EP2428762A2 - Corps de charge propulsive - Google Patents

Corps de charge propulsive Download PDF

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Publication number
EP2428762A2
EP2428762A2 EP11007293A EP11007293A EP2428762A2 EP 2428762 A2 EP2428762 A2 EP 2428762A2 EP 11007293 A EP11007293 A EP 11007293A EP 11007293 A EP11007293 A EP 11007293A EP 2428762 A2 EP2428762 A2 EP 2428762A2
Authority
EP
European Patent Office
Prior art keywords
propellant
propellant charge
radial projections
body according
base body
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Withdrawn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
EP11007293A
Other languages
German (de)
English (en)
Other versions
EP2428762A3 (fr
Inventor
Axel Dr. Pfersmann
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.)
Diehl BGT Defence GmbH and Co KG
Original Assignee
Diehl BGT Defence GmbH and Co KG
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 Diehl BGT Defence GmbH and Co KG filed Critical Diehl BGT Defence GmbH and Co KG
Publication of EP2428762A2 publication Critical patent/EP2428762A2/fr
Publication of EP2428762A3 publication Critical patent/EP2428762A3/fr
Withdrawn legal-status Critical Current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
    • F42B5/38—Separately-loaded propellant charges, e.g. cartridge bags
    • 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
    • F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02—Cartridges, i.e. cases with charge and missile
    • F42B5/18—Caseless ammunition; Cartridges having combustible cases
    • F42B5/182—Caseless cartridges characterised by their shape

Definitions

  • the invention relates to a propellant charge body according to the preamble of claim 1.
  • propellant charge bodies for introduction into a propellant charge chamber of a firearm for firing caseless ammunition are known in modern military technology.
  • a firearm for firing caseless ammunition is for example from the EP 1 731 867 B1 known.
  • the projectile and the propellant charge body are each assigned to a separate projectile warehouse or propellant charge bearings, which are aligned in firing position coaxial with the axis of the barrel of the weapon barrel.
  • propellant charge bodies have a main body containing a propellant charge which has a smaller diameter than the inner diameter of the propellant charge chamber.
  • the reason for the reduced diameter of the propellant charge body lies in the composition and the associated burn-up characteristic of the propellant charge body.
  • modern propellant charge bodies by means of a binder comprise compressed propellant grains which are arranged to granulate into individual grains upon ignition of the propellant charge body.
  • the cohesion of the powder in the individual powder grains is two orders of magnitude stronger than the cohesion of the powder grains mediated by the binder.
  • the propellant charge body granulated to individual propellant grains has a larger volume than the initially compressed propellant charge body, the propellant charge body has one with respect to the one Inner diameter of the smaller diameter propellant charge chamber used so that the propellant charge body has enough space for disassembly (granulation) in its individual powder grains.
  • a disadvantage of this conventional propellant charge body was that the central longitudinal axis of the propellant charge body inserted into the propellant charge chamber does not coincide exactly with the central longitudinal axis of the propellant charge chamber. Under certain circumstances, this makes it more difficult to ignite the propellant charge body, which as a rule takes place via an ignition means which is arranged in extension of the central longitudinal axis of the propellant charge body.
  • the Zündiniti istsmechanismus is arranged in extension of the central longitudinal axis of the propellant charge chamber, it can lead to ignition failure by the offset of the central longitudinal axes of propellant body and propellant charge chamber.
  • Another disadvantage of the conventional propellant charge body with respect to the inner diameter of the propellant charge chamber smaller diameter is the risk of tilting during insertion of the propellant charge body into the propellant charge chamber.
  • radial projections are arranged in one or more subregions on the circumference of the main body, which align the radius of the main body in these subregions with the inner radius of the propellant charge chamber.
  • the base body has the radial projections on opposite sides of the circumference.
  • the radial projections in pairs axially symmetric to the central longitudinal axis of the propellant charge body be arranged.
  • the propellant charge body can be centered particularly precisely in the propellant charge chamber.
  • the radial projections are in the form of ribs. Under ribs are particularly to be understood elongated bulges, which have a greater extent in one direction than transverse to this direction. Rib-shaped radial projections are easy to manufacture and may have additional advantageous features depending on the orientation.
  • At least one or more of the ribs can run parallel to the longitudinal axis of the propellant charge body.
  • Such a rib orientation has a favorable effect on the insertability of the propellant charge body into the propellant charge chamber.
  • the ribs can also run in the circumferential direction.
  • the ribs extending in the circumferential direction can result in an overall more stable design of the rib structure (ribbed network).
  • At least one or more of the ribs extends obliquely to the longitudinal axis and obliquely to the circumferential direction of the propellant charge body / extend.
  • a spiral running around the main body rib is conceivable.
  • the radial projections are preferably in the form of nubs or fields. Fields are to be understood in particular as square or circular bulges which have a substantially equal extent in all directions. Due to the design of the radial projections in the form of knobs or fields can be compared to the rib variant of the free space between the radial projections increased without having to accept a loss in the Zentri mecanics Koch. As a result, the space for disassembling the propellant charge body into its propellant charge grains can advantageously be increased.
  • knob-shaped or field-shaped radial projections and rib-shaped radial projections on a propellant body it is also possible to combine knob-shaped or field-shaped radial projections and rib-shaped radial projections on a propellant body to take advantage of both projection shapes.
  • the composition of the material of the radial protrusions differs from the composition of the material of the main body.
  • the radial projections on the centering function can take over further advantageous functions, regardless of optimization of the material of the body.
  • the material from which the main body containing the propellant contains by means of a binder, preferably comprises compressed propellant grains. These compressed propellant grains are arranged to granulate into individual grains upon ignition of the propellant charge body. As a result, a uniform, faster burning of the entire propellant charge is ensured, which in turn ensures reproducible from shot to shot inside ballistics in the propellant charge chamber.
  • the material of the radial projections - at least in the areas which touch the inner wall of the propellant charge chamber - has a significantly higher ignition temperature than the material of the propellant charge agent.
  • the conventional propellant charge bodies without the radial projections according to the invention there was the problem that in the case of strong heating of the propellant charge chamber after prolonged firing the next introduced into the hot propellant charge propellant charge body for premature auto-ignition outside the intended firing sequence tended (cook-off effect).
  • conventional propellant charge on the basis of nitrocellulose which can also be used for the preparation of the compressed propellant grains of the main body according to the present invention, an ignition temperature of about 160 ° C.
  • the material of the radial projections has a significantly higher ignition temperature (ie a temperature higher by 80 ° C. to 120 ° C.), for example 280 ° C., the dangerous self-ignition of the propellant charge body can be largely avoided.
  • the material of FIG radial protrusions have a low thermal conductivity.
  • an advantageous effect against the cook-off effect can be achieved if a propellant charge body lingers for a long time in a hot-fired propellant charge chamber.
  • the ignition temperature of the propellant can then be reached under certain circumstances at the contact point between the radial projection and the base body. Therefore, it is particularly advantageous if the thermal conductivity of the material of the radial protrusions is 200 mW / mK (milliwatts per meter and Kelvin) or less.
  • advantageous material as a component for the radial projections is hard foam, in particular a rigid polyurethane foam.
  • the hard foam is preferably provided with a pyrotechnic agent which promotes the burning of the rigid foam.
  • a pyrotechnic agent which promotes the burning of the rigid foam.
  • the pyrotechnic agent promoting the combustion of the rigid foam has a substantially higher ignition temperature with respect to the material of the propellent charge of the main body.
  • octogen which has the above-mentioned ignition temperature of about 280 ° C.
  • a layer is arranged between the material of the radial projections and the material of the base body, which prevents penetration of the material of the radial projections into the material of the base body, in particular during the application process of the radial projections on the base body.
  • the layer between the material of the radial projections and the material of the base body is preferably made of a material which as a result of the heat development during ignition of the propellant charge body quickly and as possible is completely consumed.
  • a thin plastic layer is recommended, the thickness of which may preferably be in the range between 0.01 mm and 0.2 mm.
  • the base body of the propellant charge body is surrounded on its entire circumference by the material of the radial projections.
  • the material thickness between the radial projections is lower than in the region of the radial projections.
  • the body is surrounded on its entire circumference of material with low thermal conductivity, the body is even better protected from heat input from the hot inner wall of the propellant charge chamber.
  • the air pockets in the foam cells ensure good insulation and low heat conduction.
  • the propellant charge body essentially has the shape of a cylinder whose edges are bevelled. Due to the conical bevel of the cylinder edges of the propellant charge body can also be easily introduced into the propellant charge chamber, when the central longitudinal axes of propellant charge chamber and propellant charge body do not coincide exactly.
  • FIGS. 1 a and 1b show the basic structure of a propellant charge body 1 according to the invention.
  • the propellant charge body 1 is provided for insertion into a propellant charge chamber 10 of a firearm for firing caseless ammunition.
  • the propellant charge body 1 has a main body 1a containing a propellant charge.
  • the main body 1 a has a diameter d smaller than the inner diameter D of the propellant charge chamber 10.
  • radial projections 2 are arranged, which equalize the radius r of the body 1 a in these sub-regions of the inner radius R of the propellant charge chamber 10.
  • FIG. 2 shows a further embodiment of the propellant charge body 1, in which the main body 1 a has the radial projections 2 on opposite sides of the circumference.
  • the projections are each arranged in pairs axially symmetric to the central longitudinal axis of the propellant charge body 1.
  • FIGS. 3a to 3e show various embodiments of a propellant charge body 1 with radial projections 2 in the form of ribs. Ribs are to be understood as elongated bulges which have a greater extent in one direction than transverse to this direction. So shows FIG. 3a a propellant charge body 1 with a plurality of ribs 2, which run parallel to the longitudinal axis of the propellant charge body 1. According to FIG. 3a Preferably, both the width of all ribs 2 equal and the distances between two adjacent ribs 2 are equal. Preferably, however, the width of the individual ribs 2 is smaller than the distance between adjacent ribs 2 in order to produce as large a clearance as possible between the ribs 2.
  • the propellant charge body 1 has a combination of ribs 2 extending parallel to the longitudinal axis of the propellant charge body 1 and ribs 2 extending in the circumferential direction.
  • a kind of mesh can be generated on the base body 1 a of the propellant charge body 1.
  • FIG. 3d figure shows ribs 2 which extend obliquely to the longitudinal axis and obliquely to the circumferential direction of the propellant charge body 1.
  • the oblique course of the ribs 2 can take place at any angle to the longitudinal axis or the circumferential direction.
  • An oblique orientation of 45 ° to the longitudinal axis and the circumferential direction represents a preferred oblique orientation, in particular with combination of obliquely oriented ribs 2 with parallel to the longitudinal axis of the propellant charge body 1 extending ribs 2 and / or extending in the circumferential direction ribs 2, because then there are uniformly large gaps between the differently oriented ribs 2.
  • the sloping ribs can - as in 3d figure shown - for example, each extend over a small compared to the total circumference of the body 1 a small distance, but they can also as in FIG. 3e shown, for example, spiral in one or more times around the main body 1 a wind.
  • FIG. 3e shown, for example, spiral in one or more times around the main body 1 a wind.
  • a plurality of spiral ribs are twisted into one another like a screw.
  • FIG. 3f and 3g show a propellant charge body 1 with radial projections 2 in the form of knobs or fields. Fields are understood to mean square or circular bulges which are essentially the same in all directions Have expansion. So shows FIG. 3f a propellant charge body 1 with evenly over the circumference of the body 1 a distributed round fields or nubs. FIG. 3g shows an equally regular arrangement of square boxes on the circumference of the main body 1 a of the propellant charge body first
  • the advantage of the formation of the radial projections 2 in the form of nubs or fields relative to the rib-shaped formation of the radial projections 2 is due to the fact that at the same height of the radial projections 2, the field-shaped formation of the radial projections 2, a larger volume of the spaces between the radial projections 2 as the rib-shaped formation of the radial projections 2 allows.
  • compositions of the material of the radial projections 2 and the material of the main body 1 a may differ from each other. This is in view of a possibly opposite optimization of the properties of the radial projections 2 and the properties of the body 1 a of advantage. So z. B. the requirements for mechanical strength, temperature resistance and thermal conductivity in the material of the radial projections 2 lead to a different choice of material than the material of the body 1 a.
  • FIG. 4 shows such a propellant charge body 1, in which the composition of the material of the radial projections 2 differs from the material of the base 1 a.
  • a layer 3 is preferably arranged between the material of the radial projections 2 and the material of the main body 1 a, which in particular during the application process of the radial projections 2 on the base 1a a penetration of the material of the radial projections 2 in the material of the body 1 a prevented.
  • the use of the intermediate layer 3 is by no means an indispensable prerequisite when using different materials for radial projections 2 and basic body. Rather, the use of the intermediate layer 3 is an optional, albeit advantageous measure.
  • the layer 3 is made of a material which is consumed rapidly and as completely as possible as a result of the heat development during ignition of the propellant charge body 1, so that no combustion residues remain in the propellant charge chamber 10.
  • a thin plastic layer offers, which preferably has a thickness of a few hundredths of a millimeter. Such a layer thickness ensured already preventing the penetration of the material of the radial projections during their application process on the main body 1 a.
  • the radial projections 2 comprise a material which has a high ignition temperature and / or a low thermal conductivity.
  • the material of the radial projections 2 burns as quickly as possible and residue-free in order to avoid residues in the propellant charge chamber 10, which could otherwise lead to disturbances in the weapon system.
  • the (desired) burning of the material of the radial projections 2 provides the least possible contribution to the internal ballistics. This means that when burning off the material of the radial projections 2 as little pressure Nolumenarbeit is to be made in order to falsify as little as possible by the body 1a predefined inner ballistics or to make consistently reproducible.
  • a material which advantageously combines all the properties listed above is rigid foam, in particular rigid polyurethane foam.
  • the residue-free burnup of the hard foam can be ensured in an advantageous manner by the rigid foam is added to the combustion of the rigid foam promotional pyrotechnic agent.
  • Octogen in particular, which has a substantially higher ignition temperature with respect to the material of the propellent charge of the main body 1 a, namely approximately 280 ° C., is particularly suitable here.
  • octogen which has a substantially higher ignition temperature with respect to the material of the propellent charge of the main body 1 a, namely approximately 280 ° C.
  • octogen provides no significant contribution to the internal ballistics, which is yes - as explained above - is desirable.
  • FIG. 5 shows a particularly preferred embodiment of a propellant charge body 1 according to the invention, in which the main body 1 a is surrounded on its entire circumference by the material of the radial projections 2.
  • the material thickness between the radial projections 2 is less than in the region of the radial projections 2.
  • the arrangement of the intermediate layer 3 is advantageous, but not essential. Due to the full enclosure of the main body 1 a, which may also include the end faces of the propellant charge body 1, a particularly good heat insulating effect is achieved.
  • rigid polyurethane foam provide the Air pockets in the foam chambers for a very good insulation effect. This can be advantageous in particular when a propellant charge body 1 remains in a hot-fired propellant charge chamber 10 for a long time.
  • FIG. 6 shows an additional optional feature, which has a positive effect on the usability of the inventive propellant charge body 1 in the propellant charge chamber 10.
  • the propellant charge body 1 substantially in the shape of a cylinder, whose edges are S beveled.
  • a funneling effect is achieved during the introduction process of the propellant charge body 1 into the propellant charge chamber 10. This funneling effect can still be supported by a conical bevel of the insertion hole of the propellant charge chamber 10.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Containers And Packaging Bodies Having A Special Means To Remove Contents (AREA)
  • Automotive Seat Belt Assembly (AREA)
  • Manufacture Of Porous Articles, And Recovery And Treatment Of Waste Products (AREA)
  • Toys (AREA)
  • Nozzles (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP11007293.1A 2010-09-14 2011-09-08 Corps de charge propulsive Withdrawn EP2428762A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102010045383.8A DE102010045383B4 (de) 2010-09-14 2010-09-14 Treibladungskörper

Publications (2)

Publication Number Publication Date
EP2428762A2 true EP2428762A2 (fr) 2012-03-14
EP2428762A3 EP2428762A3 (fr) 2014-12-03

Family

ID=44587617

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11007293.1A Withdrawn EP2428762A3 (fr) 2010-09-14 2011-09-08 Corps de charge propulsive

Country Status (5)

Country Link
US (1) US8561541B2 (fr)
EP (1) EP2428762A3 (fr)
DE (1) DE102010045383B4 (fr)
RU (1) RU2580605C2 (fr)
ZA (1) ZA201106648B (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8418619B1 (en) * 2008-01-03 2013-04-16 Kilgore Flares Company, Llc Kinematic countermeasure
DE102015005982A1 (de) * 2015-05-08 2016-11-10 Diehl Bgt Defence Gmbh & Co. Kg Sprengladung zur Aufnahme in einer Geschosshülle sowie Geschoss
GB2555616B (en) * 2016-11-04 2021-10-06 Bae Systems Plc Modular charge container

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1731867B1 (fr) 2005-06-10 2007-11-21 Diehl BGT Defence GmbH & Co.KG Système d'arme avec munition sans douilles

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US35949A (en) * 1862-07-22 Improvement in cartridges
US99078A (en) * 1870-01-25 Improvement in cartridges
US702208A (en) * 1902-02-25 1902-06-10 William Everton Hayner Cartridge.
US3713395A (en) * 1971-04-28 1973-01-30 Us Navy Solid propellant
US3815506A (en) * 1972-03-16 1974-06-11 Us Navy Rubber cellulosic tape sandwich inhibitor
DE2651653A1 (de) * 1976-11-12 1978-05-18 Odenberg Friedrich W Gestaltung und ausstattung von ladungsraeumen oder treibladungskoerpern an und fuer waffen fuer das abfeuern von huelsenloser munition
FR2380529A1 (fr) * 1977-02-14 1978-09-08 Serat Perfectionnements apportes aux charges propulsives pour projectiles, missiles ou roquettes
DE3815436A1 (de) * 1988-05-06 1989-11-16 Muiden Chemie B V Treibladungen fuer grosskalibrige geschosse
DE69111944T2 (de) * 1990-08-30 1996-04-18 Olin Corp Hülsenloses einheitsliches Ammunitionsladungsmodul.
US5269224A (en) * 1990-08-30 1993-12-14 Olin Corporation Caseless utilized ammunition charge module
RU2170908C2 (ru) * 1999-07-15 2001-07-20 Академия нового мышления Безгильзовый патрон для огнестрельного оружия
US6688232B2 (en) * 2001-12-31 2004-02-10 Legend Products Corporation Compressed powder charge for muzzleloader and black powder firearms
US7469640B2 (en) * 2006-09-28 2008-12-30 Alliant Techsystems Inc. Flares including reactive foil for igniting a combustible grain thereof and methods of fabricating and igniting such flares

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1731867B1 (fr) 2005-06-10 2007-11-21 Diehl BGT Defence GmbH & Co.KG Système d'arme avec munition sans douilles

Also Published As

Publication number Publication date
US20120060714A1 (en) 2012-03-15
RU2580605C2 (ru) 2016-04-10
DE102010045383B4 (de) 2014-01-16
RU2011137702A (ru) 2013-03-20
US8561541B2 (en) 2013-10-22
EP2428762A3 (fr) 2014-12-03
ZA201106648B (en) 2012-05-30
DE102010045383A1 (de) 2012-03-15

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