EP2229573B1 - System eines raketenbehälterbodens - Google Patents

System eines raketenbehälterbodens Download PDF

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Publication number
EP2229573B1
EP2229573B1 EP09704545.4A EP09704545A EP2229573B1 EP 2229573 B1 EP2229573 B1 EP 2229573B1 EP 09704545 A EP09704545 A EP 09704545A EP 2229573 B1 EP2229573 B1 EP 2229573B1
Authority
EP
European Patent Office
Prior art keywords
downstream
plate
container
upstream
point
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.)
Active
Application number
EP09704545.4A
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English (en)
French (fr)
Other versions
EP2229573A2 (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 PL09704545T priority Critical patent/PL2229573T3/pl
Publication of EP2229573A2 publication Critical patent/EP2229573A2/de
Application granted granted Critical
Publication of EP2229573B1 publication Critical patent/EP2229573B1/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
    • F41F3/042—Rocket or torpedo launchers for rockets the launching apparatus being used also as a transport container for the rocket
    • 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
    • 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 bottom system of a missile container comprising an upstream support frame, a downstream support frame and a rear cover of the deformable type, also called downstream cap, fitted to 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 bottom system of a missile container comprising an upstream support frame, a downstream support frame and a seal of the deformable type having a better closure after use.
  • the subject of the invention is a bottom system of a missile container comprising an upstream support frame, a downstream support frame and a deformable type cover intended to equip the bottom of the missile container and adapted to to open under the thrust of the propulsion gases of the missile contained in the container and to close after ejection of the missile, the seal comprising a gate, at least one thermal protection membrane, at least one sealing membrane and a stack of resilient blades, sandwiched between said at least one thermal protection membrane and said at least one sealing membrane, upstream and downstream, and held between the upstream support frame and the downstream support frame, characterized in that the frame of downstream support has an inner edge extended downstream and profiled so that it comprises a convex upstream portion and a rectilinear or concave downstream portion adapted to conform the free end of the lam e resilient, so as to provide the cap with abutment means defining a maximum deformation position of the elastic blades ensuring that the material constituting the blades retains its mechanical elasticity properties.
  • 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 intended to receive a formed munition 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 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 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 operculum 56, so that when the petals 65 are adjacent, it can be considered that the operculum 56 closes the bottom of the container that team.
  • 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 inner edge 80 of the downstream frame 64 is extended downstream and presented axially a profile adapted so as to constitute 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 about half the width of the orifice 81 of the operculum 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.
  • 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 56 will now be described when it equips the bottom of the container 15 of the Figure 1 , axis C of the operculum coinciding then 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.
  • 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 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 pressure inside the container 15 decreases. Since the petals 65 have retained their mechanical elasticity properties due to the presence of the extended frame 80, they effectively return to the rest position, closing the cover 56.
  • the gate 62 forms a stop ensuring that the petals 65 easily find their position. 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 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 4 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 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 any point of the blade. The person skilled in the art knows how to determine the appropriate thicknesses.
  • an improved deformable downstream cap 256 includes in addition, a stack of elastic metal strips 263 of variable thickness separated from each other by interlayer sheets 267 made of a 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.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Carbon And Carbon Compounds (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Support Of The Bearing (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
  • Closures For Containers (AREA)

Claims (9)

  1. Bodensystem für einen Flugkörperbehälter mit einem vorderen Stützrahmen, einem hinteren Stützrahmen und einem Verschluss (56; 156; 256) des verformbaren Typs, der dazu bestimmt ist, den Boden des Behälters (15) des Flugkörpers (16) auszustatten, und in der Lage ist, sich unter dem Schub der Antriebsgase des im Behälter enthaltenen Flugkörpers zu öffnen und sich nach dem Ausstoß des Flugkörpers wieder zu schließen, wobei der Verschluss ein Gitter (62), mindestens eine Wärmeschutzmembran (70, 72), mindestens eine Dichtigkeitsmembran (71, 73) und eine Stapelung elastischer Lamellen (63; 163; 263) umfasst, die zwischen der mindestens einen Wärmeschutzmembran und der mindestens einen Dichtigkeitsmembran vorne und hinten (70, 71, 72, 73) eingeschlossen und zwischen dem vorderen Stützrahmen (61) und dem hinteren Stützrahmen (64) gehalten ist, dadurch gekennzeichnet, dass der hintere Stützrahmen einen Innenrand (80) hat, der nach hinten verlängert und so profiliert ist, dass er einen vorderen konvexen Abschnitt (90) und einen hinteren geradlinigen oder konkaven Abschnitt (91) hat, der in der Lage ist, sich dem freien Ende (96) der elastischen Lamelle (63) anzupassen, um den Verschluss mit Anschlageinrichtungen zu versehen, die eine maximale Verformungsposition der Lamellen vorgeben, wodurch gewährleistet wird, dass das die Lamellen (63; 163; 263) bildende Material seine mechanischen Elastizitätseigenschaften beibehält.
  2. System nach Anspruch 1, dadurch gekennzeichnet, dass der Absolutwert der Krümmung an jedem Punkt des Profils des Innenrands kleiner als eine Schwellenkrümmung ist, jenseits derer das die Lamellen (63; 163; 263) bildende Material seine mechanischen Elastizitätseigenschaften verliert.
  3. System nach Anspruch 1 oder Anspruch 2, dadurch gekennzeichnet, dass zumindest die Oberfläche des Innenrands (80) des hinteren Stützrahmens (64) aus Silikon ist.
  4. System (156) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Dicke (ea, eb, ec) der elastischen Lamellen (163a, 163b, 163c) von einer Lamelle zur anderen von der vorderen Seite zur hinteren Seite der Stapelung abnimmt, wobei die Dicke einer Lamelle so gewählt ist, dass diese Lamelle in der verformten Position nur lokalen Beaufschlagungen unterliegt, die mit dem Elastizitätsbereich des die Lamelle bildenden Materials vereinbar sind.
  5. System (156) nach Anspruch 4, dadurch gekennzeichnet, dass die Dicke (ea, eb, ec) einer Lamelle (163a, 163b, 163c) an einem beliebigen Punkt dieser Lamelle kleiner ist als eine maximale Dicke an diesem Punkt, die proportional zum Krümmungsradius der Lamelle an diesem Punkt ist, wenn sie verformt ist.
  6. System (156) nach Anspruch 5, dadurch gekennzeichnet, dass die Dicke (ea, eb, ec) einer Lamelle an jedem Punkt der Lamelle (163a, 163b, 163c) konstant und gleich der kleinsten der maximalen Dicken (em) an jedem Punkt der Lamelle ist.
  7. System (256) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass es mindestens eine Gleitzwischeneinrichtung (267) hat, die zwischen zwei aufeinanderfolgenden elastischen Lamellen (263) angeordnet ist.
  8. System (256) nach Anspruch 7, dadurch gekennzeichnet, dass jede Gleitzwischeneinrichtung aus einer Folie (267) aus einem wärmeisolierenden Material besteht.
  9. System (256) nach Anspruch 8, dadurch gekennzeichnet, dass das Material der Folien (267) Silikon oder eine Matte, vorzugsweise eine Glasfasermatte ist.
EP09704545.4A 2008-01-11 2009-01-08 System eines raketenbehälterbodens Active EP2229573B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL09704545T PL2229573T3 (pl) 2008-01-11 2009-01-08 Układ dna kontenera pocisków rakietowych

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0850162A FR2926360B1 (fr) 2008-01-11 2008-01-11 Opercule arriere deformable pour conteneur de missile, comportant un cadre de support aval
PCT/FR2009/050020 WO2009092938A2 (fr) 2008-01-11 2009-01-08 Opercule arrière déformable pour conteneur de missile, comportant un cadre de support aval

Publications (2)

Publication Number Publication Date
EP2229573A2 EP2229573A2 (de) 2010-09-22
EP2229573B1 true EP2229573B1 (de) 2016-12-07

Family

ID=39745427

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09704545.4A Active EP2229573B1 (de) 2008-01-11 2009-01-08 System eines raketenbehälterbodens

Country Status (11)

Country Link
US (1) US8418593B2 (de)
EP (1) EP2229573B1 (de)
KR (1) KR101567998B1 (de)
CN (1) CN101918786B (de)
ES (1) ES2617208T3 (de)
FR (1) FR2926360B1 (de)
MA (1) MA32051B1 (de)
PL (1) PL2229573T3 (de)
UA (1) UA98686C2 (de)
WO (1) WO2009092938A2 (de)
ZA (1) ZA201004820B (de)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8300757B2 (en) * 2008-08-08 2012-10-30 Motorola Mobility Llc Methods for detection of failure and recovery in a radio link
US8584569B1 (en) * 2011-12-06 2013-11-19 The United States Of America As Represented By The Secretary Of The Navy Plume exhaust management for VLS
FR3039889B1 (fr) 2015-08-05 2017-07-28 Mbda France Opercule flexible pour conteneur de missile
US10813811B2 (en) 2015-08-24 2020-10-27 Handi-Move Clamp and patient lifting aids using the clamp
FR3053455B1 (fr) * 2016-07-01 2019-04-19 Mbda France Opercule flexible pour conteneur de missile
CN112985174B (zh) * 2021-02-10 2023-01-10 上海材料研究所 一种对激波反射具有整流效果的柱面正交型密封后端盖

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US4324167A (en) * 1980-04-14 1982-04-13 General Dynamics, Pomona Division Flexible area launch tube rear cover
US4498368A (en) * 1983-10-06 1985-02-12 The United States Of America As Representedby The Secretary Of The Navy Frangible fly through diaphragm for missile launch canister
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
JP2001124494A (ja) * 1999-10-25 2001-05-11 Mitsubishi Electric Corp 飛しょう体の発射装置
JP4338004B2 (ja) * 2000-03-16 2009-09-30 株式会社Ｉｈｉエアロスペース ロケットモータのノズルカバー
JP3448648B2 (ja) * 2000-11-27 2003-09-22 防衛庁技術研究本部長 飛しょう体発射筒装置
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
US7984675B2 (en) * 2006-02-21 2011-07-26 Metal Storm Limited Propellant sealing system for stackable projectiles

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Also Published As

Publication number Publication date
CN101918786A (zh) 2010-12-15
FR2926360B1 (fr) 2012-10-19
KR20100122899A (ko) 2010-11-23
KR101567998B1 (ko) 2015-11-10
WO2009092938A3 (fr) 2009-12-17
US8418593B2 (en) 2013-04-16
EP2229573A2 (de) 2010-09-22
ES2617208T3 (es) 2017-06-15
PL2229573T3 (pl) 2017-05-31
FR2926360A1 (fr) 2009-07-17
US20110011251A1 (en) 2011-01-20
ZA201004820B (en) 2011-03-30
UA98686C2 (ru) 2012-06-11
WO2009092938A2 (fr) 2009-07-30
MA32051B1 (fr) 2011-02-01
CN101918786B (zh) 2013-04-24

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