EP3264021A1 - Flexible seal for missile container - Google Patents

Flexible seal for missile container Download PDF

Info

Publication number
EP3264021A1
EP3264021A1 EP17290081.3A EP17290081A EP3264021A1 EP 3264021 A1 EP3264021 A1 EP 3264021A1 EP 17290081 A EP17290081 A EP 17290081A EP 3264021 A1 EP3264021 A1 EP 3264021A1
Authority
EP
European Patent Office
Prior art keywords
flexible
layer
flexible lid
auxiliary
composite
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
EP17290081.3A
Other languages
German (de)
French (fr)
Other versions
EP3264021B1 (en
Inventor
Bertrand Leroy
Pascal Herquel
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 EP3264021A1 publication Critical patent/EP3264021A1/en
Application granted granted Critical
Publication of EP3264021B1 publication Critical patent/EP3264021B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/077—Doors or covers for launching tubes

Definitions

  • the present invention relates to a flexible seal for a missile container.
  • a container seal has the function of sealing the container to protect a missile installed in this container.
  • the operculum must be able to open in order to let the missile or the propulsion gases pass when the latter fires.
  • the present invention aims to overcome at least some of these disadvantages. More specifically, it aims to remedy the problem of debris presenting a hazard for equipment, while ensuring a moderate effort on the radome of the missile, a low mass and a reduced manufacturing cost.
  • the present invention relates to a flexible cover, intended to be mounted on a missile container and able to open under a thrust.
  • the fabric or fabrics that are introduced into the elastomer to form the composite part ensure the mechanical strength of the flexible seal which is, moreover, made hermetic thanks in particular to the elastomer.
  • said at least one auxiliary layer (comprising petal-shaped zones defining weakening lines) makes it possible to direct a precise cut of the flexible cap along said weakening lines, which allows an easier opening.
  • the composite material part has great flexibility (or flexibility), which allows the flexible cover to return, after opening, to a position close to the position before opening.
  • a flexible seal is thus obtained which makes it possible to avoid the generation of debris (presenting a danger for the equipment), while guaranteeing a moderate effort on the missile radome, a low mass and a reduced manufacturing cost.
  • said at least one auxiliary layer is bonded to said main layer by seams, which ensures a good hold of the petal-shaped areas. These seams also participate in the maintenance during the manufacturing process of the flexible cover.
  • the present invention also relates to a missile container, which comprises at least one flexible cap as described above.
  • the present invention further relates to a weapon system that includes at least one such missile container.
  • the flexible seal 1 illustrating the invention and shown schematically on the figure 1 is intended to be mounted on a missile container (not shown).
  • This missile container is part of a weapon system (also not shown).
  • the flexible lid 1 has the function of sealing the container to protect a missile installed in the container.
  • the flexible cover must be able to open in order to let the missile or the propulsion gases pass during a firing of the latter.
  • the flexible seal 1 is configured to open under a thrust.
  • this thrust can be generated during a firing by a contact of the flexible cap by the missile, or by an internal overpressure generated by dedicated means or propulsion gases of the missile.
  • each auxiliary layer 3, 4 comprises a plurality of zones 6 (made of composite material 10) in the form of petals, for example of triangular shape, which are separated from each other by separation lines, called lines of weakness 5.
  • These weakening lines 5, free of fabric, are filled with elastomer (of the composite material 10), as shown in black on the figures 1 and 2 .
  • Said main layer 2 and said at least one auxiliary layer 3, 4 thus form a monobloc composite part 8.
  • the composite material 10 forming the auxiliary layer or layers 3, 4 is identical to the composite material 9 forming the main layer 2.
  • the composite layer 2 and the auxiliary layer or layers 3, 4 thus form a flexible composite part 8 which, thanks to its flexibility (or flexibility), allows the flexible cover 1 to return, after an opening, to a position which is close to its position before opening, as specified below.
  • auxiliary layer or layers 3, 4 with petal-shaped zones 6 makes it possible to direct a precise cut of the composite material (elastomer / fabric), along the weakening lines 5 formed between these zones 6.
  • the fabric or fabrics that are inserted into the elastomer to form the composite material 9, 10 provide the mechanical strength of the flexible seal 1.
  • This or these tissues are made, in particular, based on carbon or fiberglass, or textile fibers (polyester, polyamide, ).
  • the composite material 9, 10 also makes it possible, thanks to the elastomer, to make the flexible seal 1 hermetic.
  • the elastomer can be made of different materials.
  • this elastomer is of butyl, neoprene, silicone, ...
  • the flexible cover 1 comprises two auxiliary layers 3 and 4 which are arranged on either side of the main layer 2, respectively on the faces 2A and 2B of the latter.
  • the two auxiliary layers 3, 4 are arranged, with their petal-shaped zones 6, symmetrically, with respect to a substantially central plane P of the main layer 2 of generally planar shape.
  • the weakening zones are located at the same position on either side of the main layer 2.
  • a single auxiliary layer 3 (fabric / elastomer) is provided on the outer face 2A of the main layer 2 (fabric / elastomer), that is to say on the face 1A which will be directed towards the outside of the container in the mounted position of the flexible cover 1. This limits the effort required for opening.
  • the flexible seal 1 further comprises an anti-friction coating 11 on the inner face 1 B, which is therefore intended to be placed towards the inside of the container.
  • This anti-friction coating 11 makes it possible, in particular, to limit the friction during the passage of the missile through the flexible cover 1.
  • the antifriction coating 11 is made for example from a metallic material, which allows, in addition to reducing the coefficient of friction, to provide electrical continuity.
  • the zones 6 thus make it possible to create the weakening lines 5, which facilitates the tearing of the composite material 9 (fabric / elastomer) of the main layer 2 in precise directions.
  • the weakening lines 5 are arranged radially with respect to the center 12 of the flexible cap 1, as shown in FIGS. Figures 3 to 5 .
  • the weakening lines 5 are more or less numerous, for example two lines oriented along the diagonals as on the examples of the figures 3 and 5 or four lines oriented along the diagonals and the mediators of the sides as shown in the example of the figure 4 .
  • each auxiliary layer 3, 4 is bonded to the main layer 2 by seams 13 and 14 ( Figures 3 to 5 ).
  • These seams 13 and 14 also participate in maintaining the fabric of the auxiliary layers 3 and 4 on the main layer 2, during the manufacturing process of the flexible lid. They are conventionally made from yarns, for example made of polyamide, which correspond, preferably but not exclusively, to the yarns of the fabrics used to form the composite materials 9 and 10.
  • some seams 13 are arranged in the zones 6, parallel to the weakening lines 5, along sewing lines 15, which facilitates tearing along the weakening lines 5.
  • seams can be provided on the entire surface of the zones 6 shaped petals. The distribution of these seams can then take different forms.
  • the flexible seal 1 is preferably designed to hold pressures between 1 and 5 bar, and to open from 5 bar.
  • the operation of the flexible lid 1 is also specified.
  • the flexible seal 1 (and more particularly the composite part 8 and, where appropriate, also the anti-friction coating 11) tears along the weakening lines 5, and the flexible petals 6 thus released curl outwardly to open the flexible seal 1 and release the passage for the missile.
  • the flexible petals 6 return, thanks to their flexibility, to an initial position so that the flexible cover 1 is close to its position before opening to allow the closing of the door of the cell.
  • elements 16 for example stainless steel, in particular four elements 16 in the form of a square, allow to clamp the flexible lid 1 on the container (not shown).
  • a container of a missile launcher which is embarked on a ship.
  • a container generally comprises a series of cells, each cell being intended to receive a missile placed in its container.
  • the upper part of a cell opens at the deck of the ship and is closed, outside the launching phases, by a door.
  • the lower part of a cell has a communication opening opening into a chamber for receiving the gases emitted during the launch of a missile.
  • the upper and lower parts of each container are closed in a sealed manner, by a lid provided with a high flexible lid, such as the flexible lid 1 specified above, and by a bottom provided, for example, also with a low flexible lid such as the flexible lid 1.
  • the inner volume of the container is, in general, filled with an inert gas at overpressure relative to the atmosphere.
  • an inert gas at overpressure relative to the atmosphere.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Closures For Containers (AREA)
  • Laminated Bodies (AREA)

Abstract

- Opercule flexible pour conteneur de missile. - L'opercule flexible (1) comporte au moins une couche (2) dite principale, formée d'un matériau composite (9) constitué d'au moins un tissu et d'au moins un élastomère, et au moins une couche (3, 4) dite auxiliaire formée d'un matériau composite (10) constitué également d'au moins un tissu et d'au moins un élastomère, la couche auxiliaire (3, 4) étant solidarisée de la couche composite (2) sur l'une des faces (2A, 2B) de cette dernière, ladite couche auxiliaire (4, 5) comprenant des zones (6) en forme de pétales, séparées les unes des autres par des lignes (5) dites de fragilisation, ladite couche principale (2) et ladite au moins une couche auxiliaire (3, 4) formant une pièce composite (8).- Flexible lid for missile container. - The flexible seal (1) comprises at least one layer (2) said main, formed of a composite material (9) consisting of at least one fabric and at least one elastomer, and at least one layer (3). , 4) said auxiliary formed of a composite material (10) also consisting of at least one fabric and at least one elastomer, the auxiliary layer (3, 4) being secured to the composite layer (2) on the one of the faces (2A, 2B) of the latter, said auxiliary layer (4, 5) comprising zones (6) in the form of petals, separated from each other by so-called weakening lines (5), said main layer ( 2) and said at least one auxiliary layer (3, 4) forming a composite part (8).

Description

La présente invention concerne un opercule flexible pour conteneur de missile.The present invention relates to a flexible seal for a missile container.

On sait qu'un opercule de conteneur a pour fonction de fermer hermétiquement le conteneur afin de protéger un missile installé dans ce conteneur. L'opercule doit pouvoir s'ouvrir afin de laisser passer le missile ou les gaz de propulsion lors du tir de ce dernier.It is known that a container seal has the function of sealing the container to protect a missile installed in this container. The operculum must be able to open in order to let the missile or the propulsion gases pass when the latter fires.

Généralement, les opercules se divisent en deux catégories :

  • des opercules fragmentables, qui sont réalisés en général en matériaux composites ; et
  • des mécanismes à ouvertures automatiques, le plus généralement métalliques.
Generally, the covers are divided into two categories:
  • fragmentable opercules, which are generally made of composite materials; and
  • mechanisms with automatic openings, the most generally metallic.

Ces solutions présentent différents inconvénients. Plus précisément, les inconvénients de ces solutions sont :

  • pour les opercules en matériaux composites :
    • la présence de débris projetés à des vitesses élevées dans diverses directions, ces débris présentant un danger pour les équipements à proximité, et même parfois pour le missile lui-méme ; et
    • dans certains cas, un effort important sur le radôme du missile lors de la traversée de l'opercule en phase de départ ; et
  • pour les mécanismes à ouvertures automatiques :
    • une gestion plus complexe de la sécurité afin de garantir l'ouverture ;
    • une masse beaucoup plus importante ; et
    • un coût de fabrication élevé.
These solutions have different disadvantages. More precisely, the disadvantages of these solutions are:
  • for lids made of composite materials:
    • the presence of debris projected at high speeds in various directions, these debris presenting a danger for nearby equipment, and sometimes even for the missile itself; and
    • in some cases, a significant effort on the radome of the missile during the crossing of the seal in the departure phase; and
  • for mechanisms with automatic openings:
    • more complex security management to ensure openness;
    • a much larger mass; and
    • a high manufacturing cost.

La présente invention a pour objet de pallier au moins certains de ces inconvénients. Plus précisément, elle a pour objet de remédier au problème des débris présentant un danger pour les équipements, tout en garantissant un effort modéré sur le radôme du missile, une faible masse et un coût de fabrication réduit.The present invention aims to overcome at least some of these disadvantages. More specifically, it aims to remedy the problem of debris presenting a hazard for equipment, while ensuring a moderate effort on the radome of the missile, a low mass and a reduced manufacturing cost.

La présente invention concerne un opercule flexible, destiné à être monté sur un conteneur de missile et apte à s'ouvrir sous une poussée.The present invention relates to a flexible cover, intended to be mounted on a missile container and able to open under a thrust.

Selon l'invention, l'opercule flexible comporte :

  • une couche dite principale, formée d'un matériau composite constitué d'au moins un tissu et d'au moins un élastomère ; et
  • au moins une couche dite auxiliaire, formée d'un matériau composite constitué également d'au moins un tissu et d'au moins un élastomère, ladite couche auxiliaire étant solidarisée de ladite couche composite sur l'une des faces de cette dernière, ladite couche auxiliaire comprenant des zones en forme de pétales, séparées les unes des autres par des lignes dites de fragilisation, ladite couche principale et ladite au moins une couche auxiliaire formant une pièce composite.
According to the invention, the flexible lid comprises:
  • a so-called main layer, formed of a composite material consisting of at least one fabric and at least one elastomer; and
  • at least one so-called auxiliary layer, formed of a composite material also consisting of at least one fabric and at least one elastomer, said auxiliary layer being secured to said composite layer on one of its faces, said layer auxiliary comprising petal-shaped zones, separated from each other by lines known as embrittlement, said main layer and said at least one auxiliary layer forming a composite part.

Ainsi, grâce à l'invention, le ou les tissus qui sont introduits dans l'élastomère pour former la pièce composite assurent la tenue mécanique de l'opercule flexible qui est, de plus, rendu hermétique grâce notamment à l'élastomère. De plus, ladite au moins une couche auxiliaire (comprenant des zones en forme de pétales définissant des lignes de fragilisation) permet de diriger une découpe précise de l'opercule flexible, le long desdites lignes de fragilisation, ce qui permet une ouverture facilitée. En outre, la pièce en matériau composite présente une grande souplesse (ou flexibilité), ce qui permet à l'opercule flexible de revenir, après une ouverture, vers une position proche de la position avant l'ouverture.Thus, thanks to the invention, the fabric or fabrics that are introduced into the elastomer to form the composite part ensure the mechanical strength of the flexible seal which is, moreover, made hermetic thanks in particular to the elastomer. In addition, said at least one auxiliary layer (comprising petal-shaped zones defining weakening lines) makes it possible to direct a precise cut of the flexible cap along said weakening lines, which allows an easier opening. In addition, the composite material part has great flexibility (or flexibility), which allows the flexible cover to return, after opening, to a position close to the position before opening.

On obtient ainsi un opercule flexible qui permet d'éviter la génération de débris (présentant un danger pour les équipements), tout en garantissant un effort modéré sur le radôme du missile, une faible masse et un coût de fabrication réduit.A flexible seal is thus obtained which makes it possible to avoid the generation of debris (presenting a danger for the equipment), while guaranteeing a moderate effort on the missile radome, a low mass and a reduced manufacturing cost.

De façon avantageuse, l'opercule flexible comporte :

  • deux couches auxiliaires agencées de part et d'autre de la couche principale. De préférence, les deux couches auxiliaires sont agencées, avec leurs zones en forme de pétales, symétriquement, par rapport à un plan sensiblement central de la couche principale ; et
  • un revêtement antifriction sur une face dite interne destinée à être placée vers l'intérieur du conteneur. Ce revêtement antifriction permet notamment de limiter les frottements lors du passage du missile.
Advantageously, the flexible lid comprises:
  • two auxiliary layers arranged on either side of the main layer. Preferably, the two auxiliary layers are arranged, with their petal-shaped zones, symmetrically, with respect to a substantially central plane of the main layer; and
  • an anti-friction coating on a so-called internal face intended to be placed towards the inside of the container. This anti-friction coating makes it possible to limit the friction during the passage of the missile.

En outre, de façon avantageuse, ladite au moins une couche auxiliaire est liée à ladite couche principale par des coutures, ce qui permet d'assurer une bonne tenue des zones en forme de pétales. Ces coutures participent également au maintien lors du procédé de fabrication de l'opercule flexible.In addition, advantageously, said at least one auxiliary layer is bonded to said main layer by seams, which ensures a good hold of the petal-shaped areas. These seams also participate in the maintenance during the manufacturing process of the flexible cover.

Avantageusement :

  • au moins certaines desdites coutures sont agencées le long des lignes de fragilisation, ce qui permet de renforcer le maintien le long des lignes de fragilisation ;
  • au moins certaines desdites coutures sont agencées transversalement auxdites lignes de fragilisation ;
  • des coutures sont prévues sur l'ensemble de la surface des zones en forme de pétales ;
  • les zones en forme de pétales sont agencées de sorte que les lignes de fragilisation sont orientées radialement par rapport au centre de l'opercule flexible.
Advantageously:
  • at least some of said seams are arranged along the lines of weakening, which makes it possible to reinforce the maintenance along the weakening lines;
  • at least some of said seams are arranged transversely to said weakening lines;
  • seams are provided over the entire surface of the petal-shaped areas;
  • the petal-shaped areas are arranged so that the weakening lines are oriented radially with respect to the center of the flexible cap.

Dans un mode de réalisation préféré :

  • le matériau composite formant ladite au moins une couche auxiliaire est identique au matériau composite formant la couche principale. Dans le cadre de la présente invention, le matériau composite formant la couche auxiliaire peut également être différent du matériau composite formant la couche principale ;
  • les lignes de fragilisation sont remplies d'élastomère.
In a preferred embodiment:
  • the composite material forming said at least one auxiliary layer is identical to the composite material forming the main layer. In the context of the present invention, the composite material forming the auxiliary layer may also be different from the composite material forming the main layer;
  • the weakening lines are filled with elastomer.

La présente invention concerne également un conteneur de missile, qui comporte au moins un opercule flexible tel que décrit ci-dessus.The present invention also relates to a missile container, which comprises at least one flexible cap as described above.

La présente invention concerne, en outre, un système d'arme qui comprend au moins un tel conteneur de missile.The present invention further relates to a weapon system that includes at least one such missile container.

Les figures annexées feront bien comprendre comment l'invention peut être réalisée. Sur ces figures, des références identiques désignent des éléments semblables.

  • La figure 1 est une coupe transversale schématique d'un mode de réalisation préféré d'un opercule flexible selon l'invention.
  • La figure 2 une coupe transversale schématique d'un autre mode de réalisation d'un opercule flexible selon l'invention.
  • Les figures 3 et 4 sont deux vues schématiques en plan, illustrant des modes de réalisation différents de lignes de fragilisation d'un opercule flexible.
  • La figure 5 est une vue en plan similaire à celle de la figure 3 avec un mode d'agencement particulier de coutures.
  • La figure 6 est une vue schématique, en perspective, de moyens de fixation d'un opercule flexible.
The appended figures will make it clear how the invention can be realized. In these figures, identical references designate similar elements.
  • The figure 1 is a schematic cross section of a preferred embodiment of a flexible cap according to the invention.
  • The figure 2 a schematic cross section of another embodiment of a flexible cap according to the invention.
  • The figures 3 and 4 are two schematic plan views, illustrating different embodiments of weakening lines of a flexible cover.
  • The figure 5 is a plan view similar to that of the figure 3 with a particular arrangement of seams.
  • The figure 6 is a schematic view, in perspective, of fixing means of a flexible cover.

L'opercule flexible 1 illustrant l'invention et représenté de façon schématique sur la figure 1 est destiné à être monté sur un conteneur de missile (non représenté).The flexible seal 1 illustrating the invention and shown schematically on the figure 1 is intended to be mounted on a missile container (not shown).

Ce conteneur de missile fait partie d'un système d'arme (également non représenté).This missile container is part of a weapon system (also not shown).

L'opercule flexible 1 a pour fonction de fermer hermétiquement le conteneur afin de protéger un missile installé dans le conteneur. L'opercule flexible doit pouvoir s'ouvrir afin de laisser passer le missile ou les gaz de propulsion lors d'un tir de ce dernier.The flexible lid 1 has the function of sealing the container to protect a missile installed in the container. The flexible cover must be able to open in order to let the missile or the propulsion gases pass during a firing of the latter.

Pour ce faire, l'opercule flexible 1 est configuré pour s'ouvrir sous une poussée. Dans le cadre de la présente invention, cette poussée peut être générée lors d'un tir par un contact de l'opercule flexible par le missile, ou bien par une surpression interne générée par des moyens dédiés ou par des gaz de propulsion du missile.To do this, the flexible seal 1 is configured to open under a thrust. In the context of the present invention, this thrust can be generated during a firing by a contact of the flexible cap by the missile, or by an internal overpressure generated by dedicated means or propulsion gases of the missile.

Selon l'invention, l'opercule flexible 1 comporte, comme représenté sur les figures 1 et 2 :

  • au moins une couche (ou peau) composite, dite couche principale 2. Cette couche principale 2 est formée complètement (sur toute sa surface) d'un matériau composite 9 constitué d'au moins un tissu et d'au moins un élastomère ; et
  • au moins une couche (ou peau) composite supplémentaire, dite couche auxiliaire 3, 4. Chacune desdites couches auxiliaires 3 et 4 est formée d'un matériau composite 10 constitué d'au moins un tissu et d'au moins un élastomère. Chaque couche auxiliaire 3, 4 est liée (ou solidarisée ou unie) à ladite couche composite 2 sur l'une des faces 2A, 2B de cette dernière.
According to the invention, the flexible seal 1 comprises, as shown in the figures 1 and 2 :
  • at least one layer (or skin) composite, called the main layer 2. This main layer 2 is formed completely (over its entire surface) of a composite material 9 consisting of at least one fabric and at least one elastomer; and
  • at least one additional composite layer (or skin), called auxiliary layer 3, 4. Each of said auxiliary layers 3 and 4 is formed of a composite material consisting of at least one fabric and at least one elastomer. Each auxiliary layer 3, 4 is bonded (or secured or plain) to said composite layer 2 on one of the faces 2A, 2B of the latter.

De plus, chaque couche auxiliaire 3, 4 comprend une pluralité de zones 6 (constituées de matériau composite 10) en forme de pétales, par exemple de forme triangulaire, qui sont séparées les unes des autres par des lignes de séparation, dites lignes de fragilisation 5.In addition, each auxiliary layer 3, 4 comprises a plurality of zones 6 (made of composite material 10) in the form of petals, for example of triangular shape, which are separated from each other by separation lines, called lines of weakness 5.

Ces lignes de fragilisation 5, exemptes de tissu, sont remplies d'élastomère (du matériau composite 10), comme représenté en noir sur les figures 1 et 2.These weakening lines 5, free of fabric, are filled with elastomer (of the composite material 10), as shown in black on the figures 1 and 2 .

Ladite couche principale 2 et ladite au moins une couche auxiliaire 3, 4 forment ainsi une pièce composite 8 monobloc. Dans un mode de réalisation préféré, le matériau composite 10 formant la ou les couches auxiliaires 3, 4 est identique au matériau composite 9 formant la couche principale 2.Said main layer 2 and said at least one auxiliary layer 3, 4 thus form a monobloc composite part 8. In a preferred embodiment, the composite material 10 forming the auxiliary layer or layers 3, 4 is identical to the composite material 9 forming the main layer 2.

La couche composite 2 et la ou les couches auxiliaires 3, 4 forment donc une pièce composite 8 flexible qui, grâce à sa flexibilité (ou souplesse), permet à l'opercule flexible 1 de revenir, après une ouverture, vers une position qui est proche de sa position avant l'ouverture, comme précisé ci-dessous.The composite layer 2 and the auxiliary layer or layers 3, 4 thus form a flexible composite part 8 which, thanks to its flexibility (or flexibility), allows the flexible cover 1 to return, after an opening, to a position which is close to its position before opening, as specified below.

L'agencement de la ou des couches auxiliaires 3, 4 avec des zones 6 en forme de pétales permet de diriger une découpe précise du matériau composite (élastomère/tissu), le long des lignes de fragilisation 5 formées entre ces zones 6.The arrangement of the auxiliary layer or layers 3, 4 with petal-shaped zones 6 makes it possible to direct a precise cut of the composite material (elastomer / fabric), along the weakening lines 5 formed between these zones 6.

En outre, le ou les tissus qui sont insérés dans l'élastomère pour former le matériau composite 9, 10 assurent la tenue mécanique de l'opercule flexible 1. Ce ou ces tissus sont réalisés, en particulier, à base de fibres de carbone ou de fibres de verre, ou bien de fibres textiles (polyester, polyamide,...).In addition, the fabric or fabrics that are inserted into the elastomer to form the composite material 9, 10 provide the mechanical strength of the flexible seal 1. This or these tissues are made, in particular, based on carbon or fiberglass, or textile fibers (polyester, polyamide, ...).

Le matériau composite 9, 10 permet également, grâce à l'élastomère, de rendre l'opercule flexible 1 hermétique. L'élastomère peut être réalisé en différentes matières. De préférence, cet élastomère est de type butyle, néoprène, silicone, ...The composite material 9, 10 also makes it possible, thanks to the elastomer, to make the flexible seal 1 hermetic. The elastomer can be made of different materials. Preferably, this elastomer is of butyl, neoprene, silicone, ...

Dans un premier mode de réalisation préféré, représenté sur la figure 1, l'opercule flexible 1 comporte deux couches auxiliaires 3 et 4 qui sont agencées de part et d'autre de la couche principale 2, respectivement sur les faces 2A et 2B de cette dernière.In a first preferred embodiment, shown in the figure 1 , the flexible cover 1 comprises two auxiliary layers 3 and 4 which are arranged on either side of the main layer 2, respectively on the faces 2A and 2B of the latter.

Les deux couches auxiliaires 3, 4 sont agencées, avec leurs zones 6 en forme de pétales, symétriquement, par rapport à un plan P sensiblement central de la couche principale 2 de forme générale plane. Ainsi, les zones de fragilisation sont situées à la même position de part et d'autre de la couche principale 2.The two auxiliary layers 3, 4 are arranged, with their petal-shaped zones 6, symmetrically, with respect to a substantially central plane P of the main layer 2 of generally planar shape. Thus, the weakening zones are located at the same position on either side of the main layer 2.

Par ailleurs, dans un second mode de réalisation simplifié, représenté sur la figure 2, une seule couche auxiliaire 3 (tissu/élastomère) est prévue sur la face 2A externe de la couche principale 2 (tissu/élastomère), c'est-à-dire sur la face 1A qui sera dirigée vers l'extérieur du conteneur dans la position montée de l'opercule flexible 1. Ceci permet de limiter les efforts nécessaires à l'ouverture.Moreover, in a second simplified embodiment, represented on the figure 2 a single auxiliary layer 3 (fabric / elastomer) is provided on the outer face 2A of the main layer 2 (fabric / elastomer), that is to say on the face 1A which will be directed towards the outside of the container in the mounted position of the flexible cover 1. This limits the effort required for opening.

Sur la figure 1, on a également représenté les faces internes 1 B et 2B de l'opercule flexible 1 et de la couche principale 2.On the figure 1 the inner faces 1 B and 2B of the flexible lid 1 and of the main layer 2 are also shown.

Par ailleurs, comme représenté sur les figures 1 et 2, l'opercule flexible 1 comporte, de plus, un revêtement antifriction 11 sur la face interne 1 B, qui est donc destinée à être placée vers l'intérieur du conteneur.Moreover, as represented on figures 1 and 2 , the flexible seal 1 further comprises an anti-friction coating 11 on the inner face 1 B, which is therefore intended to be placed towards the inside of the container.

Ce revêtement antifriction 11 permet, notamment, de limiter les frottements lors du passage du missile à travers l'opercule flexible 1.This anti-friction coating 11 makes it possible, in particular, to limit the friction during the passage of the missile through the flexible cover 1.

Le revêtement antifriction 11 est réalisé par exemple à partir d'un matériau métallique, ce qui permet, en plus de réduire le coefficient de friction, d'assurer une continuité électrique.The antifriction coating 11 is made for example from a metallic material, which allows, in addition to reducing the coefficient of friction, to provide electrical continuity.

Les zones 6 permettent donc de créer les lignes de fragilisation 5, ce qui facilite le déchirement du matériau composite 9 (tissu/élastomère) de la couche principale 2 suivant des directions précises. De préférence, les lignes de fragilisation 5 sont agencées radialement par rapport au centre 12 de l'opercule flexible 1, comme représenté sur les figures 3 à 5.The zones 6 thus make it possible to create the weakening lines 5, which facilitates the tearing of the composite material 9 (fabric / elastomer) of the main layer 2 in precise directions. Preferably, the weakening lines 5 are arranged radially with respect to the center 12 of the flexible cap 1, as shown in FIGS. Figures 3 to 5 .

En fonction de la taille du missile et de l'opercule, les lignes de fragilisation 5 sont plus ou moins nombreuses, par exemple deux lignes orientées selon les diagonales comme sur les exemples des figures 3 et 5 ou quatre lignes orientées selon les diagonales et les médiatrices des côtés comme représenté sur l'exemple de la figure 4.Depending on the size of the missile and the cover, the weakening lines 5 are more or less numerous, for example two lines oriented along the diagonals as on the examples of the figures 3 and 5 or four lines oriented along the diagonals and the mediators of the sides as shown in the example of the figure 4 .

D'autres formes peuvent bien entendu être prévues pour les lignes de fragilisation dans le cadre de la présente invention.Other shapes can of course be provided for the weakening lines in the context of the present invention.

Par ailleurs, dans un mode de réalisation préféré, notamment pour assurer une bonne tenue des pétales, chaque couche auxiliaire 3, 4 est liée à la couche principale 2 par des coutures 13 et 14 (figures 3 à 5). Ces coutures 13 et 14, par le maintien supplémentaire qu'elles fournissent, apportent une aide au déchirement de la couche principale 2 au niveau des lignes de fragilisation 5. Ces coutures 13 et 14 participent également au maintien du tissu des couches auxiliaires 3 et 4 sur la couche principale 2, lors du procédé de fabrication de l'opercule flexible. Elles sont réalisées de façon usuelle à partir de fils, par exemple en polyamide, qui correspondent, de préférence mais non exclusivement, aux fils des tissus utilisés pour former les matériaux composites 9 et 10.Moreover, in a preferred embodiment, in particular to ensure good resistance of the petals, each auxiliary layer 3, 4 is bonded to the main layer 2 by seams 13 and 14 ( Figures 3 to 5 ). These seams 13 and 14, by the additional maintenance they provide, provide an aid in tearing the main layer 2 at the weakening lines 5. These seams 13 and 14 also participate in maintaining the fabric of the auxiliary layers 3 and 4 on the main layer 2, during the manufacturing process of the flexible lid. They are conventionally made from yarns, for example made of polyamide, which correspond, preferably but not exclusively, to the yarns of the fabrics used to form the composite materials 9 and 10.

De préférence, certaines coutures 13 sont agencées dans les zones 6, parallèlement aux lignes de fragilisation 5, suivant des lignes de couture 15, ce qui permet de faciliter le déchirement le long des lignes de fragilisation 5.Preferably, some seams 13 are arranged in the zones 6, parallel to the weakening lines 5, along sewing lines 15, which facilitates tearing along the weakening lines 5.

En outre, dans un mode de réalisation particulier, représenté sur la figure 5, certaines coutures 14 sont agencées transversalement auxdites lignes de fragilisation 5.In addition, in a particular embodiment, shown in the figure 5 certain seams 14 are arranged transversely to said weakening lines 5.

Par ailleurs, dans un mode de réalisation particulier (non représenté), des coutures peuvent être prévues sur l'ensemble de la surface des zones 6 en forme de pétales. La répartition de ces coutures peut alors prendre différentes formes.Furthermore, in a particular embodiment (not shown), seams can be provided on the entire surface of the zones 6 shaped petals. The distribution of these seams can then take different forms.

L'opercule flexible 1, tel que décrit ci-dessus, présente notamment les avantages suivants :

  • une ouverture et une re-fermeture facilitées ;
  • un coût de fabrication réduit ;
  • une masse réduite ;
  • une absence de génération de débris.
The flexible lid 1, as described above, has the following advantages in particular:
  • easy opening and re-closing;
  • reduced manufacturing cost;
  • a reduced mass;
  • an absence of debris generation.

À titre d'illustration, l'opercule flexible 1 peut être conçu pour des conteneurs de dimensions variables, et en particulier :

  • pour un conteneur cylindrique, de diamètre compris entre 100 mm (millimètres) et 1000 mm ; ou
  • pour un conteneur parallélépipédique, de section comprise entre 100x100 mm et 1000x1000 mm.
By way of illustration, the flexible lid 1 can be designed for containers of variable dimensions, and in particular:
  • for a cylindrical container, having a diameter of between 100 mm (millimeters) and 1000 mm; or
  • for a parallelepipedic container, with a cross section between 100x100 mm and 1000x1000 mm.

De plus, l'opercule flexible 1 est conçu, de préférence, pour tenir des pressions comprises entre 1 et 5 bars, et pour s'ouvrir à partir de 5 bars.In addition, the flexible seal 1 is preferably designed to hold pressures between 1 and 5 bar, and to open from 5 bar.

On présente, à présent, de façon générale, un procédé de fabrication d'un opercule flexible 1 tel que décrit ci-dessus. Ce procédé de fabrication comprend, notamment, les étapes suivantes :

  • une étape de mise en place du tissu de la couche principale 2 à partir de fils imprégnés ;
  • une étape de mise en place du tissu de la ou des couches auxiliaires 3, 4, avec une fixation à l'aide de coutures 13, 14 sur le tissu de la couche principale 2 ; et
  • une étape d'assemblage des différentes couches 2, 3 et 4 de l'opercule flexible par vulcanisation.
It is now generally presented a method of manufacturing a flexible seal 1 as described above. This manufacturing process comprises, in particular, the following steps:
  • a step of placing the fabric of the main layer 2 from impregnated threads;
  • a step of placing the fabric of the one or more auxiliary layers 3, 4, with fastening with seams 13, 14 on the fabric of the main layer 2; and
  • a step of assembling the various layers 2, 3 and 4 of the flexible cover by vulcanization.

On précise également le fonctionnement de l'opercule flexible 1. Lors de la génération d'une poussée pour ouvrir l'opercule flexible 1 fermant le conteneur, en vue d'un tir d'un missile installé dans le conteneur, à partir d'une certaine pression (par exemple 5 bars), l'opercule flexible 1 (et plus particulièrement la pièce composite 8 et le cas échéant également le revêtement antifriction 11) se déchire selon les lignes de fragilisation 5, et les pétales 6 flexibles ainsi libérées se courbent vers l'extérieur pour ouvrir l'opercule flexible 1 et libérer le passage pour le missile. Après la sortie du missile du conteneur, les pétales 6 flexibles reviennent, grâce à leur flexibilité, vers une position initiale pour que l'opercule flexible 1 soit proche de sa position avant l'ouverture afin de permettre la fermeture de la porte de l'alvéole.The operation of the flexible lid 1 is also specified. During the generation of a thrust for opening the flexible lid 1 closing the container, for the purpose of firing a missile installed in the container, from a certain pressure (for example 5 bars), the flexible seal 1 (and more particularly the composite part 8 and, where appropriate, also the anti-friction coating 11) tears along the weakening lines 5, and the flexible petals 6 thus released curl outwardly to open the flexible seal 1 and release the passage for the missile. After the exit of the missile from the container, the flexible petals 6 return, thanks to their flexibility, to an initial position so that the flexible cover 1 is close to its position before opening to allow the closing of the door of the cell.

Comme représenté sur la figure 6, plusieurs éléments 16 (ou brides), par exemple en acier inoxydable, en particulier quatre éléments 16 en forme d'équerre, permettent de brider l'opercule flexible 1 sur le conteneur (non représenté).As shown on the figure 6 , several elements 16 (or flanges), for example stainless steel, in particular four elements 16 in the form of a square, allow to clamp the flexible lid 1 on the container (not shown).

Une application possible de l'invention concerne un conteneur d'un lanceur de missiles, qui est embarqué sur un navire. Un tel conteneur comporte généralement une série d'alvéoles, chaque alvéole étant destinée à recevoir un missile placé dans son conteneur. La partie supérieure d'une alvéole débouche au niveau du pont du navire et est fermée, en dehors des phases de lancement, par une porte. La partie inférieure d'une alvéole comporte une ouverture de communication débouchant dans une chambre destinée à recevoir les gaz émis lors du lancement d'un missile. Les parties supérieure et inférieure de chaque conteneur sont obturées de manière étanche, par un couvercle muni d'un opercule flexible haut, tel que l'opercule flexible 1 précisé ci-dessus, et par un fond muni, par exemple, également d'un opercule flexible bas tel que l'opercule flexible 1. Le volume intérieur du conteneur est, en général, rempli d'un gaz inerte en surpression par rapport à l'atmosphère. Lors du lancement du missile, une porte de l'alvéole est ouverte, et le missile est mis à feu. Les gaz de propulsion font alors augmenter la pression et la température de manière importante à l'intérieur du conteneur, ce qui perfore l'opercule flexible haut du conteneur (et le cas échéant ouvre l'opercule flexible bas). Après le tir, le ou les opercules flexibles reviennent à peu près dans leur position initiale et la porte de l'alvéole est refermée.One possible application of the invention relates to a container of a missile launcher, which is embarked on a ship. Such a container generally comprises a series of cells, each cell being intended to receive a missile placed in its container. The upper part of a cell opens at the deck of the ship and is closed, outside the launching phases, by a door. The lower part of a cell has a communication opening opening into a chamber for receiving the gases emitted during the launch of a missile. The upper and lower parts of each container are closed in a sealed manner, by a lid provided with a high flexible lid, such as the flexible lid 1 specified above, and by a bottom provided, for example, also with a low flexible lid such as the flexible lid 1. The inner volume of the container is, in general, filled with an inert gas at overpressure relative to the atmosphere. When launching the missile, a cell door is opened, and the missile is fired. The propellant gases then increase the pressure and the temperature significantly inside the container, which perforates the top flexible lid of the container (and where appropriate opens the flexible lid down). After firing, the flexible cover (s) return to approximately their initial position and the cell door is closed again.

Claims (12)

Opercule flexible, destiné à être monté sur un conteneur de missile et apte à s'ouvrir sous une poussée, ledit opercule comprenant : - une couche (2) dite principale, formée d'un matériau composite (9) constitué d'au moins un tissu et d'au moins un élastomère ; et - au moins une couche (3, 4) dite auxiliaire, formée d'un matériau composite (10) constitué également d'au moins un tissu et d'au moins un élastomère, ladite couche auxiliaire (3, 4) étant solidarisée de ladite couche composite (2) sur l'une des faces (2A, 2B) de cette dernière, ladite couche auxiliaire (3, 4) comprenant des zones (6) en forme de pétales, séparées les unes des autres par des lignes (5) dites de fragilisation, ladite couche principale (2) et ladite au moins une couche auxiliaire (3, 4) formant une pièce composite (8), ladite au moins une couche auxiliaire (3, 4) est liée à ladite couche principale (2) par des coutures (13, 14). Flexible lid, intended to be mounted on a missile container and able to open under a thrust, said lid comprising: a so-called main layer (2) formed of a composite material (9) consisting of at least one fabric and at least one elastomer; and at least one so-called auxiliary layer (3, 4) formed of a composite material (10) also constituted of at least one fabric and at least one elastomer, said auxiliary layer (3, 4) being integral with said composite layer (2) on one of the faces (2A, 2B) thereof, said auxiliary layer (3, 4) comprising petal-shaped zones (6) separated from each other by lines (5) said embrittlement, said main layer (2) and said at least one auxiliary layer (3, 4) forming a composite part (8), said at least one auxiliary layer (3, 4) is bonded to said main layer (2) by seams (13, 14). Opercule flexible selon la revendication 1,
caractérisé en ce qu'il comporte deux couches auxiliaires (3, 4) agencées de part et d'autre de la couche principale (2).Flexible lid according to claim 1,
characterized in that it comprises two auxiliary layers (3, 4) arranged on either side of the main layer (2). Opercule flexible selon la revendication 2,
caractérisé en ce que les deux couches auxiliaires (3, 4) sont agencées, avec leurs zones (6) en forme de pétales, symétriquement, par rapport à un plan (P) sensiblement central de la couche principale (2).Flexible lid according to claim 2,
characterized in that the two auxiliary layers (3, 4) are arranged with their petal-shaped zones (6) symmetrically with respect to a substantially central plane (P) of the main layer (2). Opercule flexible selon l'une quelconque des revendications précédentes,
caractérisé en ce qu'au moins certaines (13) desdites coutures sont agencées le long des lignes de fragilisation (5).Flexible lid according to one of the preceding claims,
characterized in that at least some of said seams are arranged along the weakening lines (5). Opercule flexible selon les revendications 1 et 4,
caractérisé en ce qu'au moins certaines (14) desdites coutures sont agencées transversalement auxdites lignes de fragilisation (5).Flexible lid according to claims 1 and 4,
characterized in that at least some of said seams (14) are arranged transversely to said weakening lines (5). Opercule flexible selon l'une quelconque des revendications précédentes,
caractérisé en ce que des coutures sont prévues sur l'ensemble de la surface des zones (6) en forme de pétales.Flexible lid according to one of the preceding claims,
characterized in that seams are provided over the entire surface of the petal-shaped areas (6). Opercule flexible selon l'une quelconque des revendications précédentes,
caractérisé en ce que les zones (6) en forme de pétales sont agencées de sorte que les lignes de fragilisation (5) sont orientées radialement par rapport au centre (12) de l'opercule flexible (1).Flexible lid according to one of the preceding claims,
characterized in that the petal-shaped areas (6) are arranged such that the weakening lines (5) are oriented radially with respect to the center (12) of the flexible cover (1). Opercule flexible selon l'une quelconque des revendications précédentes,
caractérisé en ce que le matériau composite (10) formant ladite au moins une couche auxiliaire (3, 4) est identique au matériau composite (9) formant la couche principale (2).Flexible lid according to one of the preceding claims,
characterized in that the composite material (10) forming said at least one auxiliary layer (3, 4) is identical to the composite material (9) forming the main layer (2). Opercule flexible selon l'une quelconque des revendications précédentes,
caractérisé en ce que les lignes de fragilisation (5) sont remplies d'élastomère.Flexible lid according to one of the preceding claims,
characterized in that the weakening lines (5) are filled with elastomer. Opercule flexible selon l'une quelconque des revendications précédentes,
caractérisé en ce qu'il comporte un revêtement antifriction (11) sur une face dite interne (1A) destinée à être placée vers l'intérieur du conteneur.Flexible lid according to one of the preceding claims,
characterized in that it comprises an anti-friction coating (11) on a so-called internal face (1A) intended to be placed towards the inside of the container. Conteneur de missile,
caractérisé en ce qu'il comporte au moins un opercule flexible (1) selon l'une quelconque des revendications 1 à 10.Missile container,
characterized in that it comprises at least one flexible cap (1) according to any one of claims 1 to 10. Système d'arme,
caractérisé en ce qu'il comporte au moins un conteneur de missile selon la revendication 11.Weapon system,
characterized in that it comprises at least one missile container according to claim 11.
EP17290081.3A 2016-07-01 2017-06-20 Flexible seal for missile container Active EP3264021B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1601043A FR3053455B1 (en) 2016-07-01 2016-07-01 FLEXIBLE OPENER FOR MISSILE CONTAINER

Publications (2)

Publication Number Publication Date
EP3264021A1 true EP3264021A1 (en) 2018-01-03
EP3264021B1 EP3264021B1 (en) 2020-06-17

Family

ID=57396500

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17290081.3A Active EP3264021B1 (en) 2016-07-01 2017-06-20 Flexible seal for missile container

Country Status (5)

Country Link
US (1) US10845159B2 (en)
EP (1) EP3264021B1 (en)
ES (1) ES2805656T3 (en)
FR (1) FR3053455B1 (en)
WO (1) WO2018002454A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113819802A (en) * 2021-09-06 2021-12-21 南京航空航天大学 Composite material frangible cover with automatic reset function and preparation method thereof

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112066797B (en) * 2020-08-31 2022-11-25 湖北三江航天万峰科技发展有限公司 Frangible cover and forming method thereof

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1263011A (en) * 1960-07-21 1961-06-05 Dunlop Rubber Co Protective casing for projectiles
US4498368A (en) * 1983-10-06 1985-02-12 The United States Of America As Representedby The Secretary Of The Navy Frangible fly through diaphragm for missile launch canister
KR20120010589A (en) * 2010-07-19 2012-02-06 국방과학연구소 Front cover for launching tube of missile and method for fabricating the same

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5198280A (en) * 1990-10-25 1993-03-30 Allied-Signal Inc. Three dimensional fiber structures having improved penetration resistance
US5677029A (en) * 1990-11-19 1997-10-14 Alliedsignal Inc. Ballistic resistant fabric articles
US7520204B2 (en) * 2004-10-28 2009-04-21 Lockheed Martin Corporation Article comprising a composite cover
DE602007012119D1 (en) * 2007-11-14 2011-03-03 Saab Ab Protective cover for a launch tube
FR2926360B1 (en) * 2008-01-11 2012-10-19 Dcns DEFORMABLE REAR OPERATOR FOR MISSILE CONTAINER, COMPRISING A FRONT SUPPORT FRAME
US8883661B2 (en) * 2011-11-18 2014-11-11 Pro-Systems S.P.A. Composite material for ballistic protection and relative method of preparation

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1263011A (en) * 1960-07-21 1961-06-05 Dunlop Rubber Co Protective casing for projectiles
US4498368A (en) * 1983-10-06 1985-02-12 The United States Of America As Representedby The Secretary Of The Navy Frangible fly through diaphragm for missile launch canister
KR20120010589A (en) * 2010-07-19 2012-02-06 국방과학연구소 Front cover for launching tube of missile and method for fabricating the same

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113819802A (en) * 2021-09-06 2021-12-21 南京航空航天大学 Composite material frangible cover with automatic reset function and preparation method thereof

Also Published As

Publication number Publication date
US20190323799A1 (en) 2019-10-24
ES2805656T3 (en) 2021-02-15
FR3053455A1 (en) 2018-01-05
US10845159B2 (en) 2020-11-24
FR3053455B1 (en) 2019-04-19
WO2018002454A1 (en) 2018-01-04
EP3264021B1 (en) 2020-06-17

Similar Documents

Publication Publication Date Title
EP3264021B1 (en) Flexible seal for missile container
EP3128281B1 (en) Flexible seal for missile container
FR2757248A1 (en) TANK FOR PRESSURIZED FLUID, ESPECIALLY FOR LIQUEFIED GAS
EP0161450B1 (en) Assembly of at least one stack of cells or batteries of cells
EP2229573B1 (en) Missile container bottom system
EP2078918B1 (en) Container for multiple missiles and versatile launcher
FR3058966A1 (en) SAFETY DEVICE FOR VEHICLE
FR2759353A1 (en) Anti-explosion safety container
FR2759354A1 (en) Anti-explosion safety container
EP1152859B1 (en) Controlled rupture device for a structure operating in traction and equipment using same
EP2078920B1 (en) Deformable bottom closure for a missile container
EP2078919B1 (en) Deformable rearward closure with elastic strips for a missile container
FR2463382A1 (en) CONTACT HEAD FOR PROJECTILES DRAWN BY ELECTRICALLY CONTROLLED LAUNCHES
FR2466627A1 (en) Solid-fuelled rocket anti-popping outlet - has constant-section passage between space round fuel and combustion chamber
FR3085017A1 (en) Battery box
EP3880447B1 (en) Method for manufacturing a part made from composite material
FR2703444A1 (en) Armor for the fight against a perforating kinetic projectile.
WO2021144531A1 (en) Double access hatch for a liquefied-gas transport tank
FR3129444A1 (en) Composite bellows suspension spring
FR2856138A1 (en) ARMORED PROTECTION DEVICE.
FR2607240A1 (en) Protection device for transporting or storing explosive charges
FR3117880A1 (en) Hot melt cap
FR3135507A1 (en) Gas storage bottle and method of manufacturing such a bottle
FR3131361A1 (en) Tank comprising a sealed membrane having crossings
FR3001079A1 (en) PACKAGING FOR THE TRANSPORT AND / OR STORAGE OF RADIOACTIVE MATERIALS COMPRISING AN IMPROVED FIRE PROTECTION

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

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

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

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

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

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20180530

RBV Designated contracting states (corrected)

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

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20200217

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

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: 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: 602017018265

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1281824

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200715

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

Effective date: 20200617

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: 20200617

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: 20200918

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: 20200917

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: 20200617

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20200617

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

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: 20200617

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: 20200617

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: 20200617

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: 20200917

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1281824

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200617

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: 20200617

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: 20200617

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

Ref country code: CZ

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

Effective date: 20200617

Ref country code: RO

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

Effective date: 20200617

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: 20201019

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: 20200617

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: 20200617

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: 20200617

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: FG2A

Ref document number: 2805656

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20210215

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

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: 20200617

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: 20200617

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: 20201017

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602017018265

Country of ref document: DE

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

Ref country code: LU

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

Effective date: 20200620

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: 20200617

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20200630

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: LI

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

Effective date: 20200630

Ref country code: CH

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

Effective date: 20200630

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: 20200617

Ref country code: IE

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

Effective date: 20200620

26N No opposition filed

Effective date: 20210318

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: 20200630

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: 20200617

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: 20200617

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: 20200617

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: 20200617

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

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: 20200617

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

Ref country code: IT

Payment date: 20230609

Year of fee payment: 7

Ref country code: FR

Payment date: 20230622

Year of fee payment: 7

Ref country code: DE

Payment date: 20230613

Year of fee payment: 7

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

Effective date: 20230703

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

Ref country code: GB

Payment date: 20230620

Year of fee payment: 7

Ref country code: ES

Payment date: 20230706

Year of fee payment: 7