EP0275766B1 - Brake mechanism for a deployable wing and guided missile therewith - Google Patents

Brake mechanism for a deployable wing and guided missile therewith Download PDF

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Publication number
EP0275766B1
EP0275766B1 EP87402911A EP87402911A EP0275766B1 EP 0275766 B1 EP0275766 B1 EP 0275766B1 EP 87402911 A EP87402911 A EP 87402911A EP 87402911 A EP87402911 A EP 87402911A EP 0275766 B1 EP0275766 B1 EP 0275766B1
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EP
European Patent Office
Prior art keywords
trunnion
compression ring
wing
deformation member
axis
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Expired - Lifetime
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EP87402911A
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German (de)
French (fr)
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EP0275766A1 (en
Inventor
Etienne Lamarque
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Thomson Brandt Armements SA
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Thomson Brandt Armements 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 relates to deployable wings, such as those used on missiles, self-propelled rockets and the like, which will hereinafter be called guided projectiles. It relates in particular to a braking system for the deployment of these wings.
  • Deployable fins are known, which are articulated on the body of the projectile around longitudinal axes, parallel to the longitudinal axis of the body. These fins are tangential to this body in the folded position, and located in radial axial planes, in the active position.
  • This kind of empennage has a major drawback due to the brutality of the deployment of the fins. Indeed, this movement is caused mechanically either by pistons or by pyrotechnic devices which tend to spread the wings of the body of the projectile. Once these wings are spread, the increase in the speed of the projectile at the time of deployment, and the increase in the speed of rotation of the fins, due to the increase in the surface of the deploying wing, means that the latter arrives in the deployed position at a considerable speed, and therefore with sufficient energy to damage either the fin itself or the abutment elements which hold it in this deployed position.
  • the invention proposes to remedy this drawback by proposing a system for braking the deployment of the fin to avoid this sudden stop in the deployed position, and the deterioration of a fin set mounted on a guided projectile.
  • the French patent application published under No. 2448707 describes a fin assembly for a flying object, where a fin can rotate about an axis tangential to the body of the object, on a turntable, which can - even turn around an axis transverse to the machine.
  • This rotation is carried out by endless screws which transmit the rotational movement to the turntable, during the rotation of the fin about the tangential axis.
  • the fin is first applied against the surface of the flying object, its axis being directed tangentially and transversely to the longitudinal axis of the object. During the straightening, the fin rotates so that its axis is parallel to the longitudinal axis of the flying object.
  • a braking mechanism acting on the turntable to delay the rotational movement of the latter, and therefore, the deployment of the fin.
  • This device involves too many moving mechanical parts (turntable, worm, ).
  • the object of the invention is to propose another simpler braking device which acts directly on the fin, and a guided projectile equipped with such a device.
  • the invention consists in involving a thread and a deformation piece which by their combined effects allow regulation of the speed of deployment of the wing and the absorption of a maximum part of the kinetic energy due to this deployment, the remaining energy being calibrated so as not to alter the geometry of the airfoil or the supporting structure.
  • FIG. 1A is a cross-sectional view along the axis A, A '
  • the deployment of a fin is done as follows.
  • the fin 20 is shown in the folded position against the body of the projectile 21. It is pivotally mounted relative to the body, about an axis A, A 'which is oblique to the longitudinal axis of the body, and this also well relative to the plane of the fin, that is to say according to the plane FIG. 1A, than with respect to the plane perpendicular to the plane of the fin, that is to say relative to the plane of the FIG. 1 B.
  • the rotation of the fin 20 around this axis brings the latter into its deployed position, that is to say that it is always pressed against the body of the missile 21, but its plane is perpendicular to the plan it occupied in the folded position.
  • the wing 6 is shown in the case of an oblique joint, such as that described in the previous paragraph, but provided with a braking device according to the invention.
  • This consists mainly of means of transformation of the kinetic energy of rotation into energy of translation which, by the effect of the thread and the deformation part, absorb a maximum part of the speed and give the wing a regular deployment.
  • the wing 6 is integral with a journal which allows the rotation of this wing, relative to the body of the projectile.
  • the pin 1 is mounted to rotate about its axis XX 'which is fixed relative to a body 2.
  • the means for converting the kinetic energy of rotation into translation energy further comprise means for locking in translation relative to the body 2 of the journal 1.
  • These energy transformation means also comprise a ring 4 which is called the compression ring and which is screwed onto a thread 10, formed on the outside diameter of the journal 1.
  • the means of transformation of the energy also include means for locking in rotation relative to the body 2 of this compression tank 4.
  • the energy transformation means comprise a stop in translation around the pin 1.
  • the deformation part 5 is placed between this translation stop and the compression ring 4.
  • the length of this ring is less than the distance separating the stop from a shoulder 14 of the compression ring 4, of m so that there is a clearance E in length when the wing is in the folded position.
  • Trunnion 1 is mounted rotating around its axis XX ′ by means of a bearing 3, integral with body 2.
  • the inside diameter of this trunnion actually has a recess corresponding to a shoulder 11 of the trunnion 1, so that the latter either blocked in translation relative to the body 2, so as not to move in the direction indicated by the arrow F.
  • a second bearing is produced using the compression ring 4 which is fixed in rotation relative to the body 2.
  • the rotation ring of this compression ring is made by two flats, not shown, and made on the outside diameter 12 of the compression ring 4.
  • This ring has a lateral face 14 against which the deformation piece comes to bear. 5.
  • this deformation part is shown in the form of a flattened U, but this form is not limiting.
  • the system works as follows.
  • the wing 6 When the wing 6 is caused to pivot about the axis X, X ′ it drives the pin 1 which is integral with it. Due to this rotation, and the fact that the compression ring 4 is mounted screwed about this axis and locked in rotation relative to the body 2, the latter moves in translation inside the hole 13.
  • the direction of thread screw 10 of the journal 1 and the internal thread of the compression ring 4 are chosen so that the compression ring moves towards the first bearing 3 so as to compress the deformation piece 5 between a surface radial 15 of the first bearing 3 and the radial surface 4 of the compression ring 4.
  • a minimum clearance is provided.
  • the internal thread and the thread may be with several threads, which allows better mechanical resistance of the system, and greater displacement in translation of the compression part.
  • Deployment of the wing at substantially constant speed is only possible, if an additional device gives it a sufficient incidence at the start, for the air current to make it deploy. To do this, it is necessary that the wing has a free rotation at the start of its deployment before the braking phase. Depending on the case, this rotation can vary from 20 to 60 degrees.
  • the deformation piece 5 must therefore have a length such that, in the folded position of the wing, there remains the clearance E between the end 7 opposite the compression ring 4 and the radial face 15 of the bearing 3. This clearance E corresponds to the translation of the compression ring 4 during this free rotation phase.
  • the additional incidence setting device can be produced by means of a piston actuated by the action of gases generated by a charge placed on board the projectile, and ignited by an electric igniter or a mechanical striker.
  • the deformation part 5 can absorb energy in several ways.
  • this compression part has a tubular shape reinforced at these ends, so as to represent a flattened U.
  • this part When this part is compressed, there is a buckling of its central part, the material of this central part partially filling the interior of the U.
  • the materials used can be copper, aluminum, or any relatively malleable alloy and ductile.
  • the compression ring 34 and the deformation part 35 have shapes different from those of the previous embodiment.
  • the compression ring 34 is always free in translation and fixed in rotation, so as to translate towards the deformation part 35.
  • the actual deformation does not occur in the same way, because the deformation part, although being still tubular, has a more compact shape, and its internal diameter is adjusted to that of the axis 31. It is always in abutment on the radial surface 15 of the first bearing 33.
  • the opposite end receives the action of the compression ring 34 which goes towards the deformation part 35. Longitudinal compression by buckling of the latter is no longer possible, due to the compactness of this part.
  • the deformation piece 35 may be made of a more or less viscous material, depending on whether an elastomer or a grease is used.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Vibration Dampers (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Description

L'invention concerne les ailes déployables, telles que celles employées sur les missiles, les roquettes auto-propulsées et engins similaires, que l'on appellera par la suite projectiles guidés. Elle concerne en particulier un système de freinage du déploiement de ces ailes.The invention relates to deployable wings, such as those used on missiles, self-propelled rockets and the like, which will hereinafter be called guided projectiles. It relates in particular to a braking system for the deployment of these wings.

On connaît des ailettes déployables, qui sont articulées sur le corps du projectile autour d'axes longitudinaux, parallèles à l'axe longitudinal du corps. Ces ailettes sont tangentielles à ce corps en position rabattue, et situées dans des plans axiaux radiaux, en position active.Deployable fins are known, which are articulated on the body of the projectile around longitudinal axes, parallel to the longitudinal axis of the body. These fins are tangential to this body in the folded position, and located in radial axial planes, in the active position.

On connaît également par le brevet français publié sous le n01 485 580, un empennage perfectionné pour roquettes, dans lequel chaque ailette est articulée sur le corps de l'empennage, autour d'un axe oblique d'orientation. Ceci a pour effet que, au cours du déploiement des ailettes, chacune d'elles passe d'une position rabattue pour laquelle elle est appliquée tangentiellement sur le corps de l'empennage, à une position déployée, dans laquelle l'ailette est située dans un plan axial radial.Also known from the French patent published under the number 0 1 485 580, an improved tail for rockets, in which each fin is articulated on the body of the tail, around an oblique axis of orientation. This has the effect that, during the deployment of the fins, each of them passes from a folded position for which it is applied tangentially on the body of the tail, to a deployed position, in which the fin is located in a radial axial plane.

Ce genre d'empennage possède un inconvénient majeur du fait de la brutalité du déploiement des ailettes. En effet, ce déplacement est provoqué mécaniquement soit par des pistons soit par des dispositifs pyrotechniques qui tendent à écarter les ailes du corps du projectile. Une fois ces ailes écartées, l'accroissement de la vitesse du projectile au moment du déploiement, et l'accroissement de vitesse de la rotation des ailettes, dû à l'augmentation de la surface de l'aile se déployant, font que cette dernière arrive dans la position déployée à une vitesse considérable, et donc avec une énergie suffisante pour détériorer, soit l'ailette elle-même, soit les éléments de butée qui la maintiennent dans cette position déployée.This kind of empennage has a major drawback due to the brutality of the deployment of the fins. Indeed, this movement is caused mechanically either by pistons or by pyrotechnic devices which tend to spread the wings of the body of the projectile. Once these wings are spread, the increase in the speed of the projectile at the time of deployment, and the increase in the speed of rotation of the fins, due to the increase in the surface of the deploying wing, means that the latter arrives in the deployed position at a considerable speed, and therefore with sufficient energy to damage either the fin itself or the abutment elements which hold it in this deployed position.

L'invention se propose de remédier à cet inconvénient en proposant un système de freinage du déploiement de l'ailette pour éviter cet arrêt brutal en position déployée, et la détérioration d'un jeu d'ailette monté sur un projectile guidé.The invention proposes to remedy this drawback by proposing a system for braking the deployment of the fin to avoid this sudden stop in the deployed position, and the deterioration of a fin set mounted on a guided projectile.

D'autre part, la demande de brevet français publiée sous le N° 2448707 décrit un ensemble à ailettes pour engin volant, où une ailette peut tourner autour d'un axe tangentiel au corps de l'engin, sur un plateau tournant, pouvant lui-même tourner autour d'un axe transversal à l'engin. Cette rotation est effectuée par des vis sans fin qui transmettent le mouvement de rotation au plateau tournant, pendant la rotation de l'ailette autour de l'axe tangentiel. L'ailette est d'abord appliquée contre la surface de l'engin volant, son axe étant dirigé tangentiellement et transversalement à l'axe longitudinal de l'engin. Pendant le redressement l'ailette tourne de façon à ce que son axe se trouve parallèle à l'axe longitudinal de l'engin volant. Dans cet ensemble il est prévu un mécanisme de freinage, agissant sur le plateau tournant pour retarder le mouvement de rotation de ce dernier, et par conséquent, le déploiement de l'ailette.On the other hand, the French patent application published under No. 2448707 describes a fin assembly for a flying object, where a fin can rotate about an axis tangential to the body of the object, on a turntable, which can - even turn around an axis transverse to the machine. This rotation is carried out by endless screws which transmit the rotational movement to the turntable, during the rotation of the fin about the tangential axis. The fin is first applied against the surface of the flying object, its axis being directed tangentially and transversely to the longitudinal axis of the object. During the straightening, the fin rotates so that its axis is parallel to the longitudinal axis of the flying object. In this assembly there is provided a braking mechanism, acting on the turntable to delay the rotational movement of the latter, and therefore, the deployment of the fin.

Ce dispositif fait intervenir trop de pièces mécaniques en mouvements (plateau tournant, vis sans fin,...).This device involves too many moving mechanical parts (turntable, worm, ...).

Le but de l'invention est de proposer un autre dispositif de freinage plus simple et agissant directement sur l'ailette, et un projectile guidé équipé d'un tel dispositif.The object of the invention is to propose another simpler braking device which acts directly on the fin, and a guided projectile equipped with such a device.

L'objet de l'invention est un dispositif de freinage du déploiement, par rapport à un corps, d'une aile déployable, articulée autour d'un axe fixe par rapport audit corps, pour réaliser ledit déploiement par pivotement autour dudit axe, caractérisé en ce qu'il comprend des moyens de transformation de l'énergie cinétique de rotation en énergie de translation comportant un filetage et une pièce de déformation permettant d'une part, le déploiement de l'aile à vitesse sensiblement constante et, d'autre part, l'absorption en grande partie de l'énergie cinétique de rotation du déploiement de l'aile. L'invention et ses caractéristiques seront mieux comprises à la lecture de la description qui suit, et qui est illustrée des figures suivantes :

  • - Figs.1 A et 1 B, une ailette selon l'art antérieur en position rabattue selon deux vues perpendiculaires ;
  • - Fig.2, un premier mode de réalisation du dispositif selon l'invention ;
  • - Fig.3A et 3B, un deuxième mode de réalisation du dispositif selon l'invention.
The object of the invention is a device for braking the deployment, relative to a body, of a deployable wing, articulated around an axis fixed relative to said body, to carry out said deployment by pivoting around said axis, characterized in that it comprises means for transforming the kinetic energy of rotation into translational energy comprising a thread and a deformation piece allowing on the one hand, the deployment of the wing at substantially constant speed and, on the other part, the absorption largely of the kinetic energy of rotation of the deployment of the wing. The invention and its characteristics will be better understood on reading the following description, which is illustrated by the following figures:
  • - Figs.1 A and 1 B, a fin according to the prior art in the folded position in two perpendicular views;
  • - Fig.2, a first embodiment of the device according to the invention;
  • - Fig.3A and 3B, a second embodiment of the device according to the invention.

Au fur et à mesure qu'une aile déployable s'ouvre, la surface sollicitée par le courant d'air est de plus en plus importante, ceci explique l'accroissement, de la vitesse du déploiement et de l'énergie cinétiqueAs a deployable wing opens, the surface stressed by the air flow is more and more important, this explains the increase, the speed of deployment and the kinetic energy

L'invention consiste à faire intervenir un filetage et une pièce de déformation qui par leurs effets combinés permettent une régulation de la vitesse du déploiement de l'aile et l'absorption d'une partie maximale de l'énergie cinétique due à ce déploiement, l'énergie restante étant calibrée de façon à ne pas altérer la géométrie de la voilure ou la structure porteuse.The invention consists in involving a thread and a deformation piece which by their combined effects allow regulation of the speed of deployment of the wing and the absorption of a maximum part of the kinetic energy due to this deployment, the remaining energy being calibrated so as not to alter the geometry of the airfoil or the supporting structure.

En référence aux figures 1A et 1B, 1 B étant une vue en coupe transversale selon l'axe A, A', le déploiement d'une ailette selon l'art antérieur se fait de la façon suivante. L'ailette 20 est représentée en position rabattue contre le corps du projectile 21. Elle est montée pivotante par rapport au corps, autour d'un axe A,A' qui est oblique par rapport à l'axe longitudinal du corps, et ceci aussi bien par rapport au plan de l'ailette, c'est-à-dire selon le plan la figure 1A, que par rapport au plan perpendiculaire au plan de l'ailette, c'est-à-dire par rapport au plan de la figure 1 B. La rotation de l'ailette 20 autour de cet axe amène cette dernière dans sa position déployée, c'est-à-dire qu'elle se trouve toujours appuyée contre le corps du missile 21, mais son plan est perpendiculaire au plan qu'elle occupait en position rabattue.Referring to Figures 1A and 1B, 1 B being a cross-sectional view along the axis A, A ', the deployment of a fin according to the prior art is done as follows. The fin 20 is shown in the folded position against the body of the projectile 21. It is pivotally mounted relative to the body, about an axis A, A 'which is oblique to the longitudinal axis of the body, and this also well relative to the plane of the fin, that is to say according to the plane FIG. 1A, than with respect to the plane perpendicular to the plane of the fin, that is to say relative to the plane of the FIG. 1 B. The rotation of the fin 20 around this axis brings the latter into its deployed position, that is to say that it is always pressed against the body of the missile 21, but its plane is perpendicular to the plan it occupied in the folded position.

En référence à la figure 2, l'aile 6 est représentée dans le cas d'une articulation oblique, telle que celle décrite dans le précédent paragraphe, mais dotée d'un dispositif de freinage selon l'invention. Celui-ci est constitué principalement de moyens de transformation de l'énergie cinétique de rotation en énergie de translation qui, par l'effet du filetage et de la pièce de déformation, absorbent une partie maximale de la vitesse et donnent à l'aile un déploiement régulier. Dans ce but l'aile 6 est solidaire d'un tourillonl qui permet la rotation de cette aile, par rapport au corps du projectile. Le tourillon 1 est monté tournant autour de son axe X X' qui est fixe par rapport à un corps 2. Les moyens de transformation de l'énergie cinétique de rotation en énergie de translation comprennent en outre, des moyens de blocage en translation par rapport au corps 2 du tourillon 1. Ces moyens de transformation de l'énergie comprennent également une bague 4 qui est appelée bague de compression et qui est vissée sur un filetage 10, pratiqué sur le diamètre extérieur du tourillon 1. Les moyens de transformation de l'énergie comprennent également des moyens de blocage en rotation par rapport au corps 2 de cette baque de compression 4. Enfin, les moyens de transformation de l'énergie comprennent une butée en translation autour du tourillon 1. La pièce de déformation 5 est placée entre cette butée en translation et la bague de compression 4. La longueur de cette bague est inférieure à la distance séparant la butée d'un épaulement 14 de la bague de compression 4, de manière à ce qu'il reste un jeu E en longueur lorsque l'aile est en position rabattue.Referring to Figure 2, the wing 6 is shown in the case of an oblique joint, such as that described in the previous paragraph, but provided with a braking device according to the invention. This consists mainly of means of transformation of the kinetic energy of rotation into energy of translation which, by the effect of the thread and the deformation part, absorb a maximum part of the speed and give the wing a regular deployment. For this purpose the wing 6 is integral with a journal which allows the rotation of this wing, relative to the body of the projectile. The pin 1 is mounted to rotate about its axis XX 'which is fixed relative to a body 2. The means for converting the kinetic energy of rotation into translation energy further comprise means for locking in translation relative to the body 2 of the journal 1. These energy transformation means also comprise a ring 4 which is called the compression ring and which is screwed onto a thread 10, formed on the outside diameter of the journal 1. The means of transformation of the energy also include means for locking in rotation relative to the body 2 of this compression tank 4. Finally, the energy transformation means comprise a stop in translation around the pin 1. The deformation part 5 is placed between this translation stop and the compression ring 4. The length of this ring is less than the distance separating the stop from a shoulder 14 of the compression ring 4, of m so that there is a clearance E in length when the wing is in the folded position.

Pour faire référence de manière plus précise à une réalisation concrète telle que celle représentée sur la figure 2, les moyens de transformation de l'énergie cinétique en énergie de translation sont réalisés sous forme suivante. Le tourillon 1 est monté tournant autour de son axe X X' grâce à un palier 3, solidaire du corps 2. Le diamètre intérieur de ce tourillon possède en fait un décrochement correspondant à un épaulement 11 du tourillon 1, de façon à ce que ce dernier soit bloqué en translation par rapport au corps 2, de manière à ne pas se déplacer dans le sens indiqué par la flèche F. Un deuxième palier est réalisé à l'aide de la bague 4 de compression qui est fixe en rotation par rapport au corps 2. Le blocage en rotation de cette bague de compression est réalisé par deux méplats non représentés, et effectués sur le diamètre extérieur 12 de la bague de compression 4. Cette bague possède une face latérale 14 contre laquelle vient s'appuyer la pièce de déformation 5. Sur la figure 2, cette pièce de déformation est représentée en forme de U aplati, mais cette forme n'est pas limitative.To refer more precisely to a concrete embodiment such as that shown in FIG. 2, the means for transforming kinetic energy into translational energy are produced in the following form. Trunnion 1 is mounted rotating around its axis XX ′ by means of a bearing 3, integral with body 2. The inside diameter of this trunnion actually has a recess corresponding to a shoulder 11 of the trunnion 1, so that the latter either blocked in translation relative to the body 2, so as not to move in the direction indicated by the arrow F. A second bearing is produced using the compression ring 4 which is fixed in rotation relative to the body 2. The rotation ring of this compression ring is made by two flats, not shown, and made on the outside diameter 12 of the compression ring 4. This ring has a lateral face 14 against which the deformation piece comes to bear. 5. In FIG. 2, this deformation part is shown in the form of a flattened U, but this form is not limiting.

Le fonctionnement du système est le suivant. Lorsque l'aile 6 est amenée à pivoter autour de l'axe X,X' elle entraîne le tourillon 1 qui lui est solidaire. Du fait de cette rotation, et du fait que la bague de compression 4 est montée vissée autour de cet axe et bloquée en rotation par rapport au corps 2, celle-ci se déplace en translation à l'intérieur du trou 13. Le sens du pas de vis du filetage 10 du tourillon 1 et du taraudage intérieur de la bague de compression 4 sont choisis de manière à ce que la bague de compression se déplace vers le premier palier 3 de façon, à comprimer la pièce de déformation 5 entre une surface radiale 15 du premier palier 3 et la surface radialel4 de la bague de compression 4. Pour que cette translation ait lieu, il faut également, qu'entre le filetage 10 et le taraudage intérieur de la bague de compression, soit prévu un jeu minimal. Suivant l'angle de rotation de l'aile, le taraudage et le filetage pourront être à plusieurs filets, ce qui permet une meilleure résistance mécanique du système, et un plus grand déplacement en translation de la pièce de compression.The system works as follows. When the wing 6 is caused to pivot about the axis X, X ′ it drives the pin 1 which is integral with it. Due to this rotation, and the fact that the compression ring 4 is mounted screwed about this axis and locked in rotation relative to the body 2, the latter moves in translation inside the hole 13. The direction of thread screw 10 of the journal 1 and the internal thread of the compression ring 4 are chosen so that the compression ring moves towards the first bearing 3 so as to compress the deformation piece 5 between a surface radial 15 of the first bearing 3 and the radial surface 4 of the compression ring 4. For this translation to take place, it is also necessary that between the thread 10 and the internal thread of the compression ring, a minimum clearance is provided. Depending on the angle of rotation of the wing, the internal thread and the thread may be with several threads, which allows better mechanical resistance of the system, and greater displacement in translation of the compression part.

Le déploiement de l'aile à vitesse sensiblement constante n'est possible, que si un dispositif annexe lui donne une incidence suffisante au départ, pour que le courant d'air la fasse se déployer. Pour ce faire, il est nécessaire que l'aile ait une rotation libre au début de son déploiement avant la phase de freinage. Suivant le cas, cette rotation peut varier de 20 à 60 degrés. La pièce de déformation 5 doit donc avoir une longueur telle que, à la position rabattue de l'aile, il subsiste le jeu E entre l'extrémité 7 opposée à la bague de compression 4 et la face radiale 15 du palier 3. Ce jeu E correspond à la translation de la bague de compression 4 pendant cette phase de rotation libre.Deployment of the wing at substantially constant speed is only possible, if an additional device gives it a sufficient incidence at the start, for the air current to make it deploy. To do this, it is necessary that the wing has a free rotation at the start of its deployment before the braking phase. Depending on the case, this rotation can vary from 20 to 60 degrees. The deformation piece 5 must therefore have a length such that, in the folded position of the wing, there remains the clearance E between the end 7 opposite the compression ring 4 and the radial face 15 of the bearing 3. This clearance E corresponds to the translation of the compression ring 4 during this free rotation phase.

Le dispositif annexe de mise en incidence peut être réalisé grâce à un piston actionné sous l'action des gaz générés par une charge placée à bord du projectile, et mise à feu par un inflammateur électrique ou un percuteur mécanique.The additional incidence setting device can be produced by means of a piston actuated by the action of gases generated by a charge placed on board the projectile, and ignited by an electric igniter or a mechanical striker.

La pièce de déformation 5 peut absorber l'énergie de plusieurs façons. La première correspond à celle de la réalisation représentée figure 2. Dans ce cas, cette pièce de compression a une forme tubulaire renforcée à ces extrémités, de manière à représenter un U aplati. Lorsque cette pièce est comprimée, il se produit un flambement de sa partie centrale, la matière de cette partie centrale venant combler partiellement l'intérieur du U. Les matériaux utilisés, peuvent être du cuivre de l'aluminium, ou tout alliage relativement malléable et ductile.The deformation part 5 can absorb energy in several ways. The first corresponds to that of the embodiment shown in Figure 2. In this case, this compression part has a tubular shape reinforced at these ends, so as to represent a flattened U. When this part is compressed, there is a buckling of its central part, the material of this central part partially filling the interior of the U. The materials used can be copper, aluminum, or any relatively malleable alloy and ductile.

En référence aux figures 3A et 3B, la bague de compression 34 et la pièce de déformation 35 ont des formes différentes de celles de la réalisation précédente. La bague de compression 34 est toujours libre en translation et fixe en rotation, de manière à se translater vers la pièce de déformation 35. La déformation proprement dite ne se produit pas de la même manière, car la pièce de déformation, bien qu'étant toujours tubulaire, a une forme plus compacte, et son diamètre intérieur est ajusté à celui de l'axe 31. Elle est toujours en appui sur la surface radiale 15 du premier pallier 33. Par contre, l'extrémité opposée reçoit l'action de la bague de compression 34 qui se dirige vers la pièce de déformation 35. La compression longitudinale par flambement de cette dernière n'est plus possible, du fait de la compacité de cette pièce. Comme un espace 36 est aménagé entre le diamètre extérieur de la bague de compression et le diamètre intérieur du corps 32, la pièce de déformation a tendance à combler cet espace, par refoulement de la matière. La pièce de déformation 35 peut être dans un matériau plus ou moins visqueux, selon que l'on emploie un élastomère ou une graisse.With reference to FIGS. 3A and 3B, the compression ring 34 and the deformation part 35 have shapes different from those of the previous embodiment. The compression ring 34 is always free in translation and fixed in rotation, so as to translate towards the deformation part 35. The actual deformation does not occur in the same way, because the deformation part, although being still tubular, has a more compact shape, and its internal diameter is adjusted to that of the axis 31. It is always in abutment on the radial surface 15 of the first bearing 33. On the other hand, the opposite end receives the action of the compression ring 34 which goes towards the deformation part 35. Longitudinal compression by buckling of the latter is no longer possible, due to the compactness of this part. As a space 36 is arranged between the outside diameter of the compression ring and the inside diameter of the body 32, the deformation part tends to fill this space, by pushing back the material. The deformation piece 35 may be made of a more or less viscous material, depending on whether an elastomer or a grease is used.

Ces modes de réalisations sont adaptés à une application sur un projectile guidé, le corps 2 étant le corps du projectile.These embodiments are suitable for application on a guided projectile, the body 2 being the body of the projectile.

Claims (9)

1. A device for retarding the deployment of a deployable wing (6) in relation to a body (2) about an axis (X-X') in order to effect deployment by pivoting about the said axis, characterized in that it comprises means for the transformation of rotational kinetic energy into translatory energy made up of a screw thread (10)and a deformation member (5) permitting on the one hand the deployment of the wing at a substantially constant rate and on the other hand the absorption of large part of the rotational kinetic energy of the wing.
2. The device as claimed in claim 1, characterized in that the means for the transformation of energy comprise a trunnion (1) whose axis coincides with the axis (X and X') around which the wing (6) pivots and integral with the wing, and in that the deformation member (5), which is annular and placed around the trunnion, is deformed by compression along the said axis.
3. The device as claimed in claim 2, characterized in that the trunnion (1) possesses a screw thread (10) and in that the energy transforming means comprise a compression ring (4) screwed on the said screw thread and being free for translatory motion in relation to the body (2), the deformation member being placed around the trunnion, means for arresting translatory motion of the said trunnion (1) in relation to the member (2), rotation arresting means of the said compression ring (4) in relation to the member, and translatory abutment of the deformation member (5) placed between this said abutment and the compression ring in such a manner as to be compressed when the said ring is in the translated state under the effect of the rotation of the trunnion.
4. The device as claimed in claim 3, characterized in that the means for arresting the trunnion (1) in translation in relation to the body (2) and the abutment are constituted by a bearing (3) integral with the member and having a shoulder on which a shoulder (11) of the trunnion (1) comes to rest and in that the rotational arresting means of the said compression ring (4) are constituted by flats produced on the outer diameter (12) of the compression ring (4).
5. The device as claimed in claim 3 or in claim 4, characterized in that the deformation member (5) has a tubular form reinforced at its ends, in the form of a flattened U in such a manner as to be deformed by upsetting under the action of the compression ring (4).
6. The device as claimed in claim 3 or in claim 4, characterized in that the deformation member (35) has a compact tubular form, the compression ring (34) having such a shape that there is a space (36) in order to permit the deformation of the deformation member by displacement towards the said space of the material of which it is made.
7. The device as claimed in claim 5, characterized in that the deformation member (5) is made of a malleable alloy.
8. The device as claimed in claim 6, characterized in that the deformation member (35) is an elastomer.
9. A guided missile comprising at least one pair of deployable wings, characterized in that it is equipped with a retarding device for the said wings as claimed in any one of the preceding claims.
EP87402911A 1986-12-23 1987-12-18 Brake mechanism for a deployable wing and guided missile therewith Expired - Lifetime EP0275766B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8618084A FR2608750A1 (en) 1986-12-23 1986-12-23 DEVICE FOR BRAKING THE DEPLOYMENT OF A WING AND PROJECTILE GUIDE EQUIPPED WITH SUCH A DEVICE
FR8618084 1986-12-23

Publications (2)

Publication Number Publication Date
EP0275766A1 EP0275766A1 (en) 1988-07-27
EP0275766B1 true EP0275766B1 (en) 1990-08-29

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP87402911A Expired - Lifetime EP0275766B1 (en) 1986-12-23 1987-12-18 Brake mechanism for a deployable wing and guided missile therewith

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US (1) US4852828A (en)
EP (1) EP0275766B1 (en)
DE (1) DE3764633D1 (en)
FR (1) FR2608750A1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2237362B (en) * 1989-10-24 1994-01-19 British Aerospace Retardation and arming mechanism for a projectile
FR2657703B1 (en) * 1990-01-26 1992-04-10 Thomson Brandt Armements DEVICE FOR CONTROLLING THE ROLLING ATTITUDE OF A FIXTURE STABILIZED PROJECTILE.
DE4119613C2 (en) * 1991-06-14 1997-03-27 Diehl Gmbh & Co Missiles with fold-out guidance devices
SE544263C2 (en) * 2020-07-03 2022-03-22 Saab Ab A wing arrangement, a projectile, a method for deploying a wing blade, a use and a method for assembly

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3785290A (en) * 1971-03-01 1974-01-15 Us Navy Bomb fin shock absorber assembly
US3819132A (en) * 1973-02-21 1974-06-25 Sarmac Sa Self propelled projectile with fins
US4143838A (en) * 1977-08-22 1979-03-13 The United States Of America As Represented By The Secretary Of The Navy Folding fin assembly detent
US4175720A (en) * 1978-04-05 1979-11-27 The United States Of America As Represented By The Secretary Of The Navy Retainer/release mechanism for use on fin stabilized gun fired projectiles
US4323208A (en) * 1980-02-01 1982-04-06 British Aerospace Folding fins

Also Published As

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DE3764633D1 (en) 1990-10-04
US4852828A (en) 1989-08-01
EP0275766A1 (en) 1988-07-27
FR2608750B1 (en) 1993-02-26
FR2608750A1 (en) 1988-06-24

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