USRE50945E1

USRE50945E1 - Utility fixture for creating a distributed utility network

Info

Publication number: USRE50945E1
Application number: US18/763,377
Authority: US
Inventors: Harinder S. Oberoi; Alfredo Jose Gerosa; Kevin Marion Barrick; Quang T. Do; Yuanxin Charles Hu; Branko Sarh; Scott Allen Mackay; Jeffrey Lawrence Miller
Original assignee: Boeing Co
Current assignee: Boeing Co
Priority date: 2014-07-09
Filing date: 2024-07-03
Publication date: 2026-07-07
Also published as: EP2965994B1; EP2965832B1; KR102341145B1; US20160008934A1; KR102103808B1; KR20160006627A; ES2668687T3; JP2016016861A; EP2998045A2; JP6632814B2; KR102347454B1; US20160008869A1; JP6538433B2; KR102358808B1; BR102015016368A2; EP2998045A3; US9505051B2; BR102015016351A2; EP2965871A2; US20170066044A1

Abstract

A method and apparatus for distributing a number of utilities. The number of utilities may be coupled between a number of utility sources and a utility fixture. The number of utilities may be coupled between the utility fixture and a mobile system.

Description

RELATED PROVISIONAL APPLICATION

This application claims the benefit of U.S. Provisional Patent Application Ser. No. 62/022,641, filed Jul. 9, 2014, and entitled “Automated Flexible Manufacturing System for Building a Fuselage.”

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is related to the following patent applications: entitled “Autonomous Flexible Manufacturing System for Building a Fuselage,” Ser. No. 14/559,518; entitled “Mobile Platforms for Performing Operations along an Exterior of a Fuselage Assembly,” Ser. No. 14/558,933, now U.S. Pat. No. 9,505,051; entitled “Mobile Platforms for Performing Operations inside a Fuselage Assembly,” Ser. No. 14/559 073; entitled “Wheel Mounting System,” Ser. No. 14/559 115, now U.S. Pat. No. 9,782,822; entitled “Dual-Interface Coupler,” Ser. No. 14/559,153; entitled “Metrology-Based System for Operating a Flexible Manufacturing System,” Ser. No. 14/559 855; entitled “Clamping Feet for an End Effector,” Ser. No. 14/559 191; entitled “Towers for Accessing an Interior of a Fuselage Assembly,” Ser. No. 14/559,234; entitled “Assembly Fixture for Supporting a Fuselage Assembly,” Ser. No. 14/559 227; entitled “Adjustable Retaining Structure for a Cradle Fixture,” Ser. No. 14/559,303;and entitled “Two-Stage Riveting,” Ser. No. 14/559,483, filed of even date herewith, each of which claims the benefit of U.S. Provisional Patent Application Ser. No. 62/022,641, filed Jul. 9, 2014 and entitled “Automated Flexible Manufacturing System for Building a Fuselage,” each assigned to the same assignee, and each incorporated herein by reference in its entirety.

BACKGROUND INFORMATION

1. Field

The present disclosure relates generally to aircraft and, in particular, to building the fuselage of an aircraft. Still more particularly, the present disclosure relates to a method, apparatus, and system for coupling a number of utilities between various systems to establish a distributed utility network.

2. Background

Building a fuselage may include assembling skin panels and a support structure for the fuselage. The skin panels and support structure may be joined together to form a fuselage assembly. For example, without limitation, the skin panels may have support members, such as frames and stringers, attached to the surface of the skin panels that will face the interior of the fuselage assembly. These support members may be used to form the support structure for the fuselage assembly. The skin panels may be positioned relative to each other and the support members may be tied together to form this support structure.

Fastening operations may then be performed to join the skin panels and the support members together to form the fuselage assembly. These fastening operations may include, for example, riveting operations, interference-fit bolting operations, other types of attachment operations, or some combination thereof. The fuselage assembly may need to be assembled in a manner that meets outer mold line (OML) requirements and inner mold line (IML) requirements for the fuselage assembly.

With some currently available methods for building a fuselage assembly, the fastening operations performed to assemble the skin panels and the support members together may be performed manually. For example, without limitation, a first human operator positioned at an exterior of the fuselage assembly and a second human operator positioned at an interior of the fuselage assembly may use handheld tools to perform these fastening operations. In some cases, this type of manual fastening process may be more labor-intensive, time-consuming, ergonomically challenging, or expensive than desired. Further, some current assembly methods used to build fuselages that involve manual fastening processes may not allow fuselages to be built in the desired assembly facilities or factories at desired assembly rates or desired assembly costs.

In some cases, the current assembly methods and systems used to build fuselages may require that these fuselages be built in facilities or factories specifically designated and permanently configured for building fuselages. These current assembly methods and systems may be unable to accommodate different types and shapes of fuselages. For example, without limitation, large and heavy equipment needed for building fuselages may be permanently affixed to a factory and configured for use solely with fuselages of a specific type.

Further, providing utilities, such as power, air, hydraulic fluid, and other types of utilities, to the various systems used in some current assembly methods may be more difficult or cumbersome than desired. For example, without limitation, the various cables and connection devices needed to provide these types of utilities to the different tools being used to assemble a fuselage may impede or restrict the movement of personnel and tools within a manufacturing environment. Therefore, it would be desirable to have a method and apparatus that take into account at least some of the issues discussed above, as well as other possible issues.

SUMMARY

In one illustrative embodiment, a method for distributing a number of utilities may be provided. The number of utilities may be coupled between a number of utility sources and a utility fixture. The number of utilities may be coupled between the utility fixture and a mobile system.

In another illustrative embodiment, a coupling unit may comprise a quick-change device, a number of coupling elements, and an alignment system. The alignment system may align the quick-change device with a corresponding quick-change device and the number of coupling elements with a corresponding number of coupling elements.

In yet another illustrative embodiment, a method for mating a coupling unit with a corresponding coupling unit may be provided. The corresponding coupling unit may be driven towards the coupling unit. The corresponding coupling unit may be aligned with the coupling unit autonomously. The corresponding coupling unit may be mated to the coupling unit to couple a number of utilities between the coupling unit and the corresponding coupling unit.

In still another illustrative embodiment, a method for distributing a number of utilities to a tower may be provided. A tower may be driven towards a location of a utility fixture having a set of coupling units. Each of a set of corresponding coupling units associated with the tower may be aligned with the set of coupling units. A quick-change device of each of the set of coupling units may be mated with a corresponding quick-change device of each of the set of corresponding coupling units.

In yet another illustrative embodiment, an apparatus may comprise a set of coupling units associated with a utility fixture, a set of corresponding coupling units associated with a mobile system, and a number of utility cables connected to the set of corresponding coupling units. The set of corresponding coupling units may be coupled to the set of coupling units. The number of utility cables may carry away from the set of corresponding coupling units a number of utilities received at the set of corresponding coupling units from the set of coupling units.

The features and functions can be achieved independently in various embodiments of the present disclosure or may be combined in yet other embodiments in which further details can be seen with reference to the following description and drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

The novel features believed characteristic of the illustrative embodiments are set forth in the appended claims. The illustrative embodiments, however, as well as a preferred mode of use, further objectives and features thereof, will best be understood by reference to the following detailed description of an illustrative embodiment of the present disclosure when read in conjunction with the accompanying drawings, wherein:

FIG. 1 is an illustration of a manufacturing environment in the form of a block diagram in accordance with an illustrative embodiment;

FIG. 2 is an illustration of a fuselage assembly in the form of a block diagram in accordance with an illustrative embodiment;

FIG. 3 is an illustration of a plurality of mobile systems of a flexible manufacturing system within a manufacturing environment in the form of a block diagram in accordance with an illustrative embodiment;

FIG. 4 is an illustration a plurality of mobile platforms in the form of a block diagram in accordance with an illustrative embodiment;

FIG. 5 is an illustration of a flow of a number of utilities across a distributed utility network in the form of a block diagram in accordance with an illustrative embodiment;

FIG. 6 is an illustration of a utility fixture in the form of a block diagram in accordance with an illustrative embodiment;

FIG. 7 is an illustration of a distributed utility network in the form of a block diagram in accordance with an illustrative embodiment;

FIG. 8 is an illustration of an isometric view of a manufacturing environment in accordance with an illustrative embodiment;

FIG. 9 is an illustration of a first tower coupled to a utility fixture in accordance with an illustrative embodiment;

FIG. 10 is an illustration of an isometric view of a cradle system in accordance with an illustrative embodiment;

FIG. 11 is an illustration of an isometric view of an assembly fixture formed using a cradle system and coupled to a first tower in accordance with an illustrative embodiment;

FIG. 12 is an illustration of an isometric view of one stage in the assembly process for building a fuselage assembly that is being supported by an assembly fixture in accordance with an illustrative embodiment;

FIG. 13 is an illustration of an isometric view of another stage in the assembly process for building a fuselage assembly in accordance with an illustrative embodiment;

FIG. 14 is an illustration of an isometric view of another stage in the assembly process for building a fuselage assembly being supported by an assembly fixture in accordance with an illustrative embodiment;

FIG. 15 is an illustration of an isometric view of another stage in the assembly process for building a fuselage assembly in accordance with an illustrative embodiment;

FIG. 16 is an illustration of an isometric view of a second tower coupled to a utility fixture and an assembly fixture supporting a fuselage assembly in accordance with an illustrative embodiment;

FIG. 17 is an illustration of an isometric cutaway view of a plurality of mobile platforms performing fastening processes within an interior of a fuselage assembly in accordance with an illustrative embodiment;

FIG. 18 is an illustration of a cross-sectional view of a flexible manufacturing system performing operations on a fuselage assembly in accordance with an illustrative embodiment;

FIG. 19 is an illustration of an isometric view of a fully built fuselage assembly in accordance with an illustrative embodiment;

FIG. 20 is an illustration of an isometric view of fuselage assemblies being built within a manufacturing environment in accordance with an illustrative embodiment;

FIG. 21 is an illustration of an isometric view of a coupling structure and a utility fixture in accordance with an illustrative embodiment;

FIG. 22 is an illustration of an enlarged isometric view of a coupling unit and a corresponding coupling unit in accordance with an illustrative embodiment;

FIG. 23 is an illustration of a process for distributing a number of utilities in the form of a flowchart in accordance with an illustrative embodiment;

FIG. 24 is an illustration of a process for mating a coupling unit with a corresponding coupling unit in the form of a flowchart in accordance with an illustrative embodiment;

FIG. 25 is an illustration of a process for distributing a number of utilities to a tower in the form of a flowchart in accordance with an illustrative embodiment;

FIG. 26 is an illustration of a data processing system in the form of a block diagram in accordance with an illustrative embodiment;

FIG. 27 is an illustration of an aircraft manufacturing and service method in the form of a block diagram in accordance with an illustrative embodiment; and

FIG. 28 is an illustration of an aircraft in the form of a block diagram in accordance with an illustrative embodiment.

DETAILED DESCRIPTION

The illustrative embodiments recognize and take into account different considerations. For example, the illustrative embodiments recognize and take into account that it may be desirable to automate the process of building a fuselage assembly for an aircraft. Automating the process of building a fuselage assembly for an aircraft may improve build efficiency, improve build quality, and reduce costs associated with building the fuselage assembly. The illustrative embodiments also recognize and take into account that automating the process of building a fuselage assembly may improve the accuracy and precision with which assembly operations are performed, thereby ensuring improved compliance with outer mold line (OML) requirements and inner mold line (IML) requirements for the fuselage assembly.

Further, the illustrative embodiments recognize and take into account that automating the process used to build a fuselage assembly for an aircraft may significantly reduce the amount of time needed for the build cycle. For example, without limitation, automating fastening operations may reduce and, in some cases, eliminate, the need for human operators to perform these fastening operations as well as other types of assembly operations.

Further, this type of automation of the process for building a fuselage assembly for an aircraft may be less labor-intensive, time-consuming, ergonomically challenging, and expensive than performing this process primarily manually. Reduced manual labor may have a desired benefit for the human laborer. Additionally, automating the fuselage assembly process may allow fuselage assemblies to be built in desired assembly facilities and factories at desired assembly rates and desired assembly costs.

The illustrative embodiments also recognize and take into account that it may be desirable to use equipment that can be autonomously driven and operated to automate the process of building a fuselage assembly. In particular, it may be desirable to have an autonomous flexible manufacturing system comprised of mobile systems that may be autonomously driven across a factory floor, autonomously positioned relative to the factory floor as needed for building the fuselage assembly, autonomously operated to build the fuselage assembly, and then autonomously driven away when building of the fuselage assembly has been completed.

As used herein, performing any operation, action, or step autonomously may mean performing that operation substantially without any human input. For example, without limitation, a platform that may be autonomously driven is a platform that may be driven substantially independently of any human input. In this manner, an autonomously drivable platform may be a platform that is capable of driving or being driven substantially independently of human input.

Thus, the illustrative embodiments provide a method, apparatus, and system for building a fuselage assembly for an aircraft. In particular, the illustrative embodiments provide an autonomous flexible manufacturing system that automates most, if not all, of the process of building a fuselage assembly. For example, without limitation, the autonomous flexible manufacturing system may automate the process of installing fasteners to join fuselage skin panels and a fuselage support structure together to build the fuselage assembly.

However, the illustrative embodiments recognize and take into account that automating the process for building a fuselage assembly using an autonomous flexible manufacturing system may present unique technical challenges that require unique technical solutions. For example, the illustrative embodiments recognize and take into account that it may be desirable to provide utilities to all of the various systems within the autonomous flexible manufacturing system. In particular, it may be desirable to provide these utilities in a manner that will not disrupt or delay the process of building the fuselage assembly or restrict the movement of various mobile systems within the autonomous flexible manufacturing system over a factory floor.

For example, without limitation, it may be desirable to provide a set of utilities, such as power, communications, and air, to the autonomous flexible manufacturing system using an infrastructure that includes only a single direct connection to each of a set of utility sources providing the set of utilities. These direct connections may be above-ground, in-ground, or embedded. These direct connections may be established using, for example, without limitation, a utility fixture. Thus, the infrastructure may include a utility fixture that provides a direct connection to each of the set of utility sources and an assembly area with a floor space sufficiently large to allow the various systems of an autonomous flexible manufacturing system to be coupled to the utility fixture and each other in series. In this manner, the set of utilities may flow from the set of utility sources to the utility fixture and then downstream to the various systems of the autonomous flexible manufacturing system within the assembly area.

Thus, the illustrative embodiments provide a distributed utility network that may be used to provide utilities to the various systems of the autonomous flexible manufacturing system. The distributed utility network may provide these utilities in a manner that does not restrict or impede movement of the various mobile systems of the autonomous flexible manufacturing system. The different mobile systems of the autonomous flexible manufacturing system may be autonomously coupled to each other to create this distributed utility network.

Referring now to the figures and, in particular, with reference to FIGS. 1-7 , illustrations of a manufacturing environment are depicted in the form of block diagrams in accordance with an illustrative embodiment. In particular, in FIGS. 1-7 , a fuselage assembly, a flexible manufacturing system, the various systems within the flexible manufacturing system that may be used to build the fuselage assembly, and a distributed utility network are described.

Turning now to FIG. 1 , an illustration of a manufacturing environment is depicted in the form of a block diagram in accordance with an illustrative embodiment. In this illustrative example, manufacturing environment 100 may be an example of one environment in which at least a portion of fuselage 102 may be manufactured for aircraft 104.

Manufacturing environment 100 may take a number of different forms. For example, without limitation, manufacturing environment 100 may take the form of a factory, a manufacturing facility, an outdoor factory area, an enclosed manufacturing area, an offshore platform, or some other type of manufacturing environment 100 suitable for building at least a portion of fuselage 102.

Fuselage 102 may be built using manufacturing process 108. Flexible manufacturing system 106 may be used to implement at least a portion of manufacturing process 108. In one illustrative example, manufacturing process 108 may be substantially automated using flexible manufacturing system 106. In other illustrative examples, only one or more stages of manufacturing process 108 may be substantially automated.

Flexible manufacturing system 106 may be configured to perform at least a portion of manufacturing process 108 autonomously. In this manner, flexible manufacturing system 106 may be referred to as autonomous flexible manufacturing system 112. In other illustrative examples, flexible manufacturing system 106 may be referred to as an automated flexible manufacturing system.

As depicted, manufacturing process 108 may include assembly process 110 for building fuselage assembly 114. Flexible manufacturing system 106 may be configured to perform at least a portion of assembly process 110 autonomously.

Fuselage assembly 114 may be fuselage 102 at any stage during manufacturing process 108 prior to the completion of manufacturing process 108. In some cases, fuselage assembly 114 may be used to refer to a partially assembled fuselage 102. Depending on the implementation, one or more other components may need to be attached to fuselage assembly 114 to fully complete the assembly of fuselage 102. In other cases, fuselage assembly 114 may be used to refer to the fully assembled fuselage 102. Flexible manufacturing system 106 may build fuselage assembly 114 up to the point needed to move fuselage assembly 114 to a next stage in the manufacturing process for building aircraft 104. In some cases, at least a portion of flexible manufacturing system 106 may be used at one or more later stages in the manufacturing process for building aircraft 104.

In one illustrative example, fuselage assembly 114 may be an assembly for forming a particular section of fuselage 102. As one example, fuselage assembly 114 may take the form of aft fuselage assembly 116 for forming an aft section of fuselage 102. In another example, fuselage assembly 114 may take the form of forward fuselage assembly 117 for forming a forward section of fuselage 102. In yet another example, fuselage assembly 114 may take the form of middle fuselage assembly 118 for forming a center section of fuselage 102 or some other middle section of fuselage 102 between the aft and forward sections of fuselage 102.

As depicted, fuselage assembly 114 may include plurality of panels 120 and support structure 121. Support structure 121 may be comprised of plurality of members 122. Plurality of members 122 may be used to both support plurality of panels 120 and connect plurality of panels 120 to each other. Support structure 121 may help provide strength, stiffness, and load support for fuselage assembly 114.

Plurality of members 122 may be associated with plurality of panels 120. As used herein, when one component or structure is “associated” with another component or structure, the association is a physical association in the depicted examples.

For example, a first component, such as one of plurality of members 122, may be considered to be associated with a second component, such as one of plurality of panels 120, by being at least one of secured to the second component, bonded to the second component, mounted to the second component, attached to the component, coupled to the component, welded to the second component, fastened to the second component, adhered to the second component, glued to the second component, or connected to the second component in some other suitable manner. The first component also may be connected to the second component using one or more other components. For example, the first component may be connected to the second component using a third component. Further, the first component may be considered to be associated with the second component by being formed as part of the second component, an extension of the second component, or both. In another example, the first component may be considered part of the second component by being co-cured with the second component.

As used herein, the phrase “at least one of,” when used with a list of items, means different combinations of one or more of the listed items may be used and only one of the items in the list may be needed. The item may be a particular object, thing, action, process, or category. In other words, “at least one of” means any combination of items or number of items may be used from the list, but not all of the items in the list may be required.

For example, “at least one of item A, item B, and item C” or “at least one of item A, item B, or item C” may mean item A; item A and item B; item B; item A, item B, and item C; or item B and item C. In some cases, “at least one of item A, item B, and item C” may mean, for example, without limitation, two of item A, one of item B, and ten of item C; four of item B and seven of item C; or some other suitable combination.

In these illustrative examples, a member of plurality of members 122 may be associated with at least one of plurality of panels 120 in a number of different ways. For example, without limitation, a member of plurality of members 122 may be attached directly to a single panel, attached to two or more panels, attached to another member that is directly attached to at least one panel, attached to at least one member that is directly or indirectly attached to at least one panel, or associated with at least one of plurality of panels 120 in some other way.

In one illustrative example, substantially all or all of plurality of members 122 may be associated with plurality of panels 120 prior to the beginning of assembly process 110 for building fuselage assembly 114. For example, a corresponding portion of plurality of members 122 may be associated with each panel of plurality of panels 120 prior to plurality of panels 120 being joined to each other through assembly process 110.

In another illustrative example, only a first portion of plurality of members 122 may be associated with plurality of panels 120 prior to the beginning of assembly process 110. Assembly process 110 may include attaching a remaining portion of plurality of members 122 to plurality of panels 120 for at least one of providing support to plurality of panels 120 or connecting plurality of panels 120 together. The first portion of plurality of members 122 attached to plurality of panels 120 prior to assembly process 110 and the remaining portion of plurality of members 122 attached to plurality of panels 120 during assembly process 110 may together form support structure 121.

In yet another illustrative example, all of plurality of members 122 may be associated with plurality of panels 120 during assembly process 110. For example, each of plurality of panels 120 may be “naked” without any members attached to or otherwise associated with the panel prior to assembly process 110. During assembly process 110, plurality of members 122 may then be associated with plurality of panels 120.

In this manner, support structure 121 for fuselage assembly 114 may be built up in a number of different ways. Fuselage assembly 114 comprising plurality of panels 120 and support structure 121 is described in greater detail in FIG. 2 below.

Building fuselage assembly 114 may include joining plurality of panels 120 together. Joining plurality of panels 120 may be performed in a number of different ways. Depending on the implementation, joining plurality of panels 120 together may include joining one or more of plurality of members 122 to one or more of plurality of panels 120 or to other members of plurality of members 122.

In particular, joining plurality of panels 120 may include joining at least one panel to at least one other panel, joining at least one member to at least one other member, or joining at least one member to at least one panel, or some combination thereof. As one illustrative example, joining a first panel and a second panel together may include at least one of the following: fastening the first panel directly to the second panel, joining a first member associated with the first panel to a second member associated with the second panel, joining a member associated with the first panel directly to the second panel, joining one member associated with both the first panel and the second panel to another member, joining a selected member to both the first panel and the second panel, or some other type of joining operation.

Assembly process 110 may include operations 124 that may be performed to join plurality of panels 120 together to build fuselage assembly 114. In this illustrative example, flexible manufacturing system 106 may be used to perform at least a portion of operations 124 autonomously.

Operations 124 may include, for example, but are not limited to, temporary connection operations 125, drilling operations 126, fastener insertion operations 128, fastener installation operations 130, inspection operations 132, other types of assembly operations, or some combination thereof. Temporary connection operations 125 may be performed to temporarily connect plurality of panels 120 together. For example, without limitation, temporary connection operations 125 may include temporarily tacking plurality of panels 120 together using tack fasteners.

Drilling operations 126 may include drilling holes through one or more of plurality of panels 120 and, in some cases, through one or more of plurality of members 122. Fastener insertion operations 128 may include inserting fasteners into the holes drilled by drilling operations 126.

Fastener installation operations 130 may include fully installing each of the fasteners that have been inserted into the holes. Fastener installation operations 130 may include, for example, without limitation, riveting operations, interference-fit bolting operations, other types of fastener installation operations, or some combination thereof. Inspection operations 132 may include inspecting the fully installed fasteners. Depending on the implementation, flexible manufacturing system 106 may be used to perform any number of these different types of operations 124 substantially autonomously.

As depicted, flexible manufacturing system 106 may include plurality of mobile systems 134, control system 136, and utility system 138. Each of plurality of mobile systems 134 may be a drivable mobile system. In some cases, each of plurality of mobile systems 134 may be an autonomously drivable mobile system. For example, without limitation, each of plurality of mobile systems 134 may include one or more components that may be autonomously driven within manufacturing environment 100 from one location to another location. Plurality of mobile systems 134 are described in greater detail in FIG. 3 below.

In this illustrative example, control system 136 may be used to control the operation of flexible manufacturing system 106. For example, without limitation, control system 136 may be used to control plurality of mobile systems 134. In particular, control system 136 may be used to direct the movement of each of plurality of mobile systems 134 within manufacturing environment 100. Control system 136 may be at least partially associated with plurality of mobile systems 134.

In one illustrative example, control system 136 may include set of controllers 140. As used herein, a “set of” items may include one or more items. In this manner, set of controllers 140 may include one or more controllers.

Each of set of controllers 140 may be implemented using hardware, firmware, software, or some combination thereof. In one illustrative example, set of controllers 140 may be associated with plurality of mobile systems 134. For example, without limitation, one or more of set of controllers 140 may be implemented as part of plurality of mobile systems 134. In other examples, one or more of set of controllers 140 may be implemented independently of plurality of mobile systems 134.

Set of controllers 140 may generate commands 142 to control the operation of plurality of mobile systems 134 of flexible manufacturing system 106. Set of controllers 140 may communicate with plurality of mobile systems 134 using at least one of a wireless communications link, a wired communications link, an optical communications link, or other type of communications link. In this manner, any number of different types of communications links may be used for communication with and between set of controllers 140.

In these illustrative examples, control system 136 may control the operation of plurality of mobile systems 134 using data 141 received from sensor system 133. Sensor system 133 may be comprised of any number of individual sensor systems, sensor devices, controllers, other types of components, or combination thereof. In one illustrative example, sensor system 133 may include laser tracking system 135 and radar system 137. Laser tracking system 135 may be comprised of any number of laser tracking devices, laser targets, or combination thereof. Radar system 137 may be comprised of any number of radar sensors, radar targets, or combination thereof.

Sensor system 133 may be used to coordinate the movement and operation of the various mobile systems in plurality of mobile systems 134 within manufacturing environment 100. As one illustrative example, radar system 137 may be used for macro-positioning mobile systems, systems within mobile systems, components within mobile systems, or some combination thereof. Further, laser tracking system 135 may be used for micro-positioning mobile systems, systems within mobile systems, components within mobile systems, or some combination thereof.

Plurality of mobile systems 134 may be used to form distributed utility network 144. Depending on the implementation, one or more of plurality of mobile systems 134 may form distributed utility network 144. Number of utilities 146 may flow from number of utility sources 148 to the various mobile systems of plurality of mobile systems 134 that make up distributed utility network 144.

In this illustrative example, each of number of utility sources 148 may be located with manufacturing environment 100. In other illustrative examples, one or more of number of utility sources 148 may be located outside of manufacturing environment 100. The corresponding utility provided by these one or more utility sources may then be carried into manufacturing environment 100 using, for example, without limitation, one or more utility cables.

In one illustrative example, distributed utility network 144 may allow number of utilities 146 to flow directly from number of utility sources 148 to one mobile system in plurality of mobile systems 134 over some number of utility cables. This one mobile system may then distribute number of utilities 146 to other mobile systems of plurality of mobile systems 134 such that these other mobile systems do not need to directly receive number of utilities 146 from number of utility sources 148.

As depicted, distributed utility network 144 may be formed using utility system 138. Utility system 138 may include utility fixture 150. Utility system 138 may be configured to connect to number of utility sources 148 such that number of utilities 146 may flow from number of utility sources 148 to utility fixture 150. Utility fixture 150 may be above-ground or in-ground, depending on the implementation. For example, without limitation, utility fixture 150 may be embedded in a floor within manufacturing environment 100.

Utility fixture 150 may then distribute number of utilities 146 to one or more of plurality of mobile systems 134. In particular, one autonomous coupling of one of plurality of mobile systems 134 to utility fixture 150 may be followed by any number of autonomous couplings of mobile systems to each other in series to form distributed utility network 144. Utility fixture 150 may distribute number of utilities 146 to each of plurality of mobile systems 134 downstream of utility fixture 150 in the series of autonomous couplings of the mobile systems.

Depending on the implementation, distributed utility network 144 may have a chain-like configuration or a tree-like configuration. In one illustrative example, plurality of mobile systems 134 may include mobile systems A, B, C, and D (not shown in figure) with mobile system A autonomously coupled to utility fixture 150 and mobile systems B, C, and D autonomously coupled to mobile system A and each other in series. An example of a chain-like configuration for distributed utility network 144 may include number of utilities 146 flowing from number of utility sources 148 over some number of utility cables to utility fixture 150, from utility fixture 150 to mobile system A, from mobile system A to mobile system B, from mobile system B to mobile system C, and from mobile system C to mobile system D. An example of a tree-like configuration for distributed utility network 144 may include number of utilities 146 flowing from number of utility sources 148 over some number of utility cables to utility fixture 150, from utility fixture 150 to mobile system A, from mobile system A to both mobile system B and mobile system C, and from mobile system C to mobile system D. An example of one manner in which distributed utility network 144 may be implemented using plurality of mobile systems 134 is described in greater detail in FIG. 5 below.

In some illustrative examples, multiple flexible manufacturing systems may be used to build multiple fuselage assemblies concurrently. For example, flexible manufacturing system 106 may be a first flexible manufacturing system of many flexible manufacturing systems.

In one illustrative example, flexible manufacturing system 106, second flexible manufacturing system 152, and third flexible manufacturing system 154 may be used to build aft fuselage assembly 116, middle fuselage assembly 118, and forward fuselage assembly 117, respectively. Aft fuselage assembly 116, middle fuselage assembly 118, and forward fuselage assembly 117 may then be joined together to form a fully assembled fuselage 102. In this manner, in this example, flexible manufacturing system 106, second flexible manufacturing system 152, and third flexible manufacturing system 154 may together form flexible fuselage manufacturing system 158.

Thus, any number of fuselage assemblies, such as fuselage assembly 114, may be built within manufacturing environment 100 using any number of flexible manufacturing systems implemented in a manner similar to flexible manufacturing system 106. Similarly, any number of full fuselages, such as fuselage 102, may be built within manufacturing environment 100 using any number of flexible fuselage manufacturing systems implemented in a manner similar to flexible fuselage manufacturing system 158.

With reference now to FIG. 2 , an illustration of fuselage assembly 114 from FIG. 1 is depicted in the form of a block diagram in accordance with an illustrative embodiment. As described above, fuselage assembly 114 may include plurality of panels 120 and support structure 121. Fuselage assembly 114 may be used to refer to any stage in the building of fuselage assembly 114. For example, fuselage assembly 114 may be used to refer to a single one of plurality of panels 120, multiple ones of plurality of panels 120 that have been or are being joined together, a partially built fuselage assembly, or a fully built fuselage assembly.

As depicted, fuselage assembly 114 may be built such that fuselage assembly 114 has plurality of fuselage sections 205. Each of plurality of fuselage sections 205 may include one or more of plurality of panels 120. In this illustrative example, each of plurality of fuselage sections 205 may take the form of a cylindrically-shaped fuselage section, a barrel-shaped fuselage section, a tapered cylindrical fuselage section, a cone-shaped fuselage section, a dome-shaped fuselage section, or a section having some other type of shape. Depending on the implementation, a fuselage section of plurality of fuselage sections 205 may have a shape that has a substantially circular cross-sectional shape, elliptical cross-sectional shape, oval cross-sectional shape, polygon with rounded corners cross-sectional shape, or otherwise closed-curve cross-sectional shape.

As one specific illustrative example, each of plurality of fuselage sections 205 may be a portion of fuselage assembly 114 defined between two radial cross-sections of fuselage assembly 114 that are taken substantially perpendicular to a center axis or longitudinal axis through fuselage assembly 114. In this manner, plurality of fuselage sections 205 may be arranged along the longitudinal axis of fuselage assembly 114. In other words, plurality of fuselage sections 205 may be arranged longitudinally.

Fuselage section 207 may be an example of one of plurality of fuselage sections 205. Fuselage section 207 may be comprised of one or more of plurality of panels 120. In one illustrative example, multiple panel sections may be arranged circumferentially around fuselage section 207 to form the skin of fuselage section 207. In some cases, multiple rows of two or more longitudinally adjacent panels may be arranged circumferentially around fuselage section 207 to form the skin of fuselage section 207.

In one illustrative example, fuselage assembly 114 may have crown 200, keel 202, and sides 204. Sides 204 may include first side 206 and second side 208.

Crown 200 may be the top portion of fuselage assembly 114. Keel 202 may be the bottom portion of fuselage assembly 114. Sides 204 of fuselage assembly 114 may be the portions of fuselage assembly 114 between crown 200 and keel 202. In one illustrative example, each of crown 200, keel 202, first side 206, and second side 208 of fuselage assembly 114 may be formed by at least a portion of at least one of plurality of panels 120. Further, a portion of each of plurality of fuselage sections 205 may form each of crown 200, keel 202, first side 206, and second side 208.

Panel 216 may be an example of one of plurality of panels 120. Panel 216 may also be referred to as a skin panel, a fuselage panel, or a fuselage skin panel, depending on the implementation. In some illustrative examples, panel 216 may take the form of a mega-panel comprised of multiple smaller panels, which may be referred to as sub-panels. A mega-panel may also be referred to as a super panel. In these illustrative examples, panel 216 may be comprised of at least one of a metal, a metal alloy, some other type of metallic material, a composite material, or some other type of material. As one illustrative example, panel 216 may be comprised of an aluminum alloy, steel, titanium, a ceramic material, a composite material, some other type of material, or some combination thereof.

When used to form keel 202 of fuselage assembly 114, panel 216 may be referred to as a keel panel or a bottom panel. When used to form one of sides 204 of fuselage assembly 114, panel 216 may be referred to as a side panel. When used to form crown 200 of fuselage assembly 114, panel 216 may be referred to as a crown panel or a top panel. As one illustrative example, plurality of panels 120 may include crown panels 218 for forming crown 200, side panels 220 for forming sides 204, and keel panels 222 for forming keel 202. Side panels 220 may include first side panels 224 for forming first side 206 and second side panels 226 for forming second side 208.

In one illustrative example, fuselage section 207 of plurality of fuselage sections 205 of fuselage assembly 114 may include one of crown panels 218, two of side panels 220, and one of keel panels 222. In another illustrative example, fuselage section 207 may form an end of fuselage assembly 114.

In some cases, fuselage section 207 may be comprised solely of a single panel, such as panel 216. For example, without limitation, panel 216 may take the form of end panel 228.

End panel 228 may be used to form one end of fuselage assembly 114. For example, when fuselage assembly 114 takes the form of aft fuselage assembly 116 in FIG. 1 , end panel 228 may form the aftmost end of fuselage assembly 114. When fuselage assembly 114 takes the form of forward fuselage assembly 117 in FIG. 1 , end panel 228 may form the forwardmost end of fuselage assembly 114.

In one illustrative example, end panel 228 may take the form of a cylindrically-shaped panel, a cone-shaped panel, a barrel-shaped panel, or a tapered cylindrical panel. For example, end panel 228 may be a single cylindrically-shaped panel having a substantially circular cross-sectional shape that may change in diameter with respect to a center axis for fuselage assembly 114.

In this manner, as described above, fuselage section 207 may be comprised solely of end panel 228. In some illustrative examples, fuselage section 207 may be an end fuselage section that is comprised of only a single panel, which may be end panel 228. In some cases, bulkhead 272 may be associated with end panel 228 when fuselage section 207 is an end fuselage section. Bulkhead 272, which may also be referred to as a pressure bulkhead, may be considered separate from or part of end panel 228, depending on the implementation. Bulkhead 272 may have a dome-type shape in these illustrative examples.

When fuselage assembly 114 takes the form of aft fuselage assembly 116 in FIG. 1 , bulkhead 272 may be part of fuselage section 207 located at the aftmost end of aft fuselage assembly 116. When fuselage assembly 114 takes the form of forward fuselage assembly 117 in FIG. 1 , bulkhead 272 may be part of fuselage section 207 located at forwardmost end of forward fuselage assembly 117. Middle fuselage assembly 118 in FIG. 1 may not include a bulkhead, such as bulkhead 272, at either end of middle fuselage assembly 118. In this manner, plurality of fuselage sections 205 may be implemented in any number of different ways.

Panel 216 may have first surface 230 and second surface 232. First surface 230 may be configured for use as an exterior-facing surface. In other words, first surface 230 may be used to form exterior 234 of fuselage assembly 114. Second surface 232 may be configured for use as an interior-facing surface. In other words, second surface 232 may be used to form interior 236 of fuselage assembly 114. Each of plurality of panels 120 may be implemented in a manner similar to panel 216.

As described earlier, support structure 121 may be associated with a corresponding one of plurality of panels 120. Support structure 121 may be comprised of plurality of members 122 that are associated with panel 216. In one illustrative example, corresponding portion 240 may be the portion of plurality of members 122 that correspond to panel 216. Corresponding portion 240 may form support section 238 corresponding to panel 216. Support section 238 may form a part of support structure 121.

Plurality of members 122 may include support members 242. Support members 242 may include, for example, without limitation, at least one of connecting members 244, frames 246, stringers 248, stiffeners 250, stanchions 252, intercostal structural members 254, or other types of structural members.

Connecting members 244 may connect other types of support members 242 together. In some cases, connecting members 244 may also connect support members 242 to plurality of panels 120. Connecting members 244 may include, for example, without limitation, shear clips 256, ties 258, splices 260, intercostal connecting members 262, other types of mechanical connecting members, or some combination thereof.

In one illustrative example, when panel 216 is comprised of multiple sub-panels, connecting members 244 may be used to, for example, without limitation, connect together complementary frames of frames 246 running in the hoop-wise direction on adjacent sub-panels and complementary stringers of stringers 248 running in the longitudinal direction on adjacent sub-panels. In other illustrative examples, connecting members 244 may be used to connect together complementary frames, stringers, or other types of support members on two or more adjacent panels in plurality of panels 120. In some cases, connecting members 244 may be used to connect together complementary support members on two or more adjacent fuselage sections.

Operations 124, as described in FIG. 1 , may be performed to join plurality of panels 120 together to build fuselage assembly 114. In one illustrative example, plurality of fasteners 264 may be used to join plurality of panels 120 together.

As described above, joining plurality of panels 120 together may be performed in a number of different ways. Joining plurality of panels 120 together may include at least one of joining at least one panel in plurality of panels 120 to another one of plurality of panels 120, joining at least one panel in plurality of panels 120 to at least one of plurality of members 122, joining at least one member in plurality of members 122 to another one of plurality of members 122, or some other type of joining operation. Plurality of panels 120 may be joined together such that plurality of members 122 ultimately form support structure 121 for fuselage assembly 114.

As depicted, number of floors 266 may be associated with fuselage assembly 114. In this illustrative example, number of floors 266 may be part of fuselage assembly 114. Number of floors 266 may include, for example, without limitation, at least one of a passenger floor, a cargo floor, or some other type of floor.

With reference now to FIG. 3 , an illustration of plurality of mobile systems 134 of flexible manufacturing system 106 within manufacturing environment 100 from FIG. 1 is depicted in the form of a block diagram in accordance with an illustrative embodiment. As depicted, flexible manufacturing system 106 may be used to build fuselage assembly 114 on floor 300 of manufacturing environment 100. When manufacturing environment 100 takes the form of a factory, floor 300 may be referred to as factory floor 302.

In one illustrative example, floor 300 may be substantially smooth and substantially planar. For example, floor 300 may be substantially level. In other illustrative examples, one or more portions of floor 300 may be sloped, ramped, or otherwise uneven.

Assembly area 304 may be an area within manufacturing environment 100 designated for performing assembly process 110 in FIG. 1 to build a fuselage assembly, such as fuselage assembly 114. Assembly area 304 may also be referred to as a cell or a work cell. In this illustrative example, assembly area 304 may be a designated area on floor 300. However, in other illustrative examples, assembly area 304 may include a designated area on floor 300 as well as the area above this designated area. Any number of assembly areas may be present within manufacturing environment 100 such that any number of fuselage assemblies may be built concurrently within manufacturing environment 100.

As depicted, plurality of mobile systems 134 may include plurality of autonomous vehicles 306, cradle system 308, tower system 310, and autonomous tooling system 312. Each of plurality of mobile systems 134 may be drivable across floor 300. In other words, each of plurality of mobile systems 134 may be capable of being autonomously driven across floor 300 from one location 315 to another location 317 on floor 300.

In one illustrative example, each of plurality of autonomous vehicles 306 may take the form of an automated guided vehicle (AGV), which may be capable of operating independently without human direction or guidance. In some cases, plurality of autonomous vehicles 306 may be referred to as a plurality of automated guided vehicles (AGVs).

In this illustrative example, cradle system 308 may be used to support and hold fuselage assembly 114 during assembly process 110 in FIG. 1 . In some cases, cradle system 308 may be referred to as a drivable cradle system. In still other cases, cradle system 308 may be referred to as an autonomously drivable cradle system.

Cradle system 308 may include number of fixtures 313. As used herein, a “number of” items may include one or more items. In this manner, number of fixtures 313 may include one or more fixtures. In some illustrative examples, number of fixtures 313 may be referred to as a number of drivable fixtures. In other illustrative examples, number of fixtures 313 may be referred to as a number of autonomously drivable fixtures.

Number of fixtures 313 may include number of cradle fixtures 314. In some illustrative examples, number of cradle fixtures 314 may be referred to as a number of drivable cradle fixtures. In other illustrative examples, number of cradle fixtures 314 may be referred to as a number of autonomously drivable cradle fixtures. Cradle fixture 322 may be an example of one of number of cradle fixtures 314.

Number of retaining structures 326 may be associated with each of number of cradle fixtures 314. Number of retaining structures 326 associated with each of number of cradle fixtures 314 may be engaged with and used to support fuselage assembly 114. For example, number of retaining structures 326 associated with cradle fixture 322 may be engaged with and used to support one or more of plurality of panels 120.

Number of cradle fixtures 314 may be autonomously driven across floor 300 of manufacturing environment 100 to assembly area 304. In one illustrative example, each of number of cradle fixtures 314 may be autonomously driven across floor 300 using a corresponding one of plurality of autonomous vehicles 306. In other words, without limitation, number of corresponding autonomous vehicles 316 in plurality of autonomous vehicles 306 may be used to drive number of cradle fixtures 314 across floor 300 into assembly area 304.

In this illustrative example, number of corresponding autonomous vehicles 316 may drive from, for example, without limitation, holding area 318, across floor 300, to assembly area 304. Holding area 318 may be an area in which at least one of plurality of autonomous vehicles 306, cradle system 308, tower system 310, autonomous tooling system 312, or control system 136 from FIG. 1 may be held when flexible manufacturing system 106 is not in use or when that particular device or system is not in use.

Holding area 318 may be referred to as a home area, a storage area, or a base area, depending on the implementation. Although holding area 318 is depicted as being located within manufacturing environment 100, holding area 318 may be located in some other area or environment outside of manufacturing environment 100 in other illustrative examples.

Number of corresponding autonomous vehicles 316 in plurality of autonomous vehicles 306 may drive number of cradle fixtures 314 into number of selected cradle positions 320. As used herein, a “position” may be comprised of a location, an orientation, or both. The location may be in two-dimensional coordinates or three-dimensional coordinates with respect to a reference coordinate system. The orientation may be a two-dimensional or three-dimensional orientation with respect to a reference coordinate system. This reference coordinate system may be, for example, without limitation, a fuselage coordinate system, an aircraft coordinate system, a coordinate system for manufacturing environment 100, or some other type of coordinate system.

When number of cradle fixtures 314 includes more than one cradle fixture such that number of selected cradle positions 320 includes more than one cradle position, these cradle positions may be positions selected relative to each other. In this manner, number of cradle fixtures 314 may be positioned such that number of cradle fixtures 314 are in number of selected cradle positions 320 relative to each other.

In these illustrative examples, number of corresponding autonomous vehicles 316 may be used to drive number of cradle fixtures 314 into number of selected cradle positions 320 within assembly area 304. “Driving” a component or a system across floor 300 may mean, for example, but not limited to, moving substantially the entirety of that component or system from one location to another location. For example, without limitation, driving cradle fixture 322 across floor 300 may mean moving the entirety of cradle fixture 322 from one location to another location. In other words, all or substantially all components that comprise cradle fixture 322 may be simultaneously moved together from one location to another location.

Once number of cradle fixtures 314 has been driven into number of selected cradle positions 320 in assembly area 304, number of cradle fixtures 314 may be coupled to each other and to tower system 310. Number of corresponding autonomous vehicles 316 may then drive away from number of cradle fixtures 314 to, for example, without limitation, holding area 318, once number of cradle fixtures 314 is positioned in number of selected cradle positions 320 within selected tolerances. In other illustrative examples, number of corresponding autonomous vehicles 316 may be comprised of a single autonomous vehicle that is used to drive each of number of cradle fixtures 314 into a corresponding selected position in number of selected cradle positions 320 within assembly area 304 one at a time.

In assembly area 304, number of cradle fixtures 314 may be configured to form assembly fixture 324. Assembly fixture 324 may be formed when the different cradle fixtures in number of cradle fixtures 314 have been placed in number of selected cradle positions 320 relative to each other. In some cases, assembly fixture 324 may be formed when number of cradle fixtures 314 have been coupled to each other while number of cradle fixtures 314 is in number of selected cradle positions 320 and when number of retaining structures 326 associated with each of number of cradle fixtures 314 has been adjusted to receive fuselage assembly 114.

In this manner, number of cradle fixtures 314 may form a single fixture entity, such as assembly fixture 324. Assembly fixture 324 may be used to support and hold fuselage assembly 114. In some cases, assembly fixture 324 may be referred to as an assembly fixture system or a fixture system. In some cases, assembly fixture 324 may be referred to as a drivable assembly fixture. In other cases, assembly fixture 324 may be referred to as an autonomously drivable assembly fixture.

Once assembly fixture 324 has been formed, number of cradle fixtures 314 may receive fuselage assembly 114. In other words, plurality of fuselage sections 205 may be engaged with number of cradle fixtures 314. In particular, plurality of fuselage sections 205 may be engaged with number of retaining structures 326 associated with each of number of cradle fixtures 314. Plurality of fuselage sections 205 may be engaged with number of cradle fixtures 314 in any number of ways.

When number of cradle fixtures 314 includes a single cradle fixture, that cradle fixture may be used to support and hold substantially the entire fuselage assembly 114. When number of cradle fixtures 314 includes multiple cradle fixtures, each of these cradle fixtures may be used to support and hold at least one corresponding fuselage section of plurality of fuselage sections 205.

In one illustrative example, each of plurality of fuselage sections 205 may be engaged with number of cradle fixtures 314 one at a time. For example, without limitation, all of the panels for a particular fuselage section in plurality of fuselage sections 205 may be positioned relative to each other and a corresponding cradle fixture in number of cradle fixtures 314 and then engaged with the corresponding cradle fixture. The remaining fuselage sections in plurality of fuselage sections 205 may then be formed and engaged with number of cradle fixtures 314 in a similar manner. In this manner, plurality of panels 120 may be engaged with number of cradle fixtures 314 by engaging at least a portion of plurality of panels 120 with number of retaining structures 326 associated with each of number of cradle fixtures 314 that makes up assembly fixture 324 such that plurality of panels 120 is supported by number of cradle fixtures 314.

As described in FIG. 2 , plurality of panels 120 may include keel panels 222, side panels 220, and crown panels 218. In one illustrative example, all of keel panels 222 in FIG. 2 used to form keel 202 of fuselage assembly 114 in FIG. 2 may first be positioned relative to and engaged with number of cradle fixtures 314. Next, all of side panels 220 in FIG. 2 used to form sides 204 of fuselage assembly 114 in FIG. 2 may be positioned relative to and engaged with keel panels 222. Then, all of crown panels 218 in FIG. 2 used to form crown 200 of fuselage assembly 114 in FIG. 2 may be positioned relative to and engaged with side panels 220. In this manner, plurality of fuselage sections 205 may be concurrently assembled to form fuselage assembly 114.

In one illustrative example, each panel in plurality of panels 120 may have a corresponding portion of plurality of members 122 fully formed and associated with the panel prior to the panel being engaged with one of number of cradle fixtures 314. This corresponding portion of plurality of members 122 may be referred to as a support section. For example, support section 238 in FIG. 2 may be fully formed and associated with panel 216 in FIG. 2 prior to panel 216 being engaged with one of number of cradle fixtures 314 or another panel of plurality of panels 120 in FIG. 2 . In other words, a corresponding portion of support members 242 in FIG. 2 may already be attached to panel 216 and a corresponding portion of connecting members 244 in FIG. 2 already installed to connect this portion of support members 242 to each other prior to panel 216 from FIG. 2 being engaged with one of number of cradle fixtures 314.

In other illustrative examples, plurality of members 122 may be associated with plurality of panels 120 after plurality of panels 120 have been engaged with each other and number of cradle fixtures 314. In still other illustrative examples, only a portion of plurality of members 122 may be associated with plurality of panels 120 prior to plurality of panels 120 being engaged with each other and number of cradle fixtures 314 and then a remaining portion of plurality of members 122 associated with plurality of panels 120 once plurality of panels 120 have been engaged with each other and number of cradle fixtures 314.

In some illustrative examples, one or more of support members 242 in FIG. 2 , one or more of connecting members 244 in FIG. 2 , or both may not be associated with panel 216 when panel 216 from FIG. 2 is engaged with one of number of cradle fixtures 314 or with one of the other panels in plurality of panels 120. For example, without limitation, frames 246 described in FIG. 2 may be added to panel 216 from FIG. 2 after panel 216 has been engaged with cradle fixture 322. In another example, stiffeners 250 described in FIG. 2 may be added to panel 216 from FIG. 2 after panel 216 has been engaged with cradle fixture 322.

Building fuselage assembly 114 may include engaging plurality of panels 120 with each other as plurality of panels 120 are built up on number of cradle fixtures 314 of assembly fixture 324. For example, adjacent panels in plurality of panels 120 may be connected by connecting at least a portion of the support members associated with the panels. Depending on the implementation, at least one of lap splices, butt splices, or other types of splices may be used to connect the adjacent panels in addition to or in place of connecting the corresponding support members of the adjacent panels.

As one illustrative example, the support members associated with two adjacent panels in plurality of panels 120 may be connected together using connecting members, thereby connecting the two adjacent panels. The two support members associated with these two adjacent panels may be, for example, without limitation, spliced, tied, clipped, tacked, pinned, joined, or fastened together in some other manner. When the two adjacent panels are hoop-wise adjacent, complementary frames may be connected in the hoop-wise direction. When the two adjacent panels are longitudinally adjacent, complementary stringers may be connected in the longitudinal direction.

In some cases, connecting complementary stringers, frames, or other support members on these two adjacent panels may be part of splicing these panels together. Adjacent panels may be connected together using any number of panel splices, stringer splices, frame splices, or other types of splices.

In one illustrative example, plurality of panels 120 may be temporarily connected to each other by temporarily fastening at least one of plurality of panels 120 or plurality of members 122 together using temporary fasteners or permanent fasteners. For example, without limitation, temporary clamps may be used to temporarily connect and hold in place two of plurality of panels 120 together. Temporarily connecting plurality of panels 120 together may be performed by at least one of temporarily connecting at least two plurality of panels 120 together, temporarily connecting at least two plurality of members 122 together, or temporarily connecting at least one of plurality of panels 120 to at least one of plurality of members 122 such that plurality of members 122 associated with plurality of panels 120 forms support structure 121 in FIG. 2 for fuselage assembly 114.

As one illustrative example, plurality of panels 120 may be temporarily tacked or pinned together using temporary fasteners 328 until plurality of fasteners 264 are installed to join plurality of panels 120 together to form fuselage assembly 114. Temporarily connecting plurality of panels 120 may temporarily connect together plurality of fuselage sections 205 from FIG. 2 formed by plurality of panels 120. Once plurality of fasteners 264 have been installed, temporary fasteners 328 may then be removed.

In this manner, plurality of panels 120 may be connected together in a number of different ways. Once plurality of panels 120 have been connected together, plurality of members 122 may be considered as forming support structure 121 for fuselage assembly 114. Connecting plurality of panels 120 together and forming support structure 121 may maintain desired compliance with outer mold line requirements and inner mold line requirements for fuselage assembly 114. In other words, plurality of panels 120 may be held together in place relative to each other such that fuselage assembly 114 formed using plurality of panels 120 meets outer mold line requirements and inner mold line requirements for fuselage assembly 114 within selected tolerances.

In particular, assembly fixture 324 may support plurality of panels 120 and support structure 121 associated with plurality of panels 120 such that fuselage assembly 114 built using plurality of panels 120 and support structure 121 has a shape and a configuration that is within selected tolerances. In this manner, this shape and configuration may be maintained within selected tolerances while supporting plurality of panels 120 and plurality of members 122 associated with plurality of panels 120 during the building of fuselage assembly 114. This shape may be at least partially determined by, for example, without limitation, the outer mold line requirements and inner mold line requirements for fuselage assembly 114. In some cases, the shape may be at least partially determined by the location and orientation of the frames and stringers of fuselage assembly 114.

In some cases, when the assembly of plurality of panels 120 and support structure 121 that comprise fuselage assembly 114 has reached a desired point, number of corresponding autonomous vehicles 316 may drive assembly fixture 324 out of assembly area 304. For example, fuselage assembly 114 may be driven across floor 300 into a different area within manufacturing environment 100, from floor 300 onto another floor in a different manufacturing environment, or from floor 300 onto another floor in some other area or environment.

In one illustrative example, assembly fixture 324 may be driven to some other location at which another assembly fixture is located such that the two assembly fixtures may be coupled to form a larger assembly fixture. As one illustrative example, assembly fixture 324 may be used to hold and support aft fuselage assembly 116 in FIG. 1 , while another assembly fixture implemented in a manner similar to assembly fixture 324 may be used to hold and support forward fuselage assembly 117 in FIG. 1 . Yet another assembly fixture implemented in a manner similar to assembly fixture 324 may be used to hold and support middle fuselage assembly 118 in FIG. 1 .

Once these three fuselage assemblies have been built, the three assembly fixtures may be brought together to form a larger assembly fixture for holding aft fuselage assembly 116, middle fuselage assembly 118, and forward fuselage assembly 117 such that these three fuselage assemblies may be joined to form fuselage 102 described in FIG. 1 . In particular, this larger assembly fixture may hold aft fuselage assembly 116, middle fuselage assembly 118, and forward fuselage assembly 117 in alignment with each other such that fuselage 102 may be built within selected tolerances.

In another illustrative example, a first assembly fixture and a second assembly fixture implemented in a manner similar to assembly fixture 324 may be used to hold and support aft fuselage assembly 116 and forward fuselage assembly 117, respectively, from FIG. 1 . Once these two fuselage assemblies have been built, the two assembly fixtures may then be brought together to form a larger assembly fixture for holding the two fuselage assemblies such that these fuselage assemblies may be joined to form fuselage 102. The larger assembly fixture may hold aft fuselage assembly 116 and forward fuselage assembly 117 in alignment with each other such that fuselage 102 may be built within selected tolerances.

As depicted, tower system 310 includes number of towers 330. Tower 332 may be an example of one implementation for one of number of towers 330. Tower 332 may be configured to provide access to interior 236 of fuselage assembly 114 described in FIG. 2 . In some illustrative examples, tower 332 may be referred to as a drivable tower. In other illustrative examples, tower 332 may be referred to as an autonomously drivable tower.

In one illustrative example, tower 332 may take the form of first tower 334. First tower 334 may also be referred to as an operator tower in some cases. In another illustrative example, tower 332 may take the form of second tower 336. Second tower 336 may also be referred to as a robotics tower in some cases. In this manner, number of towers 330 may include both first tower 334 and second tower 336.

First tower 334 may be configured substantially for use by a human operator, whereas second tower 336 may be configured substantially for use by a mobile platform having at least one robotic device associated with the mobile platform. In other words, first tower 334 may allow a human operator to access and enter interior 236 of fuselage assembly 114. Second tower 336 may allow a mobile platform to access and enter interior 236 of fuselage assembly 114.

First tower 334 and second tower 336 may be positioned relative to assembly fixture 324 at different times during assembly process 110. As one illustrative example, one of plurality of autonomous vehicles 306 may be used to move or autonomously drive first tower 334 from holding area 318 into selected tower position 338 within assembly area 304. Number of cradle fixtures 314 may then be autonomously driven, using number of corresponding autonomous vehicles 316, into number of selected cradle positions 320 relative to first tower 334, which is in selected tower position 338 within assembly area 304.

Second tower 336 may be exchanged for first tower 334 at some later stage during assembly process 110 in FIG. 1 . For example, one of plurality of autonomous vehicles 306 may be used to autonomously drive first tower 334 out of assembly area 304 and back into holding area 318. The same autonomous vehicle or a different autonomous vehicle in plurality of autonomous vehicles 306 may then be used to autonomously drive second tower 336 from holding area 318 into selected tower position 338 within assembly area 304 that was previously occupied by first tower 334. Depending on the implementation, first tower 334 may be later exchanged for second tower 336.

In other illustrative examples, first tower 334 and second tower 336 may each have an autonomous vehicle in plurality of autonomous vehicles 306 fixedly associated with the tower. In other words, one of plurality of autonomous vehicles 306 may be integrated with first tower 334 and one of plurality of autonomous vehicles 306 may be integrated with second tower 336. For example, one of plurality of autonomous vehicles 306 may be considered part of or built into first tower 334. First tower 334 may then be considered capable of autonomously driving across floor 300. In a similar manner, one of plurality of autonomous vehicles 306 may be considered part of or built into second tower 336. Second tower 336 may then be considered capable of autonomously driving across floor 300.

Tower system 310 and assembly fixture 324 may be configured to form interface 340 with each other. Interface 340 may be a physical interface between tower system 310 and assembly fixture 324. Tower system 310 may also be configured to form interface 342 with utility system 138. In one illustrative example, interface 340 and interface 342 may be autonomously formed.

Interface 342 may be a physical interface between tower system 310 and utility system 138. In these illustrative examples, in addition to being physical interfaces, interface 340 and interface 342 may also be utility interfaces. For example, with respect to the utility of power, interface 340 and interface 342 may be considered electrical interfaces.

Utility system 138 is configured to distribute number of utilities 146 to tower system 310 when tower system 310 and utility system 138 are physically and electrically coupled through interface 342. Tower system 310 may then distribute number of utilities 146 to assembly fixture 324 formed by cradle system 308 when assembly fixture 324 and tower system 310 are physically and electrically coupled through interface 340. Number of utilities 146 may include at least one of power, air, hydraulic fluid, communications, water, or some other type of utility.

As depicted, utility system 138 may include utility fixture 150. Utility fixture 150 may be configured to receive number of utilities 146 from number of utility sources 148. Number of utility sources 148 may include, for example, without limitation, at least one of a power generator, a battery system, a water system, an electrical line, a communications system, a hydraulic fluid system, an air tank, or some other type of utility source. For example, utility fixture 150 may receive power from a power generator.

In one illustrative example, utility fixture 150 may be positioned relative to assembly area 304. Depending on the implementation, utility fixture 150 may be positioned inside assembly area 304 or outside of assembly area 304.

In some illustrative examples, utility fixture 150 may be associated with floor 300. Depending on the implementation, utility fixture 150 may be permanently associated with floor 300 or temporarily associated with floor 300. In other illustrative examples, utility fixture 150 may be associated with some other surface of manufacturing environment 100, such as a ceiling, or some other structure in manufacturing environment 100. In some cases, utility fixture 150 may be embedded within floor 300.

In one illustrative example, first tower 334 may be autonomously driven into selected tower position 338 with respect to floor 300 relative to utility fixture 150 such that interface 342 may be formed between first tower 334 and utility fixture 150. Once interface 342 has been formed, number of utilities 146 may flow from utility fixture 150 to first tower 334. Assembly fixture 324 may then autonomously form interface 340 with first tower 334 to form a network of utility cables between first tower 334 and assembly fixture 324. Once both interface 342 and interface 340 have been formed, number of utilities 146 received at utility fixture 150 may flow from utility fixture 150 to first tower 334 and to each of number of cradle fixtures 314 that forms assembly fixture 324. In this manner, first tower 334 may function as a conduit or “middleman” for distributing number of utilities 146 to assembly fixture 324.

When interface 340 has been formed between second tower 336 and assembly fixture 324 and interface 342 has been formed between second tower 336 and utility fixture 150, number of utilities 146 may be provided to second tower 336 and assembly fixture 324 in a similar manner as described above. Thus, utility fixture 150 may distribute number of utilities 146 to tower system 310 and assembly fixture 324 without tower system 310 and cradle assembly fixture 324 having to separately connect to number of utility sources 148 or any other utility sources.

Autonomous tooling system 312 may be used to assemble plurality of panels 120 and support structure 121 while fuselage assembly 114 is being supported and held by assembly fixture 324. Autonomous tooling system 312 may include plurality of mobile platforms 344. Each of plurality of mobile platforms 344 may be configured to perform one or more of operations 124 in assembly process 110 described in FIG. 1 . In particular, plurality of mobile platforms 344 may be autonomously driven into selected positions relative to plurality of panels 120 within selected tolerances to autonomously perform operations 124 that join plurality of panels 120 together to build fuselage assembly 114. Plurality of mobile platforms 344 are described in greater detail in FIG. 4 below.

In this illustrative example, set of controllers 140 in control system 136 may generate commands 142 as described in FIG. 1 to control the operation of at least one of cradle system 308, tower system 310, utility system 138, autonomous tooling system 312, or plurality of autonomous vehicles 306. Set of controllers 140 in FIG. 1 may communicate with at least one of cradle system 308, tower system 310, utility system 138, autonomous tooling system 312, or plurality of autonomous vehicles 306 using any number of wireless communications links, wired communications links, optical communications links, other types of communications links, or combination thereof.

In this manner, plurality of mobile systems 134 of flexible manufacturing system 106 may be used to automate the process of building fuselage assembly 114. Plurality of mobile systems 134 may enable fuselage assembly 114 to be built substantially autonomously with respect to joining together plurality of panels 120 to reduce the overall time, effort, and human resources needed.

Flexible manufacturing system 106 may build fuselage assembly 114 up to the point needed to move fuselage assembly 114 to the next stage in manufacturing process 108 for building fuselage 102 or the next stage in the manufacturing process for building aircraft 104, depending on the implementation. In some cases, cradle system 308 in the form of assembly fixture 324 may continue carrying and supporting fuselage assembly 114 during one or more of these later stages in manufacturing process 108 for building fuselage 102 and aircraft 104.

With reference now to FIG. 4 , an illustration of plurality of mobile platforms 344 from FIG. 3 is depicted in the form of a block diagram in accordance with an illustrative embodiment. As depicted, plurality of mobile platforms 344 may include number of external mobile platforms 400 and number of internal mobile platforms 402. In this manner, plurality of mobile platforms 344 may include at least one external mobile platform and at least one internal mobile platform.

In some illustrative examples, number of external mobile platforms 400 may be referred to as a number of drivable external mobile platforms. Similarly, in some cases, number of internal mobile platforms 402 may be referred to as a number of drivable internal mobile platforms. In other illustrative examples, number of external mobile platforms 400 and number of internal mobile platforms 402 may be referred to as a number of autonomously drivable external mobile platforms and a number of autonomously drivable internal mobile platforms, respectively.

External mobile platform 404 may be an example of one of number of external mobile platforms 400 and internal mobile platform 406 may be an example of one of number of internal mobile platforms 402. External mobile platform 404 and internal mobile platform 406 may be platforms that are autonomously drivable. Depending on the implementation, each of external mobile platform 404 and internal mobile platform 406 may be configured to autonomously drive across floor 300 on its own or with the assistance of one of plurality of autonomous vehicles 306 from FIG. 3 .

As one illustrative example, without limitation, external mobile platform 404 may be autonomously driven across floor 300 using a corresponding one of plurality of autonomous vehicles 306. In some illustrative examples, external mobile platform 404 and this corresponding one of plurality of autonomous vehicles 306 may be integrated with each other. For example, the autonomous vehicle may be fixedly associated with external mobile platform 404. An entire load of external mobile platform 404 may be transferable to the autonomous vehicle such that driving the autonomous vehicle across floor 300 drives external mobile platform 404 across floor 300.

External mobile platform 404 may be driven from, for example, without limitation, holding area 318 to a position relative to exterior 234 of fuselage assembly 114 to perform one or more operations 124 in FIG. 1 . As depicted, at least one external robotic device 408 may be associated with external mobile platform 404. In this illustrative example, external robotic device 408 may be considered part of external mobile platform 404. In other illustrative examples, external robotic device 408 may be considered a separate component that is physically attached to external mobile platform 404. External robotic device 408 may take the form of, for example, without limitation, a robotic arm.

External robotic device 408 may have first end effector 410. Any number of tools may be associated with first end effector 410. These tools may include, for example, without limitation, at least one of a drilling tool, a fastener insertion tool, a fastener installation tool, an inspection tool, or some other type of tool. In particular, any number of fastening tools may be associated with first end effector 410.

As depicted, first tool 411 may be associated with first end effector 410. In one illustrative example, first tool 411 may be any tool that is removably associated with first end effector 410. In other words, first tool 411 associated with first end effector 410 may be changed as various operations need to be performed. For example, without limitation, first tool 411 may take the form of one type of tool, such as a drilling tool, to perform one type of operation. This tool may then be exchanged with another type of tool, such as a fastener insertion tool, to become the new first tool 411 associated with first end effector 410 to perform a different type of operation.

In one illustrative example, first tool 411 may take the form of first riveting tool 412. First riveting tool 412 may be used to perform riveting operations. In some illustrative examples, a number of different tools may be exchanged with first riveting tool 412 and associated with first end effector 410. For example, without limitation, first riveting tool 412 may be exchangeable with a drilling tool, a fastener insertion tool, a fastener installation tool, an inspection tool, or some other type of tool.

External mobile platform 404 may be autonomously driven across floor 300 and positioned relative to assembly fixture 324 in FIG. 3 supporting fuselage assembly 114 to position first end effector 410 and first tool 411 associated with first end effector 410 relative to one of plurality of panels 120. For example, external mobile platform 404 may be autonomously driven across floor 300 to external position 414 relative to assembly fixture 324. In this manner, first tool 411 carried by external mobile platform 404 may be macro-positioned using external mobile platform 404.

Once in external position 414, first end effector 410 may be autonomously controlled using at least external robotic device 408 to position first tool 411 associated with first end effector 410 relative to a particular location on an exterior-facing side of one of plurality of panels 120. In this manner, first tool 411 may be micro-positioned relative to the particular location.

Internal mobile platform 406 may be located on second tower 336 in FIG. 3 when internal mobile platform 406 is not in use. When interface 342 described in FIG. 3 is formed between second tower 336 and assembly fixture 324, internal mobile platform 406 may be driven from second tower 336 into interior 236 of fuselage assembly 114 and used to perform one or more of operations 124. In one illustrative example, internal mobile platform 406 may have a movement system that allows internal mobile platform 406 to move from second tower 336 onto a floor inside fuselage assembly 114.

At least one internal robotic device 416 may be associated with internal mobile platform 406. In this illustrative example, internal robotic device 416 may be considered part of internal mobile platform 406. In other illustrative examples, internal robotic device 416 may be considered a separate component that is physically attached to internal mobile platform 406. Internal robotic device 416 may take the form of, for example, without limitation, a robotic arm.

Internal robotic device 416 may have second end effector 418. Any number of tools may be associated with second end effector 418. For example, without limitation, at least one of a drilling tool, a fastener insertion tool, a fastener installation tool, an inspection tool, or some other type of tool may be associated with second end effector 418. In particular, any number of fastening tools may be associated with second end effector 418.

As depicted, second tool 419 may be associated with second end effector 418. In one illustrative example, second tool 419 may be any tool that is removably associated with second end effector 418. In other words, second tool 419 associated with second end effector 418 may be changed as various operations need to be performed. For example, without limitation, second tool 419 may take the form of one type of tool, such as a drilling tool, to perform one type of operation. This tool may then be exchanged with another type of tool, such as a fastener insertion tool, to become the new second tool 419 associated with second end effector 418 to perform a different type of operation.

In one illustrative example, second tool 419 may take the form of second riveting tool 420. Second riveting tool 420 may be associated with second end effector 418. Second riveting tool 420 may be used to perform riveting operations. In some illustrative examples, a number of different tools may be exchanged with second riveting tool 420 and associated with second end effector 418. For example, without limitation, second riveting tool 420 may be exchangeable with a drilling tool, a fastener insertion tool, a fastener installation tool, an inspection tool, or some other type of tool.

Internal mobile platform 406 may be driven from second tower 336 into fuselage assembly 114 and positioned relative to interior 236 of fuselage assembly 114 to position second end effector 418 and second tool 419 associated with second end effector 418 relative to one of plurality of panels 120. In one illustrative example, internal mobile platform 406 may be autonomously driven onto one of number of floors 266 in FIG. 2 into internal position 422 within fuselage assembly 114 relative to fuselage assembly 114. In this manner, second tool 419 may be macro-positioned into internal position 422 using internal mobile platform 406.

Once in internal position 422, second end effector 418 may be autonomously controlled to position second tool 419 associated with second end effector 418 relative to a particular location on an interior-facing side of one of plurality of panels 120 or an interior-facing side of one of plurality of members 122 in FIG. 2 that make up support structure 121. In this manner, second tool 419 may be micro-positioned relative to the particular location.

In one illustrative example, external position 414 for external mobile platform 404 and internal position 422 for internal mobile platform 406 may be selected such that fastening process 424 may be performed at location 426 on fuselage assembly 114 using external mobile platform 404 and internal mobile platform 406. Fastening process 424 may include any number of operations. In one illustrative example, fastening process 424 may include at least one of drilling operation 428, fastener insertion operation 430, fastener installation operation 432, inspection operation 434, or some other type of operation.

As one specific example, drilling operation 428 may be performed autonomously using first tool 411 associated with first end effector 410 of external mobile platform 404 or second tool 419 associated with second end effector 418 of internal mobile platform 406. For example, without limitation, first tool 411 or second tool 419 may take the form of a drilling tool for use in performing drilling operation 428. Drilling operation 428 may be autonomously performed using first tool 411 or second tool 419 to form hole 436 at location 426. Hole 436 may pass through at least one of two panels in plurality of panels 120, two members of a plurality of members 122, or a panel and one of plurality of members 122.

Fastener insertion operation 430 may be performed autonomously using first tool 411 associated with first end effector 410 of external mobile platform 404 or second tool 419 associated with second end effector 418 of internal mobile platform 406. Fastener insertion operation 430 may result in fastener 438 being inserted into hole 436.

Fastener installation operation 432 may then be performed autonomously using at least one of first tool 411 associated with first end effector 410 of external mobile platform 404 or second tool 419 associated with second end effector 418 of internal mobile platform 406. In one illustrative example, fastener installation operation 432 may be performed autonomously using first tool 411 in the form of first riveting tool 412 and second tool 419 in the form of second riveting tool 420 such that fastener 438 becomes rivet 442 installed at location 426. Rivet 442 may be a fully installed rivet. Rivet 442 may be one of plurality of fasteners 264 described in FIG. 2 .

In one illustrative example, fastener installation operation 432 may take the form of bolt-nut type installation process 433. First tool 411 associated with first end effector 410 may be used to, for example, without limitation, install bolt 435 through hole 436. Second tool 419 associated with second end effector 418 may then be used to install nut 437 over bolt 435. In some cases, installing nut 437 may include applying a torque sufficient to nut 437 such that a portion of nut 437 breaks off. In these cases, nut 437 may be referred to as a frangible collar.

In another illustrative example, fastener installation operation 432 may take the form of interference-fit bolt-type installation process 439. First tool 411 associated with first end effector 410 may be used to, for example, without limitation, install bolt 435 through hole 436 such that an interference fit is created between bolt 435 and hole 436. Second tool 419 associated with second end effector 418 may then be used to install nut 437 over bolt 435.

In yet another illustrative example, fastener installation operation 432 may take the form of two-stage riveting process 444. Two-stage riveting process 444 may be performed using, for example, without limitation, first riveting tool 412 associated with external mobile platform 404 and second riveting tool 420 associated with internal mobile platform 406.

For example, first riveting tool 412 and second riveting tool 420 may be positioned relative to each other by external mobile platform 404 and internal mobile platform 406, respectively. For example, external mobile platform 404 and external robotic device 408 may be used to position first riveting tool 412 relative to location 426 at exterior 234 of fuselage assembly 114. Internal mobile platform 406 and internal robotic device 416 may be used to position second riveting tool 420 relative to the same location 426 at interior 236 of fuselage assembly 114.

First riveting tool 412 and second riveting tool 420 may then be used to perform two-stage riveting process 444 to form rivet 442 at location 426. Rivet 442 may join at least two of plurality of panels 120 together, a panel in plurality of panels 120 to support structure 121 formed by plurality of members 122, or two panels in plurality of panels 120 to support structure 121.

In this example, two-stage riveting process 444 may be performed at each of plurality of locations 446 on fuselage assembly 114 to install plurality of fasteners 264 as described in FIG. 2 . Two-stage riveting process 444 may ensure that plurality of fasteners 264 in FIG. 2 are installed at plurality of locations 446 with a desired quality and desired level of accuracy.

In this manner, internal mobile platform 406 may be autonomously driven and operated inside fuselage assembly 114 to position internal mobile platform 406 and second riveting tool 420 associated with internal mobile platform 406 relative to plurality of locations 446 on fuselage assembly 114 for performing assembly process 110 described in FIG. 1 . Similarly, external mobile platform 404 may be autonomously driven and operated around fuselage assembly 114 to position external mobile platform 404 and first riveting tool 412 associated with external mobile platform 404 relative to plurality of locations 446 on fuselage assembly 114 for performing operations 124.

With reference now to FIG. 5 , an illustration of a flow of number of utilities 146 across distributed utility network 144 from FIG. 1 is depicted in the form of a block diagram in accordance with an illustrative embodiment. As depicted, number of utilities 146 may be distributed across distributed utility network 144.

Distributed utility network 144 may include, for example, without limitation, number of utility sources 148, utility fixture 150, number of towers 330, assembly fixture 324, number of external mobile platforms 400, and number of utility units 500. In some cases, distributed utility network 144 may also include number of internal mobile platforms 402. In some illustrative examples, number of utility sources 148 may be considered separate from distributed utility network 144.

In this illustrative example, only one of number of towers 330 may be included in distributed utility network 144 at a time. When first tower 334 is used, distributed utility network 144 may be formed when utility fixture 150 is coupled to number of utility sources 148, first tower 334 is coupled to utility fixture 150, assembly fixture 324 is coupled to first tower 334, and number of external mobile platforms 400 is coupled to number of utility units 500.

Number of utility units 500 may be associated with number of cradle fixtures 314 of assembly fixture 324 or separated from number of cradle fixtures 314. For example, without limitation, a number of dual interfaces may be created between number of external mobile platforms 400, number of utility units 500, and number of cradle fixtures 314 using one or more dual-interface couplers.

When second tower 336 is used, distributed utility network 144 may be formed when utility fixture 150 is coupled to number of utility sources 148, second tower 336 is coupled to utility fixture 150, assembly fixture 324 is coupled to second tower 336, number of internal mobile platforms 402 is coupled to second tower 336, and number of external mobile platforms 400 is coupled to number of utility units 500, which may be associated with number of cradle fixtures 314 or separated from number of cradle fixtures 314. Number of internal mobile platforms 402 may receive number of utilities 146 through a number of cable management systems associated with second tower 336.

In this manner, number of utilities 146 may be distributed across distributed utility network 144 using a single utility fixture 150. This type of distributed utility network 144 may reduce the number of utility components, utility cables, and other types of devices needed to provide number of utilities 146 to the various components in distributed utility network 144. Further, with this type of distributed utility network 144, starting from at least utility fixture 150, number of utilities 146 may be provided completely above floor 300 of manufacturing environment in FIG. 1 .

With reference now to FIG. 6 , an illustration of utility fixture 150 from FIGS. 1 and 5 is depicted in the form of a block diagram in accordance with an illustrative embodiment. As depicted, utility fixture 150 may be associated with floor 300. In particular, utility fixture 150 may have base structure 600 that is associated with floor 300.

In one illustrative example, utility fixture 150 may be affixed to floor 300 at location 602. Depending on the implementation, utility fixture 150 may be permanently affixed to floor 300 or removably affixed to floor 300. For example, without limitation, base structure 600 of utility fixture 150 may be permanently fastened to floor 300 at location 602 using number of fastener devices 604. In particular, base structure 600 may be bolted to location 602 using number of fastener devices 604. In other examples, utility fixture 150 may be temporarily affixed to floor 300 at location 602. In still other illustrative examples, utility fixture 150 may be embedded in floor 300, mounted to a wall in manufacturing environment 100 in FIG. 1 , mounted to a ceiling of manufacturing environment 100 in FIG. 1 , or mounted to some other surface of structure in manufacturing environment 100 in FIG. 1 .

As depicted, number of input cables 606 may be connected to utility fixture 150. Number of input cables 606 may connect utility fixture 150 to number of utility sources 148. For example, without limitation, each of number of input cables 606 may be connected to utility fixture 150 at one end and to a corresponding one of number of output connections 607 associated with number of utility sources 148 at the other end. Each of number of input cables 606 may carry a corresponding one of number of utilities 146 from the corresponding one of number of utility sources 148 to utility fixture 150.

Number of utility sources 148 may include, for example, without limitation, a power source, an air supply source, a water source, a hydraulic fluid source, a communications source, some other type of source, or some combination thereof. In some cases, more than one of number of input cables 606 may connect to a same utility source.

Set of coupling units 608 may be associated with base structure 600. Set of coupling units 608 may be used to couple mobile system 610 to utility fixture 150. Mobile system 610 may take the form of tower 332 in FIG. 3 , cradle fixture 322 in FIG. 3 , or some other type of drivable system. A coupling unit that is capable of sending at least one utility to or receiving at least one utility from a corresponding coupling unit when interfaced with the corresponding coupling unit may be referred to as a utility coupling unit. The corresponding coupling unit may then also be referred to as a utility coupling unit. When a coupling unit is used to provide only a mechanical coupling, the coupling unit may be referred to as a mechanical coupling unit.

Set of coupling units 608 may be coupled to, or mated with, set of corresponding coupling units 614 associated with mobile system 610. Set of corresponding coupling units 614 may be associated with coupling structure 615, which may be associated with mobile system 610. Depending on the implementation, set of corresponding coupling units 614 may be considered part of or independent of coupling structure 615. In some illustrative examples, coupling structure 615 and set of corresponding coupling units 614 may be together referred to as a utility coupler. When mobile system 610 takes the form of tower 332, coupling structure 615 may be associated with base structure 617 of tower 332.

The mating of set of coupling units 608 to set of corresponding coupling units 614 may be performed autonomously, manually, or both, depending on the implementation. In this manner, the coupling of set of coupling units 608 to set of corresponding coupling units 614 may take the form of at least one of autonomous coupling 621, manual coupling 623, or both. In these illustrative examples, the mating of at least one of set of coupling units 608 with a corresponding one of set of corresponding coupling units 614 may be performed autonomously.

Coupling unit 612 may be an example of one of set of coupling units 608. Corresponding coupling unit 613 may be an example of one of set of corresponding coupling units 614. Coupling unit 612 may be configured to couple to corresponding coupling unit 613 associated with mobile system 610. In other words, coupling unit 612 may be mated with corresponding coupling unit 613 to physically couple utility fixture 150 to mobile system 610 and at least one of electrically or fluidly couple utility fixture 150 to mobile system 610. In one illustrative example, coupling unit 612 may be autonomously mated with or coupled to corresponding coupling unit 613.

Coupling unit 612 may take a number of different forms. Coupling unit 612 may include, for example, without limitation, quick-change device 616 and at least one of power coupling element 618, air coupling element 620, hydraulic coupling element 622, communications coupling element 624, water coupling element 626, or some other type of coupling element.

Quick-change device 616 may be configured to mate with corresponding quick-change device 627. For example, without limitation, quick-change device 616 may take the form of male quick-change device 625. Male quick-change device 625 may be configured to mate with a corresponding female quick-change device, such as female quick-change device 628 associated with mobile system 610. Mating male quick-change device 625 to female quick-change device 628 may concurrently cause the mating of at least one of power coupling element 618, air coupling element 620, hydraulic coupling element 622, communications coupling element 624, or water coupling element 626 included in coupling unit 612 with at least one of corresponding power coupling element 630, corresponding air coupling element 632, corresponding hydraulic coupling element 634, corresponding communications coupling element 636, or corresponding water coupling element 638, respectively, included in corresponding coupling unit 613.

Mating male quick-change device 625 and female quick-change device 628 may physically couple utility fixture 150 with mobile system 610. Mating power coupling element 618 with corresponding power coupling element 630 may electrically couple utility fixture 150 and mobile system 610. Mating air coupling element 620 with corresponding air coupling element 632 may fluidly connect utility fixture 150 and mobile system 610 such that air may flow from coupling unit 612 to corresponding coupling unit 613.

Further, mating hydraulic coupling element 622 with corresponding hydraulic coupling element 634 may fluidly connect utility fixture 150 and mobile system 610 such that hydraulic fluid may flow from coupling unit 612 to corresponding coupling unit 613. Similarly, mating communications coupling element 624 with corresponding communications coupling element 636 may connect utility fixture 150 and mobile system 610 such that data may be transmitted from coupling unit 612 to corresponding coupling unit 613. Still further, mating water coupling element 626 with corresponding water coupling element 638 may fluidly connect utility fixture 150 and mobile system 610 such that water may flow from coupling unit 612 to corresponding coupling unit 613.

As depicted, coupling unit 612 may also have alignment system 650 and corresponding coupling unit 613 may have alignment system 652. Alignment system 650 and alignment system 652 may be coordinated such that coupling unit 612 may be aligned with corresponding coupling unit 613 for coupling. In particular, alignment system 650 and alignment system 652 may align coupling unit 612 and corresponding coupling unit 613 such that autonomous coupling 621 may be performed. In this illustrative example, alignment system 650 and alignment system 652 may be used to align coupling unit 612 with corresponding coupling unit 613 autonomously.

In one illustrative example, alignment system 650 may include at least one of set of movement systems 654, sensor device 655, or guidance fork 656. In this example, alignment system 652 may include at least one of set of movement systems 658, sensor device 659, or roller 660. Sensor device 655 and sensor device 659 may each take the form of an imaging system, depending on the implementation.

Set of movement systems 654 may be used to move coupling unit 612 with at least one degree of freedom relative to utility fixture 150 for alignment purposes. Set of movement systems 658 may be used to move corresponding coupling unit 613 with at least one degree of freedom relative to mobile system 610 for alignment purposes. Each movement system in set of movement systems 654 and set of movement systems 658 may be implemented using at least one of an actuation device, an air cylinder, a motor, a rail system, an X-Y table, a track system, a slider, a roller, a wheel, or some other type of movement device.

In one illustrative example, at least one of set of movement systems 654 or set of movement systems 658 may be used to guide roller 660 within guidance fork 656. In this example, roller 660 may be guided within guidance fork 656 to provide horizontal alignment or vertical alignment between coupling unit 612 and corresponding coupling unit 613, depending on the orientation of guidance fork 656 relative to utility fixture 150 and roller 660 relative to mobile system 610. When roller 660 is within guidance fork 656, roller 660 may be considered engaged with guidance fork 656, thereby mating alignment system 652 with alignment system 650.

In this illustrative example, data generated by sensor device 655 may be processed and used to control the operation of set of movement systems 654. Further, data generated by sensor device 659 may be processed and used to control the operation of set of movement systems 658. In this manner, sensor device 655 may generate data for use in aligning guidance fork 656 relative to roller 660 along at least one axis. Similarly, sensor device 659 may generate data for use in aligning roller 660 relative to guidance fork 656 along at least one axis.

Depending on the implementation, alignment system 650 and alignment system 652 may include any number of structural members, connective elements, or other types of alignment elements for use in aligning coupling unit 612 and corresponding coupling unit 613 with each other within selected tolerances. In these illustrative examples, alignment system 650 and alignment system 652 may facilitate autonomous coupling 621 of coupling unit 612 and corresponding coupling unit 613.

In this manner, one or more of the utilities in number of utilities 146 may be coupled between coupling unit 612 and corresponding coupling unit 613. Each of set of coupling units 608 may be mated with one of set of corresponding coupling units 614 in a similar manner. Different combinations of utilities may be coupled between utility fixture 150 and mobile system 610 through each pair of mated coupling units.

Mating set of coupling units 608 with set of corresponding coupling units 614 may create set of interfaces 640. One or more of the utilities in number of utilities 146 may flow across each of set of interfaces 640 from utility fixture 150 to mobile system 610.

Number of input cables 606 may carry number of utilities 146 to set of coupling units 608. Number of utilities 146 may flow across set of interfaces 640 to set of corresponding coupling units 614. Number of distribution cables 642 may then carry number of utilities 146 from set of corresponding coupling units 614 to various systems and components. As one illustrative example, number of distribution cables 642 may carry number of utilities 146 from set of corresponding coupling units 614 to at least one of a utility box (not shown) associated with tower 332, number of internal mobile platforms 402 from FIG. 4 located on tower 332, number of cradle fixtures 314 in FIG. 3 , or some other component, system, or platform.

Coupling tower 332 to utility fixture 150 may establish distributed utility network 144 described in FIG. 5 . Other systems may be added to distributed utility network 144 by coupling these other systems in series to tower 332 in a similar manner.

As one illustrative example, cradle fixture 322 may be coupled to tower 332 such that number of utilities 146 may flow from tower 332 to cradle fixture 322. In particular, different set of coupling units 644 may be associated with tower 332. Different set of coupling units 644 may be autonomously mated with or coupled to different set of corresponding coupling units 646 associated with cradle fixture 322. Each of different set of coupling units 644 may be implemented in a manner similar to that described for coupling unit 612. Similarly, each of different set of corresponding coupling units 646 may be implemented in a manner similar to that described for corresponding coupling unit 613.

In one illustrative example, each of different set of coupling units 644 may include a male quick-change device that may be mated with a female quick-change device of a corresponding one of different set of corresponding coupling units 646. Each pair of mated coupling units may form an interface similar to each of set of interfaces 640.

With reference now to FIG. 7 , an illustration of one implementation for distributed utility network 144 from FIGS. 1 and 5 is depicted in accordance with an illustrative embodiment. Within distributed utility network 144, tower 332 may be coupled to utility fixture 150; first cradle fixture 700 may be coupled to tower 332; second cradle fixture 702 may be coupled to first cradle fixture 700; and third cradle fixture 704 may be coupled to second cradle fixture 702.

As depicted, set of tower coupling units 706 may be associated with tower 332. Set of corresponding first cradle coupling units 708 and set of first cradle coupling units 710 may be associated with first cradle fixture 700. Set of corresponding second cradle coupling units 712 and set of second cradle coupling units 714 may be associated with second cradle fixture 702. Set of corresponding third cradle coupling units 716 may be associated with third cradle fixture 704.

In particular, set of coupling units 608 may be mated with set of corresponding coupling units 614, thereby coupling utility fixture 150 and tower 332. In one illustrative example, set of coupling units 608 may be referred to as a set of utility fixture coupling units and set of corresponding coupling units 614 may be referred to as a set of corresponding tower coupling units. Number of utility cables 718 may carry number of utilities 146 from set of corresponding coupling units 614 to set of tower coupling units 706.

In this illustrative example, set of tower coupling units 706 may be mated with set of corresponding first cradle coupling units 708, thereby coupling first cradle fixture 700 to tower 332. Number of utility cables 720 may carry number of utilities 146 from set of corresponding first cradle coupling units 708 to set of first cradle coupling units 710. Set of first cradle coupling units 710 may be mated with set of corresponding second cradle coupling units 712, thereby coupling second cradle fixture 702 to first cradle fixture 700.

Number of utility cables 722 may carry number of utilities 146 from set of corresponding second cradle coupling units 712 to set of second cradle coupling units 714. Set of second cradle coupling units 714 may be mated with set of corresponding third cradle coupling units 716, thereby coupling third cradle fixture 704 to second cradle fixture 702. In this manner, utility fixture 150, tower 332, first cradle fixture 700, second cradle fixture 702, and third cradle fixture 704 may be connected in series.

Depending on the implementation, one or more of number of external mobile platforms 400 from FIG. 4 may be coupled to first cradle fixture 700, second cradle fixture 702, or third cradle fixture 704. In one illustrative example, these couplings may be implemented in a manner similar to that described above. In other illustrative examples, these couplings may be implemented using dual-interface couplers.

Further, number of internal mobile platforms 402 may receive number of utilities 146 from tower 332 when tower 332 takes the form of second tower 336 described in FIG. 3 . For example, at least a portion of number of distribution cables 642 in FIG. 6 may be used to carry number of utilities 146 to number of internal mobile platforms 402.

In some illustrative examples, number of utility connection devices 724 may be associated with tower 332. For example, without limitation, number of utility connection devices 724 may be associated with base structure 617 of tower 322 as shown in FIG. 6 . Base structure 617 may include any number of platform levels for tower 332. At least a portion of number of distribution cables 642 in FIG. 6 may be used to carry number of utilities 146 from set of corresponding coupling units 614 to number of utility connection devices 724.

Number of utility connection devices 724 may be used to provide number of utilities 146 from tower 332 to number of human-operated tools 726. For example, without limitation, one or more human operators may plug one or more utility cables extending from number of human-operated tools 726 into number of utility connection devices 724. Number of human-operated tools 726 may then be carried into interior 236 of fuselage assembly 114 shown in FIG. 2 . In this manner, utility sources, such as a power generator, an air compressor, a hydraulic fluid tank, and other types of utility sources, may not need to be located within interior 236 of fuselage assembly 114 shown in FIG. 2 during the building of fuselage assembly 114. Consequently, the weight placed on number of floors 266 of fuselage assembly 114 in FIG. 2 during building may be reduced. For example, the weight associated with providing number of utilities 146 to tools inside fuselage assembly 114 may be reduced to simply the weight of the tools and the weight of the utility cables used to connect the tools to number of utility connection devices 724.

The illustrations in FIGS. 1-7 are not meant to imply physical or architectural limitations to the manner in which an illustrative embodiment may be implemented. Other components in addition to or in place of the ones illustrated may be used. Some components may be optional. Also, the blocks are presented to illustrate some functional components. One or more of these blocks may be combined, divided, or combined and divided into different blocks when implemented in an illustrative embodiment.

For example, in some cases, more than one flexible manufacturing system may be present within manufacturing environment 100. These multiple flexible manufacturing systems may be used to build multiple fuselage assemblies within manufacturing environment 100. In other illustrative examples, flexible manufacturing system 106 may include multiple cradle systems, multiple tower systems, multiple utility systems, multiple autonomous tooling systems, and multiple pluralities of autonomous vehicles such that multiple fuselage assemblies may be built within manufacturing environment 100.

In some illustrative examples, utility system 138 may include multiple utility fixtures that are considered separate from flexible manufacturing system 106. Each of these multiple utility fixtures may be configured for use with flexible manufacturing system 106 and any number of other flexible manufacturing systems.

Additionally, the different couplings of mobile systems in plurality of mobile systems 134 may be performed autonomously in these illustrative examples. However, in other illustrative example, a coupling of one of plurality of mobile systems 134 to another one of plurality of mobile systems 134 may be performed manually in other illustrative examples.

Further, in other illustrative examples, one or more of plurality of mobile systems 134 may be drivable by, for example, without limitation, a human operator. For example, without limitation, in some cases, first tower 332 may be drivable with human guidance.

In some illustrative examples, set of coupling units 608 may be distributed across more than one utility fixture. For example, without limitation, in some cases, multiple utility fixtures, implemented in a manner similar to utility fixture 150 may be used to provide number of utilities 146 from number of utility sources 148 to flexible manufacturing system 106 in FIG. 1 . In some cases, the coupling units in set of coupling units 608 may be located in different locations on floor 300 or other surfaces of manufacturing environment 100. For example, without limitation, a portion of the coupling units may be mounted to or embedded in the floor, while another portion of the coupling units may be mounted to or attached to a ceiling of manufacturing environment 100.

As one illustrative example, a first coupling unit may have power coupling element 618, a second coupling unit may have air coupling element 620, a third coupling unit may have hydraulic coupling element 622 and water coupling element 626, and a fourth coupling unit may have communications coupling element 624. Depending on the implementation, all of these coupling units may be part of utility fixture 150 or may be associated with different utility fixtures. These different utility fixtures may be located in different locations on floor 300 or other surfaces of manufacturing environment 100. For example, without limitation, one or more utility fixtures may be mounted to or embedded in the floor, one or more utility fixtures may be mounted to or attached to a ceiling of manufacturing environment 100, and one or more other utility fixtures may be mounted to or attached to a wall in manufacturing environment 100.

With this type of implementation, the corresponding coupling units to be mated to these types of coupling units may also be located in different locations. For example, coupling units in set of corresponding coupling units 614 may be associated with various coupling structures attached to different locations on base structure 617 of tower 332.

In still other illustrative examples, a portion of set of coupling units 608 may be mated with corresponding coupling units associated with tower 332, while another portion of set of coupling units 608 may be mated with corresponding coupling units associated with assembly fixture 324. In this manner, distributed utility network 144 may be implemented in a number of different ways. Further, number of utilities 146 may be provided to flexible manufacturing system 106 in any number of different ways.

In still other illustrative examples, mobile system 610 in FIG. 6 may take the form of cradle fixture 322 in FIG. 3 . Consequently, utility fixture 150 may be coupled to cradle fixture 322. In these examples, number of utilities 146 may be distributed from utility fixture 150, to cradle fixture 322, and then to a remaining portion of assembly fixture 324 and tower 332. In this manner, distributed utility network 144 may have any number of configurations. Number of utilities 146 may flow downstream in series through distributed utility network 144 regardless of the configuration of distributed utility network 144.

With reference now to FIG. 8 , an illustration of an isometric view of a manufacturing environment is depicted in accordance with an illustrative embodiment. In this illustrative example, manufacturing environment 800 may be an example of one implementation for manufacturing environment 100 in FIG. 1 .

As depicted, manufacturing environment 800 may include holding environment 801 and assembly environment 802. Holding environment 801 may be a designated area on and over floor 803 of manufacturing environment 800 for storing plurality of flexible manufacturing systems 806 when plurality of flexible manufacturing systems 806 are not in use. Each of plurality of flexible manufacturing systems 806 may be an example of one implementation for flexible manufacturing system 106 described in FIGS. 1 and 3-5 . In particular, each of plurality of flexible manufacturing systems 806 may be an example of one implementation for autonomous flexible manufacturing system 112 in FIG. 1 .

Holding environment 801 may include plurality of holding cells 804. In this illustrative example, each of plurality of holding cells 804 may be considered an example of one implementation for holding area 318 in FIG. 3 . In other illustrative examples, the entire holding environment 801 may be considered an example of one implementation for holding area 318 in FIG. 3 .

Each of plurality of flexible manufacturing systems 806 may be stored in a corresponding one of plurality of holding cells 804. In particular, each of plurality of holding cells 804 may be designated for a specific one of plurality of flexible manufacturing systems 806. However, in other illustrative examples, any one of plurality of holding cells 804 may be used for storing any one of plurality of flexible manufacturing systems 806.

As depicted, flexible manufacturing system 808 may be an example of one of plurality of flexible manufacturing systems 806. Flexible manufacturing system 808 may include plurality of mobile systems 811, which may be an example of one implementation for plurality of mobile systems 134 in FIGS. 1 and 3 .

Flexible manufacturing system 808 may be stored in holding cell 810 of plurality of holding cells 804. In this example, all of holding environment 801 may be considered an example of one implementation for holding area 318 in FIG. 3 . However, in other examples, each of plurality of holding cells 804 in holding environment 801 may be considered an example of one implementation for holding area 318 in FIG. 3 .

Floor 803 of manufacturing environment 800 may be substantially smooth to allow the various components and systems of plurality of flexible manufacturing systems 806 to be autonomously driven across floor 803 of manufacturing environment 800 with ease. When one of plurality of flexible manufacturing systems 806 is ready for use, that flexible manufacturing system may be driven across floor 803 from holding environment 801 into assembly environment 802.

Assembly environment 802 may be the designated area on and above floor 803 for building fuselage assemblies. When none of plurality of flexible manufacturing systems 806 are in use, floor 803 of assembly environment 802 may be kept substantially open and substantially clear.

As depicted, assembly environment 802 may include plurality of work cells 812. In one illustrative example, each of plurality of work cells 812 may be an example of one implementation for assembly area 304 in FIG. 3 . Thus, each of plurality of work cells 812 may be designated for performing a fuselage assembly process, such as assembly process 110 in FIG. 1 , for building fuselage assembly 114 in FIG. 1 . In other illustrative examples, the entire assembly environment 802 may be considered an example of one implementation for assembly area 304 in FIG. 3 .

In this illustrative example, first portion 814 of plurality of work cells 812 may be designated for building forward fuselage assemblies, such as forward fuselage assembly 117 in FIG. 1 , while second portion 816 of plurality of work cells 812 may be designated for building aft fuselage assemblies, such as aft fuselage assembly 116 in FIG. 1 . In this manner, plurality of work cells 812 may allow multiple fuselage assemblies to be built concurrently. Depending on the implementation, the building of these fuselage assemblies may begin at the same time or at different times in plurality of work cells 812.

In one illustrative example, plurality of mobile systems 811 that belong to flexible manufacturing system 808 may be driven across floor 803 from holding cell 810 into work cell 813. Within work cell 813, plurality of mobile systems 811 may be used to build a fuselage assembly (not shown). An example of one manner in which this fuselage assembly may be built using flexible manufacturing system 808 is described in greater detail in FIGS. 9-19 below.

In some illustrative examples, a sensor system may be associated with one or more of plurality of work cells 812. For example, without limitation, in some cases, sensor system 818 may be associated with work cell 819 of plurality of work cells 812. Sensor data generated by sensor system 818 may be used to help drive the various mobile systems of the corresponding one of plurality of flexible manufacturing systems 806 designated for building a fuselage assembly within work cell 819. In one illustrative example, sensor system 818 may take the form of metrology system 820.

Depending on the implementation, sensor system 818 may be optional. For example, without limitation, other sensor systems are not depicted associated with other work cells of plurality of work cells 812. Not using sensors systems such as sensor system 818 may help keep floor 803 of manufacturing environment 800 more open and clear to help the various mobile systems of plurality of flexible manufacturing systems 806 be driven more freely across floor 803.

As depicted, plurality of utility fixtures 824 may be permanently affixed to floor 803. Each of plurality of utility fixtures 824 may be an example of one implementation for utility fixture 150 in FIG. 1 .

Plurality of utility fixtures 824 may be interfaced with a number of utility sources (not shown in this view). These utility sources (not shown) may be, for example, without limitation, located beneath floor 803. Utility fixture 826 may be an example of one of plurality of utility fixtures 824.

In this illustrative example, each of plurality of utility fixtures 824 is located in a corresponding one of plurality of work cells 812. Any one of plurality of flexible manufacturing systems 806 may be driven towards and interfaced with any one of plurality of utility fixtures 824. In this manner, plurality of utility fixtures 824 may be used to provide one or more utilities to plurality of flexible manufacturing systems 806.

Referring now to FIGS. 9-19 , illustrations of the building of a fuselage assembly within manufacturing environment 800 from FIG. 8 are depicted in accordance with an illustrative embodiment. In FIGS. 9-19 , flexible manufacturing system 808 from FIG. 8 may be used to build a fuselage assembly. The building of the fuselage assembly may be performed within any one of plurality of work cells 812 in FIG. 8 . For example, without limitation, the building of the fuselage assembly may be performed within one of the work cells in second portion 816 of plurality of work cells 812 in FIG. 8 .

Turning now to FIG. 9 , an illustration of an isometric view of a first tower coupled to utility fixture 826 from FIG. 8 is depicted in accordance with an illustrative embodiment. In this illustrative example, first tower 900 may be coupled to utility fixture 826. First tower 900 may be an example of one of plurality of mobile systems 811 of flexible manufacturing system 808 in FIG. 8 . In particular, first tower 900 may be an example of one implementation for first tower 334 in FIG. 3 .

First tower 900 may be at least one of electrically and physically coupled to utility fixture 826 such that interface 902 is formed between first tower 900 and utility fixture 826. Interface 902 may be an example of one implementation for interface 342 in FIG. 3 .

As depicted, first tower 900 may have base structure 904. Base structure 904 may include top platform 906 and bottom platform 907. In some cases, top platform 906 and bottom platform 907 may be referred to as top platform level and a bottom platform level, respectively. Top platform 906 may be used to provide a human operator with access to a top floor of a fuselage assembly (not shown), such as a passenger floor inside the fuselage assembly. Bottom platform 907 may be used to provide a human operator with access to a bottom floor of the fuselage assembly (not shown), such as a cargo floor inside the fuselage assembly.

In this illustrative example, walkway 908 may provide access from a floor, such as floor 803 in FIG. 8 , to bottom platform 907. Walkway 910 may provide access from bottom platform 907 to top platform 906. Railing 912 is associated with top platform 906 for the protection of a human operator moving around on top platform 906. Railing 914 is associated with bottom platform 907 for the protection of a human operator moving around on bottom platform 907.

First tower 900 may be autonomously driven across floor 803 using autonomous vehicle 916. Autonomous vehicle 916 may be an automated guided vehicle (AGV) in this example. Autonomous vehicle 916 may be an example of one of plurality of autonomous vehicles 306 in FIG. 3 . As depicted, autonomous vehicle 916 may be used to drive first tower 900 from holding environment 801 in FIG. 8 to selected tower position 918 relative to utility fixture 826. Selected tower position 918 may be an example of one implementation for selected tower position 338 in FIG. 3 .

Once first tower 900 has been autonomously driven into selected tower position 918, first tower 900 may autonomously couple to utility fixture 826. In particular, first tower 900 may electrically and physically couple to utility fixture 826 autonomously to form interface 902. This type of coupling may enable a number of utilities to flow from utility fixture 826 to first tower 900. In this manner, first tower 900 and utility fixture 826 may establish at least a portion of a distributed utility network, similar to distributed utility network 144 described in FIGS. 1 and 5 .

With reference now to FIG. 10 , an illustration of an isometric view of a cradle system is depicted in accordance with an illustrative embodiment. In this illustrative example, cradle system 1000 may be an example of one implementation for cradle system 308 in FIG. 3 . Further, cradle system 1000 may be an example of one of plurality of mobile systems 811 of flexible manufacturing system 808 in FIG. 8 . In this manner, cradle system 1000 may be an example of one of plurality of mobile systems 811 that are stored in holding cell 810 in FIG. 8 .

As depicted, cradle system 1000 may be comprised of number of fixtures 1003. Number of fixtures 1003 may be an example of one implementation for number of fixtures 313 in FIG. 3 . Number of fixtures 1003 may include number of cradle fixtures 1002 and fixture 1004. Number of cradle fixtures 1002 may be an example of one implementation for number of cradle fixtures 314 in FIG. 3 .

Number of cradle fixtures 1002 may include cradle fixture 1006, cradle fixture 1008, and cradle fixture 1010. Fixture 1004 may be fixedly associated with cradle fixture 1006. In this illustrative example, fixture 1004 may be considered part of cradle fixture 1006. However, in other illustrative examples, fixture 1004 may be considered a separate fixture from cradle fixture 1006.

As depicted, cradle fixture 1006, cradle fixture 1008, and cradle fixture 1010 have base 1012, base 1014, and base 1016, respectively. Number of retaining structures 1018 may be associated with base 1012. Number of retaining structures 1020 may be associated with base 1014. Number of retaining structures 1022 may be associated with base 1016. Each of number of retaining structures 1018, number of retaining structures 1020, and number of retaining structures 1022 may be an example of an implementation for number of retaining structures 326 in FIG. 3 .

Each retaining structure in number of retaining structures 1018, number of retaining structures 1020, and number of retaining structures 1022 may have a curved shape that substantially matches a curvature of a corresponding fuselage section to be received by the retaining structure. Retaining structure 1023 may be an example of one of number of retaining structures 1020. As depicted, retaining structure 1023 may have curved shape 1025.

Curved shape 1025 may be selected such that curved shape 1025 substantially matches a curvature of a corresponding keel panel (not shown) that is to be engaged with retaining structure 1023. More specifically, retaining structure 1023 may have a substantially same radius of curvature as a corresponding keel panel (not shown) that is to be engaged with retaining structure 1023.

In this illustrative example, plurality of stabilizing members 1024, plurality of stabilizing members 1026, and plurality of stabilizing members 1028 may be associated with base 1012, base 1014, and base 1016, respectively. Plurality of stabilizing members 1024, plurality of stabilizing members 1026, and plurality of stabilizing members 1028 may be used to stabilize base 1012, base 1014, and base 1016, respectively, relative to floor 803 of manufacturing environment 800.

In one illustrative example, these stabilizing members may keep their respective bases substantially level relative to floor 803. Further, each of plurality of stabilizing members 1024, plurality of stabilizing members 1026, and plurality of stabilizing members 1028 may substantially support their respective base until that base is to be moved to a new location within or outside of manufacturing environment 800. In one illustrative example, each stabilizing member of plurality of stabilizing members 1024, plurality of stabilizing members 1026, and plurality of stabilizing members 1028 may be implemented using a hydraulic leg.

Each of number of fixtures 1003 may be used to support and hold a corresponding fuselage section (not shown) for a fuselage assembly (not shown) for an aircraft (not shown), such as one of plurality of fuselage sections 205 for fuselage assembly 114 for aircraft 104 in FIG. 2 . For example, without limitation, fixture 1004 may have platform 1030 associated with base 1032. Platform 1030 may be configured to support and hold a forward fuselage section (not shown) or an aft fuselage section (not shown) for the aircraft (not shown), depending on the implementation. The forward fuselage section (not shown) may be the portion of the fuselage assembly (not shown) that is to be closest to the nose of the aircraft (not shown). The aft fuselage section (not shown) may be the portion of the fuselage assembly (not shown) that is to be closest to the tail of the aircraft (not shown).

With reference now to FIG. 11 , an illustration of an isometric view of an assembly fixture formed using cradle system 1000 from FIG. 10 and coupled to first tower 900 from FIG. 9 is depicted in accordance with an illustrative embodiment. In this illustrative example, cradle fixture 1010 is coupled to first tower 900 and cradle fixture 1010, cradle fixture 1006, and cradle fixture 1008 are coupled to each other.

Cradle fixture 1010, cradle fixture 1008, and cradle fixture 1006 may have been autonomously driven across floor 803 of manufacturing environment 800 to selected cradle position 1100, selected cradle position 1102, and selected cradle position 1104, respectively, using a number of corresponding autonomous vehicles (not shown), such as number of corresponding autonomous vehicles 316 from FIG. 3 . Driving cradle fixture 1006 may also cause fixture 1004 to be driven when fixture 1004 is part of cradle fixture 1006 as shown. Selected cradle position 1100, selected cradle position 1102, and selected cradle position 1104 may be an example of one implementation for number of selected cradle positions 320 in FIG. 3 .

After driving cradle fixture 1010, cradle fixture 1008, and cradle fixture 1006 to selected cradle position 1100, selected cradle position 1102, and selected cradle position 1104, respectively, the number of corresponding autonomous vehicles (not shown) may be autonomously driven away. In other illustrative examples, the number of corresponding autonomous vehicles (not shown) may be integrated as part of cradle fixture 1010, cradle fixture 1008, and cradle fixture 1006.

Selected cradle position 1100 may be a position relative to selected tower position 918 of first tower 900. When cradle fixture 1010 is in selected cradle position 1100 relative to first tower 900, cradle fixture 1010 may be electrically and physically coupled to first tower 900 to form interface 1106. In some cases, cradle fixture 1010 may be coupled to first tower 900 autonomously to form interface 1106. In one illustrative example, interface 1106 may be formed by autonomously coupling cradle fixture 1010 to first tower 900. Interface 1106 may be an electrical and physical interface that enables a number of utilities that are flowing from utility fixture 826 to first tower 900 to also flow to cradle fixture 1010. In this manner, interface 1106 may be formed by autonomously coupling a number of utilities between cradle fixture 1010 and first tower 900. Interface 1106 may be an example of one implementation for interface 340 in FIG. 3 . In this illustrative example, cradle fixture 1010, being coupled to first tower 900, may be referred to as primary cradle fixture 1111.

Further, as depicted, cradle fixture 1006, cradle fixture 1008, and cradle fixture 1010 may be coupled to each other. In particular, cradle fixture 1008 may be coupled to cradle fixture 1010 to form interface 1108. Similarly, cradle fixture 1006 may be coupled to cradle fixture 1008 to form interface 1110. In one illustrative example, both interface 1108 and interface 1110 may be formed by autonomously coupling these cradle fixtures to each other.

In particular, interface 1108 and interface 1110 may take the form of electrical and physical interfaces that enable the number of utilities to flow from cradle fixture 1010, to cradle fixture 1008, and to cradle fixture 1006. In this manner, interface 1108 may be formed by autonomously coupling the number of utilities between cradle fixture 1010 and cradle fixture 1008 and interface 1110 may be formed by autonomously coupling the number of utilities between cradle fixture 1008 and cradle fixture 1006. In this manner, number of utilities 146 may be autonomously coupled between adjacent cradle fixtures in number of cradle fixtures 314.

Thus, when utility fixture 826, first tower 900, cradle fixture 1010, cradle fixture 1008, and cradle fixture 1006 are all coupled in series as described above, the number of utilities may be distributed downstream from utility fixture 826 to first tower 900, cradle fixture 1010, cradle fixture 1008, and cradle fixture 1006. In this illustrative example, any utilities that flow to cradle fixture 1006 may also be distributed to fixture 1004.

Any number of coupling units, structural members, connection devices, cables, other types of elements, or combination thereof may be used to form interface 1108 and interface 1110. Depending on the implementation, interface 1108 and interface 1110 may take the form of coupling units that both physically and electrically connect cradle fixture 1010, cradle fixture 1008, and cradle fixture 1006 to each other. In other illustrative examples, interface 1108 and interface 1110 may be implemented in some other manner.

When cradle fixture 1010, cradle fixture 1008, and cradle fixture 1006 are in selected cradle position 1100, selected cradle position 1102, and selected cradle position 1104, respectively, and coupled to each other, these cradle fixtures together form assembly fixture 1112. Assembly fixture 1112 may be an example of one implementation for assembly fixture 324 in FIG. 3 . In this manner, interface 1106 between first tower 900 and cradle fixture 1010 may also be considered an electrical and physical interface between first tower 900 and assembly fixture 1112.

With reference now to FIG. 12 , an illustration of an isometric view of one stage in the assembly process for building a fuselage assembly that is being supported by assembly fixture 1112 from FIG. 11 is depicted in accordance with an illustrative embodiment. In this illustrative example, assembly fixture 1112 may support fuselage assembly 1200 as fuselage assembly 1200 is built on assembly fixture 1112.

Fuselage assembly 1200 may be an aft fuselage assembly that is an example of one implementation for aft fuselage assembly 116 in FIG. 1 . Fuselage assembly 1200 may be partially assembled in this illustrative example. Fuselage assembly 1200 may be at an early stage of assembly in this example.

At this stage of the assembly process, fuselage assembly 1200 includes end panel 1201 and plurality of keel panels 1202. End panel 1201 may have a tapered cylindrical shape in this illustrative example. In this manner, one portion of end panel 1201 may form part of the keel 1205 for fuselage assembly 1200, another portion of end panel 1201 may form part of the sides (not fully shown) for fuselage assembly 1200, and yet another portion of end panel 1201 may form part of a crown (not fully shown) for fuselage assembly 1200.

Further, as depicted, bulkhead 1203 may be associated with end panel 1201. Bulkhead 1203 may be a pressure bulkhead. Bulkhead 1203 may be an example of one implementation for bulkhead 272 in FIG. 2 .

Plurality of keel panels 1202 include keel panel 1204, keel panel 1206, and keel panel 1208. End panel 1201 and plurality of keel panels 1202 have been engaged with assembly fixture 1112. In particular, end panel 1201 has been engaged with fixture 1004. Keel panel 1204, keel panel 1206, and keel panel 1208 have been engaged with cradle fixture 1006, cradle fixture 1008, and cradle fixture 1010, respectively.

In one illustrative example, end panel 1201 is first engaged with fixture 1004 with keel panel 1204, keel panel 1206, and keel panel 1208 then being successively engaged with cradle fixture 1006, cradle fixture, 1008, and cradle fixture 1010, respectively. In this manner, keel 1205 of fuselage assembly 1200 may be assembled in a direction from the aft end of fuselage assembly 1200 to the forward end of fuselage assembly 1200.

Each of cradle fixture 1006, cradle fixture 1008, and cradle fixture 1010 may be at least one of autonomously or manually adjusted, as needed, to accommodate plurality of keel panels 1202 such that fuselage assembly 1200 may be built to meet outer mold line requirements and inner mold line requirements within selected tolerances. In some cases, at least one of cradle fixture 1006, cradle fixture 1008, and cradle fixture 1010 may have at least one retaining structure that can be adjusted to adapt to the shifting of fuselage assembly 1200 during the assembly process due to increased loading as fuselage assembly 1200 is built.

As depicted, members 1211 may be associated with end panel 1201 and plurality of keel panels 1202. Members 1211 may include frames and stringers in this illustrative example. However, depending on the implementation, members 1211 may also include, without limitation, stiffeners, stanchions, intercostal structural members, connecting members, other types of structural members, or some combination thereof. The connecting members may include, for example, without limitation, shear clips, ties, splices, intercostal connecting members, other types of mechanical connecting members, or some combination thereof.

The portion of members 1211 attached to end panel 1201 may form support section 1210. The portions of members 1211 attached to keel panel 1204, keel panel 1206, and keel panel 1208 may form support section 1212, support section 1214, and support section 1216, respectively.

In this illustrative example, end panel 1201 may form fuselage section 1218 for fuselage assembly 1200. Each of keel panel 1204, keel panel 1206, and keel panel 1208 may form a portion of fuselage section 1220, fuselage section 1222, and fuselage section 1224, respectively, for fuselage assembly 1200. Fuselage section 1218, fuselage section 1220, fuselage section 1222, and fuselage section 1224 may together form plurality of fuselage sections 1225 for fuselage assembly 1200. Each of fuselage section 1218, fuselage section 1220, fuselage section 1222, and fuselage section 1224 may be an example of one implementation for fuselage section 207 in FIG. 2 .

End panel 1201 and plurality of keel panels 1202 may be temporarily connected together using temporary fasteners such as, for example, without limitation, tack fasteners. In particular, end panel 1201 and plurality of keel panels 1202 may be temporarily connected to each other as each of the panels is engaged with assembly fixture 1112 and other panels.

For example, without limitation, coordination holes (not shown) may be present at the edges of end panel 1201 and each of plurality of keel panels 1202. In some cases, a coordination hole may pass through a panel and at least one of members 1211 associated with the panel. Engaging one panel with another panel may include aligning these coordination holes such that temporary fasteners, such as tack fasteners, may be installed in these coordination holes. In some cases, engaging one panel with another panel may include aligning a coordination hole through one panel with a coordination hole through one of members 1211 associated with another panel.

In yet another illustrative example, engaging a first panel with another panel may include aligning the edges of the two panels to form a butt splice. These two panels may then be temporarily connected together by aligning a first number of coordination holes in, for example, a splice plate, with a corresponding number of holes on the first panel and aligning a second number of coordination holes in that splice plate with a corresponding number of holes on the second panel. Temporary fasteners may then be inserted through these aligned coordination holes to temporarily connect the first panel to the second panel.

In this manner, panels and members may be engaged with each other and temporarily connected together in a number of different ways. Once end panel 1201 and plurality of keel panels 1202 have been temporarily connected together, assembly fixture 1112 may help maintain the position and orientation of end panel 1201 and each of plurality of keel panels 1202 relative to each other.

Turning now to FIG. 13 , an illustration of an isometric view of another stage in the assembly process for building a fuselage assembly is depicted in accordance with an illustrative embodiment. In this illustrative example, cargo floor 1300 has been added to fuselage assembly 1200. In particular, cargo floor 1300 may be associated with plurality of keel panels 1202.

As depicted, at least a portion of cargo floor 1300 may be substantially level with bottom platform 907 of first tower 900. In particular, at least the portion of cargo floor 1300 nearest first tower 900 may be substantially aligned with bottom platform 907 of first tower 900. In this manner, a human operator (not shown) may use bottom platform 907 of first tower 900 to easily walk onto cargo floor 1300 and access interior 1301 of fuselage assembly 1200.

As depicted, first side panels 1302 and second side panels 1304 have been added to fuselage assembly 1200. First side panels 1302 and second side panels 1304 may be an example of one implementation for first side panels 224 and second side panels 226, respectively, in FIG. 2 . First side panels 1302, second side panels 1304, and a first and second portion of end panel 1201 may form sides 1305 of fuselage assembly 1200. In this illustrative example, plurality of keel panels 1202, end panel 1201, first side panels 1302, and second side panels 1304 may all be temporarily connected together using, for example, without limitation, tack fasteners.

First side panels 1302 may include side panel 1306, side panel 1308, and side panel 1310 that have been engaged with and temporarily connected to keel panel 1204, keel panel 1206, and keel panel 1208, respectively. Similarly, second side panels 1304 may include side panel 1312, side panel 1314, and side panel 1316 that have been engaged with and temporarily connected to keel panel 1204, keel panel 1206, and keel panel 1208, respectively. Further, both side panel 1306 and side panel 1312 have been engaged with end panel 1201.

As depicted, members 1318 may be associated with first side panels 1302. Other members (not shown) may be similarly associated with second side panels 1304. Members 1318 may be implemented in a manner similar to members 1211. In this illustrative example, corresponding portion 1320 of members 1318 may be associated with side panel 1306. Corresponding portion 1320 of members 1318 may form support section 1322 associated with side panel 1306. Support section 1322 be an example of one implementation for support section 238 in FIG. 2 .

With reference now to FIG. 14 , an illustration of an isometric view of another stage in the assembly process for building a fuselage assembly is depicted in accordance with an illustrative embodiment. In this illustrative example, passenger floor 1400 has been added to fuselage assembly 1200. As depicted, passenger floor 1400 may be substantially level with top platform 906 of first tower 900. Human operator 1402 may use top platform 906 of first tower 900 to walk onto passenger floor 1400 and access interior 1301 of fuselage assembly 1200.

With reference now to FIG. 15 , an illustration of an isometric view of another stage in the assembly process for building a fuselage assembly is depicted in accordance with an illustrative embodiment. In this illustrative example, plurality of crown panels 1500 have been added to fuselage assembly 1200. Plurality of crown panels 1500 may be an example of one implementation for crown panels 218 in FIG. 2 .

In this illustrative example, plurality of crown panels 1500 may include crown panel 1502, crown panel 1504, and crown panel 1506. These crown panels along with a top portion of end panel 1201 may form crown 1507 of fuselage assembly 1200. Crown panel 1502 may be engaged with and temporarily connected to end panel 1201, side panel 1306 shown in FIG. 13 , side panel 1312, and crown panel 1504. Crown panel 1504 may be engaged with and temporarily connected to crown panel 1502, crown panel 1506, side panel 1308 shown in FIG. 13 , and side panel 1314. Further, crown panel 1506 may be engaged with and temporarily connected to crown panel 1504, side panel 1310, and side panel 1316.

Together, end panel 1201, plurality of keel panels 1202, first side panels 1302, second side panels 1304, and plurality of crown panels 1500 may form plurality of panels 1508 for fuselage assembly 1200. Plurality of panels 1508 may be an example of one implementation for plurality of panels 120 in FIG. 1 .

Plurality of panels 1508 may all be temporarily connected to each other such that desired compliance with outer mold line requirements and inner mold line requirements may be maintained during the building of fuselage assembly 1200. In other words, temporarily connecting plurality of panels 1508 to each other may enable outer mold line requirements and inner mold line requirements to be met within selected tolerances during the building of fuselage assembly 1200 and, in particular, the joining of plurality of panels 1508 together.

Members (not shown) may be associated with plurality of crown panels 1500 in a manner similar to the manner in which members 1318 are associated with first side panels 1302. These members associated with plurality of crown panels 1500 may be implemented in a manner similar to members 1318 and members 1211 as shown in FIGS. 13-14 . The various members associated with end panel 1201, plurality of keel panels 1202, plurality of crown panels 1500, first side panels 1302, and second side panels 1304 may form plurality of members 1510 for fuselage assembly 1200. When plurality of panels 1508 are joined together, plurality of members 1510 may form a support structure (not yet shown) for fuselage assembly 1200, similar to support structure 131 in FIG. 1 .

After plurality of crown panels 1500 have been added to fuselage assembly 1200, first tower 900 may be autonomously decoupled from assembly fixture 1112 and utility fixture 826. First tower 900 may then be autonomously driven away from utility fixture 826 using, for example, without limitation, autonomous vehicle 916 in FIG. 9 . In one illustrative example, first tower 900 may be autonomously driven back to holding environment 801 in FIG. 8 .

When first tower 900 is decoupled from assembly fixture 1112 and utility fixture 826, a gap is formed in the distributed utility network. This gap may be filled using a second tower (not shown), implemented in a manner similar to second tower 336 in FIG. 3 .

With reference now to FIG. 16 , an illustration of an isometric view of a second tower coupled to utility fixture 826 and assembly fixture 1112 supporting fuselage assembly 1200 from FIG. 15 is depicted in accordance with an illustrative embodiment. In this illustrative example, second tower 1600 has been positioned relative to assembly fixture 1112 and utility fixture 826. Second tower 1600 may be an example of one implementation for second tower 336 in FIG. 3 .

Second tower 1600 may be autonomously driven across floor 803 using an autonomous vehicle (not shown), similar to autonomous vehicle 916 in FIG. 9 . Second tower 1600 may be autonomously driven into selected tower position 1618 relative to utility fixture 826. Selected tower position 1618 may be an example of one implementation for selected tower position 338 in FIG. 3 . In this illustrative example, selected tower position 1618 may be substantially the same as selected tower position 918 in FIG. 9 .

Once second tower 1600 has been autonomously driven into selected tower position 1618, second tower 1600 may autonomously couple to utility fixture 826. In particular, second tower 1600 may electrically and physically couple to utility fixture 826 autonomously to form interface 1602. Interface 1602 may be another example of one implementation for interface 342 in FIG. 3 . This type of coupling may enable a number of utilities to flow from utility fixture 826 to second tower 1600.

Further, second tower 1600 may autonomously couple to cradle fixture 1010, thereby autonomously coupling to assembly fixture 1112, to form interface 1605. Interface 1605 may enable the number of utilities to flow downstream from second tower 1600. In this manner, the number of utilities may flow from second tower 1600 to cradle fixture 1010, to cradle fixture 1008, and then to cradle fixture 1006. In this manner, second tower 1600 may fill the gap in the distributed utility network that was created when first tower 900 in FIG. 15 was decoupled from assembly fixture 1112 and utility fixture 826 and driven away.

Similar to first tower 900 in FIG. 9 , second tower 1600 may include base structure 1604, top platform 1606, and bottom platform 1607. However, top platform 1606 and bottom platform 1607 may be used to provide internal mobile platforms with access to interior 1301 of fuselage assembly 1200 instead of human operators.

In this illustrative example, internal mobile platform 1608 may be positioned on top platform 1606. Top platform 1606 may be substantially aligned with passenger floor 1400 such that internal mobile platform 1608 may be able to autonomously drive across top platform 1606 onto passenger floor 1400.

Similarly, an internal mobile platform (not shown in this view) may be positioned on bottom platform 1607. Bottom platform 1607 may be substantially aligned with cargo floor 1300 (not shown in this view) from FIG. 13 such that this other internal mobile platform (not shown in this view) may be able to autonomously drive across bottom platform 1607 onto the cargo floor. Internal mobile platform 1608 and the other internal mobile platform (not shown in this view) may be examples of implementations for internal mobile platform 406 in FIG. 4 .

As depicted, internal robotic device 1610 and internal robotic device 1612 may be associated with internal mobile platform 1608. Although internal robotic device 1610 and internal robotic device 1612 are shown associated with the same internal mobile platform 1608, in other illustrative examples, internal robotic device 1610 may be associated with one internal mobile platform and internal robotic device 1612 may be associated with another internal mobile platform. Each of internal robotic device 1610 and internal robotic device 1612 may be an example of one implementation for internal robotic device 416 in FIG. 4 .

Internal robotic device 1610 and internal robotic device 1612 may be used to perform operations within interior 1301 of fuselage assembly 1200 for joining plurality of panels 1508. For example, without limitation, internal robotic device 1610 and internal robotic device 1612 may be used to perform fastening operations, such as riveting operations, within interior 1301 of fuselage assembly 1200.

In one illustrative example, utility box 1620 may be associated with base structure 1604. Utility box 1620 may manage the number of utilities received from utility fixture 826 through interface 1602 and may distribute these utilities into utility cables that are managed using cable management system 1614 and cable management system 1616.

As depicted in this example, cable management system 1614 may be associated with top platform 1606 and cable management system 1616 may be associated with bottom platform 1607. Cable management system 1614 and cable management system 1616 may be implemented similarly.

Cable management system 1614 may include cable wheels 1615 and cable management system 1616 may include cable wheels 1617. Cable wheels 1615 may be used to spool utility cables that are connected to internal mobile platform 1608. For example, without limitation, cable wheels 1615 may be biased in some manner to substantially maintain a selected amount of tension in the utility cables. This biasing may be achieved using, for example, one or more spring mechanisms.

As internal mobile platform 1608 moves away from second tower 1600 along passenger floor 1400, the utility cables may extend from cable wheels 1615 to maintain utility support to internal mobile platform 1608 and manage the utility cables such that they do not become tangled. Cable wheels 1617 may be implemented in a manner similar to cable wheels 1615.

By using cable wheels 1615 to spool the utility cables, the utility cables may be kept off of internal mobile platform 1608, thereby reducing the weight of internal mobile platform 1608 and the load applied by internal mobile platform 1608 to passenger floor 1400. The number of utilities provided to internal mobile platform 1608 may include, for example, without limitation, electricity, air, water, hydraulic fluid, communications, some other type of utility, or some combination thereof.

With reference now to FIG. 17 , an illustration of an isometric cutaway view of a plurality of mobile platforms performing fastening processes within interior 1301 of fuselage assembly 1200 is depicted in accordance with an illustrative embodiment. In this illustrative example, plurality of mobile platforms 1700 may be used to perform fastening processes to join plurality of panels 1508 together.

In particular, plurality of panels 1508 may be joined together at selected locations along fuselage assembly 1200. Plurality of panels 1508 may be joined to form at least one of lap joints, butt joints, or other types of joints. In this manner, plurality of panels 1508 may be joined such that at least one of circumferential attachment, longitudinal attachment, or some other type of attachment is created between the various panels of plurality of panels 1508.

As depicted, plurality of mobile platforms 1700 may include internal mobile platform 1608 and internal mobile platform 1701. Internal mobile platform 1608 and internal mobile platform 1701 may be an example of one implementation for number of internal mobile platforms 402 in FIG. 4 . Internal mobile platform 1608 may be configured to move along passenger floor 1400, while internal mobile platform 1701 may be configured to move along cargo floor 1300.

As depicted, internal robotic device 1702 and internal robotic device 1704 may be associated with internal mobile platform 1701. Each of internal robotic device 1702 and internal robotic device 1704 may be an example of one implementation for internal robotic device 416 in FIG. 4 . Internal robotic device 1702 and internal robotic device 1704 may be similar to internal robotic device 1610 and internal robotic device 1612.

Plurality of mobile platforms 1700 may also include external mobile platform 1705 and external mobile platform 1707. External mobile platform 1705 and external mobile platform 1707 may be an example of one implementation for at least a portion of number of external mobile platforms 400 in FIG. 4 . External mobile platform 1705 and external mobile platform 1707 may be examples of implementations for external mobile platform 404 in FIG. 4 .

External robotic device 1706 may be associated with external mobile platform 1705. External robotic device 1708 may be associated with external mobile platform 1707. Each of external robotic device 1706 and external robotic device 1708 may be an example of one implementation for external robotic device 408 in FIG. 4 .

As depicted, external robotic device 1706 and internal robotic device 1612 may work collaboratively to install fasteners autonomously in fuselage assembly 1200. These fasteners may take the form of, for example, without limitation, at least one of rivets, interference-fit bolts, non-interference-fit bolts, or other types of fasteners or fastener systems. Similarly, external robotic device 1708 and internal robotic device 1704 may work collaboratively to install fasteners autonomously in fuselage assembly 1200. As one illustrative example, end effector 1710 of internal robotic device 1612 and end effector 1712 of external robotic device 1706 may be positioned relative to a same location 1720 on fuselage assembly 1200 to perform a fastening process at location 1720, such as fastening process 424 in FIG. 4 .

The fastening process may include at least one of, for example, without limitation, a drilling operation, a fastener insertion operation, a fastener installation operation, an inspection operation, or some other type of operation. The fastener installation operation may take the form of, for example, without limitation, two-stage riveting process 444 described in FIG. 4 , interference-fit bolt-type installation process 439 described in FIG. 4 , bolt-nut type installation process 433 described in FIG. 4 , or some other type of fastener installation operation.

In this illustrative example, autonomous vehicle 1711 may be fixedly associated with external mobile platform 1705. Autonomous vehicle 1711 may be used to drive external mobile platform 1705 autonomously. For example, autonomous vehicle 1711 may be used to autonomously drive external mobile platform 1705 across floor 803 of manufacturing environment 800 relative to assembly fixture 1112.

Similarly, autonomous vehicle 1713 may be fixedly associated with external mobile platform 1707. Autonomous vehicle 1713 may be used to drive external mobile platform 1707 autonomously. For example, autonomous vehicle 1713 may be used to autonomously drive external mobile platform 1707 across floor 803 of manufacturing environment 800 relative to assembly fixture 1112.

By being fixedly associated with external mobile platform 1705 and external mobile platform 1707, autonomous vehicle 1711 and autonomous vehicle 1713 may be considered integral to external mobile platform 1705 and external mobile platform 1707, respectively. However, in other illustrative examples, these autonomous vehicles may be independent of the external mobile platforms in other illustrative examples.

Once all fastening processes have been completed for fuselage assembly 1200, internal mobile platform 1608 and internal mobile platform 1701 may be autonomously driven across passenger floor 1400 back onto top platform 1606 and bottom platform 1607, respectively, of second tower 1600. Second tower 1600 may then be autonomously decoupled from both utility fixture 826 and assembly fixture 1112. Autonomous vehicle 1714 may then be used to autonomously drive or move second tower 1600 away.

In this illustrative example, building of fuselage assembly 1200 may now be considered completed for this stage in the overall assembly process for the fuselage. Consequently, assembly fixture 1112 may be autonomously driven across floor 803 to move fuselage assembly 1200 to some other location. In other illustrative examples, first tower 900 from FIG. 9 may be autonomously driven back into selected tower position 918 in FIG. 9 relative to utility fixture 826. First tower 900 from FIG. 9 may then be autonomously recoupled to utility fixture 826 and assembly fixture 1112. First tower 900 from FIG. 9 may enable a human operator (not shown) to access interior 1301 of fuselage assembly 1200 to perform other operations including, but not limited to, at least one of inspection operations, fastening operations, system installation operations, or other types of operations. System installation operations may include operations for installing systems such as, for example, without limitation, at least one of a fuselage utility system, an air conditioning system, interior panels, electronic circuitry, some other type of system, or some combination thereof.

With reference now to FIG. 18 , an illustration of a cross-sectional view of flexible manufacturing system 808 performing operations on fuselage assembly 1200 from FIG. 17 is depicted in accordance with an illustrative embodiment. In this illustrative example, a cross-sectional view of fuselage assembly 1200 from FIG. 17 is depicted taken in the direction of lines 18-18 in FIG. 17 .

As depicted, internal mobile platform 1608 and internal mobile platform 1701 are performing operations within interior 1301 of fuselage assembly 1200. External mobile platform 1705 and external mobile platform 1707 are performing assembly operations along exterior 1800 of fuselage assembly 1200.

In this illustrative example, external mobile platform 1705 may be used to perform operations along portion 1802 of exterior 1800 between axis 1804 and axis 1806 at first side 1810 of fuselage assembly 1200. External robotic device 1706 of external mobile platform 1705 may work collaboratively with internal robotic device 1610 of internal mobile platform 1608 to perform fastening processes.

Similarly, external mobile platform 1707 may be used to perform operations along portion 1808 of exterior 1800 of fuselage assembly 1200 between axis 1804 and axis 1806 at second side 1812 of fuselage assembly 1200. External robotic device 1708 of external mobile platform 1707 may work collaboratively with internal robotic device 1704 of internal mobile platform 1701 to perform fastening processes.

Although external mobile platform 1705 is depicted as being located at first side 1810 of fuselage assembly 1200, external mobile platform 1705 may be autonomously driven by autonomous vehicle 1711 to second side 1812 of fuselage assembly 1200 to perform operations along portion 1811 of exterior 1800 of fuselage assembly 1200 between axis 1804 and axis 1806. Similarly, external mobile platform 1707 may be autonomously driven by autonomous vehicle 1713 to second side 1812 of fuselage assembly 1200 to perform operations along portion 1813 of exterior 1800 of fuselage assembly 1200 between axis 1804 and axis 1806.

Although not shown in this illustrative example, an external mobile platform similar to external mobile platform 1705 may have an external robotic device configured to work collaboratively with internal robotic device 1612 of internal mobile platform 1608 at second side 1812 of fuselage assembly 1200. Similarly, an external mobile platform similar to external mobile platform 1707 may have an external robotic device configured to work collaboratively with internal robotic device 1702 of internal mobile platform 1701 at first side 1810 of fuselage assembly 1200.

These four different external mobile platforms and two internal mobile platforms may be controlled such that the operations performed by internal mobile platform 1608 located on passenger floor 1400 may occur at a different location with respect to the longitudinal axis of fuselage assembly 1200 than the operations performed by internal mobile platform 1701 located on cargo floor 1300. The four external mobile platforms may be controlled such that the two external mobile platforms located on the same side of fuselage assembly 1200 do not collide or impede one another. The two external mobile platforms located at the same side of fuselage assembly 1200 may be unable to occupy the same footprint in this illustrative example.

In this illustrative example, external mobile platform 1705 may autonomously couple to assembly fixture 1112 to form interface 1822 such that a number of utilities may flow from assembly fixture 1112 to external mobile platform 1705. In other words, the number of utilities may be autonomously coupled between external mobile platform 1705 and assembly fixture 1112 through interface 1822. In particular, external mobile platform 1705 has been coupled to cradle fixture 1010 through interface 1822.

Similarly, external mobile platform 1707 may autonomously couple to assembly fixture 1112 to form interface 1824 such that a number of utilities may flow from assembly fixture 1112 to external mobile platform 1707. In other words, the number of utilities may be autonomously coupled between external mobile platform 1707 and assembly fixture 1112 through interface 1824. In particular, external mobile platform 1707 has been coupled to cradle fixture 1010 through interface 1824.

As operations are performed along fuselage assembly 1200 by external mobile platform 1705, external mobile platform 1707, and any other external mobile platforms, these external mobile platforms may be coupled to and decoupled from assembly fixture 1112 as needed. For example, external mobile platform 1707 may decouple from cradle fixture 1010 as external mobile platform 1707 moves aftward along fuselage assembly 1200 such that external mobile platform 1707 may then autonomously couple to cradle fixture 1008 (not shown) from FIGS. 10-17 . Further, these external mobile platforms may be coupled to and decoupled from assembly fixture 1112 to avoid collisions and prevent the external mobile platforms from impeding each other during maneuvering of the external mobile platforms relative to assembly fixture 1112 and fuselage assembly 1200.

As depicted, autonomous vehicle 1814 is shown positioned under the assembly fixture 1112 formed by cradle system 1000. In this illustrative example, autonomous vehicle 1814, autonomous vehicle 1711, and autonomous vehicle 1713 may have omnidirectional wheels 1816, omnidirectional wheels 1818, and omnidirectional wheels 1820, respectively. In some illustrative examples, metrology system 1826 may be used to help position external mobile platform 1705 and external mobile platform 1707 relative to fuselage assembly 1200.

Turning now to FIG. 19 , an illustration of an isometric view of a fully built fuselage assembly is depicted in accordance with an illustrative embodiment. In this illustrative example, fuselage assembly 1200 may be considered completed when plurality of panels 1508 have been fully joined.

In other words, all fasteners needed to join together plurality of panels 1508 have been fully installed. With plurality of panels 1508 joined together, support structure 1900 may be fully formed. Support structure 1900 may be an example of one implementation for support structure 121 in FIG. 1 . Fuselage assembly 1200, which is an aft fuselage assembly, may now be ready for attachment to a corresponding middle fuselage assembly (not shown) and forward fuselage assembly (not shown).

As depicted, autonomous vehicles (not shown in this view), similar to autonomous vehicle 1714 shown in FIG. 17 , may be positioned under base 1012 of cradle fixture 1006, base 1014 of cradle fixture 1008, and base 1016 of cradle fixture 1010, respectively. Autonomous vehicles, such as number of corresponding autonomous vehicles 316 in FIG. 3 , may lift up base 1012, base 1014, and base 1016, respectively, such that plurality of stabilizing members 1024, plurality of stabilizing members 1026, and plurality of stabilizing members 1028, respectively, no longer contact the floor.

These autonomous vehicles (not shown) may then autonomously drive cradle system 1000 carrying fuselage assembly 1200 that has been fully built away from assembly environment 802 in FIG. 8 and, in some cases, away from manufacturing environment 800 in FIG. 8 . Computer-controlled movement of these autonomous vehicles (not shown) may ensure that number of cradle fixtures 1002 maintain their positions relative to each other as fuselage assembly 1200 is being moved.

With reference now to FIG. 20 , an illustration of an isometric view of fuselage assemblies being built within manufacturing environment 800 is depicted in accordance with an illustrative embodiment. In this illustrative example, plurality of fuselage assemblies 2000 are being built within plurality of work cells 812 in manufacturing environment 800.

Plurality of fuselage assemblies 2000 may include plurality of forward fuselage assemblies 2001 being built in first portion 814 of plurality of work cells 812 and plurality of aft fuselage assemblies 2002 being built in second portion 816 of plurality of work cells 812. Each of plurality of fuselage assemblies 2000 may be an example of one implementation for fuselage assembly 114 in FIG. 1 .

As depicted, plurality of fuselage assemblies 2000 are being built concurrently. However, plurality of fuselage assemblies 2000 are at different stages of assembly in this illustrative example.

Forward fuselage assembly 2004 may be an example of one of plurality of forward fuselage assemblies 2001. Forward fuselage assembly 2004 may be an example of one implementation for forward fuselage assembly 117 in FIG. 1 . Aft fuselage assembly 2005 may be an example of one of plurality of aft fuselage assemblies 2002. Aft fuselage assembly 2005 may be an example of one implementation for aft fuselage assembly 116 in FIG. 1 . In this illustrative example, aft fuselage assembly 2005 may be at an earlier stage of assembly than forward fuselage assembly 2004.

Aft fuselage assembly 2006, which may be another example of an implementation for aft fuselage assembly 116 in FIG. 1 , may be a fuselage assembly with all panels joined. As depicted, aft fuselage assembly 2006 is being autonomously driven to some other location for a next stage in the overall fuselage and aircraft manufacturing process.

As described above, aft fuselage assembly 2005 may be partially assembled. In this illustrative example, aft fuselage assembly 2005 has keel 2010, end panel 2011, and first side 2012. End panel 2011 may form an end fuselage section of aft fuselage assembly 2005. As depicted, side panel 2014 may be added to aft fuselage assembly 2005 to build a second side of aft fuselage assembly 2005.

Forward fuselage assembly 2015 may be another example of one of plurality of forward fuselage assemblies 2001. In this illustrative example, forward fuselage assembly 2015 has keel 2016 and end panel 2018. End panel 2018 may form an end fuselage section of forward fuselage assembly 2015. As depicted, side panel 2020 may be added to forward fuselage assembly 2015 to begin building a first side of forward fuselage assembly 2015.

With reference now to FIG. 21 , an illustration of an isometric view of a coupling structure and utility fixture 826 from FIGS. 8 and 10-20 is depicted in accordance with an illustrative embodiment. As described above, utility fixture 826 may be an example of one implementation for utility fixture 150 in FIGS. 1, 5, 6, and 7 .

Coupling structure 2100 may be an example of one implementation for coupling structure 615 in FIG. 6 . Coupling structure 2100 may be used to couple a tower, such as first tower 900 in FIG. 9 or second tower 1600 in FIG. 16 to utility fixture 826. For example, without limitation, coupling structure 2100 may be associated with base structure 904 of first tower 900 in FIG. 9 and used to form interface 902 between first tower 900 and utility fixture 826 shown in FIG. 9 . In a similar manner, coupling structure 2100 may be associated with base structure 1604 of second tower 1600 in FIG. 16 and used to form interface 902 between second tower 1600 and utility fixture 826 shown in FIG. 16 .

As depicted in this example, utility fixture 826 may include base structure 2102. Base structure 2102 may be an example of one implementation for base structure 600 in FIG. 6 . Set of coupling units 2103 may be associated with base structure 2102. Set of coupling units 2103 may be an example of one implementation for set of coupling units 608 in FIG. 6 .

In this illustrative example, set of coupling units 2103 may include coupling unit 2104, coupling unit 2105, and coupling unit 2106. Coupling unit 2104 may include male quick-change device 2108 and air coupling element 2110. Coupling unit 2105 may include male quick-change device 2112, power coupling element 2114, communications coupling element 2116, power coupling element 2118, and communications coupling element 2120. Coupling unit 2106 may include male quick-change device 2122, power coupling element 2124, communications coupling element 2126, power coupling element 2128, and communications coupling element 2130.

Male quick-change device 2108, male quick-change device 2112, and male quick-change device 2122 may be examples of implementations for male quick-change device 625 in FIG. 6 . Air coupling element 2110 may be an example of one implementation for air coupling element 620 in FIG. 6 . Power coupling element 2114, power coupling element 2118, power coupling element 2124, and power coupling element 2128 may be examples of implementations for power coupling element 618 in FIG. 6 . Communications coupling element 2116, communications coupling element 2120, communications coupling element 2126, and communications coupling element 2130 may be examples of implementations for communications coupling element 624 in FIG. 6 .

Set of corresponding coupling units 2132 may be associated with coupling structure 2100. Set of corresponding coupling units 2132 may include corresponding coupling unit 2134, corresponding coupling unit 2136, and corresponding coupling unit 2138. As depicted, corresponding coupling unit 2134 may include female quick-change device 2140 and corresponding air coupling element 2142. Corresponding coupling unit 2136 may include female quick-change device 2144, corresponding power coupling element 2146, corresponding communications coupling element 2148, corresponding power coupling element 2150, and corresponding communications coupling element 2152. Corresponding coupling unit 2138 may include female quick-change device 2154, corresponding power coupling element 2156, corresponding communications coupling element 2158, corresponding power coupling element 2160, and corresponding communications coupling element 2162.

Female quick-change device 2140, female quick-change device 2144, and female quick-change device 2154 may be examples of implementations for female quick-change device 628 in FIG. 6 . Corresponding air coupling element 2142 may be an example of one implementation for air coupling element 620 in FIG. 6 . Corresponding power coupling element 2146, corresponding power coupling element 2150, corresponding power coupling element 2156, and corresponding power coupling element 2160 may be examples of implementations for corresponding power coupling element 630 in FIG. 6 . Corresponding communications coupling element 2148, corresponding communications coupling element 2152, corresponding communications coupling element 2158, and corresponding communications coupling element 2162 may be examples of implementations for corresponding communications coupling element 636 in FIG. 6 .

In this illustrative example, coupling unit 2104, coupling unit 2105, and coupling unit 2106 may mate with corresponding coupling unit 2134, corresponding coupling unit 2136, and corresponding coupling unit 2138 to couple utility fixture 826 and coupling structure 2100 together. In this manner, utility fixture 826 may be coupled with whichever tower (not shown) coupling structure 2100 is associated. Consequently, utilities such as power, air, and communications may flow from utility fixture 826 to coupling structure 2100 and the tower (not shown) with which coupling structure 2100 is associated.

As depicted, number of distribution cables 2164 may be used to distribute these utilities to the tower (not shown). When the tower is second tower 1600 in FIG. 16 , at least a portion of the utilities may be distributed to internal mobile platform 1608 and internal mobile platform 1701 shown in FIGS. 16-17 .

With reference now to FIG. 22 , an illustration of an enlarged isometric view of a coupling unit and a corresponding coupling unit is depicted in accordance with an illustrative embodiment. In this illustrative example, coupling unit 2200 may be an example of one implementation for coupling unit 612 in FIG. 6 . Corresponding coupling unit 2202 may be an example of one implementation for corresponding coupling unit 613 in FIG. 6 .

Coupling unit 2200 may be associated with one of, for example, without limitation, a utility fixture, such as utility fixture 826 in FIG. 8 , a tower such as first tower 900 in FIG. 9 or second tower 1600 in FIG. 16 , or a cradle fixture, such as one of number of cradle fixtures 1002 in FIG. 10 . Corresponding coupling unit 2202 may be associated with a mobile system, selected from one of a tower, such as first tower 900 in FIG. 9 or second tower 1600 in FIG. 16 , or a cradle fixture, such as one of number of cradle fixtures 1002 in FIG. 10 . In some illustrative examples, corresponding coupling unit 2202 may be associated with an external mobile platform, such as one of external mobile platform 1705 or external mobile platform 1707 in FIG. 17 .

Further, coupling unit 2200 may be an example of one manner in which one of set of tower coupling units 706, one of set of first cradle coupling units 710, or one of set of second cradle coupling units 714 may be implemented. Similarly, corresponding coupling unit 2202 may be an example of one manner in which one of set of corresponding first cradle coupling units 708, one of set of corresponding second cradle coupling units 712, or one of set of corresponding third cradle coupling units 716 in FIG. 7 may be implemented.

Number of utility cables 2203 may carry a number of utilities to coupling unit 2200. Number of utility cables 2205 may carry a number of utilities away from corresponding coupling unit 2202.

As depicted, coupling unit 2200 may include male quick-change device 2204, power coupling element 2206, air coupling element 2208, communications coupling element 2210, power coupling element 2212, air coupling element 2214, and communications coupling element 2216. Corresponding coupling unit 2202 may include female quick-change device 2218, corresponding power coupling element 2220, corresponding air coupling element 2222, corresponding communications coupling element 2224, corresponding power coupling element 2226, corresponding air coupling element 2228, and corresponding communications coupling element 2230.

Corresponding coupling unit 2202 is shown rotated about 90 degrees counter-clockwise from the orientation corresponding coupling unit 2202 may have when mating with coupling unit 2200. In particular, corresponding coupling unit 2202 is shown rotated in the direction of arrow 2231 about Z-axis 2235. In this manner, the various coupling elements associated with corresponding coupling unit 2202 may be more clearly seen.

In this illustrative example, guidance fork 2232 may be associated with coupling unit 2200. Roller 2234 may be associated with corresponding coupling unit 2202. The mobile system (not shown) with which corresponding coupling unit 2202 is associated may be driven autonomously towards coupling unit 2200. As corresponding coupling unit 2202 is moved towards coupling unit 2200, roller 2234 may engage guidance fork 2232. Guidance fork 2232 may guide roller 2234 during the mating of corresponding coupling unit 2202 to coupling unit 2200 to maintain alignment during coupling.

Imaging system 2236 associated with corresponding coupling unit 2202 may be used to guide the mobile system with which corresponding coupling unit 2202 is associated. For example, without limitation, the imaging data generated by imaging system 2236 may be used to drive the mobile system in a manner that moves corresponding coupling unit 2202 towards coupling unit 2200 and roller 2234 into guidance fork 2232. In this manner, movement along Y-axis 2233 may be guided using roller 2234 and guidance fork 2232. Using roller 2234 and guidance fork 2232 may also help with vertical alignment along Z-axis 2235. Roller 2234 may need to be within a selected distance of guidance fork 2232 with respect to Z-axis 2235 in order for roller 2234 to engage and be guided within guidance fork 2232.

Imaging system 2238 associated with coupling unit 2200 may be used to adjust the positioning of coupling unit 2200 relative to the system with which coupling unit 2200 is attached. For example, without limitation, the imaging data generated by imaging system 2238 may be processed to generate commands for controlling air cylinder 2240, which may move coupling unit 2200 in a direction along X-axis 2242. Further, the imaging data generated by imaging system 2238 may also be used to control movement system 2237. Movement system 2237 may control the movement of coupling unit 2200 in a direction along Z-axis 2235.

In other illustrative examples, some other type of controllable movement system may be associated with coupling unit 2200 and used to move coupling unit 2200 with at least one degree of freedom relative to the system with which coupling unit 2200 is attached. In still other illustrative examples, one or more controllable movement systems (not shown) may be associated with corresponding coupling unit 2202 and used to move corresponding unit 2202 with at least one degree of freedom relative to the system or structure with which corresponding coupling unit 2202 is attached.

The illustrations in FIGS. 8-22 are not meant to imply physical or architectural limitations to the manner in which an illustrative embodiment may be implemented. Other components in addition to or in place of the ones illustrated may be used. Some components may be optional.

The different components shown in FIGS. 8-22 may be illustrative examples of how components shown in block form in FIG. 1-7 can be implemented as physical structures. Additionally, some of the components in FIGS. 8-22 may be combined with components in FIG. 1-7 , used with components in FIG. 1-7 , or a combination of the two.

With reference now to FIG. 23 , an illustration of a process for distributing a number of utilities is depicted in the form of a flowchart in accordance with an illustrative embodiment. The process illustrated in FIG. 23 may be implemented using utility fixture 150 shown in FIGS. 1, 5, 6, and 7 .

The process may begin by coupling number of utilities 146 between number of utility sources 148 and utility fixture 150 (operation 2300). Next, number of utilities 146 may be coupled between utility fixture 150 and mobile system 610 (operation 2302). Number of utilities 146 may be distributed downstream from number of utility sources 148, through utility fixture 150, to mobile system 610 (operation 2304), with the process terminating thereafter.

With reference now to FIG. 24 , an illustration of a process for mating a coupling unit with a corresponding coupling unit is depicted in the form of a flowchart in accordance with an illustrative embodiment. The process illustrated in FIG. 24 may be used to mate a coupling unit, such as coupling unit 612 in FIG. 6 , with a corresponding coupling unit, such as corresponding coupling unit 613 in FIG. 6 .

The process may begin by driving corresponding coupling unit 613 towards coupling unit 612 (operation 2400). Corresponding coupling unit 613 may be aligned with coupling unit 612 autonomously (operation 2402). Operation 2402 may be performed by, for example, without limitation, guiding a roller associated with corresponding coupling unit 613 within a guidance fork associated with coupling unit 612 as corresponding coupling unit 613 is driven towards coupling unit 612.

Next, corresponding coupling unit 613 may be mated to coupling unit 612 to couple a number of utilities between coupling unit 612 and corresponding coupling unit 613 (operation 2404), with the process terminating thereafter. Mating these coupling units in operation 2404 may create an interface over which the number of utilities may flow from coupling unit 612 to corresponding coupling unit 613.

With reference now to FIG. 25 , an illustration of a process for distributing a number of utilities to a tower is depicted in the form of a flowchart in accordance with an illustrative embodiment. The process illustrated in FIG. 25 may be used to couple a tower, such as tower 332 in FIGS. 3 and 6 , to a utility fixture, such as utility fixture 150 in FIGS. 1, 5, 6, and 7 .

The process may begin by locating utility fixture 150 having set of coupling units 608 in assembly area 304 (operation 2500). Operation 2500 may be performed in a number of different ways. Utility fixture 150 may be, for example, without limitation, affixed to floor 300, embedded in floor 300, or attached to a wall, ceiling, or some other surface in manufacturing environment 100.

Next, tower 332 may be driven towards location 602 of utility fixture 150 having set of coupling units 608 (operation 2502). Each of set of corresponding coupling units 614 associated with tower 332 may be aligned with set of coupling units 608 using a roller associated with each of set of corresponding coupling units 614 and a guidance fork associated with each of set of coupling units 608 (operation 2504).

A male quick-change device of each of set of coupling units 608 may be mated with a female quick-change device of each of set of corresponding coupling units 614, thereby mating a number of coupling elements associated with each of set of coupling units 608 with a number of corresponding coupling elements associated with each of set of corresponding coupling units 614 (operation 2506). Number of utilities 146 may then be distributed from utility fixture 150 to tower 332 through set of interfaces 640 formed by mating set of coupling units 608 and set of corresponding coupling units 614 (operation 2508), with the process terminating thereafter.

The flowcharts and block diagrams in the different depicted embodiments illustrate the architecture, functionality, and operation of some possible implementations of apparatuses and methods in an illustrative embodiment. In this regard, each block in the flowcharts or block diagrams may represent a module, a segment, a function, a portion of an operation or step, some combination thereof.

In some alternative implementations of an illustrative embodiment, the function or functions noted in the blocks may occur out of the order noted in the figures. For example, in some cases, two blocks shown in succession may be executed substantially concurrently, or the blocks may sometimes be performed in the reverse order, depending upon the functionality involved. Also, other blocks may be added in addition to the illustrated blocks in a flowchart or block diagram.

Turning now to FIG. 26 , an illustration of a data processing system is depicted in the form of a block diagram in accordance with an illustrative embodiment. Data processing system 2600 may be used to implement any of the controllers described above, including control system 136 in FIG. 1 . In some illustrative examples, data processing system 2600 may be used to implement at least one of a controller in set of controllers 140 in FIG. 1 .

As depicted, data processing system 2600 includes communications framework 2602, which provides communications between processor unit 2604, storage devices 2606, communications unit 2608, input/output unit 2610, and display 2612. In some cases, communications framework 2602 may be implemented as a bus system.

Processor unit 2604 is configured to execute instructions for software to perform a number of operations. Processor unit 2604 may comprise at least one of a number of processors, a multi-processor core, or some other type of processor, depending on the implementation. In some cases, processor unit 2604 may take the form of a hardware unit, such as a circuit system, an application specific integrated circuit (ASIC), a programmable logic device, or some other suitable type of hardware unit.

Instructions for the operating system, applications and programs run by processor unit 2604 may be located in storage devices 2606. Storage devices 2606 may be in communication with processor unit 2604 through communications framework 2602. As used herein, a storage device, also referred to as a computer readable storage device, is any piece of hardware capable of storing information on a temporary basis, a permanent basis, or both. This information may include, but is not limited to, data, program code, other information, or some combination thereof.

Memory 2614 and persistent storage 2616 are examples of storage devices 2606. Memory 2614 may take the form of, for example, a random access memory or some type of volatile or non-volatile storage device. Persistent storage 2616 may comprise any number of components or devices. For example, persistent storage 2616 may comprise a hard drive, a flash memory, a rewritable optical disk, a rewritable magnetic tape, or some combination of the above. The media used by persistent storage 2616 may or may not be removable.

Communications unit 2608 allows data processing system 2600 to communicate with other data processing systems, devices, or both. Communications unit 2608 may provide communications using physical communications links, wireless communications links, or both.

Input/output unit 2610 allows input to be received from and output to be sent to other devices connected to data processing system 2600. For example, input/output unit 2610 may allow user input to be received through a keyboard, a mouse, some other type of input device, or a combination thereof. As another example, input/output unit 2610 may allow output to be sent to a printer connected to data processing system 2600.

Display 2612 is configured to display information to a user. Display 2612 may comprise, for example, without limitation, a monitor, a touch screen, a laser display, a holographic display, a virtual display device, some other type of display device, or a combination thereof.

In this illustrative example, the processes of the different illustrative embodiments may be performed by processor unit 2604 using computer-implemented instructions. These instructions may be referred to as program code, computer usable program code, or computer readable program code and may be read and executed by one or more processors in processor unit 2604.

In these examples, program code 2618 is located in a functional form on computer readable media 2620, which is selectively removable, and may be loaded onto or transferred to data processing system 2600 for execution by processor unit 2604. Program code 2618 and computer readable media 2620 together form computer program product 2622. In this illustrative example, computer readable media 2620 may be computer readable storage media 2624 or computer readable signal media 2626.

Computer readable storage media 2624 is a physical or tangible storage device used to store program code 2618 rather than a medium that propagates or transmits program code 2618. Computer readable storage media 2624 may be, for example, without limitation, an optical or magnetic disk or a persistent storage device that is connected to data processing system 2600.

Alternatively, program code 2618 may be transferred to data processing system 2600 using computer readable signal media 2626. Computer readable signal media 2626 may be, for example, a propagated data signal containing program code 2618. This data signal may be an electromagnetic signal, an optical signal, or some other type of signal that can be transmitted over physical communications links, wireless communications links, or both.

The illustration of data processing system 2600 in FIG. 26 is not meant to provide architectural limitations to the manner in which the illustrative embodiments may be implemented. The different illustrative embodiments may be implemented in a data processing system that includes components in addition to or in place of those illustrated for data processing system 2600. Further, components shown in FIG. 26 may be varied from the illustrative examples shown.

The illustrative embodiments of the disclosure may be described in the context of aircraft manufacturing and service method 2700 as shown in FIG. 27 and aircraft 2800 as shown in FIG. 28 . Turning first to FIG. 27 , an illustration of an aircraft manufacturing and service method is depicted in the form of a block diagram in accordance with an illustrative embodiment. During pre-production, aircraft manufacturing and service method 2700 may include specification and design 2702 of aircraft 2800 in FIG. 28 and material procurement 2704.

During production, component and subassembly manufacturing 2706 and system integration 2708 of aircraft 2800 in FIG. 28 takes place. Thereafter, aircraft 2800 in FIG. 28 may go through certification and delivery 2710 in order to be placed in service 2712. While in service 2712 by a customer, aircraft 2800 in FIG. 28 is scheduled for routine maintenance and service 2714, which may include modification, reconfiguration, refurbishment, and other maintenance or service.

Each of the processes of aircraft manufacturing and service method 2700 may be performed or carried out by at least one of a system integrator, a third party, or an operator. In these examples, the operator may be a customer. For the purposes of this description, a system integrator may include, without limitation, any number of aircraft manufacturers and major-system subcontractors; a third party may include, without limitation, any number of vendors, subcontractors, and suppliers; and an operator may be an airline, a leasing company, a military entity, a service organization, and so on.

With reference now to FIG. 28 , an illustration of an aircraft is depicted in the form of a block diagram in which an illustrative embodiment may be implemented. In this example, aircraft 2800 is produced by aircraft manufacturing and service method 2700 in FIG. 27 and may include airframe 2802 with plurality of systems 2804 and interior 2806. Examples of systems 2804 include one or more of propulsion system 2808, electrical system 2810, hydraulic system 2812, and environmental system 2814. Any number of other systems may be included. Although an aerospace example is shown, different illustrative embodiments may be applied to other industries, such as the automotive industry.

The apparatuses and methods embodied herein may be employed during at least one of the stages of aircraft manufacturing and service method 2700 in FIG. 27 . In particular, flexible manufacturing system 106 from FIG. 1 may be used to build at least a portion of airframe 2802 of aircraft 2800 during any one of the stages of aircraft manufacturing and service method 2700. For example, without limitation, flexible manufacturing system 106 from FIG. 1 may be used during at least one of component and subassembly manufacturing 2706, system integration 2708, or some other stage of aircraft manufacturing and service method 2700 to form a fuselage for aircraft 2800.

In one illustrative example, components or subassemblies produced in component and subassembly manufacturing 2706 in FIG. 27 may be fabricated or manufactured in a manner similar to components or subassemblies produced while aircraft 2800 is in service 2712 in FIG. 27 . As yet another example, one or more apparatus embodiments, method embodiments, or a combination thereof may be utilized during production stages, such as component and subassembly manufacturing 2706 and system integration 2708 in FIG. 27 . One or more apparatus embodiments, method embodiments, or a combination thereof may be utilized while aircraft 2800 is in service 2712, during maintenance and service 2714 in FIG. 27 , or both. The use of a number of the different illustrative embodiments may substantially expedite the assembly of and reduce the cost of aircraft 2800.

The description of the different illustrative embodiments has been presented for purposes of illustration and description, and is not intended to be exhaustive or limited to the embodiments in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. Further, different illustrative embodiments may provide different features as compared to other desirable embodiments. The embodiment or embodiments selected are chosen and described in order to best explain the principles of the embodiments, the practical application, and to enable others of ordinary skill in the art to understand the disclosure for various embodiments with various modifications as are suited to the particular use contemplated.

Claims

What is claimed is:

1. A method for distributing a number of utilities, the method comprising:

coupling the number of utilities between a number of utility sources and a first coupling unit of a utility fixture;

moving a first mobile system across a floor into a selected position relative to the utility fixture, wherein the first mobile system comprises a first corresponding coupling unit and a second coupling unit;

coupling the number of utilities between the utility fixture and the first mobile system by autonomously coupling the first corresponding coupling unit of the first mobile system to the first coupling unit of the utility fixture;

moving a second mobile system across the floor to the first mobile system, wherein the second mobile system comprises a second corresponding coupling unit; and

coupling the number of utilities between the second mobile system and the first mobile system by coupling the second corresponding coupling unit of the second mobile system to the second coupling unit of the first mobile system such that the number of utilities flows downstream from the number of utility sources, through the utility fixture, through the first coupling unit of the utility fixture, through the first corresponding coupling unit of the first mobile system, through the second coupling unit of the first mobile system, and through the second corresponding coupling unit of the second mobile system to the second mobile system.

2. The method of claim 1, wherein coupling the number of utilities between the utility fixture and the first mobile system comprises:

autonomously aligning the first coupling unit associated with the utility fixture with the first corresponding coupling unit associated with the first mobile system; and

autonomously mating the first coupling unit with the first corresponding coupling unit to couple the number of utilities between the utility fixture and the first mobile system.

3. The method of claim 1 further comprising:

affixing the utility fixture to a floor.

4. The method of claim 1, wherein coupling the number of utilities between the number of utility sources and the utility fixture comprises:

plugging a number of input cables extending from the utility fixture into a number of output connections associated with the number of utility sources.

5. The method of claim 1, wherein coupling the number of utilities between the utility fixture and the first mobile system comprises:

autonomously connecting the first coupling unit associated with the utility fixture to the first corresponding coupling unit associated with a drivable tower.

6. The method of claim 1 further comprising:

autonomously connecting the first coupling unit associated with the utility fixture to the first corresponding coupling unit associated with a drivable tower to physically couple the utility fixture to the drivable tower.

7. The method of claim 1, wherein moving the first mobile system comprises:

driving a tower into a selected tower position relative to the utility fixture.

8. The method of claim 7, wherein driving the tower comprises:

driving the tower autonomously from a holding area into the selected tower position within an assembly area.

9. The method of claim 1, wherein coupling the number of utilities between the utility fixture and the first mobile system comprises:

coupling a tower to the utility fixture; and

coupling an assembly fixture to the tower such that the number of utilities flows downstream from the number of utility sources, through the utility fixture, through the tower, and to the assembly fixture.

10. The method of claim 1, wherein coupling the number of utilities between the utility fixture and the first mobile system comprises:

coupling a tower to the utility fixture to establish a distributed utility network.

11. The method of claim 10 further comprising:

adding a number of cradle fixtures to the distributed utility network.

12. The method of claim 11 further comprising:

adding a number of external mobile platforms to the distributed utility network.

13. The method of claim 11, wherein adding the number of cradle fixtures to the distributed utility network comprises:

coupling the number of cradle fixtures to the tower in series.

14. The method of claim 1, wherein:

the first mobile system comprises a tower; and

the second mobile system comprises an assembly fixture holding a portion of a fuselage of an aircraft.