EP2322895B1 - Projectile body equipped with deployable control surfaces - Google Patents

Projectile body equipped with deployable control surfaces Download PDF

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Publication number
EP2322895B1
EP2322895B1 EP10290609.6A EP10290609A EP2322895B1 EP 2322895 B1 EP2322895 B1 EP 2322895B1 EP 10290609 A EP10290609 A EP 10290609A EP 2322895 B1 EP2322895 B1 EP 2322895B1
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EP
European Patent Office
Prior art keywords
control surfaces
projectile
projectile body
housings
housing
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.)
Active
Application number
EP10290609.6A
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German (de)
French (fr)
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EP2322895A1 (en
Inventor
Simon Huguenin
Richard Roy
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Nexter Munitions SA
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Nexter Munitions SA
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Publication date
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Priority to PL10290609T priority Critical patent/PL2322895T3/en
Publication of EP2322895A1 publication Critical patent/EP2322895A1/en
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Publication of EP2322895B1 publication Critical patent/EP2322895B1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • 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
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
    • F42B10/50—Brake flaps, e.g. inflatable

Definitions

  • the technical field of the invention is that of projectiles with appendices deployable around their periphery.
  • the sophistication of current projectiles aims to provide them with new functions that require the deployment of sensors or actuators on the outside of the body of the projectile.
  • the projectiles are for example equipped with airbrakes or deployable control surfaces as hereinafter retained by way of example.
  • control surfaces used to orient the trajectory of a projectile are contained in the body of the projectile during its transport and / or during its first phase of flight.
  • Each rudder finds its place within the projectile thanks to a housing provided for this purpose. It is interesting to have the widest possible control surfaces in order to optimize their influence on the trajectory once their deployment has been achieved. However, the congestion of the enlarged control surfaces generates a problem due to the limited depth of housing that can accommodate the control surfaces.
  • the invention proposes to solve the problem congestion of the control surfaces by communicating the housing of control surfaces at their intersection.
  • the use of this solution however causes, when the control surfaces are deployed, problems of aerodynamic disturbances in the control surfaces due to the air flow taking place in empty control box housing.
  • W02009 / 051866 a device closing the exit of the control housing of a projectile by panels.
  • these panels are ejected before the deployment of the control surfaces. They therefore have no effectiveness during the flight of the projectile, when the problem of aerodynamic disturbances occurs.
  • the invention proposes to solve this problem by prohibiting the passage of air through the housing of control once the control surfaces out of their homes and this despite the movements of the control surfaces.
  • the invention therefore relates to a projectile body allowing the establishment of enlarged control surfaces while not disturbing the aerodynamic behavior of the projectile once the control surfaces deployed.
  • the invention therefore relates to a projectile body intended to evolve in a fluid, body provided with at least two radially deployable control surfaces, control surfaces taking place waiting to be deployed in housings in the body, characterized in that the housing communicate at their intersection, each housing being closed by a sealing means prohibiting the passage of housing by the fluid outside the projectile body when the control surfaces are deployed.
  • the sealing means comprises for each housing at least one hatch closing the housing at its end emerging from the projectile body.
  • the sealing means comprise tube sectors placed coaxially with the projectile at the intersection of the different control surface housings, sectors of tube integral with the projectile body and in contact with each other by at least two by two.
  • a generator when the rudder is deployed generating contact which is placed in the same plane as the deployable control surfaces, tube sectors in contact with the deployable control surfaces when it is in the retracted position.
  • the orientation of the sealing means will prevent the exit of the fluid through the housings.
  • a projectile 15 is composed of a body 10, stabilizing planes 11, control surfaces 3 and housing 1 for these control surfaces.
  • the control surfaces 3 are deployed such as on the figure 1 and the slots 1 are empty. The larger the control surfaces 3 are, the more effective they are, but also the more cumbersome when they are folded within the projectile body 10.
  • the housing 1 are communicating at the axis 14 of the projectile in order to it is possible to use control surfaces 3 with a width L substantially equal to the radius R of the projectile body.
  • the projectile 15 may be in incidence on trajectory.
  • the flow of the air threads 12 is not perfectly parallel to the axis 14 of progression of the projectile 15 but with an angle ⁇ .
  • the incidence shown here shows at the external surface of the body 10 a depression in the upper part of the projectile and an inlet of air threads 12 through the housing 1 of the control surfaces 3.
  • a sealing device 2 is added as shown in FIGS. figures 3 and 4 .
  • the sealing device 2 is formed of flexible tube section 2b, 2c, 2d and 2e may be polyethylene thickness of 0.5mm.
  • Each section is integral with a sector of the projectile body 10a, 10b, 10c and 10d. These sectors are secured to the projectile body 10 by a mechanical means not shown.
  • the tube sections are placed edge to edge with slight edge compression to form a lip facing the center of the projectile body. The lip thus formed must arrive in the same central plane as that of the rudder 3.
  • the lip 20 will now prevent the flow of air streams from the inside to the outside of the body.
  • the lip 20 may allow the end of the rudder to pass as illustrated by FIG. figure 3a while maintaining the sealing characteristic by contact between the tube sectors and the rudder on either side thereof.
  • FIGS. 5a to 5c show a second embodiment in which the sealing means will be formed by a sliding door 16, at each rudder 3.
  • this trapdoor will close the housing 1 in a sealed manner (using a seal for example) such as on the figure 5a .
  • the hatch 16 actuated by a motor not shown, will slide on the side as on the figure 5b to clear the housing 1.
  • the flap 16 will resume its initial position by sliding between the projectile body 10 and the rudder 3 thanks to the engine not shown.

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

Description

Le domaine technique de l'invention est celui des projectiles dotés d'appendices déployables sur leur pourtour.The technical field of the invention is that of projectiles with appendices deployable around their periphery.

La sophistication des projectiles actuels vise à les doter de nouvelles fonctions qui nécessitent le déploiement sur trajectoire de capteurs ou d'actionneurs à l'extérieur du corps du projectile. Dans un but de précision accrue, les projectiles sont par exemple dotés d'aérofreins ou de gouvernes déployables telles que retenues dans la suite du document à titre d'exemple.The sophistication of current projectiles aims to provide them with new functions that require the deployment of sensors or actuators on the outside of the body of the projectile. For the sake of increased accuracy, the projectiles are for example equipped with airbrakes or deployable control surfaces as hereinafter retained by way of example.

Les gouvernes utilisées pour orienter la trajectoire d'un projectile sont contenues dans le corps du projectile durant son transport et/ou durant sa première phase de vol. Chaque gouverne trouve sa place au sein du projectile grâce à un logement prévu à cet effet. Il est intéressant d'avoir des gouvernes les plus larges possibles afin d'optimiser leur influence sur la trajectoire une fois leur déploiement réalisé. Cependant, l'encombrement des gouvernes élargies génère un problème du fait de la profondeur limitée des logements pouvant accueillir les gouvernes.The control surfaces used to orient the trajectory of a projectile are contained in the body of the projectile during its transport and / or during its first phase of flight. Each rudder finds its place within the projectile thanks to a housing provided for this purpose. It is interesting to have the widest possible control surfaces in order to optimize their influence on the trajectory once their deployment has been achieved. However, the congestion of the enlarged control surfaces generates a problem due to the limited depth of housing that can accommodate the control surfaces.

L'invention se propose de résoudre le problème encombrement des gouvernes en faisant communiquer les logements de gouvernes au niveau de leur intersection. L'emploi de cette solution occasionne cependant, lorsque les gouvernes sont déployées, des problèmes de perturbations aérodynamiques au niveau des gouvernes du fait de la circulation d'air ayant lieu dans les logements de gouvernes vides.The invention proposes to solve the problem congestion of the control surfaces by communicating the housing of control surfaces at their intersection. The use of this solution however causes, when the control surfaces are deployed, problems of aerodynamic disturbances in the control surfaces due to the air flow taking place in empty control box housing.

Pour éviter la circulation d'air dans les logements de gouvernes, il est connu de W02009/051866 un dispositif obturant la sortie des logements de gouvernes d'un projectile par des panneaux. Cependant ces panneaux sont éjectés avant le déploiement des gouvernes. Ils n'ont donc aucune efficacité lors du vol du projectile, lorsque le problème de perturbations aérodynamiques survient.To prevent air circulation in the control units, it is known to W02009 / 051866 a device closing the exit of the control housing of a projectile by panels. However these panels are ejected before the deployment of the control surfaces. They therefore have no effectiveness during the flight of the projectile, when the problem of aerodynamic disturbances occurs.

L'invention se propose donc de résoudre ce problème en interdisant le passage de l'air au travers des logements de gouvernes une fois les gouvernes sorties de leurs logements et ceci malgré les mouvements des gouvernes.The invention proposes to solve this problem by prohibiting the passage of air through the housing of control once the control surfaces out of their homes and this despite the movements of the control surfaces.

L'invention vise donc un corps de projectile permettant la mise en place de gouvernes élargies tout en ne perturbant pas le comportement aérodynamique du projectile une fois les gouvernes déployées.The invention therefore relates to a projectile body allowing the establishment of enlarged control surfaces while not disturbing the aerodynamic behavior of the projectile once the control surfaces deployed.

L'invention a donc pour objet un corps de projectile destiné à évoluer dans un fluide, corps doté d'au moins deux gouvernes déployables radialement, gouvernes prenant place en attente de déploiement dans des logements pratiqués dans le corps, corps caractérisé en ce que les logements communiquent au niveau de leur intersection, chaque logement étant obturé par un moyen d'étanchéité interdisant la traversée des logements par le fluide extérieur au corps de projectile lorsque les gouvernes sont déployées.The invention therefore relates to a projectile body intended to evolve in a fluid, body provided with at least two radially deployable control surfaces, control surfaces taking place waiting to be deployed in housings in the body, characterized in that the housing communicate at their intersection, each housing being closed by a sealing means prohibiting the passage of housing by the fluid outside the projectile body when the control surfaces are deployed.

Suivant un mode de réalisation, le moyen d'étanchéité comporte pour chaque logement au moins une trappe obturant le logement au niveau de son extrémité débouchant du corps de projectile.According to one embodiment, the sealing means comprises for each housing at least one hatch closing the housing at its end emerging from the projectile body.

Suivant un autre mode de réalisation, le moyen d'étanchéité comporte des secteurs de tube placés coaxialement au projectile à l'intersection des différents logements de gouvernes, secteurs de tube solidaires du corps de projectile et en contact entre eux deux par deux par au moins une génératrice quand la gouverne est déployée, génératrice de contact qui est placée dans le même plan que celui des gouvernes déployables, secteurs de tubes en contact avec les gouvernes déployables quand celle ci sont en position rentrées.According to another embodiment, the sealing means comprise tube sectors placed coaxially with the projectile at the intersection of the different control surface housings, sectors of tube integral with the projectile body and in contact with each other by at least two by two. a generator when the rudder is deployed, generating contact which is placed in the same plane as the deployable control surfaces, tube sectors in contact with the deployable control surfaces when it is in the retracted position.

L'orientation du moyen d'étanchéité empêchera la sortie du fluide au travers des logements.The orientation of the sealing means will prevent the exit of the fluid through the housings.

L'invention sera mieux comprise à la lecture de la description qui va suivre de modes particuliers de réalisation, description faite en référence aux dessins annexés et dans lesquels:

  • La figure 1 représente schématiquement le projectile en vue de trois quarts arrière avec les gouvernes et le jeu d'ailerons stabilisateurs arrière déployés. Elle localise les plans de coupe longitudinale A et transversale B.
  • La figure 2 représente schématiquement suivant la coupe longitudinale A, le projectile en incidence.
  • La figure 3 représente suivant la coupe transversale B le projectile, gouvernes dans leurs logements.
  • La figure 3a représente une vue de détail agrandie du repère F de la figure 3.
  • La figure 4 représente suivant la coupe transversale B le projectile gouvernes déployées.
  • La figure 4a représente une vue de détail agrandie du repère G de la figure 4.
  • La figure 5a représente, suivant un autre mode de réalisation, une vue de détail du corps de projectile au niveau d'une gouverne repliée dans son logement obturé par un dispositif d'étanchéité externe.
  • La figure 5b représente une vue de détail du corps de projectile au niveau d'une gouverne dans son logement où le dispositif d'étanchéité externe s'est effacé sur un coté.
  • La figure 5c représente une vue de détail du corps de projectile au niveau d'une gouverne sortie de son logement où le dispositif d'étanchéité externe est revenu obturer le logement.
The invention will be better understood on reading the following description of particular embodiments, a description given with reference to the accompanying drawings and in which:
  • The figure 1 schematically represents the projectile in view of three quarters rear with the control surfaces and the set of rear stabilizer fins deployed. It locates the longitudinal sectional planes A and transverse B.
  • The figure 2 represents schematically according to the longitudinal section A, the projectile in incidence.
  • The figure 3 represents the cross section B the projectile, control surfaces in their homes.
  • The figure 3a represents an enlarged detail view of the F mark of the figure 3 .
  • The figure 4 represents in the cross section B the projectile rudder deployed.
  • The figure 4a represents an enlarged detail view of the G mark of the figure 4 .
  • The figure 5a represents, in another embodiment, a detail view of the projectile body at a folded rim in its housing closed by an external sealing device.
  • The figure 5b is a detail view of the projectile body at a rudder in its housing where the external sealing device has cleared on one side.
  • The figure 5c is a detail view of the projectile body at a rudder output of its housing where the external sealing device has returned to close the housing.

En se reportant aux figures 1 et 2, un projectile 15 est composé d'un corps 10, de plans stabilisateurs 11, de gouvernes 3 et de logements 1 pour ces gouvernes. En vol les gouvernes 3 sont déployées telles que sur la figure 1 et les logements 1 sont donc vides. Plus les gouvernes 3 sont larges plus elles sont efficaces mais aussi plus elles sont encombrantes lorsqu'elles sont repliées au sein du corps de projectile 10.Referring to figures 1 and 2 , a projectile 15 is composed of a body 10, stabilizing planes 11, control surfaces 3 and housing 1 for these control surfaces. In flight the control surfaces 3 are deployed such as on the figure 1 and the slots 1 are empty. The larger the control surfaces 3 are, the more effective they are, but also the more cumbersome when they are folded within the projectile body 10.

Selon une première caractéristique de l'invention plus particulièrement visible à la figure 3, les logements 1 sont communicants au niveau de l'axe 14 du projectile afin de pouvoir employer des gouvernes 3 d'une largeur L sensiblement égale au rayon R du corps de projectile.According to a first feature of the invention more particularly visible in the figure 3 , the housing 1 are communicating at the axis 14 of the projectile in order to it is possible to use control surfaces 3 with a width L substantially equal to the radius R of the projectile body.

Tel qu'illustré par la figure 2 le projectile 15 peut se trouver en incidence sur trajectoire. De ce fait l'écoulement des filets d'air 12 ne se fait pas parfaitement parallèlement à l'axe 14 de progression du projectile 15 mais avec un angle α.As illustrated by figure 2 the projectile 15 may be in incidence on trajectory. As a result, the flow of the air threads 12 is not perfectly parallel to the axis 14 of progression of the projectile 15 but with an angle α.

L'incidence ici représentée fait apparaître au niveau de la surface externe du corps 10 une dépression en partie supérieure du projectile et une entrée de filets d'air 12 au travers des logements 1 des gouvernes 3.The incidence shown here shows at the external surface of the body 10 a depression in the upper part of the projectile and an inlet of air threads 12 through the housing 1 of the control surfaces 3.

La sortie de ces filets d'air au niveau du logement de gouverne opposé risque de créer des turbulences 13 perturbant l'efficacité des gouvernes. Il est nécessaire de supprimer un tel écoulement.The exit of these air streams at the opposite rudder housing may create turbulence 13 disrupting the effectiveness of the control surfaces. It is necessary to suppress such a flow.

Afin de supprimer ces écoulements parasites, selon une seconde caractéristique de l'invention, on ajoute un dispositif d'étanchéité 2 tel que montré sur les figures 3 et 4.In order to eliminate these parasitic flows, according to a second characteristic of the invention, a sealing device 2 is added as shown in FIGS. figures 3 and 4 .

Selon un premier mode de réalisation apparaissant aux figures 3 et 4 dans les cercles pointillés F et G qui sont détaillés aux figures 3a et 4a, le dispositif d'étanchéité 2 est formé de section de tube souple 2b, 2c, 2d et 2e pouvant être du polyéthylène d'épaisseur 0,5mm. Chaque section est solidaire d'un secteur du corps de projectile 10a, 10b, 10c et 10d. Ces secteurs sont solidaires du corps de projectile 10 par un moyen mécanique non représenté. Les sections de tube sont placées bord à bord avec une légère compression des bords afin de former une lèvre 20 tournée vers le centre du corps de projectile. La lèvre ainsi formée doit arriver dans le même plan central que celui de la gouverne 3. La lèvre 20 va désormais empêcher l'écoulement des filets d'air de l'intérieur vers l'extérieur du corps.According to a first embodiment appearing in figures 3 and 4 in the dotted circles F and G which are detailed at figures 3a and 4a , the sealing device 2 is formed of flexible tube section 2b, 2c, 2d and 2e may be polyethylene thickness of 0.5mm. Each section is integral with a sector of the projectile body 10a, 10b, 10c and 10d. These sectors are secured to the projectile body 10 by a mechanical means not shown. The tube sections are placed edge to edge with slight edge compression to form a lip facing the center of the projectile body. The lip thus formed must arrive in the same central plane as that of the rudder 3. The lip 20 will now prevent the flow of air streams from the inside to the outside of the body.

Gouvernes 3 en positions rentrées, la lèvre 20 pourra laisser passer l'extrémité de la gouverne comme l'illustre la figure 3a tout en conservant la caractéristique d'étanchéité par contact entre les secteurs de tube et la gouverne de part et d'autre de celle ci.Governes 3 in retracted positions, the lip 20 may allow the end of the rudder to pass as illustrated by FIG. figure 3a while maintaining the sealing characteristic by contact between the tube sectors and the rudder on either side thereof.

Les figures 5a à 5c montrent un second mode de réalisation dans lequel le moyen d'étanchéité sera formé par une trappe 16 coulissante, au niveau de chaque gouverne 3.The Figures 5a to 5c show a second embodiment in which the sealing means will be formed by a sliding door 16, at each rudder 3.

En position gouverne 3 rentrée, cette trappe va obturer le logement 1 de façon étanche (à l'aide d'un joint par exemple) tel que sur la figure 5a.In the steering position 3 retracted, this trapdoor will close the housing 1 in a sealed manner (using a seal for example) such as on the figure 5a .

Avant le déploiement de la gouverne 3, la trappe 16, actionnée par un moteur non représenté, va coulisser sur le coté tel que sur la figure 5b pour dégager le logement 1.Before the deployment of the rudder 3, the hatch 16, actuated by a motor not shown, will slide on the side as on the figure 5b to clear the housing 1.

Comme illustré sur la figure 5c, une fois la gouverne 3 déployée, la trappe 16 va reprendre sa position initiale en coulissant entre le corps de projectile 10 et la gouverne 3 grâce au moteur non représenté.As illustrated on the figure 5c once the rudder 3 has been deployed, the flap 16 will resume its initial position by sliding between the projectile body 10 and the rudder 3 thanks to the engine not shown.

De cette manière aucun filet d'air ne viendra perturber le fonctionnement des gouvernes.In this way no air flow will disturb the operation of the control surfaces.

Claims (4)

  1. A projectile body (10) intended to evolve in a fluid, such body equipped with at least two radially deployable control surfaces (3), said control surfaces (3) being accommodated prior to their deployment in housings (1) made in said body (10), said body (10) wherein said housings (1) communicate at their intersection point, each of said housings (1) being blocked by sealing means ((2, 15) preventing any fluid from the exterior of said projectile body (10) from passing through said housings (1) when said control surfaces are deployed.
  2. A projectile body (10) according to Claim 1, wherein said sealing means incorporate for each housing at least one hatch (15) blocking off said housing (1) at its outer end from said projectile body (10).
  3. A projectile body (10) according to Claim 1, wherein said sealing means (2) incorporate tubular sectors (2b,c,d,e) positioned coaxially to said projectile at the intersection of the different control surface (1) of said housings (3), said tubular sectors (2) being integral with said projectile body and in contact with each other two by two by at least one generating line when said control surface (3) is deployed, contact generating line that is in the same plane as that of said deployable control surfaces (3), said tubular sectors being in contact with said deployable control surfaces when said control surfaces (3) are in their retracted position.
  4. A projectile body (10) according to Claim 3, wherein the orientation of said sealing means (2) prevents fluid exiting through said housings (1).
EP10290609.6A 2009-11-16 2010-11-15 Projectile body equipped with deployable control surfaces Active EP2322895B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL10290609T PL2322895T3 (en) 2009-11-16 2010-11-15 Projectile body equipped with deployable control surfaces

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0905494A FR2952712A1 (en) 2009-11-16 2009-11-16 PROJECTILE BODY EQUIPPED WITH DEPLOYABLE APPENDICES

Publications (2)

Publication Number Publication Date
EP2322895A1 EP2322895A1 (en) 2011-05-18
EP2322895B1 true EP2322895B1 (en) 2014-01-08

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US (1) US8450669B2 (en)
EP (1) EP2322895B1 (en)
ES (1) ES2448390T3 (en)
FR (1) FR2952712A1 (en)
PL (1) PL2322895T3 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3089620B1 (en) 2018-12-11 2022-04-01 Nexter Munitions PROJECTILE WITH DEPLOYABLE SAIL PLANS

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
DE3432614A1 (en) * 1984-09-05 1986-03-13 Rheinmetall GmbH, 4000 Düsseldorf MISSILE
US4869442A (en) * 1988-09-02 1989-09-26 Aerojet-General Corporation Self-deploying airfoil
US6260797B1 (en) * 1998-01-13 2001-07-17 Science Applications International Corporation Transformable gun launched aero vehicle
SE518665C2 (en) * 2000-03-21 2002-11-05 Bofors Weapon Sys Ab Fine stabilized artillery grenade
US7829830B1 (en) * 2007-10-19 2010-11-09 Woodward Hrt, Inc. Techniques for controlling access through a slot on a projectile

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EP2322895A1 (en) 2011-05-18
US8450669B2 (en) 2013-05-28
US20110114783A1 (en) 2011-05-19
ES2448390T3 (en) 2014-03-13
FR2952712A1 (en) 2011-05-20
PL2322895T3 (en) 2014-06-30

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