FR2620808A1 - REAR OPERATOR FOR MISSILE CONTAINER - Google Patents

Abstract

It comprises several elements 10 which are mounted between two upper 7 and lower 8 support members, and which are liable to deform from an initial closed position by the gases produced during the firing of the missile 2, characterized in that each element 10 of the cap is elastic and deforms around at least one rounded part 19 provided on said lower member 8. Application in particular to missile containers on board warships.

Description

- 1-620808

  REAR OPERATOR FOR MISSILE CONTAINER

  The present invention relates to a rear closure

  re for missile container and more particularly for missile container embedded on warships. Warships usually include

  several missile storage and launch units

  the, each unit called module comprising a variable number of containers in each of which a missile is stored. Each container serves both

  missile storage and launch tube. Lors-

  that the missile is fired, the gases are evacuated by a gas evacuation pipe into which the lower parts of the containers open, the evacuation of gases to the atmosphere being carried out through a central chimney around which are arranged the containers of each module. In addition, each container includes means for opening the upper lid

  for the passage of the missile after firing, and the opera-

  lower limit for the passage of gases in the duct

exhaust gas.

  Missile handling means such as

  handling cranes are also planned on buildings

  warnings and are assigned to either a single module or a group of modules, usually based on

the number of module containers.

  The lower or rear lid of a container may have different structures. On the buildings of

  currently in operation, the back cover of

  content is of one piece or of several elements and is of the lost type, that is to say that it is not recovered

  or reused, for the essential reason that it is endangered

  seriously damaged by missile gas. Thus, the operculum - 2 -

2.620808

  rear of the container is open at the same time as the missile is fired, and remains open after launch

  of the missile, thus enabling permanent communication

  between the gas vent and the empty container. When firing or launching another missile stored in a nearby container, it follows that the gases of that

  other missile will come to fill the container or containers

  who communicate with each other through the evacuation

  of gases. The accumulation of gases in an empty container has the effect of creating an overpressure at the upper door of the module. Such an overpressure is more important than in the lower part

  the container is, moreover, damaging to the differences

  rents of the upper door as well

only for the adjacent container.

  Another solution would be to build a

  the lower one which would open when the missile fired, but which could close tightly after the

  departure of the missile. The door should resist the environment

  many shots. Consequently; she should be

  heavy, thick and robust which would require a motorcycle

  resulting in an important investment

  As. The present invention aims to remedy

  mentioned drawbacks and to propose a rear cover

  re or lower for missile container, non-type

  recoverable but which can close after the launch-

said missile.

  The rear cap according to the invention is of the type comprising several elements which are mounted between two

  upper and lower support organs and which are sus-

  they can deform very quickly from an initial position of closure by the gases produced during the firing of the missile, and it is characterized in that each element of the operculum is elastic and deforms around at least one rounded part arranged

on said lower member.

  Thanks to the elasticity of the elements of the lid and the rounded parts around which they deform, not only is a suitable opening of the lid obtained by the deformation of said elements between them a space sufficient for the passage of gases

  in the evacuation conduit, but also

  the elements return to their original position

closure.

  It goes without saying that the radius of curvature of the rounded portions of the support member is chosen in particular according to the desired opening for the passage of gases in the gas evacuation conduit of the module.

  - Other advantages and features apparal--

  in the other claims as well as to the

  the description of several modes of

  Preferred embodiments of the invention, as well as the accompanying drawings in which FIG. 1 is a diagrammatic representation.

  a container containing a missile and equipped with the

lower section according to the invention.

  Figure 2 is a sectional view to larger

  scale of the lower lid of the container according to

  vention. Figure 3 is a top view of the elements

elastics of the operculum.

  FIG. 4 is a view from above of a protec-

  thermal interaction between the upper and lower

  the elastic elements of the lid.

  FIG. 5 is a view from above of the operculum

  according to another embodiment of the invention.

  - 4 - Figure 6 is a larger scale section

  half of the lid shown in Figure 5.

  A missile module embarked on a warship comprises several containers (1) similar to that shown in FIG. 1, each container (1) constituting a housing and a launching tube for a missile (2), the various containers of a module being interconnected by a gas evacuation duct of which only a portion (3) is shown. Each container

  (1) is closed at the top by a top cover

  (4) which is open to the launch of the missile, and to the lower part by a lower cover generally designated by the reference (5), which is housed in a hole (6) in the lower structure

  of the module and through which the combustion gases pass

  the missile, after firing, to then be evacuated by the gas evacuation pipe (3). The means to open the upper door of the module as well

  than those of order necessary for launching and storing

  of the missile are not shown for reasons

sounds of clarity of the drawings.

  The lower lid according to the present invention

  comprises according to a first embodiment

  FIGS. 2 to 4, two upper frames (7) and

  (8), between which are arranged a set

  ble (9) of plates. The assembly (9) comprises in the center four plates (10) superimposed on each other, identical to that shown in Figure 3. Each plate 10 is constituted by four triangular elastic elements (11) made of a suitable material such as

  than spring steel, and each have a thick

  about 3/10 mm, and to have a total thickness of about 1.2 mm. The elastic elements (11) are not contiguous and form between them a space 12 between their edges, so that under the thrust of the propulsion gases of the missile, they can bend

- 5 - 2620808

  in the direction of thrust of said gases, the outer edges (13) being held firmly between the frames (7) and (8). In the example shown in FIG. 3, each plate (10) consists of distinct triangular elements (11), but it could be realized

  be in the form of a single plate presenting reas-

  or areas of lesser resistance similar to those described with respect to the plate shown in Figure 4, the goal being that each plate 10 can tear easily in appropriate places to provide a central section most effective for the passage of gases from inside the container

  (1) to the exhaust gas duct 3.

  On each side of the stack of plates (10) is

  a thin aluminum plate (14), said plates (14) opening along the lower edges (15) of

  elastic elements (11) between which is delimited the

  pace (12). On each aluminum plate (14) is glued

  a plate (16) constituting a thermal protection,

  shown in Figure 4, and which includes lines of

  least resistance (17) along which said protection

  The thermal action (16) is torn when the door is opened.

  Thermal protection is intended to preserve the

  elastic elements (11) their mechanical properties. The books

  of least resistance (17) coincide vertically - with the axes of the space 12 of the plates 10 so that

  the stack that has just been described opens up very

  in the same places and thus avoid an anarchic tearing of the different plates of the stack, which

  anarchistic rending would be detrimental to a good

  turn of said plates to their initial position

  in Figure 2, after the launch of the missile, as

it would be described later.

  A retaining grid (18) is disposed between the - 6 -

  upper frame (7) and adjacent thermal protection

  The retaining grid (18) has the function of

  fishing that the deformable and sectionable stack

  the plates (10), (14) and (16) curl upwards when they are returned to the initial position.

  the. Indeed, after the launch of the missile and the opening

  of the lower door (5) of the container (1), the elastic elements (11) could exceed the position

  after deformation because of their elasticity.

  ticity or under the pressure caused by the firing of another missile.

  Such overtaking is prevented by the grid of

  (18) who also plays the role of extra protection

  in addition to that provided by thermal protection

(16).

  The lower frame (8) has a peripheral edge

  rounded internal circle (19) around which stacking deforms

  mable and sectionable (10), (14) and (16) deforms at the opening after cutting along the edges (15) of the plates (10) and lines of least resistance

  (17) thermal protections (16). The courier radius

  of the inner peripheral edge (19) depends essentially

  the extent of the deformation desired for the

  deformable pounding or in other words the passage section for gases to the exhaust duct (3). A solution for having a small radius of curvature while ensuring a most efficient passage section for gases is to make a deformable stack of small thickness. This object is achieved by choosing elastic elements (11) with a thickness of about 0.3 mm, the plates

  of aluminum (14) and thermal protections- (16)

  both thicknesses of about 0.4 mm and 5 mm respectively.

  When cutting the stack (10), (14) and

  (16), the aluminum plates (14) are cut

  approximately along the edges (15) of the elements (11).

  Due to the high temperature of the missile-generated gases during the launch phase, the small aluminum strips protruding from the ridges (15) are

  pinned by the flames. As a result, we obtain a

  pace (12) between the elastic elements (11) perfectly clean and delimited. After deformation, the stack (10),

  (14) and (16) returns to the initial position and the

  pace (12) has a section of about 20 cm2. So,

  after launching the missile, the container (1) is fer-

  again and does not communicate with the evacuation

  of gases (6) only by the 20 cm2 section which

  corresponds to less than 5% of the total crossing section

  the one that is offered to gases. This is very important for the other containers of the module still containing the missiles. Indeed, after launching another module missile, the gases pass into the exhaust duct (6) and fill the container or containers that no longer includes missile and tend to create a sudden rise

  pressure in the empty container (s) and in particular

  at the upper door. Thanks to the space

  this (12) kept open, after recall or closure of

  the deformable stack (10), (14) and (16), the circulating gases

  in the evacuation pipe (3) are completely filtered during their passage through the empty container,

  while ensuring a flow of said gases in the con-

  discharge duct (3) of the order of 99%. As a result

  this, there is no need to oversize the containers as is done in the containers of the prior art, the lower lid remains fully

opened after launching the missile.

  Another embodiment of the invention (FIG.

  5 and 6) consists of using support members (50) (51) in the form of bars whose lower bar (51) is rounded. The lid (53) is constituted by one or two elements (54) (55), said lid being fixed

  move the two bars (50) (51). The structure of the opera-

  cule is shown in Figure 6 and includes the same

  component parts that the seal shown on the

  2, the references in the figure being assigned a

index a.

  Of course, the invention is not limited to the embodiments described and shown, it is capable of many variants accessible to those skilled in the art depending on the intended applications, without departing from the scope of the invention. By changing the shape and the number of constituent elements of the lid, it can adapt the latter to the exhaust duct to allow automatic opening of the latter in

  the case of an untimely fire of one of the missiles.

9-2620808

Claims (19)

  1.- Rear door for container of mis-   of the type comprising several elements (10) which are mounted between two upper support members (7) and lower (8) and which are likely to deform from an initial position of closure-by the gases produced during the setting fire of the missile (2), characterized in that each element (10) of the lid is elastic and deforms around at least a rounded portion (19)   arranged on said lower member (8).   2. The cap according to claim 4, characterized   characterized in that the elasticity of each element (10) and the radius of curvature of the rounded portion (19) of the frame   (8) are such that said elements (11) are   to their closed position after deformation.   3. Opercule according to one of the claims   1 or 2, characterized in that a space (13) is provided   between the inner edges (15) of said elements.   4. Opercule according to one of the claims   1 to 3, characterized in that each element (11) is of triangular shape.   5. Opercule according to one of the claims   1 to 4, characterized in that each element (11) is constituted by a set of several glued plates and   superimposed on each other.   6. Seal according to claim 5, characterized   characterized in that each plate of an element is made of spring steel and has a thickness of about 0.3 mm. - 10 - 2620808   7. Opercule according to one of the claims   1 to 6, characterized in that a thin aluminum plate   nium (14) is glued on the inner and outer faces of the elements, as well as the space between said elements.   8. A seal according to one of the claims   1 to 7, characterized in that at least one thermal protection (16) is arranged on the upper face of the elements of the operculum.   9. Opercule according to one of the claims   1 to 7, characterized in that two thermal protections (16) are arranged on the upper and lower faces elements of said operculum.   10. Opercule according to one of the claims   i to 9, characterized in that a retaining grid (18)   disposed between the upper frame (7) and the said ele- operculum.   11. Opercule according to one of the claims   8 or 9, characterized in that the thermal protection (16) comprises lines of least resistance (17) the   along which it can be cut.   12. The seal according to claims 3 and   11, characterized in that the lines of least resistance   17 are provided above the household space (13). between the elements (11).   13. The seal according to claim 3 or   12, characterized in that said space (13) has a   section less than 5% of the total passage section. - 11 - 2620808   14. The cap according to claim 7, characterized   in that the thickness of each aluminum plate nium is about 0.4 mm.   * 15.- Opercule according to claims 8, 9   or 10, characterized in that the thickness of the protection   The thermal density is approximately 5 mm.   16. A seal according to claims 3 to   9, characterized in that the triangular elements, the aluminum plates and the thermal protection are interposed between them and constitute a deformable and sectionable stack.   17. The cap according to claim 1, characterized   characterized in that the support members are constituted by two bars (50, 51) between which are arranged   the elastic elements (54, 55) of the lid.   18. The cap according to claim 16, characterized   characterized in that the elastic elements of the lid are constituted by a plate (53) which deforms in its middle.   19. The cap according to claim 16, characterized   characterized in that the elastic elements of the lid are constituted by two stacks inserted by one of their   edges between the support bars (50, 51).