Abstract:
A modular missile assembly includes a pair of modules which are separately transported and handled until just prior to firing, when they are coupled together. A forward payload-carrying module includes a forward canister which encloses a missile payload section, for example, consisting of a penetrator rod, fins, and ancillary sub-assemblies. An aft booster module includes a missile propulsion section, encased in an aft canister. Prior to firing, suitable forward and aft modules are selected, are individually loaded into a launch tube, and are coupled together. In this coupling the missile payload section and the missile propulsion section are coupled together to form a missile, and the forward and aft canisters are likewise coupled together to form a combined canister assembly. Division of the missile into separate payload and booster modules facilitates handling as compared to unitary missiles. The modular design also allows increased flexibility.

Description:
BACKGROUND OF THE INVENTION 
     1. Field of the Invention 
     The invention is in the field of missiles and methods of configuring and/or assembling missiles. 
     2. Description of the Related Art 
     For certain missile systems, for example, high-kinetic-energy anti-tank missiles and cruise missile interceptors, it is desirable to accelerate a projectile to high speed, such as supersonic or hypersonic speeds. At such speeds the projectile intercepts the target in a minimum amount of time, and has sufficient energy to penetrate and destroy the target. However, boosting the projectile to the required speed necessitates use of a large rocket motor. Moreover, to assure that adequate kinetic energy is delivered to the target, a heavy projectile is required. When combined, these two requirements may result in a missile having an extraordinarily high pre-launch weight. In tactical deployment, excessively heavy missiles make forward-staging, loading, down-loading, storage and other handling operations slow and difficult. Missile weights that exceed established thresholds for manual handling may require special equipment such as autoloaders. 
     An exemplary tactical kinetic energy anti-tank missile utilizes a rocket motor weighing from 65 to 70 pounds, and a projectile weighing between 15 and 25 pounds. To these figures must be added the weight of any control surfaces, electronics, actuation systems, and supporting structural elements. Consequently, the total pre-launch weight of such a missile may easily exceed 100 pounds. 
     From the foregoing it will be appreciated that it would be desirable to avoid the handling difficulties associated with missiles having a high weight. 
     SUMMARY OF THE INVENTION 
     A modular missile assembly includes a pair of modules which are separately transported and handled until just prior to firing, when they are coupled together. A forward payload-carrying module includes a forward canister which encloses a missile payload section, for example, consisting of a penetrator rod, fins, and ancillary sub-assemblies. An aft booster module includes a missile propulsion section, encased in an aft canister. Prior to firing, suitable forward and aft modules are selected, are individually loaded into a launch tube, and are coupled together. In this coupling the missile payload section and the missile propulsion section are coupled together to form a missile, and the forward and aft canisters are likewise coupled together to form a combined canister assembly. Division of the missile into separate payload and booster modules facilitates handling as compared to unitary missiles. The modular design also allows increased flexibility, for example, allowing a single booster module to be used with different types of payload-carrying modules, carrying different types of missile payload sections, which may be tailored for use with different kinds of targets. 
     According to an aspect of the invention, a missile assembly includes a forward payload-containing module having a first coupling mechanism at a back end; and an aft booster module having a second coupling mechanism at a front end. The first and second coupling mechanisms are operatively configured to couple the modules together in a launch tube. 
     According to another aspect of the invention, a method of assembling a missile includes the steps of individually loading a pair of missile modules into a launch tube; and coupling the modules together in the launch tube. 
     According to yet another aspect of the invention, a missile payload section includes a missile payload section which in turn includes a penetrator rod, fins coupled to the penetrator rod, and means operatively configured for coupling to a corresponding missile propulsion section, wherein the means for coupling is at an aft end of the payload section; a canister which fits around the payload; and a cap removably secured to an aft end of the canister. The cap, when secured, covers the means for coupling. 
     To the accomplishment of the foregoing and related ends, the invention comprises the features hereinafter fully described and particularly pointed out in the claims. The following description and the annexed drawings set forth in detail certain illustrative embodiments of the invention. These embodiments are indicative, however, of but a few of the various ways in which the principles of the invention may be employed. Other objects, advantages and novel features of the invention will become apparent from the following detailed description of the invention when considered in injunction with the drawings. 
    
    
     BRIEF DESCRIPTION OF DRAWINGS 
     In the annexed drawings: 
     FIG. 1 is a side view of a modular missile assembly of the present invention; 
     FIG. 2 is a side view showing the modules of the missile of FIG. 1 prior to connection; 
     FIG. 3 is an exploded view of the forward payload-carrying module of the missile assembly of FIG. 1; 
     FIG. 4 is an exploded view of the aft booster module of the missile assembly of FIG. 1; 
     FIG. 5 is a flowchart illustrating steps in the assembly of the missile assembly of FIG. 1; 
     FIG. 6 is a side view illustrating the loading of the modules of the missile assembly of FIG. 1 into a launch tube of a launcher; 
     FIG. 7 is a side view of a missile assembly embodying the present invention, which separates during flight; 
     FIG. 8 is a side view of a missile payload section for a missile of the present invention, the payload section including an articulated nose section; 
     FIG. 9 is a side view of a missile propulsion section for a missile assembly of the present invention which utilizes a torque motor to impart spin; and 
     FIG. 10 is a side view of a missile payload section for use in a modular missile assembly of the present invention, the missile payload section including a torque motor in its forward payload-carrying module. 
    
    
     DETAILED DESCRIPTION 
     A modular missile assembly includes a forward payload-containing module and an aft booster module. The forward module includes a forward canister containing a missile payload section including a payload such as a projectile for striking a target. The aft module includes an aft canister containing a missile propulsion system such as a rocket motor. The forward and aft modules may be handled separately until firing is desired. Then the modules are loaded into a launch tube and connected together, thereby completing assembly of the missile. By having the modules separate until firing is desired, handling is facilitated, since each of the modules weighs far less than the combined missile. Furthermore, use of separate modules enables greater flexibility in missile payloads. Multiple varieties of payload modules, for example for use with different targets, may be manufactured to be compatible with a single type of booster module. Selection of the payload module may be made in the field prior to firing. Since only a variety of payload modules need be maintained in inventory, as opposed to a variety of complete missiles, inventories and therefore costs may be reduced. 
     Turning now to FIG. 1, a modular missile assembly  10  of the present invention is shown. The missile assembly  10  includes a forward payload-carrying module  12  and an aft booster module  14 . The modules  12  and  14  are coupled together via a coupling  16 . As described below in greater detail, the forward module  12  includes a forward canister  18  which encloses a missile payload section  20 , and the aft module  14  includes an aft canister  22  which encloses a missile propulsion section  24 . The propulsion section  24  may include subsystems and subassemblies, such as electronics, controls, and deployable stabilizing fins. The coupling connects the payload section  20  and the propulsion section  24  together to form a modular missile  26 . The coupling  16  also connects the canisters  18  and  22  together to form a canister assembly  27 . 
     Turning now to FIGS. 2-4, details may be seen of the modules  12  and  14 . The missile payload section  20  includes a penetrator rod  28 , as well as fins  30  which are coupled to the penetrator rod. The penetrator rod  28  may be made of a heavy material, for example tungsten or depleted uranium, selected to penetrate a desired target. It will be appreciated that a variety of sizes, shapes, and/or materials may be employed in the penetrator rod  28 . 
     The fins  30  may be stabilizing fins for stabilizing flight of the missile  26 . Alternatively or in addition, the fins  30  may be canted so as to impart and/or maintain rotation of the missile  26  while the missile is in flight. The fins  30  may include folded portions which deploy as the payload section  20  emerges from the forward canister  18  and/or from a launch tube. 
     The payload section  20  may include other items such as a secondary propulsion system, a chemical energy target defeat mechanism, sensors and micro-electronics. The sensors and the micro-electronics may be utilized to aid in guiding the missile  26  to its intended target. It will be appreciated that the missile  26  may be guided by any of a variety of known means. For example, actuators may be used to move one or more of the fins  30 , thereby altering the trajectory of the missile  26 . 
     A forward cap  32  may be removably secured to the forward canister  18  until just prior to the connection of the forward module  12  to the aft module  14 . The forward cap  32  covers and protects a forward connection  34  at the back end of the payload section  20 . The forward cap  32  may also be secured to the payload section  20 , thereby holding the payload section in place relative to the forward canister  18 , prior to the assembly of the missile  10 . 
     It will be appreciated that the forward cap  32  may be secured to the forward canister  18  and/or to the payload section  20  by any of a variety of conventional means, including connections involving quick-release clamps, pins, springs, threaded fasteners, or other connections, tabs, and/or the mating together of indexed parts. 
     The aft booster module  14  includes an aft connection  40  which is operatively configured to couple to the forward connection  34  of the forward module  12 , the connections  34  and  40  being configured to combine to form the coupling  16 . The connections  34  and  40  may be any of a variety of suitable well-known means of connection. For example, the connections  34  and  40  may include a mechanical index system where features on one of the connections  34  and  40  has a corresponding mirror image feature on the other connection. For example, the connections may involve a pilot shaft on one component, or a positioning and locking mechanism on the outer edges of the connections  34  and  40 . It will be appreciated that a variety of suitable locking mechanisms may be employed, such as, for example, mechanisms involving springs and/or tabs. 
     The coupling  16  formed by connecting the connections  34  and  40  together may be merely a mechanical connection. Alternatively, the coupling  16  may include a connection for other purposes, for example, including a communication link between the payload section  20  of the forward module  12  and the propulsion section  24  of the aft booster module  14 . As noted above, the coupling  16  may also include a connection between the forward canister  18  and the aft canister  22 . 
     The aft connection  40  is located on a protruding portion  48  of the propulsion section  24 . When the missile  10  is assembled, the protruding portion  48  extends into the forward canister  18  and pushes the payload section  20  forward relative to the forward canister  18 . A tip  50  of the penetrator rod  28  may thereby extend beyond a front edge  54  of the forward canister  18 . A removable aft cap  56  may be used to cover the protruding portion  48  and the aft connection  40 , prior to the assembly of the modules  12  and  14  to form missile assembly  10 . 
     The missile propulsion section  24  may be of conventional design, for example, including a solid fuel rocket having one or more nozzles. As is well known, some or all of the nozzles may be canted to provide spin to the missile  26 , if desired. In addition, some or all of the nozzles may be tiltable, for example, to provide steering for the missile. An example of a mechanism for tilting missile nozzles may by seen in U.S. Pat. No. 3,200,586, the detailed description and figures of which are incorporated herein by reference. 
     The aft canister  22  may have protuberances such as lugs  60 . The lugs  60  may be used to index the missile assembly  10  relative to a launch tube. 
     Turning now to FIG. 5 a flowchart is shown of a method  100  for selecting components and assembling the missile assembly  10 . The method  100  is advantageous in that its steps may be performed in the field immediately prior to the firing of the missile  26 . As indicated before, this may increase flexibility as to the types of payloads employed, may reduce field inventory requirements, and/or may reduce or avoid handling problems associated with heavy missiles. 
     In step  102 , the desired forward and aft modules  12  and  14  are selected. The forward module  12  may be selected from a variety of types of forward modules. For example, a variety of types of modules with different payloads may be maintained for use with different types of targets. For example, it may be desirable to use a lighter payload for a lightly-armored target, such as a helicopter, while using a heavier payload for a heavier target, such as a tank. Further, it may be desirable to have practice rounds which utilize less expensive payloads. 
     It will also be appreciated that a variety of types of aft booster portions may be maintained. For example, different types of booster portions may be used to provide different amounts of thrust and/or different thrust characteristics. 
     Once the modules  12  and  14  have been selected, the module caps  32  and  56  are removed in step  104 , and the modules are loaded into a launch tube in step  106 . As illustrated in FIG. 6, the forward payload-carrying module  12  may be loaded into a front end  108  of a launch tube  110  of a launcher  114 . The aft booster module  14  may be loaded in a back end  118  of the launch tube  110 . It will be appreciated that alternatively the modules  12  and  14  may be loaded in the same end of the launch tube  110 , if desired. It will also be appreciated that there may be a set order for the loading of the modules  12  and  14 , or alternatively that the modules may be loaded in either order. 
     In step  120 , the modules  12  and  14  are coupled together within the launch tube  110 . Modules  12  and  14  are coupled as described above, through use of the coupling  16 , to thereby form the missile assembly  10 . After coupling, the missile  10  may be fired from the launcher  114  in a convention manner. After firing, the coupled canister of the modules  12  and  14  (the forward canister  18  and the aft canister  22 ) may be removed from the launch tube  110  as a single piece. 
     It will be appreciated that it may be possible to assemble the modules  12  and  14  of the missile assembly  10  wholly or partially outside of the launch tube  110 . However, such outside assembly may result in handling difficulties due to a need to handle the fully-assembly missile assembly  10 . 
     What follows now are several additional embodiments of the invention. The details of certain common similar features of the additional embodiments and the embodiment or embodiments described above are omitted in the description of the additional embodiments for the sake of brevity. It will be appreciated that features of the various additional embodiments may be combined with one another and may be combined with features of the embodiment or embodiments described above. 
     FIG. 7 shows a modular missile assembly  210  which includes a missile  226  which separates into two parts during flight. The missile assembly  210  includes a forward payload-carrying module  212 , which is coupled to an aft booster module  214  via a coupling  216 . The forward module  212  includes a payload section  220 , which is coupled to a missile propulsion section  224  of the aft module  214 . During flight, the missile  226  separates along a separation line  270 . The part of the missile  226  which is forward of the separation line  270  continues along toward the intended target. The part of the missile  226  which is behind the separation line  270  is jettisoned. Jettisoning the rear part of the missile  226  reduces deceleration on the remaining part of the missile, which would otherwise occur due to aerodynamic drag forces on the rear section. Thus, range and/or accuracy of the missile may be improved. 
     Separation along the separation line  270  may be accomplished by any of a variety of suitable mechanisms. For example, separation may be triggered by a system that senses mechanically the difference in forces between the forward and aft portions of the missile after the rocket motor has burned out. Alternatively, an accelerometer may be used as a trigger to decouple the parts of the missile. As another example, the decoupling of the parts may be set to occur after a certain given time from launch. The decoupling along the separation line  270  may be a purely passive event, or may alternatively involve use of active components such as electromechanical, pyrotechnic, or other small devices to aid in the separation. 
     It will be appreciated that the separation line  270  may be located on the missile  226  other than at the location shown in FIG.  7 . The separation line  270  may be located on the payload section  220 , at the coupling between the payload section  220  and the propulsion section  224 , or somewhere along the propulsion section  224 . It will be appreciated that the separation mechanism may be incorporated as part of the coupling  216  between the modules  212  and  214 . 
     Turning now to FIG. 8, an alternate embodiment missile payload section  420  includes an articulated nose portion  421 . The articulated nose portion advantageously provides steering with minimal effect on external projectile packaging, minimum drag characteristics, and smooth, continuous steering. It is well known that a simple steering mechanism can be achieved by always pointing the nose toward the target, therefore allowing resultant aerodynamic forces to fly the payload section  420  toward the target. 
     It will be appreciated that a variety of actuation implementation systems may be employed to articulate the nose. U.S. Pat. No. 4,399,962, the detailed description and figures of which are incorporated herein by reference, is an example of employment of pyrotechnic devices to articulate a nose section. U.S. Pat. No. 4,793,571, the detailed description and figures of which are incorporated by reference, discloses use of piezolectric devices to articulate a nose. U.S. Pat. No. 4,998,994, the detailed description and figures of which are incorporated by reference, discloses a self-aligning projectile nose. Also, a variety of suitable mechanical means for articulating the nose may be employed. Examples of mechanical articulation of nose sections may be found in U.S. Pat. Nos. 4,579,298 and 4,925,130, detailed descriptions and figures of which are incorporated by reference, and in pending, commonly-owned U.S. Pat. No. 6,364,248, titled “Articulated Nose Missile Control Actuation System,” filed Jul. 6, 2000, which is incorporated herein by reference in its entirety. 
     FIG. 9 shows an alternate embodiment missile propulsion section  424  which includes nozzles  425  along the perimeter of the propulsion section. The nozzles  425  may be used to impart a spin or torque to the missile during or shortly after launch. It is well known that imparting a spin to a missile may improve its accuracy. Further details regarding use of circumferentially-placed nozzles to impart a spin to a missile may be found in pending, commonly owned U.S. Pat. No. 6,478,250, entitled “Propulsive Torque Motor,” filed Sep. 11, 2000, which is herein incorporated by reference in its entirety. 
     As mentioned earlier, It will be appreciated that other well-known methods are available for imparting a spin or a torque to a missile. Examples of such other methods may be found in U.S. Pat. Nos. 4,497,460 and 5,078,336, the descriptions and figures of which are herein incorporated by reference. 
     FIG. 10 shows an alternate embodiment missile payload section  620  which incorporates a propulsive torque motor. In an exemplary embodiment, the payload section  620  includes a pressurized gas source. Pressurized gas may be ejected through nozzles  623  at a front end  625  of the payload section. The nozzles  623  the pressurized gas in a direction having a tangential component relative to the missile payload section, thereby imparting a spin to the missile. Further details of an example of such a torque motor may be found in the above-referenced U.S. Pat. No. 6,478,250, entitled “Propulsive Torque Motor.” 
     Although the invention has been shown and described with respect to a certain preferred embodiment or embodiments, it is obvious that equivalent alterations and modifications will occur to others skilled in the art upon the reading and understanding of this specification and the annexed drawings. In particular regard to the various functions performed by the above described elements (components, assemblies, devices, compositions, etc.), the terms (including a reference to a “means”) used to describe such elements are intended to correspond, unless otherwise indicated, to any element which performs the specified function of the described element (i.e., that is functionally equivalent), even though not structurally equivalent to the disclosed structure which performs the function in the herein illustrated exemplary embodiment or embodiments of the invention. In addition, while a particular feature of the invention may have been described above with respect to only one or more of several illustrated embodiments, such feature may be combined with one or more other features of the other embodiments, as may be desired and advantageous for any given or particular application.