EP0152492B1 - Gun ammunition - Google Patents

Gun ammunition Download PDF

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Publication number
EP0152492B1
EP0152492B1 EP19840100939 EP84100939A EP0152492B1 EP 0152492 B1 EP0152492 B1 EP 0152492B1 EP 19840100939 EP19840100939 EP 19840100939 EP 84100939 A EP84100939 A EP 84100939A EP 0152492 B1 EP0152492 B1 EP 0152492B1
Authority
EP
European Patent Office
Prior art keywords
sabot
projectile
cores
incisions
diameter
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
Application number
EP19840100939
Other languages
German (de)
French (fr)
Other versions
EP0152492A1 (en
Inventor
Bernhard Bisping
Herman Jansen
Peter Wallow
Rudolf Romer
Klaus Gersbach
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
Priority to EP19840100939 priority Critical patent/EP0152492B1/en
Publication of EP0152492A1 publication Critical patent/EP0152492A1/en
Application granted granted Critical
Publication of EP0152492B1 publication Critical patent/EP0152492B1/en
Expired 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
    • 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
    • F42B12/04—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type
    • F42B12/06—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type with hard or heavy core; Kinetic energy penetrators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B14/00—Projectiles or missiles characterised by arrangements for guiding or sealing them inside barrels, or for lubricating or cleaning barrels
    • F42B14/06—Sub-calibre projectiles having sabots; Sabots therefor
    • F42B14/061—Sabots for long rod fin stabilised kinetic energy projectiles, i.e. multisegment sabots attached midway on the projectile
    • 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
    • F42B5/045—Cartridges, i.e. cases with charge and missile of telescopic type

Definitions

  • the invention relates to a propellant cage with a missile, which is held in a propellant charge sleeve and has the features of the preamble of claim 1.
  • the invention has for its object to achieve a further increase in performance with simple means, as well as an increased firing resistance of the missile.
  • the Fig. Shows an embodiment of the new arrangement in side elevation after a longitudinal axis section.
  • the penetration performance of the missile against multi-plate targets is improved - even under difficult conditions.
  • the missile 10 is designed with a longitudinal axis 11 and with a center of gravity 17 in a transmission area 16 in a targeted manner; Incisions 16.1 to 16.5 provided as positive locking means are also designed as predetermined breaking points.
  • the pre-cores 19.1 to 19.4 formed by the predetermined breaking points Due to the transition cone, the pre-cores 19.1 to 19.4 formed by the predetermined breaking points have a larger diameter de than the diameter, ie the main core 14 ', and thus allow this unimpeded penetration through the penetration hole created by the pre-cores in the target.
  • the transition cone 15 is included in the transmission area 16.
  • the incisions 16.1 to 16.5 are assigned a respective smallest diameter de. They separate from one another a tip body 12 ', pre-cores 19.1 to 19.4 and an adjoining front part 14 "of the main core 14', the larger diameter being assigned to the pre-cores and the front part 14".
  • the new design of the ammunition unit results in increased performance through an increased load.
  • the transition cone as a rear extension achieves an advantageous degree of slenderness of the main core 14 '.
  • the pre-cores result in a targeted breakability, which prevents the main core from being deflected from the desired direction.
  • the mass available according to the invention for striking multi-plate targets is increased.
  • the inclusion of the transition cone 15 in the transmission area 16 achieves the increased firing resistance of the missile. Only then is it possible that only the incisions between the front cores can serve as form-locking means.
  • the propellant charge sleeve can be at least partially combustible.
  • the sabot 20 can be designed without radial projections (29) or ribs for additional holding on the sleeve, since due to the surging gas pressure also acting radially on the gas pressure receiving surface, a required positive connection between the missile 10 and the sabot 20 is ensured in the common transmission area 16.
  • the drive cage 20 is formed by a predeterminable number of segments 21 and has an essentially caliber-like part with a circular cylindrical circumferential surface 33, a front inflow surface 25 and a rear gas pressure receiving surface 27a.
  • the inflow surface 27a extends from a front end edge 26, which grips the tip 12 'of the missile 10 at a radial distance, to a rear edge 27, which closely surrounds the missile.

Landscapes

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

Description

Die Erfindung betrifft einen in einer Treibladungshülse gehaltenen Treibkäfig mit Fluggeschoß mit den Merkmalen des Oberbegriffs des Anspruchs 1.The invention relates to a propellant cage with a missile, which is held in a propellant charge sleeve and has the features of the preamble of claim 1.

Eine derartige Anordnung ist aus der 'FR-A-25 29 319 bekannt. Dort wird eine Steigerung der endballistischen Leistung durch Vorverlegen der Außenkante der Gasdruckaufnahmefläche des Treibkäfigs für die Treibgase in axiale Nachbarschaft der hinteren Kante der Anströmfläche für die Luft erreicht. Dadurch wird zusätzlicher Raum für die Treibladung rund um den hinteren Bereich des Treibkäfigs geschaffen, ohne wesentliche Änderung des waffenseitigen Ladungsraumes und/oder Vergrößerung der Gesamtlänge der Munitionseinheit, bestehend aus Hülse, Treibkäfig und Fluggeschoß. Außerdem wird dadurch ein Angriff des axialen Treibgasdruckes weit vor dem Schwerpunkt des Fluggeschosses erreicht und damit das Zentrieren im Rohr begünstigt. Weiterhin ergibt sich aus der als durchhängendes Profil ausgebildeten Gasdruckaufnahmefläche auch ein radial wirkender Treibgasdruck im Rohr, wodurch ein zuverlässiger Formschluß im Übertragungsbereich zwischen Treibkäfig und Fluggeschoß erreicht wird.Such an arrangement is known from ' FR-A-25 29 319. There, an increase in the final ballistic performance is achieved by advancing the outer edge of the gas pressure receiving surface of the sabot for the propellant gases in the axial vicinity of the rear edge of the inflow surface for the air. This creates additional space for the propellant charge around the rear area of the sabot without significantly changing the weapon-side cargo space and / or increasing the overall length of the ammunition unit, consisting of the sleeve, sabot and missile. In addition, an attack of the axial propellant pressure is achieved far in front of the center of gravity of the missile and thus the centering in the tube is promoted. Furthermore, the gas pressure receiving surface formed as a sagging profile also results in a radially acting propellant gas pressure in the tube, as a result of which a reliable positive connection is achieved in the transmission area between the propellant cage and the missile.

Demgegenüber liegt der Erfindung die Aufgabe zugrunde, mit einfachen Mitteln eine weitere Leistungssteigerung zu erreichen, sowie auch eine erhöhte Abschußfestigkeit des Fluggeschosses.In contrast, the invention has for its object to achieve a further increase in performance with simple means, as well as an increased firing resistance of the missile.

Die zur Lösung der gestellten Aufgabe wesentlichen Merkmale der Erfindung sind im kennzeichnenden Teil des Patentanspruches 1 genannt, der Unteranspruch nennt eine Ausführungsform der Erfindung.The essential features of the invention to achieve the stated object are mentioned in the characterizing part of claim 1, the subclaim mentions an embodiment of the invention.

Die Fig. zeigt eine Ausführungsform der neuen Anordnung im seitlichen Aufriß nach einem Längsachsenschnitt. Bei der dargestellten Anordnung Anordnung wird die Durchschlagsleistung des Fluggeschosses gegen Mehrplattenziele - auch unter erschwerenden Bedingungen - verbessert. Zu diesem Zweck ist das Fluggeschoß 10 mit einer Längsachse 11 und mit einem Schwerpunkt 17 in einem Übertragungsbereich 16 auf gezielte Weise abbrechbar gestaltet; Dabei sind als Formschlußmittel vorgesehene Einschnitte 16.1 bis 16.5 zugleich als Sollbruchstellen ausgebildet. Durch den Übergangskonus 15 läßt sich über eine Heckverlängerung ein schlanker Hauptpenetrator 14' verwirklichen. Die durch die Sollbruchstellen gebildeten Vorkerne 19,1 bis 19,4 haben infolge des Übergangskonus einen größeren Durchmesser de als der Durchmesser dh des Hauptkerns 14' und ermöglichen diesem somit ein ungehindertes Durchdringen durch das von den Vorkernen geschaffene Durchdringungsloch im Ziel.The Fig. Shows an embodiment of the new arrangement in side elevation after a longitudinal axis section. In the arrangement shown, the penetration performance of the missile against multi-plate targets is improved - even under difficult conditions. For this purpose, the missile 10 is designed with a longitudinal axis 11 and with a center of gravity 17 in a transmission area 16 in a targeted manner; Incisions 16.1 to 16.5 provided as positive locking means are also designed as predetermined breaking points. Through the transition cone 15, a slim main penetrator 14 'can be realized via a rear extension. Due to the transition cone, the pre-cores 19.1 to 19.4 formed by the predetermined breaking points have a larger diameter de than the diameter, ie the main core 14 ', and thus allow this unimpeded penetration through the penetration hole created by the pre-cores in the target.

Der Übergangskonus 15 ist in den Übertragungsbereich 16 einbezogen. Den Einschnitten 16,1 bis 16,5 ist ein jeweiliger kleinster Durchmesser de zugeordnet. Sie trennen von einem Spitzenkörper 12' Vorkerne 19,1 bis 19,4 und einen sich anschließenden Vorderteil 14" des Hauptkerns 14' voneinander, wobei den Vorkernen und dem Vorderteil 14" der größere Durchmesser da zugeordnet ist.The transition cone 15 is included in the transmission area 16. The incisions 16.1 to 16.5 are assigned a respective smallest diameter de. They separate from one another a tip body 12 ', pre-cores 19.1 to 19.4 and an adjoining front part 14 "of the main core 14', the larger diameter being assigned to the pre-cores and the front part 14".

Durch die neue Gestaltung der Munitionseinheit wird einerseits eine gesteigerte Leistung durch eine vergrößerte Ladung erreicht. Andererseits wird durch den Übergangskonus als Heckverlängerung ein sich günstig auswirkender Schlankheitsgrad des Hauptkerns 14' erreicht. Durch die Vorkerne ergibt sich eine gezielte Abbrechbarkeit, wodurch ein Ablenken des Hauptkerns aus der gewollten Richtung vermieden wird, insgesamt wird die zum Durchschlagen von Mehrplattenzielen zusammenhängt, verfügbaren Masse nach der Erfindung vergrößert. Durch das Einbeziehen des Übergangskonus 15 in den Übertragungsbereich 16 wird die erhöhte Abschußfestigkeit des Fluggeschosses erreicht, erst dadurch wird es ermöglicht, daß als Formschlußmittel lediglich die Einschnitte zwischen den Vorkernen dienen können.The new design of the ammunition unit, on the one hand, results in increased performance through an increased load. On the other hand, the transition cone as a rear extension achieves an advantageous degree of slenderness of the main core 14 '. The pre-cores result in a targeted breakability, which prevents the main core from being deflected from the desired direction. Overall, the mass available according to the invention for striking multi-plate targets is increased. The inclusion of the transition cone 15 in the transmission area 16 achieves the increased firing resistance of the missile. Only then is it possible that only the incisions between the front cores can serve as form-locking means.

Bei der neuen Anordnung kann die Treibladungshülse wenigstens teilweise verbrennbar sein. Der Treibkäfig 20 kann ohne radiale Vorsprünge (29) oder Rippen zum zusätzlichen Halten an der Hülse gestaltet sein, da infolge des auch radial auf die Gasdruckaufnahmefläche wirkenden Treibgasdrucks ein erforderlicher Formschluß zwischen Fluggeschoß 10 und Treibkäfig 20 im gemeinschaftlichen Übertragungsbereich 16 gewährleistet ist. Der Treibkäfig 20 wird von einer vorgebbaren Anzahl von Segmenten 21 gebildet und weist einen im wesentlichen kalibergleichen Teil mit einer kreiszylindrischen Umfangsfläche 33, eine vorderseitige Anströmfläche 25 und eine rückseitige Gasdruckaufnahmefläche 27a auf. Die Anströmfläche 27a erstreckt sich von einer vorderen Endkante 26, welche die Spitze 12' des Fluggeschosses 10 mit radialem Abstand um Greift, bis zu einer hinteren Kante 27, welche den Flugkörper eng umschliesst.In the new arrangement, the propellant charge sleeve can be at least partially combustible. The sabot 20 can be designed without radial projections (29) or ribs for additional holding on the sleeve, since due to the surging gas pressure also acting radially on the gas pressure receiving surface, a required positive connection between the missile 10 and the sabot 20 is ensured in the common transmission area 16. The drive cage 20 is formed by a predeterminable number of segments 21 and has an essentially caliber-like part with a circular cylindrical circumferential surface 33, a front inflow surface 25 and a rear gas pressure receiving surface 27a. The inflow surface 27a extends from a front end edge 26, which grips the tip 12 'of the missile 10 at a radial distance, to a rear edge 27, which closely surrounds the missile.

Claims (2)

1. Segmental sabot (20) with a front air compartment, the forward part of the sabot being secured in a propulsive charge casing, the sabot interlockingly surrounding the middle zone of an arrow-stabilized projectile (10) of high length-to- diameter ratio from a position starting immediately behind the nose (12') of the projectile, the sabot being provided at the rear with a gas pressure receiving surface (22), which extends to form a profile which falls away from an outer edge of the sabot and located immediately behind the point at which the sabot is secured in the mouth of the casing, as far as a point at the rear of the sabot close to the peripheral zone of the projectile, characterized by the fact that in the central transmission part (16) of the projectile surrounded by the sabot (20), and between the nose (12') of the projectile and the main core (14'), the latter is extended towards the front by a transition cone (15), which is followed to the front by preliminary cores (19.1 to 19.4) formed by incisions (16.1 to 16.5) which define preset breaking points and of which the diameter (de) is smaller than the maximum diameter (da) of the transition cone, the said incisions (16.1 to 16.5) also constituting the only form-closure means between the sabot (20) and the projectile.
2. Projectile in accordance with Claim 1, characterized by the fact that the preliminary cores (19.1 to 19.4) vary in length.
EP19840100939 1984-01-31 1984-01-31 Gun ammunition Expired EP0152492B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP19840100939 EP0152492B1 (en) 1984-01-31 1984-01-31 Gun ammunition

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP19840100939 EP0152492B1 (en) 1984-01-31 1984-01-31 Gun ammunition

Publications (2)

Publication Number Publication Date
EP0152492A1 EP0152492A1 (en) 1985-08-28
EP0152492B1 true EP0152492B1 (en) 1987-12-23

Family

ID=8191737

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19840100939 Expired EP0152492B1 (en) 1984-01-31 1984-01-31 Gun ammunition

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EP (1) EP0152492B1 (en)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2241309B (en) * 1986-02-20 1992-02-05 Royal Ordnance Plc Projectiles and components therefor
DE3635738A1 (en) * 1986-10-21 1988-05-19 Rheinmetall Gmbh DRIVING CAGE FLYING FLOOR ARRANGEMENT
ES2032496T3 (en) * 1987-07-20 1993-02-16 Oerlikon-Contraves Ag REDUCED CALIBER PROJECTILE STABILIZED BY FINS.
DE3811597A1 (en) * 1988-04-07 1989-10-19 Dynamit Nobel Ag DRIVING CAGE FOR A SUB-CALIBAR FLOOR
DE3842077A1 (en) * 1988-12-14 1990-06-28 Diehl Gmbh & Co DRIVING MIRROR FOR A SUB-CALIBRARY BULLET
DE3843968A1 (en) * 1988-12-24 1990-07-05 Diehl Gmbh & Co DRIVING MIRROR FOR A SUB-CALIBRARY BULLET
DE3910566A1 (en) * 1989-04-01 1990-10-04 Diehl Gmbh & Co DEVICE FOR ACCELERATING A PROJECT BY MEANS OF A PLASMA
FR2647891B1 (en) * 1989-06-01 1994-05-20 Etat Francais Delegue Armement DEVICE FOR HOLDING A SUB-CALIBRATED PROJECTILE RELATING TO THE ENVELOPE OF A TELESCOPED AMMUNITION
US5272982A (en) * 1989-06-01 1993-12-28 Giat Industries Device for maintaining a projectile relative to the casing of a telescoping ammunition
FR2647890A1 (en) * 1989-06-01 1990-12-07 France Etat Armement DEVICE FOR MAINTAINING A PROJECTILE RELATING TO THE ENVELOPE OF TELESCOPED MUNITION
US5183961A (en) * 1991-12-09 1993-02-02 Olin Corporation Extended charge cartridge assembly
US5962807A (en) * 1996-05-17 1999-10-05 Primex Technologies, Inc. Pre-molded AFT seal for discarding sabot projectiles
US5747725A (en) * 1996-05-17 1998-05-05 Primex Technologies, Inc. Pre-molded aft seal for discarding sabot projectiles

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB594517A (en) * 1940-09-04 1947-11-13 Charles Dennistoun Burney Improvements in or relating to aeroplane and other bombs or projectiles
US2968246A (en) * 1944-06-30 1961-01-17 Henry F Dunlap Projectile
US2996011A (en) * 1944-06-30 1961-08-15 Henry F Dunlap Projectile
US3262391A (en) * 1964-10-12 1966-07-26 Budd Co Subcaliber projectile and sabot
DE1428679C1 (en) * 1964-12-29 1977-09-15 Deutsch Franz Forsch Inst Hard core bullet for fighting tank targets
BE706278A (en) * 1966-11-28 1968-03-18
US4085878A (en) * 1977-02-07 1978-04-25 Union Carbide Corporation Dispenser-cutter for tacky fabric materials
DE2836963A1 (en) * 1978-08-24 1984-03-08 Rheinmetall GmbH, 4000 Düsseldorf AMMUNITION UNIT FOR TUBE ARMS
CA1141588A (en) * 1979-10-05 1983-02-22 Ghislain Dumas Range limited practice projectile
DK60581A (en) * 1980-03-27 1983-06-23 Rheinmetall Gmbh BREAKING BREAKING MASTER PROJECTILY WITH STACKED FORPENETRATOR

Also Published As

Publication number Publication date
EP0152492A1 (en) 1985-08-28

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