EP0297992A1 - Ejectable cover device, especially for multiple warhead missiles - Google Patents

Ejectable cover device, especially for multiple warhead missiles Download PDF

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Publication number
EP0297992A1
EP0297992A1 EP88401707A EP88401707A EP0297992A1 EP 0297992 A1 EP0297992 A1 EP 0297992A1 EP 88401707 A EP88401707 A EP 88401707A EP 88401707 A EP88401707 A EP 88401707A EP 0297992 A1 EP0297992 A1 EP 0297992A1
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EP
European Patent Office
Prior art keywords
cover
edge
spring
bar
key
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.)
Withdrawn
Application number
EP88401707A
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German (de)
French (fr)
Inventor
René Thouron
Jean-François Denis
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.)
Thomson Brandt Armements SA
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Thomson Brandt Armements 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 Thomson Brandt Armements SA filed Critical Thomson Brandt Armements SA
Publication of EP0297992A1 publication Critical patent/EP0297992A1/en
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
    • F42B12/60—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected radially
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
    • F42B15/38—Ring-shaped explosive elements for the separation of rocket parts

Definitions

  • the present invention relates to a device for closing a structure, such as for example a compartment for submunitions of a rocket.
  • This device can be ejected on command, thus achieving the opening at the desired time of the structure.
  • the current military strategy used to neutralize the enemy's vital installations has two stages: - the first consists in sending, either using a launcher tube or dropped from an aircraft, a cluster munition rocket over the area to be neutralized: - the second consists of ejecting the submunitions on command.
  • the submunitions are initially placed in closed compartments, located in the rocket. Just before the ejection of the submunitions, the compartments are opened on command.
  • the techniques for ejecting submunitions are widely known and are not described in the following.
  • the invention relates to the closing of the compartments using ejectable devices on command.
  • a known device consists of a hatch weakened in places, fixed to the edges of the compartment in other places. A push towards the outside of the compartment is carried out at the weakened places, which are broken, and which then protrude from the fuselage of the rocket.
  • the aerodynamic coefficient of resistance to advancement thereof (denoted Cx in the following) is then modified, and this difference in Cx causes a partial tearing of the hatch.
  • the hatch is only partially torn off, the opening of the compartment is poorly controlled: fragments of hatch may hinder the passage of submunitions.
  • the object of the present invention is to overcome this drawback. It relates to a device for ejecting a structure comprising: - a lid ; - means for pushing towards the outside of the structure; characterized in that it further comprises: - means for locking the cover: - Means for transmitting the thrust to said blocking means, the thrust being capable of releasing the cover from the blocking means, then of causing the complete expulsion of the cover.
  • the cover of the device according to the invention being completely expelled, the opening of the structure is perfectly controlled and reproducible.
  • the present invention more specifically relates to an ejectable closure device of a structure comprising: - a lid ; - pushing means towards the outside of the structure, characterized in that it further comprises: - means for locking the cover; - means for transmitting said thrust; the thrust being capable of releasing the cover from the locking means, then of causing the complete expulsion of the cover.
  • the rocket comprises, for example, a cylindrical part 24 where compartments for cluster munitions are located.
  • FIG. 1 represents an example of configuration of such a cylindrical part 24: the rocket comprises three compartments 23, for example identical, each containing a submunition 21.
  • the compartments 23 are closed by lids 1, situated at the periphery of the cylindrical part 24, and whose longitudinal edges are fixed according to the invention by means 22 (the transverse edges of these covers are fitted in the part 24).
  • the cylindrical part 24 comprises as many means 22 as there are covers 1: each means 22 maintains two different covers 1, and conversely, two opposite longitudinal edges of a given cover 1 are retained by two different means 22. In what follows, only the fixing of a single longitudinal edge of a cover 1 by a single assembly 22 will be described.
  • FIG. 2 shows a section of a first embodiment of the device according to the invention comprising a cover 1 of which only a part is drawn, and a means 22 fully shown.
  • This figure illustrates the configuration of the device before it is ejected.
  • the edge 8 of the cover 1 is held by the means 22 which comprises: - A part 2, called “key”, fitted into the edge 8, and enclosing the external part of this edge 8, thus blocking the cover 1; - means for pushing the key 2 and the edge 8 towards the outside of the structure, comprising an inflatable membrane 3; a part 10 of the membrane 3 is fixed, for example, by means of glue, to the edge 7 of the compartment 23: this edge 7 has the shape of a cut at the bottom of which the part 10 is glued; - Means for transmitting this thrust, comprising a rigid bar 4 and a spring leaf 5; the bar 4 is located between the key 2 and the membrane 3; the spring 5 is compressed between the bar 4 and the edge 8 of the cover 1 for the entire duration which separates the mounting of the
  • the edge 8 of the cover 1 has a bulge 28 pressing against the edge 7 of the compartment 23.
  • Figures 3 and 4 illustrate the ejection of the device of Figure 2.
  • Such an ejection is triggered by the swelling of the membrane 3, connected for example to a pyrotechnic gas generator not shown in FIGS. 2 to 4.
  • the techniques for swelling membranes intended to achieve any thrust are known in themselves and are therefore not described here.
  • By inflating the membrane 3 performs a radial and centrifugal thrust (relative to the edge 7 of the compartment 23) 9 (relative to the cylindrical part 24 of the rocket).
  • the thrust 9 is exerted on the bar 4, thus compressing the spring 5, as illustrated in FIG. 3; the shape of the bar 4 allows the key 2 to be disengaged from the edge 8: in FIG. 3, the key 2 is almost disengaged.
  • the device is disassembled.
  • the rocket is preferably subjected to a rotation around its axis, in a manner known to those skilled in the art, the resulting centrifugal force making it possible in particular to accentuate the ejection of the aforementioned elements.
  • the various elements then protrude from the fuselage of the rocket, thus modifying its Cx.
  • Figure 5 shows a section of a second embodiment of the device according to the invention, before its ejection.
  • the second embodiment differs from the first in that the edge 7 of the compartment 23 has a rim 12; the spring 5 is preloaded between the bar 4 (as in the case of FIG. 2) and this flange 12 (instead of the edge 8 of the cover 1), which ensures a greater expansion force of the spring 5 than in the case of the first embodiment.
  • the device of FIG. 5 operates like that of FIG. 2, except with regard to the spring 5. This is first compressed by the radial and centrifugal thrust caused by the swelling of the membrane 3 (as in the figure 3); once the key is disengaged, the spring 5 emerges from the rim 12 (unlike in FIG. 3), and relaxes by pressing on the edge 8 of the cover 1 (as in FIG. 4).
  • FIG. 6 represents a section of a third embodiment of the device according to the invention, before it is ejected.
  • the third embodiment differs from the second by the fact that it comprises a one-piece bar, consisting of a rigid part 34 and an elastic part 35, in place of the rigid bar 4 and the spring leaf 5.
  • the parts 34 and 35 respectively provide the same functions as the elements 4 and 5 in FIG. 5.
  • the elastic part 35 unlike the spring 5, is not at all compressed before the device is ejected. As a result, its elasticity is not likely to be reduced as a result of too long prestressing, military equipment being sometimes stored for long periods of time.
  • the device of FIG. 6 is therefore more reliable than that of FIG. 5, or that of FIGS. 2, 3 and 4.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)
  • Catching Or Destruction (AREA)

Abstract

La présente invention concerne un dispositif destiné à fermer un compartiment à sous-munitions (23) d'une roquette, et à être éjecté juste avant le sous-munitions, de façon à ouvrir le compartiment (23). Ce dispositif comporte un couvercle (1), bloqué à l'aide d'une clé (2), et un ballon gonflable (3), permettant de dégager le couvercle (1) de la clé (2) et de démonter le dispositif sans le briser, en expulsant complètement le couvercle (1).The present invention relates to a device intended to close a compartment for submunitions (23) of a rocket, and to be ejected just before the submunitions, so as to open the compartment (23). This device comprises a cover (1), blocked using a key (2), and an inflatable balloon (3), making it possible to release the cover (1) from the key (2) and to dismantle the device without break it, completely expelling the cover (1).

Description

La présente invention concerne un dispositif de fermeture d'une structure, comme par exemple un compartiment à sous-munitions d'une roquette. Ce dispositif peut être éjecté sur commande, réalisant ainsi l'ouverture au moment voulu de la structure.The present invention relates to a device for closing a structure, such as for example a compartment for submunitions of a rocket. This device can be ejected on command, thus achieving the opening at the desired time of the structure.

La stratégie militaire actuelle utilisée pour neutraliser les installations vitales de l'ennemi, comme par exemple les pistes d'atterissage, comporte deux étapes :
- la première, consiste à envoyer, soit à l'aide d'un tube lanceur, soit larguée d'un aéronef, une roquette à sous-munitions au-dessus de la zone à neutraliser :
- la seconde consiste à éjecter sur commande les sous-munitions.The current military strategy used to neutralize the enemy's vital installations, such as airstrips, has two stages:
- the first consists in sending, either using a launcher tube or dropped from an aircraft, a cluster munition rocket over the area to be neutralized:
- the second consists of ejecting the submunitions on command.

Les sous-munitions sont initialement placées dans des compartiments fermés, situés dans la roquette. Juste avant l'éjection des sous-munitions, les compartiments sont ouverts sur commande.The submunitions are initially placed in closed compartments, located in the rocket. Just before the ejection of the submunitions, the compartments are opened on command.

Les techniques d'éjection des sous-munitions sont largement connues et ne sont pas décrites dans ce qui suit. L'invention concerne la fermeture des compartiments à l'aide de dispositifs éjectables sur commande.The techniques for ejecting submunitions are widely known and are not described in the following. The invention relates to the closing of the compartments using ejectable devices on command.

Il existe de tels dispositifs. Un dispositif connu est constitué d'une trappe fragilisée par endroits, fixée aux bords du compartiment à d'autres endroits. Une poussée vers l'extérieur du compartiment est effectuée aux endroits fragilisés, qui sont brisés, et qui dépassent alors du fuselage de la roquette. Le coefficient aérodynamique de résistance à l'avancement de celle-ci (noté Cx dans ce qui suit) est alors modifié, et cette différence de Cx provoque un arrachement partiel de la trappe. La trappe n'étant arrachée qu'en partie, l'ouverture du compartiment est mal contrôlée : des fragments de trappe risquent de gêner le passage des sous-munitions.There are such devices. A known device consists of a hatch weakened in places, fixed to the edges of the compartment in other places. A push towards the outside of the compartment is carried out at the weakened places, which are broken, and which then protrude from the fuselage of the rocket. The aerodynamic coefficient of resistance to advancement thereof (denoted Cx in the following) is then modified, and this difference in Cx causes a partial tearing of the hatch. The hatch is only partially torn off, the opening of the compartment is poorly controlled: fragments of hatch may hinder the passage of submunitions.

La présente invention a pour objet de pallier cet inconvénient. Elle concerne un dispositif de fermeture éjectable d'une structure comportant :
- un couvercle ;
- des moyens de poussée vers l'extérieur de la structure ; caractérisé en ce qu'il comporte en outre :
- des moyens de blocage du couvercle:
- des moyens de transmission de la poussée auxdits moyens de blocage, la poussée étant susceptible de dégager le couvercle des moyens de blocage, puis de provoquer l'expulsion complète du couvercle.The object of the present invention is to overcome this drawback. It relates to a device for ejecting a structure comprising:
- a lid ;
- means for pushing towards the outside of the structure; characterized in that it further comprises:
- means for locking the cover:
- Means for transmitting the thrust to said blocking means, the thrust being capable of releasing the cover from the blocking means, then of causing the complete expulsion of the cover.

Le couvercle du dispositif selon l'invention étant totalement expulsé, l'ouverture de la structure est parfaitement contrôlée et reproductible.The cover of the device according to the invention being completely expelled, the opening of the structure is perfectly controlled and reproducible.

La présente invention a plus précisément pour objet un dispositif de fermeture éjectable d'une structure comportant :
- un couvercle ;
- des moyens de poussée vers l'extérieur de la structure, caractérisé en ce qu'il comporte en outre :
- des moyens de blocage du couvercle ;
- des moyens de transmission de ladite poussée ;
la poussée étant susceptible de dégager le couvercle des moyens de blocage, puis de provoquer, l'expulsion complète du couvercle.The present invention more specifically relates to an ejectable closure device of a structure comprising:
- a lid ;
- pushing means towards the outside of the structure, characterized in that it further comprises:
- means for locking the cover;
- means for transmitting said thrust;
the thrust being capable of releasing the cover from the locking means, then of causing the complete expulsion of the cover.

Des précisions et différents modes de réalisation de l'invention ressortiront de la description suivante illustrée par les figures annexées qui représentent :

  • - la figure 1, une coupe transversale d'une roquette comportant trois dispositifs selon l'invention ;
  • - la figure 2, une coupe partielle d'un premier mode de réalisation du dispositif selon l'invention avant son éjection ;
  • - la figure 3, une coupe partielle du dispositif de la figure 2 au début de son éjection ;
  • - la figure 4, une coupe partielle du dispositif de la figure 2 à la fin de son éjection ;
  • - la figure 5, une coupe partielle d'un second mode de réalisation du dispositif selon l'invention ;
  • - la figure 6, une coupe partielle d'un troisième mode de réalisation du dispositif selon l'invention.
Details and various embodiments of the invention will emerge from the following description illustrated by the appended figures which represent:
  • - Figure 1, a cross section of a rocket comprising three devices according to the invention;
  • - Figure 2, a partial section of a first embodiment of the device according to the invention before its ejection;
  • - Figure 3, a partial section of the device of Figure 2 at the start of its ejection;
  • - Figure 4, a partial section of the device of Figure 2 at the end of its ejection;
  • - Figure 5, a partial section of a second embodiment of the device according to the invention;
  • - Figure 6, a partial section of a third embodiment of the device according to the invention.

Sur ces différentes figures, les mêmes réferences se rapportent aux mêmes éléments.In these different figures, the same references relate to the same elements.

La description suivante sera faite à titre d'exemple dans le cadre de l'application du dispositif selon l'invention à la fermeture d'un compartiment d'une roquette contenant des sous-munitions.The following description will be given by way of example in the context of the application of the device according to the invention to the closure of a compartment of a rocket containing submunitions.

La roquette comporte par exemple une partie cylindrique 24 où sont situés des compartiments à sous-munitions. La figure 1 représente un exemple de configuration d'une telle partie cylindrique 24 : la roquette comporte trois compartiments 23, par exemple identiques, contenant chacun une sous-munition 21. Les compartiments 23 sont fermés par des couvercles 1, situés à la périphérie de la partie cylindrique 24, et dont les bords longitudinaux sont fixés selon l'invention par des moyens 22 (les bords transversaux de ces couvercles sont emboîtés dans la partie 24). La partie cylindrique 24 comporte autant de moyens 22 que de couvercles 1 : chaque moyen 22 maintient deux couvercles 1 différents, et réciproquement, deux bords longitudinaux opposés d'un couvercle 1 donné sont retenus par deux moyens 22 différents. Dans ce qui suit on ne décrira que la fixation d'un seul bord longitudinal d'un couvercle 1 par un seul ensemble 22.The rocket comprises, for example, a cylindrical part 24 where compartments for cluster munitions are located. FIG. 1 represents an example of configuration of such a cylindrical part 24: the rocket comprises three compartments 23, for example identical, each containing a submunition 21. The compartments 23 are closed by lids 1, situated at the periphery of the cylindrical part 24, and whose longitudinal edges are fixed according to the invention by means 22 (the transverse edges of these covers are fitted in the part 24). The cylindrical part 24 comprises as many means 22 as there are covers 1: each means 22 maintains two different covers 1, and conversely, two opposite longitudinal edges of a given cover 1 are retained by two different means 22. In what follows, only the fixing of a single longitudinal edge of a cover 1 by a single assembly 22 will be described.

La figure 2 représente une coupe d'une premier mode de réalisation du dispositif selon l'invention comportant un couvercle 1 dont seule une partie est dessinée, et un moyen 22 totalement représenté. Cette figure illustre la configuration du dispositif avant son éjection. Le bord 8 du couvercle 1 est maintenu par le moyen 22 qui comporte :
- une pièce 2, appelée "cle", emboîtée dans le bord 8, et enserrant la partie externe de ce bord 8, bloquant ainsi le couvercle 1 ;
- des moyens de poussée de la clé 2 et du bord 8 vers l'extérieur de la structure, comportant une membrane gonflable 3 ; une partie 10 de la membrane 3 est fixée, par exemple, au moyen de colle, au bord 7 du compartiment 23 : ce bord 7 a la forme d'une coupe au fond de laquelle est collée la partie 10 ;
- des moyens de transmission de cette poussée, comportant une barrette rigide 4 et une lame de ressort 5 ; la barrette 4 est située entre la clé 2 et la membrane 3 ; le ressort 5 est comprimé entre la barrette 4 et le bord 8 du couvercle 1 pendant toute la durée qui sépare le montage du dispositif de l'éjection de ce même dispositif : le ressort est dit en "précontrainte" entre la barrette 4 et la partie interne du bord 8 ;
- une vis 6 de fixation de la clé 2 à la barrette 4 ; cette fixation maintient le dispositif en place avant son éjection.2 shows a section of a first embodiment of the device according to the invention comprising a cover 1 of which only a part is drawn, and a means 22 fully shown. This figure illustrates the configuration of the device before it is ejected. The edge 8 of the cover 1 is held by the means 22 which comprises:
- A part 2, called "key", fitted into the edge 8, and enclosing the external part of this edge 8, thus blocking the cover 1;
- means for pushing the key 2 and the edge 8 towards the outside of the structure, comprising an inflatable membrane 3; a part 10 of the membrane 3 is fixed, for example, by means of glue, to the edge 7 of the compartment 23: this edge 7 has the shape of a cut at the bottom of which the part 10 is glued;
- Means for transmitting this thrust, comprising a rigid bar 4 and a spring leaf 5; the bar 4 is located between the key 2 and the membrane 3; the spring 5 is compressed between the bar 4 and the edge 8 of the cover 1 for the entire duration which separates the mounting of the device from the ejection of this same device: the spring is said to be "prestressed" between the bar 4 and the part internal edge 8;
- A screw 6 for fixing the key 2 to the bar 4; this fixation keeps the device in place before it is ejected.

Le bord 8 du couvercle 1 comporte un renflement 28 s'appuyant contre le bord 7 du compartiment 23. Un joint 13 situé entre les bords 8 et 7 assure l'étanchéité de la fermeture du compartiment 23 : en effet, il n'est pas souhaitable que les sous-munitions soient mouillées ou humides.The edge 8 of the cover 1 has a bulge 28 pressing against the edge 7 of the compartment 23. A seal 13 located between the edges 8 and 7 seals the closure of the compartment 23: in fact, it is not desirable for submunitions to be wet or damp.

Les figures 3 et 4 illustrent l'éjection du dispositif de la figure 2.Figures 3 and 4 illustrate the ejection of the device of Figure 2.

Une telle éjection est déclenchée par le gonflement de la membrane 3, reliée par exemple à un générateur pyrotechnique de gaz non représenté sur les figures 2 à 4. Les techniques de gonflement de membranes destinées à réaliser une poussée quelconque sont connues en elles-mêmes et ne sont donc pas décrites ici. En se gonflant la membrane 3 effectue une poussée (par rapport au bord 7 du compartiment 23) radiale et centrifuge 9 (par rapport à la partie cylindrique 24 de la roquette).Such an ejection is triggered by the swelling of the membrane 3, connected for example to a pyrotechnic gas generator not shown in FIGS. 2 to 4. The techniques for swelling membranes intended to achieve any thrust are known in themselves and are therefore not described here. By inflating the membrane 3 performs a radial and centrifugal thrust (relative to the edge 7 of the compartment 23) 9 (relative to the cylindrical part 24 of the rocket).

La poussée 9 s'exerce sur la barrette 4, comprimant ainsi le ressort 5, comme illustré sur la figure 3 ; la forme de la barrette 4 permet à la clé 2 d'être déboîtée du bord 8 : sur la figure 3, la clé 2 est presque déboîtée.The thrust 9 is exerted on the bar 4, thus compressing the spring 5, as illustrated in FIG. 3; the shape of the bar 4 allows the key 2 to be disengaged from the edge 8: in FIG. 3, the key 2 is almost disengaged.

Dès que la clé 2 est déboîtée, le ressort 5 se détend expulsant ainsi le bord 8 du couvercle 1, comme l'indiquent les flèches 11, sur la figure 4. Selon le mode de réalisation décrit, le joint 13 reste fixé au bord 8, lors de l'expulsion de ce dernier. La membrane 3, continuant à se gonfler, pousse les éléments 4, 5, 2 et 6 suivant la flèche 9. La situation obtenue est illustrée sur la figure 4 : le dispositif est démonté. La roquette est de préférence soumise à une rotation autour de son axe, d'une manière connue par l'homme de l'art, la force centrifuge résultante permettant notamment d'accentuer l'éjection des éléments précités. Les différents éléments dépassent alors du fuselage de la roquette, modifiant ainsi son Cx. Cette différence de Cx provoque l'arrachment du couvercle 1 d'une part, et des éléments 2, 6, 4 et 5, d'autre part. Seule la membrane 3 reste, au moins partiellement, fixée au bord 7 du compartiment 23, mais elle ne gêne aucunement l'éjection des sous-munitions.As soon as the key 2 is disengaged, the spring 5 expands thus expelling the edge 8 of the cover 1, as indicated by the arrows 11, in FIG. 4. According to the embodiment described, the seal 13 remains fixed to the edge 8 , when the latter was expelled. The membrane 3, continuing to swell, pushes the elements 4, 5, 2 and 6 along the arrow 9. The situation obtained is illustrated in Figure 4: the device is disassembled. The rocket is preferably subjected to a rotation around its axis, in a manner known to those skilled in the art, the resulting centrifugal force making it possible in particular to accentuate the ejection of the aforementioned elements. The various elements then protrude from the fuselage of the rocket, thus modifying its Cx. This difference in Cx causes the cover 1 to tear off on the one hand, and elements 2, 6, 4 and 5 on the other hand. Only the membrane 3 remains, at least partially, fixed to the edge 7 of the compartment 23, but it does not hinder in any way the ejection of the submunitions.

La figure 5, représente une coupe d'un second mode de réalisation du dispositif selon l'invention, avant son éjection. Le second mode de réalisation diffère du premier par le fait que le bord 7 du compartiment 23 comporte un rebord 12 ; le ressort 5 est en précontrainte entre la barrette 4 (comme dans le cas de la figure 2) et ce rebord 12 (au lieu du bord 8 du couvercle 1), ce qui assure une plus grande force de détente du ressort 5 que dans le cas du premier mode de réalisation.Figure 5 shows a section of a second embodiment of the device according to the invention, before its ejection. The second embodiment differs from the first in that the edge 7 of the compartment 23 has a rim 12; the spring 5 is preloaded between the bar 4 (as in the case of FIG. 2) and this flange 12 (instead of the edge 8 of the cover 1), which ensures a greater expansion force of the spring 5 than in the case of the first embodiment.

Le dispositif de la figure 5 fonctionne comme celui de la figure 2, sauf en ce qui concerne le ressort 5. Celui-ci est d'abord comprimé par la poussée radiale et centrifuge provoquée par le gonflement de la membrane 3 (comme sur la figure 3) ; une fois la clé déboîtée le ressort 5 se dégage du rebord 12 (contrairement à la figure 3), et se détend en appuyant sur le bord 8 du couvercle 1 (comme sur la figure 4).The device of FIG. 5 operates like that of FIG. 2, except with regard to the spring 5. This is first compressed by the radial and centrifugal thrust caused by the swelling of the membrane 3 (as in the figure 3); once the key is disengaged, the spring 5 emerges from the rim 12 (unlike in FIG. 3), and relaxes by pressing on the edge 8 of the cover 1 (as in FIG. 4).

La figure 6 représente une coupe d'un troisième mode de réalisation du dispositif selon l'invention, avant son éjection. Le troisième mode de réalisation diffère du second par le fait qu'il comporte une barrette monobloc, constituée d'une partie rigide 34 et d'une partie élastique 35, à la place de la barrette rigide 4 et de la lame de ressort 5. Les parties 34, et 35, assurent respectivement les mêmes fonctions que les éléments 4 et 5, de la figure 5. Néanmoins, la partie élastique 35, contrairement au ressort 5, n'est pas du tout comprimée avant l'éjection du dispositif. De ce fait, son élasticité ne risque pas d'être réduite par suite d'une précontrainte trop longue, les matériels militaires étant parfois stockés pendant de longues péroides. Le dispositif de la figure 6 est donc plus fiable que celui de la figure 5, ou celui des figures 2, 3 et 4.FIG. 6 represents a section of a third embodiment of the device according to the invention, before it is ejected. The third embodiment differs from the second by the fact that it comprises a one-piece bar, consisting of a rigid part 34 and an elastic part 35, in place of the rigid bar 4 and the spring leaf 5. The parts 34 and 35 respectively provide the same functions as the elements 4 and 5 in FIG. 5. Nevertheless, the elastic part 35, unlike the spring 5, is not at all compressed before the device is ejected. As a result, its elasticity is not likely to be reduced as a result of too long prestressing, military equipment being sometimes stored for long periods of time. The device of FIG. 6 is therefore more reliable than that of FIG. 5, or that of FIGS. 2, 3 and 4.

Claims (10)

1. Dispositif de fermeture éjectable d'une structure (23) comportant :
- un couvercle (1) ;
- des moyens de poussée (3, 10) vers l'extérieur de la structure (23) ;
caractérisé en ce qu'il comporte en outre :
- des moyens de blocage (2, 6) du couvercle (1) ; - des moyens de transmission (4, 5, 34, 35) de la poussée auxdits moyens de blocage, la poussée étant susceptible de dégager le couvercle (1) des moyens de blocage (2, 6), puis de provoquer l'expulsion complète du couvercle (1).1. Device for ejecting closure of a structure (23) comprising:
- a cover (1);
- pushing means (3, 10) towards the outside of the structure (23);
characterized in that it further comprises:
- locking means (2, 6) of the cover (1); - Transmission means (4, 5, 34, 35) of the thrust to said blocking means, the thrust being capable of releasing the cover (1) of the blocking means (2, 6), then of causing the complete expulsion of the cover (1). 2. Dispositif selon la revendication 1, caractérisé en ce que les moyens de transmission (4, 5, 34, 35) comportent des moyens formant ressort (5, 35) susceptibles de se détendre et de faciliter ainsi l'expulsion complète du couvercle (1).2. Device according to claim 1, characterized in that the transmission means (4, 5, 34, 35) comprise spring means (5, 35) capable of relaxing and thus facilitating the complete expulsion of the cover ( 1). 3. Dispositif selon l'une des revendication 1 ou 2, caractérisé en ce que les moyens de poussée (3, 10) comportent une membrane (3) gonflable, reliée à des moyens de gonflement, le gonflement de la membrane (3) provoquant ladite poussée.3. Device according to one of claims 1 or 2, characterized in that the pushing means (3, 10) comprise an inflatable membrane (3), connected to swelling means, the swelling of the membrane (3) causing said thrust. 4. Dispositif selon la revendication 3, caractérisé en ce que les moyens de poussée (3, 10) comportent une partie (10) fixée au bord (7) de la structure (23).4. Device according to claim 3, characterized in that the thrust means (3, 10) comprise a part (10) fixed to the edge (7) of the structure (23). 5. Dispositif selon l'une des revendications 2 à 4, caractérisé en ce que les moyens de transmission (4, 5, 34, 35) comportent une barrette rigide (4) et une lame de ressort (5), la lame de ressort (5) constituant les moyens formant ressort (5, 35).5. Device according to one of claims 2 to 4, characterized in that the transmission means (4, 5, 34, 35) comprise a rigid bar (4) and a spring leaf (5), the spring leaf (5) constituting the spring means (5, 35). 6. Dispositif selon la revendication 5, caractérisé en ce que la lame de ressort (5) est initialement en précontrainte entre la barrette (4) et le bord (8) du couvercle (1).6. Device according to claim 5, characterized in that the leaf spring (5) is initially prestressed between the bar (4) and the edge (8) of the cover (1). 7. Dispositif selon la revendication 5, caractérisé en ce que le bord (7) de la structure (23) comporte un rebord (12), la lame du ressort (5) étant initialement en précontrainte entre la barrette (4) et ce rebord (12).7. Device according to claim 5, characterized in that the edge (7) of the structure (23) has a flange (12), the leaf of the spring (5) being initially prestressed between the bar (4) and this flange (12). 8. Dispositif selon l'une des revendications 2 à 4, caractérisé en ce que les moyens de transmission (4, 5, 34, 35) comportent une barrette monobloc (34, 35), constituée d'une partie rigide (34) et d'une partie élastique (35), la partie élastique (35) constituant les moyens formant ressort (5, 35).8. Device according to one of claims 2 to 4, characterized in that the transmission means (4, 5, 34, 35) comprise a monobloc bar (34, 35), consisting of a rigid part (34) and an elastic part (35), the elastic part (35) constituting the spring means (5, 35). 9. Dispositif selon l'une des revendications 5 à 7, caractérisé en ce que les moyens de blocage (2, 6) du couvercle (1) comportent une clé (2) emboîtée dans le bord (8) du couvercle (1), et une vis (6) de fixation de la clé (2) à la barrette (4).9. Device according to one of claims 5 to 7, characterized in that the locking means (2, 6) of the cover (1) comprise a key (2) fitted into the edge (8) of the cover (1), and a screw (6) for fixing the key (2) to the bar (4). 10. Dispositif selon la revendication 8, caractérisé en ce que les moyens de blocage (2, 6) du couvercle (1), comportent une clé (2) emboîtée dans le bord (8) du couvercle (1), et une vis (6) de fixation de la clé (2) à la partie rigide (34) de la barrette monobloc (34, 35).10. Device according to claim 8, characterized in that the locking means (2, 6) of the cover (1), comprise a key (2) fitted into the edge (8) of the cover (1), and a screw ( 6) fixing the key (2) to the rigid part (34) of the one-piece bar (34, 35).
EP88401707A 1987-07-03 1988-07-01 Ejectable cover device, especially for multiple warhead missiles Withdrawn EP0297992A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8709453A FR2617464B1 (en) 1987-07-03 1987-07-03 EJECTABLE CLOSING DEVICE, PARTICULARLY FOR ROCKET MUNITIONS
FR8709453 1987-07-03

Publications (1)

Publication Number Publication Date
EP0297992A1 true EP0297992A1 (en) 1989-01-04

Family

ID=9352842

Family Applications (1)

Application Number Title Priority Date Filing Date
EP88401707A Withdrawn EP0297992A1 (en) 1987-07-03 1988-07-01 Ejectable cover device, especially for multiple warhead missiles

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Country Link
US (1) US4879941A (en)
EP (1) EP0297992A1 (en)
FR (1) FR2617464B1 (en)

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FR2641858A1 (en) * 1989-01-17 1990-07-20 Thomson Brandt Armements PNEUMATIC UNLOCKING DEVICE FOR LARGABLE AMMUNITION FROM A VECTOR
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WO2012020191A1 (en) * 2010-08-10 2012-02-16 Astrium Sas Attachment device with pyrotechnic bolt
FR2963803A1 (en) * 2010-08-10 2012-02-17 Astrium Sas FIXING DEVICE WITH PYROTECHNIC LOCK
US8967030B2 (en) 2010-08-10 2015-03-03 Airbus Defence And Space Sas Attachment device with pyrotechnic bolt

Also Published As

Publication number Publication date
FR2617464B1 (en) 1990-02-16
FR2617464A1 (en) 1989-01-06
US4879941A (en) 1989-11-14

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