EP0473498A1 - Apparatus for the evacuating of gases from a vertical launching missile module - Google Patents

Apparatus for the evacuating of gases from a vertical launching missile module Download PDF

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Publication number
EP0473498A1
EP0473498A1 EP91402293A EP91402293A EP0473498A1 EP 0473498 A1 EP0473498 A1 EP 0473498A1 EP 91402293 A EP91402293 A EP 91402293A EP 91402293 A EP91402293 A EP 91402293A EP 0473498 A1 EP0473498 A1 EP 0473498A1
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EP
European Patent Office
Prior art keywords
conduits
evacuation
gases
plenum
evacuating
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Granted
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EP91402293A
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German (de)
French (fr)
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EP0473498B1 (en
Inventor
Vincent Hartz
Jacques Pastural
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Direction General pour lArmement DGA
Etat Francais
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Direction General pour lArmement DGA
Etat Francais
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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 gas evacuation device for a vertical launch module which comprises cells regularly distributed around a gas evacuation chamber and in each of which is disposed a missile, and more specifically for a vertical launch module missiles from a surface building.
  • the vertical launch modules fitted to a surface building are generally built under the building deck.
  • the modules each include a device for discharging the propellant gases produced during a normal firing of a missile or inadvertent ignition, which evacuates the propellant gases from the upper end or from the top of the module.
  • each cell is delimited by a missile launcher container, the evacuation of the gases being ensured by means provided in each container.
  • Another architecture more widespread, includes a plenum or stilling chamber, in which the propellant gases are collected, and a single chimney for evacuation from the top of the propellant gases.
  • a plenum or stilling chamber in which the propellant gases are collected
  • a single chimney for evacuation from the top of the propellant gases.
  • Another disadvantage is that the metal can be corroded in the long term by gases.
  • the rectangular shape is ill-suited, not to say almost impossible, for making the chimney from a composite material, in particular by filament winding, which could have been a solution to the reduction of mass, due to the lightness of the composite materials.
  • the object of the present invention is to remedy the aforementioned drawbacks and it relates to a device for discharging propellant gases, with the same size as the central rectangular chimney, but of a considerably reduced weight while having excellent resistance to gases. propulsion both in terms of pressure and corrosion.
  • the present invention relates to a gas evacuation device of the type connected to a plenum and which is characterized in that the evacuation device is constituted by several evacuation conduits distinct from each other and each communicating with said plenum , at least part of said conduits being of revolution about a vertical axis.
  • An advantage of the present invention lies in the fact that the gas evacuation device can be lightened considerably, while having a total passage section for the propellant gases at least equal to that which a single chimney has.
  • the vertical launch module shown in FIG. 1, comprises a structure 1 in which cells 2 for receiving missiles are provided, not shown, the cells 2 opening into an upper plate 3 through upper openings 4 and into a lower plate 5 by passages 6.
  • the passages 6 communicate with a plenum or plenum 7 which occupies most of the base 8 of the structure 1.
  • the device for discharging the missile propulsion gases consists, in the example shown in FIG. 1, of four separate conduits 9, preferably of cylindrical shape, which are arranged between the upper and lower plates 3 and 5, of on the one hand, and between the passages 6, on the other hand, so as to occupy the volume of the module delimited by the cells.
  • Each conduit 9 communicates with the plenum 7 and leads to the atmosphere at its end upper 10, either directly at the upper plate 7 or via a collecting chamber.
  • the means for closing and isolating the propulsion gas evacuation device are not shown and can be of any suitable type.
  • FIG 2a is shown schematically, the section S 'of a single chimney 11 for discharging gases of the prior art.
  • the chimney 11 due to the thickness e of the walls 12 only offers a passage section S which is substantially less than or equal to half of the section S 'which is the section available between the cells of the vertical launch module .
  • the evacuation conduits or cylinders 9 can be aligned with the openings 4 of the alveoli, which limits the number of evacuation conduits to four, imposed by the available section.
  • the evacuation conduits 13 are three in number but arranged in staggered rows relative to the cells of the module, but each with a larger passage section.
  • Each exhaust duct 9 or 13 can be produced independently in a composite material which is both light and resistant according to a technique already proven in the space industry.
  • the simulations carried out with the device according to the invention made it possible to verify that the flow rate of the propellant gases contained in the plenum 7 was distributed equitably between the evacuation ducts and to have at the inlet of each duct a gas pressure substantially the even.
  • the general gas flow regime requires, to pass from a subsonic flow to a transonic and then supersonic flow, a very strong instantaneous pressure increase at the inlet of a discharge pipe. This relationship is materialized by the curve 14, the hatched area 15 representing the pressure prevailing in the plenum for a transonic flow in the evacuation conduits.
  • the flow rate per unit area is relatively low, and to an increase in flow rate corresponds a relatively small increase in pressure above atmospheric pressure Pa.
  • the propellant gases can then evacuate through one or more of the evacuation pipes.
  • the increase in flow is authorized by an increase in the pressure available at the inlet of said duct, a pressure which is less than or equal to the gas pressure in the plenum.
  • passage sections are chosen for the evacuation conduits which are such that there is subsonic flow or at the limit transonic on all the conduits.

Abstract

It is characterised in that it consists of a plurality of evacuation conduits (9) separate from one another and each communicating with a plenum chamber (7), at least part of said conduits being rotational about a vertical axis. The invention is used in modules for vertical launching from a surface building. <IMAGE>

Description

La présente invention concerne un dispositif d'évacuation des gaz pour module de lancement vertical qui comprend des alvéoles régulièrement réparties autour d'une chambre d'évacuation des gaz et dans chacune desquelles est disposé un missile, et plus spécialement pour un module de lancement vertical de missiles à partir d'un bâtiment de surface.The present invention relates to a gas evacuation device for a vertical launch module which comprises cells regularly distributed around a gas evacuation chamber and in each of which is disposed a missile, and more specifically for a vertical launch module missiles from a surface building.

Les modules de lancement vertical équipant un bâtiment de surface sont généralement encastrés sous le pont du bâtiment. Pour permettre leur encastrement sous le pont, les modules comprennent chacun un dispositif d'évacuation des gaz de propulsion produits lors d'un tir normal d'un missile ou d'un allumage intempestif, qui évacue les gaz de propulsion par l'extrémité supérieure ou par le haut du module.The vertical launch modules fitted to a surface building are generally built under the building deck. To allow them to be fitted under the bridge, the modules each include a device for discharging the propellant gases produced during a normal firing of a missile or inadvertent ignition, which evacuates the propellant gases from the upper end or from the top of the module.

Diverses architectures des modules de lancement vertical ont été proposées.Various architectures for vertical launch modules have been proposed.

Dans une des architectures possibles, chaque alvéole est délimitée par un conteneur lanceur de missile, l'évacuation des gaz étant assurée par des moyens prévus dans chaque conteneur.In one of the possible architectures, each cell is delimited by a missile launcher container, the evacuation of the gases being ensured by means provided in each container.

Une autre architecture, plus répandue, comprend un plénum ou chambre de tranquillisation, dans lequel sont recueillis les gaz de propulsion, et une cheminée unique d'évacuation par le haut des gaz de propulsion. Pour ce faire, et de manière à réduire le plus possible la surface occupée sur le pont, pour des raisons qui sont évidentes, on a ménagé le plénum à la base des alvéoles contenant les missiles et la cheminée unique sous forme rectangulaire entre deux rangées d'alvéoles. La cheminée rectangulaire est métallique et présente une section de passage pour les gaz évacués relativement étroite.Another architecture, more widespread, includes a plenum or stilling chamber, in which the propellant gases are collected, and a single chimney for evacuation from the top of the propellant gases. To do this, and in order to reduce as much as possible the surface occupied on the bridge, for obvious reasons, the plenum at the base of the cells containing the missiles and the single chimney in rectangular form have been provided between two rows of 'cells. The rectangular chimney is metallic and has a relatively narrow passage section for the exhaust gases.

Il est nécessaire, compte tenu de la pression des gaz, de prévoir des parois relativement épaisses et donc d'un poids de matière très important, ce qui constitue un grave inconvénient.It is necessary, taking into account the pressure of the gases, to provide relatively thick walls and therefore of a very large weight of material, which constitutes a serious drawback.

Un autre inconvénient est que le métal peut être corrodé à long terme par les gaz.Another disadvantage is that the metal can be corroded in the long term by gases.

De plus, la forme rectangulaire s'adapte mal, pour ne pas dire de façon quasiment impossible, à une réalisation de la cheminée à partir d'un matériau composite, par enroulement filamentaire notamment, ce qui aurait pu constituer une solution à la réduction de masse, en raison de la légèreté des matériaux composites.In addition, the rectangular shape is ill-suited, not to say almost impossible, for making the chimney from a composite material, in particular by filament winding, which could have been a solution to the reduction of mass, due to the lightness of the composite materials.

La présente invention a pour but de remédier aux inconvénients précités et elle a pour objet un dispositif d'évacuation des gaz de propulsion, de même encombrement que la cheminée centrale rectangulaire, mais d'un poids considérablement réduit tout en présentant une excellente résistance aux gaz de propulsion tant du point de vue de la pression que de la corrosion.The object of the present invention is to remedy the aforementioned drawbacks and it relates to a device for discharging propellant gases, with the same size as the central rectangular chimney, but of a considerably reduced weight while having excellent resistance to gases. propulsion both in terms of pressure and corrosion.

La présente invention a pour objet un dispositif d'évacuation des gaz du type relié à un plénum et qui est caractérisé en ce que le dispositif d'évacuation est constitué par plusieurs conduits d'évacuation distincts les uns des autres et communiquant chacun avec ledit plénum, au moins une partie desdits conduits étant de révolution autour d'un axe vertical.The present invention relates to a gas evacuation device of the type connected to a plenum and which is characterized in that the evacuation device is constituted by several evacuation conduits distinct from each other and each communicating with said plenum , at least part of said conduits being of revolution about a vertical axis.

Un avantage de la présente invention réside dans le fait qu'on peut alléger considérablement le dispositif d'évacuation des gaz, tout en ayant une section totale de passage pour les gaz de propulsion au moins égale à celle que présente une cheminée unique.An advantage of the present invention lies in the fact that the gas evacuation device can be lightened considerably, while having a total passage section for the propellant gases at least equal to that which a single chimney has.

De plus, la fabrication et la mise en place de conduits distincts sont plus faciles à réaliser : enfin, il devient maintenant possible d'utiliser des matériaux autres que le métal, tels que des matériaux composites très résistants et qui ne sont pas corrodés par les gaz de propulsion.In addition, the manufacture and installation of separate conduits is easier to perform: finally, it is now possible to use materials other than metal, such as very resistant composite materials which are not corroded by propellant gas.

D'autres avantages et caractéristiques ressortiront mieux à la lecture de plusieurs modes de réalisation donnés à titre indicatif, ainsi que des dessins annexés sur lesquels :

  • - la figure 1 est une vue en perspective d'un module de lancement vertical équipé d'un dispositif d'évacuation des gaz de propulsion selon un mode de réalisation de l'invention ;
  • - les figures 2a et 2b sont des représentations schématiques des sections de passage des gaz dans une cheminée rectangulaire et dans des conduits distincts, respectivement ;
  • - la figure 3 est une courbe représentant la pression instantanée dans le dispositif d'évacuation en fonction du débit dans les conduits ;
  • - la figure 4 est une représentation en plan schématique d'un autre mode de réalisation d'un dispositif selon l'invention.
Other advantages and characteristics will emerge more clearly on reading several embodiments given for information, as well as the attached drawings in which:
  • - Figure 1 is a perspective view of a vertical launch module equipped with a propulsion gas evacuation device according to an embodiment of the invention;
  • - Figures 2a and 2b are schematic representations of the gas passage sections in a rectangular chimney and in separate conduits, respectively;
  • - Figure 3 is a curve representing the instantaneous pressure in the discharge device as a function of the flow rate in the conduits;
  • - Figure 4 is a schematic plan representation of another embodiment of a device according to the invention.

Le module de lancement vertical, représenté sur la figure 1, comprend une structure 1 dans laquelle sont ménagées des alvéoles 2 de réception de missiles, non représentés, les alvéoles 2 débouchant dans une plaque supérieure 3 par des ouvertures supérieures 4 et dans une plaque inférieure 5 par des passages 6.The vertical launch module, shown in FIG. 1, comprises a structure 1 in which cells 2 for receiving missiles are provided, not shown, the cells 2 opening into an upper plate 3 through upper openings 4 and into a lower plate 5 by passages 6.

Les passages 6 communiquent avec un plénum ou chambre de tranquillisation 7 qui occupe la majeure partie de la base 8 de la structure 1.The passages 6 communicate with a plenum or plenum 7 which occupies most of the base 8 of the structure 1.

Le dispositif d'évacuation des gaz de propulsion des missiles est constitué dans l'exemple représenté sur la figure 1 par quatre conduits distincts 9, de préférence de forme cylindrique, et qui sont disposés entre les plaques supérieure et inférieure 3 et 5, d'une part, et entre les passages 6, d'autre part, de manière à occuper le volume du module délimité par les alvéoles.The device for discharging the missile propulsion gases consists, in the example shown in FIG. 1, of four separate conduits 9, preferably of cylindrical shape, which are arranged between the upper and lower plates 3 and 5, of on the one hand, and between the passages 6, on the other hand, so as to occupy the volume of the module delimited by the cells.

Chaque conduit 9 communique avec le plénum 7 et débouche à l'atmosphère par son extrémité supérieure 10, soit directement au niveau de la plaque supérieure 7 soit par l'intermédiaire d'une chambre collectrice. Les moyens de fermeture et d'isolation du dispositif d'évacuation des gaz de propulsion ne sont pas réprésentés et peuvent être de tout type approprié.Each conduit 9 communicates with the plenum 7 and leads to the atmosphere at its end upper 10, either directly at the upper plate 7 or via a collecting chamber. The means for closing and isolating the propulsion gas evacuation device are not shown and can be of any suitable type.

Sur la figure 2a est représentée de façon schématique, la section S' d'une cheminée unique 11 d'évacuation des gaz de l'art antérieur. La cheminée 11 en raison de l'épaisseur e des parois 12 n'offre qu'une section de passage S qui est sensiblement inférieure ou égale à la moitié de la section S' qui est la section disponible entre les alvéoles du module de lancement vertical.In Figure 2a is shown schematically, the section S 'of a single chimney 11 for discharging gases of the prior art. The chimney 11 due to the thickness e of the walls 12 only offers a passage section S which is substantially less than or equal to half of the section S 'which is the section available between the cells of the vertical launch module .

Comme cela est représenté schématiquement sur la figure 2b, en utilisant ladite section disponible, on peut disposer au moins quatre cylindres de diamètre égal à la largeur de la cheminée 11, ce qui offre déjà une section totale de passage pour les gaz de propulsion supérieure à S.As shown schematically in Figure 2b, using said available section, it is possible to have at least four cylinders of diameter equal to the width of the chimney 11, which already offers a total passage section for the propellant gases greater than S.

Dans le cas d'un module de lancement vertical à huit alvéoles (figure 1), les conduits ou cylindres d'évacuation 9 peuvent être alignés avec les ouvertures 4 des alvéoles, ce qui limite le nombre des conduits d'évacuation à quatre, imposé par la section disponible.In the case of a vertical launch module with eight cells (FIG. 1), the evacuation conduits or cylinders 9 can be aligned with the openings 4 of the alveoli, which limits the number of evacuation conduits to four, imposed by the available section.

Dans le cas de la figure 4, les conduits d'évacuation 13 sont au nombre de trois mais disposés en quinconces par rapport aux alvéoles du module, mais chacun avec une plus grande section de passage.In the case of FIG. 4, the evacuation conduits 13 are three in number but arranged in staggered rows relative to the cells of the module, but each with a larger passage section.

Chaque conduit d'évacuation 9 ou 13 peut être réalisé indépendamment dans un matériau composite à la fois léger et résistant suivant une technique déjà éprouvée dans l'industrie spatiale. On peut, par exemple, les réaliser à partir d'un enroulement filamentaire composite. Mais on peut également les réaliser en métal car la forme de révolution des conduits permet de diminuer les épaisseurs requises comparées à celles d'une forme rectangulaire, la masse globale des quatre conduits d'évacuation en métal étant deux à trois fois moindre qu'avec une géométrie rectangulaire.Each exhaust duct 9 or 13 can be produced independently in a composite material which is both light and resistant according to a technique already proven in the space industry. One can, for example, realize them from a composite filament winding. But they can also be made of metal because the shape of revolution of the conduits makes it possible to reduce the thicknesses required compared to those of a rectangular shape, the overall mass of the four metal evacuation conduits being two to three times less than with rectangular geometry.

Les simulations réalisées avec le dispositif selon l'invention ont permis de vérifier que le débit des gaz de propulsion contenus dans le plénum 7 se répartissait équitablement entre les conduits d'évacuation et d'avoir en entrée de chaque conduit une pression des gaz sensiblement la même.The simulations carried out with the device according to the invention made it possible to verify that the flow rate of the propellant gases contained in the plenum 7 was distributed equitably between the evacuation ducts and to have at the inlet of each duct a gas pressure substantially the even.

Ceci est explicité de la manière suivante en référence à la figure 3.This is explained as follows with reference to Figure 3.

Le régime général d'écoulement des gaz nécessite, pour passer d'un écoulement subsonique à un écoulement transonique puis supersonique, une très forte montée en pression instantanée à l'entrée d'un conduit d'évacuation. Cette relation est matérialisée par la courbe 14, la zone hachurée 15 représentant la pression régnant dans le plénum pour un écoulement transonique dans les conduits d'évacuation.The general gas flow regime requires, to pass from a subsonic flow to a transonic and then supersonic flow, a very strong instantaneous pressure increase at the inlet of a discharge pipe. This relationship is materialized by the curve 14, the hatched area 15 representing the pressure prevailing in the plenum for a transonic flow in the evacuation conduits.

Dans la zone Di (écoulement subsonique), le débit par unité de surface est relativement faible, et à une augmentation de débit correspond une augmentation relativement faible de la pression au-dessus de la pression atmosphérique Pa. Les gaz de propulsion peuvent alors s'évacuer par un ou plusieurs des conduits d'évacuation.In the zone Di (subsonic flow), the flow rate per unit area is relatively low, and to an increase in flow rate corresponds a relatively small increase in pressure above atmospheric pressure Pa. The propellant gases can then evacuate through one or more of the evacuation pipes.

Lorsque le débit tend à augmenter dans un conduit mais se situant dans la zone D2 -(écoulement transonique), l'augmentation de débit est autorisée par une augmentation de la pression disponible en entrée dudit conduit, pression qui est inférieure ou égale à la pression des gaz dans le plénum.When the flow tends to increase in a duct but is located in zone D 2 - (transonic flow), the increase in flow is authorized by an increase in the pressure available at the inlet of said duct, a pressure which is less than or equal to the gas pressure in the plenum.

Par contre, lorsque le débit surfacique dans un des conduits tend à entrer dans la zone D3 -(écoulement supersonique) alors la pression nécessaire en entrée dans le conduit n'est pas suffisante et il se trouve, en conséquence, dévié vers le conduit adjacent ce qui équilibre les débits.On the other hand, when the surface flow in one of the conduits tends to enter the zone D 3 - (supersonic flow) then the pressure required to enter the conduit is not sufficient and it is therefore diverted towards the conduit adjacent which balances the flows.

C'est pourquoi selon l'invention, en fonction des dimensions du plénum et de la section disponible entre les alvéoles, on choisit des sections de passage pour les conduits d'évacuation qui soient telles qu'on ait un écoulement subsonique ou à la limite transonique sur l'ensemble des conduits.This is why, according to the invention, depending on the dimensions of the plenum and the section available between the cells, passage sections are chosen for the evacuation conduits which are such that there is subsonic flow or at the limit transonic on all the conduits.

Claims (6)

1. Dispositif d'évacuation des gaz pour module de lancement vertical à alvéoles multiples (2) pour missiles régulièrement répartis autour du dispositif d'évacuation qui est relié à un plénum (7) ou chambre de tranquillisation des gaz, caractérisé en ce que le dispositif d'évacuation est constitué par plusieurs conduits (9) d'évacuation distincts les uns des autres et communiquant chacun avec ledit plénum, au moins une partie desdits conduits étant de révolution autour d'un axe vertical.1. Gas evacuation device for vertical launch module with multiple cells (2) for missiles regularly distributed around the evacuation device which is connected to a plenum (7) or gas still chamber, characterized in that the evacuation device is constituted by several evacuation conduits (9) distinct from each other and each communicating with said plenum, at least part of said conduits being of revolution about a vertical axis. 2. Dispositif selon la revendication 1, caractérisé en ce que chacun des conduits (9) est de forme cylindrique.2. Device according to claim 1, characterized in that each of the conduits (9) is of cylindrical shape. 3. Dispositif selon la revendication 2, caractérisé en ce que les sections des conduits cylindriques sont égales.3. Device according to claim 2, characterized in that the sections of the cylindrical conduits are equal. 4. Dispositif selon l'une des revendications 1 à 3, caractérisé en ce que les conduits sont métalliques.4. Device according to one of claims 1 to 3, characterized in that the conduits are metallic. 5. Dispositif selon l'une des revendications 1 à 3, caractérisé en ce que les conduits sont réalisés à partir d'enroulements d'un matériau composite.5. Device according to one of claims 1 to 3, characterized in that the conduits are made sés from windings of a composite material. 6. Dispositif selon la revendication 5, caractérisé en ce que les enroulements sont filementaires.6. Device according to claim 5, characterized in that the windings are wired.
EP19910402293 1990-08-23 1991-08-22 Apparatus for the evacuating of gases from a vertical launching missile module Expired - Lifetime EP0473498B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9010578 1990-08-23
FR9010578A FR2666143B1 (en) 1990-08-23 1990-08-23 GAS DISCHARGE DEVICE FOR VERTICAL MISSILES LAUNCHING MODULE.

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EP0473498A1 true EP0473498A1 (en) 1992-03-04
EP0473498B1 EP0473498B1 (en) 1995-12-06

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1442267A1 (en) * 2001-06-27 2004-08-04 Lockheed Martin Corporation Missile launcher cell with gas uptake ducts
FR2857737A1 (en) * 1992-05-14 2005-01-21 British Aerospace CONTAINER FOR FIREPROOFING MACHINE
FR2873197A1 (en) 2004-07-13 2006-01-20 Mbda France Sa LAUNCHER OF MISSILES
US7040212B1 (en) 1996-08-09 2006-05-09 Mbda Uk Limited Launching missiles
EP2003417A1 (en) * 2007-06-13 2008-12-17 Dcns Structure for supporting missile containers of a device for vertical launching of missiles
FR3079023A1 (en) * 2018-03-16 2019-09-20 Naval Group LAND VEHICLE COMPRISING AT LEAST ONE MODULE FOR LAUNCHING MISSILES

Citations (1)

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Publication number Priority date Publication date Assignee Title
US4173919A (en) * 1977-12-12 1979-11-13 General Dynamics Corporation Two-way rocket plenum for combustion suppression

Patent Citations (1)

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Publication number Priority date Publication date Assignee Title
US4173919A (en) * 1977-12-12 1979-11-13 General Dynamics Corporation Two-way rocket plenum for combustion suppression

Non-Patent Citations (1)

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Title
AVIATION WEEK AND SPACE TECHNOLOGY vol. 114, no. 9, 2 Mars 1981, NEW YORK,US pages 49 - 50; E.H.KOLCUM: 'Missile Engineering: Vertical Launching System Scheduled for Sea Tests' *

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2857737A1 (en) * 1992-05-14 2005-01-21 British Aerospace CONTAINER FOR FIREPROOFING MACHINE
US7040212B1 (en) 1996-08-09 2006-05-09 Mbda Uk Limited Launching missiles
EP1442267A1 (en) * 2001-06-27 2004-08-04 Lockheed Martin Corporation Missile launcher cell with gas uptake ducts
EP1442267A4 (en) * 2001-06-27 2010-03-24 Lockheed Corp Missile launcher cell with gas uptake ducts
FR2873197A1 (en) 2004-07-13 2006-01-20 Mbda France Sa LAUNCHER OF MISSILES
WO2006016084A1 (en) * 2004-07-13 2006-02-16 Mbda France Missile launcher
US7913605B2 (en) 2004-07-13 2011-03-29 Mbda France Missile launcher
EP2003417A1 (en) * 2007-06-13 2008-12-17 Dcns Structure for supporting missile containers of a device for vertical launching of missiles
FR2917493A1 (en) * 2007-06-13 2008-12-19 Dcn Sa MISSILE CONTAINER MAINTENANCE STRUCTURE OF A MISSILE VERTICAL LAUNCH DEVICE
US7913604B2 (en) 2007-06-13 2011-03-29 Dcns Missile container retaining structure for a vertical missile launch device
FR3079023A1 (en) * 2018-03-16 2019-09-20 Naval Group LAND VEHICLE COMPRISING AT LEAST ONE MODULE FOR LAUNCHING MISSILES

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Publication number Publication date
EP0473498B1 (en) 1995-12-06
FR2666143B1 (en) 1992-11-06
FR2666143A1 (en) 1992-02-28

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