Patent Document

FIELD OF THE INVENTION  
         [0001]    This invention relates to launchers for canisterized missiles, and more particularly to such launchers which are intended for placement below a protective deck for generally vertical launch.  
         BACKGROUND OF THE INVENTION  
         [0002]    Modern warships rely principally on missiles, rather than cannon, for their offensive and defensive armament. Thus, a warship may include a single automatic cannon, together with one or more batteries of missile launchers. A battery of missile launchers may include a single missile launcher array at the rear deck of the ship, and two similar arrays on the foredeck.  
           [0003]    A cluster of missile launchers for use on a ship may be similar to that described in U.S. Pat. No. 5,837,917, issued Nov. 17, 1998 in the name of McNab et al. McNab et al. describe a structure providing five vertical bays or “sleeves” of five juxtaposed missile launcher locations, held in a line array by muzzle-end, breech-end, and intermediate frames. Each sleeve of the missile launcher array of McNab et al. includes a support lattice dimensioned to accommodate a canisterized missile. Protection against blast and environment is provided by a hard hatch assembly which includes a plurality of individually controllable or openable hatches, each of which covers the end of one of the sleeves of the array. The breech ends of the sleeves open into a plenum, which is cooled by a water supply system. Cleats are provided for fastening the plenum to the underlying structure. The missile canisters with which the McNab launchers are used include a frangible protective seal at the muzzle and breech ends, and also include a missile ready for launch, presumably together with an electrical interface for providing information to the missile, if necessary, and for initiating the launch sequence as a result of external command. In order to use the McNab structure, one or more of the sleeve doors or hatches is opened, and a canisterized missile is lowered thereinto. While not expressly stated, an umbilical is presumably used to connect the missile canister to a portion of the launch control system near the sleeve, so that the missile may be remotely controlled. When that missile is to be launched, the door or hatch associated therewith is opened, and the corresponding hatch of a further one of the sleeves, which does not contain a canisterized missile, is opened. Missile firing is then commanded, as a result of which the missile within its container fires, expelling exhaust gases into the plenum and emerging from the muzzle end of the canister, breaking both frangible seals as it does so. The exhaust gases entering the plenum from the missile are cooled by water injection, which lowers the temperature of the exhaust gases to thereby reduce the infrared (IR) signature, reduce erosion due to the gas temperature, and in so doing generate a large amount of steam. The mixed steam and exhaust gases are routed from the plenum to above-decks by way of the vacant sleeve with its open hatch, used as a chimney. If the support structure is a lattice, as McNab illustrates, a protective sleeve may run within that vacant one of the sleeves which is used as a chimney for exhaust gases/steam. The protective sleeve may include ablatable material for further protection.  
           [0004]    Improved missile launchers are desired.  
         SUMMARY OF THE INVENTION  
         [0005]    A missile launcher cell according to an aspect of the invention is for accepting a canisterized missile which defines a missile launch end and a missile exhaust end, for, in use prior to missile launch, holding the missile canister in a generally vertical launch position below a deck. The missile launcher cell comprises at least one elongated exhaust gas chimney. It also comprises a support structure defining a generally axial cavity, also defining a missile launch end and a missile exhaust end. The cavity of the support structure has length and cross-sectional dimensions sufficient to accommodate the missile canister. The one or more exhaust chimneys lie along the exterior of the support structure and extend, parallel with the axis of the cavity, from near the missile launch end to near the missile exhaust end of the support structure. The missile launcher cell also includes a missile exhaust plenum attached to the support structure near the missile exhaust end of the support structure. The missile exhaust plenum is coupled to the one or more exhaust chimneys near the missile exhaust end of the support structure. The missile exhaust plenum further includes an attachment arrangement for attachment to the missile exhaust end of the missile canister, for routing missile exhaust gas from the missile exhaust end of the support structure to the one or more exhaust chimneys, for causing missile exhaust gas to vent from the one or more chimneys near the missile launch end of the support structure of the missile launcher cell. A door structure is attached to the missile launch end of the missile launch cell support structure, for, in the closed state, protecting at least the support structure, the one or more chimneys, and any missile canister accommodated within the cavity.  
           [0006]    In a particular embodiment of the invention, the cavity has a rectangular, or more particularly square, cross-section, and is dimensioned to accommodate a Mk 25 canisterized missile. The support structure may be a latticework. The number of chimneys in a particular embodiment is two, with the two chimneys running parallel with each other and with the cavity axis.  
           [0007]    In a particularly advantageous embodiment of the invention, an array of missile launcher cells has each of the missile launcher cells of the array dimensioned for accepting a canisterized missile, where each missile canister defines a missile launch end and a missile exhaust end. In use prior to missile launch, the array of missile launcher cells holds the missile canisters in a generally vertical launch position below a deck. Each of the missile launcher cells includes at least one elongated exhaust gas chimney, and a support structure defining a generally axial cavity defining a missile launch end and a missile exhaust end. The cavity of the support structure of each cell has length and cross-sectional dimensions sufficient to accommodate a missile canister. The one or more exhaust chimneys are attached, or lie adjacent to, the exterior of the support structure and extend, parallel with the axis of the cavity, from near the missile launch end to near the missile exhaust end of the structure. A missile exhaust plenum is attached to the support structure near the missile exhaust end of the support structure of each cell. The missile exhaust plenum of each cell is coupled to the one or more exhaust chimneys near the missile exhaust end of the support structure, and also includes an attachment arrangement or means for attachment to the missile exhaust end of the missile canister, for thereby routing missile exhaust gas from the missile exhaust end of the support structure to the one or more chimneys, for causing missile exhaust gas to vent from the at least one chimney near the missile launch end of the support structure. A door structure is attached to the missile launch end of the missile launch structure, for, when closed, protecting at least the support structure and the one or more exhaust chimneys of the missile launcher cell, and any missile canister accommodated within the cavity of the cell, and for, when open, providing for egress of the missile from its canister and exhaust gas from the one or more chimneys. This arrangement allows the array of missile launchers to be maintained in a condition in which all of the launcher cells are fitted with canisterized missiles, without keeping at least one missile launch cell clear or unloaded so as to provide a chimney or path for the escape of exhaust gas from a missile fired in a missile launch cell of the array. Thus, an aspect of the invention lies in an array of launchers in which a canisterized missile located within each of (all of) the cavities of the array. 
       
    
    
     BRIEF DESCRIPTION OF THE DRAWING  
       [0008]    [0008]FIG. 1 is a simplified perspective or isometric view, partially cut away, of a representative array of four individual missile launcher cells according to an aspect of the invention;  
         [0009]    [0009]FIG. 2 is a simplified perspective or isometric view of a single missile launcher cell of FIG. 1;  
         [0010]    [0010]FIG. 3 a  is a simplified perspective or isometric view illustrating details of the deck portion and hatch near the missile launch end of the missile launcher cell of FIG. 2, and FIG. 3 b  is a corresponding detail of the missile exhaust plenum near the missile exhaust end of the missile launcher cell of FIG. 2;  
         [0011]    [0011]FIGS. 4 a ,  4   b , and  4   c  are simplified side elevation and plan views, respectively, looking in mutually orthogonal directions, of the missile launcher cell of FIG. 2 with its hatch open, showing the individual exhaust gas management plenum, two exhaust gas chimneys or uptakes extending from the plenum to the muzzle or missile exit end of the launcher cell, and the door assemblage covering the missile launch exit and the chimneys;  
         [0012]    [0012]FIG. 5 is a simplified cross-sectional elevation view of the single missile launcher of FIG. 2, showing the location of the missile within the missile canister and a portion of the gas management system, including the plenum and one chimney, and the deck door or hatch. 
     
    
     DESCRIPTION OF THE INVENTION  
       [0013]    [0013]FIG. 1 is a simplified perspective or isometric view of an array  10  of individual missile launcher cells  10   a ,  10   b ,  10   c , and  10   d , with portions of the structure cut away to reveal interior details. In FIG. 1, the individual cells  10   a , lob,  10   c , and  10   d  are identical to each other. Each cell includes a lattice-type support structure designated  12 , thus missile launcher  10   a  includes a lattice-type support structure designated  12   a , missile launcher cell lob includes a lattice-type support structure  12   b , missile launcher cell  10   c  includes a lattice-type support structure  12   c , and launcher cell  10   d  includes a lattice-type support structure  12   d . Each support structure  12  includes four “leg” portions. Taking missile launcher cell  10   d  of FIG. 1 as being representative, three such legs can be seen, namely legs  14   d   1 ,  14   d   2 , and  14   d   3 , and the fourth leg is not illustrated. The illustrated legs of support structure  12   a  of missile launcher  10   a  are  14   a   1  and  14   a   2 , the illustrated legs of support structure  12   b  of missile launcher  10   b  are  14   b   1  and  14   b   2 , and the illustrated legs of support structure  12   c  of missile launcher  10   c  are  14   c   1  and  14   c   2 . The legs of each support structure extend parallel with the missile launcher longitudinal axis; in particular, the various legs extend parallel to their corresponding launcher cell longitudinal axes  8   a ,  8   b ,  8   c , and  8   d.    
         [0014]    A plurality of interconnecting support braces extend between the “legs” of the support structure of each missile launcher cell. As illustrated in FIG. 1, representative support braces  20   a   1 ,  20   a   2 , and  20   a   3  extend between leg elements  14   a   1  and  14   a   2 .  
         [0015]    The combination of these leg elements and support braces defines an elongated cavity (not is 15  clearly visible in FIG. 1), having a rectangular or square cross-section, which extends vertically through each support structure  12   a ,  12   b ,  12   c , and  12   d . The cross-sectional dimensions of each such cavity are dimensioned to accommodate a canisterized missile, and to hold such canisterized missile in a vertical or about-vertical posture. In a particular embodiment in which the canisterized missile is a Mark  25  canisterized missile, the cross-section is rectangular.  
         [0016]    A protective door or hatch assembly or structure is located at the upper or missile launch end of each missile launcher cell. More particularly, FIG. 1 illustrates a hatch assembly  16   a  associated with missile launcher cell  10   a , a hatch assembly  16   b  associated with missile launcher cell lob, a hatch assembly  16   c  associated with missile launcher cell  10   c , and a hatch assembly  16   d  associated with missile launcher cell  10   d . Each hatch assembly includes a generally flat deck portion or deck extension, and a hatch covering one or more apertures by which one or more missiles may exit, and or through which exhaust gases may vent. In FIG. 1, hatch assembly  16   a  of missile launcher cell  10   a  has a deck portion of deck extension  16   ad  and a hinged hatch  16   ah , hatch assembly  16   d  of missile launcher cell  10   d  has a deck  16   dd  and a hinged hatch  16   dh , with the hatches illustrated as being in the closed position. Hatch assembly  16   c  of missile launcher  16   c  has a deck  16   cd  and an open hatch  16   ch . The hatch  16   bh  of hatch assembly  16   b  is illustrated in phantom to reveal a square missile-end “aperture”  18   bm  in which a canisterized missile (not illustrated in FIG. 1) may be accommodated, and additional chimney or exhaust uptake apertures  18   bc   1  and  18   bc   2 .  
         [0017]    Each missile launcher cell  10   a ,  10   b ,  10   c , and  10   d  of array  10  of FIG. 1 also includes an a pair of missile exhaust gas uptake ducts or chimneys. In FIG. 1, portions of the two chimneys associated with missile launcher cell  10   a  are designated  30   a   1  and  30   a   2 , and portions of the corresponding chimneys of missile launcher cell lob are designated  30   b   1  and  30   b   2 , respectively. The chimneys associated with missile launcher cell  10   c  are designated  30   c   1  and  30   d   2 , and those associated with missile launcher cell  10   d  are designated  30   d   1  and  30   d   2  in FIG. 1. The chimneys associated with each launcher cell extend from near the bottom, breech or missile exhaust end of each launcher cell to near the top, muzzle, or missile launch end of the launcher cell, and are generally parallel with the axis of the corresponding support structure. Thus, chimneys  30   a   1  and  30   a   2  extend parallel with the longitudinal axis  8   a  of missile launcher support structure  12   a , chimneys  30   b   1  and  30   b   2  extend parallel with the longitudinal axis  8   b  of missile launcher support structure  12   b , chimneys  30   c   1  and  30   c   2  extend parallel with the longitudinal axis  8   c  of missile launcher support structure  12   c , chimneys  30   d   1  and  30   d   2  extend parallel with the longitudinal axis  8   d  of missile launcher support structure  12   d . At their upper ends, the various chimneys or missile exhaust gas uptake ducts open into a region which lies under the doors or hatches of the corresponding missile launcher cell when that door or hatch is in its closed position. In FIG. 1, the open ends of the two chimneys  30   b   1  and  30   b   2  are designated  18   bc   1  and  18   bc   2 , respectively. The chimneys are preferably fastened to the corresponding deck plate, as by welding if the chimney is metallic, or by other suitable fastening method for other materials, as for example the chimneys  30   b   1  and  30   b   2  should be secured to deck plate  16   bd . The corresponding hatch  16   bh , when in its closed state, covers both the two chimney openings  18   bc   1  and  18   bc   2  and also the upper end of the elongated, vertically oriented cavity associated with or defined by the support structure  12   b.    
         [0018]    In addition to the chimneys, each missile launcher cell  10   a ,  10   b ,  10   c , and  10   d  of array  10  is associated with an exhaust gas plenum or manifold. Thus, a plenum  40   a  is associated with missile launcher cell  10   a , a plenum  40   b  is associated with missile launcher cell lob, a plenum  40   c  is associated with missile launcher cell  10   c , and a plenum  40   d  is associated with missile launcher cell  10   d . Each exhaust gas plenum includes an attachment arrangement for attaching the plenum to the support structure. In a particular embodiment of the invention, the attachment arrangement also supports a “dogdown” arrangement which provides secure attachment of the plenum to the lower end of the canister of the canisterized missile used therewith. In FIG. 1, the attachment arrangement for the exhaust gas plenum of each missile launcher includes four bosses or structures of a set  42  of bosses. Thus, exhaust gas plenum  40   a  of FIG. 1 includes on its upper surface four attachment bosses, each of which is designated  42   a , spaced around a rectangular or square exhaust gas inlet port  44   a . Similarly, exhaust gas plenum  40   b  includes on its upper surface four attachment bosses, each of which is designated  42   b , spaced around a square exhaust gas inlet port  44   b , exhaust gas plenum  40   c  includes on its upper surface four attachment bosses, each of which is designated  42   c , spaced around a square exhaust gas inlet port  44   c , and exhaust gas plenum  40   d  includes on its upper surface four attachment bosses, each of which is designated  42   d , spaced around a square exhaust gas inlet port  44   d . Each of the bosses of set  42  is attached to the lower end of a leg of the associated support structure. As an example, the lower ends of the three vertically disposed legs  14   d   1 ,  14   d   2 , and  14   d   3  of support structure  12   d  of missile launcher  10   d  which are visible in FIG. 1 are attached to those three bosses  42   d  of plenum  40   d  which are nearest the viewer. This effectively fastens the plenum  40   d  to its associated support structure  12   d , with axis  8   d  of the elongated vertically-oriented cavity (not designated in FIG. 1) associated with the support structure  12   d  overlying the missile exhaust gas entry port  44   d  of the plenum  40   d.    
         [0019]    The chimneys or missile exhaust gas uptake ducts of each missile launcher cell are connected at their lower, missile exhaust, or breech ends to corresponding apertures of the associated plenum, so that missile exhaust gases entering the plenum can be vented through the chimneys to a location near the upper, missile launch, or muzzle ends of the structure. More particularly, the lower ends of chimneys  30   a   1  and  30   a   2  of missile launcher  10   a  are connected to corresponding apertures  46   a   1  and  46   a   2  of plenum  40   a , the lower ends of chimneys  30   b   1  and  30   b   2  of missile launcher lob are connected to corresponding apertures  46   b   1  and  46   b   2  of plenum  40   b , the lower ends of chimneys  30   c   1  and  30   c   2  of missile launcher  10   c  are connected to corresponding apertures  46   c   1  and  46   c   2  of plenum  40   c , and the lower ends of chimneys  30   d   1  and  30   d   2  of missile launcher  10   d  are connected to corresponding apertures  46   d   1  and  46   d   2  of plenum  40   d . The chimneys are thus supported at their lower ends by attachment to their respective plenums, and may be attached at their upper ends to their respective deck plates. In addition, further attachments may be made along their lengths to their respective support structures.  
         [0020]    [0020]FIG. 2 is a simplified perspective or isometric view of missile launcher cell  10   d  of FIG. 1, standing alone. Elements of FIG. 2 corresponding to those of FIG. 1 are designated by the same reference numerals. In FIG. 2, A portion of the drive mechanism which controls the operation of hatch  16   dh  is designated as  216 . FIG. 3 a  is a simplified perspective or isometric view of the upper, missile launch, or muzzle end  300  of the missile launcher cell  10   d  of FIG. 2. In FIG. 3 a , elements corresponding to those of FIG. 2 are designated by the same reference numerals. In FIG. 3 a , various sets of apertures or holes defined in the edge of the deck portion  16   dd  are designated  316   da   1 ,  316   da   2 ,  316   da   3 , and  316   da   4 . These sets of apertures are provided for allowing the use of bolts to fasten each deck portion to an adjacent deck portion of another missile launcher cell, in order to form an array such as that illustrated and described in conjunction with FIG. 1, or to fasten the deck portion of the cell to an adjacent deck structure of the ship or other support structure on which it is mounted, a cut-away portion of which is illustrated in phantom as  390  in FIG. 3 a.    
         [0021]    [0021]FIG. 3 b  is a simplified perspective or isometric view of a lower, missile exhaust end, or breech end  380  of the missile launcher structure of FIG. 2, illustrating some details of the structure. Elements of FIG. 3 b  corresponding to those of FIG. 2 are designated by like reference numerals. In FIG. 3 b , the structure of plenum  40   d  is seen to include legs or supports  339   a ,  339   b , and  339   c , each of which defines a plurality of plenum-to-ship mounting or attachment holes or apertures  340   d   1 ,  340   d   2 , and  340   d   3 , respectively. In addition, details of the dogdown mechanism  360  include connecting drive bars  350   a  and  350   b.    
         [0022]    In FIGS. 4 a ,  4   b , and  4   c , elements corresponding to those of FIGS. 1, 2,  3   a , and  3   b  are designated by the same reference numerals. In FIG. 4 c , the aperture  418   d  represents the end of the elongated cavity defined by the support structure  12   d , and it is centered on axis  8   d , which appears as a dot in the view of FIG. 4 c . FIG. 4 b  illustrates axis  8   d  as centered in the view, while FIG. 4 a  shows axis  8   d  as off-center relative to the entire structure. Axis  8   d  appears as off center in FIG. 4 a  because it is centered on the support structure  12   d , which is offset relative to the entire missile launcher cell  10   d  because of the presence of the chimneys  30   d   1  and  30   d   2 .  
         [0023]    [0023]FIG. 5 represents a cross-sectional view of missile launcher cell  10   d  of FIG. 1 shown alone, and partially cut away to show the missile  512  and a missile canister  510 , defining a missile launch end  510 ML and a missile exhaust end  510 ME, with the missile  512  contained within the canister  510 . In FIG. 5, the hatch  16   dh  is open.  
         [0024]    Other embodiments of the invention will be apparent to those skilled in the art. For example, while the support structure  12   x  of a cell  10   x  of the FIGURES are illustrated as being of a particular form of lattice, other types may be used, or solid (non-lattice) portions may be used. While the missile launcher array of FIG. 1 shows a linear array of missile launcher cells, the array can be rectangular, so that it includes a plurality of rows and columns, and it may intermix rectangular or square with linear arrays of missile launcher cells. While the plenum associated with each missile launch cell has been shown as being roughly cubical, it may be drum-shaped (that is, a portion of a right circular cylinder) or semispherical (some portion of a sphere, including a hemisphere). While the missile canister has been described as containing a single missile, the missile canister can be of the type containing a plurality of missiles.  
         [0025]    Thus, a missile launcher cell (any one of  12   a ,  12   b ,  12   c , or  12   d  of array  10 , with  12   d  taken as typical) according to an aspect of the invention is for accepting a canisterized missile ( 510 ,  512 ) which defines a missile launch end ( 510 ML) and a missile exhaust end ( 510 ME), for, in use prior to missile launch, holding the missile canister ( 510 ,  512 ) in a generally vertical launch position below a deck ( 390 ). The missile launcher cell ( 16   d ) comprises at least one elongated exhaust gas chimney ( 30   d   1 ,  30   d   2 ). It also comprises a support structure ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ) defining a generally axial cavity ( 418   d ), also defining a missile launch end and a missile exhaust end. The cavity ( 418   d ) of the support structure ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ) has length and cross-sectional dimensions sufficient to accommodate the missile canister The one or more exhaust chimney ( 30   d   1 ,  30   d   2 )s lie along the exterior of the support structure ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ) and extend, parallel with the axis ( 8   d ) of the cavity ( 418   d ), from near the missile launch end ( 300 ) to near the missile exhaust end ( 380 ) of the support structure ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ). The missile launcher cell ( 16   d ) also includes a missile exhaust plenum ( 40   d ) attached to the support structure ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ) near the missile exhaust end ( 380 ) of the support structure ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ). The missile exhaust plenum ( 40   d ) is to the one or more exhaust chimney ( 30   d   1 ,  30   d   2  )s near the missile exhaust end ( 380 ) of the support structure ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ). The missile exhaust plenum ( 40   d ) further includes an attachment arrangement ( 360 ) for attachment to the missile exhaust end ( 510 ME) of the missile canister ( 510 ,  512 ), for routing missile exhaust gas from the missile exhaust end ( 380 ) of the support structure ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ) to the one or more exhaust chimneys ( 30   d   1 ,  30   d   2 ), for causing missile exhaust gas to vent from the one or more chimneys ( 30   d   1 ,  30   d   2 ) near the missile launch end ( 300 ) of the support structure ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ) of the missile launcher cell ( 16   d ). A door or hatch structure ( 16   dh ) is attached to the missile launch end ( 300 ) of the missile launch cell support structure ( 14   d   1 ,  14   d   2 ,  20 d   1   ,  20   d   2 ), for, in the closed state, protecting at least the support structure ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ), the one or more chimney  30   d   1 ,  30   d   2 )s and any missile canister ( 510 ,  512 ) accommodated within the cavity ( 418   d ).  
         [0026]    In a particular embodiment of the invention, the cavity ( 418 ) has a rectangular, or more particularly square, cross-section, and is dimensioned to accommodate a Mk 25 canisterized missile ( 510 , 512 ). The support structure ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ) may be a latticework. The number of chimneys ( 30   d   1 ,  30   d   2 ) in a particular embodiment is two, with the two chimneys ( 30   d   1 ,  30   d   2 ) running parallel with each other and with the cavity axis ( 8   d ).  
         [0027]    In a particularly advantageous embodiment of the invention, an array ( 10 ) of missile launcher cells ( 16   a ,  16   b ,  16   c , and  16   d ) has each of the missile launcher cells ( 16   d ) of the array dimensioned for accepting a canisterized missile ( 510 ,  512 ), where each missile canister ( 510 ,  512 ) defines a missile launch end ( 510 ML) and a missile exhaust end ( 510 ME). In use prior to missile launch, the array ( 10 ) of missile launcher cells ( 16   d ) holds the missile canisters ( 510 ,  512 ) in a generally vertical launch position below a deck. Each of the missile launcher cells ( 16   d ) includes at least one elongated exhaust gas chimney ( 30   d   1 ,  30   d   2 ), and a support structure ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ) defining a generally axial cavity ( 418   d ), and defining a missile launch end ( 300 ) and a missile exhaust end ( 380 ). The cavity ( 418   d ) of the support structure ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ) of each cell has length and cross-sectional dimensions sufficient to accommodate a missile canister ( 510 ,  512 ). The one or more exhaust chimneys ( 30   d   1 ,  30   d   2 ) are attached, andor lie adjacent to, the exterior of the support structure ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ) ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ) and extend, parallel with the axis ( 8   d ) of the cavity, from near the missile launch end ( 300 ) to near the missile exhaust end ( 380 ) of the structure. A missile exhaust plenum ( 40   d ) is attached to the support structure ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ) near the missile exhaust end ( 380 ) of the support structure ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ) of each cell. The missile exhaust plenum ( 40   d ) of each cell ( 16 ) is coupled to the one or more exhaust chimneys ( 30   d   1 ,  30   d   2 ) near the missile exhaust end ( 380 ) of the support structure ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ), and also includes an attachment arrangement or means for attachment ( 360 ) to the missile exhaust end ( 510 ME) of the missile canister ( 510 ,  512 ), for thereby routing missile exhaust gas from the missile exhaust end ( 380 ) of the support structure ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ) to the one or more chimneys ( 30   d   1 ,  30   d   2 ), for causing missile exhaust gas to vent from the at least one chimney ( 30   d   1 ,  30   d   2 ) near the missile launch end ( 300 ) of the support structure ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ). A door or hatch structure ( 16   dh ) is attached to the missile launch end ( 300 ) of the missile launch support structure ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ), for, when closed, protecting at least the support structure ( 14   d   1 ,  14   d   2 ,  20   d   1 ,  20   d   2 ) and the one or more exhaust chimneys ( 30   d   1 ,  30   d   2 ) of the missile launcher cell ( 16   d ), and any missile canister ( 510 ,  512 ) accommodated within the cavity ( 418   d ) of the cell, and for, when open, providing for egress of the missile ( 512 ) from its canister ( 510 ) and exhaust gas from the one or more chimneys ( 30   d   1 ,  30   d   2 ). This arrangement allows the array of missile launchers to be maintained in a condition in which all of the launcher cells are fitted with canisterized missiles, without keeping at least one missile launch cell clear or unloaded so as to provide a chimney or path for the escape of exhaust gas from a missile fired in a missile launch cell of the array. Thus, an aspect of the invention lies in an array of launchers ( 10 ) in which a canisterized missile is located within each of (all of) the cavities of the array.

Technology Category: 2