EP0123299B1 - Segmented sabot - Google Patents
Segmented sabot Download PDFInfo
- 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
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
- F42B14/06—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.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
- Disintegrating Or Milling (AREA)
- Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
- Diaphragms For Electromechanical Transducers (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Testing Of Engines (AREA)
- Lining And Supports For Tunnels (AREA)
- Circuits Of Receivers In General (AREA)
- Toys (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
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.
- 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
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
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
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
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
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
Claims (4)
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 |
---|---|---|---|
DE3314749 | 1983-04-23 | ||
DE19833314749 DE3314749A1 (en) | 1983-04-23 | 1983-04-23 | SEGMENTED DRIVING CAGE |
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)
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 |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BE524168A (en) * | 1953-04-27 | |||
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 |
-
1983
- 1983-04-23 DE DE19833314749 patent/DE3314749A1/en not_active Withdrawn
-
1984
- 1984-04-19 DE DE8484104484T patent/DE3466433D1/en not_active Expired
- 1984-04-19 EP EP84104484A patent/EP0123299B1/en not_active Expired
- 1984-04-19 AT AT84104484T patent/ATE29925T1/en not_active IP Right Cessation
- 1984-04-23 JP JP59080340A patent/JPS6042599A/en active Granted
- 1984-04-23 US US06/603,131 patent/US4608927A/en not_active Expired - Fee Related
Cited By (1)
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 |
EP0123299A2 (en) | 1984-10-31 |
ATE29925T1 (en) | 1987-10-15 |
DE3466433D1 (en) | 1987-10-29 |
JPH0215798B2 (en) | 1990-04-13 |
US4608927A (en) | 1986-09-02 |
JPS6042599A (en) | 1985-03-06 |
EP0123299A3 (en) | 1985-01-16 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP0123299B1 (en) | Segmented sabot | |
DE3310529C2 (en) | Device for cooling the rotor of a gas turbine | |
DE4330417C2 (en) | Sabot for a sub-caliber projectile | |
DE3840581A1 (en) | BULLET | |
EP0853228A1 (en) | Projectile and manufacturing method therefor | |
DE2624524C2 (en) | Wing-stabilized sub-caliber bullet | |
DE3635738C2 (en) | ||
EP2529180B1 (en) | Spin-stabilized projectile | |
DE2747313C2 (en) | Sub-caliber arrow projectile with a resistance-stabilizing conical tail section | |
DE2731093A1 (en) | BULLET, IN PARTICULAR TO SHOOT FROM A SMOOTH TUBE | |
EP0072584A1 (en) | Connection between the casing and the rear part of a sabot for a projectile | |
EP0006874A1 (en) | Projectile with rotation generating flow channels | |
EP3028002B1 (en) | Method for increasing the range of spin-stabilized projectiles, and projectile of said type | |
EP0152492B1 (en) | Gun ammunition | |
DE4206217C2 (en) | Sub-caliber balancing projectile | |
EP0288721B1 (en) | Provision for a breaking line at the aft part of the sabot of a sub-calibre type projectile | |
DE2936408A1 (en) | Wing stabilized mortar shell | |
EP0049738A2 (en) | Armour-piercing projectile having stabilizing fins | |
DE3031722C2 (en) | ||
CH657449A5 (en) | BULLET WITH MEANS TO REDUCE THE BOTTOM SUCTION. | |
DE69100841T2 (en) | HIGH-SPEED DRIVE MIRROR. | |
EP0855573B1 (en) | Sabot for projectile | |
EP0989381A2 (en) | Subcalibre projectile | |
EP0123266A1 (en) | Projectile with sabot | |
DE3050474C1 (en) | Drift cage made from a one-piece blank |
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 |
Designated state(s): AT BE CH DE FR GB IT LI NL |
|
PUAL | Search report despatched |
Free format text: ORIGINAL CODE: 0009013 |
|
AK | Designated contracting states |
Designated state(s): AT BE CH DE FR GB IT LI NL |
|
17P | Request for examination filed |
Effective date: 19850211 |
|
17Q | First examination report despatched |
Effective date: 19860516 |
|
ITF | It: translation for a ep patent filed |
Owner name: CALVANI SALVI E VERONELLI S.R.L. |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AT BE CH DE FR GB IT LI NL |
|
REF | Corresponds to: |
Ref document number: 29925 Country of ref document: AT Date of ref document: 19871015 Kind code of ref document: T |
|
GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) | ||
REF | Corresponds to: |
Ref document number: 3466433 Country of ref document: DE Date of ref document: 19871029 |
|
ET | Fr: translation filed | ||
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 | ||
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: NL Payment date: 19900430 Year of fee payment: 7 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: CH Payment date: 19910319 Year of fee payment: 8 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: TP |
|
ITTA | It: last paid annual fee | ||
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: NL Effective date: 19911101 |
|
NLV4 | Nl: lapsed or anulled due to non-payment of the annual fee | ||
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LI Effective date: 19920430 Ref country code: CH Effective date: 19920430 |
|
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: AT Payment date: 19930317 Year of fee payment: 10 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: BE Payment date: 19930426 Year of fee payment: 10 |
|
ITPR | It: changes in ownership of a european patent |
Owner name: CESSIONE;GIAT INDUSTRIES |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: AT Effective date: 19940419 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: BE Effective date: 19940430 |
|
BERE | Be: lapsed |
Owner name: ETAT-FRANCAIS REPRESENTE PAR LE DELEGUE GENERAL P Effective date: 19940430 Owner name: RHEINMETALL G.M.B.H. Effective date: 19940430 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 19970314 Year of fee payment: 14 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 19980419 |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 19980419 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20020416 Year of fee payment: 19 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20020418 Year of fee payment: 19 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20031101 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20031231 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: ST |