EP0237711A2 - Allumeur pour charge propulsive d'une cartouche - Google Patents

Allumeur pour charge propulsive d'une cartouche Download PDF

Info

Publication number
EP0237711A2
EP0237711A2 EP87100480A EP87100480A EP0237711A2 EP 0237711 A2 EP0237711 A2 EP 0237711A2 EP 87100480 A EP87100480 A EP 87100480A EP 87100480 A EP87100480 A EP 87100480A EP 0237711 A2 EP0237711 A2 EP 0237711A2
Authority
EP
European Patent Office
Prior art keywords
ignition
tube
propellant
charge
openings
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
EP87100480A
Other languages
German (de)
English (en)
Other versions
EP0237711B1 (fr
EP0237711A3 (en
Inventor
Josef Fett
Guenter Huebsch
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.)
Dynamit Nobel AG
Original Assignee
BUNDESAMT fur WEHRTECHNIK und
Dynamit Nobel AG
Bundesrepublik Deutschland
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 BUNDESAMT fur WEHRTECHNIK und, Dynamit Nobel AG, Bundesrepublik Deutschland filed Critical BUNDESAMT fur WEHRTECHNIK und
Publication of EP0237711A2 publication Critical patent/EP0237711A2/fr
Publication of EP0237711A3 publication Critical patent/EP0237711A3/de
Application granted granted Critical
Publication of EP0237711B1 publication Critical patent/EP0237711B1/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
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/08—Primers; Detonators
    • F42C19/0823—Primers or igniters for the initiation or the propellant charge in a cartridged ammunition
    • F42C19/0826—Primers or igniters for the initiation or the propellant charge in a cartridged ammunition comprising an elongated perforated tube, i.e. flame tube, for the transmission of the initial energy to the propellant charge, e.g. used for artillery shells and kinetic energy penetrators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/08—Primers; Detonators
    • F42C19/0807—Primers; Detonators characterised by the particular configuration of the transmission channels from the priming energy source to the charge to be ignited, e.g. multiple channels, nozzles, diaphragms or filters

Definitions

  • the invention relates to a propellant lighter of the type specified in the preamble of claim 1.
  • a propellant lighter which is intended for cartridge ammunition with a poured propellant charge with an extremely high charge density.
  • the propellant lighter has a cylindrical ignition tube which, when the propellant lighter is installed, is arranged centrally within the propellant charge and extends practically from the bottom of the cartridge case to near the rear of the projectile inserted into the case.
  • the ignition tube has radial ignition openings on its lateral surface and an axial ignition opening on its front end facing the projectile rear. The result of this axial ignition opening is that the propellant charge powder located behind the projectile is only fired up in a very restricted sector due to the ignition flame spreading in the ignition tube, since the axial ignition beam is directed at a small central area of the rear end of the projectile.
  • the surrounding poured propellant charge is also ignited via radial and axial ignition openings in the ignition tube.
  • a comparatively short flame guide tube is additionally centrally arranged in the area of the rear end of the ignition tube, starting from the ignition piece at the rear end of the propellant charge lighter and ending at a distance from the booster charge built up from ring tablets.
  • the ignition beam emanating from the igniter and spreading forward over the flame guide tube leads to a direct ignition of the booster charge at its rear end with a corresponding radial ignition of the surrounding propellant charge.
  • the invention has for its object a propellant charge in the preamble of claim 1 given type so that a gentle ignition is achieved, with the same possible pressure and the largest possible surface area, which should proceed from the front end of the ignition tube to the rear at the highest possible speed.
  • the powder gases generated when the ignited booster charge burns off are carried along to the front end of the ignition tube and here contribute to an ignition promoting the ignition from the front end of the ignition tube Pressure build-up at.
  • the inventive fanning out of the ignition rays emerging from the front end of the ignition tube proves to be particularly advantageous in the case of projectiles with a tail unit arranged at the rear, since these are relatively deep in the cargo reach into the cartridge case and in which a more or less large amount of powder is arranged around the rear area of the projectile and the tail unit.
  • By fanning out the ignition rays direct ignition of the propellant powder located between the tail surfaces is also possible, as a result of which the proportion of the propellant powder ignited directly from the booster charge is correspondingly increased.
  • the ignition according to the invention also proves to be particularly advantageous in the case of storeys with a light track arranged in the rear, in order to avoid direct action on the light track which takes place at high pressure.
  • the ignition openings at the front end of the ignition tube are designed as flow channels for the ignition vapor, which lead to the formation of quasi-directed ignition jets.
  • the cross section of these openings or channels is preferably circular, but can also be oval or slot-shaped, for example. Their distribution is preferably even. The same also applies to the inclination of their center lines with respect to the longitudinal axis of the propellant charge lighter, so that all center lines intersect with the longitudinal axis at the same point. Depending on the circumstances of the individual case, different arrangements can also be provided in both cases.
  • the igniter tube can in principle be formed with a flat front end face, the thickness of the corresponding wall being sufficiently large to achieve the deflection of the ignition vapor leading to the spreading of the ignition rays through the inclined igniter openings in this end wall.
  • the front end is hood-shaped.
  • a dome shape can be provided.
  • the offs are preferred Formations according to claims 3 and 4.
  • the hood-shaped design has, among other things, the advantage over a flat end face that the design of the inclined ignition openings is simplified in terms of production technology.
  • the load on the individual particles of the propellant charge powder during a relative movement between the propellant charge lighter and the propellant charge is reduced by a more or less beveled, domed, dome-shaped design of the outer surface of the front ignition tube, as occurs, for example, when existing ammunition with a new propellant charge lighter is to be provided.
  • the front end of the ignition tube or the corresponding hood, which has the inclined ignition openings, can in principle be formed in one piece with it, but is preferably a separate component that is screwed, soldered or the like into the ignition tube.
  • the angle of inclination between the center lines of the ignition openings and the longitudinal axis of the propellant lighter is selected, for example, in accordance with the distance between the front end of the ignition tube and the projectile rear and the size of the clear cartridge case cross section in this area in such a way that the largest possible direct ignition of the propellant powder in the area behind or around the tailgate.
  • An inclination angle according to claim 5 is preferred.
  • the flame guide tube extends with its front region into the axial cavity of the booster charge.
  • An arrangement according to claim 6 is preferred.
  • the booster charge can consist, for example, of ring tablets arranged one behind the other in a known manner.
  • a combustible cylindrical inner tube can also be provided, which is inside of the ignition tube is arranged to form an annular cylindrical cavity, in which case this cavity in turn is filled with the actual booster charge, for example in powder form.
  • Other designs or arrangements of the booster charge are also possible, provided that a corresponding continuous axial channel is provided.
  • the hood-shaped design of the front end of the ignition tube has the further advantage over its flat end that the possibilities with regard to the number of inclined ignition openings and their spatial arrangement are increased.
  • the possibilities for this are further increased by training according to claim 7, in which case the hood acts like a "shower head", for example.
  • the training according to claim 8 can be provided.
  • the aforementioned propellant charge igniter achieves controllable, gentle and uniform ignition and conversion of the propellant charge powder by directly and locally igniting as large a portion of the propellant charge powder as possible, directly from the booster charge.
  • the rear end shown in Figure 1 of a cartridge ammunition for an armored barrel weapon has the cartridge case 17, in which the propellant lighter 18, starting from the bottom 17 ⁇ , is inserted extending axially and centrally forward.
  • the floor 9, of which only the rear can be seen is arranged with the tail unit 9 ⁇ .
  • the light trail 1o is housed in the rear floor.
  • the sabot 19 is indicated in the detail.
  • the space around the propellant lighter 18 and the tail 9 together with the tail unit 9 ⁇ takes up the propellant 8 from bulk powder.
  • the propellant charge lighter 18 has the ignition piece 1 arranged on the floor and the reinforcement set 6 accommodated therein.
  • the igniter 1 Connected to the igniter 1 is the axial cylindrical igniter tube 13 with the wall 12, in which the booster charge 3 consisting of ring tablets arranged one behind the other is accommodated at a distance from the booster set 6.
  • the flame guide tube 2 is arranged coaxially in the rear area of the ignition tube 13 and starts from the reinforcement set 6 and extends with its front area 2 ⁇ into the axial channel 16 of the booster charge 3, specifically in this case beyond the rearmost ring tablet.
  • the ignition tube 13 is provided on its cylindrical lateral surface 12 in a known manner with the radial ignition openings 7, which are designed here as bores.
  • the ogive-shaped hood 4 is arranged, which has the ignition openings 5, which are likewise designed as bores.
  • These ignition openings 5 are arranged so that their center lines 14 intersect with the longitudinal axis 15 of the propellant charge lighter 18 on the inside of the hood 4 at a common point.
  • the rupture disk 11 is arranged in a known manner between the ignition tube 13 and the hood 4.
  • the ignition flame emanating from the reinforcement set 6 passes through the interior of the flame guide tube 2 and the channel 16 of the booster charge 3 and finally reaches the hood 4.
  • the booster charge 3 is ignited on its inner lateral surface, thereby increasing the forward gas flow.
  • the ignition flame is spread according to the direction indicated by the center lines 14 into individual ignition beams, which cause a large-area ignition of the propellant particles located near the projectile tail and between the tail surfaces, with a primary direct exposure to the Light trail 1o is avoided.
  • the combustion of the booster charge 3 proceeds at a very high speed from the front end of the ignition tube 13 to the rear, whereby the surrounding propellant powder is ignited directly in the areas b1 to b7 via the ignition openings 7.
  • This axial and radial ignition sequence (ignition) which takes place in the microsecond range, avoids undesirable gas pressure peaks with regard to the internal ballistic behavior.
  • a projectile without the tail unit can of course also be inserted into the cartridge case 17.
  • FIG. 2 shows the front end of an ignition tube 13 on an enlarged scale compared to FIG. 1, whereby, in contrast to FIG. 1, the front end of the ignition tube 13 is also provided with a thick-walled flat end face 12 ⁇ .
  • the ignition openings 5 provided for the axial power output are formed in this end face and are inclined by the angle ⁇ in accordance with their center lines 14 with respect to the longitudinal axis 15 of the ignition tube 13.
  • the center lines intersect with the axis inside the ignition tube at point 2o.
  • the booster charge 3 is arranged in the interior of the ignition tube 13, bearing against the wall 12 thereof, which is designed here as a continuous powder charge arranged between the combustible sleeves 21 and 21 ⁇ .
  • the inner sleeve 21 simultaneously determines the size of the continuous channel 16 of the booster charge 3. Between the front end of the booster charge 3 and the front end face 12 ⁇ of the ignition tube 13, the spacer sleeve 22 is also arranged.
  • the radial ignition openings 7 formed in the wall 12 of the ignition tube 13 in a known manner are additionally provided with the cover 23, for example in the form of a film tube made of plastic, such as polyethylene, shrunk onto the outer surface of the wall 12.
  • the ignition tube 13 is provided at its front end with a hood 4, which is designed as a separate component and is screwed into the front end of the ignition tube 13.
  • the hood 4 is essentially frustoconical at its front end and is provided here with the four ignition openings 5 ⁇ , which are designed as funnels widening outwards.
  • the number of openings 5 ⁇ is not critical; depending on the conditions of the individual case, it can be smaller or larger.
  • an inclined arrangement corresponding to the angle ⁇ is provided between the center lines 14 and the longitudinal axis 15.
  • the hood 4 is also provided with the rupture disk 11 at its rear end.
  • the bond 24 made of, for example, epoxy resin is also provided in the region of its front end.
  • the booster charge 3 is made up of ring tablets 25 arranged one behind the other in columns and held at a distance from the hood 4 by means of the spacer sleeve 22.
  • the radial ignition openings 7 are again formed in the wall 12 and are covered on the outside by the cover 23.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Lighters Containing Fuel (AREA)
  • Air Bags (AREA)
EP19870100480 1986-01-18 1987-01-16 Allumeur pour charge propulsive d'une cartouche Expired - Lifetime EP0237711B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3601409 1986-01-18
DE3601409 1986-01-18

Publications (3)

Publication Number Publication Date
EP0237711A2 true EP0237711A2 (fr) 1987-09-23
EP0237711A3 EP0237711A3 (en) 1989-03-29
EP0237711B1 EP0237711B1 (fr) 1992-06-10

Family

ID=6292140

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19870100480 Expired - Lifetime EP0237711B1 (fr) 1986-01-18 1987-01-16 Allumeur pour charge propulsive d'une cartouche

Country Status (2)

Country Link
EP (1) EP0237711B1 (fr)
DE (1) DE3779679D1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0390756A2 (fr) * 1989-03-02 1990-10-03 Ab Bofors Allumeur pour charge propulsive
EP0428074A2 (fr) * 1989-11-16 1991-05-22 DIEHL GMBH & CO. Allumeur pour charge propulsive
FR2679994A1 (fr) * 1991-07-31 1993-02-05 Giat Ind Sa Dispositif d'allumage de la charge propulsive d'une munition, notamment telescopee, et munition initiee par un tel dispositif d'allumage.
EP0723134A3 (fr) * 1995-01-17 1996-11-13 Rheinmetall Ind Gmbh Cartouche comportant un projectile portant un traceur pyrotechnique
WO2010055086A1 (fr) * 2008-11-13 2010-05-20 Ruag Ammotec Gmbh Allumeur pyrotechnique
CN104534945A (zh) * 2014-12-13 2015-04-22 西安近代化学研究所 一种同步多点点火中心传火管
WO2018210579A1 (fr) * 2017-05-18 2018-11-22 Rheinmetall Waffe Munition Gmbh Système d'entraînement pour munition en cartouche

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE70361C (de) * 1893-01-13 H. ALLEN in London, Morley's Hotel, Trafalgar Square Geschofszünder mit elastisch gelagertem Detonator
US2366333A (en) * 1943-07-12 1945-01-02 Calumet And Hecla Cons Copper Primer and method of manufactureing and loading the same
US3151447A (en) * 1960-08-12 1964-10-06 Aerojet General Co Igniter device
DE3340618A1 (de) * 1983-11-10 1985-05-23 Bayern-Chemie Gesellschaft für flugchemische Antriebe mbH, 8261 Aschau Anzuendeinrichtung fuer einen treibsatz

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE70361C (de) * 1893-01-13 H. ALLEN in London, Morley's Hotel, Trafalgar Square Geschofszünder mit elastisch gelagertem Detonator
US2366333A (en) * 1943-07-12 1945-01-02 Calumet And Hecla Cons Copper Primer and method of manufactureing and loading the same
US3151447A (en) * 1960-08-12 1964-10-06 Aerojet General Co Igniter device
DE3340618A1 (de) * 1983-11-10 1985-05-23 Bayern-Chemie Gesellschaft für flugchemische Antriebe mbH, 8261 Aschau Anzuendeinrichtung fuer einen treibsatz

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0390756A2 (fr) * 1989-03-02 1990-10-03 Ab Bofors Allumeur pour charge propulsive
EP0390756B1 (fr) * 1989-03-02 1993-10-13 Ab Bofors Allumeur pour charge propulsive
EP0428074A2 (fr) * 1989-11-16 1991-05-22 DIEHL GMBH & CO. Allumeur pour charge propulsive
EP0428074A3 (en) * 1989-11-16 1992-08-26 Diehl Gmbh & Co. Igniter for propulsive charge
FR2679994A1 (fr) * 1991-07-31 1993-02-05 Giat Ind Sa Dispositif d'allumage de la charge propulsive d'une munition, notamment telescopee, et munition initiee par un tel dispositif d'allumage.
EP0723134A3 (fr) * 1995-01-17 1996-11-13 Rheinmetall Ind Gmbh Cartouche comportant un projectile portant un traceur pyrotechnique
US5625163A (en) * 1995-01-17 1997-04-29 Rheinmetall Industrie Gmbh Cartridge ammunition having accidental ignition preventing means
WO2010055086A1 (fr) * 2008-11-13 2010-05-20 Ruag Ammotec Gmbh Allumeur pyrotechnique
CN104534945A (zh) * 2014-12-13 2015-04-22 西安近代化学研究所 一种同步多点点火中心传火管
CN104534945B (zh) * 2014-12-13 2016-01-13 西安近代化学研究所 一种同步多点点火中心传火管
WO2018210579A1 (fr) * 2017-05-18 2018-11-22 Rheinmetall Waffe Munition Gmbh Système d'entraînement pour munition en cartouche
US10989505B2 (en) 2017-05-18 2021-04-27 Rheinmetall Waffe Munition Gmbh Propulsion system for cartridge ammunition

Also Published As

Publication number Publication date
EP0237711B1 (fr) 1992-06-10
DE3779679D1 (de) 1992-07-16
EP0237711A3 (en) 1989-03-29

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