Aircraft assembly formed from mated half-cylinder segments and method of assembly

Abstract

The invention relates to aircraft assemblies formed from mated half-cylinder segments and methods of assembling the same. The method includes receiving half-cylinder segments of a fuselage, advancing the half-cylinder segments in a processing direction across a plurality of work stations to separately and simultaneously work on the half-cylinder segments, and subsequently joining the half-cylinder segments to form a segment of the fuselage. Each pair of half-cylinder segments, such as an upper half-cylinder and a lower half-cylinder, advances through an assembly line process to be delivered to a joining station for joining the half-cylinders together to form a circumferential segment of the fuselage. A plurality of joined circumferential segments are joined together to form an elongate extent of the fuselage. Indexing features are provided during the assembly process to monitor and control the progress of the half-cylinder segments through the work stations of the assembly line process, and optionally to direct the half-cylinder segments to auxiliary work stations or to delay progress through the assembly line to provide additional work on one of the half-cylinders as needed, and to ensure proper timing of the half-cylinder segments to the joining station.

Description

Technical Field

[0001] This disclosure relates to the field of aircraft, and more specifically to the manufacture of aircraft. Background Technology

[0002] In the aerospace industry, operations related to the transport and assembly of airframe components are performed in fixed cells. Within each cell, the structure is scanned and / or rotated into the cell, and then tools, equipment, and / or workers are brought to the portion of the structure that needs to be processed within that cell. Each time a new structure is brought to the cell, the scanning and / or rotation process is repeated. Furthermore, when a structure is moved to the next cell, it is scanned and / or rotated into the cell again, and the necessary tools, equipment, and / or workers are brought to the portion of the structure that needs to be processed within that cell. Current assembly methods require tools, fixtures, and technicians to enter the semi-cylindrical section through the end of the cylinder or a doorway. The tooling and fixtures must be positioned appropriately within the complete cylindrical section. When the work is completed, the tooling, fixtures, and technicians must be transported through the end of the cylinder or a doorway.

[0003] The abstract of US2013 / 019446 describes "a method for properly positioning multiple assembly panels by means of machine data relative to a data pattern representing an assembly table, using a machine to drill full-size holes near the second skin edge of the panels, using a machine to clean the second edge of the panels, and then using an auxiliary machine to use the full-size holes near the second skin edge as alignment features to properly orient and attach the panel pairs together near the first skin edge opposite the second skin edge, forming a panel pair. The control system can be installed individually and independently into the panel pairs, and then the panel pairs can be joined together so that the full-size holes near the second edge are aligned, and fasteners are inserted through the aligned full-size holes near the second skin edge."

[0004] The abstract of EP3272454 describes that "the production facility is equipped with: AGVs for conveying various body panels of different shapes, mixed on a pre-defined conveyor path; multiple A / Rs for riveting the body panels; work areas set to correspond to the respective A / Rs and in which the A / Rs move to rivet the body panels; and buffer areas pre-set in the conveyor paths adjacent to the work areas, in which the A / Rs corresponding to the adjacent work areas move to rivet the body panels. When no body panel is riveted in the work area of ​​the adjacent buffer area and there is a body panel to be riveted in the buffer area, the control device moves the A / R corresponding to the work area of ​​the adjacent buffer area to the buffer area and rivets the body panel. Therefore, the production facility can efficiently process workpieces even when continuously processing multiple workpieces of different shapes." Summary of the Invention

[0005] Therefore, it is desirable to have methods and apparatus that take into account at least some of the problems discussed above, in order to provide a manufacturing process with enhanced accessibility for skilled workers, and a final structure with desired design features.

[0006] The embodiments described herein provide continuous assembly line layouts and systems that enable operations on moving fuselage components that continuously pulsate or move in a processing direction to intersect paths at workstations where operations are performed on the fuselage components. These operations may include laying prefabricated components to harden into composite parts, hardening composite parts in an autoclave, installing frames, cutting holes for windows or doors, etc. These arrangements offer technical benefits over existing systems because they reduce the amount of space required for manufacturing and assembly in a factory shop floor, increase throughput, and reduce downtime.

[0007] One embodiment is a system that enables the manufacture of fuselage sections in a continuous assembly line for producing upper and lower semi-cylinders that are subsequently joined together, for example using a butt joint with a splicing plate. The work on the semi-cylinder sections is facilitated by positioning the inverted sections on a mandrel to improve accessibility to tools and the work being performed. The system includes: at least a portion of the assembly line for indexing the semi-cylinder sections; a processor for assisting in monitoring and controlling the advance of the sections along the assembly line; and a processor for coordinating the advance of the upper and lower semi-cylinders to provide the semi-cylinder sections to a joining station for producing specific segments of the fuselage. Subsequent processes are used to join the individual segments into a fuselage using circumferential joining of the sections.

[0008] Another embodiment is a fuselage structure formed by segments of the fuselage, which are formed by mating semi-cylinders joined together to form circumferential sections. In a preferred embodiment, upper and lower semi-cylinders form each segment of the fuselage, wherein the upper and lower semi-cylinders pass along an assembly line for component assembly and other manufacturing processes necessary to produce substantially complete semi-cylinders, thus minimizing the manufacturing steps required within each circumferential segment of the fuselage.

[0009] According to one aspect of this disclosure, a method for assembling the fuselage of an aircraft includes: receiving a semi-cylindrical section of the fuselage; advancing the semi-cylindrical section in a processing direction across a plurality of workstations at a time; and simultaneously operating the semi-cylindrical section via the plurality of workstations.

[0010] Advantageously, the method includes: advancing the semi-cylindrical section via an assembly line.

[0011] Preferably, the method further includes advancing multiple semi-cylindrical sections across the multiple workstations in the processing direction.

[0012] Preferably, in the method, the plurality of workstations operate on the semi-cylindrical section during the same pause between micro-pulses in the processing direction.

[0013] Preferably, the method further includes: causing the semi-cylindrical section to micro-pulse through the plurality of workstations according to a common takt time, wherein the common takt time is based on the expected number of semi-cylindrical sections produced per month.

[0014] Preferably, the method further includes indexing the semi-cylindrical section to at least one work station during the pause between micropulses.

[0015] Preferably, the method further includes: performing operations on the semi-cylindrical section during pauses between micro-pulsations in the processing direction.

[0016] Preferably, the method further includes: operating the semi-cylindrical section during micro-pulsations between pauses in the processing direction.

[0017] Preferably, the method further includes: as the semi-cylindrical section advances to the work station, delivering the component to one of the work stations, and engaging the component to the semi-cylindrical section at the work station.

[0018] Preferably, in the method, the components are delivered to the workstations in a Just-In-Time (JIT) manner according to the order in which the workstations are used.

[0019] Preferably, the method further includes engaging the component to the semi-cylindrical section during a pause between micropulses.

[0020] Preferably, in the method, advancing the semi-cylindrical section includes moving the semi-cylindrical section through the plurality of working stations, the distance between the plurality of working stations being less than the length of the semi-cylindrical section.

[0021] Preferably, in the method, the distance between the workstations is equal to a multiple of the frame spacing of the semi-cylindrical section.

[0022] Preferably, in the method, performing the work includes operating the plurality of workstations independently of each other.

[0023] Preferably, in the method, multiple of the plurality of workstations remove material from the semi-cylindrical section.

[0024] Preferably, in the method, multiple workstations add material to the semi-cylindrical section.

[0025] Preferably, in the method, the work is selected from the group consisting of: frame installation, window surround installation, door surround installation, door manufacturing allowance trimming and removal, window manufacturing allowance trimming and removal, support edge allowance trimming, sealing, non-destructive inspection (NDI) of the semi-cylindrical section, non-destructive inspection (NDI) of the edge after separation of manufacturing allowance or window manufacturing allowance or door manufacturing allowance, and cleaning.

[0026] Preferably, the method further includes: joining the semi-cylindrical section to another semi-cylindrical section.

[0027] Preferably, the method further includes: operating the feeder line for the plurality of workstations according to the cycle time of the semi-cylindrical section.

[0028] Preferably, in the method, each feeder has a common beat time equal to or a portion of the fuselage beat time.

[0029] According to one aspect of this disclosure, the aircraft includes a fuselage having an elongated length between its ends, wherein at least a portion of the length of the fuselage is formed by semi-cylindrical sections joined together at a plurality of docking joints.

[0030] Advantageously, in the fuselage, at least one of the said semi-cylindrical sections of the fuselage is formed by an upper semi-cylindrical section and a lower semi-cylindrical section, the upper semi-cylindrical section and the lower semi-cylindrical section being assembled with components and respectively joined to form a uniform cylindrical section and a non-uniform cylindrical section.

[0031] Preferably, in the fuselage, at least two of the uniform cylindrical sections and non-uniform cylindrical sections of the fuselage are joined together along a circumferential joint.

[0032] Preferably, in the body, the joined upper and lower cylindrical sections include butt joints with supporting edges of splicing plates, which are fixed to the upper and lower cylindrical sections by fasteners.

[0033] Preferably, in the body, the location of the fasteners includes a row of fasteners located on each of the upper and lower cylindrical sections.

[0034] Preferably, in the body, two rows of fasteners are positioned on each of the upper and lower semi-cylindrical sections.

[0035] Preferably, in the machine body, the product is assembled by a process in which each semi-cylindrical section advances through multiple work stations that perform operations on the semi-cylindrical section before it is connected to a mating semi-cylindrical section.

[0036] Preferably, within the machine body, each mating semi-cylindrical segment is assembled by advancing through multiple workstations, which are used to simultaneously perform assembly operations on the semi-cylindrical segments to be mated before engagement.

[0037] Preferably, in the fuselage, each semi-cylindrical section includes a semi-cylindrical body and at least one component fixed to the semi-cylindrical section before being engaged with the corresponding semi-cylindrical section.

[0038] According to one aspect of this disclosure, a system for assembling the fuselage of an aircraft includes: an assembly line including a track that receives a semi-cylindrical section of the fuselage and advances the semi-cylindrical section along the assembly line in a processing direction; and workstations arranged along the track in the processing direction at a distance less than the length of the semi-cylindrical section, such that at least one of the workstations can perform a single operation on the semi-cylindrical section.

[0039] Advantageously, in the system, the semi-cylindrical section advances through multiple workstations in the processing direction, and the multiple workstations perform operations on the semi-cylindrical section at one time.

[0040] Preferably, in the system, the work performed at the workstation is selected from the group consisting of: frame installation, window installation, door installation, trimming, sealing, non-destructive inspection (NDI) of the semi-cylindrical section, non-destructive inspection (NDI) of trimmed edges, and cleaning.

[0041] Preferably, in the system, the work station performs work on one of the semi-cylindrical sections during pauses in the processing direction between micro-pulses of the semi-cylindrical sections.

[0042] Preferably, in the system, components are delivered to the workstation in just-in-time (JIT) manner according to their usage sequence.

[0043] Preferably, the system further includes a feeder, the cycle time of which is equal to a fraction of the fuselage cycle time.

[0044] Preferably, in the system, the distance is equal to the frame spacing in the processing direction.

[0045] Preferably, in the system, the work station removes material from the semi-cylindrical section.

[0046] Preferably, in the system, the semi-cylindrical section includes both an upper semi-cylindrical section and a lower semi-cylindrical section.

[0047] Preferably, in the system, multiple workstations remove material from the semi-cylindrical section.

[0048] Preferably, in the system, multiple workstations add material to the semi-cylindrical section.

[0049] Use the above system to manufacture a part of the aircraft.

[0050] According to one aspect of this disclosure, a method of manufacturing an aircraft includes: advancing a series of semi-cylindrical sections through a series of workstations at a common takt time; delivering a first type of sub-component together with a second type of sub-component produced in parallel with the first type of sub-component to the workstations in a just-in-time production manner; and joining the sub-components to the semi-cylindrical sections.

[0051] Advantageously, in the method, the sub-component is delivered according to a clock cycle time equal to or a portion of the fuselage clock cycle time.

[0052] Preferably, in the method, the work station operates on the semi-cylindrical section during the same pause in the processing direction between the micro-pulses of the semi-cylindrical section.

[0053] Preferably, in the method, the sub-components are delivered to the workstation in a just-in-time (JIT) manner and in the order of use.

[0054] Preferably, the method further includes: simultaneously operating the semi-cylindrical section via one or more workstations.

[0055] Preferably, in the method, advancing includes: making the iterative micro-pulsations of the semi-cylindrical segment smaller than the length of the semi-cylindrical segment, and then pausing while working on the semi-cylindrical segment.

[0056] Preferably, the method further includes advancing, which includes: iteratively micro-pulsating the semi-cylindrical section at least the length of the semi-cylindrical section, and then pausing while working on the semi-cylindrical section.

[0057] Preferably, the method further includes advancing, which includes continuously moving the semi-cylindrical section while performing work on the semi-cylindrical section.

[0058] Preferably, the method further includes connecting the sub-component and the semi-cylindrical section together at the work station after micro-pulsation.

[0059] Preferably, the method further includes joining two semi-cylindrical sections to form a complete cylindrical section.

[0060] Preferably, in the method, multiple workstations remove material from the sub-component.

[0061] A part of an aircraft assembled according to the method described above.

[0062] According to one aspect of this disclosure, a method for assembling the fuselage of an aircraft includes: receiving a semi-cylindrical segment of the fuselage in an assembly line; attaching a splicing plate to the semi-cylindrical segment; aligning the semi-cylindrical segment and the attached splicing plate to another semi-cylindrical segment; and joining the semi-cylindrical segments together via the splicing plate.

[0063] Advantageously, in the method, joining two semi-cylindrical sections includes butt-jointing each semi-cylindrical section together.

[0064] Preferably, in the method, the splicing plate is mounted on the inner mold line (IML) of the semi-cylindrical section.

[0065] Preferably, in the method, the splicing plate is mounted on the outer mold line (OML) of the semi-cylindrical section.

[0066] Preferably, in the method, at least one splicing plate is at least partially installed on the upper semi-cylindrical section, and at least one splicing plate is at least partially installed on the lower semi-cylindrical section.

[0067] Preferably, in the method, the splicing plate is installed at the assembly line through which the semi-cylindrical section passes.

[0068] Preferably, in the method, the splicing plate is installed during the installation of the crown module or floor grid into the semi-cylindrical section.

[0069] Preferably, in the method, the splicing plate is installed simultaneously in both the upper and lower semi-cylindrical sections.

[0070] Preferably, in the method, installing the splicing plate includes installing multiple splicing plates along the length of the upper semi-cylindrical section and / or the lower semi-cylindrical section.

[0071] Preferably, in the method, the splicing plate is installed at the assembly line during a pause between micro-pulsations in the upper and / or lower semi-cylindrical sections.

[0072] Preferably, in the method, aligning the upper cylindrical section with the lower cylindrical section includes rotating the lower cylindrical section from a vertically reverse orientation to an orientation complementary to that of the engaging upper cylindrical section.

[0073] Preferably, the method further includes placing the lower semi-cylindrical section in the support before aligning the upper semi-cylindrical section with the lower semi-cylindrical section.

[0074] Preferably, in the method, attaching the splicing plate includes driving the fastener through the splicing plate while the splicing plate contacts the inner mold line (IML) of the upper semi-cylindrical section and the IML of the lower semi-cylindrical section.

[0075] A part of an aircraft assembled according to the method described above.

[0076] According to one aspect of this disclosure, a non-transitory computer-readable medium comprising programming instructions operable, when executed by a processor, for performing a method for assembling an aircraft fuselage, the method comprising: receiving a semi-cylindrical segment of the fuselage in an assembly line; installing a splicing plate; aligning the semi-cylindrical segment with another semi-cylindrical segment of the fuselage; and joining the semi-cylindrical segment by attaching the splicing plate.

[0077] According to one aspect of this disclosure, a system for assembling the fuselage of an aircraft includes: an assembly line that conveys a semi-cylindrical section of the fuselage in a processing direction; a joining station 342 for mounting splicing plates; a support 1150 for holding the semi-cylindrical section of the fuselage; and a joining work station for joining the semi-cylindrical section by attaching the splicing plates.

[0078] Advantageously, in the system, joining the semi-cylindrical sections includes forming a butt joint between the semi-cylindrical sections.

[0079] Preferably, in the system, the splicing plate is mounted on the inner mold line (IML) of the semi-cylindrical section.

[0080] Preferably, in the method, the splicing plate is mounted on the outer mold line (OML) of the semi-cylindrical section.

[0081] Preferably, in the system, the splicing plate is partially installed on the upper semi-cylindrical section and partially installed on the lower semi-cylindrical section.

[0082] Preferably, in the system, the joining station is located after the assembly line.

[0083] Preferably, in the system, the installation of the splicing panels is performed during the installation of the crown module or floor grid into the semi-cylindrical section.

[0084] Preferably, in the system, the splicing plate is installed simultaneously in both the upper and lower semi-cylindrical sections.

[0085] Preferably, in the system, the joining station installs splicing plates on each side of the inner mold line (IML) of the upper and / or lower semi-cylindrical sections.

[0086] Preferably, in the system, the joining station installs multiple splicing plates along the length of the upper cylindrical section.

[0087] Preferably, in the system, the joining station includes an end effector that aligns the splice plate and installs fasteners through the splice plate.

[0088] Preferably, in the system, the joining station attaches the splicing plate by driving a fastener through the splicing plate, while the splicing plate contacts the inner mold line (IML) of the upper semi-cylindrical section and the IML of the lower semi-cylindrical section.

[0089] Use the system described above to manufacture a part of the aircraft.

[0090] The following describes other illustrative embodiments, including variations and methods related to the foregoing embodiments and computer-readable media. The foregoing features, functions, and advantages discussed and disclosed herein may be implemented independently in various embodiments or combined in other embodiments, further details of which can be seen in the following description and accompanying drawings. Attached Figure Description

[0091] Some embodiments of this disclosure will now be described by way of example only and with reference to the accompanying drawings. Throughout the drawings, the same reference numerals denote the same elements or elements of the same type.

[0092] Figure 1 An illustration depicts an assembled aircraft, including sections of the fuselage, in an illustrative embodiment.

[0093] Figure 1A The assembly environment of the factory in the illustrative embodiment is described.

[0094] Figure 2 This is a description of its use in the illustrative embodiments. Figure 1A A flowchart illustrating the method for assembling the fuselage of an aircraft in an assembly environment.

[0095] Figure 3 A hybrid manufacturing system is shown in an illustrative embodiment, which utilizes parallel and serial assembly lines to process the upper and lower sections of the fuselage.

[0096] Figure 4 It is a description of the use of in the illustrative embodiments Figure 3 A flowchart of a method for a hybrid manufacturing system.

[0097] Figure 5 The lower section of the fuselage in the illustrative embodiment is depicted in reverse.

[0098] Figure 6A cross-section of the fuselage in an illustrative embodiment is depicted.

[0099] Figure 7 It is a description of the use of in the illustrative embodiments Figure 5 A flowchart of a method for assembling floor gratings.

[0100] Figure 8 It is a flowchart depicting a method for installing splicing panels for joining fuselage sections in an illustrative embodiment.

[0101] Figure 9 It is a block diagram depicting segments connected via splicing panels in an illustrative embodiment.

[0102] Figures 10A to 10C An illustrative embodiment of an assembly line process is described, which uses splicing plates to join the first and second semi-cylindrical sections.

[0103] Figure 11A and Figure 11B The end view shows the upper and lower cylindrical sections that will be joined together using butt joints.

[0104] Figure 12 It is along Figure 1A End views of the upper and lower semi-cylindrical sections cut from 12A-12A in the image.

[0105] Figure 13 The diagram shows a transport mechanism that carries a section of the fuselage formed as a joined upper and lower cylindrical section.

[0106] Figure 14 This is a flowchart illustrating the feeder in an illustrative embodiment.

[0107] Figure 15 The control components of the production system in the illustrative embodiment are shown.

[0108] Figure 16 This is a flowchart illustrating a method for manufacturing a portion of the fuselage in an illustrative embodiment.

[0109] Figure 17 This is a flowchart illustrating the aircraft manufacturing and maintenance methods in the illustrative embodiments.

[0110] Figure 18 This is a block diagram of the aircraft in an illustrative embodiment.

[0111] Figure 19 An assembled aircraft in an illustrative embodiment is depicted, which has an aesthetic design of segments along the outer surface of the aircraft, wherein dashed lines depict the environment and the boundaries of the segments.

[0112] Figure 20It shows Figure 19 Side view of the embodiment shown;

[0113] Figure 21 Depicting Figure 20 An enlarged view of a segment of the aircraft shown (in) Figure 20 (The figures contain specific reference numerals), which have dashed lines and dotted lines to depict the boundaries of the segments and dashed lines to depict the environment of the segments, such as indicators of the position of windows;

[0114] Figure 22 Depicting from Figure 20 Observation from the top of the aircraft Figure 21 Side view of the segment in the middle;

[0115] Figure 23 Depicting Figure 21 The elevated side view of the segment shown illustrates the outer surface design in solid lines, while dashed lines represent cross-sectional views of embodiments having such a surface design.

[0116] Figure 24 Depicting Figure 21 An alternative embodiment of the design shown has dashed lines representing the boundaries of the segments and dashed lines depicting the environment of the segments, such as indicators of the window's position.

[0117] Figure 25 Depicting from Figure 20 Observation from the top of the aircraft Figure 24 and Figure 27 Side view of the section in the middle;

[0118] Figure 26 Depicting Figure 24 The elevated side view of the segment shown illustrates the outer surface design in solid lines, while dashed lines represent cross-sectional views of embodiments having such a surface design.

[0119] Figure 27 Depicting Figure 21 An alternative embodiment of the design shown has dashed lines for the boundaries of the segments and dashed lines depicting the environment of the segments, such as indicators of the position of windows.

[0120] Figure 28 Depicting Figure 25 and Figure 27 The elevated side view of the segment shown illustrates the outer surface design in solid lines, while dashed lines represent cross-sectional views of embodiments having such a surface design.

[0121] Figure 29 Depicting Figure 21 An alternative embodiment of the segment shown has dashed lines for the segment boundaries and dashed lines depicting the segment's environment, such as indicators of the window's position.

[0122] Figure 30 Depicting Figure 29 The elevated side view of the segment shown illustrates the outer surface design in solid lines, while dashed lines represent cross-sectional views of embodiments having such a surface design.

[0123] Figure 31 Depicting Figure 21 An alternative embodiment of the design shown has dashed lines for the boundaries of the segments and dashed lines depicting the environment of the segments, such as indicators of the position of windows.

[0124] Figure 32 Depicting from Figure 20 Observation from the top of the aircraft Figure 31 Side view of the segment in the middle;

[0125] Figure 33 Depicting Figure 31 The elevated side view of the segment shown illustrates the outer surface design in solid lines, while dashed lines represent cross-sectional views of embodiments having such a surface design.

[0126] Figure 34 An assembled aircraft in an illustrative embodiment is depicted, featuring an aesthetically pleasing design with segments along the outer top surface of the aircraft, where dashed lines depict the environment and the boundaries of the segments.

[0127] Figure 35 It shows Figure 34 A top view of the embodiment shown;

[0128] Figure 36 Depicting Figure 35 An enlarged view of a segment of the aircraft shown (in) Figure 35 (The figures contain specific reference numerals), which have dashed or dotted lines depicting the boundaries of the segments;

[0129] Figure 37 Depicting from Figure 34 and Figure 35 Side view of the aircraft Figure 36 and Figure 44 Side view of the segment in the middle;

[0130] Figure 38 Depicting Figure 36 The elevated perspective view of the segment shown illustrates the outer surface design in solid lines, while dashed lines represent cross-sectional views of embodiments having such a surface design.

[0131] Figure 39 Depicting Figure 36 An alternative embodiment of the design shown has dashed lines for the boundaries of segments;

[0132] Figure 40 Depicting from Figure 34 and Figure 35 Side view of the aircraft Figure 39 and Figure 42 Side view of the segment in the middle;

[0133] Figure 41 Depicting Figure 39 The elevated perspective view of the segment shown illustrates the outer surface design in solid lines, while dashed lines represent cross-sectional views of embodiments having such a surface design.

[0134] Figure 42 Depicting Figure 36 An alternative embodiment of the design shown has dashed lines for the boundaries of segments;

[0135] Figure 43 Depicting Figure 42 The elevated perspective view of the segment shown illustrates the outer surface design in solid lines, while dashed lines represent cross-sectional views of embodiments having such a surface design.

[0136] Figure 44 Depicting Figure 36 An alternative embodiment of the segmentation shown has dashed lines for the boundaries of the segments;

[0137] Figure 45 Depicting Figure 44 The elevated perspective view of the segment shown illustrates the outer surface design in solid lines, while dashed lines represent cross-sectional views of embodiments having such a surface design.

[0138] Figure 46 Depicting Figure 36 An alternative embodiment of the design shown has dashed lines for the boundaries of segments;

[0139] Figure 47 Depicting from Figure 34 and Figure 35 Side view of the aircraft Figure 46 Side view of the segment in the middle;

[0140] Figure 48 Depicting Figure 46 The elevated perspective view of the segment shown depicts the outer surface design in solid lines, while dashed lines represent cross-sectional views of embodiments having this surface design. Detailed Implementation

[0141] The accompanying drawings and the following description provide specific illustrative embodiments of the present disclosure. Therefore, it should be understood that those skilled in the art will be able to design various arrangements that, although not explicitly described or shown herein, embody the principles of the present disclosure and are included within its scope. Furthermore, any examples described herein are intended to aid in understanding the principles of the present disclosure and should be construed as not being limited to these specific examples and conditions. Therefore, the present disclosure is not limited to the specific embodiments or examples described below, but is limited by the claims and their equivalents.

[0142] Sub-components 398-10 (such as, but not limited to, frames 398-2, 398-4, window surrounds 398-3, and door surrounds 398-5) may be made of metal or may be manufactured as composite components. Composite components (such as carbon fiber reinforced polymer (CFRP) components) are initially laid out in multiple layers, which together are referred to as preforms. Individual fibers within each layer of the preform are aligned parallel to each other, but different layers exhibit different fiber orientations to increase the strength of the final composite component along different dimensions. The preform includes a viscous resin, which cures to harden the preform into a composite component (e.g., for use in aircraft). Carbon fibers already impregnated with uncured thermosetting or thermoplastic resins are referred to as “prepreg.” Other types of carbon fibers include “dry fibers” that are not impregnated with thermosetting resins but may contain tackifiers or adhesives. Dry fibers are impregnated with resin before curing. For thermosetting resins, curing is a unidirectional process called curing, while for thermoplastic resins, the resin reaches a viscous form if it is reheated.

[0143] Turn now Figure 1 The illustration depicts an aircraft in which an illustrative embodiment can be implemented. The aircraft 10 can be composed of... Figure 1A An example of an aircraft formed from a semi-cylindrical section. Aircraft 10 is formed from a semi-cylindrical section 24 of fuselage 12. In this illustrative example, aircraft 10 has wings 15 and 16 attached to fuselage 12. Aircraft 10 includes an engine 14 attached to wing 15 and an engine 16 attached to wing 16. Fuselage 12 has a tail section 18 and a nose section 38. Horizontal stabilizers 20, 21, and 22 are attached to the tail section 18 of fuselage 12. Fuselage 12 is manufactured from the final semi-cylindrical section 24, wherein the upper semi-cylindrical section 126 ( Figure 1A The segments are joined to the lower semi-cylindrical section 128 to form complete cylindrical sections 29-1, 29-2, 29-3, 29-4, and 29-5. Complete cylindrical section 146 corresponds to view AA, and complete cylindrical section 136 corresponds to view BB and is continuously fastened to the fuselage 12. Wings 15 and 16 are formed by wing panels 30 including an upper wing panel 32 and a lower wing panel 34 joined together.

[0144] Figure 1A Assembly environment 100 in an illustrative embodiment is depicted. Assembly environment 100 includes an arrangement of machinery and tools that facilitates efficient and repeatable manufacturing of the aircraft. Assembly environment 100 has been enhanced to enable the manufacture and assembly of wing panels or fuselage sections on continuous, micro-pulsating, and / or pulsating assembly lines. This allows parts of the structure requiring machining to be brought to the workers, tools, and equipment, rather than requiring workers, equipment, and tools to be brought to or entered the structure. Assembly environment 100 provides substantial benefits by increasing workload density through reducing the amount of non-value-adding time to the assembled fuselage and also by increasing the amount of space occupied in the factory shop.

[0145] In this embodiment, the assembly environment 100 includes a first assembly line 110 for manufacturing fuselage segments, which has a non-uniform cross-section along its length, and a second assembly line 120 for manufacturing fuselage segments, which has a substantially uniform cross-section along its length. Both the first assembly line 110 and the second assembly line 120 process upper semi-cylindrical segments 116 and 126 and complementary lower semi-cylindrical segments 118 and 128, respectively. The first assembly line 110 processes the lower semi-cylindrical segment 118 to deliver it to assembly station 330-1 (i.e., floor grille attachment station 530) for attachment to passenger floor grille 365-1 and cargo floor grille 365-2. The first assembly line 110 processes the upper semi-cylindrical segment 116 and delivers it to assembly station 320 for attachment to crown module 364-1. The second assembly line 120 processes the lower semi-cylindrical segment 128 and delivers it to assembly station 330 (…). Figure 3 (i.e., floor grille attachment station 530-1), for attachment to passenger floor grille 365-1 and cargo floor grille 365-2. The second assembly line 120 processes the upper semi-cylindrical section 126 and delivers it to assembly table 320. Figure 3 (i.e., crown module attachment station 730-1), used for joining to crown module 364 ( Figure 3 In another embodiment, an additional assembly line manufactures the wings for assembly with the fuselage to form a complete fuselage. Assembly lines 110, 120 operate in a pulsed manner, wherein the upper semi-cylindrical sections 116, 126 and the lower semi-cylindrical sections 118, 128 advance a distance in the processing direction 199 equal to the pulse lengths 123, 123-1 or the micro-pulsation 129. The micro-pulsation 129 is smaller than the pulses 123, 123-1, and in one embodiment equal to the frame 912 of the upper semi-cylindrical sections 116, 126 and the lower semi-cylindrical sections 118, 128. Figure 9The frame spacing 915 between the components is either equal to or a fraction thereof. In one embodiment, the frame spacing 915 is approximately 45 to approximately 61 centimeters (approximately 18 to approximately 24 inches). After micro-pulsation 129, the upper semi-cylindrical sections 116, 126 and the lower semi-cylindrical sections 118, 128 pause, and then micro-pulsate 129 again in the processing direction 199. In another embodiment, the upper semi-cylindrical sections 116, 126 and the lower semi-cylindrical sections 118, 128 advance continuously in the processing direction 199 without pausing. Thus, the assembly lines 110, 120 discussed herein enable composite components to travel across multiple different workstations 114 at a desired rate of pace in a pulsating, 123-1, micro-pulsating, or continuous manner. The semi-cylindrical section 117 includes the upper semi-cylindrical sections 116, 126 and the lower semi-cylindrical sections 118, 128. The arc-shaped portion 119 includes a quarter-cylindrical section and a third-cylindrical section.

[0146] The assembly lines 110 and 120 discussed herein can be further operated to manufacture multiple sets of semi-cylindrical sections 117, 117-1 or arcuate sections 119, 119-1, wherein the spacing between each semi-cylindrical section 117 or arcuate section 119 is the length of the semi-cylindrical section 117, 117-1 or arcuate section 119-1, and is at least a fraction or multiple of the frame spacing 915. The semi-cylindrical sections 117 and 117-1 correspond to the semi-cylindrical section 24 after processing via the first assembly line 110 or the second assembly line 120, respectively.

[0147] The first assembly line 110 can be designed with workstations 114 that can accommodate more foreign shapes, such as the conical semi-cylindrical section 117 or the arcuate section 119 near the head section 38 or the tail section 18. Workstations 114 exhibit a wider range of motion to accommodate the tapering characteristics of the semi-cylindrical section 117 or the arcuate section 119. The first assembly line 110 also includes a track 112-1 along which the upper semi-cylindrical section 116 and the lower semi-cylindrical section 118 travel in the processing direction 199. Track 112-1 allows the semi-cylindrical section 117 to reach tools and equipment (not shown) located at workstations 114 in the processing direction 199, which are arranged serially in the processing direction 199. Track 112-1 may include a series of discrete supports having rollers, tracks, or track assemblies (not shown), and the body at track 112-1 may pulse incrementally across work stations 114 in the processing direction 199. Work stations 114 are aligned serially, and the semi-cylindrical sections 117 or arcuate sections 119 of the segments travel serially through work stations 114. Although only a few work stations 114 are shown, work stations 114 perform operations such as, but not limited to, demolding, installing window surrounds, installing door surrounds, trimming manufacturing allowances, installing frames, cutting window manufacturing allowances or otherwise removing material, NDI inspection, edge sealing, cutting door manufacturing allowances, installing windows, and installing doors in dedicated work stations 114. In one embodiment, work stations 114 simultaneously work on a portion of the body. In another embodiment, work stations 114 are arranged at a certain work density based at least in part on the cycle time of the semi-cylindrical sections 117 or arcuate sections 119 being manufactured.

[0148] During these processes, tooling equipment such as laying mandrels can be placed on or removed from track 112-1 as needed. In one embodiment, track 112-1 includes a drive system 112 for moving the section, such as a chain drive, although in other embodiments, the section is driven independently along track 112-1.

[0149] In one embodiment, the upper semi-cylindrical section 116 and the lower semi-cylindrical section 118 are simultaneously pulsed synchronously in the processing direction 199 by the same distance. Then, workstation 114 operates on the semi-cylindrical section 116 or the arcuate section 119 during pauses between pulses and / or during pauses in a common cycle time. Therefore, during the manufacturing process, multiple workstations 114 operate on the upper semi-cylindrical section 116 and / or the lower semi-cylindrical section 118 during the same pauses between micro-pulses 129 and / or during micro-pulses 129.

[0150] In one embodiment of assembly line 110 or 120, one or more workstations 114, 124 also independently or synchronously perform their operations on the same semi-cylindrical sections 117, 117-1 or arcuate sections 119, 119-1 during pulsations. These operations may include non-destructive testing (NDI), trimming of manufacturing allowances, application of sealant, or other processes. In a further embodiment, the upper semi-cylindrical section 116 and the lower semi-cylindrical section 118 advance continuously along track 112-1, and workstation 114 performs operations on the sections as they continue to move.

[0151] In some embodiments of assembly line 110 or 120, workstations 114, 124 are spaced apart by predetermined gaps 131, 131-1, such as equal to the distance of micropulsation 129, a fraction or multiple of frame spacing 915, or any distance less than or equal to the length of the semi-cylindrical sections 117, 117-1 or the arcuate sections 119, 119-1. Gap 131, 131-1 helps to address production delays, such as rework or out-of-position work of the semi-cylindrical sections 117, 117-1 or the arcuate sections 119, 119-1, or maintenance and / or technician rest time at workstations 114, 124. When the portions of the semi-cylindrical sections 117, 117-1 or the arcuate sections 119, 119-1 requiring rework or relocation are located between workstations 114, 124 or within workstations where work such as the installation of the window surround opposite the lower semi-cylindrical section 118 is not required, the rework or relocation is performed. This allows previously unforeseen delays to be absorbed into the production process. The rework or relocation operations discussed above can be performed within the gaps 131, 131-1 between workstations 114, 124. Furthermore, in one embodiment, the semi-cylindrical sections 117, 117-1 or the arcuate sections 119, 119-1 continue to pass through workstations 114, 124 while rework or relocation is being performed. Therefore, the assembly environment 100 does not stop moving forward in the processing direction 199 to work on the semi-cylindrical sections 117, 117-1 or the arc-shaped sections 119, 119-1 to accommodate rework or relocation operations.

[0152] During movement between micro-pulses 129 or during movement of pulse lengths 123, 123-1, the semi-cylindrical sections 117, 117-1 or the arcuate sections 119, 119-1 encounter the indexing component 115 at workstations 114, 124. This component physically interacts with or non-destructively inspects the indexing feature 133 at the upper semi-cylindrical sections 116, 126 and the lower semi-cylindrical sections 118, 128, and aligns the component to workstations 114, 124 before operation. The indexing component 115, such as a physical feature or radio frequency identifier (RFID) chip, is engaged by an indexing engagement device associated with workstations 114, 124. Each indexing component 115 transmits to stations 114 and 124 the inner mold line (IML) inclination angle 116-1 and / or outer mold line (OML) inclination angle 116-2 of the upper semi-cylindrical sections 116 and 126 and the lower semi-cylindrical sections 118 and 128 within the ranges 114-1 and 124-1 of the working stations 114 and 124. Figure 1 The process involves a 3D representation of the micro-pulse 129 and the transmission of instructions to workstations 114 and 124 regarding the operations to be performed by workstations 114 and 124 on the upper semi-cylindrical sections 116 and 126 and the lower semi-cylindrical sections 118 and 128. This process can be executed multiple times for each of the corresponding workstations 114 and 124, and simultaneously. Workstations 114 and 124 can then perform operations during pauses between micro-pulses 129 or during the micro-pulse 129 itself.

[0153] The indexing component 115 includes hard stops, pins, holes, or grooves complementary to the indexing feature 133 for physical fixation thereto. Embodiments have a plurality of indexing features arranged on the upper semi-cylindrical sections 116, 126 and the lower semi-cylindrical sections 118, 128. In another embodiment, the indexing component 115 includes a laser, ultrasonic, or visual inspection system for tracking the indexing feature 133. The indexing feature 133 also includes an RFID chip, and an RFID reader is another embodiment of the indexing component 115, 125 for reading the RFID chip. For example, these contactless technologies can be used in assembly lines 110, 120 where the upper semi-cylindrical sections 116, 126 and the lower semi-cylindrical sections 118, 128 are continuously moved. In another embodiment, the indexing component 115 with hard stops, pins, holes, or grooves complementary to the indexing feature 133 is used in a continuous movement system. In such an embodiment, engagement of the indexing feature 133 with the indexing component 115 occurs during the advance of the upper cylindrical sections 116, 126 and the lower cylindrical sections 118, 128 within the ranges 114-1, 124-1 of the next workstations 114, 124. Workstations 114, 124 can track the upper cylindrical sections 116, 126 and the lower cylindrical sections 118, 128 as they advance in the processing direction 199. In another embodiment, all or part of the workstations 114, 124 are attached to the upper cylindrical sections 116, 126 and the lower cylindrical sections 118, 128, and straddle as they advance in a micro-pulsation 129, pulsating, or continuous process, as if riding along workstations 139, 139-1. Work is performed on the upper cylindrical sections 116, 126 and the lower cylindrical sections 118, 128 along the straddles at workstations 139, 139-1, and then the sections are separated and returned to attachment point 139-2 for future use. The straddles along workstations 139, 139-1 are curved tracks or similar devices. An example of a straddle along workstations 139, 139-1 is a flexible track device 1024, which follows a track 1023 removably mounted to the upper cylindrical sections 116, 126 and / or the lower cylindrical sections 118, 128.

[0154] The upper cylindrical sections 116 and 126 and the lower cylindrical sections 118 and 128 are laid on laying mandrels oriented to the crowns 135 and 135-1 and the keels 137 and 137-1, respectively. The orientation of the upper cylindrical sections 116 and 126 and the lower cylindrical sections 118 and 128 is maintained from installation through the floor grating until demolding at 136 and 146, wherein the lower cylindrical sections 118 and 128 are just at the reverse station 560. Figure 5(Just before joining stations 342, 342-1) are inverted before the keel 137, 137-1 is oriented downwards. This allows different work stations 114, 124 to process the upper semi-cylindrical sections 116, 126 and the lower semi-cylindrical sections 118, 128 in a pulsating manner sequentially through the same work stations 114, 124 during manufacturing.

[0155] In one embodiment, the orientation of the lower semi-cylindrical sections 116, 126 and 118, 128 on assembly lines 110, 120, respectively, is set by a laying mandrel on which the sections are laid. The laying mandrel advances from the stack through curing, on which the preforms are laid. After curing, the upper semi-cylindrical sections 116, 126 and lower semi-cylindrical sections 118, 128 are then removed from the laying mandrel without changing the orientation of the upper semi-cylindrical sections 116, 126 and lower semi-cylindrical sections 118, 128.

[0156] In another embodiment using more than one assembly line 110, the second assembly line 120 facilitates the manufacture of additional sections, such as those exhibiting non-cylindrical or cylindrical cross-sectional shapes. In one embodiment, multiple aircraft models are processed sequentially on assembly lines 110, 120. Upper semi-cylindrical sections 116, 126 and lower semi-cylindrical sections 118, 128 for one model are processed sequentially along assembly lines 110, 120, followed by upper semi-cylindrical sections 116, 126 and lower semi-cylindrical sections 118, 128 for different models. For example, lower semi-cylindrical sections 118, 128 advance along assembly lines 110, 120, followed by complementary upper semi-cylindrical sections 116, 126. Similarly, these lower cylindrical sections 118, 128 and upper cylindrical sections 116, 126 are followed by the lower cylindrical sections 118, 128 and upper cylindrical sections 116, 126 of another aircraft model, followed by the lower cylindrical sections 118, 128 and upper cylindrical sections 116, 126 of yet another model, and so on between one model and another. In addition, more than one assembly line 110, 120 is envisioned, each of which is also envisioned to ensure that the upper cylindrical sections 116, 126 and the lower cylindrical sections 118, 128 are produced at a desired rate.

[0157] In some embodiments, the workstations 114, 124 discussed herein have the capability to operate on different portions of the upper cylindrical sections 116, 126 and lower cylindrical sections 118, 128 with different diameters to accommodate different diameters between different models. Each indexing operation between the indexing components 115, 125 and the indexing feature 133 informs the processor communicating with the workstations 114, 124 of the following: the lower cylindrical sections 118, 128 and the upper cylindrical sections 116, 126 of any model are within their ranges 114-1, 124-1, and what operations need to be performed, or whether operations are required. For example, when a window cut is not required, the window manufacturing allowance removal station may no longer generate a window cut when the lower cylindrical sections 118, 128 are within their ranges 114-1, 124-1.

[0158] Arrow 101 indicates where the upper cylindrical section 116 and the lower cylindrical section 118 are moved to after they have passed through assembly line 110. For example, arrow 101 depicts the lower cylindrical section 118 and the upper cylindrical section 116 moving to assembly stations 320 and 330 respectively, and then moving to the joining station 342-1 for joining, and moving to different assembly lines, etc. Arrow 101 indicates where the lower cylindrical sections 118, 128 and the upper cylindrical sections 116, 126 are moved to after they have passed through assembly line 120. For example, arrow 101 depicts the lower cylindrical section 128 and the upper cylindrical section 126 moving to the joining stations 342, 342-1 for joining, and moving to different assembly lines, etc.

[0159] The second assembly line 120 includes a track 122-1 along which the upper semi-cylindrical section 126 and the lower semi-cylindrical section 128 travel in a processing direction 199 in a manner similar to that described above for the first assembly line 110. The second assembly line 120 also includes a station 124 with an indexing component 125. The workstation 124, the indexing component 125, and the track 122-1 can be implemented in a manner similar to that described for the components of the first assembly line 110. However, the stations 124 can differ because they can be more closely fitted to each of the upper semi-cylindrical section 126 and the lower semi-cylindrical section 128 being worked on. The cross-sectional variation between the upper semi-cylindrical section 126 and the lower semi-cylindrical section 128 is smaller than the cross-sectional variation between the upper semi-cylindrical section 116 and the lower semi-cylindrical section 118. The upper cylindrical section 126 and the lower cylindrical section 128 of the second assembly line 120 are more uniform in shape and size than the upper cylindrical section 116 and the lower cylindrical section 118 of the first assembly line 110.

[0160] Figure 1AThe document also depicts fuselage assembly areas 130 and 140, which assemble upper semi-cylindrical segments 116, 126 and lower semi-cylindrical segments 118, 128 at workstations 134 and 144, respectively, into complete cylindrical segments 136 and 146. A joining station 342 is part of workstations 134 and 144. Complete cylindrical segments 136, 146 advance along tracks 132 and 142 to work cells 141, 141-1, where they are assembled longitudinally to form complete cylindrical segments 138 and 148 of the fuselage 149. Complete cylindrical segment 148 is cylindrical in shape, while complete cylindrical segment 138 is not. In another embodiment, the operations of assembly lines 110, 120 discussed herein are combined into a single assembly line.

[0161] Process tracking server 102 tracks and / or manages the operation of assembly lines 110, 120 discussed herein, for example, by guiding the operation of one or more workstations 114, 124 in assembly environment 100. In this embodiment, process tracking server 102 communicates with memory 104 to retrieve information related to one or more numerical control (NC) programs used to operate assembly lines 110, 120. Controller 106 of process tracking server 102 may further process feedback from workstations 114, 124 and / or assembly lines 110, 120 and provide instructions to workstations 114, 124, or may report information to operators based on such feedback. In one embodiment, an RFID chip or other indexing component 125 enables indexing actions to directly instruct workstations 114, 124 for portions of the upper semi-cylindrical sections 116, 126 and lower semi-cylindrical sections 118, 128 within ranges 114-1, 124-1 of workstations 114, 124. In such an embodiment, instructions can be passed between controller 106 and specific workstations 114, 124. Controller 106 can be implemented as, for example, custom circuitry, a hardware processor that executes programmed instructions, or some combination thereof. Memory 104 stores instructions for operating controller 106 and may include suitable receptacles for storing digital data.

[0162] according to Figure 1A Each station 114 at assembly line 110 can be fed / supplied with materials and / or sub-components 398-10 by a corresponding feeder 149-1 (e.g., based on the cycle time for the fuselage section, and as...). Figure 1A(As shown in the diagram), and these materials and / or components are attached to the upper semi-cylindrical section 116 and lower semi-cylindrical section 118 processed by workstation 114. Feeder 149-1 supplies additional material, such as sub-components 39A-10, to workstation 114. Each feeder 149-1 is designed to generate material in a cycle time manner to supply additive material, such as sub-components 398-10, to workstation 114 in a just-in-time production manner for assembly into a larger structure (e.g., a section of the fuselage), which also pulsates in a cycle time manner. That is, feeder 149-1 delivers sub-components 398-10 to workstation 114 in a just-in-time production manner according to the order of use of workstation 114. In one embodiment, the cycle time of feeder 149-1 is equal to a portion of the fuselage cycle time.

[0163] The cycle times of feeder 149-1 and / or assembly line 110 do not need to be the same. For example, the upper semi-cylindrical section 116 and the lower semi-cylindrical section 118 can simultaneously micro-pulse through several workstations 114. The upper semi-cylindrical section 116 and the lower semi-cylindrical section 118 are indexed to workstations 114, and each dedicated feeder 149-1 performs NDI, window surround 910-1, 970-2 installation, door surround 940-1, 940-2 installation, window manufacturing allowance 970-9 trimming / removal, door manufacturing allowance 940-9 trimming / removal, window installation, and door installation, etc. Feeder 149-1 also includes outputs from workstations 114, including NDI inspection data and any allowance trimming of the upper semi-cylindrical section 116 and the lower semi-cylindrical section 118. Each semi-cylindrical section includes at least one internal sub-component 398-10, such as frame 912 ( Figure 9 ), window surrounds 970-1, 970-2 installation, door surrounds 940-1, 940-2, which are fixed to the semi-cylindrical sections before being joined to the corresponding semi-cylindrical sections.

[0164] In another example, feeder 149 supplies frame 912 to workstation 114 in a just-in-time production manner, and workstation 114 installs frame 912 onto upper semi-cylindrical section 116 and lower semi-cylindrical section 118. Figure 9Reference frame 912 is shown through view 917. Similarly, feeder 149-1 provides just-in-time production for supplying window surround 970-2 to the window surround installation station and just-in-time production for supplying door surround 940-2 to the door surround installation station. For each feeder 149-1, production time is designed based on the takt time of the associated workstation 114. Feeders 149-1 each pulsate or micro-pulse 129 serially during manufacturing, and the completed sub-parts 398-10 arrive at each workstation 114 with a common takt time. This takt time is designed to travel from the smallest part to the largest final assembly through each of feeders 149-1. If the takt time cannot be achieved, the work statement of a particular workstation 114 can be adjusted to reduce or increase the amount of work performed at that particular workstation 114. In another embodiment, it is possible to add or remove workstations 114 from the process based on the work statements and expected cycle times for the entire line of the semi-cylindrical section. Cycle time is considered to be the number of minutes per month divided by the number of units required per month (e.g., for aircraft, longitudinal beams, frames, etc.). The sum of micro-pulsations equals the pulsation of the cycle time. That is, after multiple micro-pulsations equal a full pulsation, the entire unit has advanced its length through assembly line 110. Figure 1A Each workstation 124 at assembly line 120 can be connected by a corresponding feeder 149 (e.g., based on the cycle time for the semi-cylindrical section 117-1, and as...). Figure 1A(As shown) Materials and / or sub-components 398-10 are fed / supplied, and these materials and / or sub-components 398-10 are attached to the upper semi-cylindrical section 126 and the lower semi-cylindrical section 128 processed by workstation 124. Feeder 149 supplies additive materials and / or sub-components 398-10 to workstation 124. Each feeder 149 is designed to generate material in takt time to supply additive materials and / or sub-components 398-10 to workstation 124 in a just-in-time production manner for assembly onto larger structures, such as semi-cylindrical sections, which are also pulsed in takt time. The takt time of feeders 149, 149-1 can be the same as or different from the takt time of assembly lines 110, 120. That is, feeder 149 delivers sub-components 398-10 to workstation 124 in a just-in-time production manner in the order they are used by workstation 124. In one embodiment, the cycle time of feeder 149 is equal to or a portion of the fuselage cycle time. The cycle time is equal to the micro-pulsation 129 time plus the pause time between micro-pulsations 129. Multiple lines each utilize unique or shared cycle times and provide feeds to the next line in a just-in-time production manner. In one embodiment, feeders have cycle times different from the cycle times of the lines they feed. Each feeder may have a unique cycle time or may have a cycle time similar to the lines it feeds. Each line has a common cycle time unique to that particular cycle time. In one embodiment, the cycle time is based on the number of aircraft manufactured per month. In another embodiment, the cycle time is based on the number of aircraft manufactured per month and the number of components required for each aircraft. In another embodiment, the cycle time is defined for an array of workstations that perform job assignments.

[0165] The cycle times of feeder 149 and / or assembly line 120 do not need to be the same. For example, the upper cylindrical section 126 and the lower cylindrical section 128 can simultaneously micro-pulse through several workstations 124. The upper cylindrical section 126 and the lower cylindrical section 128 are transposed to workstations 124, and each dedicated feeder 149 performs NDI, window surround installation, door surround installation, window manufacturing allowance trimming / removal, door manufacturing allowance trimming / removal, window installation, and door installation, etc. Feeder 149 also includes outputs from workstations 124, including NDI inspection data and any allowance trimming of the upper cylindrical section 126 and the lower cylindrical section 128.

[0166] In another example, feeder 149 supplies frame 912 to workstation 124 in a just-in-time production manner, whereby workstation 124 installs frame 912 onto upper semi-cylindrical section 126 and lower semi-cylindrical section 128. Similarly, feeder 149 supplies window surrounds to window surround installation workstation 124 in a just-in-time production manner and door surrounds to door surround installation workstation 124 in a just-in-time production manner. For each feeder 149, production time is designed based on the cycle time of the associated workstation 124. Each feeder 149 pulses parts serially during manufacturing, and finished parts arrive at each workstation 124 within a common cycle time. This cycle time design proceeds from the smallest part to the largest assembly through each of the feeders 149. If the cycle time cannot be achieved for assembly lines 110, 120 or feeders 149, 149-1, the work statements for a specific workstation 124 can be adjusted to reduce or increase the workload performed at that specific workstation 124. In another embodiment, it is possible to add or remove workstations 124 from the process based on the work statements for the entire assembly lines 110, 120 and the desired cycle time. The cycle time is considered to be the number of minutes per month divided by the number of units required per month (e.g., aircraft, longitudinal beams, frames 912, etc.). The sum of the micro-pulsation cycle times equals the total pulsation cycle time. That is, after multiple micro-pulsations 129 are equal, the assembly line 120 proceeds along its length.

[0167] Another embodiment of the upper semi-cylindrical section 116 and the lower semi-cylindrical section 118 are respectively mounted on assembly tables 320-1 and 330-1 ( Figure 3 The components are joined to the crown module 364-1, cargo floor grille 365-2, and passenger floor grille 365-1. Assembly stations 320-1 and 330-1 are part of the assembly process of the upper cylindrical section 116 and the lower cylindrical section 118, similar to how assembly stations 320 and 330 are part of the assembly process of the upper cylindrical section 126 and the lower cylindrical section 128. Similarly, the joining station 342-1 is part of the assembly process of the upper cylindrical section 116, while the lower cylindrical section 118 corresponds to the joining station 342, which is part of the assembly process of the upper cylindrical section 126 and the lower cylindrical section 128.

[0168] Regarding Figure 2 Illustrative details of the operation of assembly environment 100 are discussed. For this embodiment, it is assumed that the assembly line discussed herein is used to continuously manufacture semi-cylindrical sections of the fuselage for assembly into the fuselage.

[0169] Figure 2 This is a description of its use in the illustrative embodiments. Figure 1A A flowchart of a method for assembling the fuselage of an aircraft in an assembly environment (see flowchart 200). Figure 1AThe assembly environment 100 describes the steps of method 200, but those skilled in the art will understand that method 200 can be performed in other ways.

[0170] The steps in the flowchart described herein are not exhaustive and may include other steps not shown. The steps described herein may also be performed in an alternative order.

[0171] In step 202, a first assembly 103-1 of the lower cylindrical section 118 and the upper cylindrical section 116 of the fuselage is advanced along the first assembly line 110 in the processing direction 199. Track 112-1 has a drive system 112 to advance the lower cylindrical section 118 and the upper cylindrical section 116 along track 112-1. This can be performed in a synchronous micro-pulsation manner, wherein the lower cylindrical section 118 and the upper cylindrical section 116 are advanced sequentially by micro-pulsations 129 and then paused or as part of a continuous movement process. The lower cylindrical section 118 and the upper cylindrical section 116 are manufactured in an alternating manner, such that the lower cylindrical section 118 and the upper cylindrical section 116 are paired to engage into the same complete cylindrical section 138, making it necessary for them to be arranged adjacently in series on the assembly line 110. Furthermore, the lower cylindrical section 118 and the upper cylindrical section 116 are arranged from front to back or from back to front, such that adjacent sections correspond to adjacent longitudinal portions for joining together the fuselage 12 in a cylindrical manner.

[0172] Step 203 includes transposing the lower semi-cylindrical segment 118 and the upper semi-cylindrical segment 116 of the first assembly at the first assembly line 110. As discussed above, transposing transfers a portion of the lower semi-cylindrical segment 118 and the upper semi-cylindrical segment 116 within ranges 114-1, 124-1 of each station 114, and can be performed via physical connection to transposing features located at manufacturing allowances, scanning barcodes located at manufacturing allowances, reading RFID chips located at manufacturing allowances, or other means. Transposing also transfers models of the lower semi-cylindrical segment 118 and the upper semi-cylindrical segment 116 to each workstation 114.

[0173] In step 204, workstation 114 performs operations on the lower semi-cylindrical section 118 and upper semi-cylindrical section 116 of the first assembly at the first assembly line 110. This may include transposing the lower semi-cylindrical section 118 and upper semi-cylindrical section 116 to workstation 114 and performing operations such as laying, hardening, demolding, frame installation, window manufacturing allowance trimming, door manufacturing allowance trimming, etc. In an embodiment where the lower semi-cylindrical section 118 and upper semi-cylindrical section 116 are advanced by micro-pulsations 129, operations may be performed during pauses between micro-pulsations 129 and / or during micro-pulsations 129. In an embodiment where the lower semi-cylindrical section 118 and upper semi-cylindrical section 116 move continuously, operations may be performed while the lower semi-cylindrical section 118 and upper semi-cylindrical section 116 are moving in the processing direction 199.

[0174] Steps 206-210 describe various additional steps that form complete cylindrical sections 29-1, 29-2, 29-3, 29-4, and 29-5, in addition to those described above. In step 206, a second assembly 105 of the upper cylindrical section 126 and the lower cylindrical section 128 of the fuselage advances along the second assembly line 120 in the processing direction 199. Track 122-1 has a drive system to advance the lower cylindrical section 128 and the upper cylindrical section 126 along track 122-1. This can be performed in a synchronous pulsating manner, wherein the lower cylindrical section 128 and the upper cylindrical section 126 are advanced serially by micro-pulsations 129 and then paused or as part of a continuous movement process. The lower cylindrical section 128 and the upper cylindrical section 126 are manufactured alternately, such that the lower cylindrical sections 128 and 126 of the same complete cylindrical sections 29-1, 29-2, 29-3, 29-4, and 29-5 used for the fuselage are adjacent to each other on assembly line 120. Furthermore, the lower cylindrical sections 128 and 126 are arranged from front to back or from back to front, such that adjacent pairs of lower cylindrical sections 128 and upper cylindrical sections 126 correspond to adjacent longitudinal portions to be joined together to form a complete cylindrical section 136. This allows the complete cylindrical sections 29-1, 29-2, 29-3, 29-4, and 29-5 to be circumferentially joined to the fuselage 12. The lower semi-cylindrical segment 118 and the upper semi-cylindrical segment 116 are joined together at the end of each in assembly line 110 to form a fully complete cylindrical segment 136. For example, this may include assembling the lower semi-cylindrical segment 118 and the upper semi-cylindrical segment 116 together by (… Figure 9 The upper cylindrical section 116 (door surround splice 940 or window surround splice 970) is longitudinally joined to the lower cylindrical section 118 to form the first set of complete cylindrical sections 136.

[0175] In one embodiment, one or more of the complete cylindrical sections 24 may be formed by an upper and a lower cylindrical section, or alternatively by a right and a left cylindrical section, forming a fuselage to provide an outer surface with visible decoration, such as Figures 19 to 33 As shown, or as Figures 34 to 48 As shown. The method and system of this disclosure provide for the implementation of the fuselage 12 segments forming sections (29-1 to 29-5). Figures 19 to 33 The design features shown are as follows. Specifically, along the outer surface of the side of the section of fuselage 12 (such as...) Figures 19 to 33 (As shown) includes the surface appearance of an elongated line 25 having the appearance of a plurality of generally circular features 27 located on each side of the line. In another embodiment, the outer surface of the top of a section of the fuselage 12 (as shown) Figures 34 to 48 (As shown) includes the surface appearance of an elongated line 35 having a plurality of generally circular features 37 on each side of the line. In a preferred embodiment, lines 25, 35 may be defined by a seam where the semi-cylindrical sections 126, 128 of the fuselage 12 are joined, which may include a sealant and subsequent paint or other covering material to not completely cover or hide the features, thereby maintaining the selected visible decorative surface features. Similarly, the appearance of a plurality of generally circular features 27, 37 may be obtained from some fastener / rivet heads on each side of the lines 25, 37, where the lines 25, 37 are not completely covered or hidden, thereby maintaining the visible decorative surface features, such as Figures 19 to 48 As shown. Therefore, although Figures 19 to 33 as well as Figures 34 to 48 The design feature is a visible decorative design feature, which can be achieved by any number of alternative assembly processes or methods, and regardless of the structural components joined to form the fuselage, it is possible to achieve such decoration using the methods and components described herein, providing a visible decorative combination of features that are not completely covered by covering materials.

[0176] More specifically, in embodiments providing a decorative exterior appearance, the semi-cylindrical sections 24, such as the upper semi-cylindrical 126 and the lower semi-cylindrical 128, can be joined in a minimally overlapping manner to provide, for example... Figure 21 , Figure 24 , Figure 27 , Figure 29 or Figure 31 The external surface appearance shown depends on the design choice. Alternatively, depending on the design choice, the section formed by the right and left half-cylinder joined together to form a generally complete cylinder can have, as shown in the figure. Figure 36 , Figure 39 , Figure 42 , Figure 44 or Figure 46The exterior surface appearance is depicted in the image. The design choice of the exterior surface decoration can be uniform for all sections of the fuselage, or it can vary in different areas of the fuselage, such as distinguishing between uniform cylindrical sections 148 and non-uniform cylindrical sections 138 of the fuselage 12. For example, in an embodiment of this decorative design, elongated lines 25 can be provided along the main extent of the fuselage 12, wherein a continuous pattern with generally circular features on each side of the line, or having a pattern such as... Figures 19 to 33 The different variations of the design features shown (with in) Figure 21 , Figure 24 , Figure 27 , Figure 29 and Figure 31 (The variations shown in the figure). Similarly, in embodiments of this decorative design, elongated lines 35 may be provided along the main extent of the fuselage 12, having a continuous pattern of generally circular features on each side of the line, which may be derived from, for example... Figures 34 to 48 The selection of decorative elements shown (with in) Figure 36 , Figure 39 , Figure 42 , Figure 44 and Figure 46 (The variations shown in the diagram). As can be understood, the lines forming the surface appearance do not need to be obvious or have a significant depth, but can be subtle indentations that provide a visible appearance, particularly due to the refraction of light on the surface of the fuselage 12. For example, while a treatment of applying sealant after joining the semi-cylindrical sections can be used to reduce or effectively eliminate the appearance of lines at the joint, the aesthetic appearance of the outer surface, as shown and described herein, can be achieved with the moderate application of sealant.

[0177] In step 207, a first assembly 103 of the lower cylindrical section 128 and the upper cylindrical section 126 of the fuselage is advanced along the first assembly line 120 in the processing direction 199. Track 122-1 has a drive system 122 to advance the lower cylindrical section 128 and the upper cylindrical section 126 along track 122-1. This can be performed in a synchronous micro-pulsation manner, wherein the lower cylindrical section 128 and the upper cylindrical section 126 are advanced sequentially by micro-pulsations 129 and then paused or as part of a continuous movement process. The lower cylindrical section 128 and the upper cylindrical section 126 are manufactured in an alternating manner, such that the lower cylindrical section 128 and the upper cylindrical section 126 are paired to form the same complete cylindrical section 148, making it necessary for them to be arranged adjacently in series on the assembly line 120. Furthermore, the lower semi-cylindrical section 128 and the upper semi-cylindrical section 126 are arranged from front to back or from back to front, such that adjacent sections correspond to adjacent longitudinal portions for cylindrical joining into the body 12. In step 208, station 124 performs work on the first assembly of the lower semi-cylindrical section 128 and the upper semi-cylindrical section 126 at the second assembly line 120. Work station 124 performs work on the first assembly 103 of the lower semi-cylindrical section 118 and the upper semi-cylindrical section 116 at the first assembly line 120. This may include rotating the lower semi-cylindrical section 118 and the upper semi-cylindrical section 116 to station 124 and performing operations such as laying, hardening, demolding, frame installation, window cutting, etc. In an embodiment where the lower cylindrical section 118 and the upper cylindrical section 116 are advanced by micro-pulsations 129, work can be performed during pauses between micro-pulsations 129 and / or during micro-pulsations 129. In an embodiment where the lower cylindrical section 118 and the upper cylindrical section 116 move continuously, work can be performed while the lower cylindrical section 118 and the upper cylindrical section 116 are moving in the processing direction 199.

[0178] In step 210, the lower semi-cylindrical segment 128 and the upper semi-cylindrical segment 126 are joined together at the end of assembly line 120 to form a complete cylindrical segment 146. For example, this may include assembling the lower semi-cylindrical segment 128 and the upper semi-cylindrical segment 126 together to pass through (the door surround splice 940 for door surround 940-1, 940-2 or...) Figure 9The window surround splice 970 for window surrounds 970-1, 970-2 longitudinally joins the lower semi-cylindrical section 128 to the upper semi-cylindrical section 126 to form a second assembly of complete cylindrical sections 146. Before the installation of window surrounds 970-1, 970-2 and door surrounds 940-1, 940-2, or, in a preferred alternative, after the installation of window surrounds 970-1, 970-2 and door surrounds 940-1, 940-2, the window manufacturing allowance 970-9 and the door manufacturing allowance 940-9 are trimmed off. The complete cylindrical sections 136 and 146 of the fuselage can then be assembled from front to back (or from back to front) by circumferential joining. That is, in step 212, cylindrical sections 136 and 146 are attached together (e.g., via circumferential / circumferential joining to other complete cylindrical sections to form a complete fuselage).

[0179] Method 200 offers technological advantages over existing systems and technologies because it enables the manufacture of the fuselage in a manner efficient in both time and space. During assembly, Method 200 brings the lower cylindrical section 128 and the upper cylindrical section 126, as well as the lower cylindrical sections 118 to 116, closer to each other than existing whole-cylinder assembly methods. This method allows the lower cylindrical section 128 and the upper cylindrical section 126, as well as the lower cylindrical sections 118 to 116, to be brought to the work station, tooling equipment, and technicians via access to the interior 116-9 ( Figure 1The existing assembly methods require tools, fixtures, and technicians to enter the semi-cylindrical section through the cylinder end or doorway. The fixtures and tools must be positioned appropriately within the complete cylindrical section. When the work is complete, the fixtures, tools, and technicians must be transported through the cylinder end or doorway. Micro-pulsation 129 of the lower semi-cylindrical section 128 and the upper semi-cylindrical section 126, as well as the lower semi-cylindrical section 118 to the upper semi-cylindrical section 116, via workstations 124 and 114 respectively, brings the structure to the technicians, fixtures, and tools, thereby saving all non-value-adding time for the transport of tools, fixtures, and technicians, including setup, breakdown, and transport time. Furthermore, manufacturing delays become visually identifiable based on the section's position relative to other sections on the line. The newly manufactured complete cylindrical sections 136 and 146 of the fuselage can be immediately assembled together to form an air frame in process, and the continuous line assembly technology allows for the rapid construction of complete cylindrical sections 136 / 146 from the upper cylindrical section 116 and the lower cylindrical section 118, as well as the upper section 126 and the lower section 128 (or other parts of the fuselage). Furthermore, the continuous line assembly technology discussed herein enables the process to be performed rapidly, serially, on the same assembly line 110 for both the upper cylindrical section 116 and the lower cylindrical section 118, which is largely analogous to the process between the upper cylindrical section 116 and the lower cylindrical section 118. Moreover, the use of the disclosed method provides a way to achieve the outer surface appearance of the sections of the fuselage 12, or along its entire length, having, for example... Figures 19 to 48 The decorative features shown.

[0180] In the discussion above regarding the assembly environment 100 of the factory, the further details provided herein focus on its various aspects. Figure 3 A hybrid manufacturing system 300 is shown, which, in an illustrative embodiment, utilizes parallel and serial assembly lines to process the upper semi-cylindrical sections 116, 126 and the lower semi-cylindrical sections 118, 128. Specifically, Figure 3The diagram shows an area where assembly line 310 includes workstations 312 that perform operations on the lower cylindrical section 314 and the upper cylindrical section 316. Assembly line 310 corresponds to assembly lines 110 and 120. The lower cylindrical section 314 and the upper cylindrical section 316 correspond to lower cylindrical sections 118 and 128 and upper cylindrical sections 116 and 126, respectively. The work on column assembly line 310 is divided into assembly stages 330 and 320 for the lower cylindrical section 314 and the upper cylindrical section 316, respectively. Assembly stages 330 and 320 are static, fully pulsating positions for performing tasks such as installing cargo floor grilles 365-2, 507, 507-1 and passenger floor grilles 365-1, 506, 506-1 or crown modules 364, 732, 732-1, respectively. In another embodiment, assembly stations 330 and 320 are additional assembly lines that include workstations 312 arranged in a manner similar to workstations 312 in assembly line 310, to perform tasks such as the installation of cargo hold floor grilles 507, 507-1 and passenger floor grilles 506, 506-1 or crown modules 732, 732-1, respectively. Assembly stations 330 and 320 correspond to floor grille attachment workstations 530, 530-1 and crown module attachment workstations 730, 730-1. These assembly stations 320 and 330 include workstations 322 and 332 that perform specialized operations specifically for the lower semi-cylindrical section 314 and the upper semi-cylindrical section 316. When on assembly line 310, the lower semi-cylindrical section 314 and the upper semi-cylindrical section 316 are advanced along tracks 318, such as a series of discrete supports and / or rollers. The lower cylindrical section 314 and the upper cylindrical section 316 can be driven along track 318 by an autonomous guided vehicle (AGV), or the rollers (not shown) of track 318 themselves can be driven by a motor (not shown). Furthermore, workstation 312 dedicated to separating manufacturing allowances 970-9, 940-9, and / or support edges 143, 143-1 via finishing and / or removal of manufacturing allowances 143-9 includes workstation entrance / exit ports 313 (e.g., chutes, where trimmed material removal is indicated along chutes 398-1). Chutes 398-1 each represent the starting point of an output feeder removing material / fragments / debris from assembly line 310. Chutes 398-1 can be tracked outside workstation 312 using optical scanners and / or RFID scanners with attached barcodes or RFID tags to indicate manufacturing allowances. Materials / fragments / debris can be produced by subtractive manufacturing at one or more workstations 312 dedicated to removing allowances in window manufacturing, one or more workstations 312 dedicated to removing allowances in door manufacturing, and one or more workstations dedicated to removing allowances in supporting edge 143 manufacturing.In another embodiment, multiple workstation inlet / outlet ports 313 allow the frames 398-2, 398-4 and window surrounds 398-3 and door surrounds 398-5 supplied by feeder 359, as well as tooling, equipment, and technicians, to reach workstation 312 and to remove materials / fragments / debris from workstation 312 via slide rail 398-1. Materials, tools, equipment, or technicians enter or leave workstation 312 via workstation inlet / outlet ports 313, which allow entry or exit through different inlets 165-2 and outlets 165-3 of workstations 152-1, 152-N, and 312, rather than through inlets / outlets for the upper semi-cylindrical section 316 or the lower semi-cylindrical section 314. Therefore, the paths traveled by the lower cylindrical section 314 and the upper cylindrical section 316 differ from the paths of the removed materials, the frames 398-2 and 398-4 fed by the feeder 359, the tools, fixtures, or technicians. The workstation entrance / exit port 313 tracks the frames 398-2, 398-4, window surrounds 398-3, and door surrounds 398-5 supplied by the feeder 359 with attached barcodes or RFID tags to workstation 312, as well as the tooling, equipment, and technicians with attached barcodes or RFID tags, using an optical scanner and / or an RFID scanner connected to the workstation entrance / exit port 313.

[0181] exist Figure 3 In the middle, the lower semi-cylindrical section 314 is processed in processing direction 399 before its corresponding upper semi-cylindrical section 316. Further direction changes are indicated by paths 398-6 to 398-17. The lower semi-cylindrical section 314 leaves assembly line 310 (which utilizes micro-pulsation 129) before its upper semi-cylindrical section 316, which will join to form the complete cylindrical section 340. In the continuous assembly line, the lower semi-cylindrical section 314 and the upper semi-cylindrical section 316 move continuously at a desired rate without interruption. In this embodiment, the sequence of operations is such that the lower semi-cylindrical section 314 receives more labor-intensive and time-consuming work than the upper semi-cylindrical section 316, which is installed on two floor levels for cargo floor 365-2 and passenger floor 365-1, where a single crown module is installed on the next assembly station beyond the common pulse line. Specifically, the lower semi-cylindrical section 314 receives the installation of passenger floor grilles 365-1, including seat rails and floor panels, and cargo floor grilles 365-2, which include cargo rails and floor panels. For example, the upper semi-cylindrical section 316 can receive work such as the installation of windows, crown modules 364, storage boxes, lighting, and ceiling panels. The floor grilles 365 are assembled before reaching station 312, and the lower semi-cylindrical section 314 is positioned around the longitudinal centerline 567 before being joined to the upper semi-cylindrical section 316. Figure 5Before rotation, the floor grid 365 is installed entirely or less entirely into the lower semi-cylindrical section 314. In assembly table 330, the rotation and installation of the cargo floor and passenger floor for the lower semi-cylindrical section 314 takes approximately twice as long as for the upper semi-cylindrical section 316 in assembly table 320. Therefore, the lower semi-cylindrical section 314 always enters the upper semi-cylindrical section 316 via assembly line 310. The crown module 364 is assembled before receiving the upper section 316 and is installed entirely or less entirely into the upper section 316.

[0182] Additional feeders 366-1 to 366-4 may supply component 363 to feeders 361-362 that manufacture crown module 364 and floor grille 365 along paths 398-6, 398-8, 398-16, and 398-17. Components 363, 363-1, 363-2, and 363-3 may include ceiling panels or cargo compartments for crown module 364, or floor beams and floor panels for floor grille 365. All these feeders 366 may have additional feeders (not shown) that supply fasteners, sealants, or other sub-components in a just-in-time production manner. Each feeder 366-1, 366-2, 366-3, and 366-4 operates according to its own cycle time, which may be different from or the same as the cycle time of the lower semi-cylindrical section 314 and upper semi-cylindrical section 316 via workstation 312 of assembly line 310.

[0183] To accommodate this difference in time spent on specialized operations performed on the lower semi-cylindrical section 314, which is opposite the upper semi-cylindrical section 316, the lower semi-cylindrical section 314 leaves the assembly line 310 before the upper semi-cylindrical section 316. This gives the lower semi-cylindrical section 314 additional time (i.e., approximately twice as long) at the assembly table 330, during which time the corresponding upper semi-cylindrical section 316 continues to pass through the assembly line 310. At the assembly table 330, the lower semi-cylindrical section 314 can be held in place to receive work during the full pulse. For example, the lower semi-cylindrical section 314 is processed for twice as long from the time the upper semi-cylindrical section 316 leaves the assembly line 310 until it reaches the joining station 342. The joining station 342 is a full pulse work unit. Next, the lower semi-cylindrical section 314 has a mounted floor grid 365, and then the joists 563-2 are inverted from the joists oriented upwards 563-3 to the joists oriented downwards 56-1, and the lower section 563 is positioned to receive engagement at the engagement station 342. Specifically, this arrangement allows the lower section 314 to exit the switching station 350 and allows the upper section 316 to exit the assembly table 320 at approximately the same time, in order to be ready for engagement at the engagement station 342. In one embodiment, the lower semi-cylindrical section 314 exits before the upper section 316, so as to provide time for movement in path 391-9 and rotation of the lower section 314 before engagement as the components move along paths 391-11 and 391-12. The lower semi-cylindrical section 314 travels on path 39-13, and the upper semi-cylindrical section 316 travels on path 39-14. This ensures that there will be no substantial delay while waiting for the complete cylindrical section 340 to be assembled. Figure 3 Multiple feeders, including feeders 359 and 361-362, are also depicted, which respectively feed materials such as frames 398-2 and 398-4, window surrounds 398-3 and door surrounds 398-5, as well as crown modules 364 and floor grids 365. Feeder 361 includes a crown module 364 for assembly and installation into the upper semi-cylindrical section 316, and feeder 362 transports floor grids 365, including passenger floor grids 365-1 and cargo floor grids 365-2, which are assembled and ready to be fully or partially installed into the lower semi-cylindrical section 314. Door surround 398-5, window surround 398-3, frames 398-2, 398-4, and other sub-components 398-10 are fed to workstation 312 via feeder 359, while fasteners and sealant are fed via additional feeders 367-1 and 367-2 for just-in-time (JIT) insertion into workstation 312. Feeders 362 and 361 can be implemented in parallel to each other, feeding fasteners and / or sealant to workstations 312, 322, and 332 respectively in JIT to meet the requirements of those workstations.

[0184] In a further embodiment, gap 121 is provided in assembly lines 110, 120, 310 using micro-pulsation 129, wherein components are moved less than their length and then paused for short time increments. When gap 121 is within range 312-1, some gaps 121 result in gaps in the work performed by work station 312. Additionally, the lower semi-cylindrical section 314 or upper semi-cylindrical section 316 within range 312-1 of work station 312 may not require work based on whether a specific task needs to be performed by work station 312 within range 312-1. For example, a window surround or window manufacturing allowance cut-out station performs almost no work on the lower semi-cylindrical section 314, which has no windows, while the upper semi-cylindrical section 316 has numerous windows installed. However, the lower semi-cylindrical section 314 has a high work concentration required for the cargo door installation station, including installing the enclosure and removing manufacturing allowances for the door cutout, while the upper fuselage section does not have cargo door installation. Furthermore, the physical clearance 121 between the upper semi-cylindrical sections 316 and 314, which travel serially along the assembly line 310, also provides relief for the assembly work at workstation 312 as clearance 121 reaches each workstation 312. The clearance 121 discussed herein allows planned maintenance and / or technician rest periods at workstation 312 to be performed. The technicians performing maintenance are not the same as those working on the upper semi-cylindrical sections 316 and 314, although they are within the range 312-1 of workstation 312.

[0185] Figure 4 It is a description of the use of in the illustrative embodiments Figure 3 A flowchart of method 400 for a hybrid manufacturing system 300. Step 402 includes advancing the keel-upward lower section 314 of the aircraft fuselage through assembly line 310 in processing direction 399, such that the lower section 314 and the upper section 316 are advanced sequentially. As the lower section 314 advances past work station 312, the lower section 314 is in a keel-upward position and therefore has a similar cross-sectional shape and orientation to the subsequent upper section 316. This allows the upper section 316 and the lower section 314 to use more common components and tooling across work station 312. When work station 312 is not operating on both the upper section 316 and the lower section 314 (e.g., for the lower semi-cylindrical section, window surround installation or window manufacturing allowance cutting), maintenance or other stand-down functions can be performed intermittently when work station 312 is not operating on the half-fuselage. In addition, when workstation 312 is not in use, the workers assigned to workstation 312 are given a break, and / or maintenance is performed on workstation 312.

[0186] Step 402 may include driving the lower cylindrical section 314 via a motorized track or via motorized wheels on top of a support / pogo placed on the workshop floor 308 or via a separate device (e.g., a trolley or autonomous guided vehicle (AGV)) attached to the lower cylindrical section 314. Alternatively, this step may be performed by advancing the lower cylindrical section 314 via pulses 118 or micro-pulses 129 (e.g., frame spacing 147 or multiples or fractions thereof). Then, during pauses between pulses 118 or micro-pulses 129, or during both pauses and pulses 118 or micro-pulses 129, station 312 performs rotation and operations. In one embodiment, the lower cylindrical section 314 moves continuously, and rotation and operations are performed by station 312 during continuous movement.

[0187] In step 404, the upper semi-cylindrical segment 316 is advanced in the processing direction 399 through the assembly line 310, sequentially following and simultaneously advancing with the lower semi-cylindrical segment 314, such that the lower semi-cylindrical segment 314 and the upper semi-cylindrical segment 316 advance sequentially through the work station 312. This can be performed in a similar manner to step 402 described above, and can be performed synchronously with step 402. For example, driving tracks 112-1 and 122-1 at the assembly line 310 can cause the lower semi-cylindrical segment 314 and the upper semi-cylindrical segment 316 to move together in unison. Therefore, in one embodiment, the assembly line 310, the assembly station 320, and the assembly station 330 include tracks 112-1 and 122-1, which periodically cause the lower semi-cylindrical segment 314 and / or the upper semi-cylindrical segment 316 to pulsate fully 118 or slightly 129 in the processing direction 399. These sections can be arranged as alternating upper sections 316 and lower sections 314, such that pairs of these sections later, when joined longitudinally, form a complete cylindrical section 340 to form the fuselage 12 for the aircraft. The lower cylindrical section 314 and upper cylindrical section 316 are arranged such that the lower cylindrical section 314 and upper cylindrical section 316 for the first aircraft or a first model of the aircraft are immediately followed by a section for another aircraft or another model of the aircraft.

[0188] In step 406, as the segment advances through assembly line 310, workstation 312 performs operations on the upper semi-cylindrical segment 316 and the lower semi-cylindrical segment 314. Workstation 312 at assembly line 310 can perform operations such as laying, installing frames, trimming manufacturing allowances, installing window surrounds, installing door surrounds, cutting windows, and cutting doors. The upper semi-cylindrical segment 316 and the lower semi-cylindrical segment 314 are joined together to form complete cylindrical segments 136, 146, and 340, and can be used in subsequent steps discussed below.

[0189] In one embodiment, during the process, the lower cylindrical section 314 and the upper cylindrical section 316 are periodically advanced via assembly lines 110, 120, 310 in processing directions 199, 399 by tracks 112-1, 122-1 or other components through full-pulse or micro-pulse 129 (e.g., synchronously), and work is performed on the upper cylindrical section 316 and the lower cylindrical section 314 during pauses between full-pulse 118 or micro-pulse 129 and / or during full-pulse or micro-pulse 129. In another embodiment, the lower cylindrical section 314 and the upper cylindrical section 316 move continuously in processing directions 199, 399 via assembly lines 110, 120, 310, and work is performed on the upper cylindrical section 316 and the lower cylindrical section 316 while they are moving continuously.

[0190] In step 408, the lower cylindrical section 314 is removed from assembly line 310. This may include turning the lower cylindrical section 314 via a switching station 350, wherein the lower cylindrical section 314-1 advances along path 398-13 in full pulse to assembly table 330. The movement of the lower cylindrical section 314 along path 398-13 is a lateral translation, but it is also conceivable to use movements other than lateral translation.

[0191] Step 410 includes installing the floor grille 365 into the lower semi-cylindrical section 314 while the upper section 316 continues through the assembly line 310 via full-pulsation or micro-pulsation 129. Installation of the floor grille 365 can be performed at station 332 while the lower section 314 remains inverted (i.e., joists facing upwards). The floor grille 365 is horizontally attached to the lower semi-cylindrical section 314 to two floors comprising cargo floor 365-2 and passenger floor 365-1. In one embodiment, the floor grille 365 is pre-assembled into the cargo floor 365-2 and passenger floor 365-1 placed in the lower section 314, while in another embodiment, the floor grille 365 (particularly the cargo floor 365-2 and passenger floor 365-1) is assembled piece by piece from its components within the lower semi-cylindrical section 314.

[0192] As the upper semi-cylindrical section 316 advances past workstation 312 of assembly line 310, the floor grating installation process begins at the lower semi-cylindrical section 314. Specifically, at the lower semi-cylindrical section 314-1... Figure 3Prior to assembly station 330, floor grilles 365, and more specifically, cargo floor 365-2 and passenger floor 365-1, are assembled wholly or less. Cargo floor 365-2 and passenger floor 365-1 are assembled in feeders 366-3, 366-4, which are advanced with full or micro-pulsations 129 before being placed in feeder 362 via paths 398-6, 398-8, so as to be placed in work station 332 via path 398-7. The embodiment has work station 332, which, as a component of assembly station 330, is a fixed unit.

[0193] In step 412, the lower semi-cylindrical section 314, now advanced to assembly table 330 and referred to as lower semi-cylindrical section 314-1, is replaced in assembly line 310 by a new keel-upward semi-cylindrical section 314. The lower semi-cylindrical section 314, following the upper semi-cylindrical section 316, advances periodically through assembly lines 110, 120, 310 via tracks 112-1, 122-1 in processing directions 199, 399, in full-pulse or micro-pulse 129. Operations on the lower semi-cylindrical section 314 following the upper semi-cylindrical section 316 are performed during pauses between full-pulse 118 or micro-pulse 129 and / or during full-pulse or micro-pulse 129.

[0194] In step 414, the upper section 316 is matriculated through assembly line 310 and workstation 312, and then advanced to assembly table 320, where it is referred to as upper semi-cylindrical section 316-1. In assembly table 320, operations specific to the upper semi-cylindrical section 316, such as crown module installation, are performed.

[0195] In step 416, the upper semi-cylindrical section 316, now advanced to assembly table 320 and referred to as upper semi-cylindrical section 316-1, is replaced in assembly line 310 by a new keel-upward semi-cylindrical section 316. The upper semi-cylindrical section 316, following the lower semi-cylindrical section 314, periodically advances through assembly lines 110, 120, 310 in full-pulse or micro-pulse 129 via tracks 112-1, 122-1 in processing directions 199, 399, and the work on the upper semi-cylindrical section 316 following the lower semi-cylindrical section 314 is performed during pauses between full-pulse 118 or micro-pulse 129 and / or during full-pulse or micro-pulse 129.

[0196] In step 418, the upper semi-cylindrical section 316-1 is reached. Figure 3Before assembly table 330, crown module 364 is assembled entirely or partially. Crown module 364 is assembled in feed lines 366-1, 366-2, and is advanced with full or micro-pulsations 129 before being placed in feed line 361 via paths 398-16, 394-17, so as to be placed in work station 322 via path 398-10. The embodiment has work station 322 as a component of assembly table 320, which is a fixed unit. Floor grid 365 of lower semi-cylindrical section 314-1 continues to be installed at assembly table 330 until installation is complete.

[0197] In step 420, the lower cylindrical section 314-1 is positioned at the switching station 350 via path 391-9 for rotation / reversal to the keel-down position. When the lower cylindrical section 314-1 is in the switching station 350, it is referred to as the lower cylindrical section 314-3. The lower cylindrical section 314-3 is then inverted to the keel-down position.

[0198] In step 422, the lower semi-cylindrical section 314-1 in the assembly table 330 is replaced with a new lower semi-cylindrical section 314 from the assembly line, and the new lower semi-cylindrical section 314 is sequentially positioned after the upper semi-cylindrical section 316 when the floor grille 365 is installed into the new lower semi-cylindrical section 314-1. In the assembly line 310, the lower semi-cylindrical section 314-4 is positioned after the upper semi-cylindrical section 316.

[0199] In step 424, the lower cylindrical section 314-3 is transitioned from switching station 350 to joining station 342 via path 398-11. Joining station 342 is a fully pulsed work unit. While in joining station 342, the lower cylindrical section 314-3 is referred to as 314-2. The upper cylindrical section 316-1 is transitioned from assembly station 320 to joining station 342 via path 398-12. While in joining station 342, the upper cylindrical section 316-1 is referred to as 316-2. The lower cylindrical section 314-2 is joined to the upper cylindrical section 316-2 within joining station 342 to form complete cylindrical sections 136, 146, and 340. In an alternative embodiment where two side semi-cylinders are used to form a complete cylindrical section, the semi-cylinders on each side are formed together in a similar manner, wherein the butt joint seam is located on the top and bottom of each semi-cylinder section of the body 12. Fasteners are installed through the longitudinal skin joint between the upper section 316 and the lower section 314 (for the door surround splice 940 of door surrounds 940-1, 940-2, for...). Figure 9The window surrounds 970-1, 970-2 and the door surrounds 940-1, 940-2 are joined together using a splice 970. In a preferred alternative, before or after the installation of the window surrounds 970-1, 970-2 and the door surrounds 940-1, 940-2, the window manufacturing allowance 970-9 and the door manufacturing allowance 940-9 are trimmed. In one embodiment, this is achieved by having a splice plate 920 (…). Figures 10A to 10C ) docking splice 1201 ( Figure 12 However, other types of joints are possible, including lap joints and butt joints, wherein the splice plate 920 is on both the outer and inner surfaces. Fasteners, preferably in the form of flush-head rivets, countersunk clasps, or other types of pin fasteners, are spaced approximately equidistant along the length of the joined segments, as a series of fasteners (or mating butt joints) along each side of the butt joint or multiple rows of fasteners along each side of the butt joint. In alternative embodiments of the fastener arrangement, different resulting patterns are possible, wherein the joint seam and appearance of the fastener heads are visible on the outer surface of the joined complete cylinder. In yet another embodiment, the splice plate is installed in a plurality of segments 1042 arranged longitudinally along the length of the upper semi-cylindrical segments 116, 126 and / or the lower semi-cylindrical segments 118, 128. Figures 19 to 33 An alternative exterior surface decoration that can be obtained through this arrangement along the side of the fuselage is depicted. Figures 34 to 48 Alternative outer surface decorations can be depicted through this arrangement along the top (crown) and bottom (keel) of the fuselage. Furthermore, combinations of these arrangements are possible, such as having quarter-cylindrical segments formed as semi-cylindrical sections, which are subsequently joined together as a complete cylindrical segment as described herein, thus possessing an outer surface appearance as Figures 19 to 33 The surface shown is with Figures 34 to 48 The combination of surfaces shown.

[0200] Method 400 offers technical benefits superior to existing technologies because it enables the rapid manufacture of complete cylindrical sections 340 of the fuselage from curved sections (particularly for sections such as the lower semi-cylindrical sections 314-2 and the upper semi-cylindrical sections 316-2), while still allowing the fuselage sections to share one or more workstations 312 operating in a micro-pulsation 129, full-pulsation, or continuous-line environment. Furthermore, this assembly technique allows for easier access to the interiors 116-9 of the lower semi-cylindrical sections 314 and 316 being manufactured, as dividing the entire cylindrical section into longitudinal halves allows the structures requiring work to be delivered to the range 312-1 of workstations 312, where tooling, equipment, and technicians are given largely unrestricted access. With indexing, this technique significantly reduces non-value-adding setup time compared to other methods that bring tools, equipment, and technicians to the work position and set up workstations 312 within the complete cylindrical sections 136, 146. Setting up the workstations within the complete cylindrical sections 136 and 146, then moving them within all work areas within those sections, and then disassembling them again for removal, results in no added-value time during the construction process. This arrangement allows for as much assembly work as possible while the fuselage sections are in two halves, and reduces the amount of assembly work required after joining them into a complete cylinder. Easier access makes it easier to insert tools for the workstations, easier to inspect, easier for workers to exit, and easier for parts to exit. This increases the efficiency of the workstations. Furthermore, the sequence of the lower cylindrical section 314 and the upper cylindrical section 316 ensures that specialized operations performed do not delay the manufacturing of the complete cylindrical sections 136 and 146.

[0201] Figure 5 The depiction illustrates the reversal of the lower semi-cylindrical section 314-1 in the illustrative embodiment, and corresponds to... Figure 3 Arrow 5 in the view. Figure 5 In the middle, the vertical reversing station 560 includes a frame 562, to which a rotating element 564 is attached. The lower cylindrical section 314-3 surrounds the longitudinal centerline 567 before joining the upper cylindrical section 316-2. Figure 5 Rotation. A support column 566 protrudes from the rotating element 564 and is attached to the lower semi-cylindrical section 563, where one or more floor grids 565 are installed, such as a cargo floor 594 and a cabin floor 596. Figure 5For clarity, cargo floor 594 and cabin floor 596 are omitted. The rotating element 564 then rotates, reversing the keel 563-2 of the lower semi-cylindrical section 563 from keel upward orientation 563-3 to keel downward orientation 56-1, and arranging the lower semi-cylindrical section 563 in the position for engagement with the upper semi-cylindrical section 316-2 in the engagement station 342.

[0202] By using splicing panels 920 ( Figure 9 ) docking splice 1201 ( Figure 9 Fasteners are installed at the joint station 342, where the lower semi-cylindrical section 314-1 is joined to the upper semi-cylindrical section 316-1. The splicing plate 920 overlaps with the mating ends 1032, 1132 of the upper and lower semi-cylindrical sections 314-1. Each frame 147-1, 912 also has a splicing plate (e.g., ) specifically designed for each frame 147-1, 398-2, 398-4, 912 in the joint station 342. Figure 9 The splicing plates 920 are butt-jointed together. This results in the upper semi-cylindrical section 316 and the lower semi-cylindrical section 314-1 being longitudinally spliced ​​together, including splicing the skin 911 and the frame 912 together. This longitudinal splicing of the semi-cylinders can be constructed in a manner that provides the appearance of the residual outer surface along the longitudinal line of the main range of the fuselage section, and can include the appearance of fasteners on each side of the longitudinal line as a single row of fastener heads (such as...) on each side of the longitudinal line. Figure 21 , Figure 29 , Figure 36 and Figure 44 (as depicted in the text), or may have a pair of fastener heads (such as) on each side of the longitudinal line. Figure 24 , Figure 27 , Figure 31 , Figure 39 , Figure 42 or Figure 46 (As depicted in the image). Panel 597, 920 ( Figure 9 The splicing plates 597, 920 can be installed on the lower or upper semi-cylindrical section (or each side semi-cylindrical section in such an alternative embodiment having a right and left semi-cylindrical section) or both before entering the joining station 342 as part of the assembly station 320 and / or assembly station 330. The splicing plates 597, 920 can be installed entirely in the joining station 342. In this embodiment, the joining station 342 also performs any electrical or piping installation in the splicing area 914. Insulators and wall panels are installed in the splicing area 914. The floor grid attachment station 530, the vertical reversing station 560, and the joining station 342 are separated along the processing direction 501 of the lower semi-cylindrical section 314-1.

[0203] exist Figure 6The image depicts a cross-section of the fuselage 598 in the assembly station 342, which includes the installed cargo floor 365-2 and passenger floor 365-1. Figure 6 The diagram also shows that the coronal module 364 and splicing panels 597 and 920 have been added to two locations. In one embodiment, the coronal module 364 includes a storage box and internal lighting; for clarity, these details are shown in [the diagram]. Figure 6 Not shown in the figure. Insulator 591 and internal panel 593 are also shown as mounted. Top module 364, splice plates 597, 920, insulator 591, internal panel 593, mounted cargo floor 365-2 and passenger floor 365-1 are not shown to scale and are shown in block diagram form for clarity. As shown, splice plates 597, 920 are mounted on the inner mold line (IML) 595 of the semi-cylindrical section 24. In another embodiment, not shown, splice plates 597, 920 are mounted on the outer mold line (IML) (592) of the semi-cylindrical section.

[0204] Figure 7 It is a description of the use of, respectively, in the illustrative embodiments. Figure 5 , Figure 6 A flowchart of method 600 for floor grating assembly lines 500, 500-1. According to method 600, step 602 includes receiving a lower semi-cylindrical section 314-1 with the keel upward orientation 563-3, and step 604 includes installing a cargo compartment floor grating 365-2 and then a passenger floor grating 365-1 into the lower semi-cylindrical section 314-1 while the lower semi-cylindrical section 314-1 is in the keel upward orientation 563-3. In one embodiment, the lower semi-cylindrical section 314-1 is positioned in the assembly table 330 approximately twice, while the upper semi-cylindrical section 316-1 is within the assembly table 320. In one embodiment, the cycle time for the lower semi-cylindrical section 314-1 after entering the assembly table 330 is fourteen hours. Before the lower semi-cylindrical section 314-1 is inverted with the keel downward orientation 363-1, piping and electrical systems, as well as insulation and wall panels not in the joint area, are added to the assembly table 330 (not shown). Step 606 includes rotating the lower semi-cylindrical segment 314-1 into the keel downward orientation 563-1, and step 608 includes attaching the lower semi-cylindrical segment 314-2 to the upper semi-cylindrical segment 316-2 to form the complete cylindrical segment 148. Attaching the first semi-cylindrical segment 314-2 to the second semi-cylindrical segment 316-2 involves at least splicing the skin to the splice plates 597, 920 together and splicing each frame together. For example, this operation can be performed during full pulsation.

[0205] In another embodiment, the lower cylindrical section 314-1 advances in the processing direction 199 before receiving the parts produced by the floor grid assembly lines 500, 500-1, and the lower cylindrical section 314-3 advances in the processing direction 199 after the floor grid 506 is installed, and further advances in the processing direction 199 as the lower cylindrical section 314-2 after rotation.

[0206] Method 600 provides technical benefits by enabling the lower semi-cylindrical sections 314 to be processed and receive floor gratings while remaining inverted, without requiring the lower semi-cylindrical sections 314-1 to be rotated until just before the lower semi-cylindrical section 314-2 engages with the corresponding upper semi-cylindrical section 316-2. This reduces the need for specialized equipment in the factory floor for working with the inverted lower semi-cylindrical sections 314-2 prior to engagement. Specialized equipment includes flooring for technicians and / or robots, which is completely or partially removed before engaging the lower semi-cylindrical sections 314-2 with the upper semi-cylindrical section 316-2. Therefore, technicians can work detached from supports mounted to the factory floor or directly on the factory floor before inversion, without the difficulties of installing cargo or passenger flooring, instead of positioning the technician and / or robot support area in the same space as the flooring installed in the joist-down orientation 563-1. This is another example of bringing work to tools, fixtures, and technicians. The upward-oriented 563-3 floor grid allows for a more comfortable / ergonomic installation location for tools, equipment, robots, and / or technicians.

[0207] Figure 8 This is a flowchart depicting a method 900 for installing splicing plates 597, 920 for joining semi-cylindrical sections in an illustrative embodiment. Splicing plates 597, 920, 920-1 or segment 1042 ( Figure 10AThe material can be a composite material, titanium, or aluminum. If it is aluminum, the splice plates 597, 920, and 920-1 are fastened and their mating surfaces are sealed, and otherwise sealed, to avoid current problems when fixed to the lower semi-cylindrical section 314 and the upper semi-cylindrical section 316. If it is titanium, when fixed to the lower semi-cylindrical section 314 and the upper semi-cylindrical section 316, the splice plates 920, 920-1, and / or section 1042 are fastened and their mating surfaces are sealed, and otherwise sealed. The composite splice plates 920, 920-1, and / or section 1042 are joined and / or fastened in place. If the composite splice plates 920, 920-1, and / or section 1042 are fastened, the mating surface is sealed when fixed to the lower semi-cylindrical section 314 and the upper semi-cylindrical section 316. Step 902 includes receiving upper cylindrical segments 116, 126, 316 or lower cylindrical segments 118, 128, 314-2 at assembly stations 320, 330 or joining stations 342, 342-1 on assembly lines 110, 120, 310. In one embodiment, this includes receiving upper cylindrical segments 116, 126, 316-2 in assembly lines 110, 120, 310, which advance through multiple work stations 114, 124, 312 in the processing direction 199, respectively. In another embodiment, step 902 includes receiving lower cylindrical segments 118, 128, 314 in assembly lines 110, 120, 310 through multiple work stations 114, 124, 312 in the processing direction 199. Each workstation 114, 124, 312 in assembly lines 110, 120, 310 can operate simultaneously with other workstations 114, 124, 312, working on the same upper cylindrical sections 116, 126, 316 or lower cylindrical sections 118, 128, 314. These workstations 114, 124, 312 can operate independently of or in coordination with other workstations 114, 124, 312, working on the upper cylindrical sections 116, 126, 316 or lower cylindrical sections 118, 128, 314 simultaneously. A splicing plate 920 is installed on the upper cylindrical sections 116, 126, 316 or lower cylindrical sections 118, 128, 314 as it advances through workstations 114, 124, 312, or one splicing plate 920 is installed on each of them. In one embodiment, the splice plate 920 is installed in dedicated workstations 114, 124, 312. In another embodiment, the splice plate 920 is installed in assembly lines 110, 120, 310 using a flexible track device 1024, which follows a track 1023 removably mounted to upper semi-cylindrical sections 116, 126, 316 or lower semi-cylindrical sections 118, 128, 314.As the flexible track device 1024 and track 1023 advance through workstations 114, 124, and 312, they serve as temporary components of the upper cylindrical sections 116, 126, and 316 or the lower cylindrical sections 118, 128, and 314. Workstations 114, 124, and 312 are operated as the device advances through them, and the flexible track device 1024 and track 1023 also operate on them. When the splicing plate 920 is installed on the upper cylindrical sections 116, 126, and 316 or the lower cylindrical sections 118, 128, and 314, the flexible track device 1024 and track 1023 are separated and then cycle back to assembly lines 110, 120, and 310. Upper cylindrical sections 116, 126, 316 and / or lower cylindrical sections 118, 128, 314 exit assembly lines 110, 120, 310, with splice plates 920 mounted on one or both longitudinal edges and each advancing to assembly tables 320, 330, where crown modules 364 and cargo floor grilles 365-2 and passenger floor grilles 365-1 are installed, either fully or partially. The splice plate 920 is mounted on one of the lower cylindrical sections 118, 128, 314 and / or the upper cylindrical sections 116, 126, 316, while the other edge of the splice plate 920 is secured in a joining station 342. Alternatively, the splice plate 920 is mounted in assembly tables 330 and 320 onto the lower semi-cylindrical sections 118, 128, 314 and / or the upper semi-cylindrical sections 116, 126, 316, respectively. Flexible track devices 1024 and tracks 1023 are used, or otherwise, to mount the splice plate 920 onto one of the lower semi-cylindrical sections 118, 128, 314 and / or the upper semi-cylindrical sections 116, 126, 316, while the other edge of the splice plate 920 is secured in the joining station 342. In another embodiment, the splice plate 920 is fully attached within the joining station 342. Flexible track devices 1024 and track 1023 are used, or some other means, to mount splice plate 920 onto both the lower semi-cylindrical sections 118, 128, 314 and the upper semi-cylindrical sections 116, 126, 316 in the joining station 342. Step 904 includes mounting splice plate 920 at the upper semi-cylindrical sections 116, 126, 316 and / or the lower semi-cylindrical sections 118, 128, 314. In one embodiment, this includes at the boundary 1032 of the upper semi-cylindrical section 316. Figures 10A to 10C The splicing plate 920 is installed at point 1032, 1132, while the upper semi-cylindrical section 316 advances through assembly lines 110 and 120, so that the splicing plate 920 moves from the boundary 1032, 1132. Figure 11A and Figure 11BIn another embodiment, step 904 includes installing a splice plate 920 at the boundary 1032 of the lower semi-cylindrical section 314, which travels through the assembly line such that the splice plate 920 protrudes from the upper boundary, such as... Figures 10A to 10C Boundary 1032. Panel 920 at the lower boundary (e.g., Figures 10A to 10C The upper half of the lower cylindrical section 314 overlaps above the boundary 1032, wherein approximately its upper cylindrical half is attached to the upper cylindrical section 316 via multiple rows of fasteners and mating surface sealing and / or joining. This is the first part of establishing the engagement of the butt joint 1201 formed by the splice plate 920. The protruding portion of the splice plate 920 will overlap the upper boundary of the lower cylindrical section 314 (e.g., Figures 10A to 10C On the boundary 1032), and sealed and / or joined with mating surfaces by multiple rows of fasteners. The protruding portion will be half the width of the splice plate 920 divided along a longitudinal line. The longitudinal line is located approximately at half the width of the splice plate 920, and approximately at the mating point of the upper semi-cylindrical section 316 and the lower semi-cylindrical section 314. That is, a single splice plate 920 corresponding to the length of the semi-cylindrical sections 314, 316, or comprising multiple joint sections 1042 (arranged sequentially or end-to-end and installed along the length of the upper semi-cylindrical section 316) Figures 10A to 10C The splice plate 920 can be positioned to contact the IML 1034 of the upper semi-cylindrical section 316, such that the splice plate 920 protrudes below the lower boundary of the upper semi-cylindrical section 316. The splice plate 920 can be installed via jointing or via fasteners 1050 such as those used for mounting the upper semi-cylindrical section 316 and the splice plate 920. In another embodiment, the splice plate 920 is installed as a splice mounted on the OML 1035 or placed on the IML 1034 and the OML 1035 via a combination of jointing and fasteners. Similarly, the splice plate 920 can be installed on the lower semi-cylindrical section 314 before being advanced in the processing direction 199 to the jointing station 342.

[0208] At the lower boundary (e.g., Figures 10A to 10C Installing the splicing panel 920 at the boundary 1032) may include installing the splicing panel 920 such that the splicing panel 920 protrudes beyond the lower boundary (e.g., Figures 10A to 10C Below or otherwise placed near the lower boundary (e.g., 1032) Figures 10A to 10C(Boundary 1032). In one embodiment, the splice plate 920 is installed during pauses of the upper semi-cylindrical section 316 at assembly line 110 between micro-pulses 129 in the processing direction 199, during micro-pulses 129, or during pauses between micro-pulses 129 and during both micro-pulses 129 (e.g., via micro-pulsation installation in the section or via full-pulsation installation as a full splice plate installation via station 114 on a micro-pulsation or full-pulsation line). In another embodiment, the splice plate 920 is installed during continuous movement of the upper semi-cylindrical section 316 in the processing direction 199. Thus, the splice plate 920 is installed on the assembly line through which the upper semi-cylindrical section 316 travels. In yet another embodiment, the splice plate 920 is installed after the relevant upper semi-cylindrical sections 116, 126, 316 and / or lower semi-cylindrical sections 118, 128, 314 have left assembly lines 110, 120, 310 and entered assembly station 320 or assembly station 330 (where cargo hold floor grilles 365-2, passenger floor grilles 365-1, or crown modules 364 are installed). In yet another embodiment, the installation of the splice plate 920 is performed during the installation of crown modules 364, or simultaneously during the installation of cargo hold floor grilles 365-2 and passenger floor grilles 365-1 into one of the upper semi-cylindrical sections 316 and lower semi-cylindrical sections 314.

[0209] In another embodiment, the splicing plate 920 is attached to the upper cylindrical section 316-2 of the assembly table 320 (i.e., the crown module grille station 730) for mounting crown modules 364, 732. In yet another embodiment, the splicing plate 920 is mounted on the lower cylindrical section 314-2 of the assembly tables 330, 330-1 for mounting cargo floor grilles 365-2 and passenger floor grilles 365-1, or simultaneously mounted on both the upper cylindrical section 316-2 and the lower cylindrical section 314-2 in the joining station 342. Therefore, most or even all of the splicing activities in this embodiment preferably occur in the joining station 342.

[0210] According to an embodiment, the dimensions of the splicing panel 920 are designed for IML1034 ( Figures 10A to 10C ) or OML1036 ( Figures 10A to 10C Installation. The mating splice 1201 itself may include a splice plate 920 or both disposed at IML 918, 1034 or OML 916, 1036, depending on the embodiment. That is, the splice plate 920 is mounted on IML 918, 1034 or OML 916, 1036, or mounted on one edge of the upper semi-cylindrical section 316-2 and complementaryly mounted on one edge of the lower semi-cylindrical section 314-2. The splice plate 920 may be the same length as, or a portion of, the semi-cylindrical sections 117, 117-1 discussed above, such as splice section 1042 ( Figures 10A to 10C Multiple splicing segments 1042 are arranged longitudinally in series and positioned along the entire full pulse 118-4 of the semi-cylindrical segments 117, 117-1 located on two splicing pieces or a single splicing piece, as described above. Furthermore, splicing plates 920 can be longitudinally mounted onto the upper semi-cylindrical segment 316 or the lower semi-cylindrical segment 314 before entering the joining station 342, 342-1, which is part of the assembly table 320, or at the attachment table 330. Further, splicing plates 920 can be longitudinally mounted across the splicing area 914 in the width direction and onto both the upper semi-cylindrical segment 316-2 and the lower semi-cylindrical segment 314-2 as part of the work performed in the joining station 342, 342-1. In another embodiment, the splicing plate 920 also serves as a longitudinally extending longitudinal beam that straddles the splicing area 914 when connecting to the upper semi-cylindrical section 316-2 and the lower semi-cylindrical section 314-2.

[0211] The splicing component between the upper semi-cylindrical section 316-2 and the lower semi-cylindrical section 314-2 is the butt splicing component 1201. Figure 12 In yet another embodiment, the upper semi-cylindrical section 316-2 is overlapped with the lower semi-cylindrical section 314-2, which may or may not have the splicing plate 920, as needed. Thus, the overlapping portion fastened together exists between the longitudinal edge of the lower semi-cylindrical section 314-2 and the longitudinal edge of the upper semi-cylindrical section 316-2.

[0212] Step 906 includes aligning the upper semi-cylindrical segment 316-2 with the lower semi-cylindrical segment 314-2 to form a splicing area 914 therebetween. In one embodiment, this includes aligning the upper semi-cylindrical segment 316-2 with the lower semi-cylindrical segment 314-2 while the upper semi-cylindrical segment 316-2 remains abutting against the lower semi-cylindrical segment 314-2, and the upper semi-cylindrical segment 316-2 is supported by a bracket 1150 ( Figure 11A and Figure 11B This can be performed simultaneously with support from other equipment. Therefore, the lower cylindrical section 314-2 can be placed in the bracket 1150 before being aligned with the upper cylindrical section 316-2. In embodiments where the lower cylindrical section 314-2 is also processed via assembly lines 110, 120, 310, aligning the upper cylindrical section 316-2 with the lower cylindrical section 314-2 may include via... Figure 5 The vertical reversing station 560 rotates the lower semi-cylindrical section 314-2 from the keel upward orientation 563-3 to the keel downward orientation 563-1.

[0213] In step 908, the upper semi-cylindrical segment 316-2 or the lower semi-cylindrical segment 314-2 is joined by attaching the splicing plate 920 within the splicing area 914. In one embodiment, the upper semi-cylindrical segment 316-2 is joined to the lower semi-cylindrical segment 314-2 by attaching the splicing plate that straddles boundary 1032 and boundary 1132. As described herein, the splicing plate 920 is mounted to the lower semi-cylindrical segment 314-2 and the upper semi-cylindrical segment 316-2 via co-attachment and / or via mounting fasteners or both. In one embodiment, joining the first semi-cylindrical segment (such as the upper semi-cylindrical segment 316-2) and the second semi-cylindrical segment (such as the lower semi-cylindrical segment 314-2) includes butt-jointing the segments together, as described herein.

[0214] Additionally, to complete the butt joint 1201, frames 912 and 912-1 are joined together within the splicing area 914. Frames 912 and 912-1 correspond to frames 147-1 and 912, 398-2, and 398-4. Both the upper cylindrical section 316-2 and the lower cylindrical section 314-2 include frames 912 and 912-1 and frame splicing components 913, such as short frames 911-1, joining frames 912 to 912-1, and splicing plates 920 and skin 911. Frame splicing components 913 use short frames 911-1 as part of the butt joint 1201 to splice frames 912 to 912-1. Frames 912 and 912-1 are located on the upper cylindrical section 316-2 and the lower cylindrical section 314-2, respectively. Using short frame 913-1 as part of frame splice 913 ensures that frames 912 and 912-1 installed in the upper semi-cylindrical section 316-2 and the lower semi-cylindrical section 314-2 do not extend all the way to the boundary 1032. Figures 10A to 10C , Figure 11A and Figure 11B ) and boundary 1132 ( Figure 11A and Figure 11B This facilitates the placement of the splice panel 920 directly against the skin 911 within the splice area 914. A short frame 913-1 spans the splice panel 920 to join frame 912 to frame 912-1. The short frame 913-1 is also secured to the splice panel 920 via the skin 911.

[0215] The other configuration does not have a short frame 913-1 fastened by skin 911 and splice plate 920.

[0216] The frames 912 and 912-1 of the upper semi-cylindrical section 316-2 and the lower semi-cylindrical section 314-2 end before the frame splice 913, so that the splice plate 920 can be placed directly abutting against the skin 911 within the splice area 914. The frame splice 913 is installed on the IML 918 of the upper semi-cylindrical section 316 and the lower section 314, and then the short frame 91-1 is installed to connect the frames 912 and 912-1 of the upper semi-cylindrical section 316-2 to the lower semi-cylindrical section 314-2 and across the frame splice 913. Another advantage is that the frames 912 and 912-1 do not extend all the way to the boundary 1032 ( Figures 10A to 10C ) and boundary 1132 ( Figure 11A and Figure 11B This allows for the movement of the upper cylindrical section 316-2 and the lower cylindrical section 314-2 along the track 112-1 before they are spliced ​​and joined at the joining station 342. The frames 912, 912-1 do not interfere with the track 112-1. It also facilitates the installation of the splicing plate 920. The splicing plate 920 is installed in the splicing area 914 to connect the skins 911, 911-1 of the upper cylindrical section 316-2 to the lower cylindrical section 314-2, respectively. According to an embodiment, the splicing plate 920 is installed at the frame splice 913 at IML 918 or OML 916. Furthermore, the splicing plate 920 is designed to occupy the entire length of the upper cylindrical section 316-2 and the lower cylindrical section 314-2, or a portion thereof, as the splicing segment 1042. The splicing plate 920 can be installed on the upper semi-cylindrical section 316-2 or the lower semi-cylindrical section 314-2 before entering the assembly table 320 or 330, for connecting the crown module 364 or the floor grid 365 respectively.

[0217] Figure 9 It is depicted as an illustrative embodiment via a mating splice 1201 ( Figure 12 A block diagram 990 shows the upper semi-cylindrical section 316-2 and the lower semi-cylindrical section 314-2 connected by a splice plate 920. Both the upper semi-cylindrical section 316-2 and the lower semi-cylindrical section 314-2 include frames 912, 912-1 and frame splices 913, such as short frames 911-1, joining frames 912 to 912-1, splice plate 920, and skin 911. From the upper semi-cylindrical section 316-2 to the lower semi-cylindrical section 314-2, the frame joints 913 utilize short frames 911-1 to butt-joint splice 1201 frames 912, 912-1, respectively. Using short frames 913-1 as part of the frame splice 913 ensures that frames 912, 912-1 installed in the upper semi-cylindrical section 316-2 and the lower semi-cylindrical section 314-2 do not extend all the way to the boundary 1032. Figures 10A to 10C ) and boundary 1132 ( Figure 11A and Figure 11BThis facilitates the gap for the splicing panel 920. A short frame 913-1 bridges the splicing panel 920 to join frame 912 to frame 912-1. Therefore, the assembly sequence is to install the splicing panel 920 before installing the short frame 913-1.

[0218] The frames 912 and 912-1 of the upper semi-cylindrical section 316-2 and the lower semi-cylindrical section 314-2 terminate in the splicing area 914 before the frame splicing member 913 to facilitate the placement of the splicing plate 920. The frame splicing member 913 is installed on the IML 918 of the upper semi-cylindrical section 316-2 and the lower section 314-2, and then the short frame 91-1 is installed to connect / splice the frames 912 and 912-1 of the upper semi-cylindrical section 316-2 together to the lower semi-cylindrical section 314-2 and across the splicing area 914. Another benefit of terminating the frames 912 and 912-1 of the upper semi-cylindrical section 316-2 and the lower semi-cylindrical section 314-2 before the frame splicing member 913 in the splicing area 914 is that it facilitates the movement of the semi-cylindrical sections along the track 112-1 before splicing and joining at the joining station 342. Splicing plates 597, 920, and 920-1 are installed in splicing area 914 to connect the skins 911 and 911-1 of the upper semi-cylindrical section 316-2 together to the lower semi-cylindrical section 314-2, respectively. Furthermore, splicing plates 597, 920, and 920-1 are designed to occupy the entire length or a portion thereof of the upper semi-cylindrical section 316-2 and the lower semi-cylindrical section 314-2. Splicing plates 597, 920, and 920-1 can be installed onto the upper semi-cylindrical section 316-2 or the lower semi-cylindrical section 314-2 before entering assembly tables 320 and 330 for respective engagement.

[0219] In another embodiment, splice plates 597, 920, 920-1 at IML 918 operate as longitudinally extending longitudinal beams (not shown) to connect the skin 911 of the upper semi-cylindrical section 316-2 to the skin 911 of the lower semi-cylindrical section 314-2. In such an embodiment, the skin 911 of the upper semi-cylindrical section 316-2 is adjacent to the skin 911-1 of the lower semi-cylindrical section 314-2. In another embodiment, the skin 911 of the upper semi-cylindrical section 316-2 and the skin 911-1 of the lower semi-cylindrical section 314-2 overlap as part of an lap joint. In one embodiment, frame splice 913 is nested (not shown) in frames 912, 912-1 relative to the flanges (not shown) and webs (not shown) of frames 912, 912-1, or vice versa. In other words, each frame 912 will be spliced ​​to the corresponding frame 912-1. In another embodiment, the upper semi-cylindrical segment 316-2 and the lower semi-cylindrical segment 314-2 include frames 912 and 912-1. Frames 912 and 912-1 are formed by multiple frame segments 912-5, 912-6 and frame segments 912-3, 912-4 spliced ​​together, respectively. Typically, there are multiple frame segments 912-3, 912-4, 912-5, 912-6, each forming an arc of 90 degrees or 60 degrees or some other arc length, which, when spliced ​​together, form approximately 180 degrees of frame 912-1, 912 arcs, respectively. In yet another example, there are multiple frames 912, 912-1 nested within a frame splice 913 that spans from the upper semi-cylindrical segment 316-1 to the lower semi-cylindrical segment 314-2.

[0220] In this example, other components such as electrical 930, insulation 950, and conduit 960 are also found in the upper semi-cylindrical section 316-2 and / or the lower semi-cylindrical section 314-2 and / or even partially within the splicing area 914. The upper door surround 940-1 is joined to the lower door surround 940-2 via a door surround splice 940 that spans or is located within the splicing area 914. The upper window surround 970-1 is joined to the lower window surround 970-2 via a window surround splice 970 that spans or is located within the splicing area 914. Before the installation of the window surrounds 970-1, 970-2 and the door surrounds 940-1, 940-2, or in a preferred alternative, afterward, window manufacturing allowances 970-9 and door manufacturing allowances 940-9 are trimmed. The upper electrical component 930-1 is joined to the lower electrical component 930-2 via an electrical component connector 930 that spans or is located within the splicing area 914. The upper piping component 960-2 is joined to the lower piping component 960-2 via a piping component 960 that spans or is at least partially located within the splicing area 914. The piping components can be hydraulic (water or hydraulic fluid) and / or pneumatic, which is a matter of design choice.

[0221] The various arrangements of the splicing components discussed in this article can be used in a fixed unit at full pulsation 118-4, or can be part of a line advanced via micro-pulsations 129, 129-1, 129-2, 129-3, 129-4 or a continuous line, wherein the station operates on the complete cylindrical section 340 as the upper cylindrical section 316-2 and the lower cylindrical section 314-2 are pulsated through the station.

[0222] Figures 10A to 12 An illustrative embodiment of a splicing installation system advancing in micro-pulsation 129 or full-pulsation propulsion is shown, illustrating the installation of splicing plates 597, 920, 920-1 and the engagement of the upper semi-cylindrical section 316 with the lower semi-cylindrical section 314. Figure 10AIn this example, assembly line 1000 includes a track 1010, illustrated for transporting upper semi-cylindrical sections 316 and / or lower semi-cylindrical sections 314 having a lower boundary 1032 in a processing direction 199. In this example, assembly line 1000 may be a standalone system, or more likely, part of assembly lines 110, 120, 310 and workstation 1020 corresponding to workstations 114, 124. Workstation 1020 includes an end effector 1022 and / or a tool that aligns the splicing sections 1042 of splice plates 597, 920, 920-1 with the lower boundary 1032. Workstation 1020 mounts fasteners 1050 via splice plates 597, 920, 920-1 or splicing sections 1042 and the upper semi-cylindrical sections 316 and / or lower semi-cylindrical sections 314 on which the splice plates or splicing sections are mounted. Specifically, in the initial portion 1025 of this aspect of assembly line 1000, work station 1020 installs splice plates 597, 920, 920-1, or splice segments 1042 on each IMP 1034 located at the lower boundary 1032 defined by the upper semi-cylindrical segment 316 and / or the upper boundary of the lower semi-cylindrical segment 314. Segment 1042 has a length L. Splice plates 597, 920, 920-1, or segment 1042 have a height protruding a distance H from the lower boundary 1032 of the upper semi-cylindrical segment 316 and / or the lower semi-cylindrical segment 314-2. The distance H is approximately equal to half the width W of the splice plates 597, 920, 920-1, or segment 1042. During installation, splice plates 597, 920, 920-1 remain in contact with the IMP 918 of the upper semi-cylindrical segment 316-2. After installation, the height of track 1010 can be varied by a distance H, such that the highest point of the upper semi-cylindrical segment 316 or the highest point of the lower semi-cylindrical segment 314 remains constant throughout the assembly line 1000. In another example not shown, the splice plate 920-1 is only on the OML916 side, or on the IML 918 and OML916 sides, on the opposing upper boundary 1132 or lower boundary 1032. Operation of any of these configurations is possible via the end effector 1022 of work station 1020. Work station 1020 is capable of continuously and sequentially installing splice plates 920 or segments 1042 on the lower semi-cylindrical segment 314 and the upper semi-cylindrical segment 316, and then skipping subsequent lower semi-cylindrical segments 314 and upper semi-cylindrical segments 316 on which the corresponding segments to be joined will be engaged. The splicing plate 920-1 is an OML916 mounting version of the IML918 mounted on the splicing plate 920. The upper semi-cylindrical section 316 or the lower semi-cylindrical section 314 has one of the splicing plates 920, 920-1, or 1042 along each lower boundary 1032 or each upper boundary 1132.Examples not shown have an upper semi-cylindrical section 316 or a lower semi-cylindrical section 314, which includes splicing plate 920 and splicing plate 920-1 or section 1042, or a combination of splicing plate 920 or splicing plate 920-1 and section 1042, which sandwich each upper boundary 1132 or each lower boundary 1032 in the middle.

[0223] exist Figure 10B In another example, assembly line 1000-1 includes a track 1010-1, illustrated as transporting upper cylindrical sections 316 and / or lower cylindrical sections 314, each having a lower boundary 1032 and / or an upper boundary 1132, respectively, in a processing direction 199. An end effector 1022 removably places a flexible track assembly 1024 onto the upper cylindrical section 316 and / or lower cylindrical section 314 at a placement point 1028. A workstation 1020 then positions a pick-up point 1029 and waits to remove the flexible track assembly 1024 from the upper cylindrical section 316 and / or lower cylindrical section 314 after the splice plate 920 or section 1042 is installed. Then, workstation 1020-1 transports the flexible track device 1024 to placement point 1028, where it awaits placement on the next upper semi-cylindrical section 316 and / or lower semi-cylindrical section 314 where splice plates 920, 920-1, or section 1042 need to be installed. Workstation 1020-1 moves along track 1010 between placement point 1028 and pick-up point 1029. In this example, assembly line 1000-1 may be a standalone system, or more likely, part of assembly lines 110, 120, 310 and workstation 1020-1 corresponding to workstations 114, 124. The flexible track device 1024 follows track 1023, which is removably mounted on the upper semi-cylindrical section 316 or the lower semi-cylindrical section 314, and installs splice plate 920 or segment 1042, while other operations are performed by workstations 114 and 124 in assembly lines 110, 120, and 310. The upper semi-cylindrical section 316 or the lower semi-cylindrical section 314 has one of splice plate 920 or splice plate 920-1 or segment 1042 along each lower boundary 1032 or each upper boundary 1132. Examples not shown have an upper cylindrical section 316 or a lower cylindrical section 314, which includes splicing plates 920 and 920-1, or section 1042, or a combination of splicing plates 920, 920-1, and 1042, which clamp each upper boundary 1132 or each lower boundary 1032 in the middle. Another example has a flexible track 1024 that can be placed and removed manually or entirely manually without any mechanical assistance, using assistance from workstation 1020-1.

[0224] exist Figure 10CIn another example, assembly line 1000-2 includes track 1010-2, illustrated as holding upper semi-cylindrical sections 316-1 and / or lower semi-cylindrical sections 314-1, respectively, having lower boundaries 1032 and / or upper boundaries 1132, before advancing along the processing direction 199. End effector 1022-2 removably places flexible track device 1024 on the upper semi-cylindrical sections 316-1 and / or lower semi-cylindrical sections 314-1. In a full-pulse scenario, workstation 1020-2 is part of assembly table 320 for the upper semi-cylindrical section 316-1 and / or assembly table 330 for the lower semi-cylindrical section 314-1. After placing the flexible track device 1024, workstation 1020-2 does not advance. Pick-up point 1029-2 coincides with placement point 1028-2. After installing splicing plates 920, 920-1, and / or segment 1042, workstation 1020-2 awaits the removal of the flexible track device 1024 from the upper semi-cylindrical segment 316-1 and / or lower semi-cylindrical segment 314-1 (not shown in the illustration). Workstation 1020-2 then retracts and holds the flexible track device 1024, awaiting placement on the next upper semi-cylindrical segment 316-1 and / or lower semi-cylindrical segment 314-1 where splicing plate 920 or segment 1042 is not required. Splicing plate 920-1 is an OML916 mounting version of the IML918 mounted on splicing plate 920. Splicing plates 920, 920-1, and / or segment 1042 enable the installation of the flexible track device 1024. The flexible track device 1024 follows track 1023, which is removably mounted on the upper semi-cylindrical section 316-1 or the lower semi-cylindrical section 314-1, and installs splice plates 920, 920-1 or section 1042 while performing other operations, such as in assembly tables 320 and / or 330. An end effector 1022-2 removably places the flexible track device 1024 on the upper semi-cylindrical section 316-1 and / or the lower semi-cylindrical section 314-1, and then removes it upon completion of the operation. The flexible track device 1024 is conveyed by workstation 1020-2 and placed on the lower semi-cylindrical section 314-1, and splice plates 920, 920-1 or section 1042 are installed, while cargo floor grilles 365-2 and passenger floor grilles 365-1 are installed in assembly table 320. Similarly, in another example, the flexible track device 1024 is conveyed by workstation 1020-2 and placed on the upper semi-cylindrical section 316-1, while the splice plates 920, 920-1, or segment 1042 are installed in the assembly table 330 while the crown module 364-1 is being installed. One example has splice plates 920, 920-1, or segment 1042 on one boundary 1032 of the lower semi-cylindrical section 314-1 and corresponding splice plates 920 or segment 1042 on one boundary 1132 or on the upper semi-cylindrical section 316-1 or on the opposite boundary 1132.Another example has a flexible track 1024-1 that can be placed and removed entirely manually with the assistance of workstation 1020-2 or without any mechanical assistance.

[0225] Figure 11A Before bringing the upper semi-cylindrical section 316-2 and the lower semi-cylindrical section 314-2 into the mating splice 1201, they are awaiting joining to the lower semi-cylindrical section 314-2 and with... Figure 12 The end view of the corresponding upper cylindrical section 316-2. According to... Figure 11A The splice plate 920 preferably includes a profile 1110 of the IML 1034 contacting the upper semi-cylindrical section 314-2 and the IML 1134 of the lower section 1130. The splice plate 920 is not shown in proportion to the upper semi-cylindrical section 316-2 and has exaggerated curvature and taper. The splice plate 920 is held in place at the upper semi-cylindrical section 1030 by fasteners 1050. One embodiment has a splice plate that is finally fastened to the upper semi-cylindrical section 316-2, but another embodiment has a splice plate 920 that is glued in place. Yet another embodiment, similar to the upper semi-cylindrical section 316-2 but not shown, has a splice plate 920 that is finally fastened to the lower semi-cylindrical section 314-2. Another example features a splicing plate 920, which is glued in place to either the upper semi-cylindrical section 316-2 or the lower semi-cylindrical section 314-2. The lower semi-cylindrical section 314-2 is held within a bracket 1150. The last-fastened or glued splicing plate 920, 920-1, or section 1042 also facilitates alignment with the upper semi-cylindrical section 314-2 at least at the mating point 1160, where the lower semi-cylindrical section 316-2 is within the desired profile. Thus, the desired profile is carried through the mating point 1160 relative to the upper and lower semi-cylindrical sections 316-2 and 314-2, respectively, during splicing with the splicing plate 920. The bracket 1150 mechanically supports the lower semi-cylindrical section 314-2.

[0226] Another example has only such Figure 11B The splicing plate 920 or segment 1042 shown is connected to the upper semi-cylindrical section 316-2 and the lower semi-cylindrical section 314-2 in the joining station 342. Figure 11B This is an end view of the upper semi-cylindrical section 316-2, which awaits joining to the lower semi-cylindrical section 314-2, and corresponds to... Figure 12 The view, but just before bringing the upper semi-cylindrical section 316-2 and the lower semi-cylindrical section 314-2 into the mating splice 1201. According to Figure 11BThe splicing plate 920 includes a profile 1110 of an IML 1034 contacting the upper semi-cylindrical segment 314-2 and an IML 1134 of the lower segment 1130. In the example shown, the splicing plate 920 splices the lower semi-cylindrical segment 314-2 to the upper semi-cylindrical segment 316-2. The splicing plate 920 is not shown in scale relative to the upper semi-cylindrical segment 316-2. Another example shows the splicing plate 920 glued in place when the lower and upper boundaries are mated together. The splicing plate is fully installed in the joining station 342. The lower semi-cylindrical segment 314-2 is held in the bracket 1150. The splicing plate 920 also helps align with the upper semi-cylindrical section 314-2, while ensuring that the lower semi-cylindrical section 314-2 and the upper semi-cylindrical section 316-2 are in the desired profile through the mating point 1160 during the splicing of the splicing plate 920, as part of the joint. The bracket 1150 mechanically supports the lower section 1130.

[0227] In another embodiment, the upper bracket (not shown) is used in conjunction with bracket 1150. Bracket 1150 also facilitates longitudinal rotation of the lower semi-cylindrical section 314-2 before engagement with the upper semi-cylindrical section 316-2. Thus, bracket 1150 is used for rotation and engagement. The upper bracket (not shown) and bracket 1150 are indexed to each other via complementary cups and cones or similar systems mounted on the bracket. That is, one bracket uses cups in multiple locations, while the other uses complementary cones. The brackets are sized to provide sufficient clearance from the splicing area 914 to allow for the manufacture of the mating splice 1201. The clearance is located on the OML and IML. Thus, the clearance allows for the splice panel 920 mount, frame splice 913, window / door surround splices 940, 970, and other splices discussed above.

[0228] exist Figure 12 In the middle, is from Figure 1AThe obtained view shows that the upper section has been positioned in a butt-joint arrangement such that the upper boundary 1032 of the lower semi-cylindrical section 314-2 contacts the lower boundary 1132 of the upper semi-cylindrical section 316-2. Fasteners 1210 have been installed to complete the engagement of the upper semi-cylindrical section 316-2 and the lower semi-cylindrical section 314-2, resulting in a complete cylindrical section 1200. The resulting external aesthetic appearance is formed by combining the arrangement of fasteners on each side of the longitudinal lines. One embodiment has an engagement station 342 for attaching the splice plate 920 by installing fasteners through the splice plate 920 when the splice plate 920 contacts the IML 1034 of the upper semi-cylindrical section 316-2 and the IML 1134 of the lower semi-cylindrical section 314-2. The splice plate 920 can be installed on the upper semi-cylindrical section 316-2 or the lower semi-cylindrical section 314-2 before joining station 342. Alternatively, the splice plate 920 can be installed on OML 1035 or IML 1034, or both, after entering joining station 342. One example shows the splice plate 920 installed in assembly line 120 as part of the upper semi-cylindrical section 316-2, or alternatively, on the lower semi-cylindrical section 314-2. The splice plate 920 is shown with an exaggerated curved structure to match the exaggeratedly small radius of the entire cylindrical section 1200.

[0229] Figure 12 Two examples of the splice panel 920 installation equipment are shown. The flexible track device 1024-2 follows two tracks 1023-2, one of which is removably mounted to the upper semi-cylindrical section 316-2, and the other to the lower semi-cylindrical section 314-2. The flexible track 1024-2 is fitted with fasteners 1210 to complete the installation of the splice panel 920 or section 1042, while other operations are performed by the joining stations 342, 342-1. The flexible track device 1024-2 follows the two tracks 1023-2 using a connector 1033.

[0230] Figure 12 A second example of the splice panel 920 installation equipment is also shown. A fastener installation end effector 1224 is attached to a robot 1223. The robot 1223 is envisioned as a rack-type or robotic arm type or some other suitable device. The robot 1223 positions the end effector 1224 when needed to install all the fasteners 1210 required to install the splice panel 920 and / or segment 1042 onto the upper semi-cylindrical segment 316-2 and the lower semi-cylindrical segment 314-2. The fastener installation end effector 1224 installs the fasteners 1210 to complete the installation of the splice panel 920 or segment 1042, while other operations are performed by the engagement stations 342, 342-1.

[0231] Although Figure 12The diagram shows the flexible track device 1024-2 and the fastener installation end effector 1224 operating in a single engagement station 342, 342-1. However, it is possible that engagement stations 342, 342-1 would use either the previous or the subsequent one on each mating splice 1201 to form two mating splices 1201. An advantage of using the flexible track device 1024-2 is that it is a well-established technology that typically requires less station-specific infrastructure to form the mating splices 1201. Another example features the flexible track 1024-2, which can be placed and removed entirely manually, either with assistance from a workstation similar to 1020-1 or without any mechanical assistance.

[0232] Figure 13 A conveying mechanism 1290 for completing the cylindrical section 1260 is depicted. According to... Figure 13 The transport mechanism 1290 includes an upper support 1220 and a lower trolley 1230. The upper support 1220 includes a frame 1222, and the lower trolley 1230 includes a support 1240 and a support member 1250 attached to the upper support 1220. Wheels 1232 facilitate the movement of the transport mechanism 1290, and the transport mechanism 1290 can transport the complete cylindrical section 1260 to any desired additional assembly station and / or unit. The transport by the transport mechanism 1290 is also facilitated by a combination of a crane-type lifting device and / or wheels 1232. The upper support 1220 is aligned with the support 1240 and has an indexing system similar to cups and cones. Cups or cones are coupled to the support 1220 and cooperate with corresponding cones or cups 1225 coupled to the support 1240.

[0233] Figure 14 This is a flowchart illustrating mode 1500 of the feeder in an illustrative embodiment. Figure 14 Detailed specifications regarding the fabrication of the feeders and cycle times are provided. All feeders from the material-laying feeder are depicted during the fabrication process. Furthermore, each referenced line is executed according to a desired cycle time, which is related to the cycle time of the component feed and the cycle time of the feed to the component. Arrows indicate the feeder processing direction for each. Feeders can be operated as micro-pulsating, full-pulsating, and / or continuous lines, where the fabrication process proceeds from left to right, with delivery occurring in a just-in-time manner at the next line upstream of the right portion being delivered to the workstation. For micro-pulsating or full-pulsating component 170 operation, the cycle time of each of these feeders can be the same as or different from a multiple or fraction of the cycle time of the line feed or the cycle time of the feed to the line. In one embodiment, the cycle time is constant for each illustrated feeder.

[0234] In another embodiment, it is possible to skip or perform work at all workstations 114 based on the work statements and expected cycle times of the entire line or the fed line. Cycle time is considered to be the number of minutes per month divided by the number of units required per month (e.g., aircraft, beams, frames, etc.). The sum of the micro-pulsations of the cycle times equals the pulsation of the cycle time, since a micro-pulsation is a fraction of the length of component 170, while a pulsation is the length of component 170. That is, multiple micro-pulses equal a full pulsation as component 170 advances through assembly lines 110, 120, 310.

[0235] As in Figure 14 Specifically, feeder 1501-1 feeds manufacturing material to feeder 1503 for electrical and conduit formation at beat 14 in a fully pulsating, continuous, or micro-pulsating line. Feeder 1501-2 feeds laying material to feeder 1504 for ceiling panel laying in a fully pulsating, continuous, or micro-pulsating line at beat 13. Feeder 1501-3 provides laying material to feeder 1506 for manufacturing semi-cylindrical section preforms at beat 7. Feeder 1506 also receives manufactured longitudinal beam preforms via feeder 1514 at beat 16, which itself is fed laying material by feeder 1501-8. Feeder 1501-4 provides laying material to feeder 1507 for laying frame preforms and forms them at beat 8. The ends of frame feeder 1507 are located at workstations 114, 124, and 312. Frame feeder 1507 corresponds to 149, 149-1, and 359. Feeder 1507 has a cycle time of 8, sufficient to feed two 90-degree frames to workstations 114, 124, and 312 during micro-pulses 129 passing through workstations 114, 124, and 312. The number of frames required for each micro-pulse 129 establishes the relative cycle time for feeder 1508 relative to assembly lines 110, 120, and 310. Dividing the assembly process into multiple assembly lines / feeders allows for more parallel processing, making it easier to monitor the production speed of each line and track the delivered parts. The example of how frame feeder 1507, feeding frames to workstations 114, 124, and 312, establishes the relative cycle time for multiple feeders and assembly lines is shown. This system makes it easier to identify defects in the manufacturing process in real time.

[0236] Feeder 1501-5 supplies laying material to feeder 1508, used for window and door surround prefabricated components, at beat 9. Feeder 1501-6 supplies laying material to feeder 1509, used for floor beam prefabricated components, at beat 10. Feeder 1501-7 supplies laying material to feeder 1510, used for advancing intercostal prefabricated components, at beat 11. Feeder 1501-9 supplies laying material to another feeder 1511, used for intercostal components, at beat 12. Another feeder 1502 supplies storage box material to feeder 1505, used for manufacturing storage boxes, at beat 15.

[0237] The ceiling panel and cycle 13 are fed to feeder 1515 via feeder 1504. Electrical and piping system components are fed to feeder 1515 via feeder 1503 via cycle 14. Feeder 1515 receives material from feeder 1544, fasteners from feeder 1545, sealant from feeder 1546, and removes trimmed material via effluent 1547, crown module grille material feeder 1548, and insulation material feeder 1549. Feeder 1515 provides the completed crown module 364 to feeder 1524 corresponding to assembly table 320. In a non-value-added lateral movement from feeder 1526, the upper semi-cylindrical section 316-2 advances laterally along path 398-14. Feeder 1524 receives material from feeder 1531, fasteners from feeder 1533, and sealant from feeder 1535, and removes trimmed material via effluent 1536. This results in the crown module being supplied via non-value-added feeder 1537 to feeder 1538 for mating station 342.

[0238] The frame is supplied from feeder 1507 to feeder 1513, and the enclosure is supplied from feeder 1508 to the work station on feeder 1512. Feeders 1513, 1512, and 1506 feed feeder 1543. Feeder 1543 receives fasteners from feeder 1517 and sealant from feeder 1519, and removes trimmed material via effluent 1521. Additional miscellaneous materials are supplied via feeder 1523. This results in the fuselage section being supplied to feeder 1525, which supplies components to feeders 1538 and 1527. Components at feeder 1538 are supplied to feeder 1542.

[0239] Feeders 1509, 1510, and 1511 supply material to feeder 1516 for the floor grille. Feeders 1509 and 1510 correspond to feeders 519-1, 519-2, 519-3, 519-11, 519-21, and 519-31, respectively, delivering floor beams 511 and reinforcing ribs 513, and delivering the correct components in a just-in-time (JIT) manner to workstations 504-11, 504-12, 504-13, 504-1, 504-2, and 504-3 for assembly into cargo hold floors 365-2, 509, and 509-1 and passenger floor grilles 365-1, 508, and 508-1, respectively. Passenger floor grilles 365-1, 508, 508-1 and cargo floor grilles 356-2, 509, 509-1 are advanced through assembly workstations 504-1 to 504-7 and 504-11 to 504-17 respectively via micro-pulsation 129-1 at beats 6 and 6-1. Feeder 1516 receives material from feeder 1523, fasteners from feeder 1518, and sealant from feeder 1520, and removes trimmed material via outlet 1522. Passenger floor grilles 365-1, 508, 508-1 and cargo floor grilles 356-2, 509, 509-1 are advanced to feeder 1526. Feeder 1526 receives material from feeder 1528, fasteners from feeder 1530, and sealant from feeder 1532, and removes trimmed material via outlet 1534. After the installation of passenger floor grilles 365-1, 508, 508-1 and cargo floor grilles 356-2, 509, 509-1, the lower semi-cylindrical section 314-1, advanced in the non-value-added feeder 1539, proceeds to the reversing station 560, where a reversal occurs at feeder 1541. Feeder 1541 corresponds to the reversing station 560, which supplies components to feeder 1540 for use at feeder 1538, which corresponds to the joining station 342. The cycle time 30 plus cycle time 31 plus cycle time 32 plus cycle time 33 of feeders 1526, 1539, 1541, 1540 is equal to twice the cycle time 35 plus cycle time 34 of feeders 1524 and 1537. This reflects a difference of approximately twice the time compared to assembly station 320 in assembly station 330.

[0240] Follow us now Figure 15 , Figure 15The control components of a production system performing continuous manufacturing are illustrated in general. Controller 1600 coordinates and controls workstations 1620 (corresponding to workstations 114, 124, 312, 504-1 to 504-7 and 504-11 to 504-7, and 704-1 to 704-7) along a movement line 1660 having a power drive system 1662, as well as one or more semi-cylindrical sections 117, 117-1, crown module 364, passenger floor grille 365-1 and cargo hold floor grille 365-2, or sub-assemblies (such as frames 912, 912-1, window surrounds 970-1, door surrounds 940-1, floor beams 502-7, reinforcing ribs 502-8) or moving platform 1670 carrying components 170- 1. Operation of the passenger floor grille 365-1 and cargo floor grille 365-2 or sub-assemblies (such as frames 912, 912-1, window surrounds 970-1, door surrounds 940-1, floor beams 502-7, reinforcing ribs 502-8). The controller 1600 may include a processor 1610 coupled to a memory 1612 storing a program 1614. In one example, the mobile platform 1670 is driven along a movement line 1660 continuously driven by a power transmission system 1662 controlled by the controller 1600. In this example, the mobile platform 1670 includes utility connections. Connection 1672 may include an electrical, pneumatic, and / or hydraulic quick-disconnection mechanism for connecting the mobile platform 1670 to a facility 1640 from an external source. In other examples, as previously mentioned, the mobile platform 1670 includes an automated guided vehicle (AGV) with onboard facilities and a GPS / automatic guidance system 1674. The mobile platform 1670 also includes some or all of the previously discussed indexing systems, barcode and RFID systems. In another example, a laser tracker 1650 is used to control the movement of the mobile platform 1670. The tracker 1650 uses an indexing unit, a barcode reader, or an RFID reader. A position and / or motion sensor 1630, coupled to the controller 1600, is used to determine the position of the mobile platform 1670 and the power system 1662.

[0241] Figure 16 This is a flowchart illustrating a method for manufacturing a portion of the fuselage (e.g., a complete cylindrical section) in an illustrative embodiment. In step 2022, Figure 16Method 2020 includes continuously operating the lower semi-cylindrical section 118 in a processing direction 199 at a plurality of workstations 114 spaced apart along assembly line 110 with a length less than that of the lower semi-cylindrical section 118. The method also includes, in step 2024, continuously operating an upper semi-cylindrical section 116 located following the lower semi-cylindrical section 118 in the processing direction. Step 2026 includes removing the lower semi-cylindrical section 118 from assembly line 110. Step 2028 includes subsequently removing the upper semi-cylindrical section 116 from assembly line 110. Step 2029 includes attaching the lower semi-cylindrical section 118 to the upper semi-cylindrical section 116.

[0242] Example

[0243] Referring more specifically to the accompanying drawings, embodiments of this disclosure can be described as follows: Figure 17 The aircraft manufacturing and service in Method 1700 shown, and in Figure 18 The aircraft 1702 is shown in the background. During pre-production, method 1700 may include the specifications and design 174 of aircraft 1702 and material procurement 176. During production, the manufacturing of components and sub-assemblies of aircraft 1702 and system integration 1710 occur. Thereafter, aircraft 1702 may undergo certification and delivery 1712 for entry into service 1714. When used by the customer, aircraft 1702 is scheduled for routine work in maintenance and overhaul 1716 (which may also include modification, reconfiguration, refurbishment, etc.). The equipment and methods described herein may be used during any one or more suitable phases of method 1700 (e.g., specifications and design 174, material procurement 176, component and sub-component manufacturing 178, system integration 1710, certification and delivery 1712, service 1714, maintenance and overhaul 1716) and / or any suitable component of aircraft 1702 (e.g., fuselage 1718, system 1720, interior 1722, propulsion system 1724, electrical system 1726, hydraulic system 1728, environmental system 30).

[0244] Each process of Method 1700 may be performed or conducted by a systems integrator, a third party, and / or an operator (e.g., a customer). For the purposes of this specification, a systems integrator may include, but is not limited to, any number of aircraft manufacturers and main system subcontractors; a third party may include, but is not limited to, any number of suppliers, subcontractors, and vendors; and an operator may be an airline, leasing company, military entity, service organization, etc.

[0245] like Figure 18As shown, an aircraft 1702 produced by method 1700 may include a fuselage 1718 having multiple systems 1720 and an interior 1722. Examples of systems 1720 include one or more of a propulsion system 1724, an electrical system 1726, a hydraulic system 1728, and an environmental system 1730. Any number of other systems may be included. Although an aerospace example is shown, the principles of this disclosure can be applied to other industries, such as the automotive industry.

[0246] like Figures 19 to 48 As shown, a decorative exterior appearance can be provided, such as that depicted in the figures, with a combination of visible features, preferably longitudinal lines 25, and an arrangement of preferably multiple, preferably generally circular features 27, resulting in the visual appearance of the joined semi-cylinders and rivet heads. For example, as... Figures 19 to 33 as well as Figures 34 to 48 As shown, the elongated line 25, replacing the seam connecting the semi-cylindrical structure, preferably features multiple characteristics, preferably small circles 27, providing the appearance of the outer surface as a precisely, firmly, and securely constructed component in the location of rivet fasteners on each side of the longitudinal line. In this arrangement, the longitudinal splice of the semi-cylindrical structure is constructed to be readily apparent as an outer surface decoration, as a preferred longitudinal line 25 along at least one range of the fuselage, having the appearance of fasteners on each side of the longitudinal line. The appearance of the fasteners can be a single row of circles 27, 37 on each side of the longitudinal lines 25, 35 (as shown in...). Figure 21 , Figure 28 , Figure 36 and Figure 44 (in the middle) or on each side of the longitudinal lines 25, 35 (as in) Figure 24 , Figure 27 , Figure 31 , Figure 39 , Figure 42 or Figure 46 A pair of circular features 27, 37 (in the middle). The appearance of the fasteners, such as rows and approximately equidistant countersunk fasteners, can be arranged as a single row of fasteners along each side of the longitudinal line (as a visible remnant of the mating splice of the mating semi-cylinder) or two rows of fasteners along each side of the longitudinal line. This arrangement of lines 25, 35 and circular features 27, 37 can be positioned on the side of the fuselage 12, as shown in the attached figure. Figures 19 to 33 As shown, or positioned along the top of fuselage 12, such as Figures 34 to 48 As depicted in the text.

[0247] As mentioned above, the apparatus and methods embodied herein can be employed during any one or more phases of production and service as described in method 1700. For example, a component or sub-component corresponding to component and sub-assembly manufacturing 178 can be manufactured or produced in a manner similar to that of a component or sub-assembly produced when aircraft 1702 is in service. Furthermore, one or more apparatus embodiments, method embodiments, or combinations thereof can be used during sub-assembly manufacturing 178 and system integration 1710, for example, by significantly accelerating the assembly of aircraft 1702 or reducing the cost of aircraft 1702. Similarly, one or more of the apparatus embodiments, method embodiments, or combinations thereof can be utilized while aircraft 1702 is in service, for example, but not limited to, during maintenance and overhaul 1716. Therefore, the embodiments can be used for any stage or any combination thereof discussed herein, such as specifications and design 174, material procurement 176, component and sub-component manufacturing 178, system integration 1710, certification and delivery 1712, service 1714, maintenance and overhaul 1716) and / or any suitable component of aircraft 1702 (e.g., fuselage 1718, systems 1720, interior 1722, propulsion system 1724, electrical system 1726, hydraulic system 1728 and / or environmental system 1730).

[0248] In one embodiment, the component comprises a portion of fuselage 1718 or a segment as described herein, and is manufactured during component and subassembly manufacturing 178. The component can then be assembled into the aircraft in systems integration 1710, and then used in service 1714 until wear renders the component unusable. Then, in maintenance and overhaul 1716, the component can be discarded and replaced with a newly manufactured component. The components and methods of the present invention can be used throughout component and subassembly manufacturing 178 to manufacture new components.

[0249] Any of the various control elements (e.g., electrical or electronic components) shown in the accompanying drawings or described herein can be implemented as hardware, a processor implementing software, a processor implementing firmware, or some combination thereof. For example, an element can be implemented as dedicated hardware. A dedicated hardware element can be referred to as a “processor,” a “controller,” or some similar term. When provided by a processor, functionality can be provided by a single dedicated processor, by a single shared processor, or by multiple separate processors, some of which may be shared. Furthermore, the explicit use of the terms “processor” or “controller” should not be construed as specifically referring to hardware capable of executing software, and may implicitly include (but is not limited to) digital signal processor (DSP) hardware, network processors, application-specific integrated circuits (ASICs) or other circuitry, field-programmable gate arrays (FPGAs), read-only memory (ROM) for storing software, random access memory (RAM), non-volatile storage devices, logic, or some other physical hardware component or module.

[0250] Furthermore, the control element can be implemented as instructions executable by a processor or computer to perform the element's functions. Some examples of instructions are software, program code, and firmware. When executed by the processor, the instructions are operable to instruct the processor to perform the element's functions. The instructions can be stored on a processor-readable storage device. Some examples of storage devices are digital or solid-state memories, magnetic storage media such as disks and tapes, hard disk drives, or optically readable digital data storage media.

[0251] The following examples also provide for various aspects of the invention.

[0252] The first example includes a method for assembling the fuselage of an aircraft, the method comprising: receiving a semi-cylindrical section 24 of the fuselage 12; advancing the semi-cylindrical section 24 in a processing direction 199 across a plurality of workstations 114 at a time; and simultaneously performing operations on the semi-cylindrical section 24 via the plurality of workstations 114.

[0253] In the embodiment according to the first example, the advancement of the semi-cylindrical section 24 is performed via assembly lines 110, 120.

[0254] In an embodiment according to the first example, the method further includes advancing a plurality of semi-cylindrical sections 24 across a plurality of workstations 114 in a processing direction 199.

[0255] In the embodiment according to the first example, during the same pause between micropulses 129 in the processing direction 199 of the semi-cylindrical section 24, multiple workstations 114 perform operations on the semi-cylindrical section 24.

[0256] In an embodiment according to the first example, the method further includes causing the semi-cylindrical section 24 to micro-pulse 129 through a plurality of workstations 114 according to a common beat time, wherein the common beat time is based on the expected number of semi-cylindrical sections 24 produced each month.

[0257] In an embodiment according to the first example, the method further includes transposing the semi-cylindrical segment 24 to at least one working station 114 during pauses between micropulses 129.

[0258] In an embodiment according to the first example, the method further includes operating the semi-cylindrical section 24 during pauses between micropulses 129 in the processing direction 199.

[0259] In an embodiment according to the first example, the method further includes operating the semi-cylindrical section 24 during micro-pulsations 129 between pauses in the semi-cylindrical section 24 in the processing direction 199.

[0260] In an embodiment according to the first example, the method further includes delivering components 398-10 to one of the work stations 114 as the semi-cylindrical section 24 advances to the work station 114; and engaging the components to the semi-cylindrical section 24 at the work station 114.

[0261] In the embodiment according to the first example, parts are delivered to workstation 114 in a just-in-time production manner in the order used by workstation 114.

[0262] In the embodiment according to the first example, the component is engaged to the semi-cylindrical section 24 during the pause between micropulses 129.

[0263] In an embodiment according to the first example, advancing the semi-cylindrical section 24 includes moving the semi-cylindrical section 24 through a plurality of work stations 114, the plurality of work stations 114 being separated from each other by a distance less than the length of the semi-cylindrical section 24.

[0264] In the embodiment according to the first example, the distance between the workstations 114 is equal to a multiple of the frame spacing 915 of the semi-cylindrical section 24.

[0265] In the embodiment according to the first example, performing the work includes operating the plurality of workstations 114 independently of each other.

[0266] In the embodiment according to the first example, multiple of the plurality of workstations 114 remove material from the semi-cylindrical section 24.

[0267] In the embodiment according to the first example, a plurality of the plurality of workstations 114 add material to the semi-cylindrical section 24.

[0268] In the embodiment according to the first example, the operation is selected from the group consisting of: frame 912 installation, window surround 970-2 installation, door surround 940-2 installation, door manufacturing allowance 940-9 trimming and removal, window manufacturing allowance 970-9 trimming and removal, trimming manufacturing allowance 143-9 from support edge 143, sealing, non-destructive inspection (NDI) of the semi-cylindrical section 24, non-destructive inspection (NDI) of the edge after separating manufacturing allowance 143-9 or window manufacturing allowance 970-9 or door manufacturing allowance 940-9, and cleaning.

[0269] In an embodiment according to the first example, the method further includes joining the semi-cylindrical segment 24 to another semi-cylindrical segment 24.

[0270] In an embodiment according to the first example, the method further includes operating the feeders of a plurality of workstations 114 according to the cycle time of the semi-cylindrical section 24.

[0271] In the embodiment according to the first example, each feeder 149, 149-1 has a common beat time that is equal to or a portion of the body 12 beat time.

[0272] The second example includes an aircraft consisting of a fuselage 12 having an elongated length between its two ends, wherein at least a portion of the length of the fuselage 12 is formed by semi-cylindrical sections 24 joined together at a plurality of docking splices 1201 or joints.

[0273] In the embodiment according to the second example, at least one of the semi-cylindrical sections 24 of the fuselage 12 is formed by upper semi-cylindrical sections 116, 126 and lower semi-cylindrical sections 118, 128, which are assembled and joined together by components to form a uniform cylindrical section 148 and a non-uniform cylindrical section 138, respectively.

[0274] In the embodiment according to the second example, at least two of the uniform cylindrical segments 148 and the non-uniform cylindrical segments 138 of the fuselage 12 are joined together along a circumferential joint.

[0275] In the embodiment according to the second example, the joined upper cylindrical sections 116, 126 and lower cylindrical sections 118, 128 include a butt joint 1201 with a supporting edge 143 having splice plates 597, 920, 920-1 fixed to the upper cylindrical sections 116, 126 and lower cylindrical sections 118, 128 by fasteners.

[0276] In an embodiment according to the second example, the location of the fasteners includes a row of fasteners located on each of the upper semi-cylindrical sections 116, 126 and the lower semi-cylindrical sections 118, 128.

[0277] In the embodiment according to the second example, two rows of fasteners are positioned on each of the upper semi-cylindrical sections 116, 126 and the lower semi-cylindrical sections 118, 128.

[0278] In the embodiment according to the second example, the product is assembled by a process in which each semi-cylindrical segment 24 advances through a plurality of work stations 114, which perform operations on the semi-cylindrical segment 24 before engaging it with the mating semi-cylindrical segment 24.

[0279] In the embodiment according to the second example, each mating semi-cylindrical segment 24 is assembled by advancing through a plurality of work stations 114 for simultaneously performing assembly operations on the semi-cylindrical segments 24 to be mated prior to engagement.

[0280] In an embodiment according to the second example, each semi-cylindrical segment 24 includes a semi-cylindrical body and at least one component 394-10 fixed to the semi-cylindrical segment 24 prior to engagement with the corresponding semi-cylindrical segment 24.

[0281] A third example includes a system for assembling the fuselage of an aircraft, comprising: assembly lines 110 and 120, the assembly lines 110 and 120 including: a track 112 that receives a semi-cylindrical section 24 of the fuselage 12 and advances the semi-cylindrical section 24 along the assembly lines 110 and 120 in a processing direction 199 through at least one work station 114; and work stations 114 arranged along the track 112 in the processing direction 199 at a distance less than the length of the semi-cylindrical section 24, such that at least one work station 114 can perform operations on the semi-cylindrical section 24 at a time.

[0282] In the embodiment according to the third example, the semi-cylindrical section 24 is advanced through a plurality of workstations 114 in the processing direction 199, and the plurality of workstations 114 perform operations on the semi-cylindrical section 24 at one time.

[0283] In the embodiment according to the third example, the work performed at workstation 114 is selected from the group consisting of: frame installation, window installation, door installation, trimming, sealing, non-destructive inspection (NDI) of the semi-cylindrical section 24, non-destructive inspection (NDI) of trimming edges, and cleaning work.

[0284] In the embodiment according to the third example, the work station 114 performs work on one of the semi-cylindrical sections 24 during pauses between micro-pulses 129 in the processing direction 199.

[0285] In the embodiment according to the third example, components 398-10 are delivered to workstation 114 in just-in-time production according to their usage sequence.

[0286] In an embodiment according to the third example, the system further includes a feeder having a cycle time equal to a portion of the 12-cycle time of the fuselage.

[0287] In the embodiment according to the third example, the distance is equal to the frame spacing 915 in the processing direction 199.

[0288] In the embodiment according to the third example, work station 114 removes material from the semi-cylindrical section 24.

[0289] In an embodiment according to the third example, the semi-cylindrical section 24 includes upper semi-cylindrical sections 116, 126 and lower semi-cylindrical sections 118, 128.

[0290] In the embodiment according to the third example, multiple workstations 114 remove material from the semi-cylindrical section 24.

[0291] In the embodiment according to the third example, multiple workstations 114 add material to the semi-cylindrical section 24.

[0292] The fourth example includes using a system in any of the embodiments of the system according to the third example to manufacture a part of an aircraft.

[0293] The fifth example includes a method of manufacturing an aircraft, comprising: advancing a series of semi-cylindrical sections 24 through a series of workstations 114 at a common beat time; delivering a first type of sub-component 398-10 to the workstations in a just-in-time manner along with a second type of sub-component produced in parallel with the first type of sub-component; and attaching the sub-component 398-10 to the semi-cylindrical sections 24.

[0294] In the embodiment according to the fifth example, sub-components 398-10 are delivered according to a clock cycle time equal to or a portion of the 12-clock cycle time of the fuselage.

[0295] In an embodiment according to the fifth example, the method further includes the work station 114 operating on the semi-cylindrical section 24 during the same pause between micro-pulses 129 in the processing direction 199 of the semi-cylindrical section 24.

[0296] In the embodiment according to the fifth example, sub-component 39A-10 is delivered to workstation 114 in a just-in-time production manner and in the order of use.

[0297] In an embodiment according to the fifth example, the method further includes simultaneously operating the semi-cylindrical section 24 via one or more workstations 114.

[0298] In the embodiment according to the fifth example, advancing includes iteratively micro-pulsating 129 the semi-cylindrical segment 24 to a length smaller than its length, and then operating on the semi-cylindrical segment 24 while pausing.

[0299] In an embodiment according to the fifth example, the method further includes advancing, which includes iteratively micro-pulsating the semi-cylindrical segment 24 at least its length, and then operating on the semi-cylindrical segment 24 while pausing.

[0300] In an embodiment according to the fifth example, the method further includes continuously moving the semi-cylindrical section 24 while performing operations on the semi-cylindrical section 24.

[0301] In an embodiment according to the fifth example, the method further includes joining the sub-components 398-10 and the semi-cylindrical section 24 together at a work station 114 after the micro-pulsation 129.

[0302] In an embodiment according to the fifth example, the method further includes joining two semi-cylindrical segments 24 to form complete cylindrical segments 29-1, 29-2, 29-3, 29-4, 29-5.

[0303] In the embodiment according to the fifth example, multiple workstations 114 remove material from the sub-component.

[0304] The sixth example includes a portion of an aircraft assembled according to the method of the fifth example, based on any of the embodiments.

[0305] The seventh example includes a method for assembling the fuselage of an aircraft, the method comprising: receiving a semi-cylindrical segment 24 of fuselage 12 in assembly lines 110, 120; attaching splicing plates 597, 920, 920-1 to the semi-cylindrical segment 24; aligning the semi-cylindrical segment 24 and the attached splicing plates 597, 920, 920-1 to another semi-cylindrical segment 24; and joining the semi-cylindrical segments 24 together via splicing plates 597, 920, 920-1.

[0306] In the embodiment according to the seventh example, joining the two semi-cylindrical segments 24 includes butt-jointing each semi-cylindrical segment 24 together.

[0307] In the embodiment according to the seventh example, splicing plates 597, 920, 920-1 are mounted on the inner mold line (IML) 595 of the semi-cylindrical section 24.

[0308] In the embodiment according to the seventh example, splicing plates 597, 920 are mounted on the outer mold line (OML) 593 of the semi-cylindrical section 24.

[0309] In the embodiment according to the seventh example, at least one splicing plate 597, 920, 920-1 is at least partially mounted on the upper semi-cylindrical sections 116, 126, and at least one splicing plate 597, 920, 920-1 is at least partially mounted on the lower semi-cylindrical sections 118, 128.

[0310] In the embodiment according to the seventh example, splice panels 597, 920, 920-1 are installed at assembly lines 110, 120 through which the semi-cylindrical section 24 travels.

[0311] In the embodiment according to the seventh example, the splice plates 597, 920, 920-1 are installed during the installation of the crown module or floor grid into the semi-cylindrical section 24.

[0312] In the embodiment according to the seventh example, splicing plates are installed simultaneously at both the upper semi-cylindrical sections 116, 126 and the lower semi-cylindrical sections 118, 128.

[0313] In the embodiment according to the seventh example, installing splice panels 597, 920, 920-1 includes installing a plurality of segments 1042 of splice panels 597, 920, 920-1 along the length of the upper semi-cylindrical segments 116, 126 and / or the lower semi-cylindrical segments 118, 128.

[0314] In the embodiment according to the seventh example, the installation of splice plates 597, 920, 920-1 is performed at assembly lines 110, 120 during pauses between micro-pulses 129 in the upper semi-cylindrical sections 116, 126 and / or the lower semi-cylindrical sections 118, 128.

[0315] In the embodiment according to the seventh example, aligning the upper cylindrical sections 116, 126 with the lower cylindrical sections 118, 128 includes rotating the lower cylindrical sections 118, 128 from a vertically reverse orientation to an orientation complementary to that of the upper cylindrical sections 116, 126.

[0316] In the embodiment according to the seventh example, the lower cylindrical sections 118 and 128 are placed in the support before the upper cylindrical sections 116 and 126 are aligned with the lower cylindrical sections 118 and 128.

[0317] In the embodiment according to the seventh example, the attachment splicing plates 597, 920, 920-1 include driving fasteners through the splicing plates 597, 920, 920-1, while the splicing plates 597, 920, 920-1 contact the inner mold line (IML) of the upper semi-cylindrical sections 116, 126 and the IML of the lower semi-cylindrical sections 118, 128.

[0318] The eighth example includes a portion of an aircraft assembled according to the method of the seventh example, based on any of the embodiments.

[0319] The ninth example includes a non-transitory computer-readable medium containing programming instructions that, when executed by a processor, are operable for performing a method for assembling the fuselage of an aircraft, the method comprising: receiving a semi-cylindrical segment 24 of fuselage 12 in assembly lines 110, 120; installing splicing plates 597, 920, 920-1; aligning the semi-cylindrical segment 24 with another semi-cylindrical segment 24 of fuselage 12; and engaging the semi-cylindrical segment 24 by attaching the splicing plates 597, 920, 920-1.

[0320] The tenth example includes a system for assembling the fuselage of an aircraft, the system comprising: assembly lines 110, 120 which transport semi-cylindrical sections 24 of the fuselage 12 in a processing direction 199; a joining station 342 which mounts splice plates 597, 920, 920-1; a support 1150 which holds the semi-cylindrical sections 24 of the fuselage 12; and a joining work station 114 which joins the semi-cylindrical sections 24 by attaching splice plates 597, 920, 920-1.

[0321] In the embodiment according to the ninth example, the joining semi-cylindrical sections 24 include forming a butt joint 1201 between the semi-cylindrical sections 24.

[0322] In the embodiment according to the tenth example, splicing plates 597, 920, 920-1 are mounted on the inner mold line (IML) 595 of the semi-cylindrical section 24.

[0323] In the embodiment according to the tenth example, splicing plates 597, 920, 920-1 are mounted on the outer mold line (OML) 593 of the semi-cylindrical section 24.

[0324] In the embodiment according to the tenth example, splicing panels 597, 920, 920-1 are partially mounted on the upper semi-cylindrical sections 116, 126 and partially mounted on the lower semi-cylindrical section 24.

[0325] In the embodiment according to the tenth example, the joining station 342 is after assembly lines 110 and 120.

[0326] In the embodiment according to the tenth example, the installation of splice panels 597, 920, 920-1 is performed during the installation of the crown module or floor grid 506 into the semi-cylindrical section 24.

[0327] In the embodiment according to the tenth example, splicing plates 597, 920, 920-1 are simultaneously installed at both the upper semi-cylindrical sections 116, 126 and the lower semi-cylindrical sections 118, 128.

[0328] In the embodiment according to the tenth example, the joining station 342 installs splice plates 597, 920, 920-1 on each side of the inner mold line (IML) 595 of the upper semi-cylindrical sections 116, 126 and / or the lower semi-cylindrical sections 118, 128.

[0329] In the embodiment according to the tenth example, the joining station 342 installs multiple splice plates 597, 920, 920-1 along the length of the upper semi-cylindrical sections 116, 126.

[0330] In the embodiment according to the tenth example, the joining station 342 includes an end effector that aligns the splice plates 597, 920, 920-1 and installs fasteners through the splice plates 597, 920, 920-1.

[0331] In the embodiment according to the tenth example, the engagement station 114 attaches the splicing plates 597, 920, 920-1 by driving fasteners through the splicing plates 597, 920, 920-1, while the splicing plates 597, 920, 920-1 contact the inner mold line (IML) 595 of the upper semi-cylindrical sections 116, 126 and the IML of the lower semi-cylindrical sections 118, 128.

[0332] The eleventh example includes manufacturing a portion of an aircraft using any of the embodiments of the system according to the eleventh example.

[0333] Another example includes a portion of an aircraft assembled according to the method of any of the embodiments of the first example.

[0334] Note that the embodiments described for a particular example can be freely combined with each other.

[0335] This document also provides other examples, which are not intended to be confusing with the appended claims, which define the scope of protection. These other examples relate to various aspects of the invention.

[0336] 1. A method for assembling the fuselage of an aircraft, the method comprising:

[0337] The semi-cylindrical section of the fuselage is received on the assembly line;

[0338] Connect the splicing plate to the semi-cylindrical section;

[0339] Align the semi-cylindrical section and the connecting splice plate with another semi-cylindrical section; and

[0340] The semi-cylindrical sections are joined together using splicing plates.

[0341] 2. The method according to Example 1, wherein joining the two semi-cylindrical segments includes butt-jointing each semi-cylindrical segment together.

[0342] 3. The method according to Example 1 or 2, wherein the splicing plate is mounted on the inner mold line (IML) of the semi-cylindrical section.

[0343] 4. The method according to any one of Examples 1-3, wherein the splicing plate is mounted on the outer mold line (OML) of the semi-cylindrical section.

[0344] 5. The method according to any one of Examples 1-4, wherein at least one splicing plate is at least partially mounted on the upper semi-cylindrical section and at least one splicing plate is at least partially mounted on the lower semi-cylindrical section.

[0345] 6. The method according to any one of Examples 1-5, wherein the splicing plate is installed at the assembly line through which the semi-cylindrical section travels.

[0346] 7. The method according to any one of Examples 1-6, wherein the installation of the splicing plate is performed during the installation of the crown module or floor grid into the semi-cylindrical section.

[0347] 8. The method according to any one of Examples 1-7, wherein the splicing plate is installed simultaneously in both the upper and lower semi-cylindrical sections.

[0348] 9. The method according to any one of Examples 1-8, wherein installing the splicing plate includes installing multiple splicing plates along the length of the upper semi-cylindrical section and / or the lower semi-cylindrical section.

[0349] 10. The method according to any one of Examples 1-9, wherein the splice plate is installed at the assembly line during a pause between micropulsations in the upper and / or lower cylindrical sections.

[0350] 11. The method according to any one of Examples 1-10, wherein aligning the upper cylindrical section with the lower cylindrical section includes rotating the lower cylindrical section from a vertically reverse orientation to an orientation complementary to that of the engaging upper cylindrical section.

[0351] 12. The method according to any one of Examples 1-11, further comprising: placing the lower semi-cylindrical section in a support before aligning the upper semi-cylindrical section with the lower semi-cylindrical section.

[0352] 13. The method according to any one of Examples 1-12, wherein attaching the splicing plate comprises: driving the fastener through the splicing plate while the splicing plate contacts the inner mold line (IML) of the upper semi-cylindrical section and the IML of the lower semi-cylindrical section.

[0353] 14. A portion of an aircraft assembled according to any one of the foregoing examples.

[0354] 15. A non-transitory computer-readable medium comprising programming instructions, said programming instructions being operable, when executed by a processor, for performing a method for assembling the fuselage of an aircraft, said method comprising:

[0355] The semi-cylindrical section of the fuselage is received on the assembly line;

[0356] Install splicing panels;

[0357] Align the semi-cylindrical section with the other semi-cylindrical section of the fuselage; and

[0358] The semi-cylindrical sections are joined by attaching splicing plates.

[0359] 16. A system for assembling the fuselage of an aircraft, the system comprising:

[0360] Assembly line, which transports the semi-cylindrical section of the fuselage in the processing direction;

[0361] Connecting platform 342, which is used to install splicing panels;

[0362] Support 1150, which holds the semi-cylindrical section of the fuselage; and

[0363] The joining process involves attaching splicing plates to join the semi-cylindrical sections.

[0364] 17. The system according to Example 16, wherein joining the semi-cylindrical sections includes forming a butt joint between the semi-cylindrical sections.

[0365] 18. The system according to Example 16 or 17, wherein the splicing plate is mounted on the inner mold line (IML) of the semi-cylindrical section.

[0366] 19. The system according to any one of Examples 16-18, wherein the splicing plate is mounted on the outer mold line (OML) of the semi-cylindrical section.

[0367] 20. The system according to any one of Examples 16-19, wherein the splicing plate is partially mounted on the upper semi-cylindrical section and partially mounted on the lower semi-cylindrical section.

[0368] 21. The system according to any one of Examples 16-20, wherein the joining station is after the assembly line.

[0369] 22. The system according to any one of Examples 16-21, wherein the installation of the splicing plate is performed during the installation of the crown module or floor grid 506 into the semi-cylindrical section.

[0370] 23. The system according to any one of Examples 16-22, wherein the splicing plate is installed simultaneously in both the upper and lower semi-cylindrical sections.

[0371] 24. The system according to any one of Examples 16-23, wherein the joining station installs the splicing plate on each side of the inner mold line (IML) of the upper semi-cylindrical section and / or the lower semi-cylindrical section.

[0372] 25. The system according to any one of Examples 16-24, wherein the joining station installs multiple splicing plates along the length of the upper semi-cylindrical section.

[0373] 26. The system according to any one of Examples 16-25, wherein the joining station includes an end effector that aligns the splice plate and installs fasteners through the splice plate.

[0374] 27. The system according to any one of Examples 16-26, wherein the joining work station attaches the splicing plate by driving a fastener through the splicing plate, while the splicing plate contacts the inner mold line (IML) of the upper semi-cylindrical section and the IML of the lower semi-cylindrical section.

[0375] 28. Use the system of any one of Examples 16-27 to manufacture a part of an aircraft.

[0376] Although specific embodiments have been described herein, the scope of this disclosure is not limited to those specific embodiments. The scope of this disclosure is defined by the appended claims.

Claims

1. A method for assembling the fuselage of an aircraft, the method comprising: The first set (103-1) is formed by the lower semi-cylindrical section (118) and the upper semi-cylindrical section (116) of the fuselage. The first set (103-1) of advancing the lower semi-cylindrical section (118) and the upper semi-cylindrical section (116) in the processing direction crosses multiple workstations (114, 124, 312, 322, 332) at a time; and The lower cylindrical section (118) and the upper cylindrical section (116) are simultaneously operated via the multiple workstations (114, 124, 312, 322, 332); and The lower cylindrical section (118) and the upper cylindrical section (116) are manufactured in an alternating manner, including being arranged in a series adjacent to each other on an assembly line, such that the lower cylindrical section (118) and the upper cylindrical section (116) are paired to be joined together to form the same complete cylindrical section (138).

2. The method according to claim 1, wherein, The lower cylindrical section (118) and the upper cylindrical section (116) are advanced via assembly lines (110, 120, 310).

3. The method according to claim 1 or 2, further comprising advancing a plurality of semi-cylindrical sections across the plurality of workstations in the processing direction.

4. The method according to claim 1 or 2, wherein, During the same pause between micropulsations in the processing directions (199, 399) in the lower cylindrical section (118) and the upper cylindrical section (116), the plurality of workstations (114, 124, 312, 322, 332) perform operations on the lower cylindrical section (118) and the upper cylindrical section (116).

5. The method according to claim 1 or 2, further comprising one or more of the following: The lower cylindrical section (118) and the upper cylindrical section (116) are micro-pulsated through the multiple workstations (114, 124, 312, 322, 332) according to a common cycle time, wherein the common cycle time is based on the expected number of lower cylindrical sections (118) and upper cylindrical sections (116) produced per month; and / or During the pause between micro-pulse movements, the lower semi-cylindrical section (118) and the upper semi-cylindrical section (116) are transposed to at least one working station (114, 124, 312, 322, 332); and / or The semi-cylindrical section is operated on during the pauses between micro-pulses in the processing direction; and / or The semi-cylindrical section is operated on during micro-pulses between pauses in the processing direction; and / or As the semi-cylindrical section advances to the work station (114, 124, 312, 322, 332), the component is delivered to one of the work stations (114, 124, 312, 322, 332), and the component is joined to the semi-cylindrical section at the work station (114, 124, 312, 322, 332). and / or The semi-cylindrical section is joined to another semi-cylindrical section.

6. The method according to claim 1 or 2, wherein, Advancing the semi-cylindrical section includes moving the semi-cylindrical section through the plurality of working stations (114, 124, 312, 322, 332), wherein the plurality of working stations (114, 124, 312, 322, 332) are separated from each other by a distance less than the length of the semi-cylindrical section, and / or The operation includes operating the plurality of workstations (114, 124, 312, 322, 332) in a manner that is independent of each other; and / or Among them, multiple workstations remove material from the semi-cylindrical section; and / or Among them, multiple of the multiple work stations (114, 124, 312, 322, 332) add material to the semi-cylindrical section.

7. The method according to claim 1 or 2, wherein, The distance between the workstations (114, 124, 312, 322, 332) is equal to a multiple of the frame spacing of the semi-cylindrical section.

8. The method according to claim 1 or 2, wherein, The operation is selected from the group consisting of: frame installation, window surround installation, door surround installation, door manufacturing allowance trimming and removal, window manufacturing allowance trimming and removal, trimming manufacturing allowance from support edge, sealing, non-destructive inspection (NDI) of the semi-cylindrical section, non-destructive inspection (NDI) of the edge after separation of manufacturing allowance or window manufacturing allowance or door manufacturing allowance, and cleaning.

9. The method according to claim 1 or 2, further comprising: The feeders for the multiple workstations are operated according to the cycle time of the semi-cylindrical section.

10. The method according to claim 2, wherein, The assembly lines (110, 120, 310) include assembly tables (320, 330), each assembly table (320, 330) including workstations (322, 332), which perform specialized operations for the lower cylindrical sections (118, 128, 314) and the upper cylindrical sections (116, 126, 316).

11. The method according to claim 5, wherein, The delivery of the components to the workstations (114, 124, 312, 322, 332) is performed in the order of use of the workstations (114, 124, 312, 322, 332) using Just-In-Time (JIT) production, and / or It further includes engaging the component to the semi-cylindrical section during pauses between micropulses.

12. The method according to claim 9, wherein, Each feeder has a common beat time, which is equal to or a portion of the body beat time.

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