EP0123266B1 - Projectile with sabot - Google Patents

Projectile with sabot Download PDF

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Publication number
EP0123266B1
EP0123266B1 EP84104378A EP84104378A EP0123266B1 EP 0123266 B1 EP0123266 B1 EP 0123266B1 EP 84104378 A EP84104378 A EP 84104378A EP 84104378 A EP84104378 A EP 84104378A EP 0123266 B1 EP0123266 B1 EP 0123266B1
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EP
European Patent Office
Prior art keywords
projectile
zone
air compartment
sabot
accordance
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
EP84104378A
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German (de)
French (fr)
Other versions
EP0123266A1 (en
Inventor
Hansjörg Becker
Gerhard Dr. Glotz
Jürgen Dr. Böcker
Jürgen Leeker
Walter Simon
Jean-Clause Sauvestre
Patrick Montier
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
Direction General pour lArmement DGA
Original Assignee
Rheinmetall GmbH
Direction General pour lArmement DGA
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, Direction General pour lArmement DGA 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-C-1 703 507.
  • 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 is therefore based on the object to achieve a trouble-free detachment of the sabot in its front region in that the shock wave of the supersonic flow is kept away from the air pocket of the sabot and that the same pressure conditions are created within the air pocket.
  • Contour discontinuities in the area of bullet tips are known from FR-A-454822, FR-A-493 570, FR-A-1 206 606, GB-A-21 05 455 and US-A-2 373 883. These are used either to improve the penetration of the bullet tip through the target, to improve ballistic properties or to allow nitroglycerin to flow through to the bullet tip.
  • the interaction of a contour discontinuity in the area of the projectile tip with an air pocket of a sabot is not apparent from the prior art.
  • the floor 10 is only shown in parts in all figures. 1 to 3 preferably show a tip region of the projectile 10, while in FIGS. 4 and. 5 the front area of the sabot, also shown there only in parts, is shown.
  • 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 side of a comparatively larger diameter.
  • Further steps 42, 46, 50, 54, 58, 62, 66 and 70 form jumps in diameter between the adjacent circular cylinder bodies, each with a larger diameter, step 70 being delimited on the circumferential side 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.
  • 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 region 12 generates becomes larger or smaller. At a larger angle, a flatter head wave profile is formed. 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.
  • Lichen tube 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.

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

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-C-1 703 507 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-C-1 703 507. 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 daher die Aufgabe zugrunde, ein störungsfreies Ablösen des Treibkäfigs in seinen vorderen Bereich dadurch zu erreichen, daß die Stoßwelle der Überschallströmung von der Lufttasche des Treibkäfigs ferngehalten wird, und daß innerhalb der Lufttasche gleiche Druckverhältnisse geschaffen werden.The invention is therefore based on the object to achieve a trouble-free detachment of the sabot in its front region in that the shock wave of the supersonic flow is kept away from the air pocket of the sabot and that the same pressure conditions are created within the air pocket.

Es sind zwar aus der FR-A-454822, FR-A-493 570, FR-A-1 206 606, der GB-A-21 05 455 und der US-A-2 373 883 Konturdiskontinuitäten im Bereich von Geschoßspitzen bekannt. Diese dienen entweder zur Verbesserung des Durchdringens der Geschoßspitze durch das Ziel, zur Verbesserung ballistischer Eigenschaften oder zum Ermöglichen des Durchströmens von Nitroglyzerin zur Geschoßspitze. Ein Zusammenwirken einer Konturdiskontinuität im Bereich der Geschoßspitze mit einer Lufttasche eines Treibkäfigs ist aus dem Stand der Technik nicht zu entnehmen.Contour discontinuities in the area of bullet tips are known from FR-A-454822, FR-A-493 570, FR-A-1 206 606, GB-A-21 05 455 and US-A-2 373 883. These are used either to improve the penetration of the bullet tip through the target, to improve ballistic properties or to allow nitroglycerin to flow through to the bullet tip. The interaction of a contour discontinuity in the area of the projectile tip with an air pocket of a sabot is not apparent from the prior art.

Die zur Lösung der gestellten Aufgabe wesentlichen Merkmale der Erfindung sind in Anspruch 1 genannt, die Unteransprüche nennen Ausführungsarten der Erfindung. In der Zeichnung sind Ausführungsformen des neuen Geschosses dargestellt und zwar in Fig. 1, 2, 2a, 2b, 2c und 3 jeweils die Ausbildung der Geschoßspitze und un Fig. 4 und 5 der Lufttasche des Treibkäfigs.The features of the invention which are essential for achieving the stated object are mentioned in claim 1, the subclaims name embodiments of the invention. In the drawing, embodiments of the new projectile are shown, specifically in FIGS. 1, 2, 2a, 2b, 2c and 3, the design of the projectile tip and FIGS. 4 and 5 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 region of the projectile 10, while in FIGS. 4 and. 5 the front area of the sabot, also shown there only in parts, is shown. 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 side of a comparatively larger diameter. Further steps 42, 46, 50, 54, 58, 62, 66 and 70 form jumps in diameter between the adjacent circular cylinder bodies, each with a larger diameter, step 70 being delimited on the circumferential side 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 Vorderbereichs 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 limit 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 region 12 generates becomes larger or smaller. At a larger angle, a flatter head wave profile is formed. 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 ausgebildet. Die Vorderseitenfläche 88 ist zur Kreiskante 90 hin stärker gekrümmt als die Vorderseitenfläche 86 in Fig. 4.A further possibility for avoiding the aforementioned disturbance results from the design of the air pocket in the sabot. For this purpose, reference is made to FIGS. 4 and 5. One in essence Lichen tube 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 more curved toward 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.

Claims (7)

1. Sabot projectile (10) having a high length-to- diameter ratio with a sabot (72) consisting of segments and having an air compartment (74) at the front, characterized by the fact that the projectile (10) is provided in the front zone (12) with a structure of which the position (distance from the sabot) and shape are coordinated with the design of the air compartment (74) so that the boundary between the supersonic flow zone in which the air flows along the front zone (12) and the detachment of the supersonic flow is fixed in such a way that on the one hand the bow wave of the supersonic flow does not make impact on the inside of the air compartment (74) while on the other hand, in the zone between the air compartment (74) and the structure a recirculation flow occurs resulting in constant pressure in the said air compartment (74) thus ensuring the even separation of the segments.
2. Projectile in accordance with Claim 1, characterized by the structure taking the form of at least one profile discontinuity in the peripheral zone (16) of the front zone (12), the structure being in the form of a step (24) in the diameter (Figure 2a).
3. Projectile in accordance with Claims 1 or 2, characterized by circular steps (24, 28, 32, 34, 38, 42, 46, 54) forming the profile discontinuity (Figure 3).
4. Projectile in accordance with any one of Claims 1 to 3, characterized by a circular annular groove (20) in the peripheral zone (16) of the nose part (15) which forms the profile discontinuity (Figure 1).
5. Projectile in accordance with any one of Claims 1 to 4, characterized by the fact that the outer zone (76) of the sabot (62) and surrounding the air compartment (74) is provided, starting from the front edge (78), with a coupling (92) curving towards the projectile, as far as a circular rim (90) which is situated closer to the projectile (10) by a distance depending on the position of the bow wave, than the outer zone (76) surrounding the air compartment (Figure 4).
6. Projectile in accordance with Claim 5, characterized by the fact that the internal wall (88) of the air compartment (74) has a part curving towards the projectile between the wall and the coupling (92) a thin-walled zone (100) is formed which terminates in a sharp rim (90) (Figure 5).
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.

Applications Claiming Priority (2)

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

Publications (2)

Publication Number Publication Date
EP0123266A1 EP0123266A1 (en) 1984-10-31
EP0123266B1 true 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)

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GB2241309B (en) * 1986-02-20 1992-02-05 Royal Ordnance Plc Projectiles and components therefor
DE4007103A1 (en) * 1990-03-07 1991-09-12 Rheinmetall Gmbh Sabot for sub-calibre projectile
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
JPH10501883A (en) * 1995-06-07 1998-02-17 エイチイー・ホールディングス・インコーポレーテッド・ドゥーイング・ビジネス・アズ・ヒューズ・エレクトロニクス Full caliber bullet for use against underwater targets
AU685027B2 (en) * 1995-06-07 1998-01-08 Raytheon Company Gyroscopically stabilized projectile system for use against underwater objects
IL120159A (en) * 1995-06-07 2000-11-21 Raytheon Co Aerodynamically stabilized projectile system for use against under water objects

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US3672304A (en) * 1970-03-30 1972-06-27 Lockheed Aircraft Corp Special purpose firearms projectile
DE2323244C3 (en) * 1973-05-09 1979-04-19 Rheinmetall Gmbh, 4000 Duesseldorf Wing-stabilized sub-caliber bullet
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
SE444983B (en) * 1981-09-09 1986-05-20 Bofors Ab OVEN ENDAMAL EXTENSIBLE WINDOW STABILIZED AMMUNITION UNIT

Also Published As

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AU557827B2 (en) 1987-01-08
JPS61500076A (en) 1986-01-16
PT78472A (en) 1984-05-01
DE3314750A1 (en) 1984-10-25
WO1984004380A1 (en) 1984-11-08
ES287013Y (en) 1986-06-16
DK155857C (en) 1989-10-02
AU2822484A (en) 1984-11-19
EP0123266A1 (en) 1984-10-31
DK544884A (en) 1984-11-15
ATE30081T1 (en) 1987-10-15
PT78472B (en) 1986-03-20
DE3466593D1 (en) 1987-11-05
TR22229A (en) 1986-10-09
DK544884D0 (en) 1984-11-15
KR850000664A (en) 1985-02-28
GR81472B (en) 1984-12-11
ES287013U (en) 1985-11-16
BR8406813A (en) 1985-03-19
IN161067B (en) 1987-09-26
DK155857B (en) 1989-05-22

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