Abstract:
An apparatus is disclosed that is a self-contained gas management system (hereinafter “GMS”) that accommodates individual canisters of highly energetic small munitions, but is not so limited. By decoupling the gas management system for a given munition from an adjacent munition, the risk of downing a multi-pack launcher or munition adapter is reduced. Thermal wear, overheating, restrained firing and aft closure debris can be isolated through the separation of gas management systems. In addition, the GMS allows for ease of replenishment and maintenance of a given sub-cell of a multi-pack system. The GMS works with existing munitions and canisters without the need to modify them. Each GMS is dimensioned to fit the canistered munition it receives as well as the launch system with which it is used. The illustrative GMS comprises a plenum, and a first and a second uptake structure. The plenum receives the exhaust from the canistered munition when the munition fires. The plenum is fluidically coupled to the first and second uptake structures. The uptake structures in the illustrative embodiment receive the missile exhaust from the plenum and vent the exhaust to the atmosphere. In the illustrative embodiment, the first and second uptake structures are disposed along opposite sides of the canistered munition, flanking it.

Description:
FIELD OF THE INVENTION 
     The present invention relates to missile launchers, and more particularly to vertical missile launchers. 
     BACKGROUND OF THE INVENTION 
     Modern warships use guided missiles as their principal offensive and defensive weapons. Since a naval engagement may be protracted, a warship must have many missiles available for immediate launch. This need has been addressed by multiple-missile launchers, in which plural launch cells (e.g., eight cells, etc.) are loaded with missiles that can be individually launched. 
     There is also a need to launch, from a single multiple-missile launcher, missiles of different mission type. This need has been met, for example, by the below-deck, vertical MK 41 and MK 57 missile launchers. These launchers accept canisterized (or canistered) missiles, wherein the missiles can be one of several types. The canisters are loaded into corresponding canister-holding chambers or cells in the missile launcher. Each canistered missile has a standardized connector, which is connected within each cell, to a launch sequencer. The launch sequencer is an electronic assembly that identifies the missile within the canister by interrogating a code that is associated with the canister. The launch sequencer also responds to arming and firing signals from a higher level of control by generating a sequence of signals for the identified missile (e.g., firing signals, safe signals, etc.). These signals are transmitted via an umbilical cable to the canister and the missile within it to control launch. 
     A major roadblock to providing new munitions capability to naval fleets is the extremely high cost of launcher-related modifications. Specifically, integration of a new munition into an existing main battery launching system typically requires the design and qualification of a new canister for packaging, handling, storing, and transporting the munition. Furthermore, existing main battery host-launcher electronics and software must be appropriately modified to provide power and interfacing to each of the munition rounds in the newly developed canister. Additionally, integrating a new munition typically requires re-qualifying the gas management system of the launcher for the new munition. 
     One solution that is beneficial to reducing the cost of integrating new munitions in existing main-battery launchers is the “Adaptable Launch System” (hereinafter “ALS”). The ALS is described in U.S. Pat. No. 8,397,613 (application Ser. No. 12/274,409, filed on Nov. 20, 2008, which published as U.S. Patent Application Publication no. 2009/0126556 A1, titled “Adaptable Launching System,” and which is incorporated by reference in its entirety herein. In some embodiments, the ALS is used as a stand-alone launcher. In some other embodiments, the ALS is used as a “guest” launcher in one or more cells of a multi-cell “host” launching system, such as the MK 41 or MK 57 VLS main-battery launchers. In both stand-alone and guest-launcher applications, the ALS can accommodate either a single munition or a “multi-pack” of smaller munitions in its single launch cell. 
       FIG. 1A  depicts retrofitted multi-cell launcher (“RMCL”)  100 , which includes multi-cell multi-munition launcher (“MCL”)  102  and ALS  112 . In the embodiments depicted herein, MCL  102  is a MK 41 VLS main battery launcher that has been appropriately modified to operate with one or more ALS  112  units in its cells as guest launchers. 
     As depicted in  FIG. 1A , MCL  102  is a fixed, vertical, multi-missile storage and firing system. The missile launcher consists of a single eight-cell missile module that is capable of launching a variety of different types of missiles. The eight-cell module comprises upright structure  104 , which defines eight cells  106 . In a typical MK 41 VLS unit, the cells provide vertical storage space for eight missile canisters. But in accordance with an illustrative embodiment of the ALS, one or more of cells  106  receive ALS  112  unit(s). 
     The MK 41 VLS as MCL  102  is installed below deck, such that only deck and hatch assembly  108  at the top of the module is visible from the deck of a ship. The deck and hatch assembly protects ALS  112  (or missile canisters in a conventional MK 41 VLS) during storage and the hatches open to permit munitions launch. 
     Electronic equipment  110  monitors and controls various components of MCL  102 , distributes power signals originating from outside RMCL  100  to the one or more ALS  112  units, collects control and damage control signals from ALS  112  and transmits them to appropriate authorities, and assists in the launch of munitions from ALS  112  units. 
     The salient features of ALS  112  depicted in  FIG. 1  include enclosure  114 , munitions adapter  116 , and launch control electronics  118 . Enclosure  114  serves as a housing for munitions adapter  116  and launch control electronics  118 . The munitions are launched from ALS  112  under the control of their own weapon control system (“WCS”) through an instantiation of launch control electronics  118  that is tailored to that specific munition type. Launch control electronics  118  supplies electrical power to the munitions and manages the launch sequence. In most embodiments, the electrical power distribution subassembly and at least some cabling are not included in ALS  112  proper. Rather, these elements are associated with the host launcher. 
       FIG. 1B  depicts the salient elements of the structure of enclosure  114  of the ALS  112  of  FIG. 1A . Enclosure  114  comprises: top frame/seal  150 ; shell  151 ; munitions compartment  152 ; sealing bulkhead  153 ; electronics access way  154 ; electronics compartment  155 ; and bottom frame  156 . 
     Top frame and module seal  150  cooperates with the ship&#39;s deck and hatch assembly  108  of MCL  102  (in  FIG. 1A ) to create a seal or to vent exhaust to the atmosphere, as appropriate. 
     Shell  151  meets the physical requirements (e.g., size, shape, etc.) of a canister of the vertical launch system hosting ALS  112 . Shell  151  is formed from a material that meets appropriate standards that are well-known in the art, e.g., MIL-STD 2013, DDS 078-1, etc. Shell  151  is sized to accommodate both tactical length and strike length launcher applications. 
     Sealing bulkhead  153  (shown in phantom in the present figure) separates munitions compartment  152 , which houses munitions adapter  116  (in  FIG. 1A ), from electronics compartment  155 . Sealing bulkhead  153  prevents exhaust gases from entering into electronics compartment  155  and the launcher space of the ship. 
     Electronics access way  154  provides access to the electronics housed in electronics compartment  155 . 
     Bottom frame  156  provides the supporting base for enclosure  114  and is physically connected to shell  151 . More detail regarding ALS  112  and the elements of enclosure  114  is supplied in the above-cited disclosure. 
     However, for some types of munitions, the integration solutions and advantages provided by the ALS do not address the particular needs of those munitions. 
     SUMMARY OF THE INVENTION 
     The inventors of the present invention recognized that highly energetic munitions (e.g., rolling airframe missiles, Hellfire, etc.) have characteristics that the ALS and other weapons-integration solutions do not currently address. When fired, aft-venting munitions installed in a vertical launching configuration require a way to redirect exhaust gases. When the ALS is not used with the weapons system, a launch system that has its own sub-system for exhaust or gas management requires substantial retrofitting, or at the very least, substantial integration testing, to accommodate highly energetic munitions. 
     The inventors of the present invention recognized that, to sustain the viability of the ALS and other weapons-integration solutions for use with highly energetic munitions, the exhaust must be affirmatively re-directed and vented by a gas management system that is self-contained and accommodates the dimensions and characteristics of the respective munitions. By decoupling the gas management system for a given munition from an adjacent munition, the risk of downing a multi-pack launcher or munition adapter is reduced. Thermal wear, overheating, restrained firing and aft closure debris can be isolated through the separation of gas management systems. In addition, the GMS allows for ease of replenishment and maintenance of a given sub-cell of a multi-pack system. Some small highly energetic munitions types, such as rolling airframe missiles and Hellfire missiles, are particularly good candidates for the self-contained gas management system in accordance with the present invention. 
     The illustrative embodiment of the present invention is a self-contained gas management system (hereinafter “GMS”) that removably receives a single canistered munition. In the illustrative embodiment, an ALS receives four GMSs. Each canistered munition is installed in a respective one of the four GMSs. Alternative embodiments that do not comprise ALS accommodate one or more GMSs in a vertical launch system cell or, alternatively, in another weapons platform that is integral to the ship. 
     The GMS principally comprises a plenum, a first uptake structure, and a second uptake structure. The GMS removably receives a single canistered munition. The plenum accepts the exhaust from the canistered munition when the munition fires. The plenum is fluidically coupled to the first and second uptake structures. 
     The uptake structures receive the missile exhaust from the plenum and vent the exhaust to the atmosphere. In the illustrative embodiment, the first and second uptake structures are disposed along opposite sides of the canistered munition, flanking it. In conjunction with brackets and other components that are disclosed in more detail below, the uptake structures and plenum collectively provide framing and structure for the GMS. 
     An enhanced munitions adapter is disclosed, for some embodiments that comprise a plurality of GMSs, wherein the enhanced munitions adapter accommodates the plurality of GMSs, each GMS accompanying a single canistered munition. The enhanced munitions adapter thus forms a “GMS multi-pack.” In the illustrative embodiment, the ALS receives the enhanced munitions adapter and four canistered munitions installed in their respective GMSs. 
     The GMS has an “open” position for receiving and removing a canistered munition, and a “closed” position for installation into a launch system and firing the munition. Correspondingly, in some embodiments that comprise the enhanced munitions adapter, the enhanced munitions adapter also has “open” and “closed” positions. 
     The self-contained GMS disclosed herein has several advantages over the prior art, including, among others:
         The GMS works with existing munitions without the need to modify the munitions or the canisters that house them. Each GMS is dimensioned to fit the canistered munition it receives as well as the launch system in which the GMS is used. Therefore, the GMS according to the illustrative embodiment is suitable for both existing munitions and new as-yet-undeveloped munitions.   In a launch system that operates with the ALS in a host/guest configuration, the GMS enables the use of highly energetic munitions with relatively minor modifications to the ALS, but without further modifications to the host launch system.   In an ALS that operates as a stand-alone launcher, i.e., without a host launcher, the GMS enables the use of highly energetic munitions with relatively minor modifications to the ALS.   In a launch system that operates without an ALS, the GMS enables the use of highly energetic munitions with relatively minor modifications to the launch system.   The GMS provides a lower cost of integration testing and re-qualification of a new munition.       

     Some embodiments, in particular those that do not incorporate an ALS, comprise: an apparatus for use in a vertical launch system, the apparatus comprising:
         (a) a plenum that is capable of being fluidically coupled to a canistered munition, wherein the plenum receives the exhaust from the munition when the munition is fired; and   (b) a first uptake structure that is fluidically coupled to the plenum, wherein the first uptake structure guides the exhaust from the plenum to the atmosphere;   wherein the apparatus removably receives the canistered munition, and   wherein the apparatus is at least partially removable from the vertical launch system to receive the canistered munition, and   wherein the dimensions of the plenum and of the first uptake structure are based on the dimensions of the canistered munition, and   wherein the plenum and the first uptake structure collectively define a gas management system for the canistered munition.       

     Some other embodiments that incorporate an ALS comprise: an apparatus for use in a single-cell vertical launch system that is suitable for use as a guest launcher within a host launcher, the apparatus comprising:
         an enhanced munitions adapter that accommodates a plurality of canistered munitions, wherein:
           (i) each canistered munition is operatively coupled to a respective gas management system, and wherein each gas management system operates independently,   (ii) a cell in the vertical launch system includes an enclosure for receiving the enhanced munitions adapter,   (iii) the enclosure comprises a sealing bulkhead that separates the enclosure into a munitions compartment and an electronics compartment,   (iv) the enhanced munitions adapter is disposed in the munitions compartment, and   (vii) each gas management system comprises:
               (a) a plenum that is capable of being fluidically coupled to a respective canistered munition, wherein the plenum receives the exhaust from the munition when the munition is fired, and   (b) a first uptake structure that is fluidically coupled to the plenum, wherein the first uptake structure guides the exhaust from the plenum to the atmosphere; and   
               
           wherein each gas management system removably receives the respective canistered munition;   wherein the dimensions of the plenum and of the first uptake structure are based on the dimensions of the respective canistered munition.       

    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG. 1A  depicts retrofitted multi-cell launcher (“RMCL”)  100 , which includes multi-cell multi-munition launcher  102  and adaptable launch system  112 . 
         FIG. 1B  depicts the salient elements of the structure of enclosure  114  of the adaptable launch system  112  of  FIG. 1A . 
         FIG. 2  depicts a loaded ALS  112  with a view of enhanced munitions adapter  201  accommodating four GMSs  220 - n  in accordance with an illustrative embodiment. 
         FIG. 3  depicts gas management system  220 - n  in accordance with an illustrative embodiment. 
         FIG. 4  depicts gas management system  220 - n  in an “open” position. 
         FIG. 5  depicts detailed view “A” of gas management system  220 - n.    
         FIG. 6  depicts detailed view “B” of gas management system  220 - n.    
         FIG. 7  depicts enhanced munitions adapter  201  accommodating four GMSs  220 - n  in accordance with an illustrative embodiment. 
         FIG. 8  depicts enhanced munitions adapter  201  in an “open” position. 
     
    
    
     DETAILED DESCRIPTION 
     The following terms are defined for use in this disclosure and in the accompanying claims:
         The term “electrically-connected” means that two objects are in direct electrical contact without any intervening elements. In other words, the region of contact between the two objects remains at a substantially uniform voltage for substantially any current (neglecting any voltage drop due to the resistivity of the physical connection medium, such as a wire).   The term “electrically-coupled” means that two objects are in electrical contact. This can be via direct physical contact (e.g., a plug in an electrical outlet, etc.), via an electrically-conductive intermediate (e.g., a wire that connects devices, etc.), or via intermediate devices, etc. (e.g., a resistor electrically connected between two other electrical devices, etc.).   The term “enhanced munitions adapter” means the structure that accommodates a plurality of gas management systems (GMSs). It will be clear to those having ordinary skill in the art, after reading the present disclosure, that the enhanced munitions adapter is sometimes referred to herein as a “GMS multi-pack.”   The term “fluidically coupled” and inflected forms mean that liquid, gas, or vapor from a first region can flow to or otherwise cause an effect in a second region. For example, if two regions are fluidically coupled (or in fluidic communication), a pressure change in one of those regions might (but not necessarily will) result in a pressure change in the other of the regions.   The term “operatively coupled” means that the operation of one element or device affects another device, wherein the devices need not be physically coupled. For example, a laser and a mirror are operatively coupled if a laser directs a beam of light to the mirror.   The term “physically connected” or “physically coupled” means in direct physical contact and affixed (e.g., a mirror that is mounted on a linear-motor).       

     The GMS disclosed herein can be used in a vertical launch system. The vertical launch system can comprise one launcher or a battery of launchers. Furthermore, the vertical launch system can comprise a guest launcher, such as an ALS, which is fitted into a main battery host system. The principles of the GMS disclosed herein suit any and all of these variations in launch systems. Therefore, the GMS of the present invention can operate in a variety of embodiments associated with various vertical launch system configurations. 
     The illustrative embodiment of the present invention is a single-cell vertical launching system ALS  112  that accommodates four canistered munitions each installed in its respective GMS in accordance with the present invention. In the illustrative embodiment, enclosure  114  removably receives a four-GMS multi-pack. 
     In alternative embodiments where the ALS  112  is not used, one or more of cells  106  of the MCL  102  is capable of removably receiving a missile canister with the accompanying GMS. In other alternative embodiments that do not include a contained superstructure such as ALS  112  or MCL  102 , a uniquely fitted ship configuration is capable of removably receiving a missile canister with the accompanying GMS, or a plurality of missile canisters with a GMS multi-pack. 
       FIG. 2  depicts a loaded enclosure  114  of ALS  112  with a view of enhanced munitions adapter  201  accommodating four GMSs  220 - n  in accordance with an illustrative embodiment, wherein n=1, 2, 3, or 4. It will be clear to those having ordinary skill in the art, after reading the present disclosure, that any disclosure herein in respect to a component n applies equally to other components of the same kind. 
     All four GMSs are not fully visible in  FIG. 2 . The GMS  220 - n  is described in more detail in  FIGS. 3-6 . It will be clear to those having ordinary skill in the art, after reading the present disclosure, that a “GMS multi-pack” in the present disclosure comprises an enhanced munitions adapter  201 . 
     In some embodiments that do not include a contained superstructure such as ALS  112  or MCL  102 , the view of enhanced munitions adapter  201  depicted in  FIG. 2  represents enhanced munitions adapter  201  in a ship configuration that is capable of removably receiving a plurality of missile canisters each accompanied by its respective GMS  220 - n . Enhanced munitions adapter  201  is described in more detail in  FIGS. 7 and 8 . 
       FIG. 3  depicts gas management system  220 - n  with canistered munition  301  installed, in accordance with an illustrative embodiment. GMS  220 - n  comprises: umbilical cable  302 ; uptake structure  303 ; plenum  304 ; uptake structure  305 ; and a plurality of bracket structures  306 . As depicted in the present figure, GMS  220 - n  is in a “closed” position for installation into a launch system and firing the munition. 
     It is to be understood that GMS  220 - n  does not comprise canistered munition  301 . GMS  220 - n  removably receives canistered munition  301 . GMS  220 - n , including its components, is dimensioned at least in part based on the dimensions of canistered munition  301 . 
     Canistered munition  301  is depicted installed in GMS  220 - n . Canistered munition  301  comprises electronics section  301   a.    
     Umbilical cable  302  is an insulated electrical cable that is well-known in the art, that connects canistered munition  301  to launch control electronics  118  that is tailored to that specific munition type. Umbilical cable  302  enables canistered munition  301  to be electrically coupled to launch control electronics  118 . Umbilical cable  302  connects to electronics section  301   a  of canistered munition  301 . 
     Uptake structure  303  and uptake structure  305  each guides the exhaust from canistered munition  301  to the atmosphere. It will be clear to those having ordinary skill in the art, after reading the present disclosure, how to make and use alternative embodiments in which, after traveling through uptake structures  303  and  305 , the exhaust reaches the atmosphere indirectly, such as by first reaching a hatch that opens to the atmosphere. 
     Uptake structure  305  is identical to uptake structure  303 , and provides GMS  220 - n  with additional exhaust uptake capacity. It will be clear to those having ordinary skill in the art, after reading the present disclosure, how to make and use alternative embodiments of GMS  220 - n  that do not comprise uptake structure  305 , or that comprise a different number of uptake structures, e.g., one uptake structure, three uptake structures, etc. 
     In the illustrative embodiment, uptake structures  303  and  305  are disposed along opposite sides of canistered munition  301 , flanking it, but the invention is not so limited. Uptake structures  303  and  305  are dimensioned to accommodate the dimensions of the type of canistered munition for which GMS  220 - n  is designed. 
     Uptake structures  303  and  305  are each fluidically coupled to plenum  304 , from which they receive the missile exhaust. 
     Plenum  304  receives the exhaust from canistered munition  301  when it is fired. Plenum  304  is fluidically coupled to uptake structures  303  and  305 . The exhaust is guided from the aft end of canistered munition  301  towards the forward end of canistered munition  301  and thus, towards the corresponding forward end of the launch system. The exhaust travels from plenum  304  to uptake structures  303  and  305 , and ultimately to the atmosphere. Plenum  304  is dimensioned based on the dimensions of canistered munition  301 . In the illustrative embodiment, plenum  304  is positioned such that it supports, at least in part, canistered munition  301 , but in some embodiments plenum  304  is positioned otherwise within GMS  220 - n.    
     Bracket  306  is one of a plurality of brackets  306  in GMS  220 - n . The illustrative embodiment comprises four brackets  306 , but alternative embodiments can comprise any number of brackets  306 , or no brackets. Each bracket  306  is physically connected to uptake structure  303  and to uptake structure  305  (connection not visible in this view). Brackets  306 , in conjunction with uptake structures  303  and  305  and with other components that are described in more detail in  FIGS. 5 and 6 , collectively provide framing and structure to GMS  220 - n , enabling it to receive and support canistered munition  301 . 
       FIG. 4  depicts gas management system  220 - n  in an “open” position with canistered munition  301  installed. The “open” position of GMS  220 - n  enables the loading and unloading of canistered munition  301 . 
     Canistered munition  301  is depicted installed in GMS  220 - n.    
     Detail “A” is shown and discussed in further detail in  FIG. 7 . 
     Detail “B” is shown and discussed in further detail in  FIG. 8 . 
       FIG. 5  depicts detailed view “A” of gas management system  220 - n . View “A” represents the view from the forward end of uptake structures  303  and  305 . View “A” depicts: umbilical cable  302 ; bracket  501 ; uptake structures  303  and  305 ; and restraint  502 . All the components shown in view “A” are part of GMS  220 - n.    
     Bracket  501  is a bracket that receives canistered munition  301  (not shown) when it is installed in gas management system  220 - n.    
     In the illustrative embodiment, bracket  501  is physically connected to both uptake structures  303  and  305 , but it will be clear to those having ordinary skill in the art, after reading the present disclosure, how to make and use alternative embodiments in which another component receives canistered munition  301 ; or in which bracket  501  is otherwise connected to one or more of the uptake structures or to other components of GMS  220 - n.    
     Restraint  502  secures canistered munition  301  to GMS  220 - n  in a “closed” position. Restraint  502  is released when GMS  220 - n  is to receive a canistered munition or when a munition is to be removed from GMS  220 - n , i.e., when GMS  220 - n  is in an “open” position. It will be clear to those having ordinary skill in the art, after reading the present disclosure, how to make and use alternative embodiments in which canistered munition  301  (not shown) is otherwise secured to GMS  220 - n  when it is in a “closed” position. 
     Restraint  502  is physically connected at one end to uptake structure  305 , and is releasably coupled at the other end to uptake structure  303 , according to the illustrative embodiment. In the illustrative embodiment, restraint  502  comprises padding that ensures a secure fit. It will be clear to those having ordinary skill in the art, after reading the present disclosure, how to make and use alternative embodiments in which another component secures canistered munition  301 ; or in which restraint  502  is otherwise connected to one or more of the uptake structures, or to another component of gas management system  220 - n.    
       FIG. 6  depicts detailed view “B” of gas management system  220 - n  with canistered munition  301  installed. View “B” represents the view from the aft end of uptake structures  303  and  305  (not visible). View “B” depicts: umbilical cable  302 ; bracket  306 ; uptake structure  303 ; guide sleeve  601 ; canistered munition  301 ; plenum intake  602 ; and plenum  304 . GMS  220 - n  comprises all the components depicted here, except for canistered munition  301 . 
     Guide sleeve  601  is part of gas management system  220 - n  (not labeled). When GMS  220 - n  is in an “open” position, as illustrated in the present figure, guide sleeve  601  facilitates insertion and removal of canistered munition  301  to and from GMS  220 - n , respectively. 
     Guide sleeve  601  removably receives canistered munition  301 . Guide sleeve  601  is pivotably coupled to plenum  304  to pivot between an “open” position for receiving and removing a canistered munition, and a “closed” position for installation into a launch system and firing the munition. In the illustrative embodiment, guide sleeve  601  pivots via a removable claw (not shown), which enables guide sleeve  601  to be removed from plenum  304  to more conveniently (i) receive canistered munition  301 , and (ii) remove canistered munition  301 . The removable claw is coupled to a receiving structure or hinge (not shown) in plenum  304 . 
     In some alternative embodiments, guide sleeve  601  is pivotably coupled to plenum  304  by a pin and weldment arrangement, but those having ordinary skill in the art will know many other ways of coupling these components, based on the freedom of movement sought and on any rotational needs associated with GMS  220 - n . In some embodiments, guide sleeve  601  is not coupled to plenum  304 , but instead, guide sleeve  601  removably rests on plenum  304 , enabling guide sleeve  601  to be rocked or tilted to receive canistered munition  301 . 
     When GMS  220 - n  is in a “closed” position, as illustrated in  FIG. 3 , guide sleeve  601  provides a sealing interface between plenum  304  and the atmosphere, such that the exhaust from a munition that is fired travels into plenum  304  without discharging or venting. The sealing interface prevents blow-back of the exhaust. To provide the sealing interface in the illustrative embodiment, guide sleeve  601  comprises sealing features (i) on an inner surface (not shown) that faces canistered munition  301 , and (ii) on an outer surface that faces the exterior and plenum intake  602 . Those having ordinary skill in the art will know many other ways of providing guide sleeve  601  with one or more sealing interface(s). 
     Plenum intake  602  receives the exhaust from canistered munition  301  into plenum  304 . Plenum intake  602  is a gas management inlet. When GMS  220 - n  is in a “closed” position plenum intake  602  is sealed from the atmosphere by guide sleeve  601 . When GMS  220 - n  is in an “open” position, plenum intake  602  is open to the atmosphere, as illustrated in the present figure. It will be clear to those having ordinary skill in the art, after reading the present disclosure, how to make and use alternative embodiments in which plenum intake  602  provides a sealing interface to guide sleeve  601 . It will be clear to those having ordinary skill in the art, after reading the present disclosure, how to make and use alternative embodiments that comprise additional components disposed between plenum intake  602  and guide sleeve  601 , such that a component other than guide sleeve  601  provides the seal to plenum intake  602 . 
       FIG. 7  depicts enhanced munitions adapter  201  accommodating four GMSs  220 - n  in accordance with an illustrative embodiment. As depicted in the present figure, enhanced munitions adapter  201  is in a “closed” position for installation into a launch system and firing the munition(s). 
     Enhanced munitions adapter  201  receives and accommodates four GMSs  220 - n . Enhanced munitions adapter  201  comprises: lateral restraint arms  710 - n , wherein n=1, 2, 3, or 4; and base  711 . It will be clear to those having ordinary skill in the art, after reading the present disclosure, that any disclosure herein in respect to a component n applies equally to other components of the same kind. 
     In the illustrative embodiment comprising ALS  112 , enhanced munitions adapter  201  takes the place of munitions adapter  116  and is removably received by enclosure  114 . In alternative embodiments, munitions adapter  116  in ALS  112  receives enhanced munitions adapter  201 . In other alternative embodiments that do not comprise ALS  112 , the launch system removably receives enhanced munitions adapter  201 . It will be clear to those having ordinary skill in the art, after reading the present disclosure, how to make and use alternative embodiments of enhanced munitions adapter  201  that accommodate any number of GMS  220 - n , e.g., two GMSs, three GMSs, etc., and any number of corresponding lateral restraint arms  710 - n . It is to be understood that a canistered munition  301  need not be installed in every GMS  220 - n  that is accommodated by enhanced munitions adapter  201 , or in any GMS  220 - n  for that matter. 
     Enhanced munitions adapter  201  is dimensioned, at least in part, based on the dimensions of the structure that is to receive it, e.g., ALS  112 , enclosure  114 , a launch system, another ship configuration, etc. 
     Lateral restraint arms  710 - n  are arranged to receive each of the respective GMS  220 - n . In the illustrative embodiment, lateral restraint arm  710 - n  is physically connected to base  711 , and is not connected to any other lateral restraint arm in enhanced munitions adapter  201 . It will be clear to those having ordinary skill in the art, after reading the present disclosure, how to make and use lateral restraint arms  710 - n  such that they are physically connected to each other, or physically connected to the respective GMS  220 - n  or to components thereof. It will be clear to those having ordinary skill in the art, after reading the present disclosure, how to make and use alternative embodiments of enhanced munitions adapter  201  that comprise no lateral restraint arm  710 - n , or that is otherwise constructed to receive the GMSs  220 - n , such as a “cage,” etc. 
     Base  711  provides support for the other components of enhanced munitions adapter  201  and for GMS  220 - n . Base  711  is physically connected to lateral restraint arms  710 - n . In some embodiments where enhanced munitions adapter  201  is disposed in enclosure  114  of ALS  112 , base  711  comprises a sealing interface in accordance with the design of enclosure  114  and ALS  112 . Base  711  further accommodates umbilical cable  302  for access to launch control electronics  118 . It will be clear to those having ordinary skill in the art how to make and use base  711  to accommodate umbilical cable  302  for access to launch control electronics  118 . It will be further clear to those having ordinary skill in the art, after reading the present disclosure, how to make and use base  711  to be consistent with the design of the systems or components that receive enhanced munitions adapter  201 , e.g., enclosure  114 , a launch system, a ship configuration, etc. 
     GMS  220 - 1  is visible in the present figure and comprises in part: uptake structure  303 - 1 ; plenum  304 - 1 ; and uptake structure  305 - 1 . Canistered munition  301 - 1  is installed in GMS  220 - 1 . GMS  220 - 1  and its component elements are described in more detail in  FIGS. 3 through 6 . 
     GMS  220 - 2 , GMS  220 - 2 , and GMS  220 - 3  are each identical to GMS  220 - 1 , but are only partially visible in the present figure and, therefore, are not labeled. Canistered munitions  301 - n  are each installed in the respective GMS  220 - n , wherein n=1, 2, 3, or 4. 
     In the illustrative embodiment, which comprises enhanced munitions adapter  201 , each plenum  304 - n  is removably coupled to base  711 . In some embodiments that comprise enhanced munitions adapter  201 , plenum  304 - n  is pivotably coupled to base  711  to pivot between an “open” position for receiving and removing a canistered munition, and a “closed” position for installation into a launch system and firing the munition. In some embodiments that comprise enhanced munitions adapter  201 , plenum  304 - n  is physically connected to lateral restraint arm  710 - n . In some embodiments that comprise enhanced munitions adapter  201  each plenum  304 - n  physically abuts, but is not physically connected to, lateral restraint arm  710 - n —as illustrated below in  FIG. 8 . 
       FIG. 8  depicts enhanced munitions adapter  201  in an “open” position.  FIG. 8  depicts base  711  and lateral restraint arms  710 - 1 ,  710 - 2 ,  710 - 3 , and  710 - 4 , and installed canistered munitions  301 - n.    
     Lateral restraint arms  710 - 1 ,  710 - 2 ,  710 - 3 , and  710 - 4  are depicted in an “open” position relative to base  711 . In some embodiments, the “open” position of enhanced munitions adapter  201  enables GMS  220 - n  to be removed and installed from and into enhanced munitions adapter  201 . In some embodiments, the “open” position of enhanced munitions adapter  201  enables canistered munitions  301 - n  to be removed and installed from and into its respective GMS  220 - n.    
     Four GMSs  220 - n  (not labeled), with installed canistered munitions  301 - n , are depicted installed in enhanced munitions adapter  201 . Some components of GMS  220 - 1  (not labeled) are visible, including, but not limited to: uptake structure  303 - 1 ; uptake structure  305 - 1 ; and plenum  304 - 1 . Plenum  304 - 4  is also depicted in the present figure. 
     The materials used for GMS  220 - n  and for enhanced munitions adapter  201  largely depend on the application and on the type of munition to be accommodated. In the preferred embodiment, the outer components, such as lateral restraint arms  710 - n , and base  711 , use steel, but it will be clear to those having ordinary skill in the art how to identify and use alternative appropriate materials, such as aluminum, composites, etc., that are standards compliant. In the preferred embodiment, the inner components, such as plenum  304  and uptake structures  303  and  305 , use ablative materials, but it will be clear to those having ordinary skill in the art how to identify and use alternative appropriate materials that suit the type of munition for which GMS  220 - n  is designed. 
     It is to be understood that the disclosure teaches just some examples of the illustrative embodiments and that many variations of the invention can easily be devised by those skilled in the art after reading this disclosure and that the scope of the present invention is to be determined by the following claims.