EP1936317B1 - Nozzle - Google Patents

Nozzle Download PDF

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Publication number
EP1936317B1
EP1936317B1 EP06126990A EP06126990A EP1936317B1 EP 1936317 B1 EP1936317 B1 EP 1936317B1 EP 06126990 A EP06126990 A EP 06126990A EP 06126990 A EP06126990 A EP 06126990A EP 1936317 B1 EP1936317 B1 EP 1936317B1
Authority
EP
European Patent Office
Prior art keywords
nozzle
opening
weapon
area
spoiler
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.)
Active
Application number
EP06126990A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1936317A1 (en
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 DE602006010422T priority Critical patent/DE602006010422D1/de
Priority to EP06126990A priority patent/EP1936317B1/en
Priority to AT06126990T priority patent/ATE448459T1/de
Priority to ES06126990T priority patent/ES2333666T3/es
Priority to US12/003,319 priority patent/US20100275763A1/en
Publication of EP1936317A1 publication Critical patent/EP1936317A1/en
Application granted granted Critical
Publication of EP1936317B1 publication Critical patent/EP1936317B1/en
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.
  • Document DE-A1-1578050 discloses a weapon that forms the basis for the preamble of claim 1.
  • 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 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.
  • 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. 2 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.
  • 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)
  • Percussion Or Vibration Massage (AREA)
  • Surgical Instruments (AREA)
EP06126990A 2006-12-22 2006-12-22 Nozzle Active EP1936317B1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
DE602006010422T DE602006010422D1 (de) 2006-12-22 2006-12-22 Düse
EP06126990A EP1936317B1 (en) 2006-12-22 2006-12-22 Nozzle
AT06126990T ATE448459T1 (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 (en) 2006-12-22 2006-12-22 Nozzle

Publications (2)

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

Family

ID=38038731

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06126990A Active EP1936317B1 (en) 2006-12-22 2006-12-22 Nozzle

Country Status (5)

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

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3625512B1 (en) * 2017-05-17 2022-09-28 Saab Ab Breech and method for noise reduction
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

Family Cites Families (19)

* 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
BE560119A (es) * 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
DE1428637C1 (de) * 1964-02-26 1975-02-20 Messerschmitt Boelkow Blohm Rohrfoermige Abschusseinrichtung fuer Geschosse,insbesondere fuer Flugkoerper
FR1410375A (fr) * 1964-07-30 1965-09-10 Tech De Rech S Eindustrielles Arme de faible encombrement
NL132545C (es) * 1967-03-16
DE1678189A1 (de) * 1968-03-12 1972-01-13 Ludwig Bucklisch Rueckstossfreie Waffe
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
SE525137C2 (sv) 2003-06-05 2004-12-07 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
SE524912C2 (sv) 2003-06-05 2004-10-19 Saab Ab Runt vapen trycksänkande motmassa i motmassebehållare innefattande styrande vikstöd för symmetriskt öppningsförlopp

Also Published As

Publication number Publication date
DE602006010422D1 (de) 2009-12-24
US20100275763A1 (en) 2010-11-04
ES2333666T3 (es) 2010-02-25
EP1936317A1 (en) 2008-06-25
ATE448459T1 (de) 2009-11-15

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