EP0724132B1 - Vorrichtung zum Sichern und Schärfen des Zünders eines Geschosses - Google Patents

Vorrichtung zum Sichern und Schärfen des Zünders eines Geschosses Download PDF

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Publication number
EP0724132B1
EP0724132B1 EP19960400069 EP96400069A EP0724132B1 EP 0724132 B1 EP0724132 B1 EP 0724132B1 EP 19960400069 EP19960400069 EP 19960400069 EP 96400069 A EP96400069 A EP 96400069A EP 0724132 B1 EP0724132 B1 EP 0724132B1
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EP
European Patent Office
Prior art keywords
rotor
ring
safety
housing
projectile
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
EP19960400069
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English (en)
French (fr)
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EP0724132A1 (de
Inventor
Jacques Nicolas
Jean-Paul Oberle
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.)
Manurhin Defense SA
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Manurhin Defense SA
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Filing date
Publication date
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Publication of EP0724132A1 publication Critical patent/EP0724132A1/de
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Publication of EP0724132B1 publication Critical patent/EP0724132B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/18—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved
    • F42C15/188—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved using a rotatable carrier
    • F42C15/192—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved using a rotatable carrier rotatable in a plane which is parallel to the longitudinal axis of the projectile
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/18—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved
    • F42C15/188—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved using a rotatable carrier
    • F42C15/192—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved using a rotatable carrier rotatable in a plane which is parallel to the longitudinal axis of the projectile
    • F42C15/196—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved using a rotatable carrier rotatable in a plane which is parallel to the longitudinal axis of the projectile by the action of centrifugal or inertia forces on the carrier body, e.g. the carrier having eccentrically mounted weights or eccentric centre of gravity

Definitions

  • the field of the present invention is that of safety and arming devices for rockets intended to equip revolving projectiles. These devices have the function of ensuring the maintenance misaligned with a pyrotechnic initiation chain of the projectile, which guarantees safety during the ammunition storage and handling.
  • Such devices include the more often a starter rotor having an imbalance. This rotor is held in a misaligned position by a or more locks and it adopts by itself, by effect gyro, an aligned position when the locks are released.
  • Patent FR2689972 describes such a device in which the rotor is arranged in a cage mounted freely in rotation around the axis of the rocket. The rotor is returned secured to the cage in a misaligned position, of a part by means of radial pins held in place by a hairspring, and on the other hand with an axial lock which disappears when fired by the action of inertia forces.
  • Such a device therefore comprises a first means lock released by axial acceleration developed during the first moments of the shot, and a second locking means (the radial pins) released by the maximum angular acceleration appearing when the projectile is at the exit of the tube tear.
  • the release of this second means of locking is timed by the unwinding of the hairspring.
  • FR2689972 patent provides this device with means for immobilizing the axial lock which are sufficiently rigid.
  • Such a device is complex and includes a large number of moving parts. It is therefore expensive to make and assemble.
  • Patent EP360187 describes a device for safety in which the rotor is mounted sliding in a cage. This rotor is held between two spans spherical, one of which is arranged at the bottom of the cage and the other is carried by a cover. It is immobilized in safety position by a split ring, held in support on an annular seat of the rotor by a spring of compression. The ring is released by joint action axial and radial inertia forces, which is detrimental to the security of the device.
  • the device according to the invention is of simple and inexpensive design because it uses little parts and its assembly is simplified.
  • the device according to the invention also allows move the rotor away from the pyrotechnic chain main, which increases the security of the device and facilitates its adaptation to different types of rockets.
  • the device according to the invention makes it possible to maintain the rotor by at least two locking means which are sensitive each to an environmental effort of a different nature.
  • the device according to the invention also makes it possible to avoid wear on the surfaces of support which is caused by the vibrations undergone during transports.
  • the subject of the invention is a device for safety for a rocket intended to equip a projectile girant, device comprising a rotor which carries a initiates and is maintained by at least one means of locking in a position in which the primer is not aligned with a pyrotechnic chain, this device is characterized in that it comprises a ring holding axially sliding and carrying a cap spherical on which the rotor is resting, ring holding which in a safety position of the device, is kept applied to the rotor by elastic return means and which thus ensures the axial maintenance of the rotor in a locked position, the rotor being able to move axially with the ring when arming the device.
  • a first locking means is constituted by a flat arranged on the rotor, flat which, in the position of safety of the device, is maintained by the ring in support on a flat surface of the device.
  • the elastic return means are constituted advantageously by a split elastic ring placed in a peripheral groove of the ring and which, in the device safety position, comes to bear against a conical surface of the device, conical surface oriented so as to maintain the ring in safety position, and to allow the rod in the throat by the action of inertia efforts longitudinal developed during the firing of the projectile.
  • the safety device comprises a housing intended for receive the elastic ring when the ring has slid under the effect of the inertia forces developed during the shooting of the projectile, the elastic ring being dimensioned so as to be permanently open by efforts of centrifugal inertia developed during firing, this opening ensuring its positioning in the housing, which axially locks the retaining ring in an armed position which frees the rotor from its support against the flat surface.
  • the second plea locking consists of a deformable cage surrounding the rotor at an equatorial region of this one and likely to open by the action of centrifugal inertia forces developed when firing the projectile.
  • This cage can be surrounded by a hairspring ensuring a delay of its opening.
  • the cage can be maintained by the ring pressing against a surface of the device.
  • the distance in position of safety between the outer spherical surface of the rotor and the main pyrotechnic chain is sufficiently important to prohibit an initiation of this last but in the armed position this distance is low enough to allow initiation.
  • the elastic return means may be chosen rigid enough to maintain the support of the ring on the rotor when the device is subjected to shock or vibration constraints. These means thus prohibit any vibration of the moving parts which could lead to wear of the bearing surfaces.
  • a warhead rocket 1 is intended to be fixed to a front part of a gyro-stabilized projectile (not shown), for example a medium caliber projectile (less than 50 mm).
  • this rocket includes a striker 2, a security and arming device 3 and a pyrotechnic relay 23.
  • the striker here carries a collar 2a which allows to make it integral in translation with the body of the rocket 1.
  • a primer (not shown here) arranged in the security and arming device 3.
  • This primer in turn initiates relay 23 which causes the detonation an explosive charge contained in the projectile (not shown).
  • Figure 2 shows the safety device and cocking 3 in the safety position which is the before the projectile is fired.
  • the device 3 comprises a box 4 closed by a cover 5 fixed to the housing by thread.
  • the cover 5 carries a reinforcing pyrotechnic charge 6 intended for be initiated by the primer and in turn initiate the relay 23.
  • Load 6 communicates with the interior of the device by a hole 5a, and it is isolated from air humidity by sealing flakes (or again by a thin partition secured to the cover).
  • the bottom of the housing 4 is pierced by an orifice 7 intended to let the striker pass 2.
  • a rotor 8 substantially spherical and having an unbalance is placed in a bore 9 of the housing 4.
  • This rotor has a housing 10 inside which is placed the primer.
  • the housing 10 is shown in lines interrupted in the different figures. In the position of the device, the axis 11 of the housing 10 is inclined to the axis 12 of the rocket (and projectile), which prohibits both the initiation of initiation by striker 2 and transmission of a accidental initiation of the charge initiation 6.
  • the rotor 8 carries a flat 13 which, in the safety position of the device, is in support on a flat surface 14 forming the bottom of the housing 4.
  • the rotor is held in its position safety, pressing against the bottom of the case, by a retaining ring 15, which is mounted so that it can slide axially in the bore 9 of the housing 4.
  • the outer diameter of the ring is less than a few hundredths of a mm to that of bore 9 and the length of the ring is chosen sufficient to ensure good guidance.
  • the ring 15 carries a spherical cap 16 on which the rotor 8 is in abutment and an axial bore 15a.
  • the ring 15 is kept applied to the rotor by elastic return means constituted by a split rod 17.
  • the flat 13 cooperates with the bottom of the housing 4 to constitute a first means for locking the rotor in its safety position.
  • the elastic ring 17 is placed in a groove peripheral 18 of ring 15 and it comes to bear against a conical surface 19 arranged on the surface internal bore 9.
  • the base of the conical surface 19 is oriented on the side of the bottom 14 of the housing. So she maintains by the ring 15 of the rotor 8 in its position locked by flat 13.
  • the groove 18 has a depth greater than the diameter of the wire constituting the rod 17, so when this last one is compressed radially, it can be housed entirely in the throat and allow the translation of the ring 15 in the housing 4.
  • the bore 9 also carries a counterbore 20 arranged in the vicinity of the cover 5 and which is intended for constitute a housing for the rod 17 in the position army of the device.
  • the rotor 8 has an external cylindrical bearing constituting an equatorial zone 21.
  • a deformable cage split 22 surrounds the rotor 8 at this area equatorial and constitutes a second means of locking the rotor in its safety position.
  • the height of the equatorial zone is chosen sufficient to maintain the rotor by the cage. This height will for example be of the order of 25% of the diameter of the rotor.
  • the deformable cage 22 is held by the ring 15 pressing against the bottom 14 of the housing 4.
  • Such arrangement increases the rigidity of the device.
  • the ring thus prevents the opening of the cage, which increases safety and avoids all friction and deterioration of surfaces due to the influence of vibrations during the storage or transport phases of the projectile. This significantly improves the reliability of operation of rockets which must withstand severe mechanical environments during their storage and their transport.
  • the cage will be made for example of a material elastic, such as a flexible metal blade made of steel stainless or brass. It may also be made of a plastic material (for example the polytetrafluoroethylene known under the registered trademark "Teflon").
  • Teflon polytetrafluoroethylene known under the registered trademark "Teflon”
  • the elastic ring 17 will be chosen sufficiently rigid to maintain the support of the ring on the rotor when the device is subjected to constraints of shock or vibration, for example during the phases of storage or transport of the projectile.
  • the rotor when the device is located in its safety position, the rotor is at a distance D from the pyrotechnic charge 6.
  • the distance D is large enough to prohibit a initiation of charge 6 by the primer when the rotor is oriented with its axis 11 coincident with that of the device 12. This increases the safety of the device.
  • Figure 3 shows the device according to the invention at the time of firing, when the acceleration longitudinal caused the displacement of the ring 15 and its arrival in abutment against the cover 5.
  • the elastic ring 17 enters the housing 20 and thus ensures the joining of the ring 15 and the housing 4.
  • the rotor 8 follows the ring 15 in its movement.
  • the flat 13 thus emerges from the bottom 14 of the housing 4. The first means of locking the rotor is therefore released.
  • the device will of course be defined in such a way so that the displacement of the ring is sufficient to allow subsequent rotation of the rotor without interference with the bottom 14 of the housing.
  • the device is represented here in the first moments of the shooting.
  • the rotation communicated to the projectile through the gun barrel is still insufficient and the cage 22 remains applied against equatorial zone 21 of rotor, still immobilizing the latter in a position safety with its axis 11 inclined relative to the axis 12 of the device.
  • Figure 4 shows the device according to the invention at the exit of the barrel of the weapon. Acceleration angle communicated by the scratches on the barrel of the weapon a caused the opening of the cage 22 which is plated against the wall of the bore 9 of the housing.
  • the rotor 8 released from its second means of lock, adopted by gyroscopic effect a position in which its main axis of inertia 11 is coincident with axis 12 of the device.
  • the housing 10 of the primer is aligned with axis 12 and the sensitive face of the primer is in look at the end of the striker 2.
  • the primer initiates the reinforcing charge 6 at through holes 15a and 5a, the load 6 ensuring initiation of relay charge 23.
  • Figures 2 to 4 described above are simplified representations of the device in which the functional clearances between the different rooms have been intentionally exaggerated.
  • the clearance J1 (figure 4) which separates the rotor and the cage is of the order of a few tenths of mm. So the cage does not prevent movement gyroscopic of the rotor but it ensures however a radial guidance of the latter and guarantees its maintenance in a position such that the main axis 11 is aligned with axis 12 of the device.
  • a first means for locking the rotor of different structure For example a stud secured to the bottom of the housing 4 and cooperating with additional accommodation in the rotor. In this case, the displacement of the rotor following the ring 15 will release the stud from its housing in the rotor.
  • the device according to the invention is of course usable in gyrostabilized projectiles of any caliber.
  • the main pyrotechnic chain initiated by the primer can of course be of a different nature.
  • the reinforcing filler 6 can be omitted and the primer can directly initiate relay load 23.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Emergency Lowering Means (AREA)
  • Vibration Dampers (AREA)

Claims (9)

  1. Sicherungsvorrichtung (3) für einen Zünder (1), dazu bestimmt, ein gyrierendes Geschoß auszurüsten, wobei die Vorrichtung einen Rotor (8) umfaßt, der einen Zünder trägt und von mindestens einem Verriegelungsmittel in der Position gehalten wird, in welcher der Zünder nicht mit einer pyrotechnischen Kette ausgerichtet ist, gekennzeichnet dadurch, daß er einen Haltering (15) umfaßt, der axial gleitet und eine sphärische Haube trägt, auf welcher der Rotor (8) anliegt, wobei der Haltering in der Sicherungsstellung der Vorrichtung von elastischen Rückholmitteln gegen den Rotor (8) gehalten wird, und der damit das axiale Halten des Rotors in einer verriegelten Stellung sicherstellt, wobei der Rotor sich axial mit dem Ring beim Entsichern der Vorrichtung verschieben kann.
  2. Sicherungsvorrichtung gemäß dem Anspruch 1, gekennzeichnet dadurch, daß ein erstes Verriegelungsmittel aus einer Abflachung (13) besteht, die auf dem Rotor (8) angeordnet ist, welche Abflachung in der Sicherungsposition der Vorrichtung vom Ring (15) auf eine ebene Fläche (14) der Vorrichtung gedrückt wird.
  3. Sicherungsvorrichtung gemäß einem der Ansprüche 1 oder 2, gekennzeichnet dadurch, daß die elastischen Rückholmittel aus einem Federring (17) bestehen, der in einer peripheren Hohlkehle (18) des Rings (15) angeordnet ist und der in der Sicherungsposition der Vorrichtung gegen eine kegelförmige Oberfläche (19) der Vorrichtung zum Aufliegen kommt, welche kegelförmige Oberfläche so orientiert ist, daß sie das Halten des Rings (15) in der Sicherungsstellung gewährleistet, und das Eindringen des Federrings (17) in die Hohlkehle (18) durch Wirken der Längsträgheitskräfte erlaubt, die beim Abschießen des Geschosses entstehen.
  4. Sicherungsvorrichtung gemäß dem Anspruch 3, gekennzeichnet dadurch, daß sie eine Aussparung (20) umfaßt, die dazu bestimmt ist, einen Federring (17) aufzunehmen, wenn sich der Ring (15) unter der Einwirkung der beim Abschuß des Geschosses entwickelten Trägheitskräfte verschoben hat, wobei der Federring so bemaßt ist, daß er ständig von den Zentrifugalträgheitskräften geöffnet wird, die sich beim Abschuß entwickeln, wobei diese Öffnung seine Positionierung in der Aussparung (20) sicherstellt, was den Haltering (15) axial in der entsicherten Stellung verriegelt, die den Rotor (8) von seiner Auflage gegen die ebene Fläche (14) freigibt.
  5. Sicherungsvorrichtung gemäß einem der Ansprüche 1 bis 4, gekennzeichnet dadurch, daß ein zweites Verriegelungsmittel aus einem verformbaren Käfig (22) besteht, der den Rotor (8) auf der Ebene einer Äquatorialzone (21) umgibt und in der Lage ist, sich durch die Zentrifugalträgheitskräfte zu öffnen, die beim Abschuß des Geschosses entstehen.
  6. Sicherungsvorrichtung gemäß dem Anspruch 5, gekennzeichnet dadurch, daß der Käfig von einer Spiralfeder umgeben ist, die eine Verzögerung des Öffnen des Käfigs gewährleistet.
  7. Sicherungsvorrichtung gemäß einem der Ansprüche 5 oder 6, gekennzeichnet dadurch, daß der Käfig (22) vom Ring (15) gegen eine Oberfläche (14) der Vorrichtung gedrückt wird.
  8. Sicherungsvorrichtung gemäß einem der Ansprüche 1 bis 7, gekennzeichnet dadurch, daß die Entfernung (D) in Sicherungsstellung zwischen der sphärischen externen Oberfläche des Rotors (8) und der pyrotechnischen Hauptkette (6) ausreichend groß ist, um ein Zünden der pyrotechnischen Hauptkette zu untersagen, daß der Abstand jedoch in der entsicherten Stellung ausreichend klein ist, um das Zünden zu erlauben.
  9. Sicherungsvorrichtung gemäß einem der Ansprüche 1 bis 8, gekennzeichnet dadurch, daß die elastischen Rückholmittel (17) ausreichend starr sind, um das Anliegen des Rings (15) auf dem Rotor sicherzustellen, während die Vorrichtung Stoß- oder Schwingungsbeanspruchungen ausgesetzt ist.
EP19960400069 1995-01-30 1996-01-11 Vorrichtung zum Sichern und Schärfen des Zünders eines Geschosses Expired - Lifetime EP0724132B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9501033A FR2730051B1 (fr) 1995-01-30 1995-01-30 Dispositif de securite et d'armement pour fusee de projectile
FR9501033 1995-01-30

Publications (2)

Publication Number Publication Date
EP0724132A1 EP0724132A1 (de) 1996-07-31
EP0724132B1 true EP0724132B1 (de) 1999-12-01

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP19960400069 Expired - Lifetime EP0724132B1 (de) 1995-01-30 1996-01-11 Vorrichtung zum Sichern und Schärfen des Zünders eines Geschosses

Country Status (5)

Country Link
EP (1) EP0724132B1 (de)
DE (1) DE69605332T2 (de)
FR (1) FR2730051B1 (de)
GR (1) GR3032706T3 (de)
TR (1) TR199600074A2 (de)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005029326B4 (de) * 2005-06-24 2007-04-05 Junghans Feinwerktechnik Gmbh & Co. Kg Sicherungseinrichtung für einen Drallgeschosszünder mit einem kugelartigen Rotor
US7387156B2 (en) 2005-11-14 2008-06-17 Halliburton Energy Services, Inc. Perforating safety system
FR3039267B1 (fr) * 2015-07-24 2017-07-14 Nexter Munitions Dispositif de securite et d'armement pour une fusee d'ogive et fusee comportant un tel dispositif
CN115307504A (zh) * 2022-08-27 2022-11-08 山东泰山民爆器材有限公司 爆炸断索装置

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3165530D1 (en) * 1980-07-02 1984-09-20 Rheinmetall Gmbh Fuse for spinning projectiles
EP0068534B1 (de) * 1981-06-30 1985-01-23 Werkzeugmaschinenfabrik Oerlikon-Bührle AG Sicherungseinrichtung für Drallgeschosszünder
DE3831863A1 (de) * 1988-09-20 1990-03-22 Diehl Gmbh & Co Sicherungseinrichtung fuer einen drallgeschosszuender
US5243912A (en) * 1991-12-09 1993-09-14 General Electric Co. Arming delay, dual environment safe, fuze
FR2689972B1 (fr) * 1992-04-14 1995-08-11 Manurhin Defense Dispositif de securite et d'armement pour fusee de projectile comportant un moyen anti-vibratoire.

Also Published As

Publication number Publication date
TR199600074A2 (tr) 1996-08-21
EP0724132A1 (de) 1996-07-31
GR3032706T3 (en) 2000-06-30
FR2730051A1 (fr) 1996-08-02
DE69605332T2 (de) 2000-03-23
DE69605332D1 (de) 2000-01-05
FR2730051B1 (fr) 1997-03-21

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