Patent Publication Number: US-2022234314-A1

Title: Methods and Systems for Forming a Shimmed Assembly

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
     The present disclosure claims priority to U.S. Provisional Application No. 63/142,845, filed on Jan. 28, 2021, the entire contents of which are herein incorporated by reference. 
    
    
     FIELD 
     The present disclosure relates generally to a method of joining structures, and more particularly, to a method and system for manufacturing and mounting a filler or shim. 
     BACKGROUND 
     Parts may be manufactured for assembly from composite materials such as fiber glass or carbon fiber. Composite parts can be formed as a laminate comprising multiple layers of fiber material and resin. The composite parts can then be connected to other structures, such as support structure formed of composite materials or metallic materials. 
     Gaps between the composite material and the supporting structure can reduce the contact area and therefore reduce the strength of the interface between the composite part and the supporting structure. Bridging of gaps with adhesive can strain the composite joint, resulting in component damage (i.e. delamination) or reduced joint strength of the assembly therein. 
     Existing methods of assembling parts include inserting a filler or shim between the composite part and the supporting structure. The filler or shim is shaped to substantially follow the mounting surface of the composite part. Shaping the filler or shim is an iterative process that involves mounting a filler to the composite part, inspecting the assembly, noting gaps between the filler and the composite part, and adjusting the filler through subtractive or additive manufacturing. The inspection of the assembly can be destructive to the filler and/or the composite part, requiring replacements for the iterative process. 
     As such, there is a desire for an improved method and system for assembling parts using a shim or filler. 
     SUMMARY 
     In an example, a method of shimming an uncured substructure for assembly is described. The method comprises emitting a signal from an inspection system proximate a mating surface of the substructure, detecting a reflection of the signal with the inspection system, generating a data set based on detecting the reflection of the signal, the data set representing a shape of the mating surface, determining distances between a plurality of points on the mating surface and respective points on an inner surface of a support structure based on the data set, generating filler dimension data based on the distances, wherein the filler dimension data includes a varying thickness, shaping a filler structure with a computer numerical controlled shaping device using the filler dimension data, adhering a first surface of the filler structure to the mating surface of the substructure to form a shimmed substructure subassembly, and curing the shimmed substructure subassembly. 
     In another example, a method manufacturing and mounting a shim is described. The method comprises forming a substructure at least partially composed of an uncured resin material, nondestructively inspecting a mating surface of the substructure using a scanning device, generating with the scanning device a data set representing a shape of the mating surface, calculating a topographical surface map of a first surface of the shim based on the data set, manufacturing the shim with a computer numerical controlled manufacturing device, the shim having a first surface shaped based on the topographical surface map, applying the shim to the substructure such that the first surface engages the mating surface to form a subassembly, and curing the subassembly. 
     In another example, a system for manufacturing a shim for use in mating a support structure to a substructure is described. The system comprises an inspection system comprising an emitter and a detector wherein the inspection system is configured to inspect a mating surface of the substructure and generate a data set representing a shape of the mating surface. The system further comprises a computing device configured to model a first surface of the shim based on the data representing the mating surface and generate model data representing the first surface, a computer numerical control manufacturing device having a controller and a shaping structure, wherein the manufacturing device is configured to manufacture a shim having a surface shaped using the model data, and an autoclave configured to cure a subassembly including the shim and the substructure. 
     The features, functions, and advantages that have been discussed can be achieved independently in various examples or may be combined in yet other examples. Further details of the examples can be seen with reference to the following description and drawings. 
    
    
     
       BRIEF DESCRIPTION OF THE FIGURES 
       The novel features believed characteristic of the illustrative examples are set forth in the appended claims. The illustrative examples, however, as well as a preferred mode of use, further objectives and descriptions thereof, will best be understood by reference to the following detailed description of an illustrative example of the present disclosure when read in conjunction with the accompanying drawings, wherein: 
         FIG. 1  illustrates a system for manufacturing a shim and assembling a shimmed assembly, according to an example implementation. 
         FIG. 2A  depicts an aircraft, according to an example implementation. 
         FIG. 2B  depicts a composite aircraft skin panel of the aircraft of  FIG. 2A  coupled to a support structure, according to an example implementation. 
         FIG. 3  shows a shimmed subassembly, according to an example implementation. 
         FIG. 4  shows a shimmed assembly, according to an example implementation. 
         FIG. 5  is a flowchart illustrating a method of shimming an uncured substructure for assembly, according to an example implementation. 
         FIG. 6  is a flowchart illustrating a method of manufacturing and mounting a shim, according to an example implementation. 
     
    
    
     DETAILED DESCRIPTION 
     Disclosed examples will now be described more fully hereinafter with reference to the accompanying drawings, in which some, but not all of the disclosed examples are shown. Indeed, several different examples may be described and should not be construed as limited to the examples set forth herein. Rather, these examples are described so that this disclosure will be thorough and complete and will fully convey the scope of the disclosure to those skilled in the art. 
     By the terms “substantially,” “about,” “approximately,” and “proximate” used herein, it is meant that the recited characteristic, parameter, or value need not be achieved exactly, but that deviations or variations, including for example, tolerances, measurement error, measurement accuracy limitations and other factors known to skill in the art, may occur in amounts that do not preclude the effect the characteristic was intended to provide. 
     Unless otherwise specifically noted, elements depicted in the drawings are not necessarily drawn to scale. 
     Within examples, described herein are methods and systems for assembling an assembly including at least one composite substructure, a filler or shim, and a support structure, particularly where the filler or shim is manufactured using data generated from a nondestructive inspection of the composite substructure. 
     The disclosed systems and methods can be used in various contexts, such as in aircrafts or other vehicles, or in environments other than vehicles. While the examples included herein are described in the context of assembling the skin and support structures of an aircraft, it is understood that the methods and systems could be used in other applications using a composite substructure. 
     The disclosed methods and systems include performing a nondestructive inspection of an uncured composite substructure using a scanning inspection system to generate data representing a surface of the uncured composite substructure. The data is then used to manufacture a filler or shim having a surface shaped to mate to the scanned surface of the uncured composite substructure. Manufacturing the shim or filler based on the scan data reduces the time required for assembly compared to prior applications using an iterative shimming process. The shim or filler is coupled to the uncured composite substructure to form a subassembly, and the subassembly is cured. Assembling the subassembly prior to curing the substructure reduces strain on the substructure, decreasing the likelihood of strength reduction thus enabling higher composite laminate quality and joint strength. 
     These and other improvements are described in more detail below. Implementations described below are for purposes of example. The implementations described below, as well as other implementations, may provide other improvements as well. 
     Referring now to the figures,  FIG. 1  depicts an example of a system  100  for manufacturing a shim for use in mating a support structure to a substructure. The system  100  includes a scanning device or inspection system  110 , a computing device  120 , a shaping device or manufacturing device  130 , and an autoclave  140 . 
     The inspection system  110  is a nondestructive inspection system configured to inspect a mating surface of a substructure and generate a data set representing a shape of the mating surface. In some examples, the inspection system  110  is a scanning inspection system having an emitter  112  configured to emit a signal and a detector  114  configured to detect a reflected signal. Example scanning inspection systems include an ultrasonic wave scanning device, an eddy current scanning device, an x-ray device, a magnetic resonance device, an optical imaging device, or a microwave device. Accordingly, the emitter  112  is configured to admit an ultrasonic wave, an eddy current, an x-ray, a magnetic field, visible light, or microwaves. 
     In some examples, the computing device  120  takes the form of a client device (e.g., a computing device that is actively operated by a user), a server, cloud computing device, or some other type of computational platform. In some examples, the computing device  120  takes the form of a desktop computer, laptop computer, tablet computer, smartphone, wearable computing device (e.g., AR glasses), or other type of device. In some forms, the computing device  120  is in communication with inspection system  110  and/or the manufacturing device  130 . As such, the computing device  120  receives information including the data set from the inspection system  110  and/or transmit information to the manufacturing device  130 . For example, the computing device  120  transmits a control instruction to manufacturing device  130  to cause the manufacturing device  130  to manufacture the shim. 
     The processor  122  is a general-purpose processor or special purpose processor (e.g., a digital signal processor, application specific integrated circuit, etc.). The processor  122  is configured to execute the instructions  123  (e.g., computer-readable program instructions including computer executable code) that are stored in the memory  124  and are executable to provide various operations described herein. In alternative examples, the computing device  120  includes additional processors that are configured in the same manner. At least some of the operations described herein as being performed by the computing device  120  are performed by the processor  122 . 
     The memory  124  takes the form of one or more computer-readable storage media that is read or accessed by the processor  122 . In some examples, the computer-readable storage media includes volatile and/or non-volatile storage components, such as optical, magnetic, organic or other memory or disc storage, which can be integrated in whole or in part with the processor  122 . The memory  124  is considered non-transitory computer readable media. In some examples, the memory  124  is implemented using a single physical device (e.g., one optical, magnetic, organic or other memory or disc storage unit), while in other examples, the memory  124  is implemented using two or more physical devices. 
     The communication link  126  takes the form of any wired connection (e.g., Ethernet) or wireless connection (e.g., Bluetooth®) over which the computing device  120  engages in communication with the inspection system  110  and/or the manufacturing device  130 . 
     The computing device  120  is configured to receive the data set representing the shape of the mating surface of the substructure and generate model data representing a first surface of a shim based on the data set. In some examples, the computing device  120  is configured to generate model data representing the full shape of the shim. 
     In some examples, the computing device  120  is configured to predict a morphing of the substructure during curing. The computing system  120  generates the model data representing the first surface based on both the data set and the predicted morphing of the substructure such that the shim does not interfere with the morphing of the substructure. 
     The manufacturing device  130  is a computer numerical controlled manufacturing device configured to manufacture a shim based at least in part on the model data from the computing device  120 . The manufacturing device  130  includes a controller  132  and a shaping structure  134 . The controller  132  controls the shaping structure  134  to shape the shim. In some forms, the manufacturing device  130  manufactures the shim based indirectly on the model data. For example, the controller  132  of the manufacturing device, the computing device  120 , or a second computing system converts the model data into data or machine readable instructions executable by the manufacturing device. 
     In some forms, the manufacturing device  130  includes an additive manufacturing device, such as a three dimensional (“3D”) printer configured to print the shim or filler. Alternatively or additionally, the manufacturing device  130  includes a subtractive manufacturing device, such as a router, a grinder, a sander, or a cutter configured to remove material from the shim or filler. 
     The autoclave  140  is a device or machine capable of curing composite components. In some examples, the autoclave  140  is an autoclave or oven having a heated chamber into which the subassembly is inserted for curing. In some forms, the heated chamber is pressurized. However, other curing devices can be used, such as an electron beam curing device. 
     In operation, the system  100  is used to manufacture a shim for use in assembling an assembly including a composite substructure. A mating surface of the composite substructure is scanned by the inspection system  110 . The inspection system  110  generates a data set representing a shape of the mating surface. The data set is input into the computing device  120 . The computing device executes instructions stored in the memory  124  which cause the processor  122  to generate model data representing a shape of a first surface of a shim based at least in part on the data set. The model data is used by the manufacturing device  130  to manufacture a shim having a first surface shaped based on the model data. The first surface of the shim is mounted to the mating surface of the substructure to form a subassembly. The subassembly is then cured by the autoclave  140 . 
     In some example applications, the system  100  is used to assemble the skin of an aircraft to support structure.  FIG. 2A  is a perspective view of an aircraft  200 , according to an example implementation. The aircraft  200  includes a nose  230 , wings  220   a - b , a fuselage  225 , and a tail  231 , according to an example implementation. The aircraft  200  includes many areas arranged for storage of items during flight. In one example, the fuselage  225  includes storage underneath a passenger compartment for storing luggage and other items or supplies. In another example, the passenger compartment in the fuselage  225  includes overhead bins and under seat areas for storing further items. The nose  230 , wings  220   a - b , fuselage  225 , and tail  231  include an exterior skin  202  supported by internal support structures, such as frames or ribs. 
       FIG. 2B  illustrates a portion of the interior of the aircraft  200 . The aircraft  200  includes a support structure  206  and a plurality of stringers  204  attached to the skin  202 . The stringers  204  are “hat-section” stringers having a raised portion  203  and opposing flange portions  205 . The flange portions  205  are attached directly to the skin  202 . 
     The skin  202  includes a composite material having a fiber component and a resin component such as carbon fiber or fiber glass. In some forms, the skin  202  is formed of multiple layers of composite material forming a laminate. 
     The support structure  206  includes a first section  207  and a second section  208 . The first section  207  includes a base portion  209  and an upstanding leg portion  210 . The upstanding leg portion  210  is fastened to the second section  208 , and includes a plurality of openings  214  through which the raised portions  203  of the stringers  204  extend. The base portion  209  is attached to the stringer flange portions  205  and the skin  202 . The base portion  209  includes a plurality of steps or joggles  212  positioned outboard of the stringer flange portions  205 . The joggles  212  allow the base portion  209  to step off of the stringer flange portions  205  and onto the skin  202 . One or more fillers or shims (not shown) are positioned between the support structure  206  and the skin  202  to reduce gaps therebetween. As described herein, the shim or filler is manufactured based on scan data of a mating surface of the skin  202  and coupled to the skin  202  prior to curing. 
       FIG. 3  is a cross-section of a subassembly  300  including a composite substructure  302 , a filler or shim  320 , and a stringer  304 . In some examples, the substructure  302  and the stringer  304  are the skin  202  and stringer  204 , respectively, of the aircraft  200 . The composite substructure  302  includes a mating surface  303 . The shim  320  has a corresponding first surface  321  which is coupled to the mating surface  303 . As shown, the first surface  321  substantially follows the shape of the mating surface  303  such that only small gaps exist there between. In some forms, an adhesive  322  is applied between the first surface  321  and the mating surface  303  to couple the shim  320  to the composite substructure  302 . Alternatively or additionally, the shim  320  is secured to the composite substructure  302  by the resin of the substructure  302 . 
     In operation, the shim  320  is formed based at least in part on a data set representing the shape of the mating surface  303 . The first surface  321  is shaped such that when assembled, the gaps between the shim  320  and the composite substructure  302  do not exceed a predetermined gap allowance threshold value which is retrieved from computer readable memory. In some forms, a computing system predicts a morphing of the shape of the composite substructure  302  during curing. The first surface  321  is shaped such that after assembly, the composite substructure  302  is allowed to morph as predicted. 
     The shim  320  is coupled to the composite substructure  302  prior to curing. The subassembly  300  is then cured using an autoclave or other curing device. In some forms, the shim  320  is cured prior to assembly. Alternatively, the shim  320  is uncured when assembled and is cured along with the composite substructure  302 . 
     The shim  320  further includes a second surface  324  substantially opposite the first surface  321 . The second surface  324  is configured to couple to a support structure, such as a frame or rib. The second surface  324  is shaped to correspond to the shape of an inner surface of the support structure. In some forms, the second surface  324  is substantially flat so as to mate to a substantially flat inner surface of the support structure. In alternative embodiments, the second surface has a varying height, similar to the first surface  321 , which is formed based on scan data of the support structure. 
       FIG. 4  is a cross-sectional view of an assembly  400  including the subassembly  300  of  FIG. 3  and a support structure  306 . In some examples, the support structure  306  is the support structure  206  of the aircraft  200  described above. The support structure  306  includes an opening  314  through which the stringer  304  extends. The support structure  306  further includes an inner surface  307  facing toward the composite substructure  302 . The inner surface  307  is coupled to the shim  320 . 
     In some examples, the composite substructure  302  is the composite skin of an aircraft. The support structure  306  is a frame of the aircraft to which the skin is mounted. In some forms, the assembly  400  is part of the wing of the aircraft. The support structure  306  is rib structure. 
       FIG. 5  shows a flowchart of an example of a method  500  that could be used with the system  100  shown in  FIG. 1  to form at least part of the assembly  400  of  FIG. 4 . Method  500  includes one or more operations, functions, or actions as illustrated by one or more of blocks  501 - 508 . 
     At block  501 , the method  500  includes emitting a signal from an inspection system proximate a mating surface of a substructure. The inspection system is a nondestructive inspection system having an emitter and a detector, such as the inspection system  110  described above. In some examples, the signal is emitted directly at the mating surface of the substructure such that the signal is at least partially reflected by the mating surface. In other examples, the signal is emitted along the mating surface such that the substructure blocks part of the signal, and the unblocked portion of the signal illustrates a silhouette of the substructure. 
     At block  502 , the method  500  includes detecting a reflection of the signal with the inspection system. Detecting the reflection of the signal includes inspecting portions of the signal reflected off of multiple respective points along the mating surface of the substructure. 
     At block  503 , the method  500  includes generating a data set based on detecting the reflection of the signal, the data set representing a shape of the mating surface. In some forms, the data set includes a topographical surface map or surface texture gradient of the mating surface of the substructure. In some examples, block  503  further includes predicting a morphing of the substructure during curing. The data set is adjusted based on the predicted morphing to represent a shape of the mating surface after curing. 
     At block  504 , the method  500  includes determining distances between a plurality of points on the mating surface and respective points on an inner surface of a support structure based on the data set. The number and location of points on the mating surface is determined by the resolution of the inspection system. A same number of respective points are selected on the inner surface such that all lines connecting the plurality of points to the respective points are parallel. In some examples, the inner surface is substantially flat. Accordingly, the distances are determined based on the assumption that the inner surface is perfectly flat. The respective points are spaced from the plurality of points in a direction normal to the inner surface. 
     In other examples, the distances are determined using the data set representing the shape of the mating surface and a second data set representing the predicted shape of the inner surface. In one form, the second data set is produced by a nondestructive inspection or scan of the inner surface having the same resolution as the scan of the mating surface. 
     At block  505 , the method  500  includes generating filler dimension data based on the distances. Because the mating surface of the substructure is not flat, the height of the thickness of the filler will vary along the corresponding first surface to mirror the change in height of the mating surface. Accordingly, the filler dimension data includes a varying thickness. As discussed above, in some examples the computing device has a second data set representing a shape of the inner surface of the support structure. Accordingly, the filler dimension data includes modeling a second surface of the filler or shim based on the second data set. 
     The filler dimension data is data representing the shape of a custom filler or shim for assembly between the substructure and the support structure. In some examples, the filler dimension data includes data representing the full three dimensional shape of the filler or shim. Alternatively, the filler dimension data includes data representing a portion of the filler or shim proximate the substructure in assembly, the portion including a first surface configured to mate to the mating surface. 
     At block  506 , the method  500  includes shaping a filler structure with a computer numerical controlled shaping device using the filler dimension data. As discussed above, the shaping device includes a subtractive manufacturing device and/or an additive manufacturing device. In some forms, the shaping device receives the filler dimension data directly from a computing device that generated the filler dimension data. 
     At block  507 , the method  500  includes adhering a first surface of the filler structure to the mating surface of the substructure to form a shimmed substructure subassembly. In some examples, the first surface is adhered to the mating surface by an adhesive material. Alternatively, the first surface is adhered to the mating surface by the uncured resin of the substructure. In some examples, block  507  includes aligning the filler structure relative to the mating surface based on the predicted morphing of the substructure such that the filler structure does not interfere with the predicted morphing. Improper alignment can result in damage to the substructure, such as wrinkling. 
     At block  508 , the method  500  includes curing the shimmed substructure subassembly. Curing the subassembly is performed by a curing device, such as an autoclave or oven. 
       FIG. 6  shows a flowchart of an example of a method  600  that could be used with the system  100  shown in  FIG. 1  to manufacture a shim and mount in in the subassembly  300  of  FIG. 3 . Method  600  includes one or more operations, functions, or actions as illustrated by one or more of blocks  601 - 607 . 
     At block  601 , the method  600  includes forming a substructure at least partially composed of an uncured resin material. The substructure is formed of a composite material including both the uncured resin material and a fiber material. In some examples, the substructure is a laminate formed of multiple layers of the composite material. 
     At block  602 , the method  600  includes nondestructively inspecting a mating surface of the substructure using a scanning device. Inspecting comprises emitting a signal from an inspection system proximate a mating surface of a substructure and detecting a reflection of the signal. The inspection system is a nondestructive inspection system having an emitter and a detector, such as the inspection system  110  described above. In some examples, the signal is emitted directly at the mating surface of the substructure such that the signal is at least partially reflected by the mating surface. In other examples, the signal is emitted along the mating surface such that the substructure blocks part of the signal, and the unblocked portion of the signal illustrates a silhouette of the substructure. 
     At block  603 , the method  600  includes generating with the scanning device a data set based on detecting the reflection of the signal, the data set representing a shape of the mating surface. In some examples, the scanning device determines the distance to a plurality of points on the mating surface from the scanning device based on the amount of time between emitting and detecting the signal. From this distance data, the scanning device, or a computing device, the data set which includes a topographical surface map or surface texture gradient of the mating surface of the substructure. In some examples, block  603  further includes predicting a morphing of the substructure during curing. The data set is modified based on the predicted morphing such that it represents the predicted shape of the mating surface. 
     At block  604 , the method  600  includes calculating a topographical surface map of a first surface of the shim based on the data set. The topographical surface map is a three dimensional representation of the first surface of the shim illustrating changes in height of the surface (e.g., the locations and heights of peaks and valleys on the first surface). In some examples, a full three dimensional model of the shim, including the topographical surface map, is generated. In some forms, the three dimensional model further includes a second topographical surface map of a second surface of the shim, wherein the second surface is substantially opposite the first surface. 
     Calculating the topographical surface map includes first starting with the data set as the first surface is shaped to substantially follow the shape of the mating surface. In some examples, the computing device performing the calculation smooths one or more of the height transitions based on prestored parameters. Prestored parameters include the capabilities of the manufacturing device used to manufacture the shim, gap tolerances, and the material being used to form the shim. The smoothed topographical surface map is compare to the data set to determine if the first surface intersects the mating surface. The comparison further includes retrieving a predetermined gap allowance threshold from memory, and determining if there are any gaps between the first surface and the mating surface which exceed the threshold. In some forms, the smoothing is a recursive process in which the topographical surface map is revised until the comparison shows that there are no intersections or gaps exceeding the threshold. 
     At block  605 , the method  600  includes manufacturing the shim with a computer numerical controlled manufacturing, wherein the shim has a first surface shaped based on the topographical surface map. As discussed above, the manufacturing device includes a subtractive manufacturing device and/or an additive manufacturing device. In one example, manufacturing the shim includes the additive manufacturing technique of 3D printing the shim and then the subtractive manufacturing technique of selectively removing material from the first surface with a subtractive manufacturing device based on the topographical surface map to conform to the shape of the mating surface. In some examples, manufacturing the shim includes curing the shim. In other examples, the shim is in an uncured state when applied to the substructure in block  606 . 
     At block  606 , the method  600  includes applying the shim to the substructure such that the first surface engages the mating surface to form a subassembly. In some examples, and adhesive is applied to the first surface and/or the mating surface to secure the shim to the substructure. Alternatively or additionally, other fasteners are used. In some examples, applying the shim to the substructure includes aligning the shim relative to the substructure based on the predicted morphing of the substructure such that the shim does not interfere with the predicted morphing. 
     At block  607 , the method  600  includes curing the subassembly. Curing the subassembly is performed by a curing device, such as an autoclave or oven. 
     In some examples, devices or systems are used or configured to perform logical functions presented in  FIGS. 5 and 6 . In some instances, components of the devices and/or systems are configured to perform the functions such that the components are actually configured and structured (with hardware and/or software) to enable such performance. In other examples, components of the devices and/or systems are arranged to be adapted to, capable of, or suited for performing the functions, such as when operated in a specific manner. Although blocks in  FIGS. 5 and 6 , are illustrated in a sequential order, in other examples these blocks are be performed in parallel, and/or in a different order than those described herein. Also, in some examples, the various blocks are combined into fewer blocks, divided into additional blocks, and/or removed based upon the desired implementation. 
     It should be understood that for these and other processes and methods disclosed herein, flowcharts show functionality and operation of one possible implementation of present examples. In this regard, one or more of the blocks, or portions of the blocks represent a module, a segment, or a portion of program code, which includes one or more instructions executable by a processor for implementing specific logical functions or steps in the process. The program code is stored on any type of computer readable medium or data storage, for example, such as a storage device including a disk or hard drive. Further, in some examples, the program code is encoded on a computer-readable storage media in a machine-readable format, or on other non-transitory media or articles of manufacture. In some forms, the computer readable medium includes non-transitory computer readable medium or memory, for example, such as computer-readable media that stores data for short periods of time like register memory, processor cache and Random Access Memory (RAM). Alternatively or additionally, the computer readable medium includes non-transitory media, such as secondary or persistent long term storage, like read only memory (ROM), optical or magnetic disks, compact-disc read only memory (CD-ROM), for example. In other forms, the computer readable media is any other volatile or non-volatile storage systems. The computer readable medium is a tangible computer readable storage medium, for example. 
     In some examples, each block or portions of each block in  FIGS. 5 and 6  represent circuitry that is wired to perform the specific logical functions in the process. Alternative implementations are included within the scope of the examples of the present disclosure in which functions are executed out of order from that shown or discussed, including substantially concurrent or in reverse order, depending on the functionality involved, as would be understood by those reasonably skilled in the art. 
     Different examples of the system(s), device(s), and method(s) disclosed herein include a variety of components, features, and functionalities. It should be understood that the various examples of the system(s), device(s), and method(s) disclosed herein may include any of the components, features, and functionalities of any of the other examples of the system(s), device(s), and method(s) disclosed herein in any combination or any sub-combination, and all of such possibilities are intended to be within the scope of the disclosure. 
     The description of the different advantageous arrangements has been presented for purposes of illustration and description, and is not intended to be exhaustive or limited to the examples in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. Further, different advantageous examples may describe different advantages as compared to other advantageous examples. The example or examples selected are chosen and described in order to best explain the principles of the examples, the practical application, and to enable others of ordinary skill in the art to understand the disclosure for various examples with various modifications as are suited to the particular use contemplated.