Patent Publication Number: US-2023136548-A1

Title: System and method for post-cure processing of a composite workpiece

Description:
PRIORITY 
     This application claims priority from U.S. Ser. No. 63/274,982 filed on Nov. 3, 2021. 
    
    
     FIELD 
     The present disclosure relates generally to composite manufacturing and, more particularly, to systems and methods for starting post-cure processing of a composite workpiece on a cure tool. 
     BACKGROUND 
     Composite pats are commonly used in applications where light weight and high strength are desired, such as in aircraft and vehicles. Typically, one or more machining or other processing operations are performed on the composite part, such as drilling holes, machining features, and trimming edges. However, composite parts, particularly large composite parts, may tend to deform once they are removed from a tool upon which they are cured. Such deformation may present challenges related to the accuracy of the machining operations. As such, post-machining operations, such as shimming, may be required due to differences between an as-built shape of the composite structure and a shape of the composite structure during machining. These challenges may also limit the capacity for determine assembly or predictive assembly of a manufactured structure that includes the composite part. Accordingly, those skilled in the art continue with research and development efforts in the field of composite manufacturing. 
     SUMMARY 
     Disclosed are examples of a system for post-cure processing of a composite workpiece, a tool for post-cure processing of a composite workpiece, and a method for post-cure processing of a composite workpiece. The following is a non-exhaustive list of examples, which may or may not be claimed, of the subject matter according to the present disclosure. 
     In an example, the disclosed system includes a tool. The tool includes a tool surface. The tool surface supports a composite workpiece located on the tool. The system also includes a drill template. The drill template defines a drilling location for drilling a hole through the composite workpiece while the composite workpiece is on the tool. 
     In an example, the disclosed tool includes a tool surface that supports a composite workpiece located on the tool. The tool also includes a recess formed in the tool surface. The tool further includes a sacrificial material within the recess and having a top surface that is substantially flush with the tool surface. A portion of a drill bit penetrates the recess, drilling the sacrificial material, when drilling a hole through the composite workpiece while the composite workpiece is on the tool. 
     In another example, the disclosed system includes a tool. The tool includes a tool surface that supports the composite workpiece located on the tool. The tool also includes a sacrificial portion disposed on the tool surface. The system also includes a drill template that defines a drilling location on the composite workpiece. The system further includes a drill that includes a drill bit for drilling a hole through the composite workpiece at the drilling location, defined by the drill template, while the composite workpiece is on the tool. A portion of the drill bit penetrates the sacrificial portion of the tool after the drill bit passes through the composite workpiece. 
     In another example, the disclosed method includes steps of: (1) supporting a composite workpiece on a tool surface of a tool; (2) defining a drilling location on the composite workpiece while the composite workpiece is on the tool using a drill template; and (3) drilling a hole through the composite workpiece at the drilling location, defined by the drill template, while the composite workpiece is on the tool. 
     Other examples of the disclosed system, tool, and method will become apparent from the following detailed description, the accompanying drawings, and the appended claims. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG.  1    is a schematic illustration of an example of a manufacturing environment for post-cure processing of a composite workpiece; 
         FIG.  2    is a schematic block diagram of an example of a system for post-cure processing of a composite workpiece; 
         FIG.  3    is a schematic, top plan view of an example of a tool of the system; 
         FIG.  4    is a schematic, sectional view of an example of a portion of the tool and the composite workpiece on the tool; 
         FIG.  5    is a schematic, top plan view of an example of the tool and the composite workpiece on the tool; 
         FIG.  6    is a schematic, top plan view of an example of the tool and the composite workpiece on the tool after a hole is drilled through the composite workpiece on the tool; 
         FIG.  7    is a schematic, top plan view of an example of the tool, the composite workpiece on the tool, and a drill template; 
         FIG.  8    is a schematic, sectional view of an example of a portion of the tool, the composite workpiece on the tool, and the drill template; 
         FIG.  9    is a schematic, perspective view of an example of a portion of the tool, the composite workpiece on the tool, and the drill template; 
         FIG.  10    is a schematic, perspective view of an example of a portion of the tool, the composite workpiece on the tool, and the drill template; 
         FIG.  11    is a schematic, perspective view of an example of a portion of the composite workpiece on the tool, the drill template, and a drill for drilling the hole through the composite workpiece; 
         FIG.  12    is a schematic illustration of an example of a first work cell of the manufacturing environment, in which the hole is drilled through the composite workpiece while the composite workpiece is on the tool; 
         FIG.  13    is a schematic, perspective view of an example of the tool, the composite workpiece on the tool, and automated drilling machine; 
         FIG.  14    is a schematic, top plan view of a workpiece model and the drill guide; 
         FIG.  15    is a schematic illustration of an example of a second work cell of the manufacturing environment, in which a subsequent processing operation is performed on the composite workpiece; 
         FIG.  16    is a schematic flow diagram of an example of a method for post-cure processing a composite workpiece; 
         FIG.  17    is a flow diagram of an example of an aircraft manufacturing and service method; and 
         FIG.  18    is a schematic illustration of an example of an aircraft. 
     
    
    
     DETAILED DESCRIPTION 
     Referring generally to  FIGS.  1 - 15   , by way of examples, the present disclosure is directed to a system  100  for post-cure processing of a composite workpiece  102 . The system  100  facilitates an initial operation in the post-cure processing, in which at least one machining operation is performed on the composite workpiece  102  while the composite workpiece  102  is on a tool  104  in its as-built shape. The system  100  advantageously improves the accuracy and precision of the machining operation, facilitates automated indexing of the composite workpiece  102  during subsequent machining or processing operations, and facilitates determinate or predictive assembly of a structure that includes the composite workpiece  102 . 
     For the purpose of the present disclosure, the term “composite workpiece” (e.g., composite workpiece  102 ) refers to any object, article, item, or structure made of a cured composite material. In one or more examples, the composite workpiece  102  is, or forms, a part or a component of a larger manufactured article or structure, such as an aircraft or a component of an aircraft. As an example, the composite workpiece  102  is a wing panel  1230  of an aircraft  1200  (e.g., as shown in  FIG.  18   ). 
     For the purpose of the present disclosure, the term “post-cure” refers to a condition of a composite material after a curing operation, such as by application of heat and/or pressure, to cure, anneal, dry, and/or harden the composite material. 
     For the purpose of the present disclosure, the term “as-built,” such as in reference to the as-built condition or shape of the composite workpiece  102 , refers to a condition of the composite workpiece  102  in which the composite workpiece  102  has a shape (e.g., geometry, profile, contour, and the like) as formed and/or cured on the tool  104 . 
     It can be appreciated that once a composite structure (e.g., the composite workpiece  102 ) is removed from a cure tool upon which it is cured (e.g., tool  104 ), the composite structure may tend to deform (e.g., change shape), for example, due to residual stresses in the composite structure or due to external forces applied to the composite structure during post-cure processing. The principles and implementations of the system  100  disclosed herein enable a machining operation to be performed on the composite workpiece  102  while the composite workpiece  102  is on the tool  104 . As such, the machining operation is performed on the composite workpiece  102  while the composite workpiece  102  is in the as-built condition or while having the as-built shape, thereby, reducing or eliminating inaccurate or inconsistent machining due to the machining operation being performed on a composite workpiece while the composite workpiece has a shape that is different than the as-built shape. 
     Additionally, the principles and implementations of the system  100  disclosed herein enable a digital model to be generated, which is representative of the composite workpiece  102  having the as-built shape. The digital model of the composite workpiece  102  in the as-built shape may be used to index the composite workpiece  102  before a subsequent processing operation is performed on the composite workpiece  102  from the tool  104 . The digital model of the composite workpiece  102  may also be used to conform the composite workpiece  102  to the as-built shape during a subsequent processing operation performed on the composite workpiece  102  off the tool  104 . As such, subsequent machining operations performed on the composite workpiece  102 , with the composite workpiece  102  off the tool  104  but in the as-built shape, reduces or eliminates inaccurate or inconsistent machining due to the machining operation being performed on a composite workpiece while the composite workpiece has a shape that is different than the as-built shape. 
     Moreover, the principles and implementations of the system  100  disclosed herein enable the digital model to be updated after a machining operation is performed, such that the digital model is representative of an as-machined condition of the composite workpiece  102 . For the purpose of the present disclosure, the term “as-machined,” such as in reference to the as-machined condition the composite workpiece  102 , refers to a condition of the composite workpiece  102  after a machining operation is performed on the composite workpiece  102 . As such, the principles and implementations of the system  100  disclosed herein also enable determinate assembly or predictive assembly of the composite workpiece  102  based on the digital model of the composite workpiece  102 , which is updated throughout post-cure processing of the composite workpiece  102 . 
     Referring now to  FIG.  1   , which schematically illustrates a manufacturing environment  200 . The manufacturing environment  200  facilitates post-cure processing of the composite workpiece  102 , such as machining, trimming, coating, painting, sub-assembly (e.g., assembly of other parts or components to the composite workpiece  102 ), and the like. Generally, the manufacturing environment  200  includes a plurality of work cells  202 , identified individually as a first work cell  204 , a second work cell  206 , a third work cell  208 , a fourth work cell  210 , a fifth work cell  212 , etc. Each one of the work cells  202  facilitates or corresponds to a different post-cure processing operation associated with the manufacture of the composite workpiece  102 . In one or more examples, each one of the work cells  202  includes one or more systems, apparatuses, and/or machines that perform at least one post-cure processing operation. In one or more examples, the work cells  202  are interlinked (e.g., in series or parallel) and cooperate to automate at least a portion of the fabrication process. 
     The system  100  is associated with one of the work cells  202  and forms a sub-system of the manufacturing environment  200 . In one or more examples, the system  100  is associated with the first work cell  204  and facilitates an initial post-cure processing operation performed on the composite workpiece  102 . For example, after the composite workpiece  102  is cured (e.g., by a curing apparatus, such as an oven or autoclave), the composite workpiece  102  is transported to the first work cell  204  on the tool  104 , upon which it was cured. 
     Referring now to  FIG.  2   , which schematically illustrates an example of the system  100 . In one or more examples, the system  100  includes the tool  104 . The tool  104  includes a tool surface  106 . The tool surface  106  supports the composite workpiece  102  located on the tool  104 . The system  100  also includes a drill template  112 . The drill template  112  defines a drilling location  116  for drilling a hole  118 , such as a dependent-determinant assembly hole, through the composite workpiece  102  while the composite workpiece  102  is on the tool  104 . Generally, the drilling location  116  is a desired location of the hole  118  to be drilled through the composite workpiece  102 . 
     The drill template  112  enables the hole  118  to be drilled through the composite workpiece  102  at the drilling location  116 , as desired or as predetermined based on manufacturing design, while the composite workpiece  102  is on the tool  104  and while in the as-built condition (e.g., having the as-built shape). 
     In one or more examples, the hole  118  is intended for use as, or serves as, any one of various types of holes. In one or more examples, the hole  118  is a determinate assembly hole that is used for a subsequent assembly operation to couple another component or structure to the composite workpiece  102  or to couple the composite workpiece  102  to another structure. In one or more examples, the hole  118  is used as an indexing feature for indexing the composite workpiece  102  in a subsequent one of the plurality of work cells  202  for performance of a subsequent post-cure processing operation. In one or more examples, the hole  118  is used as a carrying feature, such for attachment of the composite workpiece  102  to a material handler (e.g., an overhead material handler  158  as illustrated in  FIGS.  12  and  15   ). 
     In one or more examples, the tool  104  includes a sacrificial portion  128 . The sacrificial portion  128  of the tool  104  is disposed on, or forms a portion of, the tool surface  106 . The drill template  112  indexes the drilling location  116  to the sacrificial portion  128  of the tool  104 . 
     In one or more examples, the system  100  also includes a drill  120  to drill the hole  118  through the composite workpiece  102  at the drilling location  116 , defined by the drill template  112 , while the composite workpiece  102  is on the tool  104 . The drill  120  includes a drill bit  122 . The sacrificial portion  128  of the tool  104  receives (e.g., is penetrated by) a portion of the drill bit  122  after the drill bit  122  passes through the composite workpiece  102  when drilling the hole  118  through the composite workpiece  102 . In other words, the sacrificial portion  128  defines a portion (e.g., a drill-penetration portion) of the tool  104  that is designed or that is intended to be drilled while the hole  118  is being drilled through the composite workpiece  102 . For example, a portion of the drill bit  122  extends into the sacrificial portion  128  when drilling the hole  118  through the composite workpiece  102 . 
     Referring to  FIG.  3   , which schematically illustrates an example of the tool  104 . Generally, the sacrificial portion  128  is formed in, is disposed on, or otherwise forms a portion of the tool surface  106 . In one or more examples, the tool  104  includes a plurality of sacrificial portions  160 . The sacrificial portion  128  (e.g., any one of a plurality of sacrificial portions  160 ) may be located at any suitable location on the tool surface  106 . Generally, the sacrificial portion  128  corresponds to a desired location of the hole  118  to be drilled through the composite workpiece  102 . 
     The sacrificial portion  128  may have any geometry and/or dimensions suitable to receive, or to be penetrated by, a portion of the drill bit  122  when drilling the hole  118  through the composite workpiece  102 . For example, the sacrificial portion  128  includes a two-dimensional geometry in plan view (e.g., as shown in  FIG.  3   ) and a two-dimensional geometry in section view (e.g., as shown in  FIG.  4   ). The two-dimensional geometry of the sacrificial portion  128  in plan view defines a width dimension and length dimension of the sacrificial portion  128 . The two-dimensional geometry of the sacrificial portion  128  in section view defines a depth dimension of the sacrificial portion  128 . 
     The illustrative examples show the sacrificial portion  128  as being configured to receive a portion of the drill bit  122  during a drilling operation, for example, as having a circular shape in plan view and approximately rectangular shape in section view. However, the principles and implementation of the sacrificial portion  128  may be applied to other machining operations performed on the composite workpiece  102 , while on the tool  104 , by other types of machining tools. For example, the sacrificial portion  128  may have an elongate (e.g., long and narrow) rectangular shape in plan view and be configured to receive a router bit or cutting blade during a milling, cutting, or trimming operation. Alternatively, in one or more examples, the sacrificial portion  128  may have the elongate rectangular shape in plan view and be configured to receive a portion of the drill bit  122  during a drilling operation. In these examples, the desired location of the hole  118  to be drilled through the composite workpiece  102  (e.g., the drilling location  116 ) is located along the sacrificial portion  128 . 
     Referring to  FIG.  4   , which schematically illustrates an example of a portion of the tool  104  and a portion of the composite workpiece  102  on the tool  104  before the hole  118  is drilled through the composite workpiece  102 . In one or more examples, the sacrificial portion  128  of the tool  104  includes a recess  124  formed in the tool surface  106 , for example, formed in the tool  104  and depending from the tool surface  106 . The sacrificial portion  128  also includes a sacrificial material  126  located within the recess  124 . The sacrificial material  126  includes, or forms, a top surface  170  of the sacrificial portion  128 . The top surface  170  of the sacrificial portion  128  is substantially flush with, or forms a portion of, the tool surface  106 . In one or more examples, a portion of the drill bit  122  penetrates the recess  124 , drilling the sacrificial material  126 , when drilling the hole  118  through the composite workpiece  102 , according to the drill template  112 , while the composite workpiece  102  is on the tool  104 . 
     The sacrificial material  126  includes, or is made from, any material suitable for application within the recess  124  and for use as a curing surface for a composite layup that is cured on the tool  104 . For example, the sacrificial material  126  fills the recess  124  and hardens such that the top surface  170  of the sacrificial portion  128  is compatible with and forms a portion of the tool surface  106 . In one or more examples, the sacrificial material  126  is a potting compound. However, any one of various other types of materials may be used for the sacrificial material  126 . 
     As illustrated in  FIG.  4   , the composite workpiece  102  includes a first surface  108  and a second surface  110 , which is opposite the first surface  108 . In one or more examples, the first surface  108  defines an outer mold line of the composite workpiece  102  and the second surface  110  defines an inner mold line of the composite workpiece  102 . In one or more examples, the first surface  108  defines the inner mold line of the composite workpiece  102  and the second surface  110  defines the outer mold line of the composite workpiece  102 . 
     The tool surface  106  supports, or is in contact with, the first surface  108  of the composite workpiece  102 . Additionally, the top surface  170  of the sacrificial portion  128  is in contact with a portion of the first surface  108  of the composite workpiece  102 . The drilling location  116  (e.g., the desired location for the hole  118  to be drilled through the composite workpiece  102 ) is located over the sacrificial portion  128  of the tool  104 . 
     Referring now to  FIG.  5   , which schematically illustrates an example of the tool  104  and the composite workpiece  102  on the tool  104  before the hole  118  is drilled through the composite workpiece  102 . Generally, the composite workpiece  102  is fabricated from a composite layup (e.g., a composite laminate or composite preform) that is cured on the tool  104 . As such, in one or more examples, in addition to the tool  104  serving as a support structure for machining the composite workpiece  102 , the tool  104  also serves as a cure tool and the tool surface  106  serves as a cure surface that supports the composite layup during cure. 
     Generally, the composite layup includes a plurality of plies (e.g., layers) of a composite material. Each ply of composite material may take the form of a composite sheet or a series of lengths of composite tape. The composite material includes a reinforcement material (e.g., carbon fiber, glass fiber, aramid fiber, and the like) that is embedded in a matrix binding material (e.g., a polymeric matrix, a thermoset plastic, a thermoplastic, a resin, and the like). 
     In one or more examples, the composite layup is formed on the tool  104 . As such, in one or more examples, the tool  104  also serves as a layup tool or mandrel and the tool surface  106  serves as a layup surface that supports the composite layup during fabrication and that shapes the composite layup. However, in other examples, the composite layup may be fabricated on a dedicated layup tool and transferred to the tool  104  for cure and subsequent machining on the tool  104  after cure. 
     As illustrated in  FIG.  5   , in one or more examples, the composite workpiece  102  includes a plurality of drilling locations  162 . The drilling location  116  (e.g., any one of the plurality of drilling locations  162 ) may be located at any suitable location on the composite workpiece  102 , as defined by the drill template  112 . The drilling location  116  (e.g., any one of the plurality of drilling locations  162 ) is aligned with or indexed to the sacrificial portion  128  (e.g., a corresponding one of the plurality of sacrificial portions  160 ) of the tool  104 . 
     Referring now to  FIG.  6   , which schematically illustrates an example of the tool  104  and the composite workpiece  102  on the tool  104  after the hole  118  is drilled through the composite workpiece  102 . In one or more examples, the composite workpiece  102  includes a plurality of holes  186 . The hole  118  (e.g., any one of the plurality of holes  186 ) is located at any suitable location on the composite workpiece  102  according to the drilling location  116  (e.g., a corresponding one of the plurality of drilling locations  162 ) defined by the drill template  112 . 
     Referring now to  FIGS.  7   , which schematically illustrates an example of the tool  104 , the composite workpiece  102  on the tool  104 , and the drill template  112  used to locate the drilling location  116  relative to the composite workpiece  102 . In one or more examples, the drill template  112  is a physical template, which is coupled to the tool  104 . In one or more examples, the drill template  112  includes a template body  178 . The template body  178  is coupled to the tool  104 . The drill template  112  also includes a drill guide  114  formed in the template body  178 . The drill guide  114  defines, or locates, the drilling location  116  relative to the composite workpiece  102 . For example, the drill guide  114  locates a drilling axis of the drill bit  122  relative to the composite workpiece  102 . With the drill template  112  coupled to the tool  104 , the template body  178  is indexed relative to the tool  104 . The template body  178  thereby indexes the drill guide  114  relative to the composite workpiece  102  and relative to the tool  104  such that the drilling location  116  is aligned with the sacrificial portion  128  of the tool  104 . 
     In one or more examples, the drill guide  114  includes, or is formed by, a template hole  192 . The template hole  192  is formed, or extends, through the template body  178 . The drill guide  114  (e.g., the template hole  192 ) receives and guides the drill bit  122  when drilling the hole  118  through the composite workpiece  102  on the tool  104 . 
     In one or more examples, the template body  178  locates the drill guide  114  (e.g., the template hole  192 ) relative to the second surface  110  of the composite workpiece  102 . With the drill template  112  coupled to the tool  104 , the template body  178  indexes the drill guide  114  (e.g., the template hole  192 ) relative to the tool  104  and to the composite workpiece  102  such that the drilling location  116  is at the desired location on the composite workpiece  102  and is aligned with the sacrificial portion  128  of the tool  104 . 
     In one or more examples, the drill guide  114  includes a plurality of template holes  188 . Each one of the plurality of template holes  188  corresponds to, or defines, a corresponding one of the plurality of drilling locations  162 . Each one of the plurality of template holes  188  is indexed to or is aligned with a corresponding one of the plurality of sacrificial portions  160  of the tool  104 . 
     In one or more examples, the system  100  includes a plurality of drill templates  190 . In one or more examples, each one of the plurality of drill templates  190  is coupled to the tool  104 . Each one of the plurality of drill templates  190  is designed or configured to index the drill guide  114  to a corresponding one of the plurality of sacrificial portions  160 , for example, based on the design and/or geometry of the tool  104  and/or of the composite workpiece  102 . 
     Referring now to  FIG.  8   , which schematically illustrates an example of a portion of the tool  104 , a portion of the composite workpiece  102  on the tool  104 , and the drill template  112  coupled to the tool  104  and used to locate the drilling location  116  relative to the composite workpiece  102 . In one or more examples, the drill template  112  is indexed relative to the tool  104  such that the drill guide  114  is aligned with (e.g., over) the sacrificial portion  128  of the tool  104 . Indexing the drill template  112  enables the drill template  112  to be repeatably and consistently used with the tool  104  to locate the drill guide  114  over the sacrificial portion  128  of the tool  104 . 
     In one or more examples, the tool  104  includes a first template-indexing feature  130 . The drill template  112  includes a second template-indexing feature  132 . The second template-indexing feature  132  mates with the first template-indexing feature  130  to index the drill template  112  relative to the tool  104  and to index the drill guide  114  relative to the tool  104  and to the composite workpiece  102  at the drilling location  116 . For example, the mating of the first template-indexing feature  130  and the second template-indexing feature  132  locates the template hole  192  adjacent to the second surface  110  of the composite workpiece  102  and aligns the template hole  192  with the sacrificial portion  128  of the tool  104 . 
     In one or more examples, one of the first template-indexing feature  130  or the second template-indexing feature  132  is a male feature and the other one of the first template-indexing feature  130  or the second template-indexing feature  132  is a female feature that receives and mates with the male feature. For example, one of the first template-indexing feature  130  or the second template-indexing feature  132  is a pin, protrusion, or other projection and the other one of the first template-indexing feature  130  or the second template-indexing feature  132  is an aperture, recess, or other opening. 
     In one or more examples, the drill template  112  is coupled to the tool  104  using the first template-indexing feature  130  and the second template-indexing feature  132 . In one or more examples, one of the first template-indexing feature  130  or the second template-indexing feature  132  is first component of a mechanical fastener, such as a threaded bolt, and the other one of the first template-indexing feature  130  or the second template-indexing feature  132  is a second component of the mechanical fastener, such as a nut or internally threaded aperture. 
     Referring now to  FIGS.  9  and  10   , which schematically illustrate examples of a portion of the tool  104 , a portion of the composite workpiece  102  on the tool  104 , and the drill template  112  used to locate the drilling location  116  relative to the composite workpiece  102 . In one or more examples, the tool  104  also includes a side surface  136 . The side surface  136  extends from the tool surface  106 . In one or more examples, the drill template  112  is coupled to the side surface  136  and extends over the second surface  110  of the composite workpiece  102  while the composite workpiece  102  is on the tool  104 . For example, the template body  178  is coupled to the side surface  136  of the tool  104  and extends over the second surface  110  of the composite workpiece  102  to locate the drill guide  114  over the sacrificial portion  128  of the tool  104 . 
     In one or more examples, the template body  178  of the drill template  112  includes a first template-portion  138 , a second template-portion  140 , and a third template-portion  142 . The first template-portion  138  is coupled to the tool  104 , such as to the side surface  136  of the tool  104 . The second template-portion  140  extends approximately perpendicular from the first template-portion  138 . The third template-portion  142  extends from the second template-portion  140 . The second template-portion  140  is located over the second surface  110  of the composite workpiece  102  while the composite workpiece  102  is on the tool  104 . The third template-portion  142  is located proximate to the second surface  110  of the composite workpiece  102  while the composite workpiece  102  is on the tool  104 . The drill guide  114  is formed by, or forms a portion of, the third template-portion  142 . In an example, the template hole  192  is formed through the third template-portion  142 . 
     Referring now to  FIG.  11   , which schematically illustrates an example of a portion of the composite workpiece  102 , the drill template  112 , and the drill  120 . In one or more examples, the drill guide  114  of the drill template  112  includes a drill bushing  134 . The drill bushing  134  forms, or is located in, the template hole  192 . In an example, the drill bushing  134  is coupled to the third template-portion  142 . The drill bushing  134  receives a portion of the drill bit  122  and guides the drill bit  122  when drilling the hole  118  through the composite workpiece  102  while the composite workpiece  102  is on the tool  104 . 
     Referring now to  FIG.  12   , which schematically illustrates an example of the system  100  and the first work cell  204  to which the system  100  is associated. In one or more examples, the system  100  includes a scanner  144 . The scanner  144  scans and digitizes at least a portion of the composite workpiece  102  while the composite workpiece  102  is on the tool  104 . In one or more examples, the scanner  144  scans and digitizes at least the second surface  110  of the composite workpiece  102  while the composite workpiece  102  is on the tool  104 . 
     The scanner  144  is any one of various types of three-dimensional (3D) scanners. In one or more examples, the scanner  144  includes, or is, a photogrammetric scanner  148  (e.g., as shown in  FIG.  11   ), such as a photogrammetric camera. In other examples, the scanner  144  includes, or is, one of a laser triangulation scanner, a structured light scanner, other laser-based scanners or metrology systems, and the like. 
     The scanner  144  captures the geometry (e.g., size and shape), contour (e.g., curvature), physical features (e.g., holes, edges, etc.), and other details of the composite workpiece  102 . Scan data  216  generated the scanner  144  is used by a computer to form a workpiece model  150 . The workpiece model  150  is a digital three-dimensional representation of the composite workpiece  102 . 
     Referring to  FIGS.  2  and  12   , in one or more examples, the system  100  also includes a computing device  146 . The computing device  146  is adapted to generate and/or manipulate the workpiece model  150  based on the scan data  216  generated by the scanner. The workpiece model  150  is representative of at least a portion of the composite workpiece  102  in the as-built shape. 
     The computing device  146  may include a single computer or several interconnected computers. For example, the computing device  146  may include any collection of computing devices that individually or jointly execute a set (or multiple sets) of instructions to implement any one or more of the operations discussed herein. The computing device  146  includes a processor  220  (e.g., at least one processing unit) that is coupled to memory  194 . The memory  194  includes program code  196  that is executable by the processor  220  to perform one or more operations. Generally, as used herein, the phrase “the computing device  146  is adapted to” refers to the computing device  146  being configured or otherwise operable to perform a function, such as the program code  196  being executed by the processor  220  to perform a desired operation or function. The program code  196  is any coded instructions that is (e.g., computer readable and/or machine readable. The memory  194  is any a non-transitory computer readable and/or machine readable medium, such as a hard disk drive, flash memory, read-only memory, a compact disk, a digital versatile disk, a cache, random-access memory, and/or any other storage device or storage disk in which information is stored for any duration (e.g., for extended time periods, permanently, for brief instances, for temporarily buffering, and/or for caching of the information). 
     In one or more examples, the workpiece model  150  is representative of the geometry of the second surface  110  of the composite workpiece  102  as on the tool  104  (e.g., with the composite workpiece  102  having the as-built shape). For example, the workpiece model  150  is representative of the size, the shape, and the contour of the second surface  110  of the composite workpiece  102  as on the tool  104  (e.g., in the as-built condition on the tool  104 ) relative to a reference frame  168  (e.g., as shown in  FIG.  12   ). In one or more examples, the reference frame  168  is a workpiece reference frame. 
     In one or more examples, the composite workpiece  102  is digitized, the scan data  216  is generated, and the workpiece model  150  is created before the hole  118  is drilled through the composite workpiece  102 . In one or more examples, the composite workpiece  102  is digitized, the scan data  216  is generated, and the workpiece model  150  is created, or modified, after the hole  118  is drilled through the composite workpiece  102 . As such, in one or more examples, the workpiece model  150  is also representative of a location and geometry of the hole  118  relative to the reference frame  168 . 
     Referring now to  FIG.  13   , which schematically illustrates an example of the tool  104 , the composite workpiece  102  on the tool  104 , and an automated drilling machine  182 . In one or more examples, the system  100  automatically or semi-automatically drills the hole  118  through the composite workpiece  102  at the drilling location  116  while the composite workpiece  102  is on the tool  104 . In such examples, the system  100  includes the automated drilling machine  182 . 
     In one or more examples, the automated drilling machine  182  includes a robotic arm  198  or other programmable movement mechanism. The drill  120  is coupled to an end (e.g., an end effector) of the robotic arm  198 . The robotic arm  198  selectively and controllably moves the drill  120  in three-dimensional space, for example, relative to the tool  104  and relative to the composite workpiece  102 . The automated drilling machine  182  receives instructions from the computing device  146 . For example, the automated drilling machine  182  may operate according to a numerical control (NC) program (e.g., program code  196 ) executed by the computing device  146  to automatically locate the drill  120  at the drilling location  116  and to drill the hole  118  through the composite workpiece  102  at the drilling location  116 . 
     Referring now to  FIG.  14   , which schematically illustrates an example of the workpiece model  150 . In one or more examples, such as examples in which the drilling operation is performed automatically using the automated drilling machine  182 , the drill template  112  is, or takes the form of, a virtual template  180  (e.g., a no-physical template). For example, the virtual template  180  is carried out, accessed, and/or stored by means of the computing device  146 , such as made by software (e.g., the program code  196 ). The workpiece model  150  and the virtual template  180  are used by the computing device  146  to determine the drilling location  116  on the composite workpiece  102 . 
     In one or more examples, the computing device  146  is adapted to locate the virtual template  180  relative to the workpiece model  150  such that a virtual drill guide  184  of the virtual template  180  is indexed to the sacrificial portion  128  of the tool  104 . The computing device  146  is also adapted to determine the drilling location  116  relative to the reference frame  168  based on the virtual drill guide  184 . The computing device  146  is further adapted to instruct the automated drilling machine  182  to drill the hole  118  at the drilling location  116 . 
     In one or more examples, the computing device  146  is adapted to perform various transforms (e.g., rigid body transforms and/or coordinate frame transforms) and/or other data manipulation operations to virtually locate the workpiece model  150  relative to a tool model  218  that represents the location of the composite workpiece  102  relative to the tool  104 . The computing device  146  is also adapted to perform various transforms and/or other data manipulation operations to virtually locate the virtual template  180  relative to the tool model  218  such that the virtual drill guide  184  is aligned with the location of the sacrificial portion  128  of the tool  104  represented by the tool model  218 . With the workpiece model  150  and the virtual template  180  located relative to the tool model  218 , the computing device  146  determines the drilling location  116  (e.g., XYZ-coordinates) relative to the reference frame  168 . The computing device  146  is also adapted to modify the NC program and/or compensate an NC machine reference frame based on the drilling location  116 . 
     The tool model  218  is representative of the geometry, contour, and physical features of the tool  104 , such as the geometry and location of the sacrificial portion  128 , relative to a tool reference frame. In one or more examples, the tool  104  is digitized by the scanner  144  before the composite workpiece  102  is located on the tool surface  106 . 
     Referring again to  FIG.  13   , in one or more examples, the automated drilling machine  182  is indexed to the tool  104  before being instructed to drill the hole  118  through the composite workpiece  102  on the tool  104 . In one or more examples, the tool  104  includes a tool-indexing feature  154 . The automated drilling machine  182  includes a machine-indexing feature  214 . The machine-indexing feature  214  is configured to mate with the tool-indexing feature  154  to index the automated drilling machine  182  relative to the tool  104 . 
     In one or more examples, the machine-indexing feature  214  includes at least one projection (e.g., a fork) and the tool-indexing feature  154  includes at least one opening (e.g., a mouse hole) that is configured to receive the machine-indexing feature  214 . However, in other examples, the machine-indexing feature  214  and the tool-indexing feature  154  may include, or take the form of, any one of various other physical indexing structures (e.g., probes, indexing pins, etc.) or visual indexing features (e.g., optical targets and vision-based or laser-based detectors). 
     Referring now to  FIG.  15   , which schematically illustrates an example of the composite workpiece  102  and the second work cell  206  of the manufacturing environment  200 , in which a subsequent post-cure processing operation is performed on the composite workpiece  102 . In one or more examples, the workpiece model  150  is used to index the composite workpiece  102  to the second work cell  206  for a subsequent processing operation. 
     In one or more examples, the composite workpiece  102  is loaded in the second work cell  206 . For example, the composite workpiece  102  is mounted to or is otherwise secured a tooling fixture  172 . The composite workpiece  102  (e.g., as held by the tooling fixture  172 ) is then measured, scanned, or otherwise digitized in the second work cell  206  and a second workpiece model (e.g., a second three-dimensional model) of the composite workpiece  102  is generated that represents the position (e.g., location and orientation) and shape (e.g., contour) of the composite workpiece  102  in the second work cell  206  (e.g., relative to a work-cell reference frame  174 ). The second three-dimensional model is compared to the workpiece model  150  at an indexed position relative to the work-cell reference frame  174  and the composite workpiece  102  is conformed to the indexed position based on this comparison. 
     Referring to  FIGS.  12  and  15   , in one or more examples, the system  100  includes a material loader  152  (e.g., as shown in  FIG.  12   ). The material loader  152  removes (e.g., separates and demolds) the composite workpiece  102  from the tool  104 . In one or more examples, the system  100  also includes an overhead material handler  158 . The overhead material handler  158  receives the composite workpiece  102  from the material loader  152  and transports the composite workpiece  102  from the first work cell  204  (e.g., as shown in  FIG.  12   ) to the second work cell  206  for the subsequent processing operation. The overhead material handler  158  may also transport the composite workpiece  102  from the second work cell  206 , following the processing operation, to the third work cell  208  for performance of a subsequent processing operation, and so on. 
     Referring to  FIG.  12   , in one or more examples, the material loader  152  is indexed to the tool  104  before removing the composite workpiece  102  from the tool  104 . In one or more examples, the material loader  152  includes a loader-indexing feature  156 . The loader-indexing feature  156  is configured to mate with the tool-indexing feature  154  to index the material loader  152  relative to the tool  104 . 
     In one or more examples, the loader-indexing feature  156  includes at least one projection (e.g., a fork) and the tool-indexing feature  154  includes at least one opening (e.g., a mouse hole) that is configured to receive the loader-indexing feature  156 . However, in other examples, the loader-indexing feature  156  and the tool-indexing feature  154  may include, or take the form of, any one of various other physical indexing structures (e.g., probes, indexing pins, etc.) or visual indexing features (e.g., optical targets and vision-based or laser-based detectors). 
     Referring to  FIG.  15   , in one or more examples, the overhead material handler  158  includes a support beam  164 . The overhead material handler  158  also includes a hanger  166 . The hanger  166  is connected to the support beam  164  and to the composite workpiece  102  such that the composite workpiece  102  is suspended from the support beam  164 . In one or more examples, the hanger  166  is connected to the composite workpiece  102  at, or using, the hole  118  such that the composite workpiece  102  is suspended from the hanger  166  by the hole  118 . 
     The present disclosure is also directed to a method for post-cure processing the composite workpiece  102  using the system  100 . The present disclosure is also directed to a composite workpiece  102  that includes the hole  118 , or the plurality of holes  186 ) formed while the composite workpiece  102  is on the tool  104  using the system  100 . 
     Referring now to  FIG.  16   , which illustrates an example of a method  1000  for post-cure processing of the composite workpiece  102 . In one or more examples, the method  1000  is implemented using the system  100 . 
     In one or more examples, the method  1000  includes a step of (block  1002 ) forming the sacrificial portion  128  of the tool  104 . In one or more examples, step of (block  1002 ) forming the sacrificial portion  128  includes a step of filling the recess  124  formed in the tool surface  106  of the tool  104  with the sacrificial material  126  such that the top surface  170  of the sacrificial material  126  (e.g., of the sacrificial portion  128 ) is flush with and forms a portion of the tool surface  106 . 
     In one or more examples, the method  1000  includes a step of (block  1004 ) forming the composite layup on the tool surface  106  of the tool  104 . Alternatively, the method includes a step of forming the composite layup on a dedicate layup tool and a step of transferring the composite layup to the tool  104  for curing. 
     In one or more examples, the method  1000  includes a step of ( 1006 ) curing the composite layup (e.g., an uncured or “green” composite) on the tool  104  to form the composite workpiece  102  (e.g., a cured composite). 
     In one or more examples, the method  1000  includes a step of (block  1008 ) supporting the composite workpiece  102  on the tool surface  106  of the tool  104 . 
     In one or more examples, the method  1000  includes a step of (block  1010 ) defining the drilling location  116  on the composite workpiece  102  while the composite workpiece  102  is on the tool  104  using the drill template  112 . In one or more examples, the step of (block  1010 ) defining the drilling location  116  is performed (e.g., determined) physically using the template body  178 , coupled to the tool  104 , and the drill guide  114 , located over the sacrificial portion  128  of the tool  104 . In one or more examples, step of (block  1010 ) defining the drilling location  116  is performed (e.g., determined) virtually using the virtual template  180 . 
     In one or more examples, the method  1000  includes a step of (block  1012 ) indexing the drilling location  116  to the sacrificial portion  128  of the tool  104 . In one or more examples, step of (block  1012 ) indexing the drilling location  116  to the sacrificial portion  128  is performed physically by coupling the template body  178  to the tool  104 . In one or more examples, step of (block  1012 ) indexing the drilling location  116  to the sacrificial portion  128  is performed virtually using the workpiece model  150 , the tool model  218 , and the virtual template  180 . 
     In one or more examples, the step of (block  1012 ) indexing the drilling location  116  to the sacrificial portion  128  of the tool  104  includes a step of indexing the drill template  112  to the tool  104  (e.g., coupling the template body  178  to the tool  104 ) to align the drill guide  114  (e.g., the template hole  192 ) of the drill template  112  with the sacrificial portion  128  of the tool  104 . 
     In one or more examples, the step of (block  1012 ) indexing the drilling location  116  to the sacrificial portion  128  of the tool  104  includes a step of indexing the virtual template  180  relative to the workpiece model  150  such that the virtual drill guide  184  is aligned with the sacrificial portion  128  of the tool  104  and a step of determining the drilling location  116  relative to the reference frame  168  based on the virtual drill guide  184 . 
     In one or more examples, the method  1000  includes a step of (block  1014 ) drilling the hole  118  through the composite workpiece  102  at the drilling location  116 , defined by the drill template  112 , while the composite workpiece  102  is on the tool  104 . In one or more examples, step of (block  1014 ) drilling the hole  118  through the composite workpiece  102  is performed manually using the drill  120 . In one or more examples, the step of (block  1014 ) drilling the hole  118  through the composite workpiece  102  is performed automatically or semi-automatically using the automated drilling machine  182 , such as by instructing the automated drilling machine  182  to automatically drill the hole  118  through the composite workpiece  102  on the tool  104  at the drilling location  116 . 
     In one or more examples, the method  1000  includes a step of (block  1016 ) drilling the sacrificial portion  128  of the tool  104  while drilling the hole  118  through the composite workpiece  102  while the composite workpiece  102  is on the tool  104 . In one or more examples, the step of (block  1016 ) drilling the sacrificial portion  128  of the tool  104  includes a step of drilling the sacrificial material  126  of the sacrificial portion  128  and a step of penetrating the recess  124  of the sacrificial portion  128 . 
     In one or more examples, the method  1000  includes a step of (block  1018 ) digitizing at least a portion the composite workpiece  102  while the composite workpiece  102  is on the tool  104 . 
     In one or more examples, the step of (block  1018 ) digitizing the composite workpiece  102  is performed before the step of (block  1014 ) drilling the hole  118  through the composite workpiece  102  on the tool  104 . In these examples, the workpiece model  150  is representative of at least the contour of the second surface  110  of the composite workpiece  102  relative to the reference frame  168 . 
     In one or more examples, the step of (block  1018 ) digitizing the composite workpiece  102  is performed (or is performed again) after the step of (block  1014 ) drilling the hole  118  through the composite workpiece  102 . In these examples, the workpiece model  150  is also representative of the location of the hole  118  relative to the reference frame  168 . 
     In one or more examples, the method  1000  includes a step of (block  1020 ) generating the workpiece model  150  that is representative of at least a portion of the composite workpiece  102 , such as of at least the contour of the composite workpiece  102  as on the tool  104 . 
     In one or more examples, the method  1000  includes a step of (block  1022 ) demolding the composite workpiece  102  from the tool  104 . In one or more examples, the step of (block  1022 ) demolding the composite workpiece  102  includes a step of separating the composite workpiece  102  from the tool surface  106  and a step of removing the composite workpiece  102  from the tool  104 . In one or more examples, the step of (block  1022 ) is preformed automatically or semi-automatically using the material loader  152 . In one or more examples, the step of (block  1022 ) is performed manually. 
     In one or more examples, the method  1000  includes a step of (block  1024 ) transferring the composite workpiece  102  to a subsequent work cell (e.g., the second work cell  206 ) for performance of a subsequent post-cure processing operation. In one or more examples, the step of (block  1024 ) transferring the composite workpiece  102  includes a step of transferring the composite workpiece  102  from the tool  104  to the overhead material handler  158  and a step of moving the composite workpiece  102  to the subsequent work cell using the overhead material handler  158 . In one or more examples, the step of transferring the composite workpiece  102  from the tool  104  to the overhead material handler  158  is performed using the material loader  152 . In one or more examples, transferring the composite workpiece  102  from the tool  104  to the overhead material handler  158  is performed manually. In one or more examples, the step of transferring the composite workpiece  102  to the overhead material handler  158  includes a step of coupling the hanger  166  of the overhead material handler  158  to the composite workpiece  102  using the hole  118  drilled through the composite workpiece  102  and a step of suspending the composite workpiece  102  from the support beam  164  of the overhead material handler  158 . 
     In one or more examples, the method  1000  includes a step of transferring the composite workpiece  102  from the overhead material handler  158  to the tooling fixture  172  located in the subsequent work cell (e.g., the second work cell  206  as shown in  FIG.  13   ). In one or more examples, the method  1000  includes a step of performing the subsequent processing operation (e.g., a machining operation, a trimming operation, a coating operation, and the like) on the composite workpiece  102  while the composite workpiece  102  is on, or is being held by, the tooling fixture  172 . 
     In one or more examples, the method  1000  includes a step of (block  1026 ) indexing the composite workpiece  102  to the subsequent work cell (e.g., the second work cell  206 ) for the subsequent processing operation by conforming the workpiece model  150  to the work-cell reference frame  174 . In one or more examples, the step of (block  1026 ) indexing the composite workpiece  102  includes a step of conforming the composite workpiece  102  to the workpiece model  150 . 
     In one or more examples, the method  1000  includes a step of reforming (e.g., replacing or repairing) the sacrificial portion  128  of the tool  104  after the hole  118  is drilled through the composite workpiece  102 , after the composite workpiece  102  is removed (e.g., demolded) from the tool  104 , and before a subsequent composite workpiece is located on the tool  104 . For example, remnants of the sacrificial material  126  are removed and/or cleaned from within the recess  124  and the sacrificial material  126  is replaced to fill the recess  124 . 
     The present disclosure is also directed to a system of post-cure processing the composite workpiece  102  implemented according to the method  1000 . The present disclosure is further directed to the composite workpiece  102  that includes the hole  118  or the plurality of holes  186  formed while the composite workpiece  102  is on the tool  104  according to the method  1000 . 
     Referring now to  FIGS.  17  and  18   , examples of the system  100 , the method  1000 , and the composite workpiece  102  may be related to, or used in the context of, an aircraft manufacturing and service method  1100 , as shown in the flow diagram of  FIG.  17    and the aircraft  1200 , as schematically illustrated in  FIG.  18   . For example, the aircraft  1200  and/or the aircraft production and service method  1100  may utilize the composite workpiece  102  that is machined using the system  100 , described herein and illustrated in  FIGS.  1 - 15   , and/or according to the method  1000 , described herein and illustrated in  FIG.  16   . 
     Referring to  FIG.  18   , examples of the aircraft  1200  may include an airframe  1202  having the interior  1206 . The aircraft  1200  also includes a plurality of high-level systems  1204 . Examples of the high-level systems  1204  include one or more of a propulsion system  1208 , an electrical system  1210 , a hydraulic system  1212 , and an environmental system  1214 . In other examples, the aircraft  1200  may include any number of other types of systems, such as a communications system, a flight control system, a guidance system, a weapons system, and the like. In one or more examples, the composite workpiece  102  made (e.g., machined and/or processed) using the system  100  and/or according to the method  1000  forms a component of the airframe  1202 , such as a wing  1220 , a fuselage  1218 , a panel, a stringer, a spar, and the like. 
     Referring to  FIG.  17   , during pre-production, the service method  1100  includes specification and design of the aircraft  1200  (block  1102 ) and material procurement (block  1104 ). During production of the aircraft  1200 , component and subassembly manufacturing (block  1106 ) and system integration (block  1108 ) of the aircraft  1200  take place. Thereafter, the aircraft  1200  goes through certification and delivery (block  1110 ) to be placed in service (block  1112 ). Routine maintenance and service (block  1114 ) includes modification, reconfiguration, refurbishment, etc. of one or more systems of the aircraft  1200 . 
     Each of the processes of the service method  1100  illustrated in  FIG.  17    may be performed or carried out by a system integrator, a third party, and/or an operator (e.g., a customer). For the purposes of this description, a system integrator may include, without limitation, any number of spacecraft 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, leasing company, military entity, service organization, and so on. 
     Examples of the system  100  and the method  1000  shown and described herein may be employed during any one or more of the stages of the manufacturing and service method  1100  shown in the flow diagram illustrated by  FIG.  17   . In an example, manufacture of the composite workpiece  102  in accordance with the method  1000  and/or using the system  100  may form a portion of component and subassembly manufacturing (block  1106 ) and/or system integration (block  1108 ). Further, the composite workpiece  102  manufactured in accordance with the method  1000  and/or using the system  100  may be utilized in a manner similar to components or subassemblies prepared while the aircraft  1200  is in service (block  1112 ). Also, the composite workpiece  102  manufactured in accordance with the method  1000  and/or using the system  100  may be utilized during system integration (block  1108 ) and certification and delivery (block  1110 ). Similarly, manufacture of the composite workpiece  102  in accordance with the method  1000  and/or using the system  100  may be utilized, for example and without limitation, while the aircraft  1200  is in service (block  1112 ) and during maintenance and service (block  1114 ). For example, spare and or replacement composite parts may be fabricated in accordance with the method  1000  and/or using the system  100 , which may be installed due to a prescribed maintenance cycle or after a realization of damage to a composite part. 
     In can be appreciated that performing at least a portion of the post-cure processing operation on the composite workpiece  102  while the composite workpiece  102  is on the tool  104 , using the workpiece model  150  to index the composite workpiece  102  in one or more of the plurality of work cells  202 , and updating the workpiece model  150  after each subsequent processing operation may improve the accuracy and speed of the processing operation and enable determinate or predictive assembly of the composite workpiece  102 . 
     Although an aerospace example is shown, the examples and principles disclosed herein may be applied to other industries, such as the automotive industry, the space industry, the construction industry, and other design and manufacturing industries. Accordingly, in addition to aircraft, the examples and principles disclosed herein may apply to composite structures, systems, and methods of making the same for other types of vehicles (e.g., land vehicles, marine vehicles, space vehicles, etc.) and stand-alone structures. 
     The preceding detailed description refers to the accompanying drawings, which illustrate specific examples described by the present 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. Throughout the present disclosure, any one of a plurality of items may be referred to individually as the item and a plurality of items may be referred to collectively as the items and may be referred to with like reference numerals. Moreover, as used herein, a feature, element, component or step preceded with the word “a” or “an” should be understood as not excluding a plurality of features, elements, components or steps, unless such exclusion is explicitly recited. 
     Illustrative, non-exhaustive examples, which may be, but are not necessarily, claimed, of the subject matter according to the present disclosure are provided above. Reference herein to “example” means that one or more feature, structure, element, component, characteristic, and/or operational step described in connection with the example is included in at least one aspect, embodiment, and/or implementation of the subject matter according to the present disclosure. Thus, the phrases “an example,” “another example,” “one or more examples,” and similar language throughout the present disclosure may, but do not necessarily, refer to the same example. Further, the subject matter characterizing any one example may, but does not necessarily, include the subject matter characterizing any other example. Moreover, the subject matter characterizing any one example may be, but is not necessarily, combined with the subject matter characterizing any other example. 
     As used herein, a system, apparatus, device, structure, article, element, component, or hardware “configured to” perform a specified function is indeed capable of performing the specified function without any alteration, rather than merely having potential to perform the specified function after further modification. In other words, the system, apparatus, device, structure, article, element, component, or hardware “configured to” perform a specified function is specifically selected, created, implemented, utilized, programmed, and/or designed for the purpose of performing the specified function. As used herein, “configured to” denotes existing characteristics of a system, apparatus, structure, article, element, component, or hardware that enable the system, apparatus, structure, article, element, component, or hardware to perform the specified function without further modification. For purposes of this disclosure, a system, apparatus, device, structure, article, element, component, or hardware described as being “configured to” perform a particular function may additionally or alternatively be described as being “adapted to” and/or as being “operative to” perform that function. 
     Unless otherwise indicated, the terms “first,” “second,” “third,” etc. are used herein merely as labels, and are not intended to impose ordinal, positional, or hierarchical requirements on the items to which these terms refer. Moreover, reference to, e.g., a “second” item does not require or preclude the existence of, e.g., a “first” or lower-numbered item, and/or, e.g., a “third” or higher-numbered item. 
     For the purpose of the present disclosure, the term “position” of an item refers to a location of the item in three-dimensional space relative to a fixed reference frame and an angular orientation of the item in three-dimensional space relative to the fixed reference frame. 
     For the purpose of this disclosure, the terms “coupled,” “coupling,” and similar terms refer to two or more elements that are joined, linked, fastened, attached, connected, put in communication, or otherwise associated (e.g., mechanically, electrically, fluidly, optically, electromagnetically) with one another. In various examples, the elements may be associated directly or indirectly. As an example, element A may be directly associated with element B. As another example, element A may be indirectly associated with element B, for example, via another element C. It will be understood that not all associations among the various disclosed elements are necessarily represented. Accordingly, couplings other than those depicted in the figures may also exist. 
     As used herein, the term “approximately” refers to or represent a condition that is close to, but not exactly, the stated condition that still performs the desired function or achieves the desired result. As an example, the term “approximately” refers to a condition that is within an acceptable predetermined tolerance or accuracy, such as to a condition that is within 10% of the stated condition. However, the term “approximately” does not exclude a condition that is exactly the stated condition. As used herein, the term “substantially” refers to a condition that is essentially the stated condition that performs the desired function or achieves the desired result. 
       FIGS.  1 - 15  and  18   , referred to above, may represent functional elements, features, or components thereof and do not necessarily imply any particular structure. Accordingly, modifications, additions and/or omissions may be made to the illustrated structure. Additionally, those skilled in the art will appreciate that not all elements, features, and/or components described and illustrated in  FIGS.  1 - 15  and  18   , referred to above, need be included in every example and not all elements, features, and/or components described herein are necessarily depicted in each illustrative example. Accordingly, some of the elements, features, and/or components described and illustrated in  FIGS.  1 - 15  and  18    may be combined in various ways without the need to include other features described and illustrated in  FIGS.  1 - 15  and  18   , other drawing figures, and/or the accompanying disclosure, even though such combination or combinations are not explicitly illustrated herein. Similarly, additional features not limited to the examples presented, may be combined with some or all of the features shown and described herein. Unless otherwise explicitly stated, the schematic illustrations of the examples depicted in  FIGS.  1 - 15  and  18   , referred to above, are not meant to imply structural limitations with respect to the illustrative example. Rather, although one illustrative structure is indicated, it is to be understood that the structure may be modified when appropriate. Accordingly, modifications, additions and/or omissions may be made to the illustrated structure. Furthermore, elements, features, and/or components that serve a similar, or at least substantially similar, purpose are labeled with like numbers in each of  FIGS.  1 - 15  and  18   , and such elements, features, and/or components may not be discussed in detail herein with reference to each of  FIGS.  1 - 15  and  18   . Similarly, all elements, features, and/or components may not be labeled in each of  FIGS.  1 - 15  and  18   , but reference numerals associated therewith may be utilized herein for consistency. 
     In  FIGS.  16  and  17   , referred to above, the blocks may represent operations, steps, and/or portions thereof and lines connecting the various blocks do not imply any particular order or dependency of the operations or portions thereof. It will be understood that not all dependencies among the various disclosed operations are necessarily represented.  FIGS.  16  and  17    and the accompanying disclosure describing the operations of the disclosed methods set forth herein should not be interpreted as necessarily determining a sequence in which the operations are to be performed. Rather, although one illustrative order is indicated, it is to be understood that the sequence of the operations may be modified when appropriate. Accordingly, modifications, additions and/or omissions may be made to the operations illustrated and certain operations may be performed in a different order or simultaneously. Additionally, those skilled in the art will appreciate that not all operations described need be performed. 
     Further, references throughout the present specification to features, advantages, or similar language used herein do not imply that all of the features and advantages that may be realized with the examples disclosed herein should be, or are in, any single example. Rather, language referring to the features and advantages is understood to mean that a specific feature, advantage, or characteristic described in connection with an example is included in at least one example. Thus, discussion of features, advantages, and similar language used throughout the present disclosure may, but do not necessarily, refer to the same example. 
     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 system  100 , the method  1000 , and the composite workpiece  102  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.