EP0653604B1 - Entfaltungseinrichtung für Stabilisatorflügel eines Raketengeschosses - Google Patents

Entfaltungseinrichtung für Stabilisatorflügel eines Raketengeschosses Download PDF

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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
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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
Application number
EP19940402075
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English (en)
French (fr)
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EP0653604A1 (de
Inventor
Bruno Lang
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Luchaire Defense SA
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Luchaire Defense SA
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Filing date
Publication date
Application filed by Luchaire Defense SA filed Critical Luchaire Defense SA
Publication of EP0653604A1 publication Critical patent/EP0653604A1/de
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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.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)

Claims (6)

  1. Vorrichtung zum Ausbreiten von Stabilisierungsflügeln (7) eines Geschosses (1) mit einer Torsionsfeder (9), deren Achse (YY') zur Achse (XX') des Geschosses parallel steht, gekennzeichnet dadurch, daß sich die Feder am Ende des Flügels in einer Rille (10) befindet, die in einem Träger (5) angeordnet ist, der mit dem Geschoß verbunden ist, und auf dem der Flügel (7) montiert ist, wobei eines der Enden (12) der Feder fest mit dem Träger verbunden ist und das andere Ende (11) der Feder an einer Innenfläche des Flügels (7) anliegt, wobei die Feder (9) verdreht wird, wenn der Flügel zurückgefaltet wird und dann eine Kraft ausübt, die den Flügel bezogen auf den Träger so schwenkt, daß sich der Flügel ausbreitet.
  2. Vorrichtung gemäß Anspruch 1, gekennzeichnet dadurch, daß die Rille (10) eine Breite hat, die größer ist als der Außendurchmesser der Feder (9), so daß diese nach dem Ausbreiten des Flügels (7) ausgeworfen werden kann.
  3. Vorrichtung gemäß einem der Ansprüche 1 oder 2, gekennzeichnet dadurch, daß die Feder (9) an einem ihrer Enden einen um 90° abgewinkelten Teil (21) aufweist, dessen Achse zur Achse (YY') der Feder parallel ist.
  4. Vorrichtung gemäß Anspruch 3, gekennzeichnet dadurch, daß die Feder (9) radial fest durch Eindringen des abgewinkelten Teils (21) in eine Öffnung (14) in der hinteren Fläche (13) des Trägers mit dem Träger (5) verbunden wird, wobei die Achse der Öffnung zur Achse (XX') des Geschosses parallel liegt und einen Durchmesser hat, der größer ist als der Durchmesser des Drahts, aus dem die Feder besteht, wodurch das Auswerfen der Feder nach dem Ausbreiten des Flügels möglich wird.
  5. Vorrichtung gemäß Anspruch 4, gekennzeichnet dadurch, daß die hinter Fläche (13) des Trägers eine Aussparung (15) aufweist, die eine Rille (10) mit der Öffnung (14) verbindet und das Passieren des Endes (12) der Feder erlaubt, wobei die Aussparung eine Tiefe und eine Breite aufweist, die größer sind als der Durchmesser des Drahts, aus dem die Feder besteht, so daß die Feder nach dem Aufbreiten des Flügels ausgeworfen werden kann.
  6. Vorrichtung gemäß einem beliebigen der Ansprüche 1 bis 5, gekennzeichnet dadurch, das das Ende (11) der Feder in der Nähe eines Kragens (17) des Trägers (5) liegt, der das axiale Halten der Feder (9) sicherstellt, während sich der Flügel (7) in zurückgefalteter Stellung befindet.
EP19940402075 1993-11-16 1994-09-19 Entfaltungseinrichtung für Stabilisatorflügel eines Raketengeschosses Expired - Lifetime EP0653604B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9313617A FR2712679B1 (fr) 1993-11-16 1993-11-16 Dispositif de déploiement pour une ailette de stabilisation de projectile de type roquette.
FR9313617 1993-11-16

Publications (2)

Publication Number Publication Date
EP0653604A1 EP0653604A1 (de) 1995-05-17
EP0653604B1 true EP0653604B1 (de) 1998-07-29

Family

ID=9452873

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19940402075 Expired - Lifetime EP0653604B1 (de) 1993-11-16 1994-09-19 Entfaltungseinrichtung für Stabilisatorflügel eines Raketengeschosses

Country Status (3)

Country Link
EP (1) EP0653604B1 (de)
DE (1) DE69412036T2 (de)
FR (1) FR2712679B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
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)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015004702A1 (de) 2014-12-11 2016-06-16 Mbda Deutschland Gmbh Rudersystem
EP3032212B1 (de) * 2014-12-11 2017-07-26 MBDA Deutschland GmbH Rudersystem

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2342783C2 (de) * 1973-08-24 1983-12-22 Rheinmetall GmbH, 4000 Düsseldorf Mit einem Leitwerk versehenes Geschoß
SE429266B (sv) * 1977-02-09 1983-08-22 Bofors Ab Stjertparti avsett for en i ett eldror utskjutbar fenstabiliserad granat
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

Cited By (1)

* Cited by examiner, † Cited by third party
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 (de) 1998-09-03
EP0653604A1 (de) 1995-05-17
DE69412036T2 (de) 1998-12-03
FR2712679B1 (fr) 1996-02-09
FR2712679A1 (fr) 1995-05-24

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