US3779130A - Launching tube for projectiles and missiles respectively - Google Patents

Launching tube for projectiles and missiles respectively Download PDF

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Publication number
US3779130A
US3779130A US00097479A US3779130DA US3779130A US 3779130 A US3779130 A US 3779130A US 00097479 A US00097479 A US 00097479A US 3779130D A US3779130D A US 3779130DA US 3779130 A US3779130 A US 3779130A
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United States
Prior art keywords
tube
projectile
opening
recoil
muzzle
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
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US00097479A
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English (en)
Inventor
W Schnabele
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Defence and Space GmbH
Original Assignee
Messerschmitt Bolkow Blohm AG
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Publication date
Application filed by Messerschmitt Bolkow Blohm AG filed Critical Messerschmitt Bolkow Blohm AG
Application granted granted Critical
Publication of US3779130A publication Critical patent/US3779130A/en
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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
    • F41A1/10—Recoilless guns, i.e. guns having propulsion means producing no recoil a counter projectile being used to balance recoil

Definitions

  • ABSTRACT Launching tube for projectiles and missiles, respectively, in which the serviceable projectile to be launched, a propelling charge, and in the appropriate circumstances a filling of a flowable medium of relatively high density being separated from the propelling charge by a piston or the like are arranged axially behind each other. Immediately after the projectile left the launching tube, the latters forward opening is closed.
  • the cover of the forward tube opening is preferably a pressureresistant piston which extends over the whole crosssectional area of the caliber and which is caught, in particular by a stop, within the portion of the forward tube opening immediately after the projectile left the launching tube.
  • said blow-out ports are arranged in the tube jacket directly behind the caught piston.
  • the invention relates to a launching tube for projectiles and missiles, respectively, in which the serviceable projectile to be launched, a propelling charge, and in the appropriate circumstances a filling consisting of a flowable medium of relatively high density and being separated from the propelling charge by a piston or the like are arranged axially behind each other.
  • the containers are arranged in front of the forward opening of the tube for recoil launching tubes and in front of the forward opening of the tube as well as behind the rear opening of the tube for recoilless launching tubes, the rear opening existing only in the latter case, the containers in front of the forward tube opening containing each a shooting-through ring for the projectiles.
  • the pressure gases first expand into these containers immediately after the projectiles left the respective launching tubes before they reach the open air through the bores leading outward from the expansion chambers of the respective containers.
  • the energy still existing in the pressure gases is largely dissipated on the way of the gases through the expansion chambers by the baffles, the non-return valves or the like.
  • the known mufflers which as has been shown ensure that the energy still inherent in the pressure gases of a propelling charge, which accelerate the projectile, is released gradually after the projectile left the launching tube and thus prevent the occurrence of a bang observed when this energy is released suddenly, are disadvantageous in many respects.
  • Their manufacture is relatively expensive because of their complicated design.
  • their structural volume and their structural weight are considerable which is due to the rigid walls of the container, in particular when the mufflers are designed for high performances. Therefrom result difficulties in transporting and handling launching tubes, above all the portable ones, when they are equipped with such mufflers.
  • the invention is therefore based on the object to develop a launching tube of the kind mentioned at the beginning which permits a low-noise launching of projectiles and missiles, respectively, without needing the known mufflers.
  • this task is solved in that immediately after the projectile left the launching tube the latters forward opening is closed, in which case the launching tube is connected with the outside environment through one or several blow-out port(s) provided for in the tube jacket and/or in the cover of the tube opening and/or through leaks and slots, respectively, between the cover of the forward tube opening and the tube jacket, the gases escaping from the launching tube through said ports and/or leaks and/or slots which have a considerably smaller cross-section and total crosssection, respectively, than the caliber cross-section.
  • a piston extending over the whole caliber cross-section of the launching tube is arranged between the propelling charge and the projectile, said piston separates the propelling charge from the projectile and is caught within the portion of the forward tube opening immediately after the projectile left the launching tube.
  • blow-out port and ports are arranged di rectly behind the caught piston inside the tube jacket. It and they, respectively, can also be arranged, however, in the piston which separates the projectile from the propelling charge and which serves to close the forward tube opening, its or their arrangement being such that it and they, respectively, remain covered by the projectile until the piston is caught within the portion of the forward tube opening and is separated from the projectile, respectively.
  • a ring-shaped shoulder provided for within the portion of the forward tube opening and extending radially inward has proved successful as a catching device for the piston separating the projectile from the propelling charge.
  • FIG. 1a shows in principle a recoilless type of the launching tube according to the invention before the projectile is launched
  • FIG. 1b shows the launching tube according to FIG. 1a after the projectile left the tube
  • FIG. 2 shows a section of a varied embodiment of the launching tube according to the invention.
  • the launching tube denoted by 1 according to FIGS. la and 1b is portable and has been designed to be used only once, i.e. it is a so-called throw-away" firearm.
  • the diameter of the tube is reduced within the portions of the forward end 2 and the rear end 3.
  • the forward tube opening is denoted by 4, the rear tube opening by 5, and the diaphragm covering the rear opening by 6.
  • the ring-shaped shoulders, which are due to the reduced diameters at the forward tube end 2 and at the rear tube end 3, have the reference numbers 7 and 8.
  • a projectile 10, for instance an armor-piercing projectile or shell, a propelling charge 12 provided with an ignition pellet 11, and a filling 13 of a flowable medium of relatively high density are arranged axially behind each other in the interior space 9 of the tube.
  • Those media are suited as filling media which do not evaporate at the temperatures occurring and which can easily be separated, such as water-oil-mixtures, jelly-type substances which liquefy under pressure and greases as well as gritty solid substances, e.g. sand.
  • the propelling charge 12 is separated by one piston 15 and 16, respectively, each extending over the whole cross-sectional area of the caliber of the launching tube 1 both from projectile 10 being supported and guided through one slide ring 14 in launching tube 1 and from filling 13 consisting ofa flowable medium.
  • piston 15 arranged between projectile 10 and propelling charge 12 moves together with projectile l fastened to said piston 15 toward forward tube opening 4 under the effect of the pressure gases 17 produced when propelling charge 12 is ignited, while the other piston 16 arranged between propelling charge 12 and filling 13 of a flowable medium moves toward rear tube opening 5, diaphragm 6 closing rear tube opening before the ignition of propelling charge 12 being then destroyed and the flowable medium leaving launching tube 1 through rear tube opening 5 in a dispersed form 18.
  • the quantity of filling 13 consisting of a flowable medium is so proportioned to the weight of the projectile for safely avoiding any recoil that both pistons 15 and 16 lie simultaneously against the respective ring shoulders 7 and 8 of launching tube 1.
  • two blowout ports 19 having a considerably smaller total crosssection than the caliber cross-section of launching tube 1 and being arranged within the portion of the forward tube end 2 connect the pressure-gas-filled inner space 9 of the tube with the outside environment, and hence the pressure gases 17 can escape slowly without a bang.
  • a lauching device for projectiles especially for the combatting of tanks, comprising a portable launching tube having a muzzle opening at one end and a recoil opening at the opposite end, a very dense but welldividable and flowable mass composed mostly of jellylike substances, fats and gravel-like, solid substances disposed adjacent the recoil opening and which are adapted to be accelerated by the pressure gases of a propelling charge to move out the recoil opening, a projectile disposed adjacent said muzzle end, a propellant charge between said projectile and said medium, said mass having diaphragm means associated therewith and which holds said mass within said tube but is dislodgeable from said tube by ignition of said charge, first and second pistons which are axially movable over the entire tube interior located between said charge and said projectile and between said charge and said medium, respectively, means for retaining said first and second pistons within said tube after firing and after they have been moved toward the respective ends, and means for venting pressure gases which are enclosed by said pistons after
  • vent means includes an opening in said tube at a spaced location from said muzzle opening, said means for holding said first piston including a collar formed at said muzzle end projecting into the interior, said piston being held at a location by said collar spaced toward said muzzle end from the opening.
  • a device for launching projectiles particularly a portable anti-tank projectile launcher, comprising a launching tube having a muzzle opening at one end for firing of a projectile therethrough, projectile mounting means within said tube for positioning a projectile adjacent said muzzle end for firing, a first piston adjacent said projectile, said tube having an opposite end witha recoil medium opening, a dense, flowable recoil medium in said tube adjacent said recoil opening end, a second piston adjacent said medium, a propelling charge within said tube for propelling the projectile located between said first and second pistons and being ignitable to force said first and second pistons in respective opposite directions to fire the projectile through the muzzle end and to discharge the medium through the recoil openings, said mass having diaphragm means associated therewith and which holds said mass within said tube but is dislodgeable from said tube by igntion of said charge, and vent means for venting said tube after said pistons have moved to the adjacent ends, and means for engaging said first and second pistons adjacent the
  • vent means includes an opening in said first piston.
  • vent means includes an opening in said tube located rearwardly of said first piston when said first piston has moved to said muzzle end.
  • a device for launching projectiles particularly a portable anti-tank projectile launcher, comprising a launching tube having a muzzle opening at one end for firing of a projectile therethrough, projectile mounting means within said tube for positioning a projectile adjacent said muzzle end for firing,ra first piston adjacent said projectile, said tube having an opposite end with a recoil medium opening, a dense, flowable recoil medium in said tube adjacent said recoil opening end, a second piston adjacent said medium, a propelling charge within said tube for propelling the projectile located between said first and second pistons and being ignitable to force said first and second pistons in respective opposite directions to fire the projectile through the muzzle end and to discharge the medium through the recoil openings, said mass having diaphragm means assoicated therewith and which holds said mass within said tube but is dislodgeable from said tube by ignition of said charge, and vent means for venting said tube after said pistons have moved to the adjacent ends, and means for engaging said first and second piston

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Actuator (AREA)
US00097479A 1970-01-16 1970-12-18 Launching tube for projectiles and missiles respectively Expired - Lifetime US3779130A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2001758A DE2001758C3 (de) 1970-01-16 1970-01-16 Abschußvorrichtung für Geschosse zur Panzerbekämpfung

Publications (1)

Publication Number Publication Date
US3779130A true US3779130A (en) 1973-12-18

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ID=5759729

Family Applications (1)

Application Number Title Priority Date Filing Date
US00097479A Expired - Lifetime US3779130A (en) 1970-01-16 1970-12-18 Launching tube for projectiles and missiles respectively

Country Status (7)

Country Link
US (1) US3779130A (OSRAM)
BE (1) BE760929A (OSRAM)
DE (1) DE2001758C3 (OSRAM)
FR (1) FR2166394A5 (OSRAM)
GB (1) GB1291336A (OSRAM)
NL (1) NL7100547A (OSRAM)
NO (1) NO128635B (OSRAM)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4050351A (en) * 1976-05-04 1977-09-27 Societe Anonyme Dite: Societe Europeenne Depropulsion Assembly for launching a projectile
US4148244A (en) * 1976-11-10 1979-04-10 Messerschmitt-Bolkow-Blohm Gesellschaft Mit Beschrankter Haftung Apparatus for braking a free piston, which is driven at high acceleration within a tube
US4172420A (en) * 1972-12-15 1979-10-30 Dynamit Nobel Aktiengesellschaft Propellant charge for recoilless weapons
US4244293A (en) * 1975-11-25 1981-01-13 Rheinmetall Gmbh Projectile designed for recoilless and virtually noiseless firing
US4676136A (en) * 1985-11-29 1987-06-30 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Apparatus for recoilless firing of projectiles from a lauching tube
US5515767A (en) * 1990-09-18 1996-05-14 Richmond Electronic And Engineering International Limited Device for firing a projectile
US5623113A (en) * 1994-07-19 1997-04-22 Etienne Lacroix Tous Artifices S.A. Pyrotechnic device for launching at least one projectile
US6286408B1 (en) 2000-01-04 2001-09-11 The United States Of America As Represented By The Secretary Of The Navy Energy-absorbing countermass assembly for recoilless weapons
US6408731B1 (en) * 1998-06-10 2002-06-25 Proparms Ltd. Liquid disrupter with reduced recoil
EP1348925A1 (en) 2002-03-26 2003-10-01 Raphael - Armament Development Authority Ltd. Recoilless projectile launcher
US7207254B2 (en) * 2001-03-27 2007-04-24 Mbda Uk Limited Launching of missiles
US7624668B1 (en) * 2005-06-10 2009-12-01 Sanford Matthew J Recoilless launching
US9534864B2 (en) 2014-12-16 2017-01-03 Proparms Ltd. Gas compensated recoilless liquid disrupter

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL7604649A (nl) * 1976-04-29 1977-11-01 Europ Propulsion Inrichting voor het lanceren van een projectiel.
DE3323069A1 (de) * 1983-06-27 1985-01-10 Hermann Dipl.-Ing. 5401 Kobern-Gondorf Bongers Treibladung mit axialkraft-ausgleich
FR2714165B1 (fr) * 1993-12-22 1996-02-09 Luchaire Defense Sa Système de contre-masse dispersable pour arme sans recul.
CN113587724A (zh) * 2021-06-16 2021-11-02 北京机械设备研究所 一种水下平衡发射装置及其发射方法

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB126336A (en) * 1916-12-20 1919-05-15 Andrew Jackson Stone Improvements connected with Ordnance.
US2499379A (en) * 1944-12-26 1950-03-07 Garrett Emil Grenade thrower
US2979991A (en) * 1951-10-10 1961-04-18 Martin Co Rapid firing recoilless bomb projecting device
US3279319A (en) * 1964-06-19 1966-10-18 Joseph W Semonian Floatable rocket launcher
US3490330A (en) * 1967-03-16 1970-01-20 Karlsruhe Augsburg Iweka Firearm,particularly light antitank weapon

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB126336A (en) * 1916-12-20 1919-05-15 Andrew Jackson Stone Improvements connected with Ordnance.
US2499379A (en) * 1944-12-26 1950-03-07 Garrett Emil Grenade thrower
US2979991A (en) * 1951-10-10 1961-04-18 Martin Co Rapid firing recoilless bomb projecting device
US3279319A (en) * 1964-06-19 1966-10-18 Joseph W Semonian Floatable rocket launcher
US3490330A (en) * 1967-03-16 1970-01-20 Karlsruhe Augsburg Iweka Firearm,particularly light antitank weapon

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4172420A (en) * 1972-12-15 1979-10-30 Dynamit Nobel Aktiengesellschaft Propellant charge for recoilless weapons
US4244293A (en) * 1975-11-25 1981-01-13 Rheinmetall Gmbh Projectile designed for recoilless and virtually noiseless firing
US4050351A (en) * 1976-05-04 1977-09-27 Societe Anonyme Dite: Societe Europeenne Depropulsion Assembly for launching a projectile
US4148244A (en) * 1976-11-10 1979-04-10 Messerschmitt-Bolkow-Blohm Gesellschaft Mit Beschrankter Haftung Apparatus for braking a free piston, which is driven at high acceleration within a tube
US4676136A (en) * 1985-11-29 1987-06-30 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Apparatus for recoilless firing of projectiles from a lauching tube
US5515767A (en) * 1990-09-18 1996-05-14 Richmond Electronic And Engineering International Limited Device for firing a projectile
US5623113A (en) * 1994-07-19 1997-04-22 Etienne Lacroix Tous Artifices S.A. Pyrotechnic device for launching at least one projectile
US6408731B1 (en) * 1998-06-10 2002-06-25 Proparms Ltd. Liquid disrupter with reduced recoil
US6286408B1 (en) 2000-01-04 2001-09-11 The United States Of America As Represented By The Secretary Of The Navy Energy-absorbing countermass assembly for recoilless weapons
US7207254B2 (en) * 2001-03-27 2007-04-24 Mbda Uk Limited Launching of missiles
EP1348925A1 (en) 2002-03-26 2003-10-01 Raphael - Armament Development Authority Ltd. Recoilless projectile launcher
US7624668B1 (en) * 2005-06-10 2009-12-01 Sanford Matthew J Recoilless launching
US7841267B1 (en) * 2005-06-10 2010-11-30 The United States Of America As Represented By The Navy Recoilless launching
US9534864B2 (en) 2014-12-16 2017-01-03 Proparms Ltd. Gas compensated recoilless liquid disrupter

Also Published As

Publication number Publication date
NL7100547A (OSRAM) 1972-09-25
DE2001758B2 (de) 1973-08-16
GB1291336A (en) 1972-10-04
NO128635B (OSRAM) 1973-12-17
DE2001758A1 (de) 1972-10-26
FR2166394A5 (OSRAM) 1973-08-17
BE760929A (fr) 1972-09-08
DE2001758C3 (de) 1974-03-21

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