EP0602632A2 - Fusée à sécurité de bouche et projectile comportant une telle fusée - Google Patents

Fusée à sécurité de bouche et projectile comportant une telle fusée Download PDF

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Publication number
EP0602632A2
EP0602632A2 EP93120266A EP93120266A EP0602632A2 EP 0602632 A2 EP0602632 A2 EP 0602632A2 EP 93120266 A EP93120266 A EP 93120266A EP 93120266 A EP93120266 A EP 93120266A EP 0602632 A2 EP0602632 A2 EP 0602632A2
Authority
EP
European Patent Office
Prior art keywords
ignition
securing
projectile
locking
guide
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
EP93120266A
Other languages
German (de)
English (en)
Other versions
EP0602632B1 (fr
EP0602632A3 (fr
Inventor
Uwe Brede
Alfred Hörr
Bodo Preis
Joachim Fibranz
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.)
Dynamit Nobel GmbH Explosivstoff und Systemtechnik
Original Assignee
Dynamit Nobel AG
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 Dynamit Nobel AG filed Critical Dynamit Nobel AG
Publication of EP0602632A2 publication Critical patent/EP0602632A2/fr
Publication of EP0602632A3 publication Critical patent/EP0602632A3/fr
Application granted granted Critical
Publication of EP0602632B1 publication Critical patent/EP0602632B1/fr
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
    • F42C15/24—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected by inertia means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C1/00—Impact fuzes, i.e. fuzes actuated only by ammunition impact
    • F42C1/02—Impact fuzes, i.e. fuzes actuated only by ammunition impact with firing-pin structurally combined with fuze
    • F42C1/04—Impact fuzes, i.e. fuzes actuated only by ammunition impact with firing-pin structurally combined with fuze operating by inertia of members on impact

Definitions

  • the invention relates to a fore-tube safety igniter for low-swirl or non-swirl projectiles, in particular for practice projectiles and in the subsonic area, and to a projectile equipped with such a pre-pipe safety igniter.
  • Such projectiles are fired from a pipe by means of a propellant charge. They are provided with detonators that ignite the projectile when it hits it. So that the projectile cannot ignite during handling or in the vicinity of the pipe, the so-called fore-pipe area, and thereby endanger the operating team, safety detonators are used in which the projectile is only sharp after leaving the fore-pipe area.
  • DE 21 19 574 A1 describes a safety detonator that can be used on projectiles that have little or no rotation.
  • This safety detonator has a safety sleeve and a guide sleeve in a cavity of a casing, which are slidably arranged in the cavity and are plugged into one another.
  • a firing pin provided with a firing pin is slidably guided in a securing position by first securing balls, which partially engage in a groove in the firing pin and partially in openings in the guide sleeve and thus bring about a mechanical coupling between the firing pin and the guide sleeve the guide sleeve is fixed.
  • the guide sleeve in turn, which is biased by a helical compression spring against the direction of flight of the projectile, is held in the securing position by second securing balls, which are arranged in openings in the securing sleeve and partially engage grooves in the guide sleeve, bearing against the cavity wall.
  • the securing sleeve covers the openings in which the first securing balls are arranged, so that they hold the firing pin relative to the guide sleeve.
  • the locking sleeve is fixed with locking pins.
  • the safety detonator is focused in two phases in accordance with DE 21 19 574 A1.
  • a first phase the guide sleeve, the securing sleeve and the firing pin move forward together due to their inertia in the cavity relative to the projectile due to delays acting on the projectile due to the wind resistance.
  • these must be so high that the total mass of guide and securing sleeve and firing pin, which is advanced in the projectile in the direction of flight, compresses the spring.
  • the second securing element which is arranged in the openings in the securing sleeve and the grooves in the guiding sleeve, abuts the cavity wall from the inside, which is why the mechanical coupling between the securing sleeve and the guiding sleeve is maintained.
  • the forward movement of the total mass of guide and securing sleeve and firing pin is limited in that the securing sleeve strikes against the end of the cavity lying in the direction of flight. In this position, the openings in the securing sleeve lie opposite recesses in the cavity wall into which the second securing balls penetrate.
  • the guide sleeve and firing pin remain at the front end of the cavity without the spring expanding.
  • the guide sleeve is moved out of the securing sleeve so far back that the openings in the guide sleeve are exposed. Now the first locking balls can get out of the openings in the guide sleeve, so that the mechanical coupling between the firing pin and the guide sleeve is released.
  • the firing pin which can now be moved freely, is roughly in the position at the rear end of the cavity in which it was at the beginning of the first phase.
  • the projectile or its detonator is in focus, so that the firing pin moves forward due to its inertial forces when the projectile strikes a target and ignites a charge.
  • the guide sleeve and the securing sleeve are then decoupled by disengaging the balls and the guide sleeve moves backward in the cavity under the influence of the compression spring, taking the firing pin with it.
  • the openings of the securing balls are then exposed so that they can disengage and release the firing pin. In this position the firing pin can move freely and the projectile is sharp.
  • the invention has for its object to provide a safety detonator and a projectile equipped with it, the safety detonator having a simple structure and reducing the risk of ignition failure and the flight path deviation and can be used in particular for (practice) projectiles in the subsonic area.
  • the fore-tube safety igniter has a guide element to be fixedly arranged in the cavity of a projectile in order to guide the ignition release element provided for igniting a charge.
  • the ignition trigger element is guided in a longitudinally displaceable manner on the guide element, ie it can be displaced relative to the guide element in the direction of flight (and in the opposite direction), provided that it is not locked on the stationary guide element.
  • This locking is done by a securing element.
  • the securing element In the locked state, the securing element extends both in a recess in the ignition trigger element and in a through hole in the Guide element.
  • the securing element is preferably a ball.
  • a locking and trigger element On the side of the guide element facing away from the ignition trigger element, a locking and trigger element is arranged, which is freely longitudinally displaceable within the cavity of the projectile, ie freely in the projectile flight direction and opposite thereto.
  • the locking and triggering element covers the through hole for locking the ignition triggering element on the guide element and holds the securing ball in this and thus also in the recess of the ignition triggering element. Only when the locking and release element has completely moved past the through hole is the through hole exposed, so that the securing element can emerge from the through hole and thus the locking between the ignition release element and the guide element is released.
  • the retaining force of a retaining spring acts on the ignition trigger element and holds the ignition trigger element in its locking position, in which the securing element is arranged partly in the recess of the ignition trigger element and partly in the through hole of the guide element.
  • both the guide element and the locking and triggering element are each a sleeve body, the ignition triggering element being arranged with radial play in the guide sleeve and the securing sleeve (locking and triggering element) being arranged with play around the guide sleeve.
  • the ignition trigger element is either an element (e.g. firing pin or firing pin) that strikes an (ignition) charge or an element containing an (ignition) charge that strikes a fixed ignition element (e.g. a firing pin) when the projectile hits the target.
  • the ignition trigger element is locked to the guide element via the securing element.
  • the locking and release element is located at the rear end of its displacement path when viewed in the direction of flight of the projectile. It covers the through hole and holds the securing element in this and thus also in the recess of the ignition trigger element.
  • a delay negative acceleration acts on the projectile due to its wind resistance. Due to the inertia of the locking and triggering element, which is freely movable within the cavity, it moves forward in the flight direction of the projectile within the cavity.
  • the ignition trigger element would not oppose one another the force of the retaining spring can advance more when the projectile hits the target. So that such malfunction of the front pipe safety igniter is prevented, the spring ensures that the ignition trigger element cannot move forward if only the inertial forces occurring due to a delay of the projectile due to its air resistance act on the ignition trigger element.
  • the retaining spring retains the ignition trigger element, while the locking and Trigger element is moved forward.
  • the safety device's foreline protection is canceled.
  • the ignition trigger element can move forward when the projectile strikes the target due to the inertia forces that occur due to the strong braking of the projectile against the force of the retaining spring to ignite the charge of the projectile.
  • the safety zone in which the fore-pipe safety detonator according to the invention prevents the charge of the projectile from igniting depends on the time it takes for the locking and releasing element to move completely past the through hole. This time period in turn depends on the speed with which the locking and releasing element moves relative to the guide element within the cavity of the projectile. The length of time (extension in the direction of the projectile flight) of the locking and release element is also decisive for the duration.
  • the speed at which the locking and triggering element is moved in the event of delays acting on the projectile depends in turn on the strength of the braking of the projectile and thus on the wind resistance of the projectile and on the mass of the locking and triggering element.
  • the fore-pipe area in which an undesired ignition of the projectile charge is prevented by the safety detonator according to the invention can be determined by appropriate selection of the above influencing variables.
  • the retention spring has the task of preventing the ignition trigger element from moving to ignite the projectile charge as long as only the forces acting as a result of projectile delays are exerted on the ignition trigger element. Even along the sloping branch of the trajectory of the projectile, this ensures that the ignition trigger element does not advance even before the projectile hits. If the projectile moves along the sloping branch of its trajectory, since the front pipe area has already been left, the locking and releasing element moves past the through hole in the direction of flight.
  • the locking and triggering element is the only part that has to move (when flying through the fore-pipe area) so that the safety detonator is brought into focus despite the safety device. Furthermore, only a single securing element is required in order to lock the ignition trigger element on the guide element. If several securing elements and thus also several through holes are desired in the guide element, more than one securing element can of course also be used. However, a single securing element is sufficient.
  • the front pipe safety igniter according to the invention is to be used in particular in low-swirl or low-swelling projectiles which reach speeds in the subsonic range.
  • projectiles are, in particular, training projectiles and preferably sub-caliber training projectiles with a dummy, into which a sleeve containing the propellant charge is inserted.
  • a projectile head is inserted, which is provided with the front pipe safety fuse according to the invention.
  • Such projectiles are fired with a parabolic trajectory and only have low flight speeds.
  • the trajectory of such a projectile In the initial phase of the trajectory of such a projectile, it is inclined approximately 30 ° to 80 °, preferably 45 ° to 75 °, with respect to the horizontal, in accordance with the firing angle of the launch tube.
  • the bullet is decelerated due to the air resistance. Since the locking and release element is not exposed to these delays in the interior of the projectile, it moves forward in the direction of flight relative to the projectile due to inertial forces.
  • the ignition trigger element is prevented from moving forward by the retaining spring.
  • the inertial forces acting on the locking and triggering element are greater than the resulting forces due to earth acceleration, which act on the locking and triggering element in the opposite direction to the flight.
  • the locking and release element In the front pipe area, the locking and release element first covers the securing element with its end section facing away from the load, until after leaving the front pipe area its end section facing the load has moved past the securing element.
  • the cavity and the locking and release element have corresponding dimensions so that these two end positions can be assumed. As soon as the securing element is freely movable outwards, the safety fuse is in focus.
  • the locking and releasing element (the ignition releasing element) and the projectile are subjected to gravitational forces. Since the projectile is less accelerated by the air resistance than the locking and triggering element (and the ignition triggering element), which are not exposed to the air resistance forces, the locking and triggering element remains in its previously assumed position, in which its end section facing away from the load is at abuts the front end of the cavity.
  • the ignition trigger element is prevented from moving by the retaining spring due to the acting acceleration due to gravity; It is only when the projectile hits that the kinetic energy imparted to the ignition trigger element is greater - and much greater - than the force of the retaining spring. Since the ignition trigger element is unlocked (the securing element is already or is being disengaged by the ignition trigger element through the through hole, the projectile charge is ignited.
  • the smoke bang charge with which such projectiles should be used are provided, be arranged in the rear of the projectile or projectile head, in order to make the projectile impact visible through smoke in the event of a projectile impact in the terrain where the projectile can partially penetrate into the ground.
  • the ignition trigger element is an ignition element which has an ignition charge and which, when moved counter to the force of the retaining spring, can be moved in the direction of a stationary ignition needle to ignite the ignition charge.
  • the ignition trigger element advancing in the direction of flight when the projectile hits the ground hits a fixed ignition needle which ignites the ignition charge of the ignition trigger element.
  • the smoke explosion charge housed in the rear part of the floor is ignited.
  • the ignition charge is thus located between the ignition pin arranged at the front end of the projectile head and the smoke explosion charge arranged in the rear end of the projectile head.
  • a securing part is advantageously provided which prevents the locking and release element from being displaceable longitudinally when the ignition release element is in its locking position.
  • This securing part is preferably a spring-loaded securing pin which, due to its spring preload, flies off the projectile when it leaves the launch tube or, in the case of a sub-caliber practice ammunition, emerges from the propellant sleeve received by the dummy.
  • the securing part preferably not only holds the locking and triggering element in its securing position, but also the ignition triggering element in it Locking position, so that the ignition release element is secured against longitudinal displacement, without the need for the locking with the guide element given via the securing element.
  • the recess of the ignition trigger element is preferably designed as a groove which runs in the circumferential direction and is partially circular in section.
  • the securing element is preferably designed as a ball. The ball is enclosed by part of its spherical outer surface by the groove; in the remaining area, the securing ball is immersed in the through hole of the guide element. Due to the partial encirclement of the locking ball which is essentially immovable in the through-hole covering the through-hole, a good mechanical coupling (locking) of the ignition trigger element to the guide element is achieved via the locking ball.
  • the groove opposite to the flight direction a conically widening region of the ignition trigger element adjoins.
  • the transition area between the groove and the conical area is preferably designed as a shoulder, which reinforces the disengagement movement of the securing ball by the advancing ignition trigger element.
  • a mortar 10 is shown, from the launch tube 12, a projectile 14 can be fired with a parabolic trajectory 16.
  • the launch tube 12 is around a launch angle of about 30 ° to 80 °, preferably from 45 ° to 75 °, inclined to the horizontal.
  • the projectile 14 is a non-rotating, sub-caliber mortar practice projectile with wing stabilization and is fired from a dummy with a propellant casing.
  • the projectile 14 has, in a cylindrical cavity 17, a safety detonator 18 with a safety device, which is arranged in the direction of flight on the projectile tip in the projectile head 20 (FIG. 2).
  • the securing device has a guide element in the form of a guide sleeve 32 with a securing element in the form of a ball 52 arranged in a radial through hole 54 and a locking and release element in the form of a securing sleeve 38.
  • the securing sleeve surrounds the guide sleeve with a small radial distance.
  • the projectile 14 has a smoke explosion charge to be ignited, which is arranged in the direction of flight behind the safety fuse 18 in the rear of the projectile head 20 and protrudes with its front end into the cavity of the projectile head 20.
  • the projectile head 20 is a thick-walled metal tube, which is closed at its front end in the direction of flight with a press-in fitting part, the ignition needle holder 24.
  • the firing pin holder 24 which is also made of metal, has at its rear end in the direction of flight a coaxially protruding cylindrical projection 26 which is pressed into the guide sleeve 32; the projection 26 thus also serves as a bearing for the front end of the guide sleeve 32 in the direction of flight, which is a substantially smooth tube and with its rear end in the direction of flight bears against the load 22 or a holding body 27 inserted into the cavity 17.
  • the wall thickness of the guide sleeve 32 is dimensioned such that an annular space 36 remains between the inner wall 34 and the guide sleeve 32, in which the securing sleeve 38 is inserted with little radial play to the guide sleeve 32 and with radial play to the inner surface 34 delimiting the cavity 17.
  • the securing sleeve 38 has approximately one third of the axial length of the guide sleeve 32 or the annular space 36.
  • an essentially cylindrical ignition element 40 Arranged in the interior of the guide sleeve 32 to trigger the ignition is an essentially cylindrical ignition element 40, which is inserted with play into the guide sleeve 32 and has an ignition charge on its front in the direction of flight.
  • the ignition element 40 has a groove 42, which is partially circular in section and runs in the circumferential direction, to which a conical region 44 adjoins in the opposite direction to the flight direction.
  • the cone-shaped area 44 merges with an outwardly curved curve 46 into the outer (circumferential) surface 48 of the ignition element 40.
  • a shoulder 50 is formed on the ignition element 40 between the groove 42 and the conical region 44.
  • a securing element in the form of a ball 52 is provided, which is arranged in a through hole 54 of the guide sleeve 32 and whose diameter is approximately twice as large as the wall thickness of the Guide sleeve 32.
  • the radius of the ball corresponds to the radius of the groove 42.
  • the securing sleeve 38 rests with its rear end 55 in the direction of flight against the end of the annular space 36 in the direction of flight, that is to say against the holding body 27 and also covers it its through section 54 facing away from the cargo 22 and the holding body 27 and pointing in the direction of flight, the through hole 54 with the ball 52 located therein (FIG. 2).
  • the ball 52 is thereby held in its position against the igniter 40 so that the igniter 40 cannot move and is locked (locking position).
  • At least one securing pin 56 is provided in a radial opening 58 of the projectile head 20, the securing pin 56 being prestressed to the outside by means of a helical compression spring 60.
  • the length of the securing pin 56 is greater than the wall thickness of the projectile head 20, so that the securing pin 56 protrudes into the annular space 36 of the safety igniter 18 in the secured state and the securing sleeve 38 abuts the protruding securing pin 56 with its end facing away from the load 22.
  • the operational readiness of the safety detonator 18 takes place automatically when the projectile 14 is fired, the safety detonator 18 being secured before leaving the dummy in that the securing pin 56 holds the securing sleeve 38 in its securing position according to FIG. 2, in which the securing sleeve 38 in turn the ball 52 in which the ignition element 40 locks the locking position.
  • the securing pin 56 is flung away from the projectile head 20 by the spring action of the helical compression spring 60, so that the securing sleeve 38 is freely movable.
  • the projectile 14 experiences braking due to its air resistance, but this does not affect the securing sleeve 38.
  • As a result of their mass-related Inertial force moves the securing sleeve 38 forward in the flight direction A relative to the projectile head 20.
  • the length and the mass of the securing sleeve 38, the air resistance, the weight and speed of the projectile 14 and the firing angle are coordinated with one another in such a way that the securing sleeve has only moved completely past the through hole 54 after leaving the fore-tube region and releases the ball 52 . Due to the braking effect on the projectile 14, the securing sleeve 38 is thus given a movement force, so that the securing sleeve 38 is in the front tube area (area B in FIG. 1), ie over a length of about 15 m from the mouth of the launch tube 12 Flight direction A can move forward.
  • a helical compression spring 62 is arranged inside the guide sleeve 32 between the ignition element 40 and the projection 26 of the ignition needle holder 24, which has one end on the ignition element 40 and with the other end on a circumferential shoulder 64 of the projection 26.
  • the helical compression spring 62 prevents a relative movement of the ignition element 40 relative to the projectile head 20 due to inertial forces when the projectile 14 decelerates during flight.
  • the ignition element 40 moves toward the ignition needle 30 with high kinetic energy due to its inertia, so that it ignites the ignition charge arranged in the ignition element 40.
  • the resulting fumes ignite the charge 22 arranged in the rear of the projectile 14.
  • the safety fuse 18 is not yet sharp despite the (more or less) advanced securing sleeve 38 the constellation shown in FIG. 6 results.
  • the impact causes the ignition element 40 to be moved forward in the direction of flight A due to its high inertial force (due to the high relative acceleration of the projectile head 20 relative to the ignition element 40).
  • the ball 52 which rests in the part-circular groove 42, is pressed outwards due to the movement of the ignition element 40 via the groove 42 and the cone region 44 and is thereby brought into non-positive contact with the securing sleeve 38.
  • the groove 42 and the shoulder 50 are designed so that even a slight axial forward movement of the ignition element 40 results in a large radially outward disengagement speed of the ball 52.
  • the reliable function of the front pipe safety is ensured by the quick disengagement of the one Reached inner surface portion of the through hole 54 of the immovable guide sleeve 32 ball 52.
  • the ball 52 presses on the outside against the securing sleeve 38.
  • the ignition element 40 is wedged with the securing sleeve 38 via the ball 52. This wedging is so strong that there is room security for the projectile as soon as the fore-tube security function has been initiated.
  • the ball 52 also "digs" into the groove 42 and the conical region 44 on the one hand and the securing sleeve 38 on the other hand due to the large deployment forces.
EP93120266A 1992-12-18 1993-12-16 Fusée à sécurité de bouche et projectile comportant une telle fusée Expired - Lifetime EP0602632B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4242891A DE4242891A1 (de) 1992-12-18 1992-12-18 Vorrohr-Sicherheitszünder und mit diesem ausgestattetes Geschoß
DE4242891 1992-12-18

Publications (3)

Publication Number Publication Date
EP0602632A2 true EP0602632A2 (fr) 1994-06-22
EP0602632A3 EP0602632A3 (fr) 1995-05-03
EP0602632B1 EP0602632B1 (fr) 1998-02-25

Family

ID=6475712

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93120266A Expired - Lifetime EP0602632B1 (fr) 1992-12-18 1993-12-16 Fusée à sécurité de bouche et projectile comportant une telle fusée

Country Status (6)

Country Link
EP (1) EP0602632B1 (fr)
JP (1) JPH06221800A (fr)
KR (1) KR940015456A (fr)
DE (2) DE4242891A1 (fr)
ES (1) ES2114584T3 (fr)
TW (1) TW253933B (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5889227A (en) * 1996-12-13 1999-03-30 Buck Werke Gmbh & Co. Safety mechanism for preventive premature detonation of an explosive projectile
US6457416B1 (en) 1997-10-17 2002-10-01 Rocktek Limited Method and apparatus for removing obstructions in mines
US20110297029A1 (en) * 2010-06-06 2011-12-08 Omnitek Partners Llc Inertial igniters with safety pin for initiation with low setback acceleration
CN107957221A (zh) * 2017-11-29 2018-04-24 贵州贵安新联爆破工程有限公司 一种安全系数高的爆破用雷管装置
CN115235302A (zh) * 2022-07-08 2022-10-25 湖北三江航天红林探控有限公司 一种具有短路切断特性的引爆装置

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101967309B1 (ko) * 2017-11-22 2019-04-09 주식회사 한화 탄약의 이중 안전 장전 장치
KR102645650B1 (ko) * 2021-10-08 2024-03-07 한화에어로스페이스 주식회사 발사체의 신관용 안전 잠금구조체 및 이를 포함하는 발사체

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR690879A (fr) * 1929-02-18 1930-09-26 Anciens Ets Skoda Sécurité pour fusées
US1850042A (en) * 1930-10-31 1932-03-15 Wennerstrom Ernst Joha Torsten Bottom impact fuse for armor-plate piercing shells
FR1577357A (fr) * 1967-04-07 1969-08-08
DE2119574A1 (de) * 1970-04-22 1975-02-13 France Etat Sicherheitsperkussionszuendvorrichtung nach dem traegheitsprinzip fuer geschosse und raketengeschosse

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR690879A (fr) * 1929-02-18 1930-09-26 Anciens Ets Skoda Sécurité pour fusées
US1850042A (en) * 1930-10-31 1932-03-15 Wennerstrom Ernst Joha Torsten Bottom impact fuse for armor-plate piercing shells
FR1577357A (fr) * 1967-04-07 1969-08-08
DE2119574A1 (de) * 1970-04-22 1975-02-13 France Etat Sicherheitsperkussionszuendvorrichtung nach dem traegheitsprinzip fuer geschosse und raketengeschosse

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5889227A (en) * 1996-12-13 1999-03-30 Buck Werke Gmbh & Co. Safety mechanism for preventive premature detonation of an explosive projectile
US6457416B1 (en) 1997-10-17 2002-10-01 Rocktek Limited Method and apparatus for removing obstructions in mines
US7047886B2 (en) 1997-10-17 2006-05-23 Rocktek Limited Method and apparatus for removing obstructions in the mines
US20110297029A1 (en) * 2010-06-06 2011-12-08 Omnitek Partners Llc Inertial igniters with safety pin for initiation with low setback acceleration
CN107957221A (zh) * 2017-11-29 2018-04-24 贵州贵安新联爆破工程有限公司 一种安全系数高的爆破用雷管装置
CN115235302A (zh) * 2022-07-08 2022-10-25 湖北三江航天红林探控有限公司 一种具有短路切断特性的引爆装置
CN115235302B (zh) * 2022-07-08 2023-04-28 湖北三江航天红林探控有限公司 一种具有短路切断特性的引爆装置

Also Published As

Publication number Publication date
TW253933B (fr) 1995-08-11
EP0602632B1 (fr) 1998-02-25
JPH06221800A (ja) 1994-08-12
EP0602632A3 (fr) 1995-05-03
DE59308174D1 (de) 1998-04-02
ES2114584T3 (es) 1998-06-01
KR940015456A (ko) 1994-07-21
DE4242891A1 (de) 1994-06-23

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