Longitudinal beam joints for pressure deck bodies

Abstract

To provide a pressure deck assembly for a fuselage including a longitudinal beam extending a length along a roll axis.SOLUTION: A longitudinal beam includes a central part and first and second flange parts extending from the central part to directions opposing to each other. The first flange parts includes a first upper surface and a first lower surface. The second flange part includes a second upper surface and a second lower surface. A pressure deck assembly includes a pressure deck 116 that includes first and second deck segments 126. The first deck segment is joined to the first flange part of the longitudinal beam on the first lower surface of the first flange part. The second deck segment is joined to the second flange part of the longitudinal beam on the second lower surface of the second flange part.SELECTED DRAWING: Figure 1

Description

[Technical Field]

[0001] The present disclosure relates generally to aircraft fuselages, and more particularly to pressure deck assemblies for aircraft fuselages. [Background technology]

[0002] Some aircraft fuselages are comprised of a pressure deck body, also known as a "pressure deck" or "horizontal pressure deck." The pressure deck body is a structure that divides the height of the fuselage, supports the floors of compartments (e.g., passenger cabin, cargo hold, etc.), or separates pressurized compartments (e.g., passenger cabin, cargo hold, etc.) from unpressurized compartments (e.g., wheel wells, etc.). The pressure deck body may include longitudinal beams that run the length of the fuselage.

[0003] Depending on the operating environment, aircraft fuselage structures are required to include as many corrosion-resistant components as possible. However, corrosion-resistant metals, such as titanium, are heavier than corrosion-resistant composites, such as carbon fiber. For this reason, using corrosion-resistant metals for the longitudinal beams of a pressure deck is less desirable. On the other hand, while some corrosion-resistant composites are lighter than many corrosion-resistant metals, some composites have insufficient inter-laminar tension (ILT) strength to withstand the pressure loads experienced by the pressure deck during aircraft operation. Summary of the Invention

[0004] In one aspect, a pressure deck assembly for a fuselage section is provided. The pressure deck assembly includes a longitudinal beam having a length along a roll axis of the fuselage section. The longitudinal beam includes a central portion and first and second flange portions extending in opposite directions from the central portion. The first flange portion has a first upper surface and a first lower surface. The second flange portion has a second upper surface and a second lower surface. The pressure deck assembly includes a pressure deck including first and second deck segments. The first deck segment is joined to the first flange portion of the longitudinal beam at the first lower surface of the first flange portion. The second deck segment is joined to the second flange portion of the longitudinal beam at the second lower surface of the second flange portion.

[0005] In another aspect, a pressure deck assembly for a fuselage section is provided. The pressure deck assembly includes a longitudinal beam having a length along a roll axis of the fuselage section. The longitudinal beam includes a central portion and first and second flange portions extending in opposite directions from the central portion. The first flange portions and the central portion form a first corner portion of the longitudinal beam. The second flange portions and the central portion form a second corner portion of the longitudinal beam. The pressure deck assembly includes a pressure deck including first and second deck segments. The first deck segment is joined to the first flange portion of the longitudinal beam such that the first deck segment extends on an outer surface of the first corner portion of the longitudinal beam. The second deck segment is joined to the second flange portion of the longitudinal beam such that the second deck segment extends on an outer surface of the second corner portion of the longitudinal beam.

[0006] In another aspect, a fuselage section for an aircraft is provided. The fuselage section includes a pressure deck assembly including a longitudinal beam having a length along a roll axis of the fuselage section. The longitudinal beam includes a central portion and a flange portion extending from the central portion. The flange portion has an upper surface and a lower surface. The pressure deck assembly includes a pressure deck including deck segments joined to the flange portions of the longitudinal beams at the lower surfaces of the flange portions. [Brief explanation of the drawings]

[0007] [Figure 1] 1 is a perspective view of a portion of a pressure deck assembly of an aircraft fuselage in one embodiment; [Figure 2] 2 is a cross-sectional view of the body portion shown in FIG. 1 in one embodiment. [Figure 3] FIG. 2 is an elevational view of the fuselage shown in FIG. 1 in one embodiment. [Figure 4] 2 is a cross-sectional view of a portion of the pressure deck assembly shown in FIG. 1, illustrating the joint between the pressure deck and the longitudinal beam of the pressure deck assembly in one embodiment. [Figure 5] FIG. 5 is a cross-sectional view illustrating the load path through the joint shown in FIG. 4 in one embodiment. [Figure 6] FIG. 1 is a schematic diagram illustrating an embodiment of an aircraft. [Figure 7] FIG. 1 is a block diagram illustrating an embodiment of a method for manufacturing and using an aircraft. DETAILED DESCRIPTION OF THE INVENTION

[0008] The above summary of the invention and the following detailed description of the embodiments will be more clearly understood by reference to the accompanying drawings. In this specification, the use of "a" or "an" element or step does not necessarily exclude the presence of a plurality of elements or steps. Furthermore, references to "one embodiment" or "one implementation" are not intended to exclude the existence of other embodiments or implementations that incorporate the features described therein. Furthermore, unless otherwise specified, an embodiment that "comprises" or "has" one or more elements having a particular characteristic may additionally include other elements that do not have that characteristic.

[0009] In describing the embodiments and implementations of the present disclosure, various spatial and directional terms, such as "top," "bottom," "upper," "lower," "vertical," etc., are used; these terms are used only with respect to the orientation shown in the drawings. These orientations can be reversed, rotated, or otherwise changed. For example, if a structure is rotated 180 degrees, the upper portion becomes the lower portion; if the structure is rotated 90 degrees, the upper portion becomes the right portion or the left portion, etc.

[0010] In some embodiments of the present disclosure, a pressure deck assembly for a fuselage section is provided. The pressure deck assembly includes a longitudinal beam having a length along a roll axis of the fuselage section. The longitudinal beam includes a central portion and first and second flange portions extending in opposite directions from the central portion. The first flange portion has a first upper surface and a first lower surface. The second flange portion has a second upper surface and a second lower surface. The pressure deck assembly includes a pressure deck having first and second deck segments. The first deck segment is joined to the first flange portion of the longitudinal beam at a first lower surface of the first flange portion. The second deck segment is joined to the second flange portion of the longitudinal beam at a second lower surface of the second flange portion.

[0011] In some embodiments of the present disclosure, a pressure deck assembly for a fuselage section is provided. The pressure deck assembly includes a longitudinal beam having a length along a roll axis of the fuselage section. The longitudinal beam includes a central portion and first and second flange portions extending in opposite directions from the central portion. The first flange portion and the central portion form a first corner portion of the longitudinal beam. The second flange portion and the central portion form a second corner portion of the longitudinal beam. The pressure deck assembly includes a pressure deck having first and second deck segments. The first deck segment is joined to the first flange portion of the longitudinal beam such that the first deck segment extends on an outer surface of the first corner portion of the longitudinal beam. The second deck segment is joined to the second flange portion of the longitudinal beam such that the second deck segment extends on an outer surface of the second corner portion of the longitudinal beam.

[0012] Some embodiments of the present disclosure may allow longitudinal beams of a pressure deck to be constructed of composite materials. Some embodiments of the present disclosure may allow weight reduction of a pressure deck for an aircraft fuselage. Some embodiments of the present disclosure may allow improved aircraft operational performance, efficiency, and / or functionality.

[0013] Referring now to the drawings, FIG. 1 shows a perspective view of a portion of a pressure deck assembly 100 of a fuselage 102 for an aircraft (such as, for example, the aircraft 300 shown in FIG. 6 ). The length (i.e., longitudinal direction) of the fuselage 102 extends along a roll axis 104 of the fuselage 102 and the aircraft. The width (e.g., lateral, horizontal, etc.) of the fuselage 102 extends along a pitch axis 106 of the fuselage 102 and the aircraft. The height (e.g., vertical, etc.) of the fuselage 102 extends along a yaw axis 108 of the fuselage 102 and the aircraft. As can be seen in FIG. 1 , the roll axis 104, pitch axis 106, and yaw axis 108 are perpendicular to one another. The fuselage 102 is configured to roll, pitch, and yaw about the roll axis 104, pitch axis 106, and yaw axis 108, respectively, during flight of the aircraft. In the exemplary embodiment, fuselage 102 is of semi-monocoque construction, although in other embodiments fuselage 102 may be of any other type of construction.

[0014] The fuselage section 102 includes a pressure deck body 100. As shown in FIG. 1 , the pressure deck body 100 extends along a roll axis 104 of the fuselage section 102. Specifically, the pressure deck body 100 has a length that extends along the roll axis 104. In other words, the length of the pressure deck body 100 extends along the length direction of the fuselage section 102. The width of the pressure deck body 100 extends in the width direction of the fuselage section 102 along a pitch axis 106.

[0015] The pressure deck body 100 is a structure that divides the height of the fuselage section 102 into separate compartments along at least a portion of the length of the fuselage section 102. In some embodiments, the pressure deck body 100 is a support structure that supports (or constitutes) the floor of the cargo hold and / or passenger cabin (e.g., interior compartment 306 shown in FIG. 6 ) of the aircraft. In some embodiments, the pressure deck body 100 separates a pressurized compartment (e.g., interior compartment 306 shown in FIG. 6 ) from one or more unpressurized compartments in the fuselage section 102. Unpressurized compartments include, but are not limited to, wheel wells (e.g., wheel well 320 shown in FIG. 6 ). In some embodiments, a segment of the pressure deck body 100 constitutes a portion of the length of the pressure deck body 100 (e.g., one of two or more segments). In other embodiments, a segment of the pressure deck body 100 constitutes the entire length of the pressure deck body 100.

[0016] In an exemplary embodiment, the length of the pressure deck body 100 is generally parallel to the roll axis 104 of the fuselage section 102, and the width of the pressure deck body 100 is generally parallel to the pitch axis 106. Thus, when the fuselage section 102 is in an upright position (e.g., horizontal), the pressure deck body 100 is also oriented generally horizontally. In other embodiments, at least one lengthwise segment of the pressure deck body 100 is not parallel to the roll axis 104 of the fuselage section 102 but extends at an angle (e.g., acute angle, obtuse angle, etc.) and / or at least one widthwise segment of the pressure deck body 100 is not parallel to the pitch axis 106 of the fuselage section 102 but extends at an angle (e.g., acute angle, obtuse angle, etc.). In some embodiments, the pressure deck body 100 is a component of (e.g., a component supporting, defining, or contained within) one or more compartments in the fuselage 102, such as, but not limited to, a wheel well (e.g., wheel well 320 shown in FIG. 6).

[0017] The pressure deck body 100 shown in FIG. 1 is located anywhere along the length of the fuselage section 102 (i.e., anywhere along the roll axis 104). FIG. 6 shows an example of where the pressure deck body 100 of FIG. 1 may be located in an exemplary embodiment. Specifically, the pressure deck body 100 is a component of the wheel well 320 of the fuselage section 302 (e.g., the pressure deck body 100 forms a support structure for the wheel well 320, the pressure deck body 100 forms the contour of the wheel well 320, the pressure deck body 100 is contained within the wheel well 320, etc.). However, the pressure deck body 100 can additionally or alternatively be located at any other location along the length of the fuselage section 302, whether inside or outside the wheel well of the fuselage section 302. For example, in other embodiments, the pressure deck body 100 can form a support structure, such as other components and / or structures, in addition to or instead of the wheel well of the fuselage section 302.

[0018] Referring now to FIG. 2 , the fuselage 102 of the exemplary embodiment has a cross-section that is wider-than-tall ellipse-shaped (at least when the interior of the fuselage 102 is not pressurized), at least in the portion where the pressure deck 100 is located. Specifically, the cross-sectional shape of the fuselage 102 at the position of the pressure deck 100 when the interior of the fuselage 102 is not pressurized is shown by dotted line 102a in FIG. 2 . In other words, dotted line 102a represents the unpressurized cross-sectional shape of the fuselage 102 of the exemplary embodiment at the position of the pressure deck 100. On the other hand, the cross-sectional shape of the fuselage 102 at the position of the pressure deck 100 when the interior of the fuselage 102 of the exemplary embodiment is pressurized is shown by solid line 102b in FIG. 2 . In other words, solid line 102b represents the pressurized cross-sectional shape of the fuselage 102 of the exemplary embodiment at the position of the pressure deck 100.

[0019] As can be seen from Figure 2, the unpressurized cross-sectional shape of the fuselage section 102, indicated by dotted line 102a, is a horizontally elongated ellipse. Specifically, in the unpressurized elliptical cross-sectional shape of the fuselage section 102, indicated by dotted line 102a, the diameter along the pitch axis 106 is longer than the diameter along the yaw axis 108. As is clear from a comparison of dotted line 102a and solid line 102b, the pressurized cross-sectional shape of the fuselage section 102, indicated by solid line 102b, has a shorter diameter along the pitch axis 106 and a longer diameter along the yaw axis 108 than the unpressurized cross-sectional shape of the fuselage section 102, indicated by dotted line 102a. In other words, when the interior of the fuselage section 102 is pressurized, compressive forces act (e.g., increase) on the fuselage section 102 in the directions indicated by arrows 110 and 112, causing the fuselage section 102 to contract along the pitch axis 106 and expand along the yaw axis 108.

[0020] However, the cross-sectional shape of the fuselage 102 at the pressure deck 100 is not limited to a taller-than-wide elliptical shape. In other embodiments, the cross-sectional shape of the fuselage 102 at the pressure deck 100 when the fuselage 102 is not pressurized may be generally circular. In still other embodiments, the cross-sectional shape of the fuselage 102 at the pressure deck 100 when the fuselage 102 is not pressurized may be a taller-than-wide elliptical shape.

[0021] 1 , the pressure deck assembly 100 includes a plurality of longitudinal beams 114 and a pressure deck 116. Each longitudinal beam 114 has a length that extends from one end 118 to the other end 120 along the roll axis 104 of the fuselage 102. In other words, the length of each longitudinal beam 114 extends along the length of the fuselage 102. In an exemplary embodiment, the length of each longitudinal beam 114 is generally parallel to the roll axis 104 of the fuselage 102 and generally perpendicular to each of the pitch axis 106 and yaw axis 108. However, in other embodiments, one or more of the plurality of longitudinal beams 114 may be oriented along their length such that (1) they are not parallel to the roll axis 104 of the fuselage 102 but form a given angle (e.g., acute angle, obtuse angle, etc.), (2) they are not parallel to the pitch axis 106 but form a given angle, and / or (3) they are not parallel to the yaw axis 108 but form a given angle.

[0022] Optionally, the pressure deck 100 may include one or more intercostal members 122 joined between adjacent ones of the plurality of longitudinal beams 114, for example, to help support the adjacent ones of the plurality of longitudinal beams 114 in the orientation shown in the figures. Each longitudinal beam 114 may include (e.g., as a component, material, etc.) any material that enables the longitudinal beam 114 to perform the functions described and / or illustrated herein. For example, in some embodiments, the longitudinal beams 114 may include (e.g., as a component, material, etc.) a composite material, such as, but not limited to, a carbon composite, a carbon fiber composite, a thermoplastic composite, a thermoplastic carbon fiber composite, a thermoset composite, a thermoset carbon fiber composite, and / or a polyparaphenylene terephthalamide fiber composite. In one example, one or more of the longitudinal beams 114 may include (e.g., as a component, material, etc.) a thermoplastic carbon fiber composite. In some other embodiments, one or more of the longitudinal beams 114 may include (e.g., include as components, materials, etc.) other materials in addition to or instead of composite materials, such as, but not limited to, titanium, aluminum, steel, alloys of two or more metals, etc. Note that while eight longitudinal beams 114 are shown in the exemplary embodiment shown, the pressure deck assembly 100 may include any number of longitudinal beams.

[0023] 1 and 3, the pressure deck 116 extends across the length of and between the longitudinal beams 114. Specifically, the pressure deck 116 is disposed across the length of the longitudinal beams 114 and extends laterally along the pitch axis 106 to straddle each pair of adjacent longitudinal beams 114. In an exemplary embodiment, the pressure deck 116 is divided into a plurality of separate (e.g., independent, individual) segments, each of which extends across either a pair of adjacent longitudinal beams 114 or between a longitudinal beam 114 and a longeron 124 (not shown in FIG. 1 ) of the fuselage 102.

[0024] 1 and 3 includes a plurality of compliant deck segments 126, a center bay deck segment 128, and a pair of end bay deck segments 130. Each compliant deck segment 126 extends between a pair of adjacent longitudinal beams 114. Specifically, compliant deck segment 126a extends between pair of longitudinal beams 114a and 114b, compliant deck segment 126b extends between pair of longitudinal beams 114b and 114c, compliant deck segment 126c extends between pair of longitudinal beams 114c and 114d, compliant deck segment 126d extends between pair of longitudinal beams 114e and 114f, compliant deck segment 126e extends between pair of longitudinal beams 114f and 114g, and compliant deck segment 126f extends between pair of longitudinal beams 114g and 114h. Each of the resilient deck segments 126a, 126b, 126c, 126d, 126e, and 126f is also referred to herein as a "first deck segment" and / or a "second deck segment." The center bay deck segment 128 is also referred to herein as a "first deck segment" and / or a "second deck segment." Each of the end bay deck segments 130a and 130b is also referred to herein as a "first deck segment" and / or a "second deck segment."

[0025] Referring solely to Figure 3, which will be described in more detail below, resilient deck segment 126a is joined to longitudinal beams 114a and 114b at joints 132 and 134, respectively; resilient deck segment 126b is joined to longitudinal beams 114b and 114c at joints 136 and 138, respectively; resilient deck segment 126c is joined to longitudinal beams 114c and 114d at joints 140 and 142, respectively; resilient deck segment 126d is joined to longitudinal beams 114e and 114f at joints 144 and 146, respectively; resilient deck segment 126e is joined to longitudinal beams 114f and 114g at joints 148 and 150, respectively; and resilient deck segment 126f is joined to longitudinal beams 114g and 114h at joints 152 and 154, respectively. Any suitable fasteners may be used to join each resilient deck segment 126 to the longitudinal beams 114, such as, but not limited to, bolts, rivets, adhesives, epoxies, welding, and / or brazing. Note that in the illustrated example, the pressure deck 116 includes six resilient deck segments 126, although other embodiments may include any number of resilient deck segments (e.g., the number of resilient deck segments 126 may be selected based on, for example, the number of longitudinal beams 114).

[0026] 1 and 3 , each resilient deck segment 126 of the pressure deck 116 constitutes a deflectable spring. Specifically, each resilient deck segment 126 of the pressure deck 116 is capable of elastically deflecting along the pitch axis 106 of the fuselage 102. Thus, each resilient deck segment 126 of the pressure deck 116 is capable of expanding and contracting along the pitch axis 106 of the fuselage 102. In an exemplary embodiment, each resilient deck segment 126 of the pressure deck 116 is a catenary shaped web. However, one or more of the resilient deck segments 126 may additionally or alternatively include any type of resilient member, including, but not limited to, a parabolic, sinusoidal, and / or radius shaped member.

[0027] Each resilient deck segment 126 of the pressure deck 116 includes (e.g., includes as a component, material, etc.) one or more materials that provide the resilient deck segment 126 with the ability to expand and contract along the pitch axis 106 of the fuselage section 102. For example, the resilient deck segment 126, in some embodiments, includes (e.g., includes as a component, material, etc.) a composite material, such as, but not limited to, carbon composite, carbon fiber composite, thermoplastic composite, thermoplastic carbon fiber composite, thermoset composite, thermoset carbon fiber composite, and / or polyparaphenylene terephthalamide fiber composite. In one example, one or more resilient deck segments 126 include (e.g., includes as a component, material, etc.) a thermoplastic carbon fiber composite. In some other embodiments, one or more resilient deck segments 126 include (e.g., includes as a component, material, etc.) another material in addition to or instead of a composite material, such as, but not limited to, titanium, aluminum, steel, and / or an alloy of two or more metals.

[0028] The central bay deck segment 128 extends between a pair of adjacent longitudinal beams 114. Specifically, the central bay deck segment 128 extends between longitudinal beams 114d and 114e. The central bay deck segment 128 is joined to longitudinal beams 114d and 114e at joints 158 and 160, respectively. Any suitable fasteners may be used to join the central bay deck segment 128 to the longitudinal beams 114d and 114e, such as, but not limited to, bolts, rivets, adhesives, epoxies, welding, and / or brazing. Note that while a single central bay deck segment 128 is shown in the illustrated example, in other embodiments, the pressure deck 116 may include any number of central bay deck segments 128 (e.g., the number of central bay deck segments 128 may be selected based on, for example, the number of longitudinal beams 114).

[0029] In exemplary embodiments, center bay deck segment 128 is a relatively rigid member (e.g., a stiffening structure, etc.) that connects longitudinal beams 114d and 114e in a generally planar (e.g., substantially linear) path. In other embodiments, center bay deck segment 128 is a member that is expandable (e.g., resiliently flexible along pitch axis 106 of fuselage 102), and in some other embodiments, center bay deck segment 128 is, for example, a catenary web. In some embodiments, center bay deck segment 128 is, for example, a parabolic, sinusoidal, and / or radiused member.

[0030] The central bay deck segment 128 of the pressure deck 116 may include (e.g., include as a component, material, etc.) any material that enables the central bay deck segment 128 to perform the functions described and / or illustrated herein. For example, the central bay deck segment 128 may, in some embodiments, include (e.g., include as a component, material, etc.) a composite material, such as, but not limited to, a carbon composite, a carbon fiber composite, a thermoplastic composite, a thermoplastic carbon fiber composite, a thermoset composite, a thermoset carbon fiber composite, and / or a polyparaphenylene terephthalamide fiber composite. In one example, the central bay deck segment 128 may include (e.g., include as a component, material, etc.) a thermoplastic carbon fiber composite. In some other embodiments, the central bay deck segment may include (e.g., include as a component, material, etc.) another material in addition to or instead of a composite material, such as, but not limited to, titanium, aluminum, steel, an alloy of two or more metals, etc.

[0031] The end bay deck segments 130 extend between corresponding longitudinal beams 114 and corresponding longerons 124 in the fuselage section 102. Specifically, referring solely to FIG. 3 , end bay deck segment 130a extends between longitudinal beam 114a and longeron 124a, and end bay deck segment 130b extends between longitudinal beam 114h and longeron 124b. End bay deck segment 130a is joined to longitudinal beam 114a and longeron 124a at joints 162 and 164, respectively, and end bay deck segment 130b is joined to longitudinal beam 114h and longeron 124b at joints 166 and 168, respectively. Any suitable fasteners may be used to join end bay deck segments 130a and 130b to longitudinal beams 114a and 114h, such as, but not limited to, bolts, rivets, adhesives, epoxies, welding, and / or brazing. Additionally, any suitable fasteners may be used to join the end bay deck segments 130a and 130b to the longerons 124a and 124b, such as, but not limited to, bolts, rivets, adhesives, epoxies, welding, and / or brazing.

[0032] 1 and 3 , in an exemplary embodiment, each end bay deck segment 130 is a relatively rigid member (e.g., a stiffening structure, etc.) that connects a corresponding longitudinal beam 114 and a corresponding longeron 124 in a generally planar (e.g., substantially linear) path. In other embodiments, one or both of the end bay deck segments 130 are members that are expandable (e.g., elastically flexible along the pitch axis 106 of the fuselage section 102) along the pitch axis 106 of the fuselage section 102. In some other embodiments, the end bay deck segments 130 a and / or 130 b are, for example, catenary webs. In some embodiments, for example, the end bay deck segments 130 a and / or 130 b are members that are parabolic, sinusoidal, and / or radiused.

[0033] Each end bay deck segment 130 of the pressure deck 116 may include (e.g., include as a component, material, etc.) any material that enables the end bay deck segment 130 to perform the functions described and / or illustrated herein. For example, one or both of the end bay deck segments 130 may, in some embodiments, include (e.g., include as a component, material, etc.) a composite material, such as, but not limited to, carbon composite, carbon fiber composite, thermoplastic composite, thermoplastic carbon fiber composite, thermoset composite, thermoset carbon fiber composite, and / or polyparaphenylene terephthalamide fiber composite. In one example, each end bay deck segment 130 includes (e.g., include as a component, material, etc.) a thermoplastic carbon fiber composite. In some other embodiments, one or both end bay deck segments 130 may include (e.g., include as a component, material, etc.) another material in addition to or instead of a composite material, such as, but not limited to, titanium, aluminum, steel, an alloy of two or more metals, etc.

[0034] 4 shows joints 138 and 140 between resilient deck segments 126b and 126c, respectively, and longitudinal beam 114c. Joints 134, 142, 146, 150, and 154 (shown in FIG. 3) are generally similar to joint 138. Joints 132, 136, 144, 148, and 152 (shown in FIG. 3) are generally similar to joint 140. Accordingly, although joints 132, 134, 136, 142, 144, 146, 148, 150, 152, and 154 will not be described in detail herein, it will be understood that the performance, load paths, advantages, and / or effects provided by the configuration of joints 138 and 140 apply equally to each of joints 132, 134, 136, 142, 144, 146, 148, 150, 152, and 154. Additionally, in some embodiments, joints 160, 162, and / or 168 (shown in FIG. 3 ) have substantially the same configuration as joint 138, and / or joints 158, 164, and / or 166 (shown in FIG. 3 ) have substantially the same configuration as joint 140, and thus the performance, load paths, benefits, effects, etc., provided by the configurations of joints 138 and 140 apply equally to each of joints 160, 162, 168, 158, 164, and / or 166.

[0035] As shown in FIG. 4 , the longitudinal beam 114c includes a central portion 170 and flange portions 172 and 174 extending in opposite directions from the central portion 170. The central portion 170 has a height ranging from a first end 176 to an opposite second end 178. The flange portions 172 and 174 extend outward from the first end 176 of the central portion 170. The flange portion 172 has an upper surface 180 and a lower surface 182, and the flange portion 174 has an upper surface 184 and a lower surface 186. As can be seen in FIG. 4 , the upper surface 180 and the upper surface 184 each face generally toward the second end 178 of the central portion 170, while the lower surface 182 and the lower surface 186 each face generally away from the second end 178 of the central portion 170. Flange portions 172 and 174 are also referred to as "first" and / or "second" flange portions, respectively. Upper surfaces 180 and 184 are also referred to as "first" and / or "second" upper surfaces, respectively, and lower surfaces 182 and 186 are also referred to as "first" and / or "second" lower surfaces, respectively.

[0036] In some configurations, the central portion 170 of the longitudinal beam 114c may be comprised of two or more components. For example, in the exemplary embodiment of the longitudinal beam 114c shown in FIG. 4, the central portion 170 includes two component segments 170a and 170b joined together along the length of the longitudinal beam 114c using any suitable fastener, such as, but not limited to, bolts, rivets, adhesives, epoxies, welding, and / or brazing. A flange portion 172 extends from the component segment 170a of the central portion 170, and a flange portion 174 extends from the component segment 170b of the central portion 170. In the embodiment shown in FIG. 4, a central axis 188 of an exemplary fastener (not shown), such as a bolt or rivet, is shown to indicate the joining of the component segments 170a and 170b. Note that the location of the central axis 188 of the fastener along the height of the central portion 170 is for illustrative purposes only. The central axis 188 of the fastener may additionally or alternatively be located at any other position along the height of the central portion 170. In other embodiments, the central portion 170 of the longitudinal beam 114c is comprised of a single component segment, and thus the central portion 170 is a one-piece component. The component segments 170a and 170b of the central portion 170 are also referred to as the "first" component segment and / or the "second" component segment, respectively.

[0037] As shown in FIG. 4 , the flange portion 172 of the longitudinal beam 114c extends from the central portion 170 at a given angle α1 relative to the central portion 170, such that the flange portion 172 and the central portion 170 form an L-shape. Similarly, the flange portion 174 of the longitudinal beam 114c extends from the central portion 170 at an angle α2 relative to the central portion 170, such that the flange portion 174 and the central portion 170 form an L-shape. In the exemplary embodiment, the angles α1 and α2 are substantially equal and are oblique angles greater than 90°. However, in other embodiments, the angle α1 of the L-shape formed by the flange portion 172 and the central portion 170 may be any other angle less than approximately 180° (e.g., an angle α1 of approximately 90°, an oblique angle α1 less than approximately 90°, another oblique angle α1 greater than approximately 90°, etc.). Additionally, in other embodiments, angle α2 of the L-shape formed by flange portion 174 and central portion 170 can be any other angle less than approximately 180° (e.g., angle α2 of approximately 90°, oblique angle α2 less than approximately 90°, another oblique angle α1 greater than approximately 90°, etc.) In some other embodiments, angle α1 and angle α2 of the L-shape formed by each of flange portions 172 and 174 and central portion 170 can be different angles from each other.

[0038] As shown in FIG. 4 , the flange portion 172 of the vertical beam 114c extends from the central portion 170, and the flange portion 172 and the central portion 170 form a corner portion 190 of the vertical beam 114c. The corner portion 190 has an inner surface 192 facing a space enclosed by an angle α1 formed by the central portion 170 and the flange portion 172. The corner portion 190 has an outer surface 194 facing a space enclosed by an angle α3 formed by the central portion 170 and the flange portion 172. As can be seen from FIG. 4 , the upper surface 180 of the flange portion 172 forms a part of the inner surface 192 of the corner portion 190, and a side surface 196 of the central portion 170 forms another part of the inner surface 192 of the corner portion 190. Additionally, a side surface 198 of the central portion 170 opposite to the side surface 196 forms a part of an outer surface 194 of the corner portion 190, and a lower surface 182 of the flange portion 172 forms another part of the outer surface 194 of the corner portion 190. In this specification, the corner portion 190 is also referred to as a "first" and / or a "second" corner portion.

[0039] The flange portion 174 of the longitudinal beam 114c extends from the central portion 170, and the flange portion 174 and the central portion 170 form a corner portion 200 in the longitudinal beam 114c. The corner portion 200 has an inner surface 202 facing a space enclosed by an angle α2 formed by the central portion 170 and the flange portion 174. As can be seen from FIG. 4 , the upper surface 184 of the flange portion 174 forms a part of the inner surface 202 of the corner portion 200, and the side surface 198 of the central portion 170 forms another part of the inner surface 202 of the corner portion 200. In addition, the corner portion 200 has an outer surface 204 facing a space enclosed by an angle α4 formed by the central portion 170 and the flange portion 174. The underside 186 of the flange portion 174 forms a portion of the outer surface 204 of the corner portion 200, and the side surface 196 of the central portion 170 forms another portion of the outer surface 204 of the corner portion 200. The corner portion 200 is also referred to herein as the "first" and / or "second" corner portion.

[0040] The resilient deck segment 126b of the pressure deck 116 is joined to the flange portion 172 of the longitudinal beam 114c at the underside 182 of the flange portion 172. Thus, the resilient deck segment 126b is joined to the flange portion 172 of the longitudinal beam 114c such that the resilient deck segment 126b extends to the outer side 194 of the corner 190 of the longitudinal beam 114c. Similarly, the resilient deck segment 126c of the pressure deck 116 is joined to the flange portion 174 of the longitudinal beam 114c at the underside 186 of the flange portion 174. Thus, the resilient deck segment 126c is joined to the flange portion 174 of the longitudinal beam 114c such that the resilient deck segment 126c extends to the outer side 204 of the corner 200 of the longitudinal beam 114c.

[0041] In the exemplary embodiment, a splice 206 is provided at the joints 138 and 140 between the longitudinal beam 114c and the resilient deck segments 126b and 126c, respectively. Specifically, the splice 206 has a length from one end 208 to an opposite end 210. As shown in FIG. 4, the end 208 of the splice 206 is joined between the flange portion 172 of the longitudinal beam 114c and the resilient deck segment 126b of the pressure deck 116. As also shown in FIG. 4, the end 210 of the splice 206 is joined between the flange portion 174 of the longitudinal beam 114c and the resilient deck segment 126c of the pressure deck 116. The ends 208 and 210 of the splice 206 are also referred to as the "first" and "second" ends, respectively.

[0042] Splice 206 reinforces the joint (e.g., connection, attachment, etc.) between component segments 170a and 170b at central portion 170 of longitudinal beam 114c, preventing, for example, separation of component segments 170a and 170b. Splice 206 also facilitates ensuring predetermined distance D (described in detail below with reference to FIG. 5). In other embodiments, joints 138 and / or 140 do not include splice 206, and each resilient deck segment 126b and / or 126c may be directly joined to the underside 182 and / or 186 of the corresponding flange portion 172 and / or 174. For example, in embodiments where central portion 170 of longitudinal beam 114c is comprised of a single component segment (i.e., central portion 170 has a unitary construction), splice 206 may be omitted.

[0043] Splice 206 may include (e.g., include as a component, material, etc.) any material that enables splice 206 to perform the functions described and / or illustrated herein. For example, in some embodiments, splice 206 may include (e.g., include as a component, material, etc.) a composite material, such as, but not limited to, carbon composite, carbon fiber composite, thermoplastic composite, thermoplastic carbon fiber composite, thermoset composite, thermoset carbon fiber composite, and / or polyparaphenylene terephthalamide fiber composite. In one example, splice 206 includes (e.g., include as a component, material, etc.) a thermoplastic carbon fiber composite. In some other embodiments, splice 206 may include (e.g., include as a component, material, etc.) other materials in addition to or instead of a composite material, such as, but not limited to, titanium, aluminum, steel, alloys of two or more metals, etc.

[0044] As described above, the resilient deck segments 126b and 126c are joined to the longitudinal beam 114c using any suitable fasteners, such as, but not limited to, bolts, rivets, adhesives, epoxies, welding, and / or brazing. Specifically, the resilient deck segments 126b and 126c are joined to the flanges 172 and 174, respectively, either directly or via splices 206 using any suitable fasteners, such as, but not limited to, bolts, rivets, adhesives, epoxies, welding, and / or brazing. In the example of Figure 4, central axes 212 and 214 of fasteners (not shown), such as bolts and / or rivets, are shown to indicate that the resilient deck segments 126b and 126c are joined to the flanges 172 and 174 via the splices 206. The location of the central axes 212 and 214 of each fastener along the length of the flanges 172 and 174 is for illustrative purposes only. Additionally or alternatively, central axes 212 and / or 214 can be located at any other position along the length of flange portions 172 and / or 174. In some embodiments, the fasteners joining resilient deck segment 126b to longitudinal beam 114c and the fasteners joining resilient deck segment 126c to longitudinal beam 114c can be staggered along the length (as shown in FIG. 1) of longitudinal beam 114c.

[0045] Next, the load paths at joints 138 and 140 will be described with reference to Figure 5. When the interior compartment of fuselage section 102 is pressurized, a pressure load P1 acts on flanges 172 and 174 and resilient deck segments 126b and 126c. This pressure load P1 generates a reaction force R1 in the height direction of center section 170 of longitudinal beam 114c. In addition, pressure load P1 (1) generates a tensile load P2 on resilient deck segments 126b and 126c, and (2) generates an opening moment OM (i.e., torque) that acts in a direction that opens (i.e., increases) angles α1 and α2. The opening moment OM applies (generates) an interlaminar tension (ILT) to longitudinal beam 114c.

[0046] A tensile load P2 acting on the resilient deck segments 126b and 126c generates a reaction force R2 on each of the flange portions 172 and 174. Specifically, the reaction force R2 is a force generated by the fasteners connecting the resilient deck segments 126b and 126c to the flange portions 172 and 174, respectively, in opposition to the tensile load P2. As shown in FIG. 5 , the reaction force R2 is spaced a predetermined distance D from the tensile load P2. The distance D between the tensile load P2 on the resilient deck segments 126b and 126c and the reaction force R2 on the flange portions 172 and 174 generates a closing moment CM (e.g., torque) that acts in a direction to close (i.e., reduce) the angles α1 and α2. The closing moment CM is a moment that acts in the opposite direction to the opening moment OM, opposing the opening moment OM. For example, in some embodiments, the effect of the opening moment OM acting on the longitudinal beam 114c is counteracted by the closing moment CM, thereby reducing the ILT acting on the longitudinal beam 114c. In other embodiments, for example, the closing moment CM may be substantially equal to the opening moment OM, such that the closing moment CM substantially cancels out the opening moment OM (thereby substantially eliminating the ILT acting on the longitudinal beam 114c due to the opening moment OM). The predetermined distance D between the tensile load P2 and the reaction force R2 can be set to generate a desired magnitude of closing moment CM and / or reduce the effect of the opening moment OM by a desired amount, for example, by selecting the thickness of the splice 206, whether or not to include the splice 206, or by selecting the thickness of the flange portions 172 and / or 174.

[0047] The configuration of the joints 138 and 140 shown in Figure 5 reduces or eliminates ILT on the longitudinal beam 114c, thereby allowing the longitudinal beam 114 to include (e.g., as a component, material, etc.) a material with low ILT capabilities. For example, the configuration of the joints 138 and 140 shown in Figure 5 allows the longitudinal beam 114 to include (e.g., as a component, material, etc.) a composite material, such as, but not limited to, carbon composite, carbon fiber composite, thermoplastic composite, thermoplastic carbon fiber composite, thermoset composite, thermoset carbon fiber composite, and / or polyparaphenylene terephthalamide fiber composite. Constructing the longitudinal beam 114 using composite materials can reduce the weight of the pressure deck assembly 100, thereby improving the operational performance, efficiency, and / or functionality of the aircraft.

[0048] Referring now to Figure 6, several exemplary embodiments relating to an aircraft 300 will be described. The aircraft includes an airframe 304 having a fuselage 302. The fuselage 302 includes an interior compartment 306. The airframe 304 includes a number 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 system 314, a control system 316, and an environmental system 318, as well as any number of other systems. While an aerospace example has been described, the principles of the present invention may be applied to other industries, such as, but not limited to, the automotive and / or marine industries.

[0049] An embodiment of the disclosure will be described in relation to aircraft manufacturing and service method 400, as shown in Figure 7. As a pre-production process, aircraft manufacturing and service method 400 includes specification and design 402 of an aircraft (such as aircraft 300 shown in Figure 6) and material procurement 404. During production, aircraft component and subassembly manufacturing 406 and system integration 408 occurs. The aircraft then undergoes, for example, certification and delivery 410 and enters service 412. While in customer service, the aircraft undergoes a routine maintenance and service schedule 414 (which may also include modifications, reconfigurations, retrofits, etc.).

[0050] The steps of example method 400 may be performed or implemented by a system integrator, a third party, and / or an operator (e.g., a customer). Note that 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 vendors, subcontractors, and suppliers. An operator may be an airline, a leasing company, a military entity, a service organization, etc.

[0051] Additionally, any number of other systems may be included in addition to the systems described. Although an aerospace example has been described, the principles of the present invention are applicable to other industries, such as, but not limited to, the automotive and marine industries.

[0052] The systems and methods described above can be employed at any one or more stages of manufacturing and use method 400. For example, the components or subcomponents corresponding to component and subassembly manufacturing 406 can be similarly manufactured or produced as components or subcomponents produced during the aircraft's in-service life. Additionally, one or more embodiments of the system, method, or combination thereof can be used during component and subassembly manufacturing 406 and system integration 408, which can, for example, significantly increase the speed or reduce the cost of aircraft assembly. Similarly, one or more embodiments of the apparatus, method, or combination thereof can be used during the aircraft's in-service life, such as, but not limited to, maintenance and service 414.

[0053] Various embodiments of the present disclosure may enable the longitudinal beams of a pressure deck to be constructed from composite materials. Certain embodiments of the present disclosure may enable a weight reduction of the pressure deck in an aircraft fuselage. Certain embodiments of the present disclosure may enable improved aircraft operational performance, efficiency, and / or functionality.

[0054] Further aspects of the present disclosure are described in the appendix below.

[0055] A1. A pressure deck assembly for a fuselage section, Vertical beam and a pressure deck; the longitudinal beam has a length along the roll axis of the body portion, and includes a central portion and first and second flange portions extending in opposite directions from the central portion, the first flange portion having a first upper surface and a first lower surface, and the second flange portion having a second upper surface and a second lower surface; The pressure deck includes first and second deck segments, the first deck segment being joined to the first flange portion of the longitudinal beam at the first lower surface of the first flange portion, and the second deck segment being joined to the second flange portion of the longitudinal beam at the second lower surface of the second flange portion.

[0056] A2. The pressure deck assembly of Appendix A1, wherein the longitudinal beams comprise 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.

[0057] A3. The pressure deck assembly of Appendix A1, further comprising a splice having a length from a first end to a second end, the first end of the splice being joined between the first flange portion of the longitudinal beam and the first deck segment of the pressure deck, and the second end of the splice being joined between the second flange portion of the longitudinal beam and the second deck segment of the pressure deck.

[0058] A4. A pressure deck body as described in Appendix A1, wherein the central portion of the longitudinal beam has a height extending from a first end to a second end, the first and second flange portions extend outward from the first end, and the first and second lower surfaces of the first and second flange portions face in a direction opposite to the second end of the central portion.

[0059] A5. A pressure deck assembly as described in Appendix A1, wherein the first flange portion of the longitudinal beam extends from the central portion so as to form an L-shape with the first flange portion and the central portion, and the second flange portion of the longitudinal beam extends from the central portion so as to form an L-shape with the second flange portion and the central portion.

[0060] A6. The pressure deck assembly of Appendix A1, wherein at least one of the first deck segment or the second deck segment of the pressure deck is telescopic along the pitch axis of the fuselage section.

[0061] 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 is a catenary web.

[0062] A8. The pressure deck assembly of Appendix A1, wherein at least one of the first flange portion or the second flange portion is spaced a predetermined distance from the first or second deck segment, the predetermined distance being configured to generate at least one closing moment, upon application of a pressure load, acting to close an angle between the at least one of the first flange portion or the second flange portion and the central portion.

[0063] A9. The pressure deck assembly of Appendix A1, wherein the central portion of the longitudinal beam includes first and second component segments joined together, the first flange portion extending from the first component segment, and the second flange portion extending from the second component segment.

[0064] B1. A pressure deck assembly for a fuselage section, Vertical beam and a pressure deck; the longitudinal beam has a length along the roll axis of the body portion, and includes a central portion and first and second flange portions extending in opposite directions from the central portion, the first flange portions and the central portion forming a first corner portion of the longitudinal beam, and the second flange portions and the central portion forming a second corner portion of the longitudinal beam, the pressure deck includes first and second deck segments, the first deck segment joined to the first flange portion of the longitudinal beam such that the first deck segment extends onto an outer surface of the first corner portion of the longitudinal beam, and the second deck segment joined to the second flange portion of the longitudinal beam such that the second deck segment extends onto an outer surface of the second corner portion of the longitudinal beam.

[0065] B2. The pressure deck assembly of Clause B1, wherein the longitudinal beams comprise 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] B3. The pressure deck assembly of Appendix B1, further comprising a splice having a length from a first end to a second end, the first end of the splice being joined between the first flange portion of the longitudinal beam and the first deck segment of the pressure deck, and the second end of the splice being joined between the second flange portion of the longitudinal beam and the second deck segment of the pressure deck.

[0067] B4. A pressure deck assembly as described in Appendix B1, wherein the first and second flange portions of the longitudinal beam have first and second upper surfaces and first and second lower surfaces, respectively, the first lower surface of the first flange portion forming part of the outer surface of the first corner portion, the first deck segment of the pressure deck being joined to the first flange portion at the first lower surface of the first flange portion, the second lower surface of the second flange portion forming part of the outer surface of the second corner portion, and the second deck segment of the pressure deck being joined to the second flange portion at the second lower surface of the second flange portion.

[0068] 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 is a catenary web.

[0069] B6. The pressure deck assembly of Appendix B1, wherein at least one of the first flange portion or the second flange portion is spaced a predetermined distance from the first or second deck segment, the predetermined distance configured to generate at least one closing moment, upon application of a pressure load, acting to close an angle between the at least one of the first flange portion or the second flange portion and the central portion.

[0070] C1. An aircraft fuselage section, a pressure deck body including a longitudinal beam and a pressure deck; the longitudinal beam has a length along the roll axis of the body portion, and has a central portion and a flange portion extending from the central portion, the flange portion having an upper surface and a lower surface; The pressure deck includes a deck segment, the deck segment being joined to the flange portion of the longitudinal beam at the underside of the flange portion.

[0071] C2. The fuselage section of Clause C1, 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.

[0072] C3. A body portion as described in Appendix C1, wherein the central portion of the longitudinal beam has a height extending from a first end to a second end, the flange portion extends outward from the first end, and the underside of the flange portion faces away from the second end of the central portion.

[0073] C4. The fuselage of Clause C1, wherein the deck segments of the pressure deck are catenary webs.

[0074] C5. The fuselage section of Clause C1, wherein the flange section and the deck segment are spaced a predetermined distance apart configured to generate a closing moment, upon application of a pressure load, that acts to close the angle between the central section and the flange section.

[0075] As used herein, a structure, element, or element that is defined as being "configured" to perform a process or operation is one that is structurally formed, configured, or adapted in a manner suitable for that process or operation. For clarity and avoidance of doubt, something that merely can be modified to perform that process or operation is not "configured" to perform that process or operation.

[0076] It will be apparent to those skilled in the art that the numerical values ​​or ranges set forth herein can be expanded or modified without impairing the intended effects.

[0077] Although specific language relating to structural features and / or method acts has been used in describing the subject matter of this disclosure, it will be understood that the subject matter defined by the appended claims is not necessarily limited to the specific features or acts described above. Rather, the specific features or acts described above are merely disclosed as example forms of implementing the claimed subject matter.

[0078] The benefits and advantages described above may relate to one embodiment or to several embodiments. Embodiments are not limited to those that solve some or all of the problems described above or that provide the benefits or advantages described above. Also, a reference to "an" or "an" item is a reference to one or more of that item.

[0079] As used in this specification, the term "comprises" means the inclusion of the features or operations listed after the term, but does not exclude the inclusion of one or more other features or operations.

[0080] The order of execution of the processes illustrated and described in the embodiments of the present disclosure is not required unless otherwise specified. That is, the order of execution of the processes is arbitrary unless otherwise specified. Also, the embodiments of the present disclosure may include more or fewer processes than those described. For example, a particular process may be executed before, simultaneously with, or after other processes (e.g., other steps), and all such cases are within the scope of the present disclosure.

[0081] In the aspects or examples of the present disclosure, an element described in the singular means there is one or more of that element. Additionally, unless otherwise specified, the terms "comprising" and "having" are used in an inclusive sense and mean that additional, unlisted elements may be included. Additionally, the term "exemplary" means "serving as an example." The phrase "one or more of A, B, and C" means "at least one of A, and / or at least one of B, and / or at least one of C."

[0082] Although the embodiments of the present disclosure have been described in detail above, it will be apparent that various changes and modifications can be made without departing from the scope of the embodiments disclosed in the appended claims. The structures, products, and methods described above can be modified in various ways without departing from the scope of the embodiments of the present disclosure, and the contents of the foregoing description and accompanying drawings are illustrative only and are not intended to be limiting.

[0083] It is to be understood that the foregoing description is illustrative, and not limiting. For example, the above-described embodiments (and / or aspects thereof) can be used in combination with each other. In addition, various modifications can be made to adapt to particular situations or materials without departing from the scope of the teachings of the various embodiments of the present disclosure. While the dimensions and types of materials described herein define parameters for various embodiments of the present disclosure, such embodiments are not intended to be limiting and are merely exemplary. Many other embodiments will be apparent to those skilled in the art in light of the above description. Accordingly, the scope of the various embodiments of the present disclosure should be determined with reference to the appended claims, along with all equivalents to which such claims are entitled. As used in the appended claims, the terms "comprises" and "including" and the like are used in their ordinary sense and are equivalent to the terms "comprise" and "in" and the like, respectively. In addition, the terms "first," "second," "third," etc. are used merely as distinguishing markers and do not impose quantitative requirements on the objects referred to thereby.

[0084] This written description uses examples to disclose various embodiments, including the best mode, and also enables those skilled in the art to practice various embodiments, including making and using any devices or systems, and performing the incorporated methods. The patentable scope of various embodiments of the present disclosure is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples should be considered within the scope of the claims if they contain elements that do not differ from the literal language of the claims, or if they contain equivalent elements that have only insubstantial differences from the literal language of the claims.

Claims

1. 1. A pressure deck assembly for a fuselage section, comprising: Multiple longitudinal beams and a pressure deck including a plurality of deck segments; Each longitudinal beam has a length along the roll axis of the body portion, and includes a central portion and first and second flange portions extending in opposite directions from the central portion, the first flange portion having a first upper surface and a first lower surface, and the second flange portion having a second upper surface and a second lower surface; Each deck segment is joined to the first flange portion of one longitudinal beam at the first lower surface of the first flange portion and to the second flange portion of the other longitudinal beam at the second lower surface of the second flange portion, The pressure deck body, wherein the plurality of deck segments include a central bay deck segment and a plurality of elastic deck segments located on both sides of the central bay deck segment, the central bay deck segment having a flat, rigid structure, and each elastic deck segment having a curved structure and being able to elastically bend.

2. 10. The pressure deck assembly of claim 1, wherein each 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.

3. 3. The pressure deck assembly of claim 1, further comprising a splice having a length from a first end to a second end, the first end of the splice being joined between the first flange portion of each longitudinal beam and one deck segment of the pressure deck, and the second end of the splice being joined between the second flange portion of each longitudinal beam and another deck segment on the pressure deck adjacent to the one deck segment.

4. 4. The pressure deck body according to claim 1, wherein the central portion of each of the longitudinal beams has a height extending upward from the first and second flange portions, the first and second flange portions extend laterally from the central portion, and the first and second lower surfaces of the first and second flange portions are surfaces facing in a direction opposite to the central portion.

5. 5. The pressure deck body according to claim 1, wherein the first flange portion of each longitudinal beam extends from the central portion so as to form an L-shape with the first flange portion and the central portion, and the second flange portion of each longitudinal beam extends from the central portion so as to form an L-shape with the second flange portion and the central portion.

6. A pressure deck assembly as claimed in any preceding claim, wherein at least one of the resilient deck segments is extendable along a pitch axis of the fuselage section.

7. A pressure deck assembly according to any preceding claim, wherein at least one of the resilient deck segments is a catenary web.

8. 8. The pressure deck assembly of claim 1, wherein at least one of the first flange portion or the second flange portion is spaced a predetermined distance from a respective deck segment, the predetermined distance being configured to generate a moment acting upon a pressure load that acts to reduce an angle between the at least one of the first flange portion or the second flange portion and the central portion.

9. 9. The pressure deck assembly of claim 1, wherein the central portion of each longitudinal beam includes first and second component segments joined together, the first flange portion extending from the first component segment, and the second flange portion extending from the second component segment.

10. 1. A pressure deck assembly for a fuselage section, comprising: a plurality of longitudinal beams; a pressure deck including a plurality of deck segments; each longitudinal beam has a length along the roll axis of the body portion and includes a central portion and first and second flange portions extending in opposite directions from the central portion, the first flange portions and the central portion forming a first corner portion of each longitudinal beam, and the second flange portions and the central portion forming a second corner portion of each longitudinal beam, Each deck segment is joined to the first flange portion of one longitudinal beam so as to extend under the first corner portion of the one longitudinal beam, and is joined to the second flange portion of the other longitudinal beam so as to extend under the second corner portion of the other longitudinal beam, The pressure deck body, wherein the plurality of deck segments include a central bay deck segment and a plurality of elastic deck segments located on both sides of the central bay deck segment, the central bay deck segment having a flat, rigid structure, and each elastic deck segment having a curved structure and being able to elastically bend.

11. 11. The pressure deck assembly of claim 10, wherein each longitudinal beam comprises at least one of a composite, a carbon fiber composite, a thermoplastic composite, a thermoplastic carbon fiber composite, a thermoset composite, or a thermoset carbon fiber composite.

12. 12. The pressure deck assembly of claim 10, further comprising a splice having a length from a first end to a second end, the first end of the splice being joined between the first flange portion of each longitudinal beam and one deck segment of the pressure deck, and the second end of the splice being joined between the second flange portion of each longitudinal beam and another deck segment on the pressure deck adjacent to the one deck segment.

13. 13. The pressure deck assembly of claim 12, wherein the first and second flange portions of each longitudinal beam have first and second upper surfaces and first and second lower surfaces, respectively, the first lower surface of the first flange portion forming the lower surface of the first corner portion, the one deck segment of the pressure deck being joined to the first flange portion at the first lower surface of the first flange portion, the second lower surface of the second flange portion forming the lower surface of the second corner portion, and the other deck segment of the pressure deck being joined to the second flange portion at the second lower surface of the second flange portion.

14. A pressure deck assembly according to any one of claims 10 to 13, wherein at least one of the resilient deck segments is a catenary web.

15. 15. The pressure deck assembly of claim 10, wherein at least one of the first flange portion or the second flange portion is spaced a predetermined distance from a respective deck segment, the predetermined distance being configured to generate a moment acting upon a pressure load that acts to reduce an angle between at least one of the first flange portion or the second flange portion and the central portion.

16. A fuselage for an aircraft, comprising a pressure deck body according to any one of claims 1 to 15.

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