EP0406114B1 - Dispositif d'éjection pour munition amphibie et propulseur indépendant en faisant partie - Google Patents

Dispositif d'éjection pour munition amphibie et propulseur indépendant en faisant partie Download PDF

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Publication number
EP0406114B1
EP0406114B1 EP19900401862 EP90401862A EP0406114B1 EP 0406114 B1 EP0406114 B1 EP 0406114B1 EP 19900401862 EP19900401862 EP 19900401862 EP 90401862 A EP90401862 A EP 90401862A EP 0406114 B1 EP0406114 B1 EP 0406114B1
Authority
EP
European Patent Office
Prior art keywords
amphibious
munition
motor
tube
ignition
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
Application number
EP19900401862
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0406114A1 (fr
Inventor
Lionel Knur
Roland Siegwald
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 Group SAS
Original Assignee
Airbus Group SAS
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 Airbus Group SAS filed Critical Airbus Group SAS
Publication of EP0406114A1 publication Critical patent/EP0406114A1/fr
Application granted granted Critical
Publication of EP0406114B1 publication Critical patent/EP0406114B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B17/00—Rocket torpedoes, i.e. missiles provided with separate propulsion means for movement through air and through water
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/08—Rocket or torpedo launchers for marine torpedoes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/08—Rocket or torpedo launchers for marine torpedoes
    • F41F3/10—Rocket or torpedo launchers for marine torpedoes from below the surface of the water

Definitions

  • the invention relates to a device for ejecting amphibious ammunition from a submarine not equipped with a hunting system.
  • amphibious ammunition in particular of the type described in French patent 2,588,241, can only be ejected by submarines equipped with hunting systems.
  • Document BE-A-411,330 describes a torpedo launching device without hunting system, limited to the very specific case of torpedoes provided with an annular propellant mounted at the periphery of the body of these torpedoes.
  • the invention aims to overcome this drawback and to allow any amphibious ammunition to be ejected with maximum security from any marine or submarine vehicle provided with a torpedo tube.
  • the invention as claimed in claim 1, provides for this purpose an ejection device for amphibious ammunition comprising a torpedo tube in which is disposed a powder propellant independent of the ammunition, characterized in that this propellant powder is independent of the torpedo tube and is placed with its ignition assembly resting on the rear of this ammunition so as to push and accompany this ammunition beyond the exit of the tube and then to separate from it.
  • the invention thus proposes to have in the launch tube a small propellant at the rear of the ammunition adapted to push it so as to allow it to reach a tube exit speed which can range in practice from 5 to 30 m / s .
  • This propellant is disposable.
  • the invention also relates to the aforementioned propellant per se.
  • the propellant is dimensioned so that it can eject ammunition when the launching submarine is between 0 and 750 m deep. Its total size can be contained in a cylinder 200 to 300 mm in diameter and 300 to 400 mm in length.
  • FIG. 1 represents an ejection device 1 according to the invention, adapted to eject an amphibious munition 2 such as a missile of weight P, devoid of autonomous means of ejection propulsion. It is preferably an amphibious missile in accordance with patent FR-2. 588 241.
  • This munition has an exterior shell 2A provided with rear fins 2B. Electric connection cables 2C are also provided here.
  • This device comprises a torpedo tube 3 of any known type, here comprising a front tube 4, and a propellant 5 disposed at the rear of the munition 2.
  • the torpedo tube 3 has an internal door 6 and an airlock door 7 while the front tube 4 has an external door 8 provided with maneuvering means 8A and allowing communication with the marine environment as well as slides marked 9.
  • 7A is shown the airlock door 7 in the open position.
  • the longitudinal axis X-X of the munition 2 is here slightly offset downward relative to the longitudinal axis Y-Y of the entire torpedo tube.
  • the propellant is positioned, in contact against the bottom of the munition, thanks to a connection system 30.
  • the primary safety ignition device 11 includes electrical igniters shown schematically in 11B as well as a small primary charge of ignition powder shown schematically in 11C (of all known suitable types). It is armed by means of an electric motor integrated into the igniter, shown diagrammatically in 11A. Wires 16 ensure the connection of the igniter to a control block 17. Signals from judiciously arranged sensors, conventional but not shown, are applied to this block so as to allow it to activate the electric motor only when at the less the front door 8 of the torpedo tube is open. This motor is reversible and can be returned to the safety position by reversing the electric current.
  • the secondary ignition device 12 is composed of ignition powder. It is ignited by the primary safety ignition device 11.
  • the block of powder 13 inhibited laterally is of radial combustion and operates under high pressure; it supplies the gases necessary for propulsion.
  • it presents a channel 18 with a star profile (which explains the variations in thickness appearing in FIG. 3).
  • the hull 14 of the propellant is composed of a very thin metallic internal envelope ensuring the sealing, which is covered with wound glass wires coated in a thermosetting resin of any suitable known type and ensuring the mechanical resistance of the assembly.
  • the winding can be made of carbon, kevlar or the like.
  • This wound structure has the advantage, in the event of bursting, of avoiding any significant metallic projections which could damage the interior of the torpedo tube.
  • This shell is thermally protected at the front by a system 19 which also ensures, here, the wedging of the block and at the rear by a cap 20 for thermal protection of the bottom.
  • the nozzle 15, here unique, allows the ejection of the combustion gases and is kept sealed, before firing, by a cover 21 until an external pressure greater than that corresponding to the maximum depth of use of the ammunition. However, in the event of a fire, the pressure of the combustion gases is sufficient to eject this seal.
  • the propellant has a transverse face 22 adapted to be faced at the rear of the ammunition 2, by simple pressing or by positioning and / or connecting means such as ball fixing systems, shearable. Or other.
  • the connection system 30 comprises a connection plate 31 fixed to the propellant by means of holes 32, and temporarily linked to the ammunition by frangible connection members of any suitable known cooperating type. with threads conventionally provided at the rear of the ammunition.
  • the ammunition assembly 3 and its additional propellant 4 are introduced into the "dry" torpedo tube 1 from the interior of the submarine (from the right in FIG. 1) and put in place using conventional on-board tools .
  • the outer door 8 of the tube is opened and the tube is drowned.
  • the hot gases from the igniter ignite the secondary charge 12 which allows the ignition of the block 13.
  • the combustion gases exiting through the nozzle 9 create a thrust which, transmitted by the bearing face 22 and the connection system 30, allows the ammunition 2 to exit the torpedo tube with the speed necessary for the pursuit of the mission.
  • this thrust also has the effect, shortly after firing, of breaking the connecting members with the ammunition, the propellant no longer being then only by pressing against the ammunition for its ejection.
  • the ammunition-pusher assembly is guided through the torpedo tube.
  • Said pusher at the end of combustion can disengage from the ammunition by gravity (cessation of support on the ammunition) or by ejection (in the case for example of the firing at this instant of a propellant integrated into the missile and inert until then, as for example in the case of the patent FR-2,588,241 cited above). The pusher is then lost.
  • the pyrotechnic pusher can operate up to a depth of 750 m. Its nozzle is adapted to an intermediate depth with a corresponding outlet pressure.
  • the internal pressure of the order of 100 to 200 bars, makes it possible to obtain a good efficiency of the nozzle.
  • the duration of operation of said pyrotechnic pusher is between 0.5 and 2 seconds. It is recalled in this connection that at sea level at a temperature of 20 ° C, the effective combustion time of a mass of powder from 5 to 10 kg is between 0.5 and 2 seconds and the average force corresponding effective is of the order of 5,000 to 20,000 newton (N).

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Ocean & Marine Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Automotive Seat Belt Assembly (AREA)
  • Paper (AREA)
  • Fire-Extinguishing By Fire Departments, And Fire-Extinguishing Equipment And Control Thereof (AREA)
EP19900401862 1989-06-30 1990-06-28 Dispositif d'éjection pour munition amphibie et propulseur indépendant en faisant partie Expired - Lifetime EP0406114B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8908841 1989-06-30
FR8908841A FR2649194B1 (fr) 1989-06-30 1989-06-30 Dispositif d'ejection pour munition amphibie et propulseur independant en faisant partie

Publications (2)

Publication Number Publication Date
EP0406114A1 EP0406114A1 (fr) 1991-01-02
EP0406114B1 true EP0406114B1 (fr) 1993-09-08

Family

ID=9383360

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19900401862 Expired - Lifetime EP0406114B1 (fr) 1989-06-30 1990-06-28 Dispositif d'éjection pour munition amphibie et propulseur indépendant en faisant partie

Country Status (6)

Country Link
EP (1) EP0406114B1 (da)
BR (1) BR9003075A (da)
DE (1) DE69003190T2 (da)
DK (1) DK0406114T3 (da)
ES (1) ES2044483T3 (da)
FR (1) FR2649194B1 (da)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2407148B (en) * 1996-07-04 2005-08-03 Secr Defence Weapon system for attack of underwater targets
GB2608782B (en) * 1998-06-04 2024-04-10 Bae Systems Plc Underwater launch system
FR2965913B1 (fr) 2010-10-08 2013-04-05 IFP Energies Nouvelles Dispositif de detection de la presence d'un fluide, tel qu'un fluide liquide, dans un espace d'un contenant et methode utilisant un tel dispositif
DE102013006003A1 (de) * 2013-04-09 2014-10-09 Diehl Bgt Defence Gmbh & Co. Kg Verfahren zum Starten eines Lenkflugkörpers
DE102018222490A1 (de) * 2018-12-20 2020-06-25 Atlas Elektronik Gmbh Vorrichtung und Verfahren zum Starten eines Unterwasser-Laufkörpers von einem Wasserfahrzeug aus

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE411330A (da) *
US1418795A (en) * 1916-01-12 1922-06-06 Jr John Hays Hammond Launching mechanism for torpedoes
FR2588241B1 (fr) * 1969-11-13 1989-03-10 Aerospatiale Engin amphibie.
DE3048666C2 (de) * 1980-12-23 1986-05-22 Ingenieurkontor Lübeck Prof. Gabler Nachf. GmbH, 2400 Lübeck Autarke Ausstoßeinrichtung für Lenkwaffen

Also Published As

Publication number Publication date
FR2649194B1 (fr) 1994-05-13
DE69003190D1 (de) 1993-10-14
BR9003075A (pt) 1991-08-27
DE69003190T2 (de) 1994-01-20
ES2044483T3 (es) 1994-01-01
FR2649194A1 (fr) 1991-01-04
DK0406114T3 (da) 1993-10-25
EP0406114A1 (fr) 1991-01-02

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