Abstract:
A reconfigurable missile launcher that avoids some of the costs and disadvantages associated with missile launchers in the prior art. In particular, the illustrative embodiment of the present invention uses a variable-size receptacle for locating and holding a missile canister chosen from a set of missile canister types. The illustrative embodiment also includes a controller that includes data sets that are specific to each of a plurality of missile types.

Description:
FIELD OF THE INVENTION  
       [0001]     The present invention relates to missilery in general, and, more particularly, to missile launchers.  
       BACKGROUND OF THE INVENTION  
       [0002]     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. For the purposes of this specification, a “missile” is defined as a projectile whose trajectory is not necessarily ballistic and can be altered during flight (as by a target-seeking radar device and control elements).  
         [0003]     Multi-cell missile launchers have been developed for several types of missiles.  FIG. 1  depicts two such multi-cell missile launchers mounted to the deck of warship  100  as is known in the prior art. In some prior art arrangements, the multi-cell missile launchers are mounted below the deck. Each launcher is capable of locating, holding, and launching a plurality of a single type of missile canister. The type(s) of launcher is chosen based on the desired capability of the weapons platform, such as warship  100 .  
         [0004]      FIG. 2  depicts a perspective-view of a Lockheed-Martin MK 41 multi-cell missile launcher, which is an example of a multi-cell missile launcher known in the prior art. Each cell of the multi-cell missile launcher is the same (i.e., only one type of missile is launched from the launcher). A characteristic of modern warfare is the need to derive multi-functional capability from weapons platforms used in battle. A warship, for example, might need to launch surface-to-surface missiles during one phase of a battle, and surface-to-air missiles during a different phase of the same battle. Currently, multi-functionality is derived at the level of the systems platform, such as warship  100 , by providing multiple missile launching systems wherein each missile launching system has different functionality. In order to attain multi-functional capability for the weapons platform, multiple launchers are required, which leads to added infrastructure, space requirement, and expense for the weapons platform.  
         [0005]     The multi-cell missile launcher depicted in  FIG. 2  comprises a 2×4 array of MK-41 launch cells, each of which contains a missile of the same type. Each cell is controlled by a MK-41 controller, which contains data and information that is specific to the type of guided missile contained in the launch cells.  
         [0006]     In the prior art, missile canisters have been adapted to hold missiles that are smaller than the missiles for which these missile canisters have been designed. However, this leads to wasted space and reduced firepower for the launch system. In addition, the size of the missile canister limits the size of the missile that can be used, which limits the flexibility of existing missile launchers.  
         [0007]     Therefore, the need exists for a missile launcher that avoids or mitigates some or all of these problems.  
       SUMMARY OF THE INVENTION  
       [0008]     The present invention provides a missile launch system that can be reconfigured to launch missiles of various types and sizes. In particular, the illustrative embodiment of the present invention uses variable-sized receptacles for locating and holding different types of missile canisters. In addition, the illustrative embodiment uses a controller that contains a data set of information for each type of missile for which the reconfigurable launcher can be configured. This mitigates some of the problems associated with launching multiple missile types in the prior art.  
         [0009]     The illustrative embodiment comprises: a missile canister, a missile contained in the missile canister, a reconfigurable receptacle for locating and holding any one of a plurality of missile canister types, an reconfigurable exhaust system for venting fumes from missile canisters in any allowed launcher configuration, and a controller for controlling a plurality of missile types. 
     
    
     BRIEF DESCRIPTION OF THE DRAWINGS  
       [0010]      FIG. 1  depicts a representational diagram of a naval launch system according to the prior art.  
         [0011]      FIG. 2  depicts a perspective view of a multi-cell missile launcher according to the prior art.  
         [0012]      FIG. 3  depicts a representational diagram of a naval launch system in accordance with the illustrative embodiment.  
         [0013]      FIG. 4  depicts a block diagram of reconfigurable launcher  302  in accordance with the illustrative embodiment.  
         [0014]      FIG. 5  depicts a block diagram of a launch cell in accordance with the illustrative embodiment.  
         [0015]      FIG. 6  depicts a block diagram of a multi-missile controller in accordance with the illustrative embodiment.  
         [0016]      FIG. 7  depicts a cross-sectional view of a launch cell in accordance with the illustrative embodiment.  
         [0017]      FIG. 8  depicts a cross-sectional view of an exhaust system in accordance with the illustrative embodiment. 
     
    
     DETAILED DESCRIPTION  
       [0018]      FIG. 3  depicts a representational diagram of a naval launch system in accordance with the illustrative embodiment. Although reconfigurable multi-cell missile launcher  302  (hereinafter referred to as “reconfigurable launcher”  302 ) is mounted on the deck of warship  100 , 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 reconfigurable launcher  302  is mounted below the deck of warship  100 , is terrestrially-based, or is mounted on another type of vehicle (e.g., a truck, a railroad car, a submarine, a space vehicle, a satellite, etc.)  
         [0019]      FIG. 4  depicts a block diagram of reconfigurable launcher  302  in accordance with the illustrative embodiment. Although only a one-dimensional array of four launch cells is shown in  FIG. 4 , 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 launch system  302  comprises a single reconfigurable launch cell, a one-dimensional array of any number of reconfigurable launch cells, or a two-dimensional array of any number of reconfigurable launch cells.  
         [0020]     Reconfigurable launcher  302  comprises Type-A launch cell  404   1 , two Type-B launch cells  404   2  and  404   4 , Type-C launch cell  404   3 , exhaust system  406 , cable  410 , and multi-missile controller  408 . The missile types, A, B, and C represent three different nonspecific missile types, each having a different canister size.  
         [0021]     Exhaust system  406  is connected to all launch cells  404   1  through  404   4  via exhaust outlets such that exhaust system  406  vents exhaust fumes generated during the launch of a missile in one or all of launch cells  404   1  through  404   4 . Exhaust system  406  is described in detail below and with respect to  FIGS. 7 and 8 .  
         [0022]     Multi-missile controller  408  contains multiple data sets, wherein each data set contains the data and information specific to the control and launch of each missile type for which reconfigurable launcher  302  is configured. Multi-missile controller  408  is connected to each launch cell  404   1  through  404   4  via cable  410 , so as to provide bi-directional communications between multi-missile controller  408  and each launch cell. Multi-missile controller  408  is described in detail below and with respect to  FIG. 6 .  
         [0023]      FIG. 5  depicts a block diagram of launch cell  404   i , wherein i is a positive integer in the set {1, . . . , 4}, in accordance with the illustrative embodiment. Launch cell  404   i  comprises receptacle  512   i , missile canister  514   i , missile  516   i , and exhaust outlet  518   i .  
         [0024]     Receptacle  512   i  locates and secures missile canister  514   i , which includes missile  516   i . Exhaust outlet  518   i  provides a path through which the exhaust fumes generated by missile  516   i  during launch can escape from launch cell  404   i . The size of receptacle  512   i  determines the type of missile canister  514   i . Different types of missiles are contained in missile canisters of different sizes. Therefore, in order to enable reconfigurable launcher  302  to accommodate different missile types, the size of receptacle  512   i  is reconfigurable, as well as the position of exhaust outlet  518   i . The reconfigurability of receptacle  512   i  and exhaust outlet  518   i  is described in detail below and with respect to  FIG. 7 .  
         [0025]      FIG. 6  depicts a block diagram of multi-missile controller  408  in accordance with the illustrative embodiment. Multi-missile controller  408  comprises processor  620  and memory  622 . Memory  622  comprises N data sets  624   i , wherein i is a positive integer in the set {1, . . . , N}. Each data set  624   i  includes data and information specific to the control and launch of one of the N missile types for which reconfigurable launcher  302  can be configured.  
         [0026]      FIG. 7  depicts a cross-sectional view of launch cell  404   i  in accordance with the illustrative embodiment. Launch cell  404   i  comprises missile canister  514   i , exhaust outlet  518   i , platform  720 , movable supports  722   i  and  722   i+1 , missile  516   i , missile canister connector  724   i , and missile canister-to-missile umbilical  726   i .  
         [0027]     Platform  720  and movable supports  722   i  and  722   i+1  locate and support missile canister  514 . The position of movable supports  722   i  and  722   i+1  can be changed such that the spacing between them accepts a missile canister different than missile canister  514   i , and therefore a missile different than missile  516   i . Movement of movable supports  722   i  and  722   i+1  can be accomplished using hydraulics, electric motors, or manual means. It will be clear to those skilled in the art how to position movable supports  722   i  and  722   i+1 .  
         [0028]     The total size of reconfigurable launcher  302  is fixed and each of movable supports  722  may be shared between two adjacent launch cells  404   i  and  404   i±1 . Therefore, as the size of launch cell  404   i  is changed, the size of adjacent launch cell  404   i−1  or  404   i+1  is changed as well. For example, as movable support  722   i  is moved toward the left to enable location of a larger missile canister in receptacle  512   i , the opening between movable support  722   i  and  722   i−1  (not shown) is made smaller. Thus, the type of missile canister that can be located by receptacle  512   i−1  is changed. In some configurations, reconfigurable launcher  302  will have less than four launch cells, while in other configurations reconfigurable launcher  302  will have more than four launch cells.  
         [0029]     Missile canister  514   i  includes a fly-through cover on one end, and a missile canister back plate on the other end. The missile canister back plate either opens or bursts upon ignition of missile  516   i  to provide access to exhaust outlet  518   i  for exhaust fumes from missile  516   i . Exhaust outlet  518   i  vents exhaust fumes into exhaust plenum  728 , where they combine with the exhaust fumes from other launch cells. It will be clear to those skilled in the art how to make and use a missile canister back plate that provides access to exhaust outlet  518   i  upon ignition of missile  516   i . The position of exhaust outlet  518   i  is reconfigurable to accommodate any of the missile types for which reconfigurable launcher  302  is configured.  
         [0030]     Missile  514   i  communicates with multi-missile controller  408  via cable  410 . Cable  410  is connected to missile  514   i  through cable connector  726   i , missile canister connector  724   i , and missile canister-to-missile umbilical  726   i . In the illustrative embodiment, cable connector  726  is a universal connector that can mate to any of the missile canister connectors associated with each missile canister type for which reconfigurable launcher  302  is suitable. In some embodiments, cable  410  includes a plurality of cable connectors, one for each type of missile canister type for which reconfigurable launcher  302  is suitable.  
         [0031]      FIG. 8  depicts a cross-sectional view of exhaust system  406  in accordance with the illustrative embodiment. Exhaust system  406  comprises exhaust plenum  728 , exhaust outlets  518   i , wherein i is a positive integer in the set {1, . . . , 5}, and exhaust uptake  830 . Each launch cell  404   1  through  404   4  includes an exhaust outlet  518   1  through  518   4 , such that the exhaust fumes generated during a missile launch in that cell are directed into exhaust plenum  728 . An additional exhaust outlet  518   5  provides access to exhaust uptake  830  for the exhaust fumes in exhaust plenum  728 . Exhaust uptake  830  provides egress for the exhaust fumes into the atmosphere that surrounds reconfigurable launcher  302 .  
         [0032]     In some embodiments of the present invention, exhaust system  406  includes a plurality of exhaust uptakes  830 . In some embodiments of the present invention, exhaust uptake  830  is located in the interior of reconfigurable launcher  830 , i.e. between two launch cells such as launch cells  404   2  and  404   3 . In some embodiments of the present invention, platform  720  comprises through-holes that allow exhaust fumes to vent directly through platform  720  and into and out of exhaust plenum  728 , obviating discrete exhaust outlets  518   1  through  518   5 .  
         [0033]     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 Specification, 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.  
         [0034]     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 specification 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 Specification 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.