Modular fuselage assembly, aircraft including the same, and method of assembling the same

Abstract

The name of the present invention is a modular fuselage assembly, an aircraft including the same, and an assembly method thereof. A modular fuselage assembly for an aircraft, an aircraft including the modular fuselage assembly, and a method of assembling the modular fuselage assembly. The modular fuselage assembly includes a plurality of fuselage corners that can extend along the longitudinal axis of the modular fuselage assembly. Each fuselage corner includes a plurality of frame members and a corner skin, and the corner skin is operably connected to the plurality of frame members and defines the outer surface of the fuselage corner. The modular fuselage assembly further includes a plurality of stringers that extend along the longitudinal axis of the modular fuselage assembly. At least two fuselage corners are operably connected to each stringer, and the plurality of fuselage corners and the plurality of stringers at least partially define a cargo hold defined within the modular fuselage assembly. The method includes a method of assembling the modular fuselage assembly.

Description

Technical Field

[0001] The present disclosure generally relates to modular fuselage assemblies for aircraft, aircraft including modular fuselage assemblies, and / or methods of assembling modular fuselage assemblies. Background Art

[0002] Passenger transportation is the largest market for commercial aircraft. Thus, regardless of their intended end use, commercial aircraft are generally designed and / or configured to meet the needs of the airliner market. These designs are then modified for other applications, such as commercial freight aircraft. This allows aircraft manufacturers to produce many different aircraft sub-models based entirely on a single monolithic aircraft design.

[0003] Although effectively meeting the needs of multiple market segments, this approach generally results in design compromises that may not be functionally ideal for all market segments. For example, the need for separate cabin and luggage space within a passenger aircraft means that commercial freight aircraft generally include two cargo holds, one within the area used as cabin space within a passenger aircraft and one within the area used as luggage space within a passenger aircraft. From a freight perspective, such a configuration is inefficient and somewhat arbitrarily limits the amount of freight that a commercial freight aircraft can transport.

[0004] As another example, a given aircraft model is generally a one-size-fits-all solution with respect to the overall size of the aircraft, and these sizes are selected primarily based on passenger needs. Again, these passenger needs may somewhat arbitrarily limit the utility of the aircraft for other purposes, such as freight. Accordingly, there is a need for modular fuselage assemblies for aircraft and / or methods for assembling modular fuselage assemblies. Summary of the Invention

[0005] Modular fuselage assemblies for aircraft and methods of assembling modular fuselage assemblies are discussed herein. The modular fuselage assembly may include a plurality of fuselage lobes that may extend along a longitudinal axis of the modular fuselage assembly. Each fuselage lobe may include a plurality of frame members and a lobe skin that is operably connected to the plurality of frame members and defines an outer surface of the fuselage lobe. The modular fuselage assembly may also include a plurality of stringers that extend along the longitudinal axis of the modular fuselage assembly. At least two fuselage lobes may be operably connected to each stringer, and the plurality of fuselage lobes and the plurality of stringers may at least partially define a cargo hold defined within the modular fuselage assembly.

[0006] The methods include methods of assembling a modular fuselage assembly. These methods may include providing a plurality of frame members and / or providing a plurality of stringers. These methods may also include operably connecting each frame member to at least two stringers such that the plurality of stringers extend along a longitudinal axis of the modular fuselage assembly. Brief Description of the Drawings

[0007] Figure 1 is a schematic view of an example of an aircraft that may include and / or utilize a modular airframe assembly in accordance with the present disclosure.

[0008] Figure 2 is a schematic side view of an example of a modular airframe assembly in accordance with the present disclosure.

[0009] Figure 3 is along Figure 2 taken along line 3-3 of Figure 2 a schematic cross-sectional view of the modular airframe assembly.

[0010] Figure 4 is along Figure 3 taken along line 4-4 of Figure 2-3 a schematic longitudinal cross-sectional view of the modular airframe assembly.

[0011] Figure 5 is a less schematic cross-sectional view of an example of a modular airframe assembly in accordance with the present disclosure.

[0012] Figure 6 is a less schematic cross-sectional view of an example of a modular airframe assembly in accordance with the present disclosure.

[0013] Figure 7 is a less schematic cross-sectional view of an example of a modular airframe assembly in accordance with the present disclosure.

[0014] Figure 8 is a less schematic longitudinal cross-sectional view of an example of a modular airframe assembly in accordance with the present disclosure.

[0015] Figure 9 is a less schematic cross-sectional view of an example of a modular airframe assembly in accordance with the present disclosure, showing the incorporation of crane rails.

[0016] Figure 10 is a less schematic and partially cut-away side view of an aircraft including Figure 9 the modular airframe assembly and crane rails.

[0017] Figure 11 is a less schematic cross-sectional view of an example of a region of a modular airframe assembly in accordance with the present disclosure.

[0018] Figure 12 is a less schematic cross-sectional view of an example of a region of a modular airframe assembly in accordance with the present disclosure.

[0019] Figure 13Schematic diagram of an example of a part of a modular fuselage assembly according to the present disclosure, showing both a top corner deck area and a top corner cargo area.

[0020] Figure 14 Schematic diagram of another example of a part of a modular fuselage assembly according to the present disclosure, showing a top corner deck area, a top corner cargo area, and a wing receiving area.

[0021] Figure 15 Is along Figure 13 The line 15-15 of Figure 13 Cross-sectional view of the modular fuselage assembly.

[0022] Figure 16 Is a flowchart depicting a method of assembling a modular fuselage assembly according to the present disclosure. Detailed Description

[0023] Figure 1-16 Illustrative, non-exclusive examples of an aircraft 10, a modular fuselage assembly 100, and / or a method 300 according to the present disclosure are provided. Elements for similar or at least substantially similar purposes are labeled with similar numbers in Figure 1-16 Each of them, and these elements may not be discussed in detail herein with reference to Figure 1-16 Each of them. Similarly, all elements may not be labeled in Figure 1-16 Each of them, but for consistency, the reference numbers associated herewith may be used. Without departing from the scope of the present disclosure, the elements, components, and / or features discussed herein with reference to Figure 1-16 One or more of them may be included in Figure 1-16 And / or used with any one of Figure 1-16 Each of them.

[0024] Generally, elements that may be included in a given (i.e., specific) embodiment are shown in solid lines, while elements that are optional for a given embodiment are shown in dashed lines. However, the elements shown in solid lines are not essential for all embodiments, and the elements shown in solid lines may be omitted from a given embodiment without departing from the scope of the present disclosure.

[0025] Figure 1 Schematic diagram of an example of an aircraft 10 that may include and / or utilize a modular fuselage assembly 100 according to the present disclosure. An example of the modular fuselage assembly 100 is shown in Figure 2-14 And is discussed in more detail herein with reference thereto.

[0026] The aircraft 10 may include a fuselage 20 in the form of a modular fuselage assembly 100. The aircraft 10 may also include at least one wing 30, which may be operably connected to the fuselage 20 and / or at least one engine 70 and / or may extend from the fuselage 20 and / or at least one engine 70, and the engine 70 may be operably connected to the fuselage 20, for example via a respective wing 30. The aircraft 10 may also include a tail assembly 40, which may include being operably connected to the fuselage 20 and / or at least partially defined by the fuselage 20. The tail assembly 40 includes at least one vertical stabilizer 50 and / or at least one horizontal stabilizer 60.

[0027] Figure 2 is a schematic side view of an example of a modular fuselage assembly 100 in accordance with the present disclosure. Figure 3 is along Figure 2 line 3-3 taken of Figure 2 the modular fuselage assembly 100 and is a schematic cross-sectional view, and Figure 4 is along Figure 3 line 4-4 taken of Figure 2-3 the modular fuselage assembly 100 and is a schematic longitudinal cross-sectional view. Figure 5-7 is a less schematic cross-sectional view of an example of a modular fuselage assembly 100 in accordance with the present disclosure.

[0028] As shown jointly by Figure 2-7 the modular fuselage assembly 100 includes a plurality of fuselage corners 110 and a plurality of stringers 180, both of which may extend along the longitudinal axis 102 of the fuselage assembly. Each fuselage corner 110 includes a plurality of frame members 130 and corner skin 170. The corner skin 170 may be operably connected to the frame members 130 and / or may form and / or define the outer surface 120 of each fuselage corner 110. As shown best by Figure 2 and 5 -7, at least two fuselage corners 110 may be operably connected to each stringer 180, and the fuselage corners 110 and stringers 180 may at least partially bound, define, and / or enclose a cargo hold 104 that may be defined within the modular fuselage assembly 100.

[0029] The modular fuselage assembly 100 disclosed herein can provide a number of benefits over conventional fuselage assemblies of conventional aircraft. As an example and as discussed in more detail herein, it can be direct, efficient, and / or effective to form and / or define a modular fuselage assembly 100 having and / or defining a non-circular cross-sectional shape. This non-circular cross-sectional shape can include a plurality of arcuate regions, which can be defined by fuselage corners 110 and / or can be interconnected at stringers 180. Compared to conventional fuselages that are circular or at least substantially circular in cross-section, this configuration can reduce the wet surface area of the modular fuselage assembly 100, can reduce the aerodynamic drag of the modular fuselage assembly, and / or can reduce the fuel burned in an aircraft 10 including the modular fuselage assembly.

[0030] As another example, the modular nature of the modular fuselage assembly 100 can allow a relatively small number of components (i.e., fuselage corners 110 and stringers 180) to be assembled in a variety of configurations to form and / or define a variety of different fuselages for an aircraft 10. As a more specific example, a plurality of frame members 130 within a fuselage corner 110 can simply be increased to increase the length of the modular fuselage assembly 100.

[0031] As another example, and as discussed in more detail herein, simply replacing a portion of the frame members 130 within a given fuselage corner 110 with differently shaped frame members 130 can allow the formation of more complex fuselage shapes, such as those that can include a flight deck area. As yet another example, and as discussed in more detail herein, simply replacing a portion of the frame members 130 within a given fuselage corner 110 with functionally different frame members 130 can allow the inclusion of wings, tails, and / or landing gear within the modular fuselage assembly.

[0032] As another example, the modular fuselage assembly 100 can allow and / or facilitate the formation of a flight deck area and / or the attachment of wings, tails, and / or landing gear without including structures within the cargo bay 104 of the aircraft, making the use of the modular fuselage assembly 100 more effective in a cargo aircraft configured to carry cargo.

[0033] The frame members 130 can include any suitable structure that can be operably connected to the corner skin 170, can be operably connected to the stringer 180, can operably connect the fuselage corner 110 to the stringer 180, and / or can provide structural support for the modular fuselage assembly 100 and / or its fuselage corner 110. As shown by Figure 1-7 collectively, the frame member 130 or each frame member 130 can extend perpendicular to or at least substantially perpendicular to the longitudinal axis 102. Additionally or alternatively, each frame member 130 can extend between a corresponding pair of stringers 180 and / or can optionally connect a corresponding pair of stringers 180 to each other.

[0034] The frame member 130 and / or its components may be formed of and / or defined by any suitable one and / or more materials. Examples of materials included in the frame member 130 and / or any suitable components thereof include aluminum, aerospace grade aluminum, and / or composite materials.

[0035] As Figure 3 shown by the dashed lines in Figure 5-7 and the solid lines in

[0036] At least one subset of the frame member 130 or multiple frame members 130 may include a compression member 140. When the compression member 140 is present, it may at least partially define the cargo hold 104. The compression member 140 may be configured to receive and / or resist a compressive force, such as a compressive force that may be applied along its long axis. In other words, during operation of the modular fuselage assembly 100, the compression member 140 may be compressed and / or may receive a compressive force. Examples of the compression member 140 include a linear compression member 140. Further examples of the compression member 140 include an elongated compression member, a linear compression member, and / or at least substantially linear compression member.

[0037] Also as Figure 3 shown by the dashed lines in Figure 5-7 and the solid lines in Figure 5-7 At least one subset of the frame member 130 or multiple frame members 130 may include a tension member 150. The tension member 150 may be operably connected to and / or mechanically support the corner skin 170. Additionally or alternatively, the tension member 150 may be shaped such that each fuselage corner 110 and / or its corner skin 170 has and / or defines a convex outer surface 156, and as

[0038] Perhaps best shown, within the scope of the present disclosure, the fuselage corners 110 may jointly define a modular fuselage assembly 100 having a non-circular and / or sector-shaped cross-sectional shape.

[0039] As Figure 3-7As shown, the compression member 140 may have and / or define a first compression member end 142 and a second compression member end 144. Similarly, the tension member 150 may have and / or define a first tension member end 152 and a second tension member end 154. The first tension member end 152 may be operatively connected to the first compression member end 142. Similarly, the second tension member end 154 may be operatively connected to the second compression member end 144.

[0040] As Figure 3 shown by the dashed lines in Figure 3 and Figure 5-7 the solid lines in, the frame member 130 or at least one subset of the plurality of frame members 130 may include a frame member support structure 160. When present, the frame member support structure 160 may be configured to operatively interconnect the compression member 140 and the tension member 150, such as to increase the rigidity of each frame member 130. As Figure 3 and Figure 6 shown, examples of the frame member support structure 160 include struts 162 or a plurality of struts 162. The struts 162 may extend between the compression member 140 and the tension member 150 and / or be operatively connected to both the compression member 140 and the tension member 150. As Figure 3 、 Figure 5 and Figure 7 shown, another example of the frame member support structure 160 includes trusses 164 or a plurality of trusses 164. The trusses 164 may also extend between the compression member 140 and the tension member 150 and / or be operatively connected to both the compression member 140 and the tension member 150. Examples of the trusses 164 include triangular trusses and / or Warren trusses.

[0041] As Figure 3 shown by the dashed lines in Figure 7 and the solid lines in, the frame member 130 or at least one subset of the plurality of frame members 130 may include and / or be a single-piece, integral, and / or one-piece frame member 132. Additionally or alternatively, at least one subset of the frame member 130 or the plurality of frame members 130 may include and / or may be a stamping and / or roll-formed metal frame member that can be formed and / or defined by a metal sheet.

[0042] The stringer 180 may include any suitable structure extending along the longitudinal axis 102 of the modular fuselage assembly 100, configured to be operatively connected to at least two fuselage corners 110 and / or at least partially define the cargo hold 104. For example, the stringer 180 may include and / or be a single-piece, integral, and / or one-piece stringer 180. In other words, each stringer may extend along the entire longitudinal length of the modular fuselage assembly 100. As another example, as Figure 2 and 4As shown, the longitudinal beam 180 can include and / or be a composite longitudinal beam 190, for example, which can be defined by a plurality of longitudinal beam sub-structures 192 that can be operably connected to each other by a plurality of longitudinal beam fasteners 194. In other words, each longitudinal beam sub-structure 192 can extend along a part or a small portion of the longitudinal length of the modular fuselage assembly 100. Examples of longitudinal beam fasteners 194 include bolts, nuts, and / or rivets.

[0043] The fuselage corner 110 can be operably connected to the longitudinal beam 180 in any suitable manner. As an example, and as Figure 2-4 shown, one or more corner fasteners 128 can operably connect each fuselage corner 110 to the corresponding longitudinal beam 180. Examples of corner fasteners 128 include bolts, nuts, and / or rivets.

[0044] As Figure 3-4 schematically shown in, and less schematically shown in Figure 8 the modular fuselage assembly 100 can include a longitudinal support structure 210. When there is a longitudinal support structure 210, the longitudinal support structure 210 can extend along the longitudinal axis 102 of the modular fuselage assembly 100 or at least a part or even the entire longitudinal length. Additionally or alternatively, the longitudinal support structure 210 can be operably connected to a plurality of frame members 130 within a given fuselage corner 110, to at least a subset of the plurality of frame members within a given fuselage corner, or even to all of the plurality of frame members of a given fuselage corner. The longitudinal support structure 210 can also be referred to herein as a shear web and can be configured to support the frame members 130 to support the load distribution along the longitudinal length of the modular fuselage assembly 100 and / or to resist bending and / or twisting of the modular fuselage assembly about and / or along the longitudinal axis 102.

[0045] In some instances, the longitudinal support structure 210 can include and / or can be a continuous, stamped, integral, one-piece, roll-formed, and / or formed longitudinal support structure 216, for example, which can extend along the entire longitudinal length of the modular fuselage assembly. In some instances, the longitudinal support structure 210 can include and / or be a plurality of strips 212 of support material. As Figure 4 and 8 shown, the strips 212 of support material can extend at an inclination angle 214 relative to the longitudinal axis 102 of the modular fuselage assembly 100.

[0046] As shown, the longitudinal support structure 210 can define or at least partially define the cargo hold 104. This configuration can protect the frame members 130 and / or the corner skins 170 from the cargo 80 that may be placed within the cargo hold 104. In other words, the presence of the longitudinal support structure 210 can reduce the likelihood of damage to the frame members 130 and / or the corner skins 170 that may be caused by contact and / or impact with the cargo 80.

[0047] As Figure 3 shown by the dashed lines in Figure 9-10 and the solid lines in, the modular fuselage assembly 100 can include, can form, and / or can define a crane rail 220. The crane rail 220 can extend along the length of the modular fuselage assembly 100, along the length of at least one or even both of the longitudinal beams 180 of the modular fuselage assembly, and / or along the length of the cargo hold 104.

[0048] As Figure 3 shown by the dashed lines in Figure 9 and the solid lines in, the modular fuselage assembly 100 can further include a cargo transport structure 224. The cargo transport structure 224 can be operably or rollably connected to the crane rail 220 and can be configured to move the cargo 80 within the cargo hold 104 and / or along the longitudinal axis 102 of the modular fuselage assembly 100.

[0049] As discussed, the fuselage corner 110 includes a corner skin 170 that can be operably connected to a plurality of frame members 130 within a given fuselage corner 110 and / or can define the outer surface 120 of each fuselage corner. In some instances, the corner skin 170 can include and / or can be an integral, monolithic, and / or continuous corner skin 170 that can extend along the entire longitudinal axis 102 and / or along the entire longitudinal length of each fuselage corner. Additionally or alternatively, in some instances, as Figure 2 shown in, the corner skin 170 can include a plurality of sub - skins 172, each sub - skin can be operably connected to a subset of the plurality of frame members 130 and / or each sub - skin can extend along a portion of the longitudinal length of each fuselage corner 110. Examples of a subset of the plurality of frame members 130 include at least 2, at least 3, at least 4, at least 5, at least 6, at least 6, at least 10%, at least 25%, and / or at least 50% of the plurality of frame members. Examples of a portion of the longitudinal length of each fuselage corner include at least 5%, at least 10%, at least 20%, at least 30%, at least 40%, and / or at least 50% of the longitudinal length of each fuselage corner.

[0050] As Figure 3 shown by the dashed lines in Figure 11As shown by the solid lines in, at least one stringer 180 can be inside the skin mold line 174 of the corner skin 170. In this configuration, the modular airframe assembly 100 can include a thermal insulation 200 that can extend between at least one stringer 180 and the corner skin 170, which can at least partially define an area 108 of the outer surface 106 of the modular airframe assembly and / or can thermally insulate at least one stringer 180. Additionally or alternatively, and as Figure 3 and Figure 12 shown by the solid lines in, at least one stringer 180 can define or at least partially define an area 108 of the outer surface 106 of the modular airframe assembly 100. In other words, at least one stringer 180 can be at the skin mold line 174 of the corner skin 170.

[0051] In some instances, the plurality of airframe corners 110 can include a top corner 112, a bottom corner 114, a left corner 116, and a right corner 118, as Figure 2-7 collectively shown. In these instances, the plurality of stringers 180 can include a top left stringer 182, a top right stringer 184, a bottom left stringer 186, and a bottom right stringer 188. As shown, the top left stringer 182 can be operably connected to the top corner 112 and also connected to the left corner 116, and the top right stringer 184 can be operably connected to the top corner 112 and also connected to the right corner 118. Similarly, the bottom left stringer 186 can be operably connected to the bottom corner 114 and also connected to the left corner 116, and the bottom right stringer 188 can be operably connected to the bottom corner 114 and also connected to the right corner 118.

[0052] Within the scope of the present disclosure, the modular airframe assembly 100 according to the present disclosure can have a uniform, at least substantially uniform, constant, and / or at least substantially constant cross-sectional shape along the longitudinal length of the modular airframe assembly. Optionally, and as Figure 2-4 shown in FIGS. 13 - 15, the modular airframe assembly 100 can include two or more distinct or different regions. As discussed herein, these distinct regions can be formed and / or defined simply by replacing and / or modifying a given airframe corner 110 and / or a corresponding frame member 130 of a given airframe corner 110 and / or a portion or region of the corner skin 170, thereby allowing for quick, efficient, and / or cost-effective modification and / or assembly of the modular airframe assembly 100. Also as discussed herein, the replaced and / or modified portions of a given airframe corner 110 can modify the outer surface 120 of the modular airframe assembly 100 and / or the outer surface 120 of a given airframe corner without the need or necessity to change the shape of the cargo hold 104.

[0053] As an example, as Figure 2-4 shown in FIGS. 13 - 15, the modular fuselage assembly 100 can include a top corner 112 that includes both a top corner cargo area 122 and a top corner flight deck area 124. The top corner cargo area 122 can have and / or define a cargo area shape that is different from the flight deck area shape of the top corner flight deck area 124. As an example, the cross-sectional area of the modular fuselage assembly 100 measured within the top corner flight deck area 124 can be greater than the cross-sectional area of the modular fuselage assembly measured within the top corner cargo area 122. As another example, as shown in the figures, the cross-section of the top corner cargo area 122 can be uniform or at least substantially uniform along its longitudinal length. However, the cross-section of the top corner flight deck area 124 can vary along its longitudinal length.

[0054] As another example, as Figure 2 、 4 shown in FIGS. 14, the modular fuselage assembly 100 can include a wing receiving area 126 configured to receive the wing 30. The wing receiving area 126 can be formed and / or defined in and / or through at least one fuselage corner 110 of the modular fuselage assembly 100. The at least one fuselage corner 110 can include the top corner 112 and / or the bottom corner 114, and the modular fuselage assembly 100 can be configured such that the wing receiving area 126 does not extend into the cargo hold 104 and / or such that the cross-sectional shape of the cargo hold 104 area at least partially defined by the wing receiving area 126 is the same as or at least substantially the same as the cross-sectional shape of the rest of the cargo hold. Additionally or alternatively, the wing receiving area 126 can allow the wing 30 to penetrate the fuselage loft surface and reduce drag without interrupting or changing the structure of the stringer 180. Such a configuration can facilitate the manufacture of the modular fuselage assembly 100 and / or can allow the stringer 180 to be the primary structure for carrying or supporting longitudinal fuselage bending loads.

[0055] As Figure 3-4 the dashed lines in and Figure 5-7 the solid lines in shown, the modular fuselage assembly 100 can include a floor structure 230. The floor structure 230 can be operably connected to the bottom corner 114 of the modular fuselage assembly 100 and / or at least partially defined by the bottom corner 114 of the modular fuselage assembly 100, and can form and / or define a floor surface 232 that is configured to support crew, passengers, and / or cargo 80. As shown in the figures, the floor structure 230 and / or its floor surface 232 can at least partially bound and / or define the cargo hold 104.

[0056] Figure 16is a flow chart of a method 300 of depicting an assembled modular fuselage component (e.g., Figure 1-15 modular fuselage component 100). The method 300 includes providing a frame member at 310 and providing stringers at 320. The method 300 further includes operably connecting the frame member to the stringers at 330, and may include operably connecting corner skins at 340 and / or operably connecting additional structures at 350.

[0057] Providing a frame member at 310 may include providing a plurality of frame members, and examples of frame members are disclosed herein with reference to Figure 2-8 frame members 130 of FIGS. 11 - 12.

[0058] In some instances, providing a frame member at 310 may include providing a plurality of frame members as part of a plurality of fuselage corners or as a component defining a plurality of fuselage corners, and examples thereof are disclosed herein with reference to Figure 2-8 fuselage corners 110 of FIGS. 11 - 12. In these instances, each fuselage corner may include a subset of a plurality of frame members and corner skin. The corner skin may be operably connected to the subset of a plurality of frame members and may extend along an outer surface of each fuselage corner, may form and / or may define the outer surface of each fuselage corner. Examples of corner skin are disclosed herein with reference to Figure 2-7 corner skin 170 of FIGS. 11 - 12.

[0059] Providing stringers at 320 may include providing a plurality of stringers. Examples of stringers are disclosed herein with reference to Figure 2-8 stringers 180 of FIGS. 12.

[0060] Operably connecting the frame member to the stringers at 330 may include operably connecting each of the plurality of frame members to at least two of the plurality of stringers. This may include operably connecting such that the plurality of stringers extend along a longitudinal axis of the modular fuselage component and / or such that the plurality of frame members extend perpendicular to or at least substantially perpendicular to the longitudinal axis of the modular fuselage component.

[0061] When providing a frame member at 310 includes providing a plurality of frame members as part of a plurality of fuselage corners, the operable connection at 330 may include operably connecting at least two fuselage corners to each stringer. Additionally or alternatively, the operable connection at 330 may include operably connecting each fuselage corner to at least two stringers.

[0062] In some instances, providing the frame members at 310 can include providing a plurality of frame members independent of, separate from, and / or without the corner skins. In these instances, method 300 can further include operably connecting the corner skins at 340. Operably connecting the corner skins at 340 can be performed after the operable connection at 330 and / or can include operably connecting the corner skins to the outer surfaces of the plurality of frame members. This can include operably connecting to form and / or define the outer surface of a modular airframe assembly.

[0063] Operably connecting additional structures at 350 can include operably connecting any suitable additional structures to the modular airframe assembly in any suitable manner and / or in any suitable order. As an example, the operable connection at 350 can include operably connecting any suitable one and / or more structures that are disclosed, described, and / or illustrated herein as being operably connected to the modular airframe assembly and / or forming part of an aircraft including the modular airframe assembly. This can include operably connecting a suitable one and / or more structures to at least one of the plurality of frame members, to the plurality of frame members, to at least one of the plurality of stringers, and / or to the plurality of stringers.

[0064] Illustrative, non-exclusive examples of the inventive subject matter according to the present disclosure are described in the paragraphs listed below:

[0065] A1. A modular airframe assembly for an aircraft, the modular airframe assembly comprising:

[0066] A plurality of airframe corners extending along a longitudinal axis of the modular airframe assembly, wherein each airframe corner of the plurality of airframe corners comprises:

[0067] (i) A plurality of frame members; and

[0068] (ii) A corner skin operably connected to the plurality of frame members and defining an outer surface of each airframe corner; and

[0069] A plurality of stringers extending along the longitudinal axis of the modular airframe assembly;

[0070] Wherein at least two of the plurality of airframe corners are operably, or directly and operably, connected to each of the plurality of stringers; and

[0071] Wherein the plurality of airframe corners and the plurality of stringers at least partially define a cargo hold defined within the modular airframe assembly.

[0072] A2. The modular airframe assembly of paragraph A1, wherein the plurality of airframe corners include a top corner, a bottom corner, a left corner, and a right corner.

[0073] A3. The modular fuselage assembly in paragraph A2, wherein the plurality of longitudinal beams include:

[0074] (i) A left upper longitudinal beam, which is operatively or directly and operatively connected to the top corner and to the left corner;

[0075] (ii) A right upper longitudinal beam, which is operatively or directly and operatively connected to the top corner and to the right corner;

[0076] (iii) A left lower longitudinal beam, which is operatively or directly and operatively connected to the bottom corner and to the left corner; and

[0077] (iv) A right lower longitudinal beam, which is operatively or directly and operatively connected to the bottom corner and to the right corner.

[0078] A4. The modular fuselage assembly in any one of paragraphs A2 - A3, wherein the top corner includes a top corner cargo area defining the shape of the cargo area and a top corner flight deck area defining the shape of a flight deck area different from the shape of the cargo area.

[0079] A5. The modular fuselage assembly in paragraph A4, wherein the cross-sectional area of the modular fuselage assembly measured within the top flight deck area is greater than the cross-sectional area of the modular fuselage assembly measured within the top cargo area.

[0080] A6. The modular fuselage assembly in any one of paragraphs A1 - A5, wherein at least one of the plurality of fuselage corners further includes a wing receiving area configured to be operatively connected to an aircraft wing.

[0081] A7. The modular fuselage assembly in paragraph A6, wherein at least one of the fuselage corners includes at least one of the top corner and the bottom corner.

[0082] A8. The modular fuselage assembly in any one of paragraphs A1 - A7, wherein each of the plurality of frame members extends perpendicular to or at least substantially perpendicular to the longitudinal axis of the modular fuselage assembly.

[0083] A9. The modular fuselage assembly in any one of paragraphs A1 - A8, wherein at least one subset of the plurality of frame members includes compression members.

[0084] A10. The modular fuselage assembly in paragraph A9, wherein the compression members at least partially define the cargo hold.

[0085] A11. The modular fuselage assembly in any one of paragraphs A9 - A10, wherein the compression members include linear compression members.

[0086] A modular fuselage assembly in any one of paragraphs A9 - A11, wherein each frame member in at least a subset of the plurality of frame members includes a tension member.

[0087] A13. The modular fuselage assembly of paragraph A12, wherein the compression member includes a first compression member end and a second compression member end, and further wherein the tension member includes a first tension member end and a second tension member end, wherein the first tension member end is operatively, or directly and operatively, connected to the first compression member end, and the second tension member end is operatively or directly and operatively connected to the second compression member end.

[0088] A14. The modular fuselage assembly of paragraph A13, wherein the tension member is an arcuate tension member.

[0089] A15. The modular fuselage assembly of paragraph A14, wherein the arcuate tension member is shaped such that each fuselage corner defines a convex outer surface.

[0090] A16. The modular fuselage assembly in any one of paragraphs A13 - A15, wherein the tension member is operatively or directly and operatively connected to the corner skin.

[0091] A17. The modular fuselage assembly in any one of paragraphs A12 - A16, wherein each frame member further includes a frame member support structure configured to operatively interconnect the compression member and the tension member to increase the rigidity of each frame member.

[0092] A18. The modular fuselage assembly of paragraph A17, wherein the frame member support structure includes at least one of the following:

[0093] (i) A strut, optionally wherein the strut extends between the compression member and the tension member and is operatively or directly and operatively connected to the compression member and the tension member;

[0094] (ii) A plurality of struts, optionally wherein each strut of the plurality of struts extends between the compression member and the tension member and is operatively or directly and operatively connected to the compression member and the tension member;

[0095] (iii) A truss, optionally wherein the truss extends between the compression member and the tension member and is operatively or directly and operatively connected to the compression member and the tension member;

[0096] (iv) A triangular truss, optionally wherein the triangular truss extends between the compression member and the tension member and is operatively or directly and operatively connected to the compression member and the tension member; and

[0097] (v) A Warren truss, optionally where the Warren truss extends between a compression member and a tension member and is operatively or directly and operatively connected to the compression member and the tension member.

[0098] A19. The modular fuselage assembly in any one of paragraphs A1 - A18, wherein at least one subset of the plurality of frame members includes at least one of the following:

[0099] (i) A single-piece frame member;

[0100] (ii) A monolithic frame member; and

[0101] (iii) An integral frame member.

[0102] A20. The modular fuselage assembly in any one of paragraphs A1 - A19, wherein at least one subset of the plurality of frame members includes at least one of the following:

[0103] (i) A stamped metal frame member defined by a metal sheet; and

[0104] (ii) A roll-formed metal frame member defined by a metal sheet.

[0105] A21. The modular fuselage assembly in any one of paragraphs A1 - A20, wherein the plurality of stringers includes at least one of the following:

[0106] (i) A single-piece stringer;

[0107] (ii) A monolithic stringer; and

[0108] (iii) An integral stringer.

[0109] A22. The modular fuselage assembly in any one of paragraphs A1 - A21, wherein the plurality of stringers includes a composite stringer defined by a plurality of stringer substructures.

[0110] A23. The modular fuselage assembly of paragraph A22, wherein each stringer substructure of the plurality of stringer substructures is operatively connected to other stringer substructures of the plurality of stringer substructures, optionally using a plurality of stringer fasteners.

[0111] A31. The modular fuselage assembly in any one of paragraphs A1 - A30, wherein at least two fuselage corners are operatively connected to each stringer by a plurality of corner fasteners.

[0112] A32. The modular fuselage assembly in any one of paragraphs A1 - A31, wherein the modular fuselage assembly further includes a longitudinal support structure that extends along at least a portion, and optionally the entire length, of the longitudinal axis of the modular fuselage assembly.

[0113] A33. The modular fuselage assembly of paragraph A32, wherein the longitudinal support structure is operably connected to a plurality of frame members within a given fuselage corner of the plurality of fuselage corners.

[0114] A34. The modular fuselage assembly of any one of paragraphs A32 - A33, wherein the longitudinal support structure includes a plurality of support strips.

[0115] A35. The modular fuselage assembly of paragraph A34, wherein the plurality of support strips extend at an inclined angle relative to the longitudinal axis of the modular fuselage assembly.

[0116] A36. The modular fuselage assembly of any one of paragraphs A32 - A35, wherein the longitudinal support structure at least partially defines a cargo hold.

[0117] A37. The modular fuselage assembly of any one of paragraphs A1 - A36, wherein the modular fuselage assembly further includes a crane rail and a cargo transport structure operably connected to the crane rail and configured to move cargo within the cargo hold and along the longitudinal axis of the modular fuselage assembly.

[0118] A38. The modular fuselage assembly of paragraph A37, wherein the cargo transport structure includes a rail trolley configured to roll along the crane rail.

[0119] A39. The modular fuselage assembly of any one of paragraphs A37 - A38, wherein the crane rail is at least one of the following:

[0120] (i) operably connected to at least one of the plurality of longitudinal beams; and

[0121] (ii) defined by at least one of the plurality of longitudinal beams.

[0122] A40. The modular fuselage assembly of any one of paragraphs A1 - A39, wherein the plurality of fuselage corners include a bottom corner, and further wherein the modular fuselage assembly includes a floor structure operably connected to the plurality of frame members of the bottom corner.

[0123] A41. The modular fuselage assembly of paragraph A40, wherein the floor structure at least partially defines a cargo hold.

[0124] A42. An aircraft, comprising:

[0125] The modular fuselage assembly of any one of paragraphs A1 - A41; and

[0126] At least one of the following:

[0127] (i) a wing operably connected to the modular fuselage assembly;

[0128] (ii) A tail assembly operably connected to the modular fuselage assembly;

[0129] (iii) A vertical stabilizer operably connected to the modular fuselage assembly;

[0130] (iv) A horizontal stabilizer operably connected to the modular fuselage assembly; and

[0131] (v) An engine operably connected to the modular fuselage assembly.

[0132] B1. A method of assembling a modular fuselage assembly, the method comprising:

[0133] Providing a plurality of frame members;

[0134] Providing a plurality of stringers; and

[0135] Operably connecting each of the plurality of frame members to at least two of the plurality of stringers such that the plurality of stringers extend along the longitudinal axis of the modular fuselage assembly.

[0136] The method of paragraph B1, wherein providing a plurality of frame members comprises providing a plurality of frame members as part of a plurality of fuselage corners, each of the plurality of fuselage corners comprising:

[0137] (i) A subset of the plurality of frame members; and

[0138] (ii) A corner skin operably connected to the subset of the plurality of frame members and extending along the outer surface of each fuselage corner.

[0139] The method of paragraph B2, wherein operably connecting comprises operably connecting at least two of the plurality of fuselage corners to each of the plurality of stringers.

[0140] The method of any one of paragraphs B2 - B3, wherein operably connecting comprises operably connecting each of the plurality of fuselage corners to at least two of the plurality of stringers.

[0141] The method of any one of paragraphs B1 - B4, wherein after operably connecting each frame member, the method further comprises operably connecting the corner skin to the outer surface of the plurality of frame members.

[0142] The method of any one of paragraphs B1 - B5, wherein operably connecting comprises operably connecting each frame member such that the plurality of frame members extend perpendicular to or at least substantially perpendicular to the longitudinal axis of the fuselage assembly.

[0143] A method in any one of paragraphs B1 - B6, wherein the modular fuselage assembly comprises any suitable structure of any modular fuselage assembly in any one of paragraphs A1 - A41.

[0144] B8. A method in any one of paragraphs B1 - B7, wherein the method further comprises operably connecting any suitable structure of any modular fuselage assembly in any one of paragraphs A1 - A41 to at least one of the following:

[0145] (i) At least one frame member among a plurality of frame members;

[0146] (ii) A plurality of frame members;

[0147] (iii) At least one stringer among a plurality of stringers; and

[0148] (iv) A plurality of stringers.

[0149] C1. Use of any modular fuselage assembly in any one of paragraphs A1 - A41 in conjunction with any method in any one of paragraphs B1 - B8.

[0150] C2. Use of any method in any one of paragraphs B1 - B8 in conjunction with any modular fuselage assembly in any one of paragraphs A1 - A41.

[0151] C3. Use of a plurality of fuselage corners and a plurality of stringers for defining a modular fuselage assembly.

[0152] C4. Use of a plurality of frame members and corner skins for defining the fuselage corners of a modular fuselage assembly.

[0153] D1. A modular fuselage assembly for an aircraft, the modular fuselage assembly comprising:

[0154] A plurality of fuselage corners extending along the longitudinal axis of the modular fuselage assembly, wherein each fuselage corner among the plurality of fuselage corners comprises:

[0155] (i) A plurality of frame members; and

[0156] (ii) A corner skin operably connected to the plurality of frame members and defining the outer surface of each fuselage corner; and

[0157] A plurality of stringers extending along the longitudinal axis of the modular fuselage assembly;

[0158] Wherein at least two fuselage corners among the plurality of fuselage corners are operably connected to each stringer among the plurality of stringers; and

[0159] Wherein the plurality of fuselage corners and the plurality of stringers at least partially define a cargo hold defined within the modular fuselage assembly.

[0160] D2. The modular fuselage assembly of paragraph D1, wherein the plurality of fuselage corners include a top corner, a bottom corner, a left corner, and a right corner, and further wherein the plurality of stringers include:

[0161] (i) A left upper stringer operably connected to the top corner and the left corner;

[0162] (ii) A right upper stringer operably connected to the top corner and the right corner;

[0163] (iii) A left lower stringer operably connected to the bottom corner and the left corner; and

[0164] (iv) A right lower stringer operably connected to the bottom corner and the right corner.

[0165] D3. The modular fuselage assembly of paragraph D2, wherein the top corner includes: a top corner cargo area and a top corner flight deck area, the top corner cargo area defining a cargo area shape, and the top corner flight deck area defining a flight deck area shape different from the cargo area shape.

[0166] D4. The modular fuselage assembly of paragraph D1, wherein at least one of the plurality of fuselage corners further includes a wing receiving area configured to be operably connected to an aircraft wing.

[0167] D5. The modular fuselage assembly of paragraph D1, wherein each of the plurality of frame members extends at least substantially perpendicular to the longitudinal axis of the modular fuselage assembly.

[0168] D6. The modular fuselage assembly of paragraph D1, wherein at least one subset of the plurality of frame members includes compression members that at least partially define a cargo hold.

[0169] D7. The modular fuselage assembly of paragraph D6, wherein each of the frame members in at least the subset of the plurality of frame members further includes a tension member.

[0170] D8. The modular fuselage assembly of paragraph D7, wherein the compression member includes a first compression member end and a second compression member end, and wherein the tension member includes a first tension member end and a second tension member end, the first tension member end being operably connected to the first compression member end, and the second tension member end being operably connected to the second compression member end, and further wherein the tension member is an arcuate tension member shaped such that each fuselage corner defines a convex outer surface.

[0171] D9. The modular fuselage assembly of paragraph D7, wherein the tension member is directly and operably connected to the corner skin.

[0172] D10. The modular fuselage assembly in paragraph D7, wherein each frame member further includes a frame member support structure configured to operably interconnect a compression member and a tension member to increase the rigidity of each frame member.

[0173] D11. The modular fuselage assembly in paragraph D10, wherein the frame member support structure includes at least one of the following:

[0174] (i) A strut, wherein the strut extends between the compression member and the tension member and is operably connected to the compression member and the tension member;

[0175] (ii) A plurality of struts, wherein each strut in the plurality of struts extends between the compression member and the tension member and is operably connected to the compression member and the tension member;

[0176] (iii) A truss, wherein the truss extends between the compression member and the tension member and is operably connected to the compression member and the tension member;

[0177] (iv) A triangular truss, wherein the triangular truss extends between the compression member and the tension member and is operably connected to the compression member and the tension member; and

[0178] (v) A Warren truss, wherein the Warren truss extends between the compression member and the tension member and is operably connected to the compression member and the tension member.

[0179] D12. The modular fuselage assembly in paragraph D1, wherein the plurality of stringers includes at least one of the following:

[0180] (i) A single-piece stringer;

[0181] (ii) A monolithic stringer; and

[0182] (iii) An integral stringer.

[0183] D13. The modular fuselage assembly in paragraph D1, wherein the plurality of stringers includes a composite stringer defined by a plurality of stringer sub-structures.

[0184] D14. The modular fuselage assembly in paragraph D1, wherein the corner skin includes an integral corner skin extending along the entire longitudinal axis of the modular fuselage assembly.

[0185] D15. The modular fuselage assembly in paragraph D1, wherein the corner skin includes a plurality of sub-skins, and each sub-skin in the plurality of sub-skins is operably connected to at least two of the plurality of frame members.

[0186] The modular fuselage assembly of paragraph D1, wherein at least two fuselage corners are operably connected to each longitudinal beam by a plurality of corner fasteners.

[0187] D17. The modular fuselage assembly of paragraph D1, wherein the modular fuselage assembly further includes a longitudinal support structure that extends along at least a portion of the longitudinal axis of the modular fuselage assembly.

[0188] D18. The modular fuselage assembly of paragraph D17, wherein the longitudinal support structure is operably connected to a plurality of frame members within the corners of a given fuselage of the plurality of fuselage corners.

[0189] D19. The modular fuselage assembly of paragraph D1, wherein the modular fuselage assembly further includes a crane rail and a cargo transport structure operably connected to the crane rail and configured to move cargo within the cargo hold and along the longitudinal axis of the modular fuselage assembly.

[0190] D20. A method of assembling the modular fuselage assembly of paragraph D1, the method comprising:

[0191] Providing a plurality of frame members;

[0192] Providing a plurality of longitudinal beams; and

[0193] Operably connecting each of the plurality of frame members to at least two of the plurality of longitudinal beams such that the plurality of longitudinal beams extend along the longitudinal axis of the modular fuselage assembly.

[0194] As used herein, when modifying an action, movement, configuration, or other activity of one or more components or features of a device, the terms "selective" and "selectively" mean that the specific action, movement, configuration, or other activity is an aspect of the user operating the device or a direct or indirect result of one or more components.

[0195] As used herein, the terms "adapted" and "configured" mean that an element, component, or other subject is designed and / or intended to perform a given function. Thus, the use of the terms "adapted" and "configured" should not be construed to mean that a given element, component, or other subject is merely "able to" perform the given function, but rather that the element, component, and / or other subject has been specifically selected, created, implemented, utilized, programmed, and / or designed to perform that function. Also within the scope of this disclosure, an element, component, and / or other recited subject that is recited as being adapted to perform a specific function may additionally or alternatively be described as being configured to perform that function, and vice versa. Similarly, a subject that is recited as being configured to perform a specific function may additionally or alternatively be described as being operable to perform that function.

[0196] As used herein, the phrase "at least one" with respect to a list of one or more entities shall be understood to mean at least one entity selected from any one or more of the entities in the list of entities, but not necessarily including at least one of each of the entities specifically listed in the list of entities, and not excluding any combination of the entities in the list of entities. This definition also allows for the optional presence of entities, whether related or unrelated to those specifically identified, in addition to the entities specifically identified within the list of entities referred to by the phrase "at least one". Thus, as a non-limiting example, "at least one of A and B" (or equivalently "at least one of A or B", or equivalently "at least one of A and / or B") can mean, in one embodiment, at least one A where B is absent, optionally including more than one A (and optionally including entities other than B); in another embodiment, at least one B where A is absent, optionally including more than one B (and optionally including entities other than A); in still another embodiment, at least one A, optionally including more than one A, and at least one B, optionally including more than one B (and optionally including other entities). In other words, the phrases "at least one", "one or more", and "and / or" are open-ended expressions that are both conjunctive and disjunctive in operation. For example, each of the expressions "at least one of A, B, and C", "at least one of A, B, or C", "one or more of A, B, and C", "one or more of A, B, or C", and "A, B, and / or C" can mean A alone, B alone, C alone, A and B together, A and C together, B and C together, A, B, and C together, and optionally any one of the foregoing in combination with at least one other entity.

[0197] Not all of the devices and methods in accordance with the present disclosure require the various elements of the devices and steps of the methods disclosed herein, and the present disclosure includes all novel and non-obvious combinations and sub-combinations of the various elements and steps disclosed herein. In addition, one or more of the various elements and steps disclosed herein can define an independent inventive subject matter that is independent and separate from the overall disclosed device or method. Thus, it is not necessary to associate such inventive subject matter with the specific devices and methods explicitly disclosed herein, and such inventive subject matter can find utility in devices and / or methods not explicitly disclosed herein.

[0198] As used herein, when referring to one or more components, features, details, structures, embodiments, and / or methods in accordance with the present disclosure, the phrase "for example," the phrase "as an instance," and / or merely the term "instance" are intended to convey that the components, features, details, structures, embodiments, and / or methods described in accordance with the present disclosure are illustrative, non-exclusive instances of components, features, details, structures, embodiments, and methods. Accordingly, the components, features, details, structures, embodiments, and / or methods described are not intended to be limiting, required, or exclusive / exhaustive; and other components, features, details, structures, embodiments, and / or methods that are structurally and / or functionally similar and / or equivalent are also within the scope of the present disclosure.

[0199] As used herein, when modifying a degree or relationship, "at least substantially" can include not only the recited "substantially" degree or relationship, but also the entire range of the recited degree or relationship. The substantially amount of the recited degree or relationship can include at least 75% of the recited degree or relationship. For example, an object formed at least substantially of a material includes an object in which at least 75% of the object is formed of the material, and also includes an object formed entirely of the material. As another example, a first length that is at least substantially as long as a second length includes a first length within 75% of the second length, and also includes a first length that is as long as the second length.

[0200] As used herein, the phrase "operably connected" can mean that two structures, members, and / or components can be connected to each other and / or mechanically coupled to each other. Within the scope of the present disclosure, the phrase "operably connected" can refer to two structures that are mechanically coupled to each other such that the two structures are in contact with each other, physically in contact with each other, and / or directly in contact with each other. In such an instance, the two structures can also be referred to herein as being "directly and operably connected" to each other. Within the scope of the present disclosure, the phrase "operably connected" can refer to two structures that are mechanically coupled to each other via one or more intermediate structures and / or such that the two structures are not in contact with each other, not physically in contact with each other, and / or not directly in contact with each other. In such an instance, the two structures can also be referred to herein as being "indirectly and operably connected" to each other.

Claims

1. A modular fuselage assembly for an aircraft, the modular fuselage assembly comprising: a plurality of fuselage corners extending along a longitudinal axis of the modular fuselage assembly, wherein each fuselage corner of the plurality of fuselage corners comprises: (i) a plurality of frame members; and (ii) a corner skin operably connected to the plurality of frame members and defining an outer surface of each fuselage corner; and a plurality of stringers extending along the longitudinal axis of the modular fuselage assembly; wherein at least two fuselage corners of the plurality of fuselage corners are operably connected to each stringer of the plurality of stringers; wherein the plurality of fuselage corners and the plurality of stringers at least partially define a cargo hold defined within the modular fuselage assembly; wherein at least one subset of the plurality of frame members comprises compression members that at least partially define the cargo hold; wherein each frame member of at least the subset of the plurality of frame members further comprises a tension member; and wherein each frame member further comprises a frame member support structure configured to operably interconnect the compression member and the tension member to increase the rigidity of each frame member.

2. The modular fuselage assembly according to claim 1, wherein the plurality of fuselage corners comprises a top corner, a bottom corner, a left corner, and a right corner, and further wherein the plurality of stringers comprises: (i) a left upper stringer operably connected to the top corner and to the left corner; (ii) a right upper stringer operably connected to the top corner and to the right corner; (iii) a left lower stringer operably connected to the bottom corner and to the left corner; and (iv) a right lower stringer operably connected to the bottom corner and to the right corner.

3. The modular fuselage assembly according to claim 2, wherein the top corner comprises a top corner cargo area defining a shape of a cargo area and a top corner flight deck area defining a shape of a flight deck area different from the shape of the cargo area.

4. The modular fuselage assembly according to claim 1, wherein at least one fuselage corner of the plurality of fuselage corners further comprises a wing receiving area configured to operably connect to an aircraft wing.

5. The modular fuselage assembly according to claim 1, wherein each frame member of the plurality of frame members extends at least substantially perpendicular to the longitudinal axis of the modular fuselage assembly.

6. The modular fuselage assembly according to claim 1, wherein the compression member comprises a first compression member end and a second compression member end, wherein the tension member comprises a first tension member end and a second tension member end, wherein the first tension member end is operably connected to the first compression member end, the second tension member end is operably connected to the second compression member end, and further wherein the tension member is an arcuate tension member shaped such that each fuselage corner defines a convex outer surface.

7. The modular fuselage assembly according to claim 1, wherein the tension member is directly and operably connected to the corner skin.

8. The modular fuselage assembly according to claim 1, wherein the frame member support structure includes at least one of the following: (i) a strut, wherein the strut extends between the compression member and the tension member and is operatively connected to the compression member and the tension member; (ii) a plurality of struts, wherein each of the plurality of struts extends between the compression member and the tension member and is operatively connected to the compression member and the tension member; (iii) a truss, wherein the truss extends between the compression member and the tension member and is operatively connected to the compression member and the tension member; (iv) a triangular truss, wherein the triangular truss extends between the compression member and the tension member and is operatively connected to the compression member and the tension member; and (v) a Warren truss, wherein the Warren truss extends between the compression member and the tension member and is operatively connected to the compression member and the tension member.

9. The modular fuselage assembly according to claim 1, wherein the plurality of stringers includes at least one of the following: (i) a single-piece stringer; (ii) an integral stringer; and (iii) a monolithic stringer.

10. The modular fuselage assembly according to claim 1, wherein the plurality of stringers includes a composite stringer defined by a plurality of stringer sub-structures.

11. The modular fuselage assembly according to claim 1, wherein the corner skin includes a monolithic corner skin extending along the entire longitudinal axis of the modular fuselage assembly.

12. The modular fuselage assembly according to claim 1, wherein the corner skin includes a plurality of sub-skins, and each of the plurality of sub-skins is operatively connected to at least two of the plurality of frame members.

13. The modular fuselage assembly according to claim 1, wherein the at least two fuselage corners are operatively connected to each stringer by a plurality of corner fasteners.

14. The modular fuselage assembly according to claim 1, wherein the modular fuselage assembly further includes a longitudinal support structure that extends along at least a portion of the longitudinal axis of the modular fuselage assembly.

15. The modular fuselage assembly according to claim 14, wherein the longitudinal support structure is operatively connected to the plurality of frame members within a given fuselage corner of the plurality of fuselage corners.

16. The modular fuselage assembly according to claim 1, wherein the modular fuselage assembly further includes a crane rail and a cargo transport structure, the cargo transport structure being operatively connected to the crane rail and configured to move cargo within the cargo hold and along the longitudinal axis of the modular fuselage assembly.

17. A method of assembling the modular fuselage assembly according to claim 1, the method comprising: providing the plurality of frame members; providing the plurality of stringers; and Operably connect each of the plurality of frame members to at least two of the plurality of stringers such that the plurality of stringers extend along the longitudinal axis of the modular fuselage assembly.

18. An aircraft, comprising: The modular fuselage assembly according to claim 1; And At least one of the following: (i) A wing operably connected to the modular fuselage assembly; (ii) A tail assembly operably connected to the modular fuselage assembly; (iii) A vertical stabilizer operably connected to the modular fuselage assembly; (iv) A horizontal stabilizer operably connected to the modular fuselage assembly; And (v) An engine operably connected to the modular fuselage assembly.

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