EP0215829B1 - Propulsion means for reducing the base drag - Google Patents

Propulsion means for reducing the base drag Download PDF

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Publication number
EP0215829B1
EP0215829B1 EP86901397A EP86901397A EP0215829B1 EP 0215829 B1 EP0215829 B1 EP 0215829B1 EP 86901397 A EP86901397 A EP 86901397A EP 86901397 A EP86901397 A EP 86901397A EP 0215829 B1 EP0215829 B1 EP 0215829B1
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EP
European Patent Office
Prior art keywords
ignition
propellant charge
pct
charge
projectile
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
EP86901397A
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German (de)
French (fr)
Other versions
EP0215829A1 (en
Inventor
Willi Lübbers
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.)
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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

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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 soil suction for an artillery projectile according to the preamble of patent claim 1.
  • Such propellants are known for example from GB-A-1 507 865. By pyrotechnic gas generation, they reduce the floor suction that occurs with a flying projectile 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 a sufficiently high degree of 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 tube which can be closed by a slide. So that the slide can be arranged movably, the load has a step-shaped recess.
  • the invention has for its object to provide an alternative, further improved solution for safely mastering the ignition problem.
  • Fig. 1 shows the rear end of an artillery projectile 12, which can be fired by guns, such as 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 a combustion chamber 15.
  • This propellant charge 1 comprises a centrally axially arranged ignition channel 4, which is initially closed by a rupture disk 14 for reasons of safe handling, which, however when the projectile 12 is fired from a weapon barrel (not shown) is destroyed by the hot propellant gases which are produced in the process.
  • An ignition device 16 is arranged on the front end face of the ignition channel 4, the ignition charge 16c of which, after the bursting disk 14 has been destroyed, is also ignited by the hot propellant charge gases and now in turn acts on the inner surface 1a of the propellant charge 1 by means of ignition openings 16b for the purpose of igniting it with hot gases.
  • the edge surface 1a 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 generated by the ignition device 16 can ignite the propellant charge 1 better, because gas vapors not only strike the edge surface 1a in a tangential manner.
  • steps 1b (FIG. 2) which are still stepped are arranged in the conically narrowed edge surface 1a. These paragraphs 1b further improve the willingness to ignite 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 have 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 1a of the propellant charge 1.

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  • 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

PCT No. PCT/EP86/00095 Sec. 371 Date Nov. 21, 1986 Sec. 102(e) Date Nov. 21, 1986 PCT Filed Mar. 25, 1986 PCT Pub. No. WO86/05581 PCT Pub. Date Sep. 25, 1986.A propellant charge for the reduction of base eddying or drag of a shell 12 with a centrally disposed ignition conduit and an ignition device for the charge disposed in the conduit. To improve the ignition readiness of the propellant charge, the inner surface of the propellant charge, which surrounds the ignition conduit, is formed so that it conically narrows in the aft direction. Additionally, the inner surface of the propellant charge may be provided with stepped sections. Finally, the ignition conduits disposed in the housing of the ignition device may be disposed at an angle relative to the longitudinal axis of the propellant charge so that they face the inner surface thereof.

Description

Die Erfindung betrifft einen Treibsatz zur Bodensogreduzierung für ein Artilleriegeschoß nach dem Oberbegriff des Patentanspruchs 1.The invention relates to a propellant for reducing soil suction for an artillery projectile according to the preamble of patent claim 1.

Derartige Treibsätze sind beispielsweise aus der GB-A-1 507 865 bekannt. Sie verringern durch pyrotechnische Gaserzeugung den bei einem 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 Anzündeinrichtung, 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 propellants are known for example from GB-A-1 507 865. By pyrotechnic gas generation, they reduce the floor suction that occurs with a flying projectile 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 a sufficiently high degree of 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 ausgebildte, aufgerauhte Struktur aufweist.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.

Aus der GB-A-2 131 926 ist ferner eine Anordnung zur Bodensogreduzierung bekannt, bei der die Ladung ebenfalls ringförmig ausgebildet ist, und bei der ein als Rohr ausgebildetes Druckreduzierbauteil die Ladung axial durchsetzt und eine Vielzahl von Düsen aufweist. Durch die Vielzahl der Düsen in dem Rohr, das einen Hochdruckraum von einem Niederdruckraum abgrenzt, soll am Geschoßheck ein relativ weicher Gasstrahl austreten.From GB-A-2 131 926 an arrangement for soil suction reduction is also known, in which the charge is also ring-shaped, and in which a pressure-reducing component in the form of a tube penetrates the charge axially and has a plurality of nozzles. Due to the large number of nozzles in the tube, which delimits a high-pressure chamber from a low-pressure chamber, a relatively soft gas jet should emerge from the rear of the projectile.

In einem Ausführungsbeispiel wird vorgeschlagen, in dem Rohr relativ große Anzündöffnungen vorzusehen, die durch einen Schieber verschließbar sind. Damit der Schieber beweglich angeordnet werden kann, weist die Ladung eine stufenförmige Ausnehmung auf.In one embodiment, it is proposed to provide relatively large ignition openings in the tube, which can be closed by a slide. So that the slide can be arranged movably, the load has a step-shaped recess.

Nachteilig ist bei dieser Anordnung vor allem der relativ große Aufwand, der mit der Herstellung des Treibsatzes verbunden ist.The disadvantage of this arrangement is, above all, the relatively large outlay associated with the production of the propellant charge.

Der Erfindung liegt die Aufgabe zugrunde, eine alternative, weiter verbesserte Lösung zur sicheren Beherrschung des Anzündproblems anzugeben.The invention has for its object to provide 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:

Fig. 1:
den Heckteil eines Geschosses im Längsschnitt mit einem ersten Ausführungsbeispiel der Erfindung;
Fig. 2:
den Heckteil eines Geschosses im Längschnitt mit einem weiteren Ausführungsbeispiel der Erfindung.
The invention is explained in more detail below with reference to the drawing. It shows:
Fig. 1:
the rear part of a projectile in longitudinal section with a first embodiment of the invention;
Fig. 2:
the rear part of a floor 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 Anzündkanals 4 ist eine Anzündeinrichtung 16 angeordnet, deren Anzündladung 16c nach Zerstörung der Berstscheibe 14 ebenfalls durch die heißen Treibladungsgase angezündet wird und nun ihrerseits vermittels Anzündöffnungen 16b die innere Oberfläche 1a 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 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 a combustion chamber 15. This propellant charge 1 comprises a centrally axially arranged ignition channel 4, which is initially closed by a rupture disk 14 for reasons of safe handling, which, however when the projectile 12 is fired from a weapon barrel (not shown) is destroyed by the hot propellant gases which are produced in the process. An ignition device 16 is arranged on the front end face of the ignition channel 4, the ignition charge 16c of which, after the bursting disk 14 has been destroyed, is also ignited by the hot propellant charge gases and now in turn acts on the inner surface 1a of the propellant charge 1 by means of ignition openings 16b for the purpose of igniting it with hot gases.

Um die Anzündempfindlichkeit des Treibsatzes 1 zu verbessern, ist erfindungsgemäß die den Zündkanal 4 umschließende Randfläche 1a des Treibsatzes 1 in Heckrichtung konisch verengt ausgebildet. Dadurch wird erreicht, daß die aus der Anzündöffnung 16b austretenden, von der Anzündeinrichtung 16 erzeugten heißen Gase den Treibsatz 1 besser entzünden können, weil nämlich Gasschwaden nicht nur tangential streifend auf die Randfläche 1a auftreffen.In order to improve the ignition sensitivity of the propellant charge 1, the edge surface 1a 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 generated by the ignition device 16 can ignite the propellant charge 1 better, because gas vapors not only strike the edge surface 1a in a tangential manner.

In einer vorteilhaften Ausgestaltung der Erfindung sind in der konusförmig verengten Randfläche 1a noch stufenförmig verlaufende Absätze 1b (Fig. 2) angeordnet. Durch diese Absätze 1b wird die Anzündwilligkeit 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 willingness to ignite 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 have 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 Anzündeinrichtung 16 winklig in Bezug auf die Längsachse 100 des Treibsatzes 1 angeordnet, und zwar derart, daß sie mehr oder weniger auf die Randfläche 1a des Treibsatzes 1 ausgerichtet sind.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 1a of the propellant charge 1.

Dadurch ergibt sich eine weitere Verbesserung der Zündwilligkeit des Treibsatzes 1, da nunmehr die Oberfläche 1a aus den Anzündöffnungen 16b unmittelbar angeblasen wird.This results in a further improvement in the ignitability of the propellant charge 1, since the surface 1a 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 1a 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 1a designed according to the invention still with a roughened structure or with to provide an ignition-enhancing layer.

Claims (3)

  1. Propellant charge for reducing the base drag of a projectile (12) having a central ignition channel (4) and an ignition device (16), which located in the forward end surface of the ignition channel (4) facing the nose of the projectile characterised by the fact that the peripheral surface (1a) of the propellant charge (1) surrounding the ignition channel (4) tapers conically in the direction of the tail of the projectile.
  2. Propellant charge in accordance with Claim 1, characterised by the fact that steps (1b) are provided in the peripheral surface (1a).
  3. Propellant charge in accordance with one of Claims 1 and 2, characterised by the fact that the ignition channels (16b) are provided in a housing (16a) of the ignition device (16) and are positioned at an angle in relation 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 EP0215829A1 (en) 1987-04-01
EP0215829B1 true EP0215829B1 (en) 1992-04-15

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ID=6266060

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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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US6530327B2 (en) * 2001-04-23 2003-03-11 Dmd Systems, Llc Method and apparatus for burning pyrotechnic compositions
US6727485B2 (en) * 2001-05-25 2004-04-27 Omnitek Partners Llc Methods and apparatus for increasing aerodynamic performance of projectiles
US7150232B1 (en) 2001-05-25 2006-12-19 Omnitek Partners Llc Methods and apparatus for increasing aerodynamic performance of projectiles
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
FR2997179B1 (en) * 2012-10-22 2015-01-16 Roxel France COMBINED DEVICE FOR DRIVING TRAJECTORY AND TRAINING REDUCTION.
WO2014125335A1 (en) 2013-02-15 2014-08-21 Freescale Semiconductor, Inc. Search method and apparatus for a communication system
US10852106B2 (en) * 2014-08-22 2020-12-01 Meals, Llc Firearm ammunition with projectile housing propellant

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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
EP0215829A1 (en) 1987-04-01
DE3510446A1 (en) 1986-09-25
DE3684843D1 (en) 1992-05-21
FI864530A (en) 1986-11-07
JPS62501030A (en) 1987-04-23

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