EP0227671A1 - Module propulseur. - Google Patents

Module propulseur.

Info

Publication number
EP0227671A1
EP0227671A1 EP85904443A EP85904443A EP0227671A1 EP 0227671 A1 EP0227671 A1 EP 0227671A1 EP 85904443 A EP85904443 A EP 85904443A EP 85904443 A EP85904443 A EP 85904443A EP 0227671 A1 EP0227671 A1 EP 0227671A1
Authority
EP
European Patent Office
Prior art keywords
ignition
charge
propellant charge
module
propellant
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
EP85904443A
Other languages
German (de)
English (en)
Other versions
EP0227671B1 (fr
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/fr
Application granted granted Critical
Publication of EP0227671B1 publication Critical patent/EP0227671B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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 with ignition charge and a combustible cylindrical container.
  • a significant disadvantage of this arrangement is that a multiple number of Kartuschhülsen load can not be consecutively ge, as characterized at higher loading densities' impermissibly large gas pressure differentials arise across the entire length of the propellant charge. Propellant powder tending 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 means that losers and, in extreme cases, damage to the weapon can occur.
  • the arrangement of a free ignition channel within the igniter charge 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 rapid and central ignition of the propellant charge powder, simple manufacture and processing of the ignition charge within the propellant charge module.
  • a particularly simple construction is achieved if the igniter tube consists of an integral part of the wall cross section. ignited charge exists.
  • 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 feature, these ring tablets can advantageously be arranged self-centering.
  • the propellant charge module particularly advantageously permits an axially arbitrary installation position in the cargo space.
  • the container is designed symmetrically axially and radially to the central axis such that the propellant charge module in the weapon barrel can be loaded several times in succession in any axially forward or backward position of the end walls and in the loading position the firing of the respective propellant charge modules from each end wall is made possible by fumes.
  • the clear diameter of the ignition channel advantageously has such a size that the spreading of the ignition fumes over the entire length of the charge takes place faster than the radial firing of the propellant charge powder to be transmitted by the ignition charge.
  • any modules of the same type can now be fed to different firing 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 due to moisture protection. Their handling is uncomplicated and they ensure a safe manual loading even in the dark, because now the module end walls can be interchanged arbitrarily when they are introduced into the cargo space.
  • the propellant charge modules can now also be charged automatically.
  • a time-consuming pre-sorting is advantageously dispensed with, 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 the barrel weapon can be increased in performance.
  • FIG. 1 shows a sectional view of the propellant charge module with different ignition charges corresponding to the module length
  • FIG. 2 shows a sectional view of the propellant charge module with various igniter charges consisting of ring tablets and corresponding to a partial area of the module length;
  • FIG. 3 shows a sectional illustration of the same door loading modules arranged several times in the weapon barrel.
  • 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 which has a free central cross section 25.
  • the container 10 is of symmetrical multi-axis design. 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 point 31 forming a second symmetry element.
  • the outer wall 26 of the container 10 is constructed in a tubular manner in a known manner in a cylindrical or polygonal manner, the two-sided transitions to the end walls arranged at right angles to the longitudinal axis 2 having the same radii R and the transitions 27, 27 'to the ignition channel 3 being the same have centric shapes. r .
  • the free ignition channel 3 is essentially formed by the ignition charge 5, 7, which is also symmetrical to the forehead surfaces 8,9 of the container 10 is arranged.
  • the shape of the container 10 and the design of the ignition channel 3 make it possible for 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, being in the loading position 13 (Fig. 3) from each end wall 8,9 ago 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 spread 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 is formed from the sum of the individual lengths of the propellant charge modules 1 lined up 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 swath of the propellant charge igniter 28 (FIG. 3) and the burning characteristics of the ignition charge and the caliber. a preferred favorable diameter range between 12 and 30 mm.
  • the boundary wall 4 consists of a continuous tube 14 forming the ignition channel 3, the wall cross-section of which an integrated igniter charge 5, preferably made of extruded porous nitrocellulose or extruded porous nitrocellulose and an admixture of known igniter charges.
  • the tube 14 is in a not shown Way fixed with the end walls 8.9.
  • 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, whose total length corresponds to module length 1.
  • the container 10 contains pipe connections 18 facing each other at the same distance b from the end walls 8, 9, which have spacers for the full frontal contact of the ring tablets 15, 24 16 are provided.
  • the pipe sockets 18 are each evenly necked in the transition area of the end walls 8, 9 to a pipe extension 29, and 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 in the left half 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 ′′ and an ′′ centering 30 ′′ pointing in the axial direction
  • ring tablets 24 can also be stacked axially in a centering manner.
  • the support tube 6.1 is connected to the spacers 16 in a manner not shown.
  • the ring-shaped 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 several areas a.
  • combustible or consumable or consumable foils 20 are arranged on the pipe socket 18 as moisture protection for the ignition charge 7 and the propellant charge powder 12.
  • the foils 20 are arranged in the ignition channel 3 at the inward ends 21 of the pipe sockets 18 or on the outward pipe extensions 22 or at the entry and exit of the ignition channel 3 at the transitions of the pipe sockets 18 to the end faces 8, 9. They can be designed as an individual part, but also in one piece be connected to the pipe socket 18 or the end wall 8.9 of the container 10. Films 20 of this type 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 patronized ammunition.
  • the material of the container 10 is of such strength that it is possible to charge 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 of the same propellant charge modules 1 arranged several times in the cargo space 32 of a weapon barrel 11 and loaded in any loading direction.
  • 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 via the entire charge length is faster than the radial firing of the propellant powder 12 to be transmitted by the primer 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)

Abstract

Dans un module propulseur comprenant un conteneur combustible, la charge d'allumage pour toutes les gradations de charge et dans toute situation de charge doit être agencée de telle sorte qu'un cours uniforme de la pression gazeuse et une décharge reproductible de détonation soient possibles dans la plage des hautes et des basses pressions gazeuses, en maintenant les mêmes gradations de charge; en outre, une construction modulaire en résulte qui rend possible un allumage aussi simultané que possible sur toute la longueur de la charge, le module pouvant être chargé ou échangé à volonté. Le module propulseur (1) comprend sur toute la longueur du module (1) un canal libre d'allumage (3) coaxialement angencé, formé par une charge d'allumage (5, 7) symétriquement agencé par rapport aux parois frontales (8, 9) du conteneur (10). La paroi de délimitation (4) du canal d'allumage (3) peut se composer d'un tuyau (14) dans la section transversale duquel est intégrée une charge d'allumage (5). La section transversale du canal (3) peut toutefois également se composer d'un tuyau de support (6) et d'une charge d'allumage (7) composée de préférence de pastilles annulaires. La construction symétrique du conteneur permet de le changer ou de l'allumer par n'importe quelle extrémité, à volonté. La section transversale libre du canal d'allumage (3) permet d'allumer la charge d'allumage (7) simultanément sur toute sa longueur.
EP85904443A 1984-09-01 1985-08-24 Module propulseur Expired - Lifetime EP0227671B1 (fr)

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 true EP0227671A1 (fr) 1987-07-08
EP0227671B1 EP0227671B1 (fr) 1990-01-24

Family

ID=6244501

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85904443A Expired - Lifetime EP0227671B1 (fr) 1984-09-01 1985-08-24 Module propulseur

Country Status (5)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2781879A1 (fr) 1998-07-30 2000-02-04 Giat Ind Sa Element de charge propulsive et son procede de fabrication

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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
DE4041611C2 (de) * 1990-12-22 1997-11-27 Rheinmetall Ind Ag Zweigeteilte Munition
DE4204318A1 (de) * 1991-02-15 1992-08-20 Dynamit Nobel Ag Treibladungsmodul
DE69211733T2 (de) * 1991-02-18 1996-11-07 Ici Canada Gasgenerator
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
SE9804400L (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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Publication number Priority date Publication date Assignee Title
FR2781879A1 (fr) 1998-07-30 2000-02-04 Giat Ind Sa Element de charge propulsive et son procede de fabrication

Also Published As

Publication number Publication date
EP0227671B1 (fr) 1990-01-24
JPS6231276B2 (fr) 1987-07-07
US4702167A (en) 1987-10-27
DE3432291A1 (de) 1986-03-13
JPS61502207A (ja) 1986-10-02
WO1986001584A1 (fr) 1986-03-13
DE3575602D1 (de) 1990-03-01
US4864932A (en) 1989-09-12

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