EP0525305B1 - Selbstschutz-Werfereinrichtung - Google Patents

Selbstschutz-Werfereinrichtung Download PDF

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Publication number
EP0525305B1
EP0525305B1 EP92106652A EP92106652A EP0525305B1 EP 0525305 B1 EP0525305 B1 EP 0525305B1 EP 92106652 A EP92106652 A EP 92106652A EP 92106652 A EP92106652 A EP 92106652A EP 0525305 B1 EP0525305 B1 EP 0525305B1
Authority
EP
European Patent Office
Prior art keywords
charge
missile
igniting
lead
launcher 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.)
Expired - Lifetime
Application number
EP92106652A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0525305A1 (de
Inventor
Wolfgang Dipl.-Ing. Badura
Fritz Greindl
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.)
Buck Chemisch Technische Werke GmbH and Co
Buck Werke GmbH and Co
Original Assignee
Buck Chemisch Technische Werke GmbH and Co
Buck Werke GmbH and Co
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 Buck Chemisch Technische Werke GmbH and Co, Buck Werke GmbH and Co filed Critical Buck Chemisch Technische Werke GmbH and Co
Publication of EP0525305A1 publication Critical patent/EP0525305A1/de
Application granted granted Critical
Publication of EP0525305B1 publication Critical patent/EP0525305B1/de
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
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C7/00—Fuzes actuated by application of a predetermined mechanical force, e.g. tension, torsion, pressure
    • F42C7/12—Percussion fuzes of the double-action type, i.e. fuzes cocked and fired in a single movement, e.g. by pulling an incorporated percussion pin or hammer
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/68—Line-carrying missiles, e.g. for life-saving
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02—Cartridges, i.e. cases with charge and missile
    • F42B5/145—Cartridges, i.e. cases with charge and missile for dispensing gases, vapours, powders, particles or chemically-reactive substances
    • F42B5/15—Cartridges, i.e. cases with charge and missile for dispensing gases, vapours, powders, particles or chemically-reactive substances for creating a screening or decoy effect, e.g. using radar chaff or infrared material
    • F42B5/155—Smoke-pot projectors, e.g. arranged on vehicles

Definitions

  • the invention relates to self-protection launchers, such as those used for protecting tanks.
  • the launcher device consists of a plurality of launcher tubes, which are attached to a suitable location on the outer surface of the tank, and throwing bodies inserted into the launcher tubes, which contain a propellant charge and an active charge, the latter mostly being a fog charge.
  • the firing of the throwing bodies takes place electrically from the inside of the tank, ignition contacts being arranged in the launch tube, which are in contact with contact rings located on the throwing body jacket.
  • Contactless namely inductive ignition systems are also known.
  • the electrical energy received via contacts or contactlessly is used to ignite the propellant charge, in which case the hot propellant gases in turn ignite the active charge via a pyrotechnic ignition chain with a delay element.
  • the safety and effectiveness of the protective measure are of particular importance in such a throwing device. So it must be ensured that there is no ignition of the active charge in the launch tube (pipe safety) or in the vicinity of the pipe mouth (front pipe safety and rail safety), the latter even then not if the missile hits an obstacle (tree) before it reaches its specified firing range. These safety problems also arise when the active charge is ignited not by a pyrotechnic ignition chain but by an impact detonator.
  • the effectiveness of the protective measure depends, on the one hand, on the accuracy of the missile and, on the other hand, on the time between the time the missile was fired and the onset of protection, i.e. the formation of the cloud of fog.
  • the throwing body In today's throwing devices of this type, the throwing body is usually shot at an angle of 45 ° with respect to the horizontal, so that the trajectory of the throwing body is very steep, which leads to a comparatively long flight time with the result that it takes effect late and also causes problems. to allow the active charge to take effect exactly at the desired height above the ground, because the throwing body gains high speed in the steep fall phase of its trajectory, with which even the smallest deviations in the ignition timing have a considerable influence. Due to the further development of the attack measures, one is now also forced to improve the protective measures, in particular to ensure that protective effects occur faster than before. For this reason, efforts are being made to change from the previous steep trajectories to much flatter trajectories, down to 10 °.
  • the object of the present invention is therefore to improve self-protection launcher devices of the type described so that safety and accuracy (to be defined later) are ensured even with a flat and short trajectory.
  • the solution to this problem results from the characterizing features of patent claim 1.
  • the projectile thus remains connected to the launch site after it has been fired via a safety line and this safety line is dimensioned in such a length that it reaches its full extent when the specified range is reached by the projectile, with the result that it has the
  • the throwing body brakes abruptly, tensioning the firing pin spring and releasing the firing pin so that it ignites the active charge, for example via a primer and an ignition charge.
  • the actual range of the missile is determined by the length of the safety line, which can be done very precisely and leads to an unusually high accuracy.
  • the firing pin spring is only tensioned by pulling the safety line and the firing pin is then released, which leads to very high tube, down tube and rail safety.
  • suspension line is slightly shorter than the range specified by the propellant charge or the propellant charge would allow the throwing body a slightly larger range than is permitted by the suspension line, because only then does the jerk required for tensioning the firing pin spring occur. If the throwing body hit the ground exactly at the distance from the launching point, which corresponds to the length of the line, there would be no ignition of the active charge. Even immediately before the desired meeting point, there is still a high level of security (final phase security).
  • the throwing body has a cup-like housing sleeve 10, the area adjacent to the cup base is thickened and the front cup opening of which is closed by a cover 11, which is also the base of a spontaneous active charge to be explained later; the lid 11 is held by means of a flanging of the sleeve edge, a sealing ring 12 ensuring a watertight closure.
  • the secondary side of an inductive ignition system consisting of a ferrite core 13 and a transformer coil 14, is attached to the bottom of the cup.
  • a comparatively massive and heavy anchor cover 15 with a central bore sits on the bottom of the cup, on which in turn a propellant chamber housing 16 is seated, which contains a propellant charge 17 filled with propellant charge 17 18 surrounds.
  • the propellant charge chamber 18 is covered by a thin film against the central bore of the anchor cover 15, in which an ignition pill 19 is located.
  • a suspension line primary part 21 which consists of comparatively short suspension lines which are held at one end on the drive chamber housing 16 and at the other ends on the anchor cover 15, which in turn is attached to the cup base by means of a separating element 22 and a time delay piece 23.
  • Six primary lines 21 of this type are provided coaxially to the longitudinal axis of the throwing body.
  • a drum 24 is seated for the secondary secondary line 25, which consists of a comparatively long secondary line, with its one end is attached to the drum 24 and with its other end to a central piece 26 which is held in the central opening of the ring base 27 of a point mist body container to be explained later.
  • a central support tube 28 From the central opening of the ring base 27 there is a central support tube 28, in which a piston rod 29 is slidably mounted, which is attached at one end to the central piece 26 and at the other end is connected to a firing pin 31 by means of a coupling piece 30.
  • a firing pin spring is designated.
  • a point mist charge 33 consisting of ring bodies is accommodated, which is covered on the end side by a compensating disk 42 and on the other hand by an ignition distributor cover 34.
  • the ignition distributor cover 34 contains an ignition cap 35, which is located in the path of movement of the firing pin 31, a transmission charge 36, a delay piece 37 and an ignition charge 38 for the point mist charge 33.
  • a spontaneous mist body 39 is arranged on the outside of the ignition distributor cover 34, in which is in extension to the firing pin axis an ignition-splitter charge 40 which is connected to the transfer charge 36 via an opening in the ignition distributor cover 34.
  • the point mist body container 41 is connected to the spontaneous mist body 39 via coupling pins 43, so that an active charge double body results.
  • the anchor cover 15 with the separating element 22 and the delay piece 23 and the secondary part 13, 14 of the ignition system remain in the launch tube.
  • the primary part 21 of the suspension line which is fastened at one end to the propellant charge housing 16, is carried along with the throwing body double body.
  • the length of the six individual lines of the primary part 21 is such that they are completely tensioned when the double body has left the mouth of the housing sleeve 10, at which point in time the propellant charge 17 also burned off.
  • An example value for the length of the primary part 21 of the safety line is 0.5 m.
  • the projectile is, for example, at a distance of 45 m from the launch site and at a height of 4.5 m above the ground.
  • the ignition occurs in such a way that the secondary part 25 of the suspension line pulls jerkily on the central piece 26, with the result that the firing pin 31 is pulled backwards via the piston rod 29, the spring 22 being tensioned.
  • the "jerk” mentioned is damped in such a way that comparatively small suspension line cross sections can be used; the damping results on the one hand from the elasticity of the tether system and on the other hand through the air column 44, which is compressed by the piston rod 29.
  • the firing pin 31 strikes against a stop, and as a result of the further pulling of the suspension line on The central piece 26 and thus on the piston rod 29 tears the coupling piece 30, that is, the connection between the piston rod 29 and firing pin 31 is released, so that the firing pin 31 strikes forward against the primer 35 by the now relaxing spring 32.
  • This movement is supported by the inertia of the firing pin.
  • the primer 35 struck by the firing pin 31 ignites the transfer charge 36, which in turn ignites the igniter charge 40, which leads to a spontaneous development of fog due to the fog charge 39; the transfer charge 36 also ignites the time delay piece 37, which, after a certain time delay, ignites the ignition charges 38, with the result that the point fog charge 33 begins to form fog.
  • the hot propellant gases generated when the propellant charge 17 burned off also ignited the time delay element 23 via a suitable channel. Its time delay is such that when the point mist body has reached the bottom, for example 2 seconds after firing, it has burned out and ignites the separating device 22, which releases the connection on the anchor cover 15 to the housing sleeve 10; The lines are therefore separated from the part of the throwing body remaining in the launch tube. This is also indicated in sketch D of FIG. 2.
  • the safety line system ensures an exact ignition at the desired distance from the firing point, at a predetermined height above the ground.
  • the throwing body like the Exemplary embodiment, a double body
  • the problem is to put the double body into operation at a speed of about 150 km / h at a target point, the front body above the ground and the rear body on the ground to release a cloud of fog.
  • clouds of fog should mix, that is, they form an overall cloud standing spatially one above the other.
  • an extremely precise ignition is obviously required, and this is achieved with the safety line system described.
  • the interception of the propellant charge housing 16 and the drum 24 by the primary safety lines 21 shortly after the double body emerges from the mouth of the housing sleeve 10 is important; this means that the center of gravity is shifted forward on the double body, with the result of an exact flight of the double body with exact unwinding of the secondary suspension line.
  • the safety line system By dividing the safety line system into a primary part consisting of several safety lines and a secondary part consisting of only one safety line, a high safety line safety in the area of the hot propellant gases is achieved without taking up too much space and weight for the safety line system in the throwing body.
  • the front end of the secondary secondary line can also be divided into several individual secondary lines in order to obtain the most axial pull possible on the central piece 26.
  • a strain relief in the form of a clamping ring 45 is provided for the firing pin 31, which prevents tensioning of the firing pin spring 32 during the flight. Only the interception energy at the target point overcomes the clamping force of the ring 45 and then allows the spring 32 to be tensioned.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Toys (AREA)
EP92106652A 1991-07-31 1992-04-16 Selbstschutz-Werfereinrichtung Expired - Lifetime EP0525305B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4125355 1991-07-31
DE4125355A DE4125355C1 (enrdf_load_stackoverflow) 1991-07-31 1991-07-31

Publications (2)

Publication Number Publication Date
EP0525305A1 EP0525305A1 (de) 1993-02-03
EP0525305B1 true EP0525305B1 (de) 1995-01-11

Family

ID=6437408

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92106652A Expired - Lifetime EP0525305B1 (de) 1991-07-31 1992-04-16 Selbstschutz-Werfereinrichtung

Country Status (4)

Country Link
US (1) US5272981A (enrdf_load_stackoverflow)
EP (1) EP0525305B1 (enrdf_load_stackoverflow)
CA (1) CA2068399A1 (enrdf_load_stackoverflow)
DE (2) DE4125355C1 (enrdf_load_stackoverflow)

Families Citing this family (23)

* Cited by examiner, † Cited by third party
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DE4302413C1 (de) * 1991-07-31 1994-03-17 Buck Chem Tech Werke Selbstschutz-Werfereinrichtung mit Fangleine
DE4337680C2 (de) * 1993-11-04 1995-08-24 Buck Chem Tech Werke Zweikomponenten-Nebelwurfkörper
EP0687885B1 (en) * 1993-12-01 1998-09-16 Konstruktorskoe Bjuro Mashinostroenia Vehicle self-defence system
DE4340905C2 (de) * 1993-12-01 1998-12-10 Daimler Benz Aerospace Ag Verfahren zum Bekämpfen von gewalttätigen Personen
FR2930984A1 (fr) * 1994-03-15 2009-11-13 Poudres Et Explosifs Snpe Sa S Procede et munitions de contre-mesure par ecran a vision unidirectionnelle
US5750918A (en) * 1995-10-17 1998-05-12 Foster-Miller, Inc. Ballistically deployed restraining net
FR2741434B1 (fr) * 1995-11-17 1998-01-30 Giat Ind Sa Procede de dispersion ou d'application d'un materiau actif et composition mise en oeuvre pour un tel procede
FR2741435B1 (fr) * 1995-11-17 1998-01-02 Giat Ind Sa Projectile permettant la dispersion d'un produit sur trajectoire
DE69608644T2 (de) * 1995-11-17 2000-09-21 Giat Industries, Versailles Dispersions- oder Auftragungsverfahren eines aktiven Materials, Zusammensetzung und Gemäss diesem Verfahren hergestelltes Geschoss
FR2741433B1 (fr) * 1995-11-17 1998-01-02 Giat Ind Sa Dispositif pour lancer un projectile non letal
DE19543489C1 (de) * 1995-11-22 1997-06-26 Buck Chem Tech Werke Schutzeinrichtung für sich rasch bewegende Objekte
RU2135926C1 (ru) * 1998-02-03 1999-08-27 Российский Федеральный Ядерный Центр - Всероссийский Научно-Исследовательский Институт Экспериментальной Физики Газодинамический источник давления
RU2135927C1 (ru) * 1998-02-03 1999-08-27 Российский Федеральный Ядерный Центр - Всероссийский Научно-Исследовательский Институт Экспериментальной Физики Газодинамический источник давления
RU2166722C2 (ru) * 1999-06-22 2001-05-10 Российский Федеральный Ядерный Центр - Всероссийский Научно-Исследовательский Институт Экспериментальной Физики Устройство для инициирования заряда в полете
DE10226507A1 (de) * 2002-06-14 2003-12-24 Diehl Munitionssysteme Gmbh Nebelwurfkörper
FR2886003B1 (fr) * 2005-05-20 2007-08-17 Lacroix Soc E Cartouche d'entrainement a securite simplifiee
FR2914054B1 (fr) * 2007-03-19 2009-06-05 Nexter Systems Sa Dispositif de protection rapprochee
EP2232191A4 (en) 2007-09-18 2013-03-27 Pepperball Technologies Inc SYSTEMS, METHODS AND APPARATUSES FOR USE IN INHIBITING POWDER DISPENSING
RU2357181C1 (ru) * 2008-01-28 2009-05-27 Российская Федерация, от имени которой выступает Государственный заказчик - Федеральное агентство по атомной энергии Газодинамический источник давления
FR2937123B1 (fr) * 2008-10-13 2016-09-16 Nexter Munitions Munition de controle des foules a effet non letal
ES2392984A1 (es) * 2010-05-10 2012-12-17 Falken, S.A. Artificio de ocultación multiespectral
CN103486911B (zh) * 2013-09-13 2015-04-22 长沙凯维科技有限公司 预装发热电阻丝的单发烟花底座及对应固定基座
JP6563773B2 (ja) * 2015-10-20 2019-08-21 株式会社ダイセル 煙幕発生器

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US4726295A (en) * 1986-05-16 1988-02-23 Aai Corporation Grenade arrangement for screening cloud
CA1311391C (en) * 1988-09-23 1992-12-15 Stephen B. Murray Fuel-air line-charge ordnance neutralizer
US5042390A (en) * 1989-10-18 1991-08-27 Hughes Aircraft Company Apparatus for lauching umbilical-guided missiles

Also Published As

Publication number Publication date
DE4125355C1 (enrdf_load_stackoverflow) 1993-01-28
DE59201177D1 (de) 1995-02-23
CA2068399A1 (en) 1993-02-01
EP0525305A1 (de) 1993-02-03
US5272981A (en) 1993-12-28

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