EP0251890A1 - Multiple unfolding wing, and its use in an aircraft missile - Google Patents

Multiple unfolding wing, and its use in an aircraft missile Download PDF

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Publication number
EP0251890A1
EP0251890A1 EP87401434A EP87401434A EP0251890A1 EP 0251890 A1 EP0251890 A1 EP 0251890A1 EP 87401434 A EP87401434 A EP 87401434A EP 87401434 A EP87401434 A EP 87401434A EP 0251890 A1 EP0251890 A1 EP 0251890A1
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EP
European Patent Office
Prior art keywords
wing
primary
wings
axis
deployment
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EP87401434A
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German (de)
French (fr)
Inventor
Robert Baldovi
Jean-Baptiste Koppel
Jean-Pierre Roux
Etienne Lamarque
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Thomson Brandt Armements SA
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Thomson Brandt Armements SA
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Publication of EP0251890A1 publication Critical patent/EP0251890A1/en
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42AMMUNITION; BLASTING
    • F42BEXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00Means 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
    • F42B10/02Stabilising arrangements
    • F42B10/14Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel

Definitions

  • the present invention relates to a multi-deployment wing, fitted to a projectile or a missile such as a missile. Provision is made to equip said missile with two or four wings, the latter each having a folded position in which they are not operational, and at least one deployed position in which they are operational.
  • Projectiles or missiles such as military missiles are often fitted with folding fins to allow optimized containment of several missiles inside a carrier container, before these missiles are dropped or exploded from the container. When the missile or projectile is operational, the fins are deployed to assume their stabilization function.
  • the object of the invention is to remedy this drawback by designing a deployable wing of a different design which does not give rise to the drawback mentioned in the preceding paragraph.
  • we several different shapes of the wing are required in the deployed position, according to the different navigation conditions, and in particular according to the speed of the projectile.
  • a first object of the invention is a multiple deployment wing intended to equip a flying machine with a longitudinal axis relative to the body of which it takes a folded position, and several operational positions by successive deployment, characterized in that it comprises a primary wing and at least one secondary wing which can be housed inside said primary wing, and in that said primary wing is fixed to said body by a first articulation around a first axis parallel to the body so that the wing can be folded down so that said primary wing can be applied against the body tangentially.
  • a second object of the invention is a flying machine equipped with a wing as defined in the paragraph above.
  • the cylindrical body 2 of the machine with a longitudinal axis OX is equipped with four wings according to the invention.
  • This number is not limitative.
  • Each wing consists of a primary wing 1 articulated on the body according to a rotation about an axis OY parallel to the longitudinal axis OX of the body. The rotation movement of this primary wing around its axis OY, as well as the deployment position thereof, has been shown in broken lines.
  • a secondary wing 3 is housed in a retaining chamber 4.
  • This secondary wing is articulated on the primary wing along an axis OZ perpendicular to the longitudinal axis OX of the projectile and perpendicular to the primary wing 1.
  • the wings have been folded towards each other in pairs, the joints being arranged at the periphery of the body every 90 °.
  • the wings have the same shape as those shown in Figure 1, but their position relative to the body is different.
  • one of the two pairs has been inverted in its first position, called storage, which means that, to arrive at the second position called operation or deployment, the rotation of all the wings is done in the Same direction.
  • the space occupied by this storage position does not have the same shape as the space defined by the position drawn in FIG. 1.
  • This arrangement according to FIG. 2 can be envisaged for a larger number of wings. by machine.
  • the machine is equipped with wings shown in the deployed position.
  • the primary wings 1 have made a rotation of approximately 90 ° around their axis of rotation OY.
  • the secondary wing 3 housed entirely in the primary wing.
  • These secondary wings have approached approximately the same width as the primary wings. They are mounted so as to articulate around an axis OZ perpendicular to the primary wings situated approximately in the middle of the width of the primary wings and practically at the front end 13 thereof, so that each secondary wing can pivot relative to the primary wing to deploy.
  • FIG. 4 This deployment position is described in FIG. 4, in which these secondary wings identified 3 are practically perpendicular to the longitudinal axis of the machine, thus forming a wing with maximum wingspan used for subsonic speeds.
  • This pivoting of the secondary wing relative to the primary wing is therefore made perpendicular to the first pivoting of the primary wing relative to the machine.
  • the invention provides, to improve the lift performance, of adding a tertiary wing 5 housed inside the secondary wing in a slot 6 when it is not operational.
  • This tertiary wing 5 is articulated relative to the secondary wing 3 about an axis OZ ⁇ , parallel to the axis OZ of articulation of the secondary wing on the primary wing and located practically at the rear end 7 of the secondary wing 5.
  • this tertiary wing 5 is such that, when the secondary wing 3 is deployed, this tertiary wing can pivot around the axis OZ ⁇ so as to complete the bearing surface of the wing secondary.
  • the shapes of these secondary and tertiary wings, as well as the deployment position as shown in Figure 7, are not limited to this representation.
  • the angle of deployment of the secondary wing 3 relative to the longitudinal axis OX of the machine can vary, as well as the pivoting angle of the tertiary wing 5 relative to the secondary wing.
  • the secondary wing has an approximately constant width, and the deployment angle is slightly less than 90 °.
  • the tertiary wing 5 fills the uncovered surface between the rear end 7 of the secondary wing deployed and the body of the machine.
  • a guide groove is provided for this purpose. 11, made inside the slot 4 of the primary wing 1, and in which a tenon 12 can slide, integral with the tertiary wing 5.
  • the secondary wing 3 is deployed relative to the 'primary wing 1
  • the tenon 12 is forced to follow the groove and allows the tertiary wing 5 to pivot about its axis OZ ⁇ so as to cover the surface determined between the secondary wing and the primary wing.
  • the length, shape and orientation of the groove 11 are calculated according to the deployment angles and the shapes of the secondary and tertiary wings.
  • the length of the tertiary wing 5 is also provided sufficient so that, the secondary wing 3 once deployed, the tertiary wing 5 is still in contact with the primary wing 1. This embodiment is not limiting.
  • FIG. 5B shows in section the manner in which the primary, secondary and tertiary wings are housed one inside the other. It can be noted that the secondary 3 and tertiary 5 wings do not have a constant section. These are slightly rounded because they have a large deployment angle and their profile is calculated according to the optimal air flow along these wings. The largest section of the secondary wing 3 is in the middle, the ends being of minimum thickness.
  • the articulation of the primary wing relative to the body around the longitudinal axis OY allows the wings to be folded along the body in order to obtain a minimum bulk in a container.
  • the deployment of the primary wing makes it possible to stabilize the craft at supersonic speed, with low deployment constraints.
  • the deployment of the secondary wing makes it possible to obtain a relatively high fineness ratio.
  • this tertiary wing can come to bear on the primary wing 1 by its rear end 13. This makes it possible to relieve the secondary wing in the air resistance efforts, these efforts being partially transferred via the tertiary wing 5 to the primary wing 1.

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

Abstract

The invention enables an aircraft missile to be fitted with multiple-folding wings in such a way as to reduce the bulk of the missile before use when the wings are retracted. The wing consists of a first primary wing (1) unfolding with respect to the body (2) of the missile along an axis (OY) parallel to the longitudinal axis (OX) of the body. The wing has a secondary wing (3) housed inside the primary wing and pivoting about an axis (OZ) perpendicular to the axis (OY) of the first pivoting and perpendicular to the primary wing. A tertiary wing (5) is also provided, housed inside the secondary wing and pivoted in the same way as the secondary wing at its end in such a way as to increase the lifting surface of the unfolded wing. In the retracted position, the wings are folded against the body of the aircraft missile. Application to military missiles, particularly those flying at supersonic and subsonic speeds. <IMAGE>

Description

La présente invention concerne une aile à déploiement multi­ple, équipant un projectile ou un engin tel qu'un missile. On prévoit d'équiper ledit missile de deux ou quatre ailes, ces dernières ayant chacune une position rabattue dans laquelle elles ne sont pas opérationnelles, et au moins une position déployée dans laquelle elles sont opérationnelles.The present invention relates to a multi-deployment wing, fitted to a projectile or a missile such as a missile. Provision is made to equip said missile with two or four wings, the latter each having a folded position in which they are not operational, and at least one deployed position in which they are operational.

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

Les projectiles ou engin tels que les missiles militaires sont souvent équipés d'ailettes rabattables pour permettre un confine­ment optimisé de plusieurs missiles à l'intérieur d'un conteneur porteur, avant que ces missiles soient largués ou explusés du conteneur. Lorsque le missile ou le projectile est opérationnel, les ailettes sont déployées pour assumer leur fonction de stabilisation.Projectiles or missiles such as military missiles are often fitted with folding fins to allow optimized containment of several missiles inside a carrier container, before these missiles are dropped or exploded from the container. When the missile or projectile is operational, the fins are deployed to assume their stabilization function.

On connaît des ailettes rabattables équipant un engin. Elles sont logées dans une fente à l'intérieur du fuselage, et sont articulées dans celui-ci autour d'un axe perpendiculaire à l'axe de l'engin. Après rotation autour de cet axe, chaque ailette est écartée du fuselage.We know folding fins fitted to a machine. They are housed in a slot inside the fuselage, and are articulated in it around an axis perpendicular to the axis of the craft. After rotation around this axis, each fin is moved away from the fuselage.

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

Le but de l'invention est de remédier à cet inconvénient en concevant une aile déployable d'une conception différente n'entraî­nant pas l'inconvénient cité au paragraphe précédent. De plus, on s'impose plusieurs formes différentes de l'aile en position de déploie­ment, en fonction des différentes conditions de navigation, et en particulier en fonction de la vitesse du projectile.The object of the invention is to remedy this drawback by designing a deployable wing of a different design which does not give rise to the drawback mentioned in the preceding paragraph. In addition, we several different shapes of the wing are required in the deployed position, according to the different navigation conditions, and in particular according to the speed of the projectile.

Un premier objet de l'invention est une aile à déploiement multiple destinée à équiper un engin volant d'axe longitudinal par rapport au corps duquel elle prend une position rabattue, et plusieurs positions opérationnelles par déploiement successifs, caractérisée en ce qu'elle comporte une aile primaire et au moins une aile secon­daire pouvant se loger à l'intérieur de ladite aile primaire, et en ce que ladite aile primaire est fixée audit corps par une première articulation autour d'un premier axe parallèle au corps pour que l'aile puisse être rabattue de manière à ce que ladite aile primaire puisse être appliquée contre le corps de façon tangentielle.A first object of the invention is a multiple deployment wing intended to equip a flying machine with a longitudinal axis relative to the body of which it takes a folded position, and several operational positions by successive deployment, characterized in that it comprises a primary wing and at least one secondary wing which can be housed inside said primary wing, and in that said primary wing is fixed to said body by a first articulation around a first axis parallel to the body so that the wing can be folded down so that said primary wing can be applied against the body tangentially.

Un deuxième objet d l'invention est un engin volant équipé d'une aile telle qu'elle est définie dans le paragraphe ci-dessus.A second object of the invention is a flying machine equipped with a wing as defined in the paragraph above.

L'invention et ces caractéristiques seront mieux comprises à la lecture de la description qui suit et qui illustrée des figures suivantes qui représentent :

  • - Figure 1, un engin projectile avant larguage équipé d'ailes selon l'invention;
  • - Figure 2, un deuxième engin avant larguage équipé d'ailes selon l'invention;
  • - Figure 3, un engin en position de déploiement équipé d'une aile selon une première réalisation de l'invention;
  • - Figure 4, l'engin de la figure 3 dans une deuxième position de déploiement;
  • - Figures 5A et 5B, un engin dans une première position de déploiement et équipé d'une aile selon une deuxième réalisation de l'invention;
  • - Figure 6, l'engin des figures 5 dans une deuxième position de déploiement.
The invention and these characteristics will be better understood on reading the description which follows and which illustrates the following figures which represent:
  • - Figure 1, a projectile before dropping device equipped with wings according to the invention;
  • - Figure 2, a second gear before dropping equipped with wings according to the invention;
  • - Figure 3, a machine in the deployment position equipped with a wing according to a first embodiment of the invention;
  • - Figure 4, the machine of Figure 3 in a second deployment position;
  • - Figures 5A and 5B, a machine in a first deployment position and equipped with a wing according to a second embodiment of the invention;
  • - Figure 6, the machine of Figures 5 in a second deployment position.

En référence à la figure 1, le corps 2 cylindrique de l'engin d'axe longitudinal OX, est équipé de quatre ailes selon l'invention. Ce nombre n'est pas limitatif. De manière générale, il y a un nombre quelconque de paires d'ailes, les deux ailes de chaque paire ayant une disposition et un déploiement symétriques par rapport à l'axe longitudinal OX de l'engin. Chaque aile est constituée d'une aile primaire 1 articulée sur le corps selon une rotation autour d'un axe OY parallèle à l'axe longitudinal OX du corps. On a représenté en traits interrompus le mouvement de rotation de cette aile primaire autour de son axe OY, ainsi que la position de déploiement de celle-­ci. A l'intérieur de chaque aile primaire, une aile secondaire 3 est logée dans une chambre de retenue 4. Cette aile secondaire est articulée sur l'aile primaire selon un axe OZ perpendiculaire à l'axe longitudinal OX du projectile et perpendiculaire à l'aile primaire 1. Sur cette figure 1, les ailes ont été rabattues l'une vers l'autre deux à deux, les articulations étant disposées à la périphérie du corps tous les 90°.With reference to FIG. 1, the cylindrical body 2 of the machine with a longitudinal axis OX, is equipped with four wings according to the invention. This number is not limitative. In general, there are any number of pairs of wings, the two wings of each pair having a symmetrical arrangement and deployment with respect to the longitudinal axis OX of the craft. Each wing consists of a primary wing 1 articulated on the body according to a rotation about an axis OY parallel to the longitudinal axis OX of the body. The rotation movement of this primary wing around its axis OY, as well as the deployment position thereof, has been shown in broken lines. Inside each primary wing, a secondary wing 3 is housed in a retaining chamber 4. This secondary wing is articulated on the primary wing along an axis OZ perpendicular to the longitudinal axis OX of the projectile and perpendicular to the primary wing 1. In this FIG. 1, the wings have been folded towards each other in pairs, the joints being arranged at the periphery of the body every 90 °.

En référence maintenant à la figure 2, les ailes ont la même forme que celles représentées sur la figure 1, mais leur position par rapport aux corps est différente. Dans cette disposition à quatre ailes, une des deux paires a été inversée dans sa première position, dite de stockage ce qui fait que, pour arriver à la deuxième position dite de fonctionnement ou de déploiement, la rotation de toutes les ailes se fait dans le même sens. L'encombrement qu'occupe cette position de rangement n'a pas la même forme que l'encombrement défini par la position dessinée sur la figure 1. Cette disposition selon la figure 2, peut s'envisager pour un plus grand nombre d'ailes par engin.Referring now to Figure 2, the wings have the same shape as those shown in Figure 1, but their position relative to the body is different. In this arrangement with four wings, one of the two pairs has been inverted in its first position, called storage, which means that, to arrive at the second position called operation or deployment, the rotation of all the wings is done in the Same direction. The space occupied by this storage position does not have the same shape as the space defined by the position drawn in FIG. 1. This arrangement according to FIG. 2 can be envisaged for a larger number of wings. by machine.

Sur la figure 3, l'engin est équipé d'ailes représentées en position déployée. Dans cette première réalisation d'ailes selon l'invention, les ailes primaires 1 ont effectué une rotation de 90° environ autour de leur axe de rotation OY. On aperçoit sur cette figure représentée en traits interrompus, l'aile secondaire 3 logée entièrement dans l'aile primaire. Ces ailes secondaires ont appro­ ximativement la même largeur que les ailes primaires. Elles sont montées de manière à s'articuler autour d'un axe OZ perpendiculaire aux ailes primaires situé environ au milieu de la largeur des ailes primaires et pratiquement à l'extrémité avant 13 de celles-ci, de manière à ce que chaque aile secondaire puisse pivoter par rapport à l'aile primaire pour se déployer.In Figure 3, the machine is equipped with wings shown in the deployed position. In this first embodiment of wings according to the invention, the primary wings 1 have made a rotation of approximately 90 ° around their axis of rotation OY. We see in this figure shown in broken lines, the secondary wing 3 housed entirely in the primary wing. These secondary wings have approached approximately the same width as the primary wings. They are mounted so as to articulate around an axis OZ perpendicular to the primary wings situated approximately in the middle of the width of the primary wings and practically at the front end 13 thereof, so that each secondary wing can pivot relative to the primary wing to deploy.

Cette position de déploiement est décrite sur la figure 4, sur laquelle ces ailes secondaires repérées 3 se trouvent pratiquement perpendiculaires à l'axe longitudinal de l'engin, formant ainsi une voilure à envergure maximale utilisée pour les vitesses subsonique. Ce pivotement de l'aile secondaire par rapport à l'aile primaire se fait donc de manière perpendiculaire au premier pivotement de l'aile primaire par rapport à l'engin.This deployment position is described in FIG. 4, in which these secondary wings identified 3 are practically perpendicular to the longitudinal axis of the machine, thus forming a wing with maximum wingspan used for subsonic speeds. This pivoting of the secondary wing relative to the primary wing is therefore made perpendicular to the first pivoting of the primary wing relative to the machine.

En référence à la figure 5A, l'invention prévoit, pour améliorer les performances de portance, de rajouter une aile tertiaire 5 logée à l'intérieur de l'aile secondaire dans une fente 6 lorsqu'elle n'est pas opérationnelle. Cette aile tertiaire 5 est articulée par rapport à l'aile secondaire 3 autour d'un axe OZʹ, parallèle à l'axe OZ d'articu­lation de l'aile secondaire sur l'aile primaire et situé pratiquement à l'extrémité arrière 7 de l'aile secondaire 5.With reference to FIG. 5A, the invention provides, to improve the lift performance, of adding a tertiary wing 5 housed inside the secondary wing in a slot 6 when it is not operational. This tertiary wing 5 is articulated relative to the secondary wing 3 about an axis OZʹ, parallel to the axis OZ of articulation of the secondary wing on the primary wing and located practically at the rear end 7 of the secondary wing 5.

En référence à la figure 7, la forme de cette aile tertiaire 5 est telle que, lorsque l'aile secondaire 3 est déployée, cette aile tertiaire peut pivoter autour de l'axe OZʹ de façon à compléter la surface de portance de l'aile secondaire. Les formes de ces ailes secondaires et tertiaires, ainsi que la position de déploiement telle qu'elle est représentée sur la figure 7, ne sont pas limitées à cette représentation. Par exemple l'angle de déploiement de l'aile secon­daire 3 par rapport à l'axe longitudinale OX de l'engin peut varier, ainsi que l'angle de pivotement de l'aile tertiaire 5 par rapport à l'aile secondaire.With reference to FIG. 7, the shape of this tertiary wing 5 is such that, when the secondary wing 3 is deployed, this tertiary wing can pivot around the axis OZʹ so as to complete the bearing surface of the wing secondary. The shapes of these secondary and tertiary wings, as well as the deployment position as shown in Figure 7, are not limited to this representation. For example, the angle of deployment of the secondary wing 3 relative to the longitudinal axis OX of the machine can vary, as well as the pivoting angle of the tertiary wing 5 relative to the secondary wing.

Dans la réalisation envisagée, l'aile secondaire a une largeur à peu près constante, et l'angle de déploiement est un peu inférieur à 90°. Dans ces conditions, l'aile tertiaire 5 comble la surface non couverte entre l'extrémité arrière 7 de l'aile secondaire déployée et le corps de l'engin. A cet effet, il est prévu une rainure de guidage 11, pratiquée à l'intérieur de la fente 4 de l'aile primaire 1, et dans laquelle peut coulisser un tenon 12 solidaire de l'aile tertiaire 5. De cette façon, lorsque l'aile secondaire 3 se déploie par rapport à l'aile primaire 1, le tenon 12 est obligé de suivre la rainure et permet le pivotement de l'aile tertiaire 5 autour de son axe OZʹ de manière à couvrir la surface déterminée entre l'aile secondaire et l'aile pri­maire. La longueur, la forme et l'orientation de la rainure 11 sont calculées en fonction des angles de déploiement et des formes des ailes secondaires et tertiaires. La longueur de l'aile tertiaire 5 est prévue également suffisante pour que, l'aile secondaire 3 une fois déployée, l'aile tertiaire 5 soit encore en contacte avec l'aile primaire 1. Cette réalisation n'est pas limitative.In the envisaged embodiment, the secondary wing has an approximately constant width, and the deployment angle is slightly less than 90 °. Under these conditions, the tertiary wing 5 fills the uncovered surface between the rear end 7 of the secondary wing deployed and the body of the machine. A guide groove is provided for this purpose. 11, made inside the slot 4 of the primary wing 1, and in which a tenon 12 can slide, integral with the tertiary wing 5. In this way, when the secondary wing 3 is deployed relative to the 'primary wing 1, the tenon 12 is forced to follow the groove and allows the tertiary wing 5 to pivot about its axis OZʹ so as to cover the surface determined between the secondary wing and the primary wing. The length, shape and orientation of the groove 11 are calculated according to the deployment angles and the shapes of the secondary and tertiary wings. The length of the tertiary wing 5 is also provided sufficient so that, the secondary wing 3 once deployed, the tertiary wing 5 is still in contact with the primary wing 1. This embodiment is not limiting.

La figure 5B démontre en coupe la manière dont les ailes primaires, secondaires et tertiaires sont logées les unes dans les autres. On peut remarquer que les ailes secondaires 3 et tertiaires 5 n'ont pas une section constante. Celles-ci sont légèrement bombées car elles ont un angle de déploiement important et leur profil est calculé en fonction de l'écoulement optimal de l'air le long de ces ailes. La section la plus importante de l'aile secondaire 3 se trouve en son milieu, les extrémités étant d'épaisseur minimale.FIG. 5B shows in section the manner in which the primary, secondary and tertiary wings are housed one inside the other. It can be noted that the secondary 3 and tertiary 5 wings do not have a constant section. These are slightly rounded because they have a large deployment angle and their profile is calculated according to the optimal air flow along these wings. The largest section of the secondary wing 3 is in the middle, the ends being of minimum thickness.

L'articulation de l'aile primaire par rapport au corps autour de l'axe longitudinal OY, permet de rabattre les ailes le long du corps afin d'obtenir un encombrement minimal dans un conteneur. Le déploiement de l'aile primaire permet de stabiliser en vitesse supersonique l'engin, avec des contraintes de déploiement faibles. Le déploiement de l'aile secondaire permet d'obtenir un rapport de finesse relativement élevé.The articulation of the primary wing relative to the body around the longitudinal axis OY, allows the wings to be folded along the body in order to obtain a minimum bulk in a container. The deployment of the primary wing makes it possible to stabilize the craft at supersonic speed, with low deployment constraints. The deployment of the secondary wing makes it possible to obtain a relatively high fineness ratio.

Dans le cas d'une utilisation d'une aile tertiaire, telle que représentée sur la figure 5A et la figure 6, cette aile tertiaire peut venir s'appuyer sur l'aile primaire 1 par son extrémité arrière 13. Ceci permet de soulager l'aile secondaire dans les efforts de résistance à l'air, ces efforts étant reportés partiellement par l'intermédiaire de l'aile tertiaire 5 sur l'aile primaire 1.In the case of using a tertiary wing, as shown in FIG. 5A and FIG. 6, this tertiary wing can come to bear on the primary wing 1 by its rear end 13. This makes it possible to relieve the secondary wing in the air resistance efforts, these efforts being partially transferred via the tertiary wing 5 to the primary wing 1.

Claims (8)

1. Aile à déploiement multiple destinée à équiper un engin volant d'axe longitudinal (OX) par rapport au corps (2) duquel elle prend une position repliée et plusieurs positions opérationnelles par déploiements successifs, caractérisée en ce qu'elle comporte une aile primaire (1) et au moins une aile secondaire (3) pouvant se loger à l'intérieur de ladite aile primaire, et en ce que ladite aile primaire (1) est fixée audit corps par une première articulation autour d'un axe (OY) parallèle à l'axe du corps (2) pour que l'aile puisse être rabattue de manière à ce que ladite aile primaire puisse être appliquée contre le corps de façon tangentielle.1. Wing with multiple deployment intended to equip a flying machine with longitudinal axis (OX) relative to the body (2) from which it takes a folded position and several operational positions by successive deployments, characterized in that it comprises a primary wing (1) and at least one secondary wing (3) which can be housed inside said primary wing, and in that said primary wing (1) is fixed to said body by a first articulation around an axis (OY) parallel to the axis of the body (2) so that the wing can be folded down so that said primary wing can be applied against the body tangentially. 2. Aile selon la revendication 1, caractérisée en ce que l'aile secondaire (3) est fixée à l'aile primaire (1) par une deuxième articulation autour d'un axe (OZ) perpendiculaire à l'axe (OY) d'articulation de l'aile primaire sur le corps (2) de l'engin et perpendiculaire à l'aile primaire, de façon à ce que la rotation de ladite aile secondaire par rapport à l'aile primaire permette à l'aile secondaire de s'écarter de l'ensemble formé par l'aile primaire et le corps (2) de l'engin.2. Wing according to claim 1, characterized in that the secondary wing (3) is fixed to the primary wing (1) by a second articulation around an axis (OZ) perpendicular to the axis (OY) d articulation of the primary wing on the body (2) of the machine and perpendicular to the primary wing, so that the rotation of said secondary wing relative to the primary wing allows the secondary wing to move away from the assembly formed by the primary wing and the body (2) of the machine. 3. Aile selon une quelconque des revendicatons précédentes, caractérisée en ce qu'une aile tertiaire (5) est logée à l'intérieur de l'aile secondaire (3) et articulée selon un axe (OZʹ) parallèle à l'axe (OZ) articulation de l'aile secondaire par rapport à l'aile primaire, de manière à augmenter la surface de portance de l'aile lorsque l'aile secondaire est déployée.3. Wing according to any one of the preceding claims, characterized in that a tertiary wing (5) is housed inside the secondary wing (3) and articulated along an axis (OZʹ) parallel to the axis (OZ ) articulation of the secondary wing relative to the primary wing, so as to increase the bearing surface of the wing when the secondary wing is deployed. 4. Aile selon la revendication 3, caractérisée en ce que l'aile tertiaire (5) s'appuie en position de déploiement sur l'aile primaire (1) de manière à reporter sur l'aile primaire une partie des efforts dus à la pénétration de l'aile dans l'air.4. Wing according to claim 3, characterized in that the tertiary wing (5) is supported in the deployment position on the primary wing (1) so as to transfer to the primary wing part of the forces due to the wing penetration into the air. 5. Aile selon la revendicaton 3 ou 4, caractérisée en ce qu'une rainure (11) est pratiquée sur l'aile primaire (1), et dans laquelle peut coulisser un tenon (12) solidaire de l'aile tertiaire (5), de manière à ce que, lors du déploiement de l'aile secondaire (3), l'aile tertiaire se déploie par ce guidage par rapport à l'aile primaire.5. Wing according to claim 3 or 4, characterized in that a groove (11) is formed on the primary wing (1), and in which can slide a tenon (12) integral with the tertiary wing (5), so that, during the deployment of the secondary wing (3), the tertiary wing is deployed by this guide relative to the wing primary. 6. Engin volant utilisant au moins une paire d'ailes selon l'une quelconque des revendications précédentes, les deux ailes de ladite paire étant placées de manière symétrique par rapport au corps (2) de l'engin.6. Flying vehicle using at least one pair of wings according to any one of the preceding claims, the two wings of said pair being placed symmetrically with respect to the body (2) of the vehicle. 7. Engin volant selon la revendication 6, caractérisé en ce qu'il comporte deux paires d'ailes, le sens de déploiement des ailes des deux paires étant opposé, de manière à ce que lorsque les ailes ne sont pas déployées, deux ailes de paire différente sont rabattues sur le corps (2) de l'engin l'une vers l'autre.7. Flying machine according to claim 6, characterized in that it comprises two pairs of wings, the direction of deployment of the wings of the two pairs being opposite, so that when the wings are not deployed, two wings of different pair are folded over the body (2) of the machine towards each other. 8. Engin volant selon la revendication 6, caractérisé en ce qu'il comporte deux paires d'ailes disposées symétriquement autour du corps (2) de l'engin, le sens de déploiement de chaque aile étant identique.8. Flying vehicle according to claim 6, characterized in that it comprises two pairs of wings arranged symmetrically around the body (2) of the vehicle, the direction of deployment of each wing being identical.
EP87401434A 1986-06-27 1987-06-23 Multiple unfolding wing, and its use in an aircraft missile Withdrawn EP0251890A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8609357 1986-06-27
FR8609357A FR2600618A1 (en) 1986-06-27 1986-06-27 WING WITH MULTIPLE DEPLOYMENT AND ITS APPLICATION TO A FLYING DEVICE

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EP0251890A1 true EP0251890A1 (en) 1988-01-07

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FR (1) FR2600618A1 (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4844381A (en) * 1987-09-08 1989-07-04 Diehl Gmbh & Co. Airborne submunition member
US4869442A (en) * 1988-09-02 1989-09-26 Aerojet-General Corporation Self-deploying airfoil
US5108051A (en) * 1987-11-26 1992-04-28 L'etat Francais Represente Par Le Delegue General Pour L'armement Deployment mechanism of a projectile fin
EP0811822A1 (en) * 1996-06-07 1997-12-10 Gec-Marconi Dynamics Inc. Extendable wing assembly
US6220544B1 (en) * 1998-06-19 2001-04-24 Diehl Stiftung & Co. Guided missile
GB2388094A (en) * 1986-08-12 2003-11-05 Aerospatiale Missile with variable flying surface
CN106005413A (en) * 2016-07-22 2016-10-12 珠海银通农业科技有限公司 Diverse foldable unmanned aerial vehicle
CN107161322A (en) * 2017-05-05 2017-09-15 西北工业大学 One kind becomes sweepback STOL Fixed Wing AirVehicle

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Publication number Priority date Publication date Assignee Title
CN103123292B (en) * 2013-01-07 2015-07-08 西北工业大学 Folding wings pneumatic loading unfolding experiment device
CN103879556B (en) * 2014-03-31 2016-03-02 冯加伟 Wide flight envelope morphing aircraft
CN104457443A (en) * 2014-11-24 2015-03-25 江西洪都航空工业集团有限责任公司 Up-down loading device for stacked folding wings

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DE1199664B (en) * 1962-09-11 1965-08-26 Dynamit Nobel Ag Folding tail, especially for rocket projectiles
FR1436334A (en) * 1965-05-22 1966-04-22 Contraves Ag Small rockets with four stabilizer fins
US3853288A (en) * 1967-07-17 1974-12-10 H Bode Encasement for the tail section of a rocket with a central nozzle and extendible control vanes
EP0013096A1 (en) * 1978-12-29 1980-07-09 The Commonwealth Of Australia Deployable wing mechanism
FR2564189A1 (en) * 1984-05-09 1985-11-15 Diehl Gmbh & Co FOLDING FIN, ESPECIALLY FOR PROJECTILE

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DE1199664B (en) * 1962-09-11 1965-08-26 Dynamit Nobel Ag Folding tail, especially for rocket projectiles
FR1436334A (en) * 1965-05-22 1966-04-22 Contraves Ag Small rockets with four stabilizer fins
US3853288A (en) * 1967-07-17 1974-12-10 H Bode Encasement for the tail section of a rocket with a central nozzle and extendible control vanes
EP0013096A1 (en) * 1978-12-29 1980-07-09 The Commonwealth Of Australia Deployable wing mechanism
FR2564189A1 (en) * 1984-05-09 1985-11-15 Diehl Gmbh & Co FOLDING FIN, ESPECIALLY FOR PROJECTILE

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2388094A (en) * 1986-08-12 2003-11-05 Aerospatiale Missile with variable flying surface
GB2388094B (en) * 1986-08-12 2004-04-07 Aerospatiale Missile with variable flying surface
US4844381A (en) * 1987-09-08 1989-07-04 Diehl Gmbh & Co. Airborne submunition member
US5108051A (en) * 1987-11-26 1992-04-28 L'etat Francais Represente Par Le Delegue General Pour L'armement Deployment mechanism of a projectile fin
US4869442A (en) * 1988-09-02 1989-09-26 Aerojet-General Corporation Self-deploying airfoil
EP0811822A1 (en) * 1996-06-07 1997-12-10 Gec-Marconi Dynamics Inc. Extendable wing assembly
US6220544B1 (en) * 1998-06-19 2001-04-24 Diehl Stiftung & Co. Guided missile
CN106005413A (en) * 2016-07-22 2016-10-12 珠海银通农业科技有限公司 Diverse foldable unmanned aerial vehicle
CN107161322A (en) * 2017-05-05 2017-09-15 西北工业大学 One kind becomes sweepback STOL Fixed Wing AirVehicle

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