EP0123266A1 - Projectile with sabot - Google Patents

Projectile with sabot Download PDF

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Publication number
EP0123266A1
EP0123266A1 EP84104378A EP84104378A EP0123266A1 EP 0123266 A1 EP0123266 A1 EP 0123266A1 EP 84104378 A EP84104378 A EP 84104378A EP 84104378 A EP84104378 A EP 84104378A EP 0123266 A1 EP0123266 A1 EP 0123266A1
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EP
European Patent Office
Prior art keywords
sabot
projectile
air pocket
projectile according
edge
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
EP84104378A
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German (de)
French (fr)
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EP0123266B1 (en
Inventor
Hansjörg Becker
Gerhard Dr. Glotz
Jürgen Dr. Böcker
Jürgen Leeker
Walter Simon
Jean-Clause Sauvestre
Patrick Montier
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Rheinmetall Industrie AG
Direction General pour lArmement DGA
Etat Francais
Original Assignee
Rheinmetall GmbH
Direction General pour lArmement DGA
Etat Francais
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Application filed by Rheinmetall GmbH, Direction General pour lArmement DGA, Etat Francais filed Critical Rheinmetall GmbH
Priority to AT84104378T priority Critical patent/ATE30081T1/en
Publication of EP0123266A1 publication Critical patent/EP0123266A1/en
Application granted granted Critical
Publication of EP0123266B1 publication Critical patent/EP0123266B1/en
Expired legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/38—Range-increasing arrangements
    • 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
    • F42B12/20—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type
    • F42B12/22—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type with fragmentation-hull construction
    • F42B12/24—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type with fragmentation-hull construction with grooves, recesses or other wall weakenings
    • 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 sabot projectile with a large length / diameter ratio with a sabot consisting of segments, which has an air pocket on the front.
  • a projectile of the aforementioned type is known from DE-PS 17 03 507.
  • the sabot has the air pocket in the front support and a rear edge in the vicinity of the second support, around which the segments are detached from the balancing projectile.
  • the swinging of the projectile can severely impair both its accuracy and its penetration.
  • the latter relates primarily to the effect against new types of targets, which require both particularly long projectiles with a ratio of length to diameter that is significantly higher than 10, as well as the greatest possible freedom of oscillation.
  • Studies on the behavior of projectile-sabot arrangements have shown that unstable flow conditions can occur in the area around the front part of the projectile, which impair the uniform segment-wise detachment of the sabot.
  • the invention has for its object to provide an improved sabot projectile, the improvement mainly relates to the detachment behavior of the sabot.
  • the floor 10 is only shown in parts in all figures. 1 to 3 preferably show a tip area of the projectile 10, while FIGS. 4 and 5 show the front area of the sabot, which is also shown only in parts.
  • a sabot projectile of the type described acts only because of its kinetic energy and contains no explosive charge.
  • the peripheral region 16 in the vicinity of the tip 18 has an annular projection 34.
  • the tip body 15 has a cone tip 22 with a rear step 24 which establishes a jump in diameter.
  • the tip body 15 is provided on the front with a hemisphere 26, the rear base surface of which has a step 28 for achieving a jump in diameter.
  • the tip body 15 consists of z. B. nine circular cylinder bodies 36, 40, 44, 48, 52, 56, 60, 64 and 68.
  • the circular cylinder body 36 forms the tip 18 with a comparatively small diameter and is delimited on the rear by a step 38 which delimits the subsequent circular cylinder body 40 on the front on a comparatively larger diameter.
  • Further steps 42, 46, 50, 54, 58, 62, 66 and 70 form jumps in diameter between the respectively larger circular cylinder bodies, the step 70 being bounded on the circumference by the base edge 14 between the circular cylinder rod 11 and the front region 12.
  • the structures shown all lead to at least one contour discontinuity in the front area 12.
  • This defines an otherwise oscillating, pulsating or vibrating axis in the axial direction between a flow area in which supersonic speed prevails and a recirculation area.
  • the pressure fluctuations which have a detrimental effect on the detachment behavior of the sabot segments from the projectile are avoided.
  • an angle that a head wave of the front area 12 generates becomes larger or smaller. At a larger angle, a flatter head wave profile forms. In this way, a profile can be formed in which the head shaft no longer hits the front edge of the sabot. This also prevents interference with the detachment process.
  • a substantially 76 caliber area 76 of the sabot 72 surrounds the air pocket 74.
  • the area 76 extends from a front edge 78 to a rear edge 80.
  • the edge 80 delimits a rear surface 82 which leads into a tapered central area 84.
  • a front surface 86, 88 forming the air pocket 74 is delimited on the front by a circular edge 90.
  • a track 92, which connects the circular edge 90 to the edge 78, is curved such that its center of curvature (s) lies on the side of the circular edge 90 facing away from the front region 12, not shown.
  • the retraction of the circular edge 90 ensures that it is not hit by the above-mentioned head wave, interfering with the detachment process.
  • the invention can be applied jointly both in the front area of the floor or in the design of the sabot as well as in both areas. This advantageously allows a good adaptation to the respective requirements and circumstances.
  • the segments can also detach from the floor, starting from the rear or essentially parallel to the longitudinal axis of the floor.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Testing Of Engines (AREA)
  • Investigating Or Analyzing Materials By The Use Of Ultrasonic Waves (AREA)
  • Mechanical Pencils And Projecting And Retracting Systems Therefor, And Multi-System Writing Instruments (AREA)
  • Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
  • Saccharide Compounds (AREA)
  • Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
  • Pharmaceuticals Containing Other Organic And Inorganic Compounds (AREA)
  • Carbon And Carbon Compounds (AREA)
  • Tires In General (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Other Air-Conditioning Systems (AREA)
  • Steroid Compounds (AREA)
  • Buildings Adapted To Withstand Abnormal External Influences (AREA)
  • Compositions Of Macromolecular Compounds (AREA)
  • Heterocyclic Carbon Compounds Containing A Hetero Ring Having Nitrogen And Oxygen As The Only Ring Hetero Atoms (AREA)
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Abstract

The point portion (15) of a reduced calibre projectile (10) has a discontinuous contour in the form of a circular groove (20). Thereby, a boundary layer is determined between a supersonic speed flow range and a subsonic speed flow range; thereby it is possible to eliminate perturbations due to the flow during the separation of the sabot segments, not shown, of the projectile (10).

Description

Die Erfindung betrifft ein Treibkäfiggeschoß großen Länge/Durchmesser-Verhältnisses mit einem aus Segmenten bestehenden Treibkäfig, der vorderseitig eine Lufttasche aufweist.The invention relates to a sabot projectile with a large length / diameter ratio with a sabot consisting of segments, which has an air pocket on the front.

Ein Geschoß der vorgenannten Art ist aus der DE-PS 17 03 507 bekannt. Der Treibkäfig weist in der vorderen Abstützung die Lufttasche auf und in der Nachbarschaft der zweiten Abstützung eine rückseitige Kante, um die sich die Ablösung der Segmente vom Wuchtgeschoß vollzieht. Bei Beschüssen konnte ein ungleichmäßiges Ablösen der Treibkäfigsegmente vom Geschoß festgestellt werden. Dies kann zu einer schädlichen Pendelung des Geschosses führen. Durch die Pendelung des Geschosses kann sowohl dessen Treffgenauigkeit wie auch dessen Durchschlagsleistung empfindlich beeinträchtigt werden. Letzteres bezieht sich vornehmlich auf die Wirkung gegen neuartige Ziele, die sowohl besonders lange Geschosse mit einem wesentlich über 10 liegendenden Verhältnis von Länge zu Durchmesser wie auch deren weitestgehende Pendelungsfreiheit erforderlich machen. Untersuchungen zum Verhalten von Geschoß-Treibkäfig-Anordnungen ergaben, daß im Bereich um den Vorderteil des Geschosses instabile Strömungsverhältnisse auftreten können, die das gleichmäßige segmentweise Ablösen des Treibkäfigs beeinträchtigen.A projectile of the aforementioned type is known from DE-PS 17 03 507. The sabot has the air pocket in the front support and a rear edge in the vicinity of the second support, around which the segments are detached from the balancing projectile. In the event of shelling, an uneven detachment of the sabot segments from the projectile was found. This can lead to a damaging swinging of the projectile. The swinging of the projectile can severely impair both its accuracy and its penetration. The latter relates primarily to the effect against new types of targets, which require both particularly long projectiles with a ratio of length to diameter that is significantly higher than 10, as well as the greatest possible freedom of oscillation. Studies on the behavior of projectile-sabot arrangements have shown that unstable flow conditions can occur in the area around the front part of the projectile, which impair the uniform segment-wise detachment of the sabot.

Der Erfindung liegt die Aufgabe zugrunde, ein verbessertes Treibkäfiggeschoß zu schaffen, wobei sich die Verbesserung hauptsächlich auf das Ablöseverhalten des Treibkäfigs bezieht.The invention has for its object to provide an improved sabot projectile, the improvement mainly relates to the detachment behavior of the sabot.

Gelöst wird diese Aufgabe durch die im Patentanspruch 1 angegebene Erfindung.This object is achieved by the invention specified in claim 1.

Die Erfindung wird nachstgehend anhand in der Zeichnung dargestellter bevorzugter Ausführungsbeispiele näher erläutert.The invention is explained in more detail below on the basis of preferred exemplary embodiments illustrated in the drawing.

Dabei zeigt:

  • Fig. 1: ein erstes Ausführungsbeispiel des Vorderteils des Geschosses;
  • Fig. 2, 2a, 2b, 2c: ein weiteres Ausführungsbeispiel der Erfindung mit mehreren Varianten;
  • Fig. 3: ein drittes Ausführungsbeispiel der Erfindung;
  • Fig. 4: ein erstes Ausführungsbeispiel der Lufttasche des Treibkäfigs;
  • Fig. 5: ein weiteres Ausführungsbeispiel der Lufttasche des Treibkäfigs.
It shows:
  • Fig. 1: a first embodiment of the front part of the projectile;
  • 2, 2a, 2b, 2c: a further embodiment of the invention with several variants;
  • Fig. 3: a third embodiment of the invention;
  • 4: a first exemplary embodiment of the air pocket of the sabot;
  • Fig. 5: another embodiment of the air pocket of the sabot.

Das Geschoß 10 ist in allen Figuren nur stückweise dargestellt. In Fig. 1 bis Fig. 3 ist vorzugsweise ein Spitzenbereich des Geschosses 10 abgebildet, während in Fig. 4 und Fig. 5 der vordere Bereich des auch dort nur stückweise dargestellten Treibkäfigs abgebildet ist. Ein Treibkäfiggeschoß der beschriebenen Art wirkt lediglich aufgrund seiner kinetischen Energie und enthält keine Sprengstoffladung.The floor 10 is only shown in parts in all figures. 1 to 3 preferably show a tip area of the projectile 10, while FIGS. 4 and 5 show the front area of the sabot, which is also shown only in parts. A sabot projectile of the type described acts only because of its kinetic energy and contains no explosive charge.

Gemäß Fig. 1 erstreckt sich bei einem nur teilweise dargestellten Geschoß 10 dessen Kreiszylinderstab 11 bis zu einer Basiskante 14 eines im Vorderbereich 12 angeordneten Spitzenkörpers 15. Des letzteren Umfangsbereich 16 erstreckt sich von der Basiskante 14 bis zu einer Spitze 18 und weist eine Kreisringnut 20 auf.1, in the case of a projectile 10 that is only partially shown, its circular cylindrical rod 11 extends up to a base edge 14 of a tip body 15 arranged in the front area 12. The latter circumferential area 16 extends from the base edge 14 to a tip 18 and has an annular groove 20 .

Gemäß Fig. 2 weist der Umfangsbereich 16 in der Nachbarschaft der Spitze 18 einen Kreisringvorsprung 34 auf.According to FIG. 2, the peripheral region 16 in the vicinity of the tip 18 has an annular projection 34.

Gemäß Fig. 2a weist der Spitzenkörper 15 eine Kegelspitze 22 mit einer rückseitigen Stufe 24 auf, die einen Durchmessersprung begründet.According to FIG. 2a, the tip body 15 has a cone tip 22 with a rear step 24 which establishes a jump in diameter.

Gemäß Fig. 2c ist der Spitzenkörper 15 vorderseitig mit einer Halbkugel 26 versehen, deren rückseitige Basisfläche eine Stufe 28 zum Erzielen eines Durchmessersprungs aufweist.According to FIG. 2 c, the tip body 15 is provided on the front with a hemisphere 26, the rear base surface of which has a step 28 for achieving a jump in diameter.

Gemäß Fig. 3 besteht der Spitzenkörper 15 aus z. B. neun Kreiszylinderkörpern 36, 40, 44, 48, 52, 56, 60, 64 und 68.3, the tip body 15 consists of z. B. nine circular cylinder bodies 36, 40, 44, 48, 52, 56, 60, 64 and 68.

Der Kreiszylinderkörper 36 bildet mit einem vergleichsweise kleinsten Durchmesser die Spitze 18 und wird rückseitig von einer Stufe 38 begrenzt, die den nachfolgenden Kreiszylinderkörper 40 vergleichsweise größeren Durchmessers vorderseitig begrenzt. Weitere Stufen 42, 46, 50, 54, 58, 62, 66 und 70 bilden Durchmessersprünge zwischen den jeweils im Durchmesser größeren benachbarten Kreiszylinderkörpern, wobei die Stufe 70 von der Basiskante 14 zwischen dem Kreiszylinderstab 11 und dem Vorderbereich 12 umfangsseitig begrenzt wird. Mit zunehmender (abnehmender) Zahl der Kreiszylinderkörper und Stufen verkleinern (vergrößern) sich die einzelnen Durchmessersprünge.The circular cylinder body 36 forms the tip 18 with a comparatively small diameter and is delimited on the rear by a step 38 which delimits the subsequent circular cylinder body 40 on the front on a comparatively larger diameter. Further steps 42, 46, 50, 54, 58, 62, 66 and 70 form jumps in diameter between the respectively larger circular cylinder bodies, the step 70 being bounded on the circumference by the base edge 14 between the circular cylinder rod 11 and the front region 12. With an increasing (decreasing) number of circular cylinder bodies and steps, the individual jumps in diameter decrease (increase).

Die dargestellten Strukturierungen führen allesamt im Vorderbereich 12 zu wenigstens einer Konturdiskontinuität. Durch diese wird eine andernfalls in axialer Richtung oszillierende, pulsierende oder vibrierende Grenze zwischen einem Strömungsbereich, in dem Überschallgeschwindigkeit herrscht, und einem Rezirkulationsgebiet festgelegt. Durch ihre Festlegung werden die sich auf das Ablöseverhalten der Treibkäfigsegmente vom Geschoß schädlich auswirkenden Druckschwankungen vermieden. Je nach Ausbildung der Konturdiskontinuität wird auch ein Winkel, den eine Kopfwelle des Vorderbeireichs 12 erzeugt, größer oder kleiner. Bei größerem Winkel bildet sich ein flacheres Kopfwellenprofil aus. Dieserart läßt sich ein Profil ausbilden, bei dem die Kopfwelle die Vorderkante des Treibkäfigs nicht mehr trifft. Auch hierdurch wird eine Störung des Ablösevorgans vermieden.The structures shown all lead to at least one contour discontinuity in the front area 12. This defines an otherwise oscillating, pulsating or vibrating axis in the axial direction between a flow area in which supersonic speed prevails and a recirculation area. By defining them, the pressure fluctuations which have a detrimental effect on the detachment behavior of the sabot segments from the projectile are avoided. Depending on the design of the contour discontinuity, an angle that a head wave of the front area 12 generates becomes larger or smaller. At a larger angle, a flatter head wave profile forms. In this way, a profile can be formed in which the head shaft no longer hits the front edge of the sabot. This also prevents interference with the detachment process.

Eine weitere Möglichkeit zum Vermeiden der vorgenannten Störung ergibt sich aus der Gestaltung der Lufttasche des,Treibkäfigs. Hierzu wird auf die Fig. 4 und 5 verwiesen. Ein im wesentlichen rohrkalibergleicher Bereich 76 des Treibkäfigs 72 umschließt die Lufttasche 74. Der Bereich 76 erstreckt sich von einer Vorderen Kante 78 bis zu einer hinteren Kante 80. Die Kante 80 begrenzt eine Rückseitenfläche 82, die in einem verjüngten Zentralbereich 84 überleitet. Eine die Lufttasche 74 bildende Vorderseitenfläche 86, 88 wird vorderseitig von einer Kreiskante 90 begrenzt. Eine Spur 92, die die Kreiskante 90 mit der Kante 78 verbindet, ist derart gekrümmt, daß ihr(e) Krümmungsmittelpunkt(e) auf der dem nicht dargestellten Vorderbereich 12 abgewandten Seite der Kreiskante 90 liegt (liegen). Hierdurch ergibt sich eine Differenz zwischen einem größeren Radius 94 des Bereichs 76 und einem der Kreiskante 90 zugeordneten kleineren Radius 96 (nur in Fig. 4 eingetragen). Während beim Ausführungsbeispiel nach Fig. 4 die Spur 92 einen Bereich 98 vergleichweise großer Wandstärke begrenzt, ist ein von der Spur 92 in Fig. 5 begrenzter Bereich 100 vergleichsweise dünnwandig ausgebildt. Die Vorderseitenfläche 88 ist zur Kreiskante 90 hin stärker gekrümmt als die Vorderseitenfläche 86 in Fig. 4.Another way of avoiding the aforementioned malfunction results from the design of the air pocket of the sabot. For this purpose, reference is made to FIGS. 4 and 5. A substantially 76 caliber area 76 of the sabot 72 surrounds the air pocket 74. The area 76 extends from a front edge 78 to a rear edge 80. The edge 80 delimits a rear surface 82 which leads into a tapered central area 84. A front surface 86, 88 forming the air pocket 74 is delimited on the front by a circular edge 90. A track 92, which connects the circular edge 90 to the edge 78, is curved such that its center of curvature (s) lies on the side of the circular edge 90 facing away from the front region 12, not shown. This results in a difference between a larger radius 94 of the area 76 and a smaller radius 96 assigned to the circular edge 90 (only entered in FIG. 4). While the track 92 delimits an area 98 of comparatively large wall thickness in the exemplary embodiment according to FIG. 4, an area 100 delimited by the track 92 in FIG. 5 has a comparatively thin wall. The front surface 88 is curved more towards the circular edge 90 than the front surface 86 in FIG. 4.

Durch das Einziehen der Kreiskante 90 wird erreicht, daß sie nicht - den Ablösevorgang störend - von der bereits erwähnten Kopfwelle getroffen wird.The retraction of the circular edge 90 ensures that it is not hit by the above-mentioned head wave, interfering with the detachment process.

Die Erfindung läßt sich sowohl jeweils im Vorderbereich des Geschosses oder in der Gestaltung des Treibkäfigs wie auch in beiden Bereichen gemeinschaftlich anwenden. Hierdurch ist vorteilhafterweise eine gute Anpassung an jeweilige Erfordernisse und Gegebenheiten möglich. Je nach Ausbildung der nicht dargestellten Gasdruckaufnahmefläche im Heckbereich des Treibkäfigs können sich die Segmente auch von hinten beginnend oder im wesentlichen parallel zur Geschoßlängsachse vom Geschoß ablösen.The invention can be applied jointly both in the front area of the floor or in the design of the sabot as well as in both areas. This advantageously allows a good adaptation to the respective requirements and circumstances. Depending on the design of the gas pressure receiving surface, not shown, in the rear area of the sabot, the segments can also detach from the floor, starting from the rear or essentially parallel to the longitudinal axis of the floor.

Claims (9)

1. Treibkäfiggeschoß großen Länge/Durchmesser-Verhältnisses mit einem aus Segmenten bestehenden Treibkäfig, der vorderseitig eine Lufttasche aufweist, gekennzeichnet durch eine KonturDiskontinuität im Vorderbereich (12) des Geschosses (10) und/oder eine solche Gestaltung der Lufttasche (74), daß eine die Lufttasche (74) vorderseitig begrenzende Kreiskante (90) einen Radius (96) aufweist, der um ein vorgebbares Maß kleiner ist als der im wesentlichen dem halben Rohrkaliber gleiche Radius (94) des Treibkäfigs (72) in einem die Lufttasche (74) umschließenden Bereich (76).1. sabot projectile large length / diameter ratio with a segmented sabot that has an air pocket on the front, characterized by a contour discontinuity in the front area (12) of the projectile (10) and / or such a design of the air pocket (74) that a the circular edge (90) of the air pocket (74) on the front side has a radius (96) which is smaller by a predeterminable dimension than the radius (94) of the sabot cage (72), which is essentially the same as half the tube caliber, in a radius surrounding the air pocket (74) Area (76). 2. Treibkäfiggeschoß nach Anspruch 1, gekennzeichnet durch wenigstens eine Profildiskontinuität im Umfangsbereich (16) des Vorderbereichs (12) in Form eines Durchmessersprungs.2. sabot projectile according to claim 1, characterized by at least one profile discontinuity in the peripheral region (16) of the front region (12) in the form of a jump in diameter. 3. Treibkäfiggeschoß nach einem der Ansprüche 1 und 2, dadurch gekennzeichnet, daß der Vorderbereich (12) des Geschosses (10) aus einer Kegelspitze (22) und einem als Kegelstumpf ausgebildeten Spitzenkörper (15) zusammengesetzt ist, wobei beide Teile an ihrer Berührungsfläche eine Stufe (24) bilden.3. sabot projectile according to one of claims 1 and 2, characterized in that the front region (12) of the projectile (10) is composed of a cone tip (22) and a tip body (15) designed as a truncated cone, both parts having one on their contact surface Form step (24). 4. Treibkäfiggeschoß nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet , daß der Vorderbereich (12) des Geschosses (10) aus einem Kreiszylinderkörper (30) und einem als Kegelstumpf ausgebildeten Spitzenkörper (15) besteht, wobei die beiden Teile an ihrer Berührungsfläche eine Stufe (32) bilden.4. sabot projectile according to one of claims 1 to 3, characterized in that the front region (12) of the projectile (10) consists of a circular cylinder body (30) and a truncated cone formed as a truncated cone (15), the two parts on their contact surface one Form step (32). 5. Treibkäfiggeschoß nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß der Vorderbereich (12) des Geschosses (10) aus einer Halbkugel (26) und einem als Kegelstumpf ausgebildeten Spitzenkörper (15) zusammengesetzt ist, und daß beide Teile an ihrer Berührungsfläche eine Stufe (28) bilden.5. sabot projectile according to one of claims 1 to 4, characterized in that the front region (12) of the projectile (10) is composed of a hemisphere (26) and a truncated cone formed as a truncated cone (15), and that both parts on their contact surface form a step (28). 6. Treibkäfiggeschoß nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet , daß der Spitzenkörper (15) des Geschosses (10) einen Kreisringvorsprung (34) trägt.6. sabot projectile according to one of claims 1 to 5, characterized in that the tip body (15) of the projectile (10) carries an annular projection (34). 7. Treibkäfiggeschoß nach einem der Ansprüche 1 bis 6, gekennzeichnet durch kreisförmige Stufen (24, 28, 32, 34, 38, 42, 46, 50, 54, 58, 62, 66, 70) im Umfangsbereich (16) des Spitzenkörpers (15).7. sabot projectile according to one of claims 1 to 6, characterized by circular steps (24, 28, 32, 34, 38, 42, 46, 50, 54, 58, 62, 66, 70) in the peripheral region (16) of the tip body ( 15). 8. Treibkäfiggeschoß nach einem der Ansprüche 1 bis.7, gekennzeichnet durch eine Kreisringnut (20) im Umfangsbereich (16) des Spitzenkörpers (15).8. sabot projectile according to one of claims 1 to 7, characterized by an annular groove (20) in the peripheral region (16) of the tip body (15). 9. Treibkäfiggeschoß nach einem der Ansprüche 1 bis 8, gekennzeichnet durch folgende Merkmale: a) der die Lufttasche (74) umschließende, im wesentlichen rohrkalibergleiche Bereich (76) erstreckt sich vorderseitig bis zu einer Kante (78) und b) eine Verbindungsspur (92) zwischen der Kante (78) und der Kreiskante (90) wird durch eine gekrümmte Linie gebildet, deren Krümmungsmittelpunkt(e) auf der dem Vorderbereich (12) abgewandten Seite der Kreiskante (90) liegt (liegen). 9. sabot projectile according to one of claims 1 to 8, characterized by the following features: a) the air pocket (74) enclosing, substantially pipe caliber area (76) extends on the front to an edge (78) and b) a connecting track (92) between the edge (78) and the circular edge (90) is formed by a curved line whose center of curvature (e) lies on the side of the circular edge (90) facing away from the front region (12).
EP84104378A 1983-04-23 1984-04-18 Projectile with sabot Expired EP0123266B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT84104378T ATE30081T1 (en) 1983-04-23 1984-04-18 SAVINGS PROJECTILE.

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Application Number Priority Date Filing Date Title
DE19833314750 DE3314750A1 (en) 1983-04-23 1983-04-23 AGENT FOR IMPROVING THE RELEASE BEHAVIOR OF DRIVING CAGE SEGMENTS FROM A RIFLE BULLET FOR THE PIPE ARM
DE3314750 1983-04-23

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EP0123266A1 true EP0123266A1 (en) 1984-10-31
EP0123266B1 EP0123266B1 (en) 1987-09-30

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EP84104378A Expired EP0123266B1 (en) 1983-04-23 1984-04-18 Projectile with sabot

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EP (1) EP0123266B1 (en)
JP (1) JPS61500076A (en)
KR (1) KR850000664A (en)
AT (1) ATE30081T1 (en)
AU (1) AU557827B2 (en)
BR (1) BR8406813A (en)
DE (2) DE3314750A1 (en)
DK (1) DK155857C (en)
ES (1) ES287013Y (en)
GR (1) GR81472B (en)
IN (1) IN161067B (en)
PT (1) PT78472B (en)
TR (1) TR22229A (en)
WO (1) WO1984004380A1 (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2241309A (en) * 1986-02-20 1991-08-28 Royal Ordnance Plc Sabot projectile
GB2241772A (en) * 1990-03-07 1991-09-11 Rheinmetall Gmbh Sabots
WO1996041116A1 (en) * 1995-06-07 1996-12-19 He Holdings, Inc., Doing Business As Hughes Electronics Full caliber projectile for use against underwater objects
WO1996041115A1 (en) * 1995-06-07 1996-12-19 He Holdings, Inc., Doing Business As Hughes Electronics Aerodynamically stabilized projectile system for use against underwater objects
WO1996041114A1 (en) * 1995-06-07 1996-12-19 He Holdings, Inc., Doing Business As Hughes Electronics Gyroscopically stabilized projectile system for use against underwater objects

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4022462A1 (en) * 1990-07-14 1992-01-16 Diehl Gmbh & Co Solid air-launched underwater projectile - has core with shortened front protected by ballistic cap

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR454822A (en) * 1912-09-26 1913-07-16 Robert Abbott Hadfield Breast Piercing Projectile Hats Improvements
FR493570A (en) * 1916-10-16 1919-08-13 Bento Caeiro Method and device for increasing the range of projectiles
US2373883A (en) * 1942-10-30 1945-04-17 Clyde B Ferrel Shell structure
FR1206606A (en) * 1951-11-07 1960-02-10 Tech De Rech S Ind & Mecanique Fletched projectile
US3672304A (en) * 1970-03-30 1972-06-27 Lockheed Aircraft Corp Special purpose firearms projectile
FR2229037A1 (en) * 1973-05-09 1974-12-06 Rheinmetall Gmbh
GB2105445A (en) * 1981-09-09 1983-03-23 Bofors Ab Ammunition unit
US4405100A (en) * 1981-02-20 1983-09-20 The United States Of America As Represented By The Secretary Of The Navy Turbulence generator for maximizing configuration tolerances of free flight ordnance

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR454822A (en) * 1912-09-26 1913-07-16 Robert Abbott Hadfield Breast Piercing Projectile Hats Improvements
FR493570A (en) * 1916-10-16 1919-08-13 Bento Caeiro Method and device for increasing the range of projectiles
US2373883A (en) * 1942-10-30 1945-04-17 Clyde B Ferrel Shell structure
FR1206606A (en) * 1951-11-07 1960-02-10 Tech De Rech S Ind & Mecanique Fletched projectile
US3672304A (en) * 1970-03-30 1972-06-27 Lockheed Aircraft Corp Special purpose firearms projectile
FR2229037A1 (en) * 1973-05-09 1974-12-06 Rheinmetall Gmbh
US4405100A (en) * 1981-02-20 1983-09-20 The United States Of America As Represented By The Secretary Of The Navy Turbulence generator for maximizing configuration tolerances of free flight ordnance
GB2105445A (en) * 1981-09-09 1983-03-23 Bofors Ab Ammunition unit

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2241309A (en) * 1986-02-20 1991-08-28 Royal Ordnance Plc Sabot projectile
GB2241309B (en) * 1986-02-20 1992-02-05 Royal Ordnance Plc Projectiles and components therefor
GB2241772A (en) * 1990-03-07 1991-09-11 Rheinmetall Gmbh Sabots
WO1996041116A1 (en) * 1995-06-07 1996-12-19 He Holdings, Inc., Doing Business As Hughes Electronics Full caliber projectile for use against underwater objects
WO1996041115A1 (en) * 1995-06-07 1996-12-19 He Holdings, Inc., Doing Business As Hughes Electronics Aerodynamically stabilized projectile system for use against underwater objects
WO1996041114A1 (en) * 1995-06-07 1996-12-19 He Holdings, Inc., Doing Business As Hughes Electronics Gyroscopically stabilized projectile system for use against underwater objects
AU686954B2 (en) * 1995-06-07 1998-02-12 Raytheon Company Full caliber projectile for use against underwater objects

Also Published As

Publication number Publication date
PT78472B (en) 1986-03-20
EP0123266B1 (en) 1987-09-30
DK544884A (en) 1984-11-15
DK544884D0 (en) 1984-11-15
IN161067B (en) 1987-09-26
GR81472B (en) 1984-12-11
AU557827B2 (en) 1987-01-08
DK155857B (en) 1989-05-22
JPS61500076A (en) 1986-01-16
ATE30081T1 (en) 1987-10-15
KR850000664A (en) 1985-02-28
DE3314750A1 (en) 1984-10-25
TR22229A (en) 1986-10-09
WO1984004380A1 (en) 1984-11-08
PT78472A (en) 1984-05-01
DK155857C (en) 1989-10-02
DE3466593D1 (en) 1987-11-05
ES287013Y (en) 1986-06-16
AU2822484A (en) 1984-11-19
BR8406813A (en) 1985-03-19
ES287013U (en) 1985-11-16

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