EP1936317A1 - Buse - Google Patents

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Publication number
EP1936317A1
EP1936317A1 EP06126990A EP06126990A EP1936317A1 EP 1936317 A1 EP1936317 A1 EP 1936317A1 EP 06126990 A EP06126990 A EP 06126990A EP 06126990 A EP06126990 A EP 06126990A EP 1936317 A1 EP1936317 A1 EP 1936317A1
Authority
EP
European Patent Office
Prior art keywords
nozzle
opening
area
weapon
nozzle according
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.)
Granted
Application number
EP06126990A
Other languages
German (de)
English (en)
Other versions
EP1936317B1 (fr
Inventor
Andreas Malmlöf
Mili Dugalic'
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.)
Saab AB
Original Assignee
Saab AB
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Saab AB filed Critical Saab AB
Priority to AT06126990T priority Critical patent/ATE448459T1/de
Priority to EP06126990A priority patent/EP1936317B1/fr
Priority to DE602006010422T priority patent/DE602006010422D1/de
Priority to ES06126990T priority patent/ES2333666T3/es
Priority to US12/003,319 priority patent/US20100275763A1/en
Publication of EP1936317A1 publication Critical patent/EP1936317A1/fr
Application granted granted Critical
Publication of EP1936317B1 publication Critical patent/EP1936317B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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

  • the present invention relates to a nozzle for a weapon comprising a launcher which constitutes a guide for a projectile or missile; the nozzle comprises a wall, a first opening connected to the launcher and a second opening. The area of the first opening is smaller than the area of the second opening.
  • Weapons such as handheld weapons from which a projectile or missiles are shot are in some cases provided with a launcher without a nozzle.
  • the nozzle is arranged in the rear end of a launcher which constitutes a guide for the projectile.
  • the projectile is guided by the launcher and leaves the front end of the launcher towards a target.
  • a flame is created by the projectile when the weapon is fired. The flame creates gases of high temperature which expands at the rear end of the launcher of the weapon, through the nozzle. In this connection also a high pressure being created behind the launcher.
  • the countermass may be a liquid enclosed in a container arranged in the launcher behind the projectile.
  • the countermass in form of liquid leaves the rear end of the weapon when the weapon is fired and thereby produces a pressure-reducing effect adjacent to the weapon when the countermass expands and disintegrates.
  • Documents SE 0301626-8 and SE 0301627-6 discloses examples of such countermass containers for weapons.
  • one drawback is that when the countermass is a liquid, a cloud is formed around the weapon, which makes it difficult to rapidly achieve a clear view of the target for firing the weapon again.
  • Another drawback of using a countermass is that an asymmetrical flow may be created in the countermass container, which can produce great shear forces on the weapon. Also, pieces from the container may come away from the container and constitute a risk behind the weapon.
  • the objective problem to be solved by the present invention is to avoid that a liquid cloud is formed around the weapon when the weapon is fired.
  • Another objective problem to be solved by the present invention is to reduce the pressure behind a weapon
  • Yet another objective problem to be solved by the present invention is to eliminate the need of a countermass in a weapon.
  • Yet another objective problem to be solved by the present invention is to reduce the recoil in the forward direction.
  • Ambient air is used to reduce the temperature of the hot gases which leaves the rear end of the weapon through the nozzle.
  • energy is transformed which reduces also the pressure inside the hot gases. Since the pressure is reduced also the recoil on the weapon is reduced.
  • the ambient air is introduced in the hot gases by the means provided at the nozzle.
  • said means is a number of third openings arranged in the wall of the nozzle at the area of the second opening.
  • ambient air is sucked in through the third openings by the gases that flow through the nozzle.
  • the ambient air reduces the temperature of the gases from the projectile.
  • the gases within the nozzle are over expanded.
  • said means is a spoiler is arranged substantially inside the nozzle in the area of the second opening.
  • the spoiler creates a low pressure on one of its surfaces when the gases pass the spoiler. The low pressure reduces the temperature of the gases. Also, the low pressure created by the spoiler leads to that ambient air is sucked in through the second opening of the nozzle and thereby reduces the temperature of the gases from the projectile.
  • the gases within the nozzle are under expanded.
  • a circumferential element is arranged at the first opening of the nozzle.
  • the circumferential element has an opening area which is less than the area of the first opening of the nozzle. The effect achieved by this element is that recoil in the forward direction is reduced when the weapon is fired.
  • a weapon with such a nozzle is easy to handle, cost effective when manufacturing and have no problems with shear forces which may occur when using a countermass.
  • Fig. 1 shows a section view of a nozzle 1 according to a first embodiment of the invention.
  • the nozzle 1 is arranged on a weapon 2, which comprises a launcher 4 which constitutes a guide for a projectile or missile 6.
  • the launcher 4 and the projectile 6 are schematically disclosed in the figure.
  • the nozzle 1 comprises a circumferential cone shaped wall 8, which defines a first opening 10 and a second opening 12.
  • the first opening 10 of the nozzle 1 is connected to the launcher 4.
  • the first opening 10 is an interface section or a throat of the nozzle 1 and in this case the interface section is in the substantially same plane as the throat.
  • the area of the first opening 10 is smaller than the area of the second opening 12, so that the nozzle has the form of a funnel.
  • the first and second openings 10, 12 are substantially cylindrical and are arranged substantially concentric with each others.
  • the second opening 2 of the nozzle is an exit section.
  • a gas generator 14 is arranged in the area of the first opening 10. When the weapon 2 is fired a pressure is exerted on the gas generator 14 from the projectile 6. The diameter of the gas generator 14 is so dimensioned that the forces from the projectile 6 on the gas generator 14 and the nozzle 1 will reduce the recoil when the weapon 2 is fired.
  • the gas generator 14 is attached to the launcher 4 by fastening means (not disclosed).
  • the nozzle 1 is provided with means 18 for reducing the pressure of gases 16 from the projectile 6 inside and behind the nozzle 1 when firing the weapon 2. Said means 18 is arranged at the second opening 12 of the nozzle 1.
  • said means 18 is a number of third openings 18 arranged in the wall 8 of the nozzle 1 at the area of the second opening 12.
  • said third openings 18 are arranged circumferential in a row in the wall 8 of the nozzle 1.
  • the area of each third opening 18 is substantially equal and the area of each third opening 18 is essentially smaller than the second opening 12.
  • the third openings 18 are so arranged in the wall 8 of the nozzle 1 that a centre axis 20 of each third opening 18 will intersect each other in a common point P, which is indicted in fig. 1 .
  • ambient air is sucked in through the third openings 18 by the gases 16 that flow through the nozzle 1.
  • the ambient air reduces the temperature of the gases 16 from the projectile 6.
  • ambient air is introduced in the hot gases 16, energy is transformed which reduces the pressure inside the hot gases 16. Since the pressure is reduced also the recoil on the weapon 2 is reduced.
  • said means 18 is a spoiler 18' arranged substantially inside the nozzle 1 in the area of the second opening 12.
  • the spoiler 18' is so arranged inside the nozzle 1 that an opening gap 22 is created between the wall 8 of the nozzle 1 and the spoiler 18'.
  • Fig. 4 shows a perspective view of the second embodiment.
  • the spoiler 18' has a form which is substantial circular and is connected to the wall 8 by distance elements 24.
  • the distance elements 24 have an aerodynamic form that not disturbs the flow of the gases 16.
  • the gases 16 from the projectile 6 passes through the nozzle 1 with high velocity.
  • the spoiler 18' creates a low pressure on one of its surfaces when the gases 16 pass the spoiler 18', which is indicated in fig 5 .
  • the low pressure reduces the temperature of the gases 16 and the low pressure LP created by the spoiler 18' also leads to that ambient air is sucked in through the second opening 12 of the nozzle 1 and thereby reduces the temperature of the gases 16 from the projectile 6.
  • a circumferential element 26 is arranged at the first opening 10 of the nozzle 1.
  • This circumferential element 26 is disclosed in fig. 1 .
  • An opening area 28 of the circumferential element 26 is less than the area of the first opening 10 of nozzle 1.
  • a circumferential abutment 30 or edge is created by the element 26.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Toys (AREA)
  • Surgical Instruments (AREA)
  • Percussion Or Vibration Massage (AREA)
EP06126990A 2006-12-22 2006-12-22 Buse Active EP1936317B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
AT06126990T ATE448459T1 (de) 2006-12-22 2006-12-22 Düse
EP06126990A EP1936317B1 (fr) 2006-12-22 2006-12-22 Buse
DE602006010422T DE602006010422D1 (de) 2006-12-22 2006-12-22 Düse
ES06126990T ES2333666T3 (es) 2006-12-22 2006-12-22 Tobera.
US12/003,319 US20100275763A1 (en) 2006-12-22 2007-12-21 Nozzle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06126990A EP1936317B1 (fr) 2006-12-22 2006-12-22 Buse

Publications (2)

Publication Number Publication Date
EP1936317A1 true EP1936317A1 (fr) 2008-06-25
EP1936317B1 EP1936317B1 (fr) 2009-11-11

Family

ID=38038731

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06126990A Active EP1936317B1 (fr) 2006-12-22 2006-12-22 Buse

Country Status (5)

Country Link
US (1) US20100275763A1 (fr)
EP (1) EP1936317B1 (fr)
AT (1) ATE448459T1 (fr)
DE (1) DE602006010422D1 (fr)
ES (1) ES2333666T3 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3625512A4 (fr) * 2017-05-17 2020-12-09 Saab Ab Culasse et procédé de réduction de bruit

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2557151A (en) * 1944-08-24 1951-06-19 Leslie A Skinner Spring actuated generator for rocket launchers
US2598256A (en) * 1945-04-21 1952-05-27 Us Sec War Recoilless gun
NL6509893A (fr) * 1964-07-30 1966-01-31
GB1213711A (en) * 1967-03-16 1970-11-25 Karlsruhe Augsburg Iweka Improvements in firearms
DE1678189A1 (de) * 1968-03-12 1972-01-13 Ludwig Bucklisch Rueckstossfreie Waffe
SE0301627L (sv) 2003-06-05 2004-10-19 Saab Ab Runt vapen trycksänkande motmassa i motmassebehållare innefattande styrande vikstöd för symmetriskt öppningsförlopp
SE0301626L (sv) 2003-06-05 2004-12-06 Saab Ab Anordning vid vapen innefattande en motmassa för att sänka trycket kring vapnet, varvid motmassans huvudbeståndsdel är vätska som binds och hålls kvar av kapillärkrafter

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE560119A (fr) * 1956-09-13
US2956479A (en) * 1958-02-28 1960-10-18 Musser C Walton Cascaded gun barrel
US3035494A (en) * 1960-01-26 1962-05-22 Musser C Walton Recoil adjusting device
US3251552A (en) * 1963-03-07 1966-05-17 Douglas M Ford Exhaust nozzle for jet or rocket motors
DE977818C (de) * 1963-06-22 1970-12-17 Messerschmitt Boelkow Blohm Treibladungsanordnung fuer rohrfoermige Abschusseinrichtungen
US3208384A (en) * 1964-01-21 1965-09-28 Fountain Gilbert Rocket thrust neutralizer
FR1604112A (fr) * 1964-02-26 1971-07-12
SE416230B (sv) * 1976-05-17 1980-12-08 Bofors Ab Anordning for rekylfri utskjutning av en missil
US4043248A (en) * 1976-06-10 1977-08-23 General Electric Company Liquid propellant gun (recoilless regenerative piston)
US4091709A (en) * 1976-07-26 1978-05-30 The United States Of America As Represented By The Secretary Of The Army Recoilless rifle nozzle
US4203347A (en) * 1978-04-10 1980-05-20 The Boeing Company Shock suppressing apparatus and method for a rocket launcher
US4404887A (en) * 1980-06-23 1983-09-20 General Dynamics, Pomona Division Recoil reducer

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2557151A (en) * 1944-08-24 1951-06-19 Leslie A Skinner Spring actuated generator for rocket launchers
US2598256A (en) * 1945-04-21 1952-05-27 Us Sec War Recoilless gun
NL6509893A (fr) * 1964-07-30 1966-01-31
GB1213711A (en) * 1967-03-16 1970-11-25 Karlsruhe Augsburg Iweka Improvements in firearms
DE1678189A1 (de) * 1968-03-12 1972-01-13 Ludwig Bucklisch Rueckstossfreie Waffe
SE0301627L (sv) 2003-06-05 2004-10-19 Saab Ab Runt vapen trycksänkande motmassa i motmassebehållare innefattande styrande vikstöd för symmetriskt öppningsförlopp
SE0301626L (sv) 2003-06-05 2004-12-06 Saab Ab Anordning vid vapen innefattande en motmassa för att sänka trycket kring vapnet, varvid motmassans huvudbeståndsdel är vätska som binds och hålls kvar av kapillärkrafter
EP1484572A1 (fr) * 2003-06-05 2004-12-08 Saab Ab Arme à système de contrepoids et dispositif pour sceller le système de contrepoids

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3625512A4 (fr) * 2017-05-17 2020-12-09 Saab Ab Culasse et procédé de réduction de bruit
US11067354B2 (en) 2017-05-17 2021-07-20 Saab Ab Breech and method for noise reduction

Also Published As

Publication number Publication date
US20100275763A1 (en) 2010-11-04
DE602006010422D1 (de) 2009-12-24
EP1936317B1 (fr) 2009-11-11
ES2333666T3 (es) 2010-02-25
ATE448459T1 (de) 2009-11-15

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