EP0149714B1 - Charge propulsive densifiée, procédé de sa fabrication et dispositif de réalisation de ce procédé - Google Patents

Charge propulsive densifiée, procédé de sa fabrication et dispositif de réalisation de ce procédé Download PDF

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Publication number
EP0149714B1
EP0149714B1 EP84110002A EP84110002A EP0149714B1 EP 0149714 B1 EP0149714 B1 EP 0149714B1 EP 84110002 A EP84110002 A EP 84110002A EP 84110002 A EP84110002 A EP 84110002A EP 0149714 B1 EP0149714 B1 EP 0149714B1
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EP
European Patent Office
Prior art keywords
propellant charge
elements
accordance
section
cross
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
EP84110002A
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German (de)
English (en)
Other versions
EP0149714A2 (fr
EP0149714A3 (en
Inventor
Rudolf Dipl.-Ing. Romer
Michael Schwenzer
Reinhard Dr. Dipl.-Phys. Synofzik
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
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Rheinmetall GmbH
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Filing date
Publication date
Application filed by Rheinmetall GmbH filed Critical Rheinmetall GmbH
Publication of EP0149714A2 publication Critical patent/EP0149714A2/fr
Publication of EP0149714A3 publication Critical patent/EP0149714A3/de
Application granted granted Critical
Publication of EP0149714B1 publication Critical patent/EP0149714B1/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
    • F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02—Cartridges, i.e. cases with charge and missile
    • F42B5/16—Cartridges, i.e. cases with charge and missile characterised by composition or physical dimensions or form of propellant charge, with or without projectile, or powder
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B33/00—Manufacture of ammunition; Dismantling of ammunition; Apparatus therefor
    • F42B33/02—Filling cartridges, missiles, or fuzes; Inserting propellant or explosive charges
    • F42B33/025—Filling cartridges, missiles, or fuzes; Inserting propellant or explosive charges by compacting

Definitions

  • the invention relates to a post-compressed propellant charge.
  • a propellant charge of the type mentioned is known from DE-OS 25 04 756. It relates to a method and a device for compressing finely divided solid explosives in a garnet shell or in a propellant charge case: explosive is filled into the propellant charge case; an elastic sack is introduced into the propellant charge sleeve through the neck of the propellant charge sleeve and its neck opening is sealed. The propellant charge sleeve is then evacuated and the sack is then expanded using a pressure medium. As a result, the explosive is compressed again into a charge. It is also provided that the explosive is filled and recompressed in several stages, each time using a smaller sack.
  • this method also proves to be complex and cumbersome. In addition, it can only lead to an axial density gradient. This disadvantageously complicates the ignition of the post-compressed propellant charge.
  • the invention has for its object to provide a post-compressed propellant charge with improved ignition properties.
  • the device has a frame 10 with a base plate 12 with first elements 14.1,.
  • the latter have an essentially isosceles-triangular cross section and have a curved boundary surface 16 between plane-level boundary surfaces 17 and 18, which will be explained later.
  • the first elements 14.1, ... are arranged on a circle with the same pitch, each with a passage 20 of essentially rectangular cross section remaining between mutually facing boundary surfaces 17 and 18 of adjacent first elements, for example 14.1 and 14.2.
  • the passages 20 serve for the radially movable reception of second elements 22.1, ..., the lateral boundary surfaces 25 and 26 of which face away from one another are each directly adjacent to a boundary surface 17 or 18 of the first elements 14.1, ....
  • the boundary surfaces 16 and 24 form essential areas of a wall of a room 38.
  • This is assigned a support 48 on the underside and a cover 50 on the upper side.
  • a projectile 41 with a projectile tail 42 protrudes into space 38.
  • the projectile tail 42 is delimited on the circumference by a gas pressure receiving surface 46 of a sabot not specified and carries at its rear end a stabilizing tail 43 with five stabilizing wings 44.1,... 44.5, which are supported radially against the boundary surfaces 16 of the first elements 14.1, ... 14.5. 1 and 2 show the second elements 22, 1, ... in their starting position.
  • Propellant powder 40 is poured into the space 38. The bulk quantity is equal to a propellant charge 52 (FIG. 3). Then the second elements 22.1, ... are simultaneously moved radially from their starting position in the direction of arrow 30 against the central longitudinal axis A. They act as pressing jaws and lead to a recompression of the poured propellant powder 40.
  • a radial density gradient increases over the entire length.
  • the process is ended as soon as the boundary surfaces 24 of the second elements 22.1, ..., 22.5 form a circle 28 together with the boundary surfaces 16 of the first elements 14.1, ..., 14.5 and thus the space 38 has assumed its circular cylindrical end cross-section, such as this is shown in Figures 3 and 4.
  • the circle 28 is equal to the circumference of the propellant charge 52 or smaller by a predeterminable amount.
  • an end-use space for the propellant charge 52 for example the interior 62 of a propellant charge sleeve 58 (see FIG. 5) has a slight taper.
  • a longitudinally axial movement in the direction of an arrow 60 causes the projectile 41, which is only partially shown, with the propellant charge 52 compacted around the projectile tail 42 from the space 38 of the device into the interior 62 of the propellant charge sleeve positioned in an axially aligned manner in a receptacle 56 58 transferred.
  • the circle 28 corresponds to the clear insertion cross section of the propellant charge sleeve, and after that Transferring to the interior of the propellant 52 relaxes slightly in some areas and fills the volume of the interior.
  • the procedure is as follows: As can be seen by way of example in FIG. 2 from a dividing line 35, the second elements 22.1,.. . To pour in the propellant powder 40, an upper-side second part 36 is brought into an initial position at which the radial distance from the boundary surface 24 is greater than that of a lower-side first part 34.
  • the propellant charge 52 has a greater density in the area of the upper-side second parts 36 than in the area of the lower-side first parts 34 of the second elements 22.1,... and the radial one also becomes an axial one Density gradient overlaid. This can still be present in the relevant area of the propellant charge sleeve 52 after the aforementioned slight relaxation and can be predetermined. In this advantageously simple manner, a comparatively higher density can be achieved, preferably in the rear region of the propellant charge 52, which has advantages in terms of interior ballistics.
  • the ignition of the propellant charge 52 in its central axial region is favored because the compression of the propellant charge powder 40 is less there. This also favors a better separation behavior of the propellant powder with a simultaneous increase in the internal ballistic performance achieved by the recompression.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Drilling And Exploitation, And Mining Machines And Methods (AREA)
  • Containers And Packaging Bodies Having A Special Means To Remove Contents (AREA)

Claims (10)

1. Charge propulsive (52) densifiée, caractérisée par un gradient de densité radial, donné sur toute sa longueur, augmentant vers la région périphérique (16, 24).
2. Charge propulsive selon la revendication 1, caractérisée par un gradient de densité axial, longitudinal, superposé au moins dans certaines zones.
3. Procédé de fabrication d'une charge propulsive (52) densifiée selon la revendication 1 ou 2, caractérisé par les étapes de procédé et les caractéristiques suivantes:
a) une quantité de poudre de charge propulsive (40) en vrac, de même masse que la charge propulsive (52) à densifier, est envoyée vers un volume (38) dont l'extension axiale correspond à peu près à celle de la charge propulsive (52) à densifier,
b) la poudre en vrac est compactée par des forces appliquées radialement qui réduisent la section transversale du volume (38) à une section finale, celle-ci étant inférieure ou égale à celle d'un logement (58) et
c) après obtention de la section transversale finale, la charge propulsive (52) densifiée est extraite axialement du volume (38) et introduite axialement dans le logement (58).
4. Procédé selon la revendication 3, caractérisé en ce que le volume (38) présente, sur toute sa longueur, une section transversale de sortie constante.
5. Procédé selon la revendication 3, caractérisé en ce que le volume (38) présente, sur toute sa longueur, des sections transversales de sortie de grandeur différente.
6. Procédé selon la revendication 3, 4 ou 5, caractérisé en ce qu'avant d'introduire la quantité de poudre de charge propulsive (40) en vrac, on fixe, de manière amovible, un projectile (41) avec sa partie arrière (42), dans le volume (38).
7. Procédé selon la revendication 6, caractérisé en ce qu'on déplace axialement le projectile (41), pour extraire axialement la charge propulsive (52) densifiée.
8. Dispositif de compactage d'une charge propulsive (52) de gradient de densité donné, caractérisé par les caractéristiques suivantes:
a) un bâti (10) comporte un nombre donné de premiers éléments (14.1, ...), de section transversale à peu près en triangle isocèle,
b) les premiers éléments (14.1, ...) sont placés, de manière fixe, sur un cercle aux divisions régulières, des surfaces de délimitation (16), tournées vers un axe (A) vertical, se situant sur un cercle (28) qui est au plus égal à la circonférence de la charge propulsive (52),
c) des surfaces de délimitation (17, 18) latérales, verticales, des premiers éléments (14.1 ...) adjacents, forment deux par deux un passage (20) de section transversale rectangulaire pour deux éléments (22,1, ...),
d) des surfaces de délimitation (24), tournées vers l'axe longitudinal (A) vertical des deuxièmes éléments (22.1, ...), sont courbées de manière à former des parties du cercle (28) et
e) les deuxièmes éléments (22.1,...) sont mobiles, à partir d'une position initiale, vers l'axe longitudinal (A) central, jusqu'à une position finale dans laquelle ils forment avec les surfaces de délimitation (16) des premiers éléments (14,1, ...), le cercle fermé (28).
9. Dispositif selon la revendication 8, caractérisé en ce que les deuxièmes éléments (22.1, ...) sont subdivisés au moins en une première partie (34) et une deuxième partie (36), les deuxièmes parties (36) se déplaçant, à partir de leur position initiale respective, par rapport aux premières parties (34), et conjointement avec celles-ci, radialement dans la position finale.
10. Dispositif selon la revendication 8 ou 9, caractérisé en ce que la quantité des premiers éléments (14.1, ...) et des deuxièmes éléments (22,1, ...) correspond à la quantité de stabilisateurs (44.1, ...) de l'empennage (43) d'un projectile (41) pénétrant à l'intérieur.
EP84110002A 1983-09-07 1984-08-22 Charge propulsive densifiée, procédé de sa fabrication et dispositif de réalisation de ce procédé Expired - Lifetime EP0149714B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3332224 1983-09-07
DE19833332224 DE3332224A1 (de) 1983-09-07 1983-09-07 Nachverdichtete treibladung, verfahren zu ihrer herstellung und vorrichtung zum durchfuehren des verfahrens

Publications (3)

Publication Number Publication Date
EP0149714A2 EP0149714A2 (fr) 1985-07-31
EP0149714A3 EP0149714A3 (en) 1988-10-05
EP0149714B1 true EP0149714B1 (fr) 1990-10-24

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP84110002A Expired - Lifetime EP0149714B1 (fr) 1983-09-07 1984-08-22 Charge propulsive densifiée, procédé de sa fabrication et dispositif de réalisation de ce procédé

Country Status (4)

Country Link
US (1) US4619201A (fr)
EP (1) EP0149714B1 (fr)
DE (2) DE3332224A1 (fr)
NO (1) NO843513L (fr)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE452799B (sv) * 1985-06-20 1987-12-14 Nobel Kemi Ab Sett att framstella ringformiga laddningar och enligt settet framstellda laddningar
SE449527C (sv) * 1985-06-20 1988-12-08 Nobel Kemi Ab Explosiv laddning foer spraengfogning av grova roer, samt saett att framstaella densamma
DE3840875A1 (de) * 1988-12-05 1990-06-07 Rheinmetall Gmbh Verfahren und vorrichtung zum verdichten einer treibladung und nach dem verfahren hergestellte munition
DE3843289A1 (de) * 1988-12-22 1990-06-28 Diehl Gmbh & Co Treibspiegelmunition
DE3939295A1 (de) * 1989-11-28 1991-05-29 Rheinmetall Gmbh Verfahren und vorrichtung zur herstellung von grosskalibriger munition
US5456455A (en) * 1994-02-01 1995-10-10 Thiokol Corporation Flare pellet and process for making same
US6352029B1 (en) 2000-03-30 2002-03-05 The United States Of America As Represented By The Secretary Of The Navy Thermally actuated release mechanism
US6846372B1 (en) * 2003-03-31 2005-01-25 The United States Of America As Represented By The Secretary Of The Navy Reactively induced fragmentating explosives
CN105083856A (zh) * 2015-08-20 2015-11-25 苏州听毅华自动化设备有限公司 一种不良品输出机构
US20220373310A1 (en) * 2019-09-12 2022-11-24 Carl Salmon Grenade with independently detachable carpel segments
CN112229279B (zh) * 2020-09-18 2022-08-19 西安近代化学研究所 一种不使用配重块不改变装药量且能调节质量质心的液相装药战斗部壳体装置

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US726901A (en) * 1899-05-27 1903-05-05 George Whitman Mcmullen Explosive charge.
US654471A (en) * 1899-06-26 1900-07-24 Vickers Sons & Maxim Ltd Powder-grain.
US802347A (en) * 1903-07-17 1905-10-17 Henry C Aspinwall Perforated powder-grain.
US2995011A (en) * 1959-09-17 1961-08-08 Phillips Petroleum Co Solid propellant rocket motor
SE391025B (sv) * 1974-02-08 1977-01-31 Foerenade Fabriksverken Sett att i granatholje eller laddningshylsa kompaktera finfordelat, fast explosivemne och anordning herfor
US4020736A (en) * 1976-03-29 1977-05-03 The United States Of America As Represented By The Secretary Of The Navy Automatic increment sizer-feeder for press loading
US4331081A (en) * 1980-07-25 1982-05-25 C-I-L Inc. Explosive booster
DE3205152C2 (de) * 1982-02-13 1984-04-12 Mauser-Werke Oberndorf Gmbh, 7238 Oberndorf Treibladung für Hülsenmunition und Verfahren zu ihrer Herstellung

Also Published As

Publication number Publication date
DE3332224A1 (de) 1985-03-21
EP0149714A2 (fr) 1985-07-31
EP0149714A3 (en) 1988-10-05
US4619201A (en) 1986-10-28
DE3483469D1 (de) 1990-11-29
NO843513L (no) 1985-03-08

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