EP0653604B1 - Stabilising for deployment device for a rocket type projectile - Google Patents
Stabilising for deployment device for a rocket type projectile Download PDFInfo
- Publication number
- EP0653604B1 EP0653604B1 EP19940402075 EP94402075A EP0653604B1 EP 0653604 B1 EP0653604 B1 EP 0653604B1 EP 19940402075 EP19940402075 EP 19940402075 EP 94402075 A EP94402075 A EP 94402075A EP 0653604 B1 EP0653604 B1 EP 0653604B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- spring
- fin
- support
- projectile
- axis
- 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 technical field of the invention is that of devices deployment of projectile fins, in particular of the type rockets.
- the stabilization of such projectiles is generally ensured by a tail unit of diameter corresponding substantially to internal diameter of the launching tube of the projectile considered.
- Patent FR7803397 describes such a projectile in which each fin is deployed by an elastic member.
- This organ is a spring in the form of a curved wire, placed in a groove carried out under each fin. At the exit of the launch tube, the spring relaxes by pushing back the fin and thus ensures its deployment. But this device requires the realization of a groove intended to accommodate the lower part of the fin and the spring and maintain it when deploying the fin.
- Patent EP0202734 proposes to carry out the deployment fins by an elastic member forming an integral part of the fin itself. For this it is planned to carry out a tongue on each fin.
- This device presents the disadvantage of requiring precise machining of the fin and to use for it a material having good elastic qualities, therefore a high cost.
- Patent US4523728 the description of which is taken from the preamble of independent claim 1, describes a projectile whose fins are pivotally mounted around axes parallel to the axis of the projectile. Each fin carries a spring arranged around its pivot axis, spring ensuring first of all the rotation of the fin around its axis, then the translation of the fin towards the rear of the projectile. Such a system is expensive and bulky.
- the object of the invention is therefore to provide a device for deployment of stabilization fins with no such disadvantages.
- the device allows in particular, by a reduced radial dimensions, to ensure opening torque maximum. It also allows to train the least aerodynamic disturbances possible.
- the subject of the invention is a deployment device for a projectile stabilization wing, comprising a torsion spring whose axis is parallel to the axis of the projectile, device characterized in that the spring is placed near the fin and arranged in a groove fitted in a support linked to the projectile and on which is mounted the fin, one end of the spring being integral of the support and the other end of the spring bearing against a lower face of the fin, the spring being torsional stress when the fin is folded and exerting then an effort capable of rotating it relative to the support in order to deploy it.
- the groove has a width greater than the outer diameter of the spring, allowing it to be ejected after deployment of the fin.
- the spring has at one of its ends, a part angled 90 ° and with an axis parallel to the axis of the spring and is radially integral with the support by penetration of the part angled in an orifice made in the rear face of the support, orifice of axis parallel to the axis of the projectile and having a diameter greater than the diameter of the wire constituting the spring, authorizing the ejection of it after deployment of the fin.
- the rear face of the support has a clearance connecting the groove at the orifice and allowing the passage of the end of the spring, clearance with depth and width greater than the diameter of the constituent wire of the spring, allowing ejecting it after deployment of the fin.
- the other end of the spring is near a flange of the support which ensures the axial maintenance of the spring when the fin is in the folded position.
- FIG. 1 schematically represents a projectile 1, of rocket type, placed in a launch tube 2.
- the projectile conventionally consists of a body 3 provided with a warhead 4 in the front.
- ailerons 16 regularly distributed angularly (here in number of 6).
- the rear of the projectile includes a fin support 5 consisting of a cylindrical seat 19 and a collar annular 17.
- the cylindrical bearing surface 19 of the fin support is fitted inside a bore 20, made in part rear of the body 3, and the collar 17 is in abutment against the back of the body. This ensures solidarity, for example by gluing, of the fin support 5 on the body 3.
- the fin support 5 comprises, at the level of its flange annular 17, a tail unit 6 of diameter substantially equal to the internal diameter of the projectile launching tube.
- the empennage 6 is composed of stabilization fins 7 (here 6 in number).
- the collar 17 comprises at its external diameter, yokes 18 which receive the fins 7 pivotally mounted about an axis 8.
- the fins 7 are deployed at the outlet of the launch tube under the action of a deployment device which will be described later.
- the yokes 18 and the fins 16 ensure the guidance of the projectile during its propulsion inside the launch tube.
- FIG. 2 represents the fin support 5 equipped with its tail unit 6, in the position it occupies when it is placed in the launch tube, i.e. stabilization fins folded down along the body of the projectile.
- the empennage 6 comprises six fins 7 regularly angularly spaced.
- a cylindrical torsion spring 9 with angular action is placed near each fin and serves as an elastic member allowing the deployment thereof. It is disposed inside a groove 10, arranged in the flange 17 of the support fins 5, parallel to the axis XX 'of the projectile.
- the groove 10, which is intended to guide the cylindrical spring 9 has a width greater than the outside diameter of the spring, in order to allow the ejection of the latter.
- FIG. 3 represents the fin support 5 alone in the direction F of the figure 2.
- the rear face 13 of the fin support 5 has, at each groove 10, an orifice 14 of axis parallel to the axis XX 'of the projectile and a clearance 15 connecting the hole in the groove
- the end 12 of the spring comprises a part 21 bent at 90 °, with a parallel axis to the axis YY 'of the spring (see Figure 5).
- the bent part 21 penetrates inside the orifice 14 which has a diameter slightly greater than the diameter of the wire composing the spring.
- the spring is thus guided by the groove 10 and radially integral with the support fins by the clearance 15 and the orifice 14.
- the cylindrical spring with angular action is constrained in torsion. It exerts a force on the fin, which ensures, right out of the projectile out of the launch tube, initiation of deployment of each fin corresponding.
Description
Le domaine technique de l'invention est celui des dispositifs de déploiement d'ailettes de projectiles, en particulier de type roquettes.The technical field of the invention is that of devices deployment of projectile fins, in particular of the type rockets.
La stabilisation de tels projectiles est généralement assurée par un empennage de diamètre correspondant sensiblement au diamètre interne du tube de lancement du projectile considéré.The stabilization of such projectiles is generally ensured by a tail unit of diameter corresponding substantially to internal diameter of the launching tube of the projectile considered.
Afin d'améliorer la stabilité de ces projectiles, il est souhaitable de situer leur centre de poussée le plus possible vers leur partie arrière. Pour satisfaire à cette condition, une solution consiste à rendre l'empennage déployable, et il est nécessaire d'assurer le déploiement des ailettes composant l'empennage dès la sortie du tube de lancement.In order to improve the stability of these projectiles, it is desirable to locate their center of thrust as much as possible towards their rear part. To meet this condition, a solution is to make the empennage deployable, and it's necessary to ensure the deployment of the component fins the empennage right out of the launch tube.
Il est connu d'assurer le déploiement d'ailettes de projectiles par un organe élastique.It is known to ensure the deployment of fins of projectiles by an elastic member.
Le brevet FR7803397 décrit un tel projectile dans lequel chaque ailette est déployée par un organe élastique. Cet organe est un ressort sous forme de fil incurvé, placé dans une rainure réalisée sous chaque ailette. A la sortie du tube de lancement, le ressort se détend en repoussant l'ailette et assure ainsi son déploiement. Mais ce dispositif impose la réalisation d'une rainure destinée à loger la partie inférieure de l'ailette et le ressort et à maintenir ce dernier lors du déploiement de l'ailette.Patent FR7803397 describes such a projectile in which each fin is deployed by an elastic member. This organ is a spring in the form of a curved wire, placed in a groove carried out under each fin. At the exit of the launch tube, the spring relaxes by pushing back the fin and thus ensures its deployment. But this device requires the realization of a groove intended to accommodate the lower part of the fin and the spring and maintain it when deploying the fin.
Le brevet EP0202734 propose de réaliser le déploiement d'ailettes par un organe élastique faisant partie intégrante de l'ailette elle-même. Pour cela il est prévu de réaliser une languette sur chaque ailette. Ce dispositif présente l'inconvénient de nécessiter un usinage précis de l'ailette et d'utiliser pour celle-ci une matière présentant de bonnes qualités élastiques, donc un coût élevé.Patent EP0202734 proposes to carry out the deployment fins by an elastic member forming an integral part of the fin itself. For this it is planned to carry out a tongue on each fin. This device presents the disadvantage of requiring precise machining of the fin and to use for it a material having good elastic qualities, therefore a high cost.
Le brevet US4523728 dont l'exposé est pris à base du préambule de la revendication indépendante 1, décrit un projectile dont les ailettes
sont montées pivotantes autour d'axes parallèles à l'axe du
projectile. Chaque ailette porte un ressort disposé autour de
son axe de pivotement, ressort assurant tout d'abord la rotation
de l'ailette autour de son axe, puis la translation de l'ailette
vers l'arrière du projectile. Un tel système est coûteux et
encombrant.Patent US4523728, the description of which is taken from the preamble of
Le but de l'invention est donc de réaliser un dispositif de déploiement d'ailettes de stabilisation ne présentant pas de tels inconvénients. Le dispositif permet notamment, par un encombrement radial réduit, d'assurer un couple d'ouverture maximum. Il permet également d'entraíner le moins de perturbations aérodynamiques possible.The object of the invention is therefore to provide a device for deployment of stabilization fins with no such disadvantages. The device allows in particular, by a reduced radial dimensions, to ensure opening torque maximum. It also allows to train the least aerodynamic disturbances possible.
Ainsi l'invention a pour objet un dispositif de déploiement pour une ailette de stabilisation d'un projectile, comprenant un ressort de torsion dont l'axe est parallèle à l'axe du projectile, dispositif caractérisé en ce que le ressort est placé à proximité de l'ailette et disposé dans une rainure aménagée dans un support lié au projectile et sur lequel est montée l'ailette, une des extrémités du ressort étant solidaire du support et l'autre extrémité du ressort étant en appui contre une face inférieure de l'ailette, le ressort se trouvant contraint en torsion lorsque l'ailette est repliée et exerçant alors un effort apte à faire pivoter celle-ci par rapport au support de façon à la déployer.Thus the subject of the invention is a deployment device for a projectile stabilization wing, comprising a torsion spring whose axis is parallel to the axis of the projectile, device characterized in that the spring is placed near the fin and arranged in a groove fitted in a support linked to the projectile and on which is mounted the fin, one end of the spring being integral of the support and the other end of the spring bearing against a lower face of the fin, the spring being torsional stress when the fin is folded and exerting then an effort capable of rotating it relative to the support in order to deploy it.
Avantageusement, la rainure a une largeur supérieure au diamètre externe du ressort, autorisant ainsi son éjection après déploiement de l'ailette.Advantageously, the groove has a width greater than the outer diameter of the spring, allowing it to be ejected after deployment of the fin.
Le ressort présente à l'une de ses extrémités, une partie coudée à 90° et d'axe parallèle à l'axe du ressort et est solidaire radialement du support par pénétration de la partie coudée dans un orifice réalisé dans la face arrière du support, orifice d'axe parallèle à l'axe du projectile et présentant un diamètre supérieur au diamètre du fil constitutif du ressort, autorisant l'éjection de celui-ci après déploiement de l'ailette.The spring has at one of its ends, a part angled 90 ° and with an axis parallel to the axis of the spring and is radially integral with the support by penetration of the part angled in an orifice made in the rear face of the support, orifice of axis parallel to the axis of the projectile and having a diameter greater than the diameter of the wire constituting the spring, authorizing the ejection of it after deployment of the fin.
La face arrière du support comporte un dégagement reliant la rainure à l'orifice et permettant le passage de l'extrémité du ressort, dégagement présentant une profondeur et une largeur supérieure au diamètre du fil constitutif du ressort, autorisant l'éjection de celui-ci après déploiement de l'ailette.The rear face of the support has a clearance connecting the groove at the orifice and allowing the passage of the end of the spring, clearance with depth and width greater than the diameter of the constituent wire of the spring, allowing ejecting it after deployment of the fin.
L'autre extrémité du ressort se trouve à proximité d'une collerette du support qui assure le maintien axial du ressort lorsque l'ailette se trouve en position repliée.The other end of the spring is near a flange of the support which ensures the axial maintenance of the spring when the fin is in the folded position.
L'invention sera mieux comprise à la lecture de la description faite en référence aux dessins annexés dans lesquels:
- la figure 1 représente schématiquement un projectile de type roquette muni d'un empennage.
- la figure 2 représente un support d'ailettes équipé de son empennage selon l'invention.
- la figure 3 représente le support d'ailettes seul suivant la direction F de la figure 2.
- la figure 4 représente une vue partielle de l'arrière du projectile après initiation du déploiement d'une ailette.
- la figure 5 représente une vue partielle de l'arrière du projectile lors de l'éjection d'un ressort de torsion.
- FIG. 1 schematically represents a rocket-type projectile provided with a tail unit.
- 2 shows a fin support equipped with its tail according to the invention.
- FIG. 3 represents the fin support alone in the direction F of FIG. 2.
- FIG. 4 represents a partial view of the rear of the projectile after initiation of the deployment of a fin.
- FIG. 5 represents a partial view of the rear of the projectile during the ejection of a torsion spring.
La figure 1 représente schématiquement un projectile 1, de
type roquette, placé dans un tube de lancement 2. Le projectile
est constitué de façon classique d'un corps 3 muni d'une ogive 4
à l'avant.FIG. 1 schematically represents a
Le corps 3 comporte une charge militaire qui est généralement
une charge creuse (non représentée).
Il comporte également, sur son diamètre extérieur, des
ailerons 16 régulièrement répartis angulairement (ici au nombre
de 6).It also has, on its outside diameter,
L'arrière du projectile comprend un support d'ailettes 5
constitué d'une portée cylindrique 19 et d'une collerette
annulaire 17. La portée cylindrique 19 du support d'ailettes est
ajustée à l'intérieur d'un alésage 20, réalisé à la partie
arrière du corps 3, et la collerette 17 est en butée contre la
face arrière du corps. Cela permet d'assurer la solidarisation,
par exemple par collage, du support d'ailettes 5 sur le corps 3.The rear of the projectile includes a
Le support d'ailettes 5 comporte, au niveau de sa collerette
annulaire 17, un empennage 6 de diamètre sensiblement égal au
diamètre interne du tube de lancement du projectile. The
L'empennage 6 est composé d'ailettes de stabilisation 7 (ici au nombre de 6).The empennage 6 is composed of stabilization fins 7 (here 6 in number).
La collerette 17 comporte au niveau de son diamètre externe, des chapes 18 qui
reçoivent les ailettes 7 montées de façon pivotantes autour d'un axe 8.The
Les ailettes 7 se déploient à la sortie du tube de lancement sous l'action d'un
dispositif de déploiement qui sera décrit plus loin.The
Les chapes 18 et les ailerons 16 assurent le guidage du projectile pendant sa
propulsion à l'intérieur du tube de lancement.The
La figure 2 représente le support d'ailettes 5 équipé de son empennage 6, dans
la position qu'il occupe lorsqu'il est placé dans le tube de lancement, c'est à dire
ailettes de stabilisation rabattues le long du corps du projectile.FIG. 2 represents the
L'empennage 6 comprend six ailettes 7 régulièrement espacées angulairement.The empennage 6 comprises six
Un ressort de torsion cylindrique 9 à action angulaire est placé à proximité de
chaque ailette et sert d'organe élastique permettant le déploiement de celle-ci. Il est
disposé à l'intérieur d'une rainure 10, aménagée dans la collerette 17 du support
d'ailettes 5, parallèlement à l'axe XX' du projectile.A
La rainure 10, qui est destinée à assurer le guidage du ressort cylindrique 9,
présente une largeur supérieure au diamètre extérieur du ressort, afin d'autoriser
l'éjection de ce dernier.The
L'extrémité 11 du ressort 9, perpendiculaire à l'axe YY' de ce dernier, est placé
en appui contre la face inférieure de l'ailette alors que l'autre extrémité 12 est solidaire
du support d'ailettes 5.The
La figure 3 représente le support d'ailettes 5 seul suivant la direction F de la
figure 2.FIG. 3 represents the
La face arrière 13 du support d'ailette 5 présente, au niveau de chaque rainure
10, un orifice 14 d'axe parallèle à l'axe XX' du projectile et un dégagement 15 reliant
l'orifice à la rainureThe
L'extrémité 12 du ressort comprend une partie 21 coudée à 90°, d'axe parallèle
à l'axe YY' du ressort (voir figure 5).The
Dans la position telle que représentée à la figure 2, l'extrémité 12 du ressort 9
passe dans le dégagement 15 qui présente une profondeur et une largeur légèrement
supérieure au diamètre du fil du ressort 9, afin que celui-ci soit en retrait par rapport à
la face arrière 13 du support d'ailettes.In the position as shown in Figure 2, the
La partie coudée 21 pénètre à l'intérieur de l'orifice 14 qui présente un diamètre
légèrement supérieur au diamètre du fil composant le ressort.The
Le ressort est ainsi guidé par la rainure 10 et solidaire radialement du support
d'ailettes par le dégagement 15 et l'orifice 14. L'extrémité 11 qui est proche de la
collerette 17, maintient le ressort axialement, de manière temporaire. The spring is thus guided by the
Dans cette position, le ressort cylindrique à action angulaire est contraint en torsion. Il exerce un effort sur l'ailette, ce qui permet d'assurer, dès la sortie du projectile hors du tube de lancement, l'initiation du déploiement de chaque ailette correspondante.In this position, the cylindrical spring with angular action is constrained in torsion. It exerts a force on the fin, which ensures, right out of the projectile out of the launch tube, initiation of deployment of each fin corresponding.
Dès que le ressort 9 a terminé le déploiement de l'ailette, il se retrouve libre de
se translater vers l'arrière du projectile, l'extrémité 11 n'interférant plus avec la
collerette 17 (voir figure 4).As soon as the
Sous l'effet des forces aérodynamiques, la partie coudée 21 du ressort sort de
l'orifice 14 et le ressort est éjecté et ne risque plus ainsi de perturber le vol du
projectile (voir figure 5).Under the effect of aerodynamic forces, the
Claims (6)
- A device to deploy a stabilizing fin (7) of a projectile (1), comprising a torsion spring (9) whose axis (YY') is parallel to the projectile axis (XX'), said device characterized in that the spring is placed near to the fin and arranged in a groove (10) made in a support (5) connected to the projectile and on which the fin (7) is mounted, one of the ends (12) of the spring being integral with the support and the other end (11) pressing against a lower face of the fin (7), said spring (9) being under torsional stress when the fin is folded back and therefore exerting a load able to make the fin pivot with respect to the support so as to deploy it.
- A device according to Claim 1, characterized in that the groove (10) is of a length greater than the external diametre of the spring (9), thereby enabling it to be ejected after the deployment of the fin (7).
- A device according to any one of Claims 1 or 2, characterized in that at one of its ends, the spring (9) has a part (21) bent at 90° with an axis parallel to the spring axis (YY').
- A device according to Claim 3, characterized in that the spring (9)is made radially integral with the support (5) by means of the bent part (21)which penetrates into an aperture (14) made in the rear face (13) of the support, said aperture having an axis parallel to the projectile axis (XX') and being of a greater diametre than the diametre of the wire constituting the spring, thereby enabling said spring to be ejected after deployment of the fin.
- A device according to Claim 4, characterized in that the rear face (13) of the support incorporates a recess (15) connecting the groove (10) to the aperture (14) and enabling one end (12) of the spring to pass through, said recess being of a depth and width greater than the diametre of the wire constituting the spring, thereby enabling said spring to be ejected after deployment of the fin.
- A device according to any one of Claims 1 to 5, characterized in that the end (11) of the spring lies in the vicinity of a collar (17) of the support (5) which ensures the axial hold (9) of the spring when the fin (7) is in its folded position.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR9313617A FR2712679B1 (en) | 1993-11-16 | 1993-11-16 | Deployment device for a rocket-type projectile stabilization fin. |
| FR9313617 | 1993-11-16 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0653604A1 EP0653604A1 (en) | 1995-05-17 |
| EP0653604B1 true EP0653604B1 (en) | 1998-07-29 |
Family
ID=9452873
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP19940402075 Expired - Lifetime EP0653604B1 (en) | 1993-11-16 | 1994-09-19 | Stabilising for deployment device for a rocket type projectile |
Country Status (3)
| Country | Link |
|---|---|
| EP (1) | EP0653604B1 (en) |
| DE (1) | DE69412036T2 (en) |
| FR (1) | FR2712679B1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SG101481A1 (en) * | 2001-09-18 | 2004-01-30 | Singapore Tech Dynamics Pte | A foldable wing structure for airborne vehicle or the like |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3032212B1 (en) * | 2014-12-11 | 2017-07-26 | MBDA Deutschland GmbH | Rudder system |
| DE102015004702A1 (en) | 2014-12-11 | 2016-06-16 | Mbda Deutschland Gmbh | rudder system |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2342783C2 (en) * | 1973-08-24 | 1983-12-22 | Rheinmetall GmbH, 4000 Düsseldorf | Projectile equipped with a tail unit |
| SE429266B (en) * | 1977-02-09 | 1983-08-22 | Bofors Ab | TILT PARTY PROVIDED FOR AN EXTENSIBLE WINDOW STABLED GRANATE |
| US4523728A (en) * | 1983-03-07 | 1985-06-18 | Ford Aerospace & Communications Corporation | Passive auto-erecting alignment wings for long rod penetrator |
| DE3664164D1 (en) * | 1985-03-23 | 1989-08-03 | British Aerospace | Fin erecting mechanisms |
-
1993
- 1993-11-16 FR FR9313617A patent/FR2712679B1/en not_active Expired - Fee Related
-
1994
- 1994-09-19 DE DE1994612036 patent/DE69412036T2/en not_active Expired - Fee Related
- 1994-09-19 EP EP19940402075 patent/EP0653604B1/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SG101481A1 (en) * | 2001-09-18 | 2004-01-30 | Singapore Tech Dynamics Pte | A foldable wing structure for airborne vehicle or the like |
Also Published As
| Publication number | Publication date |
|---|---|
| DE69412036D1 (en) | 1998-09-03 |
| DE69412036T2 (en) | 1998-12-03 |
| EP0653604A1 (en) | 1995-05-17 |
| FR2712679A1 (en) | 1995-05-24 |
| FR2712679B1 (en) | 1996-02-09 |
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