EP0275429B1 - Multichamber primer - Google Patents

Multichamber primer Download PDF

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Publication number
EP0275429B1
EP0275429B1 EP87117779A EP87117779A EP0275429B1 EP 0275429 B1 EP0275429 B1 EP 0275429B1 EP 87117779 A EP87117779 A EP 87117779A EP 87117779 A EP87117779 A EP 87117779A EP 0275429 B1 EP0275429 B1 EP 0275429B1
Authority
EP
European Patent Office
Prior art keywords
ignition
combustion chamber
propellent charge
combustion
charge igniter
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.)
Expired - Lifetime
Application number
EP87117779A
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German (de)
French (fr)
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EP0275429A1 (en
Inventor
Uwe Brede
Erich Zeiher
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
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Dynamit Nobel AG
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Publication date
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Publication of EP0275429A1 publication Critical patent/EP0275429A1/en
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    • 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
    • F42C19/0823—Primers or igniters for the initiation or the propellant charge in a cartridged ammunition
    • F42C19/0826—Primers or igniters for the initiation or the propellant charge in a cartridged ammunition comprising an elongated perforated tube, i.e. flame tube, for the transmission of the initial energy to the propellant charge, e.g. used for artillery shells and kinetic energy penetrators
    • 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
    • F42C19/0807—Primers; Detonators characterised by the particular configuration of the transmission channels from the priming energy source to the charge to be ignited, e.g. multiple channels, nozzles, diaphragms or filters
    • 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
    • F42C19/0823—Primers or igniters for the initiation or the propellant charge in a cartridged ammunition
    • F42C19/083—Primers or igniters for the initiation or the propellant charge in a cartridged ammunition characterised by the shape and configuration of the base element embedded in the cartridge bottom, e.g. the housing for the squib or percussion cap

Definitions

  • the invention relates to propellant charge igniters with a primary ignition element and with an ignition mixture which is arranged in a combustion chamber and is in the form of a molded body.
  • Propellant lighters are used to ignite propellant charges, in particular propellant powder beds. These propellant charge lighters are used, for example, in rockets, propellant cartridges or ejection charges or for pyrotechnic articles. In particular, however, they are used to ignite the propellant charge of ammunition for barrel weapons and are therefore referred to as propellant charge lighters. Propellant lighters of this type are described for example in DE-C-2504907.
  • the mechanically or electrically triggerable ignition element is spatially separated from a booster charge which, as a second mixture of substances, controls the actual ignition process, i.e. the ignition of the propellant powder.
  • Ignition mixtures of different shapes and compositions serve as reinforcing charges. These ignition mixtures can also be in the form of shaped bodies (ring tablets, disks, cylinders, etc.).
  • a propellant lighter should ignite a propellant powder bed as quickly and evenly as possible in the entire application temperature range with the lowest possible mechanical load.
  • the disadvantages of the known propellant charge lighter lie in non-uniformities in the flow rate of the igniting gases flowing out and the different outflowing times of the igniting gases.
  • the object of the present invention is to provide a propellant charge lighter which ensures improved ignition of the propellant powder bed.
  • a propellant charge igniter with a primary ignition element and with an ignition mixture arranged as a shaped body in a combustion chamber, which is characterized in that at least two combustion chambers are provided, which are connected in series and separated from one another by a throttle disk and via this are in direct operative connection and that in each combustion chamber there is an ignition mixture which differs from the other ignition mixture (s) in terms of its combustion properties.
  • the propellant charge lighter expediently has a cylindrical housing, one end of which is closed by a base piece in which the primary ignition element is accommodated.
  • a first combustion chamber in which an ignition mixture is located, adjoins the base piece.
  • This first combustion chamber is connected via a throttle disc to a second combustion chamber adjoining it, which also contains an ignition mixture.
  • the ignition mixtures are advantageously arranged in the central area of the combustion chambers.
  • the shape and the composition of the ignition mixtures are expediently chosen such that their combustion properties differ greatly from one another.
  • the combustion chambers are expediently designed in such a way that they are optimally matched to the ignition mixtures contained therein.
  • This multi-chamber system ensures that the different ignition mixtures, which are known to require different combustion pressure levels, can burn off at the pressure levels that are optimal for them.
  • the optimal ignition conditions for a given propellant powder bed can be created. So it is possible to ensure an optimal mixing of the ignition gases, consisting of gas, condensates and hot particles.
  • the flow rate of the ignition gases and the outflow time can be set.
  • the throttle disk is equipped with outflow bores in a preferred embodiment according to the invention.
  • These outflow bores preferably have a different diameter.
  • the ignition mixtures are in the form of compacts. This makes it possible to give them a specific shape, which also enables the outflow speeds of the ignition vapor to be controlled over time.
  • the respective combustion chamber volume is preferably matched to the combustion properties of the ignition mixtures. This coordination is preferably achieved with compensation parts attached in the combustion chamber. These are inert inserts for the combustion chambers, with which both the distance of the ignition mixtures from the throttle plate (s) or bottom or end part as well as the combustion chamber volume can be changed.
  • the compensating parts are preferably ring-shaped spacers.
  • the outer diameter of these spacers is preferably such that they abut the inner wall of the housing.
  • the ignition mixture present as a compact is held in the central region of the combustion chamber by a spacer (spacer) arranged above and below these ignition mixtures.
  • the last combustion chamber i.e. the combustion chamber facing away from the ignition element is preferably provided with a closing part which is equipped with at least one outflow bore.
  • the shape or the diameter of this outflow bore or the main outflow nozzle are also selected such that the ignition gases escape in the desired manner
  • the base piece, the compensating parts, the throttle plate and the end part are expediently produced in one piece using the cold extrusion process. This applies in particular to mass production.
  • the propellant lighter shown in FIG. 1 with two combustion chambers has a cylindrical housing 3, which is closed at the lower end by a disk-shaped base piece 1.
  • a primary ignition element 2 is attached, which can be triggered either electrically or mechanically.
  • the first combustion chamber 7 is formed from the cylindrical housing 3, the base piece 1 and the throttle disc 8.
  • the throttle disc 8 (see FIG. 4) has outflow bores 9.
  • the size of the combustion chamber is set by the length and volume of the compensating parts 4, 5 and the thickness of the ignition mixture 6 present as a compact.
  • the adjoining second combustion chamber 13 is formed by the cylindrical housing 3, the throttle disc 8 and the end part 14, which has an outflow bore 15.
  • the size of the second combustion chamber 13 is determined by the length and the volume of the compensating parts 10, 11 and the thickness of the ignition mixture 12 present as a compression body.
  • the compensating parts 4, 5, 10 and 11 are, in the embodiment shown in FIG. 1, annular spacers (spacers) which rest with their outer wall on the inner wall of the housing 3.
  • the ignition mixtures 6, 12, which are in the form of compacts, are expediently disk-shaped and, with their outer diameter, also bear against the inner wall of the housing 3. These compacts are thus on the spacers and are held by them in the central region of the combustion chambers 7, 13.
  • the resulting reaction products are blown into the combustion chamber 7 and ignite the ignition mixture 6 present as a compact.
  • this ignition mixture consists of a nitrocellulose powder, then mainly hot gases are formed.
  • the resulting gas pressure in the combustion chamber 7 is regulated by the size of the combustion chamber 7 and the choice of the outflow bores 9 of the throttle disk 8.
  • the throttle disk 8 shown in FIG. 4 acts as a pressure-dependent valve through outflow bores 9 of different sizes.
  • the large outflow bores throttle the combustion products of the ignition mixture 6 little, while the small outflow bores 9 block the more the higher the pressure in the combustion chamber 7 increases.
  • the combustion products of the ignition mixture 6 are introduced into the second combustion chamber 13 via the outflow bores 9 of the throttle disks shown in FIG. 4. These combustion products ignite the ignition mixture 12 present there as a compression body.
  • This compression body can be, for example, a ring tablet made from black powder.
  • the combustion products of the ignition mixture are mainly hot particles and condensates.
  • the optimal pressure level is set by the length of the compensating parts 10, 11 and the thickness of the ignition mixture compact 12.
  • the hot gas products of the ignition mixture 6 mixed in the second combustion chamber 13 emerge together with the hot particle-condensate-gas mixture of the second ignition mixture 12 as a common ignition vapor through the outflow bore 15 of the connection part 14 shown in FIG. which is in a cartridge, for example.
  • the inventive propellant lighter shown in FIG. 2 with a plurality of combustion chambers also has a cylindrical housing 3 with a base piece 1 in which the electrically or mechanically triggerable primary ignition element 2 is attached.
  • the first combustion chamber 19 is formed by the housing 3, the base piece 1 and the throttle disk 20 equipped with an outflow bore 21.
  • the size of the combustion chamber is determined by the length and the volume of the compensating parts 16, 17 and the thickness of the ignition mixture compact 18.
  • the further combustion chamber (s) 24 is (are) shown in simplified form in FIG. 2 and has (have) compensating parts 22, 23 and a throttle disk 25 with obliquely arranged outflow bores 26.
  • the last combustion chamber 30 of the multi-chamber system is formed by the throttle disk 25, the housing 3 and the end part 31 with the outflow holes 32.
  • the size of this combustion chamber 30 is determined by the compensating parts 27, 28 and the ignition mixture compression body 29.
  • the compensating parts 16, 17, 22, 23, 27, 28 and the ignition mixtures 18, 29 in the form of compacts of the embodiment of the propellant charge lighter according to the invention shown in FIG. 2 are configured in the same way as the corresponding parts of the embodiment shown in FIG. it is ring-shaped spacers or compact discs.
  • the diameter of the throttle disks 20, 25 is such that their radial side surface abuts the inner wall of the cylindrical housing 3.
  • the propellant lighter shown in FIG. 2 differs from that of FIG. 1 in that between the combustion chamber 19, which is adjacent to the ignition element 2, and the last combustion chamber 30, which is closed by the closing part 31, one (or more) ) further combustion chamber (s) is (are) interposed.
  • one (or more) ) further combustion chamber (s) is (are) interposed.
  • differently shaped and composed ignition mixtures or compression molding compacts can be used, so that the emerging ignition gases have the optimum temperature, speed, etc. for the ignition of the propellant powder bed.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Air Bags (AREA)
  • Lighters Containing Fuel (AREA)

Description

Die Erfindung betrifft Treibladungsanzünder mit einem Primäranzündelement und mit einer, in einer Brennkammer angeordneten als Formkörper vorliegenden Anzündmischung.The invention relates to propellant charge igniters with a primary ignition element and with an ignition mixture which is arranged in a combustion chamber and is in the form of a molded body.

Treibladungsanzünder dienen zum Anzünden von Treibladungen, insbesondere von Treibladungspulverbetten. Diese Treibladungsanzünder finden beispielsweise Anwendung bei Raketen, Treibkartuschen oder Ausstoßladungen oder für pyrotechnische Artikel. Insbesondere werden sie jedoch zum Anzünden der Treibladung von Munition für Rohrwaffen verwendet und daher als Treibladungsanzünder bezeichnet. Treibladungsanzünder dieser Art sind beispielsweise in der DE-C-2504907 beschrieben.Propellant lighters are used to ignite propellant charges, in particular propellant powder beds. These propellant charge lighters are used, for example, in rockets, propellant cartridges or ejection charges or for pyrotechnic articles. In particular, however, they are used to ignite the propellant charge of ammunition for barrel weapons and are therefore referred to as propellant charge lighters. Propellant lighters of this type are described for example in DE-C-2504907.

Bei derartigen Treibladungsanzündern ist das mechanisch oder elektrisch auslösbare Anzündelement räumlich von einer Verstärkungsladung getrennt, welche als zweites Stoffgemisch den eigentlichen Anzündvorgang, d.h. die Anzündung des Treibladungspulvers, bewirkt.In the case of propellant igniters of this type, the mechanically or electrically triggerable ignition element is spatially separated from a booster charge which, as a second mixture of substances, controls the actual ignition process, i.e. the ignition of the propellant powder.

Als Verstärkungsladungen dienen Anzündmischungen unterschiedlicher Form und Zusammensetzungen. Diese Anzündmischungen können auch als Formkörper (Ringtabletten, Scheiben, Zylinder usw.) vorliegen.Ignition mixtures of different shapes and compositions serve as reinforcing charges. These ignition mixtures can also be in the form of shaped bodies (ring tablets, disks, cylinders, etc.).

Ein Treibladungsanzünder soll bei möglichst geringer mechanischer Belastung ein Treibladungspulverbett im gesamten Anwendungstemperaturband möglichst schnell und gleichmäßig anzünden.A propellant lighter should ignite a propellant powder bed as quickly and evenly as possible in the entire application temperature range with the lowest possible mechanical load.

Die Nachteile der bekannten Treibladungsanzünder liegen in Ungleichmäßigkeiten der Strömungsgeschwindigkeit der ausströmenden Anzündgase und der unterschiedlichen Ausströmdauer der Anzündgase.The disadvantages of the known propellant charge lighter lie in non-uniformities in the flow rate of the igniting gases flowing out and the different outflowing times of the igniting gases.

So ist bekannt, daß bei zu hohen Einströmgeschwindigkeiten der Anzündgase in ein Treibladungspulverbett Löschungsvorgänge an der Treibladungspulveroberfläche auftreten können. Dies führt zu einer mehr oder weniger stark streuenden Anzündung des Treibladungspulverbettes.It is known, for example, that when the ignition gases flow into the propellant powder bed at too high a rate, extinguishing processes can occur on the propellant powder surface. This leads to a more or less scattering ignition of the propellant powder bed.

Aufgabe der vorliegenden Erfindung ist es, einen Treibladungsanzünder bereitzustellen, der eine verbesserte Anzündung des Treibladungspulverbettes gewährleistet.The object of the present invention is to provide a propellant charge lighter which ensures improved ignition of the propellant powder bed.

Gelöst wird diese Aufgabe durch einen Treibladungsanzünder mit einem Primiäranzündelement und mit einer, in einer Brennkammer angeordneten als Formkörper vorliegenden Anzündmischung, der dadurch gekennzeichnet ist, daß mindestens zwei Brenkammern vorgesehen sind, die in Reihe geschaltet und jeweils durch eine Drosselscheibe voneinander getrennt sind und über diese in direkter Wirkverbindung stehen,und daß in jeder Brennkammer eine Anzündmischung vorhanden ist, die sich von der (den) anderen Anzündmischung(en) hinsichtlich ihrer Verbrennungseigenschaften unterscheidet.This object is achieved by a propellant charge igniter with a primary ignition element and with an ignition mixture arranged as a shaped body in a combustion chamber, which is characterized in that at least two combustion chambers are provided, which are connected in series and separated from one another by a throttle disk and via this are in direct operative connection and that in each combustion chamber there is an ignition mixture which differs from the other ignition mixture (s) in terms of its combustion properties.

Der erfindungsgemäße Treibladungsanzünder besitzt zweckmäßigerweise ein zylindrisches Gehäuse, dessen eines Ende durch ein Bodenstück verschlossen ist, in dem das Primäranzündelement untergebracht ist.The propellant charge lighter according to the invention expediently has a cylindrical housing, one end of which is closed by a base piece in which the primary ignition element is accommodated.

An das Bodenstück schließt sich eine erste Brennkammer an, in der sich eine Anzündmischung befindet Diese erste Brennkammer steht über eine Drosselscheibe mit einer sich daran anschließenden zweiten Brennkammer in Verbindung, die ebenfalls eine Anzündmischung enthält.A first combustion chamber, in which an ignition mixture is located, adjoins the base piece. This first combustion chamber is connected via a throttle disc to a second combustion chamber adjoining it, which also contains an ignition mixture.

Die Anzündmischungen sind vorteilhafterweise im mittleren Bereich der Brennkammern angeordnet.The ignition mixtures are advantageously arranged in the central area of the combustion chambers.

Die Form und die Zusammensetzung der Anzündmischungen wählt man zweckmäßigerweise derart, daß sich ihre Verbrennungseigenschaften stark voneinander unterscheiden. Die Brennkammern legt man zweckmäßigerweise derart aus, daß sie möglichst optimal an die darin befindlichen Anzündmischungen angepaßt sind.The shape and the composition of the ignition mixtures are expediently chosen such that their combustion properties differ greatly from one another. The combustion chambers are expediently designed in such a way that they are optimally matched to the ignition mixtures contained therein.

Durch dieses Mehrkammersystem wird gewährleistet, daß die unterschiedlichen Anzündmischungen, die bekannterweise unterschiedliche Verbrennungsdruckniveaus benötigen, jeweils bei den für sie optimalen Druckniveaus abbrennen können.This multi-chamber system ensures that the different ignition mixtures, which are known to require different combustion pressure levels, can burn off at the pressure levels that are optimal for them.

Durch die Anwesenheit von mindestens zwei Brennkammern und darin angebrachten unterschiedlichen Anzündmischungen können die für ein gegebenes Treibladungspulverbett optimalen Anzündungsbedingungen geschaffen werden. So ist es möglich, für eine optimale Vermischung der Anzündgase, bestehend aus Gas, Kondensaten und heißen Partikeln, Sorge zu tragen. Zudem können die Strömungsgeschwindigkeit der Anzündgase sowie die Abströmzeit eingestellt werden.Due to the presence of at least two combustion chambers and different ignition mixtures attached therein, the optimal ignition conditions for a given propellant powder bed can be created. So it is possible to ensure an optimal mixing of the ignition gases, consisting of gas, condensates and hot particles. In addition, the flow rate of the ignition gases and the outflow time can be set.

Um dies zu erreichen, ist die Drosselscheibe bei einer bevorzugten erfindungsgemäßen Ausführungsform mit Abströmbohrungen ausgestattet. Diese Abströmbohrungen haben vorzugsweise einen unterschiedlichen Durchmesser. Dadurch und durch die Anordnung dieser Abströmbohrungen kann die Abströmgeschwindigkeit der Anzündschwaden zeitlich gesteuert werden.To achieve this, the throttle disk is equipped with outflow bores in a preferred embodiment according to the invention. These outflow bores preferably have a different diameter. As a result and through the arrangement of these outflow bores, the outflow rate of the ignition vapor can be controlled in time.

Nach einer weiterhin bevorzugten Ausführungsform liegen die Anzündmischungen als Preßkörper vor. Dadurch ist es möglich, ihnen eine bestimmte Form zu verleihen, die ebenfalls eine zeitliche Steuerung der Abströmgeschwindigkeiten der Anzündschwaden ermöglicht.According to a further preferred embodiment, the ignition mixtures are in the form of compacts. This makes it possible to give them a specific shape, which also enables the outflow speeds of the ignition vapor to be controlled over time.

Das jeweilige Brennkammervolumen ist vorzugsweise auf die Verbrennungseigenschaften der Anzündmischungen abgestimmt. Diese Abstimmung wird vorzugsweise mit in der Brennkammer angebrachten Ausgleichsteilen erzielt. Dabei handelt es sich um inerte Einsätze für die Brennkammern, mit denen sowohl der Abstand der Anzündmischungen von Drosselscheibe(n) bzw. Boden oder Abschlußteil als auch das Brennkammervolumen verändert werden können.The respective combustion chamber volume is preferably matched to the combustion properties of the ignition mixtures. This coordination is preferably achieved with compensation parts attached in the combustion chamber. These are inert inserts for the combustion chambers, with which both the distance of the ignition mixtures from the throttle plate (s) or bottom or end part as well as the combustion chamber volume can be changed.

Die Ausgleichsteile sind vorzugsweise ringförmige Abstandshalter (Distanzhalter). Der Außendurchmesser dieser Abstandshalter ist vorzugsweise derart, daß sie an der Innenwandung des Gehäuses anliegen.The compensating parts are preferably ring-shaped spacers. The outer diameter of these spacers is preferably such that they abut the inner wall of the housing.

Bei einer bevorzugten Ausführungsform werden die als Preßkörper vorliegenden Anzündmischung durch jeweils einen oberhalb und unterhalb dieser Anzündmischungen angeordnetes Abstandshalter (Distanzhalter) im mittleren Bereich der Brennkammer gehalten.In a preferred embodiment, the ignition mixture present as a compact is held in the central region of the combustion chamber by a spacer (spacer) arranged above and below these ignition mixtures.

Die letzte Brennkammer, d.h. die vom Anzündelement abgewandte Brennkammer ist vorzugsweise mit einem Abschlußteil versehen, das mit mindestens einer Abströmbohrung ausgestattet ist. Auch die Form bzw. der Durchmesser dieser Abströmbohrung bzw. der Hauptabströmdüse werden derart gewählt, daß die Anzündgase in der gewünschten Weise austretenThe last combustion chamber, i.e. the combustion chamber facing away from the ignition element is preferably provided with a closing part which is equipped with at least one outflow bore. The shape or the diameter of this outflow bore or the main outflow nozzle are also selected such that the ignition gases escape in the desired manner

Bei der Herstellung des erfindungsgemäßen Treibladungsanzünders werden das Bodenstück, die Ausgleichsteile, die Drosselscheibe und das Abschlußteil zweckmäßigerweise einstückig im Kaltfließpreßverfahren hergestellt. Dies gilt insbesondere für die Massenfertigung.In the manufacture of the propellant charge lighter according to the invention, the base piece, the compensating parts, the throttle plate and the end part are expediently produced in one piece using the cold extrusion process. This applies in particular to mass production.

Die Erfindung wird anhand der Fig. 1 bis 4, welche bevorzugte Ausfihrungsformen darstellen, näher erläutert:
Von den Figuren zeigen:

Figur 1
einen Längsschnitt durch einen erfindungsgemäßen Treibladungsanzünder mit zwei Brennkammern;
Figur 2
einen Längsschnitt durch einen erfindungsgemäßen Treibladungsanzünder mit mehr als zwei Brennkammern;
Figur 3
eine Aufsicht auf das Abschlußteil 14 der Fig. 1, und
Figur 4
eine Draufsicht auf die in der Fig. 1 gezeigten Drosselscheibe 8.
The invention is explained in more detail with reference to FIGS. 1 to 4, which represent preferred embodiments:
From the figures show:
Figure 1
a longitudinal section through a propellant lighter according to the invention with two combustion chambers;
Figure 2
a longitudinal section through an inventive propellant lighter with more than two combustion chambers;
Figure 3
a plan view of the end part 14 of FIG. 1, and
Figure 4
a plan view of the throttle disc 8 shown in FIG. 1.

Der in der Fig. 1 gezeigte Treibladungsanzünder mit zwei Brennkammern besitzt ein zylindrisches Gehäuse 3, das am unteren Ende durch ein scheibenförmiges Bodenstück 1 verschlossen ist. In diesem Bodenstück 1 ist ein Primäranzündelement 2 angebracht, das entweder elektrisch oder mechanisch ausgelöst werden kann.
Die erste Brennkammer 7 wird gebildet aus dem zylindrischen Gehäuse 3, dem Bodenstück 1 und der Drosselscheibe 8. Die Drosselscheibe 8 (man vergleiche Fig. 4) besitzt Abströmbohrungen 9. Die Größe der Brennkammer wird eingestellt durch die Länge und das Volumen der Ausgleichsteile 4, 5 und die Dicke der als Preßkörper vorliegenden Anzündmischung 6.The propellant lighter shown in FIG. 1 with two combustion chambers has a cylindrical housing 3, which is closed at the lower end by a disk-shaped base piece 1. In this bottom piece 1, a primary ignition element 2 is attached, which can be triggered either electrically or mechanically.
The first combustion chamber 7 is formed from the cylindrical housing 3, the base piece 1 and the throttle disc 8. The throttle disc 8 (see FIG. 4) has outflow bores 9. The size of the combustion chamber is set by the length and volume of the compensating parts 4, 5 and the thickness of the ignition mixture 6 present as a compact.

Die sich daran anschließende zweite Brennkammer 13 wird gebildet durch das zylindrische Gehäuse 3, die Drosselscheibe 8 und das Abschlußteil, 14, das eine Abströmbohrung 15 aufweist. Die Größe der zweiten Brennkammer 13 wird bestimmt durch die Länge und das Volumen der Ausgleichsteile 10, 11 und die Dicke der als Preßkörper vorliegenden Anzündmischung 12.The adjoining second combustion chamber 13 is formed by the cylindrical housing 3, the throttle disc 8 and the end part 14, which has an outflow bore 15. The size of the second combustion chamber 13 is determined by the length and the volume of the compensating parts 10, 11 and the thickness of the ignition mixture 12 present as a compression body.

Bei den Ausgleichsteilen 4, 5, 10 und 11 handelt es sich bei der in Fig. 1 gezeigten Ausführungsform um ringförmige Abstandshalter (Distanzhalter), die mit ihrer Außenwand an der Innenwand des Gehäuses 3 anliegen. Die als Preßkörper vorliegenden Anzündmischungen 6, 12 sind zweckmäßigerweise scheibenförmig und liegen mit ihrem Außendurchmesser ebenfalls an der Innenwand des Gehäuses 3 an. Diese Preßkörper liegen somit auf den Abstandshaltern auf urd werden durch diese im mittleren Bereich der Brennkammern 7, 13 gehalten.The compensating parts 4, 5, 10 and 11 are, in the embodiment shown in FIG. 1, annular spacers (spacers) which rest with their outer wall on the inner wall of the housing 3. The ignition mixtures 6, 12, which are in the form of compacts, are expediently disk-shaped and, with their outer diameter, also bear against the inner wall of the housing 3. These compacts are thus on the spacers and are held by them in the central region of the combustion chambers 7, 13.

Die Wirkungsweise dieses in Fig. 1 gezeigten Treibladungsanzünders ist die folgende:The operation of this propellant lighter shown in Fig. 1 is as follows:

Nach entweder mechanischer oder elektrischer Initiierung des Primäranzündelementes 2 werden die entstehenden Umsetzungsprodukte in die Brennkammer 7 eingeblasen und entzünden die als Preßkörper vorliegende Anzündmischung 6.After either mechanical or electrical initiation of the primary ignition element 2, the resulting reaction products are blown into the combustion chamber 7 and ignite the ignition mixture 6 present as a compact.

Besteht diese Anzündmischung aus einem Nitrocellulosepulver, dann werden vorwiegend heiße Gase gebildet. Der dabei entstehende Gasdruck in der Brennkammer 7 wird durch die Größe der Brennkammer 7 und die Wahl der Abströmbohrungen 9 der Drosselscheibe 8 reguliert. Dabei wirkt die in Fig. 4 dargestellte Drosselscheibe 8 durch unterschiedlich große Abströmbohrungen 9 als druckabhängiges Ventil. Die großen Abströmbohrungen drosseln die Verbrennungsprodukte der Anzündmischung 6 wenig, während die kleinen Abströmbohrungen 9 um so mehr verblocken, je höher der Druck in der Brennkammer 7 ansteigt. Durch Optimierung der Durchmesser der Abströmbohrurgen 9 (z.B. mehrere verschiedene Bohrungsdurchmesser) kann somit ein in weiten Grenzen variierbarer Verbrennungsdruck in der Brennkammer 7 sowie ein geregelter Massendurchsatz der Gase durch die Drosselscheibe erzielt werden.If this ignition mixture consists of a nitrocellulose powder, then mainly hot gases are formed. The resulting gas pressure in the combustion chamber 7 is regulated by the size of the combustion chamber 7 and the choice of the outflow bores 9 of the throttle disk 8. The throttle disk 8 shown in FIG. 4 acts as a pressure-dependent valve through outflow bores 9 of different sizes. The large outflow bores throttle the combustion products of the ignition mixture 6 little, while the small outflow bores 9 block the more the higher the pressure in the combustion chamber 7 increases. By optimizing the diameter of the outflow bores 9 (for example several different bore diameters), a combustion pressure in the combustion chamber 7 which can be varied within wide limits and a regulated mass flow rate of the gases through the throttle disc can thus be achieved.

Über die Abströmbohrungen 9 der in Fig. 4 gezeigten Drosselscheiben werden die Verbrennungsprodukte der Anzündmischung 6 in die zweite Brennkammer 13 eingeleitet. Diese Verbrennungsprodukte entzünden die dort befindliche, als Preßkörper vorliegende Anzündmischung 12. Dieser Preßkörper kann beispielsweise eine Ringtablette aus Schwarzpulver sein. In diesem Fall sind die Verbrennungsprodukte der Anzündmischung vorwiegend heiße Partikel und Kondensate.The combustion products of the ignition mixture 6 are introduced into the second combustion chamber 13 via the outflow bores 9 of the throttle disks shown in FIG. 4. These combustion products ignite the ignition mixture 12 present there as a compression body. This compression body can be, for example, a ring tablet made from black powder. In this case, the combustion products of the ignition mixture are mainly hot particles and condensates.

Das optimale Druckniveau wird durch die Länge der Ausgleichsteile 10, 11 und die Dicke des Anzündmischung-Preßkörpers 12 eingestellt. Die in der zweiten Brennkammer 13 gemischten heißen Gasprodukte der Anzündmischung 6 treten zusammen mit dem heißen Partikel-Kondensat-Gasgemisch der zweiten Anzündmischung 12 als gemeinsamer Anzündschwaden durch Ausströmbohrung 15 des in Fig. 3 gezeigten Anschlußteiles 14 aus und sorgen für die Anzündung eines nachgeschalteten Treibladungspulverbettes, das sich beispielsweise in einer Patrone befindet.The optimal pressure level is set by the length of the compensating parts 10, 11 and the thickness of the ignition mixture compact 12. The hot gas products of the ignition mixture 6 mixed in the second combustion chamber 13 emerge together with the hot particle-condensate-gas mixture of the second ignition mixture 12 as a common ignition vapor through the outflow bore 15 of the connection part 14 shown in FIG. which is in a cartridge, for example.

Der in der Fig. 2 gezeigte erfindungsgemäße Treibladungsanzünder mit mehreren Brennkammern besitzt ebenfalls ein zylindrisches Gehäuse 3 mit einem Bodenstück 1, in dem das elektrisch oder mechanisch auslösbare Primäranzündelement 2 angebracht ist. Die erste Brennkammer 19 wird gebildet durch das Gehäuse 3, das Bodenstück 1 und die mit einer Abströmbohrung 21 ausgestatteten Drosselscheibe 20. Die Größe der Brennkammer wird bestimmt durch die Länge und das Volumen der Ausgleichsteile 16, 17 und die Dicke des Anzündmischungs-Preßkörpers 18.The inventive propellant lighter shown in FIG. 2 with a plurality of combustion chambers also has a cylindrical housing 3 with a base piece 1 in which the electrically or mechanically triggerable primary ignition element 2 is attached. The first combustion chamber 19 is formed by the housing 3, the base piece 1 and the throttle disk 20 equipped with an outflow bore 21. The size of the combustion chamber is determined by the length and the volume of the compensating parts 16, 17 and the thickness of the ignition mixture compact 18.

Die weitere(n) Brennkammer(n) 24 ist (sind) in der Fig. 2 vereinfacht dargestellt und besitzt (besitzen) Ausgleichsteile 22, 23 und eine Drosselscheibe 25 mit schräg angeordneten Abströmbohrungen 26.The further combustion chamber (s) 24 is (are) shown in simplified form in FIG. 2 and has (have) compensating parts 22, 23 and a throttle disk 25 with obliquely arranged outflow bores 26.

Die letzte Brennkammer 30 des Mehrkammersystems wird gebildet durch die Drosselscheibe 25, das Gehäuse 3 und das Abschlußteil 31 mit den Abströmtohrungen 32. Die Größe dieser Brennkammer 30 wird bestimmt durch die Ausgleichsteile 27, 28 und den Anzündmischungs-Preßkörper 29.The last combustion chamber 30 of the multi-chamber system is formed by the throttle disk 25, the housing 3 and the end part 31 with the outflow holes 32. The size of this combustion chamber 30 is determined by the compensating parts 27, 28 and the ignition mixture compression body 29.

Die Ausgleichsteile 16, 17, 22, 23, 27, 28 und die als Preßkörper vorliegenden Anzündmischungen 18, 29 der in der Fig. 2 gezeigten Ausführungsform des erfindungsgemäßen Treibladungsanzünders sind ebenso ausgestaltet wie die entsprechenden Teile der in der Fig. 1 dargestellten Ausführungsform, d.h. es handelt sich um ringförmige Abstandshalter bzw. um Preßkörperscheiben. Der Durchmesser der Drosselscheiben 20, 25 ist ebenso wie bei der in der Fig. 1 gezeigten Ausführungsform derart, daß sie mit ihrer radialen Seitenfläche an der Innenwand des zylindrischen Gehäuses 3 anliegen.The compensating parts 16, 17, 22, 23, 27, 28 and the ignition mixtures 18, 29 in the form of compacts of the embodiment of the propellant charge lighter according to the invention shown in FIG. 2 are configured in the same way as the corresponding parts of the embodiment shown in FIG. it is ring-shaped spacers or compact discs. As in the embodiment shown in FIG. 1, the diameter of the throttle disks 20, 25 is such that their radial side surface abuts the inner wall of the cylindrical housing 3.

Der in der Fig. 2 dargestellten Treibladungsanzünder unterscheidet sich von demjenigen der Fig. 1 dadurch, daß zwischen der Brennkammer 19, die dem Anzündeement 2 benachbart ist, und der letzten Brennkammer 30, die durch das Abschlußteil 31 verschlossen ist, noch eine (oder mehrere) weitere Brennkammer(n) dazwischengeschaltet ist (sind). Man kann dadurch verschieden geformte und zusammengesetzte Anzündmischungen bzw. Zündmischungs-Preßkörper zum Einsatz bringen, so daß die austretenden Anzündgase die für die Anzundung des Treibladungspulverbettes optimale Temperatur, Geschwindigkeit usw. besitzen.The propellant lighter shown in FIG. 2 differs from that of FIG. 1 in that between the combustion chamber 19, which is adjacent to the ignition element 2, and the last combustion chamber 30, which is closed by the closing part 31, one (or more) ) further combustion chamber (s) is (are) interposed. In this way, differently shaped and composed ignition mixtures or compression molding compacts can be used, so that the emerging ignition gases have the optimum temperature, speed, etc. for the ignition of the propellant powder bed.

Claims (9)

  1. Propellent charge igniter with a primary igniter element (2) and an ignition composition present as shaped body arranged in a combustion chamber, characterised in that at least two combustion chamber (7, 13, 19, 24, 30) are provided which are connected in series and are respectively separated from one another by a throttle disc (8, 20, 25) and are directly operatively connected via this, and that there is provided in each combustion chamber (7, 13, 19, 24, 30) an ignition composition (6, 12, 18, 29) which is distinguished from the other ignition composition(s) (6, 12, 18, 29) with respect to its combustion properties.
  2. Propellent charge igniter according to claim 1, characterised in that the throttle disc (8, 20, 25,) has at least one discharge passage (9, 15, 21).
  3. Propellent charge igniter according to claim 2, characterised in that the throttle disc (8, 20, 25) has several discharge passages (9, 15, 21) of different diameter.
  4. Propellent charge igniter according to one of the foregoing claims, characterised in that the respective volumes of the combustion chambers (7, 13, 19, 24, 30) is determined by the combustion properties of the igniter compositions (6, 12, 18, 29) placed therein.
  5. Propellent charge igniter according to claim 4, characterised in that, for determination of the volumes of the combustion chambers (7, 13, 19, 24, 30), adjustment elements (4, 5, 10, 11, 17, 22, 23, 28) are arranged in the combustion chambers (7, 13, 19, 24, 30).
  6. Propellent charge igniter according to claim 5, characterised in that, the adjustment elements (4, 5, 10, 11, 16, 17, 22, 23, 28) are formed as annularly shaped spacers.
  7. Propellent charge igniter according to one of the foregoing claims, characterised in that the last combustion chamber (13, 30) has a head part (14, 31) with at least one outflow passage (15, 32).
  8. Propellent charge igniter according to one of the of the foregoing claims, characterised in that the ignition compositions (6, 12, 18, 29) are present as pressed bodies.
  9. Propellent charge igniter according to claim 8, characterised in that one or several ignition compositions (6, 12, 18, 29) contain finely ground inert material.
EP87117779A 1986-12-16 1987-12-02 Multichamber primer Expired - Lifetime EP0275429B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3642942 1986-12-16
DE19863642942 DE3642942A1 (en) 1986-12-16 1986-12-16 MULTI-CHAMBER DRIVE CHARGER

Publications (2)

Publication Number Publication Date
EP0275429A1 EP0275429A1 (en) 1988-07-27
EP0275429B1 true EP0275429B1 (en) 1991-05-22

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP87117779A Expired - Lifetime EP0275429B1 (en) 1986-12-16 1987-12-02 Multichamber primer

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US (1) US4850274A (en)
EP (1) EP0275429B1 (en)
DE (2) DE3642942A1 (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4039149C2 (en) * 1989-12-08 1996-03-21 Fraunhofer Ges Forschung Device for igniting propellant powders
US5542688A (en) * 1992-10-27 1996-08-06 Atlantic Research Corporation Two-part igniter for gas generating compositions
FR2733314B1 (en) * 1995-04-20 1997-06-06 Aerospatiale PYROTECHNIC IGNITION DEVICE FOR A GAS GENERATOR
DE19544823C2 (en) * 1995-12-01 1999-12-16 Rheinmetall W & M Gmbh Propellant lighter with a short ignition delay
US6672215B2 (en) * 2001-10-17 2004-01-06 Textron Systems Corporation Constant output high-precision microcapillary pyrotechnic initiator
FR3004530B1 (en) * 2013-04-15 2018-04-20 Nexter Munitions INFLAMMATOR AMORTI
US10989510B2 (en) * 2019-05-13 2021-04-27 Spectre Enterprises, Inc. Primer housing for firearms and other munitions

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Publication number Priority date Publication date Assignee Title
US2948219A (en) * 1953-03-12 1960-08-09 Winfred F Sapp Rocket fuze
US3162127A (en) * 1955-06-21 1964-12-22 Bertram A Breslow Delay train for fuze
US2990684A (en) * 1958-02-10 1961-07-04 Cohen William Rod assembled plastic rocket
DE1154978B (en) * 1961-06-12 1963-09-26 Rheinmetall Gmbh Propellant for solid rockets, especially for short-flame missiles
US3286472A (en) * 1964-02-24 1966-11-22 Thiokol Chemical Corp Rocket motor and ignition system
US3423943A (en) * 1967-02-27 1969-01-28 Us Navy Hybrid rocket motor
DE2509058A1 (en) * 1975-03-01 1976-09-09 Diehl Fa Delayed action ignition unit with explosive charges - has metallic expansion and delay elements between primary and secondary changes
US4047483A (en) * 1976-03-24 1977-09-13 The United States Of America As Represented By The Secretary Of The Army Initiator for use in laser beam ignition of solid propellants
US4144814A (en) * 1976-07-08 1979-03-20 Systems, Science And Software Delay detonator device
DE3113406A1 (en) * 1981-04-03 1982-12-16 Bundesrepublik Deutschland, vertreten durch den Bundesminister der Verteidigung, dieser vertreten durch den Präsidenten des Bundesamtes für Wehrtechnik und Beschaffung, 5400 Koblenz Firing chain for propulsion charges of tube weapons

Also Published As

Publication number Publication date
EP0275429A1 (en) 1988-07-27
DE3642942A1 (en) 1988-06-30
US4850274A (en) 1989-07-25
DE3770260D1 (en) 1991-06-27

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