Abstract:
A system and method for propelling pellets from a launch tube in flight includes a payload section and a stabilizing section. The launch tube and its pellets are essentially the payload section. The stabilizing section is essentially the equivalent of an arrow, and it includes a connector for selectively engaging the stabilizing section with the payload section. In use, the stabilizing section is reusable with a sequence of payload sections.

Description:
[0001]    This application is a continuation-in-part of application Ser. No. 13/298,124 filed Nov. 16, 2011, which is currently pending. The contents of application Ser. No. 13/298,124 are incorporated herein by reference. 
     
    
     FIELD OF THE INVENTION 
       [0002]    The present invention pertains generally to man-powered weapons. More particularly, the present invention pertains to systems and methods for shooting a plurality of pellets (i.e. projectiles or shot) at a target with a statistically predictable and defined shot group on the target. Further, the present invention pertains to devices for stabilizing pellet-cluster payloads, in flight, prior to a separation of the pellets from the stabilizing device. The present invention is particularly, but not exclusively, useful as a system and method for propelling a multi-pellet-filled launch tube from a man-powered weapon, and for employing the resultant acceleration force on the launch tube to unlatch and release the pellets from the launch tube for impact in a shot group on a target. 
       BACKGROUND OF THE INVENTION 
       [0003]    Typically, man-powered weapons are designed to launch only one projectile at a time. In particular, this is the case when the weapon is to be operated and fired by a single individual. For example, the arrow of a well-known bow and arrow set is such a projectile, as is the bolt of a crossbow or the dart of a blowgun. There are instances, however (e.g. the extermination of vermin or clay pigeon shooting), when it would be preferable to simultaneously launch several projectiles (e.g. pellets) all at the same time. In this respect, there is a need for a man-powered weapon that is comparable in its on-target effect to the familiar shotgun. To achieve such comparability with a man-powered weapon, like a shotgun, all of the pellets need to be collectively launched as a predictably defined group. The situation for a man-powered weapon is exacerbated, however, due to the fact that they typically employ only a single launching string or, in the case of an air gun, a single launching tube. 
         [0004]    Ideally, when a plurality of projectiles are to be launched simultaneously from a single man-powered weapon, the launching mechanism of the weapon needs to have comparably direct influence upon each projectile (e.g. pellet). Specifically, the influence and control over each projectile in the plurality must be similar, and be effective to the same extent, as if only one projectile was being launched. It happens, however, that with a single string or single barrel launcher (e.g. a bow, a crossbow or an air gun), such influence and control is virtually impossible. A solution for this problem is to, somehow, structurally combine the several projectiles into a cohesive unit for launch. This solution, of course, must be short term. Immediately after launch, the problem then becomes how to effectively separate the projectiles. Specifically, this separation must be accomplished in a manner that causes the projectiles to travel toward a target in a predictably defined group that will have the intended on-target effect. 
         [0005]    As a cost saving feature, it is desirable there be a system component that can be used, and reused. For the present invention, this component is envisioned to be a stabilizing section (i.e. an arrow) that provides initial aerodynamic stability for a payload of multiple pellets (projectiles). Specifically, the stability provided by this stabilizing section (arrow) is required immediately after a launch, but before there is pellet separation from the payload. Furthermore, depending on the target, on the capabilities of the user, and on the situational circumstance, it may be desirable that the user be able to select a particular payload. More specifically, it may be desirable to select a payload having a predetermined number of pellets in the payload, wherein the pellets are of a specific size. 
         [0006]    With the above in mind, it is an object of the present invention to provide a multi-pellet launcher that will hold a plurality of projectiles together as a single cohesive unit prior to and during launch. Another object of the present invention is to provide a multi-pellet launcher that will maintain a group integrity for the pellets (projectiles) while in flight, for the purposes of achieving an intended on-target effect (i.e. have a statistically well defined shot group). Yet another object of the present invention is to provide a reusable, aerodynamic stabilizing section that is individually engageable with different selected multi-pellet launchers (i.e. payloads). Still another object of the present invention is to provide a multi-pellet launcher that is easy to use, is simple to manufacture, and is cost effective. 
       SUMMARY OF THE INVENTION 
       [0007]    In accordance with the present invention, a system is provided for propelling pellets (projectiles) from a launch tube. In particular, the propulsion of pellets occurs after the launch tube has been shot from a man-powered weapon (e.g. a bow, a crossbow or an air gun). Prior to being shot (launched), the launch tube holds a plurality of pellets inside the tube. Specifically, this is accomplished by positioning the pellets between a retainer plug that is restrained inside the launch tube, and a compression spring that is fixedly mounted inside the launch tube. In order to restrain the retainer plug, a latch is established relative to the launch tube. The latch then prevents a forward movement of the retainer plug, and the pellets, in response to a bias force that is imposed on the retainer plug and the pellets by the partially compressed spring. 
         [0008]    In overview, while the launch tube is being propelled in a forward direction by a man-powered weapon, the resultant acceleration force on the launch tube moves the retainer plug and pellets in a relatively rearward (proximal) direction with respect to the tube. This proximal movement of the retainer plug and pellets in the launch tube further compresses the spring, and simultaneously releases the latch from the retainer plug. In flight, after the initial acceleration force has subsided, the compressed spring provides a forward propulsion force on the plurality of pellets and the retainer plug. This propulsion force then ejects the pellets and the retainer plug from the launch tube. The pellets then continue on toward an intended target. 
         [0009]    Structurally, the launch tube of the present invention is formed with a lumen, and it defines a longitudinal axis. In a preferred embodiment of the present invention, it also has an open distal end and a closed or partially closed proximal end. Beginning at the proximal end of the lumen inside the launch tube, the spring is positioned and affixed to its closed proximal end. The plurality of pellets (projectiles) is then positioned in the lumen against the spring. Next, the retainer plug is positioned in the lumen distal to the plurality of pellets (projectiles). In greater structural detail, for one embodiment of the present invention, the retainer plug has a distal ring that is dimensioned to move within the lumen, and it has a proximal ring that is also dimensioned to move within the lumen. Between these rings of the retainer ring is a mid-section that is formed with a decreasing taper in the proximal direction. 
         [0010]    In the vicinity of the retainer plug, the sidewall of the launch tube is formed with one or more lateral vents. Preferably, these vents are located equidistant from the distal end of the tube. One or more latch spheres are provided to interact between the proximal ring of the retainer plug and the vents of the launch tube. Specifically, this interaction is in response to the distally directed force that is generated when the spring is partially compressed. More specifically, each latch sphere is trapped in a respective vent, and it is urged against a distal edge of the vent by the proximal ring of the retainer plug. Thus, prior to a launch, the distal bias of the compressed spring on the retainer plug holds the retainer plug, and the pellets, stationary in the lumen of the launch tube. 
         [0011]    Upon shooting a launch tube from a man-powered weapon, an acceleration force is imposed in a distal direction on the pellets, and on the proximal end of the spring within the lumen of the launch tube. This acceleration causes the retainer plug and pellets to move proximally relative to the launch tube, and the spring is further compressed. In turn, this relative motion of the retainer plug and launch tube causes the proximal ring of the retainer plug to release the latch sphere(s) and causes a tapered or stepped region of the retainer plug to eject the latch sphere(s) from the launch tube through their respective vents. Consequently, the retainer plug and the plurality of pellets are released by the latch and are propelled from the launch tube in response to the distal bias of the spring. 
         [0012]    An additional structure of the launch tube is an inner sleeve that can be affixed inside the lumen of the launch tube, proximal to the spring. Specifically, this inner sleeve is positioned at a distance “d f ” from the distal end of the launch tube to act as an abutment for the spring when it is compressed. The distance “d f ” can, of course, be varied as desired. In any event, it is preferable that the inner sleeve be affixed to place the pellets (projectiles) relatively near the distal end of the launch tube. With this in mind, the present invention envisions that, even though the pellets may extend through a relatively short distance (i.e. a few inches), an inner sleeve will allow the total length of the launch tube to be as long as is required for a conventional bow, compound bow or crossbow. 
         [0013]    For a preferred embodiment of the present invention, there may be as many as forty or more pellets, and they can be made of steel. Also, in order to promote tumbling of the retainer plug after a launch of the launcher, the distal ring of the retainer plug may be formed with a distal recessed surface, and is made of a light-weight material such as Acrilonitrile-Butadiene-Styrene (ABS), Polycarbonate or Polysulfone. Also, for the purpose of dispensing the pellets in-flight for a controlled, on-target impact, the pellets inside the launch tube can be combined with a plurality of spacers. If used, individual spacers can be positioned between adjacent pellets in the launch tube. In another embodiment, for the same purpose, a plurality of magnets can be combined with the pellets in a configuration where adjacent magnets straddle two pellets, and pellets on opposed sides of a same magnet are subjected to a different polarity. 
         [0014]    For an alternate embodiment of a latch for the multi-pellet launcher, the launch tube is formed with a pair of axially opposed slots that extend, parallel to each other, in a proximal direction from the distal end of the launch tube. A detent is formed at the proximal end of each slot. For this embodiment, the retainer plug is cylindrical and includes a pair of axially opposed pins that extend outwardly from the retainer plug. For an assembly of the multi-pellet launcher in accordance with this alternate embodiment, the pins on the retainer plug are received in a respective slot of the launch tube and are advanced in a proximal direction. When the pins are at the proximal end of their respective slots, the retainer plug is rotated to engage the pins with a respective detent at the end of the slot. This holds the retainer plug stationary in the launch tube. Upon a subsequent launching of the launch tube, the resultant acceleration force rotates the pins out of their detents. This then frees the retainer plug for axial movement out of the launch tube in a distal direction when the acceleration force subsides. It is an important consideration for this particular embodiment of the latch, that the pins do not extend beyond the outer diameter of the launch tube when the retainer plug is engaged with the launch tube. This is necessary to allow an assembled launcher to be received within the barrel of a weapon (e.g. an air gun) without any interference of the pins on the retainer plug with the bore of the barrel. 
         [0015]    In yet another embodiment of a latch for the present invention, the launch tube is formed with at least one lateral opening. For this embodiment, the retainer plug includes a clip that is mounted on the retainer plug, and the clip is reconfigured to engage with the lateral opening. Importantly, the clip does not extend beyond the lateral opening. When the launch tube is launched, as in the other embodiments of the present invention, the resultant acceleration force moves the retainer plug in a proximal direction relative to the launch tube. Consequently, the clip is released from the lateral opening. The retainer plug is thereby released for free travel through the launch tube. 
         [0016]    In yet another alternate embodiment that is within the scope of the present invention, a system is provided for launching a pellet-cluster onto a flight path from a man-powered weapon that includes reusable components. Such a system includes a payload section as substantially disclosed above, and a reusable stabilizer section (i.e. an arrow). As before, the payload section carries pellets in a pellet-cluster for an in-flight release of the pellet-cluster from the payload section. For this particular embodiment of the present invention, however, the payload section is selectively engageable with the stabilizer section. Structurally, the stabilizer section includes a shaft that defines a longitudinal axis and has an aft-end and a fore-end. A plurality of fletches are attached to the aft-end of the shaft to establish an empennage for stabilizing the shaft and payload section during flight. Further, a connector is affixed to the fore-end of the shaft. As envisioned for the present invention, the payload section is formed with an insert extension and the connector is formed as an insert receptacle for receiving the insert extension therein to hold the payload on the arrow. With this structure, the engagement of the payload with the arrow may be either a friction fit or a bayonet fit. When assembled, the payload section and the stabilizer section will typically have an overall length that is between four and thirty two inches. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0017]    The novel features of this invention, as well as the invention itself, both as to its structure and its operation, will be best understood from the accompanying drawings, taken in conjunction with the accompanying description, in which similar reference characters refer to similar parts, and in which: 
           [0018]      FIG. 1  is a side elevation view of a multi-pellet launcher in accordance with the present invention; 
           [0019]      FIG. 2A  is a perspective view of a launcher of the present invention during mid-launch from a crossbow; 
           [0020]      FIG. 2B  is a plan/elevation view of the launcher of the present invention prepared for launch from a bow; 
           [0021]      FIG. 3  is a plan/elevation view of an air gun for use with the present invention; 
           [0022]      FIG. 4A  is a cross-section view of the multi-pellet launcher as seen along the line  4 - 4  in  FIG. 1  prior to launch; 
           [0023]      FIG. 4B  is a cross-section view of the multi-pellet launcher as seen in  FIG. 4A  as the launcher is being accelerated during launch; 
           [0024]      FIG. 4C  is a cross-section view of the multi-pellet launcher as seen in  FIG. 4B  after launch; 
           [0025]      FIG. 5  is a cross-section view of an alternate embodiment of a multi-pellet launcher as would be seen along the line  4 - 4  in  FIG. 1 ; 
           [0026]      FIG. 6  is a cross-section view of another embodiment of the multi-pellet launcher as seen along the line  4 - 4  in  FIG. 1 ; 
           [0027]      FIG. 7A  is an exploded perspective view of an alternate embodiment of a launch tube and retainer plug for use with the present invention, with the retainer plug positioned for engagement with the launch tube; 
           [0028]      FIG. 7B  is a view as shown in  FIG. 7A  with the retainer plug engaged with the launch tube; 
           [0029]      FIG. 8A  is a cross-section view of a launcher as seen along the line  8 - 8  in  FIG. 7A  prior to a launch; 
           [0030]      FIG. 8B  is a cross-section view of the launcher shown in  FIG. 8A , immediately after a launch; 
           [0031]      FIG. 8C  is a front-on view looking into the launch tube of the launcher; 
           [0032]      FIG. 8D  is a cross-section view of an alternate embodiment for the inner sleeve shown in  FIG. 8A , prior to launch; 
           [0033]      FIG. 8E  is a cross-section view of the inner sleeve shown in  FIG. 8D , immediately after launch; 
           [0034]      FIG. 9A  is a cross-section view of another alternate embodiment of a launch tube and retainer plug prior to a launch; 
           [0035]      FIG. 9B  is a cross-section view of the launch tube shown in  FIG. 9A  immediately after a launch; 
           [0036]      FIG. 10  is a perspective view of a spring guide for use with the spring in an alternate embodiment of the present invention; 
           [0037]      FIG. 11A  is a cross sectional view of a launcher using a spring guide, as seen along the line  8 - 8  in  FIG. 7A , prior to launch; 
           [0038]      FIG. 11B  is a view of the launcher shown in  FIG. 11A  immediately after launch; 
           [0039]      FIG. 12A  is an exploded perspective view of a reusable, aerodynamic stability section, positioned for engagement with a launcher of the present invention; and 
           [0040]      FIG. 12B  is an exploded perspective view of an alternate embodiment of a reusable, aerodynamic stability section, positioned for engagement with a launcher of the present invention. 
       
    
    
     DESCRIPTION OF THE PREFERRED EMBODIMENTS 
       [0041]    Referring initially to  FIG. 1 , a multi-pellet launcher in accordance with the present invention is shown and is generally designated  10 . As shown, the launcher  10  includes a hollow, elongated launch tube  12  that has a distal end  14  and a proximal end  16 . For the launcher  10 , the distal end  14  of launch tube  12  is open, and its proximal end  16  is closed or partially closed. For purposes of disclosure, the launch tube  12  defines a longitudinal axis  18  that extends between the distal end  14  and the proximal end  16 . As intended for the present invention, the launcher  10  can be used as a bolt for a crossbow  20  (see  FIG. 2A ), as an arrow for a bow  22  (see  FIG. 2B ) or as a launch tube  12  to be used with an air gun  23  and launched from its barrel  25  (see  FIG. 3 ). In all important respects, the multi-pellet launcher  10  will be essentially the same regardless of the type of man-powered weapon that is to be used (i.e. crossbow  20 , bow  22  or air gun  23 ). 
         [0042]    Referring now to  FIG. 4A , a launcher  10  is shown in greater detail to include a nock  24  at its proximal end  16  and a flight stabilizer  26  that will stabilize the launch tube  12  during its flight. Other structural aspects of the launcher  10  are discussed with reference to the lumen  28  of the launch tube  12 , and begin with an inner sleeve  30  that is fixedly attached to the launch tube  12 , inside the lumen  28 . Referring for the moment back to  FIG. 1 , it will be seen that the inner sleeve  30  is positioned in the lumen  28  of the launch tube  12  at a distance “d f ” from the distal end  14  of the launch tube  12 .  FIG. 1  also indicates that the inner sleeve  30  is positioned at a distance “d a ” from the proximal end  16  of the launch tube  12 . 
         [0043]      FIG. 4A  also shows that a spring  32  is positioned in the lumen  28  immediately distal the inner sleeve  30 , and between the inner sleeve  30  and a plurality of pellets  34 . As intended for the launcher  10 , there may be six or more pellets  34 . The pellets  34  shown in the drawings are only exemplary. It will be appreciated that the distance “d f ” will depend primarily on the number of pellets  34  that are to be used. On the other hand, the distance “d a ” may vary considerably, depending on the type of man-powered weapon to be used. As envisioned for the present invention, the overall length of the launcher  10  (i.e. d f +d a ) may be as long as twenty nine or thirty inches. 
         [0044]    Positioned distal to the pellets  34  is a retainer plug  36  that is preferably made of a light weight material such as Acrilonitrile-Butadiene-Styrene (ABS), Polycarbonate or Polysulfone. Structurally, the retainer plug  36  is formed with a proximal ring  38  and a distal ring  40 , with a mid-section  42  formed therebetween. Importantly, both the proximal ring  38  and the distal ring  40  are dimensioned for movement within the lumen  28  of the launch tube  12 . Further, it is important that the mid-section  42  be formed with a decreasing taper in the proximal direction from the distal ring  40  to the proximal ring  38 . 
         [0045]    As perhaps best seen in  FIG. 4B , the launch tube  12  is formed with one or more vents  44 . In  FIG. 4B , the vents  44   a  and  44   b  are only exemplary, as there may be more vents  44  if desired. Both  FIGS. 4A and 4B , however, show that each vent  44  interacts with a respective latch sphere  46 . Again, like the vents  44   a  and  44   b , the latch spheres  46   a  and  46   b  are only exemplary. Despite the number of vents  44  and latch spheres  46  that may be used, it is to be appreciated that each latch sphere  46  interacts individually with the retainer plug  36  and with its respective vent  44 . Importantly, the purpose of these interactions is to hold the pellets  34  in the lumen  28  of the launch tube  12  prior to a launch. Specifically,  FIG. 4A  shows that prior to a launch, each of the latch spheres  46  is trapped (wedged) between the proximal ring  38  of the retainer plug  36  and the forward (distal) edge of a vent  44 . This structural interaction changes dramatically with a launch of the launch tube  12 . 
         [0046]    As a launch tube  12  is launched from a crossbow  20 , or bow  22 , in the direction of arrow  47  (see  FIG. 4B ) an acceleration force is generated that will cause the retainer plug  36  and the plurality of pellets  34  to move in a proximal direction inside the lumen  28  of the launch tube  12 . With this movement, several things happen. For one, the spring  32  is further compressed. For another, as the retainer plug  36  moves in the proximal direction, the proximal ring  38  of retainer plug  36  disengages from the latch spheres  46 . As this happens, the tapered mid-section  42  of the retainer plug  36  ejects the latch spheres  46  away from the launch tube  12 , through their respective vents  44 . A consequence of this is that both the retainer plug  36  and the pellets  34  are no longer confined in the lumen  28  of the launch tube  12 . 
         [0047]    Shortly after launch, in accordance with well known principles, the initial acceleration force on the launch tube  12  subsides. With this diminution of the acceleration force, the potential energy in the compressed spring  32  is released to propel the retainer plug  36  and pellets  34  from the launch tube  12 . As shown in  FIG. 4C , after being propelled from the launch tube  12  by the spring  32 , the retainer plug  36  separates and tumbles away from the pellets  34 . To assist in this separation and tumbling behavior, the distal face  48  of retainer plug  36  can be formed with a recessed (concave) surface. In any event, the desired result is that the plurality of pellets  34  will then follow a planned trajectory toward a target (not shown), for an intended on-target affect. An important consideration here is that the pellets  34  need to also achieve a degree of separation from each other for the creation of the desired on-target shot group. 
         [0048]    For an alternate embodiment of the launcher  10 , as shown in  FIG. 5 , a plurality of spacers  50  can be employed to help with the separation of pellets  34  after launch. The spacers  50   a  and  50   b  shown in  FIG. 5  are exemplary. If used, the spacers  50  will typically be positioned to straddle each pellet  34  in a manner such as is shown for the spacers  50   a  and  50   b . Preferably, the spacers  50  will be made of a light weight material such as felt or paper. In another alternate embodiment of the launcher  10  for this same purpose, as shown in  FIG. 6 , a plurality of magnets  52  can be employed. In this embodiment, a pair of magnets (e.g. magnets  52   a  and  52   b ) will straddle a pair of pellets (e.g. pellets  34   a  and  34   b ). For best effect, within this structure, the opposed sides of the magnets  52   a  and  52   b  will have the same polarity. Thus, the magnets  52  (magnets  52   a  and  52   b  are exemplary) will add a repelling force on the pellets  34   a  and  34   b  that will influence their separation in flight. 
         [0049]    An alternate embodiment for the structure of a latch to be used with the present invention is shown in  FIGS. 7A &amp; 7B . In  FIG. 7A  it will be seen that a launch tube  54  has a proximal end  56  and a distal end  58 , with a pair of opposed parallel slots  60   a  and  60   b  that extends in a proximal direction from the distal end  58 . Further, with reference to the slot  60   a  in  FIG. 7A , it is seen that the end of the slot  60   a  is formed with a detent  62 , and an angled edge  64  extends in a proximal direction therefrom.  FIG. 7A  also shows a cylindrical shaped retainer plug  66  that includes a pin  68  which extends outwardly from the plug  66 . Actually, there is a pair of opposed pins  68  (one is not shown). With reference to  FIG. 7B , it will be appreciated that during an assembly of the retainer plug  66  with the launch tube  54 , the pin(s)  68  is(are) inserted into the respective slots  60   a  and  60   b . They are advanced through the slots  60   a  and  60   b , and the retainer plug  66  is then rotated to seat the pin(s)  68  against the detent(s)  62 . 
         [0050]    In an operation of the launch tube  54 , the acceleration force that initially results during a launch of the launch tube  54  will cause the retainer plug  66  to move in a rearward (proximal) direction relative to the launch tube  54 . This relative movement of the retainer plug  66  then causes the pin  68  to follow the angled edge  64 . The result here is that the retainer plug  66  is rotated to realign the pin  68  with the slot  60   a , and to thereby allow for a free distal (forward) movement of the retainer plug  66  out of the launch tube  54  when the acceleration force subsides. An important aspect of this particular embodiment of a latching action for the present invention is that the pin(s)  68  do not extend beyond the outer surface  70  of the launch tube  54 . This is so in order to allow for an assembled launch tube  54  to be positioned in a hollow launch tube (not shown), such as in the barrel of an air gun  23 . Additionally, it will be appreciated by the skilled artisan that the inside surface  72  of the barrel  25  of air gun  23  can be rifled to assist in the proper rotation and alignment of the retainer plug  66  during an operation of this embodiment of the present invention. 
         [0051]      FIG. 8A  shows an alternate configuration for components inside the launch tube  12 / 54 . One component of interest is the inner sleeve  74 . As shown, the inner sleeve  74  is positioned inside the launch tube  12 / 54 , and is preferably located at or near the proximal end  56 . Further, the inner sleeve  74  includes an abutment  76  that establishes a hollow  78  for the inner sleeve  74 . Within this structure, the spring  32  is positioned between the abutment  76  and a washer  80 . Importantly, when so positioned, a portion of the spring  32  will be inside the hollow  78 . Thus, as shown in  FIG. 8B , when the spring  32  is compressed by a force of acceleration (represented by arrow  82  in  FIG. 8B ), compression of the spring  32  is controlled. Specifically, during a launch of the launch tube  12 / 54 , the compression of spring  32  will be limited by the constraints imposed on it by dimensions of the hollow  78  inside the inner sleeve  74 .  FIGS. 8A and 8B  also indicate that the abutment  76  of the inner sleeve  74  can be formed with an opening  84 . Opening  84 , however, is optional. Indeed, when the launch tube  54  is to be used with an air gun (not shown), it is preferable that the opening  84  be closed. 
         [0052]    Still referring to  FIGS. 8A and 8B , an arrangement for stacking pellets  34  (e.g. pellets  34   c - f ) within a launch tube  12 / 54  is shown. In detail, by cross referencing  FIG. 8B  with  FIG. 8C , a stacking arrangement for a relatively large number of the pellets  34  (e.g. thirty or more pellets  34 ) is shown. In particular, this stacking arrangement is possible when each of the pellets  34  has a diameter “d p ” that is slightly less than half the inner diameter “d i ” of the launch tube  12 / 54  (see  FIG. 8C ). For purposes of disclosure, specific reference is made to pellets  34   c ,  34   d ,  34   e  and  34   f  (only pellets  34   c ,  34   d  and  34   f  are shown in  FIG. 8B ). With  FIGS. 8B and 8C , it will be appreciated that the pellets  34   c  and  34   e  are essentially positioned inside the launch tube  12 / 54 , side-by-side. Likewise, the pellets  34   d  and  34   f  are also side-by-side. In order to easily achieve this stacking configuration during loading, the pellets  34   c - f  can be introduced into the launcher tube  12 / 54  in pairs (e.g. pellets  34   d  and  34   f  together, and then pellets  34   c  and  34   e ). 
         [0053]      FIG. 8D  shows a two-part alternative structure for the inner sleeve  74  that was disclosed above and is shown in  FIG. 8A . Specifically, for this embodiment, a distal inner sleeve  74 ′ and associated abutment  76 ′ are shown in axial alignment with the inner sleeve  74  and its abutment  76 . For both embodiments, the object is to control compression of the spring  32  (compare  FIG. 8E  with  FIG. 8B ). 
         [0054]    Referring now to  FIGS. 9A and 9B , yet another embodiment of a latching mechanism for the launcher  10  of the present invention is shown. In this embodiment, the launch tube  12 / 54  is formed with at least one lateral opening  86 , and a clip  88  is mounted on a cylindrical shaped retainer plug  90 . When the retainer plug  90  and its clip  88  are positioned in the lumen  28  of a launch tube  12 / 54 , and the clip  88  is received in the lateral opening  86  of the launch tube  12  (see  FIG. 9A ), the clip  88  will hold the retainer plug  90  stationary in the launch tube  12 / 54 . Specifically, this will be in response to forces imposed on the retainer plug  90  by a spring  32  (not shown in  FIGS. 9A and 9B ). Importantly, the clip  88  will not extend beyond the lateral opening  86 . As with the other latching embodiments for the present invention, the retainer plug  90  is acceleration activated. Thus, in response to the acceleration force of a launch, the retainer plug  90  moves in a proximal (rearward) direction. This then frees the clip  88  from the lateral opening  86  for subsequent free travel of the retainer plug  90  through the launch tube  12 / 54  along with the propulsion of pellets  34   a  (et. seq.) from the launch tube  12 / 54 . 
         [0055]    In yet another configuration for components inside the launch tube  12 / 54 , a spring guide  92  is employed to control and restrict compression of the spring  32 . As shown in  FIG. 10 , the spring guide  92  includes a base  94  and an extension  96  which projects from the base  94 . A through hole  98  is formed in the spring guide  92 , and this through hole  98  extends through both the base  94  and the extension  96 . Preferably, the spring guide  92  is made of a rigid, light-weight material such as polycarbonate. 
         [0056]      FIGS. 11A and 11B  show how a spring guide  92  is employed by the present invention. First, in  FIG. 11A , it will be seen that a pair of spring guides  92  are used with the spring  32 . Specifically, there is a distal spring guide  92   a  and a proximal spring guide  92   b  that are respectively engaged with opposite ends of the spring  32 . As shown in  FIG. 11A , both of the spring guides  92   a  and  92   b  are positioned in the launch tube  12 / 54  with their respective extensions  96  inserted into the center space of spring  32 . Further, the base  94  of distal spring guide  92   a  is positioned against the pellet(s)  34 , and the base  94  of proximal spring guide  92   b  is positioned against the abutment  76  at the proximal end  56  of the launch tube  12 / 54 . As shown in  FIG. 11A , the configuration of the spring  32  with the spring guides  92   a  and  92   b  is prior to a launch. After launch, the spring  32  is compressed substantially as shown in  FIG. 11B  by the acceleration force of the launch. Importantly, this compression of spring  32  is limited during an acceleration by the contact that occurs between the extension  96  of spring guide  92   a  and the extension  96  of spring guide  92   b . A consequence of this is that the spring guides  92   a  and  92   b  help prevent a fouling of the spring  32  during its operation. 
         [0057]    Referring now to  FIG. 12A , an alternate embodiment of a system for firing the launcher  10  is shown, and is generally designated  100 . As shown, the system  100  includes a stabilizing section  102  and a payload section  104 . In particular, the payload section  104  includes a multi-pellet launcher  10 , as disclosed above, which has been modified to incorporate an insert extension  106 . In all other important respects, the launcher  10  is substantially the same as disclosed earlier. The stabilizing section  102 , however, is unique unto itself. 
         [0058]    Functionally, the stabilizing section  102  (see  FIG. 12A ) is effectively the same as an ordinary arrow that would be used with a conventional bow  22 . Also, the stabilizing section  102 ′ (see  FIG. 12B ) can be dimensioned as a bolt that would be used with a crossbow  20 . Structurally, as shown for the system  100  in  FIG. 12A , the stabilizing section  102  for both embodiments includes a shaft  108  that has an empennage  110 . A fletching  112  is provided as part of the empennage  110 . At the forward end  114  of the shaft  108  is a connector  116  that is formed with an insert receptacle  118 . As intended for the present invention, for the embodiment as shown in  FIG. 12A , an assembly of the system  100  merely requires a user to insert the insert extension  106  of the payload section  104  into the insert receptacle  118  of the payload section  104 . Preferably, this insertion results in a “friction” or “interference” fit between the insert extension  106  of the payload section  104 , and the insert receptacle  118  of the stabilizing section  102 . As intended for the present invention, after a use of the system  100 , and after pellets  34  have been released from the launcher  10 , the payload section  104  can be removed from the stabilizing section  102 . The stabilizing section  102  can then be reused, and a different payload section  104  can then be used with this same stabilizing section  102 . 
         [0059]    For an alternate embodiment of the system  100  as shown in  FIG. 12B , the insert extension  106 ′ of the payload section  104  is shown to include a pin  120 . Further, the connector  116 ′ of the stabilizing section  102  is shown to include a slot  122  that is formed with a detent  124 . Specifically, the slot  122  is axially aligned along the length of the shaft  108 ′ and is dimensioned to receive the pin  120 . Thus, a so-called “bayonet” connection is established wherein the pin  120 , after being inserted into the slot  122  and advanced in a proximal direction toward the empennage  110 , can be rotated into the detent  124 . Again, as with the embodiment shown in  FIG. 12A  and disclosed above, after a use of the system  100 , the payload section  104  can be removed from the stabilizing section  102 . Again, the stabilizing section  102  can be reused, and a different payload section  104  can then be used with the same stabilizing section  102 . 
         [0060]    As envisioned for the system  100 , the length “L” (see  FIG. 12A ) between the empennage  110  and the connector  116  of the stabilizing section  102  can be established depending on its intended use. For a conventional bow  22 , the length “L” will be equivalent to a typical arrow (e.g.  FIG. 12A ), and will be somewhere around thirty two inches. On the other hand, the length “L” may be more equivalent to a bolt (e.g. see  FIG. 12B ) that is to be shot from a crossbow  20 . In this latter case the length “L” will be somewhere around four inches. 
         [0061]    While the particular Arrow for Aerodynamically Stabilizing a Payload in Flight as herein shown and disclosed in detail is fully capable of obtaining the objects and providing the advantages herein before stated, it is to be understood that it is merely illustrative of the presently preferred embodiments of the invention and that no limitations are intended to the details of construction or design herein shown other than as described in the appended claims.