EP0463414A1 - Flügelstabilisiertes Geschoss - Google Patents

Flügelstabilisiertes Geschoss Download PDF

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Publication number
EP0463414A1
EP0463414A1 EP91109150A EP91109150A EP0463414A1 EP 0463414 A1 EP0463414 A1 EP 0463414A1 EP 91109150 A EP91109150 A EP 91109150A EP 91109150 A EP91109150 A EP 91109150A EP 0463414 A1 EP0463414 A1 EP 0463414A1
Authority
EP
European Patent Office
Prior art keywords
propellant
ammunition
ammunition according
powder
projectile
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.)
Withdrawn
Application number
EP91109150A
Other languages
German (de)
English (en)
French (fr)
Inventor
Gero Wähner
Dieter Girke
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.)
Mauser Werke Oberndorf GmbH
Dynamit Nobel AG
Original Assignee
Mauser Werke Oberndorf GmbH
Dynamit Nobel AG
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 Mauser Werke Oberndorf GmbH, Dynamit Nobel AG filed Critical Mauser Werke Oberndorf GmbH
Publication of EP0463414A1 publication Critical patent/EP0463414A1/de
Withdrawn legal-status Critical Current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

Definitions

  • the invention relates to ammunition with a sleeve containing propellant powder, into which a wing-stabilized projectile, the projectile body of which is partially or completely enclosed in a ring by a sabot, projects with its tail assembly arranged at the rear.
  • a sub-caliber projectile which has a tail unit provided with wings at the rear.
  • This tail unit is inserted into the propellant charge sleeve filled with propellant powder according to FIG.
  • projectiles are often made of tungsten and have a long design.
  • the maximum length of the sub-caliber projectiles is limited due to the cartridge length of the tube weapons put into service. This leads to the fact that the tail unit has to be inserted into the propellant charge casing; as a result, only a reduced amount of propellant powder can be introduced into the sleeve, so that such ammunition has insufficient propellant energy.
  • a wing-stabilized sub-caliber floor is known.
  • This known projectile has a tail unit on the rear which projects into the interior of a cartridge case which contains granulated propellant powder.
  • the tail unit stands with its free end on a cartridge cover that separates the granulated propellant powder from a downstream tube powder.
  • a propellant powder is filled into the propellant charge sleeve according to the state of the art and then the projectile with the empennage is gently swirled between the propellant charge powder until the sabot arranged above the empennage adjoins the sleeve mouth.
  • the cartridge is then rotated through 180 ° about the transverse axis, so that the propellant powder falls into the cavities between the fin fins and then the sabot can be carefully pressed in completely with the arrow tail.
  • the high muzzle velocity requirements are very often inversely proportional to the combustion chamber remaining in the propellant charge shell after the arrow tail with the tail unit has been inserted.
  • the moldings are introduced into the free space between the fins before the arrow projectile is labored into the sleeve together with the sabot.
  • the shaped bodies can either be plugged on, pushed on, glued in or otherwise attached to the rear of the projectile;
  • the moldings can partially or completely fill the free space, which is axially delimited by the sabot and the powder or powder surface and on the other hand radially by the arrow projectile shaft and the cylindrical shape formed in the diameter of the sleeve mouth or its lateral surface, as well as that Space behind the tail end of the tail unit if the propellant powder in the sleeve is not directly adjacent to the tail end of the tail unit.
  • high-energy molded parts are created for a wing-stabilized projectile to fill the space between the propellant sleeve mouth wall, the tail fin and the tail shaft, which simplify the workability of the arrow projectile and enable the combustion chamber volume in the propellant sleeve to be used almost completely in ballistic applications.
  • the high-energy molded parts are designed in such a way that they provide optimal internal ballistic performance in connection with the main friction charge from a loosely poured and / or compressed propellant powder.
  • the high-energy molded parts or moldings according to the invention can either be glued in as individual segments between the tail fin or as a whole body with a base plate made in one piece and attached to the tail end with the tail.
  • the moldings are therefore arranged so that they represent mechanical protection of the tail unit against the grain pressure of the powder propellant charge in the ignition phase.
  • the high-energy molded bodies are also designed so that they have a protective effect on the tail surfaces of the arrow projectile against the hot combustion gases of the main propellant charge, so that damage to the tail unit no longer occurs.
  • composition of the moldings is basically chosen so that they burn off evenly and thus make a positive contribution to interior ballistics.
  • the wing-stabilized sabot projectile 13 essentially consists of the elongated projectile body 14 with the tail unit 4 attached to the rear.
  • the projectile body tip is enclosed by a hood 15, to which the sabot 6 with the inserted guide band 16 is connected in the middle part of the projectile body 14.
  • the sabot projectile is completed by the propellant charge sleeve 1 with primer cap 17, which is held in an annular groove 18 on the outer surface of the sabot 6, to the cartridge.
  • the main propellant charge 2 made of propellant charge powder is located in the propellant charge sleeve 1.
  • the powder is either poured loosely into the propellant charge sleeve or compacted, in accordance with the manner described in DE 32 05 152 C2.
  • a combination of loosely poured propellant powder bodies with compressed propellant powder bodies is of course also possible.
  • a compressed propellant charge can be made uniformly or gradually different over the entire volume.
  • This main propellant charge 2 ends in the direction of the projectile body 14 of the sabot projectile 13 at the free rear end 5 of the tail unit 4.
  • Such individual segments 7 as molded bodies with a high energy density are produced in separate processes and fastened to the tail unit, for example by gluing or plugging in or some other connection.
  • the length of the molded body 7 extends from the free front end 5 of the tail unit 4 to the sabot bottom 21.
  • the outer diameter of the molded body 7 is slightly smaller than the inner diameter of the propellant sleeve mouth 24.
  • FIG. 2 there is between the tail fin 20 and the opposite one Surfaces of the shaped body 7 shows a comparatively large gap, for example in the case of an adhesive bond is reduced to the thickness of the adhesive layer.
  • the propellant charge sleeve 1 is filled with loosely poured and / or pre-compressed propellant charge powder to such an extent that the arrow tail to be introduced with the tail unit 4 is just freely accessible with its front end 5 in accordance with the present invention. Then the arrow projectile 13 with the sabot 6 and tail assembly 4, between the fins 20 of which the molded bodies 7 are attached by suitable methods and which fill the space between the sabot base 21 and the tail end 5 almost in the size of the inner diameter of the sleeve mouth, are pressed into the propellant charge sleeve 1.
  • the combustion chamber volume of the propellant charge sleeve 1 is used almost completely and the processing itself is technically simplified.
  • the individual shaped bodies 7 are matched to the main propellant charge 2 so that together with them they provide optimal internal ballistic performance.
  • the shaped bodies 7 are designed in such a way that the individual segments 22 together with a base plate 8 form a single molding which is pushed onto the tail unit 4 and fastened from the free tail end 5.
  • the segments 22 are preassembled on a base plate 8 or preformed together with this and pushed as a charge unit over the tail 4 of the projectile body 14.
  • shaped bodies 23 can be provided with a cylindrical outer jacket 9, from which the segments 23 are directed radially inwards towards the projectile body 14.
  • the cylindrical jacket 9 can be made in one piece with the segments 23. 5, left half, jacket 9 and individual segments 23 are composed of separate parts.
  • shaped bodies can also be formed as annular disks 10, which are pushed axially from the free tail end 5 onto the tail unit 4 and fastened. These ring disks 10 are either made in one piece with recesses for arrow projectiles and fins or from separate components.
  • the annular disks 10 can be arranged axially directly one above the other; it is possible to determine the axial distances using spacers integrally connected to the ring washers, e.g. Knobs on the discs, or separately by spacers between them.
  • the embodiment with one-piece washers is particularly useful if there is sufficient clearance between the tail diameter and the inner diameter of the propellant sleeve. Basically, these types of construction further simplify manufacture.
  • the molded bodies 7, 9, 10, 22, 23 also advantageously act as protection for the tail fin against mechanical damage and deformation, which according to the prior art can occur in the ignition phase in the case of particularly thin tail fin due to the grain pressure of the propellant powder.
  • the base material for the high-energy molded articles can be very different.
  • the use of desensitized explosives mixed with a binder is possible, as well as propellant powder bodies embedded or dissolved in a foam matrix or wetted and compressed with a binder. Molded parts made of nitrocellulose paper can also be produced.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Portable Nailing Machines And Staplers (AREA)
EP91109150A 1990-06-29 1991-06-05 Flügelstabilisiertes Geschoss Withdrawn EP0463414A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4020691A DE4020691A1 (de) 1990-06-29 1990-06-29 Fluegelstabilisiertes geschoss
DE4020691 1990-06-29

Publications (1)

Publication Number Publication Date
EP0463414A1 true EP0463414A1 (de) 1992-01-02

Family

ID=6409305

Family Applications (1)

Application Number Title Priority Date Filing Date
EP91109150A Withdrawn EP0463414A1 (de) 1990-06-29 1991-06-05 Flügelstabilisiertes Geschoss

Country Status (4)

Country Link
US (1) US5160804A (no)
EP (1) EP0463414A1 (no)
DE (1) DE4020691A1 (no)
NO (1) NO912544L (no)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2716677A1 (fr) * 1994-02-26 1995-09-01 Dynamit Nobel Ag Procédé de fabrication sans solvant de charges propulsives poreuses préformées, et charges propulsives ainsi fabriquées.
EP0707560A1 (en) * 1993-05-04 1996-04-24 Alliant Techsystems Inc. Improved propellant system

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3939295A1 (de) * 1989-11-28 1991-05-29 Rheinmetall Gmbh Verfahren und vorrichtung zur herstellung von grosskalibriger munition
DE4124657A1 (de) * 1991-07-25 1993-01-28 Rheinmetall Gmbh Modulare treibladung
US5474256A (en) * 1994-09-08 1995-12-12 The United States Of American As Represented By The Secretary Of The Army Combustible fin protection device
US6158348A (en) * 1998-10-21 2000-12-12 Primex Technologies, Inc. Propellant configuration
US6167810B1 (en) * 1998-12-04 2001-01-02 United Defense, L.P. Propelling material formed in strips for use in large caliber guns
DE10031727B4 (de) * 2000-06-29 2006-03-16 Rheinmetall W & M Gmbh Scheibenförmig aufgebautes Treibladungsmodul
DE10052741B4 (de) * 2000-10-25 2009-11-26 Rheinmetall Waffe Munition Gmbh Patrone
WO2003036222A1 (en) 2001-10-22 2003-05-01 Armtec Defense Products Co. Ammunition round assembly with combustible cartridge case
AU2002365589A1 (en) 2001-11-27 2003-06-10 Armtec Defense Products Co. Combustible cased telescoped ammunition assembly
US7712417B1 (en) * 2002-02-08 2010-05-11 The United States Of America As Represented By The Secretary Of The Army Axial modular propulsion charge design for semi-fixed ammunition
US7363861B2 (en) 2004-08-13 2008-04-29 Armtec Defense Products Co. Pyrotechnic systems and associated methods
US8146502B2 (en) 2006-01-06 2012-04-03 Armtec Defense Products Co. Combustible cartridge cased ammunition assembly
US7913625B2 (en) * 2006-04-07 2011-03-29 Armtec Defense Products Co. Ammunition assembly with alternate load path
FI121554B (fi) * 2008-01-31 2010-12-31 Patria Weapon Systems Oy Sovitelma kranaatin tukemiseksi takaaladattavan aseen putkeen ja menetelmä tukikappaleen kiinnittämiseksi kranaattiin
JP5845939B2 (ja) * 2012-02-02 2016-01-20 日油株式会社 火炎抑制材
CA3083853A1 (en) * 2017-12-08 2019-06-13 Albert Gaide Ammunition cartridge
RU2704160C1 (ru) * 2018-04-24 2019-10-24 Федеральное государственное казенное военное образовательное учреждение высшего образования "Военная академия материально-технического обеспечения имени генерала армии А.В. Хрулёва" Метательный заряд с повышенными энергетическими характеристиками к бронебойному подкалиберному снаряду
US11041701B1 (en) * 2019-07-03 2021-06-22 The United States Of America As Represented By The Secretary Of The Army Combustible munition case with cell cavities
US11378369B1 (en) * 2019-08-30 2022-07-05 The United States Of America As Represented By The Secretary Of The Army Modular test vehicle

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2622687A1 (fr) * 1987-10-29 1989-05-05 France Etat Armement Chargement propulsif pour munition comportant un projectile empenne ainsi que son procede de realisation
DE3840875A1 (de) * 1988-12-05 1990-06-07 Rheinmetall Gmbh Verfahren und vorrichtung zum verdichten einer treibladung und nach dem verfahren hergestellte munition

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA742908A (en) * 1966-09-20 A. Dickinson Lionel Ammunition sleeve for cooling gun barrels
US3648616A (en) * 1969-09-10 1972-03-14 Omark Industries Inc Multistage power load
DE2323244C3 (de) * 1973-05-09 1979-04-19 Rheinmetall Gmbh, 4000 Duesseldorf Flügelstabilisiertes Unterkalibergeschoß
DE3021914A1 (de) * 1980-06-11 1983-09-08 Deutsch Franz Forsch Inst Unterkalibergeschoss mit treibring
DE3205152C2 (de) * 1982-02-13 1984-04-12 Mauser-Werke Oberndorf Gmbh, 7238 Oberndorf Treibladung für Hülsenmunition und Verfahren zu ihrer Herstellung
USH18H (en) * 1983-11-21 1986-02-04 The United States Of America As Represented By The Secretary Of The Army Reduction of erosion and muzzle flash of gun tubes
DE3409017A1 (de) * 1984-03-13 1985-09-26 Rheinmetall GmbH, 4000 Düsseldorf Patronierte munition fuer rohrwaffen
DE3428712A1 (de) * 1984-08-03 1986-02-13 Diehl GmbH & Co, 8500 Nürnberg Geschoss mit einer zusatz-treibladung
DE3517125A1 (de) * 1985-05-11 1986-11-13 Rheinmetall GmbH, 4000 Düsseldorf Unterkalibriges geschoss
US4823699A (en) * 1987-04-14 1989-04-25 Aai Corporation Back-actuated forward ignition ammunition and method

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2622687A1 (fr) * 1987-10-29 1989-05-05 France Etat Armement Chargement propulsif pour munition comportant un projectile empenne ainsi que son procede de realisation
DE3840875A1 (de) * 1988-12-05 1990-06-07 Rheinmetall Gmbh Verfahren und vorrichtung zum verdichten einer treibladung und nach dem verfahren hergestellte munition

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0707560A1 (en) * 1993-05-04 1996-04-24 Alliant Techsystems Inc. Improved propellant system
EP0707560A4 (en) * 1993-05-04 1998-01-07 Alliant Techsystems Inc IMPROVED PROPULSIVE SYSTEM
FR2716677A1 (fr) * 1994-02-26 1995-09-01 Dynamit Nobel Ag Procédé de fabrication sans solvant de charges propulsives poreuses préformées, et charges propulsives ainsi fabriquées.

Also Published As

Publication number Publication date
US5160804A (en) 1992-11-03
NO912544D0 (no) 1991-06-27
DE4020691A1 (de) 1992-01-02
NO912544L (no) 1991-12-30

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