EP0566469A1 - 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
EP0566469A1
EP0566469A1 EP93400950A EP93400950A EP0566469A1 EP 0566469 A1 EP0566469 A1 EP 0566469A1 EP 93400950 A EP93400950 A EP 93400950A EP 93400950 A EP93400950 A EP 93400950A EP 0566469 A1 EP0566469 A1 EP 0566469A1
Authority
EP
European Patent Office
Prior art keywords
rotor
rocket
lock
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.)
Granted
Application number
EP93400950A
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English (en)
French (fr)
Other versions
EP0566469B1 (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
Original Assignee
Manurhin Defense 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 Manurhin Defense SA filed Critical Manurhin Defense SA
Publication of EP0566469A1 publication Critical patent/EP0566469A1/de
Application granted granted Critical
Publication of EP0566469B1 publication Critical patent/EP0566469B1/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
    • F42C15/20—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 initiation chain of 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 or locks are released.
  • Patent FR2533686 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 FR2537265 shows a rotor which is held in the misaligned position by a socket. 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 spaced 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 tongues, 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 lock has a flange on which the tongues come to rest and a cylindrical part capable of passing freely between the tongues and in that the means ensuring the maintenance of the lock 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 housed 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' thus opening and releasing the lock when it is driven by its inertia during of the projectile.
  • the means ensuring that the lock is held in a position spaced from the rotor comprises a ring 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 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 lock 15, which is, in the embodiment described here, a cylindrical sleeve inside which the striker 6 can slide.
  • the lock comprises a cylindrical part 15a which carries a flange 19 to 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 tabs 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 bolt 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 (by 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 bolt 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 from the barrel or within the first few 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.
  • This maintenance is particularly secure due to the support of the tongues 21 on the support 3.
  • the striker is kept spaced 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 assumes 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.
  • 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 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 is 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 vibratory 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 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) 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 front cylindrical 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 lamellae 35, arranged symmetrically with respect 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 lock 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 lamellae 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 then 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 completes to open 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 lock 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 socket in the spacer 28 will also be: sufficient depth to allow such clearance.
  • Figure 7 shows the security 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 inertia forces, is applied with part 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 on the rotor is sufficient to prevent such rotations due to the friction of the cage 10 on the plug 4.
  • the lock 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.

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  • 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)
  • Fodder In General (AREA)
  • Vibration Prevention Devices (AREA)
  • Details Of Aerials (AREA)
  • Fuses (AREA)
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 true EP0566469A1 (de) 1993-10-20
EP0566469B1 EP0566469B1 (de) 1996-11-13

Family

ID=9428854

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93400950A Expired - Lifetime EP0566469B1 (de) 1992-04-14 1993-04-13 Sicherheits- und Schärfvorrichtung für Zünder von Geschossen mit einem Erschütterungsschutzmittel

Country Status (6)

Country Link
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 (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004065891A3 (en) * 2003-01-24 2004-09-16 Olympic Technologies Ltd Safety system for the ignition chain of a projectile fuze
CN103900426A (zh) * 2014-04-23 2014-07-02 安徽理工大学 一种机械式安全雷管
EP3121553A1 (de) 2015-07-24 2017-01-25 Nexter Munitions Sicherungs- und scharfstellungseinrichtung für einen geschosszünder, und zünder, der eine solche vorrichtung umfasst
WO2023180278A1 (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

Families Citing this family (5)

* Cited by examiner, † Cited by third party
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
FR2944348A1 (fr) 2009-04-10 2010-10-15 Nexter Munitions Dispositif de mise a feu de munition par percussion
FR2959304B1 (fr) 2010-04-27 2014-10-17 Nexter Munitions Dispositif d'amorcage a initiation par influence pour projectile
FR2959303B1 (fr) 2010-04-27 2012-04-06 Nexter Munitions Dispositif d'amorcage a initiation electrique 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

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3595169A (en) * 1969-09-18 1971-07-27 Gen Electric Time delay fuze
FR2500150A1 (fr) * 1981-02-18 1982-08-20 Diehl Gmbh & Co Dispositif de surete sensible a la force centrifuge pour le percuteur d'une fusee a percussion de projectile
FR2533686A1 (fr) * 1982-09-24 1984-03-30 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
EP0360187A2 (de) * 1988-09-20 1990-03-28 DIEHL GMBH & CO. Sicherungseinrichtung für einen Drallgeschosszünder
US5081929A (en) * 1989-10-12 1992-01-21 Mertens William J Projectile having a movable interior fuze

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3595169A (en) * 1969-09-18 1971-07-27 Gen Electric Time delay fuze
FR2500150A1 (fr) * 1981-02-18 1982-08-20 Diehl Gmbh & Co Dispositif de surete sensible a la force centrifuge pour le percuteur d'une fusee a percussion de projectile
FR2533686A1 (fr) * 1982-09-24 1984-03-30 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
EP0360187A2 (de) * 1988-09-20 1990-03-28 DIEHL GMBH & CO. Sicherungseinrichtung für einen Drallgeschosszünder
US5081929A (en) * 1989-10-12 1992-01-21 Mertens William J Projectile having a movable interior fuze

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004065891A3 (en) * 2003-01-24 2004-09-16 Olympic Technologies Ltd Safety system for the ignition chain of a projectile fuze
US7360486B2 (en) 2003-01-24 2008-04-22 Olympic Technologies Ltd Safety system for the ignition chain of a projectile fuze
CN103900426A (zh) * 2014-04-23 2014-07-02 安徽理工大学 一种机械式安全雷管
CN103900426B (zh) * 2014-04-23 2015-11-18 安徽理工大学 一种机械式安全雷管
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
WO2023180278A1 (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

Also Published As

Publication number Publication date
FR2689972A1 (fr) 1993-10-15
ATE145280T1 (de) 1996-11-15
ES2095594T3 (es) 1997-02-16
EP0566469B1 (de) 1996-11-13
GR3022520T3 (en) 1997-05-31
DE69305907D1 (de) 1996-12-19
FR2689972B1 (fr) 1995-08-11
DE69305907T2 (de) 1997-03-06

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