EP0298844A1 - Device for deploying fins and its use in a projectile - Google Patents

Device for deploying fins and its use in a projectile Download PDF

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Publication number
EP0298844A1
EP0298844A1 EP88401708A EP88401708A EP0298844A1 EP 0298844 A1 EP0298844 A1 EP 0298844A1 EP 88401708 A EP88401708 A EP 88401708A EP 88401708 A EP88401708 A EP 88401708A EP 0298844 A1 EP0298844 A1 EP 0298844A1
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EP
European Patent Office
Prior art keywords
wing
ring
projectile
wings
axis
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Withdrawn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
EP88401708A
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German (de)
French (fr)
Inventor
Etienne Lamarque
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
Original Assignee
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 EP0298844A1 publication Critical patent/EP0298844A1/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Withdrawn legal-status Critical Current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
    • 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
    • F42B10/16—Wrap-around fins

Definitions

  • the present invention converges the deployment, multiple or not, of wings preferably fitted to a projectile or a missile such as a missile.
  • missile all these projectiles or flying devices such as missiles.
  • Devices such as military missiles are often equipped with folding wings to allow optimized containment of several devices inside a carrier container, before these devices are dropped or expelled from the container.
  • the wings are deployed to ensure their stabilization function.
  • the main difficulty in deploying wings of this type is to deploy them in a combined manner, that is to say at exactly the same time.
  • the object of the invention is, while designing deployable wings of a different design, to provide a device for deploying said wings.
  • the object of the invention is a device for deploying one or more unfoldable wings, positioned in the same direction, by rotation relative to a body, the wing being able to occupy a folded position and a deployed position, characterized in that that the wing has, at its lower end, a projecting part penetrating into a notch formed in an annular ring so that, during the rotation of the ring around the axis of revolution of the body, the wing pivots around the pivot axis.
  • each of them is fixed thereto by means of an articulation 7.
  • This figure represents them in the folded position, that is to say say a storage position.
  • This representation is only an example, both of from the point of view of the number of wings, only in the direction in which they are folded back towards the projectile 1.
  • a dashed line shows one of these wings in its deployed position, that is to say that this wing is perpendicular to the outer surface of the projectile, where it is attached to the latter.
  • Figure 2 shows a second example of storage of the wings 2 against the projectile 1.
  • two wings have been shown, but this is in no way limiting. The same is true with regard to the fact that they have been shown folded in an opposite direction.
  • an annular ring 4 is inserted inside the body 3, and can rotate inside and relative to it.
  • the wing 2 can pivot about an axis 6 tangential to the body 3 thanks to a mechanical articulation, which can consist for example of a boss 8 projecting from the body 3, and in which the articulation is fixed.
  • invention provides means for transmitting the rotational movement of the ring 4 relative to the body 3, in a pivoting movement of the wing 2, which are constituted by a projecting part 5 of the wing which deviates from the axis of rotation 6, in order to penetrate a notch 10 in the ring 4.
  • a rotation along arrow F1 of ring 4 causes pivoting along arrow F2 of wing 2 around axis 6.
  • a stop is provided, materialized in FIG. 3 by a surface 9 of the boss 8, which blocks the wing 2 in an unfolded position, corresponding to that shown in FIG. 4.
  • the ring 4 has rotated enough so that the wing is fully unfolded, and pressing against the surface 9. It should be noted that for the wing to be maintained in this position, it is necessary that the surface 9 representing the stop and the external surface 11 of the ring 4 make an angle corresponding to that made by the projection 5 relative to the orientation of the wing 2.
  • This mechanism is the same for all the wings, and at least for the two wings of the same pair. It can be noted that during deployment, if a wing is stressed externally by a force which tends to close it, using this mechanism, the position of the two wings of the same pair will remain symmetrical.
  • the ring 4 can be an externally toothed wheel, meshing on the base of the wing 2 situated around the axis 6 in which corresponding teeth have been machined, so as to produce a mechanism identical to that of a rack.
  • FIGS. 5A and 5B show an example of means for rotating the ring 4.
  • a cylinder 13, integral with the structure of the body contains a piston 15 which can translate.
  • a piston 12 is attached to the piston 15 by means of a joint 14, which is preferably floating, that is to say mounted with play, or may be a ball joint.
  • the other end of the link is fixed to the ring by means of a joint 18.
  • the rotation of the ring 4 is effected by the translation of the piston 15. This is carried out, preferably, by means of a pyrotechnic generator 16 placed inside the cylinder 13, and initiated by an igniter 17 The piston, under the effect of the pressure, translates, pushes the link 12 which rotates the ring 4.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aerials With Secondary Devices (AREA)
  • Transmission Devices (AREA)

Abstract

According to the invention, the projectile is equipped with fins capable of being turned down against the body (3) of the projectile and of being deployed as a result of rotation about an axis parallel to the longitudinal axis of the projectile. For deploying at least one pair of fins, use is made of at least one ring (4) placed inside the body (3) and capable of pivoting and of means for transmitting this rotational movement to the two fins. These transmission means can be produced by means of a notch (10) made in the ring opposite each fin (2) which has a projecting part (5) penetrating into the notch (10). The means used for rotating the ring (4) can be controlled pyrotechnically. The invention is used for projectiles, such as missiles. <IMAGE>

Description

La présente invention converne le déploiement, multiple ou non, d'ailes équipant de préférence un projectile ou un engin tel qu'un missile.The present invention converges the deployment, multiple or not, of wings preferably fitted to a projectile or a missile such as a missile.

On prévoit d'équiper ledit missile de deux ou quatre ailes, ces dernières ayant chacune une position rabattue dans laquelle elles ne sont pas opérationnelles, et au moins une position déployée dans laquelle elles sont opérationnelles.Provision is made to equip said missile with two or four wings, the latter each having a folded position in which they are not operational, and at least one deployed position in which they are operational.

Dans la suite de la description et dans les revendications, on a choisi de désigner par le terme "engin" tous ces projectiles ou engins volants tels que les missiles.In the following description and in the claims, we have chosen to designate by the term "missile" all these projectiles or flying devices such as missiles.

Les engins tels que les missiles militaires sont souvent équipés d'ailes rabattables pour permettre un confinement optimisé de plusieurs engins à l'intérieur d'un conteneur porteur, avant que ces engins soient largués ou expulsés du conteneur. Lorsque l'engin est opérationnel, les ailes sont déployées pour assurer leur fonction de stabilisation.Devices such as military missiles are often equipped with folding wings to allow optimized containment of several devices inside a carrier container, before these devices are dropped or expelled from the container. When the machine is operational, the wings are deployed to ensure their stabilization function.

La plupart des ailes rabattables équipant un engin sont logées dans une fente à l'intérieur du fuselage, et sont articulées dans celui-ci autour d'un axe perpendiculaire à l'axe de l'engin. Après rotation autour de cet axe, chaque aile est écartée du fuselage.Most of the folding wings fitted to a craft are housed in a slot inside the fuselage, and are articulated in the latter around an axis perpendicular to the axis of the craft. After rotation around this axis, each wing is removed from the fuselage.

Un des principaux inconvénients de ces ailes provient du fait qu'elles sont encastrées à l'intérieur du fuselage. En effet, si on envisage l'implantation de quatre ailes dans un engin de diamètre seulement deux à trois fois plus important que la largeur des ailes, celles-ci ne laissent que trop peu de place pour l'agencement d'autres éléments, qui doivent être installés dans le projectile.One of the main disadvantages of these wings comes from the fact that they are embedded inside the fuselage. Indeed, if we consider the implantation of four wings in a machine with a diameter only two to three times larger than the width of the wings, these leave only too little room for the arrangement of other elements, which must be installed in the projectile.

En dehors de ce fait, la principale difficulté du déploiement des ailes de ce type est de les déployer de façon conjuguée, c'est-à-dire exactement au même instant.Apart from this fact, the main difficulty in deploying wings of this type is to deploy them in a combined manner, that is to say at exactly the same time.

Le but de l'invention est, tout en concevant des ailes déployables d'une conception différente, de proposer un dispositif de déploiement desdites ailes.The object of the invention is, while designing deployable wings of a different design, to provide a device for deploying said wings.

L'objet de l'invention est un dispositif de déploiement d'une ou plusieurs ailes dépliables, positionnées dans le même sens, par rotation par rapport à un corps, l'aile pouvant occuper une position rabattue et une position déployée, caractérisé en ce que l'aile comporte, à son extrémité inférieure, une partie en saillie pénétrant dans une encoche pratiquée dans une bague annulaire de manière à ce que, lors de la rotation de la bague autour de l'axe de révolution du corps, l'aile pivote autour de l'axe de pivotement.The object of the invention is a device for deploying one or more unfoldable wings, positioned in the same direction, by rotation relative to a body, the wing being able to occupy a folded position and a deployed position, characterized in that that the wing has, at its lower end, a projecting part penetrating into a notch formed in an annular ring so that, during the rotation of the ring around the axis of revolution of the body, the wing pivots around the pivot axis.

L'invention et ses caractéristiques seront mieux comprises à la lecture de la description, annexée des figures suivantes :

  • - Fig.1, un schéma montrant un premier agencement des ailes sur le projectile utilisé dans l'invention ;
  • - Fig.2, un deuxième agencement des ailes sur le projectile utilisé dans l'invention ;
  • - Fig.3, un schéma du principe de déploiement des ailes selon l'invention dans la position rabattue ;
  • - Fig.4, un schéma du principe de déploiement des ailes selon l'invention, dans la position déployée ;
  • - Figs.5A et 5B, deux vues schématisant les moyens de mise en rotation d'une bague, selon l'invention ;
  • - Fig.6, une vue shcématisant les moyens de mise en rotation de deux bagues selon l'invention.
The invention and its characteristics will be better understood on reading the description, appended to the following figures:
  • - Fig.1, a diagram showing a first arrangement of the wings on the projectile used in the invention;
  • - Fig.2, a second arrangement of the wings on the projectile used in the invention;
  • - Fig.3, a diagram of the principle of deployment of the wings according to the invention in the folded position;
  • - Fig.4, a diagram of the principle of deployment of the wings according to the invention, in the deployed position;
  • - Figs.5A and 5B, two views schematizing the means for rotating a ring, according to the invention;
  • - Fig.6, a view showing the means for rotating two rings according to the invention.

En référence à la figure 1, autour du projectile 1 sont placées quatre ailes 2. Chacune d'elle est fixée sur celui-ci au moyen d'une articulation 7. Cette figure les représente dans la position rabattue, c'est-à-dire une position de stockage. Cette représentation n'est qu'un exemple, tant du point de vue du nombre des ailes, que du sens dans lequel elles sont rabattues vers le projectile 1. On a représenté en trait interrompu une de ces ailes dans sa position déployée, c'est-à-dire que cette aile se trouve perpendiculaire à la surface extérieure du projectile, à l'endroit où elle est fixée à ce dernier.With reference to FIG. 1, around the projectile 1 are placed four wings 2. Each of them is fixed thereto by means of an articulation 7. This figure represents them in the folded position, that is to say say a storage position. This representation is only an example, both of from the point of view of the number of wings, only in the direction in which they are folded back towards the projectile 1. A dashed line shows one of these wings in its deployed position, that is to say that this wing is perpendicular to the outer surface of the projectile, where it is attached to the latter.

La figure 2, montre un deuxième exemple de rangement des ailes 2 contre le projectile 1. Ici seulement deux ailes ont été représentées, mais ceci n'est aucunement limitatif. Il en est de même en ce qui concerne le fait qu'elles ont été représentées rabattues dans un sens contraire.Figure 2 shows a second example of storage of the wings 2 against the projectile 1. Here only two wings have been shown, but this is in no way limiting. The same is true with regard to the fact that they have been shown folded in an opposite direction.

En référence à la figure 3, selon l'invention, une bague annulaire 4 est insérée à l'intérieur du corps 3, et peut tourner à l'intérieur et par rapport à celui-ci. L'aile 2 peut pivoter autour d'un axe 6 tangentiel au corps 3 grâce à une articulation mécanique, qui peut être constituée par exemple d'un bossage 8 faisant saillie du corps 3, et dans lequel est fixée l'articulation.L'invention prévoit des moyens de transmission du mouvement de rotation de la bague 4 par rapport au corps 3, en un mouvement de pivotement de l'aile 2, qui sont constitués par une partie en saillie 5 de l'aile qui s'écarte de l'axe de rotation 6, pour pénétrer dans une encoche 10 de la bague 4. De ce fait, une rotation selon la flèche F1 de la bague 4 entraîne un pivotement selon la flèche F2 de l'aile 2 autour de l'axe 6. On prévoit une butée, matérialisée sur la figure 3 par une surface 9 du bossage 8, qui bloque l'aile 2 dans une position dépliée, correspondant à celle représentée sur la figure 4. Sur cette figure, la bague 4 a tourné suffisamment pour que l'aile soit complètement dépliée, et en appui contre la surface 9. Il est à noter, que pour que l'aile soit maintenue dans cette position, il est nécessaire que la surface 9 représentant la butée et la surface extérieure 11 de la bague 4 fassent un angle correspondant à celui que fait la saillie 5 par rapport à l'orientation de l'aile 2.Referring to Figure 3, according to the invention, an annular ring 4 is inserted inside the body 3, and can rotate inside and relative to it. The wing 2 can pivot about an axis 6 tangential to the body 3 thanks to a mechanical articulation, which can consist for example of a boss 8 projecting from the body 3, and in which the articulation is fixed. invention provides means for transmitting the rotational movement of the ring 4 relative to the body 3, in a pivoting movement of the wing 2, which are constituted by a projecting part 5 of the wing which deviates from the axis of rotation 6, in order to penetrate a notch 10 in the ring 4. As a result, a rotation along arrow F1 of ring 4 causes pivoting along arrow F2 of wing 2 around axis 6. A stop is provided, materialized in FIG. 3 by a surface 9 of the boss 8, which blocks the wing 2 in an unfolded position, corresponding to that shown in FIG. 4. In this figure, the ring 4 has rotated enough so that the wing is fully unfolded, and pressing against the surface 9. It should be noted that for the wing to be maintained in this position, it is necessary that the surface 9 representing the stop and the external surface 11 of the ring 4 make an angle corresponding to that made by the projection 5 relative to the orientation of the wing 2.

Ce mécanisme est le même pour toutes les ailes, et tout au moins pour les deux ailes d'une même paire. On peut noter, que lors du déploiement, si une aile est sollicitée extérieurement par un effort qui tend à la fermer, à l'aide de ce mécanisme, la position des deux ailes d'une même paire restera symétrique.This mechanism is the same for all the wings, and at least for the two wings of the same pair. It can be noted that during deployment, if a wing is stressed externally by a force which tends to close it, using this mechanism, the position of the two wings of the same pair will remain symmetrical.

La réalisation des moyens de transmission du mouvement de rotation de la bague 4, représentée sur les figures 3 et 4, n'est qu'un exemple. En effet, la bague 4 peut être une roue dentée extérieurement, engrènant sur la base de l'aile 2 située autour de l'axe 6 dans lequel on aurait usiné des dents correspondantes, de manière à réaliser un mécanisme identique à celui d'une crémaillère.The embodiment of the means for transmitting the rotational movement of the ring 4, shown in FIGS. 3 and 4, is only one example. In fact, the ring 4 can be an externally toothed wheel, meshing on the base of the wing 2 situated around the axis 6 in which corresponding teeth have been machined, so as to produce a mechanism identical to that of a rack.

Sur les figures 5A et 5B, on a représenté un exemple de moyens de mise en rotation de la bague 4. Un cylindre 13, solidaire de la structure du corps contient un piston 15 qui peut se translater. Au piston 15 est fixé une bielette 12 par l'intermédiaire d'une articulation 14, qui est de préférence flottante, c'est-à-dire montée avec du jeu, ou peut être une rotule. L'autre extrémité de la bielette est fixée à la bague par l'intermédiaire d'une articulation 18.FIGS. 5A and 5B show an example of means for rotating the ring 4. A cylinder 13, integral with the structure of the body contains a piston 15 which can translate. A piston 12 is attached to the piston 15 by means of a joint 14, which is preferably floating, that is to say mounted with play, or may be a ball joint. The other end of the link is fixed to the ring by means of a joint 18.

La rotation de la bague 4 s'effectue grâce à la translation du piston 15. On effectue celle-ci, de manière préférentielle, au moyen d'un générateur pyrotechnique 16 placé à l'intérieur du cylindre 13, et initié grâce un inflammateur 17. Le piston, sous l'effet de la pression, se translate, pousse la biellette 12 qui fait tourner la bague 4.The rotation of the ring 4 is effected by the translation of the piston 15. This is carried out, preferably, by means of a pyrotechnic generator 16 placed inside the cylinder 13, and initiated by an igniter 17 The piston, under the effect of the pressure, translates, pushes the link 12 which rotates the ring 4.

En référence à la figure 6 on peut envisager avec un seul dispositif de translation, analogue à celui que nous venons de décrire, de faire tourner deux bagues 4A et 4B, placées l'une à côté de l'autre à l'intérieur du corps 3. Avec deux bielettes 12A et 12B fixées au bout du piston par une articulation 14, et également fixée chacune à une des deux bagues, on peut faire tourner les deux bagues 4A et 4B dans des sens opposés, indiqués par les deux flèches. Ce type de réalisation peut être appliqué à la disposition décrite sur la figure 2. Le point d'application de l'effort tangentiel de rotation de chaque bielette 12A et 12B est situé sur le plan de frottement commun aux deux bagues 4A et 4B. Comme précédemment, les axes des bielettes sont flottants et peuvent être des rotules. Dans ce cas, on peut prévoir un ou plusieurs impulseurs pyrotechniques pour faire fonctionner le mécanisme.Referring to Figure 6 we can consider with a single translation device, similar to that which we have just described, to rotate two rings 4A and 4B, placed one next to the other inside the body 3. With two connecting rods 12A and 12B fixed at the end of the piston by a joint 14, and also each fixed to one of the two rings, the two rings 4A and 4B can be rotated in opposite directions, indicated by the two arrows. This kind of embodiment can be applied to the arrangement described in Figure 2. The point of application of the tangential force of rotation of each link 12A and 12B is located on the friction plane common to the two rings 4A and 4B. As before, the axes of the links are floating and can be ball joints. In this case, one or more pyrotechnic impellers can be provided to operate the mechanism.

Claims (5)

1. Dispositif de déploiement d'au moins une aile (2) dépliable par rotation autour d'un axe de pivotement (6) par rapport à un corps (3), l'aile pouvant occuper une position rabattue et une position déployée, caractérisé en ce que l'aile (2) comporte, à son extrémité inférieure, une partie en saillie (5) pénétrant dans une encoche (10) pratiquée dans une bague annulaire (4) de manière à ce que, lors de la rotation de la bague (4) autour de l'axe de révolution du corps (3), l'aile (2) pivote autour de l'axe de pivotement (6).1. Device for deploying at least one wing (2) which can be unfolded by rotation about a pivot axis (6) relative to a body (3), the wing being able to occupy a folded-down position and a deployed position, characterized in that the wing (2) has, at its lower end, a projecting part (5) penetrating into a notch (10) formed in an annular ring (4) so that, during the rotation of the ring (4) around the axis of revolution of the body (3), the wing (2) pivots around the pivot axis (6). 2. Dispositif selon la revendication 1, comprenant au moins deux ailes dépliables (2) rabattues en sens contraire, caractérisé en ce qu'il comporte une deuxième bague annulaire pouvant pivoter autour de l'axe de révolution du corps (3) en sens inverse l'un par rapport à l'autre, chacune des bagues agissant sur une aile.2. Device according to claim 1, comprising at least two foldable wings (2) folded in opposite direction, characterized in that it comprises a second annular ring which can pivot around the axis of revolution of the body (3) in opposite direction relative to each other, each of the rings acting on a wing. 3. Dispositif selon l'une des revendications précédentes, caractérisé en ce que le corps (3) possède un bossage (8) de manière à limiter le pivotement de l'aile (2) et à maintenir l'aile (2) dans sa position déployée en coopération avec la bague (4) qui maintient la partie en saillie (5) en dehors de l'encoche (10).3. Device according to one of the preceding claims, characterized in that the body (3) has a boss (8) so as to limit the pivoting of the wing (2) and to keep the wing (2) in its deployed position in cooperation with the ring (4) which keeps the projecting part (5) outside the notch (10). 4. Dispositif selon l'une quelconque des revendications précédentes, caractérisé en ce que les moyens de mise en rotation des dites bagues (4) sont constitués d'au moins un impulseur rigidement fixé au corps actionnant par translation une bielette (12) pour chaque bague (4) de manière à faire tourner lesdites bagues.4. Device according to any one of the preceding claims, characterized in that the means for rotating said rings (4) consist of at least one impeller rigidly fixed to the body actuating by translation a connecting rod (12) for each ring (4) so as to rotate said rings. 5. Dispositif selon l'une quelconque des revendications 1 à 4, caractérisé en ce que chacun des impulseurs est constitué par un générateur pyrotechnique (16) commandé conjointement aux autres.5. Device according to any one of claims 1 to 4, characterized in that each of the impellers consists of a pyrotechnic generator (16) controlled jointly with the others.
EP88401708A 1987-07-03 1988-07-01 Device for deploying fins and its use in a projectile Withdrawn EP0298844A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8709454 1987-07-03
FR8709454A FR2617587B1 (en) 1987-07-03 1987-07-03 DEVICE FOR CONJUGATED DEPLOYMENT OF WINGS, AND APPLICATION TO A FLYING MACHINE

Publications (1)

Publication Number Publication Date
EP0298844A1 true EP0298844A1 (en) 1989-01-11

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EP88401708A Withdrawn EP0298844A1 (en) 1987-07-03 1988-07-01 Device for deploying fins and its use in a projectile

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FR (1) FR2617587B1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3111157A4 (en) * 2014-02-26 2017-09-27 Israel Aerospace Industries Ltd. Fin deployment system

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3188958A (en) * 1963-03-11 1965-06-15 James D Burke Range control for a ballistic missile
US3563495A (en) * 1969-02-03 1971-02-16 Us Air Force Power operated folding wing for rockets and missiles
GB1352118A (en) * 1964-09-28 1974-05-08 Dynamit Nobel Ag Rockets
GB2121147A (en) * 1982-06-02 1983-12-14 British Aerospace Missile fin assemblies
GB2155157A (en) * 1984-02-17 1985-09-18 Hunting Eng Ltd Helix ring devices and assemblies including them

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3188958A (en) * 1963-03-11 1965-06-15 James D Burke Range control for a ballistic missile
GB1352118A (en) * 1964-09-28 1974-05-08 Dynamit Nobel Ag Rockets
US3563495A (en) * 1969-02-03 1971-02-16 Us Air Force Power operated folding wing for rockets and missiles
GB2121147A (en) * 1982-06-02 1983-12-14 British Aerospace Missile fin assemblies
GB2155157A (en) * 1984-02-17 1985-09-18 Hunting Eng Ltd Helix ring devices and assemblies including them

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3111157A4 (en) * 2014-02-26 2017-09-27 Israel Aerospace Industries Ltd. Fin deployment system
US9989338B2 (en) 2014-02-26 2018-06-05 Israel Aerospace Industries Ltd. Fin deployment system

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Publication number Publication date
FR2617587B1 (en) 1993-04-16
FR2617587A1 (en) 1989-01-06

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