EP3428570B1 - Particle flow deflector device for projectile guided by a linking wire - Google Patents

Particle flow deflector device for projectile guided by a linking wire Download PDF

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Publication number
EP3428570B1
EP3428570B1 EP18290074.6A EP18290074A EP3428570B1 EP 3428570 B1 EP3428570 B1 EP 3428570B1 EP 18290074 A EP18290074 A EP 18290074A EP 3428570 B1 EP3428570 B1 EP 3428570B1
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EP
European Patent Office
Prior art keywords
support
device support
projectile
deflecting blade
loop
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EP18290074.6A
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German (de)
French (fr)
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EP3428570A1 (en
Inventor
François Durand
Vincent Cheret
Simon Tusseau
Vincent Guibout
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MBDA France SAS
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MBDA France SAS
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Publication of EP3428570A1 publication Critical patent/EP3428570A1/en
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Publication of EP3428570B1 publication Critical patent/EP3428570B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/01—Arrangements thereon for guidance or control
    • F42B15/04—Arrangements thereon for guidance or control using wire, e.g. for guiding ground-to-ground rockets
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F42B10/20—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel deployed by combustion gas pressure, or by pneumatic or hydraulic forces
    • 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
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/665—Steering by varying intensity or direction of thrust characterised by using a nozzle provided with at least a deflector mounted within the nozzle

Definitions

  • the present invention relates to a projectile particle flow deflector device guided by a connecting wire, as described in the document US5678785 A .
  • the short-range projectiles can be guided by means of a connecting wire which connects the projectile to a firing point.
  • the control commands for projectile guidance are transmitted from the firing station to the projectile via the connecting wire which may be an optical fiber or an electrical cable.
  • the connection wire also makes it possible to transmit images to the shooting station that make it possible to visualize a target to be reached.
  • the connecting wire is unwound behind the projectile in a circular scan of the connecting wire.
  • this type of projectile is provided with a main thruster whose ejection outlet is located laterally to the projectile, so that the propellant jet from the main thruster does not damage the wire.
  • the present invention aims to overcome these disadvantages by providing a particle flow deflector device for a projectile, including a missile.
  • the invention relates to a projectile particle flow deflector device guided by a connecting wire in a direction of movement of the projectile, the projectile being provided with a fuselage and a propellant capable of producing a propellant jet. ejected by an ejection outlet of the thruster from upstream to downstream in the direction of movement of the projectile, the propellant jet containing the flow of particles.
  • the flow of particles is deflected by the deflector blade (when brought into the unfolded position) which prevents the particles from remaining trapped in the boundary layer which envelops the body of the projectile during the flight.
  • the deflector blade in the unfolded position thus eliminates any risk of interactions between the particle flow and the connecting wire, thus avoiding breakage of the connecting wire.
  • the deflector blade can be retracted when the projectile is launched.
  • the deflector blade does not disrupt the launch by friction with the launch tube.
  • the retaining member maintains the deflector blade in the extension of the device support at launch. Then, the propellant jet destroys at least a portion of the retainer so that the deflector can move the deflector blade to a position where it can deflect the particle jet.
  • the deflector blade comprises a front surface and a rear surface, the rear surface facing the fuselage, the device support being provided with at least one stop against which the rear surface of the deflector plate rests when the deflector blade is in the folded position.
  • the device holder includes a passage opening configured to surround the thruster ejection outlet, the deflector blade being located downstream of the passage opening.
  • the retaining member includes a retaining wire extended through the passage opening.
  • the lower surface of the device support comprises at least one stud disposed upstream of the passage opening, the deflector blade including a first longitudinal end in pivotal connection with the device holder and a second longitudinal end opposite to the first longitudinal end, the second longitudinal end being provided with at least one tab extending opposite the first longitudinal end, the retaining wire forming a loop arranged to pass around the tab or tabs on one side of the loop and around the stud or studs on the other side of the loop, the loop being able to press the tab or tabs of the deflector blade for holding said deflector blade in the folded position.
  • the loop is closed by a set of nodes made at the ends of the retaining wire, the set of nodes depending on the type of the retaining wire.
  • the return element comprises a leaf spring, the leaf spring comprising a spring support arranged in at least one groove of the device support, the spring support being provided with legs configured to be supported under the fuselage of the projectile when the device is fixed on the fuselage of the projectile.
  • the device support has a thickness increasing continuously from upstream to downstream.
  • the invention also relates to a missile comprising at least one particle flow deflector device as described above.
  • the invention relates to a deflector device 1 for the flow of particles 29 for a projectile 30 guided by a connecting wire 28 in a direction of movement represented by the arrow referenced F on the Figures 2 and 3 .
  • the projectile 30 is provided with a fuselage 2 and a thruster capable of producing a propulsive jet ejected by an ejection outlet 3 of the upstream propulsion unit downstream in the direction of displacement F of the projectile 30.
  • propellant comprises the stream of particles 29.
  • the fuselage 2 may comprise several parts.
  • the fuselage 2 may comprise a front part forming the front of the projectile 30 and a rear part forming the rear of the projectile 30.
  • the deflector device 1 comprises a device support 4 comprising an upper surface and a lower surface.
  • the lower surface corresponds to a surface configured to attach the device support 4 to the fuselage 2 of the projectile 30.
  • the device support 4 comprises at least one attachment element 24 disposed on the lower surface of the device support 4 (FIG. figure 17 ).
  • the fixing element 24 is arranged in the form of a hook in order to be able to engage with a projectile fuselage attachment element 30.
  • the fastening element 24 may comprise a lateral guide 27 configured to guide the support of device 4 relative to the fuselage fastening element 2.
  • the fastening element 24 also comprises a surface 25 and a longitudinal stop 26 for wedging the device support 4 with the fuselage 2 of the projectile 30.
  • device 4 by at least one fastening element 24 on the fuselage 2 may be completed by the addition of an adhesive tape.
  • the fastening element of the fuselage 2 corresponds to an L-shaped slot made through the fuselage 2 in which the fastening element 24 is engaged.
  • two fastening elements 24 are located downstream of the device support 4.
  • An adhesive tape disposed upstream of the device carrier 4 can complete the attachment of the device carrier 4 to the fuselage 2.
  • Support pads 33 may be arranged on the lower surface of the device support 4. These support pads 33 with the fastening element or elements 24 allow the device support 4 to be oriented angularly with respect to the longitudinal axis of the projectile. 30.
  • the deflector device 1 further comprises a deflector blade 5 ( figure 8 ) downstream of the ejection outlet 3 and an actuating module of the deflector blade 5.
  • the actuating module is used to bring the deflector blade 5 of a folded position in which the deflector blade 5 is substantially in extending the device carrier 4 to an unfolded position in which the deflector blade 5 is at an angle with the device carrier 4 to deflect the particle stream 29.
  • the deflector blade 5 comprises a front surface 55 and a rear surface 56.
  • the rear surface 56 of the deflector plate 5 faces the fuselage 2.
  • the deflector blade 5 can prevent a correct launch of the projectile 30 by friction between said deflector blade 5 and the launch tube. To prevent friction from occurring, the deflector blade 5 is in the folded position being retracted at the launching of the projectile 30 through the actuating module.
  • the device support 4 is provided with at least one stop 9 against which at least the rear surface 56 of the deflector blade 5 is supported when the deflector blade 5 is in the folded position.
  • the actuation module comprises a. return element 6 and a retaining element 70.
  • the deflection element 6 is configured to exert a first force capable of bringing the deflector blade 5 from the folded position to the unfolded position ( figures 5 and 11 ).
  • the return element 6 comprises a leaf spring 31 ( figure 9 ).
  • the leaf spring 31 is provided with a spring support 21 arranged in at least one groove 10 of the device support 4.
  • a fixing tongue 35 comprises a boss 34 (FIG. figure 18 ) configured to penetrate into a fixing hole 36 arranged in the spring support 21 ( figure 9 ) in order to lock the deflection element in the groove 10.
  • the fixing tongue 35 presses on the spring support 21 until the boss 34 enters in the fixing hole 36 of the spring support 21.
  • the spring support 21 is provided with tabs 20. These tabs 20 are configured to be under the fuselage 2 when the device 1 is fixed on the fuselage 2 of the projectile 30. These tabs 20 are arranged under the fuselage 2 by their insertion through L-shaped slots made on the fuselage 2.
  • the leaf spring 31 may be provided with a tongue 32 ( figure 9 ) which passes through the deflector blade 5 through an orifice 19 ( figure 8 arranged in the deflector blade 5 ( figure 11 ).
  • the retainer 70 is configured to exert a second force capable of countering the first force to maintain the deflector blade 5 in the folded position. In the folded position, the deflector blade 5 is retracted.
  • the deflection member 6 is then configured to move the deflector blade 5 from the folded position to the unfolded position, when the propellant jet destroys at least a portion of the retainer 70.
  • the destruction of a Part of the holding member 70 may be caused by the heat generated by the propellant jet.
  • the retaining element 70 comprises a retaining wire 7 stretched through the passage opening 8.
  • the device support 4 and the deflector blade 5 can be configured as follows.
  • the lower surface of the device support 4 comprises at least one pad 16 disposed upstream of the passage opening 8 ( Figures 15 and 16 ).
  • the deflector blade 5 comprises a first longitudinal end 53 which is in pivot connection with the device support 4 and a second longitudinal end 54 opposite to the first longitudinal end 53.
  • the second longitudinal end 54 is provided with at least one tab 17 extending opposite longitudinal first end 53 ( Figures 8 and 12 ).
  • the retaining wire 7 forms a loop.
  • This loop is arranged to pass around the tab or tabs 17 on one side of the loop ( Figures 12 and 13 ) and around the stud (s) 16 on the other side of the loop ( Figures 14 and 15 ).
  • the loop is able to press the tab or tabs 17 of the deflector blade 5 to maintain said deflector blade 5 in the folded position.
  • the loop comprises two strands 7 each respectively forming a part of the loop.
  • the loop is closed by a set of nodes 23 made at the ends of the retaining wire 7.
  • the set of nodes 23 is made according to the type of retaining wire 7 (material of the wire, thickness, etc.).
  • the set of nodes 23 comprises two simple nodes doubled by a third simple node ( figure 19 ).
  • the retaining wire 7 is fixed on the device support 4 by at least one point of glue.
  • a dot of glue can be applied to cover the set of nodes 23 to ensure the holding. This prevents any movement of the ends of the retaining wire 7 tending to loosen the loop, reduce or even eliminate the voltage applied to the retaining wire 7 during the implementation of the set of nodes 23.
  • Another point of glue can be applied at only one of the lower grooves 11 in the downstream part of the device support 4 to hold the retaining wire 7 which may remain after the destruction of at least a portion of the retaining wire 7. This allows to avoid any risk of encounter between the retaining wire 7 which remains and the connecting wire 28.
  • a knot may also be formed in front of a lower groove 11 for mechanically retaining the retaining wire 7.
  • several tows of retaining wire 7 may be formed around a support pad 33 to also mechanically retain the retaining wire 7.
  • the deflector blade 5 is in the extension of the device support 4 when it is in its folded position to avoid any friction with the launch tube and any risk of attachment with the connecting wire 29.
  • the retaining wire 7 may not be so tight that the deflector blade 5 is in the extension of the device support 4.
  • the fretting point or points are located in the upstream half of the device support 4.
  • one of the strands of the retaining wire 7 comprises a tensioning element 71 configured to maintain a tension of the retaining wire 7.
  • the figure 4 shows an example of a retaining wire 7 comprising a tensioning element 71 corresponding to a spring.
  • the deflector blade 5 is pivotally attached to the device holder 4 so that said deflector blade 5 can move from a folded position to the unfolded position.
  • the deflector blade 5 comprises a first lateral end 51 and a second lateral end 52. Each of the ends 51 and 52 of the deflector blade 5 are folded towards the fuselage 2.
  • the deflector blade 5 comprises two hinge orifices 18 and the device support 4 comprises two hinge hooks 22. These two hinge hooks 22 are configured to pass respectively into the two hinge orifices 18 in order to fix the deflector blade 5 in pivot connection with the device support 4.
  • the device holder 4 comprises a passage opening 8 configured to surround the thruster ejection outlet 3.
  • the deflector blade 5 is located downstream of the passage opening 8.
  • the deflector device 1 can operate in the following manner. Before launch, the projectile 30 is disposed in a launch tube. The retaining member 70 exerts the second force that overcomes the first force exerted by the deflection member 6. The retaining member 70 then holds the deflector blade 5 in its folded position. After launch, the projectile 30 flies in glider for a moment. At a given moment, the thruster produces the propellant jet which then destroys at least a portion of the retaining element 70, in particular a portion of the retaining wire 7. The retaining element 70 no longer exerts a second force or causes a second insufficient to overcome the first force exerted by the deflection element 6. The deflector blade 5 is then brought from the folded position to the unfolded position by the deflection element 6. The deflector blade 5, in its unfolded position , allows to deflect the flow of particles 29 contained in the propellant jet.
  • the device support 4 has an aerodynamic shape.
  • the device support 4 has a thickness increasing continuously from upstream to downstream.
  • the upstream portion of the device support 4 has a thickness of about 1 mm. This thickness increases continuously towards the downstream part to reach a value of about 3.5 mm.
  • the deflector device can be mounted by a method of assembling the particle flow deflector device 1 (FIG. figure 20 ).
  • the method comprises at least one step E2 of placing the deflector blade 5 on the device support 4.
  • the method further comprises a step E3 of placing the retaining element 70.
  • the step E2 of setting up the deflector blade 5 is preceded by a step E1 of setting up of the deflection element 6 on the device support 4.
  • the step E2 of setting up the deflector blade 5 consists in linking in rotation around a pivot the deflector blade 5 to the device support 4.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
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Description

DOMAINE TECHNIQUETECHNICAL AREA

La présente invention concerne un dispositif déflecteur de flux de particules pour projectile guidé par un fil de liaison, comme décrit dans le document US5678785 A .The present invention relates to a projectile particle flow deflector device guided by a connecting wire, as described in the document US5678785 A .

ÉTAT DE LA TECHNIQUESTATE OF THE ART

Il existe plusieurs techniques de guidage de projectiles autopropulsés, notamment les missiles. En particulier, les projectiles à courte portée peuvent être guidés à l'aide d'un fil de liaison qui relie le projectile à un poste de tir. Les ordres de commande pour le guidage du projectile sont transmis du poste de tir au projectile par l'intermédiaire du fil de liaison qui peut être une fibre optique ou un câble électrique. Le fil de liaison permet également de transmettre au poste de tir des images permettant une visualisation d'une cible à atteindre. Lors du vol du projectile, le fil de liaison se dévide derrière le projectile en un balayage circulaire du fil de liaison. Généralement, ce type de projectile est pourvu d'un propulseur principal dont la sortie d'éjection se situe latéralement au projectile, afin que le jet propulsif provenant du propulseur principal n'endommage pas le fil de liaison. Or, malgré cette précaution, il arrive que le fil de liaison soit endommagé. En effet, la combustion du propulseur principal n'est pas effective tout le long du vol du projectile. Cela a pour inconvénient que toutes les particules comprises dans le jet propulsif ne sont pas éjectées hors de la couche limite qui enveloppe le corps du projectile. Les particules, prisonnières de la couche limite suivent le corps du projectile et se retrouvent dans la zone de balayage circulaire du fil de liaison, ce qui peut avoir pour conséquence de rompre ledit fil de liaison.There are several self-propelled projectile guidance techniques, including missiles. In particular, the short-range projectiles can be guided by means of a connecting wire which connects the projectile to a firing point. The control commands for projectile guidance are transmitted from the firing station to the projectile via the connecting wire which may be an optical fiber or an electrical cable. The connection wire also makes it possible to transmit images to the shooting station that make it possible to visualize a target to be reached. During the flight of the projectile, the connecting wire is unwound behind the projectile in a circular scan of the connecting wire. Generally, this type of projectile is provided with a main thruster whose ejection outlet is located laterally to the projectile, so that the propellant jet from the main thruster does not damage the wire. However, despite this precaution, it happens that the connecting wire is damaged. Indeed, the combustion of the main thruster is not effective throughout the flight of the projectile. This has the disadvantage that all particles included in the propellant jet are not ejected out of the boundary layer that envelops the body of the projectile. The particles, trapped in the boundary layer, follow the body of the projectile and are found in the circular scanning zone of the connecting wire, which may have the consequence of breaking said connecting wire.

EXPOSÉ DE L'INVENTIONSTATEMENT OF THE INVENTION

La présente invention a pour objet de pallier ces inconvénients en proposant un dispositif déflecteur de flux de particules pour un projectile, notamment un missile.The present invention aims to overcome these disadvantages by providing a particle flow deflector device for a projectile, including a missile.

À cet effet, l'invention concerne un dispositif déflecteur de flux de particules pour projectile guidé par un fil de liaison selon un sens de déplacement du projectile, le projectile étant pourvu d'un fuselage et d'un propulseur apte à produire un jet propulsif éjecté par une sortie d'éjection du propulseur d'amont vers l'aval dans le sens de déplacement du projectile, le jet propulsif contenant le flux de particules.To this end, the invention relates to a projectile particle flow deflector device guided by a connecting wire in a direction of movement of the projectile, the projectile being provided with a fuselage and a propellant capable of producing a propellant jet. ejected by an ejection outlet of the thruster from upstream to downstream in the direction of movement of the projectile, the propellant jet containing the flow of particles.

Selon l'invention, le dispositif comprend :

  • un support de dispositif comprenant une surface supérieure et une surface inférieure, la surface inférieure correspondant à une surface configurée pour fixer le support de dispositif sur le fuselage du projectile,
  • une lame déflectrice en aval de la sortie d'éjection,
  • un module d'actionnement de la lame déflectrice permettant d'amener la lame déflectrice d'une position pliée dans laquelle la lame déflectrice se situe sensiblement dans le prolongement du support de dispositif à une position dépliée dans laquelle la lame déflectrice fait un angle (non nul) avec le support de dispositif pour dévier le flux de particules.
According to the invention, the device comprises:
  • a device holder comprising an upper surface and a lower surface, the lower surface corresponding to a surface configured to attach the device holder to the fuselage of the projectile,
  • a deflector blade downstream of the ejection outlet,
  • an actuator module of the deflector blade for moving the deflector blade from a folded position in which the deflector blade is substantially in the extension of the device carrier to an unfolded position in which the deflector blade is at an angle (no null) with the device holder to deflect the particle flow.

Ainsi, grâce à l'invention, le flux de particules est dévié par la lame déflectrice (lorsqu'elle est amenée dans la position dépliée) qui empêche les particules de rester prisonnières de la couche limite qui enveloppe le corps du projectile pendant le vol. La lame déflectrice dans la position dépliée supprime ainsi tout risque d'interactions entre le flux de particules et le fil de liaison, évitant ainsi la rupture du fil de liaison.Thus, thanks to the invention, the flow of particles is deflected by the deflector blade (when brought into the unfolded position) which prevents the particles from remaining trapped in the boundary layer which envelops the body of the projectile during the flight. The deflector blade in the unfolded position thus eliminates any risk of interactions between the particle flow and the connecting wire, thus avoiding breakage of the connecting wire.

En outre, le module d'actionnement comprend :

  • un élément de renvoi configuré pour exercer une première force apte à amener la lame déflectrice de la position pliée à la position dépliée,
  • un élément de retenue configuré pour exercer une deuxième force apte à contrer la première force pour maintenir la lame déflectrice dans la position pliée ;
l'élément de renvoi étant configuré pour amener la lame déflectrice de la position pliée à la position dépliée, lorsque le jet propulsif détruit au moins une partie de l'élément de retenue, la lame déflectrice étant en liaison pivot avec le support de dispositif.In addition, the actuation module comprises:
  • a return element configured to exert a first force capable of bringing the deflector blade from the folded position to the unfolded position,
  • a retaining member configured to exert a second force adapted to counter the first force to maintain the deflector blade in the folded position;
the deflection member being configured to move the deflector blade from the folded position to the unfolded position, when the propellant jet destroys at least a portion of the retainer member, the deflector blade being pivotally connected to the device carrier.

Grâce à l'action combinée de l'élément de renvoi et l'élément de retenue, la lame déflectrice peut être escamotée au moment du lancement du projectile. Ainsi, la lame déflectrice ne perturbe pas le lancement par des frottements avec le tube de lancement. L'élément de retenue permet de maintenir la lame déflectrice dans le prolongement du support de dispositif lors du lancement. Puis, le jet propulsif détruit au moins une partie de l'élément de retenue pour que l'élément de renvoi puisse amener la lame déflectrice dans une position dans laquelle elle peut dévier le jet de particules.By virtue of the combined action of the deflection element and the retaining element, the deflector blade can be retracted when the projectile is launched. Thus, the deflector blade does not disrupt the launch by friction with the launch tube. The retaining member maintains the deflector blade in the extension of the device support at launch. Then, the propellant jet destroys at least a portion of the retainer so that the deflector can move the deflector blade to a position where it can deflect the particle jet.

Selon une particularité, la lame déflectrice comprend une surface avant et une surface arrière, la surface arrière faisant face au fuselage, le support de dispositif étant pourvu d'au moins une butée contre laquelle la surface arrière de la lame déflectrice s'appuie lorsque la lame déflectrice est en position pliée.According to a particularity, the deflector blade comprises a front surface and a rear surface, the rear surface facing the fuselage, the device support being provided with at least one stop against which the rear surface of the deflector plate rests when the deflector blade is in the folded position.

Selon une autre particularité, le support de dispositif comprend une ouverture de passage configurée pour entourer la sortie d'éjection du propulseur, la lame déflectrice étant située en aval de l'ouverture de passage.In another feature, the device holder includes a passage opening configured to surround the thruster ejection outlet, the deflector blade being located downstream of the passage opening.

En outre, l'élément de retenue comprend un fil de retenue tendu à travers l'ouverture de passage.In addition, the retaining member includes a retaining wire extended through the passage opening.

De plus, la surface inférieure du support de dispositif comprend au moins un plot disposé en amont de l'ouverture de passage,
la lame déflectrice comprenant une première extrémité longitudinale en liaison pivot avec le support de dispositif et une deuxième extrémité longitudinale opposée à la première extrémité longitudinale, la deuxième extrémité longitudinale étant pourvue d'au moins une languette s'étendant à l'opposé de la première extrémité longitudinale,
le fil de retenue formant une boucle agencée pour passer autour de la ou des languettes d'un côté de la boucle et autour du ou des plots de l'autre côté de la boucle, la boucle étant apte à appuyer sur la ou les languettes de la lame déflectrice pour maintenir ladite lame déflectrice dans la position pliée.In addition, the lower surface of the device support comprises at least one stud disposed upstream of the passage opening,
the deflector blade including a first longitudinal end in pivotal connection with the device holder and a second longitudinal end opposite to the first longitudinal end, the second longitudinal end being provided with at least one tab extending opposite the first longitudinal end,
the retaining wire forming a loop arranged to pass around the tab or tabs on one side of the loop and around the stud or studs on the other side of the loop, the loop being able to press the tab or tabs of the deflector blade for holding said deflector blade in the folded position.

Par ailleurs, la boucle comprend deux brins formant chacun respectivement une partie de la boucle, chacun des deux brins étant agencé pour, en partant de la ou des languettes vers le ou les plots :

  • suivre au moins une gorge inférieure formée sur la surface inférieure du support de dispositif au moins en partie dans la ou les butées contre lesquelles la face arrière de la lame déflectrice s'appuie lorsque la lame déflectrice est en position pliée,
  • passer de la surface inférieure du support de dispositif à la surface supérieure du support de dispositif par une ouverture agencée à travers le support de dispositif,
  • suivre au moins une première gorge supérieure formée sur la surface supérieure du support de dispositif,
  • rejoindre au moins une deuxième gorge supérieure à l'opposé de la première gorge supérieure par rapport à l'ouverture de passage,
  • passer de la surface supérieure du support de dispositif à la surface inférieure du support de dispositif par une fente de passage formée à travers le support de dispositif.
Furthermore, the loop comprises two strands each respectively forming a part of the loop, each of the two strands being arranged for, starting from the tongue or tongues towards the pad or pads:
  • following at least one lower groove formed on the lower surface of the device support at least partly in the stop or stops against which the rear face of the deflector blade is supported when the deflector blade is in the folded position,
  • passing from the bottom surface of the device carrier to the upper surface of the device carrier through an opening arranged through the device carrier,
  • following at least one first upper groove formed on the upper surface of the device carrier,
  • join at least one second upper groove opposite the first upper groove with respect to the passage opening,
  • passing from the upper surface of the device holder to the lower surface of the device holder by a through slot formed through the device holder.

Par exemple, la boucle est fermée par un ensemble de noeuds réalisé aux extrémités du fil de retenue, l'ensemble de noeuds dépendant du type du fil de retenue.For example, the loop is closed by a set of nodes made at the ends of the retaining wire, the set of nodes depending on the type of the retaining wire.

Selon une particularité, l'élément de renvoi comprend un ressort à lame, le ressort à lame comprenant un support de ressort agencé dans au moins une rainure du support de dispositif, le support de ressort étant pourvu de pattes configurées pour être en appui sous le fuselage du projectile lorsque le dispositif est fixé sur le fuselage du projectile.According to a particularity, the return element comprises a leaf spring, the leaf spring comprising a spring support arranged in at least one groove of the device support, the spring support being provided with legs configured to be supported under the fuselage of the projectile when the device is fixed on the fuselage of the projectile.

De préférence, le support de dispositif présente une épaisseur augmentant continûment de l'amont vers l'aval.Preferably, the device support has a thickness increasing continuously from upstream to downstream.

L'invention concerne également un missile comprenant au moins un dispositif déflecteur de flux de particules tel que décrit ci-dessus.The invention also relates to a missile comprising at least one particle flow deflector device as described above.

BRÈVE DESCRIPTION DES FIGURESBRIEF DESCRIPTION OF THE FIGURES

L'invention, avec ses caractéristiques et avantages, ressortira plus clairement à la lecture de la description faite en référence aux dessins annexés dans lesquels :

  • la figure 1 représente une vue en perspective d'une partie de fuselage d'un projectile sur lequel est fixé un dispositif déflecteur,
  • la figure 2 représente une vue de profil d'un missile guidé par un fil de liaison,
  • la figure 3 représente une vue de profil d'un projectile dont le flux de particules est dévié par un dispositif déflecteur fixé sur le fuselage du missile,
  • la figure 4 représente une vue en perspective du dispositif déflecteur dans la position pliée selon un mode de réalisation,
  • la figure 5 représente une vue en perspective du dispositif déflecteur dans la position dépliée,
  • la figure 6 représente une vue de la surface supérieure du support de dispositif,
  • la figure 7 représente une vue de la surface inférieure du support de dispositif,
  • la figure 8 représente une vue en perspective de la lame déflectrice,
  • la figure 9 représente une vue en perspective de l'élément de renvoi selon un mode de réalisation,
  • la figure 10 représente une vue en perspective d'une partie de la surface inférieure du support de dispositif sur lequel est fixé l'élément de renvoi,
  • la figure 11 représente une vue en perspective d'une partie de la surface supérieure avec la lame déflectrice dans sa position dépliée,
  • la figure 12 représente une vue en perspective d'une partie de la surface supérieure avec la lame déflectrice dans sa position pliée,
  • la figure 13 représente une vue en perspective d'une partie de la surface inférieure avec la lame déflectrice dans sa position pliée,
  • la figure 14 représente une vue en perspective d'une partie de la surface supérieure avec le fil de retenue passant de la surface supérieure du support de dispositif à la surface inférieure du support de dispositif à travers la fente de passage,
  • la figure 15 représente une vue en perspective d'une partie de la surface inférieure avec le fil de retenue entourant les plots,
  • la figure 16 représente une partie de la surface inférieure du support de dispositif avec les plots et la fente de passage,
  • la figure 17 représente un élément de fixation du support de dispositif sur le fuselage du projectile,
  • la figure 18 représente une partie amont de la surface inférieure du support de dispositif,
  • les figures 19 a à c représentent les étapes permettant de réaliser l'ensemble de noeuds pour former la boucle à partir du fil de retenue,
  • la figure 20 représente schématiquement des étapes du procédé d'assemblage du dispositif déflecteur.
The invention, with its features and advantages, will emerge more clearly on reading the description given with reference to the appended drawings in which:
  • the figure 1 represents a perspective view of a fuselage portion of a projectile to which a deflector device is attached,
  • the figure 2 represents a profile view of a missile guided by a wire,
  • the figure 3 represents a profile view of a projectile whose particle flow is deflected by a deflector device fixed on the fuselage of the missile,
  • the figure 4 represents a perspective view of the deflector device in the folded position according to one embodiment,
  • the figure 5 represents a perspective view of the deflector device in the unfolded position,
  • the figure 6 represents a view of the upper surface of the device holder,
  • the figure 7 represents a view of the lower surface of the device support,
  • the figure 8 represents a perspective view of the deflector blade,
  • the figure 9 represents a perspective view of the deflection element according to one embodiment,
  • the figure 10 is a perspective view of a portion of the lower surface of the device support to which the deflection member is attached,
  • the figure 11 represents a perspective view of a portion of the upper surface with the deflector blade in its unfolded position,
  • the figure 12 represents a perspective view of a portion of the upper surface with the deflector blade in its folded position,
  • the figure 13 represents a perspective view of a portion of the lower surface with the deflector blade in its folded position,
  • the figure 14 is a perspective view of a portion of the upper surface with the retaining wire passing from the upper surface of the device holder to the lower surface of the device holder through the passage slot;
  • the figure 15 is a perspective view of a portion of the lower surface with the retaining wire surrounding the pads,
  • the figure 16 represents a portion of the lower surface of the device carrier with the pads and the passage slot,
  • the figure 17 represents a fastening element of the device support on the fuselage of the projectile,
  • the figure 18 represents an upstream portion of the lower surface of the device carrier,
  • the figures 19 a to c represent the steps of making the set of nodes to form the loop from the retaining wire,
  • the figure 20 schematically represents steps of the assembly method of the deflector device.

DESCRIPTION DÉTAILLÉEDETAILED DESCRIPTION

La suite de la description fera référence aux figures citées ci-dessus.The remainder of the description will refer to the figures cited above.

L'invention concerne un dispositif déflecteur 1 de flux de particules 29 pour projectile 30 guidé par un fil de liaison 28 selon un sens de déplacement représenté par la flèche référencée F sur les figures 2 et 3.The invention relates to a deflector device 1 for the flow of particles 29 for a projectile 30 guided by a connecting wire 28 in a direction of movement represented by the arrow referenced F on the Figures 2 and 3 .

Le projectile 30 est pourvu d'un fuselage 2 et d'un propulseur apte à produire un jet propulsif éjecté par une sortie d'éjection 3 du propulseur d'amont vers l'aval dans le sens de déplacement F du projectile 30. Le jet propulsif comprend le flux de particules 29. Le fuselage 2 peut comprendre plusieurs parties. Par exemple, le fuselage 2 peut comprendre une partie avant formant l'avant du projectile 30 et une partie arrière formant l'arrière du projectile 30.The projectile 30 is provided with a fuselage 2 and a thruster capable of producing a propulsive jet ejected by an ejection outlet 3 of the upstream propulsion unit downstream in the direction of displacement F of the projectile 30. propellant comprises the stream of particles 29. The fuselage 2 may comprise several parts. For example, the fuselage 2 may comprise a front part forming the front of the projectile 30 and a rear part forming the rear of the projectile 30.

Le dispositif déflecteur 1 comprend un support de dispositif 4 comprenant une surface supérieure et une surface inférieure. La surface inférieure correspond à une surface configurée pour fixer le support de dispositif 4 sur le fuselage 2 du projectile 30.The deflector device 1 comprises a device support 4 comprising an upper surface and a lower surface. The lower surface corresponds to a surface configured to attach the device support 4 to the fuselage 2 of the projectile 30.

Selon un mode de réalisation, le support de dispositif 4 comprend au moins un élément de fixation 24 disposé sur la surface inférieure du support de dispositif 4 (figure 17). Par exemple, l'élément de fixation 24 est aménagé en forme de crochet pour pouvoir s'enclencher avec un élément de fixation du fuselage 2 de projectile 30. L'élément de fixation 24 peut comprendre un guide latéral 27 configuré pour guider le support de dispositif 4 par rapport à l'élément de fixation du fuselage 2. L'élément de fixation 24 comprend également une surface 25 et une butée longitudinale 26 pour caler le support de dispositif 4 avec le fuselage 2 du projectile 30. La fixation du support de dispositif 4 par au moins un élément de fixation 24 sur le fuselage 2 peut être complétée par l'ajout d'un ruban adhésif.According to one embodiment, the device support 4 comprises at least one attachment element 24 disposed on the lower surface of the device support 4 (FIG. figure 17 ). For example, the fixing element 24 is arranged in the form of a hook in order to be able to engage with a projectile fuselage attachment element 30. The fastening element 24 may comprise a lateral guide 27 configured to guide the support of device 4 relative to the fuselage fastening element 2. The fastening element 24 also comprises a surface 25 and a longitudinal stop 26 for wedging the device support 4 with the fuselage 2 of the projectile 30. device 4 by at least one fastening element 24 on the fuselage 2 may be completed by the addition of an adhesive tape.

Avantageusement, l'élément de fixation du fuselage 2 correspond à une fente en forme de L réalisée à travers le fuselage 2 dans laquelle est enclenché l'élément de fixation 24.Advantageously, the fastening element of the fuselage 2 corresponds to an L-shaped slot made through the fuselage 2 in which the fastening element 24 is engaged.

Par exemple, dans la figure 7, deux éléments de fixation 24 se situent vers l'aval du support de dispositif 4. Un ruban adhésif disposé à l'amont du support de dispositif 4 peut compléter la fixation du support de dispositif 4 sur le fuselage 2.For example, in the figure 7 two fastening elements 24 are located downstream of the device support 4. An adhesive tape disposed upstream of the device carrier 4 can complete the attachment of the device carrier 4 to the fuselage 2.

Des plots de support 33 peuvent être disposés sur la surface inférieure du support de dispositif 4. Ces plots de supports 33 avec le ou les éléments de fixation 24 permettent d'orienter angulairement le support de dispositif 4 par rapport à l'axe longitudinal du projectile 30.Support pads 33 may be arranged on the lower surface of the device support 4. These support pads 33 with the fastening element or elements 24 allow the device support 4 to be oriented angularly with respect to the longitudinal axis of the projectile. 30.

Le dispositif déflecteur 1 comprend en outre une lame déflectrice 5 (figure 8) en aval de la sortie d'éjection 3 et un module d'actionnement de la lame déflectrice 5. Le module d'actionnement permet d'amener la lame déflectrice 5 d'une position pliée dans laquelle la lame déflectrice 5 se situe sensiblement dans le prolongement du support de dispositif 4 à une position dépliée dans laquelle la lame déflectrice 5 fait un angle avec le support de dispositif 4 pour dévier le flux de particules 29.The deflector device 1 further comprises a deflector blade 5 ( figure 8 ) downstream of the ejection outlet 3 and an actuating module of the deflector blade 5. The actuating module is used to bring the deflector blade 5 of a folded position in which the deflector blade 5 is substantially in extending the device carrier 4 to an unfolded position in which the deflector blade 5 is at an angle with the device carrier 4 to deflect the particle stream 29.

La lame déflectrice 5 comprend une surface avant 55 et une surface arrière 56. La surface arrière 56 de la lame déflectrice 5 fait face au fuselage 2.The deflector blade 5 comprises a front surface 55 and a rear surface 56. The rear surface 56 of the deflector plate 5 faces the fuselage 2.

Un projectile 30, tel qu'un missile, est généralement tiré d'un pas de tir qui comprend un tube de lancement. La lame déflectrice 5 peut empêcher un lancement correct du projectile 30 par les frottements entre ladite lame déflectrice 5 et le tube de lancement. Pour éviter que des frottements se produisent, la lame déflectrice 5 se présente dans la position pliée en étant escamotée au moment du lancement du projectile 30 grâce au module d'actionnement.A projectile 30, such as a missile, is generally fired from a firing point that includes a launch tube. The deflector blade 5 can prevent a correct launch of the projectile 30 by friction between said deflector blade 5 and the launch tube. To prevent friction from occurring, the deflector blade 5 is in the folded position being retracted at the launching of the projectile 30 through the actuating module.

Avantageusement, le support de dispositif 4 est pourvu d'au moins une butée 9 contre laquelle au moins la surface arrière 56 de la lame déflectrice 5 s'appuie lorsque la lame déflectrice 5 est en position pliée.Advantageously, the device support 4 is provided with at least one stop 9 against which at least the rear surface 56 of the deflector blade 5 is supported when the deflector blade 5 is in the folded position.

Dans un mode de réalisation, le module d'actionnement comprend un . élément de renvoi 6 et un élément de retenue 70.In one embodiment, the actuation module comprises a. return element 6 and a retaining element 70.

L'élément de renvoi 6 est configuré pour exercer une première force apte à amener la lame déflectrice 5 de la position pliée à la position dépliée (figures 5 et 11).The deflection element 6 is configured to exert a first force capable of bringing the deflector blade 5 from the folded position to the unfolded position ( figures 5 and 11 ).

Selon un mode de réalisation, l'élément de renvoi 6 comprend un ressort à lame 31 (figure 9). Le ressort à lame 31 est pourvu d'un support de ressort 21 agencé dans au moins une rainure 10 du support de dispositif 4. Une languette de fixation 35 comprend un bossage 34 (figure 18) configurée pour pénétrer dans un orifice de fixation 36 agencé dans le support de ressort 21 (figure 9) afin de bloquer l'élément de renvoi dans la rainure 10. Quand l'élément de renvoi 6 est assemblé au support de dispositif 4, la languette de fixation 35 appuie sur le support de ressort 21 jusqu'à ce que le bossage 34 pénètre dans l'orifice de fixation 36 du support de ressort 21. Le support de ressort 21 est pourvu de pattes 20. Ces pattes 20 sont configurées pour être sous le fuselage 2 lorsque le dispositif 1 est fixé sur le fuselage 2 du projectile 30. Ces pattes 20 sont disposées sous le fuselage 2 par leur insertion à travers des fentes en forme de L réalisées sur le fuselage 2.According to one embodiment, the return element 6 comprises a leaf spring 31 ( figure 9 ). The leaf spring 31 is provided with a spring support 21 arranged in at least one groove 10 of the device support 4. A fixing tongue 35 comprises a boss 34 (FIG. figure 18 ) configured to penetrate into a fixing hole 36 arranged in the spring support 21 ( figure 9 ) in order to lock the deflection element in the groove 10. When the deflection element 6 is assembled to the device support 4, the fixing tongue 35 presses on the spring support 21 until the boss 34 enters in the fixing hole 36 of the spring support 21. The spring support 21 is provided with tabs 20. These tabs 20 are configured to be under the fuselage 2 when the device 1 is fixed on the fuselage 2 of the projectile 30. These tabs 20 are arranged under the fuselage 2 by their insertion through L-shaped slots made on the fuselage 2.

Afin de lier la lame déflectrice 5 à l'élément de renvoi 6, le ressort à lame 31 peut être pourvu d'une languette 32 (figure 9) qui traverse la lame déflectrice 5 par un orifice 19 (figure 8) agencé dans la lame déflectrice 5 (figure 11).In order to bind the deflector blade 5 to the deflection element 6, the leaf spring 31 may be provided with a tongue 32 ( figure 9 ) which passes through the deflector blade 5 through an orifice 19 ( figure 8 arranged in the deflector blade 5 ( figure 11 ).

L'élément de retenue 70 est configuré pour exercer une deuxième force apte à contrer la première force pour maintenir la lame déflectrice 5 dans la position pliée. Dans la position pliée, la lame déflectrice 5 est escamotée.The retainer 70 is configured to exert a second force capable of countering the first force to maintain the deflector blade 5 in the folded position. In the folded position, the deflector blade 5 is retracted.

L'élément de renvoi 6 est alors configuré pour amener la lame déflectrice 5 de la position pliée à la position dépliée, lorsque le jet propulsif détruit au moins une partie de l'élément de retenue 70. La destruction d'une partie de l'élément de retenu 70 peut être causée par la chaleur générée par le jet propulsif.The deflection member 6 is then configured to move the deflector blade 5 from the folded position to the unfolded position, when the propellant jet destroys at least a portion of the retainer 70. The destruction of a Part of the holding member 70 may be caused by the heat generated by the propellant jet.

Selon un mode de réalisation, l'élément de retenue 70 comprend un fil de retenue 7 tendu à travers l'ouverture de passage 8.According to one embodiment, the retaining element 70 comprises a retaining wire 7 stretched through the passage opening 8.

Afin de tendre le fil de retenue 7, le support de dispositif 4 et la lame déflectrice 5 peuvent être configurés de la manière suivante.In order to tension the retaining wire 7, the device support 4 and the deflector blade 5 can be configured as follows.

La surface inférieure du support de dispositif 4 comprend au moins un plot 16 disposé en amont de l'ouverture de passage 8 (figures 15 et 16). La lame déflectrice 5 comprend une première extrémité longitudinale 53 qui est en liaison pivot avec le support de dispositif 4 et une deuxième extrémité longitudinale 54 opposée à la première extrémité longitudinale 53. La deuxième extrémité longitudinale 54 est pourvue d'au moins une languette 17 s'étendant à l'opposé de première extrémité longitudinale 53 (figures 8 et 12).The lower surface of the device support 4 comprises at least one pad 16 disposed upstream of the passage opening 8 ( Figures 15 and 16 ). The deflector blade 5 comprises a first longitudinal end 53 which is in pivot connection with the device support 4 and a second longitudinal end 54 opposite to the first longitudinal end 53. The second longitudinal end 54 is provided with at least one tab 17 extending opposite longitudinal first end 53 ( Figures 8 and 12 ).

Le fil de retenue 7 forme une boucle. Cette boucle est agencée pour passer autour de la ou des languettes 17 d'un côté de la boucle (figures 12 et 13) et autour du ou des plots 16 de l'autre côté de la boucle (figures 14 et 15). La boucle est apte à appuyer sur la ou les languettes 17 de la lame déflectrice 5 pour maintenir ladite lame déflectrice 5 dans la position pliée.The retaining wire 7 forms a loop. This loop is arranged to pass around the tab or tabs 17 on one side of the loop ( Figures 12 and 13 ) and around the stud (s) 16 on the other side of the loop ( Figures 14 and 15 ). The loop is able to press the tab or tabs 17 of the deflector blade 5 to maintain said deflector blade 5 in the folded position.

La boucle comprend deux brins 7 formant chacun respectivement une partie de la boucle.The loop comprises two strands 7 each respectively forming a part of the loop.

Chacun des deux brins 7 peut être agencé pour, en partant de la ou des languettes 17 vers le ou les plots 16 :

  • suivre au moins une gorge inférieure 11 formée sur la surface inférieure du support de dispositif 4 au moins en partie dans la ou les butées 9 contre lesquelles au moins la surface arrière 56 de la lame déflectrice 5 s'appuie lorsque la lame déflectrice 5 est en position pliée (figures 13 et 18),
  • passer de la surface inférieure du support de dispositif 4 à la surface supérieure du support de dispositif 4 par une ouverture 12 agencée à travers le support de dispositif 4 (figures 12, 13 et 18),
  • suivre au moins une première gorge supérieure 13 formée sur la surface supérieure du support de dispositif 4 (figure 12 et 13),
  • rejoindre au moins une deuxième gorge supérieure 14 à l'opposé de la première gorge supérieure 13 par rapport à l'ouverture de passage 8 (figure 6 et 14),
  • passer de la surface supérieure du support de dispositif 4 à la surface inférieure du support de dispositif 4 par une fente de passage 15 formée à travers le support de dispositif 4 (figure 6, 7 et 15).
Each of the two strands 7 can be arranged for, starting from the tab or tongues 17 towards the pad or pads 16:
  • follow at least one lower groove 11 formed on the lower surface of the device support 4 at least partly in the stop or stops 9 against which at least the rear surface 56 of the deflector blade 5 is supported when the deflector blade 5 is in folded position ( figures 13 and 18 )
  • passing from the lower surface of the device carrier 4 to the upper surface of the device carrier 4 through an opening 12 arranged through the device carrier 4 ( Figures 12, 13 and 18 )
  • follow at least one first upper groove 13 formed on the upper surface of the device support 4 ( figure 12 and 13 )
  • join at least one second upper groove 14 opposite the first upper groove 13 with respect to the passage opening 8 ( figure 6 and 14 )
  • passing from the upper surface of the device carrier 4 to the lower surface of the device carrier 4 by a passage slot 15 formed through the device carrier 4 ( figure 6, 7 and 15 ).

La boucle est fermée par un ensemble de noeuds 23 réalisé aux extrémités du fil de retenue 7. L'ensemble de noeuds 23 est réalisé en fonction du type de fil de retenue 7 (matière du fil, épaisseur, etc.). Par exemple, l'ensemble de noeuds 23 comprend deux noeuds simples doublés d'un troisième noeud simple (figure 19).The loop is closed by a set of nodes 23 made at the ends of the retaining wire 7. The set of nodes 23 is made according to the type of retaining wire 7 (material of the wire, thickness, etc.). For example, the set of nodes 23 comprises two simple nodes doubled by a third simple node ( figure 19 ).

Avantageusement, le fil de retenue 7 est fixé sur le support de dispositif 4 par au moins un point de colle. Par exemple, un point de colle peut être appliqué pour recouvrir l'ensemble de noeuds 23 pour en assurer la tenue. Cela évite tout mouvement des extrémités du fil de retenue 7 tendant à desserrer la boucle, à réduire, voire à supprimer la tension appliquée au fil de retenue 7 lors de la mise en place de l'ensemble de noeuds 23. Un autre point de colle peut être appliqué au niveau d'une seule des gorges inférieures 11 dans la partie aval du support de dispositif 4 afin de maintenir le fil de retenue 7 qui peut subsister après la destruction d'au moins une partie du fil de retenue 7. Cela permet d'éviter tout risque de rencontre entre le fil de retenue 7 qui subsiste et le fil de liaison 28.Advantageously, the retaining wire 7 is fixed on the device support 4 by at least one point of glue. For example, a dot of glue can be applied to cover the set of nodes 23 to ensure the holding. This prevents any movement of the ends of the retaining wire 7 tending to loosen the loop, reduce or even eliminate the voltage applied to the retaining wire 7 during the implementation of the set of nodes 23. Another point of glue can be applied at only one of the lower grooves 11 in the downstream part of the device support 4 to hold the retaining wire 7 which may remain after the destruction of at least a portion of the retaining wire 7. This allows to avoid any risk of encounter between the retaining wire 7 which remains and the connecting wire 28.

Un noeud peut également être formé à l'avant d'une gorge inférieure 11 pour retenir mécaniquement le fil de retenue 7. De plus, plusieurs tours de fil de retenue 7 peuvent être procédés autour d'un plot de support 33 pour également retenir mécaniquement le fil de retenue 7.A knot may also be formed in front of a lower groove 11 for mechanically retaining the retaining wire 7. In addition, several tows of retaining wire 7 may be formed around a support pad 33 to also mechanically retain the retaining wire 7.

Il est préférable que la lame déflectrice 5 soit dans le prolongement du support de dispositif 4 lorsqu'elle se présente dans sa position pliée afin d'éviter tout frottement avec le tube de lancement et tout risque d'accrochage avec le fil de liaison 29. Or, le fil de retenue 7 peut ne pas être assez tendu pour que la lame déflectrice 5 soit dans le prolongement du support de dispositif 4. Dans ce cas, il possible de tendre le fil de retenue 7 en ajoutant au moins un point de frettage pour resserrer les deux brins du fil de retenue 7 au-dessus de l'ouverture de passage 8. De préférence, le ou les points de frettage sont situés dans la moitié amont du support de dispositif 4.It is preferable that the deflector blade 5 is in the extension of the device support 4 when it is in its folded position to avoid any friction with the launch tube and any risk of attachment with the connecting wire 29. However, the retaining wire 7 may not be so tight that the deflector blade 5 is in the extension of the device support 4. In this case, it is possible to tension the retaining wire 7 by adding at least one hooping point. to tighten the two strands of the retaining wire 7 above the passage opening 8. Preferably, the fretting point or points are located in the upstream half of the device support 4.

Selon un mode de réalisation, un des brins du fil de retenue 7 comprend un élément tendeur 71 configuré pour conserver une tension du fil de retenue 7. La figure 4 montre un exemple de fil de retenue 7 comprenant un élément tendeur 71 correspondant à un ressort.According to one embodiment, one of the strands of the retaining wire 7 comprises a tensioning element 71 configured to maintain a tension of the retaining wire 7. The figure 4 shows an example of a retaining wire 7 comprising a tensioning element 71 corresponding to a spring.

La lame déflectrice 5 est fixée en liaison pivot avec le support de dispositif 4 pour que ladite lame déflectrice 5 puisse passer d'une position pliée à la position dépliée.The deflector blade 5 is pivotally attached to the device holder 4 so that said deflector blade 5 can move from a folded position to the unfolded position.

Avantageusement, la lame déflectrice 5 comprend une première extrémité latérale 51 et une deuxième extrémité latérale 52. Chacune des extrémités 51 et 52 de la lame déflectrice 5 sont pliées vers le fuselage 2.Advantageously, the deflector blade 5 comprises a first lateral end 51 and a second lateral end 52. Each of the ends 51 and 52 of the deflector blade 5 are folded towards the fuselage 2.

Selon un mode de réalisation, la lame déflectrice 5 comprend deux orifices de charnière 18 et le support de dispositif 4 comprend deux crochets de charnière 22. Ces deux crochets de charnière 22 sont configurés pour passer respectivement dans les deux orifices de charnière 18 afin de fixer la lame déflectrice 5 en liaison pivot avec le support de dispositif 4.According to one embodiment, the deflector blade 5 comprises two hinge orifices 18 and the device support 4 comprises two hinge hooks 22. These two hinge hooks 22 are configured to pass respectively into the two hinge orifices 18 in order to fix the deflector blade 5 in pivot connection with the device support 4.

De préférence, le support de dispositif 4 comprend une ouverture de passage 8 configurée pour entourer la sortie d'éjection 3 du propulseur. La lame déflectrice 5 est située en aval de l'ouverture de passage 8.Preferably, the device holder 4 comprises a passage opening 8 configured to surround the thruster ejection outlet 3. The deflector blade 5 is located downstream of the passage opening 8.

Le dispositif déflecteur 1 peut fonctionner de la manière suivante. Avant son lancement, le projectile 30 est disposé dans un tube de lancement. L'élément de retenue 70 exerce la deuxième force qui surmonte la première force exercée par l'élément de renvoi 6. L'élément de retenue 70 maintient alors la lame déflectrice 5 dans sa position pliée. Après le lancement, le projectile 30 vole en planeur pendant un instant. À un moment donné, le propulseur produit le jet propulsif qui détruit alors au moins une partie de l'élément de retenue 70, en particulier une partie du fil de retenue 7. L'élément de retenue 70 n'exerce plus de deuxième force ou exerce une deuxième insuffisante pour surmonter la première force exercée par l'élément de renvoi 6. La lame déflectrice 5 est alors amenée de la position pliée à la position dépliée par l'élément de renvoi 6. La lame déflectrice 5, dans sa position dépliée, permet de dévier le flux de particules 29 contenu dans le jet propulsif.The deflector device 1 can operate in the following manner. Before launch, the projectile 30 is disposed in a launch tube. The retaining member 70 exerts the second force that overcomes the first force exerted by the deflection member 6. The retaining member 70 then holds the deflector blade 5 in its folded position. After launch, the projectile 30 flies in glider for a moment. At a given moment, the thruster produces the propellant jet which then destroys at least a portion of the retaining element 70, in particular a portion of the retaining wire 7. The retaining element 70 no longer exerts a second force or causes a second insufficient to overcome the first force exerted by the deflection element 6. The deflector blade 5 is then brought from the folded position to the unfolded position by the deflection element 6. The deflector blade 5, in its unfolded position , allows to deflect the flow of particles 29 contained in the propellant jet.

De préférence, le support de dispositif 4 présente une forme aérodynamique. Pour cela, le support de dispositif 4 possède une épaisseur augmentant continûment de l'amont vers l'aval. Par exemple, la partie amont du support de dispositif 4 présente une épaisseur de 1 mm environ. Cette épaisseur augmente continument vers la partie aval pour atteindre une valeur de 3,5 mm environ.Preferably, the device support 4 has an aerodynamic shape. For this, the device support 4 has a thickness increasing continuously from upstream to downstream. For example, the upstream portion of the device support 4 has a thickness of about 1 mm. This thickness increases continuously towards the downstream part to reach a value of about 3.5 mm.

Le dispositif déflecteur peut être monté par un procédé d'assemblage du dispositif déflecteur 1 de flux de particules 29 (figure 20).The deflector device can be mounted by a method of assembling the particle flow deflector device 1 (FIG. figure 20 ).

La description ci-après présente un ordre d'étape selon un mode de réalisation. Toutefois, l'ordre des étapes n'est pas figé. Par exemple, certaines étapes peuvent être inversées l'une par rapport à une autre.The following description presents a step order according to one embodiment. However, the order of the steps is not fixed. For example, some steps may be reversed with respect to one another.

Le procédé comprend au moins une étape E2 de mise en place de la lame déflectrice 5 sur le support de dispositif 4.The method comprises at least one step E2 of placing the deflector blade 5 on the device support 4.

Selon un mode de réalisation, le procédé comprend en outre une étape E3 de mise en place de l'élément de retenue 70. L'étape E2 de mise en place de la lame déflectrice 5 est précédée d'une étape E1 de mise en place de l'élément de renvoi 6 sur le support de dispositif 4.According to one embodiment, the method further comprises a step E3 of placing the retaining element 70. The step E2 of setting up the deflector blade 5 is preceded by a step E1 of setting up of the deflection element 6 on the device support 4.

Par exemple, l'étape E1 de mise en place de l'élément de renvoi 6 comprend :

  • une sous-étape E11 de coulissement du support de ressort 21 dans au moins une rainure 10 du support de dispositif 4,
  • une sous-étape E12 de blocage du support de ressort 21 par rapport au support de dispositif 4.
For example, the step E1 of setting up the return element 6 comprises:
  • a substep E11 for sliding the spring support 21 in at least one groove 10 of the device support 4,
  • a sub-step E12 for locking the spring support 21 with respect to the device support 4.

Par exemple, l'étape E2 de mise en place de la lame déflectrice 5 consiste à lier en rotation autour d'un pivot la lame déflectrice 5 au support de dispositif 4.For example, the step E2 of setting up the deflector blade 5 consists in linking in rotation around a pivot the deflector blade 5 to the device support 4.

Par exemple, l'étape E3 de mise en place de l'élément de retenue 70 comprend :

  • une sous-étape E31 d'application sur la lame déflectrice 5 d'une force au moins égale à la deuxième force afin d'amener la lame déflectrice 5 dans la position pliée,
  • une sous-étape E32 de mise en place du fil de retenue 7 autour des languettes 17 de la lame déflectrice 5,
  • une sous-étape E33 de mise en place de chacun des brins du fil de retenue 7 pour qu'il suive au moins une gorge inférieure 11 formée sur la surface inférieure du support de dispositif 4,
  • une sous-étape E34 de passage de chacun des brins du fil de retenue 7 de la surface inférieure du support de dispositif 4 à la surface supérieure du support de dispositif 4 par une ouverture 12 agencée à travers le support de dispositif 4,
  • une sous-étape E35 de mise en place de chacun des brins du fil de retenue 7 pour qu'il suive au moins une première gorge supérieure 13 formée sur la surface supérieure du support de dispositif 4,
  • une sous-étape E36 de mise en place de chacun des brins du fil de retenue 7 pour qu'il rejoigne au moins une deuxième gorge supérieure 14 à l'opposé de la première gorge supérieure 13 par rapport à l'ouverture de passage 8,
  • une sous-étape E37 de passage de chacun des brins du fil de retenue 7 de la surface supérieure du support de dispositif 4 à la surface inférieure du support de dispositif 4 par une fente de passage 15 formée à travers le support de dispositif 4,
  • une sous-étape E38 de nouage des extrémités du fil de retenue 7.
For example, the step E3 of setting up the retaining element 70 comprises:
  • an application sub-step E31 on the deflector blade 5 with a force at least equal to the second force in order to bring the deflector blade 5 into the folded position,
  • a substep E32 for placing the retaining wire 7 around the tongues 17 of the deflector blade 5,
  • a sub-step E33 of placing each of the strands of the retaining wire 7 so that it follows at least one lower groove 11 formed on the lower surface of the device support 4,
  • a substep E34 for passing each of the strands of the retaining wire 7 from the lower surface of the device carrier 4 to the upper surface of the device carrier 4 through an opening 12 arranged through the device carrier 4,
  • a sub-step E35 of placing each of the strands of the retaining wire 7 so that it follows at least one first upper groove 13 formed on the upper surface of the device support 4,
  • a substep E36 of placing each of the strands of the retaining wire 7 so that it joins at least one second upper groove 14 opposite the first upper groove 13 with respect to the passage opening 8,
  • a substep E37 for passing each of the strands of the retaining wire 7 from the upper surface of the device carrier 4 to the lower surface of the device carrier 4 by a passage slot 15 formed through the device carrier 4,
  • a substep E38 of tying the ends of the retaining wire 7.

Claims (11)

  1. Particle flow (29) deflector device for projectile (30) guided by a connecting wire (28) along a direction of travel (F) of the projectile (30), the projectile (30) being provided with a fuselage (2) and a thruster capable of producing a propulsive jet ejected by an ejection outlet (3) of the projectile (30) from upstream to downstream in the direction of travel (F) of the projectile (30), the propulsive jet containing the particle flow (29),
    characterised in that the device (1) comprises:
    - a device support (4) comprising an upper surface and a lower surface, the lower surface corresponding to a surface configured to fix the device support (4) onto the fuselage (2) of the projectile (30),
    - a deflecting blade (5) downstream of the ejection outlet (3),
    - a module for actuating the deflecting blade making it possible to bring the deflecting blade (5) from a folded position, wherein the deflecting blade (5) is located substantially in the extension of the device support (4) to an unfolded position, wherein the deflecting blade (5) makes an angle with the device support (4) to deviate the particle flow (29).
  2. Device according to claim 1,
    characterised in that the module for actuating comprises:
    - a return element (6) configured to exert a first force, capable of bringing the deflecting blade (5) from the folded position to the unfolded position,
    - a retaining element (70) configured to exert a second force, capable of countering the first force to maintain the deflecting blade (5) in the folded position;
    the return element (6) being configured to bring the deflecting blade (5) from the folded position to the unfolded position, when the propulsive jet destroys at least one portion of the retaining element (70), the deflecting blade (5) being in pivotal connection with the device support (4).
  3. Device according to any one of claims 1 or 2,
    characterised in that the deflecting blade (5) comprises a front surface (55) and a rear surface (56), the rear surface (56) facing the fuselage (2), the device support (4) being provided with at least one abutment (9) against which at least the rear surface (56) of the deflecting blade (5) bears when the deflecting blade (5) is in the folded position.
  4. Device according to any one of claims 1 to 3,
    characterised in that the device support (4) comprises a passage opening (8) configured to surround the ejection outlet (3) of the thruster, the deflecting blade (5) being located downstream of the passage opening (8).
  5. Device according to claim 4,
    characterised in that the retaining element (70) comprises a retaining wire (7) extending through the passage opening (8).
  6. Device according to claim 5,
    characterised in that the lower surface of the device support (4) comprises at least one stud (16) arranged upstream of the passage opening (8),
    the deflecting blade (5) comprising a first longitudinal end (53) in pivotal connection with the device support (4) and a second longitudinal end (54) opposite the first longitudinal end (53), the second longitudinal end (54) being provided with at least one strip (17) extending tightly opposite the first longitudinal end (53),
    the retaining wire (7) forming a loop arranged to pass around the strip or strips (17) on one side of the loop and around the stud or studs (16) on the other side of the loop, the loop being capable of bearing on the strip or strips (17) of the deflecting blade (5) to maintain said deflecting blade (5) in the folded position.
  7. Device according to claim 6,
    characterised in that the loop comprises two strands (7) each forming respectively one portion of the loop, each of the two strands (7) being arranged to, starting with the strip or strips (17) to the stud or studs (16):
    - follow at least one lower recess (11) formed on the lower surface of the device support (4) at least partially in the abutment(s) (9) against which at least the rear surface (56) of the deflecting blade (5) bears when the deflecting blade (5) is in the folded position,
    - pass from the lower surface of the device support (4) to the upper surface of the device support (4) through an opening (12) arranged through the device support (4),
    - follow at least one first upper recess (13) formed on the upper surface of the device support (4),
    - join at least one second upper recess (14) opposite the first upper recess (13) with respect to the passage opening (8),
    - pass from the upper surface of the device support (4) to the lower surface of the device support (4) through a passage slot (15) formed through the device support (4).
  8. Device according to any one of claims 6 or 7,
    characterised in that the loop is closed by a set of knots (23) made at the ends of the retaining wire (7), the set of knots (23) depending on the type of retaining wire (7).
  9. Device according to any one of claims 2 to 8,
    characterised in that the return element (6) comprises a leaf spring (31), the leaf spring (31) comprising a spring support (21) arranged in at least one groove (10) of the device support (4), the spring support (21) being provided with feet (20) configured to bear under the fuselage (2) of the projectile (30) when the device (1) is fixed on the fuselage (2) of the projectile (30).
  10. Device according to any one of claims 1 to 9,
    characterised in that the device support (4) has a continually increasing thickness from upstream to downstream.
  11. Missile,
    characterised in that it comprises at least one deflector device (1) particle flows (29) according to any one of claims 1 to 10.
EP18290074.6A 2017-07-12 2018-06-28 Particle flow deflector device for projectile guided by a linking wire Active EP3428570B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1700755A FR3069051B1 (en) 2017-07-12 2017-07-12 PARTICLE FLUX DEFLECTING DEVICE FOR PROJECTILE GUIDED BY A CONNECTING THREAD

Publications (2)

Publication Number Publication Date
EP3428570A1 EP3428570A1 (en) 2019-01-16
EP3428570B1 true EP3428570B1 (en) 2019-07-31

Family

ID=60515429

Family Applications (1)

Application Number Title Priority Date Filing Date
EP18290074.6A Active EP3428570B1 (en) 2017-07-12 2018-06-28 Particle flow deflector device for projectile guided by a linking wire

Country Status (6)

Country Link
US (1) US11092412B2 (en)
EP (1) EP3428570B1 (en)
ES (1) ES2748948T3 (en)
FR (1) FR3069051B1 (en)
IL (1) IL271958B2 (en)
WO (1) WO2019012189A1 (en)

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Publication number Priority date Publication date Assignee Title
US3690595A (en) * 1970-11-19 1972-09-12 Sarmac Sa Self-propelled, vaned missile
US4967980A (en) * 1987-03-31 1990-11-06 The Boeing Company Optical fiber guided tube-launched projectile system
US5056406A (en) * 1990-03-15 1991-10-15 The Boeing Company Fiber optic mortar projectile
US5189253A (en) * 1990-07-20 1993-02-23 Hughes Aircraft Company Filament dispenser
DE4030712A1 (en) * 1990-09-28 1992-04-02 Dmt Marinetechnik Gmbh Submarine torpedo launching system - protects torpedo and guidance cable from hot exhaust gases using sliding piston
US5143319A (en) * 1991-02-01 1992-09-01 Hughes Aircraft Company Method and apparatus for dispensing an optical fiber from a powered missile through the motor exhaust
US5179612A (en) * 1991-12-19 1993-01-12 Hughes Aircraft Company Optical fiber canister with ablative coating
US5161208A (en) * 1991-12-19 1992-11-03 Hughes Aircraft Company Optical fiber canister and process with overcoat adhesive layer to prevent dispensing end breaks
WO1996018865A1 (en) * 1994-12-16 1996-06-20 Sci Systems, Inc. Fiber-optic cable dispenser and remotely controlled vehicle using same
US6502785B1 (en) * 1999-11-17 2003-01-07 Lockheed Martin Corporation Three axis flap control system
US7004424B1 (en) * 2004-04-05 2006-02-28 The United States Of America, As Represented By The Secretary Of The Army Projectile flight altering apparatus
US7642492B2 (en) * 2005-01-26 2010-01-05 Raytheon Company Single-axis fin deployment system
US8193476B2 (en) * 2008-06-13 2012-06-05 Raytheon Company Solid-fuel pellet thrust and control actuation system to maneuver a flight vehicle
DE102014003202B3 (en) * 2013-12-20 2014-11-13 Diehl Bgt Defence Gmbh & Co. Kg Coil system for a vehicle

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Also Published As

Publication number Publication date
EP3428570A1 (en) 2019-01-16
IL271958A (en) 2020-02-27
IL271958B2 (en) 2023-10-01
FR3069051A1 (en) 2019-01-18
FR3069051B1 (en) 2019-08-16
IL271958B1 (en) 2023-06-01
US20200149849A1 (en) 2020-05-14
WO2019012189A1 (en) 2019-01-17
ES2748948T3 (en) 2020-03-18
US11092412B2 (en) 2021-08-17

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