EP1934549A2 - Cartouche - Google Patents

Cartouche

Info

Publication number
EP1934549A2
EP1934549A2 EP06804349A EP06804349A EP1934549A2 EP 1934549 A2 EP1934549 A2 EP 1934549A2 EP 06804349 A EP06804349 A EP 06804349A EP 06804349 A EP06804349 A EP 06804349A EP 1934549 A2 EP1934549 A2 EP 1934549A2
Authority
EP
European Patent Office
Prior art keywords
projectile
propellant
cup
cartridge according
cartridge
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
EP06804349A
Other languages
German (de)
English (en)
Other versions
EP1934549B1 (fr
Inventor
Udo Winter
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of EP1934549A2 publication Critical patent/EP1934549A2/fr
Application granted granted Critical
Publication of EP1934549B1 publication Critical patent/EP1934549B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B14/00—Projectiles or missiles characterised by arrangements for guiding or sealing them inside barrels, or for lubricating or cleaning barrels
    • F42B14/06—Sub-calibre projectiles having sabots; Sabots therefor
    • F42B14/064—Sabots enclosing the rear end of a kinetic energy projectile, i.e. having a closed disk shaped obturator base and petals extending forward from said base
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/22—Projectiles of cannelured type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B7/00—Shotgun ammunition
    • F42B7/02—Cartridges, i.e. cases with propellant charge and missile
    • F42B7/10—Ball or slug shotgun cartridges

Definitions

  • the invention relates to a cartridge with a cartridge case and with a inserted into the cartridge case, a subcaliber projectile positively receiving, made of plasticmaschinebecher that separates the projectile from the propellant in the cartridge case and along its shell has axial separation points.
  • the invention is therefore based on the object, a cartridge of the type described in such a way that for the projectile not only advantageous for the flight stability projectile length can be ensured without having to accept reduced amounts of propellant charge, but also a centric leadership of Bullet is guaranteed in the course regardless of manufacturing tolerances.
  • the propellant cup has at least one opening in a cavity between the projectile and the cartridge case and / or in a cavity of the projectile, open towards the bottom of the cartridge case for receiving a portion of the propellant charge.
  • the propellant cup forms at least one pocket open against the bottom of the cartridge case, which extends over a length of the projectile, a portion of the propellant charge can be accommodated in that case so that the space required to accommodate the between the bottom of the cartridge case and the projectile Propellant charge is reduced by the receiving volume of the pocket of the driving cup, and additional space for the extension of the projectile is created.
  • Prerequisite is at least one free from the projectile cavity into which a pocket of the propellant can extend.
  • the cavities can be provided in different ways and depend essentially on the construction of the projectiles.
  • the projectile is rotatably connected by the guide vanes with the drive sleeve, so that the projectile when firing from a drawn barrel a swirl egg is divided when the propellant gases press the jacket of the propellant cup against the features of the barrel.
  • Another way to create space for a pocket of the propellant bucket in the projectile area is to provide the projectile with a central recess in the projectile floor into which the pocket of the propellant cup extends.
  • the annular space remaining free between the conical projectile end and the jacket of the propellant can be used to form a receiving pocket in the form of an annular chamber, via which the propellant can be sealed in the barrel after ignition of the propellant charge on the other hand, the projectile is centered inside the propellant cup.
  • the propellant cup may have a forwardly tapering lateral surface with longitudinal ribs distributed over the circumference, the envelope surface of which is an enveloping cylinder. Linder the Treibbechers corresponds. Despite the passage through the throat opening facilitating conical surface results in a good leadership of the fürbechers within the barrel by the circumferentially distributed longitudinal ribs that leak in a conical part of the shell of themaschinebechers to the seal between the fürbecher and the barrel against the Do not endanger propellants.
  • the longitudinal ribs of the jacket projecting beyond an axial section of the lateral surface can be sufficiently deformed due to the mutual lateral distances in order to allow the driving cup with the projectile to escape from the barrel through the choke opening.
  • the projectile may form at its head a re-entrant annular shoulder engaged by the propellant cup, which not only secures a secure axial hold of the projectile within the propellant cup, but also contributes to flight stabilization of the projectile.
  • the mantle of the propellant can be supported on this annular shoulder to counteract the risk of compression of the propellant cup during its expulsion from the barrel.
  • propellant gases can reach the projectile bottom during ejection of the projectile from a barrel, for example for igniting a flare unit provided in the projectile or a tear gas charge deceleration kit , If the projectile forms a cavity adjoining the overflow channel, then the gas pressure which builds up in the cavity during expulsion of the projectile from the barrel can be used to detach the propellant cup more quickly from the projectile after it leaves the barrel.
  • the shape of the driving cup is dependent on the configuration of the projectile, which can be designed differently.
  • the projectile it is possible for the projectile to form a hollow body which is open against the propellant cup and which is folded into guide vanes, which results in a machining of the projectile for the formation of the deflector blades.
  • Particularly advantageous conditions for a different design or adaptation of the projectile to different conditions arise when the projectile consists of a head and a tail inserted into the hollow head, the guide vanes extend into the head area, so that the tail combined with different projectile heads can be, if necessary, without having to make an adjustment of themaschinebechers.
  • the connection between the projectile head and the tail can preferably be achieved by the fact that the head is folded into the gusset area between the guide vanes by clamping.
  • the projectile may also have a different from a body of revolution, star-shaped cross-section, which makes the formation of separate guide vanes unnecessary and brings a greater punch-through effect.
  • This star-shaped cross-section can be produced in a particularly advantageous manner, characterized in that the projectile consists of a tubular body which is folded radially to form axial wings.
  • the remaining cavity of the folded tubular body can be at least partially filled with a metal.
  • Projectiles with a star-shaped cross-section require a propellant cup whose pockets which reach between the star-shaped wings of the projectile may have a possibly reinforced bottom in order to be able to withstand the gas pressure.
  • the propellant cup may comprise at least one circumferential sealing ring, in the formation of which the axial separation points of the jacket of the propellant cup extending into the sealing area may have to be taken into account by the sealing ring forming sections guided around the rear ends of these separating locations.
  • the mantle of the propellant cup need not extend beyond the axial length of the propellant cup.
  • the inner walls bounding the pockets of the propellant cup may protrude in the axial direction over the casing of the propellant cup against the bottom of the cartridge case.
  • the inner walls defining the pockets of the driving cup can have, in the extension of the casing, axial guide ribs which ensure a corresponding guide length for the driving cup.
  • the pressure of the propellant gases can be advantageously transferred via the propellant cup to the projectile, the projectile can be supported in the axial direction via damping elements preferably at the bottom of the propellant cup, so that when a pressurization of the propellant cup with the pressure of the propellant gases a damped pressure transmission through a Deformation of these ribs sets.
  • D'ese damping elements may consist of provided on the bottom of the propellant cup, projecting against the projectile damping ribs.
  • the damping ribs can also be used for axial tolerance compensation between the driving cup and the projectile.
  • a damped pressure transmission from the propellant cup to the projectile can also be achieved by a damping mass partially filling the pockets of the propellant cup.
  • FIG. 1 shows a cartridge according to the invention in a simplified longitudinal section
  • 2 shows the driving cup with the projectile of the cartridge of FIG. 1 in a simplified side view
  • FIG. 5 shows a representation corresponding to FIG. 4 of a variant of a driving cup with the associated projectile
  • FIG. 6 shows a further embodiment of a propellant bucket with a projectile in a simplified longitudinal section
  • FIG. 7 shows an additional embodiment of a projectile with a driving cup in a representation corresponding to FIG. 4, FIG.
  • FIG. 8 shows a further construction form of a projectile in a driving cup in a longitudinal section corresponding to FIG. 4, FIG.
  • FIG. 11 shows a further embodiment of a projectile with an associated driving cup in a longitudinal section
  • 13 is a projectile with a tail in a partially torn side view
  • FIG. 14 shows the projectile according to FIG. 13 in a section along the line XIV-XIV of FIG. 13, FIG.
  • Fig. 15 shows a further projectile shape with a driving cup in an axial section
  • 16 is a section along the line XVI - XVI of FIG. 15.
  • the cartridge comprises a cartridge case 1 with a bottom 2 and a primer 3 inserted into the bottom 2 and a blowing cup 4 made of plastic for receiving a subcaliber projectile 5.
  • the propellant cup 4 encloses the projectile 5 positively, the one against the rear end tapered projectile body.
  • the shell 10 of the propellant can 4 has a forwardly tapered lateral surface 13, which is provided with circumferentially distributed longitudinal ribs 14 whose envelope corresponds to an enveloping cylinder of the propellant can 4, so that they run flat against the rear end of the shell 10, such as this particular of Fig. 2 can be removed.
  • separation points 15 which may optionally also be designed as predetermined breaking points, must of course not affect the seal between the shell 10 of the propellant bowl 4 and the barrel, because yes, the Austriebskraft depends on this seal. Therefore, if the separation points 15 are axially extended rearwardly beyond a preferably provided sealing ring 16, as is indicated in FIGS. 2 and 4, axial sealing sections 17 surrounding each of the rear ends of the separation points 15 are provided for a seal closed on the circumference to care.
  • the projectile 5 forms at its head 18 a re-entrant annular shoulder 19 which is overlapped by the jacket 10 of the propellant can 4. Thus, the projectile 5 is fixed axially in the propellant cup 4 and can be used together with the propellant cup 4 in the cartridge case 1.
  • the Hait für the Treibbechers 4 together with the projectile 5 in the cartridge case 1 is achieved in a conventional manner by a flanged edge 20 of the cartridge case 1, as shown in FIG. 1 can be removed.
  • the axial support of the shell 10 of the propellant can 4 on the annular shoulder 19 of the projectile head 18 but not only serves for the axial location of the projectile 5 within the propellant can 4, but also causes a relief of the shell 10 of axial compressive forces, the expulsion of the projectile 5 via be acted upon by the propellant gases propellant cup 4 on the jacket 10.
  • the jacket 10 is to ensure a minimum deformation in order to improve the sealing effect between the jacket 10 and the barrel by the effective in the pockets 9 propellant gas pressure.
  • the projectile 5 can be supported in the axial direction via damping elements 21 at the bottom of the propellant cup 4, in FIGS. 1 and 4 these attenuation elements 21 are in shape provided by damping ribs 22 which extend transversely to the guide vanes 8 of the projectile 5.
  • FIG. 5 differs from that of FIGS. 1 to 4, especially in that the jacket 10 of the propellant cup 4 extends substantially over the entire length of the propellant cup 4, which compared to over the shell 10 axially protruding inner walls 11 according to the embodiment of FIGS. 1 to 4 brings with it the disadvantage of a smaller Consvolumen ⁇ for the propellant charge, but has the advantage of obtaining over the axial length of the propellant bowl 4 continuous leadership of the propellant bowl 4 in the barrel, without any to provide additional construction measures.
  • the inner walls 11 in the axial direction In the embodiment shown, these guide ribs 23 also serve as sealing sections 17.
  • the projectile head 18 has no annular shoulder 19.
  • the axial fixing of the projectile 5 in the propellant can 4 is effected by a concave inner wall 24 of the propellant can 10 which projects over the convex head 18.
  • the projectile 5 of FIG. 6 is provided with a luminous unit 25, but otherwise agrees substantially with that of FIGS. 1 to 4 match.
  • the traction cup 4 forms a closed by a membrane 26 overflow channel 27 for the propellant gases, which break through the membrane 26 upon actuation of the propellant bucket 4 and provide for ignition of the tracer unit 25.
  • the projectiles 5 can be adapted to different conditions and varied, as illustrated in FIGS. 7 to 16 in some embodiments.
  • the propellant cup 4 is to be adapted in each case to the projectile shape.
  • Fig. 7 shows a projectile 5, which is formed from a hollow body of revolution and receives its flight guidance through outgoing from the bottom end face of the projectile shell 28 Mantelaussparungen 29 through which the pockets 9 of the propellant bucket 4 extend.
  • a projectile 5 which is cylindrical in its basic form is provided, which has a central recess 32 in the projectile base into which a pocket 9 of the driving cup 4 extends.
  • the bottom of the pocket 9 is provided with a closed by a membrane 26 overflow 27, which opens into a recess 32 adjoining the cavity 30 of the projectile 5 to the up in the cavity 30 after breaking through the membrane 26 gas pressure to detach the To use blowing cup 4 from the floor 5, as soon as the driving cup 4 with the projectile 5 exits the barrel.
  • FIGS. 9 and 10 shows a projectile 5, which has a star-shaped cross-section, which represents a continuous over the projectile length tail.
  • the pockets 9 of the driving cup 4 thus engage in the gusset area between the star-shaped wings 33 of the projectile 5.
  • the bottom of the bag 34 is reinforced, so that the loading pressure can be absorbed by the propellant gases from the propellant cup 4, which can indeed be supported only at the rear end of the star-shaped wings 33 of the projectile 5.
  • the projectile according to FIGS. 11 and 12 differs from that according to FIGS. 9 and 10 above all in that it was manufactured from a tubular body which was radially folded in to form the axial wings 33, as shown particularly in FIG. 12 can be removed.
  • the outer shape of the projectile 5 thus corresponds to that of FIGS. 9 and 10, so that there is also a matchingmaschinebecher 4.
  • the remaining cavity of the folded tubular body can be filled with a metal 35.
  • To produce a projectile shape with a tail 7 from guide vanes 8 can be assumed by an open against the propellant cup 4 hollow body, which is folded according to FIGS. 13 and 14 to guide vanes 8, according to the embodiment to three guide vanes 8.
  • these folded guide wings 8 are illustrated, wherein the pockets 9 delimiting inner walls 11 of the driving cup 4 are indicated by dash-dotted lines.
  • a projectile 5 is not manufactured in one piece, but consists of a head 18 and a tail unit 7 inserted into the hollow head 18, whose guide wings 8 extend into the head area, as is the case, for example Figs. 4 to 6 is shown.
  • This two-part design of the projectile 5 allows the use of different bullet heads 18 at each matching tail 7th
  • annular chamber Is omitted in the projectile training on a tail and a conically tapered to its bottom 5 projectile as shown in FIGS. 15 and 16, so that between this projectile 5 and the jacket 10 of the propellant bowl 4 resulting annular chamber can as a receiving pocket 9 for receiving a Part of the propellant be used.
  • This annular chamber can undergo a subdivision through the axial longitudinal slots of the separating points 15, as can be seen from FIG. 16.
  • the pockets 9 may indeed have no passage points in the area of the jacket 10 to the outside.
  • Such a projectile 5, with its central cavity 37, provides a comparative storage volume for firing an agent to the destination.
  • the driving cup 4 can be more easily detached from the projectile 5, can be dispensed with a continuous planar contact of the projectile body on the jacket 10 of the propellant can 4 and the propellant can 4 are provided with an axial ribbing 36, as shown for example in FIGS. 15 and 16 is.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Toys (AREA)
  • Closures For Containers (AREA)
  • Containers And Packaging Bodies Having A Special Means To Remove Contents (AREA)

Abstract

La présente invention concerne une cartouche comprenant une douille de cartouche (1) et un culot de propulsion en plastique (4) qui est inséré dans la douille de cartouche (1) et qui vient en prise par liaison de forme avec un projectile sous-calibré (5). Ce culot de propulsion sépare le projectile (5) de la charge propulsive dans la douille de cartouche (1) et présente des points de séparation axiaux (15) le long de sa chemise (10). Afin d'obtenir une longueur avantageuse du projectile, le culot de propulsion (4) présente une poche ouverte (9) qui s'étend dans une cavité entre le projectile (5) et la douille de cartouche (1) et/ou dans une cavité du projectile (5), contre le fond (2) de la douille de cartouche (1), et qui est conçue pour recevoir une partie de la charge propulsive.
EP06804349A 2005-10-13 2006-10-12 Cartouche Not-in-force EP1934549B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
AT0167405A AT502547B1 (de) 2005-10-13 2005-10-13 Patrone
PCT/AT2006/000421 WO2007041740A2 (fr) 2005-10-13 2006-10-12 Cartouche

Publications (2)

Publication Number Publication Date
EP1934549A2 true EP1934549A2 (fr) 2008-06-25
EP1934549B1 EP1934549B1 (fr) 2011-11-16

Family

ID=37685293

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06804349A Not-in-force EP1934549B1 (fr) 2005-10-13 2006-10-12 Cartouche

Country Status (5)

Country Link
US (1) US8037830B2 (fr)
EP (1) EP1934549B1 (fr)
AT (2) AT502547B1 (fr)
RU (1) RU2419760C2 (fr)
WO (1) WO2007041740A2 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100843573B1 (ko) * 2008-03-13 2008-07-03 (주)한국원자력 엔지니어링 탄약
RU2631515C1 (ru) * 2014-08-26 2017-09-25 Ренат Абдульберович Юсупов Калиберный снаряд с жёстким креплением к корпусу стабилизирующего оперения, пластины которого имеют продолжение на корпус, центрируя снаряд по стволу
DE102014019198A1 (de) * 2014-12-19 2016-06-23 Diehl Bgt Defence Gmbh & Co. Kg Geschoss
US10502515B2 (en) * 2017-01-17 2019-12-10 Raytheon Company Launch piston brake
US10443990B2 (en) * 2017-06-08 2019-10-15 Connor Yadon Fragmenting shotgun projectile with radially-disposed segments
RU2738519C2 (ru) * 2019-03-11 2020-12-14 Виталий Анатольевич Денисов Поддон снаряда съемный

Family Cites Families (53)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US34950A (en) * 1862-04-15 Improvement in expanding sabots for hot shot
US193657A (en) * 1877-07-31 Improvement in projectiles
US178595A (en) * 1876-06-13 Improvement in projectiles for ordnance
US214843A (en) * 1879-04-29 Improvement in projectiles for rifled guns
US1166360A (en) * 1915-05-22 1915-12-28 Eli E Gregory Gun cartridge and projectile.
US2247563A (en) * 1939-10-18 1941-07-01 Robert S Spalding Projectile
US2991719A (en) * 1944-06-24 1961-07-11 Millar John Mcg Projectile
US2993444A (en) * 1945-08-02 1961-07-25 Charles E Hablutzel Sabot retainer
US2669930A (en) * 1946-01-05 1954-02-23 Remington Arms Co Inc Sabot projectile
US2982212A (en) * 1955-12-29 1961-05-02 Jr Ralph O Robinson Base fuze protector
US3055268A (en) * 1960-12-08 1962-09-25 Rosenthal Henry Discarding obturator and rotator for projectiles
US3164092A (en) * 1962-11-13 1965-01-05 Remington Arms Co Inc Ammunition sabot
US3242866A (en) * 1964-09-25 1966-03-29 Richard L Malter Primary and secondary projectile
NL6514247A (fr) * 1964-12-22 1966-06-23
US3318244A (en) 1965-07-01 1967-05-09 Charles E Rostocil Cartridge
NL137889C (fr) * 1967-07-28
US3431815A (en) * 1968-01-24 1969-03-11 Us Army Discardable rotating band
DE2630830A1 (de) 1976-07-09 1978-01-19 Dynamit Nobel Ag Treibspiegelgeschoss
DE2642222C2 (de) * 1976-09-20 1983-11-10 Rheinmetall GmbH, 4000 Düsseldorf Drallstabilisiertes Ringgeschoß
CH622883A5 (fr) * 1977-07-21 1981-04-30 Oerlikon Buehrle Ag
US4175493A (en) * 1977-11-07 1979-11-27 John Daily Patch for muzzle loading firearms
DE2836963A1 (de) 1978-08-24 1984-03-08 Rheinmetall GmbH, 4000 Düsseldorf Munition-einheit fuer rohrwaffen
DE3037560A1 (de) * 1980-10-04 1984-11-29 Rheinmetall GmbH, 4000 Düsseldorf Panzerbrechendes geschoss
US4434718A (en) 1981-09-11 1984-03-06 Kopsch Paul J Sabot and projectile
US4709638A (en) * 1981-09-24 1987-12-01 Honeywell Inc. Discarding sabot projectile
FR2555728B1 (fr) * 1983-11-29 1987-03-20 Sauvestre Jean Claude Munition pour arme de chasse
AT386896B (de) * 1986-07-08 1988-10-25 Steyr Daimler Puch Ag Patrone fuer schusswaffen
DE3811597A1 (de) 1988-04-07 1989-10-19 Dynamit Nobel Ag Treibkaefig fuer ein unterkalibergeschoss
DE3824524A1 (de) 1988-07-20 1990-02-08 Wegmann & Co Panzerbrechendes geschoss
DE3843289A1 (de) * 1988-12-22 1990-06-28 Diehl Gmbh & Co Treibspiegelmunition
FR2647891B1 (fr) * 1989-06-01 1994-05-20 Etat Francais Delegue Armement Dispositif de maintien d'un projectile sous-calibre relativement a l'enveloppe d'une munition telescopee
US4936220A (en) * 1989-07-03 1990-06-26 The United States Of America As Represented By The Secretary Of The Army Solid propellant-carrying caboted projectile
DE4026902C2 (de) * 1990-08-25 1995-01-05 Rheinmetall Gmbh Geschoß
US5359938A (en) * 1990-10-24 1994-11-01 Olin Corporation Ultra light weight sabot
US5192830A (en) * 1992-01-29 1993-03-09 The United States Of America As Represented By The Secretary Of The Army Sabot for high dispersion shot shell
US5189251A (en) * 1992-01-29 1993-02-23 The United States Of America As Represented By The Secretary Of The Army Sabot for high dispersion shot shell
US5214238A (en) * 1992-03-23 1993-05-25 Christopher Young Sabot for chambering conventional bullets in a shotgun
US5339743A (en) 1993-07-12 1994-08-23 Remington Arms Company, Inc. Ammunition system comprising slug holding sabot and slug type shot shell
EG21731A (en) * 1993-09-24 2002-02-27 Contraves Pyrotec Ag Releasable sabot for a subcaliber projectile
US5710391A (en) * 1993-10-12 1998-01-20 Chetcuti; Francis Recoil reducer wad for ammunition
US5415102A (en) * 1994-05-13 1995-05-16 White; Gary B. Muzzle loading sabot
FR2726357B1 (fr) * 1994-10-26 1997-01-17 Sauvestre Jean Claude Balle de chasse a fleche telescopee, comportant un sous-projectile associe a un lanceur
DE19741841C2 (de) 1997-09-23 2000-07-06 Rheinmetall W & M Gmbh Verfahren zur Herstellung einer Patrone
US6073560A (en) 1998-03-09 2000-06-13 Remington Arms Company, Inc. Sabot
DE10157668B4 (de) * 2001-11-24 2014-05-22 Rheinmetall Waffe Munition Gmbh Geschoss
DE10244571C1 (de) * 2002-09-25 2003-12-04 Wilhelm Brenneke Gmbh & Co Kg Flintenlaufgeschoss
US6895865B2 (en) * 2003-03-20 2005-05-24 Hornady Manufacturing Company Sabot for muzzleloading firearm
US7451705B2 (en) * 2004-03-17 2008-11-18 Fry Grant R Non-discarding sabot projectile system
US7451706B2 (en) * 2005-01-25 2008-11-18 Olin Corporation Short magnum shotshell cartridge and firing assembly
US20060278114A1 (en) * 2005-05-16 2006-12-14 Hornady Manufacturing Company Shotgun shell with slug
US7243603B2 (en) * 2005-07-12 2007-07-17 Sheaffer Clifford G Shot pattern control wad structure for shotshell
AT502514B1 (de) * 2005-10-13 2007-04-15 Winter Udo Mag Unterkalibriges geschoss
RU2349869C1 (ru) * 2007-12-13 2009-03-20 Михаил Юрьевич Иванов Пулевой снаряд для охотничьих ружей с гладкими стволами и "парадоксами"

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2007041740A2 *

Also Published As

Publication number Publication date
WO2007041740A2 (fr) 2007-04-19
WO2007041740A3 (fr) 2007-07-12
AT502547A1 (de) 2007-04-15
EP1934549B1 (fr) 2011-11-16
RU2008118477A (ru) 2009-11-20
AT502547B1 (de) 2009-10-15
RU2419760C2 (ru) 2011-05-27
ATE534013T1 (de) 2011-12-15
US8037830B2 (en) 2011-10-18
US20090064887A1 (en) 2009-03-12

Similar Documents

Publication Publication Date Title
DE2914049C2 (de) Patrone
DE2265398C3 (de) Patrone
DE69512118T2 (de) Geschoss, insbesondere nicht tötende Patrone
DE4123649C2 (de) Ausstoßvorrichtung
DE69915427T2 (de) Munitionskartusche mit ihrer Treibladungskonfiguration
DE60004289T2 (de) Hybridgasgenerator mit einem Bohrpfosten
CH625613A5 (fr)
EP0842390A1 (fr) Munition encartouchee
EP0107766A1 (fr) Cartouche d'exercice avec balle en plastique
DE7818115U1 (de) Treibspiegelgeschoss mit pyrotechnischem satz
DE60104950T2 (de) Anzündrohr für artilleriemunition
DE1625202A1 (de) Vorrichtung zur Aufnahme und Abgabe von teilchenfoermigem Material
EP1934549B1 (fr) Cartouche
EP0303198B1 (fr) Cartouche pour expulser des liquides par pression
DE2757807C2 (de) Flugkörper mit Eigenantrieb, insbesondere Rakete
DE1453824C3 (de) Treibkartusche für pulverkraftbetriebene Geräte zur gewerblichen Nutzung
CH662646A5 (de) Geschoss mit einem rohrfoermigen koerper.
AT502514B1 (de) Unterkalibriges geschoss
DE69406896T2 (de) Vorrichtung zum gleichzeitigen Ausstossen von zwei Flüssigkeiten, insbesondere pyrotechnischen Flüssigkeiten
DE949726C (de) Kraftgas erzeugende Ladung
DE611842C (de) Brandgeschoss
DE2327827A1 (de) Raketengetriebenes leuchtgeschoss
DE102023002054A1 (de) Verfahren zur Auslösung einer Zeitzündung einer in der Luft explodierbaren Sprengladung eines von einem Geschoss ablösbaren Kopfs und Anordnung seiner Flugwerkgruppe
DE2141403C3 (de) Druckbetätigungseinrichtung innerhalb von Flugkörpern
DE102004062931A1 (de) Patrone

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20080328

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

17Q First examination report despatched

Effective date: 20090806

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

DAX Request for extension of the european patent (deleted)
GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

RIN1 Information on inventor provided before grant (corrected)

Inventor name: WINTER, UDO

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502006010609

Country of ref document: DE

Effective date: 20120112

REG Reference to a national code

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20111116

LTIE Lt: invalidation of european patent or patent extension

Effective date: 20111116

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20111116

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120316

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20111116

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20111116

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20111116

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120217

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20111116

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20111116

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120316

REG Reference to a national code

Ref country code: IE

Ref legal event code: FD4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20111116

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20111116

Ref country code: IE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20111116

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20111116

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20111116

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20111116

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120216

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20111116

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20111116

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20120817

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502006010609

Country of ref document: DE

Effective date: 20120817

BERE Be: lapsed

Owner name: WINTER, UDO

Effective date: 20121031

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120227

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121031

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20121012

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20111116

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20130628

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121031

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121031

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130501

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121031

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121012

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502006010609

Country of ref document: DE

Effective date: 20130501

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121031

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 534013

Country of ref document: AT

Kind code of ref document: T

Effective date: 20121031

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121031

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20111116

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121012

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20061012