Patent Publication Number: US-2022227074-A1

Title: Method and apparatus for laying up a composite material onto a substrate

Description:
PRIORITY 
     This application claims priority from U.S. Ser. No. 63/139,458 filed on Jan. 20, 2021. 
    
    
     GOVERNMENT RIGHTS 
     This invention was made with government support under SAA1-21157; SAA1-21157, Annex 17; and SAA1-21157, Annex 17, MOD 1 awarded by the National Aeronautics and Space Administration. The government has certain rights in this invention. The invention described herein may be manufactured and used by or for the U.S. Government for U.S. Government purposes without the payment of royalties thereon or therefor. 
    
    
     FIELD 
     This application relates to manufacturing articles from composite materials and, more particularly, to the laying up of composite materials during such manufacturing and, even more particularly, to the use of plasma heating during the layup of composite materials. 
     BACKGROUND 
     Composite structures are commonly used as high-strength, low-weight materials. A composite structure includes one or more composite layers, wherein each composite layer includes a reinforcement material and a matrix material. The reinforcement material may include fibers. The matrix material may be a polymeric material, such as a thermosetting resin or a thermoplastic resin. 
     Fiber-reinforced composite structures may be manufactured by laying up multiple layers of fiber tow to form a reinforcement layup. The fiber tow generally includes a bundle of fibers (reinforcement material) impregnated with a matrix material. In fiber placement technologies, the fiber tow is generally supplied as a tape from a bulk reel and is pressed onto the underlying layup at a nip using a compaction roller. The fully assembled reinforcement layup is then cured and/or consolidated, as necessary, to form the composite structure. 
     When the matrix material of the fiber tow is a thermoplastic resin, the layup process typically requires heating to soften the thermoplastic resin and obtain layer-to-layer consolidation within the reinforcement layup. For example, a laser beam (e.g., an infrared laser beam) may be projected proximate (i.e., at or near) the nip to heat the fiber tow and/or the underlying layup during fiber placement. However, the laser light may not evenly apply heating across parts having complex curvature. Further, lasers typically require additional safety features and are thus cost prohibitive. 
     Accordingly, those skilled in the art continue with research and development efforts in the field of laying up composite materials. 
     SUMMARY 
     Disclosed a method for laying up a composite material. 
     In an example, the method for laying up a composite material includes depositing the composite material onto a substrate. The method further includes compacting the composite material with a compaction roller. The compaction roller and the substrate are configured to define a nip. The method further includes projecting a plasma flume proximate the nip to heat at least one of the composite material and the substrate. 
     Also disclosed is an apparatus for laying up composite material onto a substrate. 
     In an example, an apparatus for laying up composite material onto a substrate includes a compaction roller. The compaction roller is configured to define a nip when the compaction roller is engaged with the substrate. The apparatus further includes a plasma generating device. The plasma generating device is positioned to project a plasma flume toward the nip. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG. 1  is a cross-sectional front view of an apparatus for laying up composite material. 
         FIG. 2  is a cross-sectional front view of an apparatus for laying up composite material. 
         FIG. 3  is a cross-sectional front view of a plasma generating device. 
         FIG. 4  is a schematic representation of a plasma generating device. 
         FIG. 5  is a perspective view of a nozzle tip of the plasma generating device of  FIG. 4 . 
         FIG. 6  is a perspective view of a nozzle tip of the plasma generating device of FIG. 
         FIG. 7  is a flowchart illustrating a method for laying up a composite material. 
         FIG. 8  is a flow diagram of an aircraft manufacturing and service methodology. 
         FIG. 9  is a block diagram of an aircraft. 
     
    
    
     DETAILED DESCRIPTION 
     The following detailed description refers to the accompanying drawings, which illustrate specific examples described by the disclosure. Other examples having different structures and operations do not depart from the scope of the present disclosure. Like reference numerals may refer to the same feature, element, or component in the different drawings. 
     Illustrative, non-exhaustive examples, which may be, but are not necessarily, claimed, of the subject matter according the present disclosure are provided below. 
     The following disclosure refers to methods and accompanying apparatuses utilizing plasma treatment to facilitate tack between layers of composite material. In one or more examples, a layer of composite material is laid down and, subsequently, a layer of composite material is laid on top of the first layer. The tacking maintains the composite material layers in place relative to each other until the layup of composite material is complete and/or hardened. 
     Referring to  FIG. 1 , an exemplary embodiment of an apparatus  100  for laying up composite material  160  onto a substrate  140  is illustrated. In one or more examples, the apparatus  100  includes a housing  105 . In an example, the apparatus  100  further includes a support structure  107  located, at least partially, within the housing  105 . In one or more examples, the apparatus further includes a compaction roller  130 . In an example, compaction roller  130  is located, at least partially, within the housing  105 . The compaction roller  130  is adjustably and rotationally mounted within the apparatus  100 . In an example, the compaction roller  130  is adjustably and rotationally mounted to the support structure  107  located within the housing  105  of the apparatus  100 . The compaction roller  130  is configured to define a nip  135  when the compaction roller  130  is engaged with the substrate  140 . The compaction roller  130  is configured to exert compaction, or placement force, on the composite material  160  to press it against the substrate  140 . 
     In an example, the apparatus  100  includes a heat source  113  configured to heat at least a portion of the composite material  160  or at least a portion of the substrate  140 . In an example, the heat source  113  is an electric heater, an infrared heater, a laser, a laser diode array, a hot gas torch, or a plasma generating device  120 . In an example, the heat source  113  is positioned such that it is directed to the nip  135 . The heat source  113  is configured to treat the composite material  160  at approximately the nip  135 . In one or more examples, the heat source  113  is a plasma generating device  120  that provides heat to improve tack and otherwise activate a previous layer of towpreg/prepreg/etc. composite material  160  to improve the layer by layer tack/adhesion/placement of subsequent towpreg/prepreg/etc. layers of composite material  160 . 
     In an example, the apparatus  100  includes a bulk reel  155 . In an example, the bulk reel  155  is contained, at least partially, within the housing  105 . The bulk reel  155  is adjustably mounted within the apparatus  100 . The bulk reel  155  contains the composite material  160  and is configured to feed the composite material  160  from the apparatus  100  to the substrate  140 . In an example, the composite material  160  contained within the bulk reel  155  is tape  150 . In an example, the apparatus  100  includes a feed unit  152  located adjacent to the bulk reel  155 . The feed unit  152  is positioned to move, or feed, the composite material  160  from the bulk reel  155  to the nip  135 . 
     In an example, the apparatus  100  includes a cutting unit  154 . Cutting unit  154  is located, at least partially, within the housing  105 . The cutting unit  154  may be positioned along the feed unit  152  between the bulk reel  155  and the compaction roller  130  such that the composite material  160  may feed through the bulk reel  155 , then through the cutting unit  154 , where the composite material  160  may be cut to any desired length. The composite material  160  may then be fed to the substrate  140  where it is compacted, or consolidated, by the compaction roller  130 . The compaction roller  130  is configured to apply force to the composite material  160  against the substrate  140  while the composite material  160  is disposed or fed from the bulk reel  155 . In an example, the composite material  160  is tape  150 . In an example, the composite material  160  includes a reinforcement material. In an example, the composite material  160  includes a thermoplastic material. 
       FIG. 2  illustrates an exemplary embodiment of an apparatus  100 . In an example, the apparatus  100  includes a housing  105 . In an example, the apparatus  100  includes a support structure  107  located, at least partially, within the housing  105 . In one or more examples, the apparatus further includes a compaction roller  130 . In an example, compaction roller  130  is located, at least partially, within the housing  105 . In an example, the compaction roller  130  is adjustably and rotationally mounted to the support structure  107  located within the housing  105  of the apparatus  100 . The compaction roller  130  is configured to define a nip  135  when the compaction roller  130  is engaged with the substrate  140 . In one or more examples, the apparatus  100  includes a heat source  113  configured to heat at least a portion of the composite material  160  or at least a portion of the substrate  140 . In an example, the heat source  113  is a plasma generating device  120 . In an example, the plasma generating device  120  is located, at least partially, within the housing  105 . The plasma generating device  120  is positioned to project a plasma flume  125 , illustrated in  FIG. 3 , toward the nip  135 . In an example, the plasma generating device  120  includes an atmospheric pressure plasma head  128 . 
       FIG. 3  illustrates a cross-sectional view of an example of a plasma generating device  120 . In one or more examples, the plasma generating device  120  includes a nozzle tip  123 . The nozzle tip  123  is configured to direct the plasma flume  125  at an emanation angle. In one or more examples, the emanation angle ranges from about 0 degrees to about 15 degrees. In one or more examples, the nozzle tip  123  is configured to direct the plasma flume  125  at an emanation angle of about 0 degrees, meaning the nozzle central axis  129  of the nozzle tip  123  is approximately aligned or parallel with the plasma flume  125  flume aperture central axis  139   a , illustrated in  FIG. 4 , the flume aperture  139  being where the plasma flume  125  emanates from the nozzle tip  123 . In one or more examples, the nozzle tip  123  directs the plasma flume  125  at approximately 1.65±0.1 cm from the nip  135 . In one or more examples, the nozzle tip  123  is interchangeable such that any desired shape and emanation angle of the plasma flume  125  may be achieved. In one or more examples, the nozzle tip  123  is configured to direct the plasma flume  125  at an emanation angle of about 17 degrees. The plasma flume  125  is configured to treat the composite material  160  to improve layup or tack of the composite material  160  on the substrate  140 . Specifically, the plasma flume  125  contains charged species that may modify the surface of the composite material  160  with chemical groups (e.g. oxygen functionality) that enhance material tack and, ultimately, layup of composite material  160 . The plasma treatment may increase the surface energy of the surface of the composite material  160 , thereby increasing the propensity of the surface for material tack and layup of composite material  160  relative to the surface prior to plasma treatment. The plasma flume  125  is positioned at an emanation angle and at a distance from the composite material  160  to achieve optimum temperature for tacking and consolidation across the entire width of the composite ply or tape  150 . In one or more examples, the optimum temperature is approximately 93° C. 
       FIG. 4  illustrates an exemplary embodiment of plasma generating device  120 . The plasma generating device  120  includes a plasma generator  180  that is connected to plasma jet  121 . The plasma jet  121  includes a chamber  122 , at least one inlet  127  for compressed gas  175 , and a nozzle tip  123 . In an example, the compressed gas  175  includes compressed air. In an example, the compressed gas  175  includes ionization gas. The plasma generating device  120  may be operated manually or may be automated, such as with an automated fiber placement (AFP) machine  115 . Upon excitation with electrical power from the plasma generator  180 , compressed gas  175  within the chamber  122  is ionized to produce the plasma flume  125 . The plasma flume  125  is expelled from the chamber  122  and through the nozzle tip  123 , and impinges on the composite material  160  on the substrate  140  at approximately the nip  135  for treatment thereof. 
       FIG. 5  and  FIG. 6  illustrate various nozzle tip  123  configurations. In an example, the emanation angle of the nozzle tip  123  is about 17 degrees (±0.2%) or less, see  FIG. 5 . This example illustrates configurations used in the past. In an example, the emanation angle of the nozzle tip  123  is about 0 degrees (±0.2%) or less, see  FIG. 6 . The low emanation angle of the nozzle tip  123  provides a more intense and focused (less diffuse) plasma flume  125  relative to nozzle tips with greater emanation angles. The more intense and focused plasma flume  125  provided with the nozzle tip  123  enhances composite material  160  layup across substrate  140  surfaces at reduced treatment times compared to nozzle tips with higher emanation angles. Even materials that are typically difficult to fabricate due to their low surface energies, such as thermoplastic materials, may exhibit composite material  160  layup enhancements at reduced treatment times using the nozzle tip  123 . 
     Although nozzles having greater emanation angles are generally rotated in order to provide a more diffuse annular plasma flume  125  or plasma “cone” or “ring,” a nozzle tip  123  having a zero degree angle is generally not rotated during plasma treatment. Due to the low emanation angle, the nozzle tip  123  having a zero degree angle may provide a more focused and intense plasma flume for impingement on the surface of the composite material  160  on the substrate  140  at a given orientation, such as a normal orientation, as compared to nozzle tips having greater emanation angles. In an example, the diameter (d) of the plasma flume  125  emanating from the nozzle tip  123  having a zero degree angle may be about 6.4 millimeters (±2%), with it being understood that the exterior or outer edge of the plasma flume  125  is fluid and variable in practice. Accordingly, the diameter (d) of the plasma flume  125  disclosed herein is approximate but generally constant as it is generated by the plasma generating device  120 . Additionally, the plasma flume  125  may have a height (h) ranging from about 1.2 centimeters to about 2.0 centimeters. As such, the distance between the nozzle tip  123  and the surface of composite material  160  on the substrate  140  during plasma treatment may range from about 1.2 centimeters to about 2.0 centimeters during the plasma treatment process. In contrast, a nozzle tip having a 17 degree angle, which has an emanation angle of 17 degrees and rotates (typically at about 2800 rpm) during plasma treatment, produces an annular flume with a plasma flume  125  diameter of about 24 millimeters and a height of about 1.3 centimeters. The nozzle tip  123  having a zero degree angle thus affords a greater working distance than the nozzle tip  123  having a 17 degree angle, and provides a plasma flume  125  that is about four times more focused than the wider (more diffuse) annular plasma flume  125  of the nozzle tip  123  having a 17 degree angle. The greater working distance may facilitate processing of substrates with complex geometries. Depending on the configuration of the nozzle tip  123  having a zero degree angle and/or other factors, the diameter (d) and height (h) of the plasma flume  125  may deviate from the values provided above. 
     In an example, the composite material  160  on the substrate  140  treated by the plasma generating device  120  is a thermoplastic material. The thermoplastic material may be treated by the plasma generating device  120  to aid in composite material  160  tack. Thermoplastic materials that may exhibit increased composite material  160  layup propensities with plasma treatment in accordance with the present disclosure include, but are not limited to, polyphenylene sulfide, polyaryletherketone (PAEK), polyetherketoneketone (PEKK), polyetheretherketone (PEEK), polyimide, polyetherimide, polyamide, polyamide-imide, polyester, polybutadiene, polyurethane, polypropylene, polysulfone, polyethersulfone, polyphenylsulfone, polyacrylamide, polyketone, polyphthalamide, polyphenylene ether, polybutylene terephthalate, polyethylene, polyethylene terephthalate, polyester-polyarylate (e.g. Vectran®), polytetrafluoroethylene (PTFE), and other thermoplastic resins. 
     In an example, the composite material  160  on the substrate  140  treated by the plasma generating device  120  is a thermoset material. The thermoset material may be treated by the plasma generating device  120  to aid in composite material  160  tack. Examples of suitable thermoset materials include, but are not limited to, epoxy resins, cyanate esters, benzoxazines, polyimides, bismaleimides, vinyl esters, polyurethanes, polyureas, polyurethane/polyurea blends, polyesters, and other thermoset resins. The composite material  160  on the substrate  140  may be formed from or include other materials such as, but not limited to, metal, ceramic, rubber, glass, and composite materials. 
     Optionally, the composite material  160  on the substrate  140  may be reinforced with a reinforcing material. Reinforcing materials may include, but are not limited to, carbon fiber, glass fiber, glass spheres, mineral fiber, or other reinforcing materials. If fibers are used as a reinforcing material, the fibers may be continuous or chopped, and may be unidirectional, randomly-oriented, or in the form of a weave such as, but not limited to, a plain weave, a crowfoot weave, a basket weave, and a twill weave. 
     The intense plasma flume  125  generated by the nozzle tip  123  having a zero degree angle may substantially reduce plasma treatment times needed for increasing composite material  160  layup and material tack propensities compared to a nozzle tip  123  having emanation angles greater than 5 degrees. In an example, the layup of composite material  160  includes adhesion to like material. In an example, the layup of composite material  160  includes adhesion with other materials including prepreg material. 
       FIG. 7  illustrates a flowchart of a method  300  for laying up a composite material  160 . In an example, the method  300  includes depositing  310  a composite material  160  onto a substrate  140 . In an example, the substrate  140  is a tool  145 . In an example, the substrate  140  is a previously-applied composite material  160  on a tool  145 . Composite material  160  may be in the form of a composite ply or a tape  150 . In an example, the composite material  160  includes a reinforcement material. In an example, the composite material  160  includes a thermoplastic material. Thermoplastic materials that may exhibit increased composite material  160  layup and material tack propensities with plasma treatment in accordance with the present disclosure include, but are not limited to, polyphenylene sulfide, polyaryletherketone (PAEK), polyetherketoneketone (PEKK), polyetheretherketone (PEEK), polyimide, polyetherimide, polyamide, polyamide-imide, polyester, polybutadiene, polyurethane, polypropylene, polysulfone, polyethersulfone, polyphenylsulfone, polyacrylamide, polyketone, polyphthalamide, polyphenylene ether, polybutylene terephthalate, polyethylene, polyethylene terephthalate, polyester-polyarylate (e.g. Vectran®), polytetrafluoroethylene (PTFE), and other thermoplastic resins. 
     In an example, the composite material  160  on the substrate  140  treated by the plasma generating device  120  of the method  300  is a thermoset material. Examples of suitable thermoset materials include, but are not limited to, epoxy resins, cyanate esters, benzoxazines, polyimides, bismaleimides, vinyl esters, polyurethanes, polyureas, polyurethane/polyurea blends, polyesters, and other thermoset resins. The composite material  160  on the substrate  140  may be formed from or include other materials such as, but not limited to, metal, ceramic, rubber, glass, and composite materials. 
     In an example, the depositing  310  includes receiving composite material  160  from a bulk reel  155 . In an example, the bulk reel  155  is contained, at least partially, within the housing  105 . The bulk reel  155  is adjustably mounted within the apparatus  100 . The bulk reel  155  contains the composite material  160  and is configured to feed the composite material  160  from the apparatus  100  to where it is deposited on the substrate  140 . In an example, the composite material  160  contained within the bulk reel  155  is tape  150 . In an example, the apparatus  100  includes a feed unit  152  located adjacent to the bulk reel  155 . The feed unit  152  is positioned to move, or feed, the composite material  160  from the bulk reel  155  to the nip  135  at the substrate  140 . 
     In an example, the depositing  310  includes cutting the composite material  160  with a cutting unit  154 . Cutting unit  154  is located, at least partially, within the housing  105 . The cutting unit  154  may be positioned along the feed unit  152  between the bulk reel  155  and compaction roller  130  such that the composite material  160  may feed through the bulk reel  155 , then through the cutting unit  154 , where the composite material  160  may be cut to any desired length. The composite material  160  may then be deposited onto the substrate  140  where it is compacted, or consolidated, by the compaction roller  130 , as described below. 
     In an example, the method  300  includes compacting  320  the composite material  160  with a compaction roller  130 . The compaction roller  130  and the substrate  140  are configured to define a nip  135 . In an example, compaction roller  130  is located, at least partially, within a housing  105  of an apparatus  100 . The compaction roller  130  is adjustably and rotationally mounted within the apparatus  100 . In an example, the compaction roller  130  is adjustably and rotationally mounted to a support structure  107  located within the housing  105  of the apparatus  100 . The compaction roller  130  is configured to define the nip  135  when the compaction roller  130  is engaged with the substrate  140 . The compaction roller  130  is configured to exert compaction or placement force on the composite material  160  to press it against the substrate  140  when compacting  320  the composite material  160  on the substrate  140 . 
     In an example, the method  300  includes projecting  330  a plasma flume  125  proximate the nip  135  to heat at least one of the composite material  160  and the substrate  140 . In an example, the projecting  330  the plasma flume  125  of the method  300  includes projecting  330  the plasma flume  125  from a plasma generating device  120 . In an example, the plasma generating device  120  includes an atmospheric pressure plasma head  128 . In an example, the projection  330  the plasma flume  125  includes projecting the plasma flume  125  at a pressure ranging from about 15 psi to about 50 psi. 
     In an example, the projecting  330  the plasma flume  125  of the method  300  includes projecting the plasma flume  125  at an emanation angle, ranging from about 0 degrees to about 20 degrees. In an example, the projecting  330  the plasma flume  125  of the method  300  includes projecting the plasma flume  125  at an emanation angle, ranging from about 0 degrees to about 10 degrees. In an example, the projecting  330  the plasma flume  125  of the method  300  includes projecting the plasma flume  125  at an emanation angle, ranging from about 0 degrees to about 5 degrees. In an example, the projecting  330  the plasma flume  125  of the method  300  includes projecting the plasma flume  125  at an emanation angle of approximately zero degrees. 
     In an example, the plasma flume  125  of the method  300  has a maximum width of about 3.5 millimeters to about 9 millimeters. In an example, the plasma flume  125  has a length of about 1.25 centimeters to about 3 centimeters. In an example, the plasma flume  125  is about 1.25 centimeters to about 2 centimeters from the nip  135 . The shape of the nozzle tip  123  facilitates the shape and size of the plasma flume  125 . In an example, the diameter (d) of the plasma flume  125  emanating from the nozzle tip  123  having a zero degree angle may be about 6.5 millimeters (±2%), with it being understood that the exterior or outer edge of the plasma flume  125  is fluid and variable in practice. Accordingly, the diameter (d) of the plasma flume  125  disclosed herein is approximate but generally constant as it is generated by the plasma generating device  120 . Additionally, the plasma flume  125  may have a height (h) ranging from about 1.2 centimeters to about 2.0 centimeters. As such, the distance between the nozzle tip  123  and the surface of composite material  160  on the substrate  140  during plasma treatment may range from about 1.2 centimeters to about 2.0 centimeters during the plasma treatment process. In contrast, a nozzle tip having a 17 degree angle, which has an emanation angle of 17 degrees and rotates (typically at about 2800 rpm) during plasma treatment, produces an annular flume with a plasma flume  125  diameter of about 24 millimeters and a height of about 1.3 centimeters. The nozzle tip  123  having a zero degree angle thus affords a greater working distance than the nozzle tip  123  having a 17 degree angle, and provides a plasma flume  125  that is about four times more focused than the wider (more diffuse) annular plasma flume  125  of the nozzle tip  123  having a 17 degree angle. The greater working distance may facilitate processing of substrates with complex geometries. Depending on the configuration of the nozzle tip  123  having a zero degree angle and/or other factors, the diameter (d) and height (h) of the plasma flume  125  may deviate from the values provided above. 
     The following examples are non-limiting and only illustrate exemplary implementations of the invention. 
     Examples of the disclosure may be described in the context of an aircraft manufacturing and service method  1100 , as shown in  FIG. 8 , and an aircraft  1102 , as shown in  FIG. 9 . During pre-production, the aircraft manufacturing and service method  1100  may include specification and design  1104  of the aircraft  1102  and material procurement  1106 . During production, component/subassembly manufacturing  1108  and system integration  1110  of the aircraft  1102  takes place. Thereafter, the aircraft  1102  may go through certification and delivery  1112  in order to be placed in service  1114 . While in service by a customer, the aircraft  1102  is scheduled for routine maintenance and service  1116 , which may also include modification, reconfiguration, refurbishment and the like. 
     Each of the steps of method  1100  may be performed or carried out by a system integrator, a third party, and/or an operator  500  (e.g., 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 venders, subcontractors, and suppliers; and an operator  500  may be an airline, leasing company, military entity, service organization, and so on. 
     As shown in  FIG. 9 , the aircraft  1102  produced by example method  1100  may include an airframe  1118  with a plurality of systems  1120  and an interior  1122 . Examples of the plurality of systems  1120  may include one or more of a propulsion system  1124 , an electrical system  1126 , a hydraulic system  1128 , and an environmental system  1130 . Any number of other systems may be included. 
     The disclosed methods and systems may be employed during any one or more of the stages of the aircraft manufacturing and service method  1100 . As one example, components or subassemblies corresponding to component/subassembly manufacturing  1108 , system integration  1110  and/or maintenance and service  1116  may be assembled using the disclosed methods and systems. As another example, the airframe  1118  may be constructed using the disclosed methods and systems. Also, one or more apparatus examples, method examples, or a combination thereof may be utilized during component/subassembly manufacturing  1108  and/or system integration  1110 , for example, by substantially expediting assembly of or reducing the cost of an aircraft  1102 , such as the airframe  1118  and/or the interior  1122 . Similarly, one or more of system examples, method examples, or a combination thereof may be utilized while the aircraft  1102  is in service, for example and without limitation, to maintenance and service  1116 . 
     Aspects of disclosed examples may be implemented in software, hardware, firmware, or a combination thereof. The various elements of the system, either individually or in combination, may be implemented as a computer program product tangibly embodied in a machine-readable storage device for execution by a processor. Various steps of examples may be performed by a computer processor executing a program tangibly embodied on a computer-readable medium to perform functions by operating on input and generating output. The computer-readable medium may be, for example, a memory, a transportable medium such as a compact disk or a flash drive, such that a computer program embodying aspects of the disclosed examples can be loaded onto a computer. 
     The above-described methods and systems are described in the context of an aircraft. However, one of ordinary skill in the art will readily recognize that the disclosed methods and systems are suitable for a variety of applications, and the present disclosure is not limited to aircraft manufacturing applications. For example, the disclosed methods and systems may be implemented in various articles of manufacture not limited to aircraft or aircraft components and the like. Non-aircraft applications are also contemplated. 
     Also, although the above-description describes methods and systems that may be used to manufacture an aircraft or aircraft component in the aviation industry in accordance with various regulations (e.g., commercial, military, etc.), it is contemplated that the disclosed methods and systems may be implemented to facilitate manufacturing of a part in any industry in accordance with the applicable industry standards. The specific methods and systems can be selected and tailored depending upon the particular application. 
     The described features, advantages, and characteristics of one example may be combined in any suitable manner in one or more other examples. One skilled in the relevant art will recognize that the examples described herein may be practiced without one or more of the specific features or advantages of a particular example. In other instances, additional features and advantages may be recognized in certain examples that may not be present in all examples. Furthermore, although various examples of the manufacturing system, the process, and the method have been shown and described, modifications may occur to those skilled in the art upon reading the specification. The present application includes such modifications and is limited only by the scope of the claims.