[go: up one dir, main page]

EP2626665A1 - Method for lifting a firing safety and projectile implementing said method - Google Patents

Method for lifting a firing safety and projectile implementing said method Download PDF

Info

Publication number
EP2626665A1
EP2626665A1 EP20130290023 EP13290023A EP2626665A1 EP 2626665 A1 EP2626665 A1 EP 2626665A1 EP 20130290023 EP20130290023 EP 20130290023 EP 13290023 A EP13290023 A EP 13290023A EP 2626665 A1 EP2626665 A1 EP 2626665A1
Authority
EP
European Patent Office
Prior art keywords
projectile
wind wheel
tapered
axis
envelope
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.)
Granted
Application number
EP20130290023
Other languages
German (de)
French (fr)
Other versions
EP2626665B1 (en
Inventor
Laurent Carton
Bernard Tisseron
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.)
MBDA France SAS
Original Assignee
MBDA France SAS
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 MBDA France SAS filed Critical MBDA France SAS
Publication of EP2626665A1 publication Critical patent/EP2626665A1/en
Application granted granted Critical
Publication of EP2626665B1 publication Critical patent/EP2626665B1/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
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/28—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges operated by flow of fluent material, e.g. shot, fluids
    • F42C15/295—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges operated by flow of fluent material, e.g. shot, fluids operated by a turbine or a propeller; Mounting means therefor

Definitions

  • the present invention relates to a method for lifting at least one firing security of a military load carried by a projectile, and a projectile implementing such a method.
  • the present invention aims to overcome these disadvantages.
  • Said arming device may comprise a driven movable valve, from the wind wheel, by means of a deflection device and said movable plug may be moved by a screw driven in rotation by said return device angle.
  • the axis of said screw moving the movable plug is at least substantially orthogonal to the axis of the wind wheel.
  • a controllable coupling device is provided on the rotation shaft of said wind wheel to allow it to be decoupled from the rest of said arming device, and a contactor can control said coupling device, said contactor being actuated by an element of the cocking device, preferably the plug, when said cocking device has inhibited the action of the safety device.
  • the wheel can be made to turn crazy, to further reduce the aerodynamic drag it generates.
  • the figure 1 shows, in perspective, a missile equipped with a wind wheel in accordance with the present invention.
  • the Figure 2A is an enlarged schematic section along line II-II of the figure 1 , illustrating the arrangement of the wind wheel of the present invention, when the missile is in storage or awaiting firing.
  • the Figure 2B is an enlarged schematic section along line II-II of the figure 1 , illustrating the arrangement of the wind wheel of the present invention, when the missile is armed.
  • the figure 3 shows, in perspective, an embodiment of the wind wheel according to the present invention, associated with a disengagement device.
  • the missile 1, shown on the figure 1 comprises a fuselage 2, longitudinal axis LL, which encloses a military load WH and in which is formed a lateral opening 3, of longitudinally elongate shape. Through said lateral opening 3 pass, from the inside to the outside of the fuselage 2, the ends of the blades 4 of a wind wheel 5 disposed inside said fuselage 2.
  • the axis of rotation XX of the wind wheel 5 is substantially orthogonal to the longitudinal axis LL of the fuselage 2 of the missile 1.
  • the wind wheel 5 comprises a shaft 6, of axis XX, inside the fuselage 2 and extended by an endless screw 7, meshing with a pinion 8, to form a 90 ° angle gear.
  • the axis YY of the pinion 8 is orthogonal to the axis XX of the wind wheel 5.
  • the axis YY of the pinion 8 can, in addition, as illustrated by the Figures 2A and 2B , be orthogonal to the LL axis of missile 1.
  • a body 9 Inside the fuselage 2 is also a body 9 inside which is mounted a safety device 10 preventing the firing of the military load WH.
  • a plug 11 carrying a member 12 adapted to act on the safety device 10 to inhibit the action.
  • the plug 11 is engaged with a screw 13, integral with the pinion 8 and coaxial with it and meshing with a thread 14 of said plug 11.
  • a pin 15 loaded by a spring 16 kept compressed by a key 17 is able to lock the plug 11 in the body 9.
  • the Figure 2A illustrates the arrangement of the various elements 2 to 16 which have just been described, when the missile 1 is in storage, maintenance, transport or any other phase where the military load WH should not be armed.
  • the pin 15 held by the key 17 blocks the plug 11 inside the body 9, which has the consequence that the member 12 can not act on the safety device 10 and that the wind wheel 5 is locked in rotation through the screw 13 and the bevel gear 7, 8.
  • the missile 1 When the missile 1 is to be launched, it first eliminates the key 17, so that the spring 16 ejects the spindle 15 and blocking the bushel 11 in the body 9 is removed (see Figure 2B ). Then, the launching of the missile 1 and the result that the peripheral parts of the blades 4 of the wind wheel 5, which, passing through said lateral opening 3, are outside the fuselage 1, are subjected to the pressure of the aerodynamic flow surrounding said fuselage 2. The wheel 5, interior to the fuselage 2, is rotated, the peripheral ends of the blades 4 through successively said lateral opening 3.
  • the screw 13 is itself driven in rotation about its axis YY by the angle gear 7, 8 and, by its cooperation with the thread 14, it moves the plug 11 and the member 12 towards the safety device 10.
  • the progressive advance of the bushel towards the safety device 10 depends, among other parameters, on the speed of the missile 1, the aerodynamic performance of the wheel 5, the gear ratio between the worm 7 and the pinion 8 and the pitch of the screw 13 and the thread 14. Given the distance that the bushel 11 must travel for that its member 12 inhibits the security imposed by the device 10, the lifting time of this security is perfectly defined.
  • the wind wheel 5 is decoupled from the plug 11 to turn crazy.
  • a controllable coupling device 18 on the shaft 6, between the wind wheel 5 and the worm 7.
  • a contactor 19 whose position corresponds to the end of the time of lifting of the security by the organ 12 (see figure 3 ).

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Toys (AREA)

Abstract

- Procédé pour la levée d'une sécurité de mise à feu et projectile mettant en oeuvre ce procédé.
- Selon l'invention, on met en oeuvre, pour lever ladite sécurité, une roue éolienne (5), qui est agencée à l'intérieur du fuselage (2) du projectile, mais dont les pales (4) traversent ledit fuselage (2) par une ouverture latérale (3)

Figure imgaf001
- Method for lifting a firing and projectile security implementing this method.
According to the invention, a wind wheel (5), which is arranged inside the fuselage (2) of the projectile but whose blades (4) pass through said fuselage (2), is used to lift said security. ) by a side opening (3)
Figure imgaf001

Description

La présente invention concerne un procédé pour lever au moins une sécurité de mise à feu d'une charge militaire portée par un projectile, ainsi qu'un projectile mettant en oeuvre un tel procédé.The present invention relates to a method for lifting at least one firing security of a military load carried by a projectile, and a projectile implementing such a method.

On sait que certaines bombes aériennes sont munies d'une roue éolienne externe inamovible, mise en rotation aérodynamique au cours de leur descente vers le sol et utilisée pour armer la charge militaire desdites bombes. Dans un mode particulier de réalisation de mine décrit par le document DE 3322 926 A1 , une roue éolienne est prévue à l'extérieur du corps de la mine pour pouvoir tourner autour de l'axe dudit corps.It is known that some aerial bombs are equipped with an irremovable outer wind wheel, rotated aerodynamically during their descent to the ground and used to arm the military load of said bombs. In a particular embodiment of mine described by the document DE 3322 926 A1 , a wind wheel is provided outside the body of the mine to be rotatable about the axis of said body.

Quelle que soit leur disposition, de telles roues éoliennes externes engendrent une traînée importante et elles sont de plus vulnérables. Il en résulte que les dispositifs d'armement à roue éolienne externe ne peuvent être utilisés pour des projectiles autres que des bombes, par exemple pour des missiles.Whatever their arrangement, such external wind wheels generate significant drag and they are more vulnerable. As a result, the external wind wheel arming devices can not be used for projectiles other than bombs, for example for missiles.

Par ailleurs, par exemple par les documents US 1793567 , GB 550897 , US 3552318 , US 6481354 , FR 2566892 et FR 2927695 , on connaît des dispositifs d'armement de fusées de projectiles comportant une roue éolienne interne auxdites fusées. De telles roues éoliennes internes sont donc protégées à l'intérieur de la fusée et elles n'exercent aucune influence négative sur l'aérodynamisme du projectile. Toutefois, elles nécessitent la réalisation, dans lesdites fusées, d'un circuit interne de prélèvement et de circulation d'air pour les faire tourner ; de plus, un tel circuit limite les performances du dispositif d'armement.By the way, for example by the documents US 1793567 , GB 550897 , US 3552318 , US 6481354 , FR 2566892 and FR 2927695 projectile rocket weapon devices having a wind wheel internal to said rockets are known. Such internal wind wheels are therefore protected inside the rocket and they exert no negative influence on the aerodynamics of the projectile. However, they require the realization, in said rockets, an internal circuit for sampling and air circulation to rotate them; in addition, such a circuit limits the performance of the cocking device.

La présente invention a pour objet de remédier à ces inconvénients.The present invention aims to overcome these disadvantages.

A cette fin, selon l'invention, le procédé pour lever au moins une sécurité de mise à feu d'une charge militaire disposée dans l'enveloppe fuselée d'un projectile, ledit procédé mettant en oeuvre une roue éolienne entraînée en rotation par le flux aérodynamique entourant ledit projectile pendant son vol, est remarquable en ce que :

  • on pratique une ouverture latérale dans ladite enveloppe fuselée dudit projectile, et
  • on agence ladite roue éolienne autour d'un axe disposé à l'intérieur de ladite enveloppe fuselée au moins sensiblement orthogonalement à l'axe dudit projectile, de façon que ladite roue éolienne soit en grande partie intérieure à ladite enveloppe fuselée mais que, au cours de la rotation de ladite roue éolienne, les extrémités périphériques des pales de celle-ci passent successivement à travers ladite ouverture latérale pour faire saillie à l'extérieur de ladite enveloppe fuselée.
To this end, according to the invention, the method for raising at least one firing safety of a military load disposed in the tapered casing of a projectile, said method using a wind wheel rotated by the aerodynamic flow surrounding said projectile during its flight, is remarkable in that:
  • a lateral opening is made in said tapered envelope of said projectile, and
  • said wind wheel is arranged around an axis disposed inside said tapered casing at least substantially orthogonal to the axis of said projectile, so that said wind wheel is substantially internal to said tapered casing but that, during the rotation of said wind wheel, the peripheral ends of the blades thereof pass successively through said lateral opening to project outside said tapered casing.

Ainsi, la vulnérabilité et la traînée aérodynamique d'une telle roue éolienne, pour sa plus grande partie intérieure à l'enveloppe du projectile, sont réduites, sans pour autant nuire au rendement de ladite roue éolienne et nécessiter la réalisation d'un circuit de circulation d'air à l'intérieur dudit projectile.Thus, the vulnerability and the aerodynamic drag of such a wind wheel, for its greater part inside the shell of the projectile, are reduced, without affecting the efficiency of said wind wheel and require the realization of a circuit of air circulation inside said projectile.

Le projectile conforme à la présente invention et comportant une enveloppe fuselée dans laquelle se trouvent :

  • une charge militaire dont la mise à feu est empêchée par au moins un dispositif de sécurité, et
  • un dispositif d'armement à roue éolienne apte à agir sur ledit dispositif de sécurité pour en inhiber l'action, ladite roue éolienne étant mise en rotation par le flux aérodynamique entourant ledit projectile pendant son vol,
est donc remarquable en ce que ladite enveloppe fuselée du projectile comporte une ouverture latérale, en ce que l'axe de rotation de ladite roue éolienne est disposé à l'intérieur de ladite enveloppe fuselée au moins sensiblement orthogonalement à l'axe dudit projectile, en ce que ladite roue éolienne est en grande partie intérieure à ladite enveloppe fuselée et en ce que de ladite ouverture latérale est apte à être traversée successivement, au cours de la rotation de la dite roue éolienne, par les extrémités périphériques des pales de cette dernière pour faire saillie à l'extérieur de ladite enveloppe fuselée.The projectile according to the present invention and comprising a tapered envelope in which are:
  • a military charge whose firing is prevented by at least one security device, and
  • a wind turbine arming device capable of acting on said safety device to inhibit its action, said wind wheel being rotated by the aerodynamic flow surrounding said projectile during its flight,
is therefore remarkable in that said fuseled casing of the projectile comprises a lateral opening, in that the axis of rotation of said wind wheel is disposed inside said tapered casing at least substantially orthogonal to the axis of said projectile, in that said wind wheel is substantially internal to said tapered casing and in that said lateral opening is adapted to be traversed successively, during the rotation of said wind wheel, by the peripheral ends of the blades of the latter to project outside said tapered envelope.

Ledit dispositif d'armement peut comporter un boisseau mobile entraîné, à partir de la roue éolienne, par l'intermédiaire d'un dispositif de renvoi d'angle et ledit boisseau mobile peut être mû par une vis entraînée en rotation par ledit dispositif de renvoi d'angle.Said arming device may comprise a driven movable valve, from the wind wheel, by means of a deflection device and said movable plug may be moved by a screw driven in rotation by said return device angle.

On voit qu'ainsi le dispositif de renvoi d'angle et ladite vis d'entraînement du boisseau permettent de démultiplier la vitesse de rotation de la roue éolienne pour obtenir la progressivité désirée pour le déplacement dudit boisseau.It can be seen that in this way the angle deflection device and said drive screw of the plug make it possible to increase the speed of rotation of the wind wheel in order to obtain the desired progressivity for the displacement of said bushel.

De préférence, l'axe de ladite vis déplaçant le boisseau mobile est au moins sensiblement orthogonal à l'axe de la roue éolienne.Preferably, the axis of said screw moving the movable plug is at least substantially orthogonal to the axis of the wind wheel.

Dans un mode de réalisation avantageux, un dispositif de couplage commandable est prévu sur l'arbre de rotation de ladite roue éolienne afin de permettre à celle-ci d'être découplée du reste dudit dispositif d'armement, et un contacteur permet de commander ledit dispositif de couplage, ledit contacteur étant actionné par un élément du dispositif d'armement, de préférence le boisseau, lorsque ledit dispositif d'armement a inhibé l'action du dispositif de sécurité.In an advantageous embodiment, a controllable coupling device is provided on the rotation shaft of said wind wheel to allow it to be decoupled from the rest of said arming device, and a contactor can control said coupling device, said contactor being actuated by an element of the cocking device, preferably the plug, when said cocking device has inhibited the action of the safety device.

Ainsi, après levée de la sécurité de mise à feu, la roue peut être amenée à tourner folle, pour encore réduire la traînée aérodynamique qu'elle engendre.Thus, after lifting the ignition safety, the wheel can be made to turn crazy, to further reduce the aerodynamic drag it generates.

Par ailleurs, pour permettre la manutention, la maintenance, le transport, etc...dudit projectile, il est avantageux que celui-ci comporte des moyens mécaniques de blocage amovibles dudit boisseau mobile.Furthermore, to allow the handling, maintenance, transport, etc ... of said projectile, it is advantageous that it includes removable mechanical locking means of said movable plug.

Les figures du dessin annexé feront bien comprendre comment l'invention peut être réalisée. Sur ces figures, des références identiques désignent des éléments semblables.The figures of the appended drawing will make it clear how the invention can be realized. In these figures, identical references designate similar elements.

La figure 1 montre, en perspective, un missile équipé d'une roue éolienne conformément à la présente invention.The figure 1 shows, in perspective, a missile equipped with a wind wheel in accordance with the present invention.

La figure 2A est une coupe schématique agrandie, selon la ligne II-II de la figure 1, illustrant la disposition de la roue éolienne de la présente invention, lorsque le missile est en stockage ou en attente de tir.The Figure 2A is an enlarged schematic section along line II-II of the figure 1 , illustrating the arrangement of the wind wheel of the present invention, when the missile is in storage or awaiting firing.

La figure 2B est une coupe schématique agrandie, selon la ligne II-II de la figure 1, illustrant la disposition de la roue éolienne de la présente invention, lorsque le missile est armé.The Figure 2B is an enlarged schematic section along line II-II of the figure 1 , illustrating the arrangement of the wind wheel of the present invention, when the missile is armed.

La figure 3 montre, en perspective, un mode de réalisation de la roue éolienne conforme à la présente invention, associée à un dispositif de débrayage.The figure 3 shows, in perspective, an embodiment of the wind wheel according to the present invention, associated with a disengagement device.

Le missile 1, représenté sur la figure 1, comporte un fuselage 2, d'axe longitudinal L-L, qui enferme une charge militaire WH et dans lequel est pratiquée une ouverture latérale 3, de forme longitudinalement allongée. A travers ladite ouverture latérale 3 passent, de l'intérieur vers l'extérieur du fuselage 2, les extrémités des pales 4 d'une roue éolienne 5, disposée à l'intérieur dudit fuselage 2.The missile 1, shown on the figure 1 , comprises a fuselage 2, longitudinal axis LL, which encloses a military load WH and in which is formed a lateral opening 3, of longitudinally elongate shape. Through said lateral opening 3 pass, from the inside to the outside of the fuselage 2, the ends of the blades 4 of a wind wheel 5 disposed inside said fuselage 2.

Comme l'illustrent schématiquement les figures 2A et 2B, l'axe de rotation X-X de la roue éolienne 5 est sensiblement orthogonal à l'axe longitudinal L-L du fuselage 2 du missile 1.As illustrated schematically in Figures 2A and 2B the axis of rotation XX of the wind wheel 5 is substantially orthogonal to the longitudinal axis LL of the fuselage 2 of the missile 1.

La roue éolienne 5 comporte un arbre 6, d'axe X-X, intérieur au fuselage 2 et prolongé par une vis sans fin 7, engrenant avec un pignon 8, pour former un renvoi d'angle à 90°. Ainsi, l'axe Y-Y du pignon 8 est orthogonal à l'axe X-X de la roue éolienne 5. L'axe Y-Y du pignon 8 peut, de plus, comme cela est illustré par les figures 2A et 2B, être orthogonal à l'axe L-L du missile 1.The wind wheel 5 comprises a shaft 6, of axis XX, inside the fuselage 2 and extended by an endless screw 7, meshing with a pinion 8, to form a 90 ° angle gear. Thus, the axis YY of the pinion 8 is orthogonal to the axis XX of the wind wheel 5. The axis YY of the pinion 8 can, in addition, as illustrated by the Figures 2A and 2B , be orthogonal to the LL axis of missile 1.

A l'intérieur du fuselage 2 se trouve de plus un corps 9 à l'intérieur duquel est monté un dispositif de sécurité 10 empêchant la mise à feu de la charge militaire WH. Dans le corps 9 est monté mobile un boisseau 11 portant un organe 12 apte à agir sur le dispositif de sécurité 10 pour en inhiber l'action. Le boisseau 11 est en prise avec une vis 13, solidaire du pignon 8 et coaxiale à celui-ci et engrenant avec un filetage 14 dudit boisseau 11.Inside the fuselage 2 is also a body 9 inside which is mounted a safety device 10 preventing the firing of the military load WH. In the body 9 is movably mounted a plug 11 carrying a member 12 adapted to act on the safety device 10 to inhibit the action. The plug 11 is engaged with a screw 13, integral with the pinion 8 and coaxial with it and meshing with a thread 14 of said plug 11.

Par ailleurs, une broche 15 chargée par un ressort 16 maintenu comprimé par une clavette 17 est apte à bloquer le boisseau 11 dans le corps 9.Moreover, a pin 15 loaded by a spring 16 kept compressed by a key 17 is able to lock the plug 11 in the body 9.

La figure 2A illustre la disposition des différents éléments 2 à 16 qui viennent d'être décrits, lorsque le missile 1 se trouve en stockage, en maintenance, en transport ou en une tout autre phase où la charge militaire WH ne doit pas être armée. Dans la disposition de la figure 2A, la broche 15 maintenue par la clavette 17 bloque le boisseau 11 à l'intérieur du corps 9, ce qui a pour conséquences que l'organe 12 ne peut agir sur le dispositif de sécurité 10 et que la roue éolienne 5 est bloquée en rotation par l'intermédiaire de la vis 13 et du renvoi d'angle 7, 8.The Figure 2A illustrates the arrangement of the various elements 2 to 16 which have just been described, when the missile 1 is in storage, maintenance, transport or any other phase where the military load WH should not be armed. In the provision of the Figure 2A the pin 15 held by the key 17 blocks the plug 11 inside the body 9, which has the consequence that the member 12 can not act on the safety device 10 and that the wind wheel 5 is locked in rotation through the screw 13 and the bevel gear 7, 8.

Lorsque le missile 1 doit être lancé, on commence par éliminer la clavette 17, de sorte que le ressort 16 éjecte la broche 15 et que le blocage du boisseau 11 dans le corps 9 est supprimé (voir la figure 2B). Ensuite, on procède au lancement du missile 1 et il en résulte que les parties périphériques des pales 4 de la roue éolienne 5, qui, traversant ladite ouverture latérale 3, se trouvent à l'extérieur du fuselage 1, sont soumises à la pression du flux aérodynamique entourant ledit fuselage 2. La roue 5, intérieure au fuselage 2, est donc mise en rotation, les extrémités périphériques des pales 4 traversant successivement ladite ouverture latérale 3.When the missile 1 is to be launched, it first eliminates the key 17, so that the spring 16 ejects the spindle 15 and blocking the bushel 11 in the body 9 is removed (see Figure 2B ). Then, the launching of the missile 1 and the result that the peripheral parts of the blades 4 of the wind wheel 5, which, passing through said lateral opening 3, are outside the fuselage 1, are subjected to the pressure of the aerodynamic flow surrounding said fuselage 2. The wheel 5, interior to the fuselage 2, is rotated, the peripheral ends of the blades 4 through successively said lateral opening 3.

Par suite d'une telle mise en rotation aérodynamique de la roue 5, la vis 13 est elle-même entraînée en rotation autour de son axe Y-Y par le renvoi d'angle 7, 8 et, par sa coopération avec le filetage 14, elle déplace le boisseau 11 et l'organe 12 en direction du dispositif de sécurité 10.As a result of such aerodynamic rotation of the wheel 5, the screw 13 is itself driven in rotation about its axis YY by the angle gear 7, 8 and, by its cooperation with the thread 14, it moves the plug 11 and the member 12 towards the safety device 10.

L'avance progressive du boisseau vers le dispositif de sécurité 10 dépend, entre autres paramètres, de la vitesse du missile1, des performances aérodynamiques de la roue 5, du rapport de démultiplication entre la vis sans fin 7 et le pignon 8 et du pas de la vis 13 et du filetage 14. Compte tenu de la distance que le boisseau 11 doit parcourir pour que son organe 12 inhibe la sécurité imposée par le dispositif 10, le temps de levée de cette sécurité est donc parfaitement défini.The progressive advance of the bushel towards the safety device 10 depends, among other parameters, on the speed of the missile 1, the aerodynamic performance of the wheel 5, the gear ratio between the worm 7 and the pinion 8 and the pitch of the screw 13 and the thread 14. Given the distance that the bushel 11 must travel for that its member 12 inhibits the security imposed by the device 10, the lifting time of this security is perfectly defined.

Après levée de la sécurité par l'organe 12, il peut être avantageux, pour des raisons de traînée aérodynamique, que la roue éolienne 5 soit découplée du boisseau 11 pour tourner folle. Dans ce cas, on prévoit un dispositif de couplage commandable 18 sur l'arbre 6, entre la roue éolienne 5 et la vis sans fin 7. Pour commander ce dispositif de couplage 18 au découplage, on dispose alors, dans le corps 9, un contacteur 19 dont la position correspond à la fin du temps de levée de la sécurité par l'organe 12 (voir la figure 3).After lifting the safety by the member 12, it may be advantageous for reasons of aerodynamic drag, the wind wheel 5 is decoupled from the plug 11 to turn crazy. In this case, there is provided a controllable coupling device 18 on the shaft 6, between the wind wheel 5 and the worm 7. To control this coupling device 18 to decoupling, there is then in the body 9, a contactor 19 whose position corresponds to the end of the time of lifting of the security by the organ 12 (see figure 3 ).

Claims (8)

Procédé pour lever au moins une sécurité de mise à feu d'une charge militaire (WH) disposée dans l'enveloppe fuselée (2) d'un projectile (1), ledit procédé mettant en oeuvre une roue éolienne (5) entraînée en rotation par le flux aérodynamique entourant ledit projectile (1) pendant son vol, caractérisé en ce que : - on pratique une ouverture latérale (3) dans ladite enveloppe fuselée (2) dudit projectile (1), et - on agence ladite roue éolienne (5) autour d'un axe (XX) disposé à l'intérieur de ladite enveloppe fuselée (2) au moins sensiblement orthogonalement à l'axe (L-L) dudit projectile (1), de façon que ladite roue éolienne (5) soit en grande partie intérieure à ladite enveloppe fuselée (2), mais que, au cours de la rotation de ladite roue éolienne (5), les extrémités périphériques des pales (4) de celle-ci passent successivement à travers ladite ouverture latérale (3) pour faire saillie à l'extérieur de ladite enveloppe fuselée (2) Method for raising at least one firing safety of a military load (WH) disposed in the tapered envelope (2) of a projectile (1), said method using a wind wheel (5) rotated by the aerodynamic flow surrounding said projectile (1) during its flight, characterized in that : a lateral opening (3) is made in said tapered envelope (2) of said projectile (1), and said wind wheel (5) is arranged around an axis (XX) disposed inside said tapered envelope (2) at least substantially orthogonal to the axis (LL) of said projectile (1), so that said wind wheel (5) is substantially internal to said tapered casing (2), but during the rotation of said wind wheel (5), the peripheral ends of the blades (4) thereof pass successively through said lateral opening (3) for projecting outside of said tapered envelope (2) Projectile (1) comportant une enveloppe fuselée (2) dans laquelle se trouvent : - une charge militaire (WH) dont la mise à feu est empêchée par au moins un dispositif de sécurité (10), et - un dispositif d'armement (5 à 8, 11 à 13) à roue éolienne (5) apte à agir sur ledit dispositif de sécurité (10) pour en inhiber l'action, ladite roue éolienne (5) étant mise en rotation par le flux aérodynamique entourant ledit projectile (1) pendant son vol,
caractérisé en ce que ladite enveloppe fuselée (2) du projectile (1) comporte une ouverture latérale (3), en ce que l'axe de rotation (X-X) de ladite roue éolienne (5) est disposé à l'intérieur de ladite enveloppe fuselée (2) au moins sensiblement orthogonalement à l'axe (L-L) dudit projectile (1), en ce que ladite roue éolienne (5) est en grande partie intérieure à ladite enveloppe fuselée (2) et en ce que ladite ouverture latérale (3) est apte à être traversée successivement, au cours de la rotation de ladite roue éolienne (5), par les extrémités périphériques des pales (4) de cette dernière pour faire saillie à l'extérieur de ladite enveloppe fuselée (2). Projectile (1) comprising a tapered envelope (2) in which are: a military load (WH) whose firing is prevented by at least one safety device (10), and an arming device (5 to 8, 11 to 13) with a wind wheel (5) able to act on said safety device (10) to inhibit its action, said wind wheel (5) being rotated by the aerodynamic flow surrounding said projectile (1) during its flight,
characterized in that said tapered shell (2) of the projectile (1) has a lateral opening (3), in that the axis of rotation (XX) of said wind wheel (5) is disposed inside said envelope tapered (2) at least substantially orthogonal to the axis (LL) of said projectile (1), in that said wind wheel (5) is substantially internal to said tapered casing (2) and in that said lateral opening ( 3) is adapted to be traversed successively, during the rotation of said wind wheel (5), by the peripheral ends of the blades (4) of the latter to project outside said tapered envelope (2). Projectile selon la revendication 2,
caractérisé en ce ledit dispositif d'armement (5 à 8, 11 à 3) comporte un boisseau mobile (11) entraîné, à partir de la roue éolienne (5), par l'intermédiaire d'un dispositif de renvoi d'angle (7, 8).Projectile according to claim 2,
characterized in that said arming device (5 to 8, 11 to 3) comprises a movable plug (11) driven from the wind wheel (5) via a deflection device ( 7, 8). Projectile selon la revendication 3,
caractérisé en ce que ledit boisseau mobile (11) est mû par une vis (13) entraînée en rotation par ledit dispositif de renvoi d'angle (7, 8).Projectile according to claim 3,
characterized in that said movable plug (11) is moved by a screw (13) rotated by said angular gear (7, 8). Projectile selon la revendication 4,
caractérisé en ce que l'axe (Y-Y) de ladite vis (13) déplaçant le boisseau mobile (11) est au moins sensiblement orthogonal à l'axe (X-X) de la roue éolienne (5).Projectile according to claim 4,
characterized in that the axis (YY) of said screw (13) moving the movable plug (11) is at least substantially orthogonal to the axis (XX) of the wind wheel (5). Projectile selon l'une des revendications 2 à 5,
caractérisé en ce qu'un dispositif de couplage commandable (18) est prévu sur l'arbre de rotation (6) de ladite roue éolienne (5) afin de permettre à celle-ci d'être découplée du reste dudit dispositif d'armement (6 à 8, 11 à 13).Projectile according to one of Claims 2 to 5,
characterized in that a controllable coupling device (18) is provided on the rotation shaft (6) of said wind wheel (5) to enable it to be decoupled from the rest of said winding device ( 6-8, 11-13). Projectile selon la revendication 6,
caractérisé en ce qu'il comporte un contacteur (19) pour commander ledit dispositif de couplage (18), ledit contacteur (19) étant actionné par un élément du dispositif d'armement (5 à 8, 11 à 13), de préférence le boisseau (11), lorsque ledit dispositif d'armement a inhibé l'action du dispositif de sécurité (10).Projectile according to claim 6,
characterized in that it comprises a contactor (19) for controlling said coupling device (18), said contactor (19) being actuated by an element of the cocking device (5 to 8, 11 to 13), preferably the bushel (11), when said arming device has inhibited the action of the safety device (10). Projectile selon l'une des revendications 3 à 7,
caractérisé en ce qu'il comporte des moyens mécaniques amovibles (15, 16, 15) pour bloquer ledit boisseau mobile (11).Projectile according to one of Claims 3 to 7,
characterized in that it comprises removable mechanical means (15, 16, 15) for locking said movable plug (11).
EP13290023.4A 2012-02-08 2013-01-30 Method for lifting a firing safety and projectile implementing said method Not-in-force EP2626665B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1200381A FR2986613B1 (en) 2012-02-08 2012-02-08 METHOD FOR EXTENDING FIRE SAFETY AND PROJECTILE USING THE SAME

Publications (2)

Publication Number Publication Date
EP2626665A1 true EP2626665A1 (en) 2013-08-14
EP2626665B1 EP2626665B1 (en) 2015-06-03

Family

ID=47664223

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13290023.4A Not-in-force EP2626665B1 (en) 2012-02-08 2013-01-30 Method for lifting a firing safety and projectile implementing said method

Country Status (4)

Country Link
US (1) US9182206B2 (en)
EP (1) EP2626665B1 (en)
FR (1) FR2986613B1 (en)
WO (1) WO2013117829A1 (en)

Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB103182A (en) * 1916-01-21 1917-01-18 Sabulite Great Britain Ltd Improvements in or relating to Bombs and like Explosive Projectiles.
US1793567A (en) 1928-09-19 1931-02-24 Alfred F Teitscheid Supersensitive fuse for projectiles
GB550897A (en) 1941-09-15 1943-01-29 Albert Henry Midgley Improvements in and relating to fuzes for projectiles, bombs and the like
US2943569A (en) * 1945-11-19 1960-07-05 Richard C Wolfe Ordnance exploding mechanism
US2989920A (en) * 1951-02-27 1961-06-27 James M Kendall Torpedo exploder
US3552318A (en) 1968-05-03 1971-01-05 Us Navy Ordnance fuze
US3779194A (en) * 1956-09-27 1973-12-18 L Kahn Marine missiles for destruction of submarine targets
FR2193191A1 (en) * 1972-07-15 1974-02-15 Messerschmitt Boelkow Blohm
US3973501A (en) * 1973-01-11 1976-08-10 The United States Of America As Represented By The Secretary Of The Navy Fuze with dual safe positions and armed-safe indicator
DE3322926A1 (en) 1983-06-25 1985-01-10 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Droppable mine
FR2566892A1 (en) 1984-06-29 1986-01-03 Lacroix E Tous Artifices Aircraft bomb fuse with deceleration arming
US6481354B1 (en) 1998-11-26 2002-11-19 Junghan Feinwektechnik Gmbh & Co. Kg Mortar fuse with a rotatable fan
FR2927695A1 (en) 2008-02-19 2009-08-21 Tda Armements Sas Soc Par Acti MUNITION SPOUSE WITH SAFETY ARMING

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1234358A (en) * 1916-09-18 1917-07-24 Sabulite Great Britain Ltd Bomb, grenade, and like explosive projectile.
US2779277A (en) * 1946-12-03 1957-01-29 Robert E Smith Torpedo exploder
US3170403A (en) * 1951-05-18 1965-02-23 Laurence B Heilprin Flywheel for generator in ordnance missile
US3382805A (en) * 1967-01-31 1968-05-14 Navy Usa Air responsive delay arming device
US4027593A (en) * 1976-02-12 1977-06-07 The United States Of America As Represented By The Secretary Of The Army Multi-directional system for electrical bomb fuzes
US4567828A (en) * 1984-03-14 1986-02-04 The United States Of America As Represented By The Secretary Of The Army Bomb safety device

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB103182A (en) * 1916-01-21 1917-01-18 Sabulite Great Britain Ltd Improvements in or relating to Bombs and like Explosive Projectiles.
US1793567A (en) 1928-09-19 1931-02-24 Alfred F Teitscheid Supersensitive fuse for projectiles
GB550897A (en) 1941-09-15 1943-01-29 Albert Henry Midgley Improvements in and relating to fuzes for projectiles, bombs and the like
US2943569A (en) * 1945-11-19 1960-07-05 Richard C Wolfe Ordnance exploding mechanism
US2989920A (en) * 1951-02-27 1961-06-27 James M Kendall Torpedo exploder
US3779194A (en) * 1956-09-27 1973-12-18 L Kahn Marine missiles for destruction of submarine targets
US3552318A (en) 1968-05-03 1971-01-05 Us Navy Ordnance fuze
FR2193191A1 (en) * 1972-07-15 1974-02-15 Messerschmitt Boelkow Blohm
US3973501A (en) * 1973-01-11 1976-08-10 The United States Of America As Represented By The Secretary Of The Navy Fuze with dual safe positions and armed-safe indicator
DE3322926A1 (en) 1983-06-25 1985-01-10 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Droppable mine
FR2566892A1 (en) 1984-06-29 1986-01-03 Lacroix E Tous Artifices Aircraft bomb fuse with deceleration arming
US6481354B1 (en) 1998-11-26 2002-11-19 Junghan Feinwektechnik Gmbh & Co. Kg Mortar fuse with a rotatable fan
FR2927695A1 (en) 2008-02-19 2009-08-21 Tda Armements Sas Soc Par Acti MUNITION SPOUSE WITH SAFETY ARMING

Also Published As

Publication number Publication date
FR2986613A1 (en) 2013-08-09
FR2986613B1 (en) 2015-01-02
WO2013117829A1 (en) 2013-08-15
EP2626665B1 (en) 2015-06-03
US20150114248A1 (en) 2015-04-30
US9182206B2 (en) 2015-11-10

Similar Documents

Publication Publication Date Title
EP1550837B1 (en) Device for the deployment and the control of the control vanes of a projectile
US20040144888A1 (en) Deployment mechanism for stowable fins
EP0335761B1 (en) Airborne vehicle with at least one releasable propulsion unit
FR2986319A1 (en) PILOTAGE TRUNK FOR GUIDED MUNITION
WO2007133247A2 (en) Fin retention and deployment mechanism
EP2962060B1 (en) Munition with modifiable explosive capability
FR2977867A1 (en) COUNTERMEASURE SANDING SYSTEM FOR MOUNTING ON AN AIRCRAFT
EP2626665B1 (en) Method for lifting a firing safety and projectile implementing said method
FR2846080A1 (en) DEVICE FOR DEPLOYING AND TRAINING PROJECTILE GOVERNORS
FR3035493A1 (en) BALLISTIC PROJECTILE COMPRISING A WING OPENING MECHANISM AND METHOD OF USING SUCH A BALLISTIC PROJECTILE
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
EP0756151B1 (en) Ignition system for a propulsive charge of a submunition ejected from a cargo munition
CH664010A5 (en) ROCKET FOR PROJECTILE.
EP3121553B1 (en) Safing and arming device for a nose mounted fuze and fuze comprising such a device
EP2546143B1 (en) System for launching projectiles in particular as a countermeasure from an aircraft
FR2672673A1 (en) Priming device for a subprojectile
FR2865537A1 (en) FUSE FOR AMMUNITION
FR3127563A1 (en) MECHANICAL SELF-STRIKING FUSE FOR A NON-SPINNING AMMUNITION
EP0316216A1 (en) Gyroscopic stabilising device for a projectile steering element
WO2009103707A1 (en) Ammunition fuse with arming safety
EP2913628B1 (en) Artillery projectile warhead fuse comprising a braking device acting in flight direction
EP3187816B9 (en) Launching device and projectile especially adapted for such a launching device
EP2437025B1 (en) Ammunition-launching weapon system with tubular extension
FR2664040A1 (en) DEVICE FOR SECURING AND ARMING MILITARY LOADS.
EP2383539B1 (en) Priming device with electric initiation for a 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

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: 20130919

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

17Q First examination report despatched

Effective date: 20140704

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20150114

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: MBDA FRANCE

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): 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: 730136

Country of ref document: AT

Kind code of ref document: T

Effective date: 20150715

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: 602013001922

Country of ref document: DE

Effective date: 20150716

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 730136

Country of ref document: AT

Kind code of ref document: T

Effective date: 20150603

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

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: 20150603

Ref country code: NO

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: 20150903

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: 20150603

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: 20150603

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: 20150603

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20150603

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

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: 20150903

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: 20150603

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: 20150603

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: 20150904

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: 20150603

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

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: 20150603

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 4

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

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: 20150603

Ref country code: RO

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

Effective date: 20150603

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: 20151003

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: 20151006

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: 20150603

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: 20150603

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602013001922

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: 20150603

26N No opposition filed

Effective date: 20160304

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: 20160131

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: 20150603

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

Effective date: 20160130

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: 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: 20150603

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

Ref country code: CH

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

Effective date: 20160131

Ref country code: LI

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

Effective date: 20160131

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: 20160130

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 5

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: 20150603

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: 20150603

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: 20150603

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 6

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: 20150603

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: 20150603

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: 20130130

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: 20150603

Ref country code: MK

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: 20150603

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: 20150603

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

Ref country code: FR

Payment date: 20230125

Year of fee payment: 11

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

Ref country code: IT

Payment date: 20230110

Year of fee payment: 11

Ref country code: GB

Payment date: 20230123

Year of fee payment: 11

Ref country code: DE

Payment date: 20230112

Year of fee payment: 11

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230630

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602013001922

Country of ref document: DE

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

Effective date: 20240130

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

Ref country code: DE

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

Effective date: 20240801

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

Ref country code: GB

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

Effective date: 20240130

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: 20240131

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

Ref country code: GB

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

Effective date: 20240130

Ref country code: FR

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

Effective date: 20240131

Ref country code: DE

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

Effective date: 20240801

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: 20240130