EP2095060B1 - Guided missile with a sleeve for mounting a guiding system - Google Patents

Guided missile with a sleeve for mounting a guiding system Download PDF

Info

Publication number
EP2095060B1
EP2095060B1 EP07872426A EP07872426A EP2095060B1 EP 2095060 B1 EP2095060 B1 EP 2095060B1 EP 07872426 A EP07872426 A EP 07872426A EP 07872426 A EP07872426 A EP 07872426A EP 2095060 B1 EP2095060 B1 EP 2095060B1
Authority
EP
European Patent Office
Prior art keywords
nose
sleeve
cylindrical
guided missile
projectile
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.)
Not-in-force
Application number
EP07872426A
Other languages
German (de)
French (fr)
Other versions
EP2095060A2 (en
Inventor
Christian Martin
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.)
Ateliers Mecaniques De Pont Sur Sambre Ste
Original Assignee
Ateliers Mecaniques De Pont Sur Sambre Ste
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 Ateliers Mecaniques De Pont Sur Sambre Ste filed Critical Ateliers Mecaniques De Pont Sur Sambre Ste
Publication of EP2095060A2 publication Critical patent/EP2095060A2/en
Application granted granted Critical
Publication of EP2095060B1 publication Critical patent/EP2095060B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/01—Arrangements thereon for guidance or control

Definitions

  • the present invention relates to a guided projectile whose nose is provided with a sleeve serving as a mounting interface for a guidance system.
  • An object of the present invention is therefore to solve the problems mentioned above with the aid of a simple solution to implement, reliable and inexpensive.
  • the Figures 1 and 2 schematically represent a guided military projectile 1, such as an aerial penetration bomb.
  • the guided projectile 1 comprises in particular a cylindrical tubular body 10 terminating at the front by a nose 20 having a generally ogival shape.
  • the nose 20 comprises a front nose 21 having a first profile and ending with a penetration point 22, and a rear nose 23 having a second profile different from the profile of the nose before 21.
  • the double-pointed form of the nose nose 20 thus facilitates the penetration of the guided projectile 1 (progressive penetration) in hard targets and allows an optimal distribution of the stresses generated during the penetration phase.
  • An intermediate connecting zone 25 is situated between the front nose 21 and the rear nose 23 and connects them in a continuous manner.
  • the intermediate zone of connection 25 is constituted by a cylindrical part provided with an external thread 26.
  • Guided projectile 1 also includes a cylindrical sleeve 30 serving as a mounting interface for a NATO standard qualified guidance system (not shown), such as a laser guidance equipment cooperating with a global satellite positioning system.
  • a NATO standard qualified guidance system such as a laser guidance equipment cooperating with a global satellite positioning system.
  • the cylindrical mounting sleeve 30 is removably attached to the nose 20 of the guided projectile 1. More specifically, the cylindrical sleeve 30 has a rear portion 31 provided with an internal thread 32 for cooperating with the external thread 26 of the part cylindrical connecting 25 of the nose 20.
  • the cylindrical mounting sleeve 30 also has a flange-shaped front portion 33 extending continuously outwardly.
  • the front portion 33 of the cylindrical sleeve 30 is flared so as to oppose the maximum surface area to the impact and to concentrate the stresses in specific zones. The concentration of stresses within the cylindrical mounting sleeve 30 thus causes the destruction thereof and facilitates the subsequent penetration of the guided projectile 1.
  • the front flange 33 has an internal thread 34 intended for fixing the NATO standard guidance system in the conditions of use of the projectile 1 (for example when it is integrated with a military vehicle such as an airplane, a boat, a tank or a submarine), or a protective cap (not shown) when the projectile 1 is stored before integration.
  • a military vehicle such as an airplane, a boat, a tank or a submarine
  • a protective cap not shown
  • the cylindrical mounting sleeve 30 is made of a low-resilience material, for example a brittle steel, so as to reduce the energy dissipation during its destruction.
  • the body 10 of the projectile 1 according to the present invention is made by forging in a high-elastic, high-density and high-hardness material, for example a low-alloy steel having has undergone a suitable hardening treatment, such as quenching or carburizing.
  • the cylindrical sleeve 30 assures its function as a mounting interface for the guiding systems by keeping them close to the nose 20 of the projectile 1.
  • the cylindrical mounting sleeve 30 breaks into pieces because of the fragility of the material constituting it.
  • the destruction of the guidance system also occurs at this time, without affecting the penetration or guidance of the guided projectile 1.
  • the nose 20 is made of a rigid material and a part of absorbed stresses causes the destruction of the cylindrical sleeve 30, the guided projectile 1 can penetrate deeper into the target.
  • the present invention thus proposes a guided projectile 1 equipped with a removable cylindrical sleeve 30 which makes it possible both to easily mount a guidance system on its body 10 and to reduce the dissipation of energy during an impact against a hard target. .
  • the removable attachment of the cylindrical mounting sleeve 30 on the nose 20 of the projectile 1 can be made in another way than described, for example by axial clipping force or using a bayonet system.
  • the invention applies to any type of guided military projectile, such as a missile, a bomb, a penetrating charge, etc.
  • the guided projectile 1 according to the present invention can be launched from the ground (tank, artillery battery), from the sea (cruiser, submarine) or in the air (bomber, fighter), and the target can to be on land, at sea or in the air.
  • the profile of the rear warhead 33 may be identical to the profile of the nose before 31, that is to say that the two warheads can follow the same curvature being an extension of one another.
  • the cylindrical body may be solid or hollow so as to enclose an active or inert material.
  • the sleeve may be made of a composite material or a metal alloy having the same mechanical characteristics as those of the steel described.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Forklifts And Lifting Vehicles (AREA)
  • Mutual Connection Of Rods And Tubes (AREA)
  • Chair Legs, Seat Parts, And Backrests (AREA)
  • Toys (AREA)
  • Steering Devices For Bicycles And Motorcycles (AREA)
  • Vibration Dampers (AREA)

Abstract

The projectile (1) has a cylindrical body (10) terminated at its front by an ogive shaped nose (20). A removable cylindrical sleeve (30) allows assembly of a guiding system e.g. laser guiding equipment, at the front of the body, and is fixed on a cylindrical connection part (25) of the nose, where the guiding system conforms to OTAN standard. The connection part carries an outer thread co-operating with an inner thread formed in a rear part (31) of the sleeve. The sleeve is made of low-resilience material e.g. brittle steel, and the nose is made of rigid material e.g. steel.

Description

La présente invention concerne un projectile guidé dont le nez est muni d'un manchon servant d'interface de montage pour un système de guidage.The present invention relates to a guided projectile whose nose is provided with a sleeve serving as a mounting interface for a guidance system.

Les projectiles militaires guidés de l'art antérieur par example ceux selon WO9930106 , et en particulier les bombes aériennes actuellement en service, possèdent des interfaces de montage du système de guidage qui sont directement usinés dans leur enveloppe extérieure. La géométrie de ces bombes et de leur interface de montage réduit ainsi considérablement leurs performances de pénétration. Cependant, pour permettre l'intégration des systèmes de guidage au standard OTAN, tels qu'un système de guidage laser, un gyroscope ou encore un accéléromètre, il est nécessaire que ces bombes possèdent une interface compatible avec les normes militaires. L'usinage de cette interface dans la masse du projectile se révèle toutefois difficile et onéreux. Par ailleurs, la rupture de l'interface lors de l'impact a lieu de manière imprévisible et irrégulière, ce qui réduit les performances de pénétration. Ainsi, les projectiles guidés actuels ne donnent pas entièrement satisfaction.Guided military projectiles of the prior art for example those according to WO9930106 , and in particular the aerial bombs currently in use, have guide system mounting interfaces which are directly machined in their outer casing. The geometry of these bombs and their mounting interface significantly reduces their penetration performance. However, to allow the integration of guidance systems to the NATO standard, such as a laser guidance system, a gyroscope or an accelerometer, it is necessary that these bombs have an interface compatible with military standards. The machining of this interface in the mass of the projectile is however difficult and expensive. In addition, the rupture of the interface during the impact occurs unpredictably and irregularly, which reduces the penetration performance. Thus, the current guided projectiles are not entirely satisfactory.

Un but de la présente invention est donc de résoudre les problèmes cités précédemment à l'aide d'une solution simple à mettre en oeuvre, fiable et peu coûteuse.An object of the present invention is therefore to solve the problems mentioned above with the aid of a simple solution to implement, reliable and inexpensive.

Ce but est réalisé par l'objet de la revendication 1.This object is achieved by the subject matter of claim 1.

Selon des modes de réalisation préférés, le projectile guidé selon la présente invention peut comprendre en outre l'une au moins des caractéristiques suivantes :

  • la partie cylindrique de liaison porte un filetage externe coopérant avec un filetage interne réalisé dans une partie arrière du manchon cylindrique ;
  • le manchon cylindrique présente une collerette avant le prolongeant de manière continue vers l'extérieur ;
  • le manchon cylindrique présente, au niveau de sa collerette avant, un filetage interne pour recevoir le système de guidage lorsque le projectile est en condition d'utilisation et un bouchon de protection lorsque le projectile est stocké ;
  • le manchon cylindrique est réalisé en un matériau à faible résilience, par exemple en un acier fragile ; et
  • le nez est réalisé en un matériau à haute limite élastique, par exemple en un acier.
According to preferred embodiments, the guided projectile according to the present invention may furthermore comprise at least one of the following characteristics:
  • the cylindrical connecting portion carries an external thread cooperating with an internal thread formed in a rear portion of the cylindrical sleeve;
  • the cylindrical sleeve has a collar before extending continuously outwardly;
  • the cylindrical sleeve has, at its front flange, an internal thread for receiving the guidance system when the projectile is in use and a protective cap when the projectile is stored;
  • the cylindrical sleeve is made of a low-resilience material, for example a fragile steel; and
  • the nose is made of a high elastic limit material, for example a steel.

L'invention va maintenant être décrite plus en détail en référence à des modes de réalisation particuliers donnés à titre d'illustration uniquement et représentés sur les figures annexées dans lesquelles :

  • la figure 1 est une vue de côté montrant, séparés l'un de l'autre, un projectile et un manchon conformes à la présente invention ;
  • la figure 2 est une vue à échelle agrandie de la partie avant du projectile de la figure 1 ;
  • la figure 3 est une vue en coupe longitudinale de la figure 2 ;
  • la figure 4 est une vue de côté à échelle agrandie de la partie avant du projectile muni du manchon ; et
  • la figure 5 est une vue en coupe de la figure 4.
The invention will now be described in more detail with reference to particular embodiments given by way of illustration only and represented in the appended figures in which:
  • the figure 1 is a side view showing, separated from each other, a projectile and a sleeve according to the present invention;
  • the figure 2 is an enlarged view of the front part of the projectile of the figure 1 ;
  • the figure 3 is a longitudinal sectional view of the figure 2 ;
  • the figure 4 is an enlarged side view of the front part of the projectile fitted with the sleeve; and
  • the figure 5 is a sectional view of the figure 4 .

Les figures 1 et 2 représentent schématiquement un projectile militaire guidé 1, tel qu'une bombe aérienne de pénétration. Le projectile guidé 1 comprend notamment un corps tubulaire cylindrique 10 se terminant à l'avant par un nez 20 ayant une forme générale d'ogive.The Figures 1 and 2 schematically represent a guided military projectile 1, such as an aerial penetration bomb. The guided projectile 1 comprises in particular a cylindrical tubular body 10 terminating at the front by a nose 20 having a generally ogival shape.

Plus précisément, le nez 20 comporte une ogive avant 21 présentant un premier profil et se terminant par une pointe de pénétration 22, et une ogive arrière 23 présentant un second profil différent du profil de l'ogive avant 21. La forme à double ogive du nez 20 facilite ainsi la pénétration du projectile guidé 1 (pénétration progressive) dans des cibles dures et permet une répartition optimale des contraintes engendrées durant la phase de pénétration.More specifically, the nose 20 comprises a front nose 21 having a first profile and ending with a penetration point 22, and a rear nose 23 having a second profile different from the profile of the nose before 21. The double-pointed form of the nose nose 20 thus facilitates the penetration of the guided projectile 1 (progressive penetration) in hard targets and allows an optimal distribution of the stresses generated during the penetration phase.

Une zone intermédiaire de liaison 25 est située entre l'ogive avant 21 et l'ogive arrière 23 et relie ces dernières de manière continue. La zone intermédiaire de liaison 25 est constituée par une partie cylindrique munie d'un filetage externe 26.An intermediate connecting zone 25 is situated between the front nose 21 and the rear nose 23 and connects them in a continuous manner. The intermediate zone of connection 25 is constituted by a cylindrical part provided with an external thread 26.

Le projectile guidé 1 comporte également un manchon cylindrique 30 faisant office d'interface de montage pour un système de guidage qualifié au standard OTAN (non représenté), tel qu'un équipement de guidage laser coopérant avec un système de positionnement global par satellites.Guided projectile 1 also includes a cylindrical sleeve 30 serving as a mounting interface for a NATO standard qualified guidance system (not shown), such as a laser guidance equipment cooperating with a global satellite positioning system.

Le manchon cylindrique de montage 30 est fixé de manière amovible sur le nez 20 du projectile guidé 1. Plus précisément, le manchon cylindrique 30 présente une partie arrière 31 munie d'un filetage interne 32 destiné à coopérer avec le filetage externe 26 de la partie cylindrique de liaison 25 du nez 20.The cylindrical mounting sleeve 30 is removably attached to the nose 20 of the guided projectile 1. More specifically, the cylindrical sleeve 30 has a rear portion 31 provided with an internal thread 32 for cooperating with the external thread 26 of the part cylindrical connecting 25 of the nose 20.

Le manchon cylindrique de montage 30 présente également une partie avant en forme de collerette 33 le prolongeant de manière continue vers l'extérieur. La partie avant 33 du manchon cylindrique 30 est évasée de façon à opposer le maximum de surface à l'impact et à concentrer les contraintes dans des zones déterminées. La concentration de contraintes au sein du manchon cylindrique de montage 30 engendre ainsi la destruction de celui-ci et facilite la pénétration ultérieure du projectile guidé 1.The cylindrical mounting sleeve 30 also has a flange-shaped front portion 33 extending continuously outwardly. The front portion 33 of the cylindrical sleeve 30 is flared so as to oppose the maximum surface area to the impact and to concentrate the stresses in specific zones. The concentration of stresses within the cylindrical mounting sleeve 30 thus causes the destruction thereof and facilitates the subsequent penetration of the guided projectile 1.

La collerette avant 33 comporte un filetage interne 34 destiné à la fixation du système de guidage au standard OTAN dans les conditions d'utilisation du projectile 1 (par exemple lorsqu'il est intégré à un véhicule militaire tel qu'un avion, un bateau, un char ou un sous-marin), ou d'un bouchon de protection (non représenté) lorsque le projectile 1 est stocké avant son intégration.The front flange 33 has an internal thread 34 intended for fixing the NATO standard guidance system in the conditions of use of the projectile 1 (for example when it is integrated with a military vehicle such as an airplane, a boat, a tank or a submarine), or a protective cap (not shown) when the projectile 1 is stored before integration.

Le manchon cylindrique de montage 30 est réalisé en un matériau à faible résilience, par exemple en un acier fragile, de façon à réduire la dissipation d'énergie lors de sa destruction.The cylindrical mounting sleeve 30 is made of a low-resilience material, for example a brittle steel, so as to reduce the energy dissipation during its destruction.

Au contraire, le corps 10 du projectile 1 conforme à la présente invention, et en particulier son nez 20, est réalisé par forgeage en un matériau à haute limite élastique, à haute densité et à dureté élevée, par exemple en un acier faiblement allié ayant subi un traitement de durcissement adapté, tel qu'une trempe ou une cémentation.On the contrary, the body 10 of the projectile 1 according to the present invention, and in particular its nose 20, is made by forging in a high-elastic, high-density and high-hardness material, for example a low-alloy steel having has undergone a suitable hardening treatment, such as quenching or carburizing.

Durant toute la phase précédant la pénétration du projectile guidé dans une cible, le manchon cylindrique 30 assure sa fonction d'interface de montage des systèmes de guidage en maintenant ceux-ci à proximité du nez 20 du projectile 1.During the entire phase preceding the penetration of the guided projectile into a target, the cylindrical sleeve 30 assures its function as a mounting interface for the guiding systems by keeping them close to the nose 20 of the projectile 1.

Par contre, lors d'un impact du projectile guidé 1 contre une cible dure, par exemple un mur en béton, le manchon cylindrique de montage 30 se brise en morceaux en raison de la fragilité du matériau le constituant. La destruction du système de guidage a également lieu à ce moment là, sans que cela nuise à la pénétration ou au guidage du projectile guidé 1. En revanche, étant donné que le nez 20 est réalisé en un matériau rigide et qu'une partie des contraintes absorbées engendre la destruction du manchon cylindrique 30, le projectile guidé 1 peut pénétrer plus profondément dans la cible.On the other hand, during an impact of the guided projectile 1 against a hard target, for example a concrete wall, the cylindrical mounting sleeve 30 breaks into pieces because of the fragility of the material constituting it. The destruction of the guidance system also occurs at this time, without affecting the penetration or guidance of the guided projectile 1. On the other hand, since the nose 20 is made of a rigid material and a part of absorbed stresses causes the destruction of the cylindrical sleeve 30, the guided projectile 1 can penetrate deeper into the target.

La présente invention propose donc un projectile guidé 1 équipé d'un manchon cylindrique amovible 30 qui permet à la fois de monter facilement un système de guidage sur son corps 10 et de réduire la dissipation d'énergie lors d'un impact contre une cible dure.The present invention thus proposes a guided projectile 1 equipped with a removable cylindrical sleeve 30 which makes it possible both to easily mount a guidance system on its body 10 and to reduce the dissipation of energy during an impact against a hard target. .

Il va de soi que la description détaillée de l'objet de l'Invention, donnée uniquement à titre d'illustration, ne constitue en aucune manière une limitation, les équivalents techniques étant également compris dans le champ de la présente invention.It goes without saying that the detailed description of the subject of the invention, given solely by way of illustration, does not in any way constitute a limitation, the technical equivalents also being included in the scope of the present invention.

Ainsi, la fixation amovible du manchon cylindrique de montage 30 sur le nez 20 du projectile 1 peut être réalisée d'une autre façon que celle décrite, par exemple par clipsage axial à force ou à l'aide d'un système à baïonnette.Thus, the removable attachment of the cylindrical mounting sleeve 30 on the nose 20 of the projectile 1 can be made in another way than described, for example by axial clipping force or using a bayonet system.

L'invention s'applique à tout type de projectile militaire guidé, tel qu'un missile, une bombe, une charge pénétrante, etc. Le mode de propulsion, de même que l'endroit d'où le projectile est envoyé et l'endroit vers lequel il est dirigé, importent peu. Ainsi, le projectile guidé 1 selon la présente invention peut être lancé de la terre (tank, batterie d'artillerie), de la mer (croiseur, sous-marin) ou en l'air (bombardier, chasseur), et la cible peut être sur terre, en mer ou en l'air.The invention applies to any type of guided military projectile, such as a missile, a bomb, a penetrating charge, etc. The mode of propulsion, as well as the place from which the projectile is sent and the place to which it is directed, are of little importance. Thus, the guided projectile 1 according to the present invention can be launched from the ground (tank, artillery battery), from the sea (cruiser, submarine) or in the air (bomber, fighter), and the target can to be on land, at sea or in the air.

Le profil de l'ogive arrière 33 peut être identique au profil de l'ogive avant 31, c'est-à-dire que les deux ogives peuvent suivrent la même courbure en étant le prolongement l'une de l'autre.The profile of the rear warhead 33 may be identical to the profile of the nose before 31, that is to say that the two warheads can follow the same curvature being an extension of one another.

Le corps cylindrique peut être plein ou creux de manière à renfermer une matière active ou inerte.The cylindrical body may be solid or hollow so as to enclose an active or inert material.

Le manchon peut être réalisé en un matériau composite ou en un alliage métallique ayant les mêmes caractéristiques mécaniques que celles de l'acier décrit.The sleeve may be made of a composite material or a metal alloy having the same mechanical characteristics as those of the steel described.

Claims (6)

  1. Guided missile (1) comprising:
    - a generally cylindrical body (10) ending at the front in a cone-shaped nose (20), and a cylindrical sleeve (30) for mounting a NATO-standard guidance system at the front of the body, the nose (20) comprising a cylindrical connecting portion (25) to which the sleeve (30) is fixed,
    characterised in that the cylindrical connecting portion (25) is situated between a cone-shaped front portion (21) and a cone-shaped rear portion (23) of the nose and connects these two portions in a continuous manner.
  2. Guided missile according to claim 1, characterised in that the cylindrical connecting portion (25) is provided with an external thread (26) cooperating with an internal thread (32) formed in a rear portion (31) of the cylindrical sleeve (30).
  3. Guided missile according to claim 2, characterised in that the cylindrical sleeve (30) has a front collar (33) extending it towards the exterior in a continuous manner.
  4. Guided missile according to claim 3, characterised in that the cylindrical sleeve (30) is provided on its front collar (33) with an internal thread (34) intended to receive the guidance system when the missile (1) is ready for use and a protective cap when the missile (1) is stored.
  5. Guided missile according to any one of the preceding claims, characterised in that the cylindrical sleeve (30) is made of a material displaying low impact strength, e.g. a brittle steel.
  6. Guided missile according to any one of the preceding claims, characterised in that the nose (20) is made of a material displaying high yield strength, e.g. a steel.
EP07872426A 2006-12-21 2007-12-20 Guided missile with a sleeve for mounting a guiding system Not-in-force EP2095060B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0655787A FR2910613B1 (en) 2006-12-21 2006-12-21 GUIDE PROJECTILE HAVING A SLEEVE FOR MOUNTING A GUIDE SYSTEM
PCT/FR2007/002142 WO2008102069A2 (en) 2006-12-21 2007-12-20 Guided missile with a sleeve for mounting a guiding system

Publications (2)

Publication Number Publication Date
EP2095060A2 EP2095060A2 (en) 2009-09-02
EP2095060B1 true EP2095060B1 (en) 2011-06-08

Family

ID=38476853

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07872426A Not-in-force EP2095060B1 (en) 2006-12-21 2007-12-20 Guided missile with a sleeve for mounting a guiding system

Country Status (8)

Country Link
EP (1) EP2095060B1 (en)
KR (1) KR20090112653A (en)
CN (1) CN101578493B (en)
AT (1) ATE512347T1 (en)
BR (1) BRPI0720585A2 (en)
FR (1) FR2910613B1 (en)
WO (1) WO2008102069A2 (en)
ZA (1) ZA200905069B (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009020697A2 (en) * 2007-06-08 2009-02-12 Raytheon Company Methods and apparatus for attachment adapter for a projectile
US8291827B2 (en) 2009-09-28 2012-10-23 Raytheon Company Rocket guidance adapter

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6254031B1 (en) * 1994-08-24 2001-07-03 Lockhead Martin Corporation Precision guidance system for aircraft launched bombs
AU748098B2 (en) * 1997-12-11 2002-05-30 Lockheed Martin Corporation Shrouded aerial bomb
US6276277B1 (en) * 1999-04-22 2001-08-21 Lockheed Martin Corporation Rocket-boosted guided hard target penetrator
AUPQ776300A0 (en) * 2000-05-25 2000-08-10 Metal Storm Limited Missile control
FR2845763B1 (en) * 2002-10-11 2006-12-01 Tda Armements Sas AUTONOMOUS GUIDING SYSTEM FOR ARTILLERY MUNITION AND GUIDED ARTILLERY MUNITION
CN2656930Y (en) * 2003-12-04 2004-11-17 罗林桂 78 type platform force less cannon inner bore cannon and its analogue cannon ball
DE102005039902A1 (en) * 2005-02-04 2006-08-10 Rheinmetall Waffe Munition Gmbh Device for increasing the precision of tail-wing stabilized ammunition

Also Published As

Publication number Publication date
ZA200905069B (en) 2010-07-28
KR20090112653A (en) 2009-10-28
ATE512347T1 (en) 2011-06-15
FR2910613B1 (en) 2009-10-02
CN101578493A (en) 2009-11-11
WO2008102069A8 (en) 2009-07-30
WO2008102069A3 (en) 2008-10-30
BRPI0720585A2 (en) 2014-10-07
EP2095060A2 (en) 2009-09-02
CN101578493B (en) 2012-08-29
WO2008102069A2 (en) 2008-08-28
FR2910613A1 (en) 2008-06-27

Similar Documents

Publication Publication Date Title
FR2722873A1 (en) SYSTEM FOR PROTECTING A TARGET AGAINST MISSILES
EP1728043B1 (en) Hunting bullet comprising an expansion ring
EP0723131B1 (en) Muzzle brake for middle or large-bore barrel
US3370535A (en) Armor piercing projectile
FR2795170A1 (en) Projectile for small arms has relatively harder sub=projectile within and coaxial with bullet having profiled front part, central part and rear part carrying fin
EP2095060B1 (en) Guided missile with a sleeve for mounting a guiding system
EP0086711B1 (en) Sabot for a subcaliber projectile
FR2567257A1 (en) DEVICE FOR BRAKING A SABOT WITHIN A LAUNCHING TUBE, IN PARTICULAR FOR NON-BACK WEAPONS AND DISPERSION WEAPONS
FR2987032A1 (en) SMALL PRECISION AMMUNITION EMPLOYMENT SYSTEM ON AIRCRAFT
FR2846084A1 (en) Firearm projectile has conical nose with two or more more or less symmetrical rounded hollows and flat tip to limit penetration
EP1369349B1 (en) Weapon provided with a missile and which is mounted on a stealth aircraft, and a weapon system comprising a stealth aircraft and such a weapon
EP1541850B1 (en) Device to adapt the nozzle of a rocket motor with thrust vectoring control
EP1701131B1 (en) Armour perforating projectile
EP1375345B1 (en) Weapon provided with a missile and which is mounted on a stealth aircraft, and a weapon system comprising a stealth aircraft and such a weapon
CH651382A5 (en) HOLLOW LOAD.
EP1870640B1 (en) Warhead generating an explosively formed tubular projectile
EP0079877A1 (en) Rifle grenade
EP3999802B1 (en) Ammunition having reduced sensitivity
FR2832498A1 (en) Anti-missile launcher for armored vehicle has launcher tubes releasably mounted on turntable attached to the vehicle that is controlled in response to hostile missile detection
FR2727512A1 (en) Armour piercing projectile
FR2508624A1 (en) AMMUNITION SUCH AS HAND GRENADE, PARTICULARLY FOR THE FIGHT AGAINST ARMORED
RU2255297C1 (en) Radio-controlled missile
FR2672383A1 (en) Sub-calibre missile for automatic firearms
FR2574921A2 (en) One-piece projectile device launched by a portable firearm
EP0752571A1 (en) Short trajectory projectile

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

17P Request for examination filed

Effective date: 20090708

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

DAX Request for extension of the european patent (deleted)
GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602007015140

Country of ref document: DE

Effective date: 20110721

REG Reference to a national code

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20110608

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

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20110608

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20110608

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

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20110608

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20110909

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20110608

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20110608

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20110608

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20110608

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20110919

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

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20110608

REG Reference to a national code

Ref country code: IE

Ref legal event code: FD4D

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

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20110608

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20111010

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20111008

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20110608

Ref country code: IE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20110608

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

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20110608

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20110608

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20110608

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

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

Ref country code: FR

Payment date: 20120118

Year of fee payment: 5

26N No opposition filed

Effective date: 20120309

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

Ref country code: DE

Payment date: 20111212

Year of fee payment: 5

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

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20110608

BERE Be: lapsed

Owner name: SOC. DES ATELIERS MECANIQUES DE PONT SUR SAMBRE

Effective date: 20111231

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602007015140

Country of ref document: DE

Effective date: 20120309

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

Ref country code: MC

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20111231

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20111231

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20111231

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20111231

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

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20110608

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

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20111220

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

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20110908

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

Effective date: 20121220

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20130830

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602007015140

Country of ref document: DE

Effective date: 20130702

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

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20110608

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130702

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: 20130102

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121220

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

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121220

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

Ref country code: TR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121220