EP0123299B1 - Segmented sabot - Google Patents

Segmented sabot Download PDF

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Publication number
EP0123299B1
EP0123299B1 EP84104484A EP84104484A EP0123299B1 EP 0123299 B1 EP0123299 B1 EP 0123299B1 EP 84104484 A EP84104484 A EP 84104484A EP 84104484 A EP84104484 A EP 84104484A EP 0123299 B1 EP0123299 B1 EP 0123299B1
Authority
EP
European Patent Office
Prior art keywords
sabot
support
segments
crosspieces
fact
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
EP84104484A
Other languages
German (de)
French (fr)
Other versions
EP0123299A2 (en
EP0123299A3 (en
Inventor
Rudolf Romer
Jürgen Winkelmann
Winfried Rossmann
Klaus Walter Klein
Klaus Gersbach
Jürgen Dr. Böcker
Jean-Claude 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.)
Cessione giat Industries
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 AT84104484T priority Critical patent/ATE29925T1/en
Publication of EP0123299A2 publication Critical patent/EP0123299A2/en
Publication of EP0123299A3 publication Critical patent/EP0123299A3/en
Application granted granted Critical
Publication of EP0123299B1 publication Critical patent/EP0123299B1/en
Expired legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • 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 according to the preamble of claim 1.
  • a generic drive cage is known from US-A-2 998 780. Between the segments, circumferential slot-shaped spaces are provided for the wings of the stabilizing tail. In order to enable a rear-side seal despite the gaps, a plate-shaped traction sheave element is provided. At the front, the segments are attached in their rear areas by means of tabs and bolts. At the front, the segments extend radially outwards and thus form a front first support with a pocket-shaped inner surface for the air flowing in when exiting the weapon barrel, with the cooperation of which the sabot should be separated from the projectile. The traction sheave element forms a second support on the rear.
  • each segment has a relief bore in addition to the slots that extend to the front. This is intended to reduce the pressure which can build up during the weft development and when passing through the tube as a result of propellant gases flowing past the traction sheave on the outside.
  • the known sabot requires a high manufacturing effort; it cannot be overlooked that the sabot cautiously hinder the projectile during the detachment process and can impair its trajectory accuracy.
  • both the front first and the rear second support have bores that are inclined against the tube core axis. These are intended to enable a portion of the propellant gases formed during the weft development to pass through the pipe opening and thus help the entire arrangement to a predeterminable swirl.
  • One major disadvantage cannot be overlooked here: the amount of propellant gas used to generate the swirl is lost in order to achieve the highest possible initial velocity of a projectile.
  • the invention has for its object to provide a generic drive cage, which meets the following requirements: simple manufacture, exploitation of essentially the entire amount of propellant gas to increase performance due to the greatest possible initial speed of the projectile and trouble-free detachment of the drive cage in order to achieve the most commuting-free flight of the projectile with increased To ensure target effect.
  • a first sabot 1 with a front support 2 and a rear support 3 has three segments 4, 5 and 6, which touch each other in pairs in butt joints 7, 8 and 9.
  • the front support 2 consists of webs 10, 11 and 12, which are separated from one another by spaces 13.1, 13.2 and 13.3.
  • the webs 10, 11 and 12 are each delimited on the front by a curved surface 14 and on the rear by a curved surface 15 and inclined in the direction of an arrow S indicating the direction of the weft against a central longitudinal axis 20 and have a narrow front end surface 16 and an outside support surface 29 on.
  • a circular cylindrical central receptacle 18 for a balancing projectile extends along the longitudinal axis 20 from a rear edge 17 to a front edge 28 of the sabot 1.
  • the receptacle 18 has form-locking means 19 on the circumference for corresponding form-locking means on the balancing projectile.
  • the rear support 3 surrounds the longitudinal axis 20 with a closed circular cylindrical peripheral surface 30 and has a receptacle 32 in the peripheral region for a sealing tape (not shown).
  • the rear support 3 is formed on the front as an air pocket delimited by an edge 35 with a base area 36 and is delimited on the back by a gas pressure receiving area 31 which has a respective groove 34 in the area of the butt joints 7, 8 and 9 for receiving a sealing element (not shown).
  • the sabot 1 surrounds the balancing projectile in a form-fitting manner, the mouth of a weapon barrel in the direction of arrow S, the incoming air can pass through the spaces 13.1, 13.2 and 13.3 into the air pocket 33 and thus initiates the detaching process of the segments 4, 5 and 6 from the balancing projectile .
  • a lever arm 37 extending from the rear edge 17 (as a rolling edge opposite the balancing projectile) to the base surface 36 of the air pocket 33 is comparatively short and the detachment process of the segments 4, 5 and 6 due to the large distance from the missile tip is not affected by the pressure fluctuations in the front area. From the comparatively Small mass of the respective segment 4, 5 and 6 also results in a significantly reduced impact on the balancing projectile, which is thereby advantageously excited to oscillate considerably less.
  • the webs In a second sabot according to FIG. 3, the webs, of which only one web 40 is shown, are bounded on the front by a comparatively wider surface 42, which consequently offers greater resistance to the incoming air.
  • the webs are made of low density plastic.
  • a main part of a light metal alloy not designated in any more detail, has an outer surface 23 formed from paragraphs 23.1 to 23.5 with dovetail grooves 25.1 and 25.2.
  • the web 40 is made of plastic and is inserted into the dovetail grooves 24.1 and 24.2.
  • a region with the weakest cross section is designed as a predetermined breaking point 25.
  • the webs 40 When leaving the gun barrel, the webs 40 are flown by the air in the area of the surface 42 and break off at 25.
  • the further detaching process takes place essentially as described in connection with the first embodiment. Due to a design of the gas pressure receiving surface on the sabot not shown, the segments can be detached from the balancing projectile starting from the back or also essentially parallel to the longitudinal axis of the projectile.

Abstract

A sabot consists of a plurality of segments which define an air pocket for detaching the segments from a fin-stabilized subcaliber penetrator projectile. The air pocket is defined by a rear support region of the sabot. A front support region of the sabot includes a plurality of webs between each adjacent pair of which an air-through-streaming passage is defined. At least the web portion of each segment is made of synthetic material and such web portion has a curved part defining a fracture zone.

Description

Die Erfindung betrifft einen Treibkäfig nach dem Oberbegriff des Patentanspruchs 1.The invention relates to a sabot according to the preamble of claim 1.

Ein gattungsgleicher Treibkäfig ist bekannt aus der US-A-2 998 780. Zwischen den Segmenten sind umfangsseitige schlitzförmige Zwischenräume für die Flügel des Stabilisierungsleitwerks vorgesehen. Um angesichts der Zwischenräume trotzdem eine heckseitige Abdichtung zu ermöglichen, ist ein tellerförmiges Treibscheibenelement vorgesehen. An dessen Vorderseite sind die Segmente in deren rückseitigen Bereichen mittels Laschen und Bolzen befestigt. Vorderseitig erstrecken sich die Segmente radial nach außen und bilden derart eine vordere erste Abstützung mit einer taschenförmigen Innenfläche für die beim Austreten aus dem Waffenrohr anströmende Luft, unter deren Mitwirkung der Treibkäfig vom Projektil getrennt werden soll. Das Treibscheibenelement bildet eine rückseitige zweite Abstützung. Im vorderseitigen taschenförmigen Bereich der ersten Abstützung weist jedes Segment zusätzlich zu den sich bis nach vorn erstreckenden Schlitzen eine Entlastungsbohrung auf. Hierdurch soll der Druck vermindert werden, welcher sich bei der Schußentwicklung und beim Rohrdurchgang infolge an der Treibscheibe außenseitig vorbeiströmender Treibladungsgase aufbauen kann.A generic drive cage is known from US-A-2 998 780. Between the segments, circumferential slot-shaped spaces are provided for the wings of the stabilizing tail. In order to enable a rear-side seal despite the gaps, a plate-shaped traction sheave element is provided. At the front, the segments are attached in their rear areas by means of tabs and bolts. At the front, the segments extend radially outwards and thus form a front first support with a pocket-shaped inner surface for the air flowing in when exiting the weapon barrel, with the cooperation of which the sabot should be separated from the projectile. The traction sheave element forms a second support on the rear. In the front pocket-shaped area of the first support, each segment has a relief bore in addition to the slots that extend to the front. This is intended to reduce the pressure which can build up during the weft development and when passing through the tube as a result of propellant gases flowing past the traction sheave on the outside.

Der bekannte Treibkäfig erfordert einen hohen fertigungstechnischen Aufwand; dabei kann nicht übersehen werden, daß der Treibkäfig beim Ablösevorgang das Projektil empfindlich behindern und seine Flugbahngenauigkeit beeinträchtigen kann.The known sabot requires a high manufacturing effort; it cannot be overlooked that the sabot cautiously hinder the projectile during the detachment process and can impair its trajectory accuracy.

Bei einem Treibkäfig nach der DE-A-22 32 791 weist sowohl die vordere erste wie auch die hintere zweite Abstützung gegen die Rohrseelenachse geneigte Bohrungen auf. Diese sollen beim Rohrdurchgang einem Teil der sich bei der Schußentwicklung bildenden Treibladungsgase den Durchtritt in Richtung auf die Rohrmündung ermöglichen und damit der gesamten Anordnung zu einem vorgebbaren Drall verhelfen. Dabei kann nicht ein wesentlicher Nachteil übersehen werden: die zur Drallerzeugung verwendete Treibgasmenge geht dem Erzielen einer möglichst hohen Anfangsgeschwindigkeit eines Geschosses verloren.In a sabot according to DE-A-22 32 791, both the front first and the rear second support have bores that are inclined against the tube core axis. These are intended to enable a portion of the propellant gases formed during the weft development to pass through the pipe opening and thus help the entire arrangement to a predeterminable swirl. One major disadvantage cannot be overlooked here: the amount of propellant gas used to generate the swirl is lost in order to achieve the highest possible initial velocity of a projectile.

Der Erfindung liegt die Aufgabe zugrunde, einen gattungsgleichen Treibkäfig zu schaffen, welcher folgenden Forderungen genügt: einfache Fertigung, Ausnutzen der im wesentlichen gesamten Treibladungsgasmenge zur Leistungssteigerung infolge möglichst großer Anfangsgeschwindigkeit des Projektils und störungsfreies Ablösen des Treibkäfigs, um einen möglichst pendelungsfreien Flug des Projektils mit erhöhter Zielwirkung zu gewährleisten.The invention has for its object to provide a generic drive cage, which meets the following requirements: simple manufacture, exploitation of essentially the entire amount of propellant gas to increase performance due to the greatest possible initial speed of the projectile and trouble-free detachment of the drive cage in order to achieve the most commuting-free flight of the projectile with increased To ensure target effect.

Gelöst wird diese Aufgabe durch die im Kennzeichen des Patentanspruchs 1 angegebene Erfindung, die durch die Lehren nach den Kennzeichen der weiteren Patentansprüche vorteilhaft ausgestaltet wird.This object is achieved by the invention specified in the characterizing part of patent claim 1, which is advantageously embodied by the teachings according to the characterizing part of the further patent claims.

Die Erfindung wird nachstehend anhand zweier in der Zeichnung dargestellter Ausführungsbeispiele näher erläutert.The invention is explained below with reference to two exemplary embodiments shown in the drawing.

Es zeigen:

  • Fig. 1 einen ersten Treibkäfig nach der Erfindung in Vorderansicht,
  • Fig. 2 den ersten Treibkäfig im Schnitt nach der Linie 11 - II in Fig. 1 und
  • Fig. 3 einen vorderen Bereich eines Segments eines zweiten Treibkäfigs nach der Erfindung.
Show it:
  • 1 shows a first sabot according to the invention in front view,
  • Fig. 2 shows the first sabot in section along the line 11 - II in Fig. 1 and
  • Fig. 3 shows a front region of a segment of a second sabot according to the invention.

Beim Ausführungsbeispiel nach den Fig. 1 und 2 weist ein erster Treibkäfig 1 mit einer vorderseitigen Abstützung 2 und einer rückseitigen Abstützung 3 drei Segmente 4, 5 und 6 auf, die sich in Stoßfugen 7, 8 und 9 paarweise gegenseitig berühren. Die vorderseitige Abstützung 2 besteht aus Stegen 10, 11 und 12, die durch Zwischenräume 13.1, 13.2 und 13.3 voneinander getrennt sind. Die Stege 10, 11 und 12 sind jeweils vorderseitig durch eine gekrümmte Fläche 14 und rückseitig durch eine gekrümmte Fläche 15 begrenzt und in Richtung eines die Schußrichtung andeutenden Pfeils S gegen eine zentrale Längsachse 20 geneigt und weisen eine schmale vordere Stirnfläche 16 und eine außenseitige Stützfläche 29 auf.In the embodiment according to FIGS. 1 and 2, a first sabot 1 with a front support 2 and a rear support 3 has three segments 4, 5 and 6, which touch each other in pairs in butt joints 7, 8 and 9. The front support 2 consists of webs 10, 11 and 12, which are separated from one another by spaces 13.1, 13.2 and 13.3. The webs 10, 11 and 12 are each delimited on the front by a curved surface 14 and on the rear by a curved surface 15 and inclined in the direction of an arrow S indicating the direction of the weft against a central longitudinal axis 20 and have a narrow front end surface 16 and an outside support surface 29 on.

Entlang der Längsachse 20 erstreckt sich eine kreiszylindrische zentrale Aufnahme 18 für ein nicht dargestelltes Wuchtgeschoß von einer Heckkante 17 bis zu einer Vorderkante 28 des Treibkäfigs 1. Die Aufnahme 18 weist umfangsseitig Formschlußmittel 19 für korrespondierende Formschlußmittel am Wuchtgeschoß auf. Die rückseitige Abstützung 3 umgreift mit einer geschlossenen kreiszylindrischen Umfangsfläche 30 die Längsachse 20 und weist im Umfangsbereich eine Aufnahme 32 für ein nicht dargestelltes Dichtungsband auf. Die rückseitige Abstützung 3 ist vorderseitig als von einer Kante 35 begrenzte Lufttasche mit einer Grundfläche 36 ausgebildet und wird rückseitig von einer Gasdruckaufnahmefläche 31 begrenzt, die im Bereich der Stoßfugen 7, 8 und 9 eine jeweilige Nut 34 zur Aufnahme eines nicht dargestellten Dichtungselements aufweist.A circular cylindrical central receptacle 18 for a balancing projectile, not shown, extends along the longitudinal axis 20 from a rear edge 17 to a front edge 28 of the sabot 1. The receptacle 18 has form-locking means 19 on the circumference for corresponding form-locking means on the balancing projectile. The rear support 3 surrounds the longitudinal axis 20 with a closed circular cylindrical peripheral surface 30 and has a receptacle 32 in the peripheral region for a sealing tape (not shown). The rear support 3 is formed on the front as an air pocket delimited by an edge 35 with a base area 36 and is delimited on the back by a gas pressure receiving area 31 which has a respective groove 34 in the area of the butt joints 7, 8 and 9 for receiving a sealing element (not shown).

Verläßt der das Wuchtgeschoß formschlüssig umgreifende Treibkäfig 1 die Mündung eines Waffenrohres in Richtung des Pfeils S, kann die anströmende Luft durch die Zwischenräume 13.1, 13.2 und 13.3 in die Lufttasche 33 gelangen und leitet damit den Ablösevorgang der Segmente 4, 5 und 6 vom Wuchtgeschoß ein. Dabei erweist sich als vorteilhaft, daß sich ein von der Heckkante 17 (als Abrollkante gegenüber dem Wuchtgeschoß) bis zur Grundfläche 36 der Lufttasche 33 erstreckener Hebelarm 37 vergleichsweise kurz ist und der Ablösevorgang der Segmente 4, 5 und 6 wegen der großen Entfernung von der Fluggeschoßspitze nicht von den Druckschwankungen im vorderen Bereich beeinträchtigt wird. Aus der vergleichsweise geringen Masse des jeweiligen Segments 4, 5 und 6 resultiert zudem eine wesentlich verringerte Stoßwirkung auf das Wuchtgeschoß, das hierdurch vorteilhafterweise erheblich weniger zur Pendelung angeregt wird.If the sabot 1 surrounds the balancing projectile in a form-fitting manner, the mouth of a weapon barrel in the direction of arrow S, the incoming air can pass through the spaces 13.1, 13.2 and 13.3 into the air pocket 33 and thus initiates the detaching process of the segments 4, 5 and 6 from the balancing projectile . It proves to be advantageous that a lever arm 37 extending from the rear edge 17 (as a rolling edge opposite the balancing projectile) to the base surface 36 of the air pocket 33 is comparatively short and the detachment process of the segments 4, 5 and 6 due to the large distance from the missile tip is not affected by the pressure fluctuations in the front area. From the comparatively Small mass of the respective segment 4, 5 and 6 also results in a significantly reduced impact on the balancing projectile, which is thereby advantageously excited to oscillate considerably less.

Bei einem zweiten Treibkäfig nach der Fig. 3 sind die Stege, von denen nur ein Steg 40 dargestellt ist, vorderseitig von einer vergleichsweise b reiteren Fläche 42 begrenzt, die folglich der anströmenden Luft einen größeren Widerstand entgegensetzt. Die Stege bestehen aus Kunststoff geringer Dichte. Ein nicht näher bezeichneter Hauptteil aus einer Leichtmetallegierung weist eine aus Absätzen 23.1 bis 23.5 gebildete Außenfläche 23 mit Schwalbenschwanznuten 25.1 und 25.2 auf. Der Steg 40 ist aus Kunststoff gestaltet, und ist in die Schwalbenschwanznuten 24.1 und 24.2 eingeschoben. Ein Bereich schwächsten Querschnitts ist als Sollbruchstelle 25 ausgebildet.In a second sabot according to FIG. 3, the webs, of which only one web 40 is shown, are bounded on the front by a comparatively wider surface 42, which consequently offers greater resistance to the incoming air. The webs are made of low density plastic. A main part of a light metal alloy, not designated in any more detail, has an outer surface 23 formed from paragraphs 23.1 to 23.5 with dovetail grooves 25.1 and 25.2. The web 40 is made of plastic and is inserted into the dovetail grooves 24.1 and 24.2. A region with the weakest cross section is designed as a predetermined breaking point 25.

Beim Verlassen des Waffenrohres werden die Stege 40 im Bereich der Fläche 42 von der Luft angeströmt und brechen bei 25 ab. Der weitere Ablösevorgang vollzieht sich im wesentlichen derart, wie er im Zusammenhang mit dem ersten Ausführungsbeispiel beschrieben ist. Durch eine nicht dargestellte Ausgestaltung der Gasdruckaufnahmefläche am Treibkäfig kann das Ablösen der Segmente vom Wuchtgeschoß auch von hinten beginnend oder auch im wesentlichen parallel zur Geschoßlängsachse erfolgen.When leaving the gun barrel, the webs 40 are flown by the air in the area of the surface 42 and break off at 25. The further detaching process takes place essentially as described in connection with the first embodiment. Due to a design of the gas pressure receiving surface on the sabot not shown, the segments can be detached from the balancing projectile starting from the back or also essentially parallel to the longitudinal axis of the projectile.

Während beim Ausführungsbeispiel nach Fig. 3 die Stege 40 als aus Kunststoff gefertigt dargestellt und beschrieben sind, kann dies auch, wenigstens teilsweise, auf den nicht näher bezeichneten Hauptteil des betreffenden Segments zutreffen. Dies gilt auch für das Ausführungsbeispiel nach den Fig. 1 und 2, wobei eine der Sollbruchstelle 25 in Fig. 3 im wesentlichen entsprechende nicht näher bezeichnete jeweilige Sollbruchstelle beispielsweise im Bereich der gekrümmten Fläche 14 angeordnet sein kann.While the webs 40 are shown and described as being made of plastic in the exemplary embodiment according to FIG. 3, this can also apply, at least in part, to the unspecified main part of the relevant segment. This also applies to the exemplary embodiment according to FIGS. 1 and 2, wherein a respective predetermined breaking point, which essentially corresponds to the predetermined breaking point 25 in FIG. 3, can be arranged, for example, in the region of the curved surface 14.

Claims (4)

1. Segmented sabot for a fin-stabilized penetrator with high length-to-diameter ratio for use in a barrel weapon, the sabot having a first support (2) at the front, with through-flow apertures (13.1,13.2 and 13.3) and a second support (3) positioned at a certain distance in the axial direction behind the said first support and an air compartment (33) for approach airflow serving to detach segments (4, 5 and 6) from the penetrator after leaving the barrel of the weapon, characterized by the fact that the air compartment (33) is positioned in the second support (3) and the through-flow apertures of the first support (2) are arranged to allow the approach air flow to enter the air compartment (33).
2. Sabot in accordance with Claim 1, characterized by the fact that the first support (2) comprises individual crosspieces (10, 11, 12 and 40) connected with the respective segments (4, 5 and 6), intermediate spaces (13.1, 13.2, and 13.3) which form the through-flow apertures being provided between the crosspieces and each segment (4, 5 and 6) having at least one crosspiece (10, 11, 12 and 40).
3. Sabot in accordance with Claim 1 or 2, characterized by the fact that the crosspieces (10, 11, 12 and 40) have defined fracturing points (25) so that the first support (2) can be broken off.
4. Sabot in accordance with Claims 1, 2 or 3, characterized by the fact that at least the crosspieces (10, 11, 12 and 40) comprise plastic.
EP84104484A 1983-04-23 1984-04-19 Segmented sabot Expired EP0123299B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT84104484T ATE29925T1 (en) 1983-04-23 1984-04-19 SEGMENTED SAVINGS.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19833314749 DE3314749A1 (en) 1983-04-23 1983-04-23 SEGMENTED DRIVING CAGE
DE3314749 1983-04-23

Publications (3)

Publication Number Publication Date
EP0123299A2 EP0123299A2 (en) 1984-10-31
EP0123299A3 EP0123299A3 (en) 1985-01-16
EP0123299B1 true EP0123299B1 (en) 1987-09-23

Family

ID=6197163

Family Applications (1)

Application Number Title Priority Date Filing Date
EP84104484A Expired EP0123299B1 (en) 1983-04-23 1984-04-19 Segmented sabot

Country Status (5)

Country Link
US (1) US4608927A (en)
EP (1) EP0123299B1 (en)
JP (1) JPS6042599A (en)
AT (1) ATE29925T1 (en)
DE (2) DE3314749A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4020404A1 (en) * 1990-06-27 1992-01-09 Rheinmetall Gmbh Segmented drive cage for missile - has segments held together in outer area of adjacent webs by primary guide fillets

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DE3724401A1 (en) * 1987-07-23 1989-05-18 Rheinmetall Gmbh Wing-stabilized, sub-caliber floating cage
DE3843566C1 (en) * 1988-12-23 1995-04-06 Rheinmetall Gmbh Segmented discarding sabot
DE3904626A1 (en) * 1989-02-16 1990-08-30 Diehl Gmbh & Co Discarding sabot for a sub-calibre projectile
FR2665761B1 (en) * 1990-08-13 1994-09-16 Giat Ind Sa SEALING BELT FOR ARROW PROJECTILE.
US5359938A (en) * 1990-10-24 1994-11-01 Olin Corporation Ultra light weight sabot
US5103735A (en) * 1991-06-20 1992-04-14 The United States Of America As Represented By The Secretary Of The Army Splined sabot
DE4206217C2 (en) * 1992-02-28 1997-08-14 Rheinmetall Ind Ag Sub-caliber balancing projectile
US5473989A (en) * 1995-02-24 1995-12-12 Buc; Steven M. Fin-stabilized discarding sabot projectile
DE19944376B4 (en) * 1999-09-16 2007-05-16 Rheinmetall Waffe Munition Segmented sabot
FR2835602B1 (en) * 2002-02-04 2006-11-10 Giat Ind Sa SABOT FOR MUNITION ARROW
DE102004017674A1 (en) 2004-04-10 2005-10-27 Rheinmetall Waffe Munition Gmbh Method for producing a segmented sabot for a subcaliber mass projectile
US8468732B2 (en) * 2009-01-15 2013-06-25 Nicholas E. Young Trigger assembly
US8069791B1 (en) 2010-03-31 2011-12-06 The United States Of America As Represented By The Secretary Of The Navy Curvilinear sabot system

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US2998780A (en) * 1956-05-28 1961-09-05 William B Anspacher High velocity, fin stabilized projectile, rifled barrel gun system
US3164092A (en) * 1962-11-13 1965-01-05 Remington Arms Co Inc Ammunition sabot
US3695181A (en) * 1970-03-12 1972-10-03 Space Res Corp Sub-caliber projectile
DE2232791A1 (en) * 1972-07-04 1974-01-17 Rheinmetall Gmbh ARRANGEMENT ON FULL OR SUB-CALIBRATED FLOORS
FR2222631B1 (en) * 1973-03-19 1977-12-23 Space Res Corp
DE2731093A1 (en) * 1977-07-09 1979-01-25 Josef Prof Dr Ing Ballmann BULLET, IN PARTICULAR TO SHOOT FROM A SMOOTH TUBE
US4284008A (en) * 1979-04-12 1981-08-18 The United States Of America As Represented By The Secretary Of The Army Double ramp discarding sabot
US4326464A (en) * 1979-12-10 1982-04-27 The United States Of America As Represented By The Secretary Of The Army Gusset discarding sabot munition
DE3033041C2 (en) * 1980-09-03 1986-04-10 L'Etat Français représenté par le Délégué Général pour l'Armement, Paris Metal and plastic sabot
FR2490805B1 (en) * 1980-09-23 1985-10-31 France Etat ARROW PROJECTILE OF THE ARROW TYPE
FR2521717B1 (en) * 1982-02-16 1986-11-21 France Etat CINETIC ENERGY PROJECTILE AND LAUNCHING METHOD THEREOF

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4020404A1 (en) * 1990-06-27 1992-01-09 Rheinmetall Gmbh Segmented drive cage for missile - has segments held together in outer area of adjacent webs by primary guide fillets

Also Published As

Publication number Publication date
DE3314749A1 (en) 1984-10-25
DE3466433D1 (en) 1987-10-29
JPS6042599A (en) 1985-03-06
ATE29925T1 (en) 1987-10-15
EP0123299A2 (en) 1984-10-31
JPH0215798B2 (en) 1990-04-13
EP0123299A3 (en) 1985-01-16
US4608927A (en) 1986-09-02

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