EP0227671B1 - Treibladungsmodul - Google Patents

Treibladungsmodul Download PDF

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Publication number
EP0227671B1
EP0227671B1 EP85904443A EP85904443A EP0227671B1 EP 0227671 B1 EP0227671 B1 EP 0227671B1 EP 85904443 A EP85904443 A EP 85904443A EP 85904443 A EP85904443 A EP 85904443A EP 0227671 B1 EP0227671 B1 EP 0227671B1
Authority
EP
European Patent Office
Prior art keywords
ignition
charge
propellant
module
channel
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
EP85904443A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0227671A1 (de
Inventor
Karlheinz Reinelt
Michael Schwenzer
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.)
Rheinmetall Industrie AG
Original Assignee
Rheinmetall GmbH
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 Rheinmetall GmbH filed Critical Rheinmetall GmbH
Publication of EP0227671A1 publication Critical patent/EP0227671A1/de
Application granted granted Critical
Publication of EP0227671B1 publication Critical patent/EP0227671B1/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
    • F42C19/00—Details of fuzes
    • F42C19/08—Primers; Detonators
    • F42C19/085—Primers for caseless ammunition
    • 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
    • F42B5/38—Separately-loaded propellant charges, e.g. cartridge bags

Definitions

  • the invention relates to a propellant charge module according to the preamble of patent claim 1.
  • the tube forming the free ignition channel is cast from comparatively slow-burning nitrocellulose in a complex casting process.
  • the tube contains no means to enlarge the surface, so that a faster formation of the flame front in the axial direction of ignition cannot be achieved.
  • this ignition channel does not contain any means which, depending on the speed of the flame front emanating from a propellant charge igniter, enable the propellant charge to be burned on almost simultaneously.
  • a particular disadvantage is that the charge build-up shown in FIG.
  • the destruction of the central tube is to be initiated mechanically early on by the pressure of the ignition charge or the propellant charge.
  • destruction of the ignition channel is furthermore not expedient for a central introduction of the ignition beam and for a faster formation of the flame front in the axial ignition direction.
  • a major disadvantage of this arrangement is that a multiple number of cartridge sleeves cannot be loaded one after the other, since this results in impermissibly large gas pressure differences over the entire length of the propellant charge at higher loading densities. Propellant powder prone to brittle fracture can be destroyed on the floor of the floor, which in unfavorable cases can lead to damage to the floor or the weapon. Furthermore, it is possible with these cartridge bags or cartridge sleeves that they are inserted in the reverse position into the cargo space, which can result in failure and in extreme cases damage to the weapon.
  • Studies on barrel weapons with such or similar modular bulk powder propellant charges have shown that, especially with loading densities of more than 0.4 g / cm 3, irregular gas pressure profiles and thus non-reproducible firing sequences can occur. The reason for this behavior is to be found in the unsatisfactory central implementation of the modules, whereby the ignition on the front side can intensify this effect.
  • the arrangement of a free ignition channel within a porous ignition charge or an ignition charge consisting of ring tablets of the propellant charge module advantageously results in the propellant charge powder being ignited almost uniformly over the entire charge length and thereby minimizing the differential pressures within the cargo space. This makes it possible to influence the gas pressure curve in such a way that a perfectly reproducible firing sequence can be achieved even at high loading densities.
  • the axially symmetrical arrangement of the ignition charge in the area of the ignition channel wall ensures, in addition to fast and central ignition of the propellant charge powder, simple manufacture and processing of the igniter charge within the propellant charge module.
  • a particularly simple construction is achieved if the ignition tube consists of extruded porous nitrocellulose.
  • a simple variation of the length of the primer charge is made possible by the use of ring tablets that can be stacked on the face. According to a further design feature, these ring tablets can advantageously be arranged centering themselves.
  • the propellant charge module allows an axially arbitrary installation position in the cargo space.
  • the container is axially and radially symmetrical to the central axis such that the propellant charge module in the gun barrel can be loaded several times in a row in any axially forward or backward facing position of the end walls and in the loading position from each end wall the firing of the respective propellant charge modules by ignition clouds is possible.
  • the constant clear diameter of the ignition channel is advantageously between 5 and 40 mm, so that a spreading of the ignition vapor over the entire charge length is made possible faster than the radial firing of the propellant charge to be transmitted by the ignition charge.
  • any module of the same type can now be fed to different shot units. This advantageously eliminates the compulsory compliance with the charge sequence of previous partial propellant charges of different lengths.
  • the propellant charge modules can also be stored indefinitely thanks to moisture protection, their handling is uncomplicated and they ensure safe manual loading even in the dark, because the module end walls can now be swapped around arbitrarily when they are inserted into the cargo space.
  • the propellant charge modules can now also be charged automatically.
  • a time-consuming pre-sorting is advantageously unnecessary, so that the propellant charge modules can be stored in a simple manner and loaded by a loader without orientation.
  • the firing order can be increased significantly and an increase in the power of the gun can be achieved.
  • the propellant charge modules 1 shown in FIGS. 1 and 2 each consist of a container 10, a propellant charge powder 12 and an ignition channel 3 which is arranged coaxially over the entire module length 1 and has a free central cross section 25.
  • the container 10 is symmetrical in multiple axes. It contains two symmetry elements, the central longitudinal axis 2 forming a first symmetry element and a mirror surface 23 leading perpendicular to the longitudinal axis 2 through the module center 31 forming a second symmetry element.
  • the outer wall 26 of the container 10 is constructed in a tubular manner in a known manner, cylindrical or polygonal, the transitions on both sides to the end walls 8, 9 arranged at right angles to the longitudinal axis 2 having the same radii R and the transitions 27, 27 'to the ignition channel 3 having the same central shapes.
  • the free ignition channel 3 is essentially formed by the ignition charge 5, 7, which is also arranged symmetrically to the end faces 8, 9 of the container 10.
  • the shape of the container 10 and the design of the ignition channel 3 enable the propellant charge module 1 in the weapon barrel 11 (FIG. 3) to be loaded several times in succession in any axially forward or backward position of the end walls 8, 9, with the loading position 13 (FIG 3) from each end wall 8, 9 the firing of the respective propellant charge modules 1 is made possible by fumes.
  • the diameter d of the free cross-section 25 of the ignition channel 3 is of such a size that the spreading of the ignition vapor over the entire charge length is faster than the radial ignition of the propellant charge powder 12 to be transmitted by the ignition charge 5, 7, the charge length being the sum of the individual lengths of the propellant charge modules 1 arranged in series in the cargo space of the weapon barrel 11 (FIG. 3).
  • the clear diameter d can be at least 5 mm and a maximum of 40 mm, depending on its essential influencing variables, for example the speed of propagation of the ignition jet or the ignition swell of the propellant charge igniter 28 (FIG. 3) and the burn-up characteristic of the ignition charge and the caliber, a preferred more favorable one Diameter range is between 12 and 30 mm.
  • Fig. 1 shows left and right halves differently formed ignition propellant charges 5, 7 with a constant clear diameter d over the entire module length 1.
  • the boundary wall 4 consists of a continuous tube 14 forming the ignition channel 3, the wall cross section of which is made of an integrated one Ignition charge 5, preferably consists of extruded porous nitrocellulose or of extruded porous nitrocellulose and an admixture of known igniter charges.
  • the tube 14 is fastened to the end walls 8, 9 in a manner not shown.
  • the wall cross section of the ignition channel 3 consists radially on the outside of a combustible support tube 6 and radially on the inside of an ignition charge 7 centered by the support tube 6.
  • This ignition charge 7 is formed from ring tablets 15 stacked in the axial direction, the total length of which corresponds to the module length 1 .
  • the arrangement of self-centering ring tablets 24 (FIG. 2a) is optionally also possible.
  • the container 10 contains pipe connections 18 facing each other at the same distance b from the end walls 8, 9, which are provided with spacers 16 for the full frontal contact of the ring tablets 15, 24.
  • the pipe sockets 18 are each evenly necked in the transition area of the end walls 8, 9 to form a pipe extension 29, the necking can be rounded, for example.
  • the spacers 16 have the purpose of axially fixing the ignition charge 5, 7. However, as is shown on the left in FIG. 2a, they can also be designed with an axially inward projection 29 'or a centering 30' for the radial fastening of the self-centering ring tablets 24.
  • the ring tablets are also formed on both sides on the end faces with a shoulder 29 "pointing in the axial direction and a centering 30". In this way, the ring tablets 24 can also be stacked in an axially centering manner.
  • the ring tablets 15, 24 on the one hand allow the ignition charge to be arranged in a coherent axially symmetrical region a (FIG. 2a), but on the other hand also with the aid of a plurality of spacers 19 to be arranged between the ring tablets 15, an axially symmetrical arrangement of the ignition charge 7 in a plurality of partial regions a.
  • combustible or consumable or consumable foils 20 are arranged on the pipe socket 18 as moisture protection for the primer charge 7 and the propellant charge powder 12.
  • the foils 20 are arranged in the ignition channel 3 at the inwardly directed ends 21 of the pipe socket 18 or at the outwardly directed socket extensions 22 or at the entry and exit of the ignition channel 3 at the transitions of the pipe socket 18 to the end faces 8, 9. They can be designed as an individual part, but can also be connected in one piece with the pipe socket 18 or the end wall 8, 9 of the container 10.
  • Such films 20 are also arranged as a moisture seal on both sides of the ignition channel 3 (FIG. 1).
  • the container 10, the spacers 16, 19 and the support tube 6 are made of combustible materials which are known per se from cartridge ammunition.
  • the material of the container 10 has such a strength that there is the possibility of loading a projectile (not shown) and the charge consisting of the propellant charge modules 1 in one charge.
  • the ignition charge 7 consisting of ring tablets 15, 24 is also known and consists, for example, of a boron / potassium nitrate powder.
  • Known bulk powder is preferably also used as the propellant charge powder 12.
  • Fig. 3 illustrates the arrangement several times in the cargo space 32 of a gun barrel 11 arranged one behind the other and loaded in any loading direction of the same propellant charge modules 1.
  • the free ignition channel 3 allows the spread of the ignition jet or the ignition clouds of the propellant lighter 28 located in the tube closure 33 over the entire Charge length is faster than the radial firing of the propellant charge powder 12 to be transmitted by the ignition charge 5, 7 (FIG. 1).
  • a known propellant lighter 28 with a projectile is expediently used to overcome the protective films 20 (FIG. 2).
  • the individual propellant charge modules 1 are provided on the outside with a lacquer coating, which advantageously provides moisture protection and a reduction in flame sensitivity.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Air Bags (AREA)
  • Portable Nailing Machines And Staplers (AREA)
EP85904443A 1984-09-01 1985-08-24 Treibladungsmodul Expired - Lifetime EP0227671B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19843432291 DE3432291A1 (de) 1984-09-01 1984-09-01 Treibladungsmodul
DE3432291 1984-09-01

Publications (2)

Publication Number Publication Date
EP0227671A1 EP0227671A1 (de) 1987-07-08
EP0227671B1 true EP0227671B1 (de) 1990-01-24

Family

ID=6244501

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85904443A Expired - Lifetime EP0227671B1 (de) 1984-09-01 1985-08-24 Treibladungsmodul

Country Status (5)

Country Link
US (2) US4702167A (ja)
EP (1) EP0227671B1 (ja)
JP (1) JPS61502207A (ja)
DE (2) DE3432291A1 (ja)
WO (1) WO1986001584A1 (ja)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4041611A1 (de) * 1990-12-22 1992-06-25 Rheinmetall Gmbh Munition

Families Citing this family (31)

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Publication number Priority date Publication date Assignee Title
AU778762B1 (en) * 1986-01-09 2004-12-23 Royal Ordnance Plc A composite propellant charge
DE3730530A1 (de) * 1987-09-11 1989-03-23 Rheinmetall Gmbh Anzuenduebertragungsladung fuer eine treibladung
DE3737704C2 (de) * 1987-11-06 1998-03-12 Rheinmetall Ind Ag Steckverbindung für Treibladungsmodule
US5081930A (en) * 1990-03-13 1992-01-21 Martin Marietta Corporation Gun propellant containing ammonium azide and an inert casing
US5269224A (en) * 1990-08-30 1993-12-14 Olin Corporation Caseless utilized ammunition charge module
US5063848A (en) * 1990-10-16 1991-11-12 Olin Corporation Igniter bag
DE59208344D1 (de) * 1991-02-15 1997-05-22 Dynamit Nobel Ag Treibladungsmodul
EP0505024B1 (en) * 1991-02-18 1996-06-26 Imperial Chemical Industries Plc Gas generator
DE4124657A1 (de) * 1991-07-25 1993-01-28 Rheinmetall Gmbh Modulare treibladung
FR2710976B1 (fr) * 1993-10-05 1995-11-17 Poudres & Explosifs Ste Nale Eléments de conteneurs combustibles pour munitions d'artillerie, procédé de fabrication et utilisation de tels éléments.
DE4445991A1 (de) * 1994-12-22 1996-06-27 Rheinmetall Ind Gmbh Anzündsystem für Treibladungen und Verfahren zur Herstellung derartiger Anzündsysteme
FR2737002B1 (fr) * 1995-07-20 1997-08-29 Giat Ind Sa Systeme d'allumage d'une charge propulsive, notamment pour munition d'artillerie de campagne, et son procede de fabrication
DE19604655C2 (de) * 1996-02-09 1999-08-19 Diehl Stiftung & Co Anzündeinheit für eine Treibladung
US5726378A (en) * 1996-04-01 1998-03-10 Hodgdon Powder Company, Inc. Unitary propellant charge for muzzle loading firearms
US5747723A (en) * 1996-11-26 1998-05-05 The United States Of America As Represented By The Secretary Of The Army Modular artillery charge system
SE507659C2 (sv) * 1996-12-02 1998-06-29 Bofors Ab Sätt och anordning för att vid artilleripjäser hantera drivkrutladdningar av olika storlek och laddstyrka
SE519296C2 (sv) * 1997-08-14 2003-02-11 Bofors Defence Ab Drivladdningsmodul
FR2781879A1 (fr) 1998-07-30 2000-02-04 Giat Ind Sa Element de charge propulsive et son procede de fabrication
SE512205C2 (sv) 1998-12-18 2000-02-14 Bofors Ab Sätt att vid initiering av artilleridrivkrutladdningar bestående av ett flertal efter varandra anordnade drivkrutsmoduler åstadkomma en jämn övertändning mellan dessa samt i enlighet med sättet utformade drivkrutsmoduler och kompletta laddningar
US6360666B1 (en) 2000-06-06 2002-03-26 Alliant Techsystems Inc. Alignment fixture
US6343552B1 (en) 2000-06-06 2002-02-05 Alliant Techsystems Inc. Solvent application system
US6382104B1 (en) * 2000-11-07 2002-05-07 The United States Of America As Represented By The Secretary Of The Navy Two-piece base pad igniter bag
US6688232B2 (en) 2001-12-31 2004-02-10 Legend Products Corporation Compressed powder charge for muzzleloader and black powder firearms
US6877415B2 (en) * 2002-11-01 2005-04-12 Legend Products Corporation Individual premeasured charges with reduced moisture content and method of producing same
US7344610B2 (en) 2003-01-28 2008-03-18 Hodgdon Powder Company, Inc. Sulfur-free propellant compositions
DE102008008937B3 (de) * 2008-02-13 2009-10-22 Diehl Bgt Defence Gmbh & Co. Kg Miniaturisierte Zündkette
JP5354963B2 (ja) * 2008-06-10 2013-11-27 株式会社Ｉｈｉエアロスペース 砲弾の発射速度変更装置
JP5382782B2 (ja) * 2009-03-19 2014-01-08 株式会社Ｉｈｉエアロスペース 飛翔体の発射速度変更装置
JP5814514B2 (ja) * 2010-04-07 2015-11-17 旭化成ケミカルズ株式会社 簡便な構造の焼尽性容器
US9625242B1 (en) * 2015-02-12 2017-04-18 The United States Of America As Represented By The Secretary Of The Army Igniter for modular artillery charge system
JP6385863B2 (ja) * 2015-03-17 2018-09-05 株式会社ダイセル モジュール式発射装薬

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CA691639A (en) * 1964-07-28 R. Adelman Barnet Solid propellant rocket motors
US2405104A (en) * 1941-08-07 1946-07-30 William E Mydans Ordnance powder bag
FR1281397A (fr) * 1960-11-29 1962-01-12 Perfectionnement aux propulseurs pour fusées
US3204560A (en) * 1961-04-24 1965-09-07 Lockheed Aircraft Corp Solid rocket propellant containing metal encapsulated gas
US3176617A (en) * 1962-06-11 1965-04-06 Beloit Corp Separate loading of artiliery propellant charges
DE1428665A1 (de) * 1963-06-01 1968-12-12 Dynamit Nobel Ag Abschusspatrone fuer Werfergranaten
US3907619A (en) * 1964-01-30 1975-09-23 Us Navy Solution cast double base propellants and method
US3264997A (en) * 1964-07-20 1966-08-09 Harold E Michael Propellant configurations for use in firearms
US3304867A (en) * 1965-02-10 1967-02-21 Isidore G Nadel Solid propellants in textile form
US3372643A (en) * 1966-02-01 1968-03-12 United Shoe Machinery Corp Low explosive primerless formed charges
FR1514293A (fr) * 1967-01-11 1968-02-23 France Etat éléments de charges propulsives pour munitions d'artillerie
FR2194306A5 (en) * 1972-07-28 1974-02-22 Poudres & Explosifs Ste Nale Propellent charge without a cartridge - for use in automatic fire-arms
FR2504670A1 (fr) * 1981-04-23 1982-10-29 Lacroix E Eclairant pyrotechnique de grande puissance

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4041611A1 (de) * 1990-12-22 1992-06-25 Rheinmetall Gmbh Munition

Also Published As

Publication number Publication date
DE3432291A1 (de) 1986-03-13
US4702167A (en) 1987-10-27
US4864932A (en) 1989-09-12
WO1986001584A1 (en) 1986-03-13
JPS6231276B2 (ja) 1987-07-07
DE3575602D1 (de) 1990-03-01
EP0227671A1 (de) 1987-07-08
JPS61502207A (ja) 1986-10-02

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