EP1548392A1 - Vorrichtung zur Entfaltung der Steuerflächen eines Projektils - Google Patents

Vorrichtung zur Entfaltung der Steuerflächen eines Projektils Download PDF

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Publication number
EP1548392A1
EP1548392A1 EP04292926A EP04292926A EP1548392A1 EP 1548392 A1 EP1548392 A1 EP 1548392A1 EP 04292926 A EP04292926 A EP 04292926A EP 04292926 A EP04292926 A EP 04292926A EP 1548392 A1 EP1548392 A1 EP 1548392A1
Authority
EP
European Patent Office
Prior art keywords
star
projectile
fins
deployment device
inertial
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.)
Withdrawn
Application number
EP04292926A
Other languages
English (en)
French (fr)
Inventor
Grégoire Agnelot
Jean-François Pierrot
Vincent Cady
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.)
Nexter Munitions SA
Original Assignee
Giat Industries SA
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Giat Industries SA filed Critical Giat Industries SA
Publication of EP1548392A1 publication Critical patent/EP1548392A1/de
Withdrawn legal-status Critical Current

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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 ensuring the deployment of fins stabilization for projectiles.
  • the fins deployment devices are well known. These devices use for example the pressure of the aerodynamic flow received by the fins (solution described by FR2721702) or a borrowing of propellant gases of the weapon (solution described by US4702436).
  • Gas-based solutions have reliability insufficient because of the highly erosive nature of the gases propulsion.
  • the fin deployment device according to the invention can be implemented to control the deployment of a tail stabilizer rear.
  • This device may also, given its compactness, to be used to deploy duck rudders carried by a front part of a projectile.
  • the subject of the invention is a device for deployment of projectile fins, comprising a lock means ensuring the simultaneous immobilization of all the fins in the folded position, device characterized in that it comprises an actuator releasing the medium lock when firing, actuator comprising a inertial flyweight.
  • the lock means comprises a star pivotally mounted relative to an axis of the projectile, star with arms and each arm having an end carrying a hook engaged in a notch of a fin to ensure its immobilization.
  • the star will be advantageously pivotally mounted against the action of a spring means having the effect of clearing the hooks of their notches to ensure the release of fins.
  • the star may be immobilized in rotation by at least a finger integral with the inertial flyweight.
  • the inertial flyweight can be attached to a tray carrying a finger for each fin.
  • the device has a braking means to slow down the pivoting of the star.
  • This braking means may be constituted by a disk of friction interposed between the star and the body of the projectile.
  • the star can be held in support against the disc friction by an elastic cup.
  • the device may include means for locking of the flyweight relative to the projectile body after its recoil under the effect of shooting inertia.
  • Figures 1 and 2 show in section a front part of a projectile 1 carrying four duck rudders 2a, 2b, 2c 2d. This projectile is intended to fly along the AV arrow shown in Figure 1.
  • the control surfaces 2 provide a stabilization of the projectile.
  • Each rudder is pivotally mounted about an axis 3 integral with the projectile.
  • a spiral spring 4 is mounted around of each axis 3. It is supported on one side on the body of projectile and the other on a rim of the fin. This spring 4 has the effect of rotating the fin to bring it into the deployed position.
  • the four fins are held in their position folded, against the action of the springs 4, thanks to a means lock 5.
  • the lock means 5 comprises a star 6 which is mounted pivoting on a cylindrical support 7 which is coaxial with axis 8 of the projectile 1.
  • the star 6 has four arms 6a, 6b, 6c and 6d and each arm carries at its end a hook 9a, 9b, 9c or 9d which is engaged in a notch 10a, 10b, 10c or 10d of a fin for ensure its immobilization in the folded position.
  • a spiral spring 11 is disposed in a housing 21 of the star 6. It is interposed between the star 6 and the support 7. This spring is in the banded condition when the device is in the folded fins position shown in Figures 1 and 2. It has the effect of turn the star 6 counterclockwise shows in Figure 2, ie in the sense that clears the hooks 9a, 9b, 9c and 9d out of the notches 10a, 10b, 10c and 10d.
  • a friction disk 19 made of a thermoplastic material or elastomer is interposed between the star 6 and the body of the projectile 1.
  • a pressing force between the disc of friction 19, the star 6 and the body of the projectile 1 is provided by a cup 20 of elastic material which is disposed in the housing 21 of the star 6.
  • the cup 20 is locked axially by an elastic ring 22 positioned on axis 7.
  • the axial pressing force is ensured by the deformation elastic of the cup after mounting the ring 22.
  • the cup 20 has a V-shaped light (not visible on the figures) which allows to release the connection of the spring spiral 11 and star 6.
  • the cup also ensures the protection of the spring 11 and it contains a lubricating agent for this latest.
  • the friction disc 19 has the function of ensuring a braking of the rotation movement of the star 6. Braking can be adjusted by modifying the pressure effort given by the cup 20.
  • the star 6 is immobilized against the action of the spring 11 by a plate 12 carrying four fingers cylindrical 13a, 13b, 13c and 13d (see Figure 2).
  • Each finger 13 is in contact with one of the arms of the star 6.
  • the plate 12 is integral with an inertial flyweight 14 which is slidably mounted in a bore 15 of a portion 1a of the projectile body 1 (the connecting means between this part 1a and the rest of the projectile body are not shown in the figures).
  • the weight 14 is guided in translation by a radial pin 16 which cooperates with two grooves 18 of the bore 15 (see also Figure 3).
  • the weight 14 constitutes an actuator capable of release the lock means 5 when firing.
  • the weight is locked on an elastic ring 23 which is disposed in a groove in the bottom of the bore 15. effect it has a groove 24 inside which penetrates the ring 23.
  • the fins are released only when the projectile is out of the tube of the weapon (a delay of 20 milliseconds is sufficient). This avoids any contact between the fins and the inner wall of the barrel of the weapon.
  • FIGS 3 and 4 show the device in the deployed position.
  • Each fin 2 is immobilized in position deployed by a leaf spring 25 which cooperates with a heel 26 carried by the fin.
  • the invention has been described here applied to deployment of duck wings arranged at a front portion of a projectile. It would of course be possible to put it in works for a rear stabilizer stabilizer.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
EP04292926A 2003-12-24 2004-12-09 Vorrichtung zur Entfaltung der Steuerflächen eines Projektils Withdrawn EP1548392A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0315486 2003-12-24
FR0315486A FR2864612B1 (fr) 2003-12-24 2003-12-24 Dispositif de deploiement des ailettes d'un projectile

Publications (1)

Publication Number Publication Date
EP1548392A1 true EP1548392A1 (de) 2005-06-29

Family

ID=34531362

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04292926A Withdrawn EP1548392A1 (de) 2003-12-24 2004-12-09 Vorrichtung zur Entfaltung der Steuerflächen eines Projektils

Country Status (2)

Country Link
EP (1) EP1548392A1 (de)
FR (1) FR2864612B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2955653A1 (fr) * 2010-01-28 2011-07-29 Nexter Munitions Dispositif de deploiement simultane de gouvernes d'un projectile
CN109186370A (zh) * 2018-07-26 2019-01-11 重庆长安工业(集团)有限责任公司 一种折叠翼面展开机构
EP3543640A3 (de) * 2018-03-21 2020-01-08 Diehl Defence GmbH & Co. KG Geschoss mit ausschwenkbaren flügeln und einem gemeinsamen, um die längsachse verdrehbaren arretierbauteil zum lösbaren arretieren der flügel in der eingeschwenkten position

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB903842A (en) * 1958-04-04 1962-08-22 Bombrini Parodi Delfino Spa Improvements in pivotal fin assemblies for rocket propelled projectiles
US3234878A (en) * 1962-10-05 1966-02-15 Soc Tech De Rech Ind Powder-fuelled rocket
US3819132A (en) * 1973-02-21 1974-06-25 Sarmac Sa Self propelled projectile with fins
US4351499A (en) * 1979-09-24 1982-09-28 General Dynamics Double fabric, retractable, self-erecting wing for missle
US4702436A (en) 1984-12-13 1987-10-27 Affarsverket Ffv Projectile guide mechanism
FR2721702A1 (fr) 1994-06-28 1995-12-29 Luchaire Defense Sa Dispositif de déploiement d'une ailette de projectile.
US6073880A (en) * 1998-05-18 2000-06-13 Versatron, Inc. Integrated missile fin deployment system
US6446906B1 (en) 2000-04-06 2002-09-10 Versatron, Inc. Fin and cover release system

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE379532A (de) * 1930-05-22
FR2070389A5 (de) * 1969-12-03 1971-09-10 Serat
DE3507677A1 (de) * 1985-03-05 1986-09-11 Diehl GmbH & Co, 8500 Nürnberg Flugkoerper mit ueberkalibrigem leitwerk
DE3721512C1 (de) * 1987-06-30 1989-03-30 Diehl Gmbh & Co Flugkoerper mit ueberkalibrigem Leitwerk

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB903842A (en) * 1958-04-04 1962-08-22 Bombrini Parodi Delfino Spa Improvements in pivotal fin assemblies for rocket propelled projectiles
US3234878A (en) * 1962-10-05 1966-02-15 Soc Tech De Rech Ind Powder-fuelled rocket
US3819132A (en) * 1973-02-21 1974-06-25 Sarmac Sa Self propelled projectile with fins
US4351499A (en) * 1979-09-24 1982-09-28 General Dynamics Double fabric, retractable, self-erecting wing for missle
US4702436A (en) 1984-12-13 1987-10-27 Affarsverket Ffv Projectile guide mechanism
FR2721702A1 (fr) 1994-06-28 1995-12-29 Luchaire Defense Sa Dispositif de déploiement d'une ailette de projectile.
US6073880A (en) * 1998-05-18 2000-06-13 Versatron, Inc. Integrated missile fin deployment system
US6446906B1 (en) 2000-04-06 2002-09-10 Versatron, Inc. Fin and cover release system

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2955653A1 (fr) * 2010-01-28 2011-07-29 Nexter Munitions Dispositif de deploiement simultane de gouvernes d'un projectile
EP2354755A1 (de) * 2010-01-28 2011-08-10 Nexter Munitions Vorrichtung zum simultanen Ausklappen von Steuerflächen eines Geschosses
US8592737B2 (en) 2010-01-28 2013-11-26 Nexter Munitions Device for simultaneous deployment of the control surfaces of a projectile
EP3543640A3 (de) * 2018-03-21 2020-01-08 Diehl Defence GmbH & Co. KG Geschoss mit ausschwenkbaren flügeln und einem gemeinsamen, um die längsachse verdrehbaren arretierbauteil zum lösbaren arretieren der flügel in der eingeschwenkten position
CN109186370A (zh) * 2018-07-26 2019-01-11 重庆长安工业(集团)有限责任公司 一种折叠翼面展开机构

Also Published As

Publication number Publication date
FR2864612B1 (fr) 2007-11-23
FR2864612A1 (fr) 2005-07-01

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