EP0795114A1 - Cartridge - Google Patents

Cartridge

Info

Publication number
EP0795114A1
EP0795114A1 EP95941062A EP95941062A EP0795114A1 EP 0795114 A1 EP0795114 A1 EP 0795114A1 EP 95941062 A EP95941062 A EP 95941062A EP 95941062 A EP95941062 A EP 95941062A EP 0795114 A1 EP0795114 A1 EP 0795114A1
Authority
EP
European Patent Office
Prior art keywords
cartridge according
combustion chamber
powder
propellant charge
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.)
Withdrawn
Application number
EP95941062A
Other languages
German (de)
French (fr)
Inventor
Johannes Eich
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.)
Dynamit Nobel AG
Dynamit Nobel GmbH Explosivstoff und Systemtechnik
Original Assignee
Dynamit Nobel AG
Dynamit Nobel GmbH Explosivstoff und Systemtechnik
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 Dynamit Nobel AG, Dynamit Nobel GmbH Explosivstoff und Systemtechnik filed Critical Dynamit Nobel AG
Publication of EP0795114A1 publication Critical patent/EP0795114A1/en
Withdrawn legal-status Critical Current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
    • F42C19/0819—Primers or igniters for the initiation of rocket motors, i.e. pyrotechnical aspects thereof
    • 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
    • F42B5/05—Cartridges, i.e. cases with charge and missile for recoilless guns
    • 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
    • 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
    • F42B5/184—Caseless ammunition; Cartridges having combustible cases telescopic

Definitions

  • the present invention relates to a new cartridge.
  • the nozzle cannon which is also known as a recoil-free tube
  • the principle of the recoil-free barrel is that the weapon barrel also has an opening at the rear, which is followed by a Laval nozzle.
  • the combustion chamber is initially closed off to the rear by a damper plate against the nozzle opening. At the so-called burst pressure, this plate breaks and some of the powder gases flow out through the Lavalduse to the rear. If the system is designed correctly, a force acts on the tube in the weft direction, which compensates for the recoil generated.
  • a disadvantage of this concept is the absolutely necessary temporary closure of the combustion chamber. This is the only way to generate the gas pressure required to accelerate the projectile. The combustion chamber must therefore be temporarily sealed again before each shot; a measure that severely restricts the use of the nozzle cannon, or is impossible with a machine cannon.
  • the object of the present invention was to remedy this disadvantage.
  • the cartridge is designed so that an aerodynamic blocking can form.
  • a rapidly burning Ignition propellant charge is surrounded by slower burning propellant powder.
  • an internal igniter is provided according to the invention. The hot combustion gases generated when the propellant charge burns off then ignite the more slowly burning propellant charge powder. Since by that the ignition propellant charge, which is located in a so-called primary combustion chamber, is surrounded by slow burning of the propellant charge powder, so much gas is formed within a very short time that such a high pressure level can build up that an optimal implementation of the propellant charge powder is guaranteed is.
  • the desired aero dynamic blocking is formed.
  • the resulting total gas pressure is sufficient to accelerate the projectile to the required speed and to compensate for the recoil. Since slowly burning propellant powder acts like an internal insulation board.
  • insulation plate in the sense of the present invention, however, is not to be equated with the insulation plate known in the prior art, which seal off the combustion chamber against the nozzle opening.
  • the insulation plate according to the invention serve to allow a sufficiently high gas pressure to form inside the cartridge, which ensures the desired aerodynamic mixing.
  • Figure l sleeve 2, base plate 3, insulation plate 4, to ignition amplifier 5, combustible disc 6, 7, base disc 8 internal ignition element 10, floor 11, secondary combustion chamber 12, igniter propellant powder 13, primary combustion chamber 14, central bore 15, gap 16, main drift fertilizer 17, blind hole 19, bushing 20, contacts 21.
  • Figure 2 Combustion / storey room 1, sleeve 2, base plate 3, insulation plate 4, ignition amplifier 5, combustible disc 6, 7, base disc 8, sealing cap 9, internal ignition element 10, floor 11, secondary combustion chamber 12, ignition propellant powder 13, primary combustion chamber 14 , Central bore 15, gap 16, main propellant charge 17, projectile holder 18, blind bore 19, bushing 20, contacts 21.
  • the exemplary embodiments according to the invention consequently consist of a sleeve 2, a projectile 11, a secondary combustion chamber 12, a primary combustion chamber 14, an internal ignition element 10 and a base plate 8.
  • the primary combustion chamber 14 contains at least one internal combustible or consumable insulation plate 4 made of a propellant charge powder block with a central bore 15.
  • the primary combustion chamber 14 is closed off with a combustible disk 7 towards the secondary combustion chamber 12. This can be useful if the propellant powder block in the secondary combustion chamber 12 consists of propellant powder other than the damper plates 4.
  • the central bore 15 can be tapered towards the rear in a conical or stepped manner.
  • the central bore 15 normally receives the internal ignition element 10, but the internal ignition element 10 can also be provided outside the central bore 15, as long as it is ensured that the ignition propellant powder is first ignited.
  • the internal ignition element 10 is surrounded, at least in the upper area, by rapidly burning ignition propellant powder 13.
  • the central bore 15 is so large that the internal ignition element 10 is surrounded by rapidly burning ignition propellant powder 13.
  • the at least one internal damper plate 4 is additionally surrounded towards the sleeve 2 by rapidly burning ignition propellant powder 13.
  • the bottom of the primary Brennieris 14 can be completed with a freshlybil Deten insulation plate as a base plate 3.
  • This base plate 3 has a blind bore 19 with at least the diameter of the central bore 15.
  • bushings 20 for contacts 21 can be provided in the base plate 3.
  • the so-called inductive ignition is preferably used.
  • the secondary coil of the inductive ignition is located at the rear of the cartridge.
  • the secondary coil is connected to the internal ignition element 10 via contact wires.
  • This embodiment allows a largely free positioning of the interior ignition element 10.
  • the internal ignition element 1 can carry an ignition amplifier 5. If at least two internal insulation panels 4 are inserted according to the invention, the insulation panels 4 can be separated from one another by columns 1.
  • a further embodiment of the present invention provides partial or full telescope cartridges in which a further combustion / storey space 1 adjoins the secondary combustion space 12, which is also provided by the sleeve 2.
  • This floor space 1 takes the floor 11 on un contains for better support and management of the floor 1 a floor holder 18, which is preferably adapted to the shape of the Ge floor 11.
  • the combustion / storey space is closed by a cap 11 that centers the storey.
  • the sleeve as well as the base plate can consist of materials known per se for this purpose.
  • the sleeve 2 and / or the base plate 8 consists of combustible material, preferably based on nitrocellulose (NC).
  • the sleeve 2 is particularly preferably a nitrocellulose winding tube.
  • the conventional propellant powders known per se for example those based on NC, can be used as propellant charges.
  • high-temperature-resistant propellant powder elements can also be used.
  • the nitroamine-based propellant powder elements such as plastic-bound hexogen or octogen, may be mentioned here, for example.
  • the projectile holder 18 can consist, for example, of conventional rocket solid fuel. But the high-temperature resistant fuels can also be used here. Thus, the projectile holder 18, when it has been ignited after the disk 6 has been burned by the main propellant charge 17, contributes to the acceleration of the projectile 11.
  • the cartridges according to the invention can be used, for example, in machine guns with normal cadence and a caliber of 20 to 50 mm.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Air Bags (AREA)

Abstract

The present disclosure concerns a cartridge comprising a primary combustion chamber (14) for the detonation propellant charge, an inner detonator (10) for the detonation propellant charge, at least one confining layer (4) of propellant charge powder which surrounds the detonation propellant charge, and a projectile (11).

Description

Patrone cartridge
Gegenstand der vorliegenden Erfindung ist eine neue Patrone.The present invention relates to a new cartridge.
Sollen artilleristische Geräte möglichst leicht sein, findet die Düsenkanone, die auch als rückstoßfreies Rohr bezeichnet wird, Verwendung. Das Prinzip des rückstoßfreien Rohres be¬ steht darin, daß das Waffenrohr auch hinten eine Öffnung hat, an die sich eine Lavalduse anschließt. Um den Aufbau eines für die Bewegung des Geschosses ausreichend großen Gasdruckes zu gewährleisten, ist der Verbrennungsraum gegen die Düsen- δffnung zunächst durch eine Verdämmungsplatte nach hinten ab¬ geschlossen. Bei dem sogenannten Berstdruck bricht diese Platte und ein Teil der Pulvergase strömt durch die Lavalduse nach hinten ab. Wird das System richtig ausgelegt, greift da¬ mit in Schußrichtung eine Kraft am Rohr an, die den erzeugten Rückstoß kompensiert.If artillery equipment is to be as light as possible, the nozzle cannon, which is also known as a recoil-free tube, is used. The principle of the recoil-free barrel is that the weapon barrel also has an opening at the rear, which is followed by a Laval nozzle. In order to ensure the build-up of a gas pressure which is sufficiently high for the movement of the projectile, the combustion chamber is initially closed off to the rear by a damper plate against the nozzle opening. At the so-called burst pressure, this plate breaks and some of the powder gases flow out through the Lavalduse to the rear. If the system is designed correctly, a force acts on the tube in the weft direction, which compensates for the recoil generated.
Nachteilig bei diesem Konzept ist der unbedingt erforderliche vorübergehende Verschluß des Verbrennungsraumes. Nur so ist der für die Beschleunigung des Geschosses notwendige Gasdruck zu erzeugen. Vor jedem Schuß ist daher der Verbrennungsraum erneut vorübergehend abzudichten; eine Maßnahme, die den Ein- satz der Düsenkanone stark einschränkt, bzw. bei einer Ma¬ schinenkanone unmöglich ist.A disadvantage of this concept is the absolutely necessary temporary closure of the combustion chamber. This is the only way to generate the gas pressure required to accelerate the projectile. The combustion chamber must therefore be temporarily sealed again before each shot; a measure that severely restricts the use of the nozzle cannon, or is impossible with a machine cannon.
Aufgabe der vorliegenden Erfindung war, diesem Nachteil abzu¬ helfen.The object of the present invention was to remedy this disadvantage.
Gelöst wurde diese Aufgabe durch eine neue Patrone mit den Merkmalen des Hauptanspruchs. Vorzugsweise Ausgestaltungen sind in den Unteransprüchen beschrieben.This task was solved by a new cartridge with the characteristics of the main claim. Refinements are preferably described in the subclaims.
Erfindungsgemäß wird die Patrone so ausgestaltet, daß sich eine aerodynamische Verblockung ausbilden kann. Erfindungsge¬ mäß erzielt wird dies dadurch, daß eine schnell abbrennende Anzündtreibladung von langsamer abbrennendem Treibladungspul ver umgeben ist. Um sicherzustellen, daß zunächst die Anzünd treibladung angezündet wird, ist erfindungsgemäß ein innen liegendes Anzündelement vorgesehen. Die beim Abbrand der An zündtreibladung entstehenden heißen Verbrennungsgase zünde dann das langsamer abbrennende Treibladungspulver an. Da durch, daß die Anzündtreibladung, die sich in einem sogenann ten Primärverbrennungsraum befindet, von langsamer abbrennen dem Treibladungspulver umgeben ist, bildet sich innerhal kürzester Zeit so viel Gas, daß sich ein so hohes Drucknivea aufbauen kann, daß eine optimale Umsetzung des Treibladungs pulver gewährleistet ist. Trotz des Gasverlustes durch di Lavalduse der Düsenkanone bildet sich so die gewünschte aero dynamische Verblockung aus. Der so entstehende Gesamtgasdruc reicht aus, um das Geschoß auf die erforderliche Geschwindig keit zu beschleunigen und den Rückstoß zu kompensieren. Da langsam abbrennende Treibladungspulver wirkt quasi wie ein innenliegende Verdämmungsplatte. Der Begriff Verdämmungs platte im Sinne der vorliegenden Erfindung ist jedoch nich mit den im Stand der Technik bekannten Verdämmungsplatte gleichzusetzen, die den Verbrennungsraum gegen die Düsenδff nung abschließen. Die erfindungsgemäßen Verdämmungsplatte dienen dazu, im Innern der Patrone einen genügend hohen Gas druck sich ausbilden zu lassen, der die gewünschte aerodyna mische Verblockung gewährleistet.According to the invention, the cartridge is designed so that an aerodynamic blocking can form. This is achieved according to the invention in that a rapidly burning Ignition propellant charge is surrounded by slower burning propellant powder. To ensure that the igniter propellant charge is ignited, an internal igniter is provided according to the invention. The hot combustion gases generated when the propellant charge burns off then ignite the more slowly burning propellant charge powder. Since by that the ignition propellant charge, which is located in a so-called primary combustion chamber, is surrounded by slow burning of the propellant charge powder, so much gas is formed within a very short time that such a high pressure level can build up that an optimal implementation of the propellant charge powder is guaranteed is. Despite the gas loss due to the Lavalduse of the nozzle cannon, the desired aero dynamic blocking is formed. The resulting total gas pressure is sufficient to accelerate the projectile to the required speed and to compensate for the recoil. Since slowly burning propellant powder acts like an internal insulation board. The term insulation plate in the sense of the present invention, however, is not to be equated with the insulation plate known in the prior art, which seal off the combustion chamber against the nozzle opening. The insulation plate according to the invention serve to allow a sufficiently high gas pressure to form inside the cartridge, which ensures the desired aerodynamic mixing.
Die vorliegende Erfindung soll, ohne sie jedoch einzuschrän ken, anhand der Figuren 1 und 2 erläutert werden:The present invention is intended to be explained, however without restricting it, with reference to FIGS.
Figur l: Hülse 2, Bodenplatte 3, Verdämmungsplatte 4, An zündverstärker 5, verbrennbare Scheibe 6, 7, Bodenscheibe 8 innenliegenliegendes Anzündelement 10, Geschoß 11, Sekundär verbrennungsräum 12, Anzündtreibladungspulver 13, Primärver brennungsraum 14, Zentralbohrung 15, Spalt 16, Haupttreibla düng 17, Sackbohrung 19, Durchführung 20, Kontakte 21. Figur 2: Verbrennungs-/Geschoßraum l, Hülse 2, Bodenplatte 3, Verdämmungsplatte 4, Anzündverstärker 5, verbrennbare Scheibe 6, 7, Bodenscheibe 8, Verschlußkappe 9, innenliegen¬ des Anzündelement 10, Geschoß 11, Sekundärverbrennungsraum 12, Anzündtreibladungspulver 13, Primärverbrennungsraum 14, Zentralbohrung 15, Spalt 16, Haupttreibladung 17, Geschoßhal¬ ter 18, Sackbohrung 19, Durchführung 20, Kontakte 21.Figure l: sleeve 2, base plate 3, insulation plate 4, to ignition amplifier 5, combustible disc 6, 7, base disc 8 internal ignition element 10, floor 11, secondary combustion chamber 12, igniter propellant powder 13, primary combustion chamber 14, central bore 15, gap 16, main drift fertilizer 17, blind hole 19, bushing 20, contacts 21. Figure 2: Combustion / storey room 1, sleeve 2, base plate 3, insulation plate 4, ignition amplifier 5, combustible disc 6, 7, base disc 8, sealing cap 9, internal ignition element 10, floor 11, secondary combustion chamber 12, ignition propellant powder 13, primary combustion chamber 14 , Central bore 15, gap 16, main propellant charge 17, projectile holder 18, blind bore 19, bushing 20, contacts 21.
Die beispielhaft dargestellten erfindungsgemäßen Ausgestal- tungen bestehen folglich aus einer Hülse 2, einem Geschoß 11, einem Sekundärverbrennungsraum 12, einem Primärverbrennungs¬ raum 14, einem innenliegenden Anzündelement 10 und einer Bo¬ denscheibe 8 besteht. Der Primärverbrennungsraum 14 enthält mindestens eine innenliegende verbrenn- bzw. verzehrbare Ver- dämmungsplatte 4 aus einem Treibladungspulverblock mit Zen¬ tralbohrung 15. Der Primärverbrennungsraum 14 ist im vorlie¬ genden Beispiel zum Sekundärverbrennungsraum 12 hin mit einer verbrennbaren Scheibe 7 abgeschlossen. Dies kann dann sinn¬ voll sein, wenn der Treibladungspulverblock im Sekundärver- brennungsraum 12 aus anderem Treibladungspulver besteht, als die Verdämmungsplatten 4. Die Zentralbohrung 15 kann sich zum Heck hin kegelförmig oder auch stufenförmig verjüngen. Die Zentralbohrung 15 nimmt im Normalfall das innenliegende An¬ zündelement 10 auf, doch kann das innenliegende Anzündelement 10 auch außerhalb der Zentralbohrung 15 angebracht sein, so¬ lange sichergestelt ist, daß zunächst das Anzündtreibladungs¬ pulver angezündet wird. Um eine sichere Anzündung zu gewähr¬ leisten, ist das innenliegende Anzündelement 10 zumindest im oberen Bereich von schnell abbrennendem Anzündtreibladungs- pulver 13 umgeben. Bei einer anderen Ausführungsform, insbe¬ sondere, wenn mindestens zwei Verdämmungsplatten vorgesehen sind, ist die Zentralbohrung 15 so groß, daß das innenlie¬ gende Anzündelement 10 von schnell abbrennendem Anzünd¬ treibladungspulver 13 umgeben ist. Bei einer weiteren Ausfüh- rungsform ist die mindestens eine innenliegende Verdämmungs¬ platte 4 zur Hülse 2 hin zusätzlich von schnell abbrennendem Anzündtreibladungspulver 13 umgeben. Der Boden des Primärver- brennungsräumes 14 kann mit einer als Bodenplatte 3 ausgebil deten Verdämmungsplatte abgeschlossen sein. Diese Bodenplatt 3 weist eine Sackbohrung 19 mit mindestens dem Durchmesse der Zentralbohrung 15 auf. Je nach Wahl des innenliegende Anzündelements 10 können in der Bodenplatte 3 Durchführunge 20 für Kontakte 21 vorgesehen sein. Vorzugsweise wird die so genannte induktive Anzündung verwendet. Hierfür befindet sic am Heck der Patrone die Sekundärspule der induktiven Anzün dung. Die Sekundärspule ist über Kontaktdrähte mit dem innen liegenden Anzündelement 10 verbunden. Diese Ausgestaltung er laubt eine weitestgehend freie Positionierung des innenlie genden Anzündelementes 10. Das innenliegende Anzündelement 1 kann einen Anzündverstärker 5 tragen. Werden erfindungsgemä mindestens zwei innenliegende Verdämmungsplatten 4 einge setzt, so können die Verdämmungsplatten 4 durch Spalten 1 voneinander getrennt sein.The exemplary embodiments according to the invention consequently consist of a sleeve 2, a projectile 11, a secondary combustion chamber 12, a primary combustion chamber 14, an internal ignition element 10 and a base plate 8. The primary combustion chamber 14 contains at least one internal combustible or consumable insulation plate 4 made of a propellant charge powder block with a central bore 15. In the present example, the primary combustion chamber 14 is closed off with a combustible disk 7 towards the secondary combustion chamber 12. This can be useful if the propellant powder block in the secondary combustion chamber 12 consists of propellant powder other than the damper plates 4. The central bore 15 can be tapered towards the rear in a conical or stepped manner. The central bore 15 normally receives the internal ignition element 10, but the internal ignition element 10 can also be provided outside the central bore 15, as long as it is ensured that the ignition propellant powder is first ignited. In order to ensure reliable ignition, the internal ignition element 10 is surrounded, at least in the upper area, by rapidly burning ignition propellant powder 13. In another embodiment, in particular if at least two insulation plates are provided, the central bore 15 is so large that the internal ignition element 10 is surrounded by rapidly burning ignition propellant powder 13. In a further embodiment, the at least one internal damper plate 4 is additionally surrounded towards the sleeve 2 by rapidly burning ignition propellant powder 13. The bottom of the primary Brennräumes 14 can be completed with a ausgebil Deten insulation plate as a base plate 3. This base plate 3 has a blind bore 19 with at least the diameter of the central bore 15. Depending on the choice of the internal ignition element 10, bushings 20 for contacts 21 can be provided in the base plate 3. The so-called inductive ignition is preferably used. For this purpose, the secondary coil of the inductive ignition is located at the rear of the cartridge. The secondary coil is connected to the internal ignition element 10 via contact wires. This embodiment allows a largely free positioning of the interior ignition element 10. The internal ignition element 1 can carry an ignition amplifier 5. If at least two internal insulation panels 4 are inserted according to the invention, the insulation panels 4 can be separated from one another by columns 1.
Eine weitere Ausführung der vorliegenden Erfindung sieh Teil- oder Vollteleskop-Patronen vor, bei denen sich an de Sekundärverbrennungsraum 12 ein weiterer Verbrennungs /Geschoßraum 1 anschließt, der ebenfalls von der Hülse 2 um geben ist. Dieser Geschoßraum 1 nimmt das Geschoß 11 auf un enthält zur besseren Stütze und Führung des Geschosses 1 einen Geschoßhalter 18, der vorzugsweise der Form des Ge schosses 11 angepaßt ist. Der Verbrennungs-/Geschoßraum wird durch eine, das Geschoß 11 zentrierende Kappe verschlos sen.A further embodiment of the present invention provides partial or full telescope cartridges in which a further combustion / storey space 1 adjoins the secondary combustion space 12, which is also provided by the sleeve 2. This floor space 1 takes the floor 11 on un contains for better support and management of the floor 1 a floor holder 18, which is preferably adapted to the shape of the Ge floor 11. The combustion / storey space is closed by a cap 11 that centers the storey.
Die Hülse wie auch die Bodenscheibe können aus für dies Zwecke an sich bekannten Materialien bestehen. Vorzugsweis besteht die Hülse 2 und/oder die Bodenscheibe 8 aus verbrenn barem Material, vorzugsweise auf Nitrocellulose (NC) -Basis Die Hülse 2 ist besonders bevorzugt eine Nitrocellulose Wickelhülse. Als Treibladungen können die an sich bekannte konventionellen Treibladungspulver, beispielsweise solche au NC-Basis eingesetzt werden. So kann die mindestens eine in nenliegende Verdämmungsplatte 4 aus einem 1-basigen poröse Nitrocelluloseblock, das schnell abbrennende Anzündtreibla¬ dungspulver 13 beispielsweise aus 2-basigem Treibladungspul¬ ver, die Haupttreibladung 17 aus mehrbasigem Treibladungspul¬ ver bestehen. Statt dieser konventionellen Treibladungspulver können auch hochtemperaturbeständige Treibladungspulverele¬ mente, wie sie an sich bekannt sind, eingesetzt werden. Hier sind beispielsweise die Treibladungspulverelemente auf Nitra- minbasis, wie z.B. kunststoffgebundenes Hexogen oder Octogen, zu nennen.The sleeve as well as the base plate can consist of materials known per se for this purpose. Preferably, the sleeve 2 and / or the base plate 8 consists of combustible material, preferably based on nitrocellulose (NC). The sleeve 2 is particularly preferably a nitrocellulose winding tube. The conventional propellant powders known per se, for example those based on NC, can be used as propellant charges. For example, the at least one internal insulation plate 4 made of a 1-based porous Nitrocellulose block, the rapidly burning ignition propellant powder 13, for example, consists of 2-base propellant powder, the main propellant 17 consist of multi-base propellant powder. Instead of these conventional propellant powders, high-temperature-resistant propellant powder elements, as are known per se, can also be used. The nitroamine-based propellant powder elements, such as plastic-bound hexogen or octogen, may be mentioned here, for example.
Der Geschoßhalter 18 kann beispielsweise aus üblichem Rake- tenfesttreibstoff bestehen. Aber auch hier lassen sich die hochtemperaturbeständigen Treibstoffe einsetzen. Damit trägt der Geschoßhalter 18, wenn er nach dem Durchbrennen der Scheibe 6 durch die Haupttreibladung 17 angezündet worden ist, zur Beschleunigung des Geschosses 11 bei.The projectile holder 18 can consist, for example, of conventional rocket solid fuel. But the high-temperature resistant fuels can also be used here. Thus, the projectile holder 18, when it has been ignited after the disk 6 has been burned by the main propellant charge 17, contributes to the acceleration of the projectile 11.
Verwendet werden können die erfindungsgemäßen Patronen bei¬ spielsweise in Maschinenkanonen mit normaler Kadenz und einem Kaliber von 20 bis 50 mm. The cartridges according to the invention can be used, for example, in machine guns with normal cadence and a caliber of 20 to 50 mm.

Claims

Patentansprüche: Claims:
1. Patrone, dadurch gekennzeichnet, daß sie aus einem Primärve brennungsraum (14) für die Anzündtreibladung, einem innenlie genden Anzündelement (10) für die Anzündtreibladung, aus mi destens einer Verdämmungsplatte (4) aus Treibladungspulve die die Anzündtreibladung umgibt und einem Geschoß (11) be steht.1. Cartridge, characterized in that it consists of a primary combustion chamber (14) for the propellant charge, an inner-lying igniter (10) for the propellant charge, from mi least a damper plate (4) made from propellant charge powder which surrounds the propellant charge and a projectile (11 ) consists.
2.Second
Patrone nach Anspruch 1, dadurch gekennzeichnet, daß das i nenliegende Anzündelement (10) von schnell abbrennendem A zündtreibladungspulver (13) umgeben ist.Cartridge according to claim 1, characterized in that the igniting element (10) lying in the interior is surrounded by rapidly burning A propellant charge powder (13).
3.Third
Patrone nach einem der Ansprüche 1 und 2, dadurch gekenn zeichnet, daß sie zwischen dem Primärverbrennungsraum (14 und dem Geschoß (11) zusätzlich einen Sekundärverbrennungs raum (12) für Treibladungspulver aufweist.Cartridge according to one of claims 1 and 2, characterized in that it additionally has a secondary combustion chamber (12) for propellant powder between the primary combustion chamber (14 and the projectile (11)).
4.4th
Patrone nach einem der Ansprüche 1 bis 3, dadurch gekenn zeichnet, daß der Primärverbrennungsraum (14) zum Sekundär verbrennungsraum (12) mit einer verbrennbaren Scheibe (7) ab geschlossen ist.Cartridge according to one of claims 1 to 3, characterized in that the primary combustion chamber (14) is closed to the secondary combustion chamber (12) with a combustible disc (7).
5. Patrone nach einem der Ansprüche 1 bis 4, dadurch gekenn zeichnet, daß sie eine Hülse (2) aufweist und die innenlie gende Verdämmungsplatte (4) zur Hülse (2) hin von schnel abbrennendem Anzündtreibladungspulver (13) umgeben ist. 5. Cartridge according to one of claims 1 to 4, characterized in that it has a sleeve (2) and the interior lying insulation plate (4) to the sleeve (2) is surrounded by quick-burning ignition propellant powder (13).
6.6th
Patrone nach einem der Ansprüche 1 bis 5, dadurch gekenn¬ zeichnet, daß das innenliegende Anzündelement (10) einen An¬ zündverstärker (5) trägt.Cartridge according to one of Claims 1 to 5, characterized in that the internal ignition element (10) carries an ignition amplifier (5).
7.7.
Patrone nach einem der Ansprüche 1 bis 6, dadurch gekenn¬ zeichnet, daß der Primärverbrennungsraum (14) mindestens zwei innenliegende Verdämmungsplatten (4) enthält, die durch Spalten (16) voneinander getrennt sind.Cartridge according to one of claims 1 to 6, characterized gekenn¬ characterized in that the primary combustion chamber (14) contains at least two internal insulation plates (4) which are separated from one another by columns (16).
8.8th.
Patrone nach einem der Ansprüche 1 bis 7, dadurch gekenn¬ zeichnet, daß der Primärverbrennungsraum (14) mit einer Bo- denplatte (3) verschlossen ist.Cartridge according to one of claims 1 to 7, characterized in that the primary combustion chamber (14) is closed with a base plate (3).
9.9th
Patrone nach einem der Ansprüche 1 bis 8, dadurch gekenn¬ zeichnet, daß die Hülse (2) verbrennbar ist.Cartridge according to one of claims 1 to 8, characterized gekenn¬ characterized in that the sleeve (2) is combustible.
10.10th
Patrone nach einem der Ansprüche 1 bis 9, dadurch gekenn¬ zeichnet, daß sich an den Sekundärverbrennungsraum (12) ein Verbrennungs-/Geschoßraum (1) anschließt.Cartridge according to one of Claims 1 to 9, characterized in that a combustion / storey space (1) connects to the secondary combustion space (12).
11.11th
Patrone nach Anspruch 10, dadurch gekennzeichnet, daß der Verbrennungs-/Geschoßraum (1) einen Geschoßhalter (18) ent¬ hält, der der äußeren Form des Geschosses (l) angepaßt ist.Cartridge according to claim 10, characterized in that the combustion / projectile space (1) contains a projectile holder (18) which is adapted to the external shape of the projectile (1).
12.12th
Patrone nach einem der Ansprüche 10 oder 11, dadurch gekenn¬ zeichnet, daß der Geschoßraum (l) durch eine Verschlußkappe (9) verschlossen ist. Cartridge according to one of claims 10 or 11, characterized gekenn¬ characterized in that the floor space (l) is closed by a closure cap (9).
13.13th
Patrone nach einem der Ansprüche 1 bis 12, dadurch geken zeichnet, daß die Hülse (2) eine Nitrocellulose-Wickelhüls ist.Cartridge according to one of claims 1 to 12, characterized in that the sleeve (2) is a nitrocellulose winding sleeve.
14.14th
Patrone nach einem der Ansprüche 1 bis 13, dadurch gekenn zeichnet, daß die mindestens eine innenliegende Verdämmungs platte (4) aus einem 1-basigen porösen Nitrocellulosebloc besteht.Cartridge according to one of claims 1 to 13, characterized in that the at least one internal insulation plate (4) consists of a 1-based porous nitrocellulose block.
15.15th
Patrone nach einem der Ansprüche 1 bis 14, dadurch gekenn zeichnet, daß das schnell abbrennende Anzündtreibladungspul ver (13) mehrbasiges, vorzugsweise 2-basiges Treibladungspul ver ist.Cartridge according to one of claims 1 to 14, characterized in that the fast-burning ignition propellant powder ver (13) is a multi-base, preferably 2-base propellant charge powder.
16.16th
Patrone nach einem der Ansprüche 1 bis 15, dadurch gekenn zeichnet, daß der Sekundärverbrennungsraum (12) mehrbasige Treibladungspulver enthält.Cartridge according to one of claims 1 to 15, characterized in that the secondary combustion chamber (12) contains multi-base propellant powder.
17.17th
Patrone nach einem der Ansprüche l bis 16, dadurch gekenn zeichnet, daß der Geschoßhalter (18) aus Raketentreibstof besteht.Cartridge according to one of claims 1 to 16, characterized in that the projectile holder (18) consists of rocket fuel.
18.18th
Patrone nach einem der Ansprüche 1 bis 17, dadurch gekenn zeichnet, daß die mindestens eine innenliegende Verdämmungs platte (4) und/oder das Treibladungspulver im Sekundärver brennungsraum (12) und/oder der Geschoßhalter (18) au Treibladungspulverelementen auf Nitraminbasis besteht. Cartridge according to one of claims 1 to 17, characterized in that the at least one internal insulation plate (4) and / or the propellant charge powder in the secondary combustion chamber (12) and / or the projectile holder (18) consists of propellant charge powder elements based on nitramine.
EP95941062A 1994-12-01 1995-11-30 Cartridge Withdrawn EP0795114A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE4442811 1994-12-01
DE4442811 1994-12-01
PCT/EP1995/004721 WO1996017220A1 (en) 1994-12-01 1995-11-30 Cartridge

Publications (1)

Publication Number Publication Date
EP0795114A1 true EP0795114A1 (en) 1997-09-17

Family

ID=6534659

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95941062A Withdrawn EP0795114A1 (en) 1994-12-01 1995-11-30 Cartridge

Country Status (3)

Country Link
EP (1) EP0795114A1 (en)
DE (1) DE19544560A1 (en)
WO (1) WO1996017220A1 (en)

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Publication number Priority date Publication date Assignee Title
CN106767196A (en) * 2016-12-29 2017-05-31 刘东才 Hollow body caseless cartridge and its transmitting gun barrel

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Publication number Priority date Publication date Assignee Title
WO2001048436A1 (en) 1999-12-24 2001-07-05 Dynamit Nobel Gmbh Explosivstoff- Und Systemtechnik Cartridge case for rifle cartridges
DE10027012A1 (en) * 1999-12-24 2001-06-28 Dynamit Nobel Ag Cartridge case made of metal or plastic used as advertising support and/or receptacle has metallic galvanized layer
DE10013686B4 (en) * 2000-03-21 2009-11-26 Ruag Ammotec Gmbh Telescopic cartridge with burnable or consumable sleeve
FR2840399B1 (en) 2002-04-16 2005-01-21 Philippe Courty AUTOMATIC INDIVIDUAL WEAPON WITH ELECTRONIC MANAGEMENT AND AMMUNITION WITHOUT CASE
FR2838510B1 (en) 2002-04-16 2004-06-25 Philippe Courty INDIVIDUAL AUTOMATIC WEAPON WITH ELECTRONIC MANAGEMENT AND NON-CASE AMMUNITION

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US3336871A (en) * 1965-09-21 1967-08-22 Joseph B Quinlan Traveling ignition charge
US3575112A (en) * 1968-09-30 1971-04-13 Hercules Inc Segmented propellant charge for telescoped caseless ammunition
CA933801A (en) * 1969-04-23 1973-09-18 Brunswick Corporation Gun shell
US3613587A (en) * 1970-02-24 1971-10-19 Hercules Inc Projectile retention system for caseless ammunition
DE2852172A1 (en) * 1978-12-02 1990-06-13 Dynamit Nobel Ag Ignition chain for propellant surrounding caseless ammunition round - consisting of loose powder compacting during component insertion
DE3610424C1 (en) * 1986-03-27 1987-09-10 Dynamit Nobel Ag Self-supporting propellant body and compact charge made from it
DE4207629A1 (en) * 1992-03-10 1993-09-16 Dynamit Nobel Ag METHOD AND DEVICE FOR CLOSING SLEEVELESS AMMUNITION

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106767196A (en) * 2016-12-29 2017-05-31 刘东才 Hollow body caseless cartridge and its transmitting gun barrel

Also Published As

Publication number Publication date
WO1996017220A1 (en) 1996-06-06
DE19544560A1 (en) 1996-06-05

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