WO1996035095A1 - Dispositif de securite pour fusee percutante - Google Patents
Dispositif de securite pour fusee percutante Download PDFInfo
- Publication number
- WO1996035095A1 WO1996035095A1 PCT/AT1996/000088 AT9600088W WO9635095A1 WO 1996035095 A1 WO1996035095 A1 WO 1996035095A1 AT 9600088 W AT9600088 W AT 9600088W WO 9635095 A1 WO9635095 A1 WO 9635095A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- rotor
- detonator
- safety device
- impact
- ignition
- Prior art date
Links
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
- F42C15/44—Arrangements for disarming, or for rendering harmless, fuzes after arming, e.g. after launch
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
- F42C9/00—Time fuzes; Combined time and percussion or pressure-actuated fuzes; Fuzes for timed self-destruction of ammunition
- F42C9/14—Double fuzes; Multiple fuzes
- F42C9/142—Double fuzes; Multiple fuzes combined time and percussion fuzes in which the timing is caused by combustion
Definitions
- the invention relates to a safety device for an impact detonator of a grenade which can be swirled when fired through a weapon barrel, with a front pipe safety device and a self-destruction unit, wherein the front pipe safety device has a detonator-mounted rotor that is rotatably mounted eccentrically about a longitudinal axis and engages in a gear-wheel brake mechanism, but under centrifugal action braked by the gear inhibitor, the detonator pivoted from a starting position to a ready-to-fire focus position, and the self-destruct unit consists of a pyrotechnic delay set that can be fired via a firing pin to ignite the detonator based on impact.
- Such safety devices are intended to prevent, on the one hand, the grenades from igniting unintentionally during transport or handling and, on the other hand, that the grenades explode prematurely when fired or when the impact ignition fails to remain as unexploded ordnance.
- the self-destruct unit usually includes a pyrotechnic delay set, which is fired when the grenade is fired using its own firing pin and then leads to the firing of the grenade after a predetermined burn-off period, should no firing-related ignition have yet taken place via the firing igniter.
- This self-destruct unit is housed in its own housing screwed onto the down pipe protection and acts on the firing pin or the like of the impact detonator via the gas pressure which arises when the deceleration set burns off, in order to ignite the detonator and thus the grenade.
- Such a stacking of the front pipe protection and self-destruction unit results in a considerable space requirement for the safety device, which increases the available volume for the actual explosive and the fragment jacket.
- the invention is therefore based on the object of providing a safety device of the type described at the outset, which is distinguished by its relatively simple construction and, above all, by its small space requirement with the greatest susceptibility to malfunction.
- the invention solves this problem in that the delay set is accommodated in the rotor and is in ignition connection with the detonator at the end at the end of the erosion.
- the self-destruct unit is integrated into the down pipe protection and the entire safety device practically manages with the previous space requirement of a down pipe protection.
- the common arrangement of the delay set and the detonator in the same rotor protects the interaction between the front pipe protection and the self-destruct unit from external interference and ensures optimum functional reliability.
- the required position safeguards for the rotor, the ignition devices for the delay set or for the impact ignition can be applied to any ge be designed in a suitable way, so that despite the space-saving, compact and failure-prone construction concept, a safety device that can be adapted to a wide variety of conditions and circumstances is created.
- the deceleration set It is entirely possible to ignite the deceleration set with an ignition pin which is movable in the longitudinal direction and can be actuated by the launch acceleration, but it may also be expedient if the deceleration set carries an ignition element which is oriented in the rotor pivoting direction and which, when the rotor is pivoted into the focus position on the in A firing pin lying on a normal plane to the axis of rotation of the rotor can be opened, so that the ignition of the deceleration set takes place only at the end of the rotor pivoting movement.
- a rational ignition chain interruption can be achieved in that the front pipe safety device has a locking pin which is adjustable in the longitudinal axis direction and which, due to the impact, can be moved from a locked basic position into a blocking position which hinders the pivoting movement of the rotor.
- the forward movement of the blocking bolt into the blocking position prevents the rotor from pivoting further and thus forcibly prevents the detonator from being positioned in the armed position.
- the front pipe protection therefore leads to a triple security in a common component, namely to protect the front pipe itself, to self-destruction due to the deceleration rate and to the ignition chain interruption by the blocking bolt if the grenade hits prematurely.
- the blocking bolt can be inserted into the bottom of the housing which accommodates the rotor, so that in its blocking position this bolt protrudes into the swiveling path of the rotor and blocks its swiveling movement. However, it can also be inserted into the rotor itself, whereby it is pressed against the housing cover in the blocking position and either engages in an arch slot or penetrates directly into the housing cover with a point and leads to the rotor being blocked.
- the subject matter of the invention is illustrated in the drawing, for example, and shows
- Safety device in axial section along line I-I of FIG. 2 or in horizontal section along line II-II of FIG. 1,
- FIGS. 1 and 2 corresponding sectional views
- Fig. 5 the impact detonator in the event of an ignition chain interruption in a Fig. 3 corresponding axial section
- a safety device 1 for the impact detonator 2 of a grenade 3 comprises a front pipe safety device 4 and a self-destruct unit 5.
- the front pipe safety device 4 has a rotor 7, which is rotatably mounted eccentrically about a longitudinal axis A and which engages with a gear inhibitor 9 via a toothed segment 8 , so that there is a pivoting of the rotor 7 due to centrifugal force, which is initially braked in the region of the toothed segment 8 by the gear inhibitor 9.
- the rotor 7 carries a detonator 10, to which a connection opening 11 for the explosive charge 12 of the grenade 3 is assigned in the housing 6 in the axial extension of the impact detonator 2.
- the grenade can only explode if the detonator 10 is located in the area of this connection opening 11 and is ignited by the ignition connection thus established between the detonator 10 and the explosive charge 12.
- the self-destruct unit 5 consists of a pyrotechnic delay set 13 accommodated in the rotor 7, which has an ignition element 14 on one end and is in ignition connection on the other side with the detonator 10.
- the ignition element 14 is assigned an ignition pin 15 which is axially displaceable against spring force and which fires the delay set 13 due to the firing.
- a radial spring-loaded locking pin 16 is assigned in the housing 6 as a rotation lock and an axial locking bolt 18, which is controlled by a locking ball 17, is used as an acceleration lock, so that during transport, handling and the like.
- the rotor 7 is secured in its starting position, in which the detonator 10 lies outside the area of the connection opening 11 (FIGS. 1 and 2). If the grenade 3 is shot down by a gun barrel, the acceleration forces strike ignites the ignition pin 15 against the ignition element 14 of the delay set 13 and the delay set.
- the radial locking pin 16 is now disengaged due to centrifugal force and the rotor 7 thus released swings radially outward, braking initially taking place via the gear-wheel brake mechanism 9, which allows the pivoting time to be set exactly.
- the detonator 10 can therefore also be swiveled from its initial position into the ignition-ready arming position within a certain period of time, in which it lies above the connection opening 11 to the explosive charge 12 (FIGS. 3 and 4).
- the rotor 7 is fixed via a locking spring 20 which snaps into a housing recess 21 and the grenade remains sharp.
- the detonator 2 can therefore also activate the detonator 10 when the grenade is hit and detonate the explosive charge 12 via the detonator 10. It is of secondary importance how the impact detonator 2 works; it can have a fixed firing pin 22 and a displaceable ignition carrier 24 carrying the primer charge 23, as in the exemplary embodiment shown, but it can also be shown in a manner not shown in relation to the shell shell and solid Ignition pin of movable impact mass comprising the securing device 1 (cf. AT-PS 399 047) directly pierce the detonator 10. If the impact detonator 2 does not come into effect due to an excessively soft impact or the like, the detonator ignition takes place shortly after the impact via the burning delay set 13, the duration of which is matched to the maximum flight time of the grenade.
- a blocking pin 25 which is adjustable in the longitudinal axis direction and is locked in the retracted basic position by means of a spring catch 26 is arranged in the housing 6 on the bottom side, but disengages in the event of a delay due to impact and into a pivoting path of the rotor 7 protruding blocking position (Fig. 5). This stops the rotor from pivoting and the detonator cannot reach its focus, which also prevents a grenade explosion.
- the delay set 13 can also be assigned a ignition pin 27 fixed in the housing in a normal plane to the rotor axis A, so that the delay set 13 only when the rotor 7 is pivoted into the focus by Ignition element 28 aligned in the pivoting direction strikes the ignition pin 27 and is ignited, which results in a better ignition interruption, no malfunctions of the gear brake mechanism 9 due to combustion residues, and even with a shorter burning distance of the delay set 13, it can be found.
- the blocking bolt 25 can also be inserted into the rotor 7 itself, to which bolt an arc slot (not shown) is then assigned in the ceiling area of the housing, so that the bolt 25 engages in this blocking slot in its blocking position when the grenade is opened prematurely and blocks another rotor pivoting movement.
- the self-destruct unit 5 is integrated in the front pipe protection 4 and a compact, space-saving and fault-prone safety device 1 is obtained.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Automotive Seat Belt Assembly (AREA)
Abstract
L'invention concerne un dispositif de sécurité (1) pour la fusée percutante (2) d'une grenade (3) pouvant être mise en rotation lors d'un tir à travers le canon d'une arme. Ce dispositif comprend une sécurité de bouche (4) et une unité d'autodestruction (5). La sécurité de bouche (4) présente un rotor (7) équipé d'un détonateur, monté pour effectuer une rotation de façon excentrique autour d'un axe longitudinal (A), et venant en prise avec un échappement à pignon (9). Sous l'effet de la force centrifuge, mais freiné également par l'échappement à pignon (9), ce rotor (7) fait pivoter le détonateur entre une position initiale et une position activée prête à la détonation. L'unité d'autodestruction (5) est composée d'une composition retardatrice (13) pyrotechnique, pouvant être amorcée au moment du tir par l'intermédiaire d'un percuteur (15), afin d'amorcer le détonateur (10) indépendamment d'un impact. En vue d'une réduction de l'encombrement et de la complexité de construction, ainsi que d'une augmentation de la fiabilité de ce dispositif, la composition retardatrice (13) est logée dans le rotor (7) et est en liaison de mise à feu avec le détonateur (10), à l'extrémité du côté combustion.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP96910854A EP0870168A1 (fr) | 1995-05-05 | 1996-05-03 | Dispositif de securite pour fusee percutante |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
AT76595A ATA76595A (de) | 1995-05-05 | 1995-05-05 | Sicherheitseinrichtung für einen aufschlagzünder |
ATA765/95 | 1995-05-05 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO1996035095A1 true WO1996035095A1 (fr) | 1996-11-07 |
Family
ID=3499183
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/AT1996/000088 WO1996035095A1 (fr) | 1995-05-05 | 1996-05-03 | Dispositif de securite pour fusee percutante |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP0870168A1 (fr) |
AT (1) | ATA76595A (fr) |
WO (1) | WO1996035095A1 (fr) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
ES2161580A1 (es) * | 1997-06-25 | 2001-12-01 | Rheinmetall W & M Gmbh | Espoleta para un proyectil estabilizado por rotacion. |
US7387156B2 (en) | 2005-11-14 | 2008-06-17 | Halliburton Energy Services, Inc. | Perforating safety system |
CN109539907A (zh) * | 2018-08-30 | 2019-03-29 | 重庆长安工业(集团)有限责任公司 | 埋入式火焰反射点火高可靠性自毁机构 |
Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1486177A (en) * | 1918-12-10 | 1924-03-11 | John H Woodberry | Supersensitive fuse |
FR1179371A (fr) * | 1956-06-28 | 1959-05-22 | Inventa Ag | Dispositif de sûreté pour capsules fulminantes de projectiles |
US2999461A (en) * | 1958-03-28 | 1961-09-12 | Mach Tool Works Oerlikon | Impact fuze |
US3181467A (en) * | 1962-08-03 | 1965-05-04 | British Aircraft Corp Ltd | Control mechanisms |
US3906861A (en) * | 1974-01-21 | 1975-09-23 | Us Navy | Fuze sterilization system |
FR2477699A1 (fr) * | 1980-03-10 | 1981-09-11 | Alsetex | Bouchon allumeur de grenade a securite de lancement et fonctionnement reglable |
EP0256320A2 (fr) * | 1986-07-22 | 1988-02-24 | DIEHL GMBH & CO. | Fusée double à autodestruction pour bombe aérienne |
EP0284923A2 (fr) * | 1987-03-31 | 1988-10-05 | TAAS Israel Industries, Limited | Fusée pour une sous-munition |
EP0318996A2 (fr) * | 1987-12-03 | 1989-06-07 | DIEHL GMBH & CO. | Allumeur pyrotechnique pour projectiles, roquettes bombes et mines |
EP0411243A1 (fr) * | 1989-07-29 | 1991-02-06 | Rheinmetall GmbH | Allumeur pour sous-munition du type "bomblet" |
-
1995
- 1995-05-05 AT AT76595A patent/ATA76595A/de not_active Application Discontinuation
-
1996
- 1996-05-03 EP EP96910854A patent/EP0870168A1/fr not_active Withdrawn
- 1996-05-03 WO PCT/AT1996/000088 patent/WO1996035095A1/fr not_active Application Discontinuation
Patent Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1486177A (en) * | 1918-12-10 | 1924-03-11 | John H Woodberry | Supersensitive fuse |
FR1179371A (fr) * | 1956-06-28 | 1959-05-22 | Inventa Ag | Dispositif de sûreté pour capsules fulminantes de projectiles |
US2999461A (en) * | 1958-03-28 | 1961-09-12 | Mach Tool Works Oerlikon | Impact fuze |
US3181467A (en) * | 1962-08-03 | 1965-05-04 | British Aircraft Corp Ltd | Control mechanisms |
US3906861A (en) * | 1974-01-21 | 1975-09-23 | Us Navy | Fuze sterilization system |
FR2477699A1 (fr) * | 1980-03-10 | 1981-09-11 | Alsetex | Bouchon allumeur de grenade a securite de lancement et fonctionnement reglable |
EP0256320A2 (fr) * | 1986-07-22 | 1988-02-24 | DIEHL GMBH & CO. | Fusée double à autodestruction pour bombe aérienne |
EP0284923A2 (fr) * | 1987-03-31 | 1988-10-05 | TAAS Israel Industries, Limited | Fusée pour une sous-munition |
EP0318996A2 (fr) * | 1987-12-03 | 1989-06-07 | DIEHL GMBH & CO. | Allumeur pyrotechnique pour projectiles, roquettes bombes et mines |
EP0411243A1 (fr) * | 1989-07-29 | 1991-02-06 | Rheinmetall GmbH | Allumeur pour sous-munition du type "bomblet" |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
ES2161580A1 (es) * | 1997-06-25 | 2001-12-01 | Rheinmetall W & M Gmbh | Espoleta para un proyectil estabilizado por rotacion. |
US7387156B2 (en) | 2005-11-14 | 2008-06-17 | Halliburton Energy Services, Inc. | Perforating safety system |
CN109539907A (zh) * | 2018-08-30 | 2019-03-29 | 重庆长安工业(集团)有限责任公司 | 埋入式火焰反射点火高可靠性自毁机构 |
Also Published As
Publication number | Publication date |
---|---|
EP0870168A1 (fr) | 1998-10-14 |
ATA76595A (de) | 1998-01-15 |
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