EP0389358B1 - Opening system for spreading wings on a projectile - Google Patents

Opening system for spreading wings on a projectile Download PDF

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Publication number
EP0389358B1
EP0389358B1 EP90400758A EP90400758A EP0389358B1 EP 0389358 B1 EP0389358 B1 EP 0389358B1 EP 90400758 A EP90400758 A EP 90400758A EP 90400758 A EP90400758 A EP 90400758A EP 0389358 B1 EP0389358 B1 EP 0389358B1
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EP
European Patent Office
Prior art keywords
component
chamber
bore
winglets
opening system
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP90400758A
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German (de)
French (fr)
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EP0389358A1 (en
Inventor
Bernard Baubry
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Thomson Brandt Armements SA
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Thomson Brandt Armements SA
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Priority to AT90400758T priority Critical patent/ATE97483T1/en
Publication of EP0389358A1 publication Critical patent/EP0389358A1/en
Application granted granted Critical
Publication of EP0389358B1 publication Critical patent/EP0389358B1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F42B10/20—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel deployed by combustion gas pressure, or by pneumatic or hydraulic forces

Definitions

  • the present invention relates to a system for the combined opening of the fins of a tail unit deploying for projectiles, in particular mortar ammunition, provided with a propellant.
  • tail span larger than the caliber at the rear of a munition there are many reasons that may make it necessary, or at least preferable, to have a tail span larger than the caliber at the rear of a munition: long length of the ammunition, optimization of precision, presence of a propellant to increase range, etc.
  • a tail unit will advantageously be provided capable of assuming a folded position at rest, to make it fit into the caliber in order to reduce the size of the ammunition and to facilitate handling and storage.
  • this ability to be folded becomes a necessity, to allow the introduction of the ammunition into the barrel.
  • This type of empennage commonly called deploying empennage, is formed by a plurality of fins arranged around the munition. Their opening must meet three essential requirements: first, it must be triggered after the ammunition leaves, to protect the fins against shocks. On the other hand, the deployment must be complete and irreversible due to the radial influence of such a tail on the trajectory of the munition. Finally, the triggering of the propellant, positioned inside the projectile, must occur only after total and irreversible opening of the tail; this thus constituting a safety device for a projectile provided with a propellant.
  • Document US-A-3,304,030 describes a system for opening a deploying tail for a projectile, formed from a plurality of fins articulated on axes and distributed around the projectile, the system comprising a part capable of slide in leaktight manner, under the action of the pressure of a gas, from a first position to a second position so as to drive means for pivoting the fins, the fins being fully deployed when this part reaches the second position.
  • the projectile described in this document does not have a propellant, and the opening system is therefore not designed for the type of projectiles which interests us.
  • the object of the present invention is to provide a system for the combined opening of the fins of a deploying tail unit which is simple and which reliably meets these three requirements.
  • the subject of the invention is a system for opening a deploying tail for a projectile, as defined by claims 1 to 12.
  • a pressure sensitive delay igniter will advantageously be used, which will be triggered by the pressure inside the barrel at the time of the firing, the time delay being greater than the ejection time of ammunition.
  • the projectile is a self-propelled munition, of the type which is launched with mortars.
  • the body 1 of the ammunition in one or more sections, contains active elements such as an explosive charge 2.
  • the rear end of the body 1 has a tapped axial bore 3, into which a block 4 formed of a part is screwed cylindrical threaded 4a and a rear part consisting of radial plates 4b integral with part 4a and regularly distributed around the longitudinal axis XX.
  • Each plate 4b carries a perpendicular axis 5 on which is articulated the base 6a of a fin 6.
  • a tail fin with four fins has been shown in the drawings for reasons of clarity, these are more generally the number of six or eight, this number being determined by or for aerodynamic reasons.
  • the part 4a of the block 4 has a first axial bore 7 opening between the plates 4b, and in which a part of revolution 8 is slidably mounted.
  • a seal 9 surrounds the base of the part 8, to seal between it -ci and the wall of the bore 7.
  • the part 8 has a general bell shape, the top of which has a threaded orifice in which is fixed in leaktight manner, by means of a seal 11, a pyrotechnic assembly 10 provided with a pressure-sensitive delay igniter.
  • the function of the assembly 10 is to generate a gas under pressure in a sealed chamber 12 delimited by the interior of the part 8 and the bottom of the bore 7.
  • the external wall of the part 8 forms a first cylindrical part 8a closely matching the wall of the bore 7, a second cylindrical part 8b of smaller diameter, separated from the part 8a by a frustoconical shoulder 8c, and a groove 13 whose front edge is a frustoconical shoulder 8d, the bottom a cylindrical part 8e and the rear edge a shoulder 8f normal to the axis XX, followed by a cylindrical end portion 8g.
  • a tooth 14 is engaged formed at the periphery of the base 6a of each fin 6.
  • each tooth 14 has a shape which substantially matches the profile of the groove 13 to register there.
  • the tooth 14 forms a projection on the internal side of the base part 6a, its front side 14a being in the extension of the front side of the part 6a.
  • Figure 2 shows the fins 6 fully deployed: the outer side of their base part 6a is applied against the bottom of the cylindrical part 4a of the block 4, while the front side is applied to the cylindrical surface 8b of the part 8 which has left the bottom of the bore 7 under the effect of a gas pressure generated in the chamber 12 by the pyrotechnic assembly 10. Note that in this position, the part 8 is blocked towards the rear because the shoulder 8c abuts against the base part 6a of the fins. On the other hand, the seal 9 at the periphery of the part 8 is always in contact on the internal wall of the bore 7, so that the pressure is maintained in the chamber 12 and prevents the return towards the bottom of the bore of the part 8.
  • the fins 6 are therefore perfectly locked between the two perpendicular bearings formed by the bottom of the part 4a and the surface 8b. It will be noted, by means of the drawings, that the complete deployment is carried out irreversibly as soon as the external edge of the shoulder 8d arrives at the level of the axis 5, that is to say before the part 8 has reaches its extreme rear position.
  • an additional security may consist of one or more flexible blades 15, fixed on the bottom of the block 4 , and ensuring a mechanical blocking of the part 8 by coming to brace in the groove 13, FIG. 2.
  • the projectile is introduced into a weapon, preferably provided with a device for protecting the fins as mentioned previously, the fins 6 being in the position of FIG. 1, that is to say inside of caliber.
  • the pressure in the barrel of the weapon triggers the delay igniter of the pyrotechnic assembly 10, the timing of which is chosen such that the pressurization in the chamber 12 takes place only after the ammunition has left the muzzle of the barrel.
  • the part 8 is then driven irreversibly to the position of Figure 2 described above.
  • seals 9 and 11 ensuring the tightness of the chamber 12 must be chosen to be strong enough to withstand the temperature and pressure conditions inside the barrel. In practice, butadiene-acrylic seals are found to be satisfactory.
  • the opening system according to the invention of Figures 3 and 4 provided for a projectile provided with a propellant, comprises the same elements operating in the same way as those of the system of FIGS. 1 and 2 and, for this reason, they will not be re-described here in detail and they will be designated by the same numerical references, accompanied by the sign '.
  • an ignition device consists, for example of several igniters 17 'regularly distributed at the base of a fuel 2' contained inside the propellant and of a pyrotechnic relay 18 'ensuring the ignition of 17 'igniters.
  • the relay 18 ' is located at the end of a second chamber, for example a bore 19' the other end of which opens into the bore 7 '.
  • the bore 19 ' is coaxial with the bore 7', and it extends somewhat inside the latter, in an annular part 20 '.
  • the part 8 'engaged in the bore 7' and ensuring the pivoting of the fins 6 ' is provided internally with a cylindrical axial rod 21', fixed to the bottom of the part 8 ', and the end of which free is substantially in the same plane as its base edge inside the bore 7 '.
  • the rod 21 ' has the same diameter as the bore 19', so as to be capable of being engaged therein intimately and sealingly by means of a seal 22 '.
  • the rod 21 'and the seal 22' thus constituting a means for closing the second chamber 19 '.
  • the end of the rod 21 leaves the bore 19' after the fins have been fully deployed in an irreversible manner, that is to say, as can be seen by observing the drawings, after the 'external edge of the shoulder 8d' has reached the level of the axis 5 '. Consequently, the pressure in the chamber 12 ′ is not transmitted to the relay 18 ′ to trigger it only after the fins 6 ′ have been locked in the deployed position.
  • one or more flexible blades 15 ′ can be fixed to the bottom of the block 4 ′ to provide additional mechanical locking of the part 8 ′ in the rear position.
  • the device of the invention has the advantage of being mechanically simple, and, therefore, reliable and easy to implement. Although particularly suitable for the type of ammunition for mortar, it can be applied to all kinds of projectiles, only the delay igniter used to establish the deployment pressure of the fins having to be changed or modified according to the triggering mode usable, for example electronic. In addition, if desired, one can easily provide the system of the invention with additional security intended to keep the ammunition in the inert state until the complete deployment of the fins, in the form of a contactor in an electrical circuit for activating the ammunition, the contactor being closed by the part 8 or 8 ′ when it reaches its extreme rear position.

Abstract

According to the invention, the system should reliably provide for the complete and irreversible unfolding of the fins of the tail unit, after the departure of the projectile, and should enable the triggering, after the locking of the fins, of an ignition device for the propulsion unit contained in the projectile. A system for opening an unfolding tail unit for projectiles provided with a propulsion unit, formed by a plurality of fins hinged on shafts and distributed around the projectile, comprises a part capable of sliding imperviously from a first position to a second position in a first bore, so as to drive means for pivoting the fins. With the first bore, this part defines a first chamber and can be shifted by gas pressure in this chamber, generated by a gas generator, the fins being completely unfolded during the shifting of the part towards the second position. The opening system also includes a closing means fixed to the sliding part making it possible, before it has reached the second position, to isolate the first chamber from a second chamber and prevent the triggering of an ignition device for the propulsion unit under the effect of a pressure.

Description

La présente invention concerne un système d'ouverture conjuguée des ailettes d'un empennage déployant pour des projectiles, notamment des munitions pour mortier, munies d'un propulseur.The present invention relates to a system for the combined opening of the fins of a tail unit deploying for projectiles, in particular mortar ammunition, provided with a propellant.

De multiples raisons peuvent rendre nécessaire, ou tout au moins préférable, la présence d'un empennage d'envergure supérieure au calibre à l'arrière d'une munition: longueur importante de la munition, optimisation de la précision, présence d'un propulseur pour augmenter la portée, etc. En général, un tel empennage sera avantageusement prévu apte à prendre une position repliée au repos, pour le faire s'inscrire dans le calibre afin de réduire l'encombrement des munitions et d'en faciliter la manutention et le rangement. Pour des munitions destinées à être lancées avec une arme, cette aptitude à être replié devient une nécessité, pour permettre l'introduction de la munition dans le canon.There are many reasons that may make it necessary, or at least preferable, to have a tail span larger than the caliber at the rear of a munition: long length of the ammunition, optimization of precision, presence of a propellant to increase range, etc. In general, such a tail unit will advantageously be provided capable of assuming a folded position at rest, to make it fit into the caliber in order to reduce the size of the ammunition and to facilitate handling and storage. For ammunition intended to be launched with a weapon, this ability to be folded becomes a necessity, to allow the introduction of the ammunition into the barrel.

Ce type d'empennage, communément appelé empennage déployant, est formé d'une pluralité d'ailettes disposées autour de la munition. Leur ouverture doit satisfaire à trois exigences essentielles : d'abord, elle doit être déclenchée postérieurement au départ de la munition, pour préserver les ailettes contre les chocs. D'autre part, le déploiement doit être complet et irréversible du fait de l'influence radiale d'un tel empennage sur la trajectoire de la munition. Enfin le déclenchement du propulseur, positionné à l'intérieur du projectile, ne doit se produire qu'après ouverture totale et irréversible de l'empennage ; ceci constituant ainsi, un dispositif de sécurité pour un projectile muni d'un propulseur.This type of empennage, commonly called deploying empennage, is formed by a plurality of fins arranged around the munition. Their opening must meet three essential requirements: first, it must be triggered after the ammunition leaves, to protect the fins against shocks. On the other hand, the deployment must be complete and irreversible due to the radial influence of such a tail on the trajectory of the munition. Finally, the triggering of the propellant, positioned inside the projectile, must occur only after total and irreversible opening of the tail; this thus constituting a safety device for a projectile provided with a propellant.

Le document US-A-3.304.030 décrit un système d'ouverture d'un empennage déployant pour projectile, formé d'une pluralité d'ailettes articulées sur des axes et répartie autour du projectile, le système comprenant une pièce apte à coulisser de façon étanche, sous l'action de la pression d'un gaz, d'une première position à une seconde position de manière à entraîner des moyens de pivotements des ailettes, les ailettes étant complètement déployées lorsque cette pièce atteint la seconde position. Cependant, le projectile décrit dans ce document ne possède pas de propulseur, et le système d'ouverture n'est donc pas conçu pour le type de projectiles qui nous intéresse.Document US-A-3,304,030 describes a system for opening a deploying tail for a projectile, formed from a plurality of fins articulated on axes and distributed around the projectile, the system comprising a part capable of slide in leaktight manner, under the action of the pressure of a gas, from a first position to a second position so as to drive means for pivoting the fins, the fins being fully deployed when this part reaches the second position. However, the projectile described in this document does not have a propellant, and the opening system is therefore not designed for the type of projectiles which interests us.

La présente invention a pour objet de prévoir un système d'ouverture conjuguée des ailettes d'un empennage déployant qui soit simple et qui réponde de façon fiable à ces trois exigences.The object of the present invention is to provide a system for the combined opening of the fins of a deploying tail unit which is simple and which reliably meets these three requirements.

Plus précisément, l'invention a pour objet un système d'ouverture d'un empennage déployant pour projectile, tel que défini par les revendications 1 à 12.More specifically, the subject of the invention is a system for opening a deploying tail for a projectile, as defined by claims 1 to 12.

Pour une munition destinée à être lancée avec une arme, on utilisera avantageusement un allumeur à retard sensible à la pression, qui sera déclenché par la pression à l'intérieur du canon au moment du tir, la temporisation étant supérieure au temps d'éjection de la munition.For a munition intended to be launched with a weapon, a pressure sensitive delay igniter will advantageously be used, which will be triggered by the pressure inside the barrel at the time of the firing, the time delay being greater than the ejection time of ammunition.

L'invention sera mieux comprise à l'aide des explications qui vont suivre et des dessins joints, parmi lesquels :

  • la figure 1 est une vue en coupe axiale de l'arrière d'une munition comportant un empennage en position repliée pourvu d'un système d'ouverture basé sur un principe connu de l'art antérieur ;
  • la figure 2 est une vue similaire à la figure 1, mais montrant l'empennage déployé ; et
  • les figures 3 et 4 sont les mêmes vues que les figures 1 et 2, respectivement mais illustrant un système d'ouverture selon l'invention pour munitions munies d'un propulseur.
The invention will be better understood with the aid of the explanations which follow and of the accompanying drawings, among which:
  • Figure 1 is an axial sectional view of the rear of a munition comprising a tail in the folded position provided with an opening system based on a principle known from the prior art;
  • Figure 2 is a view similar to Figure 1, but showing the deployed tail; and
  • Figures 3 and 4 are the same views as Figures 1 and 2, respectively but illustrating an opening system according to the invention for ammunition with a propellant.

Le projectile dont la partie arrière est représentée partiellement aux figures 1 et 2 est une munition sans autopropulsion, du type de celles qui sont lancées avec des mortiers.The projectile, the rear part of which is partially shown in FIGS. 1 and 2, is a self-propelled munition, of the type which is launched with mortars.

Le corps 1 de la munition, en un ou plusieurs tronçons, renferme des éléments actifs telles qu'une charge explosive 2. L'extrémité arrière du corps 1 présente un alésage axial taraudé 3, dans lequel est vissé un bloc 4 formé d une partie cylindrique filetée 4a et d'une partie arrière consistant en des plaques radiales 4b solidaires de la partie 4a et régulièrement réparties autour de l'axe longitudinal X-X. Chaque plaque 4b porte un axe perpendiculaire 5 sur lequel est articulée la base 6a d'une ailette 6. Bien qu'on ait représenté un empennage à quatre ailettes dans les dessins pour des raisons de clarté, celles-ci sont plus généralement au nombre de six ou huit, ce nombre étant déterminé par ou pour des raisons aérodynamiques.The body 1 of the ammunition, in one or more sections, contains active elements such as an explosive charge 2. The rear end of the body 1 has a tapped axial bore 3, into which a block 4 formed of a part is screwed cylindrical threaded 4a and a rear part consisting of radial plates 4b integral with part 4a and regularly distributed around the longitudinal axis XX. Each plate 4b carries a perpendicular axis 5 on which is articulated the base 6a of a fin 6. Although a tail fin with four fins has been shown in the drawings for reasons of clarity, these are more generally the number of six or eight, this number being determined by or for aerodynamic reasons.

La partie 4a du bloc 4 présente un premier alésage axial 7 s'ouvrant entre les plaques 4b, et dans lequel est montée coulissante une pièce de révolution 8. Un joint 9 entoure la base de la pièce 8, pour assurer l'étanchéité entre celle-ci et la paroi de l'alésage 7.The part 4a of the block 4 has a first axial bore 7 opening between the plates 4b, and in which a part of revolution 8 is slidably mounted. A seal 9 surrounds the base of the part 8, to seal between it -ci and the wall of the bore 7.

La pièce 8 a une forme générale en cloche dont le sommet présente un orifice taraudé dans lequel est fixé de façon étanche, au moyen d'un joint 11, un ensemble pyrotechnique 10 pourvu d'un allumeur à retard sensible à la pression. L'ensemble 10 a pour fonction d'engendrer un gaz sous pression dans une chambre étanche 12 délimitée par l'intérieur de la pièce 8 et le fond de l'alésage 7.The part 8 has a general bell shape, the top of which has a threaded orifice in which is fixed in leaktight manner, by means of a seal 11, a pyrotechnic assembly 10 provided with a pressure-sensitive delay igniter. The function of the assembly 10 is to generate a gas under pressure in a sealed chamber 12 delimited by the interior of the part 8 and the bottom of the bore 7.

De la base au sommet, la paroi externe de la pièce 8 forme une première partie cylindrique 8a épousant intimement la paroi de l'alésage 7, une seconde partie cylindrique 8b de moindre diamètre, séparée de la partie 8a par un épaulement tronconique 8c, et une gorge 13 dont le bord avant est un épaulement tronconique 8d, le fond une partie cylindrique 8e et le bord arrière un épaulement 8f normal à l'axe X-X, suivi d une partie cylindrique d'extrémité 8g. Dans ladite gorge, est engagée une dent 14 formée à la périphérie de la base 6a de chaque ailette 6.From the base to the top, the external wall of the part 8 forms a first cylindrical part 8a closely matching the wall of the bore 7, a second cylindrical part 8b of smaller diameter, separated from the part 8a by a frustoconical shoulder 8c, and a groove 13 whose front edge is a frustoconical shoulder 8d, the bottom a cylindrical part 8e and the rear edge a shoulder 8f normal to the axis XX, followed by a cylindrical end portion 8g. In said groove, a tooth 14 is engaged formed at the periphery of the base 6a of each fin 6.

A la figure 1 qui montre les ailettes repliées et la pièce 8 au fond de l'alésage 7, il apparaît clairement que chaque dent 14 a une forme qui épouse sensiblement le profil de la gorge 13 pour s'y inscrire. La dent 14 forme une avancée sur le côté interne de la partie de base 6a, son côté avant 14a étant dans le prolongement du côté avant de la partie 6a.In Figure 1 which shows the folded fins and the part 8 at the bottom of the bore 7, it clearly appears that each tooth 14 has a shape which substantially matches the profile of the groove 13 to register there. The tooth 14 forms a projection on the internal side of the base part 6a, its front side 14a being in the extension of the front side of the part 6a.

Dans leur position repliée, figure 1, tant que la pièce 8 est immobile, les ailettes 6 sont empêchées de pivoter vers l'extérieur par la partie vive de leur côté arrière 14b qui se trouve en butée contre l'épaulement 8f. Leur pivotement vers l'intérieur est interdit du fait que la partie du côté interne de la base 6a à l'arrière de la dent 14 porte sur la partie cylindrique d'extrémité 8g. A noter qu'une sécurité peut être prévue pour maintenir la pièce 8 immobile dans l'alésage 7 avant le fonctionnement du système, consistant en une goupille de cisaillement, non montrée, engagée dans des alésages radiaux alignés dans la paroi cylindrique 8a et la paroi de l'alésage 7. On peut signaler également un dispositif de protection mécanique des ailettes, consistant en une entretoise placée axialement derrière la pièce 8 et portant des volets radiaux de largeur supérieure à celle des ailettes ledit dispositif restant dans l'arme lors du lancement de la munition.In their folded position, Figure 1, as long as the part 8 is stationary, the fins 6 are prevented from pivoting outwards by the living part of their rear side 14b which is in abutment against the shoulder 8f. Their inward pivoting is prohibited because the part of the internal side of the base 6a behind the tooth 14 bears on the cylindrical end part 8g. Note that security can be provided to keep the part 8 immobile in the bore 7 before the system operates, consisting of a shear pin, not shown, engaged in radial bores aligned in the cylindrical wall 8a and the wall of the bore 7. It is also possible to indicate a device for mechanical protection of the fins, consisting of a spacer placed axially behind the part 8 and carrying radial flaps of width greater than that of the fins, said device remaining in the weapon during launching. ammunition.

La figure 2 montre les ailettes 6 déployées complètement : le côté externe de leur partie de base 6a est appliquée contre le fond de la partie cylindrique 4a du bloc 4, alors que le côté avant est appliqué sur la surface cylindrique 8b de la pièce 8 qui a quitté le fond de l'alésage 7 sous l'effet d'une pression de gaz engendrée dans la chambre 12 par l'ensemble pyrotechnique 10. A noter que dans cette position, la pièce 8 est bloquée vers l'arrière du fait que l'épaulement 8c est en butée contre la partie de base 6a des ailettes. D'autre part, le joint 9 à la périphérie de la pièce 8 se trouve toujours en contact sur la paroi interne de l'alésage 7, de sorte que la pression est maintenue dans la chambre 12 et empêche le retour vers le fond de l'alésage de la pièce 8. Les ailettes 6 sont donc parfaitement bloquées entre les deux portées perpendiculaires formées par le fond de la partie 4a et la surface 8b. On remarquera, au moyen des dessins, que le déploiement complet est réalisé de façon irréversible dès que l'arête externe de l'épaulement 8d arrive au niveau de l'axe 5, c'est-à-dire avant que la pièce 8 ait atteint sa position arrière extrême.Figure 2 shows the fins 6 fully deployed: the outer side of their base part 6a is applied against the bottom of the cylindrical part 4a of the block 4, while the front side is applied to the cylindrical surface 8b of the part 8 which has left the bottom of the bore 7 under the effect of a gas pressure generated in the chamber 12 by the pyrotechnic assembly 10. Note that in this position, the part 8 is blocked towards the rear because the shoulder 8c abuts against the base part 6a of the fins. On the other hand, the seal 9 at the periphery of the part 8 is always in contact on the internal wall of the bore 7, so that the pressure is maintained in the chamber 12 and prevents the return towards the bottom of the bore of the part 8. The fins 6 are therefore perfectly locked between the two perpendicular bearings formed by the bottom of the part 4a and the surface 8b. It will be noted, by means of the drawings, that the complete deployment is carried out irreversibly as soon as the external edge of the shoulder 8d arrives at the level of the axis 5, that is to say before the part 8 has reaches its extreme rear position.

Bien que la pièce 8 soit normalement bloquée lorsqu'elle atteint sa position extrême arrière par le seul fait du maintien de la pression dans la chambre 12, une sécurité supplémentaire peut consister en une ou plusieurs lames flexibles 15, fixées sur le fond du bloc 4, et assurant un blocage mécanique de la pièce 8 en venant s'arc-bouter dans la gorge 13, figure 2.Although the part 8 is normally blocked when it reaches its extreme rear position by the mere fact of maintaining the pressure in the chamber 12, an additional security may consist of one or more flexible blades 15, fixed on the bottom of the block 4 , and ensuring a mechanical blocking of the part 8 by coming to brace in the groove 13, FIG. 2.

En fonctionnement, le projectile est introduit dans une arme, de préférence muni d'un dispositif de protection des ailettes comme mentionné précédemment, les ailettes 6 se trouvant dans la position de la figure 1, c'est-à-dire à l'intérieur du calibre. Au moment du tir, la pression dans le canon de l'arme déclenche l'allumeur à retard de l'ensemble pyrotechnique 10, dont la temporisation est choisie telle que la mise en pression dans la chambre 12 n'ait lieu qu'après que la munition ait quitté la bouche du canon. Sous l'effet de ladite pression, la pièce 8 est alors entraînée de façon irréversible jusqu'à la position de la figure 2 décrite plus haut.In operation, the projectile is introduced into a weapon, preferably provided with a device for protecting the fins as mentioned previously, the fins 6 being in the position of FIG. 1, that is to say inside of caliber. When firing, the pressure in the barrel of the weapon triggers the delay igniter of the pyrotechnic assembly 10, the timing of which is chosen such that the pressurization in the chamber 12 takes place only after the ammunition has left the muzzle of the barrel. Under the effect of said pressure, the part 8 is then driven irreversibly to the position of Figure 2 described above.

Bien entendu, les joints 9 et 11 assurant l'étanchéité de la chambre 12 doivent être choisis suffisamment résistants pour supporter les conditions de température et de pression à l'intérieur du canon. En pratique, des joints butadiène-acrylique s'avèrent satisfaisants.Of course, the seals 9 and 11 ensuring the tightness of the chamber 12 must be chosen to be strong enough to withstand the temperature and pressure conditions inside the barrel. In practice, butadiene-acrylic seals are found to be satisfactory.

Le système d'ouverture selon l'invention des figures 3 et 4, prévu pour un projectile muni d'un propulseur, comporte les mêmes éléments fonctionnant de la même façon que ceux du système des figures 1 et 2 et, pour cette raison, on ne les redécrira pas ici dans le détail et on les désignera par les mêmes références numériques, assorties du signe'.The opening system according to the invention of Figures 3 and 4, provided for a projectile provided with a propellant, comprises the same elements operating in the same way as those of the system of FIGS. 1 and 2 and, for this reason, they will not be re-described here in detail and they will be designated by the same numerical references, accompanied by the sign '.

Le corps 1' dans lequel est fixé de façon étanche, au moyen d'un joint 16', le bloc 4' est la partie arrière d'un tronçon de munition renfermant du combustible 2' destiné à la propulsion, celle-ci étant assurée par des tuyères, non montrées, traversant le bloc 4' et débouchant entre les ailettes 6'. Pour assurer le démarrage du propulseur, un dispositif d'allumage est constitué, par exemple de plusieurs allumeurs 17' régulièrement répartis à la base d'un combustible 2' contenu à l'intérieur du propulseur et d'un relais pyrotechnique 18' assurant la mise à feu des allumeurs 17'.The body 1 'in which is fixed in a leaktight manner, by means of a seal 16', the block 4 'is the rear part of a section of ammunition containing fuel 2' intended for propulsion, the latter being ensured by nozzles, not shown, passing through the block 4 'and emerging between the fins 6'. To ensure the starting of the propellant, an ignition device consists, for example of several igniters 17 'regularly distributed at the base of a fuel 2' contained inside the propellant and of a pyrotechnic relay 18 'ensuring the ignition of 17 'igniters.

Selon l'invention, le relais 18' se trouve à l'extrémité d'une deuxième chambre, par exemple un alésage 19' dont l'autre extrémité débouche dans l'alésage 7'. Dans l'exemple de réalisation montré, l'alésage 19' est coaxial avec l'alésage 7', et il se prolonge quelque peu à l'intérieur de ce dernier, dans une partie annulaire 20'.According to the invention, the relay 18 'is located at the end of a second chamber, for example a bore 19' the other end of which opens into the bore 7 '. In the embodiment shown, the bore 19 'is coaxial with the bore 7', and it extends somewhat inside the latter, in an annular part 20 '.

D'autre part, la pièce 8' engagée dans l'alésage 7' et assurant le pivotement des ailettes 6' est pourvue intérieurement d'une tige axiale cylindrique 21', fixée au fond de la pièce 8', et dont l'extrémité libre se trouve sensiblement dans le même plan que son bord de base à l'intérieur de l'alésage 7'. La tige 21' a le même diamètre que l'alésage 19', de manière à être susceptible d'y être engagée intimement et de façon étanche au moyen d'un joint 22'. La tige 21' et le joint 22' constituant, ainsi, un moyen de fermeture de la deuxième chambre 19'. Ainsi, à la figure 3 représentant la pièce 8 au fond de l'alésage et les ailettes 6' repliée, la tige 21' est engagée dans l'alésage 19', de sorte qu'il n'y a pas de communication entre la chambre 12' et la partie de l'alésage 19' ouverte sur le relais 18'.On the other hand, the part 8 'engaged in the bore 7' and ensuring the pivoting of the fins 6 'is provided internally with a cylindrical axial rod 21', fixed to the bottom of the part 8 ', and the end of which free is substantially in the same plane as its base edge inside the bore 7 '. The rod 21 'has the same diameter as the bore 19', so as to be capable of being engaged therein intimately and sealingly by means of a seal 22 '. The rod 21 'and the seal 22' thus constituting a means for closing the second chamber 19 '. Thus, in Figure 3 showing the part 8 at the bottom of the bore and the fins 6 'folded, the rod 21' is engaged in the bore 19 ', so that there is no communication between the chamber 12 'and the part of the bore 19' open on the relay 18 '.

A la figure 4, la pièce 8' est en position arrière extrême, les ailettes 6' étant déployées. L'extrémité libre de la tige 21' est sortie très légèrement de l'alésage 19', de sorte que la chambre 12' communique maintenant avec celui-ci.In Figure 4, the part 8 'is in the extreme rear position, the fins 6' being deployed. The free end of the rod 21 'is slightly out of the bore 19', so that the chamber 12 'now communicates with it.

En fonctionnement, l'extrémité de la tige 21' quitte l'alésage 19' après que les ailettes aient été complètement déployées de façon irréversible, c'est-à-dire, comme on peut le remarquer en observant les dessins, après que l'arête externe de l'épaulement 8d' ait atteint le niveau de l'axe 5'. Par conséquent, la pression dans la chambre 12' n'est transmise au relais 18' pour le déclencher qu'après que les ailettes 6' aient été bloquées en position déployée.In operation, the end of the rod 21 'leaves the bore 19' after the fins have been fully deployed in an irreversible manner, that is to say, as can be seen by observing the drawings, after the 'external edge of the shoulder 8d' has reached the level of the axis 5 '. Consequently, the pressure in the chamber 12 ′ is not transmitted to the relay 18 ′ to trigger it only after the fins 6 ′ have been locked in the deployed position.

On remarquera qu'ici, les gaz destinés à la propulsion peuvent pénétrer par l'alésage 19' dans la chambre 12'. Il est donc important que les joints 9' et 11' jouent pleinement leur rôle, pour éviter des fuites qui pourraient être préjudiciables au rendement du propulseur et, par voie de conséquence, à la précision du tir. Comme précédemment, une ou plusieurs lames flexibles 15' peuvent être fixées sur le fond du bloc 4' pour assurer un blocage supplémentaire de nature mécanique de la pièce 8' en position arrière.It will be noted that here, the gases intended for the propulsion can penetrate through the bore 19 'in the chamber 12'. It is therefore important that the seals 9 'and 11' play their full role, to avoid leaks which could be detrimental to the performance of the propellant and, consequently, to the accuracy of the shot. As before, one or more flexible blades 15 ′ can be fixed to the bottom of the block 4 ′ to provide additional mechanical locking of the part 8 ′ in the rear position.

Le dispositif de l'invention présente l'avantage d'être mécaniquement simple, et, par conséquent, fiable et facile à mettre en oeuvre. Bien que particulièrement adapté au type de munitions pour mortier, il peut s'appliquer aussi bien à tous genres de projectiles, seul l'allumeur à retard servant à établir la pression de déploiement des ailettes devant être changé ou modifié en fonction du mode de déclenchement utilisable, par exemple électronique. En outre, si on le désire, on peut doter facilement le système de l'invention d'une sécurité supplémentaire ayant pour but de maintenir la munition à l'état inerte jusqu'au déploiement complet des ailettes, sous la forme d'un contacteur dans un circuit électrique d'activation de la munition, le contacteur étant fermé par la pièce 8 ou 8' lorsqu'elle atteint sa position extrême arrière.The device of the invention has the advantage of being mechanically simple, and, therefore, reliable and easy to implement. Although particularly suitable for the type of ammunition for mortar, it can be applied to all kinds of projectiles, only the delay igniter used to establish the deployment pressure of the fins having to be changed or modified according to the triggering mode usable, for example electronic. In addition, if desired, one can easily provide the system of the invention with additional security intended to keep the ammunition in the inert state until the complete deployment of the fins, in the form of a contactor in an electrical circuit for activating the ammunition, the contactor being closed by the part 8 or 8 ′ when it reaches its extreme rear position.

Claims (12)

  1. System for opening deployable fins for a projectile, the system being formed by a plurality of winglets (6') articulated on pins (5') and distributed around the projectile, and by a component (8') capable of sliding in a sealed fashion from a first position to a second position in a first bore (7') so as to entrain means for pivoting the winglets (6'), the component (8) defining, together with the first bore (7'), a first chamber (12') and being capable of moving by means of the pressure of a gas generated by a gas generator in the first chamber (12'), the winglets (6') being completely deployed when the component (8') reaches the second position, the system being characterised in that since the projectile further comprises a fuel (2') intended to propel it and whose combustion is initiated by an ignition device (17',18') triggering under the action of a pressure, the said system includes a second chamber (19') and a closure means (21', 22') fixed onto the component (8'), engaging in a sealed fashion in the second chamber in order to isolate this second chamber from the first one for so long as the component (8') has not reached its second position, and letting the gas contained in the first chamber (12') pass towards the second chamber (19') when the second position has been reached, in order to trigger the said ignition device.
  2. Opening system according to Claim 1, characterised in that the said second chamber (19') is formed in a second axial bore at the bottom of the first bore (7') and in that the closure means include an axial rod (21') of the same diameter as the second bore and fixed to the bottom of the component (8'), and a seal (22') positioned around the rod (21') so that the rod (21') engages in a sealed manner in the second bore (19').
  3. Opening system according to either one of the preceding claims, characterised in that the pressurised gas in the chamber (12') is generated by a pyrotechnic unit (10') provided with a pressure-sensitive ignitor with retard for the purpose of using it for deployable fins of a munition intended to be launched with a weapon, the ignitor with retard therefore being triggered by the pressure in the barrel upon firing.
  4. Opening system according to any one of the preceding claims, characterised in that the ignition device consists of a plurality of ignitors (17') evenly distributed at the base of the fuel (2') contained inside the booster and a pyrotechnic relay (18') for firing the ignitors (17').
  5. Opening system according to any one of the preceding claims, characterised in that the first bore (7') is positioned in a block (4') located to the rear of the projectile.
  6. Opening system according to any one of the preceding claims, characterised in that the second position of the component (8') is to the rear of the first position of the said component (8').
  7. Opening system according to any one of the preceding claims, characterised in that the completely deployed winglets (6') are kept in this position by blocking means.
  8. Opening system according to Claim 7, characterised in that the said means for blocking the winglets (6') in the deployed position consist of a cylindrical bearing surface (8b') of the component (8') and the bottom of the block (4') carrying the winglets, which interact when the component (8') recoils towards its second position, in order to form two perpendicular bearing surfaces against which two adjacent sides of the base part (6a') of the deployed winglets bear.
  9. Opening system according to any one of the preceding claims, characterised in that the means for pivoting the winglets (6') consist of a tooth (14') of the base part (6a') of the winglets, engaged in a peripheral groove (13') in the component (8') when the latter is in its first position.
  10. Opening system according to any one of the preceding claims, characterised in that the second position of the component (8') is determined by abutment of a frustoconical shoulder (8c') of the latter against the base part (6a') of the winglets after these have been blocked in the deployed position.
  11. Opening system according to any one of the preceding claims, characterised in that it furthermore comprises a mechanical means for blocking the component (8') in its second position, consisting of at least one flexible strip (15') fixed to the bottom of the block (4'), which is shored up against a shoulder (8f') at the periphery of the component (8').
  12. Opening system according to any one of the preceding claims, characterised in that the pivoting means and the means for blocking the winglets (6') in the deployed position are provided so as to act during the displacement of the component (8') before it has reached the second position, and in that the component (8') furthermore includes a means for isolating the chamber (12') from a second chamber which is open onto a sensitive ignition device.
EP90400758A 1989-03-24 1990-03-20 Opening system for spreading wings on a projectile Expired - Lifetime EP0389358B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT90400758T ATE97483T1 (en) 1989-03-24 1990-03-20 TAIL SPREADING SYSTEM FOR ONE MISSLE.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8903924 1989-03-24
FR8903924A FR2644880B1 (en) 1989-03-24 1989-03-24 OPENING SYSTEM FOR A PROJECTILE DEPLOYMENT STYLE

Publications (2)

Publication Number Publication Date
EP0389358A1 EP0389358A1 (en) 1990-09-26
EP0389358B1 true EP0389358B1 (en) 1993-11-18

Family

ID=9380048

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90400758A Expired - Lifetime EP0389358B1 (en) 1989-03-24 1990-03-20 Opening system for spreading wings on a projectile

Country Status (6)

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US (1) US5082203A (en)
EP (1) EP0389358B1 (en)
AT (1) ATE97483T1 (en)
CA (1) CA2012925A1 (en)
DE (1) DE69004604T2 (en)
FR (1) FR2644880B1 (en)

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE9102702L (en) * 1991-09-18 1993-03-19 Bofors Ab warhead
US5464173A (en) * 1994-12-16 1995-11-07 The United States Of America As Represented By The Secretary Of The Navy Subassembly means
US6168111B1 (en) * 1997-03-03 2001-01-02 The United States Of America As Represented By The Secretary Of The Army Fold-out fin
US6224013B1 (en) * 1998-08-27 2001-05-01 Lockheed Martin Corporation Tail fin deployment device
DE10015514B4 (en) * 2000-03-30 2007-10-04 Rheinmetall Waffe Munition Gmbh Wing stabilized projectile
DE10205043C5 (en) * 2002-02-07 2010-06-17 Diehl Bgt Defence Gmbh & Co. Kg From a tube to be closed missile with überkalibrigem tail
US6559370B1 (en) * 2002-08-06 2003-05-06 The United States Of America As Represented By The Secretary Of The Navy Submarine countermeasure vehicle with folding propeller
US8338769B1 (en) * 2008-02-07 2012-12-25 Simmonds Precision Products, Inc. Pyrotechnic fin deployment and retention mechanism
US8438977B2 (en) * 2008-12-25 2013-05-14 Lockheed Martin Corporation Projectile having deployable fin
US9068807B1 (en) * 2009-10-29 2015-06-30 Lockheed Martin Corporation Rocket-propelled grenade
US9140528B1 (en) 2010-11-16 2015-09-22 Lockheed Martin Corporation Covert taggant dispersing grenade
US8415598B1 (en) * 2010-12-20 2013-04-09 The United States Of America As Represented By The Secretary Of The Army Extendable fins for a tube-launched projectile
US8866057B2 (en) * 2011-10-17 2014-10-21 Raytheon Company Fin deployment method and apparatus
JP6212898B2 (en) * 2012-03-29 2017-10-18 ダイキン工業株式会社 High speed flying object
US9423222B1 (en) 2013-03-14 2016-08-23 Lockheed Martin Corporation Less-than-lethal cartridge
US9200876B1 (en) 2014-03-06 2015-12-01 Lockheed Martin Corporation Multiple-charge cartridge
CN104089547B (en) * 2014-06-30 2016-01-27 中国航天时代电子公司 A kind of Deployment and locking device of folding rudder face
CN105292410A (en) * 2015-10-30 2016-02-03 北京精密机电控制设备研究所 Pop-up decelerating wing system driven by initiating explosive device and provided with locking function
US10641590B2 (en) * 2016-10-26 2020-05-05 Simmonds Precision Products, Inc. Wing deployment and lock mechanism
US11300390B1 (en) 2018-03-05 2022-04-12 Dynamic Structures And Materials, Llc Control surface deployment apparatus and method of use

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE565999A (en) * 1953-02-06
BE552288A (en) * 1953-10-20
US2821924A (en) * 1954-07-09 1958-02-04 Lawrence J Hansen Fin stabilized projectile
US3196793A (en) * 1963-01-16 1965-07-27 Milenkovic Veljko Folded fin rocket
US3304030A (en) * 1965-09-24 1967-02-14 James E Weimholt Pyrotechnic-actuated folding fin assembly
FR2221707B1 (en) * 1973-03-14 1976-04-30 France Etat
DE7804927U1 (en) * 1978-02-18 1978-06-01 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen DEVICE FOR FOLDING OUT SWING LEAVES
SE444612B (en) * 1984-12-13 1986-04-21 Ffv Affersverket GUIDELINES FOR FENOR EXPOSURE OF PROJECTIL

Also Published As

Publication number Publication date
FR2644880B1 (en) 1994-03-11
CA2012925A1 (en) 1990-09-24
EP0389358A1 (en) 1990-09-26
DE69004604T2 (en) 1994-05-11
US5082203A (en) 1992-01-21
FR2644880A1 (en) 1990-09-28
ATE97483T1 (en) 1993-12-15
DE69004604D1 (en) 1993-12-23

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