Abstract:
A missile launch system is disclosed that allows for the rapid reloading of missiles in support of missions (e.g., littoral warship missions, etc.) that require a high-volume assault of one or more targets. In particular, the illustrative embodiment of the present invention uses a munitions module that is capable of launching missiles and is able to fit inside a warship. In addition to accommodating multiple missiles, the munitions module accommodates one or more missile types. The munitions module is configured with a door at a breech end to provide access to multiple launch cells for the rapid reloading of missiles. The door is physically configured to define a plenum that couples the launch cells to an exhaust duct for the purpose of venting exhaust gases. The munitions module mitigates some of the problems associated with launch systems in the prior art.

Description:
FIELD OF THE INVENTION 
   The present invention relates to missilery in general, and, more particularly, to missile launchers. 
   BACKGROUND OF THE INVENTION 
   A missile launcher is capable of receiving, storing, and launching one or more missiles. Missile launchers-vertical missile launchers, in particular—have been developed for warships whose primary missions are in deep (“dark”) water, far away from shore, where the target is typically about 70 kilometers or more away.  FIG. 1  depicts two such vertical missile launchers, launchers  102 - 1  and  102 - 2 , mounted on outside decks of warship  100  as is known in the prior art. 
   In some prior art arrangements, the vertical missile launchers are mounted below the deck in enclosed regions.  FIG. 2  depicts a perspective-view of a Lockheed-Martin MK  41  vertical missile launch system, which is an example of a missile launch system known in the prior art. The MK  41  launch system can be located either above or below deck. Each cell of the vertical missile launcher houses a missile canister, which in turn houses a missile. Each missile must carry enough fuel for delivering the required munitions to a target, where the target can be considerably beyond the horizon. Because the missiles are big and heavy, owing to their mission, reloading the missiles can be a complex and slow process. 
   The need for warships that operate primarily in coastal areas (i.e., littoral waters), has increased in the past few years. These littoral warships have missions that generally require short-range missiles (i.e., missiles with ranges around 70 kilometers or less). In addition, littoral warships are often intended for missions in which multiple, smaller, closer targets are engaged (i.e., so called “small boat swarms,”) which require the warship to fire missiles for a prolonged period of time. In short, the relatively smaller amount of heavy, long-range missiles that deep water warships carry is undesirable in a littoral warship because of the excessive firepower of each long-range missile, the insufficient number of missiles that are ready for launching at any given time, an inability to rapidly re-load missiles, and, in some cases, an inability to re-load missiles without returning to shore. 
   Shorter-range missiles, such as those that are desirable for a littoral warship, are usually launched from a horizontal or inclined position, not a vertical position. As a consequence, these types of missiles are typically launched from on-deck launchers. Unfortunately, most on-deck missile launchers have a substantial signature (e.g., infrared, radar, etc.) which decreases their likelihood of survivability. 
   Therefore, the need exists for a missile launch system that avoids or mitigates some or all of these problems. 
   SUMMARY OF THE INVENTION 
   The present invention provides a missile launch system that allows for the rapid reloading of missiles in support of missions (e.g., littoral-warship missions, etc.) that require a high-volume assault of one or more targets. 
   In the illustrative embodiment, the missile launch system comprises a munitions module that has a plurality of launch cells for launching a plurality of missiles. The missiles can be all of one type, or, alternatively, the module can store and launch different types of missiles at the same time. In some embodiments, the launch cells are dimensioned and arranged to facilitate the use of multiple types of missiles. 
   The munitions module is configured with a door at a breech end to provide access to the launch cells to rapidly reload missiles. In the illustrative embodiment, the door is physically configured to define a plenum that fluidically couples the launch cells to an exhaust duct for the purpose of venting missile exhaust gases. 
   The munitions module is able to fit within, or partially within, a warship. The munitions module is advantageously coupled to a region of the ship where missiles can be stored nearby for faster, easier reloading than with some arrangements in the prior art. 
   In accordance with the illustrative embodiment, the front of the munitions module is physically configured to complement a surface form of the warship, such as a wall or bulkhead, at the place on the warship where the module is located. In other words, the module can be tailored to fit inside a region on a ship that has normally unusable or underutilized space, such as up against an oblique corner of a room or an inclined wall on the ship. Locating the module inside the ship, in addition to facilitating reloading, advantageously reduces the ship&#39;s signature compared to some arrangements in the prior art. 
   In accordance with the illustrative embodiment of the present invention, a heat-transferring and shock-absorbing structure is disposed between each launch cell. The structure comprises pressurized water tubes that run the length of each launch cell. The multiple rows of tubes exhibit improved thermal and vibrational transfers of energy compared to some arrangements in the prior art. 
   In addition, the illustrative embodiment uses a controller that receives controlling signals, including launch-related commands and targeting information from a source that is away from the warship (i.e., an off-ship source). One example of an off-ship source is a helicopter that marks a target by using a laser. The helicopter “lases” the target, the controller launches the selected missile based on signals from the helicopter, and the missile seeks the target while being guided to the target by the laser. The helicopter crew can, of course, use the helicopter-based munitions, as appropriate, to supplement the fire-power of the munitions module. 
   The illustrative embodiment comprises: a plurality of elongated launch cells, wherein each launch cell has a breech end and a missile egress end, and wherein an axis defined between the breech end and the egress end is substantially horizontal; a door, wherein the door is proximal to the breech end of the plurality of launch cells and enables access thereto, and wherein the door is physically configured to define a plenum for receiving a flow of exhaust gases; and at least one duct for venting the exhaust gases, wherein the at least one duct is in fluidic communication with the plenum. 

   
     BRIEF DESCRIPTION OF THE DRAWINGS 
       FIG. 1  depicts two vertical missile launchers mounted to the deck of a warship, as is known in the prior art. 
       FIG. 2  depicts a perspective-view of a vertical missile launch system, which is an example of a missile launch system known in the prior art. 
       FIGS. 3A and 3B  depict representational diagrams of a missile launch system in accordance with the illustrative embodiment of the present invention, wherein the missile launch system is disposed on a warship, 
       FIG. 4  depicts a block diagram of missile launch system  300 , in accordance with the illustrative embodiment of the present invention. 
       FIG. 5  depicts a first perspective view of munitions module  302 - 1 , in accordance with the illustrative embodiment. 
       FIG. 6  depicts a second perspective view of munitions module  302 - 1 , as seen from the breech end and in accordance with the illustrative embodiment. 
       FIG. 7  depicts a block diagram of launch cell  501 - p - q , in accordance with the illustrative embodiment. 
       FIG. 8  depicts a first cross-sectional view, as viewed from the top of munitions module  302 - 1 , in accordance with the illustrative embodiment of the present invention. 
       FIG. 9  depicts a second cross-sectional view, as viewed from the top of munitions module  302 - 1 , in accordance with the illustrative embodiment of the present invention. 
       FIG. 10  depicts a block diagram of controller  303 , in accordance with the illustrative embodiment of the present invention. 
   

   DETAILED DESCRIPTION 
   The following terms are defined for use in this Specification, including the appended claims:
         A “missile” is defined as a projectile whose trajectory is not necessarily ballistic and can be altered during flight (e.g., as by a target-seeking radar or laser-based device, etc.). A missile is propelled by fuel and a chemical-propulsion engine. A chemical-propulsion engine propels a missile by the reaction that results from the rearward discharge of gases that are liberated when the fuel is burned.   Fluidic communication is defined as the flow of a fluid, such as exhaust gas, from one space or region to another. When two regions are said to be in fluidic communication with one another, a change in pressure, or gas flow in one of the regions can affect the pressure or flow in the other region.       

     FIGS. 3A and 3B  depict representational diagrams of a missile launch system that is disposed on warship  100 , in accordance with the illustrative embodiment of the present invention.  FIG. 3A  depicts a side view and  FIG. 3B  depicts a top view of warship  100 . Missile launch system  300  comprises munitions modules  302 - h  for h=1 through H (H=2 in the illustrative embodiment), and controller  303 . Each munitions module  302 - h , which, when referenced generically, is hereinafter referred to as “munitions module  302 ,” is capable of accommodating one or more missiles, which are launched by using controller  303 . Although  FIGS. 3A and 3B  depict a configuration for H equal to two, it will be clear to those skilled in the art, after reading this disclosure, how to make and use missile launch system  300  with a different number of munitions modules. 
   Missile launch system  300  is disposed at the aft end of deck  101 , as depicted in  FIGS. 3A and 3B . Munitions modules  302 - 1  and  302 - 2  are mounted at the left and right aft positions, respectively. The munitions modules are physically configured to fit alongside the outer walls of deck  101 , thereby minimizing the additional space required to accommodate missile launch system  300 . It will be clear to those skilled in the art, after reading this disclosure, how to make and use alternative embodiments of the present invention in which one or more munitions modules  302  are mounted on an outside deck of warship  100 , are within or below a deck other than deck  101 , are terrestrially-based (e.g., with ground troops, etc.), or are mounted on another type of vehicle (e.g., a truck, a railroad car, a submarine, a space vehicle, etc.). 
     FIG. 4  depicts a block diagram of missile launch system  300 , in accordance with the illustrative embodiment of the present invention. Missile launch system  300  comprises munitions module  302 - h , for h=1 through H, and controller  303 , interconnected as shown. Munitions module  302  is described below and with respect to  FIGS. 5 through 9 . It will be clear to those skilled in the art, after reading this specification, how to make and use munitions module  302 . 
   Controller  303  is capable of controlling munitions modules  302 . Controller  303  is used to control the launching of one or more missiles, wherein the missiles can be a single type or different types. The data and information specific to the control and launch of each missile type for which each munitions module  302  is configured is stored by controller  303 . Controller  303  is able to receive and accept control signals from onboard warship  100  or from an off-ship source, such as control signal source  410 . Source  410  can be a helicopter, a fixed-wing aircraft (manned or unmanned), a ground-based force, and so forth. In some scenarios, source  410  will be in a position in which it can mark a target (e.g., with a laser, etc.) and then transmit the missile launch command to controller  303 . Controller  303  is described below and with respect to  FIG. 10 . It will be clear to those skilled in the art, after reading this specification, how to make and use controller  303 . 
     FIG. 5  depicts a first perspective view of munitions module  302 , in accordance with the illustrative embodiment. Munitions module  302  comprises Type-1-launch cells  501 - 1 - i , for i=1 through I; Type-2 launch cells  501 - 2 - j , for j=1 through J; Type-3 launch cells  501 - 3 - k , for k=1 through K; duct  502 ; and door  503 , interrelated as shown. Type-1, Type-2, and Type-3 launch cells are for launching respective Type-1, Type-2, and Type-3 missiles. The missile types 1, 2, and 3 represent three different, non-specific missile types, each having a different size (e.g., cross-section, length, etc.). Although munitions module  302  is depicted for a configuration with I=8, J=6, and K=2, it will be clear to those skilled in the art, after reading this disclosure, how to make and use alternative embodiments of the present invention for different combinations of I, J, and K. It will also be clear to those skilled in the art, after reading this disclosure, how to make and use alternative embodiments with different physical configurations (e.g., a different number of missile types, a different arrangement of launch cells with respect to each other, etc.) than that depicted in  FIG. 5 . 
   Each launch cell of munitions module  302  has a breech end and a missile egress end, wherein the elongated launch cell extends between the breech end and missile egress end. In accordance with the illustrative embodiment, an axis defined between the breech end and missile egress end is substantially horizontal. In some alternative embodiments, the axis of at least some of launch cells  501  might be situated at angles that are other than horizontal. 
   Depicted in the foreground in  FIG. 5  is the front end of munitions module  302 , wherein the front end is proximal to the missile-egress ends of launch cells  501 . Door  503  is proximal to the breech end. Munitions module  302  is shaped to fit in the left aft corner of deck  101  and, as such, is physically configured to complement a surface form (e.g., an outer wall, a bulkhead, etc.) of a region of warship  100 . Accordingly, as depicted in  FIG. 5 , the right portion (as depicted) of the front end is angled inward to complement the wall of the left aft corner region of deck  101 . As those who are skilled in the art will appreciate, in some alternative embodiments, the front end of munitions module  302  will have a different shape (e.g., flat, angled inward on the left portion, angled vertically instead of horizontally, etc.) than that depicted in  FIG. 5 , as is appropriate for the particular installation. Furthermore, in some embodiments, the openings at the missile egress ends of one or more launch cells can be covered by blast covers. 
   Within munitions module  302 , the arrangement in which launch cells  501 - p - q , for p=1 through P and q=1 through Q, are grouped is based on one or more factors, in accordance with the illustrative embodiment of the present invention. (P is equal to three and Q is dependent on i, j, and k, as depicted.) In some embodiments, the arrangement is based on the surface form of the region in which munitions module  302 - h  is disposed. In some other embodiments, the arrangement is based on a first type of missile, wherein the launch cells for the first type of missile are arranged in at least a first column (e.g., launch cells  501 - 1 - 1  and  501 - 1 - 2 , etc.). In still some other embodiments, the arrangement is based on a second type of missile, wherein the launch cells for the second type of missile are arranged in at least a first row (e.g., launch cells  501 - 3 - 1  and  501 - 3 - 2 , etc.). As those who are skilled in the art will appreciate, launch cells can be grouped, within munitions module  302 , in additional arrangements that are based on other criteria. 
   Duct  502  and door  503 , which is physically configured to define a plenum, constitute an exhaust system that is coupled with all launch cells  501  such that the exhaust system vents exhaust gases generated during the launch of a missile in one or all of launch cells  501 . Duct  502  is used for venting the exhaust gases and, therefore, is in fluidic communication with the plenum in door  503 . In accordance with the illustrative embodiment, a single duct  502  is positioned near the top of munitions module  302 . In some alternative embodiments, duct  502  overlies at least some of launch cells  501 . Also, in some other embodiments, munitions module  302  includes one or more ducts in addition to duct  502 . Duct  502  and door  503  are described in detail below and with respect to  FIGS. 8 and 9 . 
     FIG. 6  depicts a second perspective view of munitions module  302 , as seen from the breech end and in accordance with the illustrative embodiment. Depicted as seen from the breech end are Type-1 launch cells  501 - 1 - i , Type-2 launch cells  501 - 2 - j , and Type-3 launch cells  501 - 3 - k . Door  503  is shown in an open position, which reveals the plenum space that receives a flow of exhaust gases from launch cells  501  when door  503  is closed and one or more missiles are launched. 
   Structure  601  is one of several barriers that are disposed between one or more groups of launch cells  501 , and that extend from the breech end to the front end of munitions module  302 . Structure  601  comprises a physical adaptation for removing heat from one or more of launch cells  501 - p - q . In addition to transferring heat during a missile launch, structure  601  also is able to absorb shock and minimize vibration. In accordance with the illustrative embodiment, structure  601  comprises a plurality of tubes (e.g., tube  601 - 1 , tube  601 - 2 , etc.) that are physically adapted to absorb shock and remove heat from launch cells  501 . The tubes contain a pressurized liquid (e.g., water, etc.), wherein each of the tubes is substantially parallel to one or more launch cells  501 - p - q . As those who are skilled in the art will appreciate, in some alternative embodiments, structure  601  can be made up of other materials with heat-transferring and shock-absorbing properties. 
     FIG. 7  depicts a block diagram of launch cell  501 - p - q , in accordance with the illustrative embodiment. Launch cell  501 - p - q  comprises receptacle  702   p,q , missile canister  704   p,q , missile  706   p,q , and exhaust outlet  708   p,q , which are well-known in the art. 
   Receptacle  702   p,q  locates and secures missile canister  704   p,q , which contains missile  706   p,q , in well-known fashion. Exhaust outlet  708   p,q  provides a path through which the exhaust gases generated by missile  706   p,q  during launch can escape from launch cell  501 - p - q  towards the plenum space of door  503 . The size of receptacle  702   p,q  is determined by the type of missile canister  704   p,q , Different types of missiles (e.g., short-range types, etc.) are contained in missile canisters of different sizes. Therefore, in order to enable munitions module  302 - h  to accommodate different missile types, in addition to the size of launch cell  501 - p - q  being reconfigurable, the size of receptacle  702   p,q  is reconfigurable, as well as the position of exhaust outlet  708   p,q . 
   In some alternative embodiments, launch cell  501 - p - q  and receptacle  702   p,q  are combined into the same structure. For example, in those embodiments launch cell  501 - p - q  might directly locate and secure missile canister  704   p,q  without a separate receptacle  702   p,q . 
     FIG. 8  depicts a first cross-sectional view, as viewed from the top of munitions module  302 , in accordance with the illustrative embodiment of the present invention. The view depicts a cross-section of munitions module  302  that cuts across launch cells  501 - 1 - 1  and  501 - 1 - 8 , portions of structure  601 , and duct  502 . Door  503  is shown in an open position, allowing illustrative missile  706   1,8  to be loaded into the breech end of munitions module  302 , into launch cell  501 - 1 - 8 . Door  503  is able to (i) open for the purpose of loading one or more launch cells  501  with missiles and (ii) close for the purpose of securing the breech end of munitions module  302 - 1  for missile firing and for the subsequent venting of gases. Note that munitions module  302 - 1  is disposed near the left aft corner, outer walls of deck  101 . 
     FIG. 9  depicts a second cross-sectional view, as viewed from the top of munitions module  302 - 1 , in accordance with the illustrative embodiment of the present invention. The view depicts a cross-section of munitions module  302 - 1  that cuts across launch cells  501 - 1 - 1  and  501 - 1 - 8 , portions of structure  601 , and duct  502 . Door  503  is shown in the closed position. When missile  706   1,8  is fired, as shown exiting the missile-egress end of launch cell  501 - 1 - 8 , the exhaust gas first flows through launch cell  501 - 1 - 8  at the breech end. The plenum space in door  503  then enables the exhaust gas to flow to duct  502 , in accordance with the illustrative embodiment of the present invention. Finally, the exhaust gas flows through duct  502  from the breech end to the front end and is emitted through the duct opening, or “uptake,” and out of munitions module  302 . 
   In some alternative embodiments, door  503  is replaced with a structure that comprises one or more hatches and a plenum. For example, such a structure is secured to the breech end of launch cells  501  to allow for the flow of exhaust gases and could be fitted with multiple hatches on its rear side to allow for the reloading of missiles. 
     FIG. 10  depicts a block diagram of controller  303 , in accordance with the illustrative embodiment of the present invention. Controller  303  comprises receiver  1001 , processor  1002 , memory  1003 , and transmitter  1004 , interconnected as shown. 
   Receiver  1001  receives signals from control signal source  410  and forwards the information encoded in these signals (e.g., launch commands, etc.) to processor  1002 , in well-known fashion. It will be clear to those skilled in the art, after reading this specification, how to make and use receiver  1001 . 
   Processor  1002  is a general-purpose processor that is capable of receiving information from receiver  1001 , of executing instructions stored in memory  1003 , of reading data from and writing data into memory  1003 , and of transmitting information to transmitter  1004 . Processor  1002  is also capable of transmitting signals to one or more launch cells  501  for the purpose of launching missiles, in well-known fashion. In some alternative embodiments of the present invention, processor  1002  might be a special-purpose processor. In either case, it will be clear to those skilled in the art, after reading this specification, how to make and use processor  1002 . 
   Memory  1003  stores data and executable instructions, as is well-known in the art, and might be any combination of random-access memory (RAM), flash memory, disk drive memory, and so forth. Memory  1003  comprises P data sets  810   p , wherein p is a positive integer in the set {1, . . . , P}. Each data set  810   p  includes data and information specific to the control and launch of one of the P missile types for which munitions module  302  can be configured to accommodate. It will be clear to those skilled in the art how to make and use memory  1003 . 
   Transmitter  1004  receives information (e.g., acknowledgments to commands, etc.) from processor  1002  and transmits signals that encode this information to control signal source  410 , in well-known fashion. It will be clear to those skilled in the art, after reading this specification, how to make and use transmitter  1004 . 
   It is to be understood that the above-described embodiments are merely illustrative of the present invention and that many variations of the above-described embodiments can be devised by those skilled in the art without departing from the scope of the invention. For example, in this Disclosure, numerous specific details are provided in order to provide a thorough description and understanding of the illustrative embodiments of the present invention. Those skilled in the art will recognize, however, that the invention can be practiced without one or more of those details, or with other methods, materials, components, etc. 
   Furthermore, in some instances, well-known structures, materials, or operations are not shown or described in detail to avoid obscuring aspects of the illustrative embodiments. It is understood that the various embodiments shown in the Figures are illustrative, and are not necessarily drawn to scale. Reference throughout the disclosure to “one embodiment” or “an embodiment” or “some embodiments” means that a particular feature, structure, material, or characteristic described in connection with the embodiment(s) is included in at least one embodiment of the present invention, but not necessarily all embodiments. Consequently, the appearances of the phrase “in one embodiment,” “in an embodiment,” or “in some embodiments” in various places throughout the Disclosure are not necessarily all referring to the same embodiment. Furthermore, the particular features, structures, materials, or characteristics can be combined in any suitable manner in one or more embodiments. It is therefore intended that such variations be included within the scope of the following claims and their equivalents.