EP2078918A2 - Container for multiple missiles and versatile launcher - Google Patents
Container for multiple missiles and versatile launcher Download PDFInfo
- Publication number
- EP2078918A2 EP2078918A2 EP09150230A EP09150230A EP2078918A2 EP 2078918 A2 EP2078918 A2 EP 2078918A2 EP 09150230 A EP09150230 A EP 09150230A EP 09150230 A EP09150230 A EP 09150230A EP 2078918 A2 EP2078918 A2 EP 2078918A2
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- EP
- European Patent Office
- Prior art keywords
- container
- missile
- downstream
- container according
- support frame
- 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.)
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Images
Classifications
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- 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
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- 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 missile containers.
- 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 an 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 missile 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 doors of the cell are closed.
- a deformable seal that opens at the time of launching a missile and closes after.
- 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 known launcher cells are designed to receive a munition, the container and its missile, of a particular type.
- suitable launchers for launching large missiles for example 7 meters long
- launchers adapted to launch small missiles for example 4 meters long. If you want a ship to be able to fire small missiles and large missiles, it is necessary to equip it with two different launchers respectively dedicated to each type of missile, which is a drawback.
- the invention therefore aims to overcome the aforementioned drawbacks by providing a means for launching small missiles from a launcher designed for large missiles and thus to make known missile launchers versatile.
- the invention relates to a munition container adapted to be inserted into a missile launcher adapted to be shipped on a ship.
- the container comprises a bottom provided with a plurality of resealable lids and a partitioning subdividing the container into a plurality of tubes, each tube being intended to receive a missile and each lid being opposite a tube, the container thus forming a multiple container.
- the invention also relates to a munition comprising a plurality of missiles arranged in a multiple container such as that described above.
- the invention therefore has the advantage of making a launcher versatile by allowing to place in a cell either a single container containing a large diameter missile or a multiple container containing several missiles of smaller diameter.
- the screen formed by the extended downstream frame protects the neighboring lids from heat radiation and thus avoids excessive heating which could degrade the properties of the lids.
- elasticity of the elastic blades of these neighboring operculas Therefore, maintaining their elasticity, the blades ensure a satisfactory closure of the lid.
- the propulsion gases are channeled axially. They do not leave laterally towards the neighboring operculum. In this way, the influence of the opening of a lid on neighboring operculas is reduced.
- the operculum is provided with a means limiting the lateral movement of the petals forming the blades.
- the covers are very close to each other, it is then possible to simultaneously launch missiles contained in neighboring tubes, without the petals of the corresponding lids interfering with each other.
- an open position of the petals is defined, for which the deformation at all points of the petal is controlled so that they retain their elasticity.
- a petal whether or not locally lost its elasticity, returns to a rest position in which the cap effectively seals the bottom of the container.
- the tip end of a triangular petal is usually plasticized because it is in the flow of hot gases.
- the convex portion of the inner edge, on which part is supported the tip of the deformed petal allows to reach later the limit of plasticity of the material, the upstream face of the tip being in compression and not in extension.
- the convex portion allows, when the tip is plasticized, to bend it so that it is oriented towards and applied against the gate of the lid returning to the rest position.
- 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 or several missiles.
- 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 deck 4, which is 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 according to the prior art consisting of a single container 15 in which is disposed a single missile 16 of large diameter (cf. Figure 1 ) or a multiple container 17 in which are disposed a plurality of missiles 18 of smaller diameter and shorter length (cf. Figure 2 ).
- the axis A of the single or multiple container 17 coincides with the axis of the cell.
- the multi-container which will be described in more detail later constitutes a multiple ammunition that makes the launcher versatile.
- the multiple container is designed to receive missiles of reduced size so that the outer dimensions of the container are adapted so that it can be inserted into a cell designed to receive a large missile.
- the single container 15 has a side wall 20, an upper end wall or cover 21 and a lower end wall or bottom 22.
- the cover 21 is provided with an upstream cover 23.
- the bottom 22 is provided with a downstream cover 56 which will be described in detail below.
- the bottom 22 includes an adapter 25 adapted to be inserted into the opening 10 of the plenum 11 during the loading of the single munition so that the gases leaving the single container 15 during the launch of the missile 16 are guided in the plenum 11.
- the cell 2 receives a multi-container 17.
- the multi-container 17 has transverse external dimensions that exactly correspond to those of the simple container 15.
- the container 17 is provided with an interior cross-section 50 of cross-section which subdivides the container 17 in four independent tubes 51.
- On the figure 2 only an axial partition 52 separating two tubes 51a and 51b is seen.
- the lid 53 of the multi-container 17 comprises a plurality of upstream lids 54 so that the upstream end of each tube 51 is provided with an upstream lid 54.
- the bottom 55 of the multi-container 17 comprises a plurality of downstream lids 56 so that each tube 51 is provided with a deformable downstream cap 56 which will be described in detail below.
- Each tube 51 receives a missile 18 of small size placed along the axis B of the tube 51, parallel to the main axis A of the container 17.
- the propellant gases flowing through the bottom 55 of the container 17 are guided in the plenum 11 by an adapter 57.
- the container 17 being shorter in length than the single container 15, the multiple container adapter is more long than the simple container adapter.
- the nozzle of the missile 18 is placed slightly upstream of the bottom 55 of the container, close to it (about 10 cm).
- the bottom 55 of the multiple container according to the invention is equipped, on the downstream side of the container, with thermal protection means intended to protect each cap of the radiation resulting from the gases escaping through a neighboring lid when firing a missile. Cala prevents the alteration of elastic properties elastic blades of the caps under the effect of hot gases whose temperature is of the order of 3000 ° C in the center of the flame.
- thermal protection means consist of a tip portion provided on the outer wall of the bottom 55 of the multiple container 17. This tip portion, disposed in the extension of the internal partition 50, serves as a heat shield between the different opercules 56 of the bottom 55.
- the tip portion is made by extending a downstream support frame 64 so that it has a height H sufficient to effectively protect neighboring lids.
- the improved deformable downstream membrane 56 comprises, superimposed along an axis of symmetry C, from the upstream (inside the container) downstream (the outside of the container). held between an upstream support frame 61 and a downstream support frame 64, a gate 62; an upstream thermal protection membrane 70; an upstream sealing membrane 71, for example made of aluminum 71; 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 3 ) 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 operculum 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 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 downstream frame 64 is of rectangular shape, in the radial plane transverse to the main axis C. It extends axially along the axis C over a height H greater than a transverse dimension D of a petal 65, corresponding about half the width of the orifice 81 of the operculum 56.
- the cap 56 When launching the missile 18, the door 5 of the cell 2 is open. The missile 18 is then fired. The propellant gases then increase the pressure and the temperature significantly inside the tube 51. 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.
- a petal 65 is deformed around an inner edge 80 of the downstream frame 64. Due to the tearing of the membranes 70-74 and the displacement of the various petals 65 of the 63 blades apart from each other, there is created a passage providing communication between the inside of the tube 51 and the plenum 11 via the adapter 57. The latter serves to receive the gas passing through the bottom 55 of the container 17 to guide them through the inlet opening 10 of the plenum 11.
- the pressure inside the container 17 decreases. Due to their mechanical elasticity properties, the petals 65 return from 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 operculum 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 57 is overpressure due to the propulsion gases of a missile launched from a neighboring tube.
- the inner edge 80 of the downstream frame 64 forms a screen that obscures the heat radiation emitted by the hot spots of the missile flame placed upstream of a lid, which protects the neighboring lids. This is particularly desirable because of the proximity of the covers that form the bottom of a multiple container.
- the width of a cell being of the order of 55 cm
- the distance separating the main axes B of two neighboring tubes is of the order of 25 cm.
- the inner edge 80 of the downstream frame 64 defines a channel whose function is to axially guide the propulsion gases produced by the missile.
- the edge 80 also constitutes an abutment means limiting the maximum deformation of the petals 65 of the elastic blades 63. Thus, if two missiles of the multiple container 17 are fired simultaneously, the petals 65 of two neighboring lids 51 are not likely to interfere. .
- the inner edge 80 of the downstream frame 64 has a radially rectangular section, and axially a suitable profile. 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.
- 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.
- 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.
- a lid 156 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 the three blades 163a, 163b and 163c shown schematically decrease 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 the 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 thickness e of the blade 163 is chosen to be less than a maximum thickness em which is higher as the radius RM of the neutral fiber f of the blade 163 is high.
- the person skilled in the art knows how to determine the appropriate thicknesses.
- an improved deformable downstream cap 256 comprises a stack of metal elastic strips 263 separated from each other by interlayer sheets 267 of non-metallic material resistant to temperature, adapted to facilitate the sliding of the elastic strips one on the other.
- intermediate sliding means 267 prevents the formation of welds between two successive blades 263 and improves the sliding of these blades on one another. Thus, the reclosing movement of the lid 256 is facilitated.
- This intermediate sheet 267 is preferably made of a thermal insulating material such as silicone, or a mat, for example glass fibers.
- 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)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
Description
La présente invention est relative à des conteneurs de missile.The present invention relates to missile containers.
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 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 an 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, les portes de l'alvéole sont refermées.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 doors of the cell are 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. Il en résulte un régime d'ondes de choc 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 at the interface between the 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 large increase in temperature and pressure in the plenum, when firing 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
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.
Par ailleurs, les alvéoles des lanceurs connus sont conçues pour recevoir une munition, le conteneur et son missile, d'un type particulier. Ainsi, il existe des lanceurs adaptés pour lancer des missiles de grande taille, par exemple de 7 mètres de long, et il existe des lanceurs adaptés pour lancer des missiles de petite taille, par exemple de 4 mètres de long. Si l'on veut qu'un navire soit capable de tirer des missiles de petite taille et des missiles de grande taille, il est nécessaire de l'équiper de deux lanceurs différents respectivement dédiés à chaque type de missile, ce qui constitue un inconvénient.In addition, the known launcher cells are designed to receive a munition, the container and its missile, of a particular type. Thus, there are suitable launchers for launching large missiles, for example 7 meters long, and there are launchers adapted to launch small missiles, for example 4 meters long. If you want a ship to be able to fire small missiles and large missiles, it is necessary to equip it with two different launchers respectively dedicated to each type of missile, which is a drawback.
L'invention a donc pour but de remédier aux inconvénients précités en proposant un moyen permettant de lancer des petits missiles à partir d'un lanceur conçu pour des missiles de grande dimension et ainsi de rendre polyvalents les lanceurs de missiles connus.The invention therefore aims to overcome the aforementioned drawbacks by providing a means for launching small missiles from a launcher designed for large missiles and thus to make known missile launchers versatile.
A cet effet, l'invention a pour objet un conteneur de munition apte à être insérée dans un lanceur de missiles adapté pour être embarqué sur un navire. Le conteneur comporte un fond muni d'une pluralité d'opercules refermables et un cloisonnement subdivisant le conteneur en une pluralité de tubes, chaque tube étant destiné à recevoir un missile et chaque opercule étant en regard d'un tube, le conteneur formant ainsi un conteneur multiple.To this end, the invention relates to a munition container adapted to be inserted into a missile launcher adapted to be shipped on a ship. The container comprises a bottom provided with a plurality of resealable lids and a partitioning subdividing the container into a plurality of tubes, each tube being intended to receive a missile and each lid being opposite a tube, the container thus forming a multiple container.
Suivant des modes particuliers de réalisation de l'invention, le conteneur multiple comporte une ou plusieurs des caractéristiques suivantes, prise(s) isolément ou suivant toutes les combinaisons techniquement possibles :
- le conteneur comporte un adaptateur disposé sur le fond du conteneur, du côté extérieur, apte à relier le fond du conteneur à une ouverture d'entrée d'un plénum du lanceur pour guider les gaz de propulsion.
- chaque opercule est du type déformable, apte à s'ouvrir sous la poussée des gaz de propulsion du missile contenu dans le tube correspondant et à se refermer après éjection du missile, l'opercule comprenant une grille et un empilement de lames élastiques maintenus entre un cadre de support amont et un cadre de support aval.
- le fond du conteneur est muni, du côté aval, de moyens de protection thermique aptes à protéger chaque opercule voisin du flux de rayonnement thermique incident émis lors de l'ouverture d'un opercule sous l'effet des gaz de propulsion d'un missile.
- les moyens de protection thermique sont constitués par une partie d'embout du fond du conteneur, la partie d'embout comportant une paroi formant un écran thermique entre opercules voisins.
- chaque cadre de support aval a une hauteur adaptée pour constituer ladite partie d'embout jouant le rôle d'écran thermique entre opercules voisins.
- la hauteur du cadre de support aval est supérieure ou égale à la moitié de la largeur de l'orifice de l'opercule.
- au moins la surface externe du cadre de support aval est réalisée en un matériau isolant thermique, de préférence en silicone.
- le cadre de support aval forme un moyen de butée limitant le mouvement d'ouverture des lames élastiques.
- le cadre de support aval d'un opercule comporte un bord intérieur profilé de manière à munir l'opercule d'un moyen de butée 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 pour conformer l'extrémité libre de la lame élastique.
- deux lames élastiques successives d'un opercule sont séparées l'une de l'autre par une feuille intercalaire en matériau non métallique résistant à la chaleur.
- l'épaisseur des lames élastiques d'un opercule diminue de l'amont vers l'aval.
- the container comprises an adapter disposed on the bottom of the container, on the outer side, adapted to connect the bottom of the container to an inlet opening of a plenum of the launcher to guide the propulsion gases.
- each cap is of the deformable type, able to open under the thrust of the propulsion gases of the missile contained in the corresponding tube and to close after ejection of the missile, the cap comprising a grid and a stack of elastic blades held between a an upstream support frame and a downstream support frame.
- the bottom of the container is provided, on the downstream side, with thermal protection means able to protect each neighboring operculum of the incident thermal radiation flux emitted during the opening of a cap under the effect of the propulsion gases of a missile .
- the thermal protection means consist of a tip portion of the bottom of the container, the tip portion having a wall forming a heat shield between adjacent lids.
- each downstream support frame has a height adapted to form said tip portion acting as a heat shield between neighboring lids.
- the height of the downstream support frame is greater than or equal to half the width of the opening of the lid.
- at least the outer surface of the downstream support frame is made of a thermal insulating material, preferably silicone.
- the downstream support frame forms an abutment means limiting the opening movement of the elastic blades.
- the downstream support frame of a cap comprises an inner edge profiled so as to provide the cap with a stop means 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 for forming the free end of the elastic blade.
- two successive elastic blades of a lid are separated from each other by a spacer sheet of non-metallic material resistant to heat.
- the thickness of the elastic blades of a lid decreases from upstream to downstream.
L'invention a également pour objet une munition comportant une pluralité de missiles disposés dans un conteneur multiple tel que celui décrit précédemment.The invention also relates to a munition comprising a plurality of missiles arranged in a multiple container such as that described above.
L'invention présente donc l'avantage de rendre polyvalent un lanceur en permettant de placer dans une alvéole soit un conteneur simple renfermant un missile de gros diamètre, soit un conteneur multiple renfermant plusieurs missiles de plus faible diamètre.The invention therefore has the advantage of making a launcher versatile by allowing to place in a cell either a single container containing a large diameter missile or a multiple container containing several missiles of smaller diameter.
Pour la mise en oeuvre d'une pluralité d'opercules sur le fond d'un conteneur multiple, l'écran que forme le cadre aval prolongé protège du rayonnement thermique les opercules voisins et évite ainsi un échauffement excessif qui pourrait dégrader les propriétés d'élasticité des lames élastiques de ces opercules voisins. De ce fait, en conservant leur élasticité, les lames assurent une refermeture satisfaisante de l'opercule. De plus, en prolongeant le cadre aval d'une hauteur suffisante, les gaz de propulsion sont canalisés axialement. Ils ne partent pas latéralement en direction des opercules voisins. De la sorte, l'influence des l'ouverture d'un opercule sur les opercules voisins est réduite.For the implementation of a plurality of lids on the bottom of a multiple container, the screen formed by the extended downstream frame protects the neighboring lids from heat radiation and thus avoids excessive heating which could degrade the properties of the lids. elasticity of the elastic blades of these neighboring operculas. Therefore, maintaining their elasticity, the blades ensure a satisfactory closure of the lid. In addition, by extending the downstream frame by a sufficient height, the propulsion gases are channeled axially. They do not leave laterally towards the neighboring operculum. In this way, the influence of the opening of a lid on neighboring operculas is reduced.
Avantageusement encore, en prolongeant le bord intérieur du cadre aval, on munit l'opercule d'un moyen limitant le débattement latéral des pétales formant les lames. Comme, pour un conteneur multiple, les opercules sont très proches les uns des autres, il est alors possible de lancer simultanément des missiles contenus dans des tubes voisins, sans que les pétales des opercules correspondants n'interférent entre eux.Advantageously, by extending the inner edge of the downstream frame, the operculum is provided with a means limiting the lateral movement of the petals forming the blades. As, for a multiple container, the covers are very close to each other, it is then possible to simultaneously launch missiles contained in neighboring tubes, without the petals of the corresponding lids interfering with each other.
Avantageusement, en munissant le bord intérieur du cadre aval d'un profil adapté, une position ouverte des pétales est définie, pour laquelle la déformation en tout points du pétale est contrôlée pour que ceux-ci conservent leur élasticité.Advantageously, by providing the inner edge of the downstream frame with a suitable profile, an open position of the petals is defined, for which the deformation at all points of the petal is controlled so that they retain their elasticity.
De plus, un pétale, qu'il ait ou non perdu localement son élasticité, revient dans une position de repos dans laquelle l'opercule obture efficacement le fond du conteneur. En effet, l'extrémité de pointe d'un pétale triangulaire est en général plastifiée car elle se situe dans l'écoulement des gaz chauds. La partie convexe du bord intérieur, partie sur laquelle est appuyée la pointe du pétale déformé, permet d'atteindre plus tardivement la limite de plasticité du matériau, la face amont de la pointe étant en compression et non en extension. De plus, la partie convexe permet, lorsque la pointe est plastifiée, de courber celle-ci de manière à ce qu'elle soit orientée vers, et appliquée contre, la grille de l'opercule en revenant en position de repos.In addition, a petal, whether or not locally lost its elasticity, returns to a rest position in which the cap effectively seals the bottom of the container. Indeed, the tip end of a triangular petal is usually plasticized because it is in the flow of hot gases. The convex portion of the inner edge, on which part is supported the tip of the deformed petal, allows to reach later the limit of plasticity of the material, the upstream face of the tip being in compression and not in extension. In addition, the convex portion allows, when the tip is plasticized, to bend it so that it is oriented towards and applied against the gate of the lid returning to the rest position.
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, dans lesquels :
- la
Figure 1 est une représentation schématique d'un conteneur simple inséré dans une alvéole d'un lanceur vertical de missiles ; - la
Figure 2 est une représentation schématique d'un conteneur multiple inséré dans l'alvéole du lanceur de laFigure 1 ; - la
Figure 3 est une représentation en coupe du conteneur multiple de lafigure 2 ; - la
Figure 4 est une représentation en coupe axiale de l'opercule selon l'invention équipant le fond d'un conteneur et comportant un cadre aval prolongé avec un bord intérieur profilé ; - la
Figure 5 est une représentation en coupe d'une première variante de réalisation de l'opercule selon l'invention comportant des feuilles intercalaires de glissement d'un pétale sur l'autre, dans une position d'ouverture (demie vue de gauche) et dans une position de fermeture (demie vue de droite) ; et, - la
Figure 6 est une représentation en coupe d'une seconde 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
Figure 1 is a schematic representation of a single container inserted into a cell of a vertical missile launcher; - the
Figure 2 is a schematic representation of a multiple container inserted in the cell of the launcher of theFigure 1 ; - the
Figure 3 is a sectional representation of the multiple container of thefigure 2 ; - the
Figure 4 is a representation in axial section of the lid according to the invention equipping the bottom of a container and having an extended downstream frame with a profiled inner edge; - the
Figure 5 is a sectional representation of a first embodiment of the lid according to the invention comprising interlayer slip sheets of a petal on the other, in an open position (half left view) and in a closing position (half right view); and, - the
Figure 6 is a sectional representation of a second 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 les
Un lanceur vertical de missiles comporte des alvéoles aptes à recevoir une munition conformément à l'art antérieur constituée d'un conteneur simple 15 dans lequel est disposé un seul missile 16 de gros diamètre (cf.
Sur la
Sur les
Les gaz de propulsion s'écoulant à travers le fond 55 du conteneur 17 sont guidés dans le plénum 11 par un adaptateur 57. Le conteneur 17 étant d'une longueur plus courte que le conteneur simple 15, l'adaptateur du conteneur multiple est plus long que l'adaptateur du conteneur simple.The propellant gases flowing through the bottom 55 of the
La tuyère du missile 18 est placée légèrement en amont du fond 55 du conteneur, à proximité de celui-ci (environ 10 cm).The nozzle of the missile 18 is placed slightly upstream of the bottom 55 of the container, close to it (about 10 cm).
Le fond 55 du conteneur multiple selon l'invention est équipé, du côté aval du conteneur, de moyens de protection thermique destinés à protéger chaque opercule du rayonnement résultant des gaz s'échappant à travers un opercule voisin lors du tir d'un missile. Cala permet d'éviter l'altération des propriétés élastiques des lames élastiques des opercules sous l'effet des gaz chauds dont la température est de l'ordre de 3000 °C au centre de la flamme.The bottom 55 of the multiple container according to the invention is equipped, on the downstream side of the container, with thermal protection means intended to protect each cap of the radiation resulting from the gases escaping through a neighboring lid when firing a missile. Cala prevents the alteration of elastic properties elastic blades of the caps under the effect of hot gases whose temperature is of the order of 3000 ° C in the center of the flame.
Ces moyens de protection thermique sont constitués d'une partie d'embout prévue sur la paroi extérieure du fond 55 du conteneur multiple 17. Cette partie d'embout, disposée dans le prolongement du cloisonnement interne 50, sert d'écran thermique entre les différents opercules 56 du fond 55.These thermal protection means consist of a tip portion provided on the outer wall of the bottom 55 of the
Dans un mode de réalisation représenté sur la
Sur cette figure, 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 71 ; un empilement de lames élastiques 63 ; une membrane d'étanchéité aval 73 par exemple en aluminium ; et, une membrane aval de protection thermique 72.In this figure, the improved deformable
Chaque lame élastique 63 est de forme libre, mais pour des raisons pratiques de réalisation, elle est de préférence rectangulaire (cf.
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
Le cadre aval 64 est de forme rectangulaire, dans le plan radial transversal à l'axe principal C. Il 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
Le fonctionnement de l'opercule 56 va maintenant être décrit lorsqu'il équipe le fond d'un tube du conteneur multiple de la
Une fois le missile 18 tiré, la pression à l'intérieur du conteneur 17 diminue. Du fait de leurs propriétés mécaniques d'élasticité, les pétales 65 reviennent 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 57 est en surpression en raison des gaz de propulsion d'un missile lancé depuis un tube voisin.Once the missile 18 is fired, the pressure inside the
Le bord intérieur 80 du cadre aval 64 forme un écran qui occulte le rayonnement thermique émis par les points chauds de la flamme du missile placé en amont d'un opercule, ce qui protège les opercules voisins. Ceci est particulièrement souhaitable à cause de la proximité des opercules qui forment le fond d'un conteneur multiple. Par exemple, la largeur d'une alvéole étant de l'ordre de 55 cm, la distance séparant les axes principaux B de deux tubes voisins est de l'ordre de 25 cm.The
Le bord intérieur 80 du cadre aval 64 délimite un canal ayant pour fonction de guider axialement les gaz de propulsion produits par le missile. Les gaz chauds, canalisés axialement, s'écartent rapidement du fond 55 du conteneur et ne partent pas latéralement en direction d'un opercule voisin.The
Ainsi, les effets du tir d'un missile sur les opercules voisins sont fortement réduits et les lames déformables de ces opercules conservent leur élasticité et assurent une obturation plus efficace des tubes après utilisation.Thus, the effects of firing a missile on the neighboring lids are greatly reduced and the deformable blades of these lids retain their elasticity and ensure a more effective closure of the tubes after use.
Le bord 80 constitue également un moyen de butée limitant la déformation maximale des pétales 65 des lames élastiques 63. Ainsi, si deux missiles du conteneur multiple 17 sont mis à feu simultanément, les pétales 65 de deux opercules voisins 51 ne risquent pas d'interférer.The
Avantageusement, le bord intérieur 80 du cadre aval 64 présente radialement une section rectangulaire, et axialement un profil adapté. 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.Advantageously, the
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
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
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
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
Dans une variante de réalisation représenté sur la
Ainsi, si la portion amont 90 du bord 80 est arrondie de manière à présenter un centre O de courbure, l'épaisseur e de la lame 163 est choisie pour être inférieure à une épaisseur maximale em qui est d'autant plus élevée que le rayon RM de la fibre neutre f de la lame 163 est élevée. L'homme du métier sait déterminer les épaisseurs adaptées.Thus, if the
Dans une autre variante de réalisation représenté sur la
En munissant l'opercule 256 de moyens intercalaire de glissement 267 on empêche la formation de soudures entre deux lames successives 263 et on améliore le glissement de ces lames l'une sur l'autre. Ainsi, le mouvement de refermeture de l'opercule 256 est facilité.By providing the
De manière subsidiaire, en intercalant une feuille 267 d'un matériau non métallique à l'interface entre deux lames métalliques adjacentes 263, 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 256 et participent à la refermeture de celui-ci en poussant les lames amont, éventuellement plastifiées, vers la grille 62. L'obturation de l'opercule 256 est ainsi améliorée.In a subsidiary manner, by interposing a
Cette feuille intercalaire 267 est de préférence en un matériau isolant thermique tel que du silicone, ou un mat, par exemple de fibres de verre.This
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 (14)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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FR0850159A FR2926357B1 (en) | 2008-01-11 | 2008-01-11 | MULTIPLE MISSILE CONTAINER AND VERSATILE LAUNCHER |
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EP2078918A2 true EP2078918A2 (en) | 2009-07-15 |
EP2078918A3 EP2078918A3 (en) | 2009-12-02 |
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EP09150230.2A Active EP2078918B1 (en) | 2008-01-11 | 2009-01-08 | Container for multiple missiles and versatile launcher |
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EP (1) | EP2078918B1 (en) |
ES (1) | ES2581232T3 (en) |
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Cited By (6)
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RU2484408C2 (en) * | 2011-08-22 | 2013-06-10 | Открытое акционерное общество "Центральное конструкторское бюро "Титан" | Device for automatic drop and catch of cover of transporter-launcher container installed on missile launcher |
CN103913099A (en) * | 2014-03-12 | 2014-07-09 | 南京航空航天大学 | Integral hollow composite material firing box cover |
RU2544265C1 (en) * | 2014-02-28 | 2015-03-20 | Открытое акционерное общество Центральный научно-исследовательский институт специального машиностроения | Fireproof cover of multi-barrel launching unit |
CN111595199A (en) * | 2020-05-14 | 2020-08-28 | 湖北三江航天万峰科技发展有限公司 | Heating control device for launching box |
CN113074580A (en) * | 2021-04-02 | 2021-07-06 | 上海机电工程研究所 | Repeatable large-angle cartridge switch cover mechanism |
CN115164642A (en) * | 2022-07-30 | 2022-10-11 | 成都云鼎智控科技有限公司 | Disengaging and inserting support structure and launching device formed by disengaging and inserting support structure |
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RU2484408C2 (en) * | 2011-08-22 | 2013-06-10 | Открытое акционерное общество "Центральное конструкторское бюро "Титан" | Device for automatic drop and catch of cover of transporter-launcher container installed on missile launcher |
RU2544265C1 (en) * | 2014-02-28 | 2015-03-20 | Открытое акционерное общество Центральный научно-исследовательский институт специального машиностроения | Fireproof cover of multi-barrel launching unit |
CN103913099A (en) * | 2014-03-12 | 2014-07-09 | 南京航空航天大学 | Integral hollow composite material firing box cover |
CN111595199A (en) * | 2020-05-14 | 2020-08-28 | 湖北三江航天万峰科技发展有限公司 | Heating control device for launching box |
CN111595199B (en) * | 2020-05-14 | 2022-12-23 | 湖北三江航天万峰科技发展有限公司 | Heating control device for launching box |
CN113074580A (en) * | 2021-04-02 | 2021-07-06 | 上海机电工程研究所 | Repeatable large-angle cartridge switch cover mechanism |
CN115164642A (en) * | 2022-07-30 | 2022-10-11 | 成都云鼎智控科技有限公司 | Disengaging and inserting support structure and launching device formed by disengaging and inserting support structure |
Also Published As
Publication number | Publication date |
---|---|
EP2078918A3 (en) | 2009-12-02 |
FR2926357A1 (en) | 2009-07-17 |
FR2926357B1 (en) | 2013-10-25 |
ES2581232T3 (en) | 2016-09-02 |
PL2078918T3 (en) | 2016-11-30 |
EP2078918B1 (en) | 2016-04-27 |
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