EP2863164A1 - Device for braking the rotation of a shell of a payload, and spin-stabilised projectile provided with such a device - Google Patents

Device for braking the rotation of a shell of a payload, and spin-stabilised projectile provided with such a device Download PDF

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Publication number
EP2863164A1
EP2863164A1 EP20140187121 EP14187121A EP2863164A1 EP 2863164 A1 EP2863164 A1 EP 2863164A1 EP 20140187121 EP20140187121 EP 20140187121 EP 14187121 A EP14187121 A EP 14187121A EP 2863164 A1 EP2863164 A1 EP 2863164A1
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EP
European Patent Office
Prior art keywords
casing
fins
payload
rotation
envelope
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Granted
Application number
EP20140187121
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German (de)
French (fr)
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EP2863164B1 (en
Inventor
Christian Trouillot
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Nexter Munitions SA
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Nexter Munitions SA
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Priority to PL14187121T priority Critical patent/PL2863164T3/en
Publication of EP2863164A1 publication Critical patent/EP2863164A1/en
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Publication of EP2863164B1 publication Critical patent/EP2863164B1/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
    • F42B10/32—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
    • F42B10/54—Spin braking means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
    • F42B12/62—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected parallel to the longitudinal axis of the projectile
    • F42B12/625—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected parallel to the longitudinal axis of the projectile a single submissile arranged in a carrier missile for being launched or accelerated coaxially; Coaxial tandem arrangement of missiles which are active in the target one after the other

Definitions

  • the technical field of the invention is that of braking devices in rotation of an envelope of a payload ejected from a gyro-stabilized projectile.
  • Gyrostabilized projectiles that eject a payload on a trajectory are well known. These are most often artillery projectiles, so large caliber (caliber greater than or equal to 105 mm).
  • the payload may be an illuminating pyrotechnic composition pot or smoke. It can also be a cargo container carrying an electronic load such as a communication relay or a scrambling means.
  • the patent FR2260772 thus describes an illuminating shell which comprises a payload in the form of a case containing a pot of illuminating pyrotechnic composition.
  • the gyrostabilized artillery projectiles have a rotation speed of the order of 80 to 300 revolutions / second. It is necessary to greatly reduce this speed to avoid, according to the type of on-board payload, the destruction or damage of the latter, while ensuring its stability and proper operation.
  • the speed of rotation of the lighting pot must be reduced to a few revolutions per second or ideally canceled. It is therefore necessary to slow the rotation of the payload after its ejection out of the body of the projectile.
  • the patent FR2260772 describes a payload ejection that takes place in two stages (double stripping): first the ejection out of the shell body of an envelope containing the payload and the double braking in translation and in rotation of this envelope, then the ejection after a few seconds, the payload out of the envelope, ejection which is triggered by a pyrotechnic chain consisting of a pyrotechnic delay initiated by the charge of 1 unloading and a load called 2nd unloading.
  • the rotational braking of the casing is provided by radial vanes deployable by the effect of the centrifugal force.
  • These fins are most often made in the form of tongues, metal or plastic, which are fixed by one of their edge to the envelope of the payload and which are wrapped around the latter. The edge of the fins is thus parallel to the axis of the payload.
  • the patent EP466499 also describes a shelling artillery shell that ejects on trajectory an envelope enclosing an illuminating pot. Again the casing is braked in rotation by fins. It will be noted that the ejected pot out of the casing also carries fins ensuring a rotational braking. This shows that the rotational braking provided by the fins of the envelope is insufficient, since it must also slow the light pot after ejection.
  • the patent US5684267 shows an exemplary embodiment of a braking wing in rotation of a payload.
  • Known fins have an efficiency characterized by the roll damping coefficient (Clp), which depends in particular on the geometry of the fins and their aerodynamic surface. They practically allow to brake in a dozen seconds an initial rotation of the order of 50 revolutions / second to bring it back to a few revolutions / second.
  • Clp roll damping coefficient
  • the object of the invention is to propose a device for braking in rotation of the payload envelope which is more efficient and which provides rotational braking over a period of time controlled and synchronized with the translation braking of the envelope.
  • the payload of the payload can thus be ensured under optimal conditions.
  • the subject of the invention is a device for braking in rotation a cylindrical envelope of a payload ejected from a gyro-stabilized projectile, a device comprising at least two deployable wings regularly distributed angularly on an outer wall of the envelope. , characterized in that the fins are positioned relative to the casing so that their plane forms, in the deployed position, an angle with the axis of the casing, non-zero angle and oriented so that the aerodynamic flow during the flight of the envelope has the effect of curbing the rotation of the latter.
  • the fins may be formed by metal sheets attached to the wall of the envelope at one of their edges.
  • Each metal sheet may be attached along a helical line of the envelope, the various helical lines associated with the different fins being deduced from each other by rotation about the axis of the envelope.
  • the casing may thus carry fins fixed along at least two helical lines.
  • the envelope may for example carry fins fixed along two helical lines deduced from each other by rotation of 180 ° around the axis of the envelope.
  • the fins of the device are rigid and slide radially between an inner housing to the casing and the outside of the casing.
  • Each fin may then comprise a heel which will abut against a wall of a housing enclosing the fins, heel stopping the movement of the fin when it deploys.
  • the object of the invention is also to propose a gyro-stabilized projectile ejecting a payload on a trajectory, the payload or an envelope enclosing it being provided with such a device for braking the rotation.
  • This gyro-stabilized projectile may comprise a payload which is an illuminating pyrotechnic charge.
  • the figure 1 shows a field 2 of operation on which is positioned a weapon system 3 which fires a projectile 1 according to the invention along a ballistic trajectory 4.
  • the projectile 1 is a cargo projectile which comprises a body 5 which encloses a payload 6 disposed in an envelope 7.
  • the projectile 1 is here represented at the moment of the ejection of the payload 6, that is to say during the second dumping above the ground.
  • a parachute 16 provided before the second removal brake translation of the casing 7.
  • the payload 6 may be constituted by an illuminating pyrotechnic composition pot.
  • the projectile contains a gas generating charge (not shown) which ensures the ejection of the envelope 7 at a given instant determined by a time rocket.
  • the casing 7 carries a rotational braking device 8 which is constituted by fins deployed by force centrifugal.
  • the payload 6 has been removed from the casing 7 by means of a pyrotechnic unloading charge.
  • a parachute 9 ensures the slow descent of the payload to the terrain 2.
  • the debiting of the payload 6 is of course achieved with a certain delay with respect to the ejection of the casing 7 out of the body 5, so that the device 8 can provide rotational braking prior to this extraction.
  • the parachute 16 has also provided translation braking of the envelope.
  • This ejection mechanism is quite conventional and described for example by the patent FR2260772 .
  • the figure 2 is a schematic and partial perspective view of the casing 7 of the payload.
  • This envelope is cylindrical and is animated during its ejection of a rotational movement ⁇ about its axis 10, a movement that was communicated to it by the body 5 of the projectile.
  • the casing 7 is equipped with a rotational braking device according to the invention, which device comprises here two deployable fins 8, fixed on the outer wall 11 of the casing 7.
  • a single fin 8 is shown in the figure for the clarity of the drawing.
  • Each fin 8 is constituted by a sheet or metal blade of small thickness (a few tenths of a mm) which is fixed to the envelope 7 for example by continuous or spot welds (other processes such as gluing are of course possible. ).
  • each metal fin 8 has at one of its edges 8a a foot 8b which is welded to the envelope.
  • the sheet 8 is substantially perpendicular to its foot 8b once deployed.
  • the fins 8 are positioned relative to the casing 7 so that that their plane forms a non-zero angle ⁇ with the axis 10 of the envelope (so with a generatrix 12 of the envelope as visible in FIG. figure 2 ).
  • the fins 8 are no longer parallel to the axis 10 as in the prior art but inclined.
  • the angle of incidence ⁇ of the fins 8 is also oriented so that the aerodynamic flow E during the ballistic flight of the envelope has the effect of acting on the fins to generate a lift force and therefore a couple of seconds. rolling around the axis 10. This torque is oriented opposite to the initial rotation and will therefore slow the rotation of the envelope 7.
  • the angle of incidence ⁇ is between 5 ° and 10 °.
  • the metal foils constituting the fins 8 are thus fixed along helical lines 15a and 15b of the envelope 7.
  • the angle of incidence ⁇ being the same at each line, these lines 15a, 15b are deduced one from the other. others by a rotation of a given angle around the axis of the casing 7.
  • each line will be deduced from the previous one by a rotation of angle equal to 2 ⁇ / N. It will be possible for example to provide three helical lines deduced from each other by rotations of 120 ° so three fins.
  • the length of the fins 8 may be shorter than the length of the casing 7.
  • the fins will then be positioned so as to increase the stability (the static margin) of the casing 7.
  • the fins then also act as empennage .
  • the fins 8 act on the casing 7 at the same time by the conventional braking intrinsic to their geometry (characterized by the roll damping coefficient Clp) and by the opposite roll torque at the same time. to the rotation which is induced by their incidence ⁇ . This results in a much more efficient rotational braking.
  • this rotational braking is independent of the rotational speed of the casing 7 since the torque generated by the fins 8 is proportional to the square of the path velocity of the casing. This speed is still important and of the order of several tens of m / s.
  • the figure 4 shows curves giving decreases in the speed of rotation of the envelope 6 as a function of time.
  • the curve 13 corresponds to a braking device according to the prior art in which the fins 8 are fixed along generatrices parallel to the axis of the casing.
  • the moment T when the rotation speed is canceled can be easily adjusted by changing the angle of incidence of the fins. Braking synchronization is thus facilitated.
  • the delay to cancel the rotation is divided by at least two equal fin surfaces.
  • the reverse rotation speed remains low (less than 5 revolutions / second) and does not hinder the combustion of the illuminating charge.
  • FIGs 3a and 3b show in lateral and frontal projection the envelope 7 equipped with its fins 8. It has been shown in fine line the traces in projection of the helical lines 15a and 15b. The fins 8 are shown folded over the figure 3a . In their deployed position they would be parallel to line 15a or 15b. We also represented at figure 3a by points 16 the welds of each fin 8 on the casing 7 at the foot 8b of the fin.
  • fins 8 comprise front and rear bevels 18 (such an arrangement is conventional).
  • the fins 8 are sufficiently thin (of the order of 0.5 mm thick) to follow the profile of the body of the casing 7 when folded, even with the expected angle of incidence.
  • the device according to the invention is therefore particularly simple and rustic.
  • the fins are rigid fins which slide radially between an inner housing to the casing 7 and the outside. In this case it will be necessary to have inside the envelope a sufficient volume to accommodate the sliding fins.
  • figure 5 shows an envelope 7 which comprises at each end a braking device which comprises a housing 17 enclosing four rigid and sliding fins 8. Each fin 8 is inclined at an angle ⁇ with respect to the axis 10 of the envelope 7
  • the housing has an inner housing which receives the fins.
  • the casing constitutes a means of securing the casing 7 and the fins.
  • the latter are positioned in guide slots 18 which have the inclination providing the angle of incidence ⁇ .
  • each fin has a heel 19 which abuts against the wall of the housing 15 and stops its movement of movement during the deployment of the fins.
  • the fin may be locked in this deployed position by mechanical deformation or by a locking means attached to the housing 17 and engaging in the fin (an anti return blade for example).
  • the fins 8 When the casing 7 is in the projectile body, the fins 8 are housed inside each casing. The centrifugal force causes the fins to exit when the casing 7 is ejected from the projectile body.
  • the fins 8 provide braking, as explained above, both by increasing the master torque of the casing and by the opposite rotation caused by the inclination of the fins.
  • An additional device not shown will ensure the ejection of at least one of the housings 17 to allow the desired moment the extraction of the payload out of the casing 7.
  • the invention has been described in its application to an illuminating payload. It is of course possible to implement the braking device according to the invention for another type of payload, for example a cargo container carrying an electronic load such as a communication relay or a scrambling means.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Toys (AREA)
  • Non-Portable Lighting Devices Or Systems Thereof (AREA)
  • Braking Arrangements (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

L'invention a pour objet un dispositif de freinage en rotation d'une enveloppe cylindrique (7) d'une charge utile éjectée à partir d'un projectile gyrostabilisé. Ce dispositif comprend au moins deux ailettes (8) déployables régulièrement réparties angulairement sur une paroi externe (11) de l'enveloppe (7). Les ailettes (8) sont positionnées par rapport à l'enveloppe (7) de telle sorte que leur plan forme, en position déployée, un angle (±) avec l'axe (10) de l'enveloppe (7), angle non nul et orienté de telle sorte que l'écoulement aérodynamique (E) lors du vol de l'enveloppe ait pour effet de freiner la rotation de cette dernière.The subject of the invention is a device for braking in rotation a cylindrical envelope (7) with a payload ejected from a gyro-stabilized projectile. This device comprises at least two fins (8) deployable evenly distributed angularly on an outer wall (11) of the casing (7). The fins (8) are positioned with respect to the casing (7) so that their plane forms, in the deployed position, an angle (±) with the axis (10) of the casing (7). zero and oriented so that the aerodynamic flow (E) during the flight of the envelope has the effect of curbing the rotation of the latter.

Description

Le domaine technique de l'invention est celui des dispositifs de freinage en rotation d'une enveloppe d'une charge utile éjectée à partir d'un projectile gyrostabilisé.The technical field of the invention is that of braking devices in rotation of an envelope of a payload ejected from a gyro-stabilized projectile.

Les projectiles gyrostabilisés qui éjectent une charge utile sur trajectoire sont bien connus. Ce sont le plus souvent des projectiles d'artillerie, donc de gros calibre (calibre supérieur ou égal à 105 mm).Gyrostabilized projectiles that eject a payload on a trajectory are well known. These are most often artillery projectiles, so large caliber (caliber greater than or equal to 105 mm).

La charge utile peut être un pot de composition pyrotechnique éclairante ou encore fumigène. Il peut aussi s'agir d'un conteneur cargo transportant une charge électronique comme un relais de communication ou un moyen de brouillage.The payload may be an illuminating pyrotechnic composition pot or smoke. It can also be a cargo container carrying an electronic load such as a communication relay or a scrambling means.

A titre d'exemple, le brevet FR2260772 décrit ainsi un obus éclairant qui comporte une charge utile sous la forme d'un étui renfermant un pot de composition pyrotechnique éclairante.For example, the patent FR2260772 thus describes an illuminating shell which comprises a payload in the form of a case containing a pot of illuminating pyrotechnic composition.

Les projectiles d'artillerie gyrostabilisés ont une vitesse de rotation de l'ordre de 80 à 300 tours/seconde. Il est nécessaire de réduire fortement cette vitesse pour éviter, suivant le type de charge utile embarquée, la destruction ou l'endommagement de cette dernière, tout en assurant sa stabilité et son bon fonctionnement.The gyrostabilized artillery projectiles have a rotation speed of the order of 80 to 300 revolutions / second. It is necessary to greatly reduce this speed to avoid, according to the type of on-board payload, the destruction or damage of the latter, while ensuring its stability and proper operation.

En particulier, pour les compositions pyrotechniques éclairantes, la rotation dégrade les performances. L'effet de la force centrifuge entraîne en effet l'augmentation de la vitesse de combustion donc la diminution de la durée d'éclairement.In particular, for illuminating pyrotechnic compositions, rotation degrades performance. The effect of the centrifugal force indeed causes the increase of the combustion rate and thus the reduction of the duration of illumination.

La vitesse de rotation du pot éclairant doit donc être réduite à quelques tours par seconde voire idéalement annulée. Il est donc nécessaire de freiner la rotation de la charge utile après son éjection hors du corps du projectile.The speed of rotation of the lighting pot must be reduced to a few revolutions per second or ideally canceled. It is therefore necessary to slow the rotation of the payload after its ejection out of the body of the projectile.

Le brevet FR2260772 décrit une éjection de charge utile qui s'opère en deux temps (double dépotage) : tout d'abord l'éjection hors du corps d'obus d'une enveloppe renfermant la charge utile et le double freinage en translation et en rotation de cette enveloppe, puis l'éjection au bout de quelques secondes, de la charge utile hors de l'enveloppe, éjection qui est déclenchée par une chaîne pyrotechnique constituée d'un retard pyrotechnique initié par la charge de 1er dépotage et d'une charge dite de 2ème dépotage.The patent FR2260772 describes a payload ejection that takes place in two stages (double stripping): first the ejection out of the shell body of an envelope containing the payload and the double braking in translation and in rotation of this envelope, then the ejection after a few seconds, the payload out of the envelope, ejection which is triggered by a pyrotechnic chain consisting of a pyrotechnic delay initiated by the charge of 1 unloading and a load called 2nd unloading.

Le freinage en rotation de l'enveloppe est assuré par des ailettes radiales déployables par l'effet de la force centrifuge. Ces ailettes sont le plus souvent réalisées sous la forme de languettes, en métal ou en matière plastique, qui sont fixées par un de leur bord à l'enveloppe de la charge utile et qui sont enroulées autour de cette dernière. Le bord des ailettes est ainsi parallèle à l'axe de la charge utile.The rotational braking of the casing is provided by radial vanes deployable by the effect of the centrifugal force. These fins are most often made in the form of tongues, metal or plastic, which are fixed by one of their edge to the envelope of the payload and which are wrapped around the latter. The edge of the fins is thus parallel to the axis of the payload.

Le brevet EP466499 décrit lui aussi un obus éclairant d'artillerie qui éjecte sur trajectoire une enveloppe renfermant un pot éclairant. Là encore l'enveloppe est freinée en rotation par des ailettes. On notera que le pot éjecté hors de l'enveloppe porte lui aussi des ailettes assurant un freinage en rotation. Ceci montre bien que le freinage en rotation assuré par les ailettes de l'enveloppe est insuffisant, puisqu'il faut également freiner le pot éclairant après son éjection.The patent EP466499 also describes a shelling artillery shell that ejects on trajectory an envelope enclosing an illuminating pot. Again the casing is braked in rotation by fins. It will be noted that the ejected pot out of the casing also carries fins ensuring a rotational braking. This shows that the rotational braking provided by the fins of the envelope is insufficient, since it must also slow the light pot after ejection.

Le brevet US5684267 montre un exemple de réalisation d'une ailette de freinage en rotation d'une charge utile.The patent US5684267 shows an exemplary embodiment of a braking wing in rotation of a payload.

Les ailettes connues ont une efficacité caractérisée par le coefficient d'amortissement en roulis (Clp), qui dépend notamment de la géométrie des ailettes et de leur surface aérodynamique. Elles permettent pratiquement de freiner en une douzaine de secondes une rotation initiale de l'ordre de 50 tours/seconde pour la ramener à quelques tours / seconde.Known fins have an efficiency characterized by the roll damping coefficient (Clp), which depends in particular on the geometry of the fins and their aerodynamic surface. They practically allow to brake in a dozen seconds an initial rotation of the order of 50 revolutions / second to bring it back to a few revolutions / second.

Ces délais de freinage restent encore trop importants opérationnellement et il est par ailleurs impossible avec les ailettes connues de maîtriser la durée du freinage, l'efficacité des ailettes diminuant avec la vitesse de rotation.These braking times are still too important operationally and it is also impossible with known fins to control the duration of braking, the efficiency of the fins decreasing with the speed of rotation.

Les délais de freinage conduisent à un allumage du pot éclairant alors que sa vitesse de rotation est encore de l'ordre de 10 à 12 tours par seconde ce qui réduit fortement la durée de l'éclairage.The braking delays lead to an ignition of the illuminating pot while its rotational speed is still in the order of 10 to 12 revolutions per second, which greatly reduces the duration of the illumination.

L'invention a pour but de proposer un dispositif de freinage en rotation de l'enveloppe de charge utile qui soit plus efficace et qui assure un freinage en rotation sur une durée contrôlée et synchronisée avec le freinage en translation de l'enveloppe.The object of the invention is to propose a device for braking in rotation of the payload envelope which is more efficient and which provides rotational braking over a period of time controlled and synchronized with the translation braking of the envelope.

Le dépotage de la charge utile peut ainsi être assuré dans des conditions optimales.The payload of the payload can thus be ensured under optimal conditions.

Avec l'invention, il devient possible pour un projectile tel que décrit par EP0466499 , de ne plus prévoir d'ailettes de freinage en rotation au niveau du pot éclairant, le dispositif de freinage fixé à l'enveloppe assurant à lui seul un freinage en rotation efficace. L'invention permet de réduire par ailleurs la surface des ailettes de freinage et/ou leur nombre.With the invention, it becomes possible for a projectile as described by EP0466499 no longer provide rotating brake blades at the illuminating pot, the braking device attached to the casing alone ensuring effective rotational braking. The invention also makes it possible to reduce the surface area of the braking fins and / or their number.

Ainsi l'invention a pour objet un dispositif de freinage en rotation d'une enveloppe cylindrique d'une charge utile éjectée à partir d'un projectile gyrostabilisé, dispositif comprenant au moins deux ailettes déployables régulièrement réparties angulairement sur une paroi externe de l'enveloppe, dispositif caractérisé en ce que les ailettes sont positionnées par rapport à l'enveloppe de telle sorte que leur plan forme, en position déployée, un angle avec l'axe de l'enveloppe, angle non nul et orienté de telle sorte que l'écoulement aérodynamique au cours du vol de l'enveloppe ait pour effet de freiner la rotation de cette dernière.Thus, the subject of the invention is a device for braking in rotation a cylindrical envelope of a payload ejected from a gyro-stabilized projectile, a device comprising at least two deployable wings regularly distributed angularly on an outer wall of the envelope. , characterized in that the fins are positioned relative to the casing so that their plane forms, in the deployed position, an angle with the axis of the casing, non-zero angle and oriented so that the aerodynamic flow during the flight of the envelope has the effect of curbing the rotation of the latter.

Les ailettes pourront être formées par des feuilles métalliques fixées à la paroi de l'enveloppe au niveau d'un de leur bord.The fins may be formed by metal sheets attached to the wall of the envelope at one of their edges.

Chaque feuille métallique pourra être fixée le long d'une ligne hélicoïdale de l'enveloppe, les différentes lignes hélicoïdales associées aux différentes ailettes étant déduites les unes des autres par rotation autour de l'axe de l'enveloppe.Each metal sheet may be attached along a helical line of the envelope, the various helical lines associated with the different fins being deduced from each other by rotation about the axis of the envelope.

L'enveloppe pourra ainsi porter des ailettes fixées le long d'au moins deux lignes hélicoïdales.The casing may thus carry fins fixed along at least two helical lines.

L'enveloppe pourra par exemple porter des ailettes fixées le long de deux lignes hélicoïdales déduites l'une de l'autre par rotation de 180° autour de l'axe de l'enveloppe.The envelope may for example carry fins fixed along two helical lines deduced from each other by rotation of 180 ° around the axis of the envelope.

Selon un autre mode de réalisation, les ailettes du dispositif sont rigides et glissent radialement entre un logement interne à l'enveloppe et l'extérieur de l'enveloppe.According to another embodiment, the fins of the device are rigid and slide radially between an inner housing to the casing and the outside of the casing.

Chaque ailette pourra alors comporter un talon qui viendra en butée contre une paroi d'un boîtier renfermant les ailettes, talon arrêtant le mouvement de sortie de l'ailette lors de son déploiement.Each fin may then comprise a heel which will abut against a wall of a housing enclosing the fins, heel stopping the movement of the fin when it deploys.

L'invention a également pour objet de proposer un projectile gyrostabilisé éjectant une charge utile sur trajectoire, la charge utile ou une enveloppe renfermant celle-ci étant dotée d'un tel dispositif de freinage de la rotation.The object of the invention is also to propose a gyro-stabilized projectile ejecting a payload on a trajectory, the payload or an envelope enclosing it being provided with such a device for braking the rotation.

Ce projectile gyrostabilisé pourra comporter une charge utile qui est une charge pyrotechnique éclairante.This gyro-stabilized projectile may comprise a payload which is an illuminating pyrotechnic charge.

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

  • La figure 1 est un schéma montrant la mise en oeuvre opérationnelle d'un projectile selon l'invention,
  • La figure 2 est une vue en perspective schématique et partielle d'une enveloppe de charge utile équipée d'un dispositif selon l'invention,
  • Les figures 3a et 3b sont des vues latérales et de dessus de cette enveloppe, la figure 3a montrant l'enveloppe en vue latérale et au repos, la figure 3b l'enveloppe en vue de dessus et en rotation,
  • La figure 4 est une courbe montrant les effets comparés sur une enveloppe de charge utile d'un dispositif de freinage en rotation selon l'art antérieur et d'un dispositif selon l'invention,
  • La figure 5 montre en vue latérale avec découpe partielle un autre mode de réalisation du dispositif selon l'invention.
The invention will be better understood on reading the following description of a particular embodiment, a description given with reference to the appended drawings and in which:
  • The figure 1 is a diagram showing the operational implementation of a projectile according to the invention,
  • The figure 2 is a schematic and partial perspective view of a payload envelope equipped with a device according to the invention,
  • The Figures 3a and 3b are side and top views of this envelope, the figure 3a showing the envelope in side view and at rest, the figure 3b the envelope in plan view and in rotation,
  • The figure 4 is a curve showing the effects compared on a payload envelope of a rotary braking device according to the prior art and a device according to the invention,
  • The figure 5 shows in side view with partial cut another embodiment of the device according to the invention.

La figure 1 montre un terrain 2 d'opération sur lequel est positionné un système d'arme 3 qui tire un projectile 1 selon l'invention suivant une trajectoire balistique 4.The figure 1 shows a field 2 of operation on which is positioned a weapon system 3 which fires a projectile 1 according to the invention along a ballistic trajectory 4.

Le projectile 1 est un projectile cargo qui comprend un corps 5 qui renferme une charge utile 6 disposée dans une enveloppe 7. Le projectile 1 est ici représenté au moment de l'éjection de la charge utile 6, c'est à dire lors du second dépotage au-dessus du terrain. Lors d'un premier dépotage l'enveloppe 7 a été éjectée hors du corps de projectile par une première charge pyrotechnique de dépotage. Un parachute 16 a assuré avant le second dépotage le freinage en translation de l'enveloppe 7. La charge utile 6 pourra être constituée par un pot de composition pyrotechnique éclairante.The projectile 1 is a cargo projectile which comprises a body 5 which encloses a payload 6 disposed in an envelope 7. The projectile 1 is here represented at the moment of the ejection of the payload 6, that is to say during the second dumping above the ground. During a first unloading the envelope 7 has been ejected from the projectile body by a first pyrotechnic unloading charge. A parachute 16 provided before the second removal brake translation of the casing 7. The payload 6 may be constituted by an illuminating pyrotechnic composition pot.

D'une façon classique le projectile renferme une charge génératrice de gaz (non représentée) qui assure l'éjection de l'enveloppe 7 à un instant donné déterminé par une fusée chronométrique.In a conventional manner the projectile contains a gas generating charge (not shown) which ensures the ejection of the envelope 7 at a given instant determined by a time rocket.

L'enveloppe 7 porte un dispositif de freinage en rotation 8 qui est constitué par des ailettes déployées par la force centrifuge. La charge utile 6 a été dépotée hors de l'enveloppe 7 à l'aide d'une charge pyrotechnique de dépotage. Un parachute 9 assure la descente ralentie de la charge utile vers le terrain 2.The casing 7 carries a rotational braking device 8 which is constituted by fins deployed by force centrifugal. The payload 6 has been removed from the casing 7 by means of a pyrotechnic unloading charge. A parachute 9 ensures the slow descent of the payload to the terrain 2.

Le dépotage de la charge utile 6 est bien entendu réalisé avec un certain délai par rapport à l'éjection de l'enveloppe 7 hors du corps 5, cela afin que le dispositif 8 puisse assurer le freinage en rotation avant cette extraction. Le parachute 16 a assuré par ailleurs le freinage en translation de l'enveloppe.The debiting of the payload 6 is of course achieved with a certain delay with respect to the ejection of the casing 7 out of the body 5, so that the device 8 can provide rotational braking prior to this extraction. The parachute 16 has also provided translation braking of the envelope.

Ce mécanisme d'éjection est tout à fait classique et décrit par exemple par le brevet FR2260772 .This ejection mechanism is quite conventional and described for example by the patent FR2260772 .

La figure 2 est une vue en perspective schématique et partielle de l'enveloppe 7 de la charge utile. Cette enveloppe est cylindrique et elle est animée lors de son éjection d'un mouvement de rotation Ω autour de son axe 10, mouvement qui lui a été communiqué par le corps 5 du projectile.The figure 2 is a schematic and partial perspective view of the casing 7 of the payload. This envelope is cylindrical and is animated during its ejection of a rotational movement Ω about its axis 10, a movement that was communicated to it by the body 5 of the projectile.

L'enveloppe 7 est équipée d'un dispositif de freinage en rotation selon l'invention, dispositif qui comprend ici deux ailettes 8 déployables, fixées sur la paroi externe 11 de l'enveloppe 7. Une seule ailette 8 est représentée sur la figure pour la clarté du dessin.The casing 7 is equipped with a rotational braking device according to the invention, which device comprises here two deployable fins 8, fixed on the outer wall 11 of the casing 7. A single fin 8 is shown in the figure for the clarity of the drawing.

Chaque ailette 8 est constituée par une feuille ou lame métallique de faible épaisseur (quelques dixièmes de mm) qui est fixée à l'enveloppe 7 par exemple par des soudures continue ou bien par points (d'autres procédés comme le collage sont bien sûr possible). Comme on le voit sur la figure 2, chaque ailette métallique 8 comporte au niveau d'un de ses bords 8a un pied 8b qui est soudé à l'enveloppe. La feuille 8 est sensiblement perpendiculaire à son pied 8b une fois déployée.Each fin 8 is constituted by a sheet or metal blade of small thickness (a few tenths of a mm) which is fixed to the envelope 7 for example by continuous or spot welds (other processes such as gluing are of course possible. ). As we see on the figure 2 each metal fin 8 has at one of its edges 8a a foot 8b which is welded to the envelope. The sheet 8 is substantially perpendicular to its foot 8b once deployed.

Selon une caractéristique de l'invention, les ailettes 8 sont positionnées par rapport à l'enveloppe 7 de telle sorte que leur plan forme un angle α non nul avec l'axe 10 de l'enveloppe (donc avec une génératrice 12 de l'enveloppe comme visible à la figure 2).According to one characteristic of the invention, the fins 8 are positioned relative to the casing 7 so that that their plane forms a non-zero angle α with the axis 10 of the envelope (so with a generatrix 12 of the envelope as visible in FIG. figure 2 ).

Les ailettes 8 ne sont plus parallèles à l'axe 10 comme dans l'art antérieur mais inclinées. L'angle d'incidence α des ailettes 8 est par ailleurs orienté de telle sorte que l'écoulement aérodynamique E lors du vol balistique de l'enveloppe a pour effet en agissant sur les ailettes de générer une force de portance et donc un couple de roulis autour de l'axe 10. Ce couple est orienté à l'opposé de la rotation initiale et va donc freiner la rotation de l'enveloppe 7. L'angle d'incidence α est compris entre 5° et 10°.The fins 8 are no longer parallel to the axis 10 as in the prior art but inclined. The angle of incidence α of the fins 8 is also oriented so that the aerodynamic flow E during the ballistic flight of the envelope has the effect of acting on the fins to generate a lift force and therefore a couple of seconds. rolling around the axis 10. This torque is oriented opposite to the initial rotation and will therefore slow the rotation of the envelope 7. The angle of incidence α is between 5 ° and 10 °.

Les feuilles métalliques constituant les ailettes 8 sont donc fixées le long de lignes hélicoïdales 15a et 15b de l'enveloppe 7. L'angle d'incidence α étant le même au niveau de chaque ligne, ces lignes 15a,15b sont déduites les unes des autres par une rotation d'un angle donné autour de l'axe de l'enveloppe 7. On a représenté sur les figures une enveloppe dans laquelle les ailettes 8 sont fixées le long de deux lignes hélicoïdales (15a et 15b). Seule l'ailette 8 placée au niveau de la ligne 15a est représentée figure 2. Ces deux lignes sont déduites l'une de l'autre par une rotation de 180° autour de l'axe 10 de l'enveloppe.The metal foils constituting the fins 8 are thus fixed along helical lines 15a and 15b of the envelope 7. The angle of incidence α being the same at each line, these lines 15a, 15b are deduced one from the other. others by a rotation of a given angle around the axis of the casing 7. There is shown in the figures an envelope in which the fins 8 are fixed along two helical lines (15a and 15b). Only the fin 8 placed at the line 15a is shown figure 2 . These two lines are deduced from each other by a rotation of 180 ° around the axis 10 of the envelope.

Il serait bien entendu possible de définir une enveloppe dans laquelle les ailettes seraient fixées sur un nombre N de lignes hélicoïdales différent. Dans ce cas chaque ligne sera déduite de la précédente par une rotation d'angle égal à 2π/N. On pourra par exemple prévoir trois lignes hélicoïdales déduites les unes des autres par des rotations de 120° donc trois ailettes.It would of course be possible to define an envelope in which the fins would be fixed on a number N of helical lines different. In this case each line will be deduced from the previous one by a rotation of angle equal to 2π / N. It will be possible for example to provide three helical lines deduced from each other by rotations of 120 ° so three fins.

On pourra également prévoir quatre lignes hélicoïdales déduites les unes des autres par des rotations de 90° donc quatre ailettes. Le nombre et la surface des ailettes seront choisies en fonction de l'efficacité souhaitée pour le freinage.It will also be possible to provide four helical lines deduced from each other by rotations of 90 ° so four fins. The number and surface of the fins will be chosen according to the desired efficiency for braking.

La longueur des ailettes 8 pourra être inférieure à la longueur de l'enveloppe 7. Avantageusement, les ailettes seront alors positionnées de façon à augmenter la stabilité (la marge statique) de l'enveloppe 7. Les ailettes font alors également office d'empennage.The length of the fins 8 may be shorter than the length of the casing 7. Advantageously, the fins will then be positioned so as to increase the stability (the static margin) of the casing 7. The fins then also act as empennage .

Avec le dispositif selon l'invention, les ailettes 8 agissent sur l'enveloppe 7 à la fois par le freinage classique intrinsèque à leur géométrie (caractérisé par le coefficient d'amortissement de roulis Clp) et à la fois par le couple de roulis opposé à la rotation qui est induit par leur incidence α. Il en résulte un freinage en rotation beaucoup plus efficace.With the device according to the invention, the fins 8 act on the casing 7 at the same time by the conventional braking intrinsic to their geometry (characterized by the roll damping coefficient Clp) and by the opposite roll torque at the same time. to the rotation which is induced by their incidence α. This results in a much more efficient rotational braking.

Par ailleurs ce freinage en rotation est indépendant de la vitesse de rotation de l'enveloppe 7 puisque le couple engendré par les ailettes 8 est proportionnel au carré de la vitesse sur trajectoire de l'enveloppe. Cette vitesse reste toujours importante et de l'ordre de plusieurs dizaines de m/s.Furthermore, this rotational braking is independent of the rotational speed of the casing 7 since the torque generated by the fins 8 is proportional to the square of the path velocity of the casing. This speed is still important and of the order of several tens of m / s.

La figure 4 montre des courbes donnant les diminutions de la vitesse de rotation de l'enveloppe 6 en fonction du temps. la courbe 13 correspond à un dispositif de freinage selon l'art antérieur dans lequel les ailettes 8 sont fixées le long de génératrices parallèles à l'axe de l'enveloppe. La courbe 14 montre la caractéristique de freinage avec un dispositif selon l'invention (angle d'incidence α=5°), toutes choses égales par ailleurs et notamment les inerties de l'enveloppe 7, le nombre et la surface des ailettes 8.The figure 4 shows curves giving decreases in the speed of rotation of the envelope 6 as a function of time. the curve 13 corresponds to a braking device according to the prior art in which the fins 8 are fixed along generatrices parallel to the axis of the casing. Curve 14 shows the braking characteristic with a device according to the invention (angle of incidence α = 5 °), all things being equal and in particular the inertias of the casing 7, the number and the surface of the fins 8.

En considérant la courbe 13, on remarque que la vitesse de rotation de l'enveloppe s'annule théoriquement au bout d'un temps infini (la loi suivie est une loi exponentielle en Ω=Ω 0.e -kt). Concrètement avec un tel dispositif, on doit attendre une dizaine de secondes pour allumer la composition pyrotechnique éclairante disposée dans l'enveloppe (vitesse de rotation résiduelle de l'ordre de 4 à 5 tours /seconde) alors que la vitesse sur trajectoire optimale est atteinte pour réaliser le 2ème dépotage. Il y a donc un décalage entre les 2 freinages (le freinage en rotation et le freinage en translation de la charge utile) qui diminue l'efficacité opérationnelle du produit.Considering the curve 13, we note that the speed of rotation of the envelope is theoretically canceled after an infinite time (the law followed is an exponential law in Ω = Ω 0 .e - kt ). Concretely with such a device, one must wait ten seconds to light the composition illuminating pyrotechnic disposed in the casing (residual rotational speed of the order of 4 to 5 revolutions / second) while the speed on optimal trajectory is reached for carrying out the 2nd decanting. There is therefore a shift between the two braking operations (the rotational braking and the translational braking of the payload) which reduces the operational efficiency of the product.

En considérant la courbe 14 qui montre les effets du dispositif selon l'invention, on remarque que le freinage est beaucoup plus rapide et qu'il est possible d'annuler complètement la rotation ce qui permet de placer l'enveloppe dans des conditions optimales à l'instant de l'éjection de la charge utile 6.Considering the curve 14 which shows the effects of the device according to the invention, we note that the braking is much faster and it is possible to completely cancel the rotation which allows to place the envelope in optimal conditions to the moment of the ejection of the payload 6.

De plus, l'instant T où s'annule la vitesse de rotation peut être facilement ajusté en modifiant l'angle d'incidence des ailettes. La synchronisation des freinages s'en trouve donc facilitée.In addition, the moment T when the rotation speed is canceled can be easily adjusted by changing the angle of incidence of the fins. Braking synchronization is thus facilitated.

L'absence de rotation de la charge utile 6 permet de simplifier la conception du produit en supprimant l'émerillon reliant cette dernière à son parachute 9. Dans les projectiles selon l'art antérieur une vitesse de rotation résiduelle de 5 à 10 tours par seconde rendait indispensable un tel émerillon pour éviter l'entraînement en rotation du parachute 9 par la charge utile 6.The absence of rotation of the payload 6 makes it possible to simplify the design of the product by eliminating the swivel connecting the latter to its parachute 9. In the projectiles according to the prior art a residual rotational speed of 5 to 10 revolutions per second made such a swivel indispensable to avoid the rotation of the parachute 9 by the payload 6.

Dans l'exemple présenté, on voit que le délai pour annuler la rotation est donc divisé au minimum par deux à surfaces d'ailettes égales.In the example presented, we see that the delay to cancel the rotation is divided by at least two equal fin surfaces.

Ceci permet de concevoir un projectile à charge utile éclairante dans lequel l'allumage de la composition éclairante peut être initié beaucoup plus tôt ce qui permet d'augmenter la portée maxi de la zone éclairée.This makes it possible to design a projectile with illuminating payload in which the ignition of the illuminating composition can be initiated much earlier, which makes it possible to increase the maximum range of the illuminated area.

On remarque qu'au-delà de 5 secondes la vitesse de rotation de l'enveloppe 7 s'inverse en raison de l'inclinaison des ailettes 8. Ceci est sans importance pratique car l'Homme du Métier réglera l'instant T du point de rotation nulle à l'instant spécifié pour le 2ème dépotage et un écart de quelques secondes est acceptable car la vitesse de rotation inverse ne dépassera pas quelques tours par seconde en raison de la réduction de la vitesse sur trajectoire de l'enveloppe toujours freinée par parachute.Note that beyond 5 seconds the speed of rotation of the casing 7 is reversed due to the inclination of the fins 8. This is not important practical because the skilled person will adjust the instant T of the zero point of rotation at the time specified for the 2nd unloading and a difference of a few seconds is acceptable because the reverse speed of rotation will not exceed a few revolutions per second because of the reduction of the speed on the trajectory of the envelope always braked by parachute.

Même si le projectile ne comportait pas de phase d'extraction d'un pot éclairant, ce qui est le cas pour des calibres inférieurs (105 mm par exemple) pour lesquels la charge éclairante est directement logée dans l'enveloppe 7 (projectile à simple dépotage), la vitesse de rotation inverse demeure faible (inférieure à 5 tours/seconde) et ne gêne pas la combustion de la charge éclairante.Even if the projectile did not include an extraction phase of an illuminating pot, which is the case for lower calibers (105 mm for example) for which the illuminating charge is directly housed in the envelope 7 (single projectile removal), the reverse rotation speed remains low (less than 5 revolutions / second) and does not hinder the combustion of the illuminating charge.

Les figures 3a et 3b montrent en projection latérale et frontale l'enveloppe 7 équipée de ses ailettes 8. On a figuré en trait fin les traces en projection des lignes hélicoïdales 15a et 15b. Les ailettes 8 sont représentées repliées sur la figure 3a. Dans leur position déployée elles seraient parallèles à la ligne 15a ou 15b. On a aussi représenté à la figure 3a par des points 16 les soudures de chaque ailette 8 sur l'enveloppe 7 au niveau du pied 8b de l'ailette.The Figures 3a and 3b show in lateral and frontal projection the envelope 7 equipped with its fins 8. It has been shown in fine line the traces in projection of the helical lines 15a and 15b. The fins 8 are shown folded over the figure 3a . In their deployed position they would be parallel to line 15a or 15b. We also represented at figure 3a by points 16 the welds of each fin 8 on the casing 7 at the foot 8b of the fin.

On remarque que les ailettes 8 comportent des biseaux avant et arrière 18 (une telle disposition est classique).Note that the fins 8 comprise front and rear bevels 18 (such an arrangement is conventional).

Les ailettes 8 sont suffisamment minces (de l'ordre de 0,5mm d'épaisseur) pour suivre le profil du corps de l'enveloppe 7 lorsqu'elles sont repliées, même avec l'angle d'incidence prévu.The fins 8 are sufficiently thin (of the order of 0.5 mm thick) to follow the profile of the body of the casing 7 when folded, even with the expected angle of incidence.

Le dispositif selon l'invention est donc particulièrement simple et rustique.The device according to the invention is therefore particularly simple and rustic.

Différentes variantes sont possibles sans sortir du cadre de l'invention.Different variants are possible without departing from the scope of the invention.

On a vu qu'il était possible de répartir des ailettes suivant plus de 2 lignes hélicoïdales, par exemple trois ou quatre lignes.We have seen that it was possible to distribute fins in more than 2 helical lines, for example three or four lines.

On pourra aussi prévoir sur une même ligne hélicoïdale plusieurs ailettes successives fixées les unes derrière les autres.It will also be possible to provide on the same helical line several successive fins fixed one behind the other.

Il est également possible de définir un dispositif dans lequel les ailettes sont des ailettes rigides qui glissent radialement entre un logement interne à l'enveloppe 7 et l'extérieur. Dans ce cas il sera nécessaire de disposer à l'intérieur de l'enveloppe d'un volume suffisant pour loger les ailettes coulissantes.It is also possible to define a device in which the fins are rigid fins which slide radially between an inner housing to the casing 7 and the outside. In this case it will be necessary to have inside the envelope a sufficient volume to accommodate the sliding fins.

A titre d'exemple la figure 5 montre une enveloppe 7 qui comporte au niveau de chaque extrémité un dispositif de freinage qui comporte un boîtier 17 renfermant quatre ailettes rigides et coulissantes 8. Chaque ailette 8 est inclinée d'un angle α par rapport à l'axe 10 de l'enveloppe 7. Le boîtier comporte un logement interne qui reçoit les ailettes. Le boîtier constitue un moyen de solidarisation de l'enveloppe 7 et des ailettes.For example, figure 5 shows an envelope 7 which comprises at each end a braking device which comprises a housing 17 enclosing four rigid and sliding fins 8. Each fin 8 is inclined at an angle α with respect to the axis 10 of the envelope 7 The housing has an inner housing which receives the fins. The casing constitutes a means of securing the casing 7 and the fins.

Ces dernières sont positionnées dans des fentes de guidage 18 qui présentent l'inclinaison assurant l'angle d'incidence α.The latter are positioned in guide slots 18 which have the inclination providing the angle of incidence α.

Comme on le voit sur la coupe partielle représentée (sur la figure : ailette inférieure droite) chaque ailette comporte un talon 19 qui vient en butée contre la paroi du boîtier 15 et arrête son mouvement de sortie lors du déploiement des ailettes. L'ailette pourra se trouver bloquée dans cette position déployée par déformation mécanique ou grâce à un moyen de blocage fixé au boîtier 17 et s'engageant dans l'ailette (une lame anti retour par exemple).As seen in the partial section shown (in the figure: lower right fin) each fin has a heel 19 which abuts against the wall of the housing 15 and stops its movement of movement during the deployment of the fins. The fin may be locked in this deployed position by mechanical deformation or by a locking means attached to the housing 17 and engaging in the fin (an anti return blade for example).

Lorsque l'enveloppe 7 se trouve dans le corps de projectile, les ailettes 8 sont logées à l'intérieur de chaque boîtier. La force centrifuge provoque la sortie des ailettes lors de l'éjection de l'enveloppe 7 hors du corps de projectile. Les ailettes 8 assurent le freinage, comme expliqué précédemment, à la fois par l'augmentation du maître couple de l'enveloppe et par la rotation inverse provoquée par l'inclinaison des ailettes. Un dispositif annexe non représenté assurera l'éjection d'au moins un des boîtiers 17 pour permettre le moment voulu l'extraction de la charge utile hors de l'enveloppe 7.When the casing 7 is in the projectile body, the fins 8 are housed inside each casing. The centrifugal force causes the fins to exit when the casing 7 is ejected from the projectile body. The fins 8 provide braking, as explained above, both by increasing the master torque of the casing and by the opposite rotation caused by the inclination of the fins. An additional device not shown will ensure the ejection of at least one of the housings 17 to allow the desired moment the extraction of the payload out of the casing 7.

L'invention a été décrite dans son application à une charge utile éclairante. Il est bien entendu possible de mettre en oeuvre le dispositif de freinage selon l'invention pour un autre type de charge utile, par exemple un conteneur cargo transportant une charge électronique comme un relais de communication ou un moyen de brouillage.The invention has been described in its application to an illuminating payload. It is of course possible to implement the braking device according to the invention for another type of payload, for example a cargo container carrying an electronic load such as a communication relay or a scrambling means.

Claims (9)

Dispositif de freinage en rotation d'une enveloppe cylindrique (7) d'une charge utile (6) éjectée à partir d'un projectile gyrostabilisé, dispositif comprenant au moins deux ailettes (8) déployables régulièrement réparties angulairement sur une paroi externe de l'enveloppe (7), dispositif caractérisé en ce que les ailettes (8) sont positionnées par rapport à l'enveloppe (7) de telle sorte que leur plan forme, en position déployée, un angle (α) avec l'axe (10) de l'enveloppe (7), angle non nul et orienté de telle sorte que l'écoulement aérodynamique (E) au cours du vol de l'enveloppe (7) ait pour effet de freiner la rotation de cette dernière.Device for braking in rotation of a cylindrical envelope (7) with a payload (6) ejected from a gyro-stabilized projectile, device comprising at least two fins (8) deployable regularly distributed angularly on an outer wall of the casing (7), characterized in that the fins (8) are positioned relative to the casing (7) so that their plane forms, in the deployed position, an angle (α) with the axis (10) the casing (7), non-zero angle and oriented so that the aerodynamic flow (E) during the flight of the casing (7) has the effect of curbing the rotation of the latter. Dispositif de freinage en rotation selon la revendication 1, caractérisé en ce que les ailettes (8) sont formées par des feuilles métalliques fixées à la paroi de l'enveloppe (7) au niveau d'un de leur bord (8a).Rotational braking device according to claim 1, characterized in that the fins (8) are formed by metal sheets fixed to the wall of the casing (7) at one of their edges (8a). Dispositif de freinage en rotation selon la revendication 2, caractérisé en ce que chaque feuille métallique (8) est fixée le long d'une ligne hélicoïdale (15a,15b) de l'enveloppe (7), les différentes lignes hélicoïdales associées aux différentes ailettes (8) étant déduites les unes des autres par rotation autour de l'axe (10) de l'enveloppe (7).Rotational braking device according to claim 2, characterized in that each metal foil (8) is fixed along a helical line (15a, 15b) of the casing (7), the different helical lines associated with the different fins (8) being deduced from each other by rotation about the axis (10) of the casing (7). Dispositif de freinage en rotation selon la revendication 3, caractérisé en ce que l'enveloppe (7) porte des ailettes (8) fixées le long d'au moins deux lignes hélicoïdales (15a,15b).Rotational braking device according to claim 3, characterized in that the casing (7) carries fins (8) fixed along at least two helical lines (15a, 15b). Dispositif de freinage en rotation selon la revendication 4, caractérisé en ce que l'enveloppe (7) porte des ailettes (8) fixées le long de deux lignes hélicoïdales (15a,15b) déduites l'une de l'autre par rotation de 180° autour de l'axe (10) de l'enveloppe (7).Rotational braking device according to claim 4, characterized in that the casing (7) carries fins (8) fixed along two helical lines (15a, 15b) deduced from each other by rotation of 180 ° around the axis (10) of the envelope (7). Dispositif de freinage en rotation selon la revendication 1, caractérisé en ce que les ailettes (8) sont rigides et glissent radialement entre un logement interne à l'enveloppe (7) et l'extérieur de l'enveloppe.Rotational braking device according to claim 1, characterized in that the fins (8) are rigid and slide radially between a housing internal to the casing (7) and the outside of the casing. Dispositif de freinage en rotation selon la revendication 6, caractérisé en ce chaque ailette (8) comporte un talon (19) qui vient en butée contre une paroi d'un boîtier (17) renfermant les ailettes (8), talon arrêtant le mouvement de sortie de l'ailette (8) lors de son déploiement.Rotational braking device according to claim 6, characterized in that each fin (8) has a heel (19) which abuts against a wall of a housing (17) enclosing the fins (8), heel stopping the movement of exit of the fin (8) during its deployment. Projectile gyrostabilisé (1) éjectant une charge utile (6) sur trajectoire, projectile caractérisé en ce que la charge utile (6) ou une enveloppe (7) renfermant celle-ci est équipée d'un dispositif de freinage en rotation (8) selon une des revendications précédentes.Gyrostabilized projectile (1) ejecting a payload (6) on trajectory, projectile characterized in that the payload (6) or an envelope (7) enclosing it is equipped with a rotational braking device (8) according to one of the preceding claims. Projectile gyrostabilisé selon la revendication 8, caractérisé en ce que la charge utile (6) est une charge pyrotechnique éclairante.Gyro-stabilized projectile according to Claim 8, characterized in that the payload (6) is an illuminating pyrotechnic charge.
EP14187121.0A 2013-10-15 2014-09-30 Device for braking the rotation of a shell of a payload, and spin-stabilised projectile provided with such a device Active EP2863164B1 (en)

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FR1302413A FR3011919B1 (en) 2013-10-15 2013-10-15 BRAKING DEVICE FOR ROTATING AN ENVELOPE OF A USEFUL LOAD, AND GYROSTABILIZED PROJECTILE EQUIPPED WITH SUCH A DEVICE

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018229092A1 (en) 2017-06-14 2018-12-20 Nexter Munitions Aerodynamic braking device for a payload casing
SE2000241A1 (en) * 2020-12-18 2022-06-19 Bae Systems Bofors Ab Canister

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3047306B1 (en) * 2016-01-28 2019-04-05 Nexter Munitions CYLINDRICAL ENVELOPE FOR USEFUL LOAD
US20230296361A1 (en) * 2022-03-21 2023-09-21 Hazim Mohaisen System and method for end to end transport delivery

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2260772A1 (en) 1974-02-08 1975-09-05 France Etat
EP0066715A2 (en) * 1981-06-05 1982-12-15 Hüls Troisdorf Aktiengesellschaft Spin-stabilised training projectile
EP0466499A1 (en) 1990-07-13 1992-01-15 Royal Ordnance Plc Projectile surveillance apparatus
US5684267A (en) 1997-02-04 1997-11-04 The United States Of Americas As Represented By The Secretary Of The Army Resupply projectile
WO2007030687A2 (en) * 2005-09-09 2007-03-15 General Dynamics Ordnance And Tactical Systems Projectile trajectory control system

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2260772A1 (en) 1974-02-08 1975-09-05 France Etat
EP0066715A2 (en) * 1981-06-05 1982-12-15 Hüls Troisdorf Aktiengesellschaft Spin-stabilised training projectile
EP0466499A1 (en) 1990-07-13 1992-01-15 Royal Ordnance Plc Projectile surveillance apparatus
US5684267A (en) 1997-02-04 1997-11-04 The United States Of Americas As Represented By The Secretary Of The Army Resupply projectile
WO2007030687A2 (en) * 2005-09-09 2007-03-15 General Dynamics Ordnance And Tactical Systems Projectile trajectory control system

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018229092A1 (en) 2017-06-14 2018-12-20 Nexter Munitions Aerodynamic braking device for a payload casing
US11326862B2 (en) 2017-06-14 2022-05-10 Nexter Munitions Aerodynamic braking device for a payload casing
SE2000241A1 (en) * 2020-12-18 2022-06-19 Bae Systems Bofors Ab Canister
WO2022132005A1 (en) * 2020-12-18 2022-06-23 Bae Systems Bofors Ab Canister and method for distributing submunitions

Also Published As

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FR3011919B1 (en) 2017-05-19
ES2710151T3 (en) 2019-04-23
TR201903273T4 (en) 2019-03-21
EP2863164B1 (en) 2018-12-05
PL2863164T3 (en) 2019-05-31
FR3011919A1 (en) 2015-04-17

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