EP0220218A1 - Payload spin-stabilized projectile with propelling charge. - Google Patents

Payload spin-stabilized projectile with propelling charge.

Info

Publication number
EP0220218A1
EP0220218A1 EP86902375A EP86902375A EP0220218A1 EP 0220218 A1 EP0220218 A1 EP 0220218A1 EP 86902375 A EP86902375 A EP 86902375A EP 86902375 A EP86902375 A EP 86902375A EP 0220218 A1 EP0220218 A1 EP 0220218A1
Authority
EP
European Patent Office
Prior art keywords
projectile
payload
detonator
head
pressure
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
EP86902375A
Other languages
German (de)
French (fr)
Other versions
EP0220218B1 (en
Inventor
Wolfgang Meffert
Karl-Heinz Silligmann
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.)
Rheinmetall Industrie AG
Original Assignee
Rheinmetall GmbH
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 Rheinmetall GmbH filed Critical Rheinmetall GmbH
Publication of EP0220218A1 publication Critical patent/EP0220218A1/en
Application granted granted Critical
Publication of EP0220218B1 publication Critical patent/EP0220218B1/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
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
    • F42B12/62—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected parallel to the longitudinal axis of the projectile
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/02—Fuze bodies; Fuze housings

Definitions

  • the invention relates to a spin-stabilized projectile with a payload that can be ejected according to the preamble of patent claim 1.
  • the invention has for its object to improve the floor structure of a swirl-stabilized payload projectile in such a way that despite the higher ejection pressure required for an ejection process, the detonator arranged in the head of the projectile is not unduly loaded.
  • FIG. 1 shows a schematic sectional illustration of a conventional spin-stabilized payload projectile
  • Fig. 1 shows a schematic representation, partly in longitudinal section, of a conventional spin-stabilized payload projectile 10, which comprises an essentially hollow-cylindrical casing 11 and a floor 12 connected to this casing 11 in a rotationally fixed manner.
  • Payloads 13, which are ejected at a certain point in the trajectory by an ejection charge 15, which is in turn initiated by a detonator 14 arranged in the head of the projectile 10, are arranged in a tight packing one above the other in the casing 11.
  • a mechanically firmer connection between the floor 12 and the shell 11 must be provided in newly developed spin-stabilized payload projectiles with much more massive rear parts are, for the separation of which much stronger ejection charges 15 are required.
  • a pressure-reducing element 20 is arranged between the head igniter 14 and the discharge charge 15, as can be seen from FIG. 2. This pressure-reducing element 20 seals - at least to a large extent - the charge space of the discharge charge 15 towards the head igniter 14, so that no inadmissible pressurization of the head igniter 14 occurs.
  • the pressure-reducing element 20 is designed in the shape of a truncated cone or truncated cone and is arranged between the igniter 14 and the discharge charge 15 on the longitudinal axis of the projectile 10 such that the base of the cone or truncated cone is adjacent to the igniter 14, while the tip of the cone or truncated cone is directed towards the discharge charge 15.
  • An opening 20a is arranged in the tip of the cone or truncated cone of the pressure-reducing element 20, through which an ignition jet for acting on the ejection charge 15 passes when the head igniter 14 is initiated.
  • the discharge nozzle 15a After the discharge charge 15 has been ignited, a rapidly increasing pressure develops in the discharge nozzle 15a, which abruptly deforms the conical or truncated cone-shaped, pressure-reducing element 20 and compresses it into an essentially closed disc, which - at least for a short time - is pressure-resistant Concludes between igniter 14 and the pressurized payload space 16. Due to this pressure-proof seal, the ejection process of the payloads 13 can proceed unhindered, without the leakage or expulsion of the igniter 14, for example gas pressure necessary for separating the floor and expelling the payloads is reduced.
  • the measure provided according to the invention is particularly simple and inexpensive to carry out, so that u. If necessary, even store floors that have already been stored in depots.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Toys (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Infusion, Injection, And Reservoir Apparatuses (AREA)

Abstract

Un projectile (10) gyrostabilisé à charge utile comprend dans sa partie antérieure une charge d'éjection (15) activée par un détonateur de tête (14) avec un certain retard pour séparer un culot connecté à l'enveloppe (11) du projectile et pour éjecter une charge utile (13). Afin d'éviter que le détonateur de tête (14) ne soit endommagé par la pression des gaz générés par la charge d'éjection (15), un disque conique en tôle (20) est agencé entre le détonateur de tête (14) et la charge utile, sa base étant tournée du côté du détonateur de tête (14) et sa pointe du côté de la charge d'éjection (15). La pointe du disque conique (20) est pourvue d'une ouverture (20a) à travers laquelle passe un jet détonateur émis par le détonateur de tête (14) afin d'activer la charge d'éjection (15). Une fois la charge d'éjection (15) activée, le disque conique (20) se transforme en un disque plat essentiellement étanche aux gaz.A payload gyro-stabilized projectile (10) comprises in its front part an ejection charge (15) activated by a head detonator (14) with a certain delay to separate a base connected to the shell (11) of the projectile and to eject a payload (13). In order to prevent the head detonator (14) from being damaged by the pressure of the gases generated by the ejection charge (15), a conical sheet metal disc (20) is arranged between the head detonator (14) and the payload, its base being turned towards the leading detonator (14) side and its tip towards the ejection charge side (15). The tip of the conical disc (20) is provided with an opening (20a) through which passes a detonator jet emitted by the head detonator (14) in order to activate the ejection charge (15). Once the ejection charge (15) is activated, the conical disc (20) transforms into a substantially gas-tight flat disc.

Description

Drallstabilisiertes Nutzlastgeschoss mit AusstossladungSwirl-stabilized payload projectile with ejection charge
Die Erfindung betrifft ein drallstabilisiertes Geschoß mi ausstoßbarer Nutzlast nach dem Oberbegriff des Patentanspruchs 1.The invention relates to a spin-stabilized projectile with a payload that can be ejected according to the preamble of patent claim 1.
Ein derartiges Geschoß ist aus dem Waffentechnischen Taschenbuch der Firma Rheinmetall, 4. Auflage 1977, Seite 491 ff, bekannt.Such a projectile is known from the Rheinmetall Weapons Technical Paperback, 4th edition 1977, pages 491 ff.
Bei herkömmlichen drallstabilisierten Geschossen mit ausstoßbarer Nutzlast erfolgt die Übertragung der Beschleunigungskräfte im wesentlichen auch über den Geschoßboden, wobei die Drehbeschleunigung über eine geeignete drehfeste Verbindung zwischen Boden und Geschoßhülle, z. B. ein Gewinde oder Stifte übertragen wird. Zur Einleitung des Ausstoßvorgangs der Nutzlast wird von einem Kopfzünder eine Ausstoßladung initiiert, die im Innern der Geschoßhülle einen Druck aufbaut, der zunächst den Geschoßboden absprengt und dann die einzelnen Nutzlasten nacheinander ausstößt. Da bei herkömmlichen dral Istabi liserten Geschossen die Massenträgheitsmomente der Geschoßböden verhältnismäßig gering waren, wurden zu ihrer Abtrennung bei Einleitung der Ausstoßphase relativ geringe Kräfte benötigt, die von den herkömmlichen eingeführten Kopfzündern ohne Hervorrufen einer Fehlfunktion aufgenommen werden konnten. In jüngster Zeit werden re i chwe i t eng es t e iger t e drallstabilisierte Geschosse entwickelt und eingeführt, die im Vergleich zu herkömmlichen Geschoßböden ein wesentlich längeres und schwereres Heckteil aufweisen, da in diesem Hecktei l ein zur Reichweitenvergrößerung erforderlicher Treibsatz untergebracht ist. Dieser Treibsatz wird beim Abfeuerungsvorgang von der Treibladung entzündet und reduziert während des Geschoßflugs den reichweitenverkürzenden Bodensog. Die Massenträgheitsmomente derart vergrößerter Geschoßheckteile sind z. T. um ein Vielfaches höher als herkömmlicherweise üblich, so daß zwischen diesen neuartigen Geschoßböden und der Geschoßhülle mechanisch stärker belastbare Verbindungen vorgesehen werden müssen. Dies ist aber andererseits nachteilig, da beim Ausstoßvorgang durch eine stärkere Ausstoßladung wesentlich höhere Kräfte aufgebracht werden müssen, um den Geschoßboden abtrennen zu können. Es hat sich herausgestellt, daß diese höheren Kräfte den herkömmlichen Kopfzünder in nachteiliger Weise beeinflussen, so daß es zu Versagern kommt und die Nutzlast nicht in der erwarteten Weise ausgestoßen wird.In conventional spin-stabilized projectiles with ejectable payload, the transmission of the acceleration forces takes place essentially also over the floor, the rotational acceleration via a suitable non-rotatable connection between the floor and the shell, z. B. a thread or pins is transferred. To initiate the ejection process of the payload, an ejection charge is initiated by a head detonator, which builds up a pressure inside the shell, which first blows off the floor and then ejects the individual payloads one after the other. Since the mass moments of inertia of the floors were relatively low in conventional dral Istabi lisert projectiles, relatively small forces were required to separate them when the ejection phase was initiated, which could be absorbed by the conventional head igniters introduced without causing a malfunction. More recently, more and more swirl-stabilized bullets have been developed and introduced, which have a much longer and heavier rear section compared to conventional floor floors, since this rear section contains a propellant necessary to increase the range. This propellant charge is ignited by the propellant charge during the firing process and reduces the range-reducing ground suction during flight. The moments of inertia such enlarged rear tail parts are such. T. many times higher than conventionally usual, so that mechanically stronger connections must be provided between these novel floors and the shell. On the other hand, however, this is disadvantageous since, in the ejection process, much higher forces have to be applied by a stronger ejection charge in order to be able to separate the floor of the floor. It has been found that these higher forces adversely affect the conventional detonator, causing failure and the payload not being ejected in the expected manner.
Der Erfindung liegt die Aufgabe zugrunde, den Geschoßaufbau eines drallstabilisierten Nutzlastgeschosses dahingehend zu verbessern, daß trotz des für einen Ausstoßvorgang erforderlichen höheren Ausstoßdrucks der im Kopf des Geschosses angeordnete Zünder nicht unzulässig belastet wird.The invention has for its object to improve the floor structure of a swirl-stabilized payload projectile in such a way that despite the higher ejection pressure required for an ejection process, the detonator arranged in the head of the projectile is not unduly loaded.
Ausgehend von einem Geschoß der eingangs näher bezeichneten Art wird diese Aufgabe durch die in Patentanspruch 1 angegebene Erfindung gelöst. Vorteilhafte Ausgestaltungen und Weiterbildungen der Erfindung gehen aus den Unteransprüchen hervor.Starting from a projectile of the type specified in the introduction, this object is achieved by the invention specified in claim 1. 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: eine schematische Schnittdarstellung eines herkömmlichen drallstabilisierten Nutzlastgeschosses;1 shows a schematic sectional illustration of a conventional spin-stabilized payload projectile;
Fig. 2: in Schnittdarstellung den Kopfbereich eines erfindungsgemäß ausgestalteten Geschosses.2: a sectional view of the head area of a projectile designed according to the invention.
Fig. 1 zeigt in einer schematischen Darstellung zum Teil im Längsschnitt ein herkömmliches drallstabilsiertes Nutzlastgeschoß 10, das eine im wesentlichen hohlzylindrisch ausgebildete Hülle 11 und einen mit dieser Hülle 11 drehfest verbundenen Geschoßboden 12 umfaßt. In der Hülle 11 sind in enger Packung übereinander Nutzlasten 13 angeordnet, die auf einem bestimmten Punkt der Flugbahn von einer Ausstoßladung 15 ausgestoßen werden, die ihrerseits von einem im Kopf des Geschosses 10 angeordneten Zünder 14 initiiert wird. Nach der durch Einstellung des Zünders 14 vorgewählten Zeitverzögerung zündet dieser die Ausstoßladung 15, die daraufhin im Innern der Geschoßhülle 11 einen hohen Gasdruck entwickelt, der zunächst den Geschoßboden 12 von der Geschoßhülle 11 abtrennt und dann nacheinander die Nutzlasten 13 aus der nun im Geschoßheck vorhandenen Öffnung ausstößt.Fig. 1 shows a schematic representation, partly in longitudinal section, of a conventional spin-stabilized payload projectile 10, which comprises an essentially hollow-cylindrical casing 11 and a floor 12 connected to this casing 11 in a rotationally fixed manner. Payloads 13, which are ejected at a certain point in the trajectory by an ejection charge 15, which is in turn initiated by a detonator 14 arranged in the head of the projectile 10, are arranged in a tight packing one above the other in the casing 11. After the time delay selected by setting the igniter 14, this ignites the exhaust charge 15, which then develops a high gas pressure inside the projectile casing 11, which first separates the floor 12 from the projectile casing 11 and then successively the payloads 13 from the opening now present in the rear of the projectile ejects.
Wie eingangs erwähnt, muß bei neuentwickelten drallstabiliserten Nutzlastgeschossen mit wesentlich massereicheren Heckteilen eine mechanisch festere Verbindung zwischen Geschoßboden 12 und Geschoßhülle 11 vorgesehen werden, zu deren Abtrennung auch wesentlich stärkere Ausstoßladungen 15 erforderlich sind. Um dadurch den Kopfzünder 14 nicht zu beeinträchtigen, wird - wie aus Fig. 2 ersichtlich ist - zwischen Kopfzünder 14 und Ausstoßladung 15 ein druckreduzierendes Element 20 angeordnet. Dieses druckreduzierende Element 20 dichtet - zumindest weitge - hend - den Ladungsraum der Ausstoßladung 15 zum Kopfzünder 14 hin ab, so daß keine unzulässige Druckbeaufschlagung des Kopfzünders 14 auftritt.As mentioned at the beginning, a mechanically firmer connection between the floor 12 and the shell 11 must be provided in newly developed spin-stabilized payload projectiles with much more massive rear parts are, for the separation of which much stronger ejection charges 15 are required. In order not to impair the head igniter 14 as a result, a pressure-reducing element 20 is arranged between the head igniter 14 and the discharge charge 15, as can be seen from FIG. 2. This pressure-reducing element 20 seals - at least to a large extent - the charge space of the discharge charge 15 towards the head igniter 14, so that no inadmissible pressurization of the head igniter 14 occurs.
In einer besonders vorteilhaften Ausgestaltung der Erfindung ist das druckreduzierende Element 20 kegel- bzw. kegelstumpf förmig ausgebildet und derart zwischen Kopfzünder 14 und Ausstoßladung 15 liegend auf der Längsachse des Geschosses 10 angeordnet, daß die Grundfläche des Kegels bzw. Kegelstumpfs dem Kopfzünder 14 benachbart ist, während die Spitze des Kegels bzw. Kegelstumpfs auf die Ausstoßladung 15 hin gerichtet ist. In der Spitze des Kegels bzw. Kegelstumpfs des druckreduzierenden Elements 20 ist eine Öffnung 20a angeordnet, durch die bei Initiierung des Kopfzünders 14 ein Zündstrahl zur Beaufschlagung der Ausstoßladung 15 hindurchtritt. Nach dem Zünden der Ausstoßladung 15 entwickelt sich in der Ausstoßtülle 15a ein rasant ansteigender Druck, der nach dem Prinzip der Sprengumformung das kegelförmig oder kegelstumpfförmig ausgebildete, druckreduzierende Element 20 schlagartig verformt und zu einer im wesentlichen geschlossenen Scheibe verdichtet, die - zumindest kurzzeitig - einen drucksicheren Abschluß zwischen Kopfzünder 14 und dem druckbeaufschlagten Nutzlastraum 16 herstellt. Durch diese drucksichere Abdichtung kann der Ausstoßvorgang der Nutzlasten 13 ungehindert ablaufen, ohne daß etwa durch Leckage oder Austreiben des Kopfzünders 14, der für das Abtrennen des Geschoßbodens und Ausstoßen der Nutzlasten notwendige Gasdruck reduziert wird. Die erfindungsgemäß vorgesehene Maßnahme ist besonders einfach und kostengünstig durchführbar, so daß sich u. U. auch schon in Depots eingelagerte Geschosse im Bedarfsfall noch umrüsten lassen. In a particularly advantageous embodiment of the invention, the pressure-reducing element 20 is designed in the shape of a truncated cone or truncated cone and is arranged between the igniter 14 and the discharge charge 15 on the longitudinal axis of the projectile 10 such that the base of the cone or truncated cone is adjacent to the igniter 14, while the tip of the cone or truncated cone is directed towards the discharge charge 15. An opening 20a is arranged in the tip of the cone or truncated cone of the pressure-reducing element 20, through which an ignition jet for acting on the ejection charge 15 passes when the head igniter 14 is initiated. After the discharge charge 15 has been ignited, a rapidly increasing pressure develops in the discharge nozzle 15a, which abruptly deforms the conical or truncated cone-shaped, pressure-reducing element 20 and compresses it into an essentially closed disc, which - at least for a short time - is pressure-resistant Concludes between igniter 14 and the pressurized payload space 16. Due to this pressure-proof seal, the ejection process of the payloads 13 can proceed unhindered, without the leakage or expulsion of the igniter 14, for example gas pressure necessary for separating the floor and expelling the payloads is reduced. The measure provided according to the invention is particularly simple and inexpensive to carry out, so that u. If necessary, even store floors that have already been stored in depots.

Claims

P a t e n t a n s p r ü c h e Patent claims
1. Drallstabilisiertes Nutzlastgeschoß mit einer Geschoßhülle, einem abtrennbaren Geschoßboden, in der Geschoßhülle ausstoßbar angeordneten Nutzlasten, einem Kopfzünder sowie einer vom Kopfzünder aktivierbaren Ausstoßladung, d a d u r c h g e k e n n z e i c h n e t, daß zwischen Ausstoßladung (15) und dem Kopfzünder (14) ein druckreduzierendes Element (20) angeordnet ist.1. Swirl-stabilized payload projectile with a projectile shell, a detachable floor, payloads arranged in the projectile shell to be ejected, a head detonator and a discharge charge that can be activated by the head detonator, characterized in that a pressure-reducing element (20) is arranged between the discharge charge (15) and the head detonator (14) .
2. Geschoß nach Anspruch 1, d a d u r c h g e k e n nz e i c h n e t, daß das druckreduzierende Element2. Projectile according to claim 1, that the pressure reducing element
(20) die Gestalt eines Kegels oder Kegelstumpfs hat, dessen Grundfläche dem Kopfzünder (14) und dessen Spitze der Ausstoßladung (15) zugewandt ist. (20) has the shape of a cone or truncated cone, the base of which faces the igniter (14) and the tip of which is directed towards the discharge charge (15).
3. Geschoß 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 in der Spitze des druckreduzierenden Elements (20) eine Öffnung (20a) angeordnet ist.3. Projectile according to one of claims 1 and 2, d a d u r c h g e k e n n z e i c h n e t that an opening (20a) is arranged in the tip of the pressure-reducing element (20).
4. Geschoß nach einem der Ansprüche 1 bis 3, d a d u r c h g e k e n n z e i c h n e t, daß das druckreduzierende Element (20) aus einem verformbaren Metall, wie beispielsweise Aluminium, Kupfer, Stahl besteht. 4. Projectile according to one of claims 1 to 3, that the pressure-reducing element (20) consists of a deformable metal, such as aluminum, copper, steel, for example.
EP86902375A 1985-05-04 1986-03-18 Payload spin-stabilized projectile with propelling charge Expired - Lifetime EP0220218B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3516102 1985-05-04
DE19853516102 DE3516102A1 (en) 1985-05-04 1985-05-04 SPIRAL STABILIZED SHELL

Publications (2)

Publication Number Publication Date
EP0220218A1 true EP0220218A1 (en) 1987-05-06
EP0220218B1 EP0220218B1 (en) 1990-05-02

Family

ID=6269863

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86902375A Expired - Lifetime EP0220218B1 (en) 1985-05-04 1986-03-18 Payload spin-stabilized projectile with propelling charge

Country Status (7)

Country Link
US (1) US4759292A (en)
EP (1) EP0220218B1 (en)
JP (1) JPS62502770A (en)
DE (2) DE3516102A1 (en)
DK (1) DK430686A (en)
ES (1) ES8707608A1 (en)
WO (1) WO1986006829A1 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3844974C2 (en) * 1988-12-10 1999-09-02 Rheinmetall Ind Ag Practice bomblet
DE4123649C2 (en) * 1991-07-17 1993-11-11 Rheinmetall Gmbh Ejection device
DE10039988B4 (en) * 2000-08-16 2006-12-14 Rheinmetall Waffe Munition Gmbh Ejector for ejecting submunitions from a projectile

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH53275A (en) * 1910-09-29 1912-02-01 Krupp Ag Detonator housing
GB124484A (en) * 1916-01-25 1919-04-03 Frank Shinkle Hodson Improvements in Fuses for Projectiles.
US2342096A (en) * 1941-08-21 1944-02-15 Louis J Zimmerman Illuminating projectile
US3374740A (en) * 1965-12-08 1968-03-26 Whirlpool Co Projectile
US3368485A (en) * 1966-04-08 1968-02-13 Robert L. Klotz Nonexplosive detonating fuse directional interrupter
US3713392A (en) * 1971-02-09 1973-01-30 Us Navy Explosive lead plug
US3981244A (en) * 1972-02-28 1976-09-21 The United States Of America As Represented By The Secretary Of The Army Pyramid projectile payload ejection device
US3789764A (en) * 1973-02-20 1974-02-05 Us Navy Explosive lead plug
US4038900A (en) * 1976-07-19 1977-08-02 The United States Of America As Represented By The Secretary Of The Navy Explosive closure valve
DE3048617A1 (en) * 1980-12-23 1982-07-22 Dynamit Nobel Ag, 5210 Troisdorf COMBAT HEAD WITH SECONDARY BODIES AS A PAYLOAD

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO8606829A1 *

Also Published As

Publication number Publication date
DK430686A (en) 1986-11-20
DK430686D0 (en) 1986-09-09
EP0220218B1 (en) 1990-05-02
ES553865A0 (en) 1987-08-16
US4759292A (en) 1988-07-26
ES8707608A1 (en) 1987-08-16
WO1986006829A1 (en) 1986-11-20
DE3670903D1 (en) 1990-06-07
DE3516102A1 (en) 1986-11-06
JPS62502770A (en) 1987-10-22

Similar Documents

Publication Publication Date Title
DE69432769T2 (en) Gun barrel with projectiles arranged axially one behind the other
DE2835817C2 (en) In a cargo floor to several active bodies arranged one behind the other so that they can be ejected, with several daughter floors arranged in radially directed launching tubes
DE3608107C1 (en) Carrier projectile for submunition
DE2723983C2 (en) Propellant charge lighter for caseless cartridges of separately loaded ammunition
DE4123649A1 (en) EMISSION DEVICE
DE2556075C2 (en) Cartridge for shooting target objects used as bait
DE2227104A1 (en) FLOOR OR ROCKET WITH OPENING TAIL
DE1703557A1 (en) Projectile with a payload to be released at a certain point in the flight path
DE3327945A1 (en) BULLET WITH A PAYLOAD PART AND A DRIVE PART
EP0220218A1 (en) Payload spin-stabilized projectile with propelling charge.
DE3339039A1 (en) Smoke projectile
DE2557293A1 (en) PRACTICE FLOOR
DE3743840A1 (en) Projectile having a submunition
EP0237711B1 (en) Primer for a cartridge propellant charge
DE3711904A1 (en) Grenade for grenade launcher
DE3630083C2 (en)
DE2605768C2 (en) Radial burner with solid propellant for a rocket projectile
DE2647538C2 (en) Carrier floor for ejectable active bodies
DE8136383U1 (en) GRENADE
DE1170714B (en) Propellant charge for powder rockets
DE4102772C1 (en) Two stage warhead combating reactively-armoured tanks
DE10039988B4 (en) Ejector for ejecting submunitions from a projectile
EP0224640A1 (en) Carrier projectile
DE1578079C (en) Multi-stage solid rocket
DE3905061C2 (en)

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19861103

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): CH DE FR GB IT LI SE

17Q First examination report despatched

Effective date: 19881011

ITF It: translation for a ep patent filed

Owner name: CALVANI SALVI E VERONELLI S.R.L.

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): CH DE FR GB IT LI SE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Effective date: 19900502

Ref country code: FR

Effective date: 19900502

REF Corresponds to:

Ref document number: 3670903

Country of ref document: DE

Date of ref document: 19900607

EN Fr: translation not filed
GBV Gb: ep patent (uk) treated as always having been void in accordance with gb section 77(7)/1977 [no translation filed]
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Effective date: 19910319

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Effective date: 19910331

Ref country code: CH

Effective date: 19910331

26N No opposition filed
REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Effective date: 19920101

EUG Se: european patent has lapsed

Ref document number: 86902375.4

Effective date: 19911009

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.

Effective date: 20050318