Having Tubular Guide Means Patents (Class 89/1.816)
  • Patent number: 10052544
    Abstract: A ball tossing apparatus includes a support frame and a plurality of launch devices fixed to the support frame and arranged in a two-dimensional array. The launch devices include cylinders having a spring fixed therein, with a ball carrier fixed to the spring. The balls are retained in a loaded position (springs compressed) and then upon activation of the launch devices are launched vertically into the air to the sports player. In another embodiment, the launch devices include a rotating lever which is acted on by a biasing member to launch the ball vertically from the cylinder. A method for launching the balls includes the steps of loading the balls into a two dimensional array, and then launching the balls according to a launch sequence. An electronic control system for use with the ball tossing apparatus includes a launch module for launching the loaded balls in the plurality of launch devices according to a launch sequence.
    Type: Grant
    Filed: September 9, 2014
    Date of Patent: August 21, 2018
    Assignee: Garza and Gowan Sports Equipment
    Inventors: Carl W. Gowan, Guillermo A. Garza
  • Patent number: 8979033
    Abstract: A gas gun launcher having a pump tube and a launch tube with a first end of the launch tube slidably inserted into a second end of the pump tube. A sliding seal is employed to retain the gas within the launch tube and the pump tube A launch tube alignment system is preferably automatic, again to enhance the accuracy of launches. And an embodiment of the gas gun launcher suitable for use in water such as an ocean or large lake preferably utilizes a neutrally buoyant launch tube and a neutrally buoyant pump tube. And a fast-closing muffler at the second end of the launch tube conserves the light gas utilized for launching a vehicle.
    Type: Grant
    Filed: March 26, 2012
    Date of Patent: March 17, 2015
    Assignee: QuickLaunch, Inc.
    Inventors: John William Hunter, Harry E. Cartland, Philip James Sluder, Richard Edward Twogood
  • Patent number: 8973480
    Abstract: The invention covers a missile canister (10) for accommodating a missile (20) along a longitudinal axis (L) of the canister. The canister comprises a plurality of generally planar longitudinal wall portions (14) connected together to form a tubular vessel having a polygonal cross-section. The interconnecting portions (16) between wall sections (14) are generally flexible so that when a missile (20) is launched the bending moment at the interconnecting portions (16) generated by the increase of pressure in the vessel is substantially less than the bending moment (10) generated at the wall portions (14). The interconnecting portions (16) allow relative angular deflection between adjacent wall portions (14) at respective interconnecting portions (16) when said missile (20) is launched.
    Type: Grant
    Filed: August 15, 2011
    Date of Patent: March 10, 2015
    Assignee: MBDA UK Limited
    Inventors: Bryan Bowen, Anthony Machell, Terence Edward Kavanagh, Dennis George Turner
  • Patent number: 8960067
    Abstract: Recoil forces of a launched missile and the moment force imposed on the launch platform can be reduced by use of a recoil abatement element in communication with a launch tube. The recoil abatement element includes at least one nozzle configured to receive therethrough exhaust gasses from a missile when launched. The nozzle can be canted or otherwise configured to direct the exhaust gasses in a desired direction to thereby offset moment force imposed on the platform by the exhaust gasses.
    Type: Grant
    Filed: January 11, 2013
    Date of Patent: February 24, 2015
    Assignee: Lockheed Martin Corporation
    Inventor: Wayne K. Schroeder
  • Publication number: 20140238223
    Abstract: A float support member that comprises a base for mounting to an object, primary linkages rotatably coupled by a primary pin defining a primary movable pin point that moves both in a lateral direction and a transverse direction, and secondary linkages rotatably coupled to said primary linkages, respectively, by first and second secondary pins, respectively. The first and second secondary pins define first and second secondary movable pin points, respectively, that each move both in a lateral direction and a transverse direction. The first and second secondary linkages being rotatably coupled to the base by first and second stationary pins, respectively, defining first and second stationary pin points, respectively. The position of the primary movable pin point in both the lateral and transverse directions depends on the position of both of the first and second secondary moveable pin points in both the lateral and transverse directions and vice versa.
    Type: Application
    Filed: February 27, 2013
    Publication date: August 28, 2014
    Applicant: Amphenol Corporation
    Inventor: Amphenol Corporation
  • Publication number: 20140076134
    Abstract: Recoil forces of a launched missile and the moment force imposed on the launch platform can be reduced by use of a recoil abatement element in communication with a launch tube. The recoil abatement element includes at least one nozzle configured to receive therethrough exhaust gasses from a missile when launched. The nozzle can be canted or otherwise configured to direct the exhaust gasses in a desired direction to thereby offset moment force imposed on the platform by the exhaust gasses.
    Type: Application
    Filed: January 11, 2013
    Publication date: March 20, 2014
    Applicant: LOCKHEED MARTIN CORPORATION
    Inventor: Lockheed Martin Corporation
  • Patent number: 8635937
    Abstract: Systems and methods for launching munitions are provided. In some embodiments, the system may include a launcher coupled to a vehicle and configured to retain a munition during transport by a vehicle and configured to route electrical signals from the vehicle to the munition. The system may also include a flexible, peel-away connector coupled to the launcher, the peel-away connector comprising an adhesive for coupling to at least a portion of the munition. The flexible, peel-away connector may be configured to route electrical signals from the launcher to the munition during transport and detach from the munition as the munition exits from the launcher during a launch.
    Type: Grant
    Filed: September 3, 2010
    Date of Patent: January 28, 2014
    Assignee: Raytheon Company
    Inventors: Mark A. Angeloff, Roy P. McMahon
  • Patent number: 8596181
    Abstract: A waterborne munitions system is disclosed. The system includes a submersible munitions platform and a remote control module. The munitions platform has a plurality of canistered munitions, either waterborne, airborne, or both, which can be remotely launched via the remote control module.
    Type: Grant
    Filed: December 8, 2004
    Date of Patent: December 3, 2013
    Assignee: Lockheed Martin Corporation
    Inventor: George Raymond Root, Jr.
  • Patent number: 8584569
    Abstract: A system is provided for directing a flow of gas, including a launching mechanism, a plenum, a layer of meltable material, and an open-ended uptake component. The launching mechanism is adapted to expel rocket exhaust gas. The plenum includes an upper portion having at least one fire resistant breachable plug. The upper portion is adjacent to the launching mechanism. The layer of meltable material is disposed on the upper portion. The heat generated by the gas melts the layer of meltable material. The open-ended uptake component operatively connects to the plenum. The plug moves onto a lower portion of the plenum due to force generated by the gas onto the plug, and the gas flows through the plenum and the uptake component to vent said gas in a controlled manner.
    Type: Grant
    Filed: December 6, 2011
    Date of Patent: November 19, 2013
    Assignee: The United States of America as Represented by the Secretary of the Navy
    Inventors: Michael Ryan Whitney, Paul G. Atkinson, III, Perry J. Fridley, Jr., Keith M. DeLoach, Luis C. Gominho, Michael J. Morrison, Doyle B. Green, Douglas L. Wynings
  • Patent number: 8536500
    Abstract: A system and method for rapid aiming and firing of weapons and defensive countermeasures against rocket-propelled grenades or other ballistic devices suitable for use on aircraft, ground vehicles, and ships.
    Type: Grant
    Filed: August 7, 2008
    Date of Patent: September 17, 2013
    Assignee: CPI IP, LLC
    Inventor: Richard O. Glasson
  • Patent number: 8534177
    Abstract: A system and method for providing a munitions launching system with dynamic shock isolation in which a spring plate skirt having an integral spring arrangement is provided between a munitions frame and a munitions extension, the spring plate skirt defining an opening that provides for the uninterrupted flow of expelled rocket gases, as well as underside access to the munitions frame.
    Type: Grant
    Filed: March 1, 2010
    Date of Patent: September 17, 2013
    Assignee: Lockheed Martin Corporation
    Inventors: William Kalms, Tejbir Arora, John Snediker
  • Patent number: 8505430
    Abstract: An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node.
    Type: Grant
    Filed: September 9, 2011
    Date of Patent: August 13, 2013
    Assignee: Aerovironment, Inc.
    Inventors: Carlos Thomas Miralles, Guan H. Su, Oleksandr Andryukov, John McNeil
  • Patent number: 8492692
    Abstract: A sonar buoy includes a fuselage having a tube-like shape, one or more wings coupled to the fuselage, an engine coupled to the fuselage and operable to propel the sonar buoy through flight, and a guidance computer operable to direct the sonar buoy to a predetermined location. The sonar buoy further includes a sonar detachably coupled to the fuselage and forming at least a part of the fuselage, and a rocket motor detachably coupled to the fuselage. The one or more wings are operable to be folded into a position to allow the sonar buoy to be disposed within a launch tube coupled to a vehicle and to automatically deploy to an appropriate position for flight after the sonar buoy is launched from the launch tube. The rocket motor propels the sonar buoy from the launch tube and detaches from the fuselage after launch.
    Type: Grant
    Filed: April 29, 2011
    Date of Patent: July 23, 2013
    Assignee: Elbit Systems of America, LLC
    Inventor: Jeremy F. Fisher
  • Patent number: 8468924
    Abstract: A system and method for launching non-vertical launch munitions with a non-vertical launch trajectory from a launcher that is operationally coupled to a vertical launching system (VLS). The inventors of the present invention recognized that munitions that are unsuitable for vertical launches were unavailable for use with vertical launching systems, thus foreclosing important defense, attack, and cost-savings opportunities for VLS-equipped platforms. A VLS could be substantially more versatile if it accommodated munitions such as torpedoes, counter-measures, direct-fire munitions, point-and-shoot munitions, and a variety of other missiles and equipment. The launcher according to the present invention is also stowable in an upward orientation within a cell of the host vertical launching system.
    Type: Grant
    Filed: December 16, 2010
    Date of Patent: June 25, 2013
    Assignee: Lockheed Martin Corporation
    Inventors: Daniel A. Skurdal, John Snediker, William Kalms
  • Patent number: 8434394
    Abstract: An apparatus for adapting a rocket-assisted artillery projectile of a first caliber for firing from a smooth bore tube of a second caliber may include an adapter for connecting to an aft end of the rocket-assisted artillery projectile. The adapter may include a main channel for receiving rocket exhaust, a plurality of sub-channels that lead from the main channel to an exterior of the adapter, and an ignition channel that leads from the main channel to an ignition delay disposed in the adapter. A tail boom may be fixed to an aft end of the adapter. The tail boom may include an opening in a fore end that communicates with the ignition delay in the adapter. Lifting surfaces, such as fins, may be attached to the tail boom.
    Type: Grant
    Filed: October 16, 2009
    Date of Patent: May 7, 2013
    Assignee: The United States of America as Represented by the Secretary of the Army
    Inventors: Gregory Malejko, Daniel Pascua, Peter Burke, Keith Fulton
  • Patent number: 8424439
    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.
    Type: Grant
    Filed: September 3, 2010
    Date of Patent: April 23, 2013
    Assignee: Raytheon Company
    Inventor: Robert A. Bailey
  • Patent number: 8418593
    Abstract: The invention relates to an improved deformable downstream disc (56; 156; 256) to be fitted on the bottom of a container (15) for a missile (16) and including a stack of elastic blades (63) clamped between at least an upstream and a downstream thermal protection membrane and sealing membrane (70, 71, 72, 73), and maintained between an upstream bearing frame (61) and a downstream bearing frame (64), characterised in that the downstream bearing frame includes an inner edge (80) having an extension so as to provide the disc with an abutment means defining a position of maximum deformation of the elastic blades.
    Type: Grant
    Filed: January 8, 2009
    Date of Patent: April 16, 2013
    Assignee: DCNS
    Inventor: Pierre Jacques Truyman
  • Patent number: 8415597
    Abstract: Disclosed are a wing assembly including a wing movably accommodated in a launch tube, and a buffer unit detachably mounted to the wing to come in contact with the launch tube and configured to be separated from the wing after the wing comes out of an inner space of the launch tube, and an apparatus for launching a flying object having the same.
    Type: Grant
    Filed: May 13, 2010
    Date of Patent: April 9, 2013
    Assignee: Agency for Defense Development
    Inventors: Sang Hun Shin, Heon Suk Hong, Woo Yong Lee
  • Patent number: 8327747
    Abstract: A projectile propulsion system includes a launch tube, multiphase material, and a pressure barrier member. The launch tube has an interior cavity, the multiphase material disposed therein. The launch tube also has an opening to receive the multiphase material. The pressure barrier member seals the opening while the multiphase material is disposed in the interior cavity of the launch tube so as to allow the launch tube to be pressurized. When the pressure barrier member is broken, a shock wave allows the contents of the interior cavity, such as a projectile, to be expelled from the tube with a high velocity and force.
    Type: Grant
    Filed: April 18, 2012
    Date of Patent: December 11, 2012
    Assignee: Causwave, Inc.
    Inventors: Jeffrey L. Riggs, Vladislav Oleynik, Valery Borovikov, Gennadiy Albul
  • Patent number: 8317025
    Abstract: A self-adjusting bumper comprising slidably adjustable upper and lower tapered nylon wedges for eliminating rattle space between objects and their containers. A tapered lower wedge comprises a dovetail guide rail and opposing guide pin rails; a tapered upper wedge comprises a corresponding dovetail guide path and opposing slots shaped for insertion and slidable adjustment of the guide pin rails. Opposing helical extension springs secured to the sides of the upper and lower wedges minimize friction forces between the wedges as they slidably move relative to one another. External surfaces of the wedges may be contoured to accommodate the shape of the object and/or its container.
    Type: Grant
    Filed: February 28, 2008
    Date of Patent: November 27, 2012
    Assignee: San Diego Composites, Inc.
    Inventors: Robert T. Kolozs, Josh S. Moore
  • Publication number: 20120247310
    Abstract: A device is provided to connect the ammunition and the magazine to each other not only in terms of design, but also in terms of function. The magazine and ammunition are combined to form sub-modules, wherein a plurality of sub-modules would then be comparable to the quantity of conventional ammunition in the launcher tube. The sub-modules are then assembled and locked. The individual sub-module contains, inter alia, rifling, by means of which, during firing, the ammunition/submunition is caused to rotate and is thereby stabilized.
    Type: Application
    Filed: March 30, 2012
    Publication date: October 4, 2012
    Inventor: Andre KLASEN
  • Patent number: 8256340
    Abstract: The illustrative embodiment of the present invention is a launch system that includes a missile canister cover that, in use, is attached to a missile canister. The cover is capable of being blown off of the canister before there is any contact between the nose of the missile and the cover and is further capable of withstanding a higher ambient pressure than internal canister pressure. These capabilities are achieved based on an attention to material mechanics and the prevailing geometry of the system.
    Type: Grant
    Filed: March 4, 2005
    Date of Patent: September 4, 2012
    Assignee: Lockheed Martin Corporation
    Inventors: Brian E. Bohs, William E. Everitt
  • Patent number: 8191454
    Abstract: Embodiments of a canisterized interceptor and method to prevent the launch of a canisterized interceptor that may have been penetrated by small arms fire are generally described herein. In some embodiments, the canisterized interceptor includes a composite canister for housing an interceptor. The canister includes an embedded winding to provide a conductive path and comprises a conductor arranged within composite material of the canister. A maximum spacing may be provided between windings of the conductor and penetration of the canister may be indicated by an open or short circuit in the conductive path.
    Type: Grant
    Filed: June 25, 2008
    Date of Patent: June 5, 2012
    Assignee: Raytheon Company
    Inventor: James H. Dupont
  • Patent number: 8186260
    Abstract: Embodiments of a translating adjacent-blast shield and method of protecting external slots of a missile from a high-temperature, high-pressure gas plume of a missile that is launched from an adjacent or nearby launcher tube of a launcher are disclosed herein. The translating adjacent-blast shield may be provided circumferentially around each of the missiles in a launcher and may cover at least portions of external slots of the missiles. The translating adjacent-blast shield may translate along the missile during launch to expose the external slots and may remain on the missile after launch.
    Type: Grant
    Filed: November 3, 2010
    Date of Patent: May 29, 2012
    Assignee: Raytheon Company
    Inventors: Robert Wade Martin, Philip Scott Rice
  • Patent number: 8181561
    Abstract: A projectile propulsion system includes a launch tube, multiphase material, and a membrane. The launch tube has an interior cavity, the multiphase material disposed therein. The launch tube also has an opening to receive the multiphase material. The membrane seals the opening while the multiphase material is disposed in the interior cavity of the launch tube so as to allow the launch tube to be pressurized. When the membrane is broken, a supersonic wave thrusts the contents of the interior cavity, such as a projectile, outwards with a high velocity and force.
    Type: Grant
    Filed: June 2, 2009
    Date of Patent: May 22, 2012
    Assignee: Causwave, Inc.
    Inventors: Jeffrey L. Riggs, Vladislav Oleynik, Valery Borovikov, Gennadiy Albul
  • Patent number: 8158915
    Abstract: A canard includes a first section and a second section. The first section is configured for the coupling of radial forces to a fuselage of an air vehicle, and the first section is coupled to the second section via a hinge somewhere along the radial extent of the canard. An edge of the first section near the hinge provides a load support for the air vehicle within a launch canister.
    Type: Grant
    Filed: October 2, 2008
    Date of Patent: April 17, 2012
    Assignee: Raytheon Company
    Inventor: Matthew S. Earle
  • Publication number: 20120055323
    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.
    Type: Application
    Filed: September 3, 2010
    Publication date: March 8, 2012
    Applicant: RAYTHEON COMPANY
    Inventor: Robert A. Bailey
  • Patent number: 7913604
    Abstract: The invention relates to a missile container retaining structure (1a) for a missile launch device of the type comprising a plurality of cells for receiving a missile container (2) and at least one duct (3). The structure is constituted by metal plates (101, 104) which are pre-cut so as to comprise complementary elements which can be fitted one inside the other, the plates being assembled so that the complementary elements of two adjacent plates are fitted one inside the other.
    Type: Grant
    Filed: June 12, 2008
    Date of Patent: March 29, 2011
    Assignee: DCNS
    Inventors: Dominique Monteil, Hervé Bruneau
  • Patent number: 7910867
    Abstract: A scalable and distributable software architecture for use in conjunction with various different weapons control system and launch systems is disclosed. The architecture discards the proprietary and non-open protocols and services that characterize in favor of open source adaptive and middleware components. In the illustrative embodiment of the invention, the inventive architecture is implemented as a Launch Control Module that separates different layers of responsibility within a launch controller (e.g., LCU) and exposes its variation points.
    Type: Grant
    Filed: August 30, 2006
    Date of Patent: March 22, 2011
    Assignee: Lockheed Martin Corporation
    Inventors: Ralph W. Edwards, George H. Goetz, Jennifer L. Houston-Manchester, Christine A. Ballard, Benjamin D. Skurdal
  • Patent number: 7891281
    Abstract: In a ground launcher, two or more housing-transportation-launch assemblies for respective missiles are placed one on top of the other and connected releasably and interchangeably to each other; each housing-transportation-launch assembly has a respective outer casing, which in turn has longitudinal end walls breakable from inside the casing, and a deflecting body for deflecting the exhaust gas of the engine of the missile; a guide and protection assembly being interposed between the casing and the missile to guide the missile in the set launch direction, and to protect the missile against shock or vibration.
    Type: Grant
    Filed: April 7, 2006
    Date of Patent: February 22, 2011
    Assignee: MBDA Italia S.p.A.
    Inventors: Bruno Baldi, Roberto De Girolamo, Teodoro Andrea Dragani, Sandro Mazzuca, Gian Fabrizio Venarucci
  • Patent number: 7823497
    Abstract: A countermass for use in a weapon to balance the forces arising when a launch able unit is launched from a launcher tube of the weapon. The countermass includes a first container enclosing a liquid. A countermass weapon includes a launcher tube open or openable in both ends. The launcher tube houses a launch able unit, a countermass including a first container enclosing a liquid, a pressure chamber, and a propellant charge that upon firing and combustion of the charge in cooperation with the pressure chamber and the countermass accelerates the launch able unit forwards in the tube at the same time as the countermass accelerates backwards in the tube. The first container is made of a non-rigid material. A second container is provided to cover or almost cover the first container. The second container is designed with damping characteristics.
    Type: Grant
    Filed: February 21, 2006
    Date of Patent: November 2, 2010
    Assignee: SAAB AB
    Inventors: Jonas Östberg, Åke Jansson
  • Patent number: 7735440
    Abstract: An inflatable restraint, and method of using the same, is used to provide support and shock isolation for missiles, torpedoes, missile canisters or the like in naval vessels. The inflatable restraint features a structural collar, at least one inflatable bladder and at least one interference member. The interference member is attached to the inside of the structural collar and the interference member is fully adjustable to ensure a snug fit during the loading of the missile, torpedo or missile canister into the structural collar. Once the missile, torpedo, missile canister or the like is properly inserted into the structural collar, the at least one inflatable bladder, which is also attached to the inside of the structural collar, is inflated to restrain the object. The pressure of the inflatable bladder may be regulated to provide variable spring constants and stiffness.
    Type: Grant
    Filed: October 30, 2002
    Date of Patent: June 15, 2010
    Assignee: Lockheed Martin Corporation
    Inventors: Grant W. Corboy, Michael J. Shaffer, Mahendra Maheshwari
  • Publication number: 20100089227
    Abstract: A technique for launching a missile that avoids some of the costs and disadvantages for doing so in the prior art. In particular, the illustrative embodiment of the present invention uses an electromagnetic catapult to throw the missile clear of the launch platform—with sufficient velocity to attain aerodynamic flight—before the missile's engine is ignited.
    Type: Application
    Filed: April 28, 2009
    Publication date: April 15, 2010
    Applicant: Lockheed Martin Corporation
    Inventor: George Raymond Root, JR.
  • Patent number: 7673552
    Abstract: The present invention relates to a countermeasure system having a substantially vertical launch tube that is at least generally rotatable about a vertical reference axis that extends through and along a length of the launch tube. This rotation capability of the launch tube may be used to affect an aiming of an associated countermeasure cartridge at least generally disposed therein. One or both the launch tube and countermeasure cartridge of this countermeasure system are generally equipped with a rotation inhibitor for substantially preventing independent rotation of the countermeasure cartridge relative to the launch tube at least when the countermeasure cartridge is disposed within the launch tube. The present invention is also designed to enable the associated countermeasure cartridge to be pitched over to a predetermined pitch angle (relative to the reference axis of the launch tube) to affect a desired flight path after launch of the countermeasure cartridge.
    Type: Grant
    Filed: November 25, 2003
    Date of Patent: March 9, 2010
    Assignee: Kilgore Flares Company, LLC
    Inventor: David W. Herbage
  • Patent number: 7665395
    Abstract: A lateral support device system of a canister-launched missile of the present invention is provided for eliminating the clearances between missile and the canister in 4 places by 90 degrees interval, and therefore no relative movement occurs between the missile and the canister. Therefore, the missile and the detent is free from shocks and vibrations that occurs during the handling, transportation and operation. In addition, when the missile is fired, those lateral lock become free with a little energy loss.
    Type: Grant
    Filed: January 30, 2006
    Date of Patent: February 23, 2010
    Assignee: Agency For Defense Development
    Inventors: Il-Soo Kim, Woo-Jeon Shim, Hak-Yeol Lee
  • Patent number: 7600477
    Abstract: A method for discharging countermeasures, a rocket launcher, and a dispenser arrangement. A space for one or more rockets in a rocket launcher is used as a carrier for a dispenser arrangement for countermeasures. The dispenser arrangement is designed with one or more cylindrical sections specially adapted to the rocket space in the rocket launcher. Equipment already adapted to aircraft can be used in supplementing the countermeasure equipment of the aircraft.
    Type: Grant
    Filed: May 3, 2002
    Date of Patent: October 13, 2009
    Assignee: SAAB AB
    Inventor: Christer Zätterqvist
  • Publication number: 20090126556
    Abstract: A launch system for use as a standalone munition launcher or as a guest launcher within a main battery host launcher.
    Type: Application
    Filed: November 20, 2008
    Publication date: May 21, 2009
    Applicant: LOCKHEED MARTIN CORPORATION
    Inventors: Daniel A. Skurdal, Timothy R. Fouts, Jennifer L. Houston-Manchester, John Snediker
  • Patent number: 7484449
    Abstract: The present invention discloses a missile ejection system and a canister thereof.
    Type: Grant
    Filed: June 28, 2005
    Date of Patent: February 3, 2009
    Assignee: Government Agency for Defense Development
    Inventors: Woo-Jeon Shim, Il-Soo Kim, Seung-Jong Oh, Jae-Hoon Ha, Ji-Chul Kim
  • Patent number: 7467761
    Abstract: A method for adjusting the flight path of an unguided projectile, which comprises the steps of: (a) Measuring the magnitude and direction of the jittering of a projectile launch tube, at an ejection time of a projectile from the launch tube; (b) Measuring a velocity deviation of the projectile from a nominal velocity; (c) Measuring an angular deviation of the sight of the launch tube, being equal to the angular deviation between a line coinciding with the direction of gravity and a line passing through the center of the launch tube and the center of the sight; (d) Determining a compensating impulse vector to be applied to the projectile during an initial flight path thereof based on the magnitude and direction of the jittering, velocity deviation and angular deviation; and (e) Applying the compensating impulse vector to the projectile by activating a flight correction unit, the thrust developed by the flight correction unit suitable for adjusting the flight path of the projectile by a magnitude and direction
    Type: Grant
    Filed: May 13, 2005
    Date of Patent: December 23, 2008
    Assignee: Rafael-Armament Development Authority Ltd
    Inventors: Oded Yehezkeli, Irad Kunreich
  • Patent number: 7451703
    Abstract: Apparatus for venting munitions exposed to high ambient temperatures. The munition includes a casing having a nose end and an opening in the nose end; a lifting plug disposed in the opening in the nose end, the lifting plug including a bore therethrough; and a seal disposed in the bore in the lifting plug, the seal comprising an ionomer. The munition may further include a fuze well disposed in the casing, the opening in the nose end leading into the fuze well; and a second seal disposed in the fuze well. The seals will rupture and vent the munition's explosive to the atmosphere.
    Type: Grant
    Filed: December 21, 2005
    Date of Patent: November 18, 2008
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventor: Shahram Dabiri
  • Patent number: 7418914
    Abstract: A system is disclosed for pre-positioning a canister assembly at an undersea location. A transporter deploys to and releases the assembly proximate to the desired location. Once the assembly has fallen a safe distance after release, spring bands of the assembly are released by the action of lanyards of the transporter. The release allows anchor plates on each end of the assembly to separate from the assembly thereby dragging the assembly to a seafloor with the assembly buoyant at the undersea location. A vehicle deployment from the assembly is actuated by an acoustic receiver that causes a release device to release a normally compressed spring thereby allowing the spring to expand. During expansion, water is drawn into the assembly through flow ports to force a plunger plate with the water to act on a vehicle to deploy the vehicle out of a deployment tube of the assembly.
    Type: Grant
    Filed: January 4, 2008
    Date of Patent: September 2, 2008
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventors: Michael T. Ansay, Angelo Di Biasio
  • Patent number: 7389717
    Abstract: A missile launch system is disclosed that allows for the rapid reloading of missiles in support of missions (e.g., littoral warship missions, etc.) that require a high-volume assault of one or more targets. In particular, the illustrative embodiment of the present invention uses a munitions module that is capable of launching missiles and is able to fit inside a warship. In addition to accommodating multiple missiles, the munitions module accommodates one or more missile types. The munitions module is configured with a door at a breech end to provide access to multiple launch cells for the rapid reloading of missiles. The door is physically configured to define a plenum that couples the launch cells to an exhaust duct for the purpose of venting exhaust gases. The munitions module mitigates some of the problems associated with launch systems in the prior art.
    Type: Grant
    Filed: April 21, 2005
    Date of Patent: June 24, 2008
    Assignee: Lockheed Martin Corporation
    Inventors: Tushar K. Shah, Ashanna Randall, Chandler P. McCann
  • Publication number: 20070283800
    Abstract: A missile launch and guidance apparatus of a rail-shoe launching type is disclosed. In a missile adapted to be launched while moving along a rail of a launch tube, a missile launch and guidance apparatus comprises: a bushing inserted into a missile body; a shoe, one end of which is inserted into the bushing, and the other end of which is in contact with the rail; and a spring inserted between the bushing and the shoe so as to provide a separation force to the shoe against the bushing. By separating the shoe from the missile in a lateral direction of the missile launching direction by an elastic force of the spring after launching the missile, the missile launch and guidance apparatus can keep constant the gap between the missile and the launch tube rail irrespective of the behavior of the missile taking place in a launching process, and the drag and weight of the missile launched from the launch tube is reduced to thereby exhibit the maximum flight performance.
    Type: Application
    Filed: December 29, 2006
    Publication date: December 13, 2007
    Inventors: Tae-Hak PARK, Sang-Hun SHIN
  • Publication number: 20070275354
    Abstract: Apparatus and methods are described for a weapon simulator. An example weapon simulator includes a pressure piston, which is couplable to a weapon, which acts to open a breech, and which is seated in a pressure cylinder. An example pressure piston includes a slider. The slider holds a pressure intake opening open and keeps one or more pressure outlet openings closed when the breech is in a front-most position. In addition, the slider keeps the pressure intake opening closed and holds the one or more pressure outlet opening open when the breech is in a rear-most position.
    Type: Application
    Filed: March 30, 2007
    Publication date: November 29, 2007
    Inventor: Rudi Beckmann
  • Patent number: 7293492
    Abstract: In a multiple projectile launcher system, cartridges are securely held within a cassette that can be loaded into a locking and priming mechanism in a base of a multiple projectile launcher. Once the cassette is loaded into the locking and priming mechanism, the cartridges in the cassette may be primed by moving the locking and priming mechanism (which is holding the cassette) such that electric igniter contacts in the launcher base are in contact with electric igniters at the priming end of each cartridge. Once the cassette is locked (thereby priming the plural cartridges held in the cassette), the cartridges may be fired singly, severally, and/or all at the same time, using an electrically initiated fire control system. The multiple projectile launcher is particularly effective in crowd and/or riot control, where the payload of the cartridges comprise non-lethal and/or less-lethal munitions, such as tear gas grenades, sting-ball grenades, flash-bang rounds, bean bags, etc.
    Type: Grant
    Filed: October 7, 2004
    Date of Patent: November 13, 2007
    Inventor: Michael Brunn
  • Patent number: 7202809
    Abstract: A fast acting active protection system for military vehicles defeats RPG (rocket propelled grenade) threats fired from close ranges. The system minimizes the hazard to troops and civilians nearby. The system uses a plurality of passive sensors to locate the threat and initialize the system. A low cost radar or laser tracker is used as the means to determine range, velocity, and (if required) angular position of the threat. The countermunition used may be one of several choices, with the requisites being that the countermunition provides fast response with low inertia, and is able to damage or destroy the detected threat. A multi-barrel recoilless gun is the weapon of choice. A launching device is used to deploy and aim the countermunition and the tracking means. On board software and electronics are used to control the system.
    Type: Grant
    Filed: May 10, 2004
    Date of Patent: April 10, 2007
    Assignee: BAE Systems Land & Armaments L.P.
    Inventors: David A. Schade, Thomas C. Winant, Jaime Alforque, Jeffrey Faul, Kenneth B. Groves, Valent Horvatich, Marco Albert Middione, Christopher Tarantino, James Robert Turner
  • Patent number: 7128013
    Abstract: A launch tube system has two concentric sleeves. An inner sleeve having holes formed therethrough defines a launch tube, and an outer sleeve surrounds the inner sleeve and is spaced apart therefrom. One or more flexible bladders are disposed between the inner outer sleeves. When filled with fluid, the flexible bladder(s) expands and extends into and through the holes and into confines of the inner sleeve to thereby form shock isolation for a projectile housed in the inner sleeve.
    Type: Grant
    Filed: September 26, 2005
    Date of Patent: October 31, 2006
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventors: Stephen J. Plunkett, Richard E. Dooley
  • Patent number: 7089843
    Abstract: A launcher includes a plurality of launch tubes for stowing and launching a plurality of air vehicles. A central air manifold is operatively connected to an air storage tank; a first launch tube air manifold is operatively connected to a first group of the launch tubes and operatively connected to the central air manifold. The first launch tube air manifold has a separate port corresponding to each launch tube of the first group of launch tubes. A release valve mechanism is removably mounted in one of the ports of the first launch tube air manifold, the release valve mechanism controlling the passage of launch air between the first launch tube air manifold and the launch tube corresponding to the port in which the release valve mechanism is mounted. A plug is removably mounted in each of the ports not occupied by the release valve mechanism.
    Type: Grant
    Filed: March 29, 2004
    Date of Patent: August 15, 2006
    Assignee: AAI Corporation
    Inventors: Stephen W. Miller, Steven J. Fox, David M. Feild, Richard A. Bauernschub, Justin A. Mettee
  • Publication number: 20060117940
    Abstract: A reconfigurable missile launcher that avoids some of the costs and disadvantages associated with missile launchers in the prior art. In particular, the illustrative embodiment of the present invention uses a variable-size receptacle for locating and holding a missile canister chosen from a set of missile canister types. The illustrative embodiment also includes a controller that includes data sets that are specific to each of a plurality of missile types.
    Type: Application
    Filed: December 6, 2004
    Publication date: June 8, 2006
    Applicant: Lockheed Martin Corporation
    Inventors: Tushar Shah, Kristian Trauger, Mahendra Maheshwari
  • Patent number: 7040212
    Abstract: A container (1) for acting as a storage enclosure and launch tube for a missile (3), the container (1) comprising an integral missile efflux management system including an efflux deflector (1d) positioned for receiving the missile efflux and deflecting it into a series of ducts (8) which run alongside the missile to the missile exit end (16) of the container (1), which end may have an openable cover (7) operable to close both the missile exit and the exits from the ducts (8). The efflux deflector is a dome-shaped base-plate (1d) spaced from the ducts to define a plenum chamber. The particular interior shape of the base plate (1d) ensures optimum efflux management.
    Type: Grant
    Filed: August 9, 1996
    Date of Patent: May 9, 2006
    Assignee: MBDA UK Limited
    Inventors: John E. Gaywood, Ronald Hall