EP2078920A2 - Deformierbarer unterer Verschlussdeckel für Raketenbehälter - Google Patents

Deformierbarer unterer Verschlussdeckel für Raketenbehälter Download PDF

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Publication number
EP2078920A2
EP2078920A2 EP09150245A EP09150245A EP2078920A2 EP 2078920 A2 EP2078920 A2 EP 2078920A2 EP 09150245 A EP09150245 A EP 09150245A EP 09150245 A EP09150245 A EP 09150245A EP 2078920 A2 EP2078920 A2 EP 2078920A2
Authority
EP
European Patent Office
Prior art keywords
blade
downstream
blades
upstream
container
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.)
Granted
Application number
EP09150245A
Other languages
English (en)
French (fr)
Other versions
EP2078920B1 (de
EP2078920A3 (de
Inventor
Pierre Jacques Truyman
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.)
Naval Group SA
Original Assignee
DCNS SA
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by DCNS SA filed Critical DCNS SA
Priority to PL09150245T priority Critical patent/PL2078920T3/pl
Publication of EP2078920A2 publication Critical patent/EP2078920A2/de
Publication of EP2078920A3 publication Critical patent/EP2078920A3/de
Application granted granted Critical
Publication of EP2078920B1 publication Critical patent/EP2078920B1/de
Active legal-status Critical Current
Anticipated expiration legal-status 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
    • 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 a rear cover, also called downstream cap, equipping the bottom of a missile container. More particularly, the invention relates to a downstream cap of the deformable type.
  • 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 a communication 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 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 door of the cell is closed.
  • a deformable cover that opens when a missile is launched and closes afterwards.
  • 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 invention therefore aims to provide a deformable seal having a better seal after use.
  • the subject of the invention is a deformable type cover, intended to equip the bottom of a missile container and able to open under the thrust of the propulsion gases of a missile contained in the container and to closing after ejection of the missile, the cover comprising a grid and a stack of resilient blades, sandwiched between at least one thermal protection membrane and an upstream and downstream sealing membrane, and held between an upstream support frame and a frame downstream support.
  • the cover comprises at least one slip intermediate means disposed between two successive blades of the stack.
  • 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.
  • 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 bridge 4, which are 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 consisting of a container 15 in which is disposed a missile 16 of large diameter. In the inserted position in the cell 2, the axis A of the container 15 coincides with the axis of the cell.
  • the container 15 has a side wall 20, an upper end wall or cover 21 and a bottom end wall or bottom 22.
  • the cover 21 is provided with an upstream cover 23.
  • the bottom 22 is provided with a downstream cap 56 which will be described in detail below.
  • the bottom 22 comprises an adapter 25 adapted to be inserted into the opening 10 of the plenum 11 during the loading of the munition so that the gases leaving the container 15 during the launch of the missile 16 are guided in the plenum 11 .
  • the improved deformable downstream cap 56 comprises, superimposed along an axis of symmetry C, from the upstream (inside the container) downstream (outside the container), maintained between an upstream support frame 61 and a downstream support frame 64, a grid 62; an upstream thermal protection membrane 70; an upstream sealing membrane 71 for example of aluminum; 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 2 ) 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 lid 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 deformable downstream membrane 56 comprises a stack of metal resilient strips 63 separated from each other by spacer sheets 67 made of non-metallic material resistant to temperature, adapted to facilitate the sliding of the elastic strips one on the other.
  • This intermediate sheet 67 is preferably made of a thermal insulating material such as silicone, or a mat, for example glass fibers.
  • 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 lid 56 will now be described when it equips the bottom of the container 15 of the Figure 1 , the axis C of the seal then coinciding with the axis A of the container 15.
  • the door 5 of the cell 2 is open.
  • the missile 16 is then fired.
  • the propellant gases then increase the pressure and the temperature significantly inside the container 15.
  • 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. accompanying tearing of the sealing membranes and thermal protection 70 to 73.
  • a petal 65 is deformed around an inner edge 80 of the downstream frame 64. Due to the tearing of the membranes 70-73 and the displacement of the various petals 65 of the 63 blades apart from each other, it creates a passage providing communication between the interior of the container 15 and the plenum 11 via an adapter 25. The latter serves to receive the gas passing through the bottom 22 of the container 15 to guide them through the entrance opening 10 of the plenum 11.
  • the pressure inside the container 15 decreases. Since the petals 65 retain their mechanical properties of elasticity due to the interlayers, they effectively return to 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 lid 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 25 is overpressure due to the propulsion gases of a missile launched from a neighboring tube.
  • the inner edge 80 of the downstream frame 64 can be extended downstream and axially present a profile adapted to form a stop for the petals.
  • the downstream frame 64 is of rectangular shape, in the radial plane transverse to the main axis C and extends axially along the axis C over a height H greater than a transverse dimension D of a petal 65, corresponding approximately at half the width of the orifice 81 of the lid 56.
  • the edge profile 80 has a convex upstream portion 90, followed by a concave downstream portion 91.
  • 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.
  • 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.
  • the lid 156 further 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 three blades 163a, 163b and 163c schematically shown decreasing 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 an 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 edge 80 of the downstream frame 64 has a rounded portion 90 having a center O of curvature.
  • the thickness e of the blade 63 at a point is chosen to be less than a maximum thickness em which is greater than the radius of curvature RM of the neutral fiber f at this point of the blade 63 deformed around this rounded portion is high.
  • the thickness of the blade is constant and is chosen as the smallest thickness em at each point of the blade 63. The skilled person knows to determine the appropriate thicknesses.
  • 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.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Closures For Containers (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Table Devices Or Equipment (AREA)
  • Bag Frames (AREA)
  • Packages (AREA)
  • Details Of Aerials (AREA)
  • Wind Motors (AREA)
EP09150245A 2008-01-11 2009-01-08 Deformierbarer unterer Verschlussdeckel für Raketenbehälter Active EP2078920B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL09150245T PL2078920T3 (pl) 2008-01-11 2009-01-08 Osłona dolna kontenera pocisku

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0850160A FR2926358B1 (fr) 2008-01-11 2008-01-11 Opercule aval deformable ameliore pour conteneur de missile

Publications (3)

Publication Number Publication Date
EP2078920A2 true EP2078920A2 (de) 2009-07-15
EP2078920A3 EP2078920A3 (de) 2009-12-02
EP2078920B1 EP2078920B1 (de) 2010-09-22

Family

ID=39745309

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09150245A Active EP2078920B1 (de) 2008-01-11 2009-01-08 Deformierbarer unterer Verschlussdeckel für Raketenbehälter

Country Status (6)

Country Link
EP (1) EP2078920B1 (de)
AT (1) ATE482373T1 (de)
DE (1) DE602009000191D1 (de)
ES (1) ES2351379T3 (de)
FR (1) FR2926358B1 (de)
PL (1) PL2078920T3 (de)

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2620808A1 (fr) 1987-09-17 1989-03-24 France Etat Armement Opercule arriere pour conteneur de missile

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US5194688A (en) * 1992-01-31 1993-03-16 Hughes Missile Systems Company Apparatus for limiting recirculation of rocket exhaust gases during missile launch
JP2004077038A (ja) * 2002-08-20 2004-03-11 Mitsubishi Heavy Ind Ltd 飛しょう体用キャニスタの後蓋

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2620808A1 (fr) 1987-09-17 1989-03-24 France Etat Armement Opercule arriere pour conteneur de missile

Also Published As

Publication number Publication date
DE602009000191D1 (de) 2010-11-04
EP2078920B1 (de) 2010-09-22
ES2351379T3 (es) 2011-02-03
FR2926358A1 (fr) 2009-07-17
ATE482373T1 (de) 2010-10-15
FR2926358B1 (fr) 2010-01-15
EP2078920A3 (de) 2009-12-02
PL2078920T3 (pl) 2011-06-30

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