EP0326653B1 - Sabot with a driving belt - Google Patents

Sabot with a driving belt Download PDF

Info

Publication number
EP0326653B1
EP0326653B1 EP88117169A EP88117169A EP0326653B1 EP 0326653 B1 EP0326653 B1 EP 0326653B1 EP 88117169 A EP88117169 A EP 88117169A EP 88117169 A EP88117169 A EP 88117169A EP 0326653 B1 EP0326653 B1 EP 0326653B1
Authority
EP
European Patent Office
Prior art keywords
sabot
fact
guide band
break
band
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
EP88117169A
Other languages
German (de)
French (fr)
Other versions
EP0326653A1 (en
Inventor
Gregor Stollwerk
Rainer Diel
Wilfried Becker
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 EP0326653A1 publication Critical patent/EP0326653A1/en
Application granted granted Critical
Publication of EP0326653B1 publication Critical patent/EP0326653B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • 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
    • F42B14/02—Driving bands; Rotating bands
    • 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

Definitions

  • the invention relates to a droppable sabot with guide band for a sub-caliber wing-stabilized projectile according to the features in the preamble of claim 1.
  • the document US-A-4140061 discloses a short-range training projectile with a segmented sabot according to the preamble of claim 1.
  • the sabot segments are held together by a slipping rear sealing band arranged in an annular groove and a metal band.
  • the metal band is attached to the sabot on the front by means of grub screws and has three grooves to ensure that the band tears after the spin-stabilized projectile has left the weapon.
  • the rear sealing tape is destroyed by the muzzle gas pressure when fired.
  • the individual sabot segments swivel outwards due to the centrifugal forces and tear the front metal strip.
  • a guide ring for a sub-caliber projectile is known.
  • This guide ring has the function of a sabot and is made up of segments that are held together by a guide band.
  • the guide ring is provided radially with grooves which are filled with steel wedges. Due to these local weakenings, the ring breaks due to the centrifugal forces.
  • the ring is surrounded by a copper band or a band made of a material with low tensile strength.
  • the guide band itself has no predetermined breaking points, since in the case of swirl-stabilized projectiles it is worn out by the trains in the inner wall of the pipe and tears apart by the centrifugal forces after leaving the pipe. There is no tearing due to overstretching due to the sabot segments coming loose from the front of a wing-stabilized projectile.
  • the document US-A-4040359 also discloses a guide band for a spin-stabilized projectile.
  • the guide band is made from a mixture of a polymer resin and hollow glass balls.
  • several annular grooves are made, which are filled with an epoxy resin and which have the function of a predetermined breaking point under the high load of the centrifugal forces.
  • the accuracy and performance of sub-caliber projectiles which are accelerated in the barrel of a barrel weapon via the sabot, can be significantly reduced by minimal interference when the sabot is detached or when the sabot is separated from the missile.
  • Such disturbances occur e.g. with sub-caliber balancing ammunition due to asymmetrical detachment of the sabot segments. This is caused by an uneven tearing of the holding or guiding band surrounding the individual sabot segments.
  • Such a predetermined breaking point leads to a stress concentration in this area due to the reduced cross section, but also to one due to the extremely high dynamic stress rate - in contrast to a static stress, in which, depending on the plastic material, strains of approx. 70 to 200% can occur strong solidification of the plastic material in this area. This will stretch the whole Transfer tether, or extended to a larger circumferential area, so that the tether only tears at a relatively late point in time with a larger opening angle of the separating sabot segments.
  • the sealing ability of the sealing or guide tape in the gun barrel is also negatively influenced.
  • the object of the invention is to make the forces occurring between the sabot segments and the missile during the separation process symmetrical and to improve the detachment behavior.
  • the band on the sabot can be stretched mechanically or chemically.
  • the initiation of the crack can be triggered by a separating device specially provided for this purpose;
  • Another possibility of targeted crack initiation can be realized by embrittlement of the plastic material of the retaining band in the area of the parting line.
  • the reference numeral 10 designates a sub-caliber arrow-stabilized balancing projectile with a perforated cone tail unit.
  • the missile 10 is enclosed in its central region by a segmented sabot 12.
  • a sabot segment is shown with a division plane 14 running in the longitudinal direction of the floor.
  • the lower sabot segment is cut.
  • the individual sabot segments are held together in the rear area by a wider sealing or guide band 20 and in the front area by a narrow retaining band 16.
  • FIG. 2a shows a first exemplary embodiment of the guide belt 20 according to the invention.
  • the division plane 14 extending in the longitudinal direction of the floor between the individual sabot segments is indicated.
  • FIGS. 3a, 3b A further exemplary embodiment of the guide belt 20 according to the invention is shown in FIGS. 3a, 3b.
  • the guide band 20 In the vicinity of the guide band 20 to the division plane 14, the guide band 20 has on its underside a plurality of round nub-like projections 24 which, as can be seen from FIG. 3b, engage in corresponding round recesses or blind holes in the two adjacent sabot segments.
  • the guide or sealing tapes around sabot segments are usually in a mold injection molded from hot liquid plastic directly onto the outer circumference of the sabot.
  • FIGS. 4a, 4b A third exemplary embodiment according to the invention is shown in FIGS. 4a, 4b.
  • the sabot segments 23, 25 have a recess in the vicinity of the dividing line 14 (parting plane) into which a key-like insert 27, e.g. made of metal, is used.
  • the insert 27 protrudes about half from the recess and is enclosed with this half in the sprayed-on guide band 20.
  • the exemplary embodiment according to FIGS. 5a, 5b differs in that the recess in the sabot segment is formed somewhat recessed below the key 27, so that liquid plastic 29 can also flow in below the key 27 and the key 27 is completely enclosed in the guide band 20 .
  • 6a, 6b and 7b show further exemplary embodiments of the guide belt 20 according to the invention.
  • two bores are provided in the sabot segments 23, 25 in the vicinity of the parting plane 14, in each of which a pin 30 is inserted.
  • the pins 30 protrude slightly, i.e. up to a maximum of the thickness of the guide band itself out of the bore and are thus partially cast into the guide band 20.
  • the pins 30 are pointed at their upper end; the bore has a slightly larger diameter in the upper area than the pin itself, so that liquid injected plastic can also flow into this cavity around the pin and the guide band is additionally fixed in the circumferential direction of the sabot.
  • the means for introducing cracks were arranged directly in the parting plane 14.
  • the two adjacent sabot segments 23, 25 each have at least half of a corresponding recess within the parting plane 14, in which the means for initiating the crack is inserted.
  • the recess can consist of a narrow slot, a wider slot or holes (blind holes); the corresponding means used to initiate the crack are then designed as a spring-knife-like sheet metal strip 31 (FIG. 8), as a key-like insert 32, 27 (FIG. 9; FIG. 11) or as a pin 30 (FIG. 10).
  • the insert 32 has a flat, wider base 33 and a cutting knife 34 standing vertically thereon.
  • This feather key insert 32 cannot slide into the gap formed along the dividing plane 14 when opening or detachment of the sabot segments from the projectile body, but fixes the guide band 20 and cuts it immediately with the smallest possible tensile load occurring in the circumferential direction (minimizing the tearing force) and simultaneously on the three Sabot segment partition planes, so that there is a reliable and smooth and trouble-free detachment of the individual sabot segments from the projectile body.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Testing Of Engines (AREA)
  • Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
  • Injection Moulding Of Plastics Or The Like (AREA)
  • Supports Or Holders For Household Use (AREA)

Description

Die Erfindung bezieht sich auf einen abwerfbaren Treibkäfig mit Führungsband für ein unterkalibriges flügelstabilisiertes Geschoß gemäß den Merkmalen im Oberbegriff des Patentanspruches 1.The invention relates to a droppable sabot with guide band for a sub-caliber wing-stabilized projectile according to the features in the preamble of claim 1.

Die Schrift US-A-4140061 offenbart ein kurzreichweitiges Übungsgeschoß mit einem segmentierten Treibkäfig gemäß dem Oberbegriff des Patentanspruches 1. Die Treibkäfigsegmente werden durch ein in einer Ringnut angeordnetes durchrutschendes hinteres Dichtungsband und ein Metallband zusammengehalten. Das Metallband wird mittels Gewindestiften vorderseitig am Treibkäfig befestigt und weist drei Nuten auf, um ein Reißen des Bandes zu gewährleisten, nachdem das drallstabilisierte Geschoß die Waffe verlassen hat. Das hintere Dichtungsband wird beim Abschuß durch den Mündungsgasdruck zerstört. Die einzelnen Treibkäfigsegmente schwenken aufgrund der Zentrifugalkräfte nach außen und zerreißen das vordere Metallband.The document US-A-4140061 discloses a short-range training projectile with a segmented sabot according to the preamble of claim 1. The sabot segments are held together by a slipping rear sealing band arranged in an annular groove and a metal band. The metal band is attached to the sabot on the front by means of grub screws and has three grooves to ensure that the band tears after the spin-stabilized projectile has left the weapon. The rear sealing tape is destroyed by the muzzle gas pressure when fired. The individual sabot segments swivel outwards due to the centrifugal forces and tear the front metal strip.

Aus der Schrift GB-A 585794 ist ein Führungsring für ein unterkalibriges Geschoß bekannt. Dieser Führungsring hat die Funktion eines Treibspiegels und ist aus Segmenten aufgebaut, die durch ein Führungsband zusammengehalten werden. Gemäß einem der Ausführungsbeispiele ist der Führungsring radial mit Nuten versehen, die mit Keilen aus Stahl ausgefüllt sind. Durch diese lokalen Schwächungen zerbricht der Ring aufgrund der einwirkenden Zentrifugalkräfte. Der Ring wird von einem Kupferband oder einem Band aus einem Material geringer Dehnfestigkeit umgeben. Das Führungsband selbst weist keine Sollbruchstellen auf, da es bei drallstabilisierten Geschossen durch die Züge in der Rohrinnenwand verschlissen wird und nach Verlassen des Rohres durch die Zentrifugalkräfte zerreißt. Ein Zerreißen aufgrund Überdehnung durch die von der Vorderseite eines flügelstabilisierten Geschosses her sich ablösenden Treibkäfigsegmente tritt nicht auf.From GB-A 585794 a guide ring for a sub-caliber projectile is known. This guide ring has the function of a sabot and is made up of segments that are held together by a guide band. According to one of the exemplary embodiments, the guide ring is provided radially with grooves which are filled with steel wedges. Due to these local weakenings, the ring breaks due to the centrifugal forces. The ring is surrounded by a copper band or a band made of a material with low tensile strength. The guide band itself has no predetermined breaking points, since in the case of swirl-stabilized projectiles it is worn out by the trains in the inner wall of the pipe and tears apart by the centrifugal forces after leaving the pipe. There is no tearing due to overstretching due to the sabot segments coming loose from the front of a wing-stabilized projectile.

Auch die Schrift US-A-4040359 offenbart ein Führungsband für ein drallstabilisiertes Geschoß. Das Führungsband ist aus einer Mischung eines Polymerharzes und Hohlglaskugeln hergestellt. In die Innenseite des Führungsbandes sind mehrere ringförmig umlaufende Nuten eingebracht, die mit einem Epoxidharz ausgefüllt sind und die unter der hohen Belastung der Zentrifugalkräfte die Funktion einer Sollbruchstelle haben.The document US-A-4040359 also discloses a guide band for a spin-stabilized projectile. The guide band is made from a mixture of a polymer resin and hollow glass balls. In the inside of the guide belt, several annular grooves are made, which are filled with an epoxy resin and which have the function of a predetermined breaking point under the high load of the centrifugal forces.

Die Treffgenauigkeit und Leistung von unterkalibrigen Geschossen, die im Rohr einer Rohrwaffe über den Treibkäfig beschleunigt werden, können durch geringste Störeinflüsse beim Ablösen des Treibkäfigs bzw. beim Trennvorgang des Treibspiegels vom Fluggeschoß erheblich verringert werden. Solche Störungen treten z.B. bei unterkalibriger Wuchtmunition durch unsymmetrisches Ablösen der Treibkäfigsegmente auf. Dieses wird bedingt durch ein ungleichmäßiges Zerreißen des die einzelnen Treibkäfigsegmente umschließenden Halte- bzw. Führungsbandes. Um ein Zerreißen des Halte- bzw. Führungsbandes an den Teilungsebenen zu ermöglichen, ist es bekannt, nach Aufbringen des Haltebandes von außen Sollbruchstellen bzw. Querschnittsschwächungen durch Einsägen, Einfräsen oder Kerben (Eindrücken eines heißen Stempels) vorzusehen.The accuracy and performance of sub-caliber projectiles, which are accelerated in the barrel of a barrel weapon via the sabot, can be significantly reduced by minimal interference when the sabot is detached or when the sabot is separated from the missile. Such disturbances occur e.g. with sub-caliber balancing ammunition due to asymmetrical detachment of the sabot segments. This is caused by an uneven tearing of the holding or guiding band surrounding the individual sabot segments. In order to enable the holding or guide band to tear at the parting planes, it is known to provide predetermined breaking points or weakened cross-sections by sawing, milling or notching (pressing in a hot stamp) after the holding band has been applied from the outside.

Eine derartige Sollbruchstelle führt aufgrund des verkleinerten Querschnittes zwar zu einer Spannungskonzentration in diesem Bereich, aber aufgrund der extrem hohen dynamischen Beanspruchungsgeschwindigkeit ― im Gegensatz zu einer statischen Beanspruchung, bei der je nach Kunststoffmaterial Dehnungen von ca. 70 bis 200% auftreten können ― auch zu einer starken Verfestigung des Kunststoffmateriales in diesem Bereich. Dadurch wird die Dehnung auf das gesamte Halteband übertragen, bzw. auf einen größeren Umfangsbereich ausgedehnt, so daß erst zu einem relativ späten Zeitpunkt bei größerem Öffnungswinkel der sich ablösenden Treibkäfigsegmente das Halteband zerreißt.Such a predetermined breaking point leads to a stress concentration in this area due to the reduced cross section, but also to one due to the extremely high dynamic stress rate - in contrast to a static stress, in which, depending on the plastic material, strains of approx. 70 to 200% can occur strong solidification of the plastic material in this area. This will stretch the whole Transfer tether, or extended to a larger circumferential area, so that the tether only tears at a relatively late point in time with a larger opening angle of the separating sabot segments.

Gleichzeitig kommt es zu unerwünschtem Versagensmechanismen, die außerhalb des Trennfugenbereiches der Treibkäfigsegmente eintreten, womit eine Störung auf das Fluggeschoß übertragen wird.At the same time, undesirable failure mechanisms occur that occur outside the joint area of the sabot segments, with which a fault is transferred to the flight floor.

Durch die von außen eingebrachten Sollbruchstellen wird zudem die Abdichtfähigkeit des Dichtungs- bzw. Führungsbandes im Waffenrohr negativ beeinflußt.Due to the predetermined breaking points introduced from the outside, the sealing ability of the sealing or guide tape in the gun barrel is also negatively influenced.

Aufgabe der Erfindung ist es, die zwischen den Treibkäfigsegmenten und dem Fluggeschoß beim Trennvorgang auftretenden Kräfte symmetrisch zu gestalten und das Ablöseverhalten zu verbessern.The object of the invention is to make the forces occurring between the sabot segments and the missile during the separation process symmetrical and to improve the detachment behavior.

Diese Aufgabe wird erfindungsgemäß mit den Merkmalen aus dem Kennzeichnungsteil des Patentanspruches 1 gelöst.This object is achieved according to the invention with the features from the characterizing part of patent claim 1.

Durch die erfindungsgemäße Dehnungsbehinderung nahe oder auf der Teilungsebene (Trennfuge) der Treibkäfigsegmente wird ein reproduzierbares und schnelles Trennen der Treibkäfigsegmente vom Fluggeschoß mit zwischen beiden symmetrisch auftretenden Kontaktkräften erreicht. Dies führt zu einer Verringerung des Abgangsfehlers, zu einer verbesserten Außenballistik und einer Reduktion der Streuung bei der Treffgenauigkeit. Die Dehnungsbehinderung des Bandes auf dem Treibkäfig kann mechanisch oder chemisch erfolgen. Beispielsweise kann die Rißeinleitung durch eine besonders dafür vorgesehene Trennvorrichtung ausgelöst werden; eine andere Möglichkeit der gezielten Rißeinleitung kann durch eine Versprödung des Kunststoffmateriales des Haltebandes im Bereich der Trennfuge realisiert werden.Due to the expansion hindrance according to the invention near or on the parting plane (joint) of the sabot segments, a reproducible and rapid separation of the sabot segments from the missile is achieved with contact forces occurring symmetrically between the two. This leads to a reduction in the departure error, to an improved external ballistics and a reduction in the scatter in the accuracy of the hit. The band on the sabot can be stretched mechanically or chemically. For example, the initiation of the crack can be triggered by a separating device specially provided for this purpose; Another possibility of targeted crack initiation can be realized by embrittlement of the plastic material of the retaining band in the area of the parting line.

Mit der Erfindung wird eine definierte Rißeinleitung in dem Halte- bzw. Führungsband unabhängig von der Qualität und den Fertigungstoleranzen erreicht, die völlig unabhängig von sich verändernden Materialeigenschaften des Kunststoffes ist (wie z.B. Wasseraufnahmevermögen, Zugfestigkeit, Alterung). Damit wird eine frühzeitige bzw. gleichzeitige Ablösung der Treibkäfigsegmente vom Fluggeschoß ohne Störeinflüsse zu jeder Zeit mit Sicherheit gewährleistet.With the invention, a defined initiation of cracks in the holding or guide band is achieved, regardless of the quality and the manufacturing tolerances, which is completely is independent of the changing material properties of the plastic (such as water absorption, tensile strength, aging). This ensures early and simultaneous detachment of the sabot segments from the flight floor without interference at any time with certainty.

Vorteilhafte Ausgestaltungen der Erfindung sind in den Unteransprüchen enthalten.Advantageous embodiments of the invention are contained in the subclaims.

Die Erfindung wird nachfolgend anhand von in den Zeichnungen dargestellten Ausführungsbeispielen näher erläutert und beschrieben.The invention is explained and described in more detail below with reference to exemplary embodiments shown in the drawings.

Es zeigen:

Figur 1
in Seitenansicht ein unterkalibriges flügel- bzw. pfeilstabilisiertes Fluggeschoß mit einem dieses Fluggeschoß im mittleren Bereich umschließenden Treibkäfig,
Figur 2a
eine Draufsicht auf einen Teilbereich des erfindungsgemäßen Führungsbandes gemäß Pfeil II in Figur 1,
Figur 2b
eine Ansicht des erfindungsgemäßen Führungsbandes gemäß Längsschnittlinie IIb in Figur 2a,
Figur 3a
eine Draufsicht auf einen Teilbereich eines weiteren Ausführungsbeispieles des erfindungsgemäßen Führungsbandes,
Figur 3b
eine Ansicht gemäß Längsschnittlinie III in Figur 3a,
Figuren 4a bis 11a
Draufsichten auf weitere Ausführungsbeispiele des erfindungsgemäßen Führungsbandes und
Figuren 4b bis 11b
die entsprechenden Ansichten dieser Ausführungsbeispiele in Quer- oder Längsschnittdarstellung gemäß den bezifferten Pfeilen in den zugehörigen Figuren 4a bis 11a.

Show it:
Figure 1
a side view of a sub-caliber wing or arrow stabilized flight projectile with a sabot surrounding this flight projectile in the central area,
Figure 2a
2 shows a plan view of a partial area of the guide belt according to the invention according to arrow II in FIG. 1,
Figure 2b
2 shows a view of the guide belt according to the invention along the longitudinal section line IIb in FIG. 2a,
Figure 3a
3 shows a plan view of a partial area of a further exemplary embodiment of the guide belt according to the invention,
Figure 3b
3 shows a view along the longitudinal section line III in FIG. 3a,
Figures 4a to 11a
Top views of further embodiments of the guide belt according to the invention and
Figures 4b to 11b
the corresponding views of these embodiments in cross or longitudinal section according to the numbered arrows in the associated figures 4a to 11a.

In Figur 1 ist mit der Bezugsziffer 10 ein unterkalibriges pfeilstabilisiertes Wuchtgeschoß mit Lochkegelleitwerk benannt. Das Fluggeschoß 10 ist in seinem mittleren Bereich von einem segmentierten Treibkäfig 12 umschlossen. In der oberen Bildhälfte ist ein Treibkäfigsegment mit einer in Geschoßlängsrichtung verlaufenden Teilungsebene 14 dargestellt. Das untere Treibkäfigsegment ist geschnitten. Die einzelnen Treibkäfigsegmente werden im hinteren Bereich von einem breiteren Dichtungs- bzw. Führungsband 20 und im vorderen Bereich von einem schmalen Halteband 16 zusammengehalten. In Figur 2a ist ein erstes Ausführungsbeispiel des Führungsbandes 20 gemäß der Erfindung dargestellt. In der Mitte ist die in Geschoßlängsrichtung verlaufende Teilungsebene 14 zwischen den einzelnen Treibkäfigsegmenten angedeutet. Auf der Unterseite des Führungsbandes 20 sind im Nahbereich der Teilungsebene 14 zwei quer zur Längsrichtung des Führungsbandes 20 verlaufende paßfederartige Vorsprünge 22 vorgesehen. Figur 2b zeigt diese paßfederartigen Vorsprünge 22 des Führungsbandes 20, die in entsprechende Ausnehmungen in den beiden aneinanderliegenden Treibkäfigsegmenten 23, 25 eingreifen.In Figure 1, the reference numeral 10 designates a sub-caliber arrow-stabilized balancing projectile with a perforated cone tail unit. The missile 10 is enclosed in its central region by a segmented sabot 12. In the upper half of the picture, a sabot segment is shown with a division plane 14 running in the longitudinal direction of the floor. The lower sabot segment is cut. The individual sabot segments are held together in the rear area by a wider sealing or guide band 20 and in the front area by a narrow retaining band 16. FIG. 2a shows a first exemplary embodiment of the guide belt 20 according to the invention. In the middle, the division plane 14 extending in the longitudinal direction of the floor between the individual sabot segments is indicated. On the underside of the guide band 20, two feather-like projections 22 running transversely to the longitudinal direction of the guide band 20 are provided in the vicinity of the division plane 14. Figure 2b shows these feather key-like projections 22 of the guide belt 20 which engage in corresponding recesses in the two adjacent sabot segments 23, 25.

In Figur 3a, 3b ist ein weiteres Ausführungsbeispiel des erfindungsgemäßen Führungsbandes 20 dargestellt. Im Nahbereich des Führungsbandes 20 zur Teilungsebene 14 weist das Führungsband 20 auf seiner Unterseite mehrere runde noppenartige Vorsprünge 24 auf, die, wie aus Figur 3b ersichtlich ist, in entsprechende runde Ausnehmungen, bzw. Sacklochbohrungen in den beiden benachbarten Treibkäfigsegmenten eingreifen. Die Führungs- bzw. Dichtungsbänder um Treibkäfigsegmente werden üblicherweise in einer Gußform im Spritzgußverfahren aus heißem flüssigem Kunststoff direkt auf den Außenumfang des Treibkäfigs hergestellt.A further exemplary embodiment of the guide belt 20 according to the invention is shown in FIGS. 3a, 3b. In the vicinity of the guide band 20 to the division plane 14, the guide band 20 has on its underside a plurality of round nub-like projections 24 which, as can be seen from FIG. 3b, engage in corresponding round recesses or blind holes in the two adjacent sabot segments. The guide or sealing tapes around sabot segments are usually in a mold injection molded from hot liquid plastic directly onto the outer circumference of the sabot.

In Figur 4a, 4b ist ein drittes erfindungsgemäßes Ausführungsbeispiel dargestellt. Dabei weisen die Treibkäfigsegmente 23, 25 im Nahbereich zur Trennlinie 14 (Teilungsebene) eine Ausnehmung auf, in die ein paßfederartiger Einsatz 27, z.B. aus Metall, eingesetzt ist. Der Einsatz 27 ragt etwa zur Hälfte aus der Vertiefung heraus und ist mit dieser Hälfte in das aufgespritzte Führungsband 20 eingeschlossen. Das Ausführungsbeispiel gemäß Figur 5a, 5b unterscheidet sich demgegenüber dadurch, daß unterhalb der Paßfeder 27 die Ausnehmung im Treibkäfigsegment noch etwas vertieft ausgebildet ist, so daß auch unterhalb der Paßfeder 27 flüssiger Kunststoff 29 einfließen kann und die Paßfeder 27 vollständig in das Führungsband 20 eingeschlossen ist.A third exemplary embodiment according to the invention is shown in FIGS. 4a, 4b. The sabot segments 23, 25 have a recess in the vicinity of the dividing line 14 (parting plane) into which a key-like insert 27, e.g. made of metal, is used. The insert 27 protrudes about half from the recess and is enclosed with this half in the sprayed-on guide band 20. The exemplary embodiment according to FIGS. 5a, 5b differs in that the recess in the sabot segment is formed somewhat recessed below the key 27, so that liquid plastic 29 can also flow in below the key 27 and the key 27 is completely enclosed in the guide band 20 .

In den Figuren 6a, 6b und 7b sind weitere Ausführungsbeispiele des Führungsbandes 20 gemäß der Erfindung dargestellt. Hierbei sind in den Treibkäfigsegmenten 23, 25 im Nahbereich zur Teilungsebene 14 jeweils zwei Bohrungen (Sacklochbohrung) vorgesehen, in die jeweils ein Stift 30 eingesetzt ist.6a, 6b and 7b show further exemplary embodiments of the guide belt 20 according to the invention. In this case, two bores (blind holes) are provided in the sabot segments 23, 25 in the vicinity of the parting plane 14, in each of which a pin 30 is inserted.

Die Stifte 30 ragen geringfügig, d.h. bis maximal zu der Dicke des Führungsbandes selbst aus der Bohrung heraus und sind somit teilweise in das Führungsband 20 eingegossen. Bei dem Ausführungsbeispiel nach Figur 7a, 7b sind die Stifte 30 an ihrem oberen Ende zugespitzt ausgebildet; die Bohrung weist im oberen Bereich einen etwas größeren Durchmesser als der Stift selbst auf, so daß auch in diesem Hohlraum um den Stift flüssiger eingespritzter Kunststoff einfließen kann und das Führungsband in Umfangrichtung des Treibkäfigs zusätzlich fixiert ist.The pins 30 protrude slightly, i.e. up to a maximum of the thickness of the guide band itself out of the bore and are thus partially cast into the guide band 20. In the exemplary embodiment according to FIGS. 7a, 7b, the pins 30 are pointed at their upper end; the bore has a slightly larger diameter in the upper area than the pin itself, so that liquid injected plastic can also flow into this cavity around the pin and the guide band is additionally fixed in the circumferential direction of the sabot.

In den weiteren Auführungsbeispielen gemäß den Figuren 8a, 8b; 9a, 9b; 10a, 10b und 11a, 11b sind im Gegensatz zu den vorherigen Ausführungsbeispielen die Mittel zur Rißeinleitung direkt in der Teilungsebene 14 angeordnet. Dazu weisen die beiden jeweils benachbarten Treibkäfigsegmente 23, 25 innerhalb der Teilungsebene 14 jeweils zur Hälfte wenigstens eine entsprechende Ausnehmung auf, in welcher das Mittel zur Rißeinleitung eingesetzt ist. Die Ausnehmung kann aus einem schmalen Schlitz, einem breiteren Schlitz oder Bohrungen (Sacklochbohrungen) bestehen; die entsprechenden eingesetzten Mittel zur Rißeinleitung sind dann als federmesserartiger Blechstreifen 31 (Figur 8), als paßfederartiger Einsatz 32, 27 (Figur 9; Figur 11) oder als Stift 30 (Figur 10) ausgebildet.In the further exemplary embodiments according to FIGS. 8a, 8b; 9a, 9b; 10a, 10b and 11a, 11b are in contrast to the In previous exemplary embodiments, the means for introducing cracks were arranged directly in the parting plane 14. For this purpose, the two adjacent sabot segments 23, 25 each have at least half of a corresponding recess within the parting plane 14, in which the means for initiating the crack is inserted. The recess can consist of a narrow slot, a wider slot or holes (blind holes); the corresponding means used to initiate the crack are then designed as a spring-knife-like sheet metal strip 31 (FIG. 8), as a key-like insert 32, 27 (FIG. 9; FIG. 11) or as a pin 30 (FIG. 10).

Das bevorzugte Ausführungsbeispiel ist in Figur 9a, 9b dargestellt. Hierbei weist der Einsatz 32 einen flachen breiteren Sockel 33 und ein darauf senkrecht stehendes Schneidmesser 34 auf. Dieser Paßfedereinsatz 32 kann bei beginnender Öffnung, bzw. Ablösung der Treibkäfigsegmente vom Geschoßkörper nicht in den sich längs der Teilungsebene 14 bildenden Spalt rutschen, sondern fixiert das Führungsband 20 und zerschneidet es bei geringster in Umfangsrichtung auftretender Zugbelastung sofort (Zerreißkraftminimierung) und gleichzeitig an den drei Treibkäfig-Segment-Teilungsebenen, so daß auf zuverlässige Weise ein gleichmäßiges und störungsfreies Ablösen der einzelnen Treibkäfigsegmente vom Geschoßkörper erfolgt.The preferred embodiment is shown in Figure 9a, 9b. Here, the insert 32 has a flat, wider base 33 and a cutting knife 34 standing vertically thereon. This feather key insert 32 cannot slide into the gap formed along the dividing plane 14 when opening or detachment of the sabot segments from the projectile body, but fixes the guide band 20 and cuts it immediately with the smallest possible tensile load occurring in the circumferential direction (minimizing the tearing force) and simultaneously on the three Sabot segment partition planes, so that there is a reliable and smooth and trouble-free detachment of the individual sabot segments from the projectile body.

Claims (9)

1. Discarding sabot for a sub-calibre fin stabilised projectile comprising a number of segments which are subdivided in the longitudinal direction of the projectile and which are provided on their external periphery, in order to hold them together and to seal the sabot from gas pressure in the barrel, with at least one sealing band or guide band passing around the periphery, for the predetermined initiation of a break after firing the projectile or during the detachment of the sabot segments from the projectile body after leaving the mouth of the barrel, a preset breaking point is provided in the zone of each division plane of the sabot segments, characterised by the fact that on the inner side of the guide band (20), in the zone contiguous to the division plane (14), at least one interlock means (22, 24, 27, 30, 31, 32) is provided for the initiation of the break and for limiting the expansion zone around the preset breaking point, while each sabot segment (23, 25) has at least one recess serving to receive the said means (22, 24, 27, 30, 31, 32).
2. Sabot in accordance with Claim 1, characterised by the fact that within a division plane (14) at least one recess is provided, half of which is situated in each of the two adjacent sabot segments (23, 25) and in which the means for initiating the break is positioned.
3. Sabot In accordance with Claim 1, characterised by the fact that at least one recess, in which the means for initiating the break is situated, is provided in the immediate vicinity of the division plane (14) of each sabot segment (23, 25).
4. Sabot in accordance with Claim 1, 2 or 3, characterised by the fact that the recess consists of a boring and the means for initiating the break consists of a pin (30) which is situated in the said boring and which extends from the boring by a predetermined distance which is less than the thickness of the guide band (20).
5. Sabot in accordance with Claim 1, 2 or 3, characterised by the fact that the recess takes the form of a narrow slit extending transversally to the longitudinal direction of the guide band (20) and that the means for initiating the break comprises a penknife-like metal strip (31) which extends from the slit by a distance which is less than the thickness of the guide band (20).
6. Sabot in accordance with Claim 1, 2 or 3, characterised by the fact that the recess takes the form of a wide slit extending transversally to the longitudinal direction of the guide band (20), the means for initiating the break consists of an insert (31, 32) of the nature of a feathered key, which extends from the slit a distance which is less than the thickness of the guide band (20).
7. Sabot in accordance with Claim 6, characterised by the fact that the insert (32) has a flat base (33) and a cutting blade (34) standing vertically thereupon.
8. Sabot in accordance with Claim 3, characterised by the fact that the recess comprises at least one boring, while the means for initiating the break consists of a projection (24) in the band, situated on the lower side of the guide band (20) and engaging the said boring.
9. Sabot in accordance with Claim 3, characterised by the fact that the recess takes the form of a slit extending transversally to the longitudinal direction of the guide band (20) while the means for initiating the break consists of a projection (22) in the band situated on the lower side of the guide band (20) and engaging the slit.
EP88117169A 1988-02-01 1988-10-15 Sabot with a driving belt Expired - Lifetime EP0326653B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3802857 1988-02-01
DE3802857A DE3802857A1 (en) 1988-02-01 1988-02-01 DRIVING CAGE WITH GUIDE TAPE

Publications (2)

Publication Number Publication Date
EP0326653A1 EP0326653A1 (en) 1989-08-09
EP0326653B1 true EP0326653B1 (en) 1991-10-30

Family

ID=6346363

Family Applications (1)

Application Number Title Priority Date Filing Date
EP88117169A Expired - Lifetime EP0326653B1 (en) 1988-02-01 1988-10-15 Sabot with a driving belt

Country Status (4)

Country Link
EP (1) EP0326653B1 (en)
JP (1) JPH028700A (en)
DE (2) DE3802857A1 (en)
IL (1) IL88896A0 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4009220A1 (en) * 1990-03-22 1991-09-26 Rheinmetall Gmbh Disposable drive cage for low calibre firearm - comprises several segment divided in weapon longitudinal direction, with guide band on outer periphery
DE4133617C2 (en) * 1991-10-10 2002-04-11 Rheinmetall W & M Gmbh Disposable sabot
FR2694081B1 (en) * 1992-07-24 1994-09-30 Giat Ind Sa Arrow projectile sealing belt.
DE10157668B4 (en) * 2001-11-24 2014-05-22 Rheinmetall Waffe Munition Gmbh bullet
DE102009009772A1 (en) * 2009-02-20 2010-09-02 Rheinmetall Waffe Munition Gmbh Method for introducing predetermined breaking points in an annular retaining and sealing strip of a sabot projectile and Laborierwerkzeug for performing the method

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1341844A (en) * 1917-09-20 1920-06-01 Dougan Kennedy Projectile
GB585794A (en) * 1942-07-30 1947-02-25 Charles Dennistoun Burney Improvements in or relating to gun fired projectiles
US2998779A (en) * 1944-07-10 1961-09-05 Donald T Macroberts Projectile
GB630414A (en) * 1947-11-03 1949-10-12 Alan Lindsay Bruns Improvements in and connected with the driving bands of shells or projectiles
IL37041A (en) * 1971-06-14 1976-02-29 State Of Il Ministry Of Def Forward sabot for sub-calibre projectile with delayed detachment
US4040359A (en) * 1976-05-14 1977-08-09 The United States Of America As Represented By The Secretary Of The Army Discarding frangible rotating band
DE2642222C2 (en) * 1976-09-20 1983-11-10 Rheinmetall GmbH, 4000 Düsseldorf Twist-stabilized ring bullet
US4140061A (en) * 1977-06-06 1979-02-20 The United States Of America As Represented By The Secretary Of The Army Short-range discarding-sabot training practice round and self-destruct subprojectile therefor

Also Published As

Publication number Publication date
IL88896A0 (en) 1989-08-15
EP0326653A1 (en) 1989-08-09
DE3802857A1 (en) 1989-08-03
JPH028700A (en) 1990-01-12
DE3865961D1 (en) 1991-12-05

Similar Documents

Publication Publication Date Title
DE3036463C2 (en)
CH661792A5 (en) GUIDE ELEMENT FOR A SUB-CALIBRATE PROJECTILE.
DE4330417C2 (en) Sabot for a sub-caliber projectile
EP1209437A1 (en) Sabot projectile comprising a penetrator
DE3872805T2 (en) CONNECTION RING BETWEEN BULLET AND BULLET SLEEVE.
EP0326653B1 (en) Sabot with a driving belt
DE2936408A1 (en) Wing stabilized mortar shell
DE3617415C2 (en) Sub-caliber sabot bullet
EP0989381B1 (en) Subcalibre projectile
EP0624774B1 (en) Sabot for a finstabilized projectile
EP0288721B1 (en) Provision for a breaking line at the aft part of the sabot of a sub-calibre type projectile
EP0214409A1 (en) Hollow charge training projectile
EP3317607B1 (en) Fin-stabilized sub-calibre projectile which can be fired from a rifled barrel and method for the production thereof
EP0258647A2 (en) Sabot for an arrow-type kinetic energy penetrator
EP0089000B1 (en) Projectile with armour-piercing core
DE69110212T2 (en) Sealing tape for arrow stick.
DE69305018T2 (en) Sealing tape for arrow stick
EP0999426B1 (en) Sabot for sub-caliber projectile
DE3021914C2 (en)
DE2227655A1 (en) LOWER CALIBER FLOOR
DE3426847C1 (en) Projectile-forming explosive charge insert
DE2454584A1 (en) TUBULAR SHAPE
DE19504840B4 (en) Projectile with a penetrator arranged in a metal shell
DE102022108565A1 (en) Balancing bullet in the form of a sabot bullet
DE19704489A1 (en) Sub-caliber sabot bullet

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

AK Designated contracting states

Kind code of ref document: A1

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

17P Request for examination filed

Effective date: 19890630

17Q First examination report despatched

Effective date: 19901126

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 NL SE

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 FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRE;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.SCRIBED TIME-LIMIT

Effective date: 19911030

Ref country code: SE

Effective date: 19911030

Ref country code: NL

Effective date: 19911030

REF Corresponds to:

Ref document number: 3865961

Country of ref document: DE

Date of ref document: 19911205

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
ET Fr: translation filed
NLV1 Nl: lapsed or annulled due to failure to fulfill the requirements of art. 29p and 29m of the patents act
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

26N No opposition filed
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Effective date: 19921031

Ref country code: CH

Effective date: 19921031

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 19930922

Year of fee payment: 6

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 19930929

Year of fee payment: 6

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 19931015

Year of fee payment: 6

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

Ref country code: GB

Effective date: 19941015

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 19941015

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

Ref country code: FR

Effective date: 19950630

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

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

Ref country code: DE

Effective date: 19951003