US3490330A - Firearm,particularly light antitank weapon - Google Patents

Firearm,particularly light antitank weapon Download PDF

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Publication number
US3490330A
US3490330A US711607A US3490330DA US3490330A US 3490330 A US3490330 A US 3490330A US 711607 A US711607 A US 711607A US 3490330D A US3490330D A US 3490330DA US 3490330 A US3490330 A US 3490330A
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United States
Prior art keywords
barrel
gun
piston
projectile
firing
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Expired - Lifetime
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US711607A
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English (en)
Inventor
Willi Walther
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KUKA AG
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Industrie Werke Karlsruhe Ausburg AG
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Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A1/00—Missile propulsion characterised by the use of explosive or combustible propellant charges
    • F41A1/08—Recoilless guns, i.e. guns having propulsion means producing no recoil

Definitions

  • a firearm particularly a light antitank weapon in which the recoil impulse upon firing a projectile is at least partially intercepted by a counter-thrust drive device arranged at the rear end of the gun barrel.
  • the gun barrel is slidably mounted in a tubular guide provided with a shoulder support, handles and a trigger on one of the handles.
  • Within the gun barrel a slidable pistondriven by a propellant chargehas mounted thereon the projectile.
  • the piston is intercepted by an intercepter device at the muzzle end of the barrel.
  • the gun barrel then moves rearwardly in the guide and is arrested by the counter-thrust drive device and may even be completely discharged from the rear end of the tubular guide.
  • the invention relates to a weapon provided with a counter-thrust drive-system for at least partial intercept of the recoil impulses taking effect on the barrel upon firing of a projectile, particularly a light shoulder-weapon for defense against tanks.
  • Firearms are already known, in which the recoil impulse taking eifect on the gun barrel upon firing of a projectile is partially or entirely intercepted.
  • weapons of this type constructed as light-guns free from recoil
  • the disadvantage of such weapons consists therein, that even upon the slightest deviations of the nozzle axis from the gun-barrel axis, which is practically not to be prevented, the thrust power of the nozzle drive mechanism possesses a force component directed perpendicularly to the barrel axis. As a result thereof, torsional moments act on the barrel, which lead to angular distortions of the weapon with respect to the desired firing direction, while the projectile passes through the gun-barrel. Misfirings result therefrom.
  • a weapon free from recoil is also known, in which, in a gun barrel open on both ends, a liner or inner tube closed on 'one side is longitudinally slidably mounted. This liner receives the projectile and the propellent charge. Upon firing of a projectile, with this weapon, on account of the recoil impulse taking elfect on the liner or inner tube, the liner or inner tube is ejected rearwardly from the gun-barrel which is open at both ends.
  • the liner or inner tube possesses a greater bulk than the projectile, behind a projectile of this type considerable 3,490,330 Patented Jan. 20, 1970 safety areas are necessary into which the liner or inner tube is ejected. Such great safety areas, however, are solely available in exceptional cases.
  • the gun described above is adjustable solely to a limited extent and has been intended also especially as a gun for aircraft.
  • the object of the invention consists in the furnishing of a firearm, preferably a light shoulder-weapon for defense against tanks, in which the recoil impulse upon firing of'a projectile is at least partially intercepted by means of a counter-thrust drive-device whereby no acoustic effects occur upon firing, which could lead to hearing injuries of the gunner. Furthermore, upon firing of a projectile, the safety area required behind the weapon shouldbe as small as possible.
  • the solution of the stated problem consists in the arrangement of a piston serving as projectile-drive-base, which is positioned longitudinally slidably in the gun-barrel and is connected tightly with the projectile, however, still releasable upon discharge, further characterized therein, that in the gun barrel muzzle a piston-intercept-device is fixedly disposed for intercepting the piston upon forward motion.
  • the piston may be held tight in the gun-barrel by means of a holding means, whose holding power is released solely under the action of a predetermined piston force.
  • the holding means may be a tension rod connected with the end of thegun-barrel facing away from the piston and the barrel muzzle, said tension rod being provided with a suitably dimensioned breaking point corresponding to the desired breaking force of the piston.
  • the holding means may be an ignition tube which extends axially through the propellent charge and is fixedly connected with the barrel end.
  • the counter-thrust-drive-mechanism may, in a manner known 'per se, be a nozzle drive mechanism operated by the combustion gases of the propellent charge.
  • the gun barrel after the firing of a projectile acts as gas-pressure-storage member and the drive gases then first partially released are available for the supply to the counter-thrust-drivemechanism.
  • the firearm of the invention solely one propellent charge is required, and the drivemechanism-thrust may be held small in comparison with the force owing to recoil impulse of the projectile, as the operation of the co-unter-thrust-drive-mechanism lasts very long in comparison with the time in which the projectile passes through the gun-barrel.
  • the counter-thrust-drive-mechanism may have a gas-pressuring channel which discharges at such a point in the gun-barrel, that the impacting of the drivemechanism with gas pressure takes place only then when the piston has returned to a partial distanc into the gunbarrel after the ignition of the propellent charge.
  • the gas pressure impact channel may discharge in the area in the gun-barrel, which upon a non-fired propellent charge is uncovered by a shaft of the piston.
  • the counterthr-ust drive mechanism comprises a ring of nozzles which concentrically surrounds the gun-barrel, and whose nozzles are disposed preferably at equal angular spacings from one another in a manner known per se, so that the resulting thrust force acts on the center of gravity of the gunbarrel.
  • the axes of the driving mechanism-nozzles may in this connection be directed inclined outwardly and from mantle lines of a cone imagined to open towards the firing direction, and the longitudinal axis coincides with the longitudinal axis of the gun-barrel.
  • the arrangement of the nozzles may with advantage be selected in such a manner that the resulting thrust force acts on the center of gravity of the gun-barrel. In this manner it is insured that even upon loss of a thrustnozzle, no torsional moments take effect on the gunbarrel.
  • the propellent charge space which is disposed between the piston guided in the gun-barrel and the rear barrel-end, there may be disposed adjacent to the main propellent charge an additional propellent charge made of slow-burning propellent substances.
  • the additional propellent charge furnishes no noteworthy addition to the firing of the projectile, but serves for supplying gas to the counter-thrust drive mechanism for a longer period of time.
  • the additional propellent charge may also consist of a propellent substance having a great ignition inertia, or it may be shielded with respect to the main propellent charge by a covering which is destructible under the influence of heat upon combustion of the main propellent charge.
  • the additional propellent charge consists of a solid-rocket-composition disposed at the rearward end of the propellent charge space.
  • a further substantial feature of the invention consists therein, that the piston which serves as a projectile drivebase possesses a deformation section with great workrecelvlng capacities, which upon the intercept operation enters into the piston intercept device and is deformed there, whereby a conversion of the kinectic energy inherent to the piston into deformation energy takes place.
  • the deforming section of the piston lies in front of the piston base, on which the projectile is releasably mounted.
  • the piston intercept device may comprise an insert piece, which concially tapers toward the gun-barrel-muzzle, said insert piece having on the piston-entry side the same or a somewhat larger diameter than the piston.
  • FIG. 1 illustrates diagrammatically a weapon of the invention in longitudinal section
  • FIG. 2 illustrates diagrammatically and in section the same weapon shortly after the ignition of the propellent charge
  • FIG. 3 illustrates the weapon after the firing
  • FIG. 4 is a side view of the weapon with a portion in section
  • FIG. 5 illustrates the piston intercept device with intercepted piston, partly in section.
  • the weapon essentially consists of a gun-barrel 1 and a gun-barrel guide 2 constructed as shoulder-support.
  • the gun-barrel is slidably guided with anti-friction property in direction of its longitudinal axis in the guide 2.
  • the guide 2 is provided with means, not shown, for arresting of the gun-barrel which means only upon firing of the weapon are released and thereby release the gun-barrel.
  • the arrangement is made in such a manner that the gun-barrel may be shifted from the position shown in FIG. 1 upon firing solely rearwardly--namely opposite to the firing direction-and if need be may completely leave its guide.
  • the rearward end 3 of the gun-barrel 2 is closed by a rear wall 4.
  • a piston 5 which before the firing is held in its position by means of a holding device 6 provided with a breaking point and upon firing is movable along the barrel to the barrelmuzzle 7.
  • a piston intercept device 8 In the barrel muzzle is disposed a piston intercept device 8 described hereinafter more in detail.
  • the piston 5 is provided on its end facing the gun-barrel muzzle with a receiver for the projectile 9.
  • the propellent charge chamber 10 Between the piston 5 and the end of the gun-barrel closed by the rear wall 4 is disposed the propellent charge chamber 10.
  • a counter-thrust drive 11 At the rearward end 3 of the gun-barrel 2 is furthermore disposed a counter-thrust drive 11, whose nozzles lie symmetrically to the axis of the counter-thrust drive and is directed toward the rear, namely, opposite to the direction of firing.
  • the high pressure sides of the drive mechanism nozzles discharge into such a point in the gun-barrel, that the nozzles are provided only then with gas pressure, when after the ignition of the propellant charge, the piston 5 carrying the projectile 9 has traveled a pre-determined distance. This is shown in FIG. 2.
  • the barrel guide 2 surrounds the gun barrel 1 substantially concentrically and extends over a part of the length of the gun barrel.
  • the barrel guide is provided with a shoulder-support 12 as well as two handles 13, 14.
  • On the handle 13 is disposed a trigger device 15.
  • the gun barrel 1 consists of a front cylindrical barrel section 20 and the readward end 3.
  • the cylindrical barrel section 20 and the end 3 of the gun barrel are threadedly connected with each other by means of a screw thread 21.
  • the gun barrel On the front end of the screw thread, the gun barrel is provided with flange 22 projecting radially from the gun barrel, said flange engaging the rear end the barrel guide 2 and preventing a further forward movement of the gun barrel 1 in the barrel guide 2.
  • the hollow space of the gun barrel lying behind the piston 5 in FIG. 4 serves as a propellant charge chamber.
  • the propellent charge consists of a solid rocket composition 23 and a powder charge 24.
  • the piston 5 and the ignition tube 6 are secured together by means of a screw thread 25.
  • the ignition tube 6 possesses a breaking point 26.
  • the ignition tube 6 is screwed in a manner not of greater interest here, into the rear wall 4 of the end 3 of the gun barrel.
  • the ignition tube 6 is provided in the area of the propellent charge space with a number of bores 27, which connect its inner chamber with the propellent charge chamber.
  • the bridge-igniter 30 is in connection, in a manner not of interest here, through electric conductors 31 with an ignition contact actuatable by the trigger device 15.
  • the piston For insuring a smooth guidance of the projectile through the projectile passage in the gun-barrel, the piston is provided with a piston wall 33 of considerable length.
  • the forward end 34 of the piston possesses a receiver 35 for the projectile 9.
  • the piston is provided with piston rings 36, 37.
  • the counter-thrust drive mechanism 11 In the area of the end of the gun-barrel in which the piston 5 held in its position by means of the ignition tube 6, is arranged, before the firing, the counter-thrust drive mechanism 11 in the form of an annular series of thrust nozzles 40.
  • the nozzles On the high pressure side, the nozzles are provided with a gas compacting channel 41, which is covevered by piston wall 33. This channel 41 is first uncovered for gas pressure admission after, as a result of ignition of the propellent charge 24, the piston 5 has been moved from its starting position apredetermined distance forwardly. Thereafter, the thrust nozzles 40 of the counterthrust drive mechanism 11 are pressured by the propellent charge gases and exert a thrust force directed against the recoil impulse upon firing of the weapon.
  • the breaking point 26 the break-off force of the piston may be adjusted within wide limits, in such manner, that the piston upon firing of the weapon receives a high starting acceleration.
  • the propellent charge 24 consists preferably of rapidly burning powder.
  • the piston moves toward the gun-barrel muzzle, the tension release of the gas pressure in the gun-barrel occasioned thereby causes a gradual decline in the power of the counter-thrust drive mechanism.
  • another propellent charge 23 preferably consisting of a slow-burning propellent substance.
  • a foil 42 which under effect of temperature during the burning of the charge 24 is destroyed and delays the ignition of the propellent charge 23.
  • the piston intercept device comprises an insert piece secured by means of a screw-thread 45 in the gun-barrel, and has an inner wall surface tapering conically towards the gun-barrel-muzzle. This conical insert piece receives the piston driven by the gas-pressure along the gun-barrel and undergoes thereby a deformation dissipating its kinetic energy.
  • the gun-barrel is closed and the combustion gases still contained in the barrel are now completely available for the operation of the counterthrust-drive mechanism.
  • the projectile 9 is released due to its inertia from the projectile-receiver 35 in the piston bottom and moves then on a ballistic trajectory.
  • FIGS. 2 and 3 show the recoil of the gun-barrel during the firing of the weapon.
  • FIG. 2 shows the commencement of the movement of the piston 5.
  • the gun-barrel recoil movement amounts to Z1.
  • the counter-thrust drive mechanism 11 is full operative.
  • the thrust force is, however, calculated that only a part of the recoil impulse is absorbed.
  • the gun-barrel-recoil at that moment, at which the piston has entered the piston-intercept device on the gun-barrel muzzle, and the projectile has been released from the piston bottom.
  • the projectile therefore has entered on a ballistic trajectory.
  • the gun-barrel continues its return movement and depending upon the design of the counter-thrust drive mechanism leaves the gun-barrel guide entirely or is arrested and on account of the continued drive mechanism thrust is conveyed back to its starting position.
  • the counter-thrustdrive mechanism is so designed that the gun-barrel leaves the barrel guide towards the back and in the area of a predetermined safety path drops to the floor or ground behind the gun.
  • Firearm particularly light shoulder weapon for antitank defense, comprising a gun barrel accommodating a projectile and a propellent charge, a guide sleeve for said gun barrel in the form of a shoulder support in which said gun barrel is longitudinally slidable upon release of latch means by firing of a shot, trigger means on said guide sleeve connected with means for setting off said propellent charge, piston means slidably mounted in said gun barrel and serving as drive base for said projectile, connection means on said piston means rigidly holding said projectile until released after the firing of a shot, counter thrust means including space at the rear of said gun barrel for an auxiliary charge of a propellent with high ignition inertia for at least partial off-setting of the recoil impulse at the firing of a shot, and piston intercept means secured to the muzzle end of said gun barrel to intercept the forward movement of said piston means.
  • said piston intercept means comprises an insert piece tapering conically inwardly towards the gun-barrel muzzle, the piston receiving end of said insert piece having a somewhat greater diameter than the piston means.
  • Firearm according to claim 1 including a breakable ignition tube secured to said piston means and to the rear end of said gun barrel and extending through said propellent charge.
  • auxiliary charge comprises a slow-burning propellent.
  • said piston means includes a deformation section with great energy absorption capacity, said deformation section entering said piston intercept means at the firing of a shot and being deformed thereby.
  • a light antitank shoulder-weapon comprising in combination a'gun barrel accommodating a projectile and propellent charges
  • a guide sleeve for said gun barrel in the form of a shoulder support in which said gun barrel is longitudinally slidable upon release of latch means through firing of a shot
  • piston means slidably mounted in said gun barrel and having a portion which serves as a drive base for said projectile
  • counter thrust means in the rear portion of said gun barrel to at least partially offset the recoil impulse at the firing of a shot
  • said counter thrust means including a propellent chamber rearwardly of said piston means to accommodate a main propellent charge and an auxiliary propellent charge which References Cited UNITED STATES PATENTS 2/1890 Reynolds 891 X 3/1950 Garrett 891 X 2,834,255 5/1958 Musser 891.706 3,255,668 6/1966 Vilbajo 891.705 3,338,133 8/1967 Grandy 89--1.703

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
US711607A 1967-03-16 1968-03-08 Firearm,particularly light antitank weapon Expired - Lifetime US3490330A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEJ0033228 1967-03-16

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US (1) US3490330A (xx)
BE (1) BE711480A (xx)
CH (1) CH492187A (xx)
FR (1) FR1558093A (xx)
GB (1) GB1213711A (xx)
NL (2) NL6803169A (xx)

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3779130A (en) * 1970-01-16 1973-12-18 Messerschmitt Boelkow Blohm Launching tube for projectiles and missiles respectively
US3800656A (en) * 1970-11-13 1974-04-02 Messerschmitt Boelkow Blohm Launching device for projectiles
US3815469A (en) * 1972-07-29 1974-06-11 Messerschmitt Boelkow Blohm Method and device for launching missiles particularly antitank projectiles
US4026189A (en) * 1975-02-20 1977-05-31 Forenade Fabriksverken Projectile locking device
US4069739A (en) * 1974-05-13 1978-01-24 General Electric Company Liquid propellant weapon systems
US4091709A (en) * 1976-07-26 1978-05-30 The United States Of America As Represented By The Secretary Of The Army Recoilless rifle nozzle
US4126078A (en) * 1976-07-20 1978-11-21 General Electric Company Liquid propellant weapon system
US4132149A (en) * 1976-07-20 1979-01-02 General Electric Company Liquid propellant weapon system
US4208948A (en) * 1978-11-22 1980-06-24 The United States Of America As Represented By The Secretary Of The Army High efficiency propulsion system
US4672881A (en) * 1986-07-28 1987-06-16 The United States Of America As Represented By The Secretary Of The Army Recoilless rocket launcher
WO1989004451A1 (en) * 1987-11-10 1989-05-18 The Secretary Of State For Defence In Her Britanni Recoil-less launch system
US4962689A (en) * 1989-08-01 1990-10-16 Hughes Aircraft Company Gas generator missile launch system
US5109750A (en) * 1990-06-13 1992-05-05 George Kayaian Closed-breech missile and weapon system
US5357841A (en) * 1991-03-18 1994-10-25 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland Recoilless projectile launcher
USD381387S (en) * 1995-08-14 1997-07-22 The United States Of America As Represented By The Secretary Of The Navy Shoulder-launched, multiple-purpose assault weapon
US5712443A (en) * 1995-10-30 1998-01-27 The United States Of America As Represented By The Secretary Of The Navy Shoulder-launched multiple-purpose assault weapon
US5854440A (en) * 1995-10-30 1998-12-29 The United States Of America As Represented By The Secretary Of The Navy Shoulder-launched multi-purpose assault weapon
US20100275763A1 (en) * 2006-12-22 2010-11-04 Saab Ab Nozzle
RU2453788C1 (ru) * 2010-12-28 2012-06-20 Открытое акционерное общество Центральный научно-исследовательский институт специального машиностроения Пусковая труба
DE102014115721A1 (de) * 2014-10-29 2016-05-04 Bayern-Chemie Gesellschaft Für Flugchemische Antriebe Mbh Aktive Bremsung eines Ausstoßtriebwerkes
EP3431915A4 (en) * 2016-03-14 2019-10-30 Andrey Albertovich Polovnev REFRACTOR FREE UNDERWATER FIREARM
US10502515B2 (en) * 2017-01-17 2019-12-10 Raytheon Company Launch piston brake
US10788284B1 (en) * 2019-05-09 2020-09-29 The United States Of America As Represented By The Secretary Of The Army Grounded and vehicular mounted weapons with improved recoil stability

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3009342A1 (de) * 1980-03-12 1986-06-26 Rheinmetall GmbH, 4000 Düsseldorf Patronierte munition mit einer wenigstens teilverbrennbaren treibladungshuelse
GB2126320B (en) * 1982-07-16 1986-02-05 Europ Propulsion Pecoilless ammunition
FR2539503B1 (fr) * 1983-01-14 1987-01-16 Luchaire Sa Dispositif pour le deploiement automatique des ailettes d'un empennage destine a la stabilisation d'un engin lance par piston
US4944210A (en) * 1988-08-08 1990-07-31 Hughes Aircraft Company Missile launcher
FR2658597B1 (fr) * 1990-02-16 1994-05-27 Thomson Brandt Armements Arme sans recul.
FR2725268B1 (fr) * 1994-10-04 1996-12-20 Lacroix Soc E Lanceur de projectile, a canon consommable
GB0107552D0 (en) 2001-03-27 2005-01-05 Matra Bae Dynamics Uk Ltd Improvements in and relating to the launching of missiles

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US421307A (en) * 1890-02-11 reynolds
GB590268A (en) * 1942-05-14 1947-07-14 Charles Dennistoun Burney Improvements in or relating to guns having modified recoil and to breech mechanism therefor
US2499379A (en) * 1944-12-26 1950-03-07 Garrett Emil Grenade thrower
US2834255A (en) * 1952-08-27 1958-05-13 Musser C Walton Recoilless firearm and ammunition therefor
CA578595A (en) * 1959-06-30 Bloch Adolf Recoilless gun
US3255668A (en) * 1963-06-25 1966-06-14 Contigea Sa Light anti-tank weapons
US3338133A (en) * 1965-10-06 1967-08-29 Andrew J Grandy Launching system

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US421307A (en) * 1890-02-11 reynolds
CA578595A (en) * 1959-06-30 Bloch Adolf Recoilless gun
GB590268A (en) * 1942-05-14 1947-07-14 Charles Dennistoun Burney Improvements in or relating to guns having modified recoil and to breech mechanism therefor
US2499379A (en) * 1944-12-26 1950-03-07 Garrett Emil Grenade thrower
US2834255A (en) * 1952-08-27 1958-05-13 Musser C Walton Recoilless firearm and ammunition therefor
US3255668A (en) * 1963-06-25 1966-06-14 Contigea Sa Light anti-tank weapons
US3338133A (en) * 1965-10-06 1967-08-29 Andrew J Grandy Launching system

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3779130A (en) * 1970-01-16 1973-12-18 Messerschmitt Boelkow Blohm Launching tube for projectiles and missiles respectively
US3800656A (en) * 1970-11-13 1974-04-02 Messerschmitt Boelkow Blohm Launching device for projectiles
US3815469A (en) * 1972-07-29 1974-06-11 Messerschmitt Boelkow Blohm Method and device for launching missiles particularly antitank projectiles
US4069739A (en) * 1974-05-13 1978-01-24 General Electric Company Liquid propellant weapon systems
US4026189A (en) * 1975-02-20 1977-05-31 Forenade Fabriksverken Projectile locking device
US4126078A (en) * 1976-07-20 1978-11-21 General Electric Company Liquid propellant weapon system
US4132149A (en) * 1976-07-20 1979-01-02 General Electric Company Liquid propellant weapon system
US4091709A (en) * 1976-07-26 1978-05-30 The United States Of America As Represented By The Secretary Of The Army Recoilless rifle nozzle
US4208948A (en) * 1978-11-22 1980-06-24 The United States Of America As Represented By The Secretary Of The Army High efficiency propulsion system
US4672881A (en) * 1986-07-28 1987-06-16 The United States Of America As Represented By The Secretary Of The Army Recoilless rocket launcher
WO1989004451A1 (en) * 1987-11-10 1989-05-18 The Secretary Of State For Defence In Her Britanni Recoil-less launch system
AU624983B2 (en) * 1989-08-01 1992-06-25 Hughes Aircraft Company Gas generator missile launch system
US4962689A (en) * 1989-08-01 1990-10-16 Hughes Aircraft Company Gas generator missile launch system
US5109750A (en) * 1990-06-13 1992-05-05 George Kayaian Closed-breech missile and weapon system
US5357841A (en) * 1991-03-18 1994-10-25 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland Recoilless projectile launcher
USD381387S (en) * 1995-08-14 1997-07-22 The United States Of America As Represented By The Secretary Of The Navy Shoulder-launched, multiple-purpose assault weapon
US5712443A (en) * 1995-10-30 1998-01-27 The United States Of America As Represented By The Secretary Of The Navy Shoulder-launched multiple-purpose assault weapon
US5732499A (en) * 1995-10-30 1998-03-31 The United States Of America As Represented By Secretary Of The Navy Shoulder-launched multiple-purpose assault weapon
US5835978A (en) * 1995-10-30 1998-11-10 The United States Of America As Represented By The Secretary Of The Navy Shoulder-launched multiple-purpose assault weapon
US5854440A (en) * 1995-10-30 1998-12-29 The United States Of America As Represented By The Secretary Of The Navy Shoulder-launched multi-purpose assault weapon
US20100275763A1 (en) * 2006-12-22 2010-11-04 Saab Ab Nozzle
RU2453788C1 (ru) * 2010-12-28 2012-06-20 Открытое акционерное общество Центральный научно-исследовательский институт специального машиностроения Пусковая труба
DE102014115721A1 (de) * 2014-10-29 2016-05-04 Bayern-Chemie Gesellschaft Für Flugchemische Antriebe Mbh Aktive Bremsung eines Ausstoßtriebwerkes
DE102014115721B4 (de) 2014-10-29 2022-08-11 Bayern-Chemie Gesellschaft Für Flugchemische Antriebe Mbh Aktive Bremsung eines Ausstoßtriebwerkes
EP3431915A4 (en) * 2016-03-14 2019-10-30 Andrey Albertovich Polovnev REFRACTOR FREE UNDERWATER FIREARM
US10502515B2 (en) * 2017-01-17 2019-12-10 Raytheon Company Launch piston brake
US10788284B1 (en) * 2019-05-09 2020-09-29 The United States Of America As Represented By The Secretary Of The Army Grounded and vehicular mounted weapons with improved recoil stability

Also Published As

Publication number Publication date
BE711480A (xx) 1968-08-29
FR1558093A (xx) 1969-02-21
CH492187A (de) 1970-06-15
NL6803169A (xx) 1968-09-17
GB1213711A (en) 1970-11-25
NL132545C (xx)

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