EP3264021B1 - Flexibler verschlussdeckel für behälter eines flugkörpers - Google Patents

Flexibler verschlussdeckel für behälter eines flugkörpers Download PDF

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Publication number
EP3264021B1
EP3264021B1 EP17290081.3A EP17290081A EP3264021B1 EP 3264021 B1 EP3264021 B1 EP 3264021B1 EP 17290081 A EP17290081 A EP 17290081A EP 3264021 B1 EP3264021 B1 EP 3264021B1
Authority
EP
European Patent Office
Prior art keywords
flexible cover
layer
main layer
missile
cover according
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
EP17290081.3A
Other languages
English (en)
French (fr)
Other versions
EP3264021A1 (de
Inventor
Bertrand Leroy
Pascal Herquel
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.)
MBDA France SAS
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MBDA France SAS
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Filing date
Publication date
Application filed by MBDA France SAS filed Critical MBDA France SAS
Publication of EP3264021A1 publication Critical patent/EP3264021A1/de
Application granted granted Critical
Publication of EP3264021B1 publication Critical patent/EP3264021B1/de
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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
    • F41F3/077—Doors or covers for launching tubes

Definitions

  • the present invention relates to a flexible cover for a missile container.
  • a container lid has the function of hermetically closing the container in order to protect a missile installed in this container.
  • the seal must be able to open in order to allow the missile or the propellant gases to pass when the latter is fired.
  • the object of the present invention is to overcome at least some of the aforementioned drawbacks. More specifically, it aims to remedy the problem of debris presenting a danger to the equipment, while guaranteeing a moderate effort on the missile radome, a low mass and a reduced manufacturing cost.
  • the present invention relates to a flexible cover, intended to be mounted on a missile container and capable of opening under a push.
  • the fabric or fabrics which are introduced into the elastomer to form the composite part ensure the mechanical strength of the flexible seal which is, moreover, made airtight thanks in particular to the elastomer.
  • said at least one auxiliary layer (comprising zones in the form of petals defining weakening lines) makes it possible to direct a precise cutting of the flexible cover, along said weakening lines, which allows easier opening.
  • the piece of composite material has great flexibility (or flexibility), which allows the flexible seal to return, after opening, to a position close to the position before opening.
  • a flexible cover is thus obtained which makes it possible to avoid the generation of debris (presenting a danger for the equipment), while guaranteeing a moderate effort on the radome of the missile, a low mass and a reduced manufacturing cost.
  • said at least one auxiliary layer is linked to said main layer by seams, which ensures good hold of the petal-shaped areas. These seams also participate in the maintenance during the manufacturing process of the flexible seal.
  • At least some of said seams are arranged along the lines of weakness, which makes it possible to reinforce the support along the lines of weakness.
  • the present invention also relates to a missile container, which comprises at least one flexible cover as described above.
  • the present invention further relates to a weapon system which includes at least one such missile container.
  • the flexible seal 1 illustrating the invention and shown schematically on the figure 1 is intended to be mounted on a missile container (not shown).
  • This missile container is part of a weapon system (also not shown).
  • the flexible seal 1 has the function of hermetically closing the container in order to protect a missile installed in the container.
  • the flexible seal must be able to open in order to allow the missile or the propellant gases to pass when the latter is fired.
  • the flexible cover 1 is configured to open under a push.
  • this thrust can be generated during a firing by a contact of the flexible seal by the missile, or else by an internal overpressure generated by dedicated means or by propellant gases of the missile.
  • each auxiliary layer 3, 4 comprises a plurality of zones 6 (made of composite material 10) in the form of petals, for example of triangular shape, which are separated from each other by dividing lines, called weakening lines 5.
  • embrittlement lines 5 free of fabric, are filled with elastomer (of the composite material 10), as shown in black on the figures 1 and 2 .
  • Said main layer 2 and said at least one auxiliary layer 3, 4 thus form a one-piece composite part 8.
  • the composite material 10 forming the auxiliary layer or layers 3, 4 is identical to the composite material 9 forming the main layer 2.
  • the composite layer 2 and the auxiliary layer (s) 3, 4 therefore form a flexible composite part 8 which, thanks to its flexibility (or suppleness), allows the flexible cover 1 to return, after opening, to a position which is close to its position before opening, as specified below.
  • auxiliary layer (s) 3, 4 with zones 6 in the form of petals makes it possible to direct a precise cutting of the composite material (elastomer / fabric), along the lines of weakness 5 formed between these zones 6.
  • the fabric or fabrics which are inserted into the elastomer to form the composite material 9, 10 ensure the mechanical strength of the flexible seal 1.
  • This or these fabrics are made, in particular, from fibers of carbon or glass fibers, or textile fibers (polyester, polyamide, ).
  • the composite material 9, 10 also makes it possible, thanks to the elastomer, to make the flexible seal 1 hermetic.
  • the elastomer can be made of different materials.
  • this elastomer is of the butyl, neoprene, silicone type, etc.
  • the flexible cover 1 comprises two auxiliary layers 3 and 4 which are arranged on either side of the main layer 2, respectively on the faces 2A and 2B of the latter.
  • the two auxiliary layers 3, 4 are arranged, with their zones 6 in the form of petals, symmetrically, with respect to a substantially central plane P of the main layer 2 of generally planar shape.
  • the weakening zones are located in the same position on either side of the main layer 2.
  • a single auxiliary layer 3 (fabric / elastomer) is provided on the outer side 2A of the main layer 2 (fabric / elastomer), that is to say on the side 1A which will be directed towards the outside of the container in the mounted position of the flexible cover 1. This makes it possible to limit the forces necessary for opening.
  • the flexible cover 1 further comprises an anti-friction coating 11 on the internal face 1B, which is therefore intended to be placed towards the interior of the container.
  • This anti-friction coating 11 makes it possible, in particular, to limit friction during the passage of the missile through the flexible cover 1.
  • the anti-friction coating 11 is produced for example from a metallic material, which makes it possible, in addition to reducing the coefficient of friction, to ensure electrical continuity.
  • the zones 6 therefore make it possible to create the weakening lines 5, which facilitates the tearing of the composite material 9 (fabric / elastomer) of the main layer 2 in precise directions.
  • the weakening lines 5 are arranged radially with respect to the center 12 of the flexible cover 1, as shown in the figures 3 to 5 .
  • the weakening lines 5 are more or less numerous, for example two lines oriented along the diagonals as in the examples of figures 3 and 5 or four lines oriented along the diagonals and the perpendicular bisectors of the sides as shown in the example of the figure 4 .
  • each auxiliary layer 3, 4 is linked to the main layer 2 by seams 13 and 14 ( figures 3 to 5 ).
  • These seams 13 and 14 also participate in the maintenance of the fabric of the auxiliary layers 3 and 4 on the main layer 2, during the manufacturing process of the flexible seal. They are produced in the usual way from threads, for example polyamide, which correspond, preferably but not exclusively, to the threads of the fabrics used to form the composite materials 9 and 10.
  • Certain seams 13 are arranged in the zones 6, parallel to the lines of weakness 5, along seam lines 15, which makes it easier to tear along the lines of weakness 5.
  • certain seams 14 are arranged transversely to said weakening lines 5.
  • seams may be provided over the entire surface of the zones 6 in the shape of petals. The distribution of these seams can then take different forms.
  • the flexible cover 1 is preferably designed to hold pressures between 1 and 5 bars, and to open from 5 bars.
  • the operation of the flexible cover 1 is also specified.
  • the flexible cover 1 (and more particularly the composite part 8 and, where appropriate, also the anti-friction coating 11) tears along the lines of weakness 5, and the flexible petals 6 thus released bend outward to open the flexible seal 1 and free the passage for the missile.
  • the flexible petals 6 return, thanks to their flexibility, to an initial position so that the flexible seal 1 is close to its position before opening in order to allow the door to be closed. alveolus.
  • elements 16 for example made of stainless steel, in particular four elements 16 in the form of a square, make it possible to clamp the flexible seal 1 on the container (not shown).
  • a container of a missile launcher which is on board a ship.
  • a container generally comprises a series of cells, each cell being intended to receive a missile placed in its container.
  • the upper part of a cell opens out at the level of the ship's deck and is closed, outside the launch phases, by a door.
  • the lower part of a cell has a communication opening opening into a chamber intended to receive the gases emitted during the launching of a missile.
  • the upper and lower parts of each container are sealed, by a cover provided with a high flexible cover, such as the flexible cover 1 specified above, and by a bottom provided, for example, also with a low flexible cover such as flexible cover 1.
  • the interior volume of the container is, in general, filled with an inert gas at overpressure relative to the atmosphere.
  • an inert gas at overpressure relative to the atmosphere.
  • the propellants then increase the pressure and the temperature significantly inside the container, which punctures the flexible top seal of the container (and if necessary opens the bottom flexible seal). After firing, the flexible cover (s) return roughly to their initial position and the cell door is closed.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Closures For Containers (AREA)
  • Laminated Bodies (AREA)

Claims (12)

  1. Flexibler Verschlussdeckel, der dazu bestimmt ist, auf einem Behälter eines Flugkörpers montiert zu werden, und geeignet ist, sich unter einem Schub zu öffnen, wobei der Verschlussdeckel umfasst:
    - eine Schicht (2), als Hauptschicht bezeichnet, die aus einem Verbundmaterial (9) gebildet ist, das aus mindestens einem Gewebe und aus mindestens einem Elastomer besteht; und
    - mindestens eine Schicht (3, 4), als Hilfsschicht bezeichnet, die aus einem Verbundmaterial (10) gebildet ist, das auch aus mindestens einem Gewebe und aus mindestens einem Elastomer besteht, wobei die Hilfsschicht (3, 4) fest mit der Hauptschicht (2) auf einer der Seiten (2A, 2B) dieser letzteren verbunden ist, wobei die Hilfsschicht (3, 4) Bereiche (6) in Blütenblattform umfasst, die durch Linien (5), als Bruchlinien bezeichnet, voneinander getrennt sind, wobei die Hauptschicht (2) und die mindestens eine Hilfsschicht (3, 4) ein Verbundteil (8) bilden,
    dadurch gekennzeichnet, dass die mindestens eine Hilfsschicht (3, 4) über Nähte (13, 14) mit der Hauptschicht (2) verbunden ist und dadurch, dass mindestens gewisse (13) der Nähte entlang der Bruchlinien (5) angeordnet sind.
  2. Flexibler Verschlussdeckel nach Anspruch 1,
    dadurch gekennzeichnet, dass er zwei Hilfsschichten (3, 4) beinhaltet, die beiderseits der Hauptschicht (2) angeordnet sind.
  3. Flexibler Verschlussdeckel nach Anspruch 2,
    dadurch gekennzeichnet, dass die zwei Hilfsschichten (3, 4), mit ihren Bereichen (6) in Blütenblattform, symmetrisch in Bezug auf eine im Wesentlichen mittlere Ebene (P) der Hauptschicht (2) angeordnet sind.
  4. Flexibler Verschlussdeckel nach einem der vorstehenden Ansprüche,
    dadurch gekennzeichnet, dass die Nähte (13, 14) ausgehend von Fäden gefertigt sind, die den Gewebefäden entsprechen, die verwendet werden, um die Verbundmaterialien (9, 10) zu bilden.
  5. Flexibler Verschlussdeckel nach einem der vorstehenden Ansprüche,
    dadurch gekennzeichnet, dass mindestens gewisse (14) der Nähte quer zu den Bruchlinien (5) angeordnet sind.
  6. Flexibler Verschlussdeckel nach einem der vorstehenden Ansprüche,
    dadurch gekennzeichnet, dass die Nähte auf der gesamten Oberfläche der Bereiche (6) in Blütenblattform vorgesehen sind.
  7. Flexibler Verschlussdeckel nach einem der vorstehenden Ansprüche,
    dadurch gekennzeichnet, dass die Bereiche (6) in Blütenblattform derart angeordnet sind, dass die Bruchlinien (5) in Bezug auf den Mittelpunkt (12) des flexiblen Verschlussdeckels (1) radial ausgerichtet sind.
  8. Flexibler Verschlussdeckel nach einem der vorstehenden Ansprüche,
    dadurch gekennzeichnet, dass das Verbundmaterial (10), das die mindestens eine Hilfsschicht (3, 4) bildet, identisch ist mit dem Verbundmaterial (9), das die Hauptschicht (2) bildet.
  9. Flexibler Verschlussdeckel nach einem der vorstehenden Ansprüche,
    dadurch gekennzeichnet, dass die Bruchlinien (5) mit Elastomer gefüllt sind.
  10. Flexibler Verschlussdeckel nach einem der vorstehenden Ansprüche,
    dadurch gekennzeichnet, dass er auf einer Seite (1A), als innere bezeichnet, die dazu bestimmt ist, zum Inneren des Behälters hin platziert zu sein, eine Antifriktionsauskleidung (11) umfasst.
  11. Behälter eines Flugkörpers,
    dadurch gekennzeichnet, dass er mindestens einen flexiblen Verschlussdeckel (1) nach einem der Ansprüche 1 bis 10 beinhaltet.
  12. Waffensystem,
    dadurch gekennzeichnet, dass es mindestens einen Behälter eines Flugkörpers nach Anspruch 11 beinhaltet.
EP17290081.3A 2016-07-01 2017-06-20 Flexibler verschlussdeckel für behälter eines flugkörpers Active EP3264021B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1601043A FR3053455B1 (fr) 2016-07-01 2016-07-01 Opercule flexible pour conteneur de missile

Publications (2)

Publication Number Publication Date
EP3264021A1 EP3264021A1 (de) 2018-01-03
EP3264021B1 true EP3264021B1 (de) 2020-06-17

Family

ID=57396500

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17290081.3A Active EP3264021B1 (de) 2016-07-01 2017-06-20 Flexibler verschlussdeckel für behälter eines flugkörpers

Country Status (5)

Country Link
US (1) US10845159B2 (de)
EP (1) EP3264021B1 (de)
ES (1) ES2805656T3 (de)
FR (1) FR3053455B1 (de)
WO (1) WO2018002454A1 (de)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112066797B (zh) * 2020-08-31 2022-11-25 湖北三江航天万峰科技发展有限公司 一种易碎盖及其成型方法
CN113819802B (zh) * 2021-09-06 2022-10-21 南京航空航天大学 一种具备自动复位功能的复合材料易碎盖及其制备方法

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1263011A (fr) * 1960-07-21 1961-06-05 Dunlop Rubber Co Enveloppe de protection pour projectiles
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
US5198280A (en) * 1990-10-25 1993-03-30 Allied-Signal Inc. Three dimensional fiber structures having improved penetration resistance
US5677029A (en) * 1990-11-19 1997-10-14 Alliedsignal Inc. Ballistic resistant fabric articles
US7520204B2 (en) * 2004-10-28 2009-04-21 Lockheed Martin Corporation Article comprising a composite cover
EP2060867B1 (de) * 2007-11-14 2011-01-19 Saab Ab Schutzabdeckung für ein Abschussrohr
FR2926360B1 (fr) * 2008-01-11 2012-10-19 Dcns Opercule arriere deformable pour conteneur de missile, comportant un cadre de support aval
KR101222459B1 (ko) * 2010-07-19 2013-01-15 국방과학연구소 유도탄의 발사관용 전방 덮개 및 그 제조 방법
US8883661B2 (en) * 2011-11-18 2014-11-11 Pro-Systems S.P.A. Composite material for ballistic protection and relative method of preparation

Non-Patent Citations (1)

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Title
None *

Also Published As

Publication number Publication date
WO2018002454A1 (fr) 2018-01-04
US10845159B2 (en) 2020-11-24
FR3053455B1 (fr) 2019-04-19
ES2805656T3 (es) 2021-02-15
US20190323799A1 (en) 2019-10-24
EP3264021A1 (de) 2018-01-03
FR3053455A1 (fr) 2018-01-05

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