EP0566469B1 - Sicherheits- und Schärfvorrichtung für Zünder von Geschossen mit einem Erschütterungsschutzmittel - Google Patents

Sicherheits- und Schärfvorrichtung für Zünder von Geschossen mit einem Erschütterungsschutzmittel Download PDF

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Publication number
EP0566469B1
EP0566469B1 EP93400950A EP93400950A EP0566469B1 EP 0566469 B1 EP0566469 B1 EP 0566469B1 EP 93400950 A EP93400950 A EP 93400950A EP 93400950 A EP93400950 A EP 93400950A EP 0566469 B1 EP0566469 B1 EP 0566469B1
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EP
European Patent Office
Prior art keywords
lock
rotor
safety
projectile
arming 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.)
Expired - Lifetime
Application number
EP93400950A
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English (en)
French (fr)
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EP0566469A1 (de
Inventor
Jacques Nicolas
Jean-Paul Oberle
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Manurhin Defense SA
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Manurhin Defense SA
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Filing date
Publication date
Application filed by Manurhin Defense SA filed Critical Manurhin Defense SA
Publication of EP0566469A1 publication Critical patent/EP0566469A1/de
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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
    • F42C15/20—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a securing-pin or latch is removed to arm the fuze, e.g. removed from the firing-pin
    • F42C15/22—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a securing-pin or latch is removed to arm the fuze, e.g. removed from the firing-pin using centrifugal force

Definitions

  • the field of the present invention is that of safety and arming devices for rockets intended to equip revolving projectiles.
  • the safety and arming devices of rockets have the function of ensuring the misaligned maintenance of the pyrotechnic chain of initiation of the projectile, which guarantees safety during the 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.
  • Patent US-A-5081929 describes a grenade rocket which comprises a watch plate containing a primer holder flap held by two latches, one of which is sensitive to the inertia of fire acceleration and the other to centrifugal force. A spring keeps the watch plate away from a striker until it hits a target.
  • Patent FR-A-2533686 provides for placing the primer-carrying rotor inside a cage which is mounted in the rocket body with a certain axial play and which is free to rotate about the axis of the rocket.
  • the rotor is made integral with the cage in a misaligned position by means of pins held in place by a hairspring.
  • Patent FR-A-2537265 shows a rotor which is held in the misaligned position by a bush. The latter emerges from the rotor following the unwinding of a hairspring.
  • such devices include parts (cage, rotor, hairspring) which have a certain mobility relative to the rocket body.
  • the vibrations induced on a rotor which has a certain mobility can also cause the pyrotechnic composition to leave the primer, which is extremely detrimental from the point of view of safety.
  • Patent EP360187 proposes a primer holder rotor which is held in the misaligned position by a split washer.
  • the washer is applied to the rotor by a spiral spring which bears on the rocket body.
  • the spring allows axial movements of the rotor relative to its housing, which allows elastic shock absorption to be achieved.
  • Such an arrangement does not prohibit relative movements and therefore does not prevent wear of the bearing surfaces caused by the induced vibrations.
  • the subject of the invention is a safety and arming device for a rocket intended to equip a gyrating projectile, device comprising a rotor which carries a primer and is held by a lock in a position in which the primer does not is not aligned with a main pyrotechnic chain, device characterized in that the lock is held in abutment on the rotor by immobilization means which is sufficiently rigid to maintain this abutment when the device is subjected to shock or vibration stresses, means immobilizer releasing the lock following the firing of the projectile.
  • the security and arming device comprises means ensuring that the lock is kept in a position away from the rotor after its release by the immobilization means.
  • This arrangement makes it possible to prevent the lock from disturbing the subsequent movements of the rotor.
  • the immobilization means comprises an elastic washer which has a peripheral rim bearing on the rocket body and a central part constituted by at least two tabs, regularly distributed angularly, and which come to bear on the bolt and are liable to deform so as to allow the latter to pass when it is driven by its inertia when the projectile is fired.
  • the latch has a flange on which the tongues come to bear and a cylindrical part capable of passing freely between the tongues and in that the means ensuring the retention of the latch in a separated position are constituted by the tongues themselves which form a stop for the flange after the passage of the latter through the washer.
  • the peripheral edge of the washer is received in a groove in the rocket body.
  • the immobilization means comprises a split ring which is supported on the one hand on the rocket body and on the other hand on a conical surface of the lock, ring capable of s' open and release the bolt when it is driven by its inertia when firing the projectile.
  • the means ensuring that the latch is kept in a position spaced from the rotor comprises a crown carrying at least two lamellae, elastically deformable and regularly distributed angularly, lamellae kept compressed by a flat surface of the lock when the latter is supported on the rotor and which release the rotor lock when it is released by the ring.
  • the ring when the ring is driven by its inertia when the projectile is fired, it keeps the crown in abutment against the rocket body.
  • the rotor may be placed inside a cage, mounted to rotate relative to the rocket body and around the axis of the latter and the lock may be constituted by a sleeve coaxial with the rocket and through which is susceptible to slide a striker intended to initiate the primer.
  • a rocket 1 intended to be disposed at the base of a projectile comprises a body 2 of light alloy (for example aluminum) inside which is arranged a device security and arming according to the invention.
  • the body is closed by a plug 4 which carries a relay pyrotechnic charge 5 in a housing.
  • This charge is intended in a known manner to ensure the ignition of a main charge (not shown), contained in the projectile.
  • the rocket also includes a self-destruct device of known type (described for example in patent FR1227037) and which in particular comprises a striker 6, which is pushed by a spring 7 towards a primer 9.
  • a self-destruct device of known type (described for example in patent FR1227037) and which in particular comprises a striker 6, which is pushed by a spring 7 towards a primer 9.
  • a support 3 is made integral with the body 2 by means of a thread.
  • the security and arming device comprises a rotor 8 having an unbalance and inside which the primer 9 is disposed.
  • the rotor is placed inside a cage 10 which has two pins 11 and 12.
  • the pins come in corresponding housings arranged respectively on the support 3 and the plug 4, the adjustment of the pins in their housings is slippery and allows relative rotation of the cage with respect to the rocket body.
  • the rotor 8 is immobilized relative to the cage 10 in a misaligned position by means of two radial pins 14, which are themselves held in place by a hairspring 13.
  • the rotor is also immobilized by a latch 15, which is, in the embodiment described here, a cylindrical socket inside which the striker 6 can slide.
  • the latch comprises a cylindrical part 15a which carries a flange 19 at its end furthest from rotor 8.
  • the other end of the lock is held by an immobilizing means bearing on a groove 16 made on the rotor.
  • the immobilization means is an elastic washer 17.
  • This washer 17 is shown in detail in Figures 2a and 2b. It is made of pressed spring steel sheet and has a circular shape. It has a peripheral rim 20 and a central part 24.
  • the central part consists of two tongues 21 arranged symmetrically to each other relative to the axis 26 of the washer.
  • the free ends 25 of the tongues each have a cut in the shape of an arc of a circle, the center of which is positioned on the axis 26. They are separated by a free space 22.
  • the outer diameter of the cylindrical part 15a of the latch is shown in dotted lines 36, and in dotted lines 23 the outer diameter of the flange 19 of the latch.
  • the diameter of the collar is slightly greater (of the order of mm) than that of the free ends 25 of the tongues which define the free space 22.
  • the diameter of the cylindrical part 15a is slightly smaller (of the order of mm) than that of the free ends 25 of the tongues which define the free space 22.
  • the lock 15 will be dimensioned so that when it is thus supported on the rotor, there remains a clearance (j) of a few tenths of a mm between the flange 19 and the support 3.
  • the washer will be dimensioned (playing in particular on the number and dimensions of the tongues) so that it ensures that the bolt remains in contact with the rotor, therefore that the play is taken up when the device is subjected to vibrations or shocks.
  • the tabs will nevertheless be dimensioned in such a way that they release the lock when, when the projectile is fired, it is thus driven by its inertia towards the rear part D of the rocket.
  • the lock then ensures the immobilization of the rotor and the cage during the storage phases and the handling of the ammunition (maximum acceleration of the order of 30,000 times the acceleration of gravity during the placing of the ammunition in tear).
  • FIG. 3 shows the security and arming device according to this first embodiment after the release of the lock 15 under the action of its inertia and before the release of the rotor 8 by the pins 14 (therefore before the projectile leaves the of the barrel of the weapon or in the first meters of its trajectory out of the barrel).
  • the tongues 21 return to their initial position. They thus constitute a means which maintains the lock in a position spaced from the rotor.
  • the length of the cylindrical part 15a of the latch and the thickness of the washer 17 are such that, when the collar is in abutment on the washer in the arrangement shown in FIG. 3, the end of the cylindrical part 15a of the latch is completely disengaged from the rotor 8 and no longer prohibits the movements of the latter.
  • the striker is kept apart from the primer against the action of the spring 7 (for example by means of balls as described in patent FR1227037).
  • the rotor After a time delay given by the unwinding of the hairspring, the rotor is released by the pins 14 and it adopts an aligned position.
  • the striker Upon impact on a target, the striker is thrown against the primer and initiates the latter, which causes the projectile to explode.
  • the latch 15 is positioned in its bore of the support 3, then the spring washer 17 is applied against the latch and its peripheral rim is force-fitted into the groove 18 of the support 3.
  • This assembly receives the striker and the rest of the self-destruction device, then the body 2 of the rocket is screwed onto the support 3.
  • the sub-assembly consisting of the cage 10 carrying the rotor 8 and the hairspring 13, is positioned on the end of the cylindrical part 15a of the latch 15.
  • the plug 4 is screwed onto the body 2 until it is put in place. at the abutment of a peripheral shoulder 27 of the plug 4 on the body 2.
  • the dimensions of the plug are determined so that, after release of the lock, there remains a functional axial clearance between the cage 10 and the support 3.
  • the axial movements of the cage / rotor / hairspring assembly relative to the rocket body are prohibited by the latch 15, held in abutment against the rotor by the washer 17.
  • the rotational movements of the cage / rotor / hairspring assembly relative to the rocket body are also prohibited.
  • the force applied by the bolt to the rotor is chosen to be large enough to prevent such rotations due to the friction of the cage 10 on the plug 4.
  • the latch 15 is however released from the first moments of the firing since this release only uses the inertial forces in an axial direction of the projectile. Thus, the subsequent movement of the cage and the release of the rotor by the pins are not disturbed, which ensures the reliability of the security and arming device.
  • the security and arming device according to this first embodiment is particularly simple from the point of view of manufacture and assembly. It has a resistance to storage in severe vibration environments which is improved with respect to that of safety devices according to the state of the art. And such an improvement does not penalize the cost of production or the reliability of the weaponry.
  • Such a security and arming device could possibly be adapted to a warhead rocket.
  • the lock will then prevent vibrations of the rotor relative to its cage which will prevent the pyrotechnic composition from leaving the primer.
  • FIG. 4 represents a rocket 1 intended to be fixed to the warhead of a projectile (not shown).
  • It comprises a body 2 of light alloy (for example aluminum) inside which is disposed a security and arming device according to a second embodiment of the invention.
  • a body 2 of light alloy for example aluminum
  • the body is closed by a plug 4 which carries a relay pyrotechnic charge 5 in a housing.
  • This charge is intended in known manner to ensure the ignition of a main charge (not shown) contained in the projectile.
  • the rocket also includes a self-destruct device of known type (described for example in patent FR1227037) which notably comprises a striker 6 which is pushed by a spring 7 towards a primer 9.
  • a self-destruct device of known type (described for example in patent FR1227037) which notably comprises a striker 6 which is pushed by a spring 7 towards a primer 9.
  • a spacer 28 abuts on the body 2 of the rocket at a shoulder 40 and it is made integral with the body 2 by means of a support 3, itself threaded and screwed to the body 2.
  • the security and arming device comprises a rotor 8 disposed in a cage 10.
  • the cage carries two pins 11 and 12 which come in corresponding housings arranged respectively on the support 3 and the plug 4.
  • the adjustment of the pins in their housings is sliding and it allows relative rotation of the cage relative to the rocket body.
  • the rotor is immobilized by a latch 29 which is, in the embodiment described here, a socket inside which the striker 6 can slide and which has a conical surface 32 whose apex is oriented towards a front part A of the rocket.
  • the sleeve has a cylindrical front portion 29a which comes, in sliding adjustment, into a housing 33 arranged on the spacer 28.
  • a split O-ring 30 (also visible in FIG. 5) is tightened on this conical part 32 and it is also supported on the lower face 28a of the spacer 28.
  • the ring 30 constitutes a means of immobilization which ensures the support of the lock 29 on the rotor 8.
  • the latch 29 has a flat surface 29c which comes into contact with a ring 31 itself in contact with the support 3.
  • the crown 31 is visible in detail in Figures 6a and 6b. It is a substantially circular stamped sheet metal plate with an axis 37 and which carries two elastic strips 35, arranged symmetrically to each other relative to the axis 37.
  • the free ends 38 of the strips have a cut in the form of arcs of a circle, the center of which is positioned on the axis 37. They are separated by a free space 34.
  • the diameter of the rear cylindrical portion 29b of the latch is slightly smaller (of the order of mm) than that of the ends 38 of the strips which define the free space 34.
  • Crown and blades constitute a means ensuring that the lock is kept in a position away from the rotor after its release by the lock.
  • the mode of action of the slats will be explained later.
  • the assembly of this device is carried out as follows.
  • the crown 31 is positioned in its cylindrical housing of the support 3, then the lock 29 is put in place on which the ring 30 is mounted and the lock is capped with the spacer 28.
  • the latter is in support of firstly on a shoulder 39 of the support 3 and secondly on the ring 30.
  • the self-destruct device is positioned in the spacer 28 and the body 2 is screwed until the spacer 28 is brought into abutment on the shoulder 40 of the body.
  • the rotor mounted in its cage is then put in place in the engaged position on the latch 29 and finally the plug 4 is screwed onto the body 2 until a peripheral shoulder 27 of the plug 4 is brought into abutment on the body 2.
  • the dimensions of the plug and the total length of the latch 29 are chosen so that the latch 29 is supported on the groove 16 and that there remains a functional axial clearance between the cage 10 and the support 3 after release of the latch.
  • the operation of the device is as follows: When firing the ammunition and under the effect of the axial inertia forces exerted on the ring 30, the latter moves towards the rear part D of the rocket.
  • the conical surface 32 causes the opening of the ring.
  • the ring finishes opening and comes into contact with the surface of the bore 41 under the action of the inertial forces of rotation which are exerted shortly before the exit of the barrel from the weapon.
  • the withdrawal of the ring 30 authorizes the displacement of the latch 29 towards the front part A of the rocket under the action of the lamellae 35 and the deceleration.
  • the latter are dimensioned so that they can disengage the front part 29b from the lock of the groove 16 of the rotor.
  • the housing 33 of the rear part of the sleeve in the spacer 28 will also be of sufficient depth to allow such clearance.
  • Figure 7 shows the safety and arming device according to this second embodiment after clearing the lock and before the release of the rotor by the pins 14.
  • the ring 30, opened by the inertial forces, is applied on the one hand against the crown 31 and on the other hand against the bore 41 of the support 3.
  • the ring thus maintains the crown relative to the rocket body and allows the latter to keep the lock stationary relative to the rocket body.
  • this embodiment of the invention makes it possible to prohibit the axial movements of the cage / rotor / hairspring assembly relative to the rocket body by virtue of the bolt 29 held in abutment against the rotor by the ring 30.
  • the force applied by the lock to the rotor is sufficient to prevent such rotations due to the friction of the cage 10 on the plug 4.
  • the latch 29 is however released from the first moments of the firing since this release only uses the inertial forces in an axial direction of the projectile. Thus, the subsequent movement of the cage and the release of the rotor by the pins are not disturbed, which ensures the reliability of the security and arming device.
  • the security and arming device according to this second embodiment is particularly suitable for fitting into a warhead rocket.
  • the lock will then prohibit the relative vibrations of the rotor in its cage, which will prevent the pyrotechnic composition from leaving the primer.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Buildings Adapted To Withstand Abnormal External Influences (AREA)
  • Air Bags (AREA)
  • Emergency Lowering Means (AREA)
  • Fuses (AREA)
  • Details Of Aerials (AREA)
  • Vibration Prevention Devices (AREA)
  • Fodder In General (AREA)

Claims (10)

  1. Sicherheits- und Scharfmachvorrichtung für einen Zünder (1), zum Ausrüsten eines gyrierenden Geschosses, wobei die Vorrichtung einen Rotor (8) enthält, der ein Zündhütchen (9) trägt und von einem Riegel (15, 29) in einer Position gehalten wird, in der das Zündhütchen nicht mit einer pyrotechnischen Hauptkette gefluchtet ist, wobei sich die Vorrichtung gekennzeichnet dadurch , daß der Riegel (15, 29) von einem Blockierungsmittel (17, 30) auf den Rotor (8) gedrückt gehalten wird, wobei das Blockierungsmittel (17, 30) ausreichend starr ist, um dieses Andrücken beizubehalten, wenn die Vorrichtung Erschütterungs- oder Schwingungsbelastungen ausgesetzt ist, und den Riegel (15, 29) infolge des Abschießens des Geschosses freigibt.
  2. Sicherheits- und Scharfmachvorrichtung gemäß dem Anspruch 1, gekennzeichnet dadurch, daß sie Mittel (21, 31) enthält, die ein Halten des Riegels (15, 29) in einer vom Rotor (8) entfernten Stellung nach dessen Freigabe durch das Blockierungsmittel (17, 30) sicherstellen.
  3. Sicherheits- und Scharfmachvorrichtung gemäß einem der Ansprüche 1 oder 2, gekennzeichnet dadurch, daß das Blockierungsmittel eine elastische Feder (17) aufweist, die eine periphere Kante (20) hat, die auf dem Zünderkörper (2) aufliegt und einen Mittenteil (24), der aus mindestens zwei Laschen (21) besteht, die winkelig regelmäßig angeordnet sind, auf den Riegel (15) drücken und sich verformen können, so daß der Riegel beim Abschießen des Geschosses, angetrieben von seiner Trägheit passieren kann.
  4. Sicherheits- und Scharfmachvorrichtung gemäß dem Anspruch 3, gekennzeichnet dadurch, daß der Riegel (15) einen Kranz (19) aufweist, auf dem Laschen (21) aufliegen und einen zylindrischen Teil (15a), der frei zwischen den Laschen passieren kann, und dadurch, daß die Mittel zum Halten des Riegels in einer entfernten Position aus Laschen (21) bestehen, die einen Anschlag für den Kragen (19) nach dem Passieren des Kragens durch die Scheibe (17) bilden.
  5. Sicherheits- und Scharfmachvorrichtung gemäß einem der Ansprüche 3 oder 4, gekennzeichnet dadurch, daß sich die Peripheriekante (20) der Scheibe (17) in eine Hohlkehle (18) des Zünderkörpers fügt.
  6. Sicherheits- und Scharfmachvorrichtung gemäß einem der Ansprüche 1 oder 2, gekennzeichnet dadurch, daß das Blockiermittel einen Spaltring (30) aufweist, der einerseits auf dem Körper (2) des Zünders und, andererseits, auf einer kegelförmigen Oberfläche (32) des Riegels (29) aufliegt und sich öffnen und damit den Riegel (29) freigeben kann, wenn er von seiner Trägheit beim Abschießen des Geschosses angetrieben wird.
  7. Sicherheit- und Scharfmachvorrichtung gemäß dem Anspruch 6, gekennzeichnet dadurch, daß die Mittel zur Sicherstellung des Haltens des Riegels (29) in einer vom Rotor (8) entfernten Stellung einen Kranz (31) aufweisen, der mindestens zwei Lamellen (35) trägt, die elastisch verformbar und regelmäßig winkelig angebracht sind und von einer ebenen Fläche (29c) des Riegels zusammengedrückt werden, wenn letzterer auf dem Rotor (8) aufliegt, und die den Riegel (29) des Rotors freigeben, wenn er vom Ring (30) freigegeben wird.
  8. Sicherheits- und Scharfmachvorrichtung gemäß dem Anspruch 7, gekennzeichnet dadurch, daß sie den Kranz (31) gegen den Zünderkörper (2) gedrückt hält, wenn der Ring (30) von seiner Trägheit beim Abschießen des Geschosses angetrieben wird.
  9. Sicherheits- und Scharfmachvorrichtung, gemäß einem der Ansprüche 1 bis 8, gekennzeichnet dadurch, daß der Rotor (8) im Inneren eines Käfigs (10) angebracht ist, der bezogen auf den Zünderkörper und um die Achse dieses Zünderkörpers drehend montiert ist.
  10. Sicherheits- und Scharfmachvorrichtung gemäß einem der Ansprüche 1 bis 9, gekennzeichnet dadurch, daß der Riegel (15, 29) aus einer zum Zünder koaxial stehenden Hülse besteht, durch welche ein Schlagbolzen (6) zum Zünden des Zündhütchens (9) gleiten kann.
EP93400950A 1992-04-14 1993-04-13 Sicherheits- und Schärfvorrichtung für Zünder von Geschossen mit einem Erschütterungsschutzmittel Expired - Lifetime EP0566469B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9204572A FR2689972B1 (fr) 1992-04-14 1992-04-14 Dispositif de securite et d'armement pour fusee de projectile comportant un moyen anti-vibratoire.
FR9204572 1992-04-14

Publications (2)

Publication Number Publication Date
EP0566469A1 EP0566469A1 (de) 1993-10-20
EP0566469B1 true EP0566469B1 (de) 1996-11-13

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EP (1) EP0566469B1 (de)
AT (1) ATE145280T1 (de)
DE (1) DE69305907T2 (de)
ES (1) ES2095594T3 (de)
FR (1) FR2689972B1 (de)
GR (1) GR3022520T3 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170138714A1 (en) * 2015-07-24 2017-05-18 Nexter Munitions Safety and arming device for an instant impact point fuse and fuse including such a device

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Publication number Priority date Publication date Assignee Title
FR2730051B1 (fr) * 1995-01-30 1997-03-21 Manurhin Defense Dispositif de securite et d'armement pour fusee de projectile
GB0301690D0 (en) 2003-01-24 2003-02-26 Olympic Technologies Ltd Safety system
FR2944348A1 (fr) 2009-04-10 2010-10-15 Nexter Munitions Dispositif de mise a feu de munition par percussion
FR2959303B1 (fr) 2010-04-27 2012-04-06 Nexter Munitions Dispositif d'amorcage a initiation electrique pour projectile
FR2959304B1 (fr) 2010-04-27 2014-10-17 Nexter Munitions Dispositif d'amorcage a initiation par influence pour projectile
FR2965044B1 (fr) * 2010-09-22 2012-08-24 Nexter Munitions Dispositif de securite et d'armement pour projectile explosif gyrostabilise et dispositif d'amorcage mettant en oeuvre un tel dispositif de securite et d'armement
CN103900426B (zh) * 2014-04-23 2015-11-18 安徽理工大学 一种机械式安全雷管
DE102022106883A1 (de) * 2022-03-23 2023-09-28 Rheinmetall Air Defence Ag Sicherungseinheit für einen Zünder, Verwendung der Sicherungseinheit und Verfahren zur Aktivierung eines Zünders mit dieser Sicherungseinheit

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US3595169A (en) * 1969-09-18 1971-07-27 Gen Electric Time delay fuze
DE8104477U1 (de) * 1981-02-18 1982-08-05 Diehl GmbH & Co, 8500 Nürnberg Fliehkraftabhaengige sicherung fuer den schlagbolzen eines aufschlagzuenders fuer geschosse
FR2533686B1 (fr) * 1982-09-24 1987-01-02 Manurhin Dispositif de securite a cage tournante pour projectile giratoire
US4480551A (en) * 1983-06-08 1984-11-06 Whittaker Corporation Point-detonating variable time-delayed fuze
DE3831863A1 (de) * 1988-09-20 1990-03-22 Diehl Gmbh & Co Sicherungseinrichtung fuer einen drallgeschosszuender
US5081929A (en) * 1989-10-12 1992-01-21 Mertens William J Projectile having a movable interior fuze

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170138714A1 (en) * 2015-07-24 2017-05-18 Nexter Munitions Safety and arming device for an instant impact point fuse and fuse including such a device

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Publication number Publication date
DE69305907T2 (de) 1997-03-06
ES2095594T3 (es) 1997-02-16
DE69305907D1 (de) 1996-12-19
GR3022520T3 (en) 1997-05-31
ATE145280T1 (de) 1996-11-15
FR2689972B1 (fr) 1995-08-11
FR2689972A1 (fr) 1993-10-15
EP0566469A1 (de) 1993-10-20

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