EP0137958B1 - Propulsive charge and method for manufacturing - Google Patents

Propulsive charge and method for manufacturing Download PDF

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Publication number
EP0137958B1
EP0137958B1 EP84109753A EP84109753A EP0137958B1 EP 0137958 B1 EP0137958 B1 EP 0137958B1 EP 84109753 A EP84109753 A EP 84109753A EP 84109753 A EP84109753 A EP 84109753A EP 0137958 B1 EP0137958 B1 EP 0137958B1
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EP
European Patent Office
Prior art keywords
propulsive charge
propellant charge
accordance
propulsive
charge
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EP84109753A
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German (de)
French (fr)
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EP0137958A2 (en
EP0137958B2 (en
EP0137958A3 (en
Inventor
Georg Dipl.-Phys. Klein
Eckhard Dipl.-Phys. Rahnenführer
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Rheinmetall Industrie AG
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Rheinmetall GmbH
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    • CCHEMISTRY; METALLURGY
    • C06EXPLOSIVES; MATCHES
    • C06BEXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B21/00Apparatus or methods for working-up explosives, e.g. forming, cutting, drying
    • C06B21/0033Shaping the mixture
    • C06B21/0041Shaping the mixture by compression
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42AMMUNITION; BLASTING
    • F42BEXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B5/00Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02Cartridges, i.e. cases with charge and missile
    • F42B5/16Cartridges, 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 a propellant charge according to claims 1, 2 and 3 and a method for their production.
  • DE - A 3 205152 may be mentioned as an example of this. It relates to a propellant charge for case ammunition and a method for its production, by means of which the capacity is to be increased compared to the known propellant charges, without at the same time resulting in increased workload and human risk from solvent vapors, as is the case with the propellant charge according to GB-A 1 415284 the case is.
  • the propellant charge powder bodies are compressed in the propellant charge sleeve by applying external pressure and without the addition of binding agents and / or solvents to a charge density of between 1.0 and 1.5 g / cm 3 and are elastic to plastic with an almost uniform or gradually different compression deformed, partial quantities with the same or different pressures being compressed in sections uniformly or gradually differently in the propellant charge sleeve.
  • the measures described there are aimed, in particular, at increasing the mass to be accommodated in a given propellant charge sleeve by compressing the entire propellant charge, possibly in partial quantities.
  • the take-off gas pressure as the one with which a new weapon barrel is loaded one or more times to check its safety. This gas pressure is close to the design gas pressure, mostly a little below it;
  • the object of the invention and its solution is directed to a propellant charge with a structure by means of which the increase in the maximum gas pressure occurring during the shot development can be influenced with increasing temperature until it is eliminated in the upper operating temperature range.
  • the starting point is a propellant charge powder for which a p, T curve according to the above-mentioned diagram exists in the case of loose bulk and without binding agent and / or solvent, and in a first example from a corresponding total mass N of the propellant charge.
  • a first portion of preferably about 50 to 80% is at least partially compressed. This will be discussed in more detail later.
  • the above-mentioned pressure increase can advantageously be influenced with increasing temperature until it is eliminated.
  • the increase in performance consists in the possible firing of a weapon tubes, which is designed for a certain maximum gas pressure, with a propellant charge that would no longer be permitted if the propellant powder was poured loose due to the steep rise in the p, T curve at higher operating temperatures.
  • the effective area of a press ram for compression can correspond to the clear internal cross section of the propellant charge sleeve, and the first portion can be compressed overall.
  • the propellant charge according to the invention of an at least partially combustible propellant charge sleeve is to be incorporated - this can be the case with ammunition in the caliber range below 20 mm to over 120 mm - it is advisable to compress the first portion in a comparatively smooth-walled device for which the pressure load when compressing the first share is designed. From this device, the compressed - possibly, as in the case of the bottle sleeve, only partially compressed - first part can be transferred into the aforementioned propellant charge sleeve by axial pressing. In order to avoid disadvantageous wall friction, a thin-walled tube can be arranged in the propellant charge sleeve before being transferred and then removed again.
  • a curve Sp N illustrates the behavior of a propellant charge from a propellant charge loosely poured into a propellant charge sleeve.
  • the curve in question shows that in the upper service temperature range a horizontal limit G1, which indicates the mean maximum permissible gas pressure for a first weapon barrel, is exceeded by the curve Sp n in the steep slope (dashed part). The propellant charge is therefore unsuitable for the relevant temperature range.
  • a curve S YN is entered in FIG. 1b for the loose propellant charge.
  • a curve Ep N in Fig. 1a shows the behavior of a propellant according to the invention, the mass N of which corresponds to that of the loosely poured propellant.
  • the curve Ep N remains flat under the limit G1: the method according to the invention consequently assumes the propellant charge has the same mass N - in both cases it is assumed that the propellant sleeve is the same - the suitability of the propellant charge for the weapon barrel in question achieved upper operating temperature range. This results in an increase in performance in the expanded sense mentioned at the beginning.
  • FIGS. 2a and 2b each again show two curves, namely S PN and E pM as well as S vn and E vM .
  • Fig. 2a is for a second weapon barrel, which is more resilient than the first gun barrel mentioned in connection with Figs. 1a and 1b.
  • a horizontal limit G2 is consequently associated with a higher pressure than the limit G1 in FIG. 1a.
  • the corresponding curves Sp N and S YN correspond to those from FIGS. 1a a and 1b, ie there is the same propellant charge of mass N in bulk.
  • the two corresponding curves Ep M and E YM characterize the behavior of a propellant charge according to the invention, the mass M of which is greater than that of the propellant charge of bulk (mass N) known from FIGS. 1a and 1b.
  • FIGS. 1a and 1b are again based on the same propellant charge sleeve and the same propellant charge powder.
  • the propellant charge in bulk is now usable, but from the course of the curves Ep M and E VM for the propellant charge according to the invention, the increase in interior ballistic performance in the conventional sense mentioned above compared to the propellant charge in bulk is clearly recognizable.
  • a modified but similar course of the curves Ep M and E VM can be achieved when using different propellant powders.
  • FIG. 3 shows a device V1 for carrying out the method according to the invention in a bottle-shaped propellant charge sleeve 10 with a sleeve wall 11 and a sleeve base 12.
  • a threaded bore 14 is provided in the sleeve base 12 for a propellant charge lighter.
  • the propellant charge sleeve 10 ends on the upper side in a sleeve neck 16.
  • the device V1 consists of a thick-walled circular cylindrical tube 18 with an inner flange 19 on the upper side.
  • a base piece 20 engages in the tube 18 on the underside and, in addition to a central axial receiving bore 22, has horizontal locking bores 21. The latter correspond to locking bores 18 ' in the tube 18.
  • the propellant charge sleeve 10 is received on the bottom side in the base piece 20, with fixing means 23 engaging through the bores 18' and 21 in an extraction groove 24 on the sleeve bottom side.
  • the propellant charge sleeve 10 has first been inserted with the base piece 20 in the direction of an arrow 54 into the tube 18, aligned with the central longitudinal axis A.
  • the sleeve neck 16 is located in the area of a coaxial circular opening 26 in the inner flange 19.
  • a funnel 28 is placed on an unspecified upper surface of the inner flange 19 and is surrounded by two spacer rings 30 and 32 in the case shown.
  • a circular cylindrical press die 34 with a press surface 38 on the underside has a fixing groove 36 in the upper free end. With the latter, the press die 34 is received in a holder 40 with radial bores 42. Only indicated fixing means 43 in the bores 42 engage in the groove 36 and fix the press ram 34 in the holder 40.
  • a first portion of a propellant charge is poured in the form of loose bulk powder through the funnel 28. This first portion is about 50 to about 80% of the total mass of the propellant to be incorporated.
  • the holder 40 is moved in the direction of an arrow 52 with the press ram 34 fixed therein, with a prescribable pressure being applied.
  • the pressing surface 38 comes into contact with a surface of the bed, not shown, and a part 46 of the first portion 44 is compressed. Since the outside diameter of the plunger 34 is smaller than the inside diameter of the propellant charge sleeve 10 in the region of its wall 11, an annular cylindrical cavity 48 remains, in which a small amount 50 of uncompressed propellant charge powder remains.
  • the compression of the part 46 of the first portion 4 is completed as soon as a lower annular surface 41 of the holder 40 touches an upper annular surface 32 of the upper spacer ring 32.
  • the holder 40 is moved with the press ram 34 in the direction of an arrow 54 until the funnel 28 is released. A second portion of the propellant charge remaining as the remainder is then loosely poured onto the first portion 44.
  • a dummy body 15 is arranged in the threaded bore 14 for the propellant charge lighter and in the receiving bore 22 of the base piece 20.
  • the part of the dummy body 15 protruding into the interior of the propellant charge sleeve 10, which is not described in more detail, is essentially the same dimension as the propellant charge lighter. Therefore, after removing the dummy body 15, the propellant charge lighter can easily be inserted into a channel 15 ' , which remains in the compressed part after removing the dummy body 15.
  • FIG. 4 shows a device V2 with a circular cylindrical tube 60 of sufficient wall thickness, in which a bottom piece 62 is inserted on the underside.
  • the latter has a central axial threaded bore 64 for receiving a dummy body 66.
  • a press ram 68 the outside diameter of which corresponds to the inside diameter of the tube 60, has a pressing surface 70 on the underside and an actuating rod 72 on the rear.
  • a central axial bore 72 ′ creates an interior space 73 that extends into a free upper end 75 of the rod 72. Vent holes 74 'connect the interior 73 with the surrounding atmosphere.
  • Radial bores 79 are provided in a holder 76.
  • Bolt-shaped fixing means 68 grip through this and fix the pressing die 68 with its rod 72 in the holder 76 via recesses 75 '.
  • a spacer ring 80 has a central opening 80 ′ which is adapted to the outside diameter of the rod 72.
  • the spacer ring 80 lies with a flat underside surface 81 ′ on an upper-side flat circular ring surface 61 of the tube 60.
  • the spacer ring 80 After the spacer ring 80 has been pushed over, it is fixed in the holder 76 and moved in the direction of an arrow 82 along a central longitudinal axis A while applying pressure against the loose powder filling of the first portion of the propellant charge.
  • the dummy body 66 projecting over a top surface 63 of the base piece 62 corresponds essentially to the dimensions of a propellant charge lighter.
  • the ram 68 moves downward, its free end 67 gets into the bore 72 ', the air being able to escape from the interior 73 through the ventilation bores 74'.
  • the first portion 86 of the propellant charge is compressed as soon as the receptacle 76 with its circle on the underside ring surface 77 touches the top surface 81 of the spacer ring 80.
  • the propellant charge is to be incorporated in a circular cylindrical inner cross section, not shown, of a metallic propellant charge sleeve, this can be provided with the dummy body 66, in which the inner diameter of the propellant charge sleeve tube 60 is inserted from below from below; in this case, the outside diameter of the press ram 68 must be adapted to the inside diameter of the metallic propellant charge sleeve, not shown.
  • the propellant charge sleeve 90 has a base 94, for example made of metal, with a central axial threaded bore 96 for a propellant charge lighter 98.
  • a combustible part 100 of the propellant charge sleeve 90 is fixedly connected to the bottom 94.
  • the first portion 86 of the propellant charge solidified in the device V2 according to FIG. 4 is now to be transferred into an interior space 97 of the propellant charge sleeve 90.
  • a metal sleeve 102 which is adapted to the inside diameter of the combustible part 100 and is shown in the drawing as excessively thick-walled for clarification, is introduced into the interior 97.
  • the arrangement according to FIG. 5 is fixed under the device V2 in alignment with the axis.
  • the propellant charge lighter 98 gets into a channel 88 formed by the dummy body.
  • the smooth metal sleeve 100 on its top edge 104 becomes one Arrow 108 removed from the propellant charge sleeve 90 again, and the second portion of the propellant charge is applied as loose bulk powder.
  • the press ram 34 has a central axial bore for the longer dummy body and then, if appropriate, also has a ventilation bore as in the device V2 in FIG. 4 must be provided.
  • the spacer rings 30, 32 and 80 are interchangeable, so that the penetration depth of the press ram 34 and 68 can be changed in order to achieve a predetermined compression of the respective first portion 44 and 86 of the propellant charge.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Organic Chemistry (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Containers And Packaging Bodies Having A Special Means To Remove Contents (AREA)
  • Drilling And Exploitation, And Mining Machines And Methods (AREA)
  • Medicinal Preparation (AREA)
  • Photoreceptors In Electrophotography (AREA)
  • Golf Clubs (AREA)
  • Particle Formation And Scattering Control In Inkjet Printers (AREA)

Description

Die Erfindung betrifft eine Treibladung nach den Patentansprüchen 1, 2 und 3 und ein Verfahren zu ihrer Herstellung.The invention relates to a propellant charge according to claims 1, 2 and 3 and a method for their production.

Dem Aufbau von Treibladungen und Verfahren zu deren Herstellung gelten seit langem die Bemühungen der Fachwelt. Hierbei spielt eine wesentliche Rolle eine Steigerung der innenballistischen Leistung zum Erzielen einer höheren Mündungsgeschwindigkeit eines jeweiligen Geschosses. Als Beispiel hierfür sei die DE-A 3 205152 genannt. Sie betrifft eine Treibladung für Hülsenmunition und Verfahren zu ihrer Herstellung, durch welche das Leistungsvermögen gegenüber den bekannten Treibladungen erhöht werden soll, ohne dass dadurch gleichzeitig ein erhöhter Arbeitsaufwand und eine Menschengefährdung aus Lösungsmitteldämpfen entsteht, wie es bei der Treibladung gemäss der GB-A 1 415284 der Fall ist. Die Treibladungspulverkörper sind in der Treibladungshülse durch Anwendung von äusserem Druck und ohne Zusatz von Binde- und/oder Lösungsmitteln bis zu einer Ladedichte zwischen 1,0 und 1,5 g/cm3 zusammengepresst und bei einer nahezu gleichmässigen oder graduell verschiedenen Verdichtung elastisch bis plastisch verformt, wobei Teilmengen mit gleichen oder zueinander unterschiedlichen Drücken abschnittsweise gleichmässig oder graduell verschieden in der Treibladungshülse verdichtet sind.The construction of propellant charges and processes for their production have long been the efforts of experts. An important role here is an increase in interior ballistic performance in order to achieve a higher muzzle velocity for each projectile. DE - A 3 205152 may be mentioned as an example of this. It relates to a propellant charge for case ammunition and a method for its production, by means of which the capacity is to be increased compared to the known propellant charges, without at the same time resulting in increased workload and human risk from solvent vapors, as is the case with the propellant charge according to GB-A 1 415284 the case is. The propellant charge powder bodies are compressed in the propellant charge sleeve by applying external pressure and without the addition of binding agents and / or solvents to a charge density of between 1.0 and 1.5 g / cm 3 and are elastic to plastic with an almost uniform or gradually different compression deformed, partial quantities with the same or different pressures being compressed in sections uniformly or gradually differently in the propellant charge sleeve.

Die dort beschriebenen Massnahmen sind samt und sonders darauf gerichtet, durch ein Verdichten der gesamten Treibladung, ggf. in Teilmengen, deren in einer vorgegebenen Treibladungshülse unterzubringende Masse zu vergrössern.The measures described there are aimed, in particular, at increasing the mass to be accommodated in a given propellant charge sleeve by compressing the entire propellant charge, possibly in partial quantities.

Obwohl nach dem bekannten Verfahren durch Verzicht auf Binde- und/oder Lösungsmittel die hieraus möglicherweise resultierenden schädlichen Einwirkungen auf das mit der Herstellung befasste Personal vermindert werden sollen, erweisen sich die angegebenen Verfahrensarten in mehrfacher Hinsicht als nachteilig. Nach dem Verdichten müssen Vorkehrungen getroffen werden, einen freien Pressrand bzw. die Treibladungsoberfläche der komprimierten Treibladungspulverkörper gegen Ausbröckeln und/oder Aufwerfen des Pressspiegels durch eine gesonderte Abdeckung zu stabilisieren. Bei mehreren erforderlichen Verdichtungsschritten muss die betreffende Treibladungshülse nach jedem Einfüllen des losen Treibladungspulvers aus Sicherheitsgründen in einen besonderen Raum zum Verdichten gebracht werden.Although the known method is intended to reduce the possible harmful effects on the personnel involved in the production by dispensing with binding agents and / or solvents, the types of processes indicated prove to be disadvantageous in several respects. After compaction, precautions must be taken to stabilize a free press rim or the propellant charge surface of the compressed propellant charge powder bodies against crumbling and / or throwing up the press level by a separate cover. If several compaction steps are required, the propellant case in question must be brought into a special room for compaction after each filling of the loose propellant powder for safety reasons.

Im Zusammenhang mit der vorliegenden Erfindung wird ein erweiterter Begriff der innenballistischen Leistungssteigerung eingeführt. Hierauf wird noch näher eingegangen.In connection with the present invention, an expanded concept of interior ballistic performance enhancement is introduced. This will be discussed in more detail.

Bei Waffenrohren werden unterschieden:A distinction is made between gun barrels:

Der Konstruktionsgasdruck als derjenige theoretische Gasdruck, bei dem eine schädliche bleibende Formänderung des Waffenrohres gerade noch vermieden wird;The construction gas pressure as the theoretical gas pressure at which a harmful permanent change in shape of the weapon barrel is just avoided;

der Abnahmegasdruck als derjenige, mit dem ein neues Waffenrohr ein- oder mehrmals belastet wird, um seine Sicherheit zu überprüfen. Dieser Gasdruck liegt nahe dem Konstruktionsgasdruck, meistens ein wenig darunter;the take-off gas pressure as the one with which a new weapon barrel is loaded one or more times to check its safety. This gas pressure is close to the design gas pressure, mostly a little below it;

der maximal zulässige Gasdruck, der ausser bei der Abnahme auch unter ungünstigen Bedingungen nicht überschritten werden darf;the maximum permissible gas pressure, which must not be exceeded under adverse conditions, except during the acceptance test;

der mittlere Gasdruck bei 50°C Pulvertemperatur, der unter dem maximal zulässigen Gasdruck liegt undthe mean gas pressure at 50 ° C powder temperature, which is below the maximum permissible gas pressure and

der mittlere maximale Gasdruck bei 21°C Pulvertemperatur (Gebrauchsgasdruck), der unter mitteleuropäischen Verhältnissen als Bezugswert für die Verschleisslebensdauer der Geschützrohre verwendet werden sollte.the average maximum gas pressure at 21 ° C powder temperature (service gas pressure), which should be used as a reference value for the wear life of the gun barrels under Central European conditions.

Zur weiteren Erläuterung wird nachstehend auf zwei Diagramme (Fig. 1 und b) verwiesen, aus denen für eine lose geschüttete Treibladung der Einfluss der Gebrauchstemperatur auf die Mündungsgeschwindigkeit einerseits und den mittleren maximalen Gasdruck, Pm andererseits zu erkennen ist. Dabei wird von einem Treibladungspulver ausgegangen, das im unteren Gebrauchstemperaturbereich keine schädliche Druckanomalie, beispielsweise in Form gefürchteter Druckspitzen, aufweist.For further explanation, reference is made below to two diagrams (FIGS. 1 and b), from which the influence of the use temperature on the muzzle velocity on the one hand and the mean maximum gas pressure, P m on the other hand, can be seen for a loosely poured propellant charge. A propellant charge powder is assumed which has no harmful pressure anomaly in the lower operating temperature range, for example in the form of dreaded pressure peaks.

Eine wesentliche aus den Diagrammen ersichtliche Tatsache ist der mit der Gebrauchstemperatur zunehmende Gasdruck, mit dem eine zunehmende Mündungsgeschwindigkeit einhergeht: die p,T-Kurvelässt mit ihrem steilen Anstieg gegen den maximal zulässigen Gasdruck eine durch letzteren gegebene empfindliche Grenze erkennen.An essential fact that can be seen from the diagrams is the gas pressure increasing with the use temperature, which is accompanied by an increasing muzzle velocity: the p, T curve, with its steep rise against the maximum permissible gas pressure, recognizes a sensitive limit given by the latter.

Die Erfindung ist nach Aufgabe und deren Lösung auf eine Treibladung mit einem Aufbau gerichtet, durch den im oberen Gebrauchstemperaturbereich der Anstieg des während der Schussentwicklung auftretenden maximalen Gasdrucks mit zunehmender Temperatur bis zur Eliminierung beeinflussbar ist.The object of the invention and its solution is directed to a propellant charge with a structure by means of which the increase in the maximum gas pressure occurring during the shot development can be influenced with increasing temperature until it is eliminated in the upper operating temperature range.

Dabei zeichnet sich ein erfinderisches Verfahren zum Herstellen der betreffenden Treibladung durch eine erstaunliche Einfachheit aus. Dies wird nachstehend erläutert und lässt die mehrfachen Vorteile erkennen, die aus der Erfindung resultieren.An inventive method for producing the propellant charge in question is characterized by astonishing simplicity. This is explained below and reveals the multiple advantages that result from the invention.

Ausgegangen wird von einem Treibladungspulver, für das bei loser Schüttung und ohne Binde- und/oder Lösungsmittel eine p,T-Kurve nach dem vorstehend genannten Diagramm existiert und bei einem ersten Beispiel von einer entsprechenden Gesamtmasse N der Treibladung. Von der Gesamtmasse N wird nun ein erster Anteil von vorzugsweise jeweils etwa 50 bis 80% wenigstens teilverdichtet. Hierauf wird noch näher eingegangen werden. Bei einer Treibladung nach der Erfindung, bei der ein zweiter Anteil als Rest der Gesamtmasse N lose auf den ersten Anteil aufgeschüttet wird, lässt sich der vorerwähnte Druckanstieg mit zunehmender Temperatur vorteilhafterweise bis zur Eliminierung beeinflussen. Im vorliegenden Fall besteht die Leistungssteigerung in dem möglichen Beschuss eines Waffenrohres, das für einen bestimmten maximalen Gasdruck ausgelegt ist, mit einer Treibladung, die bei loser Schüttung des Treibladungspulver infolge des steilen Anstiegs der p,T-Kurve bei höheren Gebrauchstemperaturen nicht mehr zulässig wäre.The starting point is a propellant charge powder for which a p, T curve according to the above-mentioned diagram exists in the case of loose bulk and without binding agent and / or solvent, and in a first example from a corresponding total mass N of the propellant charge. Of the total mass N, a first portion of preferably about 50 to 80% is at least partially compressed. This will be discussed in more detail later. In the case of a propellant charge according to the invention, in which a second portion as the remainder of the total mass N is loosely poured onto the first portion, the above-mentioned pressure increase can advantageously be influenced with increasing temperature until it is eliminated. In the present case, the increase in performance consists in the possible firing of a weapon tubes, which is designed for a certain maximum gas pressure, with a propellant charge that would no longer be permitted if the propellant powder was poured loose due to the steep rise in the p, T curve at higher operating temperatures.

Steht nun ein Waffenrohr mit einem höheren maximal zulässigen Gasdruck zur Verfügung, dann kann bei einem zweiten Beispiel von einer Gesamtmasse M>N ausgegangen werden. Wird dann wieder auf die vorbeschriebene Weise verfahren, wird bei einem Druck p<pmaxzul eine innenballistische Leistungssteigerung erzielt: Aus den Diagrammen (Fig.2a und b) wird nämlich deutlich, dass der Einfluss der Gebrauchstemperatur beim Übergang von 21 °C auf 52°C eliminiert ist. Beim ersten Beispiel ist die Leistungssteigerung durch eine verbesserte Lebensdauer des Waffenrohres und beim zweiten Beispiel durch eine höhere Mündungsgeschwindigkeit des Geschosses gegeben. Hieraus wird die eingangs erwähnte Erweiterung des Begriffs der Leistungssteigerung im Rahmen der vorliegenden Erfindung deutlich.If a weapon barrel with a higher maximum permissible gas pressure is now available, then a total mass M> N can be assumed in a second example. If the procedure is then again as described above, an internal ballistic performance increase is achieved at a pressure p <p maxzul : from the diagrams (Fig. 2a and b) it is clear that the influence of the operating temperature during the transition from 21 ° C to 52 ° C is eliminated. In the first example, the increase in performance is given by an improved service life of the weapon barrel and in the second example by a higher muzzle velocity of the projectile. From this, the above-mentioned expansion of the concept of increasing performance within the scope of the present invention becomes clear.

Wird das Verfahren unmittelbar in einer Treibladungshülse durchgeführt, dann soll zunächst eine solche mit einem im wesentlichen über ihre gesamte Länge kreiszylindrischen Querschnitt betrachtet werden. Die Wirkfläche eines Pressstempels zum Verdichten kann hierbei dem lichten Innenquerschnitt der Treibladungshülse entsprechen, und der erste Anteil kann insgesamt verdichtet werden.If the method is carried out directly in a propellant charge sleeve, then one with a cross-section that is circular cylindrical essentially over its entire length should first be considered. The effective area of a press ram for compression can correspond to the clear internal cross section of the propellant charge sleeve, and the first portion can be compressed overall.

Bei einer Treibladungshülse mit einem vergleichsweise kleineren lichten Innenquerschnitt eines Hülsenmundes (Flaschenhülse) wurde ein dem letzteren angepasster Pressstempel verwendet. Hierbei lässt sich nicht vermeiden, dass sich lose Treibladungskörper in einem Kreisringspalt zwischen der Umfangsfläche des Pressstempels und der Innenwandfläche der Treibladungshülse entgegen der Richtung des Pressstempels beim Verdichten bewegen. Hieraus resultiert, streng genommen, nur eine teilweise Verdichtung des ersten Anteils. Überraschenderweise wirkt sich dies aber nicht nachteilig aus, und aus dieser Tatsache erhellt die Einfachheit des Verfahrens - auch im Hinblick auf einen nur geringen erforderlichen Vorrichtungsaufwand.In the case of a propellant charge case with a comparatively smaller internal cross section of a case mouth (bottle case), a press stamp adapted to the latter was used. It cannot be avoided here that loose propellant charge bodies move in a circular gap between the circumferential surface of the press ram and the inner wall surface of the propellant charge sleeve against the direction of the press ram during compression. Strictly speaking, this only results in a partial compression of the first portion. Surprisingly, however, this does not have a disadvantage, and from this fact the simplicity of the method is evident - also with regard to the fact that only a small amount of equipment is required.

Soll die Treibladung nach der Erfindung einer wenigstens teilverbrennbaren Treibladungshülse einlaboriert werden - dies kann zutreffen bei Munition im Kaliberbereich unterhalb 20 mm bis über 120 mm hinaus -, empfiehlt sich das Verdichten des ersten Anteils in einer vergleichsweise glattwandigen Vorrichtung, für die die Druckbelastung beim Verdichten des ersten Anteils ausgelegt ist. Aus dieser Vorrichtung lässt sich der verdichtete - ggf. wie im Fall der Flaschenhülse nur teilverdichtete - erste Anteil in die vorgenannte Treibladungshülse durch axiales Ausdrücken überführen. Um hierbei eine nachteilige Wandreibung-zu vermeiden, kann vor dem Überführen in der Treibladungshülse ein dünnwandiges Rohr angeordnet und anschliessend wieder entfernt werden.If the propellant charge according to the invention of an at least partially combustible propellant charge sleeve is to be incorporated - this can be the case with ammunition in the caliber range below 20 mm to over 120 mm - it is advisable to compress the first portion in a comparatively smooth-walled device for which the pressure load when compressing the first share is designed. From this device, the compressed - possibly, as in the case of the bottle sleeve, only partially compressed - first part can be transferred into the aforementioned propellant charge sleeve by axial pressing. In order to avoid disadvantageous wall friction, a thin-walled tube can be arranged in the propellant charge sleeve before being transferred and then removed again.

Die Erfindung wird nachstehend anhand der Zeichnung näher erläutert.The invention is explained below with reference to the drawing.

Es zeigen:

  • Fig. 1a bis 2b jeweils zwei einander zugeordnete Druck-Temperatur- und Geschwindigkeits-Temperatur-Diagramme, ferner jeweils in einem längsaxialen Schnitt.
  • Fig. eine Vorrichtung zum Durchführen des Verfahrens in einer flaschenförmigen Treibladungshülse,
  • Fig.4 eine Vorrichtung zum Durchführen des Verfahrens ausserhalb einer Treibladungshülse und
  • Fig. 5 eine wenigstens teilverbrennbare Treibladungshülse, die zur Aufnahme eines in der Vorrichtung nach Fig. 4 verdichteten Anteils einer Treibladung nach der Erfindung vorbereitet ist.
Show it:
  • Fig. 1a to 2b each two pressure-temperature and velocity-temperature diagrams assigned to each other, further in each case in a longitudinal axial section.
  • 1 shows a device for carrying out the method in a bottle-shaped propellant charge sleeve,
  • 4 shows a device for performing the method outside a propellant charge sleeve and
  • 5 shows an at least partially combustible propellant charge sleeve, which is prepared for receiving a portion of a propellant charge compressed in the device according to FIG. 4 according to the invention.

In Fig. 1 verdeutlicht eine Kurve SpN das Verhalten einer Treibladung aus einem lose in eine Treibladungshülse eingeschütteten Treibladungspulver. Die besagte Kurve lässt erkennen, dass im oberen Gebrauchstemperaturbereich eine waagerechte Begrenzung G1, die für ein erstes Waffenrohr den mittleren maximal zulässigen Gasdruck anzeigt, von der Kurve Spn im Steilanstieg überschritten wird (gestrichelter Teil). Die Treibladung ist folglich für den betreffenden Gebrauchstemperaturbereich ungeeignet. In Fig.1b ist für die lose geschüttete Treibladung eine Kurve SYN eingetragen. Eine Kurve EpN in Fig. 1a lässt das Verhalten einerTreibladung nach der Erfindung erkennen, deren Masse N derjenigen der lose geschütteten Treibladung entspricht. Im oberen Gebrauchstemperaturbereich bleibt die Kurve EpN bei flachem Verlauf unterhalb der Begrenzung G1: Durch das Verfahren nach der Erfindung wird folglich bei gleichbleibender Masse N der Treibladung - ausgegangen wird in beiden Fällen von einer gleichen Treibladungshülse - die Eignung der Treibladung für das erwähnte Waffenrohr im oberen Gebrauchstemperaturbereich erzielt. Hieraus resultiert eine Leistungssteigerung im eingangs erwähnten erweiterten Sinne.1, a curve Sp N illustrates the behavior of a propellant charge from a propellant charge loosely poured into a propellant charge sleeve. The curve in question shows that in the upper service temperature range a horizontal limit G1, which indicates the mean maximum permissible gas pressure for a first weapon barrel, is exceeded by the curve Sp n in the steep slope (dashed part). The propellant charge is therefore unsuitable for the relevant temperature range. A curve S YN is entered in FIG. 1b for the loose propellant charge. A curve Ep N in Fig. 1a shows the behavior of a propellant according to the invention, the mass N of which corresponds to that of the loosely poured propellant. In the upper operating temperature range, the curve Ep N remains flat under the limit G1: the method according to the invention consequently assumes the propellant charge has the same mass N - in both cases it is assumed that the propellant sleeve is the same - the suitability of the propellant charge for the weapon barrel in question achieved upper operating temperature range. This results in an increase in performance in the expanded sense mentioned at the beginning.

In den Diagrammen nach den Fig.2a und 2b sind wiederum jeweils zwei Kurven, nämlich SPN und EpM sowie Svn und EvM, eingezeichnet. In Fig. 2a ist für ein zweites Waffenrohr, das höher belastbar ist als das im Zusammenhang mit den Fig. 1a und 1b erwähnte erste Waffenrohr. Eine waagerechte Begrenzung G2 ist folglich einem höheren Druck zugeordnet als die Begrenzung G1 in Fig. 1a. Die korrespondierenden Kurven SpN und SYN entsprechen denjenigen aus den Fig. 1a a und 1b, d.h. es liegt die nämliche Treibladung der Masse N in loser Schüttung vor. Die beiden korrespondierenden Kurven EpM und EYM charakterisieren das Verhalten einer Treibladung nach der Erfindung, deren Masse M grösser ist als diejenige der aus den Fig. 1a und 1 b bekannten Treibladung loser Schüttung (Masse N). Wie in den Fig. 1a und 1b wird wiederum ausgegangen von einer gleichen Treibladungshülse und dem gleichen Treibladungspulver. Zwar ist die Treibladung loser Schüttung nun verwendbar, aber aus dem Verlauf der Kurven EpM und EVM für die Treibladung nach der Erfindung ist die innenballistische Leistungssteigerung im eingangs erwähnten herkömmlichen Sinne gegenüber der Treibladung loser Schüttung deutlich erkennbar. Ein modifizierter aber ähnlicher Verlauf der Kurven EpM und EVM lässt sich erzielen bei der Verwendung unterschiedlicherTreibladungspulver.The diagrams according to FIGS. 2a and 2b each again show two curves, namely S PN and E pM as well as S vn and E vM . In Fig. 2a is for a second weapon barrel, which is more resilient than the first gun barrel mentioned in connection with Figs. 1a and 1b. A horizontal limit G2 is consequently associated with a higher pressure than the limit G1 in FIG. 1a. The corresponding curves Sp N and S YN correspond to those from FIGS. 1a a and 1b, ie there is the same propellant charge of mass N in bulk. The two corresponding curves Ep M and E YM characterize the behavior of a propellant charge according to the invention, the mass M of which is greater than that of the propellant charge of bulk (mass N) known from FIGS. 1a and 1b. As in the FIGS. 1a and 1b are again based on the same propellant charge sleeve and the same propellant charge powder. The propellant charge in bulk is now usable, but from the course of the curves Ep M and E VM for the propellant charge according to the invention, the increase in interior ballistic performance in the conventional sense mentioned above compared to the propellant charge in bulk is clearly recognizable. A modified but similar course of the curves Ep M and E VM can be achieved when using different propellant powders.

Fig. 3 zeigt eine Vorrichtung V1 zum Durchführen des Verfahrens nach der Erfindung in einer flaschenförmigen Treibladungshülse 10 mit einer Hülsenwand 11 und einem Hülsenboden 12. Im Hülsenboden 12 ist eine Gewindebohrung 14 für einen Treibladungsanzünder vorgesehen. Die Treibladungshülse 10 endet oberseitig in einem Hülsenhals 16. Die Vorrichtung V1 besteht aus einem dickwandigen kreiszylindrischen Rohr 18 mit einem oberseitigen Innenflansch 19. Ein Bodenstück 20 greift unterseitig in das Rohr 18 und weist neben einer zentral axialen Aufnahmebohrung 22 waagerechte Arretierungsbohrungen 21 auf. Letztere korrespondieren mit Arretierungsbohrungen 18' im Rohr 18. Die Treibladungshülse 10 ist bodenseitig im Bodenstück 20 aufgenommen, wobei Fixierungsmittel 23 durch die Bohrungen 18' und 21 in eine hülsenbodenseitige Ausziehrille 24 eingreifen. Hierzu ist die Treibladungshülse 10 mit dem Bodenstück 20 in Richtung eines Pfeils 54 zunächst in das Rohr 18, fluchtend mit der zentralen Längsachse A, eingeschoben worden. Der Hülsenhals 16 befindet sich im Bereich einer koaxialen kreisförmigen Öffnung 26 im Innenflansch 19. Ein Trichter 28 ist auf eine nicht näher bezeichnete Oberseitenfläche des Innenflanschs 19 aufgesetzt und wird im dargestellten Fall von zwei Distanzringen 30 und 32 umgeben. Ein kreiszylindrischer Pressstempel 34 mit einer unterseitigen Pressfläche 38 weist eine Fixierrille 36 im oberen freien Ende auf. Mit letzterem ist der Pressstempel 34 in einer Halterung 40 mit radialen Bohrungen 42 aufgenommen. Nur angedeutete Fixiermittel 43 in den Bohrungen 42 greifen in die Rille 36 ein und legen den Pressstempel 34 in der Halterung 40 fest.FIG. 3 shows a device V1 for carrying out the method according to the invention in a bottle-shaped propellant charge sleeve 10 with a sleeve wall 11 and a sleeve base 12. A threaded bore 14 is provided in the sleeve base 12 for a propellant charge lighter. The propellant charge sleeve 10 ends on the upper side in a sleeve neck 16. The device V1 consists of a thick-walled circular cylindrical tube 18 with an inner flange 19 on the upper side. A base piece 20 engages in the tube 18 on the underside and, in addition to a central axial receiving bore 22, has horizontal locking bores 21. The latter correspond to locking bores 18 ' in the tube 18. The propellant charge sleeve 10 is received on the bottom side in the base piece 20, with fixing means 23 engaging through the bores 18' and 21 in an extraction groove 24 on the sleeve bottom side. For this purpose, the propellant charge sleeve 10 has first been inserted with the base piece 20 in the direction of an arrow 54 into the tube 18, aligned with the central longitudinal axis A. The sleeve neck 16 is located in the area of a coaxial circular opening 26 in the inner flange 19. A funnel 28 is placed on an unspecified upper surface of the inner flange 19 and is surrounded by two spacer rings 30 and 32 in the case shown. A circular cylindrical press die 34 with a press surface 38 on the underside has a fixing groove 36 in the upper free end. With the latter, the press die 34 is received in a holder 40 with radial bores 42. Only indicated fixing means 43 in the bores 42 engage in the groove 36 and fix the press ram 34 in the holder 40.

Durch den Trichter 28 wird ein erster Anteil einer Treibladung in Form losen Schüttpulvers eingefüllt. Dieser erste Anteil beträgt etwa 50 bis etwa 80% der Gesamtmasse der einzulaborierenden Treibladung. Nach dem Einfüllen des ersten Anteils 44 in die Treibladungshülse 10 wird die Halterung 40 mit dem in ihr festgelegten Pressstempel 34 in Richtung eines Pfeils 52 unter Aufbringung eines vorgebbaren Drucks verfahren. Die Pressfläche 38 kommt mit einer nicht dargestellten Oberfläche der Schüttung in Berührung und von dem ersten Anteil 44 wird ein Teil 46 verdichtet. Da der Aussendurchmesser des Pressstempels 34 kleiner ist als der lichte Innendurchmesser der Treibladungshülse 10 im Bereich ihrer Wandung 11, verbleibt ein kreisringzylindrischer Hohlraum 48, in welchem eine geringe Menge 50 unverdichteten Treibladungspulvers verbleibt. Im dargestellten Fall ist die Verdichtung des Teils 46 des ersten Anteils 4 vollzogen, sobald eine untere Kreisringfläche 41 der Halterung 40 eine obere Kreisringfläche 32 des oberen Distanzrings 32 berührt. Nach Druckentlastung wird die Halterung 40 mit dem Pressstempel 34 in Richtung eines Pfeils 54 bis zur Freigabe des Trichters 28 bewegt. Anschliessend wird ein als Rest verbleibender zweiter Anteil der Treibladung lose auf den ersten Anteil 44 aufgeschüttet.A first portion of a propellant charge is poured in the form of loose bulk powder through the funnel 28. This first portion is about 50 to about 80% of the total mass of the propellant to be incorporated. After the first portion 44 has been filled into the propellant charge sleeve 10, the holder 40 is moved in the direction of an arrow 52 with the press ram 34 fixed therein, with a prescribable pressure being applied. The pressing surface 38 comes into contact with a surface of the bed, not shown, and a part 46 of the first portion 44 is compressed. Since the outside diameter of the plunger 34 is smaller than the inside diameter of the propellant charge sleeve 10 in the region of its wall 11, an annular cylindrical cavity 48 remains, in which a small amount 50 of uncompressed propellant charge powder remains. In the illustrated case, the compression of the part 46 of the first portion 4 is completed as soon as a lower annular surface 41 of the holder 40 touches an upper annular surface 32 of the upper spacer ring 32. After pressure relief, the holder 40 is moved with the press ram 34 in the direction of an arrow 54 until the funnel 28 is released. A second portion of the propellant charge remaining as the remainder is then loosely poured onto the first portion 44.

Im dargestellten Fall ist ein Blindkörper 15 in der Gewindebohrung 14 für den Treibladungsanzünder und in der Aufnahmebohrung 22 des Bodenstücks 20 angeordnet. Der in den nicht näher bezeichneten Innenraum der Treibladungshülse 10 vorstehende Teil des Blindkörpers 15 ist im wesentlichen dem Treibladungsanzünder abmessungsgleich. Deshalb lässt sich nach Entfernen des Blindkörpers 15 der Treibladungsanzünder leicht in einen Kanal 15' einführen, der nach Entfernen des Blindkörpers 15 im verdichteten Teil verbleibt.In the case shown, a dummy body 15 is arranged in the threaded bore 14 for the propellant charge lighter and in the receiving bore 22 of the base piece 20. The part of the dummy body 15 protruding into the interior of the propellant charge sleeve 10, which is not described in more detail, is essentially the same dimension as the propellant charge lighter. Therefore, after removing the dummy body 15, the propellant charge lighter can easily be inserted into a channel 15 ' , which remains in the compressed part after removing the dummy body 15.

Fig.4 zeigt eine Vorrichtung V2 mit einem kreisringzylindrischen Rohr 60 ausreichender Wandstärke, in welches unterseitig ein Bodenstück 62 eingesetzt ist. Letzteres weist eine zentral axiale Gewindebohrung 64 zur Aufnahme eines Blindkörpers 66 auf. Ein Pressstempel 68, dessen Aussendurchmesser dem lichten Innendurchmesser des Rohrs 60 entspricht, weist eine unterseitige Pressfläche 70 und eine rückseitige Betätigungsstange 72 auf. Durch eine zentral axiale Bohrung 72' wird ein Innenraum 73 geschaffen, der sich bis in ein freies oberes Ende 75 der Stange 72 erstreckt. Entlüftungsbohrungen 74' verbinden den Innenraum 73 mit der umgebenden Atmosphäre. In einer Halterung 76 sind radiale Bohrungen 79 vorgesehen. Durch diese greifen bolzenförmige Fixiermittel 68 und legen über Ausnehmungen 75' den Presstempel 68 mit seiner Stange 72 in der Halterung 76 fest. Ein Distanzring 80 weist eine zentrale Öffnung 80' auf, die dem Aussendurchmesser der Stange 72 angepasst ist. Der Distanzring 80 liegt mit einer ebenen Unterseitenfläche 81' auf einer oberseitigen ebenen Kreisringfläche 61 des Rohrs 60 auf. Vor dem Einfüllen eines ersten Anteils der Treibladung in Form losen Schüttpulver in den Innenraum 61 ist der Pressstempel 68 aus letzterem entfernt. Er wird nach Überschieben des Distanzrings 80 in der Halterung 76 festgelegt und in Richtung eines Pfeils 82 entlang einer zentralen Längsachse A unter Druckaufbringung gegen die lose Pulverschüttung des ersten Anteils der Treibladung verfahren. Der über eine Oberseitenfläche 63 des Bodenstücks 62 vorstehende Blindkörper 66 entspricht im wesentlichen den Abmessungen eines Treibladungsanzünders. Beim Abwärtsbewegen des Pressstempels 68 gerät er mit seinem freien Ende 67 in die Bohrung 72', wobei die Luft aus dem Innenraum 73 durch die Entlüftungsbohrungen 74' entweichen kann. Der erste Anteil 86 der Treibladung ist verdichtet, sobald die Aufnahme 76 mit ihrer unterseitigen Kreisringfläche 77 die Oberseitenfläche 81 des Distanzrings 80 berührt.4 shows a device V2 with a circular cylindrical tube 60 of sufficient wall thickness, in which a bottom piece 62 is inserted on the underside. The latter has a central axial threaded bore 64 for receiving a dummy body 66. A press ram 68, the outside diameter of which corresponds to the inside diameter of the tube 60, has a pressing surface 70 on the underside and an actuating rod 72 on the rear. A central axial bore 72 ′ creates an interior space 73 that extends into a free upper end 75 of the rod 72. Vent holes 74 'connect the interior 73 with the surrounding atmosphere. Radial bores 79 are provided in a holder 76. Bolt-shaped fixing means 68 grip through this and fix the pressing die 68 with its rod 72 in the holder 76 via recesses 75 '. A spacer ring 80 has a central opening 80 ′ which is adapted to the outside diameter of the rod 72. The spacer ring 80 lies with a flat underside surface 81 ′ on an upper-side flat circular ring surface 61 of the tube 60. Before a first portion of the propellant charge is poured into the interior 61 in the form of loose bulk powder, the press ram 68 is removed from the latter. After the spacer ring 80 has been pushed over, it is fixed in the holder 76 and moved in the direction of an arrow 82 along a central longitudinal axis A while applying pressure against the loose powder filling of the first portion of the propellant charge. The dummy body 66 projecting over a top surface 63 of the base piece 62 corresponds essentially to the dimensions of a propellant charge lighter. When the ram 68 moves downward, its free end 67 gets into the bore 72 ', the air being able to escape from the interior 73 through the ventilation bores 74'. The first portion 86 of the propellant charge is compressed as soon as the receptacle 76 with its circle on the underside ring surface 77 touches the top surface 81 of the spacer ring 80.

Soll die Treibladung in einer nicht dargestellten metallischen Treibladungshülse kreiszylindrischen Innenquerschnitts einlaboriert werden, kann diese, mit dem Blindkörper 66 versehen, in dem nach seinem Innendurchmesser dem Aussendurchmesser der Treibladungshülse angepassten Rohr 60 von unten her eingeführt werden; in diesem Fall muss der Aussendurchmesser des Pressstempels 68 dem lichten Innendurchmesser der nicht dargestellten metallischen Treibladungshülse angepasst sein.If the propellant charge is to be incorporated in a circular cylindrical inner cross section, not shown, of a metallic propellant charge sleeve, this can be provided with the dummy body 66, in which the inner diameter of the propellant charge sleeve tube 60 is inserted from below from below; in this case, the outside diameter of the press ram 68 must be adapted to the inside diameter of the metallic propellant charge sleeve, not shown.

Soll die Treibladung einer Treibladungshülse nach Fig. 5 einlaboriert werden, so wird vorteilhafterweise folgendermassen verfahren:If the propellant charge of a propellant charge sleeve according to FIG. 5 is to be incorporated, the procedure is advantageously as follows:

Die Treibladungshülse 90 weist einen Boden 94, beispielsweise aus Metall, mit einer zentral axialen Gewindebohrung 96 für einen Treibladungsanzünder 98 auf. Mit dem Boden 94 ist ein verbrennbarer Teil 100 der Treibladungshülse 90 fest verbunden. Der in der Vorrichtung V2 nach Fig. 4 verfestigte erste Anteil 86 der Treibladung soll nun in einen Innenraum 97 der Treibladungshülse 90 übergeführt werden. Um eine Beschädigung einer Innenwandfläche 101 des verbrennbaren Teils 100 der Treibladungshülse 90 zu vermeiden, wird eine Metallhülse 102, die dem lichten Innendurchmesser des verbrennbaren Teils 100 angepasst und in der Zeichnung zur Verdeutlichung übermässig dickwandig dargestellt ist, in den Innenraum 97 eingeführt. Nach Entfernen des Bodenstücks 62 und des Blindkörpers 66 (siehe Fig. 4) wird die Anordnung nach Fig. 5 achsfluchtend unter der Vorrichtung V2 fixiert. Beim Ausdrücken des verfestigten ersten Anteils 86 der Treibladung gerät der Treibladungsanzünder 98 in einen von dem Blindkörper gebildeten Kanal 88. Sobald der verfestigte erste Anteil 86 der Treibladung in die Treibladungshülse 90 übergeführt ist, wird die glatte Metallhülse 100 an ihrem oberseitigen Rand 104 in Richtung eines Pfeils 108 wieder aus der Treibladungshülse 90 entfernt, und der zweite Anteil der Treibladung wird als loses Schüttpulver aufgebracht.The propellant charge sleeve 90 has a base 94, for example made of metal, with a central axial threaded bore 96 for a propellant charge lighter 98. A combustible part 100 of the propellant charge sleeve 90 is fixedly connected to the bottom 94. The first portion 86 of the propellant charge solidified in the device V2 according to FIG. 4 is now to be transferred into an interior space 97 of the propellant charge sleeve 90. In order to avoid damaging an inner wall surface 101 of the combustible part 100 of the propellant charge sleeve 90, a metal sleeve 102, which is adapted to the inside diameter of the combustible part 100 and is shown in the drawing as excessively thick-walled for clarification, is introduced into the interior 97. After removing the base piece 62 and the dummy body 66 (see FIG. 4), the arrangement according to FIG. 5 is fixed under the device V2 in alignment with the axis. When the solidified first portion 86 of the propellant charge is squeezed out, the propellant charge lighter 98 gets into a channel 88 formed by the dummy body. As soon as the solidified first portion 86 of the propellant charge has been transferred into the propellant charge sleeve 90, the smooth metal sleeve 100 on its top edge 104 becomes one Arrow 108 removed from the propellant charge sleeve 90 again, and the second portion of the propellant charge is applied as loose bulk powder.

Es versteht sich, dass bei einem Treibladungsanzünder, der wesentlich länger ist als der Blindkörper 15 nach Fig. 3 der Pressstempel 34 mit einer zentral axialen Bohrung für den längeren Blindkörper und dann auch ggfs. mit einer Entlüftungsbohrung wie bei der Vorrichtung V2 in Fig. 4 versehen sein muss. Die Distanzringe 30, 32 und 80 sind auswechselbar, so dass zum Erreichen einer vorgegebenen Verdichtung des jeweiligen ersten Anteils 44 bzw. 86 der Treibladung die Eindringtiefe des Pressstempels 34 bzw. 68 verändertwerden kann.It goes without saying that, in the case of a propellant charge lighter that is considerably longer than the dummy body 15 according to FIG. 3, the press ram 34 has a central axial bore for the longer dummy body and then, if appropriate, also has a ventilation bore as in the device V2 in FIG. 4 must be provided. The spacer rings 30, 32 and 80 are interchangeable, so that the penetration depth of the press ram 34 and 68 can be changed in order to achieve a predetermined compression of the respective first portion 44 and 86 of the propellant charge.

Claims (10)

1. Propulsive charge without the addition of solution and/or binding agents for the propulsive charge powder, wherein pressure to be applied from outside serves to compress propulsive charge powder for the purpose of increasing the internal ballistic performance, characterised by the fact that only a preselectable first part of the total mass of propulsive charge powder is at least partly present in a compressed state while the remaining second part, as a loose pile, completes the propulsive charge.
2. Propulsive charge in accordance with Claim 1 or 2, characterised by the fact that the first part preferably corresponds to about 50-80% of the total mass of the propulsive charge.
3. Propulsive charge in accordance with Claim 1 or 2, characterised by the presence of different propulsive charge powders.
4. Method for the manufacture of a propulsive charge in accordance with Claims 1, 2 or 3, characterised by the following steps in the process:
(a) the first part of the total mass of the propulsive charge is at least partly compressed as a piled powder and
(b) the second part is left as the remainder of the total mass of the propulsive charge consisting of loose piled powder and forming, when finally processed, a part of propulsive charge close to the projectile.
5. Method in accordance with Claim 4, characterised by the following steps in the process:
(a) the compression of a first part takes place in a device,
(b) the first part is transferred after compression into a propulsive charge casing and
(c) the second part is piled loosely on the first part.
6. Method in accordance with Claim 4, characterised by the fact that it is carried out in a propulsive charge casing.
7. Method in accordance with Claim 4, 5 or 6, characterised by the fact that the total mass of the propulsive charge corresponds to the mass (N) which can receive a propulsive charge casing to enable the propulsive charge to be worked in as a loose pile of the same propulsive charge powder or powders of which the propulsive charge consists.
8. Method in accordance with Claim 4, 5 or 6, characterised by the fact that the total mass of the propulsive charge corresponds to a mass (M) which is greater than the mass (N) according to the characterising part of Claim 7.
9. Method in accordance with one of claims 4 to 8, characterised by the following additional steps in the process:
(a) a blank body which corresponds at least to the dimensions of a propulsive charge detonator present in the propulsive charge casing is provided in such way that it can be removed at least for the purpose of filling in and compressing the first part of the propulsive charge, and
(b) the blank body is then removed and replaced by the propulsive charge detonator.
10. Method in accordance with one of Claims 5 to 9, particularly in the event of the use of and at least partly combustible propulsive charge casing, characterised by the fact that for the purpose of transferring the compressed first part from the device a means is inserted for reducing the wall friction in the propulsive charge casing and is subsequently removed after the transfer of the first part.
EP84109753A 1983-10-01 1984-08-16 Propulsive charge and method for manufacturing Expired - Lifetime EP0137958B2 (en)

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DE19833335821 DE3335821A1 (en) 1983-10-01 1983-10-01 DRIVE CHARGING AND METHOD FOR THEIR PRODUCTION
DE3335821 1983-10-01

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EP0137958A3 EP0137958A3 (en) 1986-10-08
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Also Published As

Publication number Publication date
EP0137958A2 (en) 1985-04-24
ES536308A0 (en) 1985-07-01
JPH0445755B2 (en) 1992-07-27
DE3472294D1 (en) 1988-07-28
NO843589L (en) 1985-04-02
EP0137958B2 (en) 1991-12-18
EP0137958A3 (en) 1986-10-08
ES8505907A1 (en) 1985-07-01
JPS6090889A (en) 1985-05-22
DE3335821A1 (en) 1985-04-11
US4625648A (en) 1986-12-02

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