US3349708A - Rocket projectile - Google Patents

Rocket projectile Download PDF

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Publication number
US3349708A
US3349708A US513461A US51346165A US3349708A US 3349708 A US3349708 A US 3349708A US 513461 A US513461 A US 513461A US 51346165 A US51346165 A US 51346165A US 3349708 A US3349708 A US 3349708A
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United States
Prior art keywords
projectile
nozzle
solid fuel
rocket
fuel
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Expired - Lifetime
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US513461A
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English (en)
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Paget Win Withers
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Individual
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/32—Constructional parts; Details not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
    • F02K9/86—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using nozzle throats of adjustable cross- section
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B14/00—Projectiles or missiles characterised by arrangements for guiding or sealing them inside barrels, or for lubricating or cleaning barrels
    • F42B14/06—Sub-calibre projectiles having sabots; Sabots therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles

Definitions

  • This invention relates to a projectile launched by a firearm, such as for example a rifle, a machinegun, a submachinegun, a cannon, a howitzer, etc.
  • a firearm such as for example a rifle, a machinegun, a submachinegun, a cannon, a howitzer, etc.
  • the principal object of the present invention is to 3,349,738 Patented Oct. 31, 1967 equip a projectile launched by a firearm with an additional propulsion device which acts after exit from the arm so that the initial velocity and kinetic energy-i.e., at the muzzle of the arm-do not decrease along the trajectory as with the known projectile, but on the contrary increase, or at least remain approximately constant during at least a portion of the trajectory.
  • the additional propulsion device is constituted by a motor of the solid fuel rocket type capable of functioning at the commencement of the trajectory for a variable, but generally short, duration; in other words, the body of the projectile contains a solid fuel with high combustion velocity, which may be constituted by any known fuel which, when once ignited, burns and yields gases under pressure which are expelled by way of a calibrated exhaust nozzle located at the rear of the projectile.
  • the ignition of the solid fuel contained in the projectile is preferably produced by the combustion gases of the powder which launches the projectile when the latter is still in the bore of the arm.
  • the correct ignition of the fuel contained in the projectile is effected by providing in the projectile, in addition to the nozzle, at least one additional conduit which temporarily permits passage of the gases originating from the combustion of the propulsive charge; this channel, which is open during the period of acceleration, is closed as soon as the projectile leaves the muzzle of the arm.
  • the additional conduit is of annular conformation and surrounds the body of the nozzle to issue behind a plate provided with passage orifices, formed for example by free spaces between radial arms and giving access to the rear face of the solid fuel, during the acceleration period, blockage of the channel being obtained by the plate coming into abutment against a shoulder around the said body of the nozzle, th-us constraining the combustion gases of the fuel to exit through the nozzle.
  • two longitudinal conduits are provided placed laterally to the body of the nozzle and terminating behind a plate integral with the said body, in a chamber behind the solid fuel, blockage of the conduits being effected by the said plate coming into abutment against a shoulder around the nozzle.
  • the body of the projectile containing the solid fuel is closed at the rear by a plug in the form of a cup of which the base is pierced with orifices closed by valves subject to a plate spring maintained by a disc carrying the nozzle screwed into the cup.
  • the additional propulsion device may be applied to any projectilesuch for example as an anti-tank projectile or shell of normal weight; the additional thrust provided by the rocket motor may be chosen to augment the velocity of the projectile after the latter has left the bore of thearm; now, since the kinetic energy is a function of the square of the velocity, an increase in the velocity during the trajectory gives the projectile a greatly increased kinetic energy, which may actually be sufliciently high to produce melting of a quantity of steel equal to several times the weight of the projectile, and thereby to render the use of armour difficult if not impossible, as its thickness would have to be too great in order to provide adequate protection.
  • any projectile such for example as an anti-tank projectile or shell of normal weight
  • the additional thrust provided by the rocket motor may be chosen to augment the velocity of the projectile after the latter has left the bore of thearm; now, since the kinetic energy is a function of the square of the velocity, an increase in the velocity during the trajectory gives the projectile a greatly increased kinetic energy, which may actually be
  • Another equally important application of the invention is to a small calibre projectile such as a rifle or machinegun bullet or the like.
  • the additional propulsion device according to the invention since by virtue of the additional propulsion device according to the invention the velocity at the place of impact can be maintained equal to the velocity on exit from the muzzle, it is possible to reduce the weight of the projectile and the charge for launching it; in other words, the device according to the invention makes it possible, for ordinary ranges, to produce a cartridge having, for example, approximately half the weight of a normal cartridge giving the same kinetic energy on impact. This has the advantage of greatly reducing the recoil, which facilitates the firing precision of lightweight or medium weight automatic arms.
  • FIGURE 1 is an enlarged view in longitudinal axial section of a small calibre projectile constructed according to the invention.
  • FIGURE 2 is an enlarged view in longitudinal axial section of another embodiment of a small calibre projectile showing a nozzle with a hole plate forming a valve
  • FIGURE 3 is a view in elevation of the front end of the nozzle.
  • FIGURE 4 is a view in longitudinal axial section of a projectile of larger calibre
  • FIGURE 5 is a section view taken along the line VV of FIGURE 4.
  • FIGURE 6 is a view in longitudinal axial section of a large calibre projectile
  • FIGURE 7 is a sectional view taken along the line VIIVII of FIGURE 6.
  • FIGURE 8 is a view in longitudinal axial section of another embodiment of a large calibre projectile.
  • FIGURE 1 clearly shows a projectile comprising a metallic casing 1, at the front of which a core 2, of lead for example, is placed; depending upon the object to be attained, this core may of course be of another material, such as steel.
  • the casing 1 also contains the solid fuel 3 of any known nature, the rear of which possesses a cavity 5 having the form of a portion of a sphere, for example; this cavity is provided to give a suitable combustion surface.
  • the projectile is closed by the body 4, in which the nozzle 4a is made. This body 4 is maintained in position by the sleeve 6. On firing, the burning gases originating from the combustion of the launching charge ignite the solid fuel 3 of the projectile, which is still in the bore of the gun.
  • the fuel commences to burn, and the gases which originate from this combustion exit through the nozzle 4a at a pressure slightly greater than the pressure in the bore.
  • the projectile has left the muzzle of the arm, it is subject to the thrust of the gases during the combustion of the fuel 3, which has a duration of approximately 0.3 to 0.5 second.
  • the duration-that is to say, the velocity-of combustion depends upon the combustion pressure, which in turn depends upon the cross-section of the passage at the throat position of the nozzle.
  • FIGURE 2 shows a projectile of which the metallic casing 8 again contains a metallic core 9 and a solid fuel 10.
  • the body 11 in which the nozzle 11a is made is secured against the rear of the fuel; this body is provided in front with a plate 12 which, as FIGURE 3 shows, has radial arms 13 for centering in the casing 8; hollow spaces 14 are made between these arms.
  • the combustion gases of the launching charge maintain the body of the nozzle 11a against the fuel 10, which they ignite at its periphery by passing through the cylindrical conduit 15 and the holes or cavities 14 between the arms 13.
  • FIGURE 4 shows an embodiment of the projectile of larger calibre for a rifled arm; this projectile is constituted by a hollow body 17 containing the solid fuel 18,
  • the plug 19 is screwed into the base of the projectile and possesses a central cavity 19a in which the body 20 provided with the nozzle 20a is housed; this body is maintained in position by the two diametrally opposite round-head pins 21 so long as the projectile is in the bore.
  • the combustion gases of the launching or firing charge pass through the longitudinal conduits 20d provided diametrically opposite laterally of the body of the nozzle and continuing as far as the rear of the plate 20b which terminates in front the body 20 containing the nozzle 20a.
  • conduits 20d issue into the channel 20c which communicates with the rear face 18a of the fuel 18 so that the combustion gases of the firing charge are made to ignite the said rear face 18a.
  • the plate 20b has a diameter slightly greater than that of the central cavity 19a housing the body 20.
  • FIGURES 6 and 7 illustrate a projectile according to the invention, specially devised for piercing armour for instance, a piercing or antitank shell.
  • the shell is constituted by a casing 22 containing the solid fuel 23, which assumes the form of a cylinder resting upon the ring 23b and having a longitudinal central cavity 23a.
  • a metallic head 24 is screwed onto the front of the casing 22 and has a ring 25 to guide and seal the projectile in the bore; a similar ring 26 is also provided at the rear.
  • the rings 25 and 26 are in two parts, as
  • FIGURE 7 clearly shows, and become separated from the projectile after the latter has left the bore of the arm.
  • Orifices 26a are provided in the ring 26 only, in order to make the space around the casing 22 communicate with the bore, so that the same pressure is established inside and outside the projectile; this makes it possible to keep the casing 22 thin.
  • a highly elongated cone 27, partly shown, is secured to the head 24; this is necessary at the high velocities involved.
  • This cone may be, for example, of a plastics material, possibly stiffened by glass fibres; the front end or summit of the cone, not shown, is preferably constituted by a tip of a sintered alloy of tungsten and molybdenum, in view of the intense heat which is produced at this point of origin on the shock wave.
  • the casing has a flange 22a for passage of the body 28, in which the nozzle 280 is made.
  • the body 28 which is terminated at the front by the plate 28a is maintained by the conical pin 26b provided on the interior face of the half-rings 26, which occupy the holes 28b located diametrally in the flange 22a and in the said body 28.
  • two longitudinal conduits 28 are made which continue as far as the rear of the plate 28a and issue into the chamber 28d which communicates, through the channel 28g, with the rear of the central cavity 23a.
  • a rod 29 passes through the head 24 and the longitudinal cavity 23a, so that its slightly tapered rear end 29a is located in the axis of the nozzle 28c; in front, this rod 29 has a screwthreaded portion 2% upon which a cap 290 is screwed by a greater or lesser amount in order to adjust the length of the rod; the pressure screw 30 permits the device to be fixed at the chosen length.
  • the tapered end 29a enters the nozzle 28c by a variable distance and reduces the passage cross-section at the throat of the nozzle to a variable extent.
  • the combustion pressure of the solid fuel 23 is modified so that the duration of combustion is also modified; it is possible to adjust this duration so that it corresponds to the time required by the projectile to travel the trajectory between the muzzle of the arm and impact.
  • the solid fuel 23 is of course subject to a strong compression during the acceleration in the bore of the arm, and it must therefore possess a high compressive strength; it may be constituted, for example, by a mixture of powdered aluminum, ammonium or potassium perchlorate, and an epoxy resin, possibly with a strong material such as glass fibre.
  • FIGURE 8 also shows, in part, another anti-tank shell constructed according tothe invention.
  • This shell comprises, as in the case of a known shell, a nose, not shown, having a metallic core 30 provided with a guiding and sealing ring 30a which maintains the pressure outside the casing equal to the pressure inside when the projectile is in the bore.
  • the casing 31 is screwed onto the core 30 and is thicker in front than at the rear of the projectile, since it is required to withstand the thrust of the parts located at the rear; this casing must also be sufficiently thick to withstand the pressure of the gases when the ring 30a has already left the bore of the arm; it contains the solid fuel of known type, arranged in a plurality of packets such as 31a possessing a central cavity 31b and each supported by a dome such as 32.
  • Each dome 32 which is of steel, has a cylindrical external part 320!
  • the end 3212 is a portion of a spherical surface, so that, due to the effect of the very great acceleration in the arm, the fuel produces a uniform force in the dome.
  • the packets of solid fuel are separated from one another by a passage-way such as 32d; they each commence burning from the free anterior face 322; from which the combustion proceeds and occurs over a surface which remains constant and approximately spherical; for a constant combustion pressure, the combustion velocity is uniform.
  • the plug 33 hollow in the center and continued by the cuplike cylindrical part 34, is screwed onto the rear of the casing 31; the base of the said cup is pierced with orifices 35 which can be contacted by the closure valves 36 which are subject to a conical plate spring 37 maintained by the disc 38 with flange 38a which is screwed into the cup 34; this disc 38 is continued to form the nozzle 39.
  • the volume of the central cavity determined by the part 320 is kept small, in conformity with the passage cross-section towards the nozzle, in order to keep small the quantity of gas which must flow through the orifices 35 to equalise the internal and external pressures.
  • the projectile In the bore of the gun, the projectile is subject to an extremely powerful accelerational thrust; since the spring 37 is not sufficiently powerful to bear upon the valves 36 at that time, the orifices 35 are not closed during this travel in the bore, and the combustion gases of the packets 31a exit through the said orifices 35 which have remained open; as soon as the projectile has left the bore, the spring 37 bears upon the valve 36, which closes the orifices 35, and the gases are then constrained to exit through the nozzle 39.
  • the rocket motor functions and its thrust maintains or increases the velocity of the projectile possibly until impact.
  • the present invention is not limited to the exemplary embodiments which have just been described, but it also relates, generally speaking, to all projectiles launched by a firearm of any calibre, whether by a light or portable arm or a heavy arm.
  • a projectile as claimed in claim 1 and radial centering arms carried by said transverse plate and defining holes and constituting said means defining said channel.
  • a projectile as claimed in claim 1 and radial pins maintaining said nozzle in the forward position to keep said additional conduit open so long as the projectile is accelerating within the firearm.
  • a projectile as claimed in claim 5 and a sleeve screwed into the projectile and housing the nozzle and traversed by said radial pins.
  • a projectile as claimed in claim 1 and a primer having an ignition temperature substantially below that of said solid fuel, said primer being disposed in said additional conduit.
  • an additional propulsion device constituted by a solid fuel rocket motor housed in the projectile, a calibrated nozzle in the rear of the rojectile for the escape of combustion gases of the solid fuel of the rocket, a cup screwed into the rear of the projectile, a disc screwed into the cup, the disc being integral with said nozzle and defining channels in said cup, valve means for closing said channels, and spring means acting on said valve means to open said valve means when the projectile has left the firearm.
  • a rocket projectile launched by a firearm comprising a solid core, a solid fuel rocket-type motor disposed behind said core, a calibrated nozzle in the rear of the projectile for the escape of combustion gases of the solid fuel of the rocket, an axial rod extending through the forward end of the projectile and through said core and said solid fuel and terminating in a tapered end located in the throat of said nozzle, and means on the forward end of said rod accessible from the forward end of the projectile to adjust the axial position of said rod thereby to alter the shape of the cross section of the nozzle.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US513461A 1964-12-16 1965-12-13 Rocket projectile Expired - Lifetime US3349708A (en)

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BE40346 1964-12-16

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BE (1) BE657225A (en(2012))
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FR (1) FR1459597A (en(2012))

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3434419A (en) * 1967-08-10 1969-03-25 Robert M Dimond Rocket assisted projectile with movable piston base plate
US3601056A (en) * 1969-10-03 1971-08-24 Morris Roger Nicholson Rocket projectile cartridge
WO1998019127A1 (en) 1996-10-28 1998-05-07 Cordant Technologies, Inc. Design for a gun-launched rocket
US5939662A (en) * 1997-12-03 1999-08-17 Raytheon Company Missile warhead design
US6581522B1 (en) * 1993-02-18 2003-06-24 Gerald J. Julien Projectile
US6966264B2 (en) 2001-11-01 2005-11-22 Alliant Techsystems Inc. Rocket motors with insensitive munitions systems and projectiles including same
US20070144393A1 (en) * 2005-12-22 2007-06-28 Maximillian Kusz Caseless ammunition with internal propellant
US20080257139A1 (en) * 2005-03-31 2008-10-23 Leslie Mervyn Harrison Method of manufacturing ammunition
US20090178585A1 (en) * 2004-04-02 2009-07-16 Leslie Mervyn Harrison Projectile
JP2011099670A (ja) * 2004-04-02 2011-05-19 Techventure Investments Pty Ltd 発射体
US20120012021A1 (en) * 2010-07-15 2012-01-19 Raytheon Company Gun fired propellant support assemblies and methods for same
US8671839B2 (en) 2011-11-04 2014-03-18 Joseph M. Bunczk Projectile and munition including projectile
DE102014115722A1 (de) * 2014-10-29 2016-05-04 Bayern-Chemie Gesellschaft Für Flugchemische Antriebe Mbh Integriertes Flugkörperantriebssystem
US9429406B2 (en) * 2013-07-31 2016-08-30 Techventure Investments Pty Ltd Projectile body and corresponding ammunition round for small arms or a light firearm
US20170322001A1 (en) * 2016-05-03 2017-11-09 Dimosthenis Panousakis Self contained internal chamber for a projectile
US20220252382A1 (en) * 2019-04-26 2022-08-11 University Of Kansas Maneuvering aeromechanically stable sabot system
SE547298C2 (sv) * 2024-01-16 2025-06-24 Bae Systems Bofors Ab Basflödesventil för hybridmotor

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1507865A (en) * 1975-10-22 1978-04-19 Liljegren T Projectiles
FR2444806A1 (fr) * 1978-12-22 1980-07-18 Poudres & Explosifs Ste Nale Propulseur a propergol solide comportant un deflecteur d'entree de tuyere, et, deflecteur d'entree de tuyere de propulseur
DE2943891C2 (de) * 1979-10-31 1982-09-23 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Betätigungsvorrichtung für ein Ventil zum Verändern des Durchströmquerschnitts einer Heißgasleitung, insbesondere für in die Brennkammer von Staustrahltriebwerken einströmende brennstoffreiche Gase
FR2479905A1 (fr) * 1980-04-03 1981-10-09 France Etat Bloc propulsif de projectile
GB2089009A (en) * 1980-12-08 1982-06-16 United Technologies Corp Blast Equalizer for a Gun fired Ramjet Projectile
FR2607585B1 (fr) * 1986-11-27 1993-04-09 Matra Mine a tir indirect d'attaque de vehicule blinde
US5001982A (en) * 1988-06-28 1991-03-26 General Dynamics Corp., Pomona Division Anti-armor weapon
KR0152968B1 (ko) * 1988-06-28 1998-10-15 찰스디. 브라운 경량 대전차 무기

Citations (9)

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US2460289A (en) * 1945-03-16 1949-02-01 Clarence N Hickman Rocket projectile
US2552407A (en) * 1950-01-25 1951-05-08 Phoenix Metal Cap Co Inc Torque indicating device for capping machines of the turning type
US2762193A (en) * 1953-02-03 1956-09-11 Scaife Company Welded end closure means for rocket motors
US2884859A (en) * 1955-11-04 1959-05-05 James M Alexander Rocket projectile
US3011309A (en) * 1958-12-31 1961-12-05 Ici Ltd Single chamber dual thrust rocket motor
US3115271A (en) * 1958-08-15 1963-12-24 Minnesota Mining & Mfg Method of constructing a reinforced resin, cone-shaped structure and product
US3122884A (en) * 1961-05-19 1964-03-03 Atlantic Res Corp Rocket motor
GB976483A (en) * 1960-02-26 1964-11-25 Zeebrugge Forges Sa A monotabular device for projectiles having stabilising fins and projectiles fitted with this device
US3277825A (en) * 1963-11-07 1966-10-11 Brevets Aero Mecaniques Self-propelled armor-piercing shells

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2460289A (en) * 1945-03-16 1949-02-01 Clarence N Hickman Rocket projectile
US2552407A (en) * 1950-01-25 1951-05-08 Phoenix Metal Cap Co Inc Torque indicating device for capping machines of the turning type
US2762193A (en) * 1953-02-03 1956-09-11 Scaife Company Welded end closure means for rocket motors
US2884859A (en) * 1955-11-04 1959-05-05 James M Alexander Rocket projectile
US3115271A (en) * 1958-08-15 1963-12-24 Minnesota Mining & Mfg Method of constructing a reinforced resin, cone-shaped structure and product
US3011309A (en) * 1958-12-31 1961-12-05 Ici Ltd Single chamber dual thrust rocket motor
GB976483A (en) * 1960-02-26 1964-11-25 Zeebrugge Forges Sa A monotabular device for projectiles having stabilising fins and projectiles fitted with this device
US3122884A (en) * 1961-05-19 1964-03-03 Atlantic Res Corp Rocket motor
US3277825A (en) * 1963-11-07 1966-10-11 Brevets Aero Mecaniques Self-propelled armor-piercing shells

Cited By (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3434419A (en) * 1967-08-10 1969-03-25 Robert M Dimond Rocket assisted projectile with movable piston base plate
US3601056A (en) * 1969-10-03 1971-08-24 Morris Roger Nicholson Rocket projectile cartridge
US6581522B1 (en) * 1993-02-18 2003-06-24 Gerald J. Julien Projectile
WO1998019127A1 (en) 1996-10-28 1998-05-07 Cordant Technologies, Inc. Design for a gun-launched rocket
US5792981A (en) * 1996-10-28 1998-08-11 Thiokol Corporation Gun-launched rocket
US6094906A (en) * 1996-10-28 2000-08-01 Cordant Technologies Inc. Design for a gun-launched rocket
US5939662A (en) * 1997-12-03 1999-08-17 Raytheon Company Missile warhead design
US6966264B2 (en) 2001-11-01 2005-11-22 Alliant Techsystems Inc. Rocket motors with insensitive munitions systems and projectiles including same
JP2011099670A (ja) * 2004-04-02 2011-05-19 Techventure Investments Pty Ltd 発射体
US20090178585A1 (en) * 2004-04-02 2009-07-16 Leslie Mervyn Harrison Projectile
US7921780B2 (en) * 2004-04-02 2011-04-12 Techventure Investments Pty Ltd Projectile
US20080257139A1 (en) * 2005-03-31 2008-10-23 Leslie Mervyn Harrison Method of manufacturing ammunition
US7665402B2 (en) 2005-03-31 2010-02-23 Techventure Investments Pty Ltd. Method of manufacturing ammunition
US20070144393A1 (en) * 2005-12-22 2007-06-28 Maximillian Kusz Caseless ammunition with internal propellant
JP2010522860A (ja) * 2007-03-30 2010-07-08 テクベンチャー インベストメンツ プロプライエタリー リミテッド 弾薬を製造する方法
US20120012021A1 (en) * 2010-07-15 2012-01-19 Raytheon Company Gun fired propellant support assemblies and methods for same
US8453572B2 (en) * 2010-07-15 2013-06-04 Raytheon Company Gun fired propellant support assemblies and methods for same
US8671839B2 (en) 2011-11-04 2014-03-18 Joseph M. Bunczk Projectile and munition including projectile
US9429406B2 (en) * 2013-07-31 2016-08-30 Techventure Investments Pty Ltd Projectile body and corresponding ammunition round for small arms or a light firearm
USRE47187E1 (en) * 2013-07-31 2019-01-01 Techventure Investments Pty Ltd Projectile body and corresponding ammunition round for small arms or a light firearm
DE102014115722A1 (de) * 2014-10-29 2016-05-04 Bayern-Chemie Gesellschaft Für Flugchemische Antriebe Mbh Integriertes Flugkörperantriebssystem
DE102014115722B4 (de) 2014-10-29 2022-08-11 Bayern-Chemie Gesellschaft Für Flugchemische Antriebe Mbh Integriertes Flugkörperantriebssystem
US20170322001A1 (en) * 2016-05-03 2017-11-09 Dimosthenis Panousakis Self contained internal chamber for a projectile
US10677574B2 (en) * 2016-05-03 2020-06-09 Dimosthenis Panousakis Self contained internal chamber for a projectile
US20220252382A1 (en) * 2019-04-26 2022-08-11 University Of Kansas Maneuvering aeromechanically stable sabot system
US11852447B2 (en) * 2019-04-26 2023-12-26 The University Of Kansas Maneuvering aeromechanically stable sabot system
SE547298C2 (sv) * 2024-01-16 2025-06-24 Bae Systems Bofors Ab Basflödesventil för hybridmotor
SE2400008A1 (sv) * 2024-01-16 2025-06-24 Bae Systems Bofors Ab Basflödesventil för hybridmotor
WO2025155227A1 (en) * 2024-01-16 2025-07-24 Bae Systems Bofors Ab Nozzle for hybrid engine

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Publication number Publication date
BE657225A (en(2012))
CH447884A (fr) 1967-11-30
FR1459597A (fr) 1966-11-18

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