EP0308344B1 - Opercule arrière pour conteneur de missile - Google Patents

Opercule arrière pour conteneur de missile Download PDF

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Publication number
EP0308344B1
EP0308344B1 EP88402343A EP88402343A EP0308344B1 EP 0308344 B1 EP0308344 B1 EP 0308344B1 EP 88402343 A EP88402343 A EP 88402343A EP 88402343 A EP88402343 A EP 88402343A EP 0308344 B1 EP0308344 B1 EP 0308344B1
Authority
EP
European Patent Office
Prior art keywords
fact
door according
door
plates
plate
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
Application number
EP88402343A
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German (de)
English (en)
French (fr)
Other versions
EP0308344A1 (fr
Inventor
Pierre-Jacques Truyman
Michel Bouron
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Direction General pour lArmement DGA
Original Assignee
Direction General pour lArmement DGA
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Filing date
Publication date
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Application granted granted Critical
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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

Definitions

  • the present invention relates to a rear cover for a missile container and more particularly for a missile container on board warships.
  • Warships generally include several units for storing and launching missiles, each unit called a module comprising a variable number of containers in each of which a missile is stored. Each container is used both for storing the missile and as a launch tube. When the missile is fired, the gases are evacuated by a gas evacuation conduit into which the lower parts of the containers open, the evacuation of the gases to the atmosphere being carried out through a central chimney around which are arranged the containers of each module.
  • each container comprises means suitable for opening the upper cover for the passage of the missile after firing, and the lower cover for the passage of gases in the gas evacuation duct.
  • Missile handling means such as handling cranes are also provided on warships and are assigned either to a single module or to a group of modules and this, generally according to the number of module containers.
  • the lower or rear lid of a container can have different structures.
  • the rear container lid On warships currently in service, the rear container lid is in one piece or in several elements and is of the lost type, that is to say that it is not recovered or reused, to the main reason that it is badly damaged by missile gas. So the seal rear of the container is therefore opened at the same time as the missile is fired, and remains open after launching the missile, thus permitting permanent communication between the gas evacuation pipe and the empty container.
  • the gases of this other missile will come to fill the empty container or containers which communicate with each other through the gas evacuation duct.
  • the accumulation of gases in an empty container has the effect of creating an overpressure at the level of the upper door of the module. Such an overpressure which is greater than in the lower part of the container is, moreover, damaging for the various seals of the upper door as well as for the adjacent container.
  • Another solution would be to mount a lower door which would open when the missile was fired, but which could close tightly after the missile had left.
  • the door should withstand the environment of many shots. Consequently, it should be heavy, thick and robust, which would require a motorization, thereby entailing a significant investment.
  • the present invention aims to remedy the aforementioned drawbacks and to provide a rear or lower cover for a missile container, of the non-recoverable type but which can be closed after the launch of said missile.
  • the rear cover according to the invention is of the type according to the preamble of claim 1 and representing the state of the art according to Article 54 (2) of the EPC comprising several plates which are mounted between two upper and lower supports and which are liable to deform very quickly from an initial closed position by the gases produced during the firing of the missile, and it is characterized in that that each plate of the cover is elastic and deforms around at least one rounded part formed on said lower support.
  • the radius of curvature of the rounded parts of the support is chosen in particular as a function of the opening which it is desired to provide for the passage of gases in the gas evacuation duct of the module.
  • Figure 1 is a schematic representation of a container containing a missile and provided with the lower cover according to the invention.
  • Figure 2 is an enlarged sectional view of the lower lid of the container according to the invention.
  • Figure 3 is a top view of the elastic plates of the cover.
  • Figure 4 is a top view of a thermal protection interposed between the upper support and the elastic plates of the cover.
  • Figure 5 is a top view of the cover according to another embodiment of the invention.
  • FIG. 6 is a section on a larger scale of half of the cover shown in FIG. 5.
  • a missile module on board a warship comprises several containers (1) similar to that shown in FIG. 1, each container (1) constituting a housing and a launch tube for a missile (2), the various containers a module being interconnected by a gas discharge conduit of which only a part (3) is shown.
  • Each container (1) is closed at the upper part by an upper cover (4) which is open when the missile is launched, and at the lower part by a lower cover designated as a whole by the reference (5), which is housed in an orifice (6) formed in the lower structure of the module and through which the combustion gases of the missile pass, after firing, to then be evacuated by the gas evacuation pipe (3).
  • the means for opening the upper door of the module as well as the control means necessary for launching and storing the missile are not shown for the sake of clarity of the drawings.
  • the lower cover according to the present invention comprises, according to a first embodiment shown in FIGS. 2 to 4, two upper (7) and lower (8) supports, between which are arranged a set (9) of plates as shown in the FIG. 3.
  • Each plate (11) consists of a stack of triangular elastic sheets (10) made of an appropriate material such as spring steel, and each has a thickness of approximately 3/10 mm, and this, to have a total thickness of about 1.2 mm.
  • the plates (11) are not contiguous and provide between them a space (12) between their edges, so that under the thrust of the missile propellants, they can bend in the thrust direction of said gases, the outer edges (13) being held firmly between the supports (7) and (8).
  • FIG. 1 In the example shown in FIG.
  • the cover comprises four triangular plates (11), but this set of plates (11) could be replaced by a single plate having grooves or zones of lower resistance similar to those which will be described in connection with the plate shown in FIG. 4, the aim being that the cover can be easily torn in appropriate places in order to provide a most efficient central section for the passage of gases from inside the container (1 ) to the gas exhaust pipe (3).
  • each plate (11) On each side of the stack of sheets (10) constituting each plate (11) is bonded a thin aluminum plate (14), said plates (14) opening along the lower edges (15) of the plates (11) between which the space (12) is delimited.
  • a plate (16) constituting a thermal protection On each aluminum plate (14) is bonded a plate (16) constituting a thermal protection, shown in FIG. 4, and which comprises lines of weaker resistance (17) along which said thermal protection (16) is torn at opening the door.
  • the thermal protection is intended to keep the elastic elements (11) their mechanical properties.
  • the lines of least resistance (17) coincide vertically with the axes of the space (12) formed between the plates (11) so that the stack which has just been described opens very exactly in the same places and thus avoids an anarchic tearing of the different plates of the stack, which anarchic tearing would be detrimental to a good return of said plates to their initial position shown in Figure 2, after launching the missile, as will be described later.
  • a retaining grid (18) is arranged between the upper frame (7) and the adjacent thermal protection.
  • the retaining grid (18) has the function of preventing the deformable and sectionable stack constituted by the plates (11), (14) and (16) from bending upwards when they are returned to the initial position. Indeed, after the launch of the missile and the opening of the lower door (5) of the container (1), the elastic plates (11) could exceed the initial position after deformation, due to their elasticity or under pressure due to the firing of another missile. Such overshoot is prevented by the retaining grid (18) which also plays the role of additional protection in addition to that provided by the thermal protection (16).
  • the lower frame (8) has a rounded internal peripheral edge (19) around which the deformable and sectionable stack (11), (14) and (16) deforms upon opening after sectioning along the edges (15) of the plates (11) and lines of least resistance (17) of thermal protections (16).
  • the radius of curvature of the internal peripheral edge (19) depends essentially on the extent of the deformation desired for the deformable stack or in other words the cross section for the gases to the exhaust duct (3).
  • One solution for having a small radius of curvature while ensuring a most efficient passage section for gases is to produce a deformable stack of small thickness. This object is achieved by choosing elastic sheets (10) with a thickness of approximately 0.3 mm, the aluminum plates (14) and thermal protections (161 having thicknesses of approximately 0.4 mm and 5 respectively. mm.
  • the aluminum plates (14) are cut approximately along the edges (15) of the plates ( 11). Due to the high temperature of the gases produced by the missile during the launching phase, the small aluminum strips which protrude from the edges (15) are leveled by the flames. Therefore, we obtain a space (12) between the elastic plates (11) perfectly clean and delimited. After deformation, the stack (10), (14) and (16) returns to the initial position and the space (12) provides a section of approximately 20 cm2.
  • the container (1) is closed again and communicates with the gas evacuation duct (6) only through the section of 20 cm2, which corresponds to less than 5% of the section of total passage which is offered to gases. This is very important for the other containers of the module still containing the missiles. In fact, after launching another missile from the module, the gases pass through the evacuation duct (6) and fill the container or containers no longer comprising a missile and tend to create a sudden increase in pressure in the container or containers empty and especially at the upper door.
  • the gases flowing in the exhaust duct (3) are completely filtered during their passage in the empty container, while ensuring a flow of said gases in the exhaust duct (3) of the order of 99%. Consequently, there is no need to oversize the containers as is done in the containers of the prior art, the lower cover of which remains completely open after launching the missile.
  • FIG. 6 Another embodiment of the invention ( Figures 5 and 6) consists in using support members (50) (51) in the form of bars, the lower bar (51) of which is rounded.
  • the cover (53) consists of a for two elements (54) (55), the said cover being fixed between the two bars (50) (51).
  • the structure of the cover is shown in Figure 6 and includes the same constituent parts as the cover shown in Figure 2, the references in the figure being assigned an index a.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Carbon And Carbon Compounds (AREA)
EP88402343A 1987-09-17 1988-09-16 Opercule arrière pour conteneur de missile Expired - Lifetime EP0308344B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8712862 1987-09-17
FR8712862A FR2620808B1 (fr) 1987-09-17 1987-09-17 Opercule arriere pour conteneur de missile

Publications (2)

Publication Number Publication Date
EP0308344A1 EP0308344A1 (fr) 1989-03-22
EP0308344B1 true EP0308344B1 (fr) 1992-04-15

Family

ID=9354974

Family Applications (1)

Application Number Title Priority Date Filing Date
EP88402343A Expired - Lifetime EP0308344B1 (fr) 1987-09-17 1988-09-16 Opercule arrière pour conteneur de missile

Country Status (3)

Country Link
EP (1) EP0308344B1 (es)
ES (1) ES2031261T3 (es)
FR (1) FR2620808B1 (es)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5194688A (en) * 1992-01-31 1993-03-16 Hughes Missile Systems Company Apparatus for limiting recirculation of rocket exhaust gases during missile launch
FR2926359B1 (fr) 2008-01-11 2010-02-12 Dcns Opercule arriere deformable a lames elastiques pour conteneur de missile
FR2926360B1 (fr) 2008-01-11 2012-10-19 Dcns Opercule arriere deformable pour conteneur de missile, comportant un cadre de support aval
FR2926358B1 (fr) 2008-01-11 2010-01-15 Dcns Opercule aval deformable ameliore pour conteneur de missile
FR2926357B1 (fr) 2008-01-11 2013-10-25 Dcns Conteneur de missile multiple et lanceur polyvalent
FR3039889B1 (fr) * 2015-08-05 2017-07-28 Mbda France Opercule flexible pour conteneur de missile

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1540803A (en) * 1977-06-14 1979-02-14 Gen Dynamics Corp Rocket exhaust plenum flow control apparatus

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2445423A (en) * 1946-03-06 1948-07-20 United Shoe Machinery Corp Safety container for rockets
DE2715704A1 (de) * 1976-04-08 1977-10-20 Mcevoy Oilfield Equipment Co Verbindungsanordnung fuer ein sich vom meeresboden zu einem schwimmenden bohrgeraet erstreckendes steigrohr
US4134327A (en) * 1977-12-12 1979-01-16 General Dynamics Corporation Rocket launcher tube post-launch rear closure

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1540803A (en) * 1977-06-14 1979-02-14 Gen Dynamics Corp Rocket exhaust plenum flow control apparatus

Also Published As

Publication number Publication date
ES2031261T3 (es) 1992-12-01
FR2620808A1 (fr) 1989-03-24
EP0308344A1 (fr) 1989-03-22
FR2620808B1 (fr) 1990-01-12

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