Rocket Launching Patents (Class 89/1.8)
  • Patent number: 11261890
    Abstract: A system includes an elongated cylindrical body having a first end extending to a second end; an outer surface and an inner surface; a thickness extending from the inner surface to the outer surface; and a plurality of openings extending from the inner surface to the outer surface. The system further includes a fluid injection apparatus disposed within the elongated cylindrical body, the fluid injection apparatus is configured to pass fluid through the openings.
    Type: Grant
    Filed: November 29, 2018
    Date of Patent: March 1, 2022
    Inventor: Khaled Abdullah Alhussan
  • Patent number: 11187494
    Abstract: A modular missile launch system for launching missiles from a mobile platform includes a rectangular first support frame having a first longitudinal beam having a platform coupling structure formed for releasably fastening the first support frame to the mobile platform. A second longitudinal beam arranged at a distance from the first longitudinal beam includes a first connecting structure on an underside and a launch tube securing structure for mounting a missile launch tube to the first support frame. The first connecting structure defines a first plug connection portion extending in a longitudinal direction, onto which a second support frame with a second plug connection portion can be plugged in the vertical direction, having at least two first through bores that are spaced apart in the longitudinal direction, through each of which one connecting device can be passed in order to secure the first and the second support frame.
    Type: Grant
    Filed: October 29, 2020
    Date of Patent: November 30, 2021
    Assignee: MBDA Deutschland GmbH
    Inventor: Robert Kroyer
  • Patent number: 11181340
    Abstract: A missile launching system for launching missiles from a mobile platform includes a rectangular primary carrier frame having a platform coupling structure for releasably fastening the first carrier frame to the mobile platform, and a launch tube. A locking device on the primary carrier frame includes a lock hook which projects from the primary carrier frame and has a receiving piece. A stop piece extends transverse to the receiving piece. A locking plate is inserted between the receiving piece and the stop piece. The launch tube has a fastening bracket with a fastening recess fitted onto the receiving piece and locked with the lock hook by inserting the locking plate between the stop piece and the receiving piece. Alternatively, two launch tube receiving devices are laterally attached to the primary carrier frame, each of which is designed as a closed frame defining a receiving opening.
    Type: Grant
    Filed: October 29, 2020
    Date of Patent: November 23, 2021
    Assignee: MBDA Deutschland GmbH
    Inventors: Robert Kroyer, Herbert Ertl
  • Patent number: 10723351
    Abstract: A vehicle safety system includes one or more sensors interfaced to an index vehicle and a computer that is operatively interfaced to the one or more sensors, thereby the computer obtains sensor data from the one or more sensors. One or more propulsion devices are operatively coupled to the computer such that the computer controls activation of each propulsion device. The computer executes software that causes the computer to iteratively calculate a size of a safety zone based upon the sensor data and to iteratively determine if an object enters the safety zone as well as if a collision with the object is imminent. If it is determined that the collision with the object is imminent, the software causes the computer to signal one or more of the propulsion devices to emit a jet of liquid, thereby decelerating and/or changing direction of the index vehicle and/or of the object.
    Type: Grant
    Filed: March 20, 2020
    Date of Patent: July 28, 2020
    Assignee: Physician Electronic Networks, L.L.C.
    Inventors: A-Hamid Hakki, Maryam Hakki, Dina A. Hakki, Belmina Hakki, Nadia Hana Hakki
  • Patent number: 10584938
    Abstract: A flexible cover comprising at least one, so-called composite, layer, formed from a composite material consisting of at least one fabric and at least one elastomer and a flat metal blade secured to the composite layer by elastomer and comprising pre-cut lines for fragilisation of the flexible cover, the pre-cut lines being arranged so as to create areas in the form of petals, the composite layer and the metal blade being designed so as to return to an initial position once the flexible cover has been opened.
    Type: Grant
    Filed: July 20, 2016
    Date of Patent: March 10, 2020
    Assignee: MBDA FRANCE
    Inventors: Bertrand Leroy, Pascal Herquel
  • Patent number: 10288388
    Abstract: A cartridge for coupling to a conducted electrical weapon to launch electrodes toward a target to provide a current through the target to impede locomotion of the target. The cartridge includes a cover that covers a forward portion of the cartridge. The cover may be over molded on the forward portion of the cartridge. The cover includes a frangible portion. The frangible portion may surround the perimeter of a door or be positioned between flaps. The frangible portion may be broken to separate the door from the cover or to disengage the flaps so they can move. The electrode may launch through a door opening or between the flaps to travel toward the target.
    Type: Grant
    Filed: December 28, 2015
    Date of Patent: May 14, 2019
    Assignee: TASER International, Inc.
    Inventors: Albert K. Lavin, Luke A. Salisbury, Milan Cerovic
  • Patent number: 9745063
    Abstract: A system for air-launching a liquid fueled rocket launch vehicle using a tubular rocket support structure for holding the launch vehicle and for supplying the launch vehicle with make-up cryogenics, electrical power, and control signals, and for providing coupling to a launch-assist aircraft. The tubular rocket support structure contains cryogenic fluids, in addition to fuel and oxidizer, to cool the fuel and oxidizer during the pre-launch phase. The tubular rocket support structure has features that keep the liquid fuel and oxidizer from sloshing away from the tank outlet ports to the launch vehicle's rocket engine after release from the aircraft but before rocket launch. In operation, the aircraft controllably releases the tubular rocket support structure containing the launch vehicle, and the launch vehicle then launches from the rocket support structure.
    Type: Grant
    Filed: May 9, 2015
    Date of Patent: August 29, 2017
    Inventors: Adam P. London, Lucas A. Hundley, Lloyd J. Droppers
  • Patent number: 9704469
    Abstract: A vehicle combustion noise-masking control method is provided that includes the steps of determining whether a combustion noise that is equal to or greater than a predetermined level is generated in a driving condition of a vehicle engine, determining whether the level of the combustion noise generated in the driving condition is within a predetermined range, and outputting a masking sound reducing the combustion noise to the inside of the vehicle when the level of the combustion noise is within the predetermined range.
    Type: Grant
    Filed: November 12, 2015
    Date of Patent: July 11, 2017
    Assignee: Hyundai Motor Company
    Inventor: In Soo Jung
  • Patent number: 9074841
    Abstract: A missile container sealing assembly includes an end cap capable of sealing an end of a container for a missile, and one or more linkage assemblies for controllably opening the end cap. The end cap has a frame portion that defines an opening for a missile and is mountable to the end of the missile container, and a door portion that includes one or more doors that close and seal the opening in the frame portion. Each linkage assembly is associated with a respective one of the one or more doors, for opening the doors relative to the frame portion. Moreover, each linkage assembly includes a link that transmits a force ahead of the leading end of the missile to open the doors and permit the missile's egress through the opening.
    Type: Grant
    Filed: September 19, 2013
    Date of Patent: July 7, 2015
    Assignee: Raytheon Company
    Inventors: John F. Bugge, Dylan Foster Bixby
  • 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: 8910557
    Abstract: A payload deployment system includes a mount for receiving one or more payload modules that each include one or more payloads to be deployed. The payload modules also each include a sleeve, with the one or more payloads are in one or more openings in the sleeve. The payloads may be contained in respective containers, such as hermetically-sealed containers, that are in the openings. The electrical coupling may be wireless coupling, for transferring electrical power to the payload module(s), and for communication, such as networked communication, between the mount and the one or more payload modules. The wireless coupling may be inductive coupling that involves overlap of inductive elements such as wire coils. The payload deployment system may also include one or more translators for translating commands and/or other communications between the one or more payload modules and a platform to which the payload deployment system is coupled.
    Type: Grant
    Filed: January 30, 2013
    Date of Patent: December 16, 2014
    Assignee: Raython Company
    Inventors: Donald P Cox, Robert W Knox, Derek S Wall, Michael D Stokes, Darren C Smith, Scott G Martin, Michael J Holt, Bradley M Gaul
  • Publication number: 20140202322
    Abstract: A mounting set for use in mounting an external stores to a mounting station of an aerospace vehicle includes a mounting bracket arrangement and a strap arrangement. The bracket arrangement is configured for selective reversible engagement with respect to the mounting station and for cooperating with the strap arrangement. The strap arrangement is configured for securing the bracket arrangement to the stores in load bearing abutment therewith to enable transfer of loads between the stores and the mounting station via said bracket arrangement, in operation of said mounting set. A mounting system is also provided for mounting an external stores to an aerospace vehicle having two or more mounting stations, including a mounting set for each mounting station. Mounting methods are also provided.
    Type: Application
    Filed: March 13, 2013
    Publication date: July 24, 2014
    Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
    Inventor: Israel SCHNITZER
  • Patent number: 8788120
    Abstract: System and methods for managing targets of a vehicle is provided. In some aspects, a system may include a boundary check module configured to receive boundary information from a flight safety system. The boundary information comprises a selected termination boundary of a plurality of termination boundaries confining navigation of the vehicle. Each of the plurality of termination boundaries is associated with a target of a plurality of targets of the vehicle. The system may further include a target modification module configured to select the target associated with the selected termination boundary, and a target guidance module configured to provide the selected target to a guidance and control system of the vehicle.
    Type: Grant
    Filed: April 19, 2011
    Date of Patent: July 22, 2014
    Assignee: Lockheed Martin Corporation
    Inventors: Andrew P. Imbrie, Steven A. Dunn, Andrew A. Myers
  • Publication number: 20130319211
    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: Application
    Filed: December 6, 2011
    Publication date: December 5, 2013
    Applicant: United States Government, as represented by the Secretary of the Navy
    Inventors: Michael Ryan Whitney, Paul G. Atkinson, Perry J. Fridley, JR., Keith M. DeLoach, Luis C. Gominho, Michael J. Morrison, Doyle B. Green, Douglas L. Wynings
  • 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: 8495945
    Abstract: A system that provides wireless power transfer between a weapon and a platform. A method for loading, testing, targeting, and launching a weapon.
    Type: Grant
    Filed: August 2, 2012
    Date of Patent: July 30, 2013
    Assignee: The United States of America as Represented by the Secretary of the Navy
    Inventors: Richard Kirchner, Mallory Boyd
  • 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
  • Publication number: 20130139676
    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: Application
    Filed: August 15, 2011
    Publication date: June 6, 2013
    Applicant: MBDA UK LIMITED
    Inventors: Bryan Bowen, Anthony Machell, Terence Edward Kavanagh, Dennis George Turner
  • Patent number: 8443707
    Abstract: An apparatus is disclosed that is a self-contained gas management system (hereinafter “GMS”) that accommodates individual canisters of highly energetic small munitions, but is not so limited. By decoupling the gas management system for a given munition from an adjacent munition, the risk of downing a multi-pack launcher or munition adapter is reduced. Thermal wear, overheating, restrained firing and aft closure debris can be isolated through the separation of gas management systems. In addition, the GMS allows for ease of replenishment and maintenance of a given sub-cell of a multi-pack system. The GMS works with existing munitions and canisters without the need to modify them. Each GMS is dimensioned to fit the canistered munition it receives as well as the launch system with which it is used. The illustrative GMS comprises a plenum, and a first and a second uptake structure. The plenum receives the exhaust from the canistered munition when the munition fires.
    Type: Grant
    Filed: August 24, 2010
    Date of Patent: May 21, 2013
    Assignee: Lockheed Martin Corporation
    Inventors: Daniel A. Skurdal, John Snediker
  • 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: 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
  • 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: 8275498
    Abstract: A system and method for assessing the risk of conjunction of a rocket body with orbiting and non-orbiting platforms. Two-body orbital dynamics are used to initially determine the kinematic access for a ballistic vehicle. The access may be represented in two ways: as a volume relative to its launcher and also as a geographical footprint relative to a target position that encompasses all possible launcher locations.
    Type: Grant
    Filed: August 2, 2010
    Date of Patent: September 25, 2012
    Assignee: Analytical Graphics Inc.
    Inventor: Salvatore Alfano
  • Patent number: 8266999
    Abstract: A mobile terrestrial vertical missile launch system is provided for relocatable ballistic missile deployment. The system is connectable to a transport truck and includes a trailer, a pivotable canister, a plurality of stabilizing legs, and an equipment module. The trailer has a hitch for connecting to the truck, a base for supporting wheels for road travel, and a flatbed platform having a transverse hinge. The canister contains launcher for at least one missile and is configurable by rotation at the hinge for disposal in either a longitudinal position for stowage or an erected position for deployment. The stabilizing legs are disposed along a periphery of the trailer. The legs can be disposed in one of an elevated position for stowage and a retarded position for ground engagement. The equipment container supplies electrical power, environmental conditioning, tracking, communication and control for the missile.
    Type: Grant
    Filed: February 1, 2011
    Date of Patent: September 18, 2012
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventors: Carl L. Sisemore, Myron Lyn Thomas, II
  • Patent number: 8256338
    Abstract: A system that provides wireless power transfer between a weapon and a platform. A method for loading, testing, targeting, and launching a weapon.
    Type: Grant
    Filed: January 6, 2010
    Date of Patent: September 4, 2012
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventors: Richard Kirchner, Mallory Boyd
  • Publication number: 20120210851
    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: Application
    Filed: August 7, 2008
    Publication date: August 23, 2012
    Inventor: Richard Glasson
  • Publication number: 20120210852
    Abstract: An air-based vertical launch system is described by means of which ballistic missile defense can be achieved effectively from a large aircraft. A method for ensuring safe missile egress is proposed. A method for ensuring that the missile strikes the ballistic missile payload section is also proposed. Together, the air basing method employing vertical (or near-vertical) launch and semi-active laser guidance yield an affordable and operationally effective missile defense against both tactical and long-range ballistic missiles. The affordability of missile defense is enhanced by the ability of an aircraft equipped with a vertical launcher to simultaneously carry out several defensive and offensive missions and to provide other capabilities such as satellite launch at other times.
    Type: Application
    Filed: September 19, 2011
    Publication date: August 23, 2012
    Applicant: BAE SYSTEMS TECHNOLOGY SOLUTIONS & SERVICES INC.
    Inventor: Thomas H. McCants, JR.
  • Publication number: 20120174741
    Abstract: This is directed to systems, processes, machines, and other means that allow a pan/tilt gun mount to be radio controlled by a plurality of frequencies. The invention can rapidly rotate and adjust elevation to aim a gun mount as directed by a user.
    Type: Application
    Filed: December 30, 2011
    Publication date: July 12, 2012
    Inventor: CHRIS ROGERS
  • Patent number: 8207480
    Abstract: Methods and apparatus for launching an effector according to various aspects of the present invention may include a fire control system. The fire control system may be responsive to a sensor, such as a radar, and may be connected to the effector, such as via a launcher. The file control system may be adapted to generate a fire control solution according to the data from the sensor, initiate a launch of the effector, and provide the fire control solution to the effector after initiating the launch.
    Type: Grant
    Filed: May 14, 2008
    Date of Patent: June 26, 2012
    Assignee: Raytheon Company
    Inventors: David A. Lance, Steven T. Siddens
  • Publication number: 20120152090
    Abstract: An apparatus is disclosed that is a self-contained gas management system (hereinafter “GMS”) that accommodates individual canisters of highly energetic small munitions, but is not so limited. By decoupling the gas management system for a given munition from an adjacent munition, the risk of downing a multi-pack launcher or munition adapter is reduced. Thermal wear, overheating, restrained firing and aft closure debris can be isolated through the separation of gas management systems. In addition, the GMS allows for ease of replenishment and maintenance of a given sub-cell of a multi-pack system. The GMS works with existing munitions and canisters without the need to modify them. Each GMS is dimensioned to fit the canistered munition it receives as well as the launch system with which it is used. The illustrative GMS comprises a plenum, and a first and a second uptake structure. The plenum receives the exhaust from the canistered munition when the munition fires.
    Type: Application
    Filed: August 24, 2010
    Publication date: June 21, 2012
    Applicant: LOCKHEED MARTIN CORPORATION
    Inventors: Daniel A. Skurdal, John Snediker
  • 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
  • Publication number: 20120103175
    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: Application
    Filed: November 3, 2010
    Publication date: May 3, 2012
    Applicant: Raytheon Company
    Inventors: Robert Wade Martin, Philip Scott Rice
  • Publication number: 20120060672
    Abstract: A host vehicle, rocket launcher and rocket assembly connectivity system that automatically determines inventory of plural rocket assemblies of different types randomly loaded in plural rocket launcher tubes in multiple host vehicle rocket launcher installations, manages pre-launch functions for new guided rocket-types, manages fuze setting of time-set fuzes, fires selected guided and unguided rocket assemblies using stored inventory information automatically acquired directly from rocket assemblies and verifies rocket-away after firing command, while maintaining compatibility with legacy US military time-set fuzes, warheads and Rocket Management Systems (RMS).
    Type: Application
    Filed: October 8, 2009
    Publication date: March 15, 2012
    Inventor: Tommy Grigg
  • Publication number: 20120060673
    Abstract: Aspects of the present disclosure provide an armored helmet assembly that is fully or completely assembled and quickly mounted onto a host vehicle to form a military vehicle. The armored helmet assembly provides protection, weapons, cameras, and other equipment for the driver. When desired, the armored helmet assembly in a completely assembled state is unlocked and removed from the host vehicle. The host vehicle is typically a construction vehicle and useful as such. In some embodiments, a weapons platform assembly is mounted on the armored helmet assembly. Other embodiments include one or more of an expandable battle shield, a front end container for storage of equipment or weapons, and a command surveillance module. In certain embodiments, in addition to the armored helmet assembly, a lower armored assembly in a completely assembled state is mounted onto a lower portion of the host vehicle.
    Type: Application
    Filed: May 23, 2011
    Publication date: March 15, 2012
    Inventor: Todd Burton
  • Publication number: 20120055321
    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.
    Type: Application
    Filed: September 3, 2010
    Publication date: March 8, 2012
    Applicant: RAYTHEON COMPANY
    Inventor: Mark A. Angeloff
  • Publication number: 20120024136
    Abstract: An air-based vertical launch system is described by means of which ballistic missile defense can be achieved effectively from a large aircraft. A method for ensuring safe missile egress is proposed. A method for ensuring that the missile strikes the ballistic missile payload section is also proposed. Together, the air basing method employing vertical (or near-vertical) launch and semi-active laser guidance yield an affordable and operationally effective missile defense against both tactical and long-range ballistic missiles. The affordability of missile defense is enhanced by the ability of an aircraft equipped with a vertical launcher to simultaneously carry out several defensive and offensive missions and to provide other capabilities such as satellite launch at other times.
    Type: Application
    Filed: September 19, 2011
    Publication date: February 2, 2012
    Applicant: BAE SYSTEMS TECHNOLOGY SOLUTIONS & SERVICES INC.
    Inventor: Thomas H. McCants, JR.
  • Patent number: 8089033
    Abstract: A method and apparatus for attacking a plurality of dispersed targets are herein presented. In particular, the method and apparatus herein presented allow the user to upload target data onto a pod mounted on a host aircraft. Upon reaching the pre loaded target location, the pod releases a plurality of individually targeted Micro Air Vehicles (MAVs), thereby allowing the user to attack a plurality of dispersed targets from a single aircraft standing off at a significant distance from the target area.
    Type: Grant
    Filed: June 18, 2008
    Date of Patent: January 3, 2012
    Assignee: BAE Systems Information and Electronic Systems Integration Inc.
    Inventors: Paul A. Zank, Paul D. Zemany
  • Patent number: 8087336
    Abstract: A system and method for actuating a hatch door. One embodiment includes a vertical launcher system that has a hatch door disposed in a plane at the top of a hold. The hatch door includes a leading edge and a trailing edge at opposite ends of the hatch door. When an actuator arm for maneuvering the hatch door is extended, the leading edge is lifted away from the plane by the actuator arm while the trailing edge remains in the plane and slides across the top of the plane toward the point where the leading edge was first lifted away. Such a sliding hatch mechanism allows for quick opening and closing of a hatch door while providing more efficient use of mechanical energy for breaking ice build up or prevent intrusion.
    Type: Grant
    Filed: November 6, 2008
    Date of Patent: January 3, 2012
    Assignee: Lockheed Martin Corporation
    Inventors: Corey A. Fleischer, Bruce S. Chiu, Kristopher Heick
  • Patent number: 8082832
    Abstract: In some embodiments, the present invention provides an apparatus and process that includes control electronics that generate an electronic control signal; and a plurality of optically or electrically pumped semiconductor lasers, quantum-cascade lasers, optical parametric generators, or optical parametric oscillators, operatively coupled to the control electronics, that output an optical signal having a plurality of wavelengths, each wavelength having an output intensity that is varied over time to simulate a combustion signature of a weapon. In some embodiments, at least two different infrared wavelengths are varied differently with time. Some embodiment are implemented as part of, for example, a anti-aircraft defense system, wherein incoming aircraft need to be disabled, and the present invention provides a way of distracting, exhausting, confusing, overwhelming, or bypassing the hostile aircraft's anti-missile defenses so that, e.g.
    Type: Grant
    Filed: May 14, 2008
    Date of Patent: December 27, 2011
    Assignee: Lockheed Martin Corporation
    Inventors: Steven C. Tidwell, Charles A. Lemaire
  • Patent number: 8037799
    Abstract: A system includes a housing and an electromagnetic coil within the housing. The electromagnetic coil is arranged in a coil stack. A thermal damper is positioned adjacent to the electromagnetic coil, and a thermal structural plate is positioned adjacent to the coil stack. The thermal damper manages temperature rise of the electromagnetic coil and the thermal structural plate provides cooling to the coil stack. In an embodiment, the system is used to launch projectiles.
    Type: Grant
    Filed: February 29, 2008
    Date of Patent: October 18, 2011
    Assignee: Lockheed Martin Corporation
    Inventors: Randy L. Gaigler, Jimmy C. Tong
  • Patent number: 7946209
    Abstract: The present invention generally concerns systems and methods for supplying electric power using supercapacitors; and more particularly, representative and exemplary embodiments of the present invention generally relate to improved methods and systems for supplying power to a guided rocket.
    Type: Grant
    Filed: October 4, 2007
    Date of Patent: May 24, 2011
    Assignee: Raytheon Company
    Inventors: Arthur Schneider, Jeffrey S. Supp
  • 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: 7908973
    Abstract: The disclosed system, device and method for deploying a sub-module from a carrier vehicle generally includes: a sub-module projectile (100) housed within a carrier vehicle; a rolling diaphragm (115) sealed between a first pressure chamber volume (145) and a second sub-module containment volume (e.g., substantially formed on the opposing side of rolling diaphragm 115 relative to pressure chamber 145); and a release mechanism (500), wherein the sub-module projectile (100) is secured until releasable deployment from the carrier vehicle. Disclosed features and specifications may be variously controlled, adapted or otherwise optionally modified to improve ejection, deployment and/or dispersal of a variety of sub-modules from a variety of carrier modules. Exemplary embodiments of the present invention generally provide for the ejection and dispersal of kinetic energy rod warheads from a kill-vehicle.
    Type: Grant
    Filed: November 5, 2004
    Date of Patent: March 22, 2011
    Assignee: Raytheon Company
    Inventors: Charles M. De Lair, Christopher P. Owan, Jeffrey P. Sowers, Derek L. Budisalich, Matthew B. Castor, Matthew P. Francis
  • Publication number: 20110062281
    Abstract: The present disclosure relates to a launch system for air vehicles. More specifically, the present disclosure relates to launching unmanned air vehicles (UAVs) that are unable to be launched by hand. The present disclosure provides a system for launching a winged vehicle, including: a projectile launching device; and a device for converting projectile momentum into acceleration of a winged vehicle.
    Type: Application
    Filed: May 13, 2009
    Publication date: March 17, 2011
    Applicant: BAE SYSTEMS plc
    Inventors: Christopher Colin Anthony Woolley, Kevin William Beggs, Ryan Andrew Bakewell, Richard Desmond Joseph Axford, John Wainwright
  • Patent number: 7874237
    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: Grant
    Filed: April 28, 2009
    Date of Patent: January 25, 2011
    Assignee: Lockheed Martin Corporation
    Inventor: George Raymond Root, Jr.
  • Publication number: 20110011251
    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: Application
    Filed: January 8, 2009
    Publication date: January 20, 2011
    Inventor: Pierre Jacques Truyman