EP2921812B1 - Spin-stabilised projectile - Google Patents

Spin-stabilised projectile Download PDF

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Publication number
EP2921812B1
EP2921812B1 EP15152943.5A EP15152943A EP2921812B1 EP 2921812 B1 EP2921812 B1 EP 2921812B1 EP 15152943 A EP15152943 A EP 15152943A EP 2921812 B1 EP2921812 B1 EP 2921812B1
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EP
European Patent Office
Prior art keywords
projectile
balls
ring
groove
stop surface
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EP15152943.5A
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German (de)
French (fr)
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EP2921812A1 (en
Inventor
M Richard Roy
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Nexter Munitions SA
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Nexter Munitions SA
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Publication of EP2921812A1 publication Critical patent/EP2921812A1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/26—Stabilising arrangements using spin

Definitions

  • the technical field of the invention is that of the gyro-stabilized projectiles comprising at least two neighboring parts intended to rotate at different roll speeds, as for example described in the publication US 2008/315032 A1 .
  • the longitudinal stabilization of a large caliber projectile is conventionally obtained by rolling the projectile about its longitudinal axis. Such rotation is achieved by driving the projectile with helical grooves located in the launcher tube.
  • Modern projectiles include means for guiding or increasing the range, such as control surfaces and vanes, which hardly accommodate the high speeds of roll rotation of the projectile due to the aerodynamic opposition of these planes to the rotation.
  • the warhead has control surfaces.
  • the body is called to rotate at a high speed of the order of 200 to 400 revolutions per second while the warhead must not or little rotate in an absolute reference system.
  • To operate the decoupling in rotation between the nose and the body it is known to use ball bearings at the interface between body and warhead.
  • the acceleration is so violent that the bearing surfaces of the balls wedged between warhead and body are often deformed by the contact pressure, which does not allow a satisfactory operation of the bearing. ball during the flight phase.
  • the firing acceleration leads to a deformation of the rolling tracks of the balls which interferes with the correct operation of the decoupling in rotation during the flight.
  • the invention proposes to solve this problem of degradation of the decoupling means on the gyro-stabilized projectiles comprising a part detachable in rotation.
  • the angle between the conical surface and a plane perpendicular to the axis of the projectile is greater than 0.001 degree.
  • a plurality of housings are distributed radially equally around the ring thus forming a ball bearing cage.
  • the detachable portion may be constituted by a ring having deployable fins.
  • the abutment surface of the body will then be formed by a surface of a base disposed behind the body and carrying a sealing belt.
  • the detachable portion may be constituted by an ogive of the projectile comprising control surfaces.
  • a projectile 1 comprises a body ogivé 3 surrounded by a ring 100.
  • the body 3 has in its rear part a base 2.
  • the ring 100 is a part of the projectile which is detachable in rotation relative to the body 3 and has fins deployable 4 located in the vicinity of the base 2. Outside the flight phases of the projectile 1, the fins 4 are folded into the housings 6 of the ring 100 and thus adopt a non-represented folded position that they occupy during the storage phases of the projectile 1 and during gunfire.
  • the base 2 is surrounded by a belt 5.
  • This belt 5 is intended to engage in helical grooves of a weapon tube (tube and grooves not shown) to communicate a rotational movement in roll around the longitudinal axis 7 of the projectile 1, during the firing phase of the projectile 1. This phase extends from the departure of the projectile 1 to its exit from the tube.
  • the projectile receives a sudden thrust on the rear face AR of the base 2 which causes a longitudinal acceleration of the projectile throughout the phase in question.
  • the projectile 1 is in so-called flight phase until it reaches the goal.
  • the projectile is in barrel firing phase, the fins 4 are folded integrally in the housings 6 of the ring 100 (ring not visible at the figure 3 ).
  • the front portion AV of the body 3 comprises an elongated and threaded portion 3a corresponding to a tapping 2a of the base 2.
  • the ring 100 has an annular surface 9 (visible surface at the figure 2 ) transverse to the projectile 1 and directed towards the rear AR.
  • This surface 9 is intended to serve as a rolling surface for balls 12 in flight phase.
  • the base 2 further comprises a bearing surface 10 which is located facing the bearing surface 9 of the body at the joint 8 between the ring 100 and the base 2.
  • the bearing surface forms a ring abutment surface 10 .
  • the bearing surface 9 is, during the firing phase, bearing on the abutment surface 10.
  • the base 2 comprises, at its bearing surface and delimited by two annular partitions 101a and 101b, a conical groove 101 intended to contain a ring 102 having housings 11 intended to each contain a ball 12.
  • Each ball housing 12 extends radially and is traversed relative to each of the faces of the ring.
  • Each housing 11 of the ring 102 thus comprises a pair radial partitions capable of holding the balls by the side walls of the housing 11.
  • the ring 102 has in its central part a solid annular zone 102a coaxial with the projectile and able to rotate around the central wall 101a of the groove 101.
  • the ring 102 thus constitutes a ball bearing cage allowing the balls to roll on the conical surface 13 of the bottom of the groove 101.
  • the conical surface 13 of the bottom of the groove 101 has its deepest part located towards the axis. 7 of the projectile and the shallower part towards the outside of the projectile.
  • the cross section of the ring preferably corresponds to the conical surface 13 of the groove 101 in order to be able to guide the balls 12 laterally throughout their radial movements on this conical surface 13.
  • the conicity of the conical surface 13 and the diameter of the balls 12 are chosen such that, when the balls 12 are placed at the most axial ends of their housings 11 (closest to the axis 7 of the projectile), the balls are fully in the throat 101.
  • the ring 100 (detachable part) is then in abutment against the abutment surface 10 of the base via its rolling surface 9.
  • the depth P of the groove 101 is greater than the diameter of the balls when the balls are at the end of their housing closest to the axis 7 of the projectile.
  • This depth P is greater than the diameter of a ball 12 so that the bearing surface 9 can bear against the abutment surface 10 of the base during the firing phase.
  • all the balls 12 are located in the part of their housing 11 closest to the axis 7 of the projectile, the deepest part of the groove 101.
  • the conical surface of the groove 13 forms an angle with a plane perpendicular to the axis of the projectile which is greater than 0.001 °.
  • the projectile 1 is in flight phase. Stopping the axial acceleration of the projectile decreases the bearing force of the ring 100 on its abutment surface 10.
  • a clearance J is thus created at the joint 8 between the ring 100 and the base 2.
  • This depth p is smaller than the diameter D of a ball 12.
  • Each ball 12 is then bearing on the bearing surface 9 of the body 3 on the one hand and on the conical face 13 of the groove 101 on the other hand.
  • the balls 12 rotate on themselves in the housings 11 and thus run through the tread 9, the assembly forming a ball bearing which prevents friction between the ring 100 and base 2.
  • the invention allows the use of ball bearings for decoupling in rotation a ring 100 carrying fins and a projectile body 3 in flight without degrading the ball bearing during the firing phase of the projectile.
  • the fins 4 of the ring are deployed by an actuator not shown at a given moment on the trajectory of the projectile and as a function of the trajectory correction needs of the projectile considered.
  • the fins will make it possible, at a given moment, to correct horizontal deflection of the trajectory of the projectile as described, for example, by the patent. EP884554 .
  • the decoupling in rotation between the ring and the projectile body will allow braking of the ring without impairing the gyrostabilization.
  • the means of the invention can also be implemented to ensure a rotational decoupling of an ogive relative to the body of the projectile as described by FR2980842 and as shown in figure 6 where the ogive 100 is free to rotate relative to the body 3 along the longitudinal axis 7 by means of a needle bearing 21 and a ring 102 having balls 12 as for the embodiment described above.
  • the detachable portion will be constituted by the warhead 100 of the projectile which will include control surfaces 20.
  • the abutment surface 10 will be formed by a surface of the projectile body 3 located directly behind the detachable warhead 100.

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

Description

Le domaine technique de l'invention est celui des projectiles gyrostabilisés comportant au moins deux parties voisines destinées à tourner à des vitesses de roulis différentes, tel que par exemple décrit dans la publication US 2008/315032 A1 .The technical field of the invention is that of the gyro-stabilized projectiles comprising at least two neighboring parts intended to rotate at different roll speeds, as for example described in the publication US 2008/315032 A1 .

La stabilisation longitudinale d'un projectile de gros calibre est classiquement obtenue par la mise en roulis du projectile autour de son axe longitudinal. Une telle mise en rotation est obtenue en entraînant le projectile avec des rainures hélicoïdales situées dans le tube lanceur. Les projectiles modernes comportent des moyens de guidage ou d'augmentation de la portée, tels que des gouvernes et des ailettes, qui s'accommodent difficilement des vitesses élevées de rotation en roulis du projectile du fait de l'opposition aérodynamique de ces plans à la rotation.The longitudinal stabilization of a large caliber projectile is conventionally obtained by rolling the projectile about its longitudinal axis. Such rotation is achieved by driving the projectile with helical grooves located in the launcher tube. Modern projectiles include means for guiding or increasing the range, such as control surfaces and vanes, which hardly accommodate the high speeds of roll rotation of the projectile due to the aerodynamic opposition of these planes to the rotation.

Il est connu par le brevet FR2980842 un projectile comportant une ogive de guidage disposée devant un corps gyrostabilisé, ogive et corps pouvant tourner l'un par rapport à l'autre. L'ogive comporte des gouvernes. Le corps est appelé à tourner à une vitesse importante de l'ordre de 200 à 400 tours par secondes alors que l'ogive ne doit pas ou peu tourner dans un référentiel absolu. Pour opérer le découplage en rotation entre l'ogive et le corps, il est connu d'employer des roulements à billes à l'interface entre corps et ogive. Cependant, durant la phase de poussée du projectile, l'accélération est tellement violente que les portées de roulement des billes coincées entre ogive et corps sont souvent déformées par la pression de contact, ce qui ne permet pas d'avoir un fonctionnement satisfaisant du roulement à billes pendant la phase de vol.He is known by the patent FR2980842 a projectile comprising a guide ogive disposed in front of a gyrostabilized body, ogive and body rotatable relative to each other. The warhead has control surfaces. The body is called to rotate at a high speed of the order of 200 to 400 revolutions per second while the warhead must not or little rotate in an absolute reference system. To operate the decoupling in rotation between the nose and the body, it is known to use ball bearings at the interface between body and warhead. However, during the thrust phase of the projectile, the acceleration is so violent that the bearing surfaces of the balls wedged between warhead and body are often deformed by the contact pressure, which does not allow a satisfactory operation of the bearing. ball during the flight phase.

Il est aussi connu de réaliser des projectiles dans lesquels on dispose des ailettes déployables solidaires d'une bague qui est libre en rotation par rapport au corps du projectile.It is also known to produce projectiles in which deployable vanes integral with a ring which is free in rotation relative to the body of the projectile.

Ces ailettes sont déployées à un instant donné sur trajectoire à l'aide d'un actionneur commandable par la fusée du projectile. Elles permettent d'assurer une correction de la déviation horizontale du projectile. Ce mécanisme de correction est décrit en détails par le brevet EP884554 .These fins are deployed at a given moment on trajectory with the aid of an actuator controllable by the rocket of the projectile. They make it possible to ensure a correction of the horizontal deflection of the projectile. This correction mechanism is described in detail by the patent EP884554 .

Pour ces projectiles également, l'accélération de tir conduit à une déformation des pistes de roulement des billes ce qui nuit au fonctionnement correct du découplage en rotation lors du vol.For these projectiles also, the firing acceleration leads to a deformation of the rolling tracks of the balls which interferes with the correct operation of the decoupling in rotation during the flight.

L'invention propose de résoudre ce problème de dégradation des moyens de découplage sur les projectiles gyrostabilisés comportant une partie désolidarisable en rotation.The invention proposes to solve this problem of degradation of the decoupling means on the gyro-stabilized projectiles comprising a part detachable in rotation.

Ainsi, l'invention porte sur un projectile gyrostabilisé comportant un corps et au moins une partie désolidarisable en rotation par rapport au corps, projectile caractérisé en ce que :

  • la partie désolidarisable est apte à se mouvoir longitudinalement par rapport au corps avec un jeu axial, jusqu'à venir en appui contre une surface de butée du corps, la partie désolidarisable pouvant tourner, lorsqu'elle n'est pas en appui contre sa surface de butée, par rapport au corps autour de l'axe longitudinal de roulis du projectile et comportant au moins une surface circulaire transversale au projectile et orientée vers l'arrière et apte à servir de portée de roulement pour des billes,
  • la surface de butée située en regard de la portée de roulement de la partie désolidarisable comporte une gorge annulaire recevant un anneau comportant au moins trois logements destinés à contenir chacun une bille, logements s'étendant radialement vers l'extérieur de l'anneau et débouchant sur chaque face de celui-ci, le fond de la gorge comportant une surface conique dont la plus grande profondeur relativement à la surface de butée est située vers l'axe du projectile, la conicité de cette surface et le diamètre des billes étant choisis tels que, lorsque les billes sont placées au niveau de l'extrémité la plus axiale de leur logement, les billes sont entièrement dans la gorge et la partie désolidarisable est en appui contre sa surface de butée et lorsque les billes sont placées à l'extrémité la plus externe de leur logement les billes sortent partiellement de la gorge et sont en appui contre la portée de roulement.
Thus, the invention relates to a gyro-stabilized projectile comprising a body and at least one part that is detachable in rotation relative to the body, a projectile characterized in that:
  • the detachable part is able to move longitudinally with respect to the body with an axial clearance, until it bears against an abutment surface of the body, the detachable part being rotatable when it is not resting against its surface abutment, with respect to the body about the longitudinal axis of roll of the projectile and having at least one circular surface transverse to the projectile and oriented rearwardly and adapted to serve as a bearing surface for balls,
  • the abutment surface facing the rolling surface of the separable portion comprises an annular groove receiving a ring having at least three housings each for holding a ball, housing extending radially outwardly of the ring and opening on each side of it, the back of the throat having a conical surface whose greatest depth relative to the abutment surface is located towards the axis of the projectile, the conicity of this surface and the diameter of the balls being chosen such that, when the balls are placed at the end the most axial of their housing, the balls are entirely in the groove and the releasable portion bears against its abutment surface and when the balls are placed at the outermost end of their housing the balls partially leave the groove and are in support against the rolling range.

Avantageusement, l'angle entre la surface conique et un plan perpendiculaire à l'axe du projectile est supérieur à 0.001 degré.Advantageously, the angle between the conical surface and a plane perpendicular to the axis of the projectile is greater than 0.001 degree.

Avantageusement, une multitude de logements sont répartis radialement de manière égale autour de l'anneau formant ainsi une cage de roulement à billes.Advantageously, a plurality of housings are distributed radially equally around the ring thus forming a ball bearing cage.

Selon un mode de réalisation, la partie désolidarisable pourra être constituée par une bague comportant des ailettes déployables.According to one embodiment, the detachable portion may be constituted by a ring having deployable fins.

La surface de butée du corps sera alors formée par une surface d'un culot disposé en arrière du corps et portant une ceinture d'étanchéité.The abutment surface of the body will then be formed by a surface of a base disposed behind the body and carrying a sealing belt.

Selon un autre mode de réalisation, la partie désolidarisable pourra être constituée par une ogive du projectile comportant des gouvernes de pilotage.According to another embodiment, the detachable portion may be constituted by an ogive of the projectile comprising control surfaces.

L'invention sera mieux comprise à la lecture de la description suivante, description faite en référence aux dessins en annexe, dessins dans lesquels :

  • La figure 1 représente une vue en coupe longitudinale d'un projectile selon un mode de réalisation de l'invention en position de vol.
  • La figure 2 représente une vue de détail en coupe longitudinale du projectile selon ce mode de réalisation, en phase de tir canon.
  • La figure 3 représente une vue de détail partielle de ce projectile en phase de tir canon, et avec la bague retirée.
  • La figure 4 représente une vue de détail en coupe longitudinale de ce même mode de réalisation d'un projectile selon l'invention en phase de vol.
  • La figure 5 est une vue analogue à la figure 3, en phase de vol.
  • La figure 6 représente une vue de détail en coupe longitudinale d'un projectile selon un autre mode de réalisation de l'invention.
The invention will be better understood on reading the following description, description made with reference to the appended drawings, drawings in which:
  • The figure 1 is a longitudinal sectional view of a projectile according to an embodiment of the invention in flight position.
  • The figure 2 is a detail view in longitudinal section of the projectile according to this embodiment, in the barrel firing phase.
  • The figure 3 represents a partial detail view of this projectile in the barrel firing phase, and with the ring removed.
  • The figure 4 is a detail view in longitudinal section of the same embodiment of a projectile according to the invention in flight phase.
  • The figure 5 is a view similar to the figure 3 , in phase of flight.
  • The figure 6 is a detail view in longitudinal section of a projectile according to another embodiment of the invention.

Selon la figure 1, un projectile 1 comporte un corps ogivé 3 entouré par une bague 100. Le corps 3 comporte dans sa partie arrière un culot 2. La bague 100 constitue une partie du projectile qui est désolidarisable en rotation par rapport au corps 3 et elle comporte des ailettes déployables 4 situées au voisinage du culot 2. En dehors des phases de vol du projectile 1, les ailettes 4 sont repliées dans des logements 6 de la bague 100 et adoptent ainsi une position repliée non représentée qu'elles occupent lors des phases de stockage du projectile 1 et lors du tir canon.According to figure 1 , a projectile 1 comprises a body ogivé 3 surrounded by a ring 100. The body 3 has in its rear part a base 2. The ring 100 is a part of the projectile which is detachable in rotation relative to the body 3 and has fins deployable 4 located in the vicinity of the base 2. Outside the flight phases of the projectile 1, the fins 4 are folded into the housings 6 of the ring 100 and thus adopt a non-represented folded position that they occupy during the storage phases of the projectile 1 and during gunfire.

Le culot 2 est entouré par une ceinture 5. Cette ceinture 5 est destinée à s'engager dans des rainures hélicoïdales d'un tube d'arme (tube et rainures non représentées) afin de communiquer un mouvement de rotation en roulis autour de l'axe longitudinal 7 du projectile 1, lors de la phase de tir canon du projectile 1. Cette phase s'étend depuis le départ du projectile 1 jusqu'à sa sortie du tube.The base 2 is surrounded by a belt 5. This belt 5 is intended to engage in helical grooves of a weapon tube (tube and grooves not shown) to communicate a rotational movement in roll around the longitudinal axis 7 of the projectile 1, during the firing phase of the projectile 1. This phase extends from the departure of the projectile 1 to its exit from the tube.

Durant cette phase, le projectile reçoit une poussée brutale sur la face arrière AR du culot 2 qui provoque une accélération longitudinale du projectile durant toute la phase en question. A la sortie du tube, le projectile 1 est en phase dite de vol jusqu'à son arrivée au but visé.During this phase, the projectile receives a sudden thrust on the rear face AR of the base 2 which causes a longitudinal acceleration of the projectile throughout the phase in question. At the exit of the tube, the projectile 1 is in so-called flight phase until it reaches the goal.

Durant la phase de vol il n'est plus soumis à la poussée des gaz et subit une décélération progressive et poursuit sa trajectoire par inertie. On notera que le culot 2 et la bague 100 sont voisins au niveau d'une jointure 8 qui sera mieux vue aux figures suivantes.During the flight phase it is no longer subject to thrust and undergoes a gradual deceleration and continues its trajectory by inertia. Note that the base 2 and the ring 100 are neighbors at a joint 8 which will be better seen in the following figures.

Selon les figures 2 et 3, le projectile est en phase de tir canon, les ailettes 4 sont repliées intégralement dans les logements 6 de la bague 100 (bague non visible à la figure 3). La partie avant AV du corps 3 comporte une portion allongée et filetée 3a correspondant avec un taraudage 2a du culot 2.According to figures 2 and 3 , the projectile is in barrel firing phase, the fins 4 are folded integrally in the housings 6 of the ring 100 (ring not visible at the figure 3 ). The front portion AV of the body 3 comprises an elongated and threaded portion 3a corresponding to a tapping 2a of the base 2.

Ces deux formes 2a et 3a sont concentriques relativement à l'axe longitudinal de roulis 7 et solidaires l'une de l'autre. La bague 100 comporte une surface annulaire 9 (surface visible à la figure 2) transversale au projectile 1 et orientée vers l'arrière AR.These two forms 2a and 3a are concentric with respect to the longitudinal axis of roll 7 and integral with each other. The ring 100 has an annular surface 9 (visible surface at the figure 2 ) transverse to the projectile 1 and directed towards the rear AR.

Cette surface 9 est destinée à servir de portée de roulement pour des billes 12 en phase de vol.This surface 9 is intended to serve as a rolling surface for balls 12 in flight phase.

Le culot 2 comporte par ailleurs une surface d'appui 10 qui est située en regard de la portée de roulement 9 du corps au niveau de la jointure 8 entre bague 100 et culot 2. La surface d'appui forme une surface de butée 10 annulaire.The base 2 further comprises a bearing surface 10 which is located facing the bearing surface 9 of the body at the joint 8 between the ring 100 and the base 2. The bearing surface forms a ring abutment surface 10 .

La portée de roulement 9 est, en phase de tir canon, en appui sur la surface de butée 10.The bearing surface 9 is, during the firing phase, bearing on the abutment surface 10.

Le culot 2 comporte, au niveau de sa surface d'appui et délimitée par deux cloisons annulaires 101a et 101b, une gorge conique 101 destinée à contenir un anneau 102 comportant des logements 11 destinés à contenir chacun une bille 12.The base 2 comprises, at its bearing surface and delimited by two annular partitions 101a and 101b, a conical groove 101 intended to contain a ring 102 having housings 11 intended to each contain a ball 12.

Chaque logement 11 de bille 12 s'étend radialement et il est traversant relativement à chacune des faces de l'anneau. Chaque logement 11 de l'anneau 102 comporte ainsi une paire de cloisons radiales aptes à retenir les billes par les parois latérales des logements 11.Each ball housing 12 extends radially and is traversed relative to each of the faces of the ring. Each housing 11 of the ring 102 thus comprises a pair radial partitions capable of holding the balls by the side walls of the housing 11.

L'anneau 102 comporte dans sa partie centrale une zone annulaire pleine 102a coaxiale au projectile et apte à tourner autour de la paroi centrale 101a de la gorge 101.The ring 102 has in its central part a solid annular zone 102a coaxial with the projectile and able to rotate around the central wall 101a of the groove 101.

L'anneau 102 constitue ainsi une cage de roulement à billes permettant aux billes de rouler sur la surface conique 13 du fond de la gorge 101. La surface conique 13 du fond de la gorge 101 a sa partie la plus profonde située vers l'axe 7 du projectile et la partie la moins profonde vers l'extérieur du projectile. La section transversale de l'anneau correspond préférentiellement avec la surface conique 13 de la gorge 101 pour pouvoir guider latéralement les billes 12 tout au long de leurs mouvements radiaux sur cette surface conique 13.The ring 102 thus constitutes a ball bearing cage allowing the balls to roll on the conical surface 13 of the bottom of the groove 101. The conical surface 13 of the bottom of the groove 101 has its deepest part located towards the axis. 7 of the projectile and the shallower part towards the outside of the projectile. The cross section of the ring preferably corresponds to the conical surface 13 of the groove 101 in order to be able to guide the balls 12 laterally throughout their radial movements on this conical surface 13.

La conicité de la surface conique 13 et le diamètre des billes 12 sont choisis tels que, lorsque les billes 12 sont placées au niveau des extrémités les plus axiales de leurs logements 11 (les plus proches de l'axe 7 du projectile), les billes sont entièrement dans la gorge 101.The conicity of the conical surface 13 and the diameter of the balls 12 are chosen such that, when the balls 12 are placed at the most axial ends of their housings 11 (closest to the axis 7 of the projectile), the balls are fully in the throat 101.

La bague 100 (partie désolidarisable) est alors en appui contre la surface de butée 10 du culot via sa portée de roulement 9.The ring 100 (detachable part) is then in abutment against the abutment surface 10 of the base via its rolling surface 9.

Lorsque les billes 12 sont placées au niveau des extrémités les plus externes de leurs logements, les billes 12 sortent partiellement de la gorge 101 et elles sont en appui contre la portée de roulement 9.When the balls 12 are placed at the outermost ends of their housings, the balls 12 partially leave the groove 101 and they bear against the bearing surface 9.

Ainsi la profondeur P de la gorge 101 est supérieure au diamètre des billes lorsque les billes se situent à l'extrémité de leurs logements la plus proche de l'axe 7 du projectile.Thus the depth P of the groove 101 is greater than the diameter of the balls when the balls are at the end of their housing closest to the axis 7 of the projectile.

Cette profondeur P est supérieure au diamètre d'une bille 12 de manière à ce que la portée 9 puisse être en appui sur la surface de butée 10 du culot en phase de tir canon.This depth P is greater than the diameter of a ball 12 so that the bearing surface 9 can bear against the abutment surface 10 of the base during the firing phase.

Ainsi, durant cette phase, les billes 12 ne sont pas en appui avec la portée 9 et elles ne peuvent pas détériorer celle-ci.Thus, during this phase, the balls 12 are not supported with the scope 9 and they can not damage it.

Comme on peut le voir à la figure 3, toutes les billes 12 sont situées dans la partie de leur logement 11 la plus proche de l'axe 7 du projectile, partie la plus profonde de la gorge 101.As can be seen at figure 3 , all the balls 12 are located in the part of their housing 11 closest to the axis 7 of the projectile, the deepest part of the groove 101.

La surface conique de la gorge 13 forme un angle avec un plan perpendiculaire à l'axe du projectile qui est supérieur à 0.001°.The conical surface of the groove 13 forms an angle with a plane perpendicular to the axis of the projectile which is greater than 0.001 °.

Selon les figures 4 et 5, le projectile 1 est en phase de vol. L'arrêt de l'accélération axiale du projectile diminue l'effort d'appui de la bague 100 sur sa surface de butée 10.According to figures 4 and 5 , the projectile 1 is in flight phase. Stopping the axial acceleration of the projectile decreases the bearing force of the ring 100 on its abutment surface 10.

Parallèlement la force centrifuge subie par les billes 12, du fait de la giration du culot 2, va provoquer un mouvement des billes 12 vers l'extérieur du culot 2 au sein des logements 11 et donc le déplacement longitudinal de la bague 100 relativement au corps 3.At the same time, the centrifugal force experienced by the balls 12, because of the gyration of the base 2, will cause the balls 12 to move towards the outside of the base 2 within the housings 11 and thus the longitudinal displacement of the ring 100 relative to the body 3.

Il se crée ainsi un jeu J au niveau de la jointure 8 entre bague 100 et culot 2. Une fois à l'extrémité externe de leurs logements 11, les billes 12 sont dans la zone de plus faible profondeur p de la gorge 101.A clearance J is thus created at the joint 8 between the ring 100 and the base 2. Once at the outer end of their housings 11, the balls 12 are in the zone of shallower depth p of the groove 101.

Cette profondeur p est inférieure au diamètre D d'une bille 12. Chaque bille 12 est alors en appui sur la portée 9 du corps 3 d'une part et sur la face conique 13 de la gorge 101 d'autre part. Les billes 12 tournent sur elles-mêmes dans les logements 11 et parcourent ainsi la bande de roulement 9, l'ensemble formant un roulement à billes qui évite les frottements entre bague 100 et culot 2.This depth p is smaller than the diameter D of a ball 12. Each ball 12 is then bearing on the bearing surface 9 of the body 3 on the one hand and on the conical face 13 of the groove 101 on the other hand. The balls 12 rotate on themselves in the housings 11 and thus run through the tread 9, the assembly forming a ball bearing which prevents friction between the ring 100 and base 2.

On voit sur la figure 5 que toutes les billes 12 sont situées aux extrémités des logements 11 situées les plus vers l'extérieur du projectile.We see on the figure 5 that all the balls 12 are located at the ends of the housing 11 located towards the outside of the projectile.

On voit donc que l'invention permet l'usage de roulements à billes pour découpler en rotation une bague 100 portant des ailettes et un corps 3 de projectile 1 en vol sans dégrader le roulement à billes pendant la phase de tir du projectile.It can thus be seen that the invention allows the use of ball bearings for decoupling in rotation a ring 100 carrying fins and a projectile body 3 in flight without degrading the ball bearing during the firing phase of the projectile.

Les ailettes 4 de la bague sont déployées par un actionneur non représenté à un instant donné sur la trajectoire du projectile et en fonction des besoins de correction de trajectoire du projectile considéré.The fins 4 of the ring are deployed by an actuator not shown at a given moment on the trajectory of the projectile and as a function of the trajectory correction needs of the projectile considered.

Les ailettes permettront d'assurer à un instant choisi une correction en déviation horizontale de la trajectoire du projectile comme décrit par exemple par le brevet EP884554 .The fins will make it possible, at a given moment, to correct horizontal deflection of the trajectory of the projectile as described, for example, by the patent. EP884554 .

Le déploiement des ailettes sera assuré par la force centrifuge due à la rotation du projectile autour de son axe de roulis 7.The deployment of the fins will be ensured by the centrifugal force due to the rotation of the projectile around its axis of roll 7.

Le découplage en rotation entre la bague et le corps de projectile permettra le freinage de la bague sans nuire à la gyrostabilisation.The decoupling in rotation between the ring and the projectile body will allow braking of the ring without impairing the gyrostabilization.

Les moyens de l'invention peuvent aussi être mis en oeuvre pour assurer un découplage en rotation d'une ogive par rapport au corps du projectile tel que décrit par FR2980842 et tel que représenté à la figure 6 où l'ogive 100 est libre de tourner relativement au corps 3 selon l'axe longitudinal 7 grâce à un roulement à aiguilles 21 et à un anneau 102 comportant des billes 12 comme pour le mode de réalisation précédemment décrit.The means of the invention can also be implemented to ensure a rotational decoupling of an ogive relative to the body of the projectile as described by FR2980842 and as shown in figure 6 where the ogive 100 is free to rotate relative to the body 3 along the longitudinal axis 7 by means of a needle bearing 21 and a ring 102 having balls 12 as for the embodiment described above.

Dans ce cas la partie désolidarisable sera constituée par l'ogive 100 du projectile qui comportera des gouvernes de pilotage 20. La surface de butée 10 sera formée par une surface du corps 3 de projectile située directement derrière l'ogive désolidarisable 100.In this case the detachable portion will be constituted by the warhead 100 of the projectile which will include control surfaces 20. The abutment surface 10 will be formed by a surface of the projectile body 3 located directly behind the detachable warhead 100.

Claims (6)

  1. A gyrostabilized projectile (1) comprising a body and at least one part (100) separable in rotation with respect to the body (3), such that:
    the separable part (100) is able to longitudinally move with respect to the body (3) with an axial clearance (J), until abutting against a stop surface (10) of the body (3), wherein the separable part (100) can rotate, when it does not abut against the stop surface thereof, with respect to the body (3) around the longitudinal axis (7) of roll of the projectile (1) and comprising at least one circular surface (9) transverse to the projectile (1) and directed rearwards and able to act as a ball bearing seat (9) for balls (12),
    the stop surface (10) located opposite the ball bearing seat (9) of the separable part (100) comprises an annular groove (101), the projectile (1) being characterized in that said annular groove (101) receives a ring (102) having at least three housings (11) each intended to hold a ball (12), the housings (11) radially extending towards the exterior of the ring (102) and opening on each face thereof, the bottom of the groove (101) comprising a conical surface (13) the greatest depth (P) of which, with respect to the stop surface (10), is located towards the axis (7) of the projectile (1), the taper of this surface (13) and the diameter of the balls (12) being chosen such that, when the balls (12) are arranged at the most axial end of their housing (11), the balls (12) are entirely within the groove (101) and the separable part (100) abuts against the stop surface (10) thereof and, when the balls (12) are arranged at the most outer end of their housing (11), the balls (12) partially exit the groove (101) and abut against the ball bearing seat (9).
  2. The projectile (1) according to claim 1, characterized in that the angle between the conical surface (13) and a plane perpendicular to the axis of the projectile is greater than 0.001 degree.
  3. The projectile (1) according to one of claims 1 or 2, characterized in that a multitude of housings (11) are radially distributed evenly around the ring (102), thereby forming a ball race (102).
  4. The projectile according to one of claims 1 to 3, characterized in that the separable part is constituted by a ring (100) comprising deployable fins (4).
  5. The projectile according to claim 4, characterized in that the stop surface (10) of the body is formed by a surface of a base (2) provided at the rear of the body (3) and carrying a sealing belt (5).
  6. The projectile according to one of claims 1 to 3, characterized in that the separable part is constituted by a warhead of the projectile having steering control surfaces.
EP15152943.5A 2014-03-18 2015-01-28 Spin-stabilised projectile Active EP2921812B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1400660A FR3018908B1 (en) 2014-03-18 2014-03-18 GYROSTABILIZED PROJECTILE

Publications (2)

Publication Number Publication Date
EP2921812A1 EP2921812A1 (en) 2015-09-23
EP2921812B1 true EP2921812B1 (en) 2016-09-14

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ID=51260911

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15152943.5A Active EP2921812B1 (en) 2014-03-18 2015-01-28 Spin-stabilised projectile

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EP (1) EP2921812B1 (en)
FR (1) FR3018908B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2764689B1 (en) 1997-06-13 1999-08-27 Tda Armements Sas METHOD FOR CONTROLLING THE LATERAL DISPERSION OF GYROSCOPIC STABILIZED AMMUNITION
US7791007B2 (en) * 2007-06-21 2010-09-07 Woodward Hrt, Inc. Techniques for providing surface control to a guidable projectile
JP4882099B2 (en) * 2008-09-25 2012-02-22 防衛省技術研究本部長 Flying body
FR2980842B1 (en) * 2011-10-03 2013-09-13 Nexter Munitions GYROSTABILIZED PROJECTILE COMPRISING A PAIR OF FINS AND METHOD FOR CONTROLLING SUCH A PROJECTILE

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Publication number Publication date
FR3018908B1 (en) 2016-03-04
EP2921812A1 (en) 2015-09-23
FR3018908A1 (en) 2015-09-25

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