EP0149714A2 - 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
EP0149714A2
EP0149714A2 EP84110002A EP84110002A EP0149714A2 EP 0149714 A2 EP0149714 A2 EP 0149714A2 EP 84110002 A EP84110002 A EP 84110002A EP 84110002 A EP84110002 A EP 84110002A EP 0149714 A2 EP0149714 A2 EP 0149714A2
Authority
EP
European Patent Office
Prior art keywords
propellant charge
elements
section
cross
space
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
EP84110002A
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German (de)
English (en)
Other versions
EP0149714A3 (en
EP0149714B1 (fr
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
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 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. This is intended to increase indoor ballistic performance.
  • a propellant charge of the type mentioned is known from DE-OS 25 04 765. It relates to a method and an apparatus 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 a verver-. to create a sealed 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, with adjacent first elements, for example 14.1 and 14.2, between mutually facing boundary surfaces 17 and 18, in each case one passage 20 of essentially rectangular cross section remains.
  • the passages 20 serve to accommodate two elements 22.1, ..., ; the lateral boundary surfaces 25 and 26 facing away from each other are 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. 1). 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 press jaws and lead to a recompression of the poured-in 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 which and thus the space 38 has assumed its circular cylindrical end cross-section, as shown in FIGS. 3 and 4.
  • the circle 28 is equal to the circumference of the propellant charge 52 or smaller by a predeterminable amount. The latter is necessary if 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. As can be seen from FIG.
  • a longitudinally axial movement in the direction of an arrow 6Q causes the projectile 41, which is only partially shown, with the propellant charge 52 compressed 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 transfer into the interior thereof, the propellant charge 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 charge powder 40, an upper-side second part 36 is brought into an initial position, in which the radial distance of the boundary surface 24 is greater than in the case of a second part 36 on the underside. This creates an additional space (not shown) in the device for accommodating propellant charge powder'40.
  • the propellant charge 52 After the parts 34 and 36 have reached their end position, the propellant charge 52 has a greater density in the region of the upper-side second parts 36 than in the region of the lower-side first parts of the second elements 22.1,... And the radial one also becomes an axial one Density gradient overlaid. This can also occur after the aforementioned slight relaxation in the relevant area of the propellant charge sleeve 52 still exist and can be specified. 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.

Landscapes

  • 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)
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
DE19833332224 DE3332224A1 (de) 1983-09-07 1983-09-07 Nachverdichtete treibladung, verfahren zu ihrer herstellung und vorrichtung zum durchfuehren des verfahrens
DE3332224 1983-09-07

Publications (3)

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

Family

ID=6208424

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 1988-12-19 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
WO2021118666A2 (fr) * 2019-09-12 2021-06-17 Carl Salmon Grenade comprenant des segments de carpe détachables indépendamment
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

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Family Cites Families (7)

* 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
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

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Also Published As

Publication number Publication date
US4619201A (en) 1986-10-28
EP0149714A3 (en) 1988-10-05
NO843513L (no) 1985-03-08
DE3332224A1 (de) 1985-03-21
EP0149714B1 (fr) 1990-10-24
DE3483469D1 (de) 1990-11-29

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