EP0246958A1 - Device for pyrotechnically separating two elements - Google Patents

Device for pyrotechnically separating two elements Download PDF

Info

Publication number
EP0246958A1
EP0246958A1 EP87401102A EP87401102A EP0246958A1 EP 0246958 A1 EP0246958 A1 EP 0246958A1 EP 87401102 A EP87401102 A EP 87401102A EP 87401102 A EP87401102 A EP 87401102A EP 0246958 A1 EP0246958 A1 EP 0246958A1
Authority
EP
European Patent Office
Prior art keywords
parts
projecting parts
fixing means
cavity
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
EP87401102A
Other languages
German (de)
French (fr)
Other versions
EP0246958B1 (en
Inventor
Hubert Vaillant De Guelis
Jean Langlois
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.)
Airbus Group SAS
Original Assignee
Airbus Group 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 Airbus Group SAS filed Critical Airbus Group SAS
Publication of EP0246958A1 publication Critical patent/EP0246958A1/en
Application granted granted Critical
Publication of EP0246958B1 publication Critical patent/EP0246958B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
    • F42B15/38—Ring-shaped explosive elements for the separation of rocket parts

Definitions

  • the present invention relates to a device for the separation of two elements by means of a pyrotechnic charge usable in particular for separating elements in the form of panels in aeronautical or spacecraft.
  • the plates have, on their faces opposite to this housing, grooves defining a thinned zone, therefore weakened, along which the fracture must be made. These grooves are located at the central part of the plates, therefore towards the middle of the cavity in which is placed the deformable envelope which contains the detonating cords. When the detonating cord is ignited, this causes the deformable envelope to expand. This tends to take a circular configuration, which has the effect of deforming the central part of the two plates connecting the panels to be separated and causing rupture along the weakened sections. If such a device is satisfactory, it does however make it possible to break only relatively small sheet thicknesses, for example of the order of 1 mm.
  • the object of the present invention is to remedy these drawbacks by proposing a separation device pyrotechnic between two elements, for example elements in the form of panels, making it possible to cut a greater thickness of sheet metal with the same charge of explosive.
  • the invention relates to a pyrotechnic separation device between a first element and a second element using a pyrotechnic charge placed in a deformable envelope.
  • the first element comprises two protruding parts which define a certain space between them, the device further comprising first fixing means for fixing the first element to the second by means of said protruding parts, thus defining a cavity in which is placed said deformable envelope, this cavity having a first end close to said first fixing means and a second end remote from these first fixing means, and the first element has thinned parts which break when the charge explodes pyrotechnic.
  • the thinned parts are located approximately at the second end of said cavity.
  • the envelope deforms and causes rupture at these thinned parts.
  • the deformable envelope acts at the time of the explosion on a relatively large lever arm corresponding to the length of the projecting parts: this allows better efficiency, for a given load, than with a device such as that described in document US-A-3 698 281.
  • the weakened parts of the connection plates are found in the middle of these, so halfway between the plate attachments on the elements to be separated, and the lever arm is weaker.
  • the first fixing means comprise at least one screw passing through a hole formed in each protruding part and a hole formed in the second element, and a nut, the tightening of this nut on the screw causing the application of said protruding parts on the second element.
  • at least one stirrup a part of which at least partially surrounds the deformable envelope while being in contact with the latter and of which another part has a hole through which the screw can pass.
  • the detonating cord and the deformable envelope are of elongated shape and there are several fixing devices such as that which has just been described with screws, nuts and possibly stirrups, regularly distributed along the separation zone.
  • the projecting parts form an integral part of the first element and are connected to the rest of this element by thin connection zones which constitute said thinned parts.
  • the projecting parts consist of plates fixed to the first element by second fixing means, each of these plates having a thin zone which constitutes one of said thinned parts.
  • the first element 2 has two projecting parts 6 and 8, connected respectively to the body of element 2 by thin zones 10 and 12.
  • the projecting parts 6 and 8 are not attached elements, but form an integral part of the body 2, the latter having been machined in order to produce the protruding parts 6 and 8.
  • the element 2, including the protruding parts 6 and 8 has, seen in section, a symmetry with respect to a plane P perpendicular to the plane of the figure, represented schematically in dashed lines.
  • the second element 4 has, along its edge closest to the first element 2, an enlarged part 14 whose width is slightly less than the width of the cavity 16 defined between the projecting parts 6 and 8.
  • the pyrotechnic charge takes the form of a detonating cord 18 placed inside a deformable envelope 20, the space between the detonating cord and the deformable envelope being filled with a flexible material 22, for example a sheath silicone rubber.
  • the sheath 22 performs several functions. First of all, it supports and maintains the detonating cord 18 in the correct position, that is to say substantially along the axis of symmetry of the envelope 20. In the particular case described here, this envelope has two parts flattened connected by semi-circular parts, but it would not depart from the scope of the invention by giving it another shape, oval for example. In addition, if silicone rubber is used, it behaves like a thermal insulator and protects the cord 18 from sudden temperature variations that the components of a spacecraft can undergo. Finally, the damping qualities of rubber protect the detonating cord from external shocks to which a spacecraft may be subjected upon departure or when certain propulsion engines are ignited.
  • the flexible sheath 22 also has the role of preventing the ignition of the second cord by shock waves due to the explosion of the first.
  • FIGS. 1 and 2 also show the means for fixing the first element 2 to the second element 4 via the projecting parts 6 and 8. It can be seen that the latter have, at their ends opposite to the connection zones 10 and 12, holes 24 and 26 respectively, which can be aligned with a hole 28 formed in the enlarged part 14 of the element 4, these different holes being of the same diameter.
  • a screw 30 passes through the holes 24, 28 and 26 and it is held by a nut 32, the tightening of the nut 32 on the screw 30 having the effect of applying the projecting parts 6 and 8 of the first element on the part enlarged 14 of the second element.
  • a socket 34 can be placed inside the passage formed by the holes 24, 28 and 26, in order to better adjust the screw 30.
  • the fixing device can be completed using one or more stirrups such as 36, distributed from place to place along the deformable envelope 20.
  • stirrups such as 36
  • These can be made of any ductile material such as mild steel.
  • each stirrup 36 consists of an upper part 38 in the form of a semicircle extended by two branches 40 and 42.
  • the upper part 38 is in contact with the upper part of the deformable envelope 20 which is also in the shape of a semicircle.
  • the branches 40 and 42 they are substantially parallel and their spacing is such that they can be placed between the internal face of the projecting parts 6 and 8 and the external face of the widened part 14 of the element 4 (FIG. 1).
  • the branches 40 and 42 of the stirrup 36 also have holes 44 and 46 respectively (FIG. 2) of the same diameter as the holes 24, 26 and 28, the screw 30 also passing through the holes 44 and 46.
  • the deformable envelope 20 is held against the internal faces of each protruding part 6 and 8, against the wall of the cavity 16 situated on the body side of the element 2 and, finally, against a boss 48 provided on the enlarged part 14 of element 4.
  • This arrangement means that the envelope 20 is held on all sides, but it would not go beyond the scope of the invention by using an equivalent assembly, provided that the envelope 20 is maintained so that the energy of the explosion causes tearing at the connection zones 10 and 12.
  • the device which is the subject of the invention has interesting advantages, the main one of which is that it allows, for a given explosive mass, to cut a greater thickness of sheet metal than with the devices of the prior art.
  • Tests comparisons were made with a device according to that described in document US-A-3,698,281 and with a device according to that of the invention, as illustrated in FIG. 1.
  • there is no was able to cut a set of two thin sheets, that is to say for each of the order of 0.85 mm, while with the device of the invention, it was possible to cut a element in which the thinned zones 10 and 12 each had a thickness of 1.70 mm, or a cutting capacity doubled.
  • the zones 10 and 12 can therefore have a relatively large thickness, which contributes to maintaining the rigidity of the assembly of the element 2.
  • the projecting parts can be an integral part of the first element, as in the embodiment described above, but can also be produced in the form of independent plates.
  • the plates are fixed to the first element by second fixing means, which can be identical to the first.
  • Each plate has an external face and an internal face, the internal faces of the plates constituting walls of the cavity containing the deformable envelope.
  • the plates have longitudinal grooves or grooves (that is to say substantially parallel to the detonating cord) formed from their external face and situated approximately at the level of the second end of the cavity.
  • the thinned parts are then formed by the zones located between the bottom of the grooves and the internal face of the plates.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Connection Of Plates (AREA)

Abstract

Device for the pyrotechnic separation between two elements (2, 4), for example panel-shaped elements. The first element (2) comprises two projecting parts (6, 8) connected to the remainder portion of the element by areas of reduced thickness (10, 12). The projecting parts (6, 8) are secured to the second element (4) by means of screws (30) and nuts (32). A deformable envelope (20) containing a detonating fuse is placed into the cavity (16) formed by the projecting parts (6, 8), the body of the first element (2) and the second element (4). Upon firing, the envelope (20) deforms and causes the rupture at the connection areas (10, 12). The thin areas (10, 12) being close to the extremity of the cavity (16) which is remote from the fixing point of the projecting parts (10, 12) to the second element (4), a greater lever arm and therefore an improved efficiency are obtained. Application to the aeronautical or spatial field.

Description

La présente invention a pour objet un dispositif pour la séparation de deux éléments au moyen d'une charge pyrotechnique utilisable notamment pour séparer des éléments en forme de panneaux dans les engins aéronautiques ou spatiaux.The present invention relates to a device for the separation of two elements by means of a pyrotechnic charge usable in particular for separating elements in the form of panels in aeronautical or spacecraft.

L'utilisation d'une charge pyrotechnique pour séparer des éléments d'un engin aéronautique ou spatial est connue et largement utilisée à l'heure actuelle. Par exemple, le document US-A-3 698 281 décrit un système de ce genre dans lequel la charge explosive se présente sous la forme de deux cordeaux détonants placés à l'intérieur d'une enveloppe déformable de forme oblongue, l'espace entre les cordeaux détonants et l'enveloppe étant rempli d'un matériau souple, tel que du caoutchouc par exemple. Les panneaux à séparer sont reliès l'un à l'autre par deux plaques métalliques, une sur chacune de leur face, ces plaques étant boulonnées sur les panneaux. L'enveloppe déformable est placée entre ces plaques dans un logement formé par des évidements prévus sur les plaques et qui épouse la forme de l'enveloppe. De plus, les plaques comportent, sur leurs faces opposées à ce logement, des rainures définissant une zone amincie, donc affaiblie, le long de laquelle doit se faire la fracture. Ces rainures se trouvent au niveau de la partie centrale des plaques, donc vers le milieu de la cavité dans laquelle est placée l'enveloppe déformable qui contient les cordeaux détonants. Lorsque le cordeau détonant est mis à feu, ceci provoque l'expansion de l'enveloppe déformable. Celle-ci tend à prendre une configuration circulaire, ce qui a pour effet de déformer la partie centrale des deux plaques reliant les panneaux à séparer et de provoquer la rupture le long des sections affaiblies. Si un tel dispositif donne satisfaction, il ne permet cependant de briser que des épaisseurs de tôles relativement faibles, par exemple de l'ordre d'1 mm.The use of a pyrotechnic charge to separate elements of an aeronautical or spacecraft is known and widely used at present. For example, document US-A-3,698,281 describes a system of this kind in which the explosive charge is in the form of two detonating cords placed inside a deformable envelope of oblong shape, the space between the detonating cords and the envelope being filled with a flexible material, such as rubber for example. The panels to be separated are connected to each other by two metal plates, one on each of their faces, these plates being bolted to the panels. The deformable envelope is placed between these plates in a housing formed by recesses provided on the plates and which matches the shape of the envelope. In addition, the plates have, on their faces opposite to this housing, grooves defining a thinned zone, therefore weakened, along which the fracture must be made. These grooves are located at the central part of the plates, therefore towards the middle of the cavity in which is placed the deformable envelope which contains the detonating cords. When the detonating cord is ignited, this causes the deformable envelope to expand. This tends to take a circular configuration, which has the effect of deforming the central part of the two plates connecting the panels to be separated and causing rupture along the weakened sections. If such a device is satisfactory, it does however make it possible to break only relatively small sheet thicknesses, for example of the order of 1 mm.

La présente invention a pour but de remédier à ces inconvénients en proposant un dispositif de séparation pyrotechnique entre deux éléments, par exemple des éléments en forme de panneaux, permettant de découper une épaisseur de tôle plus importante avec une même charge d'explosif.The object of the present invention is to remedy these drawbacks by proposing a separation device pyrotechnic between two elements, for example elements in the form of panels, making it possible to cut a greater thickness of sheet metal with the same charge of explosive.

Plus précisément, l'invention a pour objet un dispositif de séparation pyrotechnique entre un premier élément et un deuxième élément à l'aide d'une charge pyrotechnique placée dans une enveloppe déformable.More specifically, the invention relates to a pyrotechnic separation device between a first element and a second element using a pyrotechnic charge placed in a deformable envelope.

De manière connue, le premier élément comporte deux parties saillantes qui définissent entre elles un certain espace, le dispositif comportant en outre des premiers moyens de fixation pour fixer le premier élément sur le deuxième par l'intermédiaire desdites parties saillantes, définissant ainsi une cavité dans laquelle est placée ladite enveloppe déformable, cette cavité ayant une première extrémité proche desdits premiers moyens de fixation et une deuxième extrémité éloignée de ces premiers moyens de fixation, et le premier élément présente des parties amincies qui se rompent lors de l'explosion de la charge pyrotechnique.In a known manner, the first element comprises two protruding parts which define a certain space between them, the device further comprising first fixing means for fixing the first element to the second by means of said protruding parts, thus defining a cavity in which is placed said deformable envelope, this cavity having a first end close to said first fixing means and a second end remote from these first fixing means, and the first element has thinned parts which break when the charge explodes pyrotechnic.

Selon l'invention, les parties amincies se trouvent approximativement au niveau de la deuxième extrémité de ladite cavité.According to the invention, the thinned parts are located approximately at the second end of said cavity.

Ainsi, lors de la mise à feu, l'enveloppe se déforme et provoque la rupture au niveau de ces parties amincies. Comme ces dernières se trouvent au niveau de l'extrémité de la cavité la plus éloignée des premiers moyens de fixation, l'enveloppe déformable agit au moment de l'explosion sur un bras de levier relativement important correspondant à la longueur des parties saillantes : ceci permet d'avoir une meilleure efficacité, pour une charge donnée, qu'avec un dispositif tel que celui décrit dans le document US-A-3 698 281. En effet, dans ce dernier cas, les parties affaiblies des plaques de liaison se trouvent au milieu de celles-ci, donc à mi-chemin entre les fixations des plaques sur les éléments à séparer, et le bras de levier est plus faible.Thus, during ignition, the envelope deforms and causes rupture at these thinned parts. As the latter are located at the end of the cavity furthest from the first fixing means, the deformable envelope acts at the time of the explosion on a relatively large lever arm corresponding to the length of the projecting parts: this allows better efficiency, for a given load, than with a device such as that described in document US-A-3 698 281. Indeed, in the latter case, the weakened parts of the connection plates are found in the middle of these, so halfway between the plate attachments on the elements to be separated, and the lever arm is weaker.

Selon un mode préféré de réalisation de la présente invention, les premiers moyens de fixation comprennent au moins une vis passant à travers un trou ménagé dans chaque partie saillante et un trou ménagé dans le deuxième élément, et un écrou, le serrage de cet écrou sur la vis entraînant l'application desdites parties saillantes sur le deuxième élément. Dans ce cas, on peut prévoir en outre au moins un étrier dont une partie entoure au moins partiellement l'enveloppe déformable en étant en contact avec cette dernière et dont une autre partie comporte un trou à travers lequel peut passer la vis.According to a preferred embodiment of the present invention, the first fixing means comprise at least one screw passing through a hole formed in each protruding part and a hole formed in the second element, and a nut, the tightening of this nut on the screw causing the application of said protruding parts on the second element. In this case, it is also possible to provide at least one stirrup, a part of which at least partially surrounds the deformable envelope while being in contact with the latter and of which another part has a hole through which the screw can pass.

Dans le cas général où les éléments à séparer sont en forme de panneaux, le cordeau détonant et l'enveloppe déformable sont de forme allongée et il y a plusieurs dispositifs de fixation tels que celui qui vient d'être décrit avec des vis, des écrous et éventuellement des étriers, régulièrement répartis le long de la zone de séparation.In the general case where the elements to be separated are in the form of panels, the detonating cord and the deformable envelope are of elongated shape and there are several fixing devices such as that which has just been described with screws, nuts and possibly stirrups, regularly distributed along the separation zone.

Dans un premier mode de réalisation, les parties saillantes font partie intégrante du premier élément et sont raccordées au reste de cet élément par des zones de raccordement de faible épaisseur qui constituent lesdites parties amincies.In a first embodiment, the projecting parts form an integral part of the first element and are connected to the rest of this element by thin connection zones which constitute said thinned parts.

Dans un deuxième mode de réalisation, les parties saillantes sont constituées par des plaques fixées au premier élément par des deuxièmes moyens de fixation, chacune de ces plaques présentant une zone de faible épaisseur qui constitue l'une desdites parties amincies.In a second embodiment, the projecting parts consist of plates fixed to the first element by second fixing means, each of these plates having a thin zone which constitutes one of said thinned parts.

L'invention sera mieux comprise à la lecture de la description qui va suivre, donnée à titre d'exemple purement illustratif et nullement limitatif, en référence aux dessins annexés dans lesquels :

  • - la figure 1 est une vue schématique en coupe d'un dispositif conforme à l'invention avant la mise à feu de la charge,
  • - la figure 2 est une vue schématique en perspective montrant comment l'enveloppe déformable peut être maintenue à l'aide d'étriers, et
  • - la figure 3 est une vue semblable à la figure 1 montrant le dispositif objet de l'invention après mise à feu de la charge.
The invention will be better understood on reading the description which follows, given by way of purely illustrative and in no way limiting, with reference to the appended drawings in which:
  • FIG. 1 is a diagrammatic section view of a device according to the invention before the charge is ignited,
  • FIG. 2 is a schematic perspective view showing how the deformable envelope can be maintained using stirrups, and
  • - Figure 3 is a view similar to Figure 1 showing the device object of the invention after firing of the load.

Si l'on se reporte à la figure 1, on voit les deux éléments à séparer qui portent les références 2 et 4. Dans le mode de réalisation décrit ici, le premier élément 2 comporte deux parties saillantes 6 et 8, raccordées respectivement au corps de l'élément 2 par des zones de faible épaisseur 10 et 12. Dans cet exemple, les parties saillantes 6 et 8 ne sont pas des éléments rapportés, mais font partie intégrante du corps 2, celui-ci ayant été usiné afin de réaliser les parties saillantes 6 et 8. On voit encore sur la figure 1 que l'élément 2, y compris les parties saillantes 6 et 8, présente, vu en coupe, une symétrie par rapport à un plan P perpendiculaire au plan de la figure, représenté schématiquement en traits mixtes.If we refer to Figure 1, we see the two elements to be separated which bear the references 2 and 4. In the embodiment described here, the first element 2 has two projecting parts 6 and 8, connected respectively to the body of element 2 by thin zones 10 and 12. In this example, the projecting parts 6 and 8 are not attached elements, but form an integral part of the body 2, the latter having been machined in order to produce the protruding parts 6 and 8. It can also be seen in FIG. 1 that the element 2, including the protruding parts 6 and 8, has, seen in section, a symmetry with respect to a plane P perpendicular to the plane of the figure, represented schematically in dashed lines.

D'autre part, le deuxième élément 4 présente, le long de son bord le plus proche du premier élément 2, une partie élargie 14 dont la largeur est légèrement inférieure à la largeur de la cavité 16 définie entre les parties saillantes 6 et 8. La charge pyrotechnique se présente sous la forme d'un cordeau détonant 18 placé à l'intérieur d'une enveloppe déformable 20, l'espace entre le cordeau détonant et l'enveloppe déformable étant rempli par un matériau souple 22, par exemple une gaine de caoutchouc silicone.On the other hand, the second element 4 has, along its edge closest to the first element 2, an enlarged part 14 whose width is slightly less than the width of the cavity 16 defined between the projecting parts 6 and 8. The pyrotechnic charge takes the form of a detonating cord 18 placed inside a deformable envelope 20, the space between the detonating cord and the deformable envelope being filled with a flexible material 22, for example a sheath silicone rubber.

La gaine 22 remplit plusieurs fonctions. Tout d'abord, elle supporte et maintient le cordeau détonant 18 dans la bonne position, c'est-à-dire sensiblement suivant l'axe de symétrie de l'enveloppe 20. Dans le cas particulier décrit ici, cette enveloppe présente deux parties aplaties reliées par des parties semi-circulaires, mais on ne sortirait pas du cadre de l'invention en lui donnant une autre forme, ovale par exemple. De plus, si on utilise du caoutchouc silicone, celui-ci se comporte comme un isolant thermique et protège le cordeau 18 des brusques variations de températures que peuvent subir les composants d'un engin spatial. Enfin, les qualités d'amortissement du caoutchouc protègent le cordeau détonant des chocs externes auxquels un vaisseau spatial peut être soumis au moment du départ ou lors de la mise à feu de certains moteurs de propulsion.The sheath 22 performs several functions. First of all, it supports and maintains the detonating cord 18 in the correct position, that is to say substantially along the axis of symmetry of the envelope 20. In the particular case described here, this envelope has two parts flattened connected by semi-circular parts, but it would not depart from the scope of the invention by giving it another shape, oval for example. In addition, if silicone rubber is used, it behaves like a thermal insulator and protects the cord 18 from sudden temperature variations that the components of a spacecraft can undergo. Finally, the damping qualities of rubber protect the detonating cord from external shocks to which a spacecraft may be subjected upon departure or when certain propulsion engines are ignited.

Dans le cas particulier décrit ici, il n'y a qu'un seul cordeau détonant 18, mais on ne sortirait pas du cadre de l'invention en en mettant plusieurs, deux par exemple, afin que le deuxième puisse fonctionner en cas de défaillance du premier. Dans ce cas, la gaine souple 22 a aussi pour rôle d'empêcher la mise à feu du deuxième cordeau par les ondes de choc dues à l'explosion du premier.In the particular case described here, there is only one detonating cord 18, but it would not go beyond the scope of the invention by putting several, two for example, so that the second can operate in the event of failure from the first. In this case, the flexible sheath 22 also has the role of preventing the ignition of the second cord by shock waves due to the explosion of the first.

Les figures 1 et 2 montrent également les moyens de fixation du premier élément 2 sur le deuxième élément 4 par l'intermédiaire des parties saillantes 6 et 8. On voit que ces dernières présentent, à leurs extrémités opposées aux zones de raccordement 10 et 12, des trous 24 et 26 respectivement, qui peuvent être alignés avec un trou 28 ménagé dans la partie élargie 14 de l'élément 4, ces différents trous étant de même diamètre. Une vis 30 passe dans les trous 24, 28 et 26 et elle est maintenue par un écrou 32, le serrage de l'écrou 32 sur la vis 30 ayant pour effet d'appliquer les parties saillantes 6 et 8 du premier élément sur la partie élargie 14 du deuxième élément. Eventuellement, on peut placer une douille 34 à l'intérieur du passage formé par les trous 24, 28 et 26, afin de mieux ajuster la vis 30.FIGS. 1 and 2 also show the means for fixing the first element 2 to the second element 4 via the projecting parts 6 and 8. It can be seen that the latter have, at their ends opposite to the connection zones 10 and 12, holes 24 and 26 respectively, which can be aligned with a hole 28 formed in the enlarged part 14 of the element 4, these different holes being of the same diameter. A screw 30 passes through the holes 24, 28 and 26 and it is held by a nut 32, the tightening of the nut 32 on the screw 30 having the effect of applying the projecting parts 6 and 8 of the first element on the part enlarged 14 of the second element. Optionally, a socket 34 can be placed inside the passage formed by the holes 24, 28 and 26, in order to better adjust the screw 30.

On voit encore sur les figures 1 et 2 que le dispositif de fixation peut être complété à l'aide d'un ou plusieurs étriers tels que 36, répartis de place en place le long de l'enveloppe déformable 20. Ceux-ci peuvent être réalisés en tout matériau ductile tel que de l'acier doux.It can also be seen in FIGS. 1 and 2 that the fixing device can be completed using one or more stirrups such as 36, distributed from place to place along the deformable envelope 20. These can be made of any ductile material such as mild steel.

On voit sur la figure 2 que chaque étrier 36 se compose d'une partie supérieure 38 en forme de demi-cercle prolongée par deux branches 40 et 42. La partie supérieure 38 se trouve en contact avec la partie supérieure de l'enveloppe déformable 20 qui est, elle aussi, en forme de demi-cercle. Quant aux branches 40 et 42, elles sont sensiblement parallèles et leur écartement est tel qu'elles peuvent être placées entre la face interne des parties saillantes 6 et 8 et la face externe de la partie élargie 14 de l'élément 4 (figure 1). Les branches 40 et 42 de l'étrier 36 comportent en outre des trous 44 et 46 respectivement (figure 2) de même diamètre que les trous 24, 26 et 28, la vis 30 passant également à travers les trous 44 et 46.It can be seen in FIG. 2 that each stirrup 36 consists of an upper part 38 in the form of a semicircle extended by two branches 40 and 42. The upper part 38 is in contact with the upper part of the deformable envelope 20 which is also in the shape of a semicircle. As for the branches 40 and 42, they are substantially parallel and their spacing is such that they can be placed between the internal face of the projecting parts 6 and 8 and the external face of the widened part 14 of the element 4 (FIG. 1). The branches 40 and 42 of the stirrup 36 also have holes 44 and 46 respectively (FIG. 2) of the same diameter as the holes 24, 26 and 28, the screw 30 also passing through the holes 44 and 46.

Si l'on se reporte à nouveau à la figure 1, on voit que l'enveloppe déformable 20 est maintenue contre les faces internes de chaque partie saillante 6 et 8, contre la paroi de la cavité 16 située du côté du corps de l'élément 2 et, enfin, contre un bossage 48 prévu sur la partie élargie 14 de l'élément 4. Cette disposition fait que l'enveloppe 20 est tenue de tous les côtés, mais on ne sortirait pas du cadre de l'invention en utilisant un montage équivalent, pourvu que l'enveloppe 20 soit maintenue de façon à ce que l'énergie de l'explosion provoque la déchirure au niveau des zones de raccordement 10 et 12.Referring again to FIG. 1, it can be seen that the deformable envelope 20 is held against the internal faces of each protruding part 6 and 8, against the wall of the cavity 16 situated on the body side of the element 2 and, finally, against a boss 48 provided on the enlarged part 14 of element 4. This arrangement means that the envelope 20 is held on all sides, but it would not go beyond the scope of the invention by using an equivalent assembly, provided that the envelope 20 is maintained so that the energy of the explosion causes tearing at the connection zones 10 and 12.

On va maintenant décrire le fonctionnement de ce dispositif en référence à la figure 3. Lors de la mise à feu, le cordeau détonant 18 explose et l'énergie de l'explosion est transmise à travers la gaine souple 22 jusqu'à l'enveloppe déformable. Celle-ci se déforme donc et tend à prendre une section plus ou moins circulaire. Un effort est donc exercé sur les faces internes des parties saillantes 6 et 8, sensiblement perpendiculairement à ces faces. Les parties saillantes 6 et 8 subissent un couple et ont tendance à pivoter autour d'une zone voisine de leur extrémité maintenue contre l'élément 4 (zones 6a et 8a sur la figure 3). C'est à l'extrémité des parties saillantes 6 et 8 la plus éloignée de la vis 30 que s'exerce le couple le plus important, c'est-à-dire au niveau des zones de raccordement 10 et 12 car c'est là que le bras de levier est le plus important. C'est donc à cet endroit que se fait la rupture.We will now describe the operation of this device with reference to Figure 3. When fired, the detonating cord 18 explodes and the energy of the explosion is transmitted through the flexible sheath 22 to the envelope deformable. It therefore deforms and tends to take a more or less circular section. A force is therefore exerted on the internal faces of the projecting parts 6 and 8, substantially perpendicular to these faces. The protrusions 6 and 8 undergo a torque and tend to pivot around an area close to their end held against the element 4 (areas 6a and 8a in FIG. 3). It is at the end of the protrusions 6 and 8 furthest from the screw 30 that the greatest torque is exerted, that is to say at the level of the connection zones 10 and 12 because it is where the lever arm is most important. So this is where the break is made.

Ainsi, le dispositif objet de l'invention présente des avantages intéressants dont le principal est qu'il permet, pour une masse d'explosif donnée, de couper une épaisseur de tôle plus importante qu'avec les dispositifs de l'art antérieur. Des essais comparatifs ont été réalisés avec un dispositif conforme à celui décrit dans le document US-A-3 698 281 et avec un dispositif conforme à celui de l'invention, tel qu'illustré à la figure 1. Dans le premier cas, on n'a pu couper qu'un ensemble de deux tôles d'épaisseur faible, c'est-à-dire pour chacune de l'ordre de 0,85 mm, tandis qu'avec le dispositif de l'invention, on a pu découper un élément dans lequel les zones amincies 10 et 12 avaient chacune une épaisseur de 1,70 mm, soit une capacité de découpage doublée.Thus, the device which is the subject of the invention has interesting advantages, the main one of which is that it allows, for a given explosive mass, to cut a greater thickness of sheet metal than with the devices of the prior art. Tests comparisons were made with a device according to that described in document US-A-3,698,281 and with a device according to that of the invention, as illustrated in FIG. 1. In the first case, there is no was able to cut a set of two thin sheets, that is to say for each of the order of 0.85 mm, while with the device of the invention, it was possible to cut a element in which the thinned zones 10 and 12 each had a thickness of 1.70 mm, or a cutting capacity doubled.

Les zones 10 et 12 peuvent donc avoir une épaisseur relativement importante, ce qui contribue à maintenir la rigidité de l'ensemble de l'élément 2.The zones 10 and 12 can therefore have a relatively large thickness, which contributes to maintaining the rigidity of the assembly of the element 2.

Enfin, il est bien entendu que l'invention ne se limite pas au seul mode de réalisation qui vient d'être décrit, mais qu'on peut envisager des variantes sans sortir pour autant du cadre de l'invention. Par exemple, les parties saillantes peuvent faire partie intégrante du premier élément, comme dans le mode de réalisation décrit ci-dessus, mais peuvent aussi être réalisées sous forme de plaques indépendantes. Dans ce cas, les plaques sont fixées au premier élément par des deuxièmes moyens de fixation, qui peuvent être identiques aux premiers. Chaque plaque présente une face externe et une face interne, les faces internes des plaques constituant des parois de la cavité contenant l'enveloppe déformable. Les plaques comportent des gorges ou rainures longitudinales (c'est-à-dire sensiblement parallèles au cordeau détonant) ménagées à partir de leur face externe et situées approximativement au niveau de la deuxième extrémité de la cavité. Les parties amincies sont alors constituées par les zones se trouvant entre le fond des gorges et la face interne des plaques.Finally, it is understood that the invention is not limited to the single embodiment which has just been described, but that it is possible to envisage variants without thereby departing from the scope of the invention. For example, the projecting parts can be an integral part of the first element, as in the embodiment described above, but can also be produced in the form of independent plates. In this case, the plates are fixed to the first element by second fixing means, which can be identical to the first. Each plate has an external face and an internal face, the internal faces of the plates constituting walls of the cavity containing the deformable envelope. The plates have longitudinal grooves or grooves (that is to say substantially parallel to the detonating cord) formed from their external face and situated approximately at the level of the second end of the cavity. The thinned parts are then formed by the zones located between the bottom of the grooves and the internal face of the plates.

Claims (5)

1. Dispositif de séparation pyrotechnique entre un premier élément (2) et un deuxième élément (4) à l'aide d'une charge pyrotechnique (18) placée dans une enveloppe déformable (20), le premier élément (2) comportant deux parties saillantes (6, 8) qui définissent entre elles un certain espace, le dispositif comportant en outre des premiers moyens de fixation (30, 32) pour fixer le premier élément (2) sur le deuxième (4) par l'intermédiaire desdites parties saillantes (6, 8), définissant ainsi une cavité (16) dans laquelle est placée ladite enveloppe déformable (20), cette cavité (16) ayant une première extrémité proche desdits premiers moyens de fixation (30, 32) et une deuxième extrémité éloignée de ces premiers moyens de fixation, le premier élément (2) présentant des parties amincies (10, 12) qui se rompent lors de l'explosion de la charge pyrotechnique (18), caractérisé en ce que lesdites parties amincies (6, 8) se trouvent approximativement au niveau de la deuxième extrémité de ladite cavité (16).1. Pyrotechnic separation device between a first element (2) and a second element (4) using a pyrotechnic charge (18) placed in a deformable envelope (20), the first element (2) comprising two parts projections (6, 8) which define a certain space between them, the device further comprising first fixing means (30, 32) for fixing the first element (2) on the second (4) by means of said projecting parts (6, 8), thus defining a cavity (16) in which said deformable envelope (20) is placed, this cavity (16) having a first end close to said first fixing means (30, 32) and a second end distant from these first fixing means, the first element (2) having thinned parts (10, 12) which break when the pyrotechnic charge (18) explodes, characterized in that said thinned parts (6, 8) are found approximately at the second end of the lad ite cavity (16). 2. Dispositif selon la revendication 1, caractérisé en ce que les premiers moyens de fixation comprennent au moins une vis (30) passant à travers un trou (24, 26) ménagé dans chaque partie saillante (6, 8) et un trou (28) ménagé dans le deuxième élément (4), et un écrou (32), le serrage de cet écrou (32) sur la vis (30) entraînant l'application desdites parties saillantes sur le deuxième élément (4).2. Device according to claim 1, characterized in that the first fixing means comprise at least one screw (30) passing through a hole (24, 26) formed in each projection (6, 8) and a hole (28 ) formed in the second element (4), and a nut (32), the tightening of this nut (32) on the screw (30) causing the application of said projecting parts on the second element (4). 3. Dispositif selon la revendication 2, caractérisé en ce que les premiers moyens de fixation comprennent en outre au moins un étrier (36) dont une partie entoure au moins partiellement l'enveloppe déformable (20) en étant en contact avec cette dernière et dont une autre partie comporte un trou (44) à travers lequel peut passer ladite vis (30).3. Device according to claim 2, characterized in that the first fixing means further comprise at least one stirrup (36) of which a part at least partially surrounds the deformable envelope (20) while being in contact with the latter and whose another part has a hole (44) through which said screw (30) can pass. 4. Dispositif selon la revendication 1, caractérisé en ce que lesdites parties saillantes (6, 8) font partie intégrante du premier élément (2) et sont raccordées au reste de cet élément (2) par des zones de raccordement de faible épaisseur qui constituent lesdites parties amincies (10, 12).4. Device according to claim 1, characterized in that said projecting parts (6, 8) are an integral part of the first element (2) and are connected to the rest of this element (2) by thin connection zones which constitute said thinned parts (10, 12). 5. Dispositif selon la revendication 1, caractérisé en ce que lesdites parties saillantes (6, 8) sont constituées par des plaques fixées au premier élément par des deuxièmes moyens de fixation, chacune de ces plaques présentant une zone de faible épaisseur qui constitue l'une desdites parties amincies (10, 12).5. Device according to claim 1, characterized in that said projecting parts (6, 8) are constituted by plates fixed to the first element by second fixing means, each of these plates having a thin area which constitutes the one of said thinned parts (10, 12).
EP87401102A 1986-05-16 1987-05-15 Device for pyrotechnically separating two elements Expired - Lifetime EP0246958B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8607063A FR2598796B1 (en) 1986-05-16 1986-05-16 DEVICE FOR PYROTECHNIC SEPARATION OF TWO ELEMENTS
FR8607063 1986-05-16

Publications (2)

Publication Number Publication Date
EP0246958A1 true EP0246958A1 (en) 1987-11-25
EP0246958B1 EP0246958B1 (en) 1990-08-16

Family

ID=9335324

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87401102A Expired - Lifetime EP0246958B1 (en) 1986-05-16 1987-05-15 Device for pyrotechnically separating two elements

Country Status (5)

Country Link
EP (1) EP0246958B1 (en)
DE (1) DE3764311D1 (en)
ES (1) ES2018281B3 (en)
FR (1) FR2598796B1 (en)
WO (1) WO1987007006A1 (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2638228A1 (en) * 1988-10-25 1990-04-27 Oea Inc SEPARABLE STRUCTURE ACTION BY EXPLOSIVE
FR2665951A1 (en) * 1990-08-20 1992-02-21 Aerospatiale BREAKABLE CONNECTION SYSTEM FOR SEPARATING PARTS BY MEANS OF A DETONATING LOAD.
EP0596400A2 (en) * 1992-11-02 1994-05-11 Orbital Sciences Corporation Frangible annular joint for connecting and disconnecting two elements
US6125762A (en) * 1997-07-03 2000-10-03 The Ensign-Bickford Company Flat-form separation devices
US6170400B1 (en) 1998-06-02 2001-01-09 AEROSPATIALE Soci{acute over (e)}t{acute over (e)}Nationale Industrielle Device for the cutting of nonmetallic parts by means of a pyrotechnic expansion tube
US6286430B1 (en) 1998-06-02 2001-09-11 AEROSPATIALE SOCIéTé NATIONALE INDUSTRIELLE Device for the pyrotechnic cutting of non-metallic parts
US6820559B1 (en) 2002-05-07 2004-11-23 Eads Launch Vehicles Moving part device for the temporary connection and pyrotechnic separation of two elements
FR2957143A1 (en) * 2010-03-02 2011-09-09 Astrium Sas PYROTECHNIC RUPTURE CONNECTION DEVICE
FR3028608A1 (en) * 2014-11-19 2016-05-20 Dassault Aviat PYROTECHNIC SEPARATOR COMPRISING A SHOCK ABSORPTION MEMBER

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2779222B1 (en) 1998-06-02 2000-08-11 Aerospatiale DEVICE FOR PROVISIONAL CONNECTION AND PYROTECHNICAL SEPARATION OF TWO NON-METAL ASSEMBLIES
FR2838818B1 (en) 2002-04-19 2006-12-08 Eads Launch Vehicules DEVICE FOR PROVISIONAL BONDING AND PYROTECHNIC SEPARATION OF TWO ELEMENTS, WITHOUT BREAK
FR2850454B1 (en) 2003-01-24 2005-04-15 Eads Launch Vehicles METHOD FOR ASSEMBLING A PYROTECHNIC SEPARATION DEVICE, AND PYROTECHNIC SEPARATION DEVICE OBTAINED THEREBY
US10934029B2 (en) * 2017-05-04 2021-03-02 Paragon Space Development Corporation Thermally isolating joint assembly in a space vehicle
US11787571B2 (en) * 2017-12-01 2023-10-17 Ensign-Bickford Aerospace & Defense Company Separation device assemblies

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3362290A (en) * 1965-04-13 1968-01-09 Mc Donnell Douglas Corp Non-contaminating thrusting separation system
US3453960A (en) * 1967-12-11 1969-07-08 Gen Dynamics Corp Noncontaminating linear explosive separation
US3486410A (en) * 1968-04-18 1969-12-30 Mc Donnell Douglas Corp Explosive severance means
US3698281A (en) * 1970-02-27 1972-10-17 Lockheed Aircraft Corp Explosive system
US4137848A (en) * 1975-11-05 1979-02-06 The United States Of America As Represented By The Secretary Of The Navy Rocket engine mount

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3362290A (en) * 1965-04-13 1968-01-09 Mc Donnell Douglas Corp Non-contaminating thrusting separation system
US3453960A (en) * 1967-12-11 1969-07-08 Gen Dynamics Corp Noncontaminating linear explosive separation
US3486410A (en) * 1968-04-18 1969-12-30 Mc Donnell Douglas Corp Explosive severance means
US3698281A (en) * 1970-02-27 1972-10-17 Lockheed Aircraft Corp Explosive system
US4137848A (en) * 1975-11-05 1979-02-06 The United States Of America As Represented By The Secretary Of The Navy Rocket engine mount

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2638228A1 (en) * 1988-10-25 1990-04-27 Oea Inc SEPARABLE STRUCTURE ACTION BY EXPLOSIVE
GB2224338A (en) * 1988-10-25 1990-05-02 Oea Inc Explosively actuated separable structure
GB2224338B (en) * 1988-10-25 1992-11-11 Oea Inc Explosively actuated separable structure
FR2665951A1 (en) * 1990-08-20 1992-02-21 Aerospatiale BREAKABLE CONNECTION SYSTEM FOR SEPARATING PARTS BY MEANS OF A DETONATING LOAD.
EP0472453A1 (en) * 1990-08-20 1992-02-26 AEROSPATIALE Société Nationale Industrielle Connection breakable by means of an explosive charge
US5535502A (en) * 1992-11-02 1996-07-16 Orbital Sciences Corporation Method for making an explosive separation system
EP0596400A3 (en) * 1992-11-02 1994-07-13 Orbital Sciences Corp Frangible annular joint for connecting and disconnecting two elements
US5390606A (en) * 1992-11-02 1995-02-21 Orbital Sciences Corporation Frangible joint separation system
EP0596400A2 (en) * 1992-11-02 1994-05-11 Orbital Sciences Corporation Frangible annular joint for connecting and disconnecting two elements
US6125762A (en) * 1997-07-03 2000-10-03 The Ensign-Bickford Company Flat-form separation devices
US6170400B1 (en) 1998-06-02 2001-01-09 AEROSPATIALE Soci{acute over (e)}t{acute over (e)}Nationale Industrielle Device for the cutting of nonmetallic parts by means of a pyrotechnic expansion tube
US6286430B1 (en) 1998-06-02 2001-09-11 AEROSPATIALE SOCIéTé NATIONALE INDUSTRIELLE Device for the pyrotechnic cutting of non-metallic parts
US6820559B1 (en) 2002-05-07 2004-11-23 Eads Launch Vehicles Moving part device for the temporary connection and pyrotechnic separation of two elements
FR2957143A1 (en) * 2010-03-02 2011-09-09 Astrium Sas PYROTECHNIC RUPTURE CONNECTION DEVICE
WO2011107690A1 (en) * 2010-03-02 2011-09-09 Astrium Sas Connecting device having pyrotechnic rupture
US8776661B2 (en) 2010-03-02 2014-07-15 Astrium Sas Connecting device having pyrotechnic rupture
FR3028608A1 (en) * 2014-11-19 2016-05-20 Dassault Aviat PYROTECHNIC SEPARATOR COMPRISING A SHOCK ABSORPTION MEMBER
EP3023733A1 (en) * 2014-11-19 2016-05-25 Dassault Aviation Pyrotechnical separator comprising a bump absorbing element

Also Published As

Publication number Publication date
ES2018281B3 (en) 1991-04-01
FR2598796B1 (en) 1990-04-20
DE3764311D1 (en) 1990-09-20
EP0246958B1 (en) 1990-08-16
WO1987007006A1 (en) 1987-11-19
FR2598796A1 (en) 1987-11-20

Similar Documents

Publication Publication Date Title
EP0246958B1 (en) Device for pyrotechnically separating two elements
FR2665951A1 (en) BREAKABLE CONNECTION SYSTEM FOR SEPARATING PARTS BY MEANS OF A DETONATING LOAD.
EP1355120B1 (en) Device for provisionally connecting and pyrotechnically separating two elements, with no rupture
EP1361411B1 (en) Device with a mobile element, for provisionally connecting and pyrotechnically separating two units
EP3396300A1 (en) Actuating device for ejecting at least one removable part of a missile, in particular a fairing
EP0539257B1 (en) Cargo munition
EP0454545B1 (en) Device for the temporal mechanical assembly and for its fast separation of an ejecting object attached to a support
EP3344547B1 (en) Method for the linear separation and connection of two elements
EP1319920B1 (en) Pyrotechnical separator and separation system equipped with said separator
EP3617075B1 (en) Localised link device for controlled separation comprising a layer with multidirectional link
EP0454546B1 (en) Device for temporal holding of an object to a support, with a traction calibrated breaking neck
EP2035717B1 (en) Link rod providing the connection between two moving parts and corresponding motor vehicle
EP0773424B1 (en) Projectile forming charge improved in withstanding acceleration
EP1152859B1 (en) Controlled rupture device for a structure operating in traction and equipment using same
EP3023733A1 (en) Pyrotechnical separator comprising a bump absorbing element
FR2986843A1 (en) Structural connection device for transmitting tensile or compressive stress between engine and mast reactor of aircraft, has connection ring connecting beams for ensuring filtering of vibrations generated by structure elements
EP0675334B1 (en) Aerodynamic stabilisation and braking device for air-drop body
FR2817955A1 (en) Damper for explosive charge has enclosure block for initiator relay having dampers for axial shock wave across block
EP0633449B1 (en) Safety and arming device for an explosive object
WO2024023410A1 (en) Annular enclosure for an intermediate stage of an aerospace launcher with fall retarder
EP3985345A1 (en) Piercing and explosive projectile provided with a stabilisation tail
WO2021209724A1 (en) Low-shock and reusable retention and release device
EP0210602A1 (en) Test bar holding device permitting a sudden release
FR2662790A2 (en) Improvements made to the production of projectiles having tandem charges with explosive effects
FR2738908A1 (en) Aerodynamic brake for sub=munitions released from spinning carrier shell

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): BE CH DE ES FR GB IT LI NL SE

17P Request for examination filed

Effective date: 19880503

17Q First examination report despatched

Effective date: 19890120

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): BE CH DE ES FR GB IT LI NL SE

REF Corresponds to:

Ref document number: 3764311

Country of ref document: DE

Date of ref document: 19900920

ITF It: translation for a ep patent filed

Owner name: JACOBACCI & PERANI S.P.A.

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
ITTA It: last paid annual fee
EAL Se: european patent in force in sweden

Ref document number: 87401102.6

REG Reference to a national code

Ref country code: CH

Ref legal event code: PLI

Owner name: SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE -DANN

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

REG Reference to a national code

Ref country code: ES

Ref legal event code: GD2A

Effective date: 20000320

REG Reference to a national code

Ref country code: CH

Ref legal event code: PFA

Free format text: SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE TRANSFER- AEROSPATIALE MATRA

REG Reference to a national code

Ref country code: FR

Ref legal event code: CL

Ref country code: FR

Ref legal event code: CD

REG Reference to a national code

Ref country code: ES

Ref legal event code: PC2A

REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

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

Ref country code: NL

Payment date: 20050503

Year of fee payment: 19

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

Ref country code: SE

Payment date: 20050506

Year of fee payment: 19

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

Ref country code: BE

Payment date: 20050714

Year of fee payment: 19

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

Ref country code: GB

Payment date: 20060510

Year of fee payment: 20

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

Ref country code: SE

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

Effective date: 20060516

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

Ref country code: FR

Payment date: 20060526

Year of fee payment: 20

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: 20060531

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

Ref country code: IT

Payment date: 20060531

Year of fee payment: 20

Ref country code: CH

Payment date: 20060531

Year of fee payment: 20

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

Ref country code: DE

Payment date: 20060601

Year of fee payment: 20

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

Ref country code: ES

Payment date: 20060621

Year of fee payment: 20

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 NON-PAYMENT OF DUE FEES

Effective date: 20061201

EUG Se: european patent has lapsed
NLV4 Nl: lapsed or anulled due to non-payment of the annual fee

Effective date: 20061201

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

Ref country code: ES

Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION

Effective date: 20070516

REG Reference to a national code

Ref country code: GB

Ref legal event code: PE20

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20070516

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 EXPIRATION OF PROTECTION

Effective date: 20070514

BERE Be: lapsed

Owner name: *AEROSPATIALE SOC. NATIONALE INDUSTRIELLE

Effective date: 20060531