EP0308344B1 - Rearward closure for a missile container - Google Patents

Rearward closure for a missile container Download PDF

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Publication number
EP0308344B1
EP0308344B1 EP88402343A EP88402343A EP0308344B1 EP 0308344 B1 EP0308344 B1 EP 0308344B1 EP 88402343 A EP88402343 A EP 88402343A EP 88402343 A EP88402343 A EP 88402343A EP 0308344 B1 EP0308344 B1 EP 0308344B1
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EP
European Patent Office
Prior art keywords
fact
door according
door
plates
plate
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EP88402343A
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German (de)
French (fr)
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EP0308344A1 (en
Inventor
Pierre-Jacques Truyman
Michel Bouron
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Direction General pour lArmement DGA
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Direction General pour lArmement DGA
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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

Definitions

  • the present invention relates to a rear cover for a missile container and more particularly for a missile container on board warships.
  • Warships generally include several units for storing and launching missiles, each unit called a module comprising a variable number of containers in each of which a missile is stored. Each container is used both for storing the missile and as a launch tube. When the missile is fired, the gases are evacuated by a gas evacuation conduit into which the lower parts of the containers open, the evacuation of the gases to the atmosphere being carried out through a central chimney around which are arranged the containers of each module.
  • each container comprises means suitable for opening the upper cover for the passage of the missile after firing, and the lower cover for the passage of gases in the gas evacuation duct.
  • Missile handling means such as handling cranes are also provided on warships and are assigned either to a single module or to a group of modules and this, generally according to the number of module containers.
  • the lower or rear lid of a container can have different structures.
  • the rear container lid On warships currently in service, the rear container lid is in one piece or in several elements and is of the lost type, that is to say that it is not recovered or reused, to the main reason that it is badly damaged by missile gas. So the seal rear of the container is therefore opened at the same time as the missile is fired, and remains open after launching the missile, thus permitting permanent communication between the gas evacuation pipe and the empty container.
  • the gases of this other missile will come to fill the empty container or containers which communicate with each other through the gas evacuation duct.
  • the accumulation of gases in an empty container has the effect of creating an overpressure at the level of the upper door of the module. Such an overpressure which is greater than in the lower part of the container is, moreover, damaging for the various seals of the upper door as well as for the adjacent container.
  • Another solution would be to mount a lower door which would open when the missile was fired, but which could close tightly after the missile had left.
  • the door should withstand the environment of many shots. Consequently, it should be heavy, thick and robust, which would require a motorization, thereby entailing a significant investment.
  • the present invention aims to remedy the aforementioned drawbacks and to provide a rear or lower cover for a missile container, of the non-recoverable type but which can be closed after the launch of said missile.
  • the rear cover according to the invention is of the type according to the preamble of claim 1 and representing the state of the art according to Article 54 (2) of the EPC comprising several plates which are mounted between two upper and lower supports and which are liable to deform very quickly from an initial closed position by the gases produced during the firing of the missile, and it is characterized in that that each plate of the cover is elastic and deforms around at least one rounded part formed on said lower support.
  • the radius of curvature of the rounded parts of the support is chosen in particular as a function of the opening which it is desired to provide for the passage of gases in the gas evacuation duct of the module.
  • Figure 1 is a schematic representation of a container containing a missile and provided with the lower cover according to the invention.
  • Figure 2 is an enlarged sectional view of the lower lid of the container according to the invention.
  • Figure 3 is a top view of the elastic plates of the cover.
  • Figure 4 is a top view of a thermal protection interposed between the upper support and the elastic plates of the cover.
  • Figure 5 is a top view of the cover according to another embodiment of the invention.
  • FIG. 6 is a section on a larger scale of half of the cover shown in FIG. 5.
  • a missile module on board a warship comprises several containers (1) similar to that shown in FIG. 1, each container (1) constituting a housing and a launch tube for a missile (2), the various containers a module being interconnected by a gas discharge conduit of which only a part (3) is shown.
  • Each container (1) is closed at the upper part by an upper cover (4) which is open when the missile is launched, and at the lower part by a lower cover designated as a whole by the reference (5), which is housed in an orifice (6) formed in the lower structure of the module and through which the combustion gases of the missile pass, after firing, to then be evacuated by the gas evacuation pipe (3).
  • the means for opening the upper door of the module as well as the control means necessary for launching and storing the missile are not shown for the sake of clarity of the drawings.
  • the lower cover according to the present invention comprises, according to a first embodiment shown in FIGS. 2 to 4, two upper (7) and lower (8) supports, between which are arranged a set (9) of plates as shown in the FIG. 3.
  • Each plate (11) consists of a stack of triangular elastic sheets (10) made of an appropriate material such as spring steel, and each has a thickness of approximately 3/10 mm, and this, to have a total thickness of about 1.2 mm.
  • the plates (11) are not contiguous and provide between them a space (12) between their edges, so that under the thrust of the missile propellants, they can bend in the thrust direction of said gases, the outer edges (13) being held firmly between the supports (7) and (8).
  • FIG. 1 In the example shown in FIG.
  • the cover comprises four triangular plates (11), but this set of plates (11) could be replaced by a single plate having grooves or zones of lower resistance similar to those which will be described in connection with the plate shown in FIG. 4, the aim being that the cover can be easily torn in appropriate places in order to provide a most efficient central section for the passage of gases from inside the container (1 ) to the gas exhaust pipe (3).
  • each plate (11) On each side of the stack of sheets (10) constituting each plate (11) is bonded a thin aluminum plate (14), said plates (14) opening along the lower edges (15) of the plates (11) between which the space (12) is delimited.
  • a plate (16) constituting a thermal protection On each aluminum plate (14) is bonded a plate (16) constituting a thermal protection, shown in FIG. 4, and which comprises lines of weaker resistance (17) along which said thermal protection (16) is torn at opening the door.
  • the thermal protection is intended to keep the elastic elements (11) their mechanical properties.
  • the lines of least resistance (17) coincide vertically with the axes of the space (12) formed between the plates (11) so that the stack which has just been described opens very exactly in the same places and thus avoids an anarchic tearing of the different plates of the stack, which anarchic tearing would be detrimental to a good return of said plates to their initial position shown in Figure 2, after launching the missile, as will be described later.
  • a retaining grid (18) is arranged between the upper frame (7) and the adjacent thermal protection.
  • the retaining grid (18) has the function of preventing the deformable and sectionable stack constituted by the plates (11), (14) and (16) from bending upwards when they are returned to the initial position. Indeed, after the launch of the missile and the opening of the lower door (5) of the container (1), the elastic plates (11) could exceed the initial position after deformation, due to their elasticity or under pressure due to the firing of another missile. Such overshoot is prevented by the retaining grid (18) which also plays the role of additional protection in addition to that provided by the thermal protection (16).
  • the lower frame (8) has a rounded internal peripheral edge (19) around which the deformable and sectionable stack (11), (14) and (16) deforms upon opening after sectioning along the edges (15) of the plates (11) and lines of least resistance (17) of thermal protections (16).
  • the radius of curvature of the internal peripheral edge (19) depends essentially on the extent of the deformation desired for the deformable stack or in other words the cross section for the gases to the exhaust duct (3).
  • One solution for having a small radius of curvature while ensuring a most efficient passage section for gases is to produce a deformable stack of small thickness. This object is achieved by choosing elastic sheets (10) with a thickness of approximately 0.3 mm, the aluminum plates (14) and thermal protections (161 having thicknesses of approximately 0.4 mm and 5 respectively. mm.
  • the aluminum plates (14) are cut approximately along the edges (15) of the plates ( 11). Due to the high temperature of the gases produced by the missile during the launching phase, the small aluminum strips which protrude from the edges (15) are leveled by the flames. Therefore, we obtain a space (12) between the elastic plates (11) perfectly clean and delimited. After deformation, the stack (10), (14) and (16) returns to the initial position and the space (12) provides a section of approximately 20 cm2.
  • the container (1) is closed again and communicates with the gas evacuation duct (6) only through the section of 20 cm2, which corresponds to less than 5% of the section of total passage which is offered to gases. This is very important for the other containers of the module still containing the missiles. In fact, after launching another missile from the module, the gases pass through the evacuation duct (6) and fill the container or containers no longer comprising a missile and tend to create a sudden increase in pressure in the container or containers empty and especially at the upper door.
  • the gases flowing in the exhaust duct (3) are completely filtered during their passage in the empty container, while ensuring a flow of said gases in the exhaust duct (3) of the order of 99%. Consequently, there is no need to oversize the containers as is done in the containers of the prior art, the lower cover of which remains completely open after launching the missile.
  • FIG. 6 Another embodiment of the invention ( Figures 5 and 6) consists in using support members (50) (51) in the form of bars, the lower bar (51) of which is rounded.
  • the cover (53) consists of a for two elements (54) (55), the said cover being fixed between the two bars (50) (51).
  • the structure of the cover is shown in Figure 6 and includes the same constituent parts as the cover shown in Figure 2, the references in the figure being assigned an index a.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Carbon And Carbon Compounds (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Description

La présente invention concerne un opercule arrière pour conteneur de missile et plus particulièrement pour conteneur de missile embarqué sur des bâtiments de guerre.The present invention relates to a rear cover for a missile container and more particularly for a missile container on board warships.

Les bâtiments de guerre comprennent généralement plusieurs unités de stockage et de lancement des missiles, chaque unité appelée module comportant un certain nombre variable de conteneurs dans chacun desquels un missile est entreposé. Chaque conteneur sert à la fois au stockage du missile et comme tube de lancement. Lorsque le missile est mis à feu, les gaz sont évacués par un conduit d'évacuation des gaz dans lequel débouchent les parties inférieures des conteneurs, l'évacuation des gaz à l'atmosphère étant effectuée à travers une cheminée centrale autour de laquelle sont disposés les conteneurs de chaque module. De plus, chaque conteneur comprend des moyens propres à ouvrir l'opercule supérieur pour le passage du missile après la mise à feu, et l'opercule inférieur pour le passage des gaz dans le conduit d'évacuation des gaz.Warships generally include several units for storing and launching missiles, each unit called a module comprising a variable number of containers in each of which a missile is stored. Each container is used both for storing the missile and as a launch tube. When the missile is fired, the gases are evacuated by a gas evacuation conduit into which the lower parts of the containers open, the evacuation of the gases to the atmosphere being carried out through a central chimney around which are arranged the containers of each module. In addition, each container comprises means suitable for opening the upper cover for the passage of the missile after firing, and the lower cover for the passage of gases in the gas evacuation duct.

Des moyens de manutention de missile tels que des grues de manutention sont également prévus sur les bâtiments de guerre et sont affectés soit à un seul module ou à un groupe de modules et ce, généralement en fonction du nombre de conteneurs de modules.Missile handling means such as handling cranes are also provided on warships and are assigned either to a single module or to a group of modules and this, generally according to the number of module containers.

L'opercule inférieur ou arrière d'un conteneur peut présenter différentes structures. Sur les bâtiments de guerre actuellement en service, l'opercule arrière de conteneur est d'une seule pièce ou en plusieurs éléments et est du type perdu, c'est-à-dire qu'il n'est pas récupéré ou reutilisé, pour la raison essentielle qu'il est endommagé gravement par les gaz du missile. Ainsi, l'opercule arrière du conteneur est donc ouvert en même temps que le missile est tiré, et reste ouvert après le lancement du missile, permettant alors une communication permanente entre le conduit d'évacuation des gaz et le conteneur vide. Lors d'un tir ou lancement d'un autre missile stocké dans un conteneur voisin, il s'ensuit que les gaz de cet autre missile vont venir remplir le ou les conteneurs vides qui communiquent entre eux par le conduit d'évacuation des gaz. L'accumulation des gaz dans un conteneur vide a pour effet de créer une surpression au niveau de la porte supérieure du module. Une telle surpression qui est plus importante que dans la partie inférieure du conteneur est, de plus, dommageable pour les différents joints d'étanchéité de la porte supérieure ainsi que pour le conteneur adjacent.The lower or rear lid of a container can have different structures. On warships currently in service, the rear container lid is in one piece or in several elements and is of the lost type, that is to say that it is not recovered or reused, to the main reason that it is badly damaged by missile gas. So the seal rear of the container is therefore opened at the same time as the missile is fired, and remains open after launching the missile, thus permitting permanent communication between the gas evacuation pipe and the empty container. During a firing or launching of another missile stored in a neighboring container, it follows that the gases of this other missile will come to fill the empty container or containers which communicate with each other through the gas evacuation duct. The accumulation of gases in an empty container has the effect of creating an overpressure at the level of the upper door of the module. Such an overpressure which is greater than in the lower part of the container is, moreover, damaging for the various seals of the upper door as well as for the adjacent container.

Une autre solution consisterait à monter une porte inférieure qui s'ouvrirait à la mise à feu du missile, mais qui pourrait se refermer de façon étanche après le départ du missile. La porte devrait résister à l'environnement de nombreux tirs. En conséquence, elle devrait être lourde, épaisse et robuste ce qui nécessiterait une motorisation, entrainant par là même un investissement important.Another solution would be to mount a lower door which would open when the missile was fired, but which could close tightly after the missile had left. The door should withstand the environment of many shots. Consequently, it should be heavy, thick and robust, which would require a motorization, thereby entailing a significant investment.

La présente invention a pour but de remédier aux inconvénients précités et de proposer un opercule arrière ou inférieur pour conteneur de missile, du type non récupérable mais qui puisse se refermer après le lancement dudit missile.The present invention aims to remedy the aforementioned drawbacks and to provide a rear or lower cover for a missile container, of the non-recoverable type but which can be closed after the launch of said missile.

L'opercule arrière selon l'invention est du type selon le préambule de la revendication 1 et représentant l'état de la technique selon l'article 54 (2) de la CBE comportant plusieurs plaques qui sont montées entre deux supports supérieur et inférieur et qui sont susceptibles de se déformer très rapidement d'une position initiale de fermeture par les gaz produits lors de la mise à feu du missile, et il est caractérisé en ce que chaque plaque de l'opercule est élastique et se déforme autour d'au moins une partie arrondie ménagée sur ledit support inférieur.The rear cover according to the invention is of the type according to the preamble of claim 1 and representing the state of the art according to Article 54 (2) of the EPC comprising several plates which are mounted between two upper and lower supports and which are liable to deform very quickly from an initial closed position by the gases produced during the firing of the missile, and it is characterized in that that each plate of the cover is elastic and deforms around at least one rounded part formed on said lower support.

Grâce à l'élasticité des plaques de l'opercule et aux parties arrondies autour desquelles ils se déforment, on obtient non seulement une ouverture convenable de l'opercule par la déformation desdits éléments ménageant entre eux un espace suffisant pour le passage des gaz dans le conduit d'évacuation, mais également l'assurance que les plaques reviennent vers leur position initiale de fermeture.Thanks to the elasticity of the plates of the cover and to the rounded parts around which they deform, one obtains not only a suitable opening of the cover by the deformation of said elements leaving between them sufficient space for the passage of gases in the evacuation duct, but also the assurance that the plates return to their initial closed position.

Il va de soi que le rayon de courbure des parties arrondies du support est choisi notamment en fonction de l'ouverture qu'on souhaite ménager pour le passage des gaz dans le conduit d'évacuation des gaz du module.It goes without saying that the radius of curvature of the rounded parts of the support is chosen in particular as a function of the opening which it is desired to provide for the passage of gases in the gas evacuation duct of the module.

D'autres avantages et caractéristiques apparaitront dans les autres revendications ainsi qu'à la lecture de la description de plusieurs modes de réalisation préférés de l'invention, ainsi que des dessins annexés sur lesquels:Other advantages and characteristics will appear in the other claims as well as on reading the description of several preferred embodiments of the invention, as well as the appended drawings in which:

La figure 1 est une représentation schématique d'un conteneur renfermant un missile et muni de l'opercule inférieur selon l'invention.Figure 1 is a schematic representation of a container containing a missile and provided with the lower cover according to the invention.

La figure 2 est une vue en coupe à plus grande échelle de l'opercule inférieur du conteneur selon l'invention.Figure 2 is an enlarged sectional view of the lower lid of the container according to the invention.

La figure 3 est une vue de dessus des plaques élastiques de l'opercule.Figure 3 is a top view of the elastic plates of the cover.

La figure 4 est une vue de dessus d'une protection thermique interposée entre le support supérieur et les plaques élastiques de l'opercule.Figure 4 is a top view of a thermal protection interposed between the upper support and the elastic plates of the cover.

La figure 5 est une vue de dessus de l'opercule suivant un autre mode de réalisation de l'invention.Figure 5 is a top view of the cover according to another embodiment of the invention.

La figure 6 est une coupe à plus grande échelle de la moitié de l'opercule représentée sur la figure 5.FIG. 6 is a section on a larger scale of half of the cover shown in FIG. 5.

Un module de missiles embarqués sur un bâtiment de guerre comprend plusieurs conteneurs (1) analogues à celui représenté sur la figure 1, chaque conteneur (1) constituant un logement et un tube de lancement pour un missile (2), les différents conteneurs d'un module étant reliés entre eux par un conduit d'évacuation des gaz dont seule une partie (3) est représentée. Chaque conteneur (1) est fermé à la partie supérieure par un opercule supérieur (4) qui est ouvert au lancement du missile, et à la partie inférieure par un opercule inférieur désigné dans son ensemble par la référence (5), qui est logé dans un orifice (6) ménagé dans la structure inférieure du module et à travers lequel passent les gaz de combustion du missile, après la mise à feu, pour être évacués ensuite par le conduit d'évacuation des gaz (3). Les moyens pour ouvrir la porte supérieure du module ainsi que ceux de commande nécessaires au lancement et au stockage du missile ne sont pas représentés pour des raisons de clarté des dessins.A missile module on board a warship comprises several containers (1) similar to that shown in FIG. 1, each container (1) constituting a housing and a launch tube for a missile (2), the various containers a module being interconnected by a gas discharge conduit of which only a part (3) is shown. Each container (1) is closed at the upper part by an upper cover (4) which is open when the missile is launched, and at the lower part by a lower cover designated as a whole by the reference (5), which is housed in an orifice (6) formed in the lower structure of the module and through which the combustion gases of the missile pass, after firing, to then be evacuated by the gas evacuation pipe (3). The means for opening the upper door of the module as well as the control means necessary for launching and storing the missile are not shown for the sake of clarity of the drawings.

L'opercule inférieur selon la présente invention comprend suivant un premier mode de réalisation représenté sur les figures 2 à 4, deux supports supérieur (7) et inférieur (8), entre lesquels sont disposés un ensemble (9) de plaques comme représenté sur la figure 3. Chaque plaque (11) est constituée par un empilement de feuilles élastiques triangulaires (10) réalisées en un matériau approprié tel que de l'acier à ressort, et présentent chacune une épaisseur d'environ 3/10 mm, et ce, pour avoir une épaisseur totale d'environ 1,2 mm. Les plaques (11) ne sont pas jointives et ménagent entre elles un espace (12) entre leurs bords, de manière que sous la poussée des gaz de propulsion du missile, elles puissent se courber dans la direction de poussée desdits gaz, les bords extérieurs (13) étant maintenus fermement entre les supports (7) et (8). Dans l'exemple représenté sur la figure 3, l'opercule comporte quatre plaques (11) triangulaires, mais on pourrait remplacer cet ensemble de plaques (11) par une plaque unique présentant des rainures ou des zones de moindre résistance analogues à celles qui seront décrites à propos de la plaque représentée sur la figure 4, le but poursuivi étant que l'opercule puisse se déchirer facilement en des endroits appropriés afin de ménager une section centrale la plus efficace pour le passage des gaz depuis l'intérieur du conteneur (1) vers le conduit d'évacuation des gaz (3).The lower cover according to the present invention comprises, according to a first embodiment shown in FIGS. 2 to 4, two upper (7) and lower (8) supports, between which are arranged a set (9) of plates as shown in the FIG. 3. Each plate (11) consists of a stack of triangular elastic sheets (10) made of an appropriate material such as spring steel, and each has a thickness of approximately 3/10 mm, and this, to have a total thickness of about 1.2 mm. The plates (11) are not contiguous and provide between them a space (12) between their edges, so that under the thrust of the missile propellants, they can bend in the thrust direction of said gases, the outer edges (13) being held firmly between the supports (7) and (8). In the example shown in FIG. 3, the cover comprises four triangular plates (11), but this set of plates (11) could be replaced by a single plate having grooves or zones of lower resistance similar to those which will be described in connection with the plate shown in FIG. 4, the aim being that the cover can be easily torn in appropriate places in order to provide a most efficient central section for the passage of gases from inside the container (1 ) to the gas exhaust pipe (3).

De chaque côté de l'empilement de feuilles (10) constitutif de chaque plaque (11) est collée une mince plaque d'aluminium (14), les dites plaques (14) s'ouvrant le long des arêtes inférieures (15) des plaques (11) entre lesquels est délimité l'espace (12). Sur chaque plaque d'aluminium (14) est collée une plaque (16) constituant une protection thermique, représentée sur la figure 4, et qui comprend des lignes de moindre résistance (17) le long desquelles ladite protection thermique (16) est déchirée à l'ouverture de la porte. La protection thermique est destinée à conserver aux éléments élastiques (11) leurs propriétés mécaniques. Les lignes de moindre résistance (17) coïncident verticalement avec les axes de l'espace (12) ménagé entre les plaques (11) de façon que l'empilage qui vient d'être décrit s'ouvre très exactement aux mêmes endroits et éviter ainsi un déchirement anarchique des différentes plaques de l'empilage, lequel déchirement anarchique serait préjudiciable à un bon retour desdites plaques vers leur position initiale représentée sur la figure 2, après lancement du missile, comme il sera décrit ultérieurement.On each side of the stack of sheets (10) constituting each plate (11) is bonded a thin aluminum plate (14), said plates (14) opening along the lower edges (15) of the plates (11) between which the space (12) is delimited. On each aluminum plate (14) is bonded a plate (16) constituting a thermal protection, shown in FIG. 4, and which comprises lines of weaker resistance (17) along which said thermal protection (16) is torn at opening the door. The thermal protection is intended to keep the elastic elements (11) their mechanical properties. The lines of least resistance (17) coincide vertically with the axes of the space (12) formed between the plates (11) so that the stack which has just been described opens very exactly in the same places and thus avoids an anarchic tearing of the different plates of the stack, which anarchic tearing would be detrimental to a good return of said plates to their initial position shown in Figure 2, after launching the missile, as will be described later.

Une grille de retenue (18) est disposée entre le cadre supérieur (7) et la protection thermique adjacente.A retaining grid (18) is arranged between the upper frame (7) and the adjacent thermal protection.

La grille de retenue (18) a pour fonction d'empêcher que l'empilage déformable et sectionnable constitué par les plaques (11), (14) et (16) ne se recourbent vers le haut lors de leur rappel vers la position initiale. En effet, après le lancement du missile et l'ouverture de la porte inférieure (5) du conteneur (1), les plaques élastiques (11) pourraient dépasser la position initiale après déformation et ce, en raison de leur élasticité ou sous la pression dûe au tir d'un autre missile. Un tel dépassement est empêché grâce à la grille de retenue (18) qui joue également le rôle de protection supplémentaire en plus de celle assurée par la protection thermique (16).The retaining grid (18) has the function of preventing the deformable and sectionable stack constituted by the plates (11), (14) and (16) from bending upwards when they are returned to the initial position. Indeed, after the launch of the missile and the opening of the lower door (5) of the container (1), the elastic plates (11) could exceed the initial position after deformation, due to their elasticity or under pressure due to the firing of another missile. Such overshoot is prevented by the retaining grid (18) which also plays the role of additional protection in addition to that provided by the thermal protection (16).

Le cadre inférieur (8) présente un bord périphérique interne arrondi (19) autour duquel l'empilage déformable et sectionnable (11), (14) et (16) se déforme à l'ouverture après sectionnement le long des arrêtes (15) des plaques (11) et des lignes de moindre résistance (17) des protections thermiques (16). Le rayon de courbure du bord périphérique interne (19) dépend essentiellement de l'ampleur de la déformation souhaitée pour l'empilaqe déformable ou en d'autres termes de la section de passage pour les gaz vers le conduit d'évacuation (3). Une solution pour avoir un rayon de courbure faible tout en assurant une section de passage la plus efficace pour les gaz est de réaliser un empilage déformable de faible épaisseur. Ce but est atteint en choisissant des feuilles élastiques (10) d'épaisseur d'environ 0,3 mm, les plaques d'aluminium (14) et les protections thermiques (161 présentant des épaisseurs respectivement d'environ 0,4 mm et 5 mm.The lower frame (8) has a rounded internal peripheral edge (19) around which the deformable and sectionable stack (11), (14) and (16) deforms upon opening after sectioning along the edges (15) of the plates (11) and lines of least resistance (17) of thermal protections (16). The radius of curvature of the internal peripheral edge (19) depends essentially on the extent of the deformation desired for the deformable stack or in other words the cross section for the gases to the exhaust duct (3). One solution for having a small radius of curvature while ensuring a most efficient passage section for gases is to produce a deformable stack of small thickness. This object is achieved by choosing elastic sheets (10) with a thickness of approximately 0.3 mm, the aluminum plates (14) and thermal protections (161 having thicknesses of approximately 0.4 mm and 5 respectively. mm.

Lors du sectionnement de l'empilage des feuilles (10) formant les plaques (11) et des plaques (14) et (16), les plaques d'aluminium (14) sont sectionnées approximativement le long des arrêtes (15) des plaques (11). En raison de la température élevée des gaz produits par le missile pendant la phase de lancement, les petites bandes d'aluminium qui dépassent des arêtes (15) sont arrasées par les flammes. De ce fait, on obtient un espace (12) entre les plaques élastiques (11) parfaitement net et délimité. Après déformation, l'empilage (10), (14) et (16) revient vers la position initiale et l'espace (12) ménage une section d'environ 20 cm². Ainsi, après lancement du missile, le conteneur (1) est fermé à nouveau et ne communique avec le conduit d'évacuation des gaz (6) que par la section de 20 cm², ce qui correspond à moins de 5 % de la section de passage totale qui est offerte aux gaz. Ceci est très important pour les autres conteneurs du module contenant encore les missiles. En effet, après lancement d'un autre missile du module, les gaz passent dans le conduit d'évacuation (6) et remplissent le ou les conteneurs ne comprenant plus de missile et tendent à créer une montée brutale de pression dans le ou les conteneurs vides et notamment au niveau de la porte supérieure. Grâce à l'espace (12) maintenu ouvert, après rappel ou fermeture de l'empilage déformable (10), (14) et (16), les gaz circulant dans le conduit d'évacuation (3) sont filtrés totalement lors de leur passage dans le conteneur vide, tout en assurant un écoulement desdits gaz dans le conduit d'évacuation (3) de l'ordre de 99 %. En conséquence, il n'y a pas lieu de surdimensionner les conteneurs comme cela est effectué dans les conteneurs de l'art antérieur, dont l'opercule inférieur reste totalement ouvert après lancement du missile.During the sectioning of the stacking of the sheets (10) forming the plates (11) and of the plates (14) and (16), the aluminum plates (14) are cut approximately along the edges (15) of the plates ( 11). Due to the high temperature of the gases produced by the missile during the launching phase, the small aluminum strips which protrude from the edges (15) are leveled by the flames. Therefore, we obtain a space (12) between the elastic plates (11) perfectly clean and delimited. After deformation, the stack (10), (14) and (16) returns to the initial position and the space (12) provides a section of approximately 20 cm². Thus, after launching the missile, the container (1) is closed again and communicates with the gas evacuation duct (6) only through the section of 20 cm², which corresponds to less than 5% of the section of total passage which is offered to gases. This is very important for the other containers of the module still containing the missiles. In fact, after launching another missile from the module, the gases pass through the evacuation duct (6) and fill the container or containers no longer comprising a missile and tend to create a sudden increase in pressure in the container or containers empty and especially at the upper door. Thanks to the space (12) kept open, after recalling or closing the deformable stack (10), (14) and (16), the gases flowing in the exhaust duct (3) are completely filtered during their passage in the empty container, while ensuring a flow of said gases in the exhaust duct (3) of the order of 99%. Consequently, there is no need to oversize the containers as is done in the containers of the prior art, the lower cover of which remains completely open after launching the missile.

Un autre mode de réalisation de l'invention (figures 5 et 6) consiste à utiliser des organes de support (50) (51) sous forme de barres dont la barre inférieure (51) est arrondie. L'opercule (53) est constitué par un pour deux éléments (54) (55), le dit opercule étant fixé entre les deux barres (50) (51). La structure de l'opercule est représentée sur la figure 6 et comprend les mêmes parties constitutives que l'opercule représenté sur la figure 2, les références sur la figure étant affectées d'un indice a. Another embodiment of the invention (Figures 5 and 6) consists in using support members (50) (51) in the form of bars, the lower bar (51) of which is rounded. The cover (53) consists of a for two elements (54) (55), the said cover being fixed between the two bars (50) (51). The structure of the cover is shown in Figure 6 and includes the same constituent parts as the cover shown in Figure 2, the references in the figure being assigned an index a.

Dans ce mode de réalisation, on retrouve l'espace (12) aménagé entre le bord extérieur des feuilles (10 a) et la paroi du conduit d'évacuation (56).In this embodiment, there is the space (12) arranged between the outer edge of the sheets (10a) and the wall of the discharge duct (56).

Claims (19)

1. Rear door for missile container, of the type comprising several plates (11) which are mounted between two supports, one upper (7) and one lower (8) and which are capable of deforming from an initial closed position under the effect of the gases produced when the missile (2) is fired, characterised by the fact that each plate (11) of the door is flexible and deforms around at least one curved section (19) made on the lower support (8).
2. Door according to Claim 1, characterised by the fact that the elasticity of each plate (11) and the radius of curvature of the curved section (19) of the lower frame (8) are such that the plates (11) return to their closed position after deformation.
3. Door according to either of the claims 1 or 2, characterised by the fact that a space (12) is left between the inner edges (15) of the said plates.
4. Door according to any of the claims 1 to 3, characterised by the fact that each plate (11) is triangular in shape.
5. Door according to any of the claims 1 to 4, characterised by the fact that each plate (11) consists of a stack of several sheets (10) bonded together and superimposed upon one another.
6. Door according to Claim 5, characterised by the fact that each sheet (10) of a plate (11) is made of spring steel and is about 0.3 mm in thickness.
7. Door according to any of the claims 1 to 6, characterised by the fact that a thin aluminium plate (14) is bonded on the inner and outer faces of the plates (11) and by the space left between the plates (11).
8. Door according to any of the claims 1 to 7, characterised by the fact that at least one thermal shield (16) is placed on the upper surface of the elements of the door.
9. Door according to any of the claims 1 to 7, characterised by the fact that two thermal shields (16) are placed on the upper and lower surfaces of the elements of the said door.
10. Door according to any of the claims 1 to 9, characterised by the fact that a retaining grille (18) is arranged between the upper frame (7) and the said elements of the door
11. Door according to either of the claims 8 or 9, characterised by the fact that the thermal shield (16) has lines of least resistance (17) along which it can be sect ioned
12. Door according to claims 3 and 11, characterised by the fact that the lines of least resistance 17 are arranged above the space (12) left between the plates (11).
13. Door according to claims 3 or 12, characterised by the fact that the said space (12) has a cross-section of at least 5% of the total cross-section of the passage.
14. Door according to Claim 7, characterised by the fact that the thickness of each aluminium plate is approximately 0.4 mm
15. Door according to claims 8, 9 or 10, characterised by the fact that the thickness of the thermal shield is approximately 5 mm.
16. Door according to claims 3 to 9, characterised by the fact that the triangular plates (11), the aluminium plates and the thermal shield are bonded together and form a deformable and sectionable stack.
17. Door according to Claim 1, characterised by the fact that the supports consist of two bars (50, 51) between which the flexible elements (54, 55) of the door are arranged. 18. Door according to Claim 17, characterised by the fact that the flexible elements of the door consist of a plate (53) deforming at its centre.
19. Door according to Claim 17, characterised by the fact that the flexible elements of the door consist of two stacks inserted with one of their edges between the support bars (50, 51).
EP88402343A 1987-09-17 1988-09-16 Rearward closure for a missile container Expired - Lifetime EP0308344B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8712862A FR2620808B1 (en) 1987-09-17 1987-09-17 REAR LID FOR MISSILE CONTAINER
FR8712862 1987-09-17

Publications (2)

Publication Number Publication Date
EP0308344A1 EP0308344A1 (en) 1989-03-22
EP0308344B1 true EP0308344B1 (en) 1992-04-15

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Application Number Title Priority Date Filing Date
EP88402343A Expired - Lifetime EP0308344B1 (en) 1987-09-17 1988-09-16 Rearward closure for a missile container

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EP (1) EP0308344B1 (en)
ES (1) ES2031261T3 (en)
FR (1) FR2620808B1 (en)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5194688A (en) * 1992-01-31 1993-03-16 Hughes Missile Systems Company Apparatus for limiting recirculation of rocket exhaust gases during missile launch
FR2926358B1 (en) 2008-01-11 2010-01-15 Dcns IMPROVED DEFORMABLE AVAL OPERATED FOR MISSILE CONTAINER
FR2926357B1 (en) 2008-01-11 2013-10-25 Dcns MULTIPLE MISSILE CONTAINER AND VERSATILE LAUNCHER
FR2926359B1 (en) 2008-01-11 2010-02-12 Dcns DEFORMABLE REAR OPERATOR WITH ELASTIC BLADES FOR MISSILE CONTAINER
FR2926360B1 (en) * 2008-01-11 2012-10-19 Dcns DEFORMABLE REAR OPERATOR FOR MISSILE CONTAINER, COMPRISING A FRONT SUPPORT FRAME
FR3039889B1 (en) * 2015-08-05 2017-07-28 Mbda France FLEXIBLE OPENER FOR MISSILE CONTAINER

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1540803A (en) * 1977-06-14 1979-02-14 Gen Dynamics Corp Rocket exhaust plenum flow control apparatus

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2445423A (en) * 1946-03-06 1948-07-20 United Shoe Machinery Corp Safety container for rockets
GB1540503A (en) * 1976-04-08 1979-02-14 Mcevoy Oilfield Equipment Co Marine riser pipe section
US4134327A (en) * 1977-12-12 1979-01-16 General Dynamics Corporation Rocket launcher tube post-launch rear closure

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1540803A (en) * 1977-06-14 1979-02-14 Gen Dynamics Corp Rocket exhaust plenum flow control apparatus

Also Published As

Publication number Publication date
FR2620808B1 (en) 1990-01-12
FR2620808A1 (en) 1989-03-24
EP0308344A1 (en) 1989-03-22
ES2031261T3 (en) 1992-12-01

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