ES2581232T3 - Multiple missile container and multi-purpose launcher - Google Patents

Abstract

Ammunition container suitable for insertion into an alveolus (2) of a missile launcher (1) adapted to be shipped on a ship, the bottom container (55) provided with a plurality of recerrable operculums (56; 156; 256) and a compartmentalization (50) that subdivides the container into a plurality of tubes (51), each tube being destined to receive a missile (18) and each operculum being in front of a tube, said container thus forming a multiple container (17) .

Description

DESCRIPTION

Multiple missile container and multipurpose launcher 5 [0001] The present invention relates to missile containers.

[0002] A missile launcher adapted to ship it in a ship consisting of a series of alveoli is known, each socket being destined to receive a munition consisting of a missile placed in a container. The upper part of a socket ends at the level of the bridge of the ship and is closed, outside the phases of

10 launch, by a door. The lower part of an alveolus consists of an opening that flows into a buffer chamber or impeller chamber intended to receive the gases emitted during the launch of a missile. The impending chamber, common to the different alveoli, is equipped with a gas extraction chimney.

[0003] A munition is formed by a missile placed inside a container. The upper and lower portions of the container 15 are sealed tightly, respectively by a lid provided with an opercle.

upstream and by a bottom endowed with an opercle downstream. The interior volume of the container is, in general, filled with an inert gas in overpressure with respect 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 socket and the impeller chamber. The ammunition is inserted from above into a socket of the launcher, the bottom of the container 20 being then placed in fluid communication with the impending chamber by means of the adapter.

[0004] During the launch of the missile, with the door of the socket previously open, the missile is turned on. The propulsion gases then increase the pressure and temperature significantly inside the container, which perforates the opercle upstream of the container and opens the opercle downstream. The

The communication of the interior of the container with the impeller chamber by means of the adapter allows the evacuation of the propulsion gases in the impeller chamber, then its extraction by means of the chimney. After the shot, the alveolus doors close again.

[0005] When the downstream opercle opens, the propulsion gases that are hot and for which the speed of sound is of the order of 1000 m / s, meet the gases present in the chamber

It is imperative that they are cold and for which the speed of sound is of the order of 300 m / s. This results in a shock wave regime at the interface between the hot and cold gas masses. This phenomenon lasts between 100 and 150 ms, at which time the cold gases propagate outside the impending chamber through the extraction chimney, and translates into a sharp increase in temperature and pressure in the impending chamber, during ignition. of a 35 missile.

[0006] When a missile has been fired and the container containing it is empty, the firing of a missile contained in a neighboring container generates a high pressure and high temperature gas production that could penetrate from the impending chamber into the empty container and, due to this, deteriorate the socket door

40 corresponding. To prevent this from happening, it is necessary that the opercle downstream of the empty container be closed again to prevent the shock wave and the propulsion gases present in the impending chamber from penetrating into this empty container.

[0007] To this end, it has been proposed, specifically in document FR 2 620 808, a deformable opercle 45 that opens at the time of launching a missile and closes again afterwards. This deformable opercle

It consists of, superimposed axially along a main axis of symmetry, which coincides with the axis of the container, a grid, tear-off upstream sealing membranes, a stack of elastic sheets and tear-down downstream sealing membranes. The elastic sheets are preferably rectangular and are supported by their periphery between upstream and downstream support frames. Each elastic sheet is made up of several triangular petals made of a thin flexible and elastic metal plate. In their resting position, the petals are attached and thus obstruct the hole in the opercle of the bottom of the container.

[0008] When the propulsion gases are expelled from the missile, an overpressure tears the sealing membranes and deforms the petals by bending around a rounded inner edge of the frame.

55 lower support. The edges of the petals separate from each other and create a passage that communicates the interior of the container and the impellent chamber through the adapter. Once the missile is fired, the pressure inside the container decreases. The petals elastically return to their resting position, butt against the grid, and close the opercle hole again.

[0009] The grid also forms a stop which has the advantage of preventing the petals from deforming towards the

inside the container, when the impeller chamber is under pressure due to the propulsion gases of a neighboring missile in the process of launching.

5 [0010] These deformable opercles with elastic sheets adapted for container closure intended

to receive a missile, they have the inconvenience of closing again imperfectly after utilization.

[0011] On the other hand, the alveoli of known launchers are designed to receive a munition, the

container and its missile, of a particular type. In this way, there are launchers adapted to launch large-sized missiles, for example 7 meters long, and there are launchers adapted to launch small-sized missiles, for example 4 meters long. If you want a ship to be able to fire small-sized missiles and large-sized missiles, it is necessary to equip it with two different launchers dedicated respectively to each type of missile, which is inconvenient.

[0012] The invention is therefore intended to remedy the aforementioned drawbacks.

proposing a means that allows small missiles to be launched from a launcher designed for large missiles and thus make known missile launchers versatile.

[0013] For this purpose, the invention aims at a container of ammunition suitable for insertion into a

20 missile launchers adapted to embark on a ship. The container consists of a bottom provided with a plurality of recerrable opercles and a compartmentalisation that subdivides the container into a plurality of tubes, each tube being destined to receive a missile and each opercle being in front of a tube, thus forming the container a multiple container

[0014] According to particular embodiments of the invention, the multiple container consists of one or more of the

following characteristics, taken in isolation or according to all the technically possible combinations:

- the container consists of an adapter arranged on the bottom of the container, on the outer side, suitable for connecting the bottom of the container to an inlet opening of an impellent chamber of the launcher to guide the

30 propulsion gases.

- each opercle is of the deformable type, suitable for opening under the thrust of the missile propulsion gases contained in the corresponding tube and for closing again after the expulsion of the missile, the opercle comprising a grid and a stack of sustained elastic sheets between an upstream support frame and a downstream support frame.

35 - the bottom of the container is provided, on the downstream side, with thermal protection means capable of protecting each neighboring opercle from the incident thermal radiation flow emitted during the opening of an operculum under the effect of missile propulsion gases .

- the thermal protection means are constituted by a splice part of the bottom of the container, the splice part consisting of a wall forming a thermal screen between neighboring opercles.

40 - each support frame downstream has a height adapted to constitute said splice part that plays the role of thermal screen between neighboring opercles.

- the height of the downstream support frame is greater than or equal to half the width of the opercle hole.

- at least the external surface of the downstream support frame is made of a thermal insulating material, preferably silicone.

45 - the downstream support frame forms a stop means that limits the opening movement of the elastic sheets.

- the support frame downstream of an opercle consists of a profiled inner edge to provide the operculum with a stop means defining a maximum deformation position of the elastic sheets.

- the profile of said inner edge of the downstream support frame consists of a convex upstream part and a straight or concave downstream part to form the free end of the elastic sheet.

- two successive elastic sheets of an opercle are separated from each other by a separating sheet of heat-resistant non-metallic material.

- The thickness of the elastic sheets of an opercle decreases from upstream to downstream.

55 [0015] The object of the invention is also an ammunition consisting of a plurality of missiles

arranged in a multiple container, as described above.

[0016] The invention therefore has the advantage of making a launcher versatile, allowing to place,

in a socket a simple container that contains a large diameter missile, or a multiple container that

It contains several missiles of smaller diameter.

[0017] For the realization of a plurality of operculos at the bottom of a multiple container, the screen forming the prolonged downstream frame protects the neighboring opercles from thermal radiation and avoids, from this

Thus, excessive heating that could degrade the elastic properties of the elastic sheets of these neighboring opercles. Due to this, while maintaining its elasticity, the sheets guarantee a satisfactory closure of the opercle again. In addition, by extending the frame downstream by a sufficient height, the propulsion gases are axially channeled. They do not leave laterally in the direction of neighboring opercles. In this way, the influence from the opening of an opercle on the neighboring opercles is reduced.

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[0018] More advantageously, by prolonging the inner edge of the frame downstream, the opercle is provided with a means that limits the lateral displacement of the petals that form the sheets. As, for a multiple container, the opercles are very close to each other, it is then possible to simultaneously launch missiles contained in neighboring tubes, without the petals of the corresponding opercles interfering with each other.

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[0019] Advantageously, by providing the inner edge of the frame downstream with an adapted profile, an open position of the petals is defined, for which the deformation at any point of the petal is controlled so that they retain their elasticity.

[0020] In addition, a petal, whether or not it has locally lost its elasticity, returns to a resting position in

which the operculo effectively seals the bottom of the container. In fact, the tip end of a triangular petal is generally plasticized, since it is located in the flow of hot gases. The convex part of the inner edge, part on which the tip of the deformed petal rests, allows the plasticity limit of the material to be reached later, the face being upstream of the tip in compression and not in extension. In addition, the convex part 25 allows, when the tip is plasticized, to bend it so that it is oriented towards, and applied against, the grid of the opercle when returning to the resting position.

[0021] The invention and its advantages will be better understood by reading the description a continuation, given

only by way of example, and made referring to the attached drawings, in which:

30

- Figure 1 is a schematic representation of a simple container inserted in a socket of a vertical missile launcher;

- Figure 2 is a schematic representation of a multiple container inserted in the socket of the launcher of Figure 1;

35 - Figure 3 is a sectional representation of the multiple container of Figure 2;

- Figure 4 is an representation in axial section of the opercle according to the invention that equips the bottom of a container and consisting of a prolonged downstream frame with a profiled inner edge;

- Figure 5 is a sectional representation of a first variant of the opercle embodiment according to the invention consisting of sliding separator blades of one petal over another, in an opening position (half view

40 left) and in a closed position (right half view); Y,

- Figure 6 is a sectional representation of a second variant of the embodiment of the opercle according to the invention consisting of sheets of variable thickness, in an opening position (left half view) and in a closing position (right half view).

[0022] In Figures 1 and 2, the vertical missile launcher 1 consists of several arranged alveoli 2

vertically in hull 3 of a ship. A socket 2 is a structure constituted by a metal frame intended to receive a munition formed by a container containing a missile or several missiles. The upper part of the socket 2 is located at the level of the bridge 4 of the ship and is closed by a door 5, mounted on the bridge 4, which opens during firing and then closes again. The lower part of the socket 2 consists of an opening 50 10 for communicating with an impeller chamber 11. The impellent chamber 11 is common to the different alveoli 2 of the launcher and allows the evacuation of the propulsion gases through a chimney 12, which extends vertically between the two rows of alveoli 2. The chimney 12 ends at the upper level of the pitcher, that is to say in this case at the level of the bridge 4.

[0023] A vertical missile launcher consists of alveoli suitable for receiving ammunition according to the technique

above constituted by a simple container 15 in which a single missile 16 of large diameter is arranged (see Figure 1) or by a multiple container 17 in which a plurality of missiles 18 of smaller and smaller lengths are arranged ( see figure 2). In position inserted in socket 2, axis A of single container 15 or multiple 17 coincides with axis of socket. The multiple container that will be described in more detail

later, it constitutes a multiple ammunition that allows to make the versatile launcher. For this, 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 socket designed to receive a large-sized missile.

5

[0024] In Figure 1, the simple container 15 consists of a side wall 20, a top end wall or lid 21 and a bottom end wall or bottom 22. The lid 21 is provided with an upstream opercle 23. The bottom 22 is provided with an opercle downstream 56 which will be described in detail below. On the outer side, the bottom 22 consists of an adapter 25 suitable for insertion into the opening 10 of the impeller chamber 11 during the

10 loading of the simple ammunition, so that the gases leaving the simple container 15 during the launch of the missile 16 are guided into the impeller chamber 11.

[0025] In Figures 2 and 3, the socket 2 receives a multiple container 17. The multiple container 17 has transverse outer dimensions that correspond exactly to those of the single container 15. The container

15 17 is provided with a cross-sectional interior compartment 50 that subdivides the container 17 into four independent tubes 51. In Figure 2, only an axial partition 52 is seen separating two tubes 51a and 51b. The lid 53 of the multiple container 17 consists of a plurality of upstream opercles 54 such that the upstream end of each tube 51 is provided with an upstream opercle 54. The bottom 55 of the multiple container 17 consists of a plurality of opercles. downstream 56 so that each tube 51 is provided with a deformable downstream opercle 56 which will be described in detail below. Each tube 51 receives a small size missile 18 placed along the axis B of the tube 51, parallel to the main axis A of the container 17.

[0026] The propulsion gases flowing through the bottom 55 of the container 17 are guided into the impeller chamber 11 by an adapter 57. The container 17 being shorter in length than the container

25 simple 15, the multiple container adapter is longer than the simple container adapter.

[0027] The nozzle of the missile 18 is placed slightly upstream from the bottom 55 of the container, in the vicinity of the latter (about 10 cm).

[0028] 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 opercle from radiation resulting from the gases that escape through a neighboring opercle during the firing of a missile. This allows to avoid the alteration of the elastic properties of the elastic sheets of the opercles under the effect of hot gases whose temperature is of the order of 3000 ° C in the center of the flame.

35

[0029] These thermal protection means are constituted by a splice part provided on the wall

exterior of the bottom 55 of the multiple container 17. This splicing part, arranged in the extension of the internal compartmentalization 50, serves as a thermal screen between the different operculars 56 of the bottom 55.

[0030] In an embodiment shown in Figure 4, the splicing part is made by extending a frame

of downstream support 64 so that it has a height H sufficient to effectively protect neighboring opercles.

[0031] In this figure, the improved deformable downstream opercle 56 according to the invention consists of 45 superimposed along a symmetry axis C, from upstream (inside the container) to downstream (the

outside the container), held between an upstream support frame 61 and a downstream support frame 64, a grid 62; a thermal protection upstream membrane 70; an upstream sealing membrane 71 for example of aluminum 71; a stack of elastic sheets 63; a downstream sealing membrane 73 for example of aluminum; and, a thermal protection downstream membrane 72.

fifty

[0032] Each elastic sheet 63 is free-form, but for practical reasons, it is preferably rectangular (see Figure 3) and the stacking of elastic sheets is supported by its peripheral edge between the upstream and downstream frames 61 and 64 rectangular. Each elastic sheet 63 is composed of four triangular shaped petals 65. Each petal 65 corresponds practically to a part of the sheet 63

55 divided according to its two diagonals. The edges of two petals 65 facing each other create a cross-shaped space 66 whose total area is much smaller than the surface of hole 81 of opercle 56, so that, when the petals 65 are adjacent, it can be considered that the operculo 56 seals the bottom of the container it equips.

[0033] Before the opening of opercle 56, the different intermediate membranes 70, 71, 72 and 73 are of

only one piece. These can be provided with diagonal lines of lower resistance corresponding to the subdivision of the sheets 63 in petals 65. In this way, under the effect of the propulsion gases, these intermediate membranes 70 to 73 are torn cleanly along the lines of least resistance.

5 [0034] The downstream frame 64 is rectangular in the radial plane transverse to the main axis C. It

extends axially along the axis C for a height H greater than a transverse dimension D of a petal 65, corresponding to approximately half the width of the hole 81 of the opercle 56.

[0035] The operation of opercle 56 will be described below when it equips the bottom of a tube 10 of the multiple container of Figure 2, the axis C of the opercle then coinciding with the axis B of a tube 51.

During the launch of the missile 18, the door 5 of the socket 2 is open. Missile 18 is then turned on. The propulsion gases then increase the pressure and temperature significantly inside the tube 51. Under the effect of the pressure, the upstream opercle 54 is perforated and the downstream opercle 56 opens, which allows the exit of the missile and the evacuation of the gases. The opening of the downstream opercle is performed by the action of the pressure applied on the upper surface or upstream of a sheet 63, so that it deforms and moves away from its resting position, this deformation of the petals being accompanied by tearing the sealing and thermal protection membranes 71 to 74. A petal 65 deforms around an inner edge 80 of the downstream frame 64. Due to the tearing of the membranes 70-74 and the displacement of the different petals 65 of the sheets 63 one away from the other, a passage is created that guarantees a communication 20 between the inside of the tube 51 and the impellent chamber 11 by means of the adapter 57. The latter serves to receive the gases that pass through the bottom 55 of the container 17 to guide them through the inlet opening 10 of the impeller chamber 11.

[0036] Once the missile 18 has been fired, the pressure inside the container 17 decreases. Due to its 25 mechanical properties of elasticity, the petals 65 return from a deformed position to the resting position,

closing opercle 56 again. The grid 62 forms a stop which ensures that the petals 65 easily recover their resting position in which they are in a plane transverse to the C axis of the opercle and for which the space 66 is the smallest. The grid 62 also allows the petals 65 not to fold back into the tube 51, when the adapter 57 is in overpressure due to the propulsion gases of a missile launched from a neighboring tube.

30

[0037] The leading edge 80 of the downstream frame 64 forms a screen that hides the thermal radiation emitted by the hot spots of the missile flame placed upstream of an opercle, which protects the neighboring opercles. This is particularly desirable due to the proximity of the opercles that form the bottom of a multiple container. For example, being the width of a socket of the order of 55 cm, the distance that separates the

35 main axes B of two neighboring tubes is of the order of 25 cm.

[0038] The inner edge 80 of the downstream frame 64 delimits a channel whose function is to axially guide the propulsion gases produced by the missile. The hot gases, axially channeled, move quickly away from the bottom 55 of the container and no longer split laterally in the direction of a neighboring opercle.

40

[0039] In this way, the effects of firing a missile on neighboring opercles are strongly reduced and the deformable sheets of these opercles retain their elasticity and guarantee a more efficient sealing of the tubes after use.

[0040] The edge 80 also constitutes a stop means that limits the maximum deformation of the petals 65

of the elastic sheets 63. Thus, if two missiles of the multiple container 17 are ignited simultaneously, there is no risk that the petals 65 of two neighboring opercles 51 interfere.

[0041] Advantageously, the inner edge 80 of the downstream frame 64 radially has a section

50 rectangular, and axially an adapted profile. By orienting the flow of the propulsion gases on the C axis, the edge profile 80 consists of a convex upstream part 90, followed by a concave downstream portion 91. As a variant, the downstream part 91 could be straight. The upstream and downstream parts 90, 91 connect to each other tangently.

[0042] The concavity of the upstream part 90 is interpreted considering that the center of curvature C90

of the edge profile 90 at any point P90 of this profile is projected on a radial plane outside the central hole 81. Similarly, the convexity of the downstream part 91 is interpreted considering that the center of curvature C91 of the edge profile 91 at any point P91 of this profile is projected in a radial plane, inside the central hole 81. Thus, the convexity of the part

upstream 90 is oriented towards the C axis of opercle 56 and the concavity of the downstream part 91 is oriented towards the C axis of operculo 56.

[0043] The curvature at each point P of the edge profile 80 is determined so that the area of the petal 65 5 that rests on this point P of the profile has a limited and controlled maximum deformation. Forming the profile of

edge 80 so that the absolute value of the curvature remains less than a threshold value, it is ensured that the local deformation of the constituent material of the petals 65 remains less than a threshold deformation beyond which the material acquires a permanent deformation . This ensures that each petal 65 retains its elasticity and effectively returns to its resting position.

10

[0044] The fact that 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 in the immediate vicinity of the combustion flame produced by the missile, is plasticized. Now, in the position of maximum deformation, the tip 96 rests on the downstream part 91 concave or rectilinear which then gives it a shape that has

15 a curvature oriented towards the C axis. Thus, the plasticized tip 96 is curved towards the grid 62, so that it is applied against it when the petal returns to the resting position. In this way, it is guaranteed that the space 66 between the petals 65 is minimal after use.

[0045] Advantageously, the edge 80 of the downstream frame 64, is constituted by a material such as silicone which is both a thermal insulator and has a mechanical resistance to support the petals.

[0046] In an embodiment variant shown in Figure 5, an operculum 156 consists of a stack of elastic sheets 163a, 163b, 163c of thickness ea, eb, ec variable. More precisely, the elastic sheets placed upstream of the stack are thicker than those of the elastic sheets placed waters

25 down the stack. In Figure 5, the thicknesses ea, eb and ec of the three sheets 163a, 163b and 163c shown schematically decrease progressively from upstream to downstream of the stack. The thickness of each sheet 163a, 163b or 163c is selected so that, when under tension, resting against the inner edge 80 of the downstream support frame 64, its upstream face, oriented towards the combustion flame, undergoes an elongation which is still compatible with the scope of elasticity of the metal constituting the sheet.

[0047] Thus, if the upstream part 90 of the edge 80 is rounded to present a center of curvature O, the thickness e of the sheet 163 is selected to be less than a maximum thickness em which is much higher the more high is the RM radius of the neutral fiber f of the sheet 163. The person skilled in the art knows

35 determine the appropriate thicknesses.

[0048] In another variant embodiment shown in Figure 6, an improved deformable downstream opercle 256 consists of a stack of metallic elastic sheets 263 separated from each other by separating sheets 267 of temperature-resistant non-metallic material, adapted to facilitate the slip of the

40 elastic sheets one over another.

[0049] By providing opercle 256 with sliding separating means 267, the formation of welds between two successive sheets 263 is prevented and the sliding of these sheets on one another is improved. In this way, the closing movement of opercle 256 is again facilitated.

Four. Five

[0050] Secondly, by inserting a sheet 267 of a non-metallic material into the interface between two adjacent metal sheets 263 the heat conduction from one sheet to another is limited. Thus, even if the temperature of the propulsion gases entails a plasticization of an upstream sheet, the heat of this sheet is only partially transmitted to the next downstream sheet which, consequently, is heated

50 less and better retains its elasticity. It follows that the sheets downstream of the stack retain their elastic properties well after the opening of opercle 256 and participate in its closing again, pushing the sheets upstream, possibly plasticized, towards the grid 62. The sealing of the opercle 256 improves in this way.

[0051] This separator sheet 267 is preferably of a thermal insulating material such as silicone, or a

felt, for example of glass fibers.

[0052] The variants of embodiment just described, which improve each of the conditions of

elastic return of the elastic sheets to guarantee the closing of the opercle again. The subject matter expert

You will understand that these different means are complementary and can be combined as necessary.

[0053] It should be noted that it is sufficient that the opercle be closed again to a sufficient partial seal. In

In effect, beyond this threshold seal, the loss of charge of the shock wave when passing through the half-open opercle 5 is such that it generates sufficient force on the sheets to support them against the grid and thus completely close the opercle.

Claims (12)

1. Ammunition container suitable for insertion into a socket (2) of a missile launcher (1) adapted to be shipped on a ship, the bottom container (55) provided with a plurality of opercles. 5 recerrables (56; 156; 256) and a compartment (50) that subdivides the container into a plurality of tubes (51), each tube being destined to receive a missile (18) and each opercle being in front of a tube, forming said container thus a multiple container (17). 2. Container according to claim 1, characterized in that it consists of an adapter (57) arranged 10 on the bottom (55) of the container (17), on the outer side, suitable for connecting the bottom of the container to a inlet opening (10) of an impeller chamber (11) of the launcher (1) to guide the propulsion gases. 3. Container according to claim 1 or claim 2, characterized in that each opercle (56; 156; 256) is of the deformable type, suitable for opening under the thrust of the missile propulsion gases (18) 15 contained in the corresponding tube (51) and to close again after the expulsion of the missile, the opercle comprising a grid (62) and a stack of elastic sheets (63; 163; 263) held between an upstream support frame (61) and a downstream support frame (64). 4. Container according to claim 3, characterized in that the bottom (55) of the container (17) is provided, on the downstream side, with thermal protection means (64) capable of protecting each opercle close to the incident thermal radiation flow emitted during the opening of an opercle under the effect of the missile propulsion gases (18). 5. Container according to claim 4, characterized in that the thermal protection means are constituted by a splice part (64) of the bottom (55) of the container (17), the splice part consisting of a wall that forms a thermal screen between opercles (56; 156; 256) neighbors. 6. Container according to claim 5, characterized in that each downstream support frame (64) has a height (H) adapted to constitute said splice part that plays the role of thermal screen between 30 operculos (56; 156; 256) neighbors. 7. Container according to claim 6, characterized in that the height (H) of the downstream support frame (64) is greater than or equal to half the width of the hole (81) of the opercle (56; 156; 256). 35 8. Container according to claim 6 or claim 7, characterized in that at least the External surface (80) of the downstream support frame (64) is made of a thermal insulating material, preferably silicone. 9. Container according to any one of claims 6 to 8, characterized in that the downstream support frame (64) forms a stop means that limits the opening movement of the elastic sheets (63; 163; 263). 10. Container according to claim 9, characterized in that the downstream support frame (64) of an opercle consists of an inner edge (80) profiled to provide the opercle with a stop means defining a 45 position of maximum deformation of the elastic sheets (63; 163; 263). 11. Container according to claim 10, characterized in that the profile of said inner edge (80) of the downstream support frame (64) consists of a convex upstream part (90) and a rectilinear or concave downstream part (91) for forming the free end (96) of the elastic sheet (63). fifty 12. Container according to any one of claims 3 to 11, characterized in that two successive elastic sheets (263) of an opercle (256) are separated from each other by a separating sheet (267) of heat-resistant non-metallic material. 13. Container according to any one of claims 3 to 12, characterized in that the thickness (e) of the elastic sheets (163) of an opercle (156) decreases from upstream to downstream. 14. System consisting of a multiple container (17) according to any one of claims 1 to 13 and a plurality of missiles (18) arranged in said multiple container (17).