EP3121553B1 - Safing and arming device for a nose mounted fuze and fuze comprising such a device - Google Patents

Safing and arming device for a nose mounted fuze and fuze comprising such a device Download PDF

Info

Publication number
EP3121553B1
EP3121553B1 EP16177301.5A EP16177301A EP3121553B1 EP 3121553 B1 EP3121553 B1 EP 3121553B1 EP 16177301 A EP16177301 A EP 16177301A EP 3121553 B1 EP3121553 B1 EP 3121553B1
Authority
EP
European Patent Office
Prior art keywords
sleeve
levers
rotor
lever
safety device
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.)
Active
Application number
EP16177301.5A
Other languages
German (de)
French (fr)
Other versions
EP3121553A1 (en
Inventor
Nicolas Caillaut
Sylvain Jayet
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.)
Nexter Munitions SA
Original Assignee
Nexter Munitions SA
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 Nexter Munitions SA filed Critical Nexter Munitions SA
Publication of EP3121553A1 publication Critical patent/EP3121553A1/en
Application granted granted Critical
Publication of EP3121553B1 publication Critical patent/EP3121553B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/18—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved
    • F42C15/188—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved using a rotatable carrier
    • F42C15/192—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved using a rotatable carrier rotatable in a plane which is parallel to the longitudinal axis of the projectile
    • F42C15/196—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved using a rotatable carrier rotatable in a plane which is parallel to the longitudinal axis of the projectile by the action of centrifugal or inertia forces on the carrier body, e.g. the carrier having eccentrically mounted weights or eccentric centre of gravity
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/005—Combination-type safety mechanisms, i.e. two or more safeties are moved in a predetermined sequence to each other
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/18—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved
    • F42C15/188—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved using a rotatable carrier
    • F42C15/192—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved using a rotatable carrier rotatable in a plane which is parallel to the longitudinal axis of the projectile
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/24—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected by inertia means

Definitions

  • the technical field of the invention is that of safety devices and weapons for a rocket intended to equip a gyrating projectile.
  • a projectile rocket comprises in a conventional manner a safety and arming device which is intended to prevent any inadvertent operation of the primer it contains or the projectile on which this rocket is fixed.
  • the patent EP566469 describes a safety device comprising a lead-in rotor maintained misaligned by a socket.
  • the sleeve locks the rotor in the misaligned position by pressing on a flat part of the rotor.
  • the sleeve releases the rotor by moving away by inertia under the effect of the shot.
  • Such a device is suitable for ammunition of medium caliber and is located in the rear part of the projectile at the base.
  • Such a device is not suitable for warhead rockets which comprise a firing pin which is projected on impact on a target towards the rear of the projectile.
  • the invention makes it possible to add a second safety device to an ogive rocket already having a first rotor safety device as described in the patent. FR2533686 .
  • the invention also aims to solve a problem of integration of safety devices for a rocket having a firing pin configuration projected backward on impact.
  • the invention relates to a safety and arming device for a warhead rocket according to independent claim 1, intended for a gyrating projectile, device comprising a lead-in rotor held in a safety position misaligned with respect to a striker by a sleeve supported on a flattened rotor by a spring, characterized in that it comprises a flyweight intended when subjected to the longitudinal acceleration following firing, to exert a thrust force on a first end of at least one lever, the second end of the at least one lever being located under a flange of the sleeve, the thrust force of the counterweight rotating the lever or levers around a pivot point located between the two lever ends, the pivoting of the lever or levers spacing the sleeve of the rotor flat permanently to release the rotation of the latter.
  • the device comprises at least two levers evenly distributed angularly around the sleeve.
  • the levers may be constituted by tabs integral with a washer by their first end, plastically deformable tongues at their junction with the washer.
  • the weight may be annular and may exert its thrust force at the level of the washer.
  • the weight may also include a locking means in the end position when the levers have spread the sleeve of the rotor.
  • the socket may include a groove receiving the second end of the levers when the socket is pressed on the flat, to integrally translate the sleeve and the levers in the safety position of the device.
  • the invention also relates to a gyrating projectile warhead rocket comprising such a safety device.
  • a projectile 100 of medium caliber (that is to say of caliber between 12.7 mm and 75 mm) comprises a projectile body 100a, which has an ogivated part 100b and a fuse 101 fixed at the front tip of the projectile 100 (so-called ogive rocket).
  • This projectile 100 is stabilized on its trajectory thanks to a gyrating movement around its longitudinal axis 7, movement printed to the projectile by means of scratches in a barrel of a weapon (weapon not shown).
  • the rocket 101 has the function of ensuring the triggering of a payload embedded in the body 100a of the projectile such as an explosive for example.
  • the rocket 101 includes a safety and arming device designed to prevent the rocket to trigger the charge inappropriately outside a firing phase of the projectile.
  • This device contains a primer which is kept in the misaligned position by at least two locking means which are released by effects of different environments, a locking means released by the axial firing acceleration and the other released by the acceleration centrifugal consecutive shooting.
  • the rocket 101 comprises a safety device 1 comprising a rotor 2 carrying a primer 3.
  • the rotor 2 is substantially spherical and disposed in a cage 6 and the primer 3 is disposed transversely to the longitudinal axis 7 of the rocket 101.
  • the cage 6 is rotatably mounted relative to the axis 7.
  • the rotor has a flat portion 2a serving as a bearing surface at the end of a sleeve 4.
  • the sleeve 4 is pierced longitudinally so as to allow the passage of a striker 5 which is intended to impact the primer 3 when it is aligned with the striker 5 and as a result of an impact on a target.
  • the first security consists in unlocking the rotor 2 only during a centrifugal acceleration comparable to that caused by the rotation of the projectile around its longitudinal axis when it is actually pulled.
  • radial pins 20 arranged in radial bores of the cage 6 block the rotor 2. They are released from the rotor 2 after the unwinding of a spiral 21 which delays their release so that the unlocking of the rotor 2 occurs only when the projectile has left the barrel of the weapon.
  • the second security is provided by the bushing 4.
  • the bushing 4 By bearing on the flat part 2a, the bushing 4 contributes to preventing the rotor 2 from rotating. In this way the safety device 1 also keeps the rotor 2 gate primer 3 in the safety position, primer 3 misaligned with respect to the striker 5.
  • the sleeve 4 has a collar 4a at its second end facing the front AV of the rocket 101.
  • the sleeve 4 passes through a washer 9 and bears with a central portion of the washer 9 by its lower rearward facing AR of the rocket 101.
  • the face of the washer 9 facing the front of the fuze 101 supports, in the vicinity of its outer edge, an annular flyweight 8.
  • the washer 9 comprises radial tabs 10 regularly distributed angularly and extending towards the center of the washer 9.
  • These tongues 10 constitute levers 10 whose first ends are integral with the washer 9 and the second ends are disjointed one of the others and are located under the lower face of the flange 4a of the sleeve 4 visible to the figures 2 , 3 and 5 .
  • the second end of the tongues 10 is placed in a groove 22 of the sleeve 4 so as to translate the sleeve 4 in translation relative to the second ends of the levers 10.
  • the sleeve 4 will not leave its safety position accidentally during the manipulations of the rocket 101 and will remain supported on the flat portion 2a of the rotor 2 in the safety position.
  • the device 1 comprises a centering ring 11 intended to ensure the linear guide of the sleeve 4 along the longitudinal axis 7 of the device 1.
  • the edge of the centering ring 11 located under the levers 10 and between the first and the second end each lever 10 is a circular area on which each lever is supported at a tipping point 12, for pivoting each lever 10 around this point 12 according to the action applied to the ends of the levers 10.
  • the second end of the levers 10 is wedged between the underside of the flange 4a and the centering ring 11.
  • the weight 8 is able to translate longitudinally but is held in position by a ring ring 13 part of his section in a groove 14 of the weight 8 and partly in a first recess 15a carried by a cylindrical extension 17 of the ring 11 and located opposite the groove 14.
  • the ring 13 is narrowed in the groove 14 by the translational action of the weight 8 and the compression exerted by the inner wall of the cylindrical extension 17 of the ring 11.
  • the weight 8 exerts a thrust force on the washer 9 at the second ends of the levers 10.
  • the levers 10 rotate about their tipping points 12, thereby producing a lever arm effect which causes a movement of the first end of the levers toward the front AV of the device 1.
  • levers are not limiting, just as a single lever could suffice. But the implementation of several levers distributed regularly ensures safer operation.
  • the washer 9 and levers will be made of a plastically deformable material under the thrust force of the flyweight 8 to prevent the levers and especially the sleeve return to their original position once the projectile pulled.
  • the inner wall of the extension 17 of the ring 11 may comprise a second recess 15b intended to allow the expansion of the ring rod 13.
  • the recess 15b and the rod 13 thus form a means for locking the weight 8 on its end position.
  • the outer portion of the washer 9 has the function of ensuring the connection between the levers 10 but is not essential. It could indeed position each lever 10 individually and pivotally relative to the ring 11.

Description

DOMAINE TECHNIQUE DE L'INVENTIONTECHNICAL FIELD OF THE INVENTION

Le domaine technique de l'invention est celui des dispositifs de sécurité et d'armement pour une fusée destinée à équiper un projectile girant.The technical field of the invention is that of safety devices and weapons for a rocket intended to equip a gyrating projectile.

ETAT DE LA TECHNIQUE ANTERIEURESTATE OF THE PRIOR ART

Une fusée de projectile comporte d'une façon classique un dispositif de sécurité et d'armement qui est destiné à éviter tout fonctionnement intempestif de l'amorce qu'elle comporte ou du projectile sur lequel cette fusée est fixée.A projectile rocket comprises in a conventional manner a safety and arming device which is intended to prevent any inadvertent operation of the primer it contains or the projectile on which this rocket is fixed.

A cette fin il existe des dispositifs empêchant l'alignement de l'amorce avec un percuteur de la fusée. Ainsi le brevet EP566469 décrit un dispositif de sécurité comportant un rotor porte amorce maintenu désaligné par une douille. La douille bloque le rotor en position désalignée en prenant appui sur un méplat du rotor. La douille libère le rotor en s'en écartant par inertie sous l'effet du tir. Un tel dispositif est adapté aux munitions de moyen calibre et se situe en partie arrière du projectile au niveau du culot.For this purpose there are devices preventing the alignment of the primer with a firing pin of the rocket. So the patent EP566469 describes a safety device comprising a lead-in rotor maintained misaligned by a socket. The sleeve locks the rotor in the misaligned position by pressing on a flat part of the rotor. The sleeve releases the rotor by moving away by inertia under the effect of the shot. Such a device is suitable for ammunition of medium caliber and is located in the rear part of the projectile at the base.

Un tel dispositif n'est pas adapté aux fusées d'ogive qui comportent un percuteur qui est projeté à l'impact sur une cible en direction de l'arrière du projectile.Such a device is not suitable for warhead rockets which comprise a firing pin which is projected on impact on a target towards the rear of the projectile.

De plus, l'accord de normalisation STANAG 4187 édité par l'OTAN, exige que les fusées de projectile comportent une double sécurité. Ainsi l'invention permet d'ajouter un second dispositif de sécurité à une fusée d'ogive comportant déjà un premier dispositif de sécurité à rotor tel que décrit dans le brevet FR2533686 .In addition, the NATO standardization agreement STANAG 4187 requires projectile rockets to have double security. Thus, the invention makes it possible to add a second safety device to an ogive rocket already having a first rotor safety device as described in the patent. FR2533686 .

L'invention vise aussi à résoudre un problème d'intégration des dispositifs de sécurité pour une fusée ayant une configuration de percuteur projeté vers l'arrière à l'impact.The invention also aims to solve a problem of integration of safety devices for a rocket having a firing pin configuration projected backward on impact.

EXPOSE DE L'INVENTIONSUMMARY OF THE INVENTION

Ainsi, l'invention porte sur un dispositif de sécurité et d'armement pour une fusée d'ogive selon la revendication indépendante 1, destinée à un projectile girant, dispositif comportant un rotor porte amorce maintenu dans une position de sécurité désalignée par rapport à un percuteur par une douille appuyée sur un méplat du rotor par un ressort, dispositif caractérisé en ce qu'il comporte une masselotte destinée lorsqu'elle est soumise à l'accélération longitudinale consécutive au tir, à exercer un effort de poussée sur une première extrémité d'au moins un levier, la seconde extrémité de l'au moins un levier étant située sous une collerette de la douille, l'effort de poussée de la masselotte faisant pivoter le ou les leviers autour d'un point de pivot situé entre les deux extrémités du levier, le pivotement du ou des leviers écartant la douille du méplat de rotor de manière permanente pour libérer la rotation de ce dernier.Thus, the invention relates to a safety and arming device for a warhead rocket according to independent claim 1, intended for a gyrating projectile, device comprising a lead-in rotor held in a safety position misaligned with respect to a striker by a sleeve supported on a flattened rotor by a spring, characterized in that it comprises a flyweight intended when subjected to the longitudinal acceleration following firing, to exert a thrust force on a first end of at least one lever, the second end of the at least one lever being located under a flange of the sleeve, the thrust force of the counterweight rotating the lever or levers around a pivot point located between the two lever ends, the pivoting of the lever or levers spacing the sleeve of the rotor flat permanently to release the rotation of the latter.

Avantageusement, le dispositif comporte au moins deux leviers régulièrement répartis angulairement autour de la douille.Advantageously, the device comprises at least two levers evenly distributed angularly around the sleeve.

Les leviers pourront être constitués par des languettes solidaires d'une rondelle par leur première extrémité, languettes plastiquement déformables au niveau de leur jonction avec la rondelle.The levers may be constituted by tabs integral with a washer by their first end, plastically deformable tongues at their junction with the washer.

La masselotte pourra être annulaire et pourra exercer son effort de poussée au niveau de la rondelle.The weight may be annular and may exert its thrust force at the level of the washer.

La masselotte pourra par ailleurs comporter un moyen de blocage en position de fin de course lorsque les leviers ont écarté la douille du rotor.The weight may also include a locking means in the end position when the levers have spread the sleeve of the rotor.

La douille pourra comporter une gorge recevant la seconde extrémité des leviers lorsque la douille est appuyée sur le méplat, afin de solidariser en translation la douille et les leviers dans la position de sécurité du dispositif.The socket may include a groove receiving the second end of the levers when the socket is pressed on the flat, to integrally translate the sleeve and the levers in the safety position of the device.

L'invention porte aussi sur une fusée d'ogive pour projectile girant comportant un tel dispositif de sécurité.The invention also relates to a gyrating projectile warhead rocket comprising such a safety device.

BREVE DESCRIPTION DES FIGURESBRIEF DESCRIPTION OF THE FIGURES

L'invention sera mieux comprise à la lecture de la description suivante, description illustrée par les dessins annexés dans lesquels:

  • La figure 1 représente une vue d'ensemble d'un projectile comportant un dispositif de sécurité selon l'invention.
  • La figure 2 représente une vue en coupe longitudinale d'une fusée comportant un dispositif de sécurité selon l'invention en position de sécurité.
  • La figure 3 représente une vue en coupe longitudinale d'une fusée comportant un dispositif de sécurité selon l'invention en position armée.
  • La figure 4 représente une vue de dessus d'une rondelle mise en oeuvre dans le dispositif selon l'invention.
  • La figure 5 représente une vue de détail en coupe longitudinale de la fusée de la figure 2 au niveau de sa douille.
The invention will be better understood on reading the following description, a description illustrated by the appended drawings in which:
  • The figure 1 represents an overview of a projectile comprising a security device according to the invention.
  • The figure 2 is a longitudinal sectional view of a rocket comprising a safety device according to the invention in the safety position.
  • The figure 3 is a longitudinal sectional view of a rocket comprising a safety device according to the invention in the armed position.
  • The figure 4 represents a top view of a washer implemented in the device according to the invention.
  • The figure 5 represents a detail view in longitudinal section of the rocket of the figure 2 at the level of its socket.

DESCRIPTION DETAILLEE DE DIFFERENTS MODES DE REALISATION DE L'INVENTIONDETAILED DESCRIPTION OF DIFFERENT MODES FOR CARRYING OUT THE INVENTION

Selon la figure 1, un projectile 100 de moyen calibre (c'est à dire de calibre compris entre 12,7 mm et 75 mm) comporte un corps 100a de projectile, qui présente une partie ogivée 100b et une fusée 101 fixée au niveau de la pointe avant du projectile 100 (fusée dite d'ogive).According to figure 1 , a projectile 100 of medium caliber (that is to say of caliber between 12.7 mm and 75 mm) comprises a projectile body 100a, which has an ogivated part 100b and a fuse 101 fixed at the front tip of the projectile 100 (so-called ogive rocket).

Ce projectile 100 est stabilisé sur sa trajectoire grâce à un mouvement de giration autour de son axe longitudinal 7, mouvement imprimé au projectile au moyen de rayures dans un canon d'une arme (arme non représentée). La fusée 101 a pour fonction d'assurer le déclenchement d'une charge utile embarquée dans le corps 100a du projectile telle qu'un explosif par exemple. Comme nous allons le voir après, la fusée 101 comporte un dispositif de sécurité et d'armement destiné à empêcher la fusée de déclencher la charge de manière inappropriée en dehors d'une phase de tir du projectile.This projectile 100 is stabilized on its trajectory thanks to a gyrating movement around its longitudinal axis 7, movement printed to the projectile by means of scratches in a barrel of a weapon (weapon not shown). The rocket 101 has the function of ensuring the triggering of a payload embedded in the body 100a of the projectile such as an explosive for example. As we will see later, the rocket 101 includes a safety and arming device designed to prevent the rocket to trigger the charge inappropriately outside a firing phase of the projectile.

Ce dispositif renferme une amorce qui est maintenue en position désalignée par au moins deux moyens de verrouillage qui sont libérés par des effets d'environnements différents, un moyen de verrouillage libéré par l'accélération axiale de tir et l'autre libéré par l'accélération centrifuge consécutive au tir.This device contains a primer which is kept in the misaligned position by at least two locking means which are released by effects of different environments, a locking means released by the axial firing acceleration and the other released by the acceleration centrifugal consecutive shooting.

Selon la figure 2, la fusée 101 comporte un dispositif de sécurité 1 comportant un rotor 2 portant une amorce 3. Le rotor 2 est sensiblement sphérique et disposé dans une cage 6 et l'amorce 3 est disposée transversalement à l'axe longitudinal 7 de la fusée 101. La cage 6 est montée tournante par rapport à l'axe 7. Le rotor comporte un méplat 2a servant de face d'appui à l'extrémité d'une douille 4. La douille 4 est percée longitudinalement de manière à permettre le passage d'un percuteur 5 qui est destiné à impacter l'amorce 3 lorsqu'elle est alignée avec le percuteur 5 et comme suite à un impact sur une cible.According to figure 2 , the rocket 101 comprises a safety device 1 comprising a rotor 2 carrying a primer 3. The rotor 2 is substantially spherical and disposed in a cage 6 and the primer 3 is disposed transversely to the longitudinal axis 7 of the rocket 101. The cage 6 is rotatably mounted relative to the axis 7. The rotor has a flat portion 2a serving as a bearing surface at the end of a sleeve 4. The sleeve 4 is pierced longitudinally so as to allow the passage of a striker 5 which is intended to impact the primer 3 when it is aligned with the striker 5 and as a result of an impact on a target.

Afin d'empêcher l'alignement du rotor 2 en dehors des conditions d'emploi opérationnelles, deux sécurités sont mises en place.In order to prevent the alignment of the rotor 2 outside the operational conditions of use, two safeties are put in place.

La première sécurité, décrite dans le brevet EP105001 , consiste à ne débloquer le rotor 2 que lors d'une accélération centrifuge comparable à celle induite par la mise en rotation du projectile autour de son axe longitudinal lorsqu'il est effectivement tiré. Pour cela des goupilles radiales 20 disposées dans des perçages radiaux de la cage 6 bloquent le rotor 2. Elles sont dégagées du rotor 2 après le déroulement d'un spiral 21 qui temporise leur dégagement afin que le déblocage du rotor 2 n'intervienne que lorsque le projectile a quitté le tube de l'arme.The first security, described in the patent EP105001 , consists in unlocking the rotor 2 only during a centrifugal acceleration comparable to that caused by the rotation of the projectile around its longitudinal axis when it is actually pulled. For this radial pins 20 arranged in radial bores of the cage 6 block the rotor 2. They are released from the rotor 2 after the unwinding of a spiral 21 which delays their release so that the unlocking of the rotor 2 occurs only when the projectile has left the barrel of the weapon.

La seconde sécurité est apportée par la douille 4. En prenant appui sur le méplat 2a, la douille 4 contribue à empêcher le rotor 2 de tourner. De cette manière le dispositif 1 de sécurité maintient également le rotor 2 porte amorce 3 en position de sécurité, amorce 3 désalignée par rapport au percuteur 5.The second security is provided by the bushing 4. By bearing on the flat part 2a, the bushing 4 contributes to preventing the rotor 2 from rotating. In this way the safety device 1 also keeps the rotor 2 gate primer 3 in the safety position, primer 3 misaligned with respect to the striker 5.

On notera que la douille 4 comporte une collerette 4a à sa seconde extrémité orientée vers l'avant AV de la fusée 101. La douille 4 traverse une rondelle 9 et est en appui avec une partie centrale de la rondelle 9 par sa face inférieure orientée vers l'arrière AR de la fusée 101.Note that the sleeve 4 has a collar 4a at its second end facing the front AV of the rocket 101. The sleeve 4 passes through a washer 9 and bears with a central portion of the washer 9 by its lower rearward facing AR of the rocket 101.

La face de la rondelle 9 orientée vers l'avant AV de la fusée 101 supporte, au voisinage de son bord externe, une masselotte annulaire 8.The face of the washer 9 facing the front of the fuze 101 supports, in the vicinity of its outer edge, an annular flyweight 8.

Comme visible à la figure 4, la rondelle 9 comporte des languettes 10 radiales régulièrement réparties angulairement et s'étendant vers le centre de la rondelle 9. Ces languettes 10 constituent des leviers 10 dont les premières extrémités sont solidaires de la rondelle 9 et les secondes extrémités sont disjointes les unes des autres et sont situées sous la face inférieure de la collerette 4a de la douille 4 visible aux figures 2, 3 et 5.As visible at figure 4 , the washer 9 comprises radial tabs 10 regularly distributed angularly and extending towards the center of the washer 9. These tongues 10 constitute levers 10 whose first ends are integral with the washer 9 and the second ends are disjointed one of the others and are located under the lower face of the flange 4a of the sleeve 4 visible to the figures 2 , 3 and 5 .

On peut voir à la figure 5 que la seconde extrémité des languettes 10 est placée dans une gorge 22 de la douille 4 de manière à solidariser en translation la douille 4 relativement aux secondes extrémités des leviers 10. Ainsi, la douille 4 ne quittera pas sa position de sécurité de manière accidentelle durant les manipulations de la fusée 101 et restera appuyée sur le méplat 2a du rotor 2 en position de sécurité.We can see at the figure 5 that the second end of the tongues 10 is placed in a groove 22 of the sleeve 4 so as to translate the sleeve 4 in translation relative to the second ends of the levers 10. Thus, the sleeve 4 will not leave its safety position accidentally during the manipulations of the rocket 101 and will remain supported on the flat portion 2a of the rotor 2 in the safety position.

Le dispositif 1 comporte une bague 11 de centrage destinée à assurer le guidage linéaire de la douille 4 selon l'axe longitudinal 7 du dispositif 1. Le bord de la bague de centrage 11 situé sous les leviers 10 et entre la première et la seconde extrémité de chaque levier 10 est une zone circulaire sur laquelle chaque levier est en appui au niveau d'un point de bascule 12, permettant de faire pivoter chaque levier 10 autour de ce point 12 selon l'action appliquée aux extrémités des leviers 10.The device 1 comprises a centering ring 11 intended to ensure the linear guide of the sleeve 4 along the longitudinal axis 7 of the device 1. The edge of the centering ring 11 located under the levers 10 and between the first and the second end each lever 10 is a circular area on which each lever is supported at a tipping point 12, for pivoting each lever 10 around this point 12 according to the action applied to the ends of the levers 10.

En position de sécurité telle qu'à la figure 2, les leviers 10 ont leur première extrémité en porte-à-faux par rapport à leur point de bascule 12.In a safety position such as figure 2 the levers 10 have their first end cantilevered with respect to their tipping point 12.

On notera qu'en position de sécurité, la seconde extrémité des leviers 10 est coincée entre le dessous de la collerette 4a et la bague de centrage 11. La masselotte 8 est apte à se translater longitudinalement mais elle est maintenue en position par un jonc torique 13 élastique situé pour partie de sa section dans une gorge 14 de la masselotte 8 et pour partie dans un premier évidement 15a porté par un prolongement cylindrique 17 de la bague 11 et situé en regard de la gorge 14.Note that in the safety position, the second end of the levers 10 is wedged between the underside of the flange 4a and the centering ring 11. The weight 8 is able to translate longitudinally but is held in position by a ring ring 13 part of his section in a groove 14 of the weight 8 and partly in a first recess 15a carried by a cylindrical extension 17 of the ring 11 and located opposite the groove 14.

Selon la figure 3, lorsque le projectile est tiré, la violente accélération subie par la fusée 101 impose par inertie un recul de la masselotte 8 vers l'arrière AR du dispositif selon l'axe longitudinal 7.According to figure 3 when the projectile is fired, the violent acceleration experienced by the rocket 101 imposes by inertia a recoil of the weight 8 towards the rear AR of the device along the longitudinal axis 7.

Ce faisant, le jonc 13 torique est rétreint dans la gorge 14 par l'action de translation de la masselotte 8 et la compression exercée par les parois interne du prolongement cylindrique 17 de la bague 11. La masselotte 8 exerce un effort de poussée sur la rondelle 9 au niveau des secondes extrémités des leviers 10. Les leviers 10 opèrent une rotation autour de leurs points de bascule 12, produisant ainsi un effet de bras de levier qui provoque un mouvement de la première extrémité des leviers vers l'avant AV du dispositif 1.In doing so, the ring 13 is narrowed in the groove 14 by the translational action of the weight 8 and the compression exerted by the inner wall of the cylindrical extension 17 of the ring 11. The weight 8 exerts a thrust force on the washer 9 at the second ends of the levers 10. The levers 10 rotate about their tipping points 12, thereby producing a lever arm effect which causes a movement of the first end of the levers toward the front AV of the device 1.

En se levant, les premières extrémités des leviers soulèvent la douille 4 via sa collerette 4a et la translatent axialement au travers de la bague de centrage 11. La douille 4 n'est alors plus en appui avec le méplat du rotor qui pourra ensuite tourner pour aligner l'amorce 3 avec le percuteur 5, lorsque les goupilles de verrouillage centrifuge 20 auront été éjectées.By rising, the first ends of the levers lift the sleeve 4 via its flange 4a and the translatent axially through the centering ring 11. The sleeve 4 is then no longer supported with the flat part of the rotor which can then turn to align the primer 3 with the firing pin 5, when the centrifugal locking pins 20 have been ejected.

Il est évident pour l'Homme du métier que le nombre de leviers n'est pas limitatif, de même qu'un unique levier pourrait suffire. Mais la mise en place de plusieurs leviers répartis régulièrement assure un fonctionnement plus sûr.It is obvious to those skilled in the art that the number of levers is not limiting, just as a single lever could suffice. But the implementation of several levers distributed regularly ensures safer operation.

La rondelle 9 et ses leviers seront réalisés dans un matériau plastiquement déformable sous l'effort de poussée de la masselotte 8 afin d'empêcher que les leviers et surtout la douille ne reviennent à leur position d'origine une fois le projectile tiré.The washer 9 and levers will be made of a plastically deformable material under the thrust force of the flyweight 8 to prevent the levers and especially the sleeve return to their original position once the projectile pulled.

Toujours dans le but d'empêcher le retour en position de sécurité de la douille 4, la paroi interne du prolongement 17 de la bague 11 pourra comporter un second évidement 15b destiné à permettre l'expansion du jonc torique 13. L'évidement 15b et le jonc 13 forment ainsi un moyen de blocage de la masselotte 8 sur sa position de fin de course.Still in order to prevent the return to the safety position of the sleeve 4, the inner wall of the extension 17 of the ring 11 may comprise a second recess 15b intended to allow the expansion of the ring rod 13. The recess 15b and the rod 13 thus form a means for locking the weight 8 on its end position.

On notera que la partie externe de la rondelle 9 a pour fonction d'assurer la liaison entre les leviers 10 mais n'est pas indispensable. On pourrait en effet positionner chaque levier 10 individuellement et de façon pivotante par rapport à la bague 11.Note that the outer portion of the washer 9 has the function of ensuring the connection between the levers 10 but is not essential. It could indeed position each lever 10 individually and pivotally relative to the ring 11.

Claims (7)

  1. Safety and arming device (1) for a point detonating fuse (101) for a rotating projectile, the device (1) having a rotor (2) carrying a primer (3) held in a safe non-aligned position in relation to a striker (5) by a sleeve (4) bearing on a flat surface (2a) of the rotor (2), the device being characterised in that it has a flyweight (8) which when subjected to the longitudinal acceleration resulting from firing, is designed to exert a thrust force on a first end of at least one lever (10), the second end of the at least one lever (10) being located under a collar (4a) of the sleeve (4), the thrust force of the flyweight (8) causing the lever or levers (10) to pivot about a pivot point (12) located between the two ends of the lever (10), the pivoting of the lever or levers (10) moving the sleeve (4) away from the flat surface (2a) of the rotor (2) permanently in order to release the rotation of the latter.
  2. Safety device (1) according to claim 1, characterised in that it has at least two levers (10) which are uniformly distributed angularly around the sleeve (4).
  3. Safety device according to claim 2, characterised in that the levers (10) are constituted by tabs (10) which are locked to a washer (9) by their first end, the tabs (10) being plastically deformable at their junction with the washer (9).
  4. Safety device (1) according to claim 3, characterised in that the flyweight (8) is annular and exerts its thrust force at the washer (9).
  5. Safety device (1) according to one of claims 1 to 4, characterised in that the flyweight (8) has a blocking means (13, 15b) at the end of travel position when the levers (10) have moved the sleeve (4) away from the rotor (5).
  6. Safety device (1) according to one of claims 1 to 5, characterised in that the sleeve (4) has a recess (22) receiving the second end of the levers (10) when the sleeve is bearing on the flat in order to lock in translation the sleeve (4) and the levers (10) in the safe position of the device.
  7. Point detonating fuse (101) for a rotating projectile having a safety device according to one of claims 1 to 6.
EP16177301.5A 2015-07-24 2016-06-30 Safing and arming device for a nose mounted fuze and fuze comprising such a device Active EP3121553B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1501604A FR3039267B1 (en) 2015-07-24 2015-07-24 SAFETY AND ARMING DEVICE FOR AN OGIVE ROCKET AND ROCKER COMPRISING SUCH A DEVICE

Publications (2)

Publication Number Publication Date
EP3121553A1 EP3121553A1 (en) 2017-01-25
EP3121553B1 true EP3121553B1 (en) 2017-12-27

Family

ID=54937130

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16177301.5A Active EP3121553B1 (en) 2015-07-24 2016-06-30 Safing and arming device for a nose mounted fuze and fuze comprising such a device

Country Status (6)

Country Link
US (1) US10041775B2 (en)
EP (1) EP3121553B1 (en)
ES (1) ES2659813T3 (en)
FR (1) FR3039267B1 (en)
NO (1) NO3121553T3 (en)
PT (1) PT3121553T (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102022106883A1 (en) * 2022-03-23 2023-09-28 Rheinmetall Air Defence Ag Fuse unit for a detonator, use of the fuse unit and method for activating a detonator with this fuse unit

Family Cites Families (50)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2232714A (en) * 1937-10-01 1941-02-25 Marvin L Mathsen Mechanical time fuse
US2412695A (en) * 1942-01-07 1946-12-17 Rost Helge Fabian Projectile
US2609753A (en) * 1949-03-23 1952-09-09 Herbert L Rosenberg Fuse functioning mechanism
US2715873A (en) * 1950-01-25 1955-08-23 Parke H Thompson Fuze
US2863393A (en) * 1955-06-09 1958-12-09 Eugene N Sheeley Safety and arming mechanism
US2962968A (en) * 1955-09-21 1960-12-06 Jr Alois G Neuwirth Centrifugally armed and selfdestroying impact fuze
US2943573A (en) * 1959-01-05 1960-07-05 Gilbert E Graser Self destruction device
US3117522A (en) * 1960-11-30 1964-01-14 Frank C Hutchison Set-back device for fuze
US3136252A (en) * 1962-08-07 1964-06-09 Sabla Louis J De Force discriminating mechanism
GB1165754A (en) * 1965-10-25 1969-10-01 Bombrini Parodi Delfino Spa Mechanical Percussion Fuse for Rockets
CH430505A (en) * 1965-12-06 1967-02-15 Oerlikon Buehrle Holding Ag Impact fuse
US4040358A (en) * 1965-12-14 1977-08-09 Avco Corporation Hydraulic delayed arming fuze
US3397640A (en) * 1966-10-28 1968-08-20 Gen Electric Fuze with improved time delay and self-destruct mechanism
US3620163A (en) * 1968-08-12 1971-11-16 Kdi Corp Second environment safety for projectiles
FR2041039B1 (en) * 1969-02-03 1975-12-26 Snia Viscosa
US3595169A (en) * 1969-09-18 1971-07-27 Gen Electric Time delay fuze
DE2061765A1 (en) * 1970-12-15 1972-06-29 Gebr. Junghans Gmbh, 7230 Schramberg Fuzes for twist projectiles
US3996857A (en) * 1972-05-10 1976-12-14 The United States Of America As Represented By The Secretary Of The Army Jungle penetration munition
LU65387A1 (en) * 1972-05-18 1972-08-24 Interep Associes Sa DEVICE FOR HAND GRENADE
FR2256697A5 (en) * 1972-07-20 1975-07-25 Haut Rhin Manufacture Machines
FR2203500A5 (en) * 1972-10-13 1974-05-10 France Etat
BE828255R (en) * 1974-05-06 1975-08-18 MECHANISM FOR FIRE A PROJECTILE, SUCH AS A FULIS GRENADE
US4242964A (en) * 1978-12-18 1981-01-06 Ares, Inc. Explosive fuse for projectile
US4237788A (en) * 1978-12-18 1980-12-09 Ares, Inc. Explosive fuse for ballistic projectile
EP0042957B1 (en) * 1980-07-02 1984-08-15 Rheinmetall GmbH Fuse for spinning projectiles
US4494459A (en) * 1980-09-05 1985-01-22 General Electric Company Explosive projectile
DE3049082C2 (en) * 1980-12-24 1984-08-23 Diehl GmbH & Co, 8500 Nürnberg Safety device for a detonator
EP0068534B1 (en) * 1981-06-30 1985-01-23 Werkzeugmaschinenfabrik Oerlikon-Bührle AG Safety means for a fuze of a spin-stabilised projectile
FR2533686B1 (en) * 1982-09-24 1987-01-02 Manurhin SECURITY DEVICE WITH A ROTATING CAGE FOR A GIRATORY PROJECTILE
FR2537265A1 (en) * 1982-12-07 1984-06-08 Manurhin AN ANNULAR LOCKING DEVICE SAFETY DEVICE FOR GYRATORY PROJECTILE
US4480551A (en) * 1983-06-08 1984-11-06 Whittaker Corporation Point-detonating variable time-delayed fuze
US4604953A (en) * 1984-04-26 1986-08-12 Hi-Shear Corporation Void-sensing fuze
DE3435402A1 (en) * 1984-09-27 1986-04-03 Gebrüder Junghans GmbH, 7230 Schramberg SPHERICAL SAFETY ROTOR OF A SPIRAL BULLET IGNITION
DE8437159U1 (en) * 1984-12-19 1986-04-10 Diehl GmbH & Co, 8500 Nürnberg Detonator for a bomblet
DE3831862A1 (en) * 1988-09-20 1990-03-22 Diehl Gmbh & Co SAFETY DEVICE FOR A SWIRL-FLOWER
US5081929A (en) * 1989-10-12 1992-01-21 Mertens William J Projectile having a movable interior fuze
US5243912A (en) * 1991-12-09 1993-09-14 General Electric Co. Arming delay, dual environment safe, fuze
FR2689972B1 (en) * 1992-04-14 1995-08-11 Manurhin Defense SECURITY AND ARMING DEVICE FOR A PROJECTILE ROCKET COMPRISING AN ANTI-VIBRATORY MEANS.
US5355801A (en) * 1993-06-21 1994-10-18 Donahue William J Small caliber fuze with arming delay, second impact and graze sensitivity
FR2730051B1 (en) * 1995-01-30 1997-03-21 Manurhin Defense SECURITY AND ARMING DEVICE FOR PROJECTILE ROCKET
US6314887B1 (en) * 2000-02-22 2001-11-13 The United States Of America As Represented By The Secretary Of The Army Microelectromechanical systems (MEMS)-type high-capacity inertial-switching device
US6964231B1 (en) * 2002-11-25 2005-11-15 The United States Of America As Represented By The Secretary Of The Army Miniature MEMS-based electro-mechanical safety and arming device
GB0301690D0 (en) * 2003-01-24 2003-02-26 Olympic Technologies Ltd Safety system
DE10302967B4 (en) * 2003-01-25 2006-04-06 Junghans Feinwerktechnik Gmbh & Co. Kg Projectile fuze with a force element
US7258068B2 (en) * 2003-06-30 2007-08-21 Kdi Precision Products, Inc. Safety and arming apparatus and method for a munition
FR2864219B1 (en) * 2003-12-22 2006-02-24 Giat Ind Sa DEVICE FOR DECONFINING A MUNITION ENVELOPE
US7600475B1 (en) * 2005-03-31 2009-10-13 The United States Of America As Represented By The Secretary Of The Army Multi-mode fuze
DE102005029326B4 (en) * 2005-06-24 2007-04-05 Junghans Feinwerktechnik Gmbh & Co. Kg Securing device for a twist projectile igniter with a spherical rotor
FR2959304B1 (en) * 2010-04-27 2014-10-17 Nexter Munitions INFLATION-BASED INITIATION STARTING DEVICE FOR PROJECTILE
US8151709B1 (en) * 2010-04-30 2012-04-10 The United States Of America As Represented By The Secretary Of The Army Anti-setback spin clip application

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
FR3039267A1 (en) 2017-01-27
US20170138714A1 (en) 2017-05-18
PT3121553T (en) 2018-02-26
FR3039267B1 (en) 2017-07-14
EP3121553A1 (en) 2017-01-25
NO3121553T3 (en) 2018-05-26
US10041775B2 (en) 2018-08-07
ES2659813T3 (en) 2018-03-19

Similar Documents

Publication Publication Date Title
FR2650662A1 (en) PYROTECHNIC CHAIN PRIMING DEVICE FOR SUBUSTING OBUS CARGO
CH634142A5 (en) MECHANISM FOR LAUNCHING A SUB-CALIBER PROJECTILE.
EP2239535B1 (en) Ignition device of a munition by percussion
FR2954485A1 (en) LAUNCHING DEVICE FOR PROJECTILE OF ARTILLERY UNDER CALIBER.
EP1045221B1 (en) Aerodynamic brake for reducing the velocity of a projectile on its trajectory
EP1006335B1 (en) Device for reducing the velocity of a projectile on its trajectory
FR2881517A1 (en) "SAFETY DEVICE FOR A ROTATION STABILIZED PROJECTILE SHAFT"
EP0086711B1 (en) Sabot for a subcaliber projectile
EP3121553B1 (en) Safing and arming device for a nose mounted fuze and fuze comprising such a device
EP0566469B1 (en) Safety and arming device for the fuse of a projectile comprising an anti-vibratory means
EP2434252B1 (en) Security and arming device for a gyrostabilised explosive projectile and priming device implementing such a security and arming device
EP2913628B1 (en) Artillery projectile warhead fuse comprising a braking device acting in flight direction
EP0724132B1 (en) Safety and arming device for a projectile fuse
EP1597534B1 (en) Projectile fuze
EP4008992B1 (en) Spin-stabilised projectile
CH617262A5 (en)
EP0117373B1 (en) Safety mechanism for spinning projectile fuzes
FR2672673A1 (en) Priming device for a subprojectile
FR3037390A1 (en) STABILIZATION DEVICE AND PROJECTILE EQUIPPED WITH SUCH A DEVICE
EP1548392A1 (en) Device for the deployment of the vanes of a projectile
FR2641859A1 (en) SAFETY FOR LARGABLE AIRBORNE LOAD
EP2921812B1 (en) Spin-stabilised projectile
WO2022002462A1 (en) Fuze comprising a self-destruction device for a gyratory projectile
EP1332329A1 (en) Priming device for the explosive charge of a submunition
FR3040482A1 (en) OGIVE ROCKER WITH PERCUTOR

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

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

17P Request for examination filed

Effective date: 20170216

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20170802

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM 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: AT

Ref legal event code: REF

Ref document number: 958675

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180115

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: 602016001221

Country of ref document: DE

REG Reference to a national code

Ref country code: PT

Ref legal event code: SC4A

Ref document number: 3121553

Country of ref document: PT

Date of ref document: 20180226

Kind code of ref document: T

Free format text: AVAILABILITY OF NATIONAL TRANSLATION

Effective date: 20180214

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: FIAMMENGHI-FIAMMENGHI, CH

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2659813

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20180319

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

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: 20171227

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20171227

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 958675

Country of ref document: AT

Kind code of ref document: T

Effective date: 20171227

REG Reference to a national code

Ref country code: NO

Ref legal event code: T2

Effective date: 20171227

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: 20180327

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: 20180328

Ref country code: HR

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: 20171227

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: 20171227

Ref country code: RS

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: 20171227

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 3

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: 20171227

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

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: 20171227

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: 20171227

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: 20171227

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: 20171227

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: 20171227

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: 20171227

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: 20180427

Ref country code: SM

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: 20171227

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: 20171227

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602016001221

Country of ref document: DE

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

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: 20171227

26N No opposition filed

Effective date: 20180928

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

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: 20171227

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 FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

Ref country code: LU

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

Effective date: 20180630

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

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

Ref country code: IE

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

Effective date: 20180630

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 FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

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: 20171227

Ref country code: MK

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

Effective date: 20171227

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; INVALID AB INITIO

Effective date: 20160630

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

Ref country code: AL

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: 20171227

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

Ref country code: PT

Payment date: 20230524

Year of fee payment: 8

Ref country code: NO

Payment date: 20230525

Year of fee payment: 8

Ref country code: IT

Payment date: 20230523

Year of fee payment: 8

Ref country code: FR

Payment date: 20230524

Year of fee payment: 8

Ref country code: DE

Payment date: 20230523

Year of fee payment: 8

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

Ref country code: SE

Payment date: 20230523

Year of fee payment: 8

Ref country code: FI

Payment date: 20230523

Year of fee payment: 8

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

Ref country code: BE

Payment date: 20230523

Year of fee payment: 8

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

Ref country code: GB

Payment date: 20230523

Year of fee payment: 8

Ref country code: ES

Payment date: 20230703

Year of fee payment: 8

Ref country code: CH

Payment date: 20230702

Year of fee payment: 8