Patent Abstract:
Systems and methods for launching munitions are provided. In some embodiments, a launcher configured to retain a munition during transport by a vehicle may comprise a first housing, circuitry, and a second housing. The first housing may define a tube configured to hold a munition for transportation. The circuitry may provide electrical communication with a munition present within the tube. The second housing may define a tube corresponding to the tube defined by the first housing. The second housing may be configured to mount to the first housing so that the tubes defined by the first housing and the second housing combine to house and launch a munition.

Full Description:
TECHNICAL FIELD 
     The present disclosure relates to munitions, and in particular, systems and methods for launching munitions. 
     BACKGROUND 
     Munitions such as air to ground missiles (AGM), air to air missiles (AMM), and rockets can be carried and launched from various vehicle types including aircraft vehicles (e.g., fighter jets, helicopters), land vehicles (e.g., tanks, BMPs), and/or watercraft (e.g., aircraft carrier, submarines, other surface craft). Launchers, fixed to the vehicle, may be used to secure the munitions during transportation as well as used to deploy the munitions. Conventional munition launchers include a tube for holding the munitions and electromechanical apparatus for fixing the munitions to the launcher. A release mechanism arms the munitions and releases it for launching. For example, the launcher may include power supply equipment that controls the fusing and firing of the munitions. 
     The next generation of munitions may include further developments in target viewing, seeking, and/or detection (e.g., smart rockets). Individual munitions with target viewing, seeking, and/or detection features may require improvements in launcher technology, including changes in the tube structure, electromechanical apparatus for fixing the munitions to the launcher, and/or the release mechanism. In other applications, munitions and their respective launchers may be used without an associated vehicle, instead being adapted for transportation by an individual and/or alternative forms of transportation. 
     SUMMARY 
     The present disclosure provides techniques for launching munitions that substantially eliminates or reduces at least some of the disadvantages and problems associated with previous methods and systems. 
     In one embodiment, a launcher configured to retain a munition during transport by a vehicle is provided. The launcher may comprise a first housing, circuitry, and a second housing. The first housing may define a tube configured to hold a munition for transportation. The circuitry may provide electrical communication with a munition present within the tube. The second housing may define a tube corresponding to the tube defined by the first housing. The second housing may be configured to mount to the first housing so that the tubes defined by the first housing and the second housing combine to house and launch a munition. 
     In other embodiments, a system for launching munitions from a vehicle is provided. The system may comprise a first housing, couplings, and a second housing. The first housing may define a tube configured to hold a munition for transportation. The munition may have a length longer than a length of the tube of the first housing. The couplings may provide mechanical connection between the vehicle and the housing and electrical connectivity between the vehicle and the housing. The couplings may be configured to route electrical signals from the vehicle to the first housing. The second housing may define a tube corresponding to the tube defined by the first housing. The second housing may be configured to mount to the first housing at a junction so that the tubes defined by the first housing and the second housing combine to house and launch a munition. The second housing may be removable from the first housing without decoupling the first housing from the vehicle so that a user may access the munition at a point on its length corresponding to the length of the first housing. 
     In some embodiments, a method for accessing a munition housed in a launcher coupled to a vehicle is provided. The method may include removing a second housing of the launcher from a first housing, exposing a portion of the munition protruding from the first housing, accessing the exposed portion of the munition, replacing the second housing of the launcher, and covering the exposed portion of the munition for transport. The second housing may be removed from the first housing without decoupling the first housing from the vehicle. 
     The systems and methods of the present disclosure may provide an improved system for launching munitions capable of target viewing, seeking, and/or detection (e.g., smart rockets). For example, in contrast to known systems, the teachings of the present disclosure may protect sensors associated with a guidance and control unit housed in the nose of a munition. In known systems, the nose of a munition may be exposed to the exhaust plume of a neighboring munition once launched. The systems and methods of the present disclosure may provide improved performance and/or reliability of munitions, including associated electronic circuitry, sensors, and/or guidance and control functions. Other technical advantages will be readily apparent to one skilled in the art from the following figures, descriptions, and claims. Moreover, while specific advantages have been enumerated above, various embodiments may include all, some or none of the enumerated advantages. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       A more complete understanding of the present embodiments and advantages thereof may be acquired by referring to the following description taken in conjunction with the accompanying drawings, in which like reference numbers indicate like features, and wherein: 
         FIG. 1A  illustrates an aircraft vehicle with an example launcher transporting munitions, in accordance the teachings of the present disclosure; 
         FIG. 1B  illustrates the launcher of  FIG. 1A , in accordance with the teachings of the present disclosure; 
         FIG. 2  illustrates an example munition that may be launched in accordance with the teachings of the present disclosure; 
         FIG. 3  shows the launcher of  FIG. 1A  during the launch of a munition, in accordance with one embodiment of the present disclosure; 
         FIG. 4  illustrates an example launcher incorporating the teachings of the present disclosure; and 
         FIG. 5  illustrates an example launcher incorporating the teachings of the present disclosure. 
     
    
    
     DETAILED DESCRIPTION 
     Preferred embodiments and their advantages are best understood by reference to  FIGS. 1 through 5 , wherein like numbers are used to indicate like and corresponding parts. 
       FIG. 1A  illustrates an example vehicle  1  that includes an example launcher  2 , in accordance with teachings of the present disclosure. Vehicle  1  may be an aircraft vehicle such as a helicopter, an unmanned aerial system (UAS), fighter jets (e.g., F-16, F/A-18, etc.) and/or other aircraft vehicles configured to transport and launch munitions. While  FIG. 1  illustrates an aircraft vehicle, other vehicles are also contemplated. For example, vehicle  1  may be a land vehicle (e.g., tankers, transporter erector launchers, and/or military vehicles), a watercraft vehicle (e.g., submarines, surface ships, etc.) or other suitable vehicle. 
     Launcher  2  coupled to vehicle  1  may be configured to house munitions  20  (see  FIG. 2 ) during transport. In some embodiments, launcher  2  may include electrical contacts through couplings  12  providing electrical communication between each of munitions  20  and a user (e.g., pilot of vehicle  1 , mission control in communication with vehicle  1 , etc.). In some embodiments, during deployment of vehicle  1 , a user (e.g., a pilot of vehicle  1  or mission control remotely located from vehicle  1  and in communication with vehicle  1 ) may launch munitions  20  by communicating with munitions  20  via the electrical communication provided by launcher  2 . The communication may include signals defining the coordinate information of a specific target and/or other information that allows munitions  20  to accurately strike the target, reducing or substantially eliminating incidental or collateral damage. 
       FIG. 1B  illustrates launcher  2  of  FIG. 1A  in more detail. In some embodiments, launcher  2  may include housing  10 , couplings  12 , and tubes  14 . Launcher  2  may be configured to secure munitions  20  during transportation (e.g., during flight and/or ground travel) and provide continuous electrical communication to munitions  20  until time of launch, in accordance with certain embodiments of the present disclosure. Launcher  2  may be configured to house munitions  20  in tubes  14 . Launcher  2  may also include optional housing  10  configured to enclose various electrical components that couple with munitions  20  as well as munitions  20 . It is noted that launcher  2  shown in  FIG. 1B  is an example. Other suitable types of apparatuses or system configured to launch a munition will be understood by persons having ordinary skill in the art. 
     Housing  10  may include any device, component, and/or features of launcher  2  configured to enclose various components of launcher  2  and couple to vehicle  1 . Housing  10  may be integrally formed as a part of launcher  2  or may be secured to launcher  2 . In some embodiments, housing  10  may enclose one or more electrical components disposed therein and may route the appropriate electrical components to each munition  20  in housing  10 . 
     Housing  10  may include one or more electrical transmission wires or cables and/or any other transmission component configured to provide a communication channel between a user (e.g., a pilot or mission control in communication with vehicle  1 ) and munition  20 . In some embodiments, electrical components of housing  10  may transmit signals sent from a user to one or more munitions  20 , where the signals provide details about a launching including, for example, GPS coordinates of a target, launch time, etc. 
     Couplings  12  may include any component, device, and/or feature of launcher  2  and/or housing  10  configured to attach launcher  2  to vehicle  1 . Couplings  12  may include electrical connections between vehicle  1  and launcher  2  and/or munitions  20 . For example, in some embodiments, couplings  12  may include both mechanical attachment points and electrical connectors. Couplings  12  may be configured to mate with matching and/or corresponding features of vehicle  1 , depending on the type of vehicle  1  in use. 
     Couplings  12  may include one or more conductors that provide electrical communication between vehicle  1  and munition  20 . Couplings  12  may include electrical adaptor or interface configured to connect electrical components of vehicle  1  to launcher  2 . In some embodiments, couplings  12  may include small computer system interface (SCSI), male or female electrical connectors, and/or other adaptors and/or interfaces. 
     Tubes  14  may include any component, device, and/or feature of launcher  2  and/or housing  10  configured for use with munitions  20 . For example, tubes  14  may provide a housing for individual munitions  20 , including protection from physical impact, contact, and/or contamination during storage, transport, and/or launching of neighboring munitions  20 . Tubes  14  may be arranged within launcher  2  and/or housing  10  in various stacking patterns. As shown in  FIGS. 1A and 1B , in the example embodiment, housing  10  provides 19 tubes  14  for munitions  20 . 
       FIG. 2  illustrates an example munition  20 , in accordance with the teachings of the present disclosure. Munition  20  may be a precision-guided munition (PGs), smart bomb, smart weapon, guided bomb unit (GBU), guided missile (e.g., laser guided missile, infrared guided missile, etc.), smart rocket, and/or other weapon that may include electronics. Munition  20 , as directed by commands sent via electrical components by the pilot or mission control in communication with vehicle  1 , may be configured to precisely hit a specific target with greater reliability and/or accuracy which may, in turn, reduce collateral damage. 
     Munition  20  may include a payload  21 , a nose  22 , a body  26 , and a propulsion unit  28 . Although one particular embodiment is shown in  FIG. 2 , persons having ordinary skill in the art will be able to apply the teachings of the present disclosure to a variety of munitions as described above. 
     Payload  21  may include any feature, device, and/or component of munition  20  configured to increase the damage to a target upon impact of munition  20 . In some embodiments, payload  21  may include an explosive material and a detonator (e.g., a warhead). For example, payload  21  may include gunpowder, high explosives, and/or other conventional explosives. In other examples, payload  21  may include chemical, biologic, and/or nuclear warheads. 
     In some embodiments of munition  20 , nose  22  may house electronic components (e.g., sensors) configured to view, search for, and/or detect targets as part of a guidance and control (G&amp;C) unit of munition  20 . For example, G&amp;C may include a signal processing unit, a global positioning system (GPS), an inertial measurement units (IMUs) configured to provide needed inertial guidance to the munitions, imaging system, and/or other components. One or more of the components of the G&amp;C unit of munition  20  may be used to precisely guide munition  20  during launch and/or after launch. In other embodiments, the G&amp;C unit may be used to track, view, and/or identify potential targets for munition  20  prior to launch. 
     Nose  22  may include one or more sensitive electronics components subject to compromised performance when dirty, obscured, and/or impacted. In some embodiments, nose  22  may include a leading surface  24 . Leading surface  24  may include different materials than the rest of nose  22 , those materials selected to be transparent to one or more sensors in nose  22 . For example, leading surface  24  may be transparent to infrared sensors, thermal sensors, visible light, etc. 
     Body  26  may include any component, device, and/or feature of munition  20  configured to provide structure and/or housing for the various components, including a G&amp;C unit, nose  22 , and/or propulsion unit  28 . In some embodiments, munition  20  may have a roughly cylindrical shape. For example, body  26  may include a metal cylinder housing propellant for use by propulsion unit  28 , electrical conductors for communication between a G&amp;C unit and various components of launcher  2  and/or vehicle  1 . 
     Propulsion unit  28  may include any component, device, and/or feature of munition  20  configured to provide thrust to munition  20  for launching. For example, propulsion unit  28  may include a jet engine, a rocket, and/or other forms of propulsion (e.g., chemical rockets, solid-propellant rockets, liquid-propellant rockets, hybrid rockets, and/or thermal rockets). Some embodiments may include a chemical rocket generating thrust by the combustion of rocket propellant. Some embodiments may generate thrust by expelling propellants that exit propulsion unit  28  at great velocity. The exit of propellant from propulsion unit  28  through exhaust  30  may create an exhaust plume  32 . Exhaust plume  32  may include flame, combustion products, noise, unburned propellant, etc. 
     Referring to  FIG. 3 , a view of launcher  2  and munitions  20   a  and  20   b  is shown, with portions of housing  10  removed, in accordance with certain embodiments of the present disclosure. Munition  20   a , secured in launcher  2 , and specifically in tube  14  of launcher  2 , may be in continuous contact with vehicle  1  and/or mission control in contact with vehicle  1 . The electrical signals communicated between vehicle  1  and munition  20   a  may include, for example, GPS coordinates of a target, launch time, and/or other mission-specific information regarding the intended target. 
     At time of launch, after appropriate signals and/or other information are sent to munition  20 , launcher  2  may launch munition  20 . As shown in  FIG. 3 , munition  20   a  may exit tube  14  of launcher  2 . Launching munition  20   a  may include igniting propellant in propulsion unit  28   a  and generating exhaust plume  32   a . During the launch of munition  20   a , various components of a G&amp;C unit in nose  22   a  may gather information and/or data through leading surface  24   a  of nose  22   a . As leading surface  24   a  of nose  22   a  always remains ahead of exhaust plume  32   a , the materials and/or energy of exhaust plume  32   a  is unlikely to impinge on leading surface  24   a  of nose  22   a  of munition  20   a.    
     In contrast, however, the leading surface  24   b  of munition  20   b  may be exposed to exhaust plume  32   a  as munition  20   a  exits housing  10  of launcher  2 . Exhaust plume  32   a  may deposit dirt, film, unspent propellant, combustion products, and/or heat on leading surface  24   b  of nose  22   b  of munition  20   b , as well as any other munitions  20 . The contents and/or force of the propellant exiting exhaust  30   a  may detrimentally impact the performance and/or operation of munition  20   b  and/or other remaining munitions  20 . 
       FIG. 4  illustrates an example launcher  2  shown with the nose  22  of a munition  20  protruding from housing  10 . In the embodiment shown, launcher  2  may include an electrical connection  34  between housing  10  and nose  22  of munition  20 . In embodiments with a unitary housing  10  and continuous launch tubes  14 , electrical connection  34  may be connected to munition  20  only at the launching face  16  of housing  10  or at the exhaust face. Electrical connection  34  may be restricted to either the nose  22  or the exhaust  30  of munition  20 . Both locations may be subject to fouling, debris, and/or impact during transportation, including but not limited to exposure to exhaust plume  32  resulting from the launch of munition  20 . In some embodiments of munition  20  (e.g., a smart rocket), additional electrical and mechanical connections between munition  20  and tube  14  and/or housing  10  may be disposed at various locations along the length of munition  20 . 
     As discussed in detail above, nose  22  may house electronic components (e.g., sensors) configured to view, search for, and/or detect targets as part of a guidance and control (G&amp;C) unit of munition  20 . For example, G&amp;C may include a signal processing unit, a global positioning system (GPS), an inertial measurement units (IMUs) configured to provide needed inertial guidance to the munitions, imaging system, and/or other components. 
     In some embodiments, the G&amp;C unit of munition  20  may receive data from a control unit, through electrical connection  34 . The data sent through electrical connection  34  may include updates to target information and/or may include control data sent by a pilot of vehicle  1 , a munitions operator, a remote firing control operator, and/or some other user. In some embodiments, particular software and/or hardware associated with a G&amp;C unit may receive software and/or firmware update related to the operation of processing units and/or other electronic components. 
       FIG. 5  illustrates an example embodiment of launcher  2  that provides access to various positions along the length of munition  20  for various interfaces (e.g., mechanical and/or electrical connections). In such embodiments, munition  20  may include multiple interfaces  23  and  25 . Interfaces  23  and  25  may include electrical connections for data transmission, mechanical detents, and/or other connections between launcher  2  and munition  20 . Launcher  2  may include a housing with various sections separable from one another. For example, in the embodiment shown in  FIG. 5 , launcher  2  includes three separate parts: a forward housing  40 , an intermediate housing  42 , and an aft housing  44 . Aft housing  44  may be attached to a vehicle  1  (not expressly shown in  FIG. 5 ) by couplings  12 . The couplings  12  may include electrical connections such as circuitry  46 , between vehicle  1  and launcher  2  and/or munitions  20 . Aft housing  44  may include continuous tubes that run the length of aft housing  44  for transportation and mounting of munitions  20 . 
     Forward housing  40  and intermediate housing  42  may be configured to attach to aft housing  44  without coupling directly to vehicle  1 . The various sections of the housing of launcher  2  may be connected by any appropriate devices, components, and/or features of launcher  2 . For example, all three sections may include a flange that can be bolted by an operator. In another example, aft section  44  and/or forward section  40  may include pegs  48  that protrude through intermediate section  42  to support intermediate section  42 . The connection may provide access to an operator and/or maintenance of the various connections  23  and  25  of munition  20 . Even after launcher  2  is fixed to vehicle  1 , an operator may remove one or more sections of the housing (e.g., forward housing  40 ) and perform maintenance, installation, inspection, and/or cleaning of the various connections  23  and  25 , and/or complete manual electrical connections between launcher  2  and munition  20 . 
     Embodiments of a launcher including a housing comprising multiple sections may provide an effectively continuous tube and access to various points along the length of munition  20  at the same time. Although the figures and embodiments disclosed herein have been described with respect to information handling systems, it should be understood that various changes, substitutions and alternations can be made herein without departing from the spirit and scope of the disclosure as illustrated by the following claims.

Technology Classification (CPC): 5