EP2078918B1 - Multipler Raketenbehälter und Vielzweckraketenabschussvorrichtung - Google Patents

Multipler Raketenbehälter und Vielzweckraketenabschussvorrichtung Download PDF

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Publication number
EP2078918B1
EP2078918B1 EP09150230.2A EP09150230A EP2078918B1 EP 2078918 B1 EP2078918 B1 EP 2078918B1 EP 09150230 A EP09150230 A EP 09150230A EP 2078918 B1 EP2078918 B1 EP 2078918B1
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EP
European Patent Office
Prior art keywords
container
downstream
missile
doorway
container according
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Active
Application number
EP09150230.2A
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English (en)
French (fr)
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EP2078918A2 (de
EP2078918A3 (de
Inventor
Pierre Jacques Truyman
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Naval Group SA
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DCNS SA
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Publication of EP2078918A3 publication Critical patent/EP2078918A3/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/0413—Means for exhaust gas disposal, e.g. exhaust deflectors, gas evacuation systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/042—Rocket or torpedo launchers for rockets the launching apparatus being used also as a transport container for the rocket

Definitions

  • the present invention relates to missile containers.
  • a missile launcher is known adapted to be embarked on a vessel comprising a series of cells, each cell being intended to receive a munition consisting of a missile placed in a container.
  • the upper part of a cell opens at the deck of the ship and is closed, outside the launch phases, by a door.
  • the lower part of a cell has an opening opening into a plenum chamber or plenum for receiving the gases emitted during the launch of a missile.
  • the plenum common to the various cells, is equipped with a gas extraction chimney.
  • a munition is formed by a missile placed inside a container.
  • the upper and lower parts of the container are sealed, respectively by a lid provided with an upstream cap and a bottom provided with a downstream cap.
  • the internal volume of the container is generally filled with an inert gas at overpressure relative to the atmosphere (typically 1.5 bar).
  • the lower part of the container is extended by an adapter intended to cooperate with the communication opening between a cell and the plenum.
  • the ammunition is inserted from above into a pitcher cell, the bottom of the container being then in fluid communication with the plenum by means of the adapter.
  • the missile When launching the missile, the door of the cell being opened beforehand, the missile is fired.
  • the propellant gases then increase the pressure and the temperature significantly inside the container, which perforates the upstream lid of the container and opens the downstream cap.
  • the communication of the interior of the container with the plenum via the adapter allows the evacuation of the propulsion gases in the plenum, then their extraction via the chimney. After firing, the doors of the cell are closed.
  • a deformable seal that opens at the time of launching a missile and closes after.
  • This deformable seal comprises, superimposed axially along a principal axis of symmetry, which coincides with the axis of the container, a gate, upstream sealing membranes, a stack of resilient blades and tear-off membranes .
  • the resilient blades are preferably rectangular and are held on their periphery between upstream and downstream support frames.
  • Each elastic blade consists of several triangular petals made in a flexible and elastic thin metal plate. In their rest position, the petals are contiguous and thus obstruct the opening of the lid of the bottom of the container.
  • the grid also forms an abutment having the advantage of preventing the petals from deforming towards the interior of the container, when the plenum is overpressurized due to the propulsion gases of a neighboring missile being launched.
  • the known launcher cells are designed to receive a munition, the container and its missile, of a particular type.
  • suitable launchers for launching large missiles for example 7 meters long
  • launchers adapted to launch small missiles for example 4 meters long. If you want a ship to be able to fire small missiles and large missiles, it is necessary to equip it with two different launchers respectively dedicated to each type of missile, which is a drawback.
  • the invention therefore aims to overcome the aforementioned drawbacks by providing a means for launching small missiles from a launcher designed for large missiles and thus to make known missile launchers versatile.
  • the invention relates to a munition container adapted to be inserted into a missile launcher adapted to be shipped on a ship.
  • the container comprises a bottom provided with a plurality of resealable lids and a partitioning subdividing the container into a plurality of tubes, each tube being intended to receive a missile and each lid being opposite a tube, the container thus forming a multiple container.
  • the invention also relates to a munition comprising a plurality of missiles arranged in a multiple container such as that described above.
  • the invention therefore has the advantage of making a launcher versatile by allowing to place in a cell either a single container containing a large diameter missile or a multiple container containing several missiles of smaller diameter.
  • the screen formed by the extended downstream frame protects the neighboring lids from heat radiation and thus avoids excessive heating which could degrade the properties of the lids.
  • elasticity of the elastic blades of these neighboring operculas Therefore, maintaining their elasticity, the blades ensure a satisfactory closure of the lid.
  • the propulsion gases are channeled axially. They do not leave laterally towards the neighboring operculum. In this way, the influence of the opening of a lid on neighboring operculas is reduced.
  • the operculum is provided with a means limiting the lateral movement of the petals forming the blades.
  • the covers are very close to each other, it is then possible to simultaneously launch missiles contained in neighboring tubes, without the petals of the corresponding lids interfering with each other.
  • an open position of the petals is defined, for which the deformation at all points of the petal is controlled so that they retain their elasticity.
  • a petal whether or not locally lost its elasticity, returns to a rest position in which the cap effectively seals the bottom of the container.
  • the tip end of a triangular petal is usually plasticized because it is in the flow of hot gases.
  • the convex portion of the inner edge, on which part is supported the tip of the deformed petal allows to reach later the limit of plasticity of the material, the upstream face of the tip being in compression and not in extension.
  • the convex portion allows, when the tip is plasticized, to bend it so that it is oriented towards and applied against the gate of the lid returning to the rest position.
  • the vertical missile launcher 1 comprises several cells 2 arranged vertically in the hull 3 of a ship.
  • a cell 2 is a structure consisting of a wire mesh for receiving a munition formed of a container containing a missile or several missiles.
  • the upper part of the cell 2 is located at the deck 4 of the ship and is closed by a door 5, mounted on the deck 4, which is open when fired and then closed again.
  • the lower part of the cell 2 has an opening 10 communicating with a plenum 11.
  • the plenum 11 is common to the various cells 2 of the launcher and allows the evacuation of the propulsion gases through a chimney 12, extending vertically between the two rows of cells 2.
  • the chimney 12 opens to the upper level of the launcher, that is to say here at the bridge 4.
  • a vertical missile launcher has cells capable of receiving a munition according to the prior art consisting of a single container 15 in which is disposed a single missile 16 of large diameter (cf. Figure 1 ) or a multiple container 17 in which are disposed a plurality of missiles 18 of smaller diameter and shorter length (cf. Figure 2 ).
  • the axis A of the single or multiple container 17 coincides with the axis of the cell.
  • the multi-container which will be described in more detail later constitutes a multiple ammunition that makes the launcher versatile.
  • the multiple container is designed to receive missiles of reduced size so that the outer dimensions of the container are adapted so that it can be inserted into a cell designed to receive a large missile.
  • the single container 15 has a side wall 20, an upper end wall or cover 21 and a lower end wall or bottom 22.
  • the cover 21 is provided with an upstream cover 23.
  • the bottom 22 is provided with a downstream cover 56 which will be described in detail below.
  • the bottom 22 includes an adapter 25 adapted to be inserted into the opening 10 of the plenum 11 during the loading of the single munition so that the gases leaving the single container 15 during the launch of the missile 16 are guided in the plenum 11.
  • the cell 2 receives a multi-container 17.
  • the multi-container 17 has transverse external dimensions that exactly correspond to those of the simple container 15.
  • the container 17 is provided with an interior cross-section 50 of cross-section which subdivides the container 17 in four independent tubes 51.
  • On the figure 2 only an axial partition 52 separating two tubes 51a and 51b is seen.
  • the lid 53 of the multi-container 17 comprises a plurality of upstream lids 54 so that the upstream end of each tube 51 is provided with an upstream lid 54.
  • the bottom 55 of the multi-container 17 comprises a plurality of downstream lids 56 so that each tube 51 is provided with a deformable downstream cap 56 which will be described in detail below.
  • Each tube 51 receives a missile 18 of small size placed along the axis B of the tube 51, parallel to the main axis A of the container 17.
  • the propellant gases flowing through the bottom 55 of the container 17 are guided in the plenum 11 by an adapter 57.
  • the container 17 being shorter in length than the single container 15, the multiple container adapter is more long than the simple container adapter.
  • the nozzle of the missile 18 is placed slightly upstream of the bottom 55 of the container, close to it (about 10 cm).
  • the bottom 55 of the multiple container according to the invention is equipped, on the downstream side of the container, with thermal protection means intended to protect each cap of the radiation resulting from the gases escaping through a neighboring lid when firing a missile. Cala prevents the alteration of elastic properties elastic blades of the caps under the effect of hot gases whose temperature is of the order of 3000 ° C in the center of the flame.
  • thermal protection means consist of a tip portion provided on the outer wall of the bottom 55 of the multiple container 17. This tip portion, disposed in the extension of the internal partition 50, serves as a heat shield between the different opercules 56 of the bottom 55.
  • the tip portion is made by extending a downstream support frame 64 so that it has a height H sufficient to effectively protect neighboring lids.
  • the improved deformable downstream membrane 56 comprises, superimposed along an axis of symmetry C, from the upstream (inside the container) downstream (the outside of the container). held between an upstream support frame 61 and a downstream support frame 64, a gate 62; an upstream thermal protection membrane 70; an upstream sealing membrane 71, for example made of aluminum 71; a stack of resilient blades 63; a downstream sealing membrane 73, for example made of aluminum; and, a downstream thermal protection membrane 72.
  • Each elastic blade 63 is free-form, but for practical reasons, it is preferably rectangular (cf. Figure 3 ) and the stack of elastic blades is maintained by its peripheral edge between the upstream and downstream frames 61 and 64 rectangular.
  • Each elastic blade 63 consists of four petals of triangular shape 65. Each petal 65 corresponds substantially to a portion of the blade 63 divided along its two diagonals. The edges of two petals 65 facing each other provide a space 66 in the form of a cross whose total surface is much smaller than the surface of the orifice 81 of the operculum 56, so that when the petals 65 are adjacent, it can be considered that the operculum 56 closes the bottom of the container it equips.
  • the various intermediate membranes 70, 71, 72 and 73 are in one piece. They may be provided with diagonal lines of lesser resistance corresponding to the subdivision of the blades 63 into petals 65. Thus, under the effect of the propulsion gases, these intermediate membranes 70 to 73 tear cleanly along the lines of least resistance.
  • the downstream frame 64 is of rectangular shape, in the radial plane transverse to the main axis C. It extends axially along the axis C over a height H greater than a transverse dimension D of a petal 65, corresponding about half the width of the orifice 81 of the operculum 56.
  • the cap 56 When launching the missile 18, the door 5 of the cell 2 is open. The missile 18 is then fired. The propellant gases then increase the pressure and the temperature significantly inside the tube 51. Under the effect of the pressure, the upstream cover 54 is perforated and the downstream cover 56 opens allowing the departure of the missile and the evacuation of the gases.
  • the opening of the downstream cap is effected by the action of the pressure applied to the upper or upstream surface of a blade 63 so that it deforms and deviates from its rest position, this deformation of the petals.
  • a petal 65 is deformed around an inner edge 80 of the downstream frame 64. Due to the tearing of the membranes 70-74 and the displacement of the various petals 65 of the 63 blades apart from each other, there is created a passage providing communication between the inside of the tube 51 and the plenum 11 via the adapter 57. The latter serves to receive the gas passing through the bottom 55 of the container 17 to guide them through the inlet opening 10 of the plenum 11.
  • the pressure inside the container 17 decreases. Due to their mechanical elasticity properties, the petals 65 return from a deformed position in the rest position, closing the cover 56.
  • the gate 62 forms a stop ensuring that the petals 65 easily find their rest position in which they are in a plane transverse to the axis C of the operculum and for which the space 66 is the weakest.
  • the gate 62 also allows the petals 65 do not fold towards the inside of the tube 51, when the adapter 57 is overpressure due to the propulsion gases of a missile launched from a neighboring tube.
  • the front edge 80 of the downstream frame 64 forms a screen that obscures the heat radiation emitted by the hot spots of the missile flame placed upstream of a cap, which protects the neighboring caps. This is particularly desirable because of the proximity of the covers that form the bottom of a multiple container.
  • the width of a cell being of the order of 55 cm
  • the distance separating the main axes B of two neighboring tubes is of the order of 25 cm.
  • the inner edge 80 of the downstream frame 64 defines a channel whose function is to axially guide the propulsion gases produced by the missile.
  • the edge 80 also constitutes an abutment means limiting the maximum deformation of the petals 65 of the elastic blades 63. Thus, if two missiles of the multiple container 17 are fired simultaneously, the petals 65 of two neighboring lids 51 are not likely to interfere. .
  • the inner edge 80 of the downstream frame 64 has a radially rectangular section, and axially a suitable profile. Since the flow of propellant gases directs the C axis, the edge profile 80 has a convex upstream portion 90, followed by a concave downstream portion 91. As a variant, the downstream portion 91 could be rectilinear. The upstream and downstream portions 90, 91 connect to each other tangentially.
  • the concavity of the upstream portion 90 is understood in that the center of curvature C90 of the edge profile 90 at any point P90 of this profile is located, in projection in a radial plane, outside the central orifice. 81.
  • the convexity of the downstream portion 91 means that the center of curvature C91 of the edge profile 91 at any point P91 of this profile lies, in projection in a radial plane, at Inside the central orifice 81.
  • the convexity of the upstream portion 90 is oriented towards the axis C of the cap 56 and the concavity of the downstream portion 91 is oriented towards the axis C of the cap 56.
  • the curvature at each point P of the edge profile 80 is determined in such a way that the area of the petal 65 bearing at this point P of the profile has a limited and controlled maximum deformation.
  • the downstream portion 91 of the edge 80 is concave, or at least straight, has the following advantage. It is possible that the tip 96 of the triangular petal 65, which is placed near the combustion flame produced by the missile, is plasticized. However, in the maximum deformation position, the tip 96 is supported on the concave or rectilinear downstream portion 91 which then gives it a shape having a curvature oriented towards the axis C. Thus, the plasticized tip 96 is bent towards the gate 62 , so that it is applied against it when the petal returns to the rest position. This ensures that the space 66 between the petals 65 is minimal after use.
  • the edge 80 of the downstream frame 64 is made of a material such as silicone which is both a thermal insulator and has a mechanical strength for the support of the petals.
  • a lid 156 comprises a stack of resilient blades 163a, 163b, 163c of thickness ea, eb, ec variable. More specifically, the elastic blades placed upstream of the stack have a thickness greater than those of the elastic blades placed downstream of the stack. On the Figure 5 the thicknesses ea, eb and ec of the three blades 163a, 163b and 163c shown schematically decrease progressively from upstream to downstream of the stack.
  • each blade 163a, 163b or 163c is chosen so that, when it is under stress, bearing against the inner edge 80 of the downstream support frame 64, its upstream face, facing the combustion flame, undergoes an elongation that remains compatible with the field of elasticity of the constituent metal of the blade.
  • the thickness e of the blade 163 is chosen to be less than a maximum thickness em which is higher as the radius RM of the neutral fiber f of the blade 163 is high.
  • the person skilled in the art knows how to determine the appropriate thicknesses.
  • an improved deformable downstream cap 256 comprises a stack of metal elastic strips 263 separated from each other by interlayer sheets 267 of non-metallic material resistant to temperature, adapted to facilitate the sliding of the elastic strips one on the other.
  • intermediate sliding means 267 prevents the formation of welds between two successive blades 263 and improves the sliding of these blades on one another. Thus, the reclosing movement of the lid 256 is facilitated.
  • This intermediate sheet 267 is preferably made of a thermal insulating material such as silicone, or a mat, for example glass fibers.
  • the lid closes until a sufficient partial closure. Indeed, beyond this threshold sealing, the pressure drop of the shock wave at the crossing of the partially open lid is such that it generates a force on the blades sufficient to press them against the gate and close the lid completely.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)

Claims (14)

  1. Munitionsbehälter, geeignet zum Einlegen in eine Kammer (2) einer Raketenabschusseinrichtung (1), die ausgebildet ist, auf einem Schiff mitgeführt zu werden, wobei der Behälter einen mit einer Mehrzahl von verschließbaren Deckeln (56; 156; 256) ausgerüsteten Boden (55) und eine Trennschottung (50), die den Behälter in eine Mehrzahl von Rohren (51) unterteilt, umfasst, wobei jedes Rohr dazu vorgesehen ist, eine Rakete (18) aufzunehmen und jeder Deckel gegenüberstehend zum Rohr liegt, wobei der Behälter auf diese Weise einen Mehrfachbehälter (17) bildet.
  2. Behälter nach Anspruch 1, dadurch gekennzeichnet, dass er einen Adapter (57) aufweist, der an dem Boden (55) des Behälters (17) an der Außenseite angeordnet ist, und geeignet ist, den Boden des Behälters mit einer Eingangsöffnung (10) eines Hohlraums (11) der Abschusseinrichtung (1) zu verbinden, um die Treibgase zu leiten.
  3. Behälter nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass jeder Deckel (56; 156; 256) deformierbar ist, geeignet ist, sich durch den Schub des Treibgases der in dem korrespondierenden Rohr (51) enthaltenen Rakete (18) zu öffnen und sich nach dem Auswurf der Rakete zu verschließen, wobei der Deckel ein Gitter (62) und einen Stapel aus elastischen Lamellen (63,; 163; 263), die zwischen einem stromaufwärts liegenden Trägerrahmen (61) und einem stromabwärts liegenden Trägerrahmen (64) gehalten werden, umfasst.
  4. Behälter nach Anspruch 3, dadurch gekennzeichnet, dass der Boden (55) des Behälters (17) an der stromabwärts liegenden Seite mit Wärmeschutzmitteln (64) ausgerüstet ist, die geeignet sind, jeden Deckel zu schützen, der benachbart zu dem Strom der einfallenden Wärmestrahlung liegt, der bei der Öffnung eines Deckels unter der Wirkung des Treibgases einer Rakete (18) emittiert wird.
  5. Behälter nach Anspruch 4, dadurch gekennzeichnet, dass die Wärmeschutzmittel durch ein Ansatzteil (64) des Bodens (55) des Behälter (17) gebildet wird, wobei das Ansatzteil eine Wand aufweist, die einen Wärmeschirm zwischen benachbarten Deckeln (56; 156; 256) bildet.
  6. Behälter nach Anspruch 5, dadurch gekennzeichnet, dass jeder stromabwärts liegenden Trägerrahmen (64) eine Höhe (H) aufweist, die angepasst ist, um das Ansatzteil zu bilden, das die Rolle des Wärmeschirms zwischen den benachbarten Deckeln (56; 156; 256) übernimmt.
  7. Behälter nach Anspruch 6, dadurch gekennzeichnet, dass die Höhe (H) des stromabwärts liegenden Trägerrahmens (64) größer oder gleich der Hälfte der Breite der Öffnung (81) des Deckels (56; 156; 256) ist.
  8. Behälter nach Anspruch 6 oder Anspruch 7, dadurch gekennzeichnet, dass mindestens die Außenfläche (80) des stromabwärts liegenden Trägerrahmens (64) aus einem wärmeisolierenden Material, vorzugsweise Silikon, hergestellt ist.
  9. Behälter nach einem beliebigen der Ansprüche 6 bis 8, dadurch gekennzeichnet, dass der stromabwärts liegende Trägerrahmen (64) ein Anschlagmittel bildet, das die Öffnungsbewegung der elastischen Lamellen (63; 163; 263) begrenzt.
  10. Behälter nach Anspruch 9, dadurch gekennzeichnet, dass der stromabwärts liegende Trägerrahmen (64) eines Deckels einen Innenrand (80) aufweist, der derart ausgebildet ist, dass er der Öffnung ein Anschlagmittel liefert, das eine maximale Verformungsposition der elastischen Lamelle (63; 163; 263) begrenzt.
  11. Behälter nach Anspruch 10, dadurch gekennzeichnet, dass das Profil des Innenrandes (80) des stromabwärts liegenden Trägerrahmens (64) einen konvexen stromaufwärts gelegenen Bereich (90) und einen geradlinigen oder konkaven stromabwärts gelegenen Bereich (91) aufweist, um dem freien Ende (96) der elastischen Lamelle (63) zu entsprechen.
  12. Behälter nach einem beliebigen der Ansprüche 3 bis 11, dadurch gekennzeichnet, dass zwei aufeinanderfolgende elastische Lamellen (263) eines Deckels (256) voneinander durch ein Zwischenblatt (267) aus nichtmetallischem Material, das der Wärme widersteht, getrennt sind.
  13. Behälter nach einem beliebigen der Ansprüche 3 bis 12, dadurch gekennzeichnet, dass die Dicke (e) der elastischen Lamellen (163) eines Deckels (156) sich von stromaufwärts nach stromabwärts verringert.
  14. System, umfassend einen Mehrfachbehälter nach einem der Ansprüche 1 bis 13 und eine Mehrzahl von Raketen (18), die in dem Mehrfachbehälter (17) angeordnet ist.
EP09150230.2A 2008-01-11 2009-01-08 Multipler Raketenbehälter und Vielzweckraketenabschussvorrichtung Active EP2078918B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0850159A FR2926357B1 (fr) 2008-01-11 2008-01-11 Conteneur de missile multiple et lanceur polyvalent

Publications (3)

Publication Number Publication Date
EP2078918A2 EP2078918A2 (de) 2009-07-15
EP2078918A3 EP2078918A3 (de) 2009-12-02
EP2078918B1 true EP2078918B1 (de) 2016-04-27

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EP (1) EP2078918B1 (de)
ES (1) ES2581232T3 (de)
FR (1) FR2926357B1 (de)
PL (1) PL2078918T3 (de)

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Publication number Priority date Publication date Assignee Title
RU2484408C2 (ru) * 2011-08-22 2013-06-10 Открытое акционерное общество "Центральное конструкторское бюро "Титан" Устройство для автоматического сброса и улавливания крышки транспортно-пускового контейнера, установленного на пусковой установке
RU2544265C1 (ru) * 2014-02-28 2015-03-20 Открытое акционерное общество Центральный научно-исследовательский институт специального машиностроения Огнестойкая крышка многоствольной пусковой установки
CN103913099B (zh) * 2014-03-12 2015-09-09 南京航空航天大学 整体中空复合材料发射箱盖
CN111595199B (zh) * 2020-05-14 2022-12-23 湖北三江航天万峰科技发展有限公司 一种发射箱加热控制装置
CN113074580B (zh) * 2021-04-02 2022-08-12 上海机电工程研究所 可重复大角度筒弹开关盖机构

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US4324167A (en) * 1980-04-14 1982-04-13 General Dynamics, Pomona Division Flexible area launch tube rear cover
US4686884A (en) * 1985-12-27 1987-08-18 General Dynamics, Pomona Division Gas management deflector
US4683798A (en) * 1985-12-27 1987-08-04 General Dynamics, Pomona Division Gas management transition device
FR2620808B1 (fr) 1987-09-17 1990-01-12 France Etat Armement Opercule arriere pour conteneur de missile
US5194688A (en) * 1992-01-31 1993-03-16 Hughes Missile Systems Company Apparatus for limiting recirculation of rocket exhaust gases during missile launch
US5327809A (en) * 1993-03-24 1994-07-12 Fmc Corporation Dual pack canister
US6230604B1 (en) * 1997-01-14 2001-05-15 United Defense, L.P. Concentric canister launcher
JPH11183089A (ja) * 1997-12-24 1999-07-06 Mitsubishi Electric Corp 飛しょう体の発射装置
US6125734A (en) * 1998-10-14 2000-10-03 The United States Of America As Represented By The Secretary Of The Navy Multi-warfare area launcher
JP2001124494A (ja) * 1999-10-25 2001-05-11 Mitsubishi Electric Corp 飛しょう体の発射装置

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Publication number Publication date
FR2926357A1 (fr) 2009-07-17
FR2926357B1 (fr) 2013-10-25
EP2078918A2 (de) 2009-07-15
EP2078918A3 (de) 2009-12-02
PL2078918T3 (pl) 2016-11-30
ES2581232T3 (es) 2016-09-02

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