Patent Publication Number: US-10317170-B2

Title: Pyrotechnic launching system with rifled mortar

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
     The present Patent Application claims the benefit of U.S. Provisional Patent Application No. 62/440,264 filed Dec. 29, 2016. 
    
    
     INCORPORATION BY REFERENCE 
     The disclosure of U.S. Provisional Patent Application No. 62/440,264 filed Dec. 29, 2016, is hereby incorporated by reference as if presented herein in its entirety. 
     SUMMARY 
     In one aspect, the present disclosure is directed to a pyrotechnic or firework launching system. The pyrotechnic launching system can include a launcher and one or more aerial shells configured to be launched or fired from the launcher. The launcher typically comprises an elongated body having a tubular or cylindrical shape, with a cavity or passage defined at least partially through the launcher body that is configured to receive the one or more aerial shells. The launcher body can include an interior surface adjacent or proximate to the cavity or passage. The launcher body additionally can include one or more rifled portions or rifling features defined along the interior surface of the launcher body. The rifled portion(s) can comprise one or more grooves or channels defined about the interior surface of the launcher body. The one or more grooves or channels can be arranged in a spiral or helical pattern, for example, at least partially along the interior surface of the launcher body. In one aspect, the grooves or channels may cause the aerial shell(s) to spin or rotate as the aerial shell(s) moves along the launcher body during launching/firing thereof. The rotation or spin of the aerial shells, for example, can result in higher and/or more controlled flight paths, especially in comparison to aerial shells fired from launchers having smooth or continuous bores or interior surfaces, i.e., launchers without rifling. 
     In another aspect, the aerial shell(s) can include a lift portion and an effects portion. The lift portion can comprise a tubular body that at least partially defines an interior chamber. The interior chamber of the lift portion can at least partially receive a lift charge or propellant operable to generate combustion gases that force or propel the aerial shell(s) along and out of the launcher body and which aerial shell(s) can proceed upward, e.g. to a predetermined height. The effects portion can include a generally spherical body that at least partially defines an interior chamber. The interior chamber of the effects portion typically at least partially receives a breaking charge and one or more effects charges. The breaking charge can be operable to at least partially break or open a sidewall of the spherical body to release the effects charge(s). The effects charge(s) can be operable to generate a predetermined effect, such as a specific shape or noise signature. The increased height and/or control of the aerial shells provided by the rifled launcher can, for example, allow the aerial shell to require less (i.e., a reduced amount of) propellant in comparison to aerial shells fired from a launcher without rifling. For example, the aerial shells according to the present disclosure can use about 5% to about 15% less propellant or lift charge in comparison to aerial shells used with/fired from launchers without rifling. The reduction in the percentage of the lift charge required can provide several additional benefits. For example, utilizing less charge in a typical sized shell can allow space for additional effects charge and further allow, for example, more complex patterns or effects. In one example, while fireworks for personal use generally do not include a sufficient amount of effects charge to allow for complex patterns, e.g., patterns other than spherical shapes, the launcher detailed in the present disclosure can provide fireworks that have complex effects patterns. 
     In yet another aspect, a launcher assembly can be provided. The launcher assembly can include an outer portion comprising a sleeve having a body with a cavity defined therethrough. The launcher assembly further can include at least one insert portion comprising a firing tube having a generally cylindrical shape that is sized, configured, and/or dimensioned to be at least partially received within the cavity of the sleeve. The firing tube can have a passage defined therethrough that is sized, dimensioned, and/or otherwise configured for receipt of one or more aerial shells to facilitate firing thereof. The firing tube further can have a plurality of rifling features or rifled portions defined about an interior surface of the firing tube. The interior surface can extend along or can be substantially adjacent to the passage of the firing tube. In one embodiment, the plurality of rifling features can include one or more channels or grooves defined in and along the interior surface of the firing tube. The channels or grooves can be recessed at a prescribed depth in relation to the interior surface of the firing tube. The grooves or channels further can be arranged in a spiral or helical pattern at least partially along the interior surface of the firing tube and can cause the aerial shells to spin or rotate as the aerial shells move along the firing tube during launching/firing thereof. The rotation or spin of the aerial shells, for example, can result in higher and/or more controlled flight paths, especially in comparison to aerial shells fired from launcher assemblies having smooth or continuous bores, i.e., launchers without rifling features as provided herein. The launcher assembly further can include a base portion connected to a lower end of the firing tube, e.g., by one or more fasteners. The launching assembly also can include a wadding insert or portion that is press-fitted into the cavity of the firing tube so as to be positioned at or substantially adjacent to the lower end of the firing tube. The wadding insert can at least partially dampen and/or at least partially absorb forces/stresses generated from firing/launching of aerial shells from the firing tube, and can be replaceable/interchangeable to prolong the working life of the firing tube. 
     In an even further aspect, a process/method for manufacturing and/or assembling the launching assembly can be provided. The method can include obtaining a blank of sheet material (e.g., sheet metal) for forming the firing tube, and forming a plurality of rifling features in a surface of the blank. Upon forming of the plurality of rifling features in the blank, the method can include bending or otherwise forming the blank to at least partially define a cylinder having open or disconnected end or side portions. The method further can include forming one or more flange portions at the ends/sides of the at least partially defined cylinder, and then engaging or connecting the one or more flange portions formed at the ends/sides of the cylinder. For example, the flanges of the ends can be interlaced to join the open/disconnected end/side portions. Thereafter, the one or more flange portions at each end of the cylinder can be pressed together to at least partially form a seam fixedly attaching the open ends of the partially formed cylinder to facilitate the formation of a completed cylinder. In addition, the method can include reinforcing the seam by forming a plurality of corresponding recesses and protuberances therealong. A lip, ring, bulge, or other suitable protruding portion further can be formed along an upper end of the firing tube. 
     Additionally, upon formation of the firing tube, the firing tube can be received, e.g., press-fitted, into the cavity of the sleeve. A wadding insert further can be received, e.g., press-fitted into, the passage of the firing tube such that the wadding insert is positioned at or substantially adjacent the lower end of the firing tube. The base portion further can be aligned with and then connected to the lower end of the firing tube, for example, using one or more fasteners, e.g., nails, screws, rivets, etc., and/or another suitable attachment mechanism, such as an adhesive, soldering, welding, etc. 
     Various objects, features and advantages of the present disclosure will become apparent to those skilled in the art upon a review of the following detail description, when taken in conjunction with the accompanying drawings. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The accompanying drawings, which are included to provide a further understanding of the embodiments of the present disclosure, are incorporated in and constitute a part of this specification, illustrate embodiments of the present disclosure, and together with the detailed description, serve to explain the principles of the embodiments discussed herein. No attempt is made to show structural details of this disclosure in more detail than may be necessary for a fundamental understanding of the exemplary embodiments discussed herein and the various ways in which they may be practiced. According to common practice, the various features of the drawings discussed below are not necessarily drawn to scale. Dimensions of various features and elements in the drawings may be expanded or reduced to more clearly illustrate the embodiments of the disclosure. 
         FIG. 1  shows an example embodiment of a pyrotechnic launching system according to principles of the present disclosure. 
         FIG. 2  shows an exemplary aerial shell according to principles of the present disclosure. 
         FIG. 3  shows a perspective view of a launcher assembly of the pyrotechnic launching system of  FIG. 1 . 
         FIG. 4  illustrates a schematic view of the launcher of  FIG. 1 . 
         FIGS. 5A and 5B  show perspective and exploded views of a launcher assembly according to an additional aspect of the present disclosure. 
         FIG. 6  shows a schematic illustration of a process step of forming a blank for a firing tube according to principles of the present disclosure. 
         FIG. 7  shows a schematic illustration of a process step for forming the rifling features or rifled portions in the blank of  FIG. 6  according to one aspect of the present disclosure. 
         FIG. 8  shows a schematic illustration of a process step for bending or otherwise forming the blank of  FIG. 7  to define an at least partial cylinder according to one aspect of the present disclosure. 
         FIG. 9  provides a schematic illustration of a process step for forming one or more flanges on the blank of  FIG. 8  according to one aspect of the present disclosure. 
         FIG. 10  provides a schematic illustration of a process step for generating a seam to form the blank of  FIG. 9  into a completed cylinder according to one aspect of the present disclosure. 
         FIG. 11  provides a schematic illustration of a process step for reinforcing the seam along the completed cylinder according to one aspect of the present disclosure. 
         FIG. 12  provides a schematic illustration of a process step for forming a lip or ring portion about the upper end of the firing tube according to one aspect of the present disclosure. 
         FIG. 13  shows a schematic illustration of a process step for assembling the launcher assembly upon formation of the firing tube according to one aspect of the present disclosure. 
     
    
    
     Corresponding parts are designated by corresponding reference numbers throughout the drawings. 
     DETAILED DESCRIPTION 
     The following description is provided as an enabling teaching of embodiments of this disclosure. Those skilled in the relevant art will recognize that many changes can be made to the embodiments described, while still obtaining the beneficial results. It will also be apparent that some of the desired benefits of the embodiments described can be obtained by selecting some of the features of the embodiments without utilizing other features. Accordingly, those who work in the art will recognize that many modifications and adaptations to the embodiments described are possible and may even be desirable in certain circumstances. Thus, the following description is provided as illustrative of the principles of the embodiments of the present disclosure and not in limitation thereof. 
       FIG. 1  shows a pyrotechnic launching system  10  according to principles of the present disclosure. The pyrotechnic launching system  10  comprises a launcher or mortar  12  and one or more aerial shells  14 . The aerial shell(s)  14  is configured to be fired or launched from the launcher  12 . 
     As shown in  FIG. 1 , the launcher  12  includes an elongated body  16 . The elongated launcher body  16  has a first or upper end  16 A, second or lower end  16 B, and a sidewall  18 . The launcher body  16  has a generally cylindrical shape, though other shapes are possible without departing from the present disclosure. The launcher body  16  can be formed from any suitable material, with one example being a plastic, such as High Density Polyethylene (“HDPE”), Polyvinyl Chloride (“PVC”), or other suitable plastic or polymeric material. The launcher body  16 , however, can be formed of paper, cardboard, other or paper products; metallic products, such as steel, iron, or aluminum; or combinations of the above products and other materials, without departing from the present disclosure. The launcher  12  has a cavity or passage  20  defined at least partially through the launcher body  16 . The cavity  20  has an opening  22  at the upper end  16 A of the launcher body  16 . The aerial shells  14  can be loaded into the launcher body  16  through the opening  22 . The cavity  20  at least partially defines, or is substantially adjacent to, an inner or interior surface  24  of the launcher body  16 . 
     While the launcher  12  and system  10  can be dimensioned in any desired size and configuration, one exemplary system  10  and launcher  12  is now described. In this example, the launcher body  16  can have a height H from between about 100 mm to about 400 mm, for example, the height H of the launcher body  16  can be about 265 mm. Also, the exemplary launcher body  16  can have an outer diameter OD from about 35 mm to about 70 mm, and the launcher body  16  can have an inner diameter ID from about 30 mm to about 65 mm. The inner diameter ID typically is sized, dimensioned, or otherwise configured such that the aerial shell(s)  14  can be received within and expelled from the opening  22  of the cavity  20 . For example, the inner diameter ID is sized, configured and/or dimensioned to allow a user to insert one or more aerial shells  14  into the opening  22  of the launcher body  16  such that the shells  14  can slide or otherwise move along the cavity  20  to a firing position, for example, at the lower end  16 B of the launcher body  16 . Further, the inner diameter ID can be sized, configured and/or dimensioned such that at least a portion of the aerial shell  14  is in sliding contact or engagement with the inner surface  24  of the launcher body  16  as the aerial shell  14  moves along the launcher body  16  during launching/firing. In one exemplary embodiment, the launcher body  16  can have an outer diameter OD of about 51 mm and an inner diameter ID of about 47 mm. The launcher body  16  can have any suitable size, dimensions, configuration, or arrangement, however, without departing from the scope of the present disclosure. 
       FIG. 1  additionally shows the launcher  12  including a base or support portion  26 . The base  26  typically is connected to, or formed with, the lower end  16 B of the launcher body  16 . The base  26  has a square or rectangular shape, though other shapes, such as oval, circular, triangular, polygonal, etc. are possible without departing from the present disclosure. The base  26  can be formed from plastic or other polymeric material, such as High Density Polyethylene (“HDPE”), Polyvinyl Chloride (“PVC”), or other suitable plastic or polymeric material. However, the base  26  may be formed from any suitable material having a density or weight sufficient to at least partially support the launcher body  16  during loading and firing of the aerial shells  14  without departing from the present disclosure. The base  26  typically is formed from the same material as the launcher body  16 , but the base  26  and the launcher body  16  can be formed of different materials without departing from the present disclosure. In one exemplary embodiment, the base  26  can have a width W from about 65 mm to about 145 mm, for example, the base  26  can have a width W of about 98 mm. The base  26  can have a thickness or height H 1  from about 2.5 mm to about 20 mm, for example, the base  26  can have a thickness or height H 1  of about 10 mm. The base  26  can be formed to include any size, dimensions, or configurations suitable to at least partially support, stabilize, and/or maintain the launcher body  16  in a generally vertical or erect arrangement/configuration prior to, during, and/or after firing/launching of the aerial shell  14  from the launcher  12 . 
       FIG. 2  shows an aerial shell  14  according to principles of the present disclosure. The aerial shell  14  includes a lift portion  28  and a show portion  30 . As shown in  FIG. 2 , the lift portion  28  includes a body  32  that has a generally tubular or cylindrical shape, though the body  32  of the lift portion  28  can have any suitable shape without departing from the scope of the present disclosure. For example, the tubular body  32  can have an outer diameter OD 1  of about 20 mm to about 35 mm. The tubular body  32  can have an inner diameter ID 1  from about 18 mm to about 33 mm. In one embodiment, for example, the tubular body  32  can have an inner diameter of about 24 mm and an outer diameter of about 28 mm. The body  32  of the lift portion  28  can be formed from any suitable material. In one example, the body  32  can be formed from paper-based products, for example, paper, cardboard, other laminate material, or combinations of these materials and/or other materials. 
     The lift portion  28  also includes a cavity or chamber  34  defined in the body  32  of the lift portion  28 . The chamber  34  typically is sized, dimensioned, and/or configured to at least partially house or receive a lift charge or propellant  36  operable to propel the aerial shell  14  from the launcher  12 . Activation or ignition of the lift charge  36  generates combustion gases that propel the aerial shell  14  along the launcher body  16  and out of opening  22  in the upper end  16 A of the launcher body  16 . The lift charge  36  may include Potassium Nitrate (KNO 3 ), Sulfur (S), and/or Carbon (C), though any suitable materials and proportions of materials can be used without departing from the scope of the present disclosure. The aerial shell  14  typically includes an ignition mechanism, for example, a fuse  38 , or other suitable detonation mechanism, in communication with the lift charge  36 , which fuse  38  can be ignited or otherwise activated to ignite/activate the lift charge  36 . The fuse  38  can afford a delay time of about 3 seconds to about 9 seconds, with the delay time being the time from ignition of the fuse  38  to activation of the propellant. The fuse  38  can have any suitable delay time, however, to allow a user to move to a safe distance from the launcher  12  after ignition/activation of the fuse  38 . In one embodiment, one or more retainer features, such as a ring or loop, can be provided with the aerial shell  14  to position the fuse  38 . 
     As further shown in  FIG. 2 , the show portion  30  of the aerial shell  14  can include a body  40  that, for example, has a generally spherical shape, though other shapes are possible without departing from the scope of the present disclosure. The body  40  of the show portion  30  can be connected to, or formed with, the tubular body  32  of the lift portion  28  at a first or upper end  32 A of the tubular body  32 . The total height TH of the aerial shell  14  can be any desired dimension, for example, the total height TH can be from about 50 mm to about 80 mm. In one embodiment, for example, the total height TH of the aerial shell  14  is about 62 mm. The spherical body  40  of the show portion  30  can have a diameter D from about 25 mm to about 60 mm. In one embodiment, for example, the diameter D of the spherical body  40  is about 44 mm. The show portion  30  can have any desired diameter, size, dimensions, arrangement or configuration without departing from the present disclosure, for example, to allow a user to load or insert one or more area shells  14  into launcher body  16  and/or such that at least a portion of the aerial shell  14  is in sliding contact or engagement with the inner surface  24  of the launcher body  16  as the aerial shell  14  moves along the launcher body  16  during launching/firing thereof. The body  40  of the show portion  30  can be formed, for example, from a paper product or other laminate material, though other materials are possible without departing from the scope of the present disclosure. The show portion  30  further can have a cavity or chamber  42  defined in the body  40  of the show portion  30 . The cavity or chamber  42  typically is sized, dimensioned, and/or configured to least partially house or receive a breaking charge  44  and/or one or more effects charges  46 . 
     The breaking charge  44  is operable to at least partially break open the body  40  of the show portion  30  to release the effects charge(s)  46 . The effects charge(s)  46  is activated or released to provide one or more effects. The effect(s) may include one or more visual effects having predetermined pattern or arrangement. For example, visual effects may include a specific shape, such as a peony,  chrysanthemum , a dahlia, willow, palm, ring, diadem, kamuro, crossette, spider, horsetail, time rain, fish, mine, and/or cake patterns or arrangements, though any suitable visual pattern or arrangement can be used without departing from the scope of present disclosure. The visual effect further can include a specific color, for example, red, orange, yellow, green, blue, indigo, violet, white, gray, etc. Any color or combination of colors can be used, however, without departing from the scope of the present disclosure. The effect(s) also may include an audio effect, such as a specific noise signature, for example, a loud bang or a whistling effect. The effects charge  46  can comprise any suitable charge, for example, a charge comprising Potassium Perchlorate (KClO 4 ), Sulfur (S), or Carbon (C), or combinations of these and/or other materials. The breaking charge  44  can comprise any suitable charge, e.g., for example, Potassium Perchlorate (KClO 4 ), Barium Nitrate (Ba(NO 3 ) 2 ), Sodium Oxalate (Na 2 C 2 O 4 ), Strontium Carbonate (SrCO 3 ), Magnalium (AL-Mg), Phenolic Resin (C 48 H 42 O 7 ), or Shellac (C 16 H 32 O 5 ), or combinations of these or other materials. 
       FIG. 2  additionally shows that the aerial shell  14  includes an internal fuse  48  in communication with the lift and show portions  28 / 30 . The internal fuse  48  is ignited by the lift charge  36  and is configured to ignite or activate the breaking charge  44  and/or the effects charge(s)  46 . The internal fuse  48  can be configured to activate the breaking charge  44  or the effects charge(s)  46  when the aerial shell  14  reaches a predetermined height in the flight path of the aerial shell  14 . The predetermined height may include a maximum height of the flight path of the aerial shell  14 , though the breaking charge  44 /effects charge(s)  46  can be activated at any suitable height along the flight path of the aerial shell  14 , typically the breaking charge  44 /effects charge(s)  46  are extinguished before the breaking charge  44 /effects charge(s)  46  reach the ground. 
       FIG. 3  illustrates a perspective view of the launcher body  16  showing the inner surface  24  of the launcher body  16 , and  FIG. 4  provides a schematic view of the launcher body  16 . As shown in  FIGS. 3 and 4 , the inner surface  24  comprises rifled portions or rifling features  50  that extend at least partially about/along the inner surface  24  of the launcher body  16 . Although other patterns of rifled portions are within the scope of the present disclosure, as shown in  FIGS. 3 and 4 , the rifled portions  50  typically include one or more grooves or channels  52  defined in the inner surface  24 , and that extend at least partially along the inner surface  24  in a pattern. The pattern can include a spiral or helical pattern, configuration, or arrangement. The spiral or helical grooves or channels  52  can be angled or have a twist rate. In one exemplary embodiment, the channels or grooves  52  can extend 360° about the interior surface  24  of the launcher body  16  about every 12 inches (about every 304.8 mm). However, the grooves or channels  52  can have any suitable angle or twist rate, for example, the channels or grooves  52  can extend approximately 360° about the interior surface  24  of the launcher body  16  in a range from about every 6 inches (about every 152.4 mm) to about every 18 inches (about every 457.2 mm), without departing from the present disclosure. Additionally, the grooves or channels  52  can have a depth in the range of about 0.5 mm to about 1.5 mm. In one embodiment, the grooves or channels  52  can have a depth of about 1 mm. The grooves or channels  52  further can have a thickness in the range of about 1 mm to about 3 mm. As shown in  FIGS. 3 and 4 , the rifled portions  50  can include, for example, eight equally spaced grooves  52  arranged about the interior surface  24  of the launcher body  16 . However, any suitable number, arrangement, or configuration of grooves or channels  52 , for example, four, five, six, seven, eight, nine, or ten or more grooves/channels may be used without departing from the scope of the present disclosure. 
     In order to fire the aerial shell(s)  14  from the launcher  12 , the aerial shell(s)  14  is typically is inserted into the opening  22  of the launcher body  16 . The fuse  38  can be ignited/activated to activate/ignite the propellant/lift charge  36 . Activation of the lift charge  36  generates combustion gases that force or propel the aerial shell  14  along the launcher body  16  and out from the opening  22  along a predetermined flight path. As the aerial shell  14  moves along the launcher body  16 , the grooves or channels  52  of the rifled portions  50  cause the aerial shell  14  to spin or rotate. For example, the grooves/channels  52  may interact with the combustion gases to cause a swirling effect and generate spin or rotation of the aerial shell  14 . Additionally, or in the alternative, at least a portion of the aerial shell  14  may at least partially engage or contact the grooves or channels  52  to generate spin or rotation of the aerial shell  14 . The rotation or spin of the aerial shells  14  may be in a direction that is perpendicular or transverse to a central axis CA of the aerial shell  14 . 
     The spinning or rotation of the aerial shell(s)  14  can provide, for example, enhanced control and increase height of the flight path of the aerial shells  14  in comparison to shells fired from a launcher without rifling. By way of example, rotation or spinning of the aerial shells  14  can counteract or substantially prevent the Magnus effect, e.g., the tendency for moving objects to generate backspin or end-to-end tumbling during air-resistant flight. The increased height and/or control of the aerial shells  14  provided by the rifled launcher according to embodiments of the present disclosure can allow the aerial shell  14  to have less (a reduced amount of) propellant in comparison to aerial shells fired from a launcher without rifling. For example, the aerial shells  14  according to the present disclosure can utilize about 5% to about 15% less propellant or lift charge  36  in comparison to aerial shells used with launchers that do not include rifling. The reduction in the percentage of the lift charge  36  can allow more effects charge  46  to be provided to provide more complex patterns or effects. For example, some fireworks, such as fireworks available to ordinary consumers, do not include sufficient amounts of effects charge to allow for complex patterns, e.g., patterns other than spherical shapes, but with the launcher according to principles of the present disclosure, these fireworks can be designed to have complex effects patterns. 
       FIGS. 5A and 5B  show perspective and exploded views of a launcher assembly  100  according to an additional aspect of the present disclosure. The launcher assembly  100  generally includes an outer portion  102 , an inner portion  104 , a wadding portion or insert  106 , and a base portion  108 , and can be used to launch one or more aerial shells  14  ( FIG. 2 ) as described above. 
     As shown in  FIGS. 5A and 5B , the outer portion  102  generally comprises a sleeve or tube  110  that has a body  112  with a sidewall  114  and a cavity or passage  116  defined therethrough. The body  112  of the sleeve  110  comprises upper  118  and lower  120  open ends, and a generally cylindrical or tubular shape, though other shapes, such as tubular shapes having square, rectangular, and/or polygonal cross-sections and/or other suitable shapes or cross-sections can be used without departing from the scope of the present disclosure. In some embodiments, the sleeve  110  can be formed from composite materials, such as paper-based products or plastic materials. For example, in one embodiment, the sleeve  112  can be formed from a hard plastic material, such as High Density Polyethylene (“HDPE”), though other plastics, such as Polyvinyl Chloride (“PVC”), and/or other polymeric materials. In an alternative embodiment, the sleeve  110  can be formed from paper, cardboard, or other paper-based products or laminate materials; however, any other suitable materials or combinations thereof can be employed without departing from the scope of the present disclosure. 
     In one example embodiment, the sleeve  110  can have a length from about 300 mm to about 400 mm, for example about 310 mm, about 320 mm, about 330 mm, about 340 mm, about 350 mm, about 360 mm, about 370 mm, about 380 mm, about 390 mm, or other integer and non-integer numbers therebetween. The sleeve  110  can have a length less than 300 mm or greater than 400 mm, however, without departing from the scope of the present disclosure. In addition, the sleeve  110  can have an outer diameter of about 50 mm to about 60 mm, such as about 51 mm, about 52 mm, about 53 mm, about 54 mm, about 55 mm, about 56 mm, about 57 mm, about 58 mm, about 59 mm, or other non-integer numbers therebetween, and the sleeve  110  can have an inner diameter of about 45 mm to about 55 mm, such as about 46 mm, about 47 mm, about 48 mm, about 49 mm, about 50 mm, about 51 mm, about 52 mm, about 53 mm, about 54 mm, or other non-integer numbers therebetween. The sidewall  114  of the sleeve  110  further can have a thickness of about 1 mm to about 3 mm, such as about 2 mm or other non-integer numbers therebetween. In an exemplary embodiment, the sidewall  114  of the sleeve  110  can have a thickness of about 2.25 mm. The cavity  116  of the sleeve  110  further can be sized, dimensioned, or otherwise configured to at least partially receive the inner portion  104 . It should be understood that the sleeve  110  can have any suitable size, dimensions, and/or configurations, without departing from the scope of the present disclosure. 
     As additionally shown in  FIGS. 5A and 5B , the inner portion  104  can include a firing tube  122 . The firing tube  122  comprises a body  124  with an outer sidewall  126  and a passage or cavity  128  defined therethrough. The passage  128  can be sized, dimensioned, or otherwise configured to receive one or more aerial shells  14  for firing from the launcher assembly  100 . For example, the aerial shell(s)  14  can be received/loaded into the passage  128  at an opening  130  along an upper end  132  of the firing tube  122 . The firing tube  122  further can include an interior surface  134  opposite the outer sidewall  126 , and the aerial shells  14  may at least partially engage, e.g., be in slidable contact with, the interior surface  134  during launching thereof. In one embodiment, the firing tube  122  can be formed from a metallic material, such as tin or aluminum, though other metals, e.g., steel, and/or other suitable materials, e.g., high strength plastics or other composite materials, can be used without departing from the scope of the present disclosure. 
       FIGS. 5A and 5B  further show that the firing tube  122  also can have a lip, bulge, or ring portion  136  defined at the upper end  132  thereof. In addition, or in the alternative, one or more lip, bulge, or ring portions can be formed along a lower end  156 , or other intermediate portion, of the firing tube  122 . The lip  136  can extend circumferentially about the sidewall  126  of the firing tube  122 . The lip  136  further can at least partially engage the interior surface  139  of the sleeve  110  of the outer portion  102 , for example, in frictional contact therewith, to facilitate attachment and/or to help to secure firing tube  122  within the cavity  116  of the sleeve  112 . The lip  136  can also substantially reinforce, for example, increase the strength or stress capacity along, the upper end  132  of the firing tube  122 . By way of example, it will be understood that, during or after firing of the aerial shell(s)  14  in the firing tube  122 , a maximum pressure may be experienced along the upper end  132  of the firing tube  122  and the lip  136  may help to prevent or minimize damage thereto during firing, and repeated firing, of the aerial shell(s)  14 . 
     The firing tube  122  also can include a plurality of rifling features  140  defined in and extending at least partially along the interior surface  134  of the firing tube  122 , as generally shown in  FIGS. 5A and 5B . For example, the rifling features  140  include one or more grooves or channels  142  defined in the interior surface  134  of the firing tube  122  and arranged in a prescribed pattern or configuration, e.g., a spiral or helical pattern, along the firing tube  122 , although other patterns of rifling are within the scope of the present disclosure. The channels  142  generally comprise a square or rectangular shape that is recessed to a prescribed depth with respect to the interior surface  134 , though other shapes, e.g., circular, triangular, or polygonal shapes, etc., can be employed without departing from the scope of the present disclosure. As described herein, the rifling features  140  can be formed through the sidewall  126  of the firing tube  122  such that complementary surface features are formed on the interior surface  134  of the firing tube  122  and the outer surface of the sidewall  126 . In one embodiment, the complementary surface features on the outer surface of the sidewall  126  can at least partially engage, e.g., grip or frictionally engage, the interior surface  139  of the sleeve  110  to maintain a secure coupling of the sleeve  110  and the firing tube  122  upon assembly thereof. However, any suitable retaining features can be arranged along the outer surface of the sidewall  126  to facilitate a secure coupling of the sleeve  110  and the firing tube  122 , without departing from the scope of the present disclosure. 
     As the aerial shell(s)  14  moves along the firing tube  122  after ignition thereof, the grooves or channels  142  of the rifling features  140  can cause the aerial shell(s)  14  to spin or rotate. For example, the grooves/channels  142  may interact with the combustion gases to cause a swirling effect and generate spin or rotation of the aerial shell(s)  14 . Additionally, or in the alternative, at least a portion of the aerial shell  14  may at least partially engage or contact the grooves or channels  142  to generate spin or rotation of the aerial shell  14 . The rotation or spin of the aerial shells  14  may be in a direction that is perpendicular or transverse to a central axis CA of the aerial shell  14 . The spinning or rotation of the aerial shell(s)  14  can provide, for example, enhanced control and increase height of the flight path of the aerial shells in comparison to shells fired from a launcher without rifling. The increased height and/or control of the aerial shells  14  provided by the rifled launcher assembly  100  according to embodiments of the present disclosure can allow the aerial shell  14  to have less (a reduced amount of) propellant in comparison to aerial shells fired from a launcher without rifling. For example, the aerial shells  14  according to the present disclosure can utilize about 5% to about 15% less propellant or lift charge  36  in comparison to aerial shells used with launchers that do not include rifling features. The reduction in the percentage of the lift charge  36  can allow the aerial charge  14  to include more effects charge  46  to allow for more complex patterns or effects. For example, some fireworks, such as fireworks available to ordinary consumers, do not include sufficient amounts of effects charge to allow for complex patterns, e.g., patterns other than spherical shapes, but with the launcher assembly  100  according to principles of the present disclosure, these fireworks can be designed to have complex effects patterns. 
     In one embodiment, the channels  142  can include a pair of opposing side walls or portions  144  with an intermediate wall or portion  146  extending therebetween ( FIGS. 5A and 5B ). The side walls  144  generally are positioned perpendicular with respect to the intermediate wall  146 , though the sidewalls  144  can be angled with respect to the intermediate wall/portion  146  without departing from the scope of present disclosure. In one example, the side walls  144  can have a length, i.e., the channel  142  can have a depth, of about 0.5 mm to about 5.0 mm, for example, about 1 mm, about 2 mm, about 3 mm, about 4 mm, or other non-integer numbers therebetween, though the sidewalls  144  can have a length (i.e., the channel  142  can have a depth) of less than 0.5 mm or greater than 5.0 mm without departing from the scope of the present disclosure. In addition, the intermediate wall  146  can have a length, i.e., the channels can have a width, of about 0.5 mm to about 5.0 mm, for example, about 1 mm, about 2 mm, about 3 mm, about 4 mm or other non-integer numbers therebetween, though the intermediate wall  146  can have a length (i.e., the channel can have a width) of less than 0.5 mm or greater than 5.0 mm without departing from the scope of the present disclosure. Although each of the channels  142  in  FIGS. 5A and 5B  are generally shown to have the same, or substantially similar, size or configuration, various channels can have different or varying sizes, dimensions, and/or configurations along the firing tube  122  without departing from the scope of the present disclosure. 
     The channels  142  further can be angled or have a twist rate so as to extend approximately 360° about the interior surface  134  of the firing tube  122  in a range from about every 50 mm to about every 500 mm, or other integer and non-integer numbers therebetween. Although the channels  142  can have any suitable twist rates, such as twist rates in which the channels  142  extend approximately 360° about the interior surface  134  of the firing tube  122  at a distance less than every 50 mm or at a distance greater than every 500 mm, without departing from the scope of the present disclosure. The rifling features  140  can include, for example, 10 or more equally spaced channels  142  arranged about the interior surface  134  of the firing tube  122 . However, any suitable number, arrangement, or configuration of channels  142 , for example, 10 or less, 11, 12, 13, 14, 15, 16, 17, 18, 19, or 20 or more channels  142  may be used without departing from the scope of the present disclosure. The channels  142  further can be spaced apart at a distance from about 0.5 mm to about 10 mm, for example, about 1 mm, about 2 mm, about 3 mm, about 4 mm, about 5 mm, about 6 mm, about 7 mm, about 8 mm, about 9 mm, or other non-integer numbers therebetween. The channels  142  can be spaced apart at any suitable distance, however, such as less than 0.5 mm or greater than 10 mm without departing from the scope of the present disclosure. 
     As further shown in  FIGS. 5A and 5B , the launcher assembly  100  can include a wadding portion or insert  106 . The wadding portion  106  can include a body  150  having a substantially cylindrical shape, or other suitable shape or configuration, that can be at least partially received within the passage  128  of the firing tube  122 . The body  150  of the wadding portion  106  can be formed from cork or other suitable material. The body  150  of the wadding portion  106  further can have a diameter of about 45 mm to about 55 mm, such as about 46 mm, about 47 mm, about 48 mm, about 49 mm, about 50 mm, about, 51 mm, about 52 mm, about 53 mm, about 54 mm, or other non-integer numbers therebetween, or any another suitable diameter that allows the wadding portion  106  to be at least partially received within the passage  128  of the firing tube  122 . The body  150  further can have a thickness or height of about 15 mm to about 25 mm, such as about 16 mm, about 17 mm, about 18 mm, about 19 mm, about 20 mm, about 21 mm, about 22 mm, about 23 mm, or about 24 mm, though the height/width can include any suitable value such as less than 15 mm or greater than 25 mm, without departing from the present disclosure. 
       FIG. 5B  additionally shows that the wadding portion  106  can be at least partially received within the passage  128  of the firing tube  122  at or substantially adjacent to a lower end  156  of the firing tube  122 . In one embodiment, the firing tube  122  further can have one or more projecting portions and/or other retaining features to at least partially engage the wadding portion  106  to substantially hold the wadding portion  106  in its position at the lower end  156  of the firing tube  122 . The wadding portion  106  further has a surface or face  152  at an upper end  154  thereof, which surface/face  152  can at least partially support aerial shells  14  received/loaded into the firing tube  122 . As a result, the wadding portion  106  may at least partially dampen and/or absorb stresses, pressure, or other forces generated from combustion gases resulting from ignition of the aerial shells  14 . The wadding portion  106  further may be replaceable/interchangeable to prolong the working life of the firing tube  122 , e.g., to prevent or reduce damage to, or wear of, the firing tube  122  due to firing, and repeated firing, of aerial shells  14  therefrom. 
       FIGS. 5A and 5B  also show that the launcher assembly  100  further can include a base or support portion  108 . The base  108  can have a body  160  with square or rectangular shape, though other shapes, such as triangular, circular, polygonal shapes, etc. are possible without departing from the present disclosure. The base  108  further can be formed from hard plastics or other polymeric materials, such as High Density Polyethylene (“HDPE”), Polyvinyl Chloride (“PVC”), etc., though any suitable material, such as metallic materials, paper-based products, or other composite materials can be employed without departing from the scope of the present disclosure. The base  108  further can have a width or diameter of about 1,000 mm to about 1,400 mm, such as about 1,100 mm, about 1,200 mm, about 1,300 mm, or other integer or non-integer numbers therebetween. For example, in an exemplary embodiment, the base  108  can have a width of about 1,255 mm. The base  108  can include any suitable width, such as widths less than 1,000 mm and greater than 1,400 mm, or other suitable dimensions, configurations, and/or constructions, so long as the base is generally configured to maintain the launcher assembly  100  in a generally erect/upright orientation before, during, and after firing of the aerial shell(s)  14  therefrom, without departing from the present disclosure. 
     The base  108  additionally has a projecting portion or other extending portion  162  defined along an upper surface  164  thereof. The projecting portion  162  can have a generally cylindrical shape that is configured to be at least partially received along or at least partially within the interior passage  134  of the firing tube  122 , e.g., at its lower end  156 , to facilitate connection of the base portion  108  to the firing tube  122 . In one example embodiment, the projecting portion  162  can have a diameter of about 45 mm to about 55 mm, such as about 46 mm, about 47 mm, about 48 mm, about 49 mm, about 50 mm, about 51 mm, about 52 mm, about 53 mm, about 54 mm, or other non-integer numbers therebetween, or another suitable diameter that allows the projecting portion to be at least partially received within or aligned along the firing tube  122 . In addition, in one embodiment, the projecting portion  162  can be fixedly connected to the firing tube  122 , for example, using one or more fasteners  166  such as nails, rivets, screws etc. ( FIG. 13 ). Any suitable fixing mechanism, such as an adhesive, soldering, welding, etc., however, may be employed to connect the base  108  and the firing tube  122 , without departing from the scope of the present disclosure. 
       FIGS. 6-13  show an exemplary method/process  200  for manufacturing and/or assembling the launcher assembly  100  according to one aspect of the present disclosure.  FIG. 6  shows a schematic view of a step  202  of forming a blank  204  for the firing tube  122  from a supply of material  206 , e.g., a supply of sheet metal, such as tin, aluminum, stainless steel, etc. For example, as shown in  FIG. 6 , a supply of sheet metal  206  can be at least partially fed into/received in a cutting machine  208 , such as a manually operated or hydraulic shear machine, to at least partially cut the supply of sheet metal  206  into a blank(s)  204  for forming the firing tube  122 . The cutting machine  208  can have a head  210  and a base portion  212 . The head  210  can have a cutting blade or other sharpened portion  214  attached thereto/arranged therealong, which cutting blade  214  can be brought into engagement with the supply of sheet metal  206  to cut a portion, e.g., a blank  204 , therefrom. The blank(s)  204  can be formed in any suitable manner, however, for example, by punching out the blank(s)  204  from the supply of sheet metal, or cast molding methods, etc., without departing from the scope of the present disclosure. Upon forming/obtaining the blank  204 , the rifling features  140  can be at least partially formed in and along a surface/face  216  of the blank  204 . 
       FIG. 7  shows a schematic view of a step  220  forming the rifling features  140  in the blank(s)  204 . As shown in  FIG. 7 , in one embodiment, the blank(s)  204  can be loaded into a machine press or other suitable machine  222  having a base portion  224  and a head portion  226 . The head portion  226  can be moveable, for example, along the vertical direction (shown as VD in  FIG. 7 ), for bringing or pressing a die portion  228  connected to the head portion  226  into engagement or contact with the surface/face  216  of the blank  204 .  FIG. 7  further illustrates that the die portion  228  can have a generally flat surface  230  with a plurality of protruding portions  232  formed therealong for forming the rifling features  140  in and along the surface/face  216  of the blank  204 . In one embodiment, the protruding portions  232  can have, for example, a generally rectangular or square cross-section shape, or other suitable cross-section or shape, e.g., round, arcuate, triangular, polygonal, etc., to facilitate the formation of corresponding channels  142 , for example, having a generally rectangular or square cross-section or other suitable cross-section or shape, into the surface  216  of the blank  204 . Additionally, the protruding portions  232  can be angled along the surface  230  of the die portion  228 . For example, the protruding portions  232  can be angled from about 20° to about 70°, such as, for example, about 25°, about 30°, about 35°, about 40°, about 45°, about 50°, about 55°, about 60°, about 65° or other integer or non-integer numbers therebetween, or combinations thereof, with respect to an end  234  of the die portion  228 . The protruding portions  232  can be disposed at suitable angle with respect to end  234  of the die portion  228 , however, such as less than 20° or greater than 70°, without departing from the scope of the present disclosure. As a result, after the die portion  228  has been at least partially pressed into engagement with the surface  216  of the blank  204  by movement of the head  226  upon activation of the machine press  222 , the surface  216  will have a plurality of channels  142  defined therealong to form the rifling features  140  along the firing tube  122 , and further, an opposing surface/face  236  of the blank  204  will have a plurality of corresponding projecting portions  238 , e.g., generally having rectangular or square cross-section, defined therealong. Although a machine press  222  is employed in step  220 , as shown in  FIG. 7 , to form the rifling features  140  into the blank(s)  204 , any suitable machine, mechanism, tool, process, etc. can be used to form the rifling features  140  in the blank(s)  204 . For example, the blank(s) can be fed through a press rolling machine with a roller having a plurality of projection portions defined therealong, or alternatively, cast molding or other suitable process can be employed for forming the rifling features in the blank without departing from the scope of the present disclosure. 
     In some embodiments, a protective layer can be applied to one or more of the surfaces  216  or  236  of the blank  204  after formation of the rifling features  140  therein. For example, the protective layer can include a protective coating, for example a PTFE (polytetrafluoroethylene) coating such as Teflon™ (available from The Chemours Company of Wilmington, Del.), or other suitable protective coating, at least partially applied to the surface/face  216  and the channels  142  defined therein to prevent or reduce wear or damage, for example, due to firing and/or repeated firing of aerial shells  14  from the firing tube  122 . 
       FIG. 8  provides a schematic illustration of a step  240  for forming, e.g., bending, the blank  204  to have a generally cylindrical shape. As shown in  FIG. 8 , the generally flat blank  204 , with the rifling features  140  defined therein, can be at least partially received within a roller apparatus/mechanism  242 . In one embodiment, the roller apparatus/mechanism  242  can include a roll forming machine or slip roll machine or any other suitable machine having a plurality of tubular or cylindrical portions  244  that can at least partially engage the blank  204  to bend or deform the blank  204  to have a generally cylindrical or tubular shape. For example, the plurality of tubular or cylindrical portions  244  can be rotated, e.g., by actuating a wheel or lever  246  of the roller apparatus/mechanism  242 , to engage or contact the blank  204  and bend or deform the blank  204  such that the blank  204  will define an at least partially formed cylinder  245  with discontinuous portion  246  therealong, e.g., with opposing sides/ends  248 / 250  of the blank  204  spaced apart and disconnected. Although  FIG. 8  shows a manually activated roll machine  242 , a hydraulic roll machine or other suitable apparatus can be used to form/bend the blank(s)  204  to have a generally cylindrical shape without departing from the scope of the present disclosure. 
       FIG. 9  provides a schematic illustration of a step  260  for forming one or more flanges  264 / 266  onto end/sides  248 / 250  of the blank  204 . As shown in  FIG. 9 , the disconnected ends/sides  248 / 250  of the at least partially formed cylinder  245  can be fed or received in a machine press  262  to bend or deform the ends/sides  248 / 250  to include one or more flanges  264 / 266  or other suitable portions. The machine press  262  may have a base portion  268  that has one or more angled or sloped surfaces or portions  270  and a movable head  272  with a die portion  276  attached thereto, which die portion  276  has a groove or notch  278  defined therealong to at least partially receive the angled or sloped portions  270  of the base portion  268 . Accordingly, at least a portion of the disconnected ends  248 / 250  of the cylinder  245  can be placed on or otherwise positioned along the one sloped/angled surfaces  270 , and the head  272  can be moved to bring the die portion  276  into contact or engagement with the disconnected ends  248 / 250  to bend or deform at least a portion of the disconnected ends  248 / 250  to form one or more flanges  264 / 266  therealong. The one or more flanges  264 / 266  formed along the disconnected ends  248 / 250  can be interlocked, intermeshed, or otherwise engaged together to facilitate the formation of a completed cylinder  275  ( FIG. 10 ). Any suitable mechanism, machine, process, etc. can be employed to form the flanges, however, without departing from the scope of the present disclosure. 
       FIG. 10  provides a schematic illustration of a step  278  of generating a seam  280  to form the partially formed cylinder  245  into a completed cylinder  275 . As shown in  FIG. 10 , the one or more flanges  232  along the disconnected ends  248 / 250  of the partially formed cylinder  245  can be interlocked or otherwise brought into engagement with each other to join the disconnected ends  248 / 250 . The interlocked flanges  264 / 266  then can be at least partially received along a mandrel  282  or other suitable cylindrical portion within a machine press  284  having a movable head  286  with a die portion  288  attached thereto. In one embodiment, the interlocked flanges  264 / 266  can be arranged in at least partial alignment with a groove or notch  290  ( FIG. 10 ), or alternatively a projecting portion (not shown), defined along the mandrel  282 . The head  286  of the machine press  284  then can be moved to bring the die portion  288  into engagement with the interlock flanges  264 / 266  to press the interlocked flanges  264 / 266  together and generate the seam  280  to form the completed cylinder  275 . The seam  280  can include a plurality of layers pressed together, with at least one layer from end  248  and at least one layer from end  250  sandwiched between the outer and interior surfaces of the completed cylinder  275 . 
       FIG. 11  provides a schematic illustration of a step  300  for reinforcing the seam  280  formed along the completed cylinder  275 . As shown in  FIG. 11 , the completed cylinder  275  can be placed or otherwise received along a mandrel  302  or other suitable portion having a series of protuberances or projections  304  formed therealong. For example, the completed cylinder  275  can be positioned about the mandrel  302  such that the protuberances or projections  304  are at least partially aligned along the seam  280 . The mandrel  302  further can have projection portions  306  arranged therealong that are sized to be at least partially received within the rifling features  140  defined along the firing tube  122 , for example, to facilitate alignment of the seam  280  therealong, as well to prevent damage to the rifling features  140  during reinforcement of the seam  280 . Accordingly, when a head  308  of the machine press  310 , in which the mandrel  302  is loaded into, is moved to bring a die portion  312  attached to the head portion  308  into engagement with the seam  280 , the plurality of protuberances or projections  304  at least partially engage the seam  280  to form a plurality of interlocking indentations/dimples and projections/protuberances therealong. The die portion  312  connected to the head  308  of the machine press  310  further can have grooves or notches  314  defined therealong that correspond to the rifling features  140  to prevent damage thereto when the die portion  312  is pressed against the seam  280  for reinforcement thereof. By way of example, when the die portion  312  is pressed or engaged against the seam  280 , corresponding indentations and projections can be formed in each of the layers of the seam  280  to facilitate locking therebetween, e.g., a projection of at least one layer of the seam  280  can be received within a corresponding indention of at least one adjacent layer of the seam  280  to prevent separation thereof. Accordingly, the firing tube  122 , and the seam  280  formed therealong, is able to withstand pressure/stresses developed during firing (and repeated firing) of one or more aerial shells  14  from the firing tube  122 . 
       FIG. 12  provides a schematic illustration of a step  320  for forming a lip, bulge, or ring portion  136  about the upper end  132  of the firing tube  122 . As shown in  FIG. 12 , the firing tube  122  can be at least partially loaded or received within a machine press  322 . Then, a die portion  324  attached to a head  326  of the machine press  322  can be brought into contact or engagement with the upper end  132  of the firing tube  122  to at least partially fold over a portion of the upper end  132  of the firing tube  122  to form a lip, bulge, or ring portion  136  therealong. The lip/ring  136  can substantially reinforce the upper end  132  of the firing tube  122 , where the pressure is the highest during launching of aerial shells  14 , and thereby prevent, reduce, or minimize damage to the firing tube  122  upon firing and/or repeated firing of one or more aerial shells  14  therefrom. In addition, the lip/ring  136  further can facilitate connection between the sleeve  110 , and the firing tube  122 . For example, with the sleeve  110  received about the firing tube  122 , the lip/ring  136  can at least partially engage the interior surface  139  of the sleeve  110  to substantially secure the firing tube  122  therein. In one embodiment, a lip/ring is additionally or alternatively provided at the lower end  156  of the firing tube  122 . 
       FIG. 13  shows a step  340  for assembling the launcher assembly  100  upon formation of the firing tube  122 . As shown in  FIG. 13 , the firing tube  122  can be at least partially received within the cavity  116  of the sleeve  110 . For example, the firing tube  122  can be press-fitted, for example, using a machine press or other suitable mechanism, machine, tool, etc., at least partially into the cavity  139  of the sleeve  110 . The lip/ring  136  of the firing tube  122  further can at least partially engage the interior surface  139  of the sleeve  110  to substantially secure the firing tube  122  therein. Additionally, the wadding portion  106  can be at least partially received within the passage  128  of the firing tube  122  at or substantially adjacent to a lower end  156  of the firing tube  122 . For example, the wadding insert  106  can be press-fitted, for example using a machine press or other suitable mechanism, machine, tool, etc., into the firing tube  122  such that the wadding insert  106  is positioned substantially adjacent the lower end  156  of the firing tube  122 . 
     Thereafter, as further shown in  FIG. 13 , the base  108  can be connected to the lower end  156  of the firing tube  122 . In one embodiment, the projecting portion  162  of the base  108  can be at least partially aligned with the lower end  156  of the firing tube  122  and in some embodiments, may be at least partially received within the passage  128  of the firing tube  122 . Then, the projecting portion  162  can be attached or secured to the firing tube  122  using one or more fasteners  166 , e.g., nails, screws, rivets, etc., though any suitable fixing mechanism, such as an adhesive, soldering, welding, etc., can be employed without departing from the scope of the present disclosure. 
     The foregoing description of the disclosure illustrates and describes various exemplary embodiments. Various additions, modifications, changes, etc. could be made to the exemplary embodiments without departing from the spirit and scope of the claims. It is intended that all matter contained in the above description or shown in the accompanying drawings shall be interpreted as illustrative and not in a limiting sense. Additionally, the disclosure shows and describes only selected embodiments of the disclosure, but the disclosure is capable of use in various other combinations, modifications, and environments and is capable of changes or modifications within the scope of the inventive concept as expressed herein, commensurate with the above teachings, and/or within the skill or knowledge of the relevant art. Furthermore, certain features and characteristics of each embodiment may be selectively interchanged and applied to other illustrated and non-illustrated embodiments of the disclosure.