EP0724132A1 - 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
EP0724132A1
EP0724132A1 EP96400069A EP96400069A EP0724132A1 EP 0724132 A1 EP0724132 A1 EP 0724132A1 EP 96400069 A EP96400069 A EP 96400069A EP 96400069 A EP96400069 A EP 96400069A EP 0724132 A1 EP0724132 A1 EP 0724132A1
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EP
European Patent Office
Prior art keywords
rotor
ring
safety
projectile
safety device
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.)
Granted
Application number
EP96400069A
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English (en)
French (fr)
Other versions
EP0724132B1 (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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Publication date
Application filed by Manurhin Defense SA filed Critical Manurhin Defense SA
Publication of EP0724132A1 publication Critical patent/EP0724132A1/de
Application granted granted Critical
Publication of EP0724132B1 publication Critical patent/EP0724132B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • 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 misaligned maintenance of a pyrotechnic initiation chain for the projectile, which guarantees safety during storage and handling of the ammunition.
  • Such devices are known and most often include a primer carrier rotor having an unbalance. This rotor is held in a misaligned position by one or more locks and it adopts by itself, by gyroscopic effect, an aligned position when the lock (s) are released.
  • the patent FR2689972 describes such a device in which the rotor is arranged in a cage mounted free in rotation around the axis of the rocket.
  • the rotor is made integral with the cage in a misaligned position, on the one hand by means of radial pins held in place by a hairspring, and on the other hand with an axial lock which disappears during the firing by the action of the inertia efforts.
  • Such a device therefore comprises a first locking means released by the 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 out of the barrel.
  • the release of this second locking means is delayed by the unwinding of the hairspring.
  • patent FR2689972 provides for providing 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 safety device in which the rotor is mounted sliding in a cage. This rotor is held between two spherical bearings, one of which is arranged at the bottom of the cage and the other is carried by a cover. It is immobilized in the safety position by a split ring, held in abutment on an annular seat of the rotor by a compression spring. The ring is released by the joint action of axial and radial inertia forces, which is detrimental to the safety of the device.
  • the device according to the invention is simple and inexpensive in design since it uses few parts and its assembly is simplified.
  • the device according to the invention also makes it possible to move the rotor away from the main pyrotechnic chain, which increases the safety 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 each sensitive to an environmental stress of a different nature.
  • the device according to the invention also makes it possible to avoid the wear of the bearing surfaces which is caused by the vibrations undergone during transport.
  • the subject of the invention is a safety device for a rocket intended to equip a rotating projectile, device comprising a rotor which carries a primer and is held by at least one locking means in a position in which the primer does not is not aligned with a pyrotechnic chain, this device is characterized in that it comprises an axially sliding retaining ring and carrying a spherical cap on which the rotor is resting, retaining ring which, in a device safety position , 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 capable of moving axially with the ring during the arming of the device.
  • a first locking means is constituted by a flat arranged on the rotor, flat which, in the safety position of the device, is held by the ring bearing on a flat surface of the device.
  • the elastic return means advantageously consist of a split elastic ring placed in a peripheral groove of the ring and which, in the safety position of the device, comes to bear against a conical surface of the device, conical surface oriented so as to ensure the maintaining the ring in the safety position, and allowing the rod to be pushed into the groove by the action of the longitudinal inertia forces developed during the firing of the projectile.
  • the safety device comprises a housing intended to receive the elastic ring when the ring has slid under the effect of the inertia forces developed during the firing of the projectile, the elastic ring being dimensioned so to be opened permanently by the centrifugal inertia forces developed during firing, this opening ensuring its positioning in the housing, which axially locks the retaining ring in an armed position which releases the rotor from its support against the flat surface.
  • the second locking means consists of a deformable cage surrounding the rotor at an equatorial region thereof and capable of opening by the action of the centrifugal inertia forces developed during the firing of the projectile.
  • This cage may be surrounded by a hairspring ensuring a delay in its opening.
  • the cage can be held by the ring in abutment against a surface of the device.
  • the distance in the safety position between the external spherical surface of the rotor and the main pyrotechnic chain is large enough to prohibit initiation of the latter, but in the armed position this distance is sufficiently small to allow initiation.
  • the elastic return means may be chosen to be rigid enough to maintain the support of the ring on the rotor when the device is subjected to shock or vibration stresses. These means thus prohibit any vibration of the moving parts which can lead to wear of the bearing surfaces.
  • a warhead rocket 1 is intended to be fixed to a front part of a gyrostabilized projectile (not shown), for example a medium caliber projectile (less than 50 mm).
  • this rocket comprises a striker 2, a safety and arming device 3 and a pyrotechnic relay 23.
  • the striker here carries a flange 2a which makes it possible 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 the relay 23 which causes the detonation of an explosive charge contained in the projectile (not shown).
  • FIG. 2 represents the security and arming device 3 in the security position which is hers before the projectile is fired.
  • the device 3 comprises a housing 4 closed by a cover 5 fixed to the housing by thread.
  • the cover 5 carries a reinforcing pyrotechnic charge 6 intended to be initiated by the primer and in turn to initiate the relay 23.
  • the charge 6 communicates with the interior of the device by a bore 5a, and it is isolated from moisture air by sealing flakes (or by a thin partition secured to the cover).
  • the bottom of the housing 4 is pierced by an orifice 7 intended to allow the striker 2 to pass.
  • a rotor 8 substantially spherical and having an unbalance, is disposed 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 broken lines in the various figures. In the safety position of the device, the axis 11 of the housing 10 is inclined relative to the axis 12 of the rocket (and of the projectile), which prohibits both the initiation of the primer by the striker 2 and the transmission of an accidental initiation of the primer to the load 6.
  • the rotor 8 carries a flat 13 which, in the safety position of the device, is supported on a flat surface 14 forming the bottom of the housing 4.
  • the rotor is held in its safety position, pressing against the bottom of the housing, by a retaining ring 15, which is mounted so as to be able to slide axially in the bore 9 of the housing 4.
  • the external diameter of the ring is a few hundredths of a millimeter less than that of bore 9 and the length of the ring is chosen to be sufficient to ensure good guidance.
  • the ring 15 carries a spherical cap 16 on which the rotor 8 is supported 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 peripheral groove 18 of the ring 15 and it comes to bear against a conical surface 19 arranged on the internal surface of the bore 9.
  • the base of the conical surface 19 is oriented on the side of the bottom 14 of the housing. Thus, it maintains the rotor 8 by the ring 15 in its position locked by the flat 13.
  • the groove 18 has a depth greater than the diameter of the wire constituting the rod 17, so when the latter is compressed radially, it can be housed entirely in the groove and allow the translation of the ring 15 in the housing 4.
  • the bore 9 also carries a counterbore 20 disposed in the vicinity of the cover 5 and which is intended to constitute a housing for the rod 17 in the armed position of the device.
  • the rotor 8 has an external cylindrical surface constituting an equatorial zone 21.
  • a split deformable cage 22 surrounds the rotor 8 at the level of this equatorial zone and constitutes a second means for locking the rotor in its safety position.
  • the height of the equatorial zone, and therefore of the rotor / cage contact zone, is chosen to be 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 an arrangement increases the rigidity of the device.
  • the ring thus prohibits the opening of the cage, which increases safety and makes it possible to avoid any friction and deterioration of surfaces due to the influence of vibrations during the phases of storage or transport of the projectile. This significantly improves the operating reliability of rockets which must withstand severe mechanical environments during their storage and transport.
  • the cage will be made for example of an elastic material, such as a flexible metal blade of stainless steel or brass. It can also be made of a plastic material (for example polytetrafluoroethylene known under the registered trademark "Teflon").
  • Teflon polytetrafluoroethylene known under the registered trademark "Teflon”
  • the cage is intended to open by the action of centrifugal inertia forces as will be described below.
  • the elastic ring 17 will be chosen to be rigid enough to maintain the support of the ring on the rotor when the device is subjected to shock or vibration stresses, for example during the phases of storage or transport of the projectile.
  • the rotor when the device is in its safety position, the rotor is at a distance D from the pyrotechnic charge 6.
  • the device will be defined so that the distance D is large enough to prohibit initiation of the load 6 by the primer when the rotor is oriented with its axis 11 coinciding with that of the device 12. This increases the safety of the device.
  • a distance D equal to a few millimeters (from 1 to 5 mm).
  • FIG. 3 represents the device according to the invention at the time of the firing, when the longitudinal acceleration 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 secures 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 for locking the rotor is therefore released.
  • the device will of course be defined so that the displacement of the ring is sufficient to allow the subsequent rotation of the rotor without interference with the bottom 14 of the housing.
  • the device is shown here in the first moments of the shot.
  • the rotation communicated to the projectile by the barrel of the weapon is still insufficient and the cage 22 remains applied against the equatorial zone 21 of the rotor, further immobilizing the latter in a safety position with its axis 11 inclined relative to the axis 12 of the device.
  • Figure 4 shows the device according to the invention at the outlet of the barrel of the weapon.
  • the angular acceleration communicated by the scratches in the barrel of the weapon caused the opening of the cage 22 which is pressed against the wall of the bore 9 of the housing.
  • the rotor 8 released from its second locking means, has adopted by gyroscopic effect a position in which its main axis of inertia 11 coincides with the axis 12 of the device.
  • the housing 10 of the primer is aligned with the axis 12 and the sensitive face of the primer is opposite the end of the striker 2.
  • the initiation initiates the reinforcing load 6 through the holes 15a and 5a, the load 6 ensuring the initiation of the relay load 23.
  • Figures 2 to 4 described above are simplified representations of the device in which the functional clearances between the different parts have been deliberately exaggerated.
  • the clearance J1 (FIG. 4) which separates the rotor and the cage is of the order of a few tenths of mm.
  • the cage does not prohibit the gyroscopic movement of the rotor but it nevertheless ensures radial guiding of the latter and guarantees that it is held in a position such that the main axis 11 is aligned with the axis 12 of the device.
  • a first means for locking the rotor of different structure.
  • a stud secured to the bottom of the housing 4 and cooperating with an additional housing arranged in the rotor. In this case, the movement 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 load 6 can be omitted and the primer can directly initiate the relay load 23.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Emergency Lowering Means (AREA)
  • Vibration Dampers (AREA)
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
FR9501033 1995-01-30
FR9501033A FR2730051B1 (fr) 1995-01-30 1995-01-30 Dispositif de securite et d'armement pour fusee de projectile

Publications (2)

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

Family

ID=9475627

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)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1736729A1 (de) * 2005-06-24 2006-12-27 Junghans Feinwerktechnik GmbH & Co.KG Sicherungseinrichtung für einen Drallgeschosszünder
US7387156B2 (en) 2005-11-14 2008-06-17 Halliburton Energy Services, Inc. Perforating safety system
EP3121553A1 (de) * 2015-07-24 2017-01-25 Nexter Munitions Sicherungs- und scharfstellungseinrichtung für einen geschosszünder, und zünder, der eine solche vorrichtung umfasst
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

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0042957A2 (de) * 1980-07-02 1982-01-06 Rheinmetall GmbH Zünder für Drallgeschosse
EP0068534A2 (de) * 1981-06-30 1983-01-05 Werkzeugmaschinenfabrik Oerlikon-Bührle AG Sicherungseinrichtung für Drallgeschosszünder
EP0360187A2 (de) * 1988-09-20 1990-03-28 DIEHL GMBH & CO. Sicherungseinrichtung für einen Drallgeschosszünder
US5243912A (en) * 1991-12-09 1993-09-14 General Electric Co. Arming delay, dual environment safe, fuze
FR2689972A1 (fr) * 1992-04-14 1993-10-15 Manurhin Defense Dispositif de sécurité et d'armement pour fusée de projectile comportant un moyen anti-vibratoire.

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0042957A2 (de) * 1980-07-02 1982-01-06 Rheinmetall GmbH Zünder für Drallgeschosse
EP0068534A2 (de) * 1981-06-30 1983-01-05 Werkzeugmaschinenfabrik Oerlikon-Bührle AG Sicherungseinrichtung für Drallgeschosszünder
EP0360187A2 (de) * 1988-09-20 1990-03-28 DIEHL GMBH & CO. Sicherungseinrichtung für einen Drallgeschosszünder
US5243912A (en) * 1991-12-09 1993-09-14 General Electric Co. Arming delay, dual environment safe, fuze
FR2689972A1 (fr) * 1992-04-14 1993-10-15 Manurhin Defense Dispositif de sécurité et d'armement pour fusée de projectile comportant un moyen anti-vibratoire.

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1736729A1 (de) * 2005-06-24 2006-12-27 Junghans Feinwerktechnik GmbH & Co.KG Sicherungseinrichtung für einen Drallgeschosszünder
US7357081B2 (en) 2005-06-24 2008-04-15 Junghans Microtec Gmbh Safety and arming unit for a spinning projectile fuze
US7461596B2 (en) 2005-06-24 2008-12-09 Junghans Microtec Gmbh Safety and arming unit for a spinning projectile fuze
NO337722B1 (no) * 2005-06-24 2016-06-13 Junghans Microtec Gmbh Sikringsinnretning for et rotasjonsprosjekttilbrannrør
US7387156B2 (en) 2005-11-14 2008-06-17 Halliburton Energy Services, Inc. Perforating safety system
EP3121553A1 (de) * 2015-07-24 2017-01-25 Nexter Munitions Sicherungs- und scharfstellungseinrichtung für einen geschosszünder, und zünder, der eine solche vorrichtung umfasst
FR3039267A1 (fr) * 2015-07-24 2017-01-27 Nexter Munitions Dispositif de securite et d'armement pour une fusee d'ogive et fusee comportant un tel dispositif
US10041775B2 (en) 2015-07-24 2018-08-07 Nexter Munitions Safety and arming device for an instant impact point fuse and fuse including such a device
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

Also Published As

Publication number Publication date
EP0724132B1 (de) 1999-12-01
DE69605332D1 (de) 2000-01-05
DE69605332T2 (de) 2000-03-23
FR2730051A1 (fr) 1996-08-02
GR3032706T3 (en) 2000-06-30
FR2730051B1 (fr) 1997-03-21
TR199600074A2 (tr) 1996-08-21

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