US20120055321A1 - Systems and Methods for Launching Munitions - Google Patents
Systems and Methods for Launching Munitions Download PDFInfo
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- US20120055321A1 US20120055321A1 US12/875,758 US87575810A US2012055321A1 US 20120055321 A1 US20120055321 A1 US 20120055321A1 US 87575810 A US87575810 A US 87575810A US 2012055321 A1 US2012055321 A1 US 2012055321A1
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- Prior art keywords
- munitions
- launcher
- lid
- housing
- vehicle
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/077—Doors or covers for launching tubes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/06—Rocket or torpedo launchers for rockets from aircraft
- F41F3/065—Rocket pods, i.e. detachable containers for launching a plurality of rockets
Definitions
- the present disclosure relates to munitions, and in particular, systems and methods for launching munitions.
- 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, unmanned air vehicles (UAVs)), land vehicles (e.g., tanks, BMPs), and/or watercraft (e.g., aircraft carrier, submarines, other surface craft and/or undersea 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 rail or tube structure 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.
- 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 rail structure, electromechanical apparatus for fixing the munitions to the launcher, and/or the release mechanism.
- 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.
- 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.
- the system may include a cover for use with a munitions launcher including a housing with a face.
- the cover may include a lid, a defined passage through the lid, and an actuator.
- the lid may be configured to mount to the face of the munitions launcher.
- the defined passage through the lid may be sized to allow a munition to pass through the lid when launched by the launcher and to substantially cover any other munitions disposed at least partially within the munitions launcher.
- the actuator may be configured to operate the lid in a manner that moves the defined passage in relation to the face of the munitions launcher. Movement of the defined passage in relation to the face of the munitions launcher may uncover at least one munition that was substantially covered prior to the movement of the defined passage and substantially cover any other munitions disposed at least partially within the munitions launcher.
- a launcher configured to retain a munition during transport by a vehicle.
- the launcher may comprise a housing, at least two tubes, circuitry, a lid with a defined passage, and an actuator.
- the housing may have a face through which munitions pass when launched.
- the at least two tubes may be disposed at least partially within the housing and configured to hold munitions for transportation.
- the circuitry may provide electrical communication with munitions present within the at least two tubes.
- the lid may be configured to mount to the face of the munitions launcher.
- the defined passage through the lid may be sized to allow a munition launched from a first tube to pass through the lid when launched by the launcher and to substantially cover any other munitions disposed in a second tube.
- the actuator may be configured to operate the lid in a manner that moves the defined passage in relation to the face of the munitions launcher. Movement of the defined passage in relation to the face of the munitions launcher may uncover a munition held in the second tube and substantially cover the first tube.
- a method for launching a munition from a launcher coupled to a vehicle may include a housing, couplings, tubes, a lid, a defined passage through the lid, and an actuator.
- the housing may have a face through which munitions pass when launched.
- the housing may be coupled to a vehicle and configured to retain at least two munitions during transport by the vehicle.
- 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 at least two munitions.
- the tubes may be disposed at least partially within the housing and configured to hold the at least two munitions for transportation.
- the lid may be configured to mount to the face of the housing.
- the defined passage through the lid may be sized to allow a munition launched from a first tube to pass through the lid when launched by the launcher and to substantially cover any other munitions disposed in a second tube.
- the actuator may be configured to operate the lid in a manner that moves the defined passage in relation to the face of the housing. Movement of the defined passage in relation to the face of the munitions launcher may uncovers a munition held in the second tube and substantially cover the first tube.
- 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).
- the teachings of the present disclosure may protect sensors associated with a guidance and control unit housed in the nose of a munition.
- 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.
- various embodiments may include all, some or none of the enumerated advantages.
- 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 launching in accordance with the teachings of the present disclosure
- FIG. 4 illustrates an example launcher incorporating the teachings of the present disclosure
- FIGS. 5A and 5B show the launcher of FIG. 4 during successive launches of munitions, in accordance with the teachings of the present disclosure.
- FIGS. 1 through 5B wherein like numbers are used to indicate like and corresponding parts.
- FIG. 1A illustrates an example vehicle 1 that includes an example launcher 2 , 110 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.
- 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.
- 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.).
- a user e.g., a pilot of vehicle 1 or mission control remotely located from vehicle 1 and in communication with vehicle 1
- 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.
- 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 .
- 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 .
- 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 .
- 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 .
- couplings 12 may include small computer system interface (SCSI), male or female electrical connectors, and/or other adaptors and/or interfaces.
- SCSI small computer system interface
- Tubes 14 may include any component, device, and/or feature of launcher 2 and/or housing 10 configured for use with munitions 20 .
- 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 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.
- 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&C) unit of munition 20 .
- G&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.
- GPS global positioning system
- IMUs inertial measurement units
- One or more of the components of the G&C unit of munition 20 may be used to precisely guide munition 20 during launch and/or after launch.
- the G&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.
- 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 .
- 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&C unit, nose 22 , and/or propulsion unit 28 .
- munition 20 may have a roughly cylindrical shape.
- body 26 may include a metal cylinder housing propellant for use by propulsion unit 28 , electrical conductors for communication between a G&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.
- 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.
- 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.
- launcher 2 may launch munition 20 .
- 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 .
- various components of a G&C unit in nose 22 a may gather information and/or data through leading surface 24 a of nose 22 a .
- 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.
- 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 40 with a rotating munitions cover 50 incorporating the teachings of the present disclosure.
- Launcher 40 may include housing 42 and cover 50 .
- Housing 42 may include any components, devices, and/or features as described in relation to housing 10 , including couplings 44 , and tubes 46 .
- tubes 46 in launcher 40 may be arrayed around a centerline 48 at a matching radius, R.
- tubes 46 may include any components, devices, and/or features as described in relation to tubes 14 .
- launcher 40 may include twelve tubes 46 arrayed near the perimeter of a face 43 of a generally cylindrical housing 42 . Such an array of tubes 46 may allow the use of rotating cover 50 as shown in FIG. 4 .
- FIGS. 5A and 5B show launcher 40 during successive launches of munitions 20 , in accordance with the teachings of the present disclosure.
- Cover 50 may include any device, component, and/or feature of launcher 40 configured to define a passage for a munition 20 as it is launched and, at the same time, protect one or more other munitions 20 mounted in launcher 40 .
- cover 50 may include a flat panel generally matching the shape of face 43 of housing 42 .
- Cover 50 may include a hole 52 generally configured to match the shape of tube 46 .
- hole 52 may be a circular opening in cover 50 with a diameter similar to the diameter of a cylindrical tube 46 .
- substantially round tubes 46 and hole 52 may be depicted, any shape or configuration may be used as may be appropriate depending on the form and function of munition 20 .
- Hole 52 may also be configured to allow a G&C unit housed in nose 22 of munition 20 to view, seek, and/or detect a target prior to its launch from launcher 40 .
- Cover 50 may be mounted to housing 42 by any device, component, and/or feature of launcher 40 configured to move cover 50 as necessary to define a passage for the various tubes 46 of launcher 40 .
- cover 50 may rotate around centerline 48 to move hole 52 to reveal various tubes 46 and, thereby, define successive passages for various munitions 20 .
- Cover 50 may provide protection to munitions 20 , and specifically leading surface 24 of nose 22 of munition 20 .
- the use of cover 50 during the launch of munition 20 a may no longer subject the leading surface 24 b to the exhaust plume 32 a of munition 20 a.
- cover 50 may be mounted to launcher 40 by means of an actuator 54 mounted along centerline 48 of housing 42 .
- Actuator 54 may include a rotating motor mounted between the array of tubes 46 in launcher 40 .
- cover 50 may be mounted to the rotor of an electric motor 54 controlled by the operation of electronic logic and/or circuitry associated with the firing mechanism of launcher 40 and/or munitions 20 .
- cover 50 may be mounted to housing 40 around the perimeter of face 43 using an appropriate bearing rather than at centerline 48 .
- cover 50 may be configured to cover a single tube 46 and be individually operated (e.g., one cover per tube).
Abstract
Systems and methods for launching munitions are provided. In some embodiments, the system may include a cover for use with a munitions launcher including a housing with a face. The cover may include a lid, a defined passage through the lid, and an actuator. The lid may be configured to mount to the face of the munitions launcher. The defined passage through the lid may be sized to allow a munition to pass through the lid when launched by the launcher and to substantially cover any other munitions disposed at least partially within the munitions launcher. The actuator may be configured to operate the lid in a manner that moves the defined passage in relation to the face of the munitions launcher. Movement of the defined passage in relation to the face of the munitions launcher may uncover at least one munition that was substantially covered prior to the movement of the defined passage and substantially cover any other munitions disposed at least partially within the munitions launcher.
Description
- The present disclosure relates to munitions, and in particular, systems and methods for launching munitions.
- 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, unmanned air vehicles (UAVs)), land vehicles (e.g., tanks, BMPs), and/or watercraft (e.g., aircraft carrier, submarines, other surface craft and/or undersea 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 rail or tube structure 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 rail 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.
- 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 some embodiments, the system may include a cover for use with a munitions launcher including a housing with a face. The cover may include a lid, a defined passage through the lid, and an actuator. The lid may be configured to mount to the face of the munitions launcher. The defined passage through the lid may be sized to allow a munition to pass through the lid when launched by the launcher and to substantially cover any other munitions disposed at least partially within the munitions launcher. The actuator may be configured to operate the lid in a manner that moves the defined passage in relation to the face of the munitions launcher. Movement of the defined passage in relation to the face of the munitions launcher may uncover at least one munition that was substantially covered prior to the movement of the defined passage and substantially cover any other munitions disposed at least partially within the munitions launcher.
- In other embodiments, a launcher configured to retain a munition during transport by a vehicle is provided. The launcher may comprise a housing, at least two tubes, circuitry, a lid with a defined passage, and an actuator. The housing may have a face through which munitions pass when launched. The at least two tubes may be disposed at least partially within the housing and configured to hold munitions for transportation. The circuitry may provide electrical communication with munitions present within the at least two tubes. The lid may be configured to mount to the face of the munitions launcher. The defined passage through the lid may be sized to allow a munition launched from a first tube to pass through the lid when launched by the launcher and to substantially cover any other munitions disposed in a second tube. The actuator may be configured to operate the lid in a manner that moves the defined passage in relation to the face of the munitions launcher. Movement of the defined passage in relation to the face of the munitions launcher may uncover a munition held in the second tube and substantially cover the first tube.
- In some embodiments, a method for launching a munition from a launcher coupled to a vehicle is provided. The system may include a housing, couplings, tubes, a lid, a defined passage through the lid, and an actuator. The housing may have a face through which munitions pass when launched. The housing may be coupled to a vehicle and configured to retain at least two munitions during transport by the vehicle. 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 at least two munitions. The tubes may be disposed at least partially within the housing and configured to hold the at least two munitions for transportation. The lid may be configured to mount to the face of the housing. The defined passage through the lid may be sized to allow a munition launched from a first tube to pass through the lid when launched by the launcher and to substantially cover any other munitions disposed in a second tube. The actuator may be configured to operate the lid in a manner that moves the defined passage in relation to the face of the housing. Movement of the defined passage in relation to the face of the munitions launcher may uncovers a munition held in the second tube and substantially cover the first tube.
- 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.
- 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 ofFIG. 1A , in accordance with the teachings of the present disclosure; -
FIG. 2 illustrates an example munition that may be launching in accordance with the teachings of the present disclosure; -
FIG. 3 shows the launcher ofFIG. 1A during a 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 -
FIGS. 5A and 5B show the launcher ofFIG. 4 during successive launches of munitions, in accordance with the teachings of the present disclosure. - Preferred embodiments and their advantages are best understood by reference to
FIGS. 1 through 5B , wherein like numbers are used to indicate like and corresponding parts. -
FIG. 1A illustrates an example vehicle 1 that includes anexample launcher 2, 110 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. WhileFIG. 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 (seeFIG. 2 ) during transport. In some embodiments,launcher 2 may include electrical contacts throughcouplings 12 providing electrical communication between each ofmunitions 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 launchmunitions 20 by communicating withmunitions 20 via the electrical communication provided bylauncher 2. The communication may include signals defining the coordinate information of a specific target and/or other information that allowsmunitions 20 to accurately strike the target, reducing or substantially eliminating incidental or collateral damage. -
FIG. 1B illustrateslauncher 2 ofFIG. 1A in more detail. In some embodiments,launcher 2 may includehousing 10,couplings 12, andtubes 14.Launcher 2 may be configured to securemunitions 20 during transportation (e.g., during flight and/or ground travel) and provide continuous electrical communication tomunitions 20 until time of launch, in accordance with certain embodiments of the present disclosure.Launcher 2 may be configured to housemunitions 20 intubes 14.Launcher 2 may also includeoptional housing 10 configured to enclose various electrical components that couple withmunitions 20 as well asmunitions 20. It is noted thatlauncher 2 shown inFIG. 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 oflauncher 2 configured to enclose various components oflauncher 2 and couple to vehicle 1.Housing 10 may be integrally formed as a part oflauncher 2 or may be secured tolauncher 2. In some embodiments,housing 10 may enclose one or more electrical components disposed therein and may route the appropriate electrical components to eachmunition 20 inhousing 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) andmunition 20. In some embodiments, electrical components ofhousing 10 may transmit signals sent from a user to one ormore 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 oflauncher 2 and/orhousing 10 configured to attachlauncher 2 to vehicle 1.Couplings 12 may include electrical connections between vehicle 1 andlauncher 2 and/ormunitions 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 andmunition 20.Couplings 12 may include electrical adaptor or interface configured to connect electrical components of vehicle 1 tolauncher 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 oflauncher 2 and/orhousing 10 configured for use withmunitions 20. For example,tubes 14 may provide a housing forindividual munitions 20, including protection from physical impact, contact, and/or contamination during storage, transport, and/or launching of neighboringmunitions 20.Tubes 14 may be arranged withinlauncher 2 and/orhousing 10 in various stacking patterns. As shown inFIGS. 1A and 1B , in the example embodiment,housing 10 provides 19tubes 14 formunitions 20. -
FIG. 2 illustrates anexample 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 anose 22, abody 26, and apropulsion unit 28. Although one particular embodiment is shown inFIG. 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. - 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&C) unit ofmunition 20. For example, G&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&C unit ofmunition 20 may be used to precisely guidemunition 20 during launch and/or after launch. In other embodiments, the G&C unit may be used to track, view, and/or identify potential targets formunition 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 leadingsurface 24. Leadingsurface 24 may include different materials than the rest ofnose 22, those materials selected to be transparent to one or more sensors innose 22. For example, leadingsurface 24 may be transparent to infrared sensors, thermal sensors, visible light, etc. -
Body 26 may include any component, device, and/or feature ofmunition 20 configured to provide structure and/or housing for the various components, including a G&C unit,nose 22, and/orpropulsion 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 bypropulsion unit 28, electrical conductors for communication between a G&C unit and various components oflauncher 2 and/or vehicle 1. -
Propulsion unit 28 may include any component, device, and/or feature ofmunition 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 exitpropulsion unit 28 at great velocity. The exit of propellant frompropulsion unit 28 throughexhaust 30 may create anexhaust plume 32.Exhaust plume 32 may include flame, combustion products, noise, unburned propellant, etc. - Referring to
FIG. 3 , a view oflauncher 2 andmunitions housing 10 removed, in accordance with certain embodiments of the present disclosure.Munition 20 a, secured inlauncher 2, and specifically intube 14 oflauncher 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 andmunition 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 launchmunition 20. As shown inFIG. 3 ,munition 20 a may exittube 14 oflauncher 2. Launchingmunition 20 a may include igniting propellant inpropulsion unit 28 a and generatingexhaust plume 32 a. During the launch ofmunition 20 a, various components of a G&C unit innose 22 a may gather information and/or data through leadingsurface 24 a ofnose 22 a. As leadingsurface 24 a ofnose 22 a always remains ahead ofexhaust plume 32 a, the materials and/or energy ofexhaust plume 32 a is unlikely to impinge on leadingsurface 24 a ofnose 22 a ofmunition 20 a. - In contrast, however, the leading
surface 24 b ofmunition 20 b may be exposed toexhaust plume 32 a asmunition 20 a exits housing 10 oflauncher 2.Exhaust plume 32 a may deposit dirt, film, unspent propellant, combustion products, and/or heat on leadingsurface 24 b ofnose 22 b ofmunition 20 b, as well as anyother munitions 20. The contents and/or force of thepropellant exiting exhaust 30 a may detrimentally impact the performance and/or operation ofmunition 20 b and/or other remainingmunitions 20. -
FIG. 4 illustrates anexample launcher 40 with a rotating munitions cover 50 incorporating the teachings of the present disclosure.Launcher 40 may includehousing 42 andcover 50.Housing 42 may include any components, devices, and/or features as described in relation tohousing 10, includingcouplings 44, andtubes 46. As shown inFIG. 4 , however,tubes 46 inlauncher 40 may be arrayed around acenterline 48 at a matching radius, R. Inother respects tubes 46 may include any components, devices, and/or features as described in relation totubes 14. In the embodiment shown,launcher 40 may include twelvetubes 46 arrayed near the perimeter of aface 43 of a generallycylindrical housing 42. Such an array oftubes 46 may allow the use ofrotating cover 50 as shown inFIG. 4 .FIGS. 5A and 5B showlauncher 40 during successive launches ofmunitions 20, in accordance with the teachings of the present disclosure. -
Cover 50 may include any device, component, and/or feature oflauncher 40 configured to define a passage for amunition 20 as it is launched and, at the same time, protect one or moreother munitions 20 mounted inlauncher 40. For example, cover 50 may include a flat panel generally matching the shape offace 43 ofhousing 42.Cover 50 may include ahole 52 generally configured to match the shape oftube 46. For example,hole 52 may be a circular opening incover 50 with a diameter similar to the diameter of acylindrical tube 46. Although substantiallyround tubes 46 andhole 52 may be depicted, any shape or configuration may be used as may be appropriate depending on the form and function ofmunition 20.Hole 52 may also be configured to allow a G&C unit housed innose 22 ofmunition 20 to view, seek, and/or detect a target prior to its launch fromlauncher 40. -
Cover 50 may be mounted tohousing 42 by any device, component, and/or feature oflauncher 40 configured to movecover 50 as necessary to define a passage for thevarious tubes 46 oflauncher 40. For example, as shown inFIGS. 5A and 5B , cover 50 may rotate aroundcenterline 48 to movehole 52 to revealvarious tubes 46 and, thereby, define successive passages forvarious munitions 20.Cover 50 may provide protection tomunitions 20, and specifically leadingsurface 24 ofnose 22 ofmunition 20. As shown inFIGS. 5A and 5B , the use ofcover 50 during the launch ofmunition 20 a may no longer subject the leadingsurface 24 b to theexhaust plume 32 a ofmunition 20 a. - In one example embodiment, cover 50 may be mounted to
launcher 40 by means of anactuator 54 mounted alongcenterline 48 ofhousing 42.Actuator 54 may include a rotating motor mounted between the array oftubes 46 inlauncher 40. In some embodiments, cover 50 may be mounted to the rotor of anelectric motor 54 controlled by the operation of electronic logic and/or circuitry associated with the firing mechanism oflauncher 40 and/ormunitions 20. In some embodiments, cover 50 may be mounted tohousing 40 around the perimeter offace 43 using an appropriate bearing rather than atcenterline 48. In some embodiments, cover 50 may be configured to cover asingle tube 46 and be individually operated (e.g., one cover per tube). - 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.
Claims (16)
1. A cover for use with a munitions launcher including a housing with a face, the cover comprising:
a lid configured to mount to the face of the munitions launcher;
a defined passage through the lid, the passage sized to allow a munition to pass through the lid when launched by the launcher and to substantially cover any other munitions disposed at least partially within the munitions launcher; and
a actuator configured to operate the lid in a manner that moves the defined passage in relation to the face of the munitions launcher;
wherein movement of the defined passage in relation to the face of the munitions launcher uncovers at least one munition that was substantially covered prior to the movement of the defined passage and substantially covers any other munitions disposed at least partially within the munitions launcher.
2. A cover according to claim 1 , wherein the lid includes a plate having a substantially equivalent shape of the face of the housing of the munitions launcher.
3. A cover according to claim 1 , wherein the defined passage includes a hole passing through the lid, the hole having a diameter substantially equivalent to a diameter of a tube in the housing of the munitions launcher.
4. A cover according to claim 1 , further comprising the lid mounted to a rotor of a motor.
5. A cover according to claim 1 , further comprising the lid mounted to a perimeter of the face of the housing of the munitions launcher.
6. A launcher for launching munitions, the launcher comprising:
a housing having a face through which munitions pass when launched;
at least two tubes disposed at least partially within the housing, the at least two tubes configured to hold munitions for transportation;
circuitry providing electrical communication with munitions present within the at least two tubes;
a lid configured to mount to the face of the munitions launcher;
a defined passage through the lid, the passage sized to allow a munition launched from a first tube to pass through the lid when launched by the launcher and to substantially cover any other munitions disposed in a second tube; and
an actuator configured to operate the lid in a manner that moves the defined passage in relation to the face of the munitions launcher;
wherein movement of the defined passage in relation to the face of the munitions launcher uncovers a munition held in the second tube and substantially covers the first tube.
7. A launcher according to claim 6 , further comprising the launcher configured to mount to a vehicle.
8. A launcher according to claim 6 , further comprising the launcher configured to mount to a vehicle and wherein the vehicle comprises an aircraft vehicle, a land vehicle, or a watercraft vehicle.
9. A launcher according to claim 6 , wherein the munition is a precision-guided munition (PGM), a smart bomb, a smart weapon, a guided bomb unit (GBU), a guided missile or a smart rocket.
10. A launcher according to claim 6 , wherein the lid includes a plate having a shape substantially equivalent to a shape of the face of the housing of the munitions launcher.
11. A launcher according to claim 6 , wherein the defined passage includes a hole passing through the lid, the hole having a diameter substantially equivalent to a diameter of the at least two tubes.
12. A launcher according to claim 6 , further comprising the lid mounted to a rotor of a motor.
13. A launcher according to claim 6 , further comprising the lid mounted to a perimeter of the face of the housing of the munitions launcher.
14. A system for launching munitions from a vehicle, the system comprising:
a housing having a face through which munitions pass when launched;
the housing coupled to a vehicle and configured to retain at least two munitions during transport by the vehicle;
couplings providing mechanical connection between the vehicle and the housing and electrical connectivity between the vehicle and the housing;
the couplings configured to route electrical signals from the vehicle to the at least two munitions;
tubes disposed at least partially within the housing, the tubes configured to hold the at least two munitions for transportation;
a lid configured to mount to the face of the housing;
a defined passage through the lid, the passage sized to allow a munition launched from a first tube to pass through the lid when launched by the launcher and to substantially cover any other munitions disposed in a second tube; and
an actuator configured to operate the lid in a manner that moves the defined passage in relation to the face of the housing;
wherein movement of the defined passage in relation to the face of the munitions launcher uncovers a munition held in the second tube and substantially covers the first tube.
15. A system according to claim 14 , wherein the vehicle comprises an aircraft vehicle, a land vehicle, or a watercraft vehicle.
16. A system according to claim 14 , wherein the munition is a precision-guided munition (PGM), a smart bomb, a smart weapon, a guided bomb unit (GBU), a guided missile or a smart rocket.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
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US12/875,758 US20120055321A1 (en) | 2010-09-03 | 2010-09-03 | Systems and Methods for Launching Munitions |
PCT/US2011/049272 WO2012030637A1 (en) | 2010-09-03 | 2011-08-26 | Munitions launcher |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/875,758 US20120055321A1 (en) | 2010-09-03 | 2010-09-03 | Systems and Methods for Launching Munitions |
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US20120055321A1 true US20120055321A1 (en) | 2012-03-08 |
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US12/875,758 Abandoned US20120055321A1 (en) | 2010-09-03 | 2010-09-03 | Systems and Methods for Launching Munitions |
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US (1) | US20120055321A1 (en) |
WO (1) | WO2012030637A1 (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
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US20140222249A1 (en) * | 2011-06-24 | 2014-08-07 | Bae Systems Plc | Apparatus for use on unmanned vehicles |
US10240896B2 (en) | 2015-03-12 | 2019-03-26 | Raytheon Company | Tube to bulkhead bonded joint design |
US20190346241A1 (en) * | 2016-12-02 | 2019-11-14 | Rheinmetall Air Defence Ag | Launching arrangement for a missile for intercepting alien drones |
US10578398B1 (en) * | 2018-10-22 | 2020-03-03 | Michael S. Bradbury | Drone deployment apparatus for accommodating aircraft fuselages |
CN111442694A (en) * | 2020-04-22 | 2020-07-24 | 上海机电工程研究所 | Multi-connected barrel missile cover opening device, missile and method for launching by using device |
IT201900025273A1 (en) * | 2019-12-23 | 2021-06-23 | Aerea Spa | ROTATING PROTECTION COVER |
RU218147U1 (en) * | 2022-12-01 | 2023-05-12 | Федеральное государственное казенное военное образовательное учреждение высшего образования "ВОЕННАЯ АКАДЕМИЯ МАТЕРИАЛЬНО-ТЕХНИЧЕСКОГО ОБЕСПЕЧЕНИЯ имени генерала армии А.В. Хрулева" | Bicaliber honeycomb block for guided missiles |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
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IT202100029102A1 (en) | 2021-11-17 | 2023-05-17 | Aerea Spa | BOW SECTION WITH ROTATING FLANGE FOR ROCKET LAUNCHES |
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US3988961A (en) * | 1975-08-08 | 1976-11-02 | The United States Of America As Represented By The Secretary Of The Army | Integrated rocket shipping container and launcher |
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US4455917A (en) * | 1982-03-15 | 1984-06-26 | General Dynamics, Pomona Division | Shock wave end cap removal device |
DE3523443C1 (en) * | 1985-06-29 | 1987-02-05 | Messerschmitt Boelkow Blohm | Cover for ammunition and firing containers for aircraft |
FR2866105B1 (en) * | 2004-02-10 | 2008-08-29 | Alkan Sa | SECURE DEVICE FOR EMPLOYING AND FITTING CARTRIDGES SUCH AS SANDING CARTRIDGES |
CA2745395A1 (en) * | 2008-12-02 | 2010-06-10 | American Dynamics Flight Systems, Inc. | Aerodynamic rotating launcher |
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2010
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US3988961A (en) * | 1975-08-08 | 1976-11-02 | The United States Of America As Represented By The Secretary Of The Army | Integrated rocket shipping container and launcher |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20140222249A1 (en) * | 2011-06-24 | 2014-08-07 | Bae Systems Plc | Apparatus for use on unmanned vehicles |
US9156552B2 (en) * | 2011-06-24 | 2015-10-13 | Bae Systems Plc | Apparatus for use on unmanned vehicles |
US10240896B2 (en) | 2015-03-12 | 2019-03-26 | Raytheon Company | Tube to bulkhead bonded joint design |
US20190346241A1 (en) * | 2016-12-02 | 2019-11-14 | Rheinmetall Air Defence Ag | Launching arrangement for a missile for intercepting alien drones |
US10578398B1 (en) * | 2018-10-22 | 2020-03-03 | Michael S. Bradbury | Drone deployment apparatus for accommodating aircraft fuselages |
IT201900025273A1 (en) * | 2019-12-23 | 2021-06-23 | Aerea Spa | ROTATING PROTECTION COVER |
CN111442694A (en) * | 2020-04-22 | 2020-07-24 | 上海机电工程研究所 | Multi-connected barrel missile cover opening device, missile and method for launching by using device |
RU218147U1 (en) * | 2022-12-01 | 2023-05-12 | Федеральное государственное казенное военное образовательное учреждение высшего образования "ВОЕННАЯ АКАДЕМИЯ МАТЕРИАЛЬНО-ТЕХНИЧЕСКОГО ОБЕСПЕЧЕНИЯ имени генерала армии А.В. Хрулева" | Bicaliber honeycomb block for guided missiles |
Also Published As
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WO2012030637A1 (en) | 2012-03-08 |
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