EP0473498B1 - 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 PDFInfo
- Publication number
- EP0473498B1 EP0473498B1 EP19910402293 EP91402293A EP0473498B1 EP 0473498 B1 EP0473498 B1 EP 0473498B1 EP 19910402293 EP19910402293 EP 19910402293 EP 91402293 A EP91402293 A EP 91402293A EP 0473498 B1 EP0473498 B1 EP 0473498B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- ducts
- gases
- fact
- plenum
- gas
- 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.)
- Expired - Lifetime
Links
- 239000007789 gas Substances 0.000 title description 29
- 239000002131 composite material Substances 0.000 claims description 6
- 238000009730 filament winding Methods 0.000 claims description 3
- 238000004804 winding Methods 0.000 claims 1
- 239000003380 propellant Substances 0.000 description 10
- 238000007599 discharging Methods 0.000 description 4
- 239000002184 metal Substances 0.000 description 4
- 239000000463 material Substances 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/0413—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 arranged 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 fitted 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 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.
- the plenum was provided at the base of the cells containing the missiles and the single chimney in rectangular form between two rows of 'cells.
- the rectangular chimney is metallic and has a relatively narrow passage section for the exhaust 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 in mass. , due to the lightness of the composite materials.
- the present invention aims to remedy the aforementioned drawbacks and it relates to a device for discharging propellant gases, 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 for vertical launch module with multiple cells for missiles, the device, connected to a plenum or gas stilling chamber, being constituted by several distinct evacuation conduits, one from the other. others and each communicating with the plenum, at least part of the conduits being of revolution about a vertical axis, characterized in that the multiple cells for missiles are regularly distributed around the evacuation device, internal and constituted by at least three ducts.
- An advantage of the present invention lies in the fact that the gas evacuation device can be made considerably lighter, while having a total passage section for the propellant gases at least equal to that of a single chimney.
- 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 a plate upper 3 by upper openings 4 and in 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 opens into the atmosphere through its upper end 10, either directly at the level of the upper plate 7 or via a collecting chamber.
- the closing and isolating means of the propulsion gas evacuation device are not shown and may 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 ducts or cylinders 9 can be aligned with the openings 4 of the cells, 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.
- zone D1 (subsonic flow)
- the flow rate per unit area is relatively low, and an increase in flow rate corresponds to 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 pressure of the gas in the plenum.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Rigid Pipes And Flexible Pipes (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
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 arranged 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 fitted 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.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.
Pour ce faire, et de manière à reduire 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.To do this, and in order to reduce as much as possible the surface occupied on the bridge, for obvious reasons, the plenum was provided at the base of the cells containing the missiles and the single chimney in rectangular form 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 in mass. , due to the lightness of the composite materials.
Enfin, une autre architecture préconise un agencement particulier pour lutter contre les poches stagnantes d'air dans le plénum et dans tout tube contenant un missile en attente, voisin du missile tiré. En effet, ces poches sont susceptibles de créer des explosions indésirables, dues à la réaction de combustion des émissions gazeuses des missiles et de l'oxygène stagnant. Pour ce faire, on dispose de moyens de fermeture des tubes contenant les missiles (à l'interface tube-plénum) et d'une seule paire de tubes externes et incurvés, prolongeant le plénum à ses deux extrémités (figures 1-4 du brevet US-A-4173919). La configuration des deux conduits d'évacuation a donc un caractère externe, afin d'éliminer ces poches stagnantes d'air. Ce document sert de base au préambule de la revendication 1Finally, another architecture recommends a particular arrangement to combat stagnant pockets of air in the plenum and in any tube containing a missile on standby, close to the missile fired. Indeed, these pockets are capable of creating undesirable explosions, due to the reaction of combustion of the gaseous emissions of missiles and of stagnant oxygen. To do this, there are means for closing the tubes containing the missiles (at the tube-plenum interface) and a single pair of external and curved tubes, extending the plenum at its two ends (Figures 1-4 of the patent US-A-4173919). The configuration of the two exhaust ducts therefore has an external character, in order to eliminate these stagnant pockets of air. This document forms the basis for the preamble of claim 1
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 present invention aims to remedy the aforementioned drawbacks and it relates to a device for discharging propellant gases, 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 pour module de lancement vertical à alvéoles multiples pour missiles, le dispositif, relié à un plénum ou chambre de tranquillisation des gaz, étant constitué par plusieurs conduits d'évacuation distincts les uns des autres et communiquant chacun avec le plénum, au moins une partie des conduits étant de révolution autour d'un axe vertical, caractérisé en ce que les alvéoles multiples pour missiles sont régulièrement réparties autour du dispositif d'évacuation, interne et constitué par au moins trois conduits.The present invention relates to a gas evacuation device for vertical launch module with multiple cells for missiles, the device, connected to a plenum or gas stilling chamber, being constituted by several distinct evacuation conduits, one from the other. others and each communicating with the plenum, at least part of the conduits being of revolution about a vertical axis, characterized in that the multiple cells for missiles are regularly distributed around the evacuation device, internal and constituted by at least three ducts.
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 made considerably lighter, while having a total passage section for the propellant gases at least equal to that of a single chimney.
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.
- Figure 1 is a perspective view of a vertical launch module equipped with a propulsion gas discharge 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 showing 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
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
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
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
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
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, one can have at least four cylinders with a diameter equal to the width of the
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 (Figure 1), the evacuation ducts or
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
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
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
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, in order to pass from a subsonic flow to a transonic then supersonic flow, a very strong instantaneous rise in pressure at the inlet of a discharge pipe. This relationship is shown by curve 14, the
Dans la zone D₁ (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 zone D₁ (subsonic flow), the flow rate per unit area is relatively low, and an increase in flow rate corresponds to 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 D₂ (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 pressure of the gas 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 D₃ (supersonic flow) then the pressure necessary for entry into the conduit is not sufficient and it is, consequently, deflected towards the adjacent conduit this 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, we choose passage sections for the evacuation conduits which are such that there is a subsonic flow or at the limit. transonic on all the conduits.
Claims (6)
- Gas exhaust manifold for vertical launching module with multiple missile launching tubes (2). The manifold, connected to a plenum (7) or gas tranquillization chamber, is made from several exhaust ducts (9) separated from each other and each communicating with the plenum (7), at least one part of the ducts (9) being cylindrical around a vertical axis, characterized by the fact that the multiple missile launching tubes (2) are regularly distributed around the internal exhaust manifold, formed by at least three ducts (9).
- Device according to claim 1, characterized by the fact that each duct (9) is cylindrical.
- Device according to claim 2, characterized by the fact that the cross-sections of the cylindrical ducts (9) are equal.
- Device according to one of the claims 1 to 3 characterized by the fact that the ducts (9) are metallic.
- Device according to one of the claims 1 to 3, characterized by the fact that the ducts (9) are made from windings of a composite material.
- Device according to claim 5, characterized by the fact that filament windings are used
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR9010578A FR2666143B1 (en) | 1990-08-23 | 1990-08-23 | GAS DISCHARGE DEVICE FOR VERTICAL MISSILES LAUNCHING MODULE. |
| FR9010578 | 1990-08-23 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0473498A1 EP0473498A1 (en) | 1992-03-04 |
| EP0473498B1 true EP0473498B1 (en) | 1995-12-06 |
Family
ID=9399799
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP19910402293 Expired - Lifetime EP0473498B1 (en) | 1990-08-23 | 1991-08-22 | Apparatus for the evacuating of gases from a vertical launching missile module |
Country Status (2)
| Country | Link |
|---|---|
| EP (1) | EP0473498B1 (en) |
| FR (1) | FR2666143B1 (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2324593B (en) * | 1992-05-14 | 1999-12-01 | British Aerospace | Launching missiles |
| US7040212B1 (en) | 1996-08-09 | 2006-05-09 | Mbda Uk Limited | Launching missiles |
| US6755111B2 (en) * | 2001-06-27 | 2004-06-29 | Lockheed Martin Corporation | Missile launcher cell with exhaust gas uptake ducts, and array of such missile launcher cells |
| FR2873197B1 (en) * | 2004-07-13 | 2006-10-27 | Mbda France Sa | LAUNCHER OF MISSILES |
| FR2917493B1 (en) * | 2007-06-13 | 2009-09-25 | Dcn Sa | MISSILE CONTAINER MAINTENANCE STRUCTURE OF A MISSILE VERTICAL LAUNCH DEVICE |
| FR3079023B1 (en) * | 2018-03-16 | 2021-04-09 | Naval Group | LAND VEHICLE INCLUDING AT LEAST ONE MISSILES LAUNCH MODULE |
Family Cites Families (1)
| 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 |
-
1990
- 1990-08-23 FR FR9010578A patent/FR2666143B1/en not_active Expired - Lifetime
-
1991
- 1991-08-22 EP EP19910402293 patent/EP0473498B1/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| FR2666143B1 (en) | 1992-11-06 |
| EP0473498A1 (en) | 1992-03-04 |
| FR2666143A1 (en) | 1992-02-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| WO1998026209A1 (en) | Tank for pressurised fluid, in particular for liquefied gas | |
| BE1010543A3 (en) | Grid arrangement of a holding active material in a container and container and team. | |
| FR2639678A1 (en) | COMPARTMENT, ESPECIALLY OF CHICANES, OF THE RESONATOR TYPE OF HELMHOLTZ NOISE ATTENUATOR, ACOUSTIC SHIRT PARTICULARLY ANNULAR, FOR A PARTICULARLY ANNULAR CHANNEL OF A GAS TURBINE ENGINE, AND ENGINE EQUIPPED WITH THESE DEVICES | |
| EP2394735B1 (en) | Reactor-exchanger with bayonet tubes and fire tubes suspended from the upper vault of the reactor | |
| EP0677694A1 (en) | Double-walled container for transporting and storing liquefied gas | |
| EP0473498B1 (en) | Apparatus for the evacuating of gases from a vertical launching missile module | |
| EP1774249B1 (en) | Missile launcher | |
| EP1907750B1 (en) | Composite material reservoir for storing natural gas for vehicle | |
| FR2767716A1 (en) | APPARATUS FOR SEPARATING GAS BY ADSORPTION AND USE FOR TREATING AIRFLOWS | |
| EP2229573B1 (en) | Missile container bottom system | |
| WO2020174162A1 (en) | Expandable cellular system for a sandwich panel | |
| FR2766906A1 (en) | TANK FOR PRESSURE FLUID | |
| EP0836001A1 (en) | Rocket nozzle with ejectable inserts | |
| EP4196254B1 (en) | Tubular fixed-bed reactor | |
| EP0308344B1 (en) | Rearward closure for a missile container | |
| FR2802119A1 (en) | Coupling between heat exchange tube and pressurized chemical reactor permits has stuffing box between tube and casing and coupled by bellows, etc. to flange attached to reactor casing | |
| CH629889A5 (en) | ROCKET EXHAUST GAS COLLECTOR. | |
| EP2979020A1 (en) | Method and device for thermally insulating an item of equipment | |
| EP0481851B1 (en) | Closing and protecting device for a gas exhaust of a vertical launching unit | |
| EP3636907A1 (en) | Intermediate bottom for pressurised enclosure | |
| EP4267905A1 (en) | System and method for cleaning a heat exchanger of a boiler using supersonic shock waves | |
| EP2078919B1 (en) | Deformable rearward closure with elastic strips for a missile container | |
| WO2022258930A1 (en) | Avalanche-triggering device equipped with a device for generating sound waves | |
| FR3079023A1 (en) | LAND VEHICLE COMPRISING AT LEAST ONE MODULE FOR LAUNCHING MISSILES | |
| FR2801342A1 (en) | Cooling device for exhaust of e.g. direct injection diesel engine has two paths each of same axial length with different heat exchange properties and valve directing flow from one path to other path |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
| 17P | Request for examination filed |
Effective date: 19910916 |
|
| AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): ES GB IT |
|
| 17Q | First examination report despatched |
Effective date: 19931005 |
|
| GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
| AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): ES GB IT |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: ES Free format text: THE PATENT HAS BEEN ANNULLED BY A DECISION OF A NATIONAL AUTHORITY Effective date: 19951206 |
|
| ITF | It: translation for a ep patent filed | ||
| GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) |
Effective date: 19960115 |
|
| PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
| STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
| 26N | No opposition filed | ||
| REG | Reference to a national code |
Ref country code: GB Ref legal event code: IF02 |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: IT Payment date: 20100825 Year of fee payment: 20 |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20100721 Year of fee payment: 20 |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION Effective date: 20110821 |