includes a second upper side and a second lower side. The pressure deck assembly includes a pressure deck including a first deck segment and a second deck segment. The first deck segment is joined to a first flange of the stringer along a first lower side of the first flange. The second deck segment is joined to a second flange of the stringer along a second lower side of the second flange.

Description

Technical Field

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

[0002] The fuselage of some aircraft is constructed with a pressure deck assembly, which is sometimes referred to as a "pressure deck" or "horizontal pressure deck". The pressure deck assembly forms a partitioning structure that divides the height of the fuselage into different compartments, such as to support the floor of a compartment (e.g., a passenger compartment, a cargo compartment, etc.), to separate a pressurized compartment (e.g., a passenger compartment, a cargo compartment, etc.) from an unpressurized compartment (e.g., a wheel well, etc.), etc. The pressure deck assembly sometimes includes longitudinal beams that extend along the length of the fuselage.

[0003] The operating environment of some aircraft requires that the fuselage include as many corrosion-resistant components as possible. However, corrosion-resistant metals such as titanium may be relatively heavy, for example, compared to corrosion-resistant composite materials such as carbon fiber. Therefore, it may be less desirable to manufacture the longitudinal beams of the pressure deck assembly from corrosion-resistant metals. In addition, although some corrosion-resistant composite materials are lighter than many corrosion-resistant metals, the interlaminar tension (ILT) capability of some corrosion-resistant composite materials may not be sufficient to withstand the pressure loads applied to the pressure deck assembly during operation of the aircraft. Summary of the invention

[0004] In one aspect, a pressure deck assembly for a fuselage is provided. The pressure deck assembly includes a stringer extending a length along a roll axis of the fuselage. The stringer includes a center member and opposing first and second flanges extending from the center member. The first flange includes a first upper side and a first lower side. The second flange includes a second upper side and a second lower side. The pressure deck assembly includes a pressure deck including a first deck segment and a second deck segment. The first deck segment is joined to a first flange of the stringer along a first lower side of the first flange. The second deck segment is joined to a second flange of the stringer along a second lower side of the second flange.

[0005] In another aspect, a pressure deck assembly for a fuselage is provided. The pressure deck assembly includes a longitudinal beam extending a length along the roll axis of the fuselage. The longitudinal beam includes a center member and first and second flanges extending from the center member. The first flange forms a first corner of the longitudinal beam with the center member. The second flange forms a second corner of the longitudinal beam with the center member. The pressure deck assembly includes a pressure deck including a first deck segment and a second deck segment. The first deck segment is joined to the first flange of the longitudinal beam so that the first deck segment extends outside the first corner of the longitudinal beam. The second deck segment is joined to the second flange of the longitudinal beam so that the second deck segment extends outside the second corner of the longitudinal beam.

[0006] In another aspect, a fuselage for an aircraft is provided. The fuselage includes a pressure deck assembly including a stringer extending a length along a roll axis of the fuselage. The stringer includes a center member and a flange extending from the center member. The flange includes an upper side and a lower side. The pressure deck assembly includes a pressure deck including a deck segment. The deck segment is joined to the flange of the stringer along the lower side of the flange. BRIEF DESCRIPTION OF THE DRAWINGS

[0007] Figure 1 is a perspective view showing a segment of a pressure deck assembly for a fuselage of an aircraft according to an implementation.

[0008] Figure 2 It is based on the implementation Figure 1 A cross-sectional view of the fuselage is shown in FIG.

[0009] Figure 3 It is based on the implementation Figure 1 A front view of a pressure deck assembly segment is shown in FIG.

[0010] Figure 4 yes Figure 1 A cross-sectional view of a portion of a pressure deck assembly segment shown in , illustrating a joint between a pressure deck and a stringer of a pressure deck assembly according to an implementation.

[0011] Figure 5 is shown according to the realization of the through Figure 4 Cross-sectional view of the load path of the joint shown in .

[0012] Figure 6 It is a schematic diagram of the realization of the aircraft.

[0013] Figure 7 It is a block diagram of the implementation of the aircraft production and maintenance method. DETAILED DESCRIPTION

[0014] When read in conjunction with the accompanying drawings, the foregoing summary of the invention and the following detailed description of certain embodiments and implementations will be better understood. As used herein, an element or step described in the singular and preceded by the word "one" or "an" should be understood to not necessarily exclude the plural number of elements or steps. In addition, reference to "an embodiment" or "an implementation" is not intended to be interpreted as excluding the existence of additional embodiments or implementations that also incorporate the described features. In addition, unless explicitly stated to the contrary, an embodiment that "includes" or "has" an element or multiple elements of a particular property may include additional elements that do not have that property.

[0015] 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 orientation shown in the drawings. The orientation can be reversed, rotated, or otherwise changed so that if the structure is flipped 180 degrees, the top side becomes the bottom side, if the structure is pivoted 90 degrees, the top side becomes the left or right side, and so on.

[0016] Certain implementations of the present disclosure provide a pressure deck assembly for a fuselage. The pressure deck assembly includes a longitudinal beam extending a length along a roll axis of the fuselage. The longitudinal beam includes a center member and opposing first and second flanges extending from the center member. The first flange includes a first upper side and a first lower side. The second flange includes a second upper side and a second lower side. The pressure deck assembly includes a pressure deck including a first deck segment and a second deck segment. The first deck segment is joined to a first flange of the longitudinal beam along a first lower side of the first flange. The second deck segment is joined to a second flange of the longitudinal beam along a second lower side of the second flange.

[0017] Certain implementations of the present disclosure provide a pressure deck assembly for a fuselage. The pressure deck assembly includes a longitudinal beam extending a length along the roll axis of the fuselage. The longitudinal beam includes a center member and a first flange and a second flange extending from the center member. The first flange forms a first corner of the longitudinal beam with the center member. The second flange forms a second corner of the longitudinal beam with the center member. The pressure deck assembly includes a pressure deck, which includes a first deck segment and a second deck segment. The first deck segment is joined to the first flange of the longitudinal beam so that the first deck segment extends outside the first corner of the longitudinal beam. The second deck segment is joined to the second flange of the longitudinal beam so that the second deck segment extends outside the second corner of the longitudinal beam.

[0018] Certain implementations of the present disclosure enable longitudinal beams of a pressure deck assembly to be manufactured from composite materials. Certain implementations of the present disclosure reduce the weight of a pressure deck assembly of an aircraft fuselage. Certain implementations of the present disclosure improve the operational performance, efficiency, and / or capability of an aircraft.

[0019] Referring now to the accompanying drawings, Figure 1 Provided in the invention are for use in aircraft (e.g., Figure 6 300, etc.) of a fuselage 102. The fuselage 102 extends a length (i.e., longitudinally) along a roll axis 104 of the fuselage 102 and the aircraft. The fuselage 102 extends a width (e.g., laterally, horizontally, etc.) along a pitch axis 106 of the fuselage 102 and the aircraft. The fuselage 102 extends a height (e.g., vertically, etc.) along a yaw axis 108 of the fuselage 102 and the aircraft. Figure 1As can be seen in FIG. 1 , roll axis 104, pitch axis 106, and yaw axis 108 extend perpendicularly relative to each other. During flight of the aircraft, fuselage 102 is configured to perform roll, pitch, and yaw motions about roll axis 104, pitch axis 106, and yaw axis 108, respectively. In an exemplary implementation, fuselage 102 is a semi-monocoque fuselage, but in other implementations fuselage 102 is any other type of fuselage 102.

[0020] The fuselage 102 includes a pressure deck assembly 100. Figure 1 As shown, the pressure deck assembly 100 extends along a roll axis 104 of the fuselage 102. Specifically, the pressure deck assembly 100 extends a length along the roll axis 104. In other words, the length of the pressure deck assembly 100 extends longitudinally along the length of the fuselage 102. The width of the pressure deck assembly 100 extends transversely across the width of the fuselage 102 along the pitch axis 106.

[0021] The pressure deck assembly 100 forms a partitioning structure that divides the height of the fuselage 102 into different compartments along at least a portion of the length of the fuselage 102. In some implementations, the pressure deck assembly 100 is a structure that supports (or directly forms) a cargo compartment and / or a passenger compartment (e.g., Figure 6 In some implementations, the pressure deck assembly 100 will pressurize the cabin (e.g., Figure 6 306 shown in FIG. 1 ) is separated from one or more unpressurized compartments of the fuselage 102, such as, but not limited to, wheel wells (e.g., Figure 6 320 shown in FIG. 1 ) and / or the like. In some implementations, a segment of a pressure deck assembly 100 defines a portion (one of two or more segments) of the length of the pressure deck assembly 100. In other implementations, a segment of a pressure deck assembly 100 defines the entire length of the pressure deck assembly 100.

[0022] In an exemplary implementation, the length of the pressure deck assembly 100 extends generally parallel to the roll axis 104 of the fuselage 102, and the width of the pressure deck assembly 100 extends generally parallel to the pitch axis 106, such that when the fuselage 102 is oriented vertically (e.g., flush with the horizontal), the pressure deck assembly 100 extends generally horizontally. In other implementations, at least one segment of the length of the pressure deck assembly 100 extends at a non-parallel angle (e.g., acute angle, obtuse angle, etc.) relative to the roll axis 104 of the fuselage 102, and / or at least one segment of the width of the pressure deck assembly 100 extends at a non-parallel angle (e.g., acute angle, obtuse angle, etc.) relative to the pitch axis 106 of the fuselage 102. In some implementations, the pressure deck assembly 100 is a component of (e.g., forms a support structure for, forms a boundary for, extends within, etc.) one or more compartments of the fuselage 102, such as, but not limited to, wheel wells (e.g., Figure 6 320 shown in FIG. 1 , etc.) and / or the like.

[0023] Figure 1 The pressure deck assembly 100 shown in FIG. 1 extends anywhere along the length of the fuselage 102 (ie, anywhere along the length of the roll axis 104 ). Figure 6 According to an exemplary implementation Figure 1 . Specifically, the pressure deck assembly 100 is a component of the wheel well 320 of the fuselage 302 (e.g., the pressure deck assembly 100 forms a support structure for the wheel well 320, the pressure deck assembly 100 forms a boundary for the wheel well 320, the pressure deck assembly 100 extends within the wheel well 320, etc.). However, additionally or alternatively, the pressure deck assembly 100 has any other location along the length of the fuselage 302, whether or not such location is within the wheel well of the fuselage 302. For example, in other implementations, the pressure deck assembly 100 forms a support structure for another component, structure, etc. of the fuselage 302 in addition to or in lieu of the wheel well.

[0024] Reference now Figure 2 , an exemplary implementation of the fuselage 102 includes an elliptical cross-sectional shape that is wider than it is tall, at least at the location of the pressure deck assembly 100 (at least when the interior of the fuselage 102 is not pressurized). Specifically, when the interior of the fuselage 102 is not pressurized, the cross-sectional shape of the fuselage 102 at the pressure deck assembly 100 is approximately Figure 2 In other words, the dashed line 102a shows the unpressurized cross-sectional shape of the fuselage 102 at the location of the pressure deck assembly 100. The cross-sectional shape of the fuselage 102 at the pressure deck assembly 100 when the interior of the fuselage 102 is pressurized is shown in FIG. Figure 2 In other words, the solid line 102 b shows the pressurized cross-sectional shape of the fuselage 102 at the location of the pressure deck assembly 100 .

[0025] like Figure 2 106 than along the yaw axis 108. As can be seen from a comparison of the dashed line 102a and the solid line 102b, the pressurized cross-sectional shape of the fuselage 102 represented by the dashed line 102a is smaller along the pitch axis 106 and larger along the yaw axis 108 than the unpressurized cross-sectional shape of the fuselage 102 represented by the dashed line 102a. Thus, the pressurization of the interior of the fuselage 102 applies (e.g., increases, etc.) a compressive force to the fuselage 102 in the directions of arrows 110 and 112, which contracts the fuselage 102 along the pitch axis 106 and expands the fuselage 102 along the yaw axis 108.

[0026] The fuselage 102 is not limited to including an elliptical cross-sectional shape that is wider than it is tall at the location of the pressure deck assembly 100. Rather, in other implementations, the fuselage 102 includes an approximately circular cross-sectional shape at the location of the pressure deck assembly 100 when the fuselage 102 is not pressurized. In other implementations, the fuselage 102 includes an elliptical cross-sectional shape that is taller than it is wide at the location of the pressure deck assembly 100 when the fuselage 102 is not pressurized.

[0027] Reference again Figure 1 , the pressure deck assembly 100 includes a plurality of stringers 114 and a pressure deck 116. Each of the plurality of stringers 114 extends a length along the roll axis 104 of the fuselage 102 from an end portion 118 to an opposite end portion 120. In other words, the length of each of the plurality of stringers 114 extends longitudinally along the length of the fuselage 102. In an exemplary implementation, the length of each of the plurality of stringers 114 extends substantially parallel to the roll axis 104 of the fuselage 102 and substantially perpendicular to each of the pitch axis 106 and the yaw axis 108. However, in other implementations, the length of one or more of the plurality of stringers 114 extends in the following manner: (1) at a non-parallel angle (e.g., an acute angle, an obtuse angle, etc.) relative to the roll axis 104 of the fuselage 102; (2) at a non-perpendicular angle relative to the pitch axis 106; and / or (3) at a non-perpendicular angle relative to the yaw axis 108.

[0028] Optionally, the pressure deck assembly 100 includes one or more reinforcing ribs 122 that are joined between adjacent ones of the plurality of stringers 114, for example, to facilitate supporting adjacent ones of the plurality of stringers 114 in the orientations shown herein. Each of the plurality of stringers 114 includes (e.g., is made of, is composed of, etc.) any material that enables each of the plurality of stringers 114 to function as described and / or shown herein. For example, in some implementations, the stringers 114 include (e.g., are made of, are composed of, etc.) a composite material, such as, but not limited to, a carbon composite material, a carbon fiber composite material, a thermoplastic composite material, a thermoplastic carbon fiber composite material, a thermoset composite material, a thermoset carbon fiber composite material, a poly(p-phenylene terephthalamide) fiber composite material, etc. In one example, one or more of the stringers 114 include (e.g., are made of, are composed of, etc.) a thermoplastic carbon fiber composite material. In some other implementations, one or more of the stringers 114 include (e.g., are made of, consist of, etc.) another material in addition to or in place of the composite material, such as, but not limited to, titanium, aluminum, steel, alloys of two or more metals, etc. Although eight are shown in the exemplary implementation, the pressure deck assembly 100 includes any number of stringers 114 .

[0029] Reference now Figure 1 and Figure 3 , the pressure deck 116 extends between the plurality of stringers 114 along the length of the plurality of stringers 114. Specifically, along the length of the plurality of stringers 114, the pressure deck 116 extends transversely between each pair of adjacent stringers of the plurality of stringers 114 along the pitch axis 106. In an exemplary implementation, the pressure deck 116 is divided into a plurality of discrete (e.g., separate, individual, etc.) segments, each segment extending between a corresponding pair of adjacent stringers 114 or between a corresponding stringer 114 and a corresponding beam 124 ( Figure 1 (not shown) extending between.

[0030] For example, Figure 1 and Figure 3The exemplary implementation of the pressure deck 116 shown in FIG. 1 includes a plurality of compliant deck segments 126, a center bulkhead deck segment 128, and a pair of opposing end bulkhead deck segments 130. Each compliant deck segment 126 extends between a corresponding pair of adjacent stringers 114. Specifically, compliant deck segment 126a extends between corresponding stringers 114a and 114b; compliant deck segment 126b extends between corresponding stringers 114b and 114c; compliant deck segment 126c extends between corresponding stringers 114c and 114d; compliant deck segment 126d extends between corresponding stringers 114e and 114f; compliant deck segment 126e extends between corresponding stringers 114f and 114g; and compliant deck segment 126f extends between corresponding stringers 114g and 114h. Each of the compliant deck segments 126a, 126b, 126c, 126d, 126e, and 126f may be referred to herein as a "first deck segment" and / or a "second deck segment". The center deck segment 128 may be referred to herein as a "first deck segment" and / or a "second deck segment". Each of the end bulkhead deck segments 130a and 130b may be referred to herein as a "first deck segment" and / or a "second deck segment".

[0031] As will be described in more detail below, and with reference now only to Figure 3 , compliant deck segment 126a is joined to stringers 114a and 114b at respective joints 132 and 134; compliant deck segment 126b is joined to stringers 114b and 114c at respective joints 136 and 138; compliant deck segment 126c is joined to stringers 114c and 114d at respective joints 140 and 142; compliant deck segment 126d is joined to stringers 114e and 114f at respective joints 144 and 146; compliant deck segment 126e is joined to stringers 114f and 114g at respective joints 148 and 150; and compliant deck segment 126f is joined to stringers 114g and 114h at respective joints 152 and 154. Each compliant deck segment 126 is joined to a corresponding stringer 114 using any suitable fasteners, such as, but not limited to, bolts, rivets, adhesives, epoxies, welds, brazes, and / or the like. Although six are shown, in other implementations, the pressure deck 116 includes any other number of compliant deck segments 126 (e.g., the number of compliant deck segments 128 is selected based on the number of stringers 114, etc.).

[0032] Reference again Figure 1 and Figure 3, each compliant deck segment 126 of the pressure deck 116 is a deflectable spring. Specifically, each compliant deck segment 126 of the pressure deck 116 can be elastically deflected along the pitch axis 106 of the fuselage 102. Therefore, each compliant deck segment 126 of the pressure deck 116 is compliant along the pitch axis 106 of the fuselage 102. In an exemplary implementation, each compliant deck segment 126 of the pressure deck 116 is a catenary web. However, one or more of the compliant deck segments 126 additionally or alternatively include any type of compliant structure, such as, but not limited to, a parabolic shape, a sinusoidal shape, a radius shape, and / or the like.

[0033] Each compliant deck segment 126 of the pressure deck 116 includes (e.g., is made of, is composed of, etc.) any material that enables the compliant deck segment 126 to be compliant along the pitch axis 106 of the fuselage 102. For example, in some implementations, the compliant deck segments 126 include (e.g., are made of, are composed of, etc.) a composite material, such as, but not limited to, a carbon composite material, a carbon fiber composite material, a thermoplastic composite material, a thermoplastic carbon fiber composite material, a thermoset composite material, a thermoset carbon fiber composite material, a poly(p-phenylene terephthalamide) fiber composite material, and the like. In one example, one or more of the compliant deck segments 126 include (e.g., are made of, are composed of, etc.) a thermoplastic carbon fiber composite material. In some other implementations, one or more of the compliant deck segments 126 include (e.g., are made of, are composed of, etc.) another material in addition to or in place of a composite material, such as, but not limited to, titanium, aluminum, steel, an alloy of two or more metals, and the like.

[0034] The center bulkhead deck segment 128 extends between corresponding pairs of adjacent stringers 114. Specifically, the center bulkhead deck segment 128 extends between corresponding stringers 114d and 114e. The center bulkhead deck segment 128 is joined to the stringers 114d and 114e at corresponding joints 158 and 160. The center bulkhead deck segment 128 is joined to the corresponding stringers 114d and 114e using any suitable fasteners, such as but not limited to bolts, rivets, adhesives, epoxies, welding, brazing, and / or similar fasteners. Although only a single center bulkhead deck segment 128 is shown, in other implementations, the pressure deck 116 includes any other number of center bulkhead deck segments 128 (e.g., the number of center bulkhead deck segments 128 is selected based on the number of stringers 114, etc.).

[0035] In an exemplary implementation, the center bulkhead deck segment 128 is a relatively rigid structure (e.g., a stiffening structure, etc.) that extends along a generally planar (e.g., generally straight, etc.) path between the longerons 114d and 114e. In other implementations, the center bulkhead deck segment 128 is compliant along the pitch axis 106 of the fuselage 102 (i.e., elastically deflectable along the pitch axis 106 of the fuselage 102); for example, in some other implementations, the center bulkhead deck segment 128 is a catenary web. In some implementations, and for example, the center bulkhead segment 128 includes a parabolic shape, a sinusoidal shape, a radius shape, and / or the like.

[0036] The center bulkhead deck segment 128 of the pressure deck 116 includes (e.g., is made of, is composed of, etc.) any material that enables the center bulkhead deck segment 128 to function as described and / or illustrated herein. For example, in some implementations, the center bulkhead deck segment 128 includes (e.g., is made of, is composed of, etc.) a composite material, such as, but not limited to, a carbon composite material, a carbon fiber composite material, a thermoplastic composite material, a thermoplastic carbon fiber composite material, a thermoset composite material, a thermoset carbon fiber composite material, a poly(p-phenylene terephthalamide) fiber composite material, etc. In one example, the center bulkhead deck segment 128 includes (e.g., is made of, is composed of, etc.) a thermoplastic carbon fiber composite material. In some other implementations, the center bulkhead deck segment includes (e.g., is made of, is composed of, etc.) another material in addition to or in place of a composite material, such as, but not limited to, titanium, aluminum, steel, an alloy of two or more metals, etc.

[0037] The end bulkhead segments 130 extend between the corresponding longitudinal beams 114 and the corresponding beams 124 of the fuselage 102. Specifically, only reference will now be made to Figure 3 , the end bulkhead deck segment 130a extends between the stringer 114a and the beam 124a, and the end bulkhead deck segment 130b extends between the stringer 114h and the beam 124b. The end bulkhead deck segment 130a is joined to the stringer 114a and the beam 124a at respective joints 162 and 164; and the end bulkhead deck segment 130b is joined to the stringer 114h and the beam 124b at respective joints 166 and 168. The end bulkhead deck segments 130a and 130b are joined to the respective stringers 114a and 114h using any suitable fasteners, such as, but not limited to, bolts, rivets, adhesives, epoxies, welds, brazes, and / or the like. The end bulkhead segments 130a and 130b are joined to the respective beams 124a and 124b using any suitable fasteners, such as, but not limited to, bolts, rivets, adhesives, epoxies, welds, brazes, and / or the like.

[0038] Refer again Figure 1 and Figure 3 In an exemplary implementation, the end bulkhead deck segments 130 are each a relatively rigid structure (e.g., a stiffening structure, etc.) that extends along a generally planar (e.g., generally straight, etc.) path between a corresponding stringer 114 and a corresponding beam 124. In other implementations, one or both of the end bulkhead deck segments 130 are compliant along the pitch axis 106 of the fuselage 102 (i.e., elastically deflectable along the pitch axis 106 of the fuselage 102); for example, in some other implementations, the end bulkhead segments 130a and / or 130b are catenary webs. In some implementations, and for example, the end bulkhead segments 130a and / or 130b include a parabolic shape, a sinusoidal shape, a radius shape, and / or the like.

[0039] Each end bulkhead deck segment 130 of the pressure deck 116 includes (e.g., is made of, is composed of, etc.) any material that enables the end bulkhead deck segment 130 to function as described and / or illustrated herein. For example, in some implementations, one or both of the end bulkhead deck segments 130 include (e.g., are made of, are composed of, etc.) a composite material, such as, but not limited to, a carbon composite material, a carbon fiber composite material, a thermoplastic composite material, a thermoplastic carbon fiber composite material, a thermoset composite material, a thermoset carbon fiber composite material, a poly(p-phenylene terephthalamide) fiber composite material, etc. In one example, each end bulkhead deck segment 130 includes (e.g., is made of, is composed of, etc.) a thermoplastic carbon fiber composite material. In some other implementations, one or both of the end bulkhead deck segments 130 include (e.g., are made of, are composed of, etc.) another material in addition to or in place of a composite material, such as, but not limited to, titanium, aluminum, steel, an alloy of two or more metals, etc.

[0040] Figure 4 Joints 138 and 140 are shown between compliant deck segments 126b and 126c and stringer 114c, respectively, according to implementation. Figure 3 ) is substantially similar in construction to joint 138; and joints 132, 136, 144, 148, and 152 ( Figure 3) are substantially similar in construction to joint 140. Thus, joints 132, 134, 136, 142, 144, 146, 148, 150, 152, and 154 will not be described in further detail herein, but it should be understood that the performance, load paths, benefits, advantages, and / or similar aspects of the construction of joints 138 and 140 are equally applicable to joints 132, 134, 136, 142, 144, 146, 148, 150, 152, and 154. Additionally, in some implementations, joints 160, 162, and / or 168 ( Figure 3 ) have a substantially similar construction to connector 138, and / or connectors 158, 164, and / or 166 ( Figure 3 ) has a substantially similar construction to joint 140 such that the performance, load paths, benefits, advantages, etc. of the construction of joints 138 and 140 are equally applicable to joints 160, 162, 168, 158, 164 and / or 166, respectively.

[0041] like Figure 4 As shown, the longitudinal beam 114c includes a center member 170 and opposite flanges 172 and 174 extending from the center member 170. The center member 170 extends a height from a first end portion 176 to an opposite second end portion 178. The flanges 172 and 174 extend outwardly from the first end portion 176 of the center member 170. The flange 172 includes an upper side 180 and an opposite lower side 182; the flange 174 includes an upper side 184 and an opposite lower side 186. Figure 4 As shown, each of the upper sides 180 and 184 generally faces the second end portion 178 of the center member 170, while each of the lower sides 182 and 186 generally faces away from the second end portion 178 of the center member 170. Each of the flanges 172 and 174 may be referred to herein as a "first" and / or "second" flange. Each of the upper sides 180 and 184 may be referred to herein as a "first" and / or "second" upper side, while each of the lower sides 182 and 186 may be referred to herein as a "first" and / or "second" lower side.

[0042] Optionally, the central member 170 of the longitudinal beam 114c has a two-piece or multi-piece construction. For example, Figure 4 The center member 170 of the exemplary implementation of the longitudinal beam 114c shown in FIG. 1 includes two member segments 170a and 170b that are joined together along the length of the longitudinal beam 114c using any suitable fasteners, such as, but not limited to, bolts, rivets, adhesives, epoxies, welds, brazes, and / or the like. A flange 172 extends from the member segment 170a of the center member 170, while a flange 174 extends from the member segment 170b of the center member 170. Figure 4In the example of the embodiment of the present invention, the central axis 188 of an exemplary fastener (not shown), such as a bolt or rivet, is shown to indicate that the member segments 170a and 170b are joined together. It should be understood that the location of the central axis 188 of the fastener along the height of the central member 170 is merely exemplary. The central axis 188 of the fastener may additionally or alternatively have any other location along the height of the central member 170. In other implementations, the central member 170 of the longitudinal beam 114C is defined by a single member segment, so that the central member 170 has a one-piece construction. Each of the member segments 170a and 170b of the central member 170 may be referred to herein as a "first" member segment and / or a "second" member segment.

[0043] like Figure 4 As shown, the flange 172 of the longitudinal beam 114c is at an angle α relative to the center member 170. 1 The flange 172 extends from the center member 170 so that the flange 172 and the center member 170 form an L-shape. Similarly, the flange 174 of the longitudinal beam 114c is at an angle α relative to the center member 170. 2 The flange 174 and the center member 170 extend from the center member 170 such that the flange 174 and the center member 170 form an L-shape. In an exemplary implementation, the angle α 1 and α 2 The angles α and α are approximately equal and greater than 90°. However, in other implementations, the L-shape defined by the flange 172 and the center member 170 has any other angle α that is less than about 180°. 1 (For example, an angle α of about 90° 1 , an inclination angle α of less than about 90° 1 , different tilt angles α greater than about 90° 1 In addition, in some other implementations, the L-shape defined by the flange 174 and the center member 170 has any other angle α less than about 180°. 2 (For example, an angle α of about 90° 2 , an inclination angle α of less than about 90° 2 , different tilt angles α greater than about 90° 1 In some other implementations, the L-shape defined by the center member 170 and the flanges 172 and 174 has a corresponding angle α of different values. 1 and α 2 .

[0044] like Figure 4 As also shown in FIG. 1 , the flange 172 of the longitudinal beam 114c extends from the center member 170 such that the flange 172 and the center member 170 form a corner 190 of the longitudinal beam 114c. The corner 190 includes an angle α between the center member 170 and the flange 172. 1The inner side 192 is defined by the spatial volume extending therein. The corner 190 includes an angle α between the center member 170 and the flange 172. 3 Another space volume extending inside defines an outer side 194. Figure 4 As shown, the upper side 180 of the flange 172 defines a portion of the inner side 192 of the corner 190, while the side 196 of the center member 170 defines another portion of the inner side 192 of the corner 190. The side 198 of the center member 170 opposite the side 196 defines a portion of the outer side 194 of the corner 190, while the lower side 182 of the flange 172 defines another portion of the outer side 194 of the corner 190. The corner 190 may be referred to herein as a "first" and / or "second" corner.

[0045] The flange 174 of the longitudinal beam 114c extends from the center member 170 such that the flange 174 and the center member 170 form a corner 200 of the longitudinal beam 114c. The corner 200 includes an angle α between the center member 170 and the flange 174. 2 The inner side 202 is defined by the space volume extending inside. Figure 4 As shown, the upper side 184 of the flange 174 defines a portion of the inner side 202 of the corner 200, while the side 198 of the center member 170 defines another portion of the inner side 202 of the corner 200. The corner 200 includes an angle α between the center member 170 and the flange 174. 4 Another volume of space extending therein defines an outer side 204. The underside 186 of the flange 174 defines a portion of the outer side 204 of the corner 200, while the side 196 of the center member 170 defines another portion of the outer side 204 of the corner 200. The corner 200 may be referred to herein as a "first" and / or "second" corner.

[0046] The compliant deck segment 126b of the pressure deck 116 is joined to the flange 172 of the stringer 114c along the underside 182 of the flange 172. Thus, the compliant deck segment 126b is joined to the flange 172 of the stringer 114c such that the compliant deck segment 126b extends over the outboard side 194 of the corner 190 of the stringer 114c. Similarly, the compliant deck segment 126c of the pressure deck 116 is joined to the flange 174 of the stringer 114c along the underside 186 of the flange 174. Thus, the compliant deck segment 126c is joined to the flange 174 of the stringer 114c such that the compliant deck segment 126c extends over the outboard side 204 of the corner 200 of the stringer 114c.

[0047] In an exemplary implementation, the joints 138 and 140 between the stringer 114C and the compliant deck segments 126B and 126C, respectively, include a splice 206. Specifically, the splice 206 extends a length from an end portion 208 to an opposite end portion 210. Figure 4 As shown, the end portion 208 of the splice 206 is engaged between the flange 172 of the stringer 114c and the compliant deck segment 126b of the pressure deck 116. The end portion 210 of the splice 206 is engaged between the flange 174 of the stringer 114c and the compliant deck segment 126c of the pressure deck 116, also as shown. Figure 4 Each of the end portions 208 and 210 of the splicing element 206 may be referred to herein as a "first" end portion and / or a "second" end portion.

[0048] The splice 206 strengthens the joint (e.g., connection, attachment, etc.) between the member segments 170a and 170b of the center member 170 of the longitudinal beam 114c, for example, to prevent the member segments 170a and 170b from separating, etc. The splice 206 can also facilitate providing a predetermined distance D (see below). Figure 5 In other implementations, the joints 138 and / or 140 do not include the splice 206, and the respective compliant deck segments 126b and / or 126c are directly joined to the respective undersides 182 and / or 186 of the respective flanges 172 and / or 174. For example, the splice 206 may not be included in some embodiments in which the center member 170 of the stringer 114C is defined by a single member segment (i.e., the center member 170 has a one-piece construction).

[0049] The splice 206 includes (e.g., is made of, is composed of, etc.) any material that enables the splice 206 to function as described and / or shown herein. For example, in some implementations, the splice 206 includes (e.g., is made of, is composed of, etc.) a composite material, such as, but not limited to, a carbon composite material, a carbon fiber composite material, a thermoplastic composite material, a thermoplastic carbon fiber composite material, a thermoset composite material, a thermoset carbon fiber composite material, a poly(p-phenylene terephthalamide) fiber composite material, and the like. In one example, the splice 206 includes (e.g., is made of, is composed of, etc.) a thermoplastic carbon fiber composite material. In some other implementations, the splice 206 includes (e.g., is made of, is composed of, etc.) another material in addition to or in place of a composite material, such as, but not limited to, titanium, aluminum, steel, an alloy of two or more metals, and the like.

[0050] As described above, the compliant deck segments 126b and 126c are joined to the stringer 114c using any suitable fasteners, such as, but not limited to, bolts, rivets, adhesives, epoxies, welds, brazes, and / or the like. Specifically, the compliant deck segments 126b and 126c are joined to the respective flanges 172 and 174 directly or with a splice 206 therebetween using any suitable fasteners, such as, but not limited to, bolts, rivets, adhesives, epoxies, welds, brazes, and / or the like. Figure 4 1, central axes 212 and 214 of exemplary fasteners (not shown), such as bolts and / or rivets, are shown to indicate that the compliant deck segments 126b and 126c are joined to the respective flanges 172 and 174 with the splice 206 joined therebetween. The locations of the central axes 212 and 214 of the fasteners along the lengths of the flanges 172 and 174, respectively, are merely exemplary. The central axes 212 and / or 214 may additionally or alternatively have any other locations along the lengths of the respective flanges 172 and / or 174. In some implementations, the fasteners joining the compliant deck segment 126b to the stringer 114c are located at a greater distance along the length of the stringer 114c than the fasteners joining the compliant deck segment 126c to the stringer 114c. Figure 1 ) staggered.

[0051] Reference now Figure 5 , the load paths through joints 138 and 140 will now be described. When the internal compartment of fuselage 102 is pressurized, the pressure will be pressure load P 1 Applied on flanges 172 and 174 and on compliant deck segments 126b and 126c. Pressure load P 1 The reaction force R along the height of the center member 170 of the longitudinal beam 114c is caused 1 . Pressure load P 1 This also results in: (1) the tension load P in the compliant deck segments 126b and 126c 2 ; and (2) for opening (i.e., increasing) the angle α 1 and α 2 The opening moment OM (ie, torque) generates (ie, causes) an interlaminar tension (ILT) in the longitudinal beam 114 c.

[0052] The tension load P2 in the compliant deck segments 126b and 126c generates a reaction force R in the flanges 172 and 174, respectively. 2 . Specifically, the reaction force R 2 The tensile load P reacted by the fastener 2 The fasteners join the compliant deck segments 126b and 126c to the respective flanges 172 and 174. Figure 5 As shown, the reaction force R 2 With tension load P 2 Separated by a predetermined distance D. Tension load P in compliant deck segments 126b and 126c 2 The reaction force R in flanges 172 and 174 2 The predetermined distance D between the two angles generates a closing moment CM (eg, torque, etc.) for closing (ie, reducing) the angle α. 1 and α 2 The closing moment CM acts in an opposite direction to the opening moment OM, such that the closing moment CM counteracts the opening moment OM. For example, in some implementations, the closing moment CM reduces the effect of the opening moment OM on the longitudinal beam 114c, thereby reducing the ILT generated in the longitudinal beam 114c. In other implementations, for example, the closing moment CM is substantially equal to the opening moment OM, such that the closing moment CM substantially counteracts the opening moment OM (and thereby substantially eliminates the ILT generated in the longitudinal beam 114c from OM). The tension load P may be selected to 2 and the reaction force R 2 The predetermined distance D therebetween may be selected to provide a closing moment CM of any magnitude and / or reduce the effect of OM by any amount, such as by selecting the thickness of the splicing piece 206, selecting whether to include the splicing piece 206, selecting the thickness of the flanges 172 and / or 174, etc.

[0053] By reducing or eliminating the ILT generated in the longitudinal beam 114c, Figure 5 The configuration of the joints 138 and 140 shown in FIG. 1 enables the stringer 114 to include (eg, be made of, be composed of, etc.) a material having a lower ILT capability. For example, Figure 5 The configuration of the joints 138 and 140 shown in the drawings may enable the stringer 114 to include (e.g., be made of, consist of, etc.) a composite material, such as, but not limited to, a carbon composite material, a carbon fiber composite material, a thermoplastic composite material, a thermoplastic carbon fiber composite material, a thermoset composite material, a thermoset carbon fiber composite material, a poly(p-phenylene terephthalamide) fiber composite material, and / or the like. Using a composite material to construct the stringer 114 may reduce the weight of the pressure deck assembly 100, which may result in improvements in aircraft operating performance, efficiency, and / or capability.

[0054] Reference now Figure 6, some examples of the disclosure are described in the context of an aircraft 300 including an airframe 304 having a fuselage 302. Fuselage 302 includes an interior cabin 306. Airframe 304 includes a plurality of high-level systems 308. Examples of high-level 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 an aerospace example is shown, the principles may be applied to other industries, such as, but not limited to, the automotive industry, the marine industry, and the like.

[0055] Examples of the present disclosure can be found in Figure 7 The illustrative method 400 is described in the context of aircraft manufacturing and service method 400. During pre-production, illustrative method 400 may include an aircraft (e.g., Figure 6 300, etc.) and material procurement 404. During production, component and subassembly manufacturing 406 and system integration 408 of the aircraft occur. Thereafter, the aircraft may undergo certification and delivery 410 to enter service 412. While in use by a customer, the aircraft is scheduled for routine maintenance and repair 414 (which may also include modification, rebuilding, refurbishment, etc.).

[0056] Each of the processes of illustrative method 400 may be performed or carried out by a system integrator, a third party, and / or an operator (e.g., a customer, etc.). For purposes of this description, a system integrator may include, but is not limited to, any number of aircraft manufacturers and major system subcontractors; a third party may include, but is not limited to, any number of suppliers, subcontractors, and vendors; and an operator may be an airline, a leasing company, a military entity, a maintenance organization, etc.

[0057] It should be noted that the systems described herein may include any number of other systems. Furthermore, although an aerospace example is shown, the principles may be applied to other industries, such as, but not limited to, the automotive industry, the marine industry, and the like.

[0058] During any one or more stages of manufacturing and service method 400, the systems and methods shown or described herein may be employed. For example, components or subassemblies corresponding to component and subassembly manufacturing 406 may be manufactured or produced in a manner similar to components or subassemblies produced while the aircraft is in service. Moreover, during the production state of subassembly manufacturing 406 and system integration 408, one or more aspects of the systems, methods, or combinations thereof may be utilized, such as by substantially expediting assembly of the aircraft or reducing the cost of the aircraft. Similarly, one or more aspects of the apparatus or method implementations or combinations thereof may be utilized while the aircraft is in service, such as, but not limited to, maintenance and repair 414.

[0059] Various implementations of the present disclosure enable longitudinal beams of a pressure deck assembly to be manufactured from composite materials. Certain implementations of the present disclosure reduce the weight of a pressure deck assembly of an aircraft fuselage. Certain implementations of the present disclosure improve the operational performance, efficiency, and / or capability of an aircraft.

[0060] The following clauses describe additional aspects:

[0061] Clause Group A:

[0062] A1. A pressure deck assembly for a fuselage, the pressure deck assembly comprising:

[0063] a longitudinal beam extending a length along a roll axis of the fuselage, the longitudinal beam comprising a center member and opposing first and second flanges extending from the center member, the first flange comprising a first upper side and a first lower side, the second flange comprising a second upper side and a second lower side,

[0064] A pressure deck comprising a first deck segment and a second deck segment, wherein the first deck segment is joined to the first flange of the stringer along the first underside of the first flange, and wherein the second deck segment is joined to the second flange of the stringer along the second underside of the second flange.

[0065] A2. The pressure deck assembly of clause A1, wherein the longitudinal beam comprises at least one of a composite material, a carbon fiber composite material, a thermoplastic composite material, a thermoplastic carbon fiber composite material, a thermoset composite material, or a thermoset carbon fiber composite material.

[0066] A3. The pressure deck assembly described in clause A1 further comprises a splicing piece, wherein the splicing piece extends a certain length from a first end portion to a second end portion, the first end portion of the splicing piece is joined between the first flange of the longitudinal beam and the first deck segment of the pressure deck, and the second end portion of the splicing piece is joined between the second flange of the longitudinal beam and the second deck segment of the pressure deck.

[0067] A4. A pressure deck assembly as described in clause A1, wherein the central member of the longitudinal beam extends a certain height from a first end portion to a second end portion, and the first flange and the second flange extend outward from the first end portion, wherein the first lower side of the first flange and the second lower side of the second flange are respectively facing away from the second end portion of the central member.

[0068] A5. The pressure deck assembly of clause A1, wherein the first flange of the longitudinal beam extends from the central member so that the first flange and the central member form an L-shape, and wherein the second flange of the longitudinal beam extends from the central member so that the second flange and the central member form an L-shape.

[0069] A6. The pressure deck assembly of clause A1, wherein at least one of the first deck segment or the second deck segment of the pressure deck is compliant along a pitch axis of the fuselage.

[0070] A7. The pressure deck assembly of clause A1, wherein at least one of the first deck segment or the second deck segment of the pressure deck comprises a catenary web.

[0071] A8. A pressure deck assembly as described in clause A1, wherein at least one of the first flange or the second flange is separated from the corresponding first deck segment or the second deck segment by a predetermined distance, and the predetermined distance is configured to generate at least one closing moment, and the at least one closing moment is used to close the angle between the central member and at least one of the first flange or the second flange under pressure load.

[0072] A9. The pressure deck assembly of clause A1, wherein the center member of the longitudinal beam includes a first member segment and a second member segment joined together, the first flange extends from the first member segment, and the second flange extends from the second member segment.

[0073] Clause Group B:

[0074] B1. A pressure deck assembly for a fuselage, the pressure deck assembly comprising:

[0075] a longitudinal beam extending a length along the roll axis of the fuselage, the longitudinal beam comprising a central member and first and second opposed flanges extending from the central member, the first flange forming a first corner of the longitudinal beam with the central member, and the second flange forming a second corner of the longitudinal beam with the central member; and

[0076] A pressure deck comprising a first deck segment and a second deck segment, wherein the first deck segment is joined to the first flange of the longitudinal beam so that the first deck segment extends outside the first corner of the longitudinal beam, and wherein the second deck segment is joined to the second flange of the longitudinal beam so that the second deck segment extends outside the second corner of the longitudinal beam.

[0077] B2. The pressure deck assembly of clause B1, wherein the longitudinal beam comprises at least one of a composite material, a carbon fiber composite material, a thermoplastic composite material, a thermoplastic carbon fiber composite material, a thermoset composite material, or a thermoset carbon fiber composite material.

[0078] B3. The pressure deck assembly described in clause B1, further comprising a splicing piece, the splicing piece extending a length from a first end portion to a second end portion, the first end portion of the splicing piece being joined between the first flange of the longitudinal beam and the first deck segment of the pressure deck, and the second end portion of the splicing piece being joined between the second flange of the longitudinal beam and the second deck segment of the pressure deck.

[0079] B4. A pressure deck assembly as described in clause B1, wherein the first flange and the second flange of the longitudinal beam include corresponding first and second upper sides and corresponding first and second lower sides, the first lower side of the first flange defines a portion of the outer side of the first corner, the first deck segment of the pressure deck is joined to the first flange along the first lower side of the first flange, the second lower side of the second flange defines a portion of the outer side of the second corner, and the second deck segment of the pressure deck is joined to the second flange along the second lower side of the second flange.

[0080] B5. The pressure deck assembly of clause B1, wherein at least one of the first deck segment or the second deck segment of the pressure deck comprises a catenary web.

[0081] B6. A pressure deck assembly as described in clause B1, wherein at least one of the first flange or the second flange is separated from the corresponding first deck segment or the second deck segment by a predetermined distance, and the predetermined distance is configured to generate at least one closing moment, and the at least one closing moment is used to close the angle between the central member and at least one of the first flange or the second flange under pressure load.

[0082] Clause Group C:

[0083] C1. A fuselage for an aircraft, the fuselage comprising:

[0084] A pressure deck assembly, the pressure deck assembly comprising:

[0085] a stringer extending a length along a roll axis of the fuselage, the stringer comprising a center member and a flange extending from the center member, the flange comprising an upper side and a lower side; and

[0086] A pressure deck comprises a deck segment, wherein the deck segment is joined to the flange of the stringer along the underside of the flange.

[0087] C2. The fuselage of clause C1, wherein the stringer comprises at least one of a composite material, a carbon fiber composite material, a thermoplastic composite material, a thermoplastic carbon fiber composite material, a thermoset composite material, or a thermoset carbon fiber composite material.

[0088] C3. A fuselage as described in clause C1, wherein the central member of the longitudinal beam extends a height from a first end portion to a second end portion, and the flange extends outward from the first end portion, wherein the lower side of the flange faces away from the second end portion of the central member.

[0089] C4. The fuselage of clause C1, wherein the deck segment of the pressure deck comprises a catenary web.

[0090] C5. The fuselage of clause C1, wherein the flange and the deck segment are separated by a predetermined distance, the predetermined distance being configured to generate a closing moment for closing the angle between the center member and the flange under a pressure load of the flange.

[0091] As used herein, a structure, limitation, or element that is "configured to" perform a task or operation is specifically structurally formed, constructed, or adapted in a manner corresponding to the task or operation. For purposes of clarity and avoidance of doubt, an object that can merely be modified to perform a task or operation is not "configured to" perform a task or operation as used herein.

[0092] As will be apparent to one skilled in the art, any range or value given herein may be expanded or altered without losing the effect sought.

[0093] Although the subject matter has been described in language specific to structural features and / or methodological acts, it should be understood that the subject matter defined in the appended claims is not necessarily limited to the specific features or acts described above. Rather, the specific features and acts described above are disclosed as example forms of implementing the claims.

[0094] It should be understood that the above benefits and advantages may relate to one embodiment or may relate to several embodiments. The embodiments are not limited to those embodiments that solve any or all of the problems described, or those embodiments that have any or all of the benefits and advantages described. It will also be understood that reference to "an" item refers to one or more of these items.

[0095] The word “comprising” is used in this specification to indicate including the following (one or more) features or actions, but does not exclude the existence of one or more additional features or actions.

[0096] Unless otherwise specified, the order of execution or performance of the operations in the examples of the present disclosure shown and described herein is not required. That is, unless otherwise specified, the operations can be performed in any order, and the examples of the present disclosure may include more or less operations than the operations disclosed herein. For example, it is conceivable that it is within the scope of the various aspects of the present disclosure to perform or perform a specific operation before, simultaneously, or after another operation (e.g., different steps, etc.).

[0097] When introducing elements of aspects of the disclosure or examples thereof, the articles "a," "an," "the," and "said" are intended to indicate that there are one or more elements. The words "comprising," "including," and "having" are intended to be inclusive and indicate that additional elements may be present in addition to the listed elements. The word "exemplary" is intended to mean "an example thereof." The phrase "one or more of the following A, B, and C" means "at least one of A and / or at least one of B and / or at least one of C."

[0098] Having described various aspects of the disclosure in detail, it will be apparent that modifications and variations are possible without departing from the scope of the various aspects of the disclosure as defined in the appended claims. As various changes may be made to the above-described constructions, products and methods without departing from the scope of the various aspects of the disclosure, it is intended that all matter contained in the above description and shown in the accompanying drawings shall be interpreted as illustrative and not limiting.

[0099] It should be understood that the above description is intended to be illustrative, not restrictive. For example, the above embodiments (and / or aspects thereof) can be used in combination with each other. In addition, without departing from the scope of the various embodiments of the present disclosure, many modifications can be made to adapt specific situations or materials to the teachings of the various embodiments of the present disclosure. Although the size and type of materials described herein are intended to limit the parameters of the various embodiments of the present disclosure, the embodiments are by no means restrictive, but exemplary embodiments. After reading the above description, many other embodiments will be obvious to those of ordinary skill in the art. Therefore, the scope of the various embodiments of the present invention should be determined with reference to the appended claims together with the full scope of equivalents granted by this claim. In the appended claims, the words "including" and "wherein" are used as simple equivalents of the corresponding words "having" and "in...", and in addition, the words "first", "second" and "third" are used only as marks, and are not intended to impose numerical requirements on their objects. In addition, the limitations of the appended claims are not written in the format of device plus function, and are not intended to be interpreted based on 35 U.S.C. § 112 (f), unless and until such claim limitations explicitly use the phrase "refer to" followed by a functional statement without further structure.

[0100] This written description uses examples to disclose 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 combined 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 one of ordinary skill in the art. If these other examples have structural elements that do not differ from the literal language of the claims, or if these examples include equivalent structural elements that do not differ substantially from the literal language of the claims, then these other examples are intended to be within the scope of the claims.

Claims

1. A pressure deck assembly for an aircraft fuselage, the pressure deck assembly extending a length along the roll axis of the fuselage and dividing the height of the fuselage into different compartments along at least a portion of the length of the fuselage, the pressure deck assembly include: a plurality of stringers extending a length along the roll axis of the fuselage, the stringers comprising a center member and opposing first and second flanges extending from the center member, the first flange comprising a first upper side and a first lower side, the second flange comprising a second upper side and a second lower side, a pressure deck extending along the length of the plurality of stringers and extending transversely between each pair of adjacent stringers along a pitch axis of the fuselage, the pressure deck comprising a first deck segment and a second deck segment, wherein the first deck segment is joined to the first flange of the stringer along the first underside of the first flange, and wherein the second deck segment is joined to the second flange of the stringer along the second underside of the second flange.

2. The pressure deck assembly according to claim 1, in, The longitudinal beam includes at least one of a composite material, a carbon fiber composite material, a thermoplastic composite material, a thermoplastic carbon fiber composite material, a thermosetting composite material, or a thermosetting carbon fiber composite material.

3. The pressure deck assembly according to claim 1, further comprising a splicing piece, the splicing piece extending a length from a first end portion to a second end portion, the first end portion of the splicing piece being joined between the first flange of the longitudinal beam and the first deck segment of the pressure deck, and the second end portion of the splicing piece being joined between the second flange of the longitudinal beam and the second deck segment of the pressure deck.

4. The pressure deck assembly according to claim 1, in, The central member of the longitudinal beam extends a height from a first end portion to a second end portion, and the first flange and the second flange extend outward from the first end portion, wherein the first lower side of the first flange and the second lower side of the second flange are respectively facing away from the second end portion of the central member.

5. The pressure deck assembly according to claim 1, in, The first flange of the longeron extends from the center member such that the first flange and the center member form an L-shape, and wherein the second flange of the longeron extends from the center member such that the second flange and the center member form an L-shape.

6. The pressure deck assembly according to claim 1, in, At least one of the first deck segment or the second deck segment of the pressure deck is compliant along a pitch axis of the fuselage.

7. The pressure deck assembly according to claim 1, in, At least one of the first deck segment or the second deck segment of the pressure deck includes a catenary web.

8. The pressure deck assembly according to claim 1, in, At least one of the first flange or the second flange is separated from the corresponding first deck segment or the second deck segment by a predetermined distance, and the predetermined distance is configured to generate at least one closing moment, and the at least one closing moment is used to close the angle between the central member and at least one of the first flange or the second flange under a pressure load.

9. The pressure deck assembly according to claim 1, in, The central member of the longitudinal beam includes a first member segment and a second member segment joined together, the first flange extends from the first member segment, and the second flange extends from the second member segment.

10. A pressure deck assembly for an aircraft fuselage, the pressure deck assembly extending a length along the roll axis of the fuselage and dividing the height of the fuselage into different compartments along at least a portion of the length of the fuselage, the pressure deck assembly include: a plurality of stringers extending a length along the roll axis of the fuselage, the stringers comprising a center member and first and second opposed flanges extending from the center member, the first flange forming a first corner of the stringer with the center member, and the second flange forming a second corner of the stringer with the center member; as well as a pressure deck extending along the length of the plurality of stringers and extending transversely between each pair of adjacent stringers along a pitch axis of the fuselage, the pressure deck comprising a first deck segment and a second deck segment, wherein the first deck segment is joined to the first flange of the stringer such that the first deck segment extends outboard of the first corner of the stringer, and wherein the second deck segment is joined to the second flange of the stringer such that the second deck segment extends outboard of the second corner of the stringer.

11. The pressure deck assembly according to claim 10, in, The longitudinal beam includes at least one of a composite material, a carbon fiber composite material, a thermoplastic composite material, a thermoplastic carbon fiber composite material, a thermosetting composite material, or a thermosetting carbon fiber composite material.

12. The pressure deck assembly according to claim 10, further comprising a splicing piece, the splicing piece extending a length from a first end portion to a second end portion, the first end portion of the splicing piece being joined between the first flange of the longitudinal beam and the first deck segment of the pressure deck, and the second end portion of the splicing piece being joined between the second flange of the longitudinal beam and the second deck segment of the pressure deck.

13. The pressure deck assembly according to claim 10, in, The first flange and the second flange of the longitudinal beam include respective first and second upper sides and respective first and second lower sides, the first lower side of the first flange defining a portion of the outer side of the first corner, the first deck segment of the pressure deck being joined to the first flange along the first lower side of the first flange, the second lower side of the second flange defining a portion of the outer side of the second corner, and the second deck segment of the pressure deck being joined to the second flange along the second lower side of the second flange.

14. The pressure deck assembly according to claim 10, in, At least one of the first deck segment or the second deck segment of the pressure deck includes a catenary web.

15. The pressure deck assembly according to claim 10, in, At least one of the first flange or the second flange is separated from the corresponding first deck segment or the second deck segment by a predetermined distance, and the predetermined distance is configured to generate at least one closing moment, and the at least one closing moment is used to close the angle between the central member and at least one of the first flange or the second flange under a pressure load.

16. A fuselage for an aircraft, the fuselage comprising a pressure deck assembly according to claim 1 or 10.

17. The body according to claim 16, in, The longitudinal beam includes at least one of a composite material, a carbon fiber composite material, a thermoplastic composite material, a thermoplastic carbon fiber composite material, a thermosetting composite material, or a thermosetting carbon fiber composite material.

18. The body according to claim 16, in, The central member of the longitudinal beam extends a height from a first end portion to a second end portion, and the flange extends outwardly from the first end portion, wherein the lower side of the flange faces away from the second end portion of the central member.

19. The body according to claim 16, in, The deck segment of the pressure deck comprises a catenary shaped web.

20. The body according to claim 16, in, The flange and the deck segment are separated by a predetermined distance configured to generate a closing moment for closing an angle between the center member and the flange under a pressure load of the flange.

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