EP0448437A1 - Improvements concerning a system for deploying rail fins - Google Patents

Improvements concerning a system for deploying rail fins Download PDF

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Publication number
EP0448437A1
EP0448437A1 EP91400595A EP91400595A EP0448437A1 EP 0448437 A1 EP0448437 A1 EP 0448437A1 EP 91400595 A EP91400595 A EP 91400595A EP 91400595 A EP91400595 A EP 91400595A EP 0448437 A1 EP0448437 A1 EP 0448437A1
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EP
European Patent Office
Prior art keywords
fins
machine
stabilizer according
flight
rotation
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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.)
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EP91400595A
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German (de)
French (fr)
Inventor
Alain Boely
Gérard Joset
Michel Maxel
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Thomson Brandt Armements SA
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Thomson Brandt Armements SA
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Publication of EP0448437A1 publication Critical patent/EP0448437A1/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
    • F42B10/16—Wrap-around fins

Definitions

  • the present invention relates to empennages comprising a plurality of fins regularly distributed around the periphery of a machine and articulated around axes oriented longitudinally. It relates more particularly to the combined opening of these fins.
  • the empennages with deployable fins provide a satisfactory response to the problems of storage, carrying, firing or ejection of missiles, ammunition or submunitions, as well as to aerodynamic requirements.
  • the fact that the fins are articulated around longitudinally oriented axes offers the advantage of being able to accommodate them in the caliber of the machine.
  • French patent application n ° 87 09454 in the name of the present plaintiff, relates to deployable tail units of the type defined above, in which each fin is able to pivot, in conjunction with the others, from a folded position to a deployed position thanks to pivoting means comprising an annular ring which can rotate around the axis of revolution of the machine, means for transmitting the rotation movement of the ring in pivoting movement of the wings, and setting means in rotation of the ring.
  • pivoting means comprising an annular ring which can rotate around the axis of revolution of the machine, means for transmitting the rotation movement of the ring in pivoting movement of the wings, and setting means in rotation of the ring.
  • These empennages are "all or nothing" systems, that is to say that the fins are capable of occupying in a controlled manner only the closed position or the fully open position, and that the passage between the two positions is almost instantaneous. Therefore, they cannot be used other than for the function for which they were designed, namely to ensure stability in flight.
  • a tail unit comprises a plurality of fins 2 distributed around the periphery of a machine 1 and articulated on axes Y-Y oriented longitudinally.
  • the fins are in even number to be diametrically opposite two by two, so that the aerodynamic forces on each in the direction of opening or closing are compensated by the aerodynamic forces exerted on the opposite fin.
  • the closed position they are completely housed in the caliber of machine 1.
  • Each fin 2 has at its base a pinion 2a centered on the axis Y-Y and meshed around the periphery of a ring 3, itself centered on the longitudinal axis or axis of revolution X-X of the machine 1.
  • the ring 3 is connected to the shaft 4a of a torque motor 4 which has the function of driving it in rotation between a first angular position corresponding to the closing of the fins and a second angular position corresponding to their complete opening.
  • the motor 4 also has the function of ensuring the maintenance of the ring 3 in any intermediate angular position, to which corresponds an identical partial opening position of all the fins, as illustrated in broken lines at Fig. 2.
  • the motor 4 is mounted on the longitudinal axis of the machine 1, and the ring 3 is toothed on its internal periphery, its connection with the shaft 4a being established by a pinion 5 carried by the latter and an intermediate pinion 6.
  • the torque motor 4 is controlled from a control unit 7 of the machine, the electrical junction comprising, for example , rotary contacts 8.
  • the tail unit is integrated into the machine 1, namely that the fins 2, the ring 3, the engine 4 and the transmission means 5, 6 are mounted on the body of the machine 1.
  • the empennage can be used to fulfill two functions in a distinct manner: in one case, to influence the trajectory of a non-animated craft in flight with a rotational movement on itself; in the other case, on a machine driven by such a rotational movement on itself, ensure at the end of the flight the braking and stopping of this movement (skewing).
  • the progressive opening control of the fins by means of the motor 4 can be preprogrammed as a function of flight time only, or, preferably, as a function of flight criteria, the processing of which takes place in unit 7
  • the movement of the fins is capable of being controlled either in the direction of opening or in the direction of closing, just as the fins can be immobilized for any given period in intermediate open position.
  • the system thus used makes it possible in particular to grant the drag as a function of the flight speed, by deploying minimal fins from the departure of the machine when the speed is high, and increasing as the speed decreases. It also allows control to a certain extent the length of the trajectory, for example according to the flight conditions.
  • the tail In the application to "despinning", the tail remains closed until the terminal flight phase.
  • the instant of its entry into play can be, as in the previous case, preprogrammed as a function of the flight time, or else determined as a function of flight criteria treated in unit 7. From this instant, the opening fins 2 is controlled so as to be progressive as the speed of rotation decreases, failing which the tail unit would be unable to withstand without breaking the significant aerodynamic starting forces exerted on the fully deployed fins.
  • the tail unit of the invention compared to a deploying tail unit of the "all or nothing" type mentioned above, and which would include fins dimensioned small enough to withstand full opening to the aerodynamic starting forces, the tail unit of the invention, by the progressive opening of the fins as the rotational speed decreases, ensures a much faster "skidding".
  • the possibility offered by the invention to use the same empennage indifferently to one or the other of the two functions described above, since none requires its own characteristic (such as dimensioning characteristic fins) relative to each other. This gives an obvious advantage from a manufacturing point of view.
  • Fig. 3 the empennage which comprises the same elements as previously, arranged in the same way, is no longer mounted on the body 1 of the machine, but in a tail block 1b free to rotate about the axis XX relative to the actual body 1a of the machine, by means of bearings 9.
  • the rotary contacts 8 which were only preferred in the example of embodiment of FIG. 1 are here necessary for controlling the motor 4 from the unit 7.
  • This arrangement makes the empennage usable to influence in a controlled way the trajectory of a machine, which is animated in flight by a rotational movement on itself: at the start, the whole of the machine is ie the main body 1a and the tail block 1b, is animated by this rotational movement on itself.
  • the empennage accomplishes the "destining" of the only tail block 1b by progressive opening of the fins 2.
  • the empennage can operate as previously explained with regard to the craft of the Fig. 1, that is to say to influence the trajectory of the craft 1 in a preprogrammed manner as a function of the flight time, or else as a function of flight criteria processed in unit 7.
  • Clutch means can also be provided between the tail block 1b and the body 1a, controllable from the unit 7. These clutch means then make it possible to "strip" the body 1a in the following manner : at a given instant in the terminal flight phase, the fins 2 are retracted, at least partially, then the clutch means are actuated, which has the effect of putting the tail block 1b back into rotation, together with the body 1a. Following this, the fins 2 are gradually redeployed to carry out the "peeling" of the entire body 1a and the tail block 1b. Consequently, in this embodiment, the tail is able to perform successively in a machine rotating on itself the two above-mentioned functions of influencing the trajectory and of stopping the rotation on itself of the 'contraption.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)

Abstract

The invention concerns those tail units with fins (2) articulated on axes (Y-Y) oriented longitudinally and comprising a device for the simultaneous opening of the fins. According to the invention, this device comprises a circular element (3) engaged with the base of all of the fins (2), and a means (4) of driving the circular element (3) in rotation, able to rotate it in both directions, and of maintaining it in any angular position between two extreme angular positions respectively corresponding to the closed position and the completely open position of the fins (2). Applications to the in-flight control of the trajectory and to the stoppage of a rotation about itself of a missile having such a movement during its flight. <IMAGE>

Description

La présente invention se rapporte à des empennages comprenant une pluralité d'ailettes régulièrement réparties sur le pourtour d'un engin et articulées autour d'axes orientés longitudinalement. Elle concerne plus particulièrement l'ouverture conjuguée de ces ailettes.The present invention relates to empennages comprising a plurality of fins regularly distributed around the periphery of a machine and articulated around axes oriented longitudinally. It relates more particularly to the combined opening of these fins.

Les empennages à ailettes déployables apportent une réponse satisfaisante aux problèmes de stockage, d'emport, de tir ou d'éjection de missiles, munitions ou sous-munitions, ainsi qu'aux impératifs aérodynamiques. Le fait que les ailettes soient articulées autour d'axes orientés longitudinalement offre l'intérêt de pouvoir les loger dans le calibre de l'engin.The empennages with deployable fins provide a satisfactory response to the problems of storage, carrying, firing or ejection of missiles, ammunition or submunitions, as well as to aerodynamic requirements. The fact that the fins are articulated around longitudinally oriented axes offers the advantage of being able to accommodate them in the caliber of the machine.

La demande de brevet français n° 87 09454, au nom de la présente demanderesse, concerne des empennages déployants du type ci-dessus défini, dans lesquels chaque ailette est apte à pivoter, de façon conjuguée avec les autres, d'une position rabattue à une position déployée grâce à des moyens de pivotement comprenant une bague annulaire pouvant tourner autour de l'axe de révolution de l'engin, des moyens de transmission du mouvement de rotation de la bague en mouvement de pivotement des ailes, et des moyens de mise en rotation de la bague. Ces empennages sont des systèmes "tout ou rien", c'est-à-dire que les ailettes ne sont susceptibles d'occuper de manière contrôlée que la position de fermeture ou la position de totale ouverture, et que le passage entre les deux positions est quasi instantané. De ce fait, on ne peut les utiliser autrement que pour la fonction pour laquelle ils ont été conçus, à savoir assurer la stabilité en vol.French patent application n ° 87 09454, in the name of the present plaintiff, relates to deployable tail units of the type defined above, in which each fin is able to pivot, in conjunction with the others, from a folded position to a deployed position thanks to pivoting means comprising an annular ring which can rotate around the axis of revolution of the machine, means for transmitting the rotation movement of the ring in pivoting movement of the wings, and setting means in rotation of the ring. These empennages are "all or nothing" systems, that is to say that the fins are capable of occupying in a controlled manner only the closed position or the fully open position, and that the passage between the two positions is almost instantaneous. Therefore, they cannot be used other than for the function for which they were designed, namely to ensure stability in flight.

L'invention a pour objet d'apporter des pefectionnements à ce type d'empennage à ailettes déployables, en vue d'en élargir leur domaine d'application, notamment de les rendre utilisables :

  • pour une optimisation de trajectoire ou un contrôle en vol de celle-ci, par exemple en fonction de critères de vol;
  • ou bien pour le freinage et l'arrêt en rotation autour de son axe de révolution d'un engin animé d'un tel mouvement en vol, cette opération étant communément appelée "déspinage".
The object of the invention is to provide improvements to this type of fin fin deployable, in order to widen their field of application, in particular to make them usable:
  • for trajectory optimization or flight control thereof, for example according to flight criteria;
  • or else for braking and stopping in rotation around its axis of revolution of a machine animated by such a movement in flight, this operation being commonly called "skidding".

Conformément à l'invention, un empennage comportant des ailettes déployables régulièrement réparties sur le pourtour d'un engin, et articulées autour d'axes orientés longitudinalement, ainsi qu'un dispositif d'ouverture conjuguée des ailettes, est caractérisé en ce que ce dispositif comprend :

  • un élément circulaire transversal centré sur l'axe longitudinal de l'engin;
  • des moyens de transmission entre cet élément circulaire et la base de chaque ailette, lesquels moyens de transmission assurent pour toute position angulaire de l'élément circulaire entre des première et seconde positions angulaires extrêmes correspondant respectivement à la fermeture et à la complète ouverture des ailettes, des positions identiques et stables de toutes les ailettes; et
  • un moyen d'entraînement dudit élément circulaire, apte à le déplacer en rotation dans les deux sens entre lesdites première et seconde positions angulaires extrêmes, et à le maintenir dans une position quelconque entre ces deux positions.
In accordance with the invention, a tail unit comprising deployable fins regularly distributed around the periphery of a machine, and articulated around axes oriented longitudinally, as well as a device for conjugate opening of the fins, is characterized in that this device includes:
  • a transverse circular element centered on the longitudinal axis of the machine;
  • transmission means between this circular element and the base of each fin, which transmission means ensure for any angular position of the circular element between first and second extreme angular positions corresponding respectively to the closing and to the complete opening of the fins, identical and stable positions of all the fins; and
  • means for driving said circular element, adapted to move it in rotation in both directions between said first and second extreme angular positions, and to maintain it in any position between these two positions.

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

  • la Fig. 1 est une vue schématique et partiellement en coupe axiale d'un engin doté d'un empennage selon l'invention,
  • la Fig. 2 est une vue schématique illustrant le système d'ouverture des ailettes de l'empennage, et
  • la Fig. 3 est une vue semblable à la Fig. 1, mais illustrant un autre arrangement d'un empennage selon l'invention dans un engin.
The invention will be better understood with the aid of the explanations which follow and of the appended drawings, in which:
  • Fig. 1 is a schematic view, partially in axial section, of a machine provided with a tail unit according to the invention,
  • Fig. 2 is a schematic view illustrating the system for opening the tail fins, and
  • Fig. 3 is a view similar to FIG. 1, but illustrating another arrangement of a tail according to the invention in a machine.

Dans les dessins, les mêmes références ont été utilisées partout pour désigner les mêmes éléments.In the drawings, the same references have been used everywhere to designate the same elements.

Un empennage conforme à l'invention comprend une pluralité d'ailettes 2 réparties sur le pourtour d'un engin 1 et articulées sur des axes Y-Y orientés longitudinalement. De préférence, les ailettes sont en nombre pair pour être diamétralement opposées deux à deux, afin que les efforts aérodynamiques sur chacune dans le sens de l'ouverture ou de la fermeture soient compensés par les efforts aérodynamiques s'exerçant sur l'ailette opposée. De plus, en position de fermeture, elles sont logées complètement dans le calibre de l'engin 1.A tail unit according to the invention comprises a plurality of fins 2 distributed around the periphery of a machine 1 and articulated on axes Y-Y oriented longitudinally. Preferably, the fins are in even number to be diametrically opposite two by two, so that the aerodynamic forces on each in the direction of opening or closing are compensated by the aerodynamic forces exerted on the opposite fin. In addition, in the closed position, they are completely housed in the caliber of machine 1.

Chaque ailette 2 comporte à sa base un pignon 2a centré sur l'axe Y-Y et engrené sur le pourtour d'une bague 3, centrée elle-même sur l'axe longitudinal ou axe de révolution X-X de l'engin 1.Each fin 2 has at its base a pinion 2a centered on the axis Y-Y and meshed around the periphery of a ring 3, itself centered on the longitudinal axis or axis of revolution X-X of the machine 1.

Selon l'invention, la bague 3 est reliée à l'arbre 4a d'un moteur-couple 4 qui a pour fonction de l'entraîner en rotation entre une première position angulaire correspondant à la fermeture des ailettes et une seconde position angulaire correspondant à leur complète ouverture. Le moteur 4 a également pour fonction d'assurer le maintien de la bague 3 dans une position angulaire intermédiaire quelconque, à laquelle correspond une position d'ouverture partielle identique de toutes les ailettes, telle qu'illustrée en traits interrompus à la Fig. 2. Dans une forme de réalisation préférée, et comme représenté dans les dessins, le moteur 4 est monté sur l'axe longitudinal de l'engin 1, et la bague 3 est dentée sur son pourtour interne, sa liaison avec l'arbre 4a étant établie par un pignon 5 porté par celui-ci et un pignon intermédiaire 6. D'autre part, le moteur-couple 4 est commandé à partir d'une unité de commande 7 de l'engin, la jonction électrique comportant, par exemple, des contacts rotatifs 8.According to the invention, the ring 3 is connected to the shaft 4a of a torque motor 4 which has the function of driving it in rotation between a first angular position corresponding to the closing of the fins and a second angular position corresponding to their complete opening. The motor 4 also has the function of ensuring the maintenance of the ring 3 in any intermediate angular position, to which corresponds an identical partial opening position of all the fins, as illustrated in broken lines at Fig. 2. In a preferred embodiment, and as shown in the drawings, the motor 4 is mounted on the longitudinal axis of the machine 1, and the ring 3 is toothed on its internal periphery, its connection with the shaft 4a being established by a pinion 5 carried by the latter and an intermediate pinion 6. On the other hand, the torque motor 4 is controlled from a control unit 7 of the machine, the electrical junction comprising, for example , rotary contacts 8.

A la Fig. 1, l'empennage est intégré à l'engin 1, à savoir que les ailettes 2, la bague 3, le moteur 4 et les moyens de transmission 5, 6 sont montés à même le corps de l'engin 1.In Fig. 1, the tail unit is integrated into the machine 1, namely that the fins 2, the ring 3, the engine 4 and the transmission means 5, 6 are mounted on the body of the machine 1.

Dans cet arrangement, l'empennage peut être utilisé pour remplir de façon distincte deux fonctions : dans un cas, influer sur la trajectoire d'un engin non animé en vol d'un mouvement de rotation sur lui-même; dans l'autre cas, sur un engin animé d'un tel mouvement de rotation sur lui-même, assurer en fin de vol le freinage et l'arrêt de ce mouvement (déspinage).In this arrangement, the empennage can be used to fulfill two functions in a distinct manner: in one case, to influence the trajectory of a non-animated craft in flight with a rotational movement on itself; in the other case, on a machine driven by such a rotational movement on itself, ensure at the end of the flight the braking and stopping of this movement (skewing).

Dans le premier cas, la commande d'ouverture évolutive des ailettes au moyen du moteur 4 peut être préprogrammée en fonction uniquement du temps de vol, ou, de préférence, être fonction de critères de vol dont le traitement a lieu dans l'unité 7. En cours de fonctionnement de l'empennage, le mouvement des ailettes est susceptible d'être commandé indifféremment dans le sens de l'ouverture et dans le sens de la fermeture, de même que les ailettes peuvent être immobilisées pour une période donnée quelconque en position d'ouverture intermédiaire. Le système ainsi utilisé permet notamment d'accorder la traînée en fonction de la vitesse de vol, par un déploiement des ailettes minimal au départ de l'engin quand la vitesse est élevée, et augmentant à mesure que la vitesse diminue. Il permet également de contrôler dans une certaine mesure la longueur de la trajectoire, par exemple en fonction des conditions de vol.In the first case, the progressive opening control of the fins by means of the motor 4 can be preprogrammed as a function of flight time only, or, preferably, as a function of flight criteria, the processing of which takes place in unit 7 During the operation of the tail, the movement of the fins is capable of being controlled either in the direction of opening or in the direction of closing, just as the fins can be immobilized for any given period in intermediate open position. The system thus used makes it possible in particular to grant the drag as a function of the flight speed, by deploying minimal fins from the departure of the machine when the speed is high, and increasing as the speed decreases. It also allows control to a certain extent the length of the trajectory, for example according to the flight conditions.

Dans l'application au "déspinage", l'empennage reste fermé jusqu'à la phase de vol terminale. L'instant de son entrée en jeu peut être, comme dans le cas précédent, préprogrammé en fonction du temps de vol, ou bien déterminé en fonction de critères de vol traités dans l'unité 7. A partir de cet instant, l'ouverture des ailettes 2 est contrôlée de manière à être progressive à mesure que la vitesse de rotation diminue, faute de quoi l'empennage serait incapable de supporter sans casse les importants efforts aérodynamiques de départ s'exerçant sur les ailettes complètement déployées. Inversement, comparé à un empennage déployant du type "tout ou rien" mentionné précédemment, et qui comporterait des ailettes dimensionnées suffisamment petites pour résister à pleine ouverture aux efforts aérodynamiques de départ, l'empennage de l'invention, par l'ouverture progressive des ailettes à mesure que la vitesse de rotation diminue, assure un "déspinage" beaucoup plus rapide. A noter, de plus, la possibilité offerte par l'invention d'utiliser le même empennage indifféremment à l'une ou l'autre des deux fonctions ci-dessus exposées, puisqu'aucune ne requiert de caractéristique propre (telle que caractéristique de dimensionnement des ailettes) par rapport à l'autre. Il en découle un avantage évident du point de vue de la fabrication.In the application to "despinning", the tail remains closed until the terminal flight phase. The instant of its entry into play can be, as in the previous case, preprogrammed as a function of the flight time, or else determined as a function of flight criteria treated in unit 7. From this instant, the opening fins 2 is controlled so as to be progressive as the speed of rotation decreases, failing which the tail unit would be unable to withstand without breaking the significant aerodynamic starting forces exerted on the fully deployed fins. Conversely, compared to a deploying tail unit of the "all or nothing" type mentioned above, and which would include fins dimensioned small enough to withstand full opening to the aerodynamic starting forces, the tail unit of the invention, by the progressive opening of the fins as the rotational speed decreases, ensures a much faster "skidding". Note, moreover, the possibility offered by the invention to use the same empennage indifferently to one or the other of the two functions described above, since none requires its own characteristic (such as dimensioning characteristic fins) relative to each other. This gives an obvious advantage from a manufacturing point of view.

A la Fig. 3, l'empennage qui comporte les mêmes éléments que précédemment, arrangés de la même façon, n'est plus monté à même le corps 1 de l'engin, mais dans un bloc de queue 1b libre en rotation autour de l'axe X-X par rapport au corps proprement dit 1a de l'engin, par l'intermédiaire de roulements 9. Les contacts rotatifs 8 qui n'étaient que préférentiels dans l'exemple de réalisation de la Fig. 1 sont ici nécessaires pour assurer la commande du moteur 4 à partir de l'unité 7.In Fig. 3, the empennage which comprises the same elements as previously, arranged in the same way, is no longer mounted on the body 1 of the machine, but in a tail block 1b free to rotate about the axis XX relative to the actual body 1a of the machine, by means of bearings 9. The rotary contacts 8 which were only preferred in the example of embodiment of FIG. 1 are here necessary for controlling the motor 4 from the unit 7.

Cet arrangement rend l'empennage utilisable pour influer de façon contrôlée sur la trajectoire d'un engin, lequel est animé en vol d'un mouvement de rotation sur lui-même : au départ, l'ensemble de l'engin, c'est-à-dire le corps principal 1a et le bloc de queue 1b, est animé de ce mouvement de rotation sur lui-même. Dans une première phase, l'empennage accomplit le "déspinage" du seul bloc de queue 1b par ouverture progressive des ailettes 2. Une fois ce "déspinage" réalisé, l'empennage peut opérer comme précédemment exposé à propos de l'engin de la Fig. 1, c'est-à-dire influer sur la trajectoire de l'engin 1 de façon préprogrammée en fonction du temps de vol, ou bien en fonction de critères de vol traités dans l'unité 7.This arrangement makes the empennage usable to influence in a controlled way the trajectory of a machine, which is animated in flight by a rotational movement on itself: at the start, the whole of the machine is ie the main body 1a and the tail block 1b, is animated by this rotational movement on itself. In a first phase, the empennage accomplishes the "destining" of the only tail block 1b by progressive opening of the fins 2. Once this "destining" carried out, the empennage can operate as previously explained with regard to the craft of the Fig. 1, that is to say to influence the trajectory of the craft 1 in a preprogrammed manner as a function of the flight time, or else as a function of flight criteria processed in unit 7.

Des moyens d'embrayage peuvent en outre être prévus entre le bloc de queue 1b et le corps 1a, commandables à partir de l'unité 7. Ces moyens d'embrayage permettent alors de réaliser le "déspinage" du corps 1a de la façon suivante : à un instant donné de la phase de vol terminale, les ailettes 2 sont rétractées, au moins partiellement, puis sont actionnés les moyens d'embrayage, ce qui a pour effet de remettre en rotation le bloc de queue 1b, en ensemble avec le corps 1a. Suite à cela, les ailettes 2 sont redéployées progressivement pour réaliser le "déspinage" de l'ensemble du corps 1a et du bloc de queue 1b. Par conséquent, dans cette forme de réalisation, l'empennage est apte à effectuer successivement dans un engin tournant sur lui-même les deux fonctions ci-dessus exposées d'influer sur la trajectoire et d'arrêter la rotation sur lui-même de l'engin.Clutch means can also be provided between the tail block 1b and the body 1a, controllable from the unit 7. These clutch means then make it possible to "strip" the body 1a in the following manner : at a given instant in the terminal flight phase, the fins 2 are retracted, at least partially, then the clutch means are actuated, which has the effect of putting the tail block 1b back into rotation, together with the body 1a. Following this, the fins 2 are gradually redeployed to carry out the "peeling" of the entire body 1a and the tail block 1b. Consequently, in this embodiment, the tail is able to perform successively in a machine rotating on itself the two above-mentioned functions of influencing the trajectory and of stopping the rotation on itself of the 'contraption.

Claims (7)

1) Empennage prévu dans un engin tel que missile, munition, sous-munition, etc., comportant des ailettes déployables (2) régulièrement réparties sur le pourtour de l'engin (1) et articulées autour d'axes (Y-Y) orientés longitudinalement, ainsi qu'un dispositif d'ouverture conjuguée des ailettes, caractérisé en ce que ce dispositif comprend : - un élément circulaire transversal (3) centré sur l'axe longitudinal (X-X) de l'engin; - des moyens de transmission entre l'élément circulaire (3) et la base de chaque ailette (2), lesquels moyens de transmission assurent pour toute position angulaire de l'élément (3) entre des première et seconde positions angulaires extrêmes correspondant respectivement à la fermeture et à la complète ouverture des ailettes (2), des positions identiques et stables de toutes les ailettes (2); et - un moyen d'entraînement de l'élément circulaire (3), apte à le déplacer en rotation dans les deux sens entre lesdites première et seconde positions angulaires extrêmes, et à le maintenir dans une position quelconque entre ces deux positions, en vue de permettre l'utilisation de l'empennage pour l'optimisation ou le contrôle en vol de la trajectoire, ainsi que pour le freinage et l'arrêt en rotation d'un engin tournant sur lui-même. 1) stabilizer provided in a missile, munition, submunition, etc., comprising deployable fins (2) regularly distributed around the periphery of the missile (1) and articulated around axes (YY) oriented longitudinally , as well as a device for the combined opening of the fins, characterized in that this device comprises: - a transverse circular element (3) centered on the longitudinal axis (XX) of the machine; - transmission means between the circular element (3) and the base of each fin (2), which transmission means ensure for any angular position of the element (3) between first and second extreme angular positions corresponding respectively to closing and fully opening the fins (2), identical and stable positions of all the fins (2); and a means for driving the circular element (3), able to move it in rotation in both directions between said first and second extreme angular positions, and to maintain it in any position between these two positions, with a view to allow the use of the tail for the optimization or the flight control of the trajectory, as well as for the braking and the stop in rotation of a machine turning on itself. 2) Empennage selon la revendication 1, caractérisé en ce que ledit moyen d'entraînement est un moteur-couple (4). 2) stabilizer according to claim 1, characterized in that said drive means is a torque motor (4). 3) Empennage selon la revendication 1 ou 2, caractérisé en ce que les ailettes (2) sont en nombre pair et diamétralement opposées deux à deux. 3) stabilizer according to claim 1 or 2, characterized in that the fins (2) are in even number and diametrically opposite two by two. 4) Empennage selon l'une des revendications 1 à 3, caractérisé en ce que ses éléments (2 à 6) sont montés à même le corps de l'engin (1). 4) stabilizer according to one of claims 1 to 3, characterized in that its elements (2 to 6) are mounted on the body of the machine (1). 5) Empennage selon l'une des revendications 1 à 4, caractérisé en ce que ses éléments (2 à 6) sont montés dans un bloc de queue (1b) libre en rotation autour de l'axe de révolution (X-X) de l'engin par rapport au corps proprement dit (1a) de ce dernier.
6) Empennage selon la revendication 5, caractérisé en ce que sont en outre prévus des moyens d'embrayage entre le corps proprement dit (1a) de l'engin et le bloc de queue (1b). 5) stabilizer according to one of claims 1 to 4, characterized in that its elements (2 to 6) are mounted in a tail block (1b) free to rotate about the axis of revolution (XX) of the machine in relation to the body itself (1a) of the latter.
6) stabilizer according to claim 5, characterized in that there are further provided clutch means between the body itself (1a) of the machine and the tail block (1b). 7) Empennage selon l'une des revendications 1 à 6, caractérisé en ce qu'il est commandé de façon préprogrammée en fonction du temps de vol à partir d'une unité de commande (7) de l'engin (1). 7) stabilizer according to one of claims 1 to 6, characterized in that it is controlled in a preprogrammed manner as a function of the flight time from a control unit (7) of the craft (1). 8) Empennage selon l'une des revendications 1 à 6, caractérisé en ce qu'il est commandé à partir d'une unité de commande (7) de l'engin (1), en fonction de critères de vol traités dans l'unité (7). 8) stabilizer according to one of claims 1 to 6, characterized in that it is controlled from a control unit (7) of the craft (1), according to flight criteria treated in the unit (7).
EP91400595A 1990-03-09 1991-03-05 Improvements concerning a system for deploying rail fins Withdrawn EP0448437A1 (en)

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FR9003033 1990-03-09
FR9003033A FR2659433B1 (en) 1990-03-09 1990-03-09 IMPROVEMENTS ON FENDERING WING TANKS.

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US5927643A (en) * 1997-11-05 1999-07-27 Atlantic Research Corporation Self-deploying airfoil for missile or the like
RU2176066C1 (en) * 2001-03-20 2001-11-20 Государственное унитарное предприятие "Государственное научно-производственное предприятие "Сплав" Tail plane stabilizer of supersonic jet projectile
WO2002079716A1 (en) * 2001-03-20 2002-10-10 Bofors Defence Ab Method of synchronizing fin fold-out on a fin-stabilized artillery shell, and an artillery shell designed in accordance therewith
DE102006022248B3 (en) * 2006-05-12 2007-11-08 Lfk-Lenkflugkörpersysteme Gmbh Retaining device on wrapped wings of flying object, allowing reliable release of wings into working position, comprises controlled release holder on one wing and cooperating fixtures on others
RU2328695C2 (en) * 2006-09-04 2008-07-10 Федеральное Государственное унитарное предприятие "Государственное научно-производственное предприятие "Сплав" Supersonic jet shell fin
EP3111157A4 (en) * 2014-02-26 2017-09-27 Israel Aerospace Industries Ltd. Fin deployment system
CN105129082B (en) * 2015-09-01 2018-07-27 湖南云顶智能科技有限公司 Propeller Folding device for unmanned plane
RU2732370C1 (en) * 2020-02-27 2020-09-16 Акционерное общество "Брянский химический завод имени 50-летия СССР" Rotating missile

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RU2166179C1 (en) * 2000-06-26 2001-04-27 Государственное унитарное предприятие Брянский химический завод Jet projectile
RU2642693C2 (en) * 2016-04-21 2018-01-25 Акционерное общество "Новосибирский завод искусственного волокна" Supersonic projectile

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Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5927643A (en) * 1997-11-05 1999-07-27 Atlantic Research Corporation Self-deploying airfoil for missile or the like
RU2176066C1 (en) * 2001-03-20 2001-11-20 Государственное унитарное предприятие "Государственное научно-производственное предприятие "Сплав" Tail plane stabilizer of supersonic jet projectile
WO2002079716A1 (en) * 2001-03-20 2002-10-10 Bofors Defence Ab Method of synchronizing fin fold-out on a fin-stabilized artillery shell, and an artillery shell designed in accordance therewith
US7104497B2 (en) 2001-03-20 2006-09-12 Bae Systems Bofors Ab Method of synchronizing fin fold-out on a fin-stabilized artillery shell, and an artillery shell designed in accordance therewith
US7487934B2 (en) 2001-03-20 2009-02-10 Bae Systems Bofors Ab Method of synchronizing fin fold-out on a fin-stabilized artillery shell, and an artillery shell designed in accordance therewith
DE102006022248B3 (en) * 2006-05-12 2007-11-08 Lfk-Lenkflugkörpersysteme Gmbh Retaining device on wrapped wings of flying object, allowing reliable release of wings into working position, comprises controlled release holder on one wing and cooperating fixtures on others
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RU2328695C2 (en) * 2006-09-04 2008-07-10 Федеральное Государственное унитарное предприятие "Государственное научно-производственное предприятие "Сплав" Supersonic jet shell fin
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
CN105129082B (en) * 2015-09-01 2018-07-27 湖南云顶智能科技有限公司 Propeller Folding device for unmanned plane
RU2732370C1 (en) * 2020-02-27 2020-09-16 Акционерное общество "Брянский химический завод имени 50-летия СССР" Rotating missile

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Publication number Publication date
FR2659433B1 (en) 1992-05-15
FR2659433A1 (en) 1991-09-13

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