EP0690284B1 - Deploying device for a projectile wing - Google Patents
Deploying device for a projectile wing Download PDFInfo
- Publication number
- EP0690284B1 EP0690284B1 EP95401557A EP95401557A EP0690284B1 EP 0690284 B1 EP0690284 B1 EP 0690284B1 EP 95401557 A EP95401557 A EP 95401557A EP 95401557 A EP95401557 A EP 95401557A EP 0690284 B1 EP0690284 B1 EP 0690284B1
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- EP
- European Patent Office
- Prior art keywords
- projectile
- fin
- lateral
- deployment
- fins
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
Definitions
- the present invention relates to a device for deployment of a projectile stabilization wing, including a projectile fired by a recoilless weapon.
- Certain projectiles notably those fired by a tube smooth like that of a recoilless weapon, have stabilization fins at their rear. These fins are folded back when the projectile is in the tube launch and they deploy at the exit of this one.
- the known deployment devices put the most often using springs which are kept in good condition tension when the fins are folded along the body of the projectile and which relax by deploying the fin at the exit from the launch tube.
- Patent FR7803397 describes such a device for deployment.
- the patent GB2136930 which represents the preambles of claims 1 and 4, describes a sub-calibrated projectile in which the deployment of the fin is ensured by the aerodynamic flow exerted on the front end fin. The efficiency of such a system is reduced and the deployment symmetry is not guaranteed.
- a fin deployment device stabilization for a projectile comprising at least one pallet, made integral with a fin by means drive, and oriented to receive a flow aerodynamics when firing the projectile and transmitting thus an effort resulting in the fin in order to deploy it, device characterized in that it comprises at least two pallets separated by a groove in which is positioned the fin, the groove having a bottom on which the fin comes into support when it is in the folded position on along the projectile body, bottom which constitutes the means which is unlockable so as to separate the deployment device and the fin from a certain opening angle of the latter.
- the device will advantageously include a wall front closing the groove at a front part of the device and constituting an axial stop for the end fin.
- It may include at least two lateral support feet which are in contact with an external surface of the projectile and which are held by stop profiles carried by the projectile and arranged to prevent displacement of the device in a direction perpendicular to a lateral surface of the fin.
- the stabilizer fin deployment device is characterized in that it comprises at least one pallet secured to at least two lateral drive surfaces, each of these drive surfaces being intended for receive support from a different wing of the projectile when the latter are in the folded position along of the projectile body, lateral drive surfaces which constitute the means of training which is unlockable so as to separate the deployment device and the fin from a certain opening angle of the latter.
- This device may include a tab intended to come into abutment against a flange secured to the projectile and which constitutes an axial stop for the device.
- It may include at least one substantially wall perpendicular to each drive surface and constituting an axial stop for the end of the fin considered.
- Each lateral drive surface may include a zone for holding a first lateral surface of the fin.
- the device according to the invention may include a external guide surface with circular profile and the diameter is equal to that of a launch tube of the projectile.
- An advantage of the invention is that it makes it possible to avoid, to open a fin, the use of potential energy elastic stored in springs.
- Another advantage of the invention is that it allows exert maximum force at the start of the opening, when the resistant efforts are also the greatest.
- the invention also makes it possible to avoid any drag residual aerodynamics caused by the device. In releasing the fin early enough we also limit rebounds of the latter.
- Figure 1 shows schematically the rear part a projectile 1 intended to be fired by a launcher without known type of recoil (not shown).
- This rear part includes a flange 2 on which are arranged screeds 3 regularly distributed angularly. Each yoke receives a fin 4, mounted pivoting around an axis 5.
- the projectile thus represented therefore carries six fins 4 regularly distributed (see figure 2).
- the fins 4 are represented here in their position folded along the body of projectile 1, position which is theirs inside the launch tube.
- Each fin 4 carries at a front end 4a a deployment device 6 according to the invention (here a only device is shown for clarity of the figure).
- the device 6 comprises two pallets 7a and 7b for receiving the aerodynamic flow that appears when firing along of the body of the projectile between the front part (AV mark) and the rear part (AR mark).
- These pallets have substantially the shape of two planes inclined to the axis 8 of the projectile and perpendicular to the lateral surfaces 4b and 4c of the fin 4.
- the inclination of the pallets relative to axis 8 of the projectile is chosen such that aerodynamic flow has the effect of removing the device 6 from the body 1a of the projectile.
- the device according to the invention can only be used to deploy fins which in the rest position are folded along the body of the projectile, the free ends of the fins being oriented towards the front part of the projectile and the screeds being arranged at the rear thereof.
- FIGS 3a, 3b and 3c show in detail the deployment device 6.
- This device is made for example in material molded plastic (such as high density polyethylene or polyamide). The material thickness is substantially constant for the whole device.
- Pallets 7a and 7b are connected to side walls 8a and 8b which are end with lateral support feet 9a and 9b.
- the side walls 8a, 8b are flat and substantially parallel to the lateral surfaces 4b, 4c of the fin 4.
- the device after being placed on the projectile, is shaped so as to present opposite aerodynamic flow two channels 6a, 6b whose inlet openings (arranged towards the front part of the projectile) have a surface greater than the openings of outlet (oriented towards the rear part AR), this due the tilt of the pallet.
- the support feet 9a, 9b are intended to come into contact with the external surface of the projectile body 1a, they have therefore a cylindrical profile with a diameter equal to that of the body 1a of the projectile.
- the two pallets 7a and 7b are separated by a groove 10 in which the fin 4 is positioned.
- the groove 10 has a bottom 10a on which the fin comes into support when it is in the folded position on along the projectile body 1a.
- the groove 10 is closed by a front wall 11 at the level of a front part of the device 6.
- the end 4a of the fin is in axial abutment on the wall 11.
- the fin balances the inertia forces to which subject the pallet when firing.
- the width of the groove 10 will be chosen such that it there is no play when installing the device 6 on the fin.
- the feet 9a and 9b of the device are maintained laterally by stop profiles 12 carried by the projectile. These profiles 12 are arranged so as to prevent any movement of the device in a perpendicular direction to the lateral surfaces 4b, 4c of the fin 4.
- stop profiles 12 could also play the role of axial stop for the device, it would then suffice to provide a setback on each foot preventing any retreat of the device.
- Figure 2 shows in section along the plane AA of the figure 1 the projectile 1 placed in a tube of launch 13.
- the device 6 has an external guide surface 14 whose diameter is equal to that of the launch tube 13. The device thus improves the guidance of the projectile in the tube launch.
- the operation of the device is as follows.
- the fins are firmly held by the device throughout the course inside the launch tube.
- All fins are symmetrically open this mainly because, thanks to the device according to the invention, the force applied to the fin is of origin aerodynamic and it is maximum at the start of the opening.
- the symmetry is also favored by the absence of vibrations of the fin obtained thanks to the transverse setting provided by the stop profiles 12.
- the device according to the invention therefore makes it possible to avoid problems with known deployment springs whose mechanical characteristics are likely to deteriorate during storage of the projectile.
- the resulting aerodynamic forces as well as the centrifugal force which are exercised on the device 6 manage to overcome the friction between the fin and the groove 10 and entrain the separation of the device and the fin.
- the devices are automatically ejected and do not interfere with the flight of the projectile by causing aerodynamic braking.
- FIG. 4 thus shows by way of example a device in which the bottom 11 is set back relative to the inlet openings of channels 6a, 6b.
- Figure 5 shows schematically the rear part a projectile 1 equipped with a deployment device 15 according to a second embodiment of the invention which is for projectiles equipped with an even number of fins.
- This device includes a pallet 7 intended to receive the aerodynamic flow that appears when firing along of the body of the projectile between the front part (AV mark) and the rear part (AR mark).
- the inclination of the pallet relative to axis 8 of the projectile is still chosen such that the flow aerodynamics has the effect of removing the device 15 from the body of the projectile.
- FIGS 7a, 7b and 7c show in detail what deployment device.
- Pallet 7 is connected to side walls 8a and 8b which end with lateral support feet 9a and 9b.
- the walls side 8a, 8b are planar and substantially parallel to lateral surfaces 4b, 4c of the fin 4.
- the device after its installation on the projectile, is shaped so as to present, in view of the aerodynamic flow, a channel 15a whose the entry opening (arranged towards the front part of the projectile) has a surface larger than that of the opening outlet (oriented towards the rear rear part).
- the support feet 9a, 9b come into contact with the external surface of the projectile body 1a, they have a profile cylindrical with a diameter equal to that of this body.
- Each surface 16a, 16b therefore receives a different fin when the latter are in the folded position on along the body 1a of the projectile.
- the feet 9a, 9b also carry holding zones 17a, 17b which are each in contact with a surface lateral of the fin considered.
- Each fin is held laterally on one side by a holding zone 17 carried by one of the devices 15 and on the other by a stop profile 18 secured to a flange 19 also made of plastic and made secured to the projectile body, for example by bonding.
- the flanges are axially offset from the device, so that the flanges do not prevent the opening of the fin.
- the dimensions of the devices 15 and the flanges 19 will be chosen so that there is no play during the placement on the fin.
- Each device 15 finally comprises a rear tab 20 which is intended to come into abutment against a flange 21 of the projectile and which constitutes an axial stop for the device.
- the tab also makes it possible to locate, at the level of the rear flange and at equal distance from each fin, the pivot point of the device. Such a provision ensures symmetrical opening of the two fins by the device.
- the device 15 has an external guide surface 14 whose diameter is equal to that of the launch tube 13. The device thus improves the guidance of the projectile in the tube launch.
- the deployment device is still ejected at from a certain opening angle of the fins.
- An advantage of this embodiment is that it allows to eject the device very quickly which reduces its action to a simple initial impulse on the fins which end then their opening by inertia and by the effect of their clean trail.
- the rapid ejection of the device also presents the advantage of limiting the angular speed of the fin in limit switch which limits the rebounds of the fin and improves the stabilization of the projectile.
- the distance between the ends of two neighboring fins increases during opening.
- the fins are therefore quickly released from surfaces 16a, 16b and it is possible to determine precisely the instant of ejection of the device by playing on the dimensions of the drive surfaces 16a, 16b and especially on the length L (see Figures 6 and 7a).
- Another advantage of this embodiment is that it reduces the number of devices used for a projectile, therefore the cost of production.
- Such a device would include for example one or more fixed pallets to the side walls of each fin.
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- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
- Pallets (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Iron Core Of Rotating Electric Machines (AREA)
Description
La présente invention a pour objet un dispositif de déploiement d'ailette de stabilisation d'un projectile, notamment d'un projectile tiré par une arme sans recul.The present invention relates to a device for deployment of a projectile stabilization wing, including a projectile fired by a recoilless weapon.
Certains projectiles, notamment ceux tirés par un tube lisse tel celui d'une arme sans recul, comportent des ailettes de stabilisation à leur partie arrière. Ces ailettes sont repliées lorsque le projectile se trouve dans le tube de lancement et elles se déploient à la sortie de celui ci.Certain projectiles, notably those fired by a tube smooth like that of a recoilless weapon, have stabilization fins at their rear. These fins are folded back when the projectile is in the tube launch and they deploy at the exit of this one.
Les dispositifs de déploiement connus mettent le plus souvent en oeuvre des ressorts qui sont maintenus en état de tension lorsque les ailettes sont repliées le long du corps du projectile et qui se détendent en déployant l'ailette à la sortie du tube de lancement.The known deployment devices put the most often using springs which are kept in good condition tension when the fins are folded along the body of the projectile and which relax by deploying the fin at the exit from the launch tube.
Le brevet FR7803397 décrit un tel dispositif de déploiement.Patent FR7803397 describes such a device for deployment.
L'inconvénient de tels dispositifs est qu'ils imposent le maintien à l'état bandé de plusieurs ressorts (un par ailette) pendant toute la durée de stockage du projectile.The disadvantage of such devices is that they impose the maintenance of several springs (one per wing) during the entire storage time of the projectile.
Les caractéristiques mécaniques des ressorts se dégradent au cours du temps et il en résulte, d'une part une diminution de l'efficacité du déploiement, et d'autre part des dissymétries lors de l'ouverture des ailettes, qui nuisent à la stabilisation du projectile sur trajectoire donc à la précision du tir.The mechanical characteristics of the springs deteriorate over time and as a result, on the one hand a decrease deployment efficiency, and secondly asymmetries when opening the fins, which harm stabilization of the projectile on trajectory therefore at the shot accuracy.
De plus, la mise en place de ressorts impose la réalisation sur le corps de projectile de logements pour ceux-ci, et pose des problèmes lors du montage et du contrôle, ce qui augmente les coûts de fabrication.In addition, the installation of springs imposes the housing housing for the projectile body these, and poses problems during assembly and control, which increases manufacturing costs.
Le brevet GB2136930 qui représente les préambules des revendications 1 et 4, décrit un projectile sous calibré
dans lequel le déploiement d'ailette est assuré par
l'écoulement aérodynamique qui s'exerce sur l'extrémité avant
de l'ailette. L'efficacité d'un tel système est réduite et la
symétrie du déploiement n'est pas assurée.The patent GB2136930 which represents the preambles of
C'est le but de l'invention que de proposer un dispositif de déploiement d'ailettes de stabilisation pour un projectile qui ne présente pas de tels inconvénients et qui assure à moindre coût un déploiement efficace et symétrique des ailettes de stabilisation. It is the object of the invention to propose a device deployment of stabilization fins for a projectile which does not have such disadvantages and which ensures lower cost efficient and symmetrical deployment of stabilization fins.
Ainsi l'invention a pour objet, selon un premier mode de réalisation, un dispositif de déploiement d'ailette de stabilisation pour un projectile comportant au moins une palette, rendue solidaire d'une ailette par des moyens d'entraínement, et orientée de façon à recevoir un écoulement aérodynamique lors du tir du projectile et à transmettre ainsi un effort résultant à l'ailette afin de la déployer, dispositif caractérisé en ce qu'il comprend au moins deux palettes séparées par une rainure dans laquelle se positionne l'ailette, la rainure comportant un fond sur lequel l'ailette vient en appui lorsqu'elle se trouve en position repliée le long du corps de projectile, fond qui constitue le moyen d'entraínement qui est déverrouillable de façon à séparer le dispositif de déploiement et l'ailette à partir d'un certain angle d'ouverture de cette dernière.Thus the subject of the invention is, according to a first mode of realization, a fin deployment device stabilization for a projectile comprising at least one pallet, made integral with a fin by means drive, and oriented to receive a flow aerodynamics when firing the projectile and transmitting thus an effort resulting in the fin in order to deploy it, device characterized in that it comprises at least two pallets separated by a groove in which is positioned the fin, the groove having a bottom on which the fin comes into support when it is in the folded position on along the projectile body, bottom which constitutes the means which is unlockable so as to separate the deployment device and the fin from a certain opening angle of the latter.
Le dispositif comportera avantageusement une paroi frontale fermant la rainure au niveau d'une partie avant du dispositif et constituant une butée axiale pour l'extrémité de l'ailette.The device will advantageously include a wall front closing the groove at a front part of the device and constituting an axial stop for the end fin.
Il pourra comporter au moins deux pieds d'appui latéraux qui sont en contact avec une surface externe du projectile et qui sont maintenus par des profils de butée portés par le projectile et disposés de façon à empêcher tout déplacement du dispositif suivant une direction perpendiculaire à une surface latérale de l'ailette.It may include at least two lateral support feet which are in contact with an external surface of the projectile and which are held by stop profiles carried by the projectile and arranged to prevent displacement of the device in a direction perpendicular to a lateral surface of the fin.
Selon un deuxième mode de réalisation de l'invention le dispositif de déploiement d'ailette de stabilisation est caractérisé en ce qu'il comporte au moins une palette solidaire d'au moins deux surfaces d'entraínement latérales, chacune de ces surfaces d'entraínement étant destinée à recevoir l'appui d'une ailette différente du projectile lorsque ces dernières se trouvent en position repliée le long du corps de projectile, surfaces d'entraínement latérales qui constituent le moyen d'entraínement qui est déverrouillable de façon à séparer le dispositif de déploiement et l'ailette à partir d'un certain angle d'ouverture de cette dernière. According to a second embodiment of the invention the stabilizer fin deployment device is characterized in that it comprises at least one pallet secured to at least two lateral drive surfaces, each of these drive surfaces being intended for receive support from a different wing of the projectile when the latter are in the folded position along of the projectile body, lateral drive surfaces which constitute the means of training which is unlockable so as to separate the deployment device and the fin from a certain opening angle of the latter.
Ce dispositif pourra comporter une languette destinée à venir en appui contre une collerette solidaire du projectile et qui constitue une butée axiale pour le dispositif.This device may include a tab intended to come into abutment against a flange secured to the projectile and which constitutes an axial stop for the device.
Il pourra comporter au moins une paroi sensiblement perpendiculaire à chaque surface d'entraínement et constituant une butée axiale pour l'extrémité de l'ailette considérée.It may include at least one substantially wall perpendicular to each drive surface and constituting an axial stop for the end of the fin considered.
Chaque surface d'entraínement latérale pourra comporter une zone de maintien d'une première surface latérale de l'ailette.Each lateral drive surface may include a zone for holding a first lateral surface of the fin.
Le dispositif selon l'invention pourra comporter une surface de guidage externe à profil circulaire et dont le diamètre est égal à celui d'un tube de lancement du projectile.The device according to the invention may include a external guide surface with circular profile and the diameter is equal to that of a launch tube of the projectile.
Un avantage de l'invention est qu'elle permet d'éviter, pour ouvrir une ailette, l'emploi d'une énergie potentielle élastique stockée dans des ressorts.An advantage of the invention is that it makes it possible to avoid, to open a fin, the use of potential energy elastic stored in springs.
Un autre avantage de l'invention est qu'elle permet d'exercer une force maximale au début de l'ouverture, lorsque les efforts résistants sont également les plus grands.Another advantage of the invention is that it allows exert maximum force at the start of the opening, when the resistant efforts are also the greatest.
L'invention permet également d'éviter toute traínée aérodynamique résiduelle occasionnée par le dispositif. En libérant l'ailette assez tôt on limite également les rebonds de cette dernière.The invention also makes it possible to avoid any drag residual aerodynamics caused by the device. In releasing the fin early enough we also limit rebounds of the latter.
D'autres avantages de l'invention apparaítront à la lecture de la description de différents modes de réalisation, description faite en référence aux dessins annexés et dans lesquels:
- la figure 1 représente partiellement la partie arrière d'un projectile équipé d'un dispositif de déploiement d'ailettes selon un premier mode de réalisation de l'invention,
- la figure 2 est une vue en coupe transversale de la partie arrière de ce projectile au niveau des dispositifs de déploiement d'ailettes, suivant le plan repéré AA sur la figure 1,
- les figures 3a, 3b et 3c représentent ce premier dispositif de déploiement d'ailettes suivant trois vues orthogonales,
- la figure 4 représente une variante de ce dispositif,
- la figure 5 représente partiellement la partie arrière d'un projectile équipé d'un dispositif de déploiement d'ailettes selon un deuxième mode de réalisation de l'invention,
- la figure 6 est une vue en coupe transversale de la partie arrière de ce projectile au niveau des dispositifs de déploiement d'ailettes, suivant le plan repéré BB sur la figure 5,
- les figures 7a, 7b et 7c représentent ce deuxième dispositif de déploiement d'ailettes suivant trois vues orthogonales.
- FIG. 1 partially represents the rear part of a projectile equipped with a device for deploying fins according to a first embodiment of the invention,
- FIG. 2 is a cross-sectional view of the rear part of this projectile at the level of the fins deployment devices, along the plane marked AA in FIG. 1,
- FIGS. 3a, 3b and 3c represent this first device for deploying fins in three orthogonal views,
- FIG. 4 represents a variant of this device,
- FIG. 5 partially represents the rear part of a projectile equipped with a device for deploying fins according to a second embodiment of the invention,
- FIG. 6 is a cross-sectional view of the rear part of this projectile at the level of the fins deployment devices, along the plane marked BB in FIG. 5,
- Figures 7a, 7b and 7c show this second device for deploying fins in three orthogonal views.
La figure 1 représente schématiquement la partie arrière
d'un projectile 1 destiné à être tiré par un lanceur sans
recul de type connu (non représenté).Figure 1 shows schematically the rear part
a
Cette partie arrière comprend une collerette 2 sur
laquelle sont aménagées des chapes 3 régulièrement réparties
angulairement. Chaque chape reçoit une ailette 4, montée
pivotante autour d'un axe 5.This rear part includes a
Le projectile ainsi représenté porte donc six ailettes 4
régulièrement réparties (voir figure 2).The projectile thus represented therefore carries six
Les ailettes 4 sont représentées ici dans leur position
repliée le long du corps la de projectile 1, position qui
est la leur à l'intérieur du tube de lancement.The
Chaque ailette 4 porte au niveau d'une extrémité avant 4a
un dispositif de déploiement 6 selon l'invention (ici un
seul dispositif est représenté pour la clarté de la figure).Each
Selon le premier mode de réalisation décrit, le
dispositif 6 comporte deux palettes 7a et 7b de réception de
l'écoulement aérodynamique qui apparait lors du tir le long
du corps la du projectile entre la partie avant (repère AV)
et la partie arrière (repère AR).According to the first embodiment described, the
Ces palettes ont sensiblement la forme de deux plans
inclinés par rapport à l'axe 8 du projectile et perpendiculaires
aux surfaces latérales 4b et 4c de l'ailette 4.These pallets have substantially the shape of two planes
inclined to the
L'inclinaison des palettes par rapport à l'axe 8 du
projectile est choisie telle que l'écoulement aérodynamique
ait pour effet d'écarter le dispositif 6 du corps 1a du
projectile. The inclination of the pallets relative to
Ainsi du fait du mode d'action utilisé, le dispositif selon l'invention ne peut être employé que pour déployer des ailettes qui en position de repos sont repliées le long du corps du projectile, les extrémités libres des ailettes étant orientées vers la partie avant du projectile et les chapes étant disposées à l'arrière de celui-ci.Because of the mode of action used, the device according to the invention can only be used to deploy fins which in the rest position are folded along the body of the projectile, the free ends of the fins being oriented towards the front part of the projectile and the screeds being arranged at the rear thereof.
Les figures 3a, 3b et 3c représentent en détail le
dispositif de déploiement 6.Figures 3a, 3b and 3c show in detail the
Ce dispositif est réalisé par exemple en matière
plastique moulée (telle du polyéthylène haute densité ou du
polyamide). L'épaisseur de matière est sensiblement
constante pour tout le dispositif. Les palettes 7a et 7b
sont reliées à des parois latérales 8a et 8b qui se
terminent par des pieds d'appui latéraux 9a et 9b.This device is made for example in material
molded plastic (such as high density polyethylene or
polyamide). The material thickness is substantially
constant for the whole device.
Les parois latérales 8a, 8b sont planes et sensiblement
parallèles aux surfaces latérales 4b,4c de l'ailette 4.The
Le dispositif, après sa mise en place sur le projectile, se trouve conformé de façon à présenter en regard de l'écoulement aérodynamique deux canaux 6a,6b dont les ouvertures d'entrée (disposées vers la partie avant AV du projectile) ont une surface supérieure aux ouvertures de sortie (orientées vers la partie arrière AR), cela en raison de l'inclinaison de la palette.The device, after being placed on the projectile, is shaped so as to present opposite aerodynamic flow two channels 6a, 6b whose inlet openings (arranged towards the front part of the projectile) have a surface greater than the openings of outlet (oriented towards the rear part AR), this due the tilt of the pallet.
Les pieds d'appui 9a,9b sont destinés à venir en contact
avec la surface externe du corps 1a du projectile, ils ont
donc un profil cylindrique de diamètre égal à celui du corps
1a du projectile.The
Les deux palettes 7a et 7b sont séparées par une rainure
10 dans laquelle se positionne l'ailette 4.The two
La rainure 10 comporte un fond 10a sur lequel l'ailette
vient en appui lorsqu'elle se trouve en position repliée le
long du corps 1a de projectile.The
La rainure 10 est fermée par une paroi frontale 11 au
niveau d'une partie avant du dispositif 6. Quand le
dispositif 6 est mis en place sur le projectile, l'extrémité
4a de l'ailette est en butée axiale sur la paroi 11. Ainsi
l'ailette équilibre les efforts d'inertie auxquels est
soumise la palette lors du tir. The
La largeur de la rainure 10 sera choisie telle qu'il
n'y ait pas de jeu lors de la mise en place du dispositif
6 sur l'ailette.The width of the
De plus les pieds 9a et 9b du dispositif sont maintenus
latéralement par des profils de butée 12 portés par le
projectile. Ces profils 12 sont disposés de façon à empêcher
tout déplacement du dispositif suivant une direction perpendiculaire
aux surfaces latérales 4b,4c de l'ailette 4.In addition, the
A titre de variante les profils de butée 12 pourraient
également jouer le rôle de butée axiale pour le dispositif,
il suffirait alors de prévoir un décrochement sur chaque
pied interdisant tout recul du dispositif.Alternatively the
En immobilisant le dispositif, d'une part par rapport à l'ailette et d'autre part par rapport au corps de projectile, on évite la flexion de l'ailette pendant son parcours à l'intérieur du tube de lancement, ce qui évite les vibrations de l'extrémité de l'ailette à la sortie du tube et améliore le processus de déploiement et la stabilisation du projectile.By immobilizing the device, on the one hand in relation to the fin and secondly with respect to the body of projectile, we avoid the bending of the fin during its course inside the launch tube, which avoids vibrations from the tip of the fin at the outlet of the tube and improves the deployment process and stabilization of the projectile.
La figure 2 représente en coupe suivant le plan AA de la
figure 1 le projectile 1 mis en place dans un tube de
lancement 13.Figure 2 shows in section along the plane AA of the
figure 1 the
Comme cela apparait sur cette figure, le dispositif 6
comporte une surface de guidage externe 14 dont le diamètre
est égal à celui du tube de lancement 13. Le dispositif
améliore ainsi le guidage du projectile dans le tube de
lancement.As shown in this figure, the
Le fonctionnement du dispositif est le suivant.The operation of the device is as follows.
Lors du tir du projectile, les ailettes se trouvent fermement maintenues par le dispositif tout le long du parcours à l'intérieur du tube de lancement.When the projectile is fired, the fins are firmly held by the device throughout the course inside the launch tube.
A la sortie du tube l'écoulement aérodynamique pénètre
dans les ouvertures 6a et 6b et exerce un effort sur les
palettes 7a et 7b. Cet effort écarte les dispositifs 6 du
corps la du projectile ce qui a pour effet d'entraíner les
ailettes 4 par l'intermédiaire du fond 10a des rainures 10
et de la cloison 11. At the exit of the tube the aerodynamic flow penetrates
in the openings 6a and 6b and exerts a force on the
Toutes les ailettes sont ouvertes de façon symétrique cela principalement parce que, grâce au dispositif selon l'invention, l'effort appliqué à l'ailette est d'origine aérodynamique et il est maximal au début de l'ouverture. La symétrie est également favorisée par l'absence de vibrations de l'ailette obtenue grâce au calage transversal fourni par les profils de butée 12.All fins are symmetrically open this mainly because, thanks to the device according to the invention, the force applied to the fin is of origin aerodynamic and it is maximum at the start of the opening. The symmetry is also favored by the absence of vibrations of the fin obtained thanks to the transverse setting provided by the stop profiles 12.
Le dispositif selon l'invention permet donc d'éviter les problèmes rencontrés avec les ressorts de déploiement connus dont les caractéristiques mécaniques risquent de se dégrader au cours du stockage du projectile.The device according to the invention therefore makes it possible to avoid problems with known deployment springs whose mechanical characteristics are likely to deteriorate during storage of the projectile.
Au delà d'un certain angle de déploiement, la résultante
des efforts aérodynamiques ainsi que la force centrifuge qui
s'exercent sur le dispositif 6 arrivent à vaincre les
frottements entre l'ailette et la rainure 10 et entraínent
la séparation du dispositif et de l'ailette.Beyond a certain deployment angle, the resulting
aerodynamic forces as well as the centrifugal force which
are exercised on the
Ainsi lors du déploiement, les dispositifs se trouvent automatiquement éjectés et ne viennent pas perturber le vol du projectile en occasionnant un freinage aérodynamique.So during deployment, the devices are automatically ejected and do not interfere with the flight of the projectile by causing aerodynamic braking.
Il est possible de déterminer l'angle d'ouverture de l'ailette à partir duquel le dispositif se trouve éjecté en jouant sur les dimensions des surfaces de contact ailette/rainure (par exemple en donnant à la rainure une forme non parallèle aux faces latérales de l'ailette).It is possible to determine the opening angle of the fin from which the device is ejected in playing on the dimensions of the contact surfaces fin / groove (for example by giving the groove a shape not parallel to the lateral faces of the fin).
Il est possible également de déterminer l'angle auquel se
produit l'éjection du dispositif en jouant sur la position
de la paroi frontale 11 et/ou sur la forme de l'extrémité de
l'ailette.It is also possible to determine the angle at which
produces the ejection of the device by playing on the position
of the
Dans ce cas à l'action de la force centrifuge s'ajoute celle du couple de basculement du dispositif par rapport à l'ailette qui est engendré par les forces aérodynamiques.In this case the action of the centrifugal force is added that of the tilting torque of the device with respect to the fin which is generated by aerodynamic forces.
La figure 4 montre ainsi à titre d'exemple un dispositif dans lequel le fond 11 se trouve en retrait par rapport aux ouvertures d'entrée des canaux 6a, 6b. FIG. 4 thus shows by way of example a device in which the bottom 11 is set back relative to the inlet openings of channels 6a, 6b.
La figure 5 représente schématiquement la partie arrière
d'un projectile 1 équipé d'un dispositif de déploiement 15
selon un deuxième mode de réalisation de l'invention qui
est destiné aux projectiles équipés d'un nombre pair
d'ailettes.Figure 5 shows schematically the rear part
a projectile 1 equipped with a
Ce dispositif comprend une palette 7 destinée à recevoir
l'écoulement aérodynamique qui apparait lors du tir le long
du corps la du projectile entre la partie avant (repère AV)
et la partie arrière (repère AR).This device includes a
L'inclinaison de la palette par rapport à l'axe 8 du
projectile est encore choisie telle que l'écoulement
aérodynamique ait pour effet d'écarter le dispositif 15 du
corps la du projectile.The inclination of the pallet relative to
Les figures 7a, 7b et 7c représentent en détail ce dispositif de déploiement.Figures 7a, 7b and 7c show in detail what deployment device.
Il est lui aussi réalisé de préférence en matière plastique moulée.It is also preferably made in terms of molded plastic.
La palette 7 est reliée à des parois latérales 8a et 8b
qui se terminent par des pieds d'appui latéraux 9a et 9b.
Comme dans le mode de réalisation précédent, les parois
latérales 8a, 8b sont planes et sensiblement parallèles aux
surfaces latérales 4b,4c de l'ailette 4.As in the previous embodiment, the
Ainsi le dispositif, après sa mise en place sur le projectile, se trouve conformé de façon à présenter, en regard de l'écoulement aérodynamique, un canal 15a dont l'ouverture d'entrée (disposée vers la partie avant AV du projectile) a une surface supérieure à celle de l'ouverture de sortie (orientée vers la partie arrière AR).Thus the device, after its installation on the projectile, is shaped so as to present, in view of the aerodynamic flow, a channel 15a whose the entry opening (arranged towards the front part of the projectile) has a surface larger than that of the opening outlet (oriented towards the rear rear part).
Les pieds d'appui 9a,9b viennent en contact avec la
surface externe du corps 1a du projectile, ils ont un profil
cylindrique de diamètre égal à celui de ce corps.The
Ils portent chacun une surface d'entraínement latérale
16a,16b qui est destinée à recevoir l'appui d'une ailette 4.They each carry a
Chaque surface 16a,16b reçoit donc une ailette différente
lorsque ces dernières se trouvent en position repliée le
long du corps 1a du projectile. Each
Les pieds 9a, 9b portent également des zones de maintien
17a, 17b qui sont en contact chacune avec une surface
latérale de l'ailette considérée.The
Comme cela est plus particulièrement visible figure 6,
trois dispositifs 15 selon l'invention permettent de
déployer six ailettes.As is more particularly visible in Figure 6,
three
Chaque ailette se trouve maintenue latéralement d'un côté
par une zone de maintien 17 portée par un des dispositifs
15 et de l'autre par un profil de butée 18 solidaire d'une
bride 19 réalisée également en matière plastique et rendue
solidaire du corps de projectile, par exemple par collage.Each fin is held laterally on one side
by a holding zone 17 carried by one of the
Comme cela est visible sur la figure 5, les brides sont décalées axialement par rapport au dispositif, celà afin que les brides n'interdisent pas l'ouverture de l'ailette.As shown in Figure 5, the flanges are axially offset from the device, so that the flanges do not prevent the opening of the fin.
Les dimensions des dispositifs 15 et des brides 19 seront
choisies de telle sorte qu'il n'y ait pas de jeu lors de la
mise en place sur l'ailette.The dimensions of the
Une telle disposition permet d'immobiliser les extrémités des ailettes ce qui évite les vibrations lors du tir et améliore le processus de déploiement et la stabilisation du projectile.Such an arrangement makes it possible to immobilize the ends fins which avoid vibrations during shooting and improves the deployment process and stabilizes the projectile.
Il serait néanmoins possible d'omettre les brides 19 et
de ne conserver qu'un maintien unilatéral de l'ailette par
la zone de maintien 17, le résultat obtenu serait cependant
d'une efficacité moindre.It would nevertheless be possible to omit the
Chaque dispositif 15 comporte enfin une languette arrière
20 qui est destinée à venir en appui contre une collerette
21 du projectile et qui constitue une butée axiale pour le
dispositif.Each
La languette permet également de localiser, au niveau de la collerette arrière et à égale distance de chaque ailette, le point de pivotement du dispositif. Une telle disposition assure une ouverture symétrique des deux ailettes par le dispositif. The tab also makes it possible to locate, at the level of the rear flange and at equal distance from each fin, the pivot point of the device. Such a provision ensures symmetrical opening of the two fins by the device.
Il serait possible à titre de variante de remplacer cette
languette par deux parois, chacune portée par un pied 9a,9b
et perpendiculaire à la surface d'entraínement considérée
16a,16b. Ces parois venant en butée contre l'extrémité 4a de
l'ailette lors du montage.It would be possible as an alternative to replace this
tongue by two walls, each carried by a
Comme dans la variante précédente, le dispositif 15
comporte une surface de guidage externe 14 dont le diamètre
est égal à celui du tube de lancement 13. Le dispositif
améliore ainsi le guidage du projectile dans le tube de
lancement.As in the previous variant, the
Le fonctionnement de ce mode de réalisation est analogue à celui du précédent.The operation of this embodiment is analogous to that of the previous one.
Le dispositif de déploiement se trouve encore éjecté à partir d'un certain angle d'ouverture des ailettes.The deployment device is still ejected at from a certain opening angle of the fins.
Un avantage de ce mode de réalisation est qu'il permet d'éjecter très vite le dispositif ce qui réduit son action à une simple impulsion initiale sur les ailettes qui terminent ensuite leur ouverture par inertie et par l'effet de leur traínée propre.An advantage of this embodiment is that it allows to eject the device very quickly which reduces its action to a simple initial impulse on the fins which end then their opening by inertia and by the effect of their clean trail.
L'éjection rapide du dispositif présente également l'avantage de limiter la vitesse angulaire de l'ailette en fin de course ce qui limite les rebonds de l'ailette et améliore la stabilisation du projectile.The rapid ejection of the device also presents the advantage of limiting the angular speed of the fin in limit switch which limits the rebounds of the fin and improves the stabilization of the projectile.
En effet, la distance entre les extrémités de deux
ailettes voisines augmente au cours de l'ouverture. Les
ailettes se trouvent donc rapidement dégagées des surfaces
d'entraínement 16a,16b et il est possible de déterminer
précisément l'instant d'éjection du dispositif en jouant sur
les dimensions des surfaces d'entraínement 16a,16b et
notamment sur la longueur L (voir figures 6 et 7a).Indeed, the distance between the ends of two
neighboring fins increases during opening. The
fins are therefore quickly released from
Un autre avantage de ce mode de réalisation est qu'il permet de réduire le nombre de dispositifs utilisés pour un projectile, donc le coût de réalisation.Another advantage of this embodiment is that it reduces the number of devices used for a projectile, therefore the cost of production.
Enfin à titre de variante il serait possible de définir un dispositif de déploiement qui resterait solidaire de l'ailette même après déploiement. Un tel dispositif comprendrait par exemple une ou plusieurs palettes fixées aux parois latérales de chaque ailette.Finally as a variant it would be possible to define a deployment system which would remain united to the fin even after deployment. Such a device would include for example one or more fixed pallets to the side walls of each fin.
Claims (8)
- A deployment device for the stabilizing fins (4) of a projectile (1) comprising at least one pallet made integral with a fin (4) by drive means, and facing so that it receives an aerodynamic flow when the projectile is fired and thus transferring a resultant strain to the fin (4) so as to deploy it, characterised in that it comprises at least two pallets (7a, 7b) separated by a groove (10) in which the fin (4) is positioned, the groove (10) comprising a bottom (10a) whereupon the fin (4) comes to bear when it is in a folded position along the body of the projectile (1), said bottom constitutes a drive means unlockable so as to separate the deployment device from the fin from a certain angle of opening of the latter.
- A device according to Claim 1, characterised in that it comprises a front wall (11) closing the groove (10) at a front part of the device and constituting an axial stop for the end of the fin (4).
- A device according to one of Claims 1 or 2, characterised in that it comprises at least two lateral support feet (9a, 9b) which are in contact with an outer surface of the projectile (1) and which are held by stop profiles (12) carried by the projectile and arranged so as to prevent any movement of the device in a perpendicular direction to a lateral surface (4b, 4c) of the fin (4).
- A deployment device for the stabilizing fins (4) of a projectile (1) comprising at least one pallet made integral with a fin (4) by drive means, and facing so that it receives an aerodynamic flow when the projectile is fired and thus transferring a resultant strain to the fin (4) so as to deploy it, characterised in that it comprises at least one pallet (7) integral with at least two lateral drive surfaces (16a, 16b), each of these drive surfaces being designed to accommodate a different fin (4) of the projectile (1) when the latter are in their folded position along the body of the projectile, said lateral surfaces (1) constitute a drive means unlockable so as to separate the deployment device from the fin from a certain angle of opening of the latter.
- A device according to Claim 4, characterised in that it comprises a tab (20) designed to come to bear on a flange (21) integral with the projectile (1) and constituting an axial stop for the device.
- A device according to Claim 4, characterised in that it comprises at least one wall which is roughly perpendicular to each drive surface (16a, 16b) and constitutes an axial stop for the end of the concerned fin (4).
- A device according to one of Claims 4 to 6, characterised in that each lateral drive surface (16a, 16b) comprises a holding area (17a, 17b) of a first lateral surface of the fin (4).
- A device according to one of Claims 1 to 7, characterised in that it comprises an outer guiding surface (14) having a circular profile and wherein the diametre is equal to that of the launch tube of the projectile (1).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9407953 | 1994-06-28 | ||
FR9407953A FR2721702B1 (en) | 1994-06-28 | 1994-06-28 | Device for deploying a projectile fin. |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0690284A1 EP0690284A1 (en) | 1996-01-03 |
EP0690284B1 true EP0690284B1 (en) | 1999-09-15 |
Family
ID=9464743
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP95401557A Expired - Lifetime EP0690284B1 (en) | 1994-06-28 | 1995-06-28 | Deploying device for a projectile wing |
Country Status (7)
Country | Link |
---|---|
US (1) | US5685503A (en) |
EP (1) | EP0690284B1 (en) |
DE (1) | DE69512146T2 (en) |
ES (1) | ES2138165T3 (en) |
FR (1) | FR2721702B1 (en) |
IL (1) | IL114383A (en) |
ZA (1) | ZA955302B (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1947415A1 (en) * | 2007-01-19 | 2008-07-23 | Diehl BGT Defence GmbH & Co.KG | Apparatus for folding a hydrofoil |
Families Citing this family (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE19827278A1 (en) * | 1998-06-19 | 1999-12-23 | Diehl Stiftung & Co | Steerable missile can be launched by thrust of propellant gas charge |
DE10118216A1 (en) * | 2001-04-12 | 2002-10-17 | Diehl Munitionssysteme Gmbh | Rudder blade storage device for one floor |
US6691948B1 (en) | 2003-04-10 | 2004-02-17 | The United States Of America As Represented By The Secretary Of The Navy | High torque rocket nozzle |
FR2864612B1 (en) | 2003-12-24 | 2007-11-23 | Giat Ind Sa | DEVICE FOR DEPLOYING THE FINS OF A PROJECTILE |
US7262394B2 (en) * | 2004-03-05 | 2007-08-28 | The Boeing Company | Mortar shell ring tail and associated method |
US7856929B2 (en) | 2007-06-29 | 2010-12-28 | Taser International, Inc. | Systems and methods for deploying an electrode using torsion |
US7984676B1 (en) | 2007-06-29 | 2011-07-26 | Taser International, Inc. | Systems and methods for a rear anchored projectile |
WO2009005540A1 (en) * | 2007-06-29 | 2009-01-08 | Taser International, Inc. | Systems and methods for a projectile having a stabilizer for spin stabilization |
FI120709B (en) * | 2008-01-31 | 2010-01-29 | Patria Weapon Systems Oy | Support means for supporting a grenade and procedure |
RU2462685C1 (en) * | 2011-02-15 | 2012-09-27 | Николай Евгеньевич Староверов | Multielement cartridge of staroverov (versions) |
US9212877B2 (en) * | 2012-07-05 | 2015-12-15 | The United States Of America As Represented By The Secretary Of The Army | Retention system for a deployable projectile fin |
RU2512041C1 (en) * | 2012-11-13 | 2014-04-10 | Открытое акционерное общество "Конструкторское бюро приборостроения" | Projectile fin |
RU2551299C1 (en) * | 2014-06-26 | 2015-05-20 | Открытое акционерное общество "Конструкторское бюро приборостроения им. академика А.Г. Шипунова" | Shell test method |
FR3041744B1 (en) * | 2015-09-29 | 2018-08-17 | Nexter Munitions | ARTILLERY PROJECTILE HAVING A PILOTED PHASE. |
RU2651671C1 (en) * | 2017-01-17 | 2018-04-23 | Акционерное общество "Конструкторское бюро приборостроения им. академика А.Г. Шипунова" | Missile that is fired from the launching tube |
FR3071917B1 (en) * | 2017-10-04 | 2021-11-19 | Nexter Munitions | WING AND PROJECTILE LOCKING DEVICE INCLUDING SUCH A DEVICE |
US20230072799A1 (en) * | 2021-09-03 | 2023-03-09 | Raytheon Company | Control surface restraining system for tactical flight vehicles |
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US2427217A (en) * | 1943-09-23 | 1947-09-09 | Harry J Lebherz | Rocket fin assembly |
US2666387A (en) * | 1949-12-07 | 1954-01-19 | United Aircraft Corp | Stabilizing fins for missiles |
NL106348C (en) * | 1959-03-09 | |||
US3188957A (en) * | 1962-04-03 | 1965-06-15 | Aerojet General Co | Ring stabilizer |
FR2070389A5 (en) * | 1969-12-03 | 1971-09-10 | Serat | |
CH552189A (en) * | 1972-05-10 | 1974-07-31 | Oerlikon Buehrle Ag | DRIVING MIRROR FLOOR. |
DE2264338A1 (en) * | 1972-12-30 | 1974-07-04 | Dynamit Nobel Ag | FOLD-OUT TAIL, ESPECIALLY FOR MISSILE |
FR2221707B1 (en) * | 1973-03-14 | 1976-04-30 | France Etat | |
DE2721536A1 (en) * | 1977-05-13 | 1978-11-16 | Brunsch Kurt | Ballistic shell with vanes for stabilising flight path - gives greater accuracy whilst dispensing with rifled gun barrel bore |
US4143838A (en) * | 1977-08-22 | 1979-03-13 | The United States Of America As Represented By The Secretary Of The Navy | Folding fin assembly detent |
US4158447A (en) * | 1977-11-29 | 1979-06-19 | The United States Of America As Represented By The Secretary Of The Navy | Expanding stabilizing fin cup |
US4332360A (en) * | 1980-07-21 | 1982-06-01 | The United States Of America As Represented By The Secretary Of The Army | Automatically deployed shell fins |
IL66624A (en) * | 1982-02-10 | 1986-04-29 | Gen Dynamics Corp | Wing housing and cover release assembly for self-erecting wing of a structure such as missile |
DE3309533A1 (en) * | 1983-03-17 | 1984-09-20 | Diehl GmbH & Co, 8500 Nürnberg | WING-STABILIZED SHELL WITH DRIVING CAGE |
IL72000A (en) * | 1984-06-04 | 1989-09-10 | Israel State | Projectile stabilization system |
US4667899A (en) * | 1984-11-28 | 1987-05-26 | General Dynamics, Pomona Division | Double swing wing self-erecting missile wing structure |
SE444612B (en) * | 1984-12-13 | 1986-04-21 | Ffv Affersverket | GUIDELINES FOR FENOR EXPOSURE OF PROJECTIL |
GB8815060D0 (en) * | 1988-06-24 | 1988-11-16 | British Aerospace | Fin assembly for projectile |
-
1994
- 1994-06-28 FR FR9407953A patent/FR2721702B1/en not_active Expired - Fee Related
-
1995
- 1995-06-23 US US08/481,038 patent/US5685503A/en not_active Expired - Fee Related
- 1995-06-27 ZA ZA955302A patent/ZA955302B/en unknown
- 1995-06-28 EP EP95401557A patent/EP0690284B1/en not_active Expired - Lifetime
- 1995-06-28 ES ES95401557T patent/ES2138165T3/en not_active Expired - Lifetime
- 1995-06-28 IL IL11438395A patent/IL114383A/en not_active IP Right Cessation
- 1995-06-28 DE DE69512146T patent/DE69512146T2/en not_active Expired - Fee Related
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1947415A1 (en) * | 2007-01-19 | 2008-07-23 | Diehl BGT Defence GmbH & Co.KG | Apparatus for folding a hydrofoil |
Also Published As
Publication number | Publication date |
---|---|
ZA955302B (en) | 1996-12-23 |
FR2721702B1 (en) | 1996-08-14 |
FR2721702A1 (en) | 1995-12-29 |
EP0690284A1 (en) | 1996-01-03 |
DE69512146T2 (en) | 2000-01-27 |
US5685503A (en) | 1997-11-11 |
IL114383A0 (en) | 1995-10-31 |
DE69512146D1 (en) | 1999-10-21 |
IL114383A (en) | 1998-12-06 |
ES2138165T3 (en) | 2000-01-01 |
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