EP2078920A2 - Deformable bottom closure for a missile container - Google Patents

Deformable bottom closure for a missile container Download PDF

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Publication number
EP2078920A2
EP2078920A2 EP09150245A EP09150245A EP2078920A2 EP 2078920 A2 EP2078920 A2 EP 2078920A2 EP 09150245 A EP09150245 A EP 09150245A EP 09150245 A EP09150245 A EP 09150245A EP 2078920 A2 EP2078920 A2 EP 2078920A2
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EP
European Patent Office
Prior art keywords
blade
downstream
blades
upstream
container
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
EP09150245A
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German (de)
French (fr)
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EP2078920A3 (en
EP2078920B1 (en
Inventor
Pierre Jacques Truyman
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.)
Naval Group SA
Original Assignee
DCNS SA
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Priority to PL09150245T priority Critical patent/PL2078920T3/en
Publication of EP2078920A2 publication Critical patent/EP2078920A2/en
Publication of EP2078920A3 publication Critical patent/EP2078920A3/en
Application granted granted Critical
Publication of EP2078920B1 publication Critical patent/EP2078920B1/en
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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
    • F41F3/0413—Means for exhaust gas disposal, e.g. exhaust deflectors, gas evacuation systems
    • 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
    • F41F3/042—Rocket or torpedo launchers for rockets the launching apparatus being used also as a transport container for the rocket

Definitions

  • the present invention relates to a rear cover, also called downstream cap, equipping the bottom of a missile container. More particularly, the invention relates to a downstream cap of the deformable type.
  • a missile launcher is known adapted to be embarked on a vessel comprising a series of cells, each cell being intended to receive a munition consisting of a missile placed in a container.
  • the upper part of a cell opens at the deck of the ship and is closed, outside the launch phases, by a door.
  • the lower part of a cell has a communication opening opening into a plenum chamber or plenum for receiving the gases emitted during the launch of a missile.
  • the plenum common to the various cells, is equipped with a gas extraction chimney.
  • a munition is formed by a missile placed inside a container.
  • the upper and lower parts of the container are sealed, respectively by a lid provided with an upstream cap and a bottom provided with a downstream cap.
  • the internal volume of the container is generally filled with an inert gas at overpressure relative to the atmosphere (typically 1.5 bar).
  • the lower part of the container is extended by an adapter intended to cooperate with the communication opening between a cell and the plenum.
  • the ammunition is inserted from above into a pitcher cell, the bottom of the container being then in fluid communication with the plenum by means of the adapter.
  • the door of the cell being opened beforehand, the missile is fired.
  • the propellant gases then increase the pressure and the temperature significantly inside the container, which perforates the upstream lid of the container and opens the downstream cap.
  • the communication of the interior of the container with the plenum via the adapter allows the evacuation of the propulsion gases in the plenum, then their extraction via the chimney. After firing, the door of the cell is closed.
  • a deformable cover that opens when a missile is launched and closes afterwards.
  • This deformable seal comprises, superimposed axially along a principal axis of symmetry, which coincides with the axis of the container, a gate, upstream sealing membranes, a stack of resilient blades and tear-off membranes .
  • the resilient blades are preferably rectangular and are held on their periphery between upstream and downstream support frames.
  • Each elastic blade consists of several triangular petals made in a flexible and elastic thin metal plate. In their rest position, the petals are contiguous and thus obstruct the opening of the lid of the bottom of the container.
  • the grid also forms an abutment having the advantage of preventing the petals from deforming towards the interior of the container, when the plenum is overpressurized due to the propulsion gases of a neighboring missile being launched.
  • the invention therefore aims to provide a deformable seal having a better seal after use.
  • the subject of the invention is a deformable type cover, intended to equip the bottom of a missile container and able to open under the thrust of the propulsion gases of a missile contained in the container and to closing after ejection of the missile, the cover comprising a grid and a stack of resilient blades, sandwiched between at least one thermal protection membrane and an upstream and downstream sealing membrane, and held between an upstream support frame and a frame downstream support.
  • the cover comprises at least one slip intermediate means disposed between two successive blades of the stack.
  • the vertical missile launcher 1 comprises several cells 2 arranged vertically in the hull 3 of a ship.
  • a cell 2 is a structure consisting of a wire mesh for receiving a munition formed of a container containing a missile.
  • the upper part of the cell 2 is located at the deck 4 of the ship and is closed by a door 5, mounted on the bridge 4, which are open when fired and then closed again.
  • the lower part of the cell 2 has an opening 10 communicating with a plenum 11.
  • the plenum 11 is common to the various cells 2 of the launcher and allows the evacuation of the propulsion gases through a chimney 12, extending vertically between the two rows of cells 2.
  • the chimney 12 opens to the upper level of the launcher, that is to say here at the bridge 4.
  • a vertical missile launcher has cells capable of receiving a munition consisting of a container 15 in which is disposed a missile 16 of large diameter. In the inserted position in the cell 2, the axis A of the container 15 coincides with the axis of the cell.
  • the container 15 has a side wall 20, an upper end wall or cover 21 and a bottom end wall or bottom 22.
  • the cover 21 is provided with an upstream cover 23.
  • the bottom 22 is provided with a downstream cap 56 which will be described in detail below.
  • the bottom 22 comprises an adapter 25 adapted to be inserted into the opening 10 of the plenum 11 during the loading of the munition so that the gases leaving the container 15 during the launch of the missile 16 are guided in the plenum 11 .
  • the improved deformable downstream cap 56 comprises, superimposed along an axis of symmetry C, from the upstream (inside the container) downstream (outside the container), maintained between an upstream support frame 61 and a downstream support frame 64, a grid 62; an upstream thermal protection membrane 70; an upstream sealing membrane 71 for example of aluminum; a stack of resilient blades 63; a downstream sealing membrane 73, for example made of aluminum; and, a downstream thermal protection membrane 72.
  • Each elastic blade 63 is free-form, but for practical reasons, it is preferably rectangular (cf. Figure 2 ) and the stack of elastic blades is maintained by its peripheral edge between the upstream and downstream frames 61 and 64 rectangular.
  • Each elastic blade 63 consists of four petals of triangular shape 65. Each petal 65 corresponds substantially to a portion of the blade 63 divided along its two diagonals. The edges of two petals 65 facing each other provide a space 66 in the form of a cross whose total surface is much smaller than the surface of the orifice 81 of the lid 56, so that when the petals 65 are adjacent, it can be considered that the operculum 56 closes the bottom of the container it equips.
  • the deformable downstream membrane 56 comprises a stack of metal resilient strips 63 separated from each other by spacer sheets 67 made of non-metallic material resistant to temperature, adapted to facilitate the sliding of the elastic strips one on the other.
  • This intermediate sheet 67 is preferably made of a thermal insulating material such as silicone, or a mat, for example glass fibers.
  • the various intermediate membranes 70, 71, 72 and 73 are in one piece. They may be provided with diagonal lines of lesser resistance corresponding to the subdivision of the blades 63 into petals 65. Thus, under the effect of the propulsion gases, these intermediate membranes 70 to 73 tear cleanly along the lines of least resistance.
  • the lid 56 will now be described when it equips the bottom of the container 15 of the Figure 1 , the axis C of the seal then coinciding with the axis A of the container 15.
  • the door 5 of the cell 2 is open.
  • the missile 16 is then fired.
  • the propellant gases then increase the pressure and the temperature significantly inside the container 15.
  • the upstream cover 54 is perforated and the downstream cover 56 opens allowing the departure of the missile and the evacuation of the gases.
  • the opening of the downstream cap is effected by the action of the pressure applied to the upper or upstream surface of a blade 63 so that it deforms and deviates from its rest position, this deformation of the petals. accompanying tearing of the sealing membranes and thermal protection 70 to 73.
  • a petal 65 is deformed around an inner edge 80 of the downstream frame 64. Due to the tearing of the membranes 70-73 and the displacement of the various petals 65 of the 63 blades apart from each other, it creates a passage providing communication between the interior of the container 15 and the plenum 11 via an adapter 25. The latter serves to receive the gas passing through the bottom 22 of the container 15 to guide them through the entrance opening 10 of the plenum 11.
  • the pressure inside the container 15 decreases. Since the petals 65 retain their mechanical properties of elasticity due to the interlayers, they effectively return to a deformed position in the rest position, closing the cover 56.
  • the gate 62 forms a stop ensuring that the petals 65 easily find their rest position in which they are in a plane transverse to the axis C of the lid and for which the space 66 is the weakest.
  • the gate 62 also allows the petals 65 do not fold towards the inside of the tube 51, when the adapter 25 is overpressure due to the propulsion gases of a missile launched from a neighboring tube.
  • the inner edge 80 of the downstream frame 64 can be extended downstream and axially present a profile adapted to form a stop for the petals.
  • the downstream frame 64 is of rectangular shape, in the radial plane transverse to the main axis C and extends axially along the axis C over a height H greater than a transverse dimension D of a petal 65, corresponding approximately at half the width of the orifice 81 of the lid 56.
  • the edge profile 80 has a convex upstream portion 90, followed by a concave downstream portion 91.
  • the downstream portion 91 could be rectilinear.
  • the upstream and downstream portions 90, 91 connect to each other tangentially.
  • the concavity of the upstream portion 90 is understood in that the center of curvature C90 of the edge profile 90 at any point P90 of this profile is located, in projection in a radial plane, outside the central orifice. 81.
  • the convexity of the downstream portion 91 means that the center of curvature C91 of the edge profile 91 at any point P91 of this profile lies, in projection in a radial plane, at Inside the central orifice 81.
  • the convexity of the upstream portion 90 is oriented towards the axis C of the cap 56 and the concavity of the downstream portion 91 is oriented towards the axis C of the cap 56.
  • the curvature at each point P of the edge profile 80 is determined in such a way that the area of the petal 65 bearing at this point P of the profile has a limited and controlled maximum deformation.
  • the downstream portion 91 of the edge 80 is concave, or at least straight, has the following advantage. It is possible that the tip 96 of the triangular petal 65, which is placed near the combustion flame produced by the missile, is plasticized. However, in the maximum deformation position, the tip 96 is supported on the concave or rectilinear downstream portion 91 which then gives it a shape having a curvature oriented towards the axis C. Thus, the plasticized tip 96 is bent towards the gate 62 , so that it is applied against it when the petal returns to the rest position. This ensures that the space 66 between the petals 65 is minimal after use.
  • edge 80 of the downstream frame 64 is made of a material such as silicone which is both a thermal insulator and has a mechanical strength for the support of the petals.
  • the lid 156 further comprises a stack of resilient blades 163a, 163b, 163c of thickness ea, eb, ec variable. More specifically, the elastic blades placed upstream of the stack have a thickness greater than those of the elastic blades placed downstream of the stack. On the Figure 5 , the thicknesses ea, eb and ec of three blades 163a, 163b and 163c schematically shown decreasing progressively from upstream to downstream of the stack.
  • each blade 163a, 163b or 163c is chosen so that, when it is under stress, bearing against an inner edge 80 of the downstream support frame 64, its upstream face, facing the combustion flame, undergoes an elongation that remains compatible with the field of elasticity of the constituent metal of the blade.
  • the edge 80 of the downstream frame 64 has a rounded portion 90 having a center O of curvature.
  • the thickness e of the blade 63 at a point is chosen to be less than a maximum thickness em which is greater than the radius of curvature RM of the neutral fiber f at this point of the blade 63 deformed around this rounded portion is high.
  • the thickness of the blade is constant and is chosen as the smallest thickness em at each point of the blade 63. The skilled person knows to determine the appropriate thicknesses.
  • the lid closes until a sufficient partial closure. Indeed, beyond this threshold sealing, the pressure drop of the shock wave at the crossing of the partially open lid is such that it generates a force on the blades sufficient to press them against the gate and close the lid completely.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Closures For Containers (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Table Devices Or Equipment (AREA)
  • Details Of Aerials (AREA)
  • Bag Frames (AREA)
  • Packages (AREA)
  • Wind Motors (AREA)

Abstract

The closure has elastic blades (63) whose grid (62) and stack are locked between a thermal protection membrane and an upstream and downstream sealed membrane, and are maintained between an upstream support frame (61) and a downstream support frame (64). Interposed sliding unit (67) is arranged between the two successive blades of the stack. Each blade is separated from an adjacent blade in a pile by the sliding unit.

Description

La présente invention concerne un opercule arrière, dit aussi opercule aval, équipant le fond d'un conteneur de missile. Plus particulièrement, l'invention concerne un opercule aval du type déformable.The present invention relates to a rear cover, also called downstream cap, equipping the bottom of a missile container. More particularly, the invention relates to a downstream cap of the deformable type.

On connaît un lanceur de missiles adapté pour être embarqué sur un navire comportant une série d'alvéoles, chaque alvéole étant destinée à recevoir une munition constituée d'un missile placé dans un conteneur. La partie supérieure d'une alvéole débouche au niveau du pont du navire et est fermée, hors des phases de lancement, par une porte. La partie inférieure d'une alvéole comporte une ouverture de communication débouchant dans une chambre de tranquillisation ou plénum destiné à recevoir les gaz émis lors du lancement d'un missile. Le plénum, commun aux différentes alvéoles, est équipé d'une cheminée d'extraction des gaz.A missile launcher is known adapted to be embarked on a vessel comprising a series of cells, each cell being intended to receive a munition consisting of a missile placed in a container. The upper part of a cell opens at the deck of the ship and is closed, outside the launch phases, by a door. The lower part of a cell has a communication opening opening into a plenum chamber or plenum for receiving the gases emitted during the launch of a missile. The plenum, common to the various cells, is equipped with a gas extraction chimney.

Une munition est formée par un missile placé à l'intérieur d'un conteneur. Les parties supérieure et inférieure du conteneur sont obturées de manière étanche, respectivement par un couvercle muni d'un opercule amont et par un fond muni d'un opercule aval. Le volume intérieur du conteneur est en général rempli d'un gaz inerte en surpression par rapport à l'atmosphère (typiquement 1,5 bars). La partie inférieure du conteneur est prolongée par un adaptateur destiné à coopérer avec l'ouverture de communication entre une alvéole et le plénum. La munition est insérée par le haut dans une alvéole du lanceur, le fond du conteneur étant alors mis en communication fluidique avec le plénum au moyen de l'adaptateur.A munition is formed by a missile placed inside a container. The upper and lower parts of the container are sealed, respectively by a lid provided with an upstream cap and a bottom provided with a downstream cap. The internal volume of the container is generally filled with an inert gas at overpressure relative to the atmosphere (typically 1.5 bar). The lower part of the container is extended by an adapter intended to cooperate with the communication opening between a cell and the plenum. The ammunition is inserted from above into a pitcher cell, the bottom of the container being then in fluid communication with the plenum by means of the adapter.

Lors du lancement du missile, la porte de l'alvéole étant préalablement ouverte, 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 amont du conteneur et ouvre l'opercule aval. La mise en communication de l'intérieur du conteneur avec le plénum via l'adaptateur permet l'évacuation des gaz de propulsion dans le plénum, puis leur extraction via la cheminée. Après le tir, la porte de l'alvéole est refermée.When launching the missile, the door of the cell being opened beforehand, the missile is fired. The propellant gases then increase the pressure and the temperature significantly inside the container, which perforates the upstream lid of the container and opens the downstream cap. The communication of the interior of the container with the plenum via the adapter allows the evacuation of the propulsion gases in the plenum, then their extraction via the chimney. After firing, the door of the cell is closed.

Lorsque l'opercule aval s'ouvre, les gaz de propulsion qui sont chauds et pour lesquels la vitesse du son est de l'ordre de 1000 m/s, rencontrent des gaz présents dans le plénum qui sont froids et pour lesquels la vitesse du son est de l'ordre de 300 m/s. II en résulte un régime d'ondes de choc, avec en particulier des variations de pression importantes à l'interface entre les masses de gaz chaud et froid. Ce phénomène dure entre 100 et 150 ms, le temps que les gaz froids se propagent hors du plénum par la cheminée d'extraction, et se traduit par une forte augmentation de la température et de la pression dans le plénum, lors de la mise à feu d'un missile.When the downstream cap opens, the propulsion gases that are hot and for which the speed of sound is of the order of 1000 m / s, encounter gases in the plenum that are cold and for which the speed of the its is of the order of 300 m / s. This results in a shock wave regime, in particular with significant pressure variations at the interface between hot and cold gas masses. This phenomenon lasts between 100 and 150 ms, the time that the cold gases propagate out of the plenum by the extraction chimney, and results in a strong increase of the temperature and the pressure in the plenum, when the fire of a missile.

Lorsqu'un missile a été tiré et que le conteneur qui le contenait est vide, le tir d'un missile contenu dans un conteneur voisin engendre une production de gaz à haute pression et haute température qui pourrait pénétrer depuis le plénum dans le conteneur vide et, de ce fait, détériorer la porte de l'alvéole correspondante. Afin d'éviter qu'il en soit ainsi, il est nécessaire que l'opercule aval du conteneur vide se referme pour empêcher l'onde de choc et les gaz de propulsion présents dans le plénum de pénétrer à l'intérieur de ce conteneur vide.When a missile has been fired and the container containing it is empty, the firing of a missile contained in a nearby container results in the production of high-pressure, high-temperature gas that could enter from the plenum into the empty container. thus, to deteriorate the door of the corresponding cell. In order to prevent this from occurring, it is necessary that the downstream lid of the empty container closes to prevent the shock wave and the propellant gases present in the plenum from entering this empty container. .

Pour cela, on a proposé, notamment dans FR 2 620 808 , un opercule déformable qui s'ouvre au moment du lancement d'un missile et se referme après. Cet opercule déformable comporte, superposés axialement le long d'un axe principal de symétrie, qui coïncide avec l'axe du conteneur, une grille, des membranes d'étanchéité amont déchirables, un empilement de lames élastiques et des membranes d'étanchéité aval déchirables. Les lames élastiques sont de préférence rectangulaires et sont maintenues sur leur périphérie entre des cadres de support amont et aval. Chaque lame élastique se compose de plusieurs pétales triangulaires réalisés dans une plaque métallique fine souple et élastique. Dans leur position de repos, les pétales sont jointifs et ainsi obstruent l'orifice de l'opercule du fond du conteneur.For this, it has been proposed, particularly in FR 2 620 808 , a deformable cover that opens when a missile is launched and closes afterwards. This deformable seal comprises, superimposed axially along a principal axis of symmetry, which coincides with the axis of the container, a gate, upstream sealing membranes, a stack of resilient blades and tear-off membranes . The resilient blades are preferably rectangular and are held on their periphery between upstream and downstream support frames. Each elastic blade consists of several triangular petals made in a flexible and elastic thin metal plate. In their rest position, the petals are contiguous and thus obstruct the opening of the lid of the bottom of the container.

Lorsque les gaz de propulsion sont éjectés du missile, une surpression déchire les membranes d'étanchéité et déforme les pétales par flexion autour d'un bord intérieur arrondi du cadre de support inférieur. Les bords des pétales s'écartent les uns des autres et créent un passage mettant en communication l'intérieur du conteneur et le plénum via l'adaptateur. Une fois le missile tiré, la pression à l'intérieur du conteneur diminue. Les pétales reviennent élastiquement dans leur position de repos, en butée contre la grille, et referment l'orifice de l'opercule.When the propellant gases are ejected from the missile, an overpressure tears the waterproofing membranes and deforms the petals by bending around a rounded inner edge of the lower support frame. The edges of the petals separate from each other and create a passage connecting the interior of the container and the plenum via the adapter. Once the missile is fired, the pressure inside the container decreases. The petals return elastically in their resting position, abutting against the gate, and close the orifice of the operculum.

La grille forme également une butée ayant l'avantage d'empêcher les pétales de se déformer vers l'intérieur du conteneur, lorsque le plénum est en surpression du fait des gaz de propulsion d'un missile voisin en cours de lancement.The grid also forms an abutment having the advantage of preventing the petals from deforming towards the interior of the container, when the plenum is overpressurized due to the propulsion gases of a neighboring missile being launched.

Ces opercules déformables à lames élastiques adaptés à la fermeture de conteneur destinés à recevoir un missile, présentent l'inconvénient de se refermer imparfaitement après utilisation.These deformable caps with elastic blades adapted to the container closure for receiving a missile, have the disadvantage of closing imperfectly after use.

L'invention a donc pour but de proposer un opercule déformable présentant une meilleure obturation après utilisation.The invention therefore aims to provide a deformable seal having a better seal after use.

A cet effet, l'invention a pour objet un opercule du type déformable, destiné à équiper le fond d'un conteneur de missile et apte à s'ouvrir sous la poussée des gaz de propulsion d'un missile contenu dans le conteneur et à se refermer après éjection du missile, l'opercule comprenant une grille et un empilement de lames élastiques, enserré entre au moins une membrane de protection thermique et une membrane d'étanchéité amont et aval, et maintenu entre un cadre de support amont et un cadre de support aval. Selon l'invention, l'opercule comporte au moins un moyen intercalaire de glissement disposé entre deux lames successives de l'empilement.For this purpose, the subject of the invention is a deformable type cover, intended to equip the bottom of a missile container and able to open under the thrust of the propulsion gases of a missile contained in the container and to closing after ejection of the missile, the cover comprising a grid and a stack of resilient blades, sandwiched between at least one thermal protection membrane and an upstream and downstream sealing membrane, and held between an upstream support frame and a frame downstream support. According to the invention, the cover comprises at least one slip intermediate means disposed between two successive blades of the stack.

Suivant des modes particuliers de l'invention, l'opercule comporte une ou plusieurs des caractéristiques suivantes, prise(s) isolément ou suivant toutes les combinaisons techniquement possibles :

  • chaque lame élastique est séparée de la lame élastique suivante dans ledit empilement par un moyen intercalaire de glissement.
  • ledit au moins un moyen intercalaire est en un matériau différent du matériau des lames adjacentes, de préférence en un matériau isolant thermique.
  • ledit au moins un moyen intercalaire de glissement est constitué par une feuille.
  • le matériau de ladite feuille est du silicone ou un mat, de préférence un mat de fibres de verre.
  • l'épaisseur des lames élastiques diminue de l'amont vers l'aval de l'empilement de lames.
  • l'épaisseur d'une lame, en un point quelconque de cette lame, est inférieure à une épaisseur maximale en ce point définie, alors que la lame est en position déformée, par une fonction linéaire croissante du rayon de courbure en ce point.
  • l'épaisseur d'une lame est constante en tout point de cette lame et est inférieure ou égale à la plus petite des épaisseurs maximales en chaque point de la lame.
  • le cadre de support aval est prolongé vers l'aval de manière à munir l'opercule de moyens de butée, et comporte un bord intérieur profilé définissant une position de déformation maximale des lames élastiques.
  • le profil dudit bord intérieur du cadre de support aval comporte une portion amont convexe et une portion aval rectiligne ou concave apte à conformer l'extrémité libre de la lame élastique.
According to particular embodiments of the invention, the lid comprises one or more of the following characteristics, taken separately or in any technically possible combination:
  • each elastic blade is separated from the next elastic blade in said stack by intermediate slip means.
  • said at least one intermediate means is of a material different from the material of the adjacent blades, preferably of a thermal insulating material.
  • said at least one intermediate slip means is constituted by a sheet.
  • the material of said sheet is silicone or a mat, preferably a mat of glass fibers.
  • the thickness of the elastic blades decreases from upstream to downstream of the stack of blades.
  • the thickness of a blade, at any point of this blade, is less than a maximum thickness at this defined point, while the blade is in position deformed, by an increasing linear function of the radius of curvature at this point.
  • the thickness of a blade is constant at any point of this blade and is less than or equal to the smallest maximum thickness at each point of the blade.
  • the downstream support frame is extended downstream so as to provide the cap with abutment means, and comprises a profiled inner edge defining a maximum deformation position of the elastic blades.
  • the profile of said inner edge of the downstream support frame comprises a convex upstream portion and a rectilinear or concave downstream portion adapted to conform the free end of the elastic blade.

L'invention et ses avantages seront mieux compris à la lecture de la description qui va suivre, donnée uniquement à titre d'exemple, et faite en se référant aux dessins annexés, sur lesquels :

  • la Figure 1 est une représentation schématique en coupe d'un conteneur inséré dans une alvéole standard ;
  • la Figure 2 est une représentation en vue de dessus du fond du conteneur de la figure 1 ;
  • la Figure 3 est une représentation en coupe axiale de l'opercule selon l'invention équipant le fond d'un conteneur ;
  • la Figure 4 est une représentation schématique agrandie de l'opercule de la Figure 3 comportant des feuilles intercalaires de glissement, dans une position d'ouverture (demie vue de gauche) et dans une position de fermeture (demie vue de droite ; et
  • la Figure 5 est une représentation schématique agrandie d'une variante de réalisation de l'opercule selon l'invention, comportant des lames d'épaisseur variable, dans une position d'ouverture (demie vue de gauche) et dans une position de fermeture (demie vue de droite).
The invention and its advantages will be better understood on reading the description which follows, given solely by way of example, and with reference to the appended drawings, in which:
  • the Figure 1 is a schematic representation in section of a container inserted into a standard cell;
  • the Figure 2 is a representation in top view of the bottom of the container of the figure 1 ;
  • the Figure 3 is a representation in axial section of the lid according to the invention equipping the bottom of a container;
  • the Figure 4 is an enlarged schematic representation of the operculum of the Figure 3 having intermediate slip sheets, in an open position (left half view) and in a closed position (half right view, and
  • the Figure 5 is an enlarged schematic representation of an alternative embodiment of the lid according to the invention, comprising blades of variable thickness, in an open position (half left view) and in a closed position (half view of right).

Sur la figure 1, le lanceur vertical de missiles 1 comporte plusieurs alvéoles 2 disposées verticalement dans la coque 3 d'un navire. Une alvéole 2 est une structure constituée d'un treillis métallique destiné à recevoir une munition formée d'un conteneur contenant un missile. La partie supérieure de l'alvéole 2 se situe au niveau du pont 4 du navire et est fermée par une porte 5, montée sur le pont 4, qui sont ouvertes lors du tir et refermées ensuite. La partie inférieure de l'alvéole 2 comporte une ouverture 10 de communication avec un plénum 11. Le plénum 11 est commun aux différentes alvéoles 2 du lanceur et permet l'évacuation des gaz de propulsion par une cheminée 12, s'étendant verticalement entre les deux rangées d'alvéoles 2. La cheminée 12 débouche au niveau supérieur du lanceur, c'est-à-dire ici au niveau du pont 4.On the figure 1 , the vertical missile launcher 1 comprises several cells 2 arranged vertically in the hull 3 of a ship. A cell 2 is a structure consisting of a wire mesh for receiving a munition formed of a container containing a missile. The upper part of the cell 2 is located at the deck 4 of the ship and is closed by a door 5, mounted on the bridge 4, which are open when fired and then closed again. The lower part of the cell 2 has an opening 10 communicating with a plenum 11. The plenum 11 is common to the various cells 2 of the launcher and allows the evacuation of the propulsion gases through a chimney 12, extending vertically between the two rows of cells 2. The chimney 12 opens to the upper level of the launcher, that is to say here at the bridge 4.

Un lanceur vertical de missiles comporte des alvéoles aptes à recevoir une munition constituée d'un conteneur 15 dans lequel est disposé un missile 16 de gros diamètre. En position insérée dans l'alvéole 2, l'axe A du conteneur 15 coïncide avec l'axe de l'alvéole.A vertical missile launcher has cells capable of receiving a munition consisting of a container 15 in which is disposed a missile 16 of large diameter. In the inserted position in the cell 2, the axis A of the container 15 coincides with the axis of the cell.

Sur la Figure 1, le conteneur 15 comporte une paroi latérale 20, une paroi d'extrémité supérieure ou couvercle 21 et une paroi d'extrémité inférieure ou fond 22. Le couvercle 21 est muni d'un opercule amont 23. Le fond 22 est muni d'un opercule aval 56 qui sera décrit en détail ci-après. Du côté extérieur, le fond 22 comporte un adaptateur 25 apte à être inséré dans l'ouverture 10 du plénum 11 lors du chargement de la munition de sorte que les gaz quittant le conteneur 15 lors du lancement du missile 16 soient guidés dans le plénum 11.On the Figure 1 , the container 15 has a side wall 20, an upper end wall or cover 21 and a bottom end wall or bottom 22. The cover 21 is provided with an upstream cover 23. The bottom 22 is provided with a downstream cap 56 which will be described in detail below. On the outside, the bottom 22 comprises an adapter 25 adapted to be inserted into the opening 10 of the plenum 11 during the loading of the munition so that the gases leaving the container 15 during the launch of the missile 16 are guided in the plenum 11 .

En se référant aux figures 2 et 3, l'opercule aval déformable amélioré 56 selon l'invention comporte, superposés le long d'un axe de symétrie C, de l'amont (l'intérieur du conteneur) vers l'aval (l'extérieur du conteneur), maintenus entre un cadre de support amont 61 et un cadre de support aval 64, une grille 62 ; une membrane amont de protection thermique 70 ; une membrane d'étanchéité amont 71 par exemple en aluminium ; un empilement de lames élastiques 63 ; une membrane d'étanchéité aval 73 par exemple en aluminium ; et, une membrane aval de protection thermique 72.Referring to figures 2 and 3 , the improved deformable downstream cap 56 according to the invention comprises, superimposed along an axis of symmetry C, from the upstream (inside the container) downstream (outside the container), maintained between an upstream support frame 61 and a downstream support frame 64, a grid 62; an upstream thermal protection membrane 70; an upstream sealing membrane 71 for example of aluminum; a stack of resilient blades 63; a downstream sealing membrane 73, for example made of aluminum; and, a downstream thermal protection membrane 72.

Chaque lame élastique 63 est de forme libre, mais pour des raisons pratiques, elle est de préférence rectangulaire (cf. Figure 2) et l'empilement de lames élastiques est maintenu par son bord périphérique entre les cadres amont et aval 61 et 64 rectangulaires. Chaque lame élastique 63 se compose de quatre pétales de forme triangulaire 65. Chaque pétale 65 correspond sensiblement à une portion de la lame 63 divisée selon ses deux diagonales. Les bords de deux pétales 65 en regard l'un de l'autre ménagent un espace 66 en forme de croix dont la surface totale est très inférieure à la surface de l'orifice 81 de l'opercule 56, de sorte que lorsque les pétales 65 sont adjacents, on peut considérer que l'opercule 56 obture le fond du conteneur qu'il équipe.Each elastic blade 63 is free-form, but for practical reasons, it is preferably rectangular (cf. Figure 2 ) and the stack of elastic blades is maintained by its peripheral edge between the upstream and downstream frames 61 and 64 rectangular. Each elastic blade 63 consists of four petals of triangular shape 65. Each petal 65 corresponds substantially to a portion of the blade 63 divided along its two diagonals. The edges of two petals 65 facing each other provide a space 66 in the form of a cross whose total surface is much smaller than the surface of the orifice 81 of the lid 56, so that when the petals 65 are adjacent, it can be considered that the operculum 56 closes the bottom of the container it equips.

Selon l'invention, comme cela est représenté sur la Figure 4 schématiquement pour plus de clarté, l'opercule aval déformable 56 comporte un empilement de lames élastiques 63 métalliques séparées les unes des autres par des feuilles intercalaires 67 en matériau non métallique résistant à la température, adapté pour faciliter le glissement des lames élastiques l'une sur l'autre. Cette feuille intercalaire 67 est de préférence en un matériau isolant thermique tel que du silicone, ou un mat, par exemple de fibres de verre.According to the invention, as shown on the Figure 4 schematically for the sake of clarity, the deformable downstream membrane 56 comprises a stack of metal resilient strips 63 separated from each other by spacer sheets 67 made of non-metallic material resistant to temperature, adapted to facilitate the sliding of the elastic strips one on the other. This intermediate sheet 67 is preferably made of a thermal insulating material such as silicone, or a mat, for example glass fibers.

Avant l'ouverture de l'opercule 56, les différentes membranes intermédiaires 70, 71, 72 et 73 sont d'une seule pièce. Elles peuvent être munies de lignes diagonales de moindre résistance correspondant à la subdivision des lames 63 en pétales 65. Ainsi, sous l'effet des gaz de propulsion, ces membranes intermédiaires 70 à 73 se déchirent proprement le long des lignes de moindre résistance.Before the operculum 56 is opened, the various intermediate membranes 70, 71, 72 and 73 are in one piece. They may be provided with diagonal lines of lesser resistance corresponding to the subdivision of the blades 63 into petals 65. Thus, under the effect of the propulsion gases, these intermediate membranes 70 to 73 tear cleanly along the lines of least resistance.

Le fonctionnement de l'opercule 56 va maintenant être décrit lorsqu'il équipe le fond du conteneur 15 de la Figure 1, l'axe C de l'opercule coïncidant alors avec l'axe A du conteneur 15. Lors du lancement du missile 16, la porte 5 de l'alvéole 2 est ouverte. Le missile 16 est ensuite mis à feu. Les gaz de propulsion font alors augmenter la pression et la température de manière importante à l'intérieur du conteneur 15. Sous l'effet de la pression, l'opercule amont 54 est perforé et l'opercule aval 56 s'ouvre ce qui permet le départ du missile et l'évacuation des gaz. L'ouverture de l'opercule aval se fait par action de la pression appliquée sur la surface supérieure ou amont d'une lame 63 de sorte qu'elle se déforme et s'écarte de sa position de repos, cette déformation des pétales s'accompagnant du déchirement des membranes d'étanchéité et de protection thermique 70 à 73. Un pétale 65 se déforme autour d'un bord intérieur 80 du cadre aval 64. Du fait du déchirement des membranes 70-73 et du déplacement des différents pétales 65 des lames 63 les uns à l'écart des autres, il se crée un passage assurant une communication entre l'intérieur du conteneur 15 et le plénum 11 via un adaptateur 25. Ce dernier sert à recevoir les gaz passant à travers le fond 22 du conteneur 15 pour les guider à travers l'ouverture 10 d'entrée du plénum 11.The operation of the lid 56 will now be described when it equips the bottom of the container 15 of the Figure 1 , the axis C of the seal then coinciding with the axis A of the container 15. When launching the missile 16, the door 5 of the cell 2 is open. The missile 16 is then fired. The propellant gases then increase the pressure and the temperature significantly inside the container 15. Under the effect of the pressure, the upstream cover 54 is perforated and the downstream cover 56 opens allowing the departure of the missile and the evacuation of the gases. The opening of the downstream cap is effected by the action of the pressure applied to the upper or upstream surface of a blade 63 so that it deforms and deviates from its rest position, this deformation of the petals. accompanying tearing of the sealing membranes and thermal protection 70 to 73. A petal 65 is deformed around an inner edge 80 of the downstream frame 64. Due to the tearing of the membranes 70-73 and the displacement of the various petals 65 of the 63 blades apart from each other, it creates a passage providing communication between the interior of the container 15 and the plenum 11 via an adapter 25. The latter serves to receive the gas passing through the bottom 22 of the container 15 to guide them through the entrance opening 10 of the plenum 11.

En munissant l'opercule 56 de moyens intercalaire de glissement 67 on empêche la formation de soudures entre deux lames successives 63 et on améliore le glissement de ces lames l'une sur l'autre. Ainsi, le mouvement de refermeture de l'opercule 56 est facilité.By providing the cover 56 with sliding intermediate means 67, the formation of welds between two successive blades 63 is prevented and improved. the sliding of these blades on one another. Thus, the closing movement of the cover 56 is facilitated.

De manière subsidiaire, en intercalant une feuille 67 d'un matériau non métallique à l'interface entre deux lames métalliques adjacentes 63, la conduction de la chaleur d'une lame à l'autre est limitée. Ainsi, même si la température des gaz de propulsion entraîne une plastification d'une lame amont, la chaleur de cette lame ne se transmet que partiellement à la lame aval suivante qui, par conséquent, s'échauffe moins et conserve mieux son élasticité. Il en résulte que les lames aval de l'empilement conservent bien leurs propriétés élastiques après ouverture de l'opercule 56 et participent à la refermeture de celui-ci en poussant les lames amont, éventuellement plastifiées, vers la grille 62. L'obturation de l'opercule 56 est ainsi améliorée.In a subsidiary manner, by inserting a sheet 67 of a non-metallic material at the interface between two adjacent metal blades 63, the conduction of heat from one blade to the other is limited. Thus, even if the temperature of the propulsion gases leads to a plasticization of an upstream blade, the heat of this blade is transmitted only partially to the next downstream blade which, therefore, heats less and retains its elasticity better. As a result, the blades downstream of the stack retain their elastic properties after opening of the cap 56 and participate in the reclosing thereof by pushing the upstream blades, possibly plasticized, to the gate 62. The shutter the cover 56 is thus improved.

Une fois le missile 16 tiré, la pression à l'intérieur du conteneur 15 diminue. Puisque les pétales 65 conservent leurs propriétés mécaniques d'élasticité du fait des feuilles intercalaires, ils reviennent effectivement d'une position déformée en position de repos, refermant l'opercule 56. La grille 62 forme une butée assurant que les pétales 65 retrouvent facilement leur position de repos dans laquelle ils sont dans un plan transversal à l'axe C de l'opercule et pour laquelle l'espace 66 est le plus faible. La grille 62 permet également que les pétales 65 ne se replient pas vers l'intérieur du tube 51, lorsque l'adaptateur 25 est en surpression en raison des gaz de propulsion d'un missile lancé depuis un tube voisin.Once the missile 16 is fired, the pressure inside the container 15 decreases. Since the petals 65 retain their mechanical properties of elasticity due to the interlayers, they effectively return to a deformed position in the rest position, closing the cover 56. The gate 62 forms a stop ensuring that the petals 65 easily find their rest position in which they are in a plane transverse to the axis C of the lid and for which the space 66 is the weakest. The gate 62 also allows the petals 65 do not fold towards the inside of the tube 51, when the adapter 25 is overpressure due to the propulsion gases of a missile launched from a neighboring tube.

En complément, le bord intérieur 80 du cadre aval 64 peut être prolongé vers l'aval et présenter axialement un profil adapté de manière à constituer une butée pour les pétales.In addition, the inner edge 80 of the downstream frame 64 can be extended downstream and axially present a profile adapted to form a stop for the petals.

Le cadre aval 64 est de forme rectangulaire, dans le plan radial transversal à l'axe principal C et s'étend axialement le long de l'axe C sur une hauteur H supérieure à une dimension D transversale d'un pétale 65, correspondant environ à la demi largeur de l'orifice 81 de l'opercule 56.The downstream frame 64 is of rectangular shape, in the radial plane transverse to the main axis C and extends axially along the axis C over a height H greater than a transverse dimension D of a petal 65, corresponding approximately at half the width of the orifice 81 of the lid 56.

L'écoulement des gaz de propulsion orientant l'axe C, le profil du bord 80 comporte une portion amont 90 convexe, suivie par une portion aval 91 concave. En variante, la portion aval 91 pourrait être rectiligne. Les portions amont et aval 90, 91 se connectent l'une à l'autre de manière tangente.Since the flow of propellant gases directs the C axis, the edge profile 80 has a convex upstream portion 90, followed by a concave downstream portion 91. As a variant, the downstream portion 91 could be rectilinear. The upstream and downstream portions 90, 91 connect to each other tangentially.

La concavité de la portion amont 90 s'entend en ce que le centre de courbure C90 du profil du bord 90 en un point quelconque P90 de ce profil se situe, en projection dans un plan radial, à l'extérieur de l'orifice central 81. De manière similaire, la convexité de la portion aval 91 s'entend en ce que le centre de courbure C91 du profil du bord 91 en un point quelconque P91 de ce profil se situe, en projection dans un plan radial, à l'intérieur de l'orifice central 81. Ainsi, la convexité de la partie amont 90 est orientée vers l'axe C de l'opercule 56 et la concavité de la partie aval 91 est orientée vers l'axe C de l'opercule 56.The concavity of the upstream portion 90 is understood in that the center of curvature C90 of the edge profile 90 at any point P90 of this profile is located, in projection in a radial plane, outside the central orifice. 81. Similarly, the convexity of the downstream portion 91 means that the center of curvature C91 of the edge profile 91 at any point P91 of this profile lies, in projection in a radial plane, at Inside the central orifice 81. Thus, the convexity of the upstream portion 90 is oriented towards the axis C of the cap 56 and the concavity of the downstream portion 91 is oriented towards the axis C of the cap 56.

La courbure en chaque point P du profil du bord 80 est déterminée de manière à ce que la zone du pétale 65 venant en appui en ce point P du profil ait une déformation maximale limitée et contrôlée. En formant le profil du bord 80 de sorte que la valeur absolue de la courbure reste inférieure à une valeur seuil, on assure que la déformation locale du matériau constitutif des pétales 65 reste inférieure à une déformation seuil au-delà de laquelle le matériau acquiert une déformation permanente. On garantit ainsi que chaque pétale 65 conserve son élasticité et revienne effectivement dans sa position de repos.The curvature at each point P of the edge profile 80 is determined in such a way that the area of the petal 65 bearing at this point P of the profile has a limited and controlled maximum deformation. By forming the profile of the edge 80 so that the absolute value of the curvature remains lower than a threshold value, it is ensured that the local deformation of the constituent material of the petals 65 remains lower than a threshold deformation beyond which the material acquires a permanent deformation. This ensures that each petal 65 retains its elasticity and effectively returns to its rest position.

Le fait que la partie aval 91 du bord 80 est concave, ou tout au moins rectiligne, présente l'avantage suivant. Il est possible que la pointe 96 du pétale 65 triangulaire, qui est placée à proximité de la flamme de combustion produite par le missile, soit plastifiée. Or, dans la position de déformation maximale, la pointe 96 est appuyée sur la partie aval 91 concave ou rectiligne qui lui confère alors une forme ayant une courbure orientée vers l'axe C. Ainsi, la pointe 96 plastifiée est courbée vers la grille 62, de telle sorte qu'elle est appliquée contre celle-ci lorsque le pétale retourne vers la position de repos. On assure ainsi que l'espace 66 entre les pétales 65 est minimal après utilisation.The fact that the downstream portion 91 of the edge 80 is concave, or at least straight, has the following advantage. It is possible that the tip 96 of the triangular petal 65, which is placed near the combustion flame produced by the missile, is plasticized. However, in the maximum deformation position, the tip 96 is supported on the concave or rectilinear downstream portion 91 which then gives it a shape having a curvature oriented towards the axis C. Thus, the plasticized tip 96 is bent towards the gate 62 , so that it is applied against it when the petal returns to the rest position. This ensures that the space 66 between the petals 65 is minimal after use.

Avantageusement le bord 80 du cadre aval 64 est constitué d'un matériau tel que du silicone qui est à la fois un isolant thermique et présente une résistance mécanique pour l'appui des pétales.Advantageously the edge 80 of the downstream frame 64 is made of a material such as silicone which is both a thermal insulator and has a mechanical strength for the support of the petals.

Dans une autre variante de réalisation représenté sur la Figure 5, l'opercule 156 comporte en outre un empilement de lames élastiques 163a, 163b, 163c d'épaisseur ea, eb, ec variable. Plus précisément, les lames élastiques placées en amont de l'empilement ont une épaisseur supérieure à celles des lames élastiques placées en aval de l'empilement. Sur la Figure 5, les épaisseurs ea, eb et ec des trois lames 163a, 163b et 163c représentées schématiquement diminuent progressivement depuis l'amont vers l'aval de l'empilement. L'épaisseur de chaque lame 163a, 163b ou 163c est choisie pour que, lorsque celle-ci est sous contrainte, en appui contre un bord intérieur 80 du cadre de support aval 64, sa face amont, tournée vers la flamme de combustion, subisse une élongation qui reste compatible avec le domaine d'élasticité du métal constitutif de la lame.In another variant embodiment shown on the Figure 5 , the lid 156 further comprises a stack of resilient blades 163a, 163b, 163c of thickness ea, eb, ec variable. More specifically, the elastic blades placed upstream of the stack have a thickness greater than those of the elastic blades placed downstream of the stack. On the Figure 5 , the thicknesses ea, eb and ec of three blades 163a, 163b and 163c schematically shown decreasing progressively from upstream to downstream of the stack. The thickness of each blade 163a, 163b or 163c is chosen so that, when it is under stress, bearing against an inner edge 80 of the downstream support frame 64, its upstream face, facing the combustion flame, undergoes an elongation that remains compatible with the field of elasticity of the constituent metal of the blade.

Plus précisément, le bord 80 du cadre aval 64 présente une portion arrondie 90 ayant un centre O de courbure. L'épaisseur e de la lame 63 en un point est choisie pour être inférieure à une épaisseur maximale em qui est d'autant plus élevée que le rayon de courbure RM de la fibre neutre f en ce point de la lame 63 déformée autour de cette portion arrondie est élevé. De préférence, l'épaisseur de la lame est constante et est choisie comme la plus petite des épaisseurs em en chaque point de la lame 63. L'homme du métier sait déterminer les épaisseurs adaptées.More specifically, the edge 80 of the downstream frame 64 has a rounded portion 90 having a center O of curvature. The thickness e of the blade 63 at a point is chosen to be less than a maximum thickness em which is greater than the radius of curvature RM of the neutral fiber f at this point of the blade 63 deformed around this rounded portion is high. Preferably, the thickness of the blade is constant and is chosen as the smallest thickness em at each point of the blade 63. The skilled person knows to determine the appropriate thicknesses.

En conférant aux lames élastiques des épaisseurs variant de l'amont vers l'aval le long de l'axe de l'opercule, on évite l'apparition locale d'une élongation sous contrainte qui ferrait perdre au matériau de la lame son élasticité.By conferring the elastic blades thicknesses varying from upstream to downstream along the axis of the cap, it avoids the local appearance of a strain elongation that would lose the material of the blade elasticity.

Les variantes de réalisation qui viennent d'être décrites, améliorent chacune les conditions de retour élastique des lames élastiques pour assurer la refermeture de l'opercule. L'homme du métier comprendra que ces différents moyens sont complémentaires et peuvent être combinés en tant que de besoin.The embodiments that have just been described, each improve the elastic return conditions of the elastic blades to ensure the closure of the lid. Those skilled in the art will understand that these different means are complementary and can be combined as needed.

On remarquera qu'il suffit que l'opercule se referme jusqu'à une obturation partielle suffisante. En effet, au-delà de cette obturation seuil, la perte de charge de l'onde de choc à la traversée de l'opercule entrouvert est telle qu'elle génère une force sur les lames suffisante pour plaquer celles-ci contre la grille et fermer ainsi complètement l'opercule.Note that it is sufficient that the lid closes until a sufficient partial closure. Indeed, beyond this threshold sealing, the pressure drop of the shock wave at the crossing of the partially open lid is such that it generates a force on the blades sufficient to press them against the gate and close the lid completely.

Claims (10)

Opercule (56) du type déformable, destiné à équiper le fond d'un conteneur de missile (15) et apte à s'ouvrir sous la poussée des gaz de propulsion d'un missile (16) contenu dans le conteneur et à se refermer après éjection du missile, l'opercule comprenant une grille (62) et un empilement de lames élastiques (63 ; 163), enserré entre au moins une membrane de protection thermique et une membrane d'étanchéité amont et aval (70, 71, 72, 73), et maintenu entre un cadre de support amont (61) et un cadre de support aval (64), caractérisé en ce qu'il comporte au moins un moyen intercalaire de glissement (67) disposé entre deux lames successives de l'empilement.Opercule (56) of the deformable type, intended to equip the bottom of a missile container (15) and able to open under the thrust of the propulsion gases of a missile (16) contained in the container and to close again after ejection of the missile, the lid comprising a grid (62) and a stack of elastic blades (63; 163) sandwiched between at least one thermal protection membrane and an upstream and downstream sealing membrane (70, 71, 72 , 73), and held between an upstream support frame (61) and a downstream support frame (64), characterized in that it comprises at least one slip intermediate means (67) arranged between two successive blades of the stack. Opercule selon la revendication 1, caractérisé en ce que chaque lame élastique (63 ; 163) est séparée de la lame élastique suivante dans ledit empilement par un moyen intercalaire de glissement (67).Seal according to claim 1, characterized in that each resilient blade (63; 163) is separated from the next resilient blade in said stack by slip intermediate means (67). Opercule selon la revendication 1 ou la revendication 2, caractérisé en ce que ledit au moins un moyen intercalaire (67) est en un matériau différent du matériau des lames (63 ; 163) adjacentes, de préférence en un matériau isolant thermique.A cap according to claim 1 or claim 2, characterized in that said at least one intermediate means (67) is of a material different from the material of the adjacent blades (63; 163), preferably of thermal insulating material. Opercule selon l'une quelconque des revendications précédentes, caractérisé en ce que ledit au moins un moyen intercalaire de glissement est constitué par une feuille (67).Operacle according to any one of the preceding claims, characterized in that said at least one slip intermediate means is constituted by a sheet (67). Opercule selon la revendication 4, caractérisé en ce que le matériau de ladite feuille (67) est du silicone ou un mat, de préférence un mat de fibres de verre.Seal according to claim 4, characterized in that the material of said sheet (67) is silicone or a mat, preferably a mat of glass fibers. opercule selon l'une quelconque des revendications 1 à 5, caractérisé en ce que l'épaisseur (e) des lames élastiques (163) diminue de l'amont vers l'aval de l'empilement de lames.Cover according to any one of claims 1 to 5, characterized in that the thickness (e) of the resilient blades (163) decreases from upstream to downstream of the stack of blades. Opercule selon la revendication 6, caractérisé en ce que l'épaisseur (e) d'une lame (163), en un point quelconque de cette lame, est inférieure à une épaisseur maximale (em) en ce point définie, alors que la lame est en position déformée, par une fonction linéaire croissante du rayon de courbure (Rm) en ce point.Seal according to claim 6, characterized in that the thickness (e) of a blade (163), at any point of this blade, is less than a maximum thickness (em) at this defined point, while the blade is in deformed position, by an increasing linear function of the radius of curvature (Rm) at this point. Opercule selon la revendication 7, caractérisé en ce que l'épaisseur (e) d'une lame (163) est constante en tout point de cette lame et est inférieure ou égale à la plus petite des épaisseurs maximales (em) en chaque point de la lame.Seal according to claim 7, characterized in that the thickness (e) of a blade (163) is constant at any point of this blade and is less than or equal to the smallest of the maximum thicknesses (em) at each point of the blade. the blade. Opercule selon l'une quelconque des revendications précédentes, caractérisé en ce que le cadre de support aval (64) est prolongé vers l'aval de manière à munir l'opercule de moyens de butée, et comporte un bord intérieur (80) profilé définissant une position de déformation maximale des lames élastiques (63 ; 163).Seal according to any one of the preceding claims, characterized in that the downstream support frame (64) is extended downstream so as to provide the cap with abutment means, and comprises a profiled inner edge (80) defining a position of maximum deformation of the elastic blades (63; 163). Opercule selon la revendication 9, caractérisé en ce que le profil dudit bord intérieur (80) du cadre de support aval (64) comporte une portion amont convexe (90) et une portion aval rectiligne ou concave (91) apte à conformer l'extrémité libre (96) de la lame élastique.Seal according to claim 9, characterized in that the profile of said inner edge (80) of the downstream support frame (64) comprises a convex upstream portion (90) and a rectilinear or concave downstream portion (91) capable of conforming the end. free (96) of the elastic blade.
EP09150245A 2008-01-11 2009-01-08 Deformable bottom closure for a missile container Active EP2078920B1 (en)

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FR0850160A FR2926358B1 (en) 2008-01-11 2008-01-11 IMPROVED DEFORMABLE AVAL OPERATED FOR MISSILE CONTAINER

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Citations (1)

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Publication number Priority date Publication date Assignee Title
FR2620808A1 (en) 1987-09-17 1989-03-24 France Etat Armement REAR OPERATOR FOR MISSILE CONTAINER

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4324167A (en) * 1980-04-14 1982-04-13 General Dynamics, Pomona Division Flexible area launch tube rear cover
US4686884A (en) * 1985-12-27 1987-08-18 General Dynamics, Pomona Division Gas management deflector
US4683798A (en) * 1985-12-27 1987-08-04 General Dynamics, Pomona Division Gas management transition device
US5194688A (en) * 1992-01-31 1993-03-16 Hughes Missile Systems Company Apparatus for limiting recirculation of rocket exhaust gases during missile launch
JP2004077038A (en) * 2002-08-20 2004-03-11 Mitsubishi Heavy Ind Ltd Back lid of canister for missile

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FR2620808A1 (en) 1987-09-17 1989-03-24 France Etat Armement REAR OPERATOR FOR MISSILE CONTAINER

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FR2926358B1 (en) 2010-01-15
ATE482373T1 (en) 2010-10-15
EP2078920A3 (en) 2009-12-02
EP2078920B1 (en) 2010-09-22
DE602009000191D1 (en) 2010-11-04
ES2351379T3 (en) 2011-02-03
FR2926358A1 (en) 2009-07-17
PL2078920T3 (en) 2011-06-30

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