EP0215829A1 - Propulsion means for reducing the base drag. - Google Patents

Propulsion means for reducing the base drag.

Info

Publication number
EP0215829A1
EP0215829A1 EP86901397A EP86901397A EP0215829A1 EP 0215829 A1 EP0215829 A1 EP 0215829A1 EP 86901397 A EP86901397 A EP 86901397A EP 86901397 A EP86901397 A EP 86901397A EP 0215829 A1 EP0215829 A1 EP 0215829A1
Authority
EP
European Patent Office
Prior art keywords
ignition
propellant charge
propellant
propulsion means
reducing
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.)
Granted
Application number
EP86901397A
Other languages
German (de)
French (fr)
Other versions
EP0215829B1 (en
Inventor
Willi Luebbers
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.)
Nico Pyrotechnik Hanns Juergen Diederichs GmbH and Co KG
Original Assignee
Nico Pyrotechnik Hanns Juergen Diederichs GmbH and Co KG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Nico Pyrotechnik Hanns Juergen Diederichs GmbH and Co KG filed Critical Nico Pyrotechnik Hanns Juergen Diederichs GmbH and Co KG
Priority to AT86901397T priority Critical patent/ATE75031T1/en
Publication of EP0215829A1 publication Critical patent/EP0215829A1/en
Application granted granted Critical
Publication of EP0215829B1 publication Critical patent/EP0215829B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/38—Range-increasing arrangements
    • F42B10/40—Range-increasing arrangements with combustion of a slow-burning charge, e.g. fumers, base-bleed projectiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02—Cartridges, i.e. cases with charge and missile
    • F42B5/16—Cartridges, i.e. cases with charge and missile characterised by composition or physical dimensions or form of propellant charge, with or without projectile, or powder

Definitions

  • the invention relates to a propellant for reducing ground suction for an artillery projectile according to the preamble of patent claim 1.
  • Such propellant charges reduce the ground suction occurring in a flying projectile by pyrotechnic gas generation and thereby increase the projectile range.
  • a propellant charge base bleed effect
  • an artillery projectile of the caliber can travel 155 mm distances of over 30 km.
  • the propellants have an ignition device which is activated by the hot propellant gases when the projectile is fired and which in turn ignites the base bleed propellant. With conventional propellants, it has been observed that this ignition process does not take place with sufficient reliability.
  • a propellant charge is already known from DE patent application P 34 37 250.4, in which, in order to improve the ignition process, the wall of the propellant charge delimiting the ignition channel has an ignition-enhancing layer or a roughened structure designed to enlarge the surface.
  • the invention is based on the object of specifying an alternative, further improved solution for safely mastering the ignition problem.
  • Fig. 2 the rear part of a projectile in longitudinal section with a further embodiment of the invention.
  • Fig. 1 shows the rear end of an artillery projectile 12, which can be fired by guns, such as field howitzers, self-propelled howitzers or mortars.
  • the projectile 12 comprises a propellant charge 1 reducing the bottom suction in a screw-on base piece 12a with a cavity serving as the combustion chamber 15.
  • This propellant charge 1 comprises a centrally axially arranged ignition channel 4 which, for reasons of safe handling, is initially closed by a rupture disk 14 which however, when the projectile 12 is fired from a weapon barrel (not shown), it is destroyed by the hot propellant gases that are produced in the process,
  • an ignition device 16 is arranged, the ignition charge 16c of which after the destruction of the rupture disk 14 is also ignited by the hot propellant gases and now in turn by means of ignition openings 16b the inner surface la of the propellant charge 1 for the purpose of igniting it with hot gases acted upon.
  • the edge surface la of the propellant charge 1 surrounding the ignition channel 4 is conically narrowed in the rear direction. It is thereby achieved that the hot gases emerging from the ignition opening 16b and produced by the lighting device 16 can ignite the propellant charge 1 better, because gas clouds not only strike the edge surface la tangentially.
  • steps 1b (FIG. 2) which are still stepped are arranged in the conically narrowed edge surface 1a. These paragraphs 1b further improve the ignition characteristic of the propellant charge 1, since the ignition gases emerging from the ignition openings 16b are caught in the annular edges formed by the paragraphs 1b and thus a better opportunity. to ignite the propellant charge 1.
  • At least some of the ignition openings 16b in the housing 16a of the ignition device 16 are arranged at an angle with respect to the longitudinal axis 100 of the propellant charge 1, in such a way that they are more or less aligned with the edge surface la of the propellant charge 1 . This results in a further improvement in the ignitability of the propellant charge 1, since the surface la is now blown directly from the ignition openings 16b.

Landscapes

  • General Engineering & Computer Science (AREA)
  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Air Bags (AREA)
  • Medicines Containing Plant Substances (AREA)
  • Earth Drilling (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Braking Arrangements (AREA)
  • Golf Clubs (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Ultra Sonic Daignosis Equipment (AREA)
  • Sealing With Elastic Sealing Lips (AREA)
  • Investigation Of Foundation Soil And Reinforcement Of Foundation Soil By Compacting Or Drainage (AREA)
  • Excavating Of Shafts Or Tunnels (AREA)
  • Superconductors And Manufacturing Methods Therefor (AREA)
  • Feeding, Discharge, Calcimining, Fusing, And Gas-Generation Devices (AREA)
  • Control Of The Air-Fuel Ratio Of Carburetors (AREA)
  • Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
  • Vending Machines For Individual Products (AREA)
  • Catching Or Destruction (AREA)
  • Disintegrating Or Milling (AREA)
  • Spark Plugs (AREA)

Abstract

Le moyen de propulsion (1) pour réduire la trainée de culot d'un engin ballistique (12) est constitué d'un canal central d'allumage (4) et d'un dispositif d'allumage (16). Afin d'améliorer la susceptibilité d'allumage du moyen de propulsion (1) la surface (1a) délimitant le canal central (4) présente une forme conique se resserrant vers l'arrière. En outre, la surface (1) présente des gradins (1b). Enfin, la boîte (16a) du dispositif d'allumage (16) est pourvue de canaux d'allumage (16b) disposés de façon inclinée par rapport à l'axe longitudinal (100).The propulsion means (1) for reducing the base drag of a ballistic vehicle (12) consists of a central ignition channel (4) and an ignition device (16). In order to improve the ignition susceptibility of the propulsion means (1) the surface (1a) delimiting the central channel (4) has a conical shape tightening towards the rear. In addition, the surface (1) has steps (1b). Finally, the box (16a) of the ignition device (16) is provided with ignition channels (16b) arranged in an inclination relative to the longitudinal axis (100).

Description

Treibsatz zur Bodensogreduzierung Propellant to reduce soil suction
Die Erfindung b et r i f f t einen Treibsatz zur Bodensogreduzierung für ein Artilleriegeschoß nach dem Oberbegriff des Patentanspruchs 1.The invention relates to a propellant for reducing ground suction for an artillery projectile according to the preamble of patent claim 1.
Derartige Treibsätze verringern durch pyrotechnische Gaserzeugung den bei einen, fliegenden Geschoß auftretenden Bodensog und vergrößern dadurch die Geschoßreichweite. Beispielsweise kann mit einem solchen Treibsatz (base bleed-Effekt) ein Artilleriegeschoß des Kalibers 155 mm Entfernungen von über 30 km zurücklegen. Die Treibsätze verfügen über eine Anzündeinrich tung, die beim Abfeuern des Geschosses von den heißen Treibladungsgasen aktiviert wird und ihrerseits den base bleed-Treibsatz anzündet. Bei herkömmlichen Treibsätzen wurde beobachtet, daß dieser Anzündvorgang nicht mit hinreichend großer Zuverlässigkeit erfolgt.Such propellant charges reduce the ground suction occurring in a flying projectile by pyrotechnic gas generation and thereby increase the projectile range. For example, with such a propellant charge (base bleed effect) an artillery projectile of the caliber can travel 155 mm distances of over 30 km. The propellants have an ignition device which is activated by the hot propellant gases when the projectile is fired and which in turn ignites the base bleed propellant. With conventional propellants, it has been observed that this ignition process does not take place with sufficient reliability.
Aus der DE-Patentanmeldung P 34 37 250.4 ist schon ein Treibsatz bekannt, bei dem zur Verbesserung des Anzündvorgangs, die den Zündkanal begrenzende Wand des Treibsatzes eine anzündverstärkende Schicht oder eine oberflächenvergrößernd ausgebildete, aufgerauhte Struktur aufweist. Der Erfindung l iegt d ie Aufgabe zugrunde, eine alternative, weiter verbesserte Lösung zur sicheren Beherrschung des Anzündproblems anzugeben.A propellant charge is already known from DE patent application P 34 37 250.4, in which, in order to improve the ignition process, the wall of the propellant charge delimiting the ignition channel has an ignition-enhancing layer or a roughened structure designed to enlarge the surface. The invention is based on the object of specifying an alternative, further improved solution for safely mastering the ignition problem.
Diese Aufgabe wird durch das im kennzeichnenden Teil des Patentanspruchs 1 angegebene Merkmal gelöst.This object is achieved by the feature specified in the characterizing part of patent claim 1.
Vorteilhafte Ausgestaltungen und Weiterbildungen der Erfindung gehen aus den Unteransprüchen hervor.Advantageous refinements and developments of the invention emerge from the subclaims.
Die Erfindung wird nachfolgend unter Bezug auf die Zeichnung näher erläutert. Dabei zeigt:The invention is explained in more detail below with reference to the drawing. It shows:
Fig. 1: den Heckteil eines Geschosses im Läng s schn it t mit einem ersten Ausführungsbeispiel der Erfindung;1: the rear part of a projectile in the longitudinal direction s cuts with a first exemplary embodiment of the invention;
Fig. 2: den Heckteil eines Geschosses im Längschnitt mit einem weiteren Ausführungsbeispiel der Erfindung.Fig. 2: the rear part of a projectile in longitudinal section with a further embodiment of the invention.
Fig. 1 zeigt das heckseitige Ende eines Artilleriegeschosses 12, das von Rohrwaffen, wie Feldhaubitzen, Panzerhaubitzen oder Mörsern verschießbar ist. Das Geschoß 12 umfaßt einen in einem aufschraubbaren Bodenstück 12a mit einem als Brennkammer 15. dienenden Hohlraum einen den Bodensog reduzierenden Treibsatz 1. Dieser Treibsatz 1 umfaßt einen zentralaxial angeordneten Zündkanal 4, der aus Gründen der sicheren Handhabung zunächst durch eine Berstscheibe 14 verschlossen ist, die jedoch beim Abfeuern des Geschosses 12 aus einem nicht dargestellten Waffenrohr durch die dabei entstehenden heißen Treibladungsgase zerstört wird, An der vorderen Stirnfläche des Anzündkan al s 4 ist eine Anzünde inrichtung 16 angeordnet, deren Anzündladung 16c nach Zerstörung der Berstscheibe 14 ebenfalls durch die heißen Treibladuugsgase angezündet wird und nun ihrerseits vermittels Anzündöffnungen 16b die innere Oberfläche la des Treibsatzes 1 zwecks dessen Anzündung mit heißen Gasen beaufschlagt.Fig. 1 shows the rear end of an artillery projectile 12, which can be fired by guns, such as field howitzers, self-propelled howitzers or mortars. The projectile 12 comprises a propellant charge 1 reducing the bottom suction in a screw-on base piece 12a with a cavity serving as the combustion chamber 15. This propellant charge 1 comprises a centrally axially arranged ignition channel 4 which, for reasons of safe handling, is initially closed by a rupture disk 14 which however, when the projectile 12 is fired from a weapon barrel (not shown), it is destroyed by the hot propellant gases that are produced in the process, On the front end face of the ignition channel 4, an ignition device 16 is arranged, the ignition charge 16c of which after the destruction of the rupture disk 14 is also ignited by the hot propellant gases and now in turn by means of ignition openings 16b the inner surface la of the propellant charge 1 for the purpose of igniting it with hot gases acted upon.
Um die Anzündempfindlichkeit des Treibsatzes 1 zu verbessern, ist erfindungsgemäß die den Zündkanal 4 umschließende Randfläche la des Treibsatzes 1 in Heckrichtung konisch verengt ausgebildet. Dadurch wird erreicht, daß die aus der Anzündöffnung 16b austretenden, von der Anzünde inrichtung 16 erzeugten heißen Gase den Treibsatz 1 besser entzünden können, weil nämlich Gasschwaden nicht nur tangential streifend auf die Randfläche la auftreffen.In order to improve the ignition sensitivity of the propellant charge 1, the edge surface la of the propellant charge 1 surrounding the ignition channel 4 is conically narrowed in the rear direction. It is thereby achieved that the hot gases emerging from the ignition opening 16b and produced by the lighting device 16 can ignite the propellant charge 1 better, because gas clouds not only strike the edge surface la tangentially.
In einer vorteilhaften Ausgestaltung der Erfindung sind in der konusförmig verengten Randfläche la noch stufenförmig verlaufende Absätze 1b (Fig. 2) angeordnet. Durch diese Absätze 1b wird die Anz'dndwil 1 igkei t des Treibsatzes 1 noch weiter verbessert, da sich in den von den Absätzen 1b gebildeten, ringförmig umlaufenden Kanten die aus den Anzündöffnungen 16b austretenden Anzündgase verfangen und so eine bessere Gelegenheit. zur Anzündung des Treibsatzes 1 haben.In an advantageous embodiment of the invention, steps 1b (FIG. 2) which are still stepped are arranged in the conically narrowed edge surface 1a. These paragraphs 1b further improve the ignition characteristic of the propellant charge 1, since the ignition gases emerging from the ignition openings 16b are caught in the annular edges formed by the paragraphs 1b and thus a better opportunity. to ignite the propellant charge 1.
In einer vorteilhaften Weiterbildung der Erfindung sind mindestens einige der Anzündöffnungen 16b im Gehäuse 16a der Anzündeinr icht ung 16 winklig in Bezug auf die Längsachse 100 des Treibsatzes 1 angeordnet, und zwar derart, daß sie mehr oder weniger auf die Randfläche la des Treibsatzes 1 ausgerichtet sind. Dadurch ergibt sich eine weitere Verbesserung der Zündwilligkeit des Treibsatzes 1, da nunmehr die Oberfläche la aus den Anzündöffnungen 16b unmittelbar angeblasen wird.In an advantageous development of the invention, at least some of the ignition openings 16b in the housing 16a of the ignition device 16 are arranged at an angle with respect to the longitudinal axis 100 of the propellant charge 1, in such a way that they are more or less aligned with the edge surface la of the propellant charge 1 . This results in a further improvement in the ignitability of the propellant charge 1, since the surface la is now blown directly from the ignition openings 16b.
Es ist selbstverständlich möglich, die in Fig. 1 und Fig. 2 dargestellten Ausführungsformen der Erfindung noch mit der aus der DE-Patentanmeldung P 34 37 250.4 offenbarten Lehre zu kombinieren, also beispielsweise die erfindungsgemäß ausgestaltete Randfläche la noch mit einer aufgerauhten Struktur oder aber mit einer anzündverstärkenden Schicht zu versehen. It is of course possible to combine the embodiments of the invention shown in FIGS. 1 and 2 with the teaching disclosed in DE patent application P 34 37 250.4, for example the edge surface la designed according to the invention still with a roughened structure or with to provide an ignition-enhancing layer.

Claims

P a t e n t a n s p r ü c h e Patent claims
1. Treibsatz zur Bodensogreduzierung für ein Geschoß mit einem zentral angeordneten Zündkanal und einer Anzündeinrichtung, d a d u r c h g e k e n n z e i c h n e t, daß die den Zündkanal (4) umschließende Randfläche (la) des Treibsatzes (1) sich in Heckrichtung konisch verengend ausgebildet ist.1. Propellant for reducing soil suction for a projectile with a centrally arranged ignition channel and an ignition device, so that the peripheral surface (la) of the propellant charge (1) surrounding the ignition channel (4) is conically narrowing in the rear direction.
2. Treibsatz nach Anspruch 1, d a d u r c h g e k e n n z e i c h n e t, daß in der Randfläche (la) stufenförmige Absätze (lb) angeordnet sind.2. Propellant charge according to claim 1, d a d u r c h g e k e n n z e i c h n e t that step-shaped shoulders (lb) are arranged in the edge surface (la).
3. Treibsatz nach einem der Ansprüche 1 und 2, d a d u r c h g e k e n n z e i c h n e t, daß die im Gehäuse (16a) der Anzünde inrichtung (16) angeordneten Anzündöffnungen (16b) winklig in Bezug auf die Längsachse (100) des Treibsatzes (1) angeordnet sind. 3. Propellant charge according to one of claims 1 and 2, so that the ignition openings (16) arranged in the housing (16a) of the ignition device (16) are arranged at an angle with respect to the longitudinal axis (100) of the propellant charge (1).
EP86901397A 1985-03-22 1986-02-25 Propulsion means for reducing the base drag Expired - Lifetime EP0215829B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT86901397T ATE75031T1 (en) 1985-03-22 1986-02-25 FUEL FOR SOIL REDUCTION.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3510446 1985-03-22
DE19853510446 DE3510446A1 (en) 1985-03-22 1985-03-22 DRIVE SET FOR SOIL REDUCTION

Publications (2)

Publication Number Publication Date
EP0215829A1 true EP0215829A1 (en) 1987-04-01
EP0215829B1 EP0215829B1 (en) 1992-04-15

Family

ID=6266060

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86901397A Expired - Lifetime EP0215829B1 (en) 1985-03-22 1986-02-25 Propulsion means for reducing the base drag

Country Status (16)

Country Link
US (1) US4754704A (en)
EP (1) EP0215829B1 (en)
JP (1) JPS62501030A (en)
AT (1) ATE75031T1 (en)
AU (1) AU580860B2 (en)
CA (1) CA1271083A (en)
DE (2) DE3510446A1 (en)
DK (1) DK448486A (en)
ES (1) ES8707607A1 (en)
FI (1) FI864530A (en)
GR (1) GR860347B (en)
IL (1) IL78035A0 (en)
NO (1) NO158273C (en)
NZ (1) NZ215536A (en)
WO (1) WO1986005581A1 (en)
ZA (1) ZA861796B (en)

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US6727485B2 (en) * 2001-05-25 2004-04-27 Omnitek Partners Llc Methods and apparatus for increasing aerodynamic performance of projectiles
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US7802520B2 (en) * 2007-07-25 2010-09-28 Martin Electronics Drag minimizing projectile delivery system
KR101153989B1 (en) 2009-11-16 2012-06-08 한국항공대학교산학협력단 Hybrid rocket fuel with grain port of tapered shape
KR100968878B1 (en) * 2010-04-02 2011-05-31 (주)제이제이테크 Propellant disposal device for propulsion system
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Also Published As

Publication number Publication date
NO158273C (en) 1988-08-10
NO863940D0 (en) 1986-10-03
AU580860B2 (en) 1989-02-02
CA1271083A (en) 1990-07-03
JPH0411800B2 (en) 1992-03-02
NO863940L (en) 1986-10-03
DK448486A (en) 1986-11-03
ES8707607A1 (en) 1987-08-16
GR860347B (en) 1986-06-26
ATE75031T1 (en) 1992-05-15
AU5543386A (en) 1986-10-13
FI864530A0 (en) 1986-11-07
ES553068A0 (en) 1987-08-16
DK448486D0 (en) 1986-09-18
ZA861796B (en) 1986-11-26
NO158273B (en) 1988-05-02
WO1986005581A1 (en) 1986-09-25
NZ215536A (en) 1987-11-27
US4754704A (en) 1988-07-05
IL78035A0 (en) 1986-07-31
EP0215829B1 (en) 1992-04-15
DE3510446A1 (en) 1986-09-25
DE3684843D1 (en) 1992-05-21
FI864530A (en) 1986-11-07
JPS62501030A (en) 1987-04-23

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