With Range Increasing Means Patents (Class 102/490)
  • Patent number: 10753715
    Abstract: The present invention is directed to a projectile configured to provide a submunition payload across a wide impact pattern, similar to that of a shotgun, at a range typically beyond the capability of standard shotgun rounds. The additional range is provided in some embodiments of the invention by allowing the tailoring deployment range of the submunition payload based upon a given threat.
    Type: Grant
    Filed: September 23, 2019
    Date of Patent: August 25, 2020
    Inventors: Joseph Garst, Robert Folaron
  • Patent number: 9010248
    Abstract: A non-spinning 40 mm ammunition round for firing in an M320 grenade launcher. The round includes a cylindrical shaped gun sleeve cartridge case, which covers the standard rifling inside the M320, and thus presents a smooth bore surface to the fired ammunition. Because the ammunition is not launched in a spinning mode, it may now comprise those guidance and camera components as may be desired which components would not have been possible to employ on a round that is spinning.
    Type: Grant
    Filed: December 14, 2012
    Date of Patent: April 21, 2015
    Assignee: The United States of America as Represented by the Secretary of the Army
    Inventors: Leon Manole, Arthur Ricardo Pizza, Ernest Lee Logsdon, Gary Anthony Pacella, Anthony J. Sebasto
  • Patent number: 8973504
    Abstract: The present invention relates to a bullet including an air-guiding recess, comprising: a head 20; and a tail 30 disposed behind the head 20, and including an odd number of air-guiding recesses 32 formed so as to be curved in the bottom and outer circumferential surfaces thereof. The air-guiding recess 32 is characterized by having a sloped bottom that increases in depth while progressing to the bottom surface of the tail 30. Accordingly, vortex is prevented from being generated at the rear side of the bullet, so as to significantly increase the effective range thereof and simultaneously improve accuracy when shooting same.
    Type: Grant
    Filed: April 29, 2011
    Date of Patent: March 10, 2015
    Assignee: Duretek Inc.
    Inventor: Jun-Kyu Kim
  • Patent number: 8844443
    Abstract: Disclosed is spin-stabilized ammunition for use in grooved or smooth bore handheld firearms with calibers up to 60 mm. The projectile of the ammunition features a body in the shape of a truncated cone at the top of a cylinder with proportions of the cone length to the cylinder length varying between from one-to-six to one-to-three depending on the expected initial speed of the projectile after the ammunition has been discharged. A central longitudinal barrel extends through the projectile with a proportion of the entrance diameter and exit diameter of 1.38-to-one for expected discharge speeds near sound velocity or of 1.22-to-one for expected discharge of hypersonic velocities. Finally, nozzles within the projectile create a spinning motion around the projectile's axis, the nozzles being located between cavities for propellant charges.
    Type: Grant
    Filed: July 27, 2012
    Date of Patent: September 30, 2014
    Inventor: Lubomir Mihaylov Tomov
  • Patent number: 8604402
    Abstract: An afterbody device for a spacecraft fitted with at least one rocket engine at the rear of the craft includes at least one movable cover element designed to take a first position, masking and reducing the vehicle's rear drag, where it prolongs the vehicle's fuselage around at least one part of a rocket engine nozzle of the vehicle and extends beyond the rear of the vehicle's fuselage, and to take a second position fully deployed, increasing the vehicle's aerodynamic drag.
    Type: Grant
    Filed: November 21, 2008
    Date of Patent: December 10, 2013
    Assignee: Astrium SAS
    Inventor: Marco Prampolini
  • Patent number: 8487227
    Abstract: A base cone for a projectile including: a cone member being movable between a retracted position and an extended deployed position, the deployed position being longer in an axial direction than the refracted position; a member adapted to connect the cone member to a trailing portion of the projectile; and a release mechanism for releasing the cone member from the refracted position to the extended deployed position.
    Type: Grant
    Filed: November 3, 2010
    Date of Patent: July 16, 2013
    Assignee: Omnitek Partners LLC
    Inventors: Jahangir S. Rastegar, Richard T. Murray
  • Patent number: 8453572
    Abstract: A gun fired projectile includes a rocket motor housing including a pressure chamber and an exhaust nozzle. A plurality of propellant cells are positioned within the pressure chamber. The rocket motor propellant is mechanically supported during the severe gun fire event. This support may take several forms, each of which is discussed herein. The projectile further includes a support structure including one or more supports: wherein each of the one or more supports is engaged with the rocket motor housing. Each of the one or more supports is engaged with one propellant cell of the plurality of propellant cells, and each of the one or more supports suspends an individual propellant cell from the remainder of the plurality of propellant cells. All of these approaches provide the opportunity to tailor the performance of the rocket motor by combining a combination of propellant formulations and geometries to optimize the projectile performance.
    Type: Grant
    Filed: July 15, 2010
    Date of Patent: June 4, 2013
    Assignee: Raytheon Company
    Inventors: Richard Dryer, Chris E. Geswender
  • 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: 8415598
    Abstract: A stabilizing fin deployment apparatus may include a base assembly for attachment to the rear end of a projectile. The base assembly may include a base, a spacer, a fin mount, a gas cavity and an opening that extends from the rear end of the base to the gas cavity. A retention nut may engage the base and secure the fin mount and spacer to the base. A retention plug may be disposed in the opening in the base assembly. The retention plug may include at least one gas conduit between an outer surface of the retention plug and the gas cavity. A retention bolt may extend through the retention plug and may be fixed to the base. A plurality of fins hubs may be rotatably fixed to the base. A plurality of fins may be translatably connected to the fin hubs. When deployed, the fin hubs may rotate forward and the fins may translate outward far into the airstream.
    Type: Grant
    Filed: December 20, 2010
    Date of Patent: April 9, 2013
    Assignee: The United States of America as Represented by the Secretary of the Army
    Inventors: Robert Terhune, Michael Hollis
  • Patent number: 8312813
    Abstract: A deployable fairing is driven off of high-pressure gun gases to reduce aerodynamic drag and extend the range of the artillery shell. An artillery shell is provided with a fabric fairing and a piston attached thereto in a rear section of the shell in a stowed state and a chamber. During launch high-pressure gun gasses are captured and stored in the chamber. Once the shell clears the end of the artillery tube, the pressure aft of the shell drops from the high pressure inside the tube to atmospheric pressure outside the tube. The high pressure gun gasses stored in the chamber act over the top surface of the piston to drive the piston aft against the much lower pressure behind the projectile to deploy the fabric fairing attached thereto to reduce the base area of the projectile creating or extending the boat-tail of the shell, hence reduce aerodynamic drag. The aft driven piston engages a locking mechanism that locks the piston in a deployed position.
    Type: Grant
    Filed: July 30, 2010
    Date of Patent: November 20, 2012
    Assignees: Raytheon Company, General Dynamics Ordnance and Tactical Systems
    Inventors: Brian K. McDermott, Kevin R. Greenwood, James D. Streeter
  • Patent number: 8193476
    Abstract: A solid-fuel pellet thrust and control actuation system (PT-CAS) provides command authority for maneuvering flight vehicles over subsonic and supersonic speeds and within the atmosphere and exo-atmosphere. The PT-CAS includes a chamber or solid-fuel pellets that are ignited to expel gas through a throat. The expelled gas is directed at supersonic vehicle speeds in atmosphere to a cavity between an aero control surface and the airframe to pressurize the cavity and deploy the surface or at subsonic speeds in atmosphere or any speed in exo-atmosphere allowed to flow out a through-hole in the surface where the throat and through-hole provide a virtual converging/diverging nozzle to produce a supersonic divert thrust. A pellet and control actuation system (P-CAS) without the through-hole provides command authority at supersonic speeds in atmosphere.
    Type: Grant
    Filed: September 3, 2008
    Date of Patent: June 5, 2012
    Assignee: Raytheon Company
    Inventors: Thomas A. Olden, Robert Cavalleri, Lloyd E. Kinsey, Jr.
  • Patent number: 8097838
    Abstract: The invention relates to a method for increasing the range of shells (1, 8, 13) charged with an explosive substance and other types of shell, which function as carriers of the one or other type of active payload. The method according to the invention thus provides an opportunity for increasing the range of fire of most types of artillery piece by increasing the muzzle velocity and the gliding flight capability of shells or projectiles fired from them, but without the need to increase the energy content in the propellant charges utilized for firing the shells or the projectiles concerned. The novelty proposed in accordance with the invention instead represents a radical modification to the design of the shell (1, 8, 13) utilized in conjunction therewith. The invention also relates to a shell charged with an explosive substance or provided with some other active payload which has been given a long range.
    Type: Grant
    Filed: September 14, 2006
    Date of Patent: January 17, 2012
    Assignee: BAE Systems Bofors AB
    Inventors: Torsten Rönn, Thomas Pettersson, Ulf Heiche
  • Patent number: 7997205
    Abstract: A projectile may include a base drag reduction fairing preform adapted to be plastically deformed into a base drag reduction fairing after the projectile is launched from a gun barrel.
    Type: Grant
    Filed: May 8, 2009
    Date of Patent: August 16, 2011
    Assignee: Raytheon Company
    Inventors: Kevin R. Greenwood, James D. Streeter, Jeremy C. Danforth, Timothy A. Yoder
  • Publication number: 20110061556
    Abstract: A projectile in accordance with one embodiment includes a combustible material structure (e.g., a base burn assembly or rocket motor assembly) having a longitudinal bore extending therethrough, wherein the longitudinal bore defines a gas outlet port on a first end of the combustible material structure. An igniter is provided adjacent to a second end of the longitudinal bore. A clog inhibitor provided within the longitudinal bore, the clog inhibitor including a plurality of openings. The openings are be selected to block extraneous portions of the combustible material structure that are greater than a predetermined size.
    Type: Application
    Filed: September 15, 2009
    Publication date: March 17, 2011
    Inventor: William S. Peterson
  • Patent number: 7905178
    Abstract: Methods and apparatus according to various aspects of the present invention comprise a propelling system for propelling projectiles with variable velocity. In one embodiment, a cartridge comprises a cartridge case, the propelling system, and the projectile attached to the cartridge case.
    Type: Grant
    Filed: January 10, 2005
    Date of Patent: March 15, 2011
    Assignee: Raytheon Company
    Inventors: Richard Dryer, Neal M Conrardy
  • Patent number: 7891298
    Abstract: A non-propulsive projectile and method of maneuvering the non-propulsive projectile. The non-propulsive projectile includes a divert system with a multiple of valves to maneuver the projectile in response to a control system.
    Type: Grant
    Filed: May 14, 2008
    Date of Patent: February 22, 2011
    Assignee: Pratt & Whitney Rocketdyne, Inc.
    Inventors: Alan B. Minick, Stephen Alan Hobart, Frederick Widman, Timothy S. Kokan, Frederic H. Massey
  • Patent number: 7849800
    Abstract: A hybrid spin/fin stabilized projectile. The novel projectile includes a body, a first mechanism for spin stabilizing the body during a first mode, and a second mechanism for fin stabilizing the body during a second mode. In an illustrative embodiment, the projectile includes a rifling band adapted to engage with rifling in a gun during gun launch to impart a spin rate compatible with spin stabilization to the projectile, and a plurality of folding fins attached to an aft end of the body. A fin locking mechanism locks the fins in an undeployed position during the first mode and unlocks to deploy the fins at a predetermined time to switch the projectile to fin stabilization during the second mode. The projectile also includes a mechanism for reducing the spin of the projectile to a rate compatible with guided flight during the second mode.
    Type: Grant
    Filed: June 24, 2007
    Date of Patent: December 14, 2010
    Assignee: Raytheon Company
    Inventors: Andrew J. Hinsdale, Richard Dryer
  • Patent number: 7823510
    Abstract: A projectile and method of extending the range of the projectile. The projectile includes a storage tank operable to release a working fluid through an exhaust manifold to at least partially fill a wake aft of the projectile during projectile flight.
    Type: Grant
    Filed: May 14, 2008
    Date of Patent: November 2, 2010
    Assignee: Pratt & Whitney Rocketdyne, Inc.
    Inventors: Stephen Alan Hobart, Timothy S. Kokan, Alan B. Minick, Frederic H. Massey
  • Patent number: 7816635
    Abstract: A stowable wing structure incorporates a wing having a span equal to a fuselage length and movable from a stowed position longitudinally aligned with the fuselage to a deployed position perpendicular to the fuselage. A pivot offset laterally from a centerline of the fuselage and aft from a symmetry point on the centerline with a corresponding offset forward toward the leading edge from a chord centerpoint on the wing allows rotation of the wing from the stowed position to the deployed position with the rotation resulting in an aft position of the chord center point relative to the fuselage symmetry point.
    Type: Grant
    Filed: November 2, 2007
    Date of Patent: October 19, 2010
    Assignee: The Boeing Company
    Inventor: Lawrence E. Fink
  • Patent number: 7802520
    Abstract: A modified cartridge assembly including a projectile having a gas generator proximate its aft end. The projectile includes an aft closure having a cavity filled with gas generating material. The gas generating material is ignited around the time the projectile exits the weapon's muzzle. The gas generating material then burns while the projectile is in flight, spewing pressurized gas into the wake region immediately behind the projectile. The pressurized gas reduces the projectile's base drag.
    Type: Grant
    Filed: July 25, 2007
    Date of Patent: September 28, 2010
    Assignee: Martin Electronics
    Inventor: Bruce G. Van Stratum
  • Patent number: 7728265
    Abstract: A MEMS type flow actuated out-of-plane flap apparatus includes a substrate defining a plane; a duct attached to the substrate, the duct and the substrate defining a fluid flow channel; and a rotatable flap having a flow receiving portion and an extension portion. The flow receiving portion being disposed in the fluid flow channel where, in an actuated position of the flap, a fluid flow against the flow receiving portion causes rotation of the flap and movement of the extension portion out of the plane of the substrate.
    Type: Grant
    Filed: March 26, 2007
    Date of Patent: June 1, 2010
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventors: Michael A. Deeds, David Herman
  • Patent number: 7690305
    Abstract: The invention relates to an increment charge (4) to be placed around a tail shaft of a fin-stabilized mortar projectile (1), the increment charge (4) having a centrally located space for the tail shaft and a mounting opening in the space for mounting the increment charge (4). On the opposite side of the increment charge (4) there is provided a protrusion that fits into the mounting opening of an adjacent increment charge (4) for locking them in relation to each other.
    Type: Grant
    Filed: November 2, 2004
    Date of Patent: April 6, 2010
    Assignee: Patria Vammas Oy
    Inventors: Timo Pekka Harjula, Ville-Pekka Pesonen
  • Patent number: 7578238
    Abstract: A projectile may be used in a boat tail or base bleed configuration. The projectile includes a warhead casing having a nose end and a base end; a payload disposed in the warhead casing; a motor body attached to the base end of the warhead casing and having an igniter disposed therein; a base closure attached to the motor body, an exterior surface of the base closure being tapered to form a boat tail, the base closure and the motor body defining an interior volume; a propellant disposed in the interior volume, the propellant being used for base bleed operation; and a converter attached to the base closure and extending into the interior volume.
    Type: Grant
    Filed: January 12, 2006
    Date of Patent: August 25, 2009
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventor: Shahram Dabiri
  • Patent number: 7360355
    Abstract: A long range artillery shell having a rocket motor which comprises a combustion chamber (shown filled with solid propellant 9, burn inhibitor 10, igniter material 13 and propellant support 11,12) which has at one end a plenum chamber 8 and a rocket nozzle 14 for venting the plenum chamber 8. The propellant 9 is arranged in an end-burn configuration and housed within the combustion chamber and the propellant support 11,12 is located between the propellant 9 and the plenum chamber 8 and is capable of preventing entry of unburnt propellant into the plenum chamber 8 while permitting, in use, the substantially unhindered transfer of propellant combustion products to the plenum chamber 8.
    Type: Grant
    Filed: June 7, 1996
    Date of Patent: April 22, 2008
    Assignee: QinetiQ Limited
    Inventor: Guillaume M. H. J. L. Gadiot
  • Patent number: 7267298
    Abstract: At very low apparatus expenditure, namely with a canard system which is adjustable in a single-axis mode, it is possible to achieve a spatially two-dimensional trajectory correction in respect of the artillery ammunition which in itself is unguided, with the additional degree of freedom in respect of trajectory extension and thus an extraordinary increase in the precision of delivery in relation to the predetermined target point.
    Type: Grant
    Filed: July 11, 2002
    Date of Patent: September 11, 2007
    Assignee: Diehl Munitionssysteme GmbH & Co. KG
    Inventor: Jürgen Leininger
  • Patent number: 7255044
    Abstract: A method for enhancing an aerodynamic performance of an unmanned projectile. The method including at least one of the following: (a) morphing a cross-sectional shape of the projectile after launch thereof; (b) morphing a longitudinal shape of the projectile after launch thereof; (c) bleeding a fluid at a base of the projectile during flight thereof: (d) varying a base cone angle of the projectile as a function of speed thereof; (e) deploying at least one wing from a body of the projectile after launch thereof; and (f) deploying a fin from the body of the projectile after launch thereof.
    Type: Grant
    Filed: July 11, 2005
    Date of Patent: August 14, 2007
    Assignee: Omnitek Partners, LLC
    Inventors: Jahangir S. Rastegar, Richard B. Pelz
  • Patent number: 7185846
    Abstract: Asymmetrical Control Surface System for Tube-Launched Air Vehicles places one control surface, such as a wing or a horizontal tail, above horizontal midplane axis of an air vehicle, such as a tube-launched missile, and the opposing control surface below the midplane axis. Such asymmetrical arrangement of the control surfaces increases the lift and maneuverability of the air vehicle during flight. For stowage inside the tube prior to launch, each control surface slides into its corresponding slot in the body of the vehicle, making the entire control system compact.
    Type: Grant
    Filed: March 6, 2006
    Date of Patent: March 6, 2007
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventors: David A. Bittle, Gary T. Jimmerson, Julian L. Cothran
  • Patent number: 7163176
    Abstract: A 2-D correction system uses intermittent deployment of aerodynamic surfaces to control a spin or fin stabilized projectile in flight; correcting both crossrange and downrange impact errors. Intermittent surface deployment develops rotational moments, which create body lift that nudge the projectile in two-dimensions to correct the projectile in its ballistic trajectory. In low spin rate projectiles (“fin stabilized”), the rotational moment directly produces the body lift that moves the projectile. In high spin rate projectiles (“spin stabilized”), the rotational moment creates a much larger orthogonal precession that in turn produces the body lift that moves the projectile. The aerodynamic surfaces are suitably deployed over multiple partial roll cycles at precise on (deployed) and off (stowed) positions in the cycle to nudge the projectile up or down range or left or right cross range until the desired ballistic trajectory is restored.
    Type: Grant
    Filed: January 15, 2004
    Date of Patent: January 16, 2007
    Assignee: Raytheon Company
    Inventors: Chris E. Geswender, Andrew J. Hinsdale, George A. Blaha, Richard Dryer
  • Patent number: 6923123
    Abstract: A method for enhancing an aerodynamic performance of an unmanned projectile. The method including at least one of the following: (a) morphing a cross-sectional shape of the projectile after launch thereof; (b) morphing a longitudinal shape of the projectile after launch thereof; (c) bleeding a fluid at a base of the projectile during flight thereof: (d) varying a base cone angle of the projectile as a function of speed thereof; (e) deploying at least one wing from a body of the projectile after launch thereof; and (f) deploying a fin from the body of the projectile after launch thereof.
    Type: Grant
    Filed: April 26, 2004
    Date of Patent: August 2, 2005
    Assignee: Omnitek Partners LLC
    Inventors: Jahangir S. Rastegar, Richard B. Pelz
  • Patent number: 6862996
    Abstract: An ammunition system for a rapid fire gun. The ammunition system includes a bullet having a tip that is stored in a retracted position and during flight is deployed create an aerodynamic shape. Another aspect of the ammunition system is that the bullet has a cylindrical body having a first length in storage and a second longer length after ignition of the propellant.
    Type: Grant
    Filed: October 15, 2002
    Date of Patent: March 8, 2005
    Inventor: Mark Key
  • Patent number: 6748871
    Abstract: The present invention relates to an artillery missile (1) intended for firing on a ballistic trajectory, with gliding characteristics which can be put into effect, after it has reached the summit of this trajectory, to increase the maximum range of the missile.
    Type: Grant
    Filed: July 29, 2003
    Date of Patent: June 15, 2004
    Assignee: Bofors Defence AB
    Inventor: Ulf Hellman
  • Patent number: 6543364
    Abstract: A launchable, multi-sensory distraction grenade including a base, three outer grenade walls arranged together on the base to pivotally move from a first position, to a second position, extending outward laterally from the base in different directions, to form lateral legs to support the base after it lands on a surface, a plurality of spring fingers retaining the walls in contact with the base, at least two distraction devices mounted in the grenade for initiating an extended period of personnel distraction in the area of the grenade with its walls in their second position, a distraction device ignitor and safety trigger at least a portion of which is external the casing for controlling the ignition means.
    Type: Grant
    Filed: February 14, 2002
    Date of Patent: April 8, 2003
    Assignee: Scientific Applications & Research Associates
    Inventors: James A. Wes, Genyvieve A. Donne, John P. Deering, Jay B. Cleckler, Michael W. Zintl
  • Patent number: 6435097
    Abstract: A low cost protective cap that will offer protection of deployable fins for full bore artillery projectiles. A form fitting, composite cap that disintegrates on muzzle exit acts as a protective measure. The cap interfaces with the projectile obturator to form a temporary seal against hot gun gasses. The composition and thickness of the cap allows gas infiltration into the cap material and essentially instant cap degradation upon shot exit.
    Type: Grant
    Filed: April 9, 2001
    Date of Patent: August 20, 2002
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventors: James M. Garner, James M. Bender, Peter Dehmer, Melissa Klusewitz
  • Patent number: 6405653
    Abstract: A supercavitating underwater projectile adapted to be fired from a gun or the like, comprising a front end or nose portion and a rear end portion. An auxiliary rocket motor is disposed within the rear end portion of the projectile for providing additional thrust after the projectile has been fired. Vents are disposed within the projectile and are in communication with the rocket motor and the exterior of the projectile for venting some of the combustion gases from the rocket motor to the exterior of the projectile near the nose portion thereof to increase the size of the cavitation bubble formed as the projectile travels through the water and thereby reduce hydrodynamic drag on the projectile.
    Type: Grant
    Filed: October 26, 2000
    Date of Patent: June 18, 2002
    Assignee: Atlantic Research Corporation
    Inventor: Hermann L Miskelly
  • Patent number: 6352218
    Abstract: The present invention relates to a method and a device designed for use with such shells (1) that are equipped with a base-bleed unit (8) for extended range and which during the first phase of their trajectory are spin-stabilised but which in the subsequent phase are subjected to spin deceleration by fins (9-13) that deploy from the shell body and take over the stabilising function. More exactly the present invention is a method and a device that enables the said shells (1) to achieve an effective and functional deployment of the fins (9-13) at the desired point in time with simultaneous ejection of the base-bleed unit (8) which at this point in time either no longer performs any useful function since it is burnt-out and solely constitutes a dead-weight or its function is no longer required.
    Type: Grant
    Filed: November 2, 1999
    Date of Patent: March 5, 2002
    Assignee: Bofors Defence Aktiebolag
    Inventors: Ulf Holmqvist, Ulf Hellman, Stig Johnsson
  • Patent number: 6336609
    Abstract: The present invention relates to a method and a device relating to shells with deployable fins and which are fired from large caliber guns into ballistic trajectories, for preventing the propellant gas pressure in the barrel during firing from directly or indirectly deforming the said fins (9-13). The type of fins that the present invention primarily relates to are those that are deployed on command in order to fin-stabilize the shell. Usually such fins are protected prior to deployment by an ejectable fin protector (19). To prevent this fin protector from being deformed and consequently impeding fin deployment or degrading fin functionality, the present invention proposes that all unoccupied space inside the said fin protector be filled with an inert, noncombustible, non-glutinous substance (32) of low compressibility and very low inherent strength.
    Type: Grant
    Filed: November 2, 1999
    Date of Patent: January 8, 2002
    Assignee: Bofors Defence Aktiebolag
    Inventor: Stig Johnsson
  • Patent number: 6305288
    Abstract: The present invention relates to a propellant charge module for artillery guns, of the type which is usually referred to by the term “modular charges” (1). A special feature of this type is that, in an otherwise empty pyrophoric relay tube (10) arranged axially in the longitudinal direction of the charge, it has a firing charge which is made up of a plurality of successive powder rings (14), the different ring-shaped parts of this firing charge having distancing members (16) which are directed towards each other and give rise to narrow ignition gaps (18) between them.
    Type: Grant
    Filed: March 14, 2000
    Date of Patent: October 23, 2001
    Assignee: Bofors Defence Aktiebolag
    Inventors: Neile Nilsson, Larseric Larsson, Anders Hafstrand
  • Patent number: 6297486
    Abstract: A device for reducing base drag on cylindrical rear truncated objects moving in a fluid, caused by the shedding of vortices at the base of the object. The device consists of ring shaped winglets attached to the rear of the object which may be sub-divided into a plurality of hinged partial winglets. The parameters of distance of winglet from cylinder shaped object, winglet circumference, angle, profile and chord length may be varied automatically for optimum drag-reducing capability.
    Type: Grant
    Filed: October 8, 1997
    Date of Patent: October 2, 2001
    Assignee: Rafael Armament Development Authority Ltd.
    Inventors: Hanan Rom, Zvi Weinberg
  • Patent number: 6213023
    Abstract: Base bleed unit comprising a surrounding housing (1) surrounding at least one mass flow generating gun powder charge (7), and having at least one outlet hole (6, 6′) extending through a rear wall (3) of the housing (1), in which also at least one igniter charge (4) is arranged. According to the invention, an internal and the rear wall (3) adjacent portion of the mass flow generating gun powder charge (7) is arranged abutting a preferably substantially conically narrowing supporting wall surface extending from the rear wall (3). The preferably substantially conically narrowing supporting wall surface may comprise a centrally located member (5), extending from and integrated with the internal surface of the rear wall (3) of the base bleed unit, arranged to act as a supporting surface with its external surface, or with such a member attached to said internal surface. The preferably substantially conically narrowing wall surface may also comprise a collar shaped member.
    Type: Grant
    Filed: June 14, 1999
    Date of Patent: April 10, 2001
    Inventor: Nils-Erik Gunners
  • Patent number: 6158349
    Abstract: A gas generator adapted to be disposed in a rear part of a projectile for increasing the flight range thereof, includes a housing defining a combustion chamber and having a bottom and a longitudinal axis; a fuel accommodated in the combustion chamber; an outlet opening provided in the housing bottom for passage of combustion gases generated in the combustion chamber upon combustion of the fuel; and a plastic fuel-supporting tube extending axially from the outlet opening into the combustion chamber. The plastic material of the fuel-supporting tube is selected such that upon combustion of the fuel aided by a gas pressure of a projectile propellant and by a drag effect, the fuel-supporting tube is deformed and driven out of the outlet opening.
    Type: Grant
    Filed: November 20, 1998
    Date of Patent: December 12, 2000
    Assignee: Rheinmetall W & M GmbH
    Inventors: Ernst-Wilhelm Altenau, Siegmar Fischer, Gunter Sikorski, Ulf Hahn
  • Patent number: 5886289
    Abstract: A long range artillery shell (1) comprising rocket propellant material (10), a rocket motor nozzle (14) and base bleed propellant material (12). Ignition of the rocket propellant material (10) is delayed until the base bleed propellant material (12) has substantially finished burning. The base bleed propellant material (12) may be housed in the same chamber and behind the rocket propellant material (10) in order to provide support to the rocket propellant material (10) during launch. The two propellant materials (10, 12) may be separated by a thermal ignition barrier (18) to prevent premature rocket ignition.
    Type: Grant
    Filed: July 16, 1993
    Date of Patent: March 23, 1999
    Assignee: The Secretary of State for Defence in Her Britannic Majesty's Government of the United Kingdom of Great Britain and Northern Ireland
    Inventors: Robert J. Nixon, Martin J. Lewin, Terence L. Spellward
  • Patent number: 5798478
    Abstract: An ammunition projectile of enhanced flight characteristics, having a boat tail portion and including a circular land provided on the rear surface of the boat tail portion and concentric with the longitudinal centerline of the projectile, the land having a circular concave wall extending from the flat rear face of the boat tail portion to a circular flat surface of the land. Among other things, the projectile exhibits a lesser rate of velocity deceleration along its flight path to a target than like projectiles that do not include the land.
    Type: Grant
    Filed: April 16, 1997
    Date of Patent: August 25, 1998
    Assignee: Cove Corporation
    Inventor: Harold F. Beal
  • Patent number: 5656792
    Abstract: A ballistic projectile including a subcaliber-sized penetrator which is coaxially carried in the casing of the projectile, and in which the penetrator additionally carries an explosive charge. The projectile possesses a proximity fuze at its tip which electrically triggers a penetrator-propellent charge which is arranged in the projectile base and which fills the volume of the projectile base, which accelerates the penetrator through a therebetween arranged propellant base, and in which the penetrator additionally possesses an impact detonator.
    Type: Grant
    Filed: September 16, 1996
    Date of Patent: August 12, 1997
    Assignee: Diehl GmbH & Co.
    Inventors: Max Rentzsch, Manfred Schildknecht, Hans Strauss, Rainer Himmert
  • Patent number: 5639985
    Abstract: To mitigate groove drag in a kinetic energy projectile, an intumescent maial is inserted in the grooves wherein the material will expand to fill the grooves once the sabot has been discarded. The groove material inhibits aerodynamic recirculation that can occur in the grooves, fills the groove and keeps out freestream gasses. The expanding groove material occupies the space previously filled by the sabot tooth. The groove-filling material expands quickly, because the flight of the projectile is typically on the order of one to two seconds. The groove filling material may also be an elastic material.
    Type: Grant
    Filed: September 4, 1996
    Date of Patent: June 17, 1997
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventors: James M. Garner, Harris L. Edge
  • Patent number: 5578783
    Abstract: A method for accelerating projectiles comprises introducing the projectile into an accelerator barrel, feeding a combustible gas mixture into said barrel and igniting said mixture to accelerate the projectile, and is characterized in that a fluid is stored in the projectile and is ejected therefrom into the space between the projectile and the barrel. Suitable accelerator systems are disclosed.
    Type: Grant
    Filed: December 19, 1994
    Date of Patent: November 26, 1996
    Assignee: State of Israel, Ministry of Defence, Rafael Armaments Development Authority
    Inventor: Julius Brandeis
  • Patent number: 5353711
    Abstract: The disclosure is of an artillery projectile including a projectile body taining, among other things, a rocket motor at the front of the projectile and coupled to nozzles in the body of the projectile through which burning propellant gases flow.
    Type: Grant
    Filed: October 4, 1993
    Date of Patent: October 11, 1994
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventors: Richard D. Botticelli, Frank A. Brody, Francis Ottaviano
  • Patent number: 5141175
    Abstract: A device having pop-out wings and a guidance and control system is detachably mounted on a munition such as a bomb and is used to extend the range capability of the munition. Prior to launch, the wings are folded together. The control system is contained within a saddle portion of the device, and when the munition is released from the aircraft, the wings are caused to pop out to their flying position. The saddle is secured to the munition through a single bolt. Controllable flaps are installed along the trailing edges of the wings, such flaps being operated to control the pitch and roll angle of the munition. When the target area is reached, the device is jettisoned by detonating a charge which shears the securing bolt, thereby permitting the device to pivot rearwardly and separate from the munition.
    Type: Grant
    Filed: March 22, 1991
    Date of Patent: August 25, 1992
    Inventor: Gordon L. Harris
  • Patent number: 5056436
    Abstract: The invention is directed to a solid, pyrotechnic composition as a base-bleed composition for reducing the base-drag of non-self-propelled projectiles. The composition comprises a oxygenated hydrocarbon component and an oxidizing agent component.
    Type: Grant
    Filed: October 3, 1988
    Date of Patent: October 15, 1991
    Assignee: Loral Aerospace Corp.
    Inventor: Robert W. Greene
  • Patent number: 4964341
    Abstract: An extendible probe projectile and an extendible probe assembly therefor, in which the extendible probe reduces drag on the projectile in its extended position and is moved to its extended locked drag-reducing position by ram air action which is converted into a forwardly acting force on the probe during forward motion of the projectile.
    Type: Grant
    Filed: August 21, 1989
    Date of Patent: October 23, 1990
    Assignee: AAI Corporation
    Inventor: John R. Hebert
  • Patent number: 4930422
    Abstract: A device for the impervious sealing of a structure, for example a munitions compartment of a rocket, is disclosed. This device comprises an elastic shaped section inside which the edge of the structure and rim of a lid are imperviously embedded. This device further has means for thrusting the lid outwards from the structure. This thrust pushes the rim and/or the edge out of the shaped section through the deformation of this elastic shaped section, and causes the total expulsion of lid. When the device is fitted into a rocket, the moving away of the rim modifies the aerodynamic drag coefficient (Cx) of the rocket. This difference in Cx causes the total expulsion of the lid and thus causes the structure to be opened.
    Type: Grant
    Filed: May 24, 1988
    Date of Patent: June 5, 1990
    Assignee: Thomson-Brandt Armements
    Inventors: Rene Thouron, Jean-Francois Denis