EP0318359B1 - Device for spreading projectile wings - Google Patents

Device for spreading projectile wings Download PDF

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Publication number
EP0318359B1
EP0318359B1 EP88402880A EP88402880A EP0318359B1 EP 0318359 B1 EP0318359 B1 EP 0318359B1 EP 88402880 A EP88402880 A EP 88402880A EP 88402880 A EP88402880 A EP 88402880A EP 0318359 B1 EP0318359 B1 EP 0318359B1
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EP
European Patent Office
Prior art keywords
fin
projectile
fact
deployment
mechanism according
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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EP88402880A
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German (de)
French (fr)
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EP0318359A1 (en
Inventor
André Blin
Alain Bonnet
Eric Crotet
Patrick Dauvergne
Bernard Masson
Evelyne Montet
Roger Crépin
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Giat Industries SA
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Giat Industries SA
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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

Definitions

  • the invention is that of deployment devices for projectile fins, and more particularly for orientable fins, that is to say which can pivot in the deployed position under the action of a soup motor around a substantially perpendicular axis. to the axis of the projectile.
  • the deployable fins can only play a stabilizing role for a projectile animated by a slow or zero rotation movement, or also a guiding role, similar to that of the control surfaces for an airplane; in the latter case, they are controlled by a motor, itself controlled by an electronic assembly, they then make it possible to modify the trajectory of the projectile during its flight and therefore to correct possible aiming errors, or even to orient automatically, after detection of a target, the projectile towards it.
  • US-A-4,588,146 describes deployable fins for missile in a movement comprising a translation of the fins followed by two rotations.
  • the translation is carried out beforehand by an operator, which constitutes a risk of damage to the fins and consequently a malfunction of the assembly, causing destabilization of the missile.
  • the fins begin by presenting their largest surface facing the aerodynamic flow; the leading edge of the fins, the surface of which is smaller, being oriented in the direction of this flow only at the end of the deployment movement. It follows a braking of the projectile and a risk of destabilization all the more important as the asymmetries at the level of the movements of opening of the fins will be amplified by the importance of the forces which are exerted on them. The risk of destabilization will be even more critical in the case where the projectile is initially gyro-stabilized and where the deployment of the fins must allow it to adopt a regime stabilized by tailplane.
  • the invention applied to fins which have to provide a guiding function, also provides a means making it possible to completely control their opening movement as well as the instant of triggering of the latter, without however requiring an additional locking device.
  • the subject of the invention is a device for deploying a projectile fin between a carrying position, in which its plane is substantially parallel to the axis of the projectile, and a deployed position, the fin being made integral with the projectile by an articulation, device characterized in that the articulation is such that the deployment movement comprises at least two phases: a first in which the fin passes from the carrying position to a semi-deployed position, this passage being obtained by a rotation along a first axis which is perpendicular to the plane of the fin when the latter is in the position of takeout and a second in which the fin passes from the semi-deployed position to the deployed position, by a rotation along a second axis which is parallel to the plane of the fin.
  • the fin is moved by an actuator during all or part of the first phase of the deployment movement, and it is immobilized relative to the projectile by a locking means when it is in its carrying position.
  • the fin in the deployed position can pivot around the first axis under the action of a pilot motor, and this constitutes the actuator and / or the locking means .
  • the fin is secured to a support, itself immobilized relative to the inner ring of a bearing, the outer ring of this bearing being immobilized relative to the projectile, and on the other apart the motor is immobilized relative to the projectile and controls the rotation of the support by means of a coupling joint.
  • the fin may be moved by aerodynamic forces during the second phase of the deployment movement; in this case it may carry a pin, circulating during the first phase of the deployment movement in a circular groove immobilized relative to the projectile, the second phase intervening during the passage of the pin before a clearance of this groove.
  • the support will carry a lock immobilizing the fin relative to the latter in the deployed position.
  • a projectile 1 has at its rear part four fins 2, (shown schematically in the form of parallelepipeds to simplify the description), intended to provide both a stabilizing function and a guiding function; these fins are made integral with the projectile by joints 11, which will be described in detail below.
  • the projectile is fired by a weapon, not shown, and is gyro-stabilized during a first part of its trajectory, it therefore comprises known means and not shown here (such as a belt) such as to drive it in rotation during its journey to l inside the weapon.
  • This belt may be integral with the projectile itself or with a stationary cylindrical element relative to the projectile, and released on trajectory by pyrotechnic means (see for example patent W081 / 00908).
  • the fins 2 are shown in Figure 1 in the carrying position. They are immobilized relative to the projectile by a blocking means which will be described later.
  • the plane of the fin which is defined by an axis 8, materializing the main direction thereof, and an axis 7 orthogonal to the previous one, is substantially parallel to the axis 4 of the projectile.
  • This position is analogous to the carrying position described in patent US4664339.
  • the front end of each fin comes into a housing 3 in the body of the projectile 1.
  • Figure 2 shows the projectile with its fins without a semi-deployed position.
  • Figure 3 shows the projectile with the fins fully deployed.
  • the transition from the semi-deployed position to the deployed position (second phase of the deployment movement) is obtained by a rotation in the ⁇ direction, of each fin around a second axis 6, which is parallel to the plane of the 'fin.
  • the forces undergone by the fins are also reduced in substantially the same ratio, which makes it possible to reduce the mass of the fins in favor of the payload of the projectile, and to reduce shock and destabilizing asymmetries.
  • each fin being greater in direction 7 than in the direction normal to the plane of the fin (inertia ratio of the order of 60), the latter are less sensitive to the bending deformations induced by the aerodynamic forces.
  • This increase in the rigidity of the fins results in an increase in their natural vibration frequencies, which, in combination with the notable reduction in the forces to which they are subjected, makes it possible to guarantee a regular deployment movement of each fin, which reduces the risks destabilization of the projectile.
  • FIGS 4 and 5 show in detail the joint 11, the locking means and the actuator, which allow to obtain the two phases of the deployment movement described above, in this particular embodiment of the device according to invention.
  • Each fin 2 is made integral with a support 13 by means of a pivot 21 which materializes the second axis 6.
  • the mounting of the fin on the support is of the clevis-tenon type, the fin having one end constituting a clevis and the post being formed by the support 13. This type of arrangement made it possible to obtain better guidance of the fin during its deployment movement.
  • the fin is here shown in the carrying position with its plane parallel to the axis 4 of the projectile 1.
  • the support 13 is immobilized relative to the inner ring 16 of a bearing with two rows of angular contact balls.
  • the outer ring 15 of this bearing is immobilized by threading relative to a housing 12, itself secured to the projectile 1.
  • the bearing-bearing assembly thus constitutes the joint 11.
  • a motor 14, here an electric geared motor, is also immobilized relative to the box 12; in this particular embodiment, it is linked in translation to the housing by means of a shoulder of the latter and of the outer ring 15 of the bearing, and in rotation by pins not shown.
  • the motor 14 carries, on the upper part of its axis, a groove 20, and the support 13 a groove 19, these two grooves constitute, with an intermediate part 18, a seal of coupling, preferably a constant velocity joint, such as an Oldham joint here, which allows the motor 14 to drive the support 13, carrying the fin 2, in rotation around the first axis 5.
  • the coupling joint makes it possible to tolerate poor axial alignment when mounting the support and the motor, but it also makes it possible to isolate the latter from the vibrations which the fin could impart to it.
  • the bearing also makes it possible to isolate the engine from the aerodynamic forces which the fin will therefore transmit directly to the projectile 1, via the support and the bearing.
  • the fin carries a pin 22, one end of which is housed in a circular groove 24 carried by the housing. This circular groove ends with a clearance 27 (see FIG. 5), the usefulness of which will be specified below.
  • the support 13 also carries a lock 23, which is constituted by a finger 25, sliding against the action of a return spring, and which is intended to come into a housing 26 carried by the fin 2, this for the purpose to lock it in the deployed position at the end of the second phase of the deployment movement.
  • an encoder 17, of known type, and integral with the support 13, will make it possible to give an electronic control assembly, not shown, the information on the angular position of the fin 2 relative to the first axis 5.
  • the motor the main function of which is to guide the projectile by pivoting the deployed fin around the first axis 5
  • the actuator which causes the first phase of the deployment movement of the fin: its passage from the carrying position to the semi-deployed position.
  • the motor due to the irreversibility of the mechanical reducer which it comprises, also plays the role of means for blocking the fin in the carrying position.
  • the start of the opening is completely controlled and corresponds to the control of the motors; speeds and positions of the fins can be controlled by an electronic device, known per se, which will play individually on the control voltages of the different motors as a function of the information given by the encoders.
  • the control of the motors therefore makes it possible to accomplish the first phase of the deployment movement, which as has been seen previously will make it possible to obtain progressive braking of the rotation of the projectile; (but it is also possible to use other types of vanes of known type, such as those described in patent W081 / 00908, to cause braking in rotation, the deployment of the guide vanes then being controlled only when the speed of rotation has fallen below a certain value, of the order of 20 to 30 revolutions / second); when the fins are in the position of FIG. 2, the pin 22, which has circulated during the first phase of the deployment movement in the groove 24 and has thus maintained the fin in the plane defined by the axes 7 and 8, is then opposite the clearance 27.
  • the aerodynamic forces exerted on the fin are sufficient to rotate it around the second axis 6 and therefore to make it accomplish the second phase of the deployment movement, just until the locking of the fin; the engine then fulfilling its guiding role by pivoting the deployed fin around the first axis.
  • motors can be envisaged to fulfill both the function of actuator of the deployment movement of the fin, and the function of piloting the projectile; such as a pneumatic motor, powered by a gas reserve or else by a gas generator with pyrotechnic initiation.

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

Description

L'invention est celui des dispositifs de déploiement pour des ailettes de projectiles, et plus particulièrement pour des ailettes orientables, c'est à dire pouvant pivoter en position déployée sous l'actions d'un moteur de potage autour d'un axe sensiblement perpendiculaire à l'axe du projectile.The invention is that of deployment devices for projectile fins, and more particularly for orientable fins, that is to say which can pivot in the deployed position under the action of a soup motor around a substantially perpendicular axis. to the axis of the projectile.

Les ailettes déployables peuvent jouer uniquement un rôle de stabilisation pour un projectile animé d'un mouvement de rotation lent ou nul, ou également un rôle de guidage, analogue à celui des gouvernes pour un avion ; dans ce dernier cas, elles sont commandées par un moteur, lui-même piloté par un ensemble électronique, elles permettent alors de modifier la trajectoire du projectile pendant son vol et donc de corriger des erreurs éventuelles de pointage, ou encore d'orienter automatiquement, après détection d'une cible, le projectile vers cette dernière.The deployable fins can only play a stabilizing role for a projectile animated by a slow or zero rotation movement, or also a guiding role, similar to that of the control surfaces for an airplane; in the latter case, they are controlled by a motor, itself controlled by an electronic assembly, they then make it possible to modify the trajectory of the projectile during its flight and therefore to correct possible aiming errors, or even to orient automatically, after detection of a target, the projectile towards it.

De telles ailettes ont pour principal inconvénient de devoir posséder, pour être efficaces, des dimensions importantes (la longueur de l'ailette est habituellement de l'ordre du calibre), ce qui rend impossible le tir du projectile à partir d'une arme au calibre. Ainsi depuis de nombreuses années ont été développés différents mécanismes de déploiement d'ailettes, ces dernières pouvant être orientables ou plus simplement stabilisatrices, et le projectile qui les porte pouvant être un missile ou une roquette ou encore un sous-projectile porté par un projectile cargo de gros calibre gyrostabilisé.The main drawback of such fins has to have, to be effective, large dimensions (the length of the fin is usually of the order of the caliber), which makes it impossible to fire the projectile from a weapon at caliber. Thus for many years various mechanisms have been developed for deploying fins, the latter being able to be orientable or more simply stabilizing, and the projectile which carries them being able to be a missile or a rocket or even a sub-projectile carried by a cargo projectile large caliber gyro-stabilized.

Le brevet US-A-4 588 146 décrit des ailettes déployables pour missile selon un mouvement comprenant une translation des ailettes suivie de deux rotations. La translation est effectuée au préalable par un opérateur ce qui constitue des risques d'endommagement des ailettes et par suite un mauvais fonctionnement de l'ensemble, entraînant une destabilisation du missile.US-A-4,588,146 describes deployable fins for missile in a movement comprising a translation of the fins followed by two rotations. The translation is carried out beforehand by an operator, which constitutes a risk of damage to the fins and consequently a malfunction of the assembly, causing destabilization of the missile.

On regardera en particulier le brevet US-A-4 664 339 qui décrit une ailette orientable dans sa position déployée par l'action d'un moteur, et qui se trouve, en position d'emport, orientée sensiblement parallèlement à l'axe du projectile, conformément au préambule de la revendication de la présente demande. Cette ailette passe en position déployée sous l'effet des efforts aérodynamiques qui s'exercent sur elle après la libération d'un verrou de blocage, le décolement de l'ailette étant provoqué par un ressort.
Cette disposition d'emport est particulièrement avantageuse car elle ne diminue pas le volume utile du projectile ; une telle solution présente donc un très net progrès en regard des ailettes déployables proposées antérieurement et qui se trouvaient disposées à l'intérieur du projectile en position d'emport (voir par exemple le brevet US4659037).We will in particular look at US-A-4,664,339 which describes a fin which can be oriented in its deployed position by the action of a motor, and which is, in the carrying position, oriented substantially parallel to the axis of the projectile, in accordance with the preamble of the claim of this application. This fin passes into the deployed position under the effect of the aerodynamic forces which are exerted on it after the release of a locking bolt, the separation of the fin being caused by a spring.
This carrying arrangement is particularly advantageous since it does not reduce the useful volume of the projectile; such a solution therefore presents a very clear progress with regard to the deployable fins previously proposed and which were arranged inside the projectile in the carrying position (see for example the patent US4659037).

Mais ce dispositif présente néanmoins des inconvénients. Ainsi au moment de leur déploiement, les ailettes, commencent par présenter leur plus grande surface en regard de l'écoulement aérodynamique; le bord d'attaque des ailettes, dont la surface est plus réduite, ne se trouvant orienté dans le sens de cet écoulement qu'à la fin du mouvement de déploiement. Il s'ensuit un freinage du projectile et un risque de déstabilisation d'autant plus important que les dissymétries au niveau des mouvements d'ouverture des ailettes vont se trouver amplifiées par l'importance des efforts qui s'exercent sur elles. Le risque de destabilisation sera encore plus critique dans le cas ou le projectile est au départ gyrostabilisé et où le déploiement des ailettes doit lui permettre d'adopter un régime stabilisé par empennage.However, this device nevertheless has drawbacks. Thus at the time of their deployment, the fins, begin by presenting their largest surface facing the aerodynamic flow; the leading edge of the fins, the surface of which is smaller, being oriented in the direction of this flow only at the end of the deployment movement. It follows a braking of the projectile and a risk of destabilization all the more important as the asymmetries at the level of the movements of opening of the fins will be amplified by the importance of the forces which are exerted on them. The risk of destabilization will be even more critical in the case where the projectile is initially gyro-stabilized and where the deployment of the fins must allow it to adopt a regime stabilized by tailplane.

Enfin, et cela surtout dans le cas d'un sous-projectile libéré sur trajectoire par un projectile cargo, il est nécessaire d'attendre que la vitesse de rotation du sous-projectile se trouve en dessous d'un certain niveau pour provoquer le déploiement des ailettes de guidage, cela dans le but de diminuer les contraintes subies par ces dernières. L'emploi d'un verrou commandé, proposé par le brevet US4664339, s'il permet de remplir cette fonction, complique la réalisation industrielle du projectile et introduit une cause supplémentaire de mauvais fonctionnement.Finally, and this especially in the case of a sub-projectile released on trajectory by a cargo projectile, it is necessary to wait until the speed of rotation of the sub-projectile is below a certain level to cause deployment. guide fins, this in order to reduce the stresses suffered by the latter. The use of a controlled lock, proposed by patent US4664339, if it makes it possible to fulfill this function, complicates the industrial production of the projectile and introduces an additional cause of malfunction.

C'est le but de la présente invention que de proposer un dispositif de déploiement pour des ailettes solidaires d'un projectile, dispositif assurant une ouverture provoquant le minimum de perturbations aérodynamiques ainsi que le minimum d'efforts sur les ailettes, tout en ne diminuant pas le volume intérieur utile du projectile.It is the aim of the present invention to propose a deployment device for fins integral with a projectile, device ensuring an opening causing the minimum of aerodynamic disturbances as well as the minimum of efforts on the fins, while not decreasing not the useful interior volume of the projectile.

L'invention, appliquée à des ailettes devant assurer une fonction de guidage, propose également un moyen permettant de maîtriser totalement leur mouvement d'ouverture ainsi qui l'instant de déclenchement de celui-ci, sans pour autant nécessiter de dispositif annexe de verrouillage.The invention, applied to fins which have to provide a guiding function, also provides a means making it possible to completely control their opening movement as well as the instant of triggering of the latter, without however requiring an additional locking device.

Ainsi l'invention a pour objet un dispositif de déploiement d'une ailette de projectile entre une position d'emport, dans laquelle son plan est sensiblement parallèle à l'axe du projectile, et une position déployée, l'ailette étant rendue solidaire du projectile par une articulation, dispositif caractérisé en ce que l'articulation est telle que le mouvement de déploiement comprenne au moins deux phase:
   une première dans laquelle l'ailette passe de la position d'emport à une position semi-déployée, ce passage étant obtenu par une rotation suivant un premier axe qui est perpendiculaire au plan de l'ailette quand celle-ci est en position d'emport
   et une deuxième dans laquelle l'ailette passe de la position semi-déployée à la position déployée, par une rotation suivant un deuxième axe qui est parallèle au plan de l'ailette.Thus, the subject of the invention is a device for deploying a projectile fin between a carrying position, in which its plane is substantially parallel to the axis of the projectile, and a deployed position, the fin being made integral with the projectile by an articulation, device characterized in that the articulation is such that the deployment movement comprises at least two phases:
a first in which the fin passes from the carrying position to a semi-deployed position, this passage being obtained by a rotation along a first axis which is perpendicular to the plane of the fin when the latter is in the position of takeout
and a second in which the fin passes from the semi-deployed position to the deployed position, by a rotation along a second axis which is parallel to the plane of the fin.

Selon des caractéristiques avantageuses, l'ailette est mue par un actionneur pendant tout ou partie de la première phase du mouvement de déploiement, et elle est immobilisée relativement au projectile par un moyen de blocage quand elle se trouve dans sa position d'emport.According to advantageous characteristics, the fin is moved by an actuator during all or part of the first phase of the deployment movement, and it is immobilized relative to the projectile by a locking means when it is in its carrying position.

Selon un mode particulier d'application de l'invention, l'ailette en position déployée peut pivoter autour du premier axe sous l'action d'un moteur de pilotage, et celui-ci constitue l'actionneur et/ou le moyen de blocage.According to a particular mode of application of the invention, the fin in the deployed position can pivot around the first axis under the action of a pilot motor, and this constitutes the actuator and / or the locking means .

Dans un mode préférentiel de réalisation, d'une part l'ailette est solidaire d'un support, lui même immobilisé relativement à la bague intérieure d'un roulement, la bague extérieure de ce roulement étant immobilisée relativement au projectile, et d'autre part le moteur est immobilisé relativement au projectile et commande la rotation du support par l'intermédiaire d'un joint de couplage.In a preferred embodiment, on the one hand the fin is secured to a support, itself immobilized relative to the inner ring of a bearing, the outer ring of this bearing being immobilized relative to the projectile, and on the other apart the motor is immobilized relative to the projectile and controls the rotation of the support by means of a coupling joint.

L'ailette pourra être mue par les efforts aérodynamiques au cours de la deuxième phase du mouvement de déploiement; dans ce cas elle pourra porter un pion, circulant pendant la première phase du mouvement de déploiement dans une rainure circulaire immobilisée relativement au projectile, la deuxième phase intervenant lors du passage du pion devant un dégagement de cette rainure.The fin may be moved by aerodynamic forces during the second phase of the deployment movement; in this case it may carry a pin, circulating during the first phase of the deployment movement in a circular groove immobilized relative to the projectile, the second phase intervening during the passage of the pin before a clearance of this groove.

Enfin le support portera un verrou immobilisant l'ailette relativement à celui-là en position déployée.Finally, the support will carry a lock immobilizing the fin relative to the latter in the deployed position.

D'autres avantages de l'invention aparaîtront à la lecture de la description qui va suivre d'un mode particulier de réalisation. Description faite en regard des dessins annexés dans lesquels:

  • La figure 1 représente schématiquement un projectile équipé d'ailettes, ces dernières se trouvant en position d'emport.
  • Les figures 2 et 3 sont analogues à la précédente, et montrent les ailettes en positions respectivement semi-déployée et déployée.
  • Les figures 4 et 5 montrent un mode particulier de réalisation d'un dispositif de déploiement selon l'invention. La figure 5 étant une vue de la figure 4 suivant la direction Z.
Other advantages of the invention will appear on reading the description which follows of a particular embodiment. Description made with reference to the appended drawings in which:
  • FIG. 1 schematically represents a projectile equipped with fins, the latter being in the carrying position.
  • Figures 2 and 3 are similar to the previous one, and show the fins in the semi-deployed and deployed positions, respectively.
  • Figures 4 and 5 show a particular embodiment of a deployment device according to the invention. Figure 5 is a view of Figure 4 in the direction Z.

En se reportant aux figures 1 à 3, un projectile 1 comporte à sa partie arrière quatre ailettes 2, (représentées schématiquement sous forme de parallélépipèdes pour simplifier la description ), destinées à assurer à la fois une fonction de stabilisation et une fonction de guidage; ces ailettes sont rendues solidaires du projectile par des articulations 11, qui seront décrites en détail plus loin.Referring to Figures 1 to 3, a projectile 1 has at its rear part four fins 2, (shown schematically in the form of parallelepipeds to simplify the description), intended to provide both a stabilizing function and a guiding function; these fins are made integral with the projectile by joints 11, which will be described in detail below.

Le projectile est tiré par une arme, non représentée, et est gyrostabilisé pendant une première partie de sa trajectoire, il comporte donc des moyens connus et non représentés ici (tel une ceinture) de nature à l'entraîner en rotation pendant son trajet à l'intérieur de l'arme.The projectile is fired by a weapon, not shown, and is gyro-stabilized during a first part of its trajectory, it therefore comprises known means and not shown here (such as a belt) such as to drive it in rotation during its journey to l inside the weapon.

Cette ceinture pourra être solidaire du projectile lui-même ou bien d'un élément cylindrique immobile relativement au projectile, et libéré sur trajectoire par des moyens pyrotechniques (voir par exemple le brevet W081/00908).This belt may be integral with the projectile itself or with a stationary cylindrical element relative to the projectile, and released on trajectory by pyrotechnic means (see for example patent W081 / 00908).

Les ailettes 2 sont représentées sur la figure 1 en position d'emport. Elles sont immobilisées relativement au projectile par un moyen de blocage qui sera décrit plus loin. Dans la position d'emport, le plan de l'ailette, qui est défini par un axe 8, matérialisant la direction principale de celle-ci, et un axe 7 orthogonal au précédent, est sensiblement parallèle à l'axe 4 du projectile. Cette position est analogue à la position d'emport décrite dans le brevet US4664339. L'extrémité avant de chaque ailette vient dans un logement 3 du corps du projectile 1.The fins 2 are shown in Figure 1 in the carrying position. They are immobilized relative to the projectile by a blocking means which will be described later. In the carrying position, the plane of the fin, which is defined by an axis 8, materializing the main direction thereof, and an axis 7 orthogonal to the previous one, is substantially parallel to the axis 4 of the projectile. This position is analogous to the carrying position described in patent US4664339. The front end of each fin comes into a housing 3 in the body of the projectile 1.

La figure 2 représenté le projectile avec ses ailettes sans une position semi-déployée. Le passage de la position d'emport à la position semi-déployée, qui constitue une première phase du mouvement de déploiement, a été obtenu par une rotation dans le sens Ω (voir la figure 1), de chaque ailette, autour d'un premier axe 5 sensiblement perpendiculaire à l'axe 4 du projectile, et donc au plan de l'ailette quand elle se trouve en position d'emport. Cette rotation a été provoquée pendant tout ou partie du mouvement part un actionneur qui sera décrit par la suite.Figure 2 shows the projectile with its fins without a semi-deployed position. The transition from the carrying position to the semi-deployed position, which constitutes a first phase of the deployment movement, was obtained by a rotation in the Ω direction (see FIG. 1), of each fin, around a first axis 5 substantially perpendicular to the axis 4 of the projectile, and therefore to the plane of the fin when it is in the carrying position. This rotation was caused during all or part of the movement by an actuator which will be described later.

La figure 3 représente le projectile avec les ailettes complètements déployées. Le passage de la position semi-déployée à la position déployée, (deuxième phase du mouvement de déploiement), est obtenu par une rotation dans le sens ϑ, de chaque ailette autour d'un deuxième axe 6, qui est parallèle au plan de l'ailette.Figure 3 shows the projectile with the fins fully deployed. The transition from the semi-deployed position to the deployed position (second phase of the deployment movement) is obtained by a rotation in the ϑ direction, of each fin around a second axis 6, which is parallel to the plane of the 'fin.

Aussi bien pendant la première phase que pendant la deuxième, les mouvements de rotation permettent de ne présenter que la bord d'attaque 10 de chaque ailette dans le sens de l'écoulement aérodynamique.Both during the first phase and during the second, the rotational movements make it possible to present only the leading edge 10 of each fin in the direction of the aerodynamic flow.

L'augmentation de traînée, qui résulte pour le projectile du déploiement de ses ailettes, est nettement inférieure à celle obtenue avec le dispositif d'ouverture décrit dans le brevet US4664339. Relativement à ce dernier dispositif, et grâce à l'invention, on peut évaluer que l'augmentation de traînée se trouve réduite sensiblement dans le rapport de la surface totale des bords d'attaque 10 à la surface totale des voilures 9, ce qui donne une réduction de l'ordre de 10.The increase in drag, which results for the projectile from the deployment of its fins, is much less than that obtained with the opening device described in the Patent US4664339. Relative to the latter device, and thanks to the invention, it can be assessed that the increase in drag is reduced substantially in the ratio of the total area of the leading edges 10 to the total area of the wings 9, which gives a reduction of around 10.

Les efforts subis par les ailettes se trouvent également réduits dans sensiblement le même rapport, ce qui permet de diminuer la masse des ailettes au profit de la charge utile du projectile, et de diminuer les chocs et les dissymétries déstabilisatrices.The forces undergone by the fins are also reduced in substantially the same ratio, which makes it possible to reduce the mass of the fins in favor of the payload of the projectile, and to reduce shock and destabilizing asymmetries.

Enfin l'inertie de chaque ailette étant plus importante dans la direction 7 que dans la direction normale au plan de l'ailette (rapport des inerties de l'ordre de 60), ces dernières se trouvent moins sensibles aux deformations de flexion induits par les efforts aérodynamiques. Cette augmentation de la rigidité des ailettes entraîne un accroissement de leurs fréquences propres de vibration, ce qui, en combinaison avec la diminution notable des efforts auxquels elles sont soumises, permet de garantir un mouvement de déploiement régulier de chaque ailette, ce qui réduit les risques de déstabilisation du projectile.Finally, the inertia of each fin being greater in direction 7 than in the direction normal to the plane of the fin (inertia ratio of the order of 60), the latter are less sensitive to the bending deformations induced by the aerodynamic forces. This increase in the rigidity of the fins results in an increase in their natural vibration frequencies, which, in combination with the notable reduction in the forces to which they are subjected, makes it possible to guarantee a regular deployment movement of each fin, which reduces the risks destabilization of the projectile.

On voit ainsi le principal avantage de l'invention qui est de proposer un dispositif de déploiement d'ailettes induisant le minimum de perturbation à la trajectoire du projectile.We thus see the main advantage of the invention which is to propose a device for deploying fins inducing the minimum disturbance to the trajectory of the projectile.

Dans le cas particulier d'un projectile gyrostabilisé pendant le première partie de sa trajectoire, on peut remarquer qu'un tel mouvement de déploiement permet également de réduire la vitesse de rotation du projectile au moment du passage de la gyrostabilisation à la stabilisation par empennage. Mais l'avantage particulier apporté par l'invention est que ce freinage en rotation est ici très progressif; en effet, la part de la voilure 9 qui est saillante par rapport au projectile, croît de façon continue pendant toute cette première phase du mouvement de déploiement justqu'à atteindre sa valeur maximale, dans la position semi-déployée représentée figure 2. Cette augmentation progressive du freinage en rotation se produisant conjointement avec une augmentation progressive de l'envergure des ailettes et de leur orientation relativement au projectile, donc de la marge statique (distance entre le foyer des efforts aérodynamiques s'exerçant sur le projectile et le centre de gravité de ce dernier), est un facteur de régularité pour le passage de la gyrostabilisation à la stabilisation par empennage; les risques de perturbation de la trajectoire du projectile se trouvent donc encore réduits grâce à cette particularité de l'invention.In the particular case of a gyrostabilized projectile during the first part of its trajectory, it can be noted that such a deployment movement also makes it possible to reduce the speed of rotation of the projectile at the time of the transition from gyrostabilization to stabilization by empennage. But the particular advantage provided by the invention is that this braking in rotation is here very progressive; in fact, the part of the wing 9 which projects from the projectile, increases continuously throughout this first phase of the deployment movement until it reaches its maximum value, in the semi-deployed position shown in FIG. 2. This increase progressive braking in rotation producing jointly with a progressive increase in the wingspan and their orientation relative to the projectile, therefore of the static margin (distance between the focus of the aerodynamic forces exerted on the projectile and the center of gravity of the latter), is a regularity factor for the transition from gyrostabilization to stabilization by empennage; the risk of disturbing the trajectory of the projectile is therefore further reduced by this feature of the invention.

Les figures 4 et 5 permettent de voir en détail l'articulation 11, le moyen de blocage et l'actionneur, qui permettent d'obtenir les deux phases du mouvement de déploiement décrit précédemment, dans ce mode particulier de réalisation du dispositif selon l'invention.Figures 4 and 5 show in detail the joint 11, the locking means and the actuator, which allow to obtain the two phases of the deployment movement described above, in this particular embodiment of the device according to invention.

Chaque ailette 2 est rendue solidaire d'un support 13 au moyen d'un pivot 21 qui matérialise le deuxième axe 6. Le montage de l'ailette sur le support est du type chape-tenon, l'ailette ayant une extrémité constituant une chape et le tenon étant constitué par le support 13. Ce type de disposition permit d'obtenir un meilleur guidage de l'ailette au cours de son mouvement de déploiement. L'ailette est ici représentée en position d'emport avec son plan parallèle à l'axe 4 du projectile 1. Le support 13 est immobilisé relativement à la bague intérieure 16 d'un roulement à deux rangées de billes à contact oblique. La bague extérieure 15 de ce roulement est immobilisée par filetage relativement à un boîtier 12, lui-même solidaire du projectile 1. L'ensemble support-roulement constitue ainsi l'articulation 11. Un moteur 14, ici un motoréducteur électrique, est également immobilisé relativement au boîter 12; dans ce mode particulier de réalisation, il est lié en translation au boîter par l'intermédiaire d'un épaulement de ce dernier et de la bague exterieure 15 du roulement, et en rotation par des pions non représentés. Le moteur 14 porte, sur la partie supérieure de son axe, une rainure 20, et le support 13 une rainure 19, ces deux rainures constituent, avec une pièce intermédiaire 18, un joint de couplage, de préférence un joint homocinétique, tel ici un joint de Oldham, qui permet au moteur 14 d'entraîner le support 13, portant l'ailette 2, en rotation autour du premier axe 5.Each fin 2 is made integral with a support 13 by means of a pivot 21 which materializes the second axis 6. The mounting of the fin on the support is of the clevis-tenon type, the fin having one end constituting a clevis and the post being formed by the support 13. This type of arrangement made it possible to obtain better guidance of the fin during its deployment movement. The fin is here shown in the carrying position with its plane parallel to the axis 4 of the projectile 1. The support 13 is immobilized relative to the inner ring 16 of a bearing with two rows of angular contact balls. The outer ring 15 of this bearing is immobilized by threading relative to a housing 12, itself secured to the projectile 1. The bearing-bearing assembly thus constitutes the joint 11. A motor 14, here an electric geared motor, is also immobilized relative to the box 12; in this particular embodiment, it is linked in translation to the housing by means of a shoulder of the latter and of the outer ring 15 of the bearing, and in rotation by pins not shown. The motor 14 carries, on the upper part of its axis, a groove 20, and the support 13 a groove 19, these two grooves constitute, with an intermediate part 18, a seal of coupling, preferably a constant velocity joint, such as an Oldham joint here, which allows the motor 14 to drive the support 13, carrying the fin 2, in rotation around the first axis 5.

Le joint de couplage permet de tolerer un mauvais alignement axial au montage du support et du moteur, mais il permet également d'isoler celui-ci des vibrations que pourrait lui communiquer l'ailette. Le roulement permet également d'isoler le moteur des efforts aerodynamiques que l'ailette transmettra donc directement au projectile 1, par l'intermédiaire du support et du roulement.The coupling joint makes it possible to tolerate poor axial alignment when mounting the support and the motor, but it also makes it possible to isolate the latter from the vibrations which the fin could impart to it. The bearing also makes it possible to isolate the engine from the aerodynamic forces which the fin will therefore transmit directly to the projectile 1, via the support and the bearing.

L'ailette porte un pion 22 dont une extrémité vient se loger dans une rainure circulaire 24 portée par le boîtier. Cette rainure circulaire se termine par un dégagement 27 (voir figure 5), dont l'utilité sera précisée plus loin. Le support 13 porte également un verrou 23, qui est constitué par un doigt 25, coulissant contre l'action d'un ressort de rappel, et qui est destiné à venir dans un logement 26 porté par l'ailette 2, cela dans le but de la verouiller en position déployée à la fin de la deuxième phase du mouvement de déploiement.The fin carries a pin 22, one end of which is housed in a circular groove 24 carried by the housing. This circular groove ends with a clearance 27 (see FIG. 5), the usefulness of which will be specified below. The support 13 also carries a lock 23, which is constituted by a finger 25, sliding against the action of a return spring, and which is intended to come into a housing 26 carried by the fin 2, this for the purpose to lock it in the deployed position at the end of the second phase of the deployment movement.

Enfin un codeur 17, de type connu, et solidaire du support 13, permettra de donner à un ensemble electronique de pilotage, non représenté, l'information de position angulaire de l'ailette 2 relativement au premier axe 5.Finally, an encoder 17, of known type, and integral with the support 13, will make it possible to give an electronic control assembly, not shown, the information on the angular position of the fin 2 relative to the first axis 5.

Ainsi dans ce mode particulier de réalisation, le moteur, dont la fonction principale est d'assurer le guidage du projectile en faisant pivoter l'ailette déployée autour du premier axe 5, est aussi l'actionneur qui provoque la première phase du mouvement de déploiement de l'ailette: son passage de la position d'emport à la position semi-déployée.Thus in this particular embodiment, the motor, the main function of which is to guide the projectile by pivoting the deployed fin around the first axis 5, is also the actuator which causes the first phase of the deployment movement of the fin: its passage from the carrying position to the semi-deployed position.

Le moteur, en raison de l'irreversibilité du réducteur mécanique qu'il comprend, joue aussi le rôle de moyen de blocage de l'ailette en position d'emport.The motor, due to the irreversibility of the mechanical reducer which it comprises, also plays the role of means for blocking the fin in the carrying position.

Une telle disposition présente un certain nombre d'avantages :
   Elle évite l'emploi de dispositifs annexes du type verrou (voir brevet US4664339), pour immobiliser l'ailette en position d'emport, ce qui supprime un risque de panne en simplifiant l'ensemble de la commande du déploiement.Such an arrangement has a number of advantages:
It avoids the use of additional devices of the lock type (see patent US4664339), for immobilizing the fin in the carrying position, which eliminates the risk of failure by simplifying the whole control of deployment.

Elle permet d'assurer une maîtrise de la cinématique de la première phase du mouvement d'ouverture, ce qui entraîne une symétrie des mouvements d'ouverture des différentes ailettes. Le début de l'ouverture est totalement maîtrisé et correspond à la commande des moteurs; vitesses et positions des ailettes peuvent être asservies par un dispositif electronique, connu en soi, qui jouera individuellement sur les tensions de commande des différents moteurs en fonction des informations données par les codeurs.It ensures control of the kinematics of the first phase of the opening movement, which results in symmetry of the opening movements of the different fins. The start of the opening is completely controlled and corresponds to the control of the motors; speeds and positions of the fins can be controlled by an electronic device, known per se, which will play individually on the control voltages of the different motors as a function of the information given by the encoders.

La commande des moteurs permet donc d'accomplir la première phase du mouvement de déploiement, ce qui comme il a été vu précédemment va permettre d'obtenir un freinage progressif de la rotation du projectile; (mais il est également possible d'employer d'autres types d'ailettes de type connu, telles celles qui sont décrites dans le brevet W081/00908, pour provoquer le freinage en rotation, le déploiement des ailettes de guidage n'étant alors commandé que lorsque la vitesse de rotation est tombée en dessous d'une certaine valeur, de l'ordre de 20 à 30 tours/seconde); lorsque les ailettes se trouvent dans la position de la figure 2, le pion 22, qui a circulé pendant le première phase du mouvement de déploiement dans la rainure 24 et a ainsi maintenu l'ailette dans le plan défini par les axes 7 et 8, est alors en regard du dégagement 27. Les efforts aérodynamiques qui s'exercent sur l'ailette suffisent à la faire pivoter autour du deuxième axe 6 et donc à lui faire accomplir la deuxième phase du mouvement de déploiement, justqu'au verouillage de l'ailette; le moteur remplissant ensuite son rôle de guidage en faisant pivoter l'ailette déployée autour du premier axe.The control of the motors therefore makes it possible to accomplish the first phase of the deployment movement, which as has been seen previously will make it possible to obtain progressive braking of the rotation of the projectile; (but it is also possible to use other types of vanes of known type, such as those described in patent W081 / 00908, to cause braking in rotation, the deployment of the guide vanes then being controlled only when the speed of rotation has fallen below a certain value, of the order of 20 to 30 revolutions / second); when the fins are in the position of FIG. 2, the pin 22, which has circulated during the first phase of the deployment movement in the groove 24 and has thus maintained the fin in the plane defined by the axes 7 and 8, is then opposite the clearance 27. The aerodynamic forces exerted on the fin are sufficient to rotate it around the second axis 6 and therefore to make it accomplish the second phase of the deployment movement, just until the locking of the fin; the engine then fulfilling its guiding role by pivoting the deployed fin around the first axis.

Il est bien évident qu'il serait possible, sans pour autant sortir du cadre de l'invention, de remplacer le pion par une zone saillante de l'ailette elle-même, ou tout autre équivalent technique assurant le maintien de l'ailette, au cours de la première phase du mouvement de déploiement, dans le plan défini par les axes 7 et 8.It is quite obvious that it would be possible, without departing from the scope of the invention, to replace the pin with a protruding area of the fin itself, or any other technical equivalent ensuring the maintenance of the fin, during the first phase of the deployment movement, in the plane defined by axes 7 and 8.

D'autres variantes sont possibles sans sortir du cadre de l'invention. D'autres types de moteurs sont envisageables pour remplir à la fois la fonction d'actionneur du mouvement de déploiement de l'ailette, et la fonction de pilotage du projectile; tel un moteur pneumatique, alimenté par une reserve de gaz ou bien par un générateur de gaz à initiation pyrotechnique.Other variants are possible without departing from the scope of the invention. Other types of motors can be envisaged to fulfill both the function of actuator of the deployment movement of the fin, and the function of piloting the projectile; such as a pneumatic motor, powered by a gas reserve or else by a gas generator with pyrotechnic initiation.

Il est possible d'appliquer l'invention à des ailettes uniquement stabilisatrices et ne remplissant donc pas de fonction de guidage. On aura alors une articulation 11 du type de celle précédemment décrite, mais l'absence de moteur conduira à utiliser alors un actionneur, par exemple mécanique, tel un ressort donnant une impulsion à l'ailette, les efforts aérodynamiques agissant sur celli-ci de façon à achever le mouvement de déploiement; et il sera éventuellement necessaire de prévoir un moyen de blocage, tel celui décrit dans le brevet US4664339.It is possible to apply the invention to fins which are only stabilizers and therefore do not fulfill any guiding function. We will then have a joint 11 of the type described above, but the absence of a motor will then lead to the use of an actuator, for example mechanical, such as a spring giving an impulse to the fin, the aerodynamic forces acting on it. so as to complete the deployment movement; and it may be necessary to provide a blocking means, such as that described in patent US4664339.

Il est possible également de combiner ce dernier mode de blocage et d'ouverture des ailettes avec l'emploi d'un moteur electrique de guidage, il sera alors necessaire de prévoir un dispositif de débrayage du moteur pendant la première phase du mouvement de déploiement.It is also possible to combine this latter method of locking and opening the fins with the use of an electric guide motor, it will then be necessary to provide a device for disengaging the motor during the first phase of the deployment movement.

Claims (10)

  1. Mechanism for deploying a fin (2) of a projectile (1), from a stowed position, in which its plane is substantially parallel to the axis (4) of the projectile, to a deployed position, the fin being attached to the projectile by a pivot (11), characterised by the fact that the pivot is such that the deployment movement takes place in at least two stages:
    a first phase in which the fin moves from the stowed position to a semi-deployed position, this movement being a rotation about a first axis (5) which is perpendicular to the plane of the fin when the latter is in the stowed position
    and a second phase in which the fin (2) moves from the semi-deployed position to the deployed position by rotating about a second axis (6) which is parallel to the plane of the fin.
  2. Deployment mechanism according to claim 1, characterised by the fact that the fin (2) is moved by an actuator during all or part of the first phase of the deployment movement.
  3. Deployment mechanism according to claim 1 characterised by the fact that in the stowed position the fin (2) is immobilised relative to the projectile (1) by a locking device.
  4. Deployment mechanism according to claim 1, characterised by the fact that the fin (2) in the deployed position can pivot about the first axis (5) under the action of a servo motor (14).
  5. Deployment mechanism according to claim 4, characterised by the fact that the servo motor (14) is the actuator and/or the locking device.
  6. Deployment mechanism according to claim 5, characterised by the fact that the fin (2) is attached to a mounting (13), which is itself fixed relative to the inner ring (16) of a bearing and that the outer ring (15) of this bearing is fixed relative to the projectile (1).
  7. Deployment mechanism according to claim 6, characterised by the fact that the motor 14 is fixed relative to the projectile (1) and rotates the mounting (13) through a coupling.
  8. Deployment mechanism according to claims 1 to 7, characterised by the fact that the fin (2) is moved by the aerodynamic forces during the second phase of the deployment movement.
  9. Deployment mechanism according to claim 8, characterised by the fact that the fin (2) carries a pin (22) which during the first phase of the deployment movement travels in a circular groove (24) which is fixed relative to the projectile, the second phase commencing when the pin (22) passes in front of an opening (27) in this grove.
  10. Deployment mechanism according to claim 6, characterised by the fact that the mounting (13) includes a bolt (23) which immobilises the fin (2) relative to the mounting in the deployed position.
EP88402880A 1987-11-26 1988-11-16 Device for spreading projectile wings Expired - Lifetime EP0318359B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8716389 1987-11-26
FR8716389A FR2623898B1 (en) 1987-11-26 1987-11-26 DEVICE FOR DEPLOYING A PROJECTILE FIN

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EP0318359A1 EP0318359A1 (en) 1989-05-31
EP0318359B1 true EP0318359B1 (en) 1992-06-17

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EP (1) EP0318359B1 (en)
CA (1) CA1333027C (en)
DE (1) DE3872181T2 (en)
ES (1) ES2032045T3 (en)
FR (1) FR2623898B1 (en)
TR (1) TR23598A (en)

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US4588146A (en) * 1984-03-29 1986-05-13 The United States Of America As Represented By The Secretary Of The Army Biaxial folding lever wing
US4592525A (en) * 1985-02-07 1986-06-03 The United States Of America As Represented By The Secretary Of The Army Counter-rotating folding wings
FR2600618A1 (en) * 1986-06-27 1987-12-31 Thomson Brandt Armements WING WITH MULTIPLE DEPLOYMENT AND ITS APPLICATION TO A FLYING DEVICE
US4869442A (en) * 1988-09-02 1989-09-26 Aerojet-General Corporation Self-deploying airfoil

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106352746A (en) * 2016-10-18 2017-01-25 湖北航天技术研究院总体设计所 Folding fin automatic and synchronous unlocking driving device

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Publication number Publication date
US5108051A (en) 1992-04-28
FR2623898B1 (en) 1990-03-23
CA1333027C (en) 1994-11-15
DE3872181D1 (en) 1992-07-23
TR23598A (en) 1990-04-24
EP0318359A1 (en) 1989-05-31
DE3872181T2 (en) 1992-12-17
ES2032045T3 (en) 1993-01-01
FR2623898A1 (en) 1989-06-02

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