EP1934549A2

EP1934549A2 - Cartridge

Info

Publication number: EP1934549A2
Application number: EP06804349A
Authority: EP
Inventors: Udo Winter
Original assignee: Individual
Current assignee: Individual
Priority date: 2005-10-13
Filing date: 2006-10-12
Publication date: 2008-06-25
Anticipated expiration: 2026-10-12
Also published as: WO2007041740A3; AT502547A1; RU2008118477A; EP1934549B1; ATE534013T1; RU2419760C2; AT502547B1; WO2007041740A2; US20090064887A1; US8037830B2

Abstract

The invention relates to a cartridge which comprises a cartridge bushing (1) and a plastic propulsion cup (4) which is inserted into the cartridge bushing (1) and which is received in a positive fit with a sub-calibre projectile (5). Said propulsion cup separates the projectile (5) from the propellant charge in the cartridge bushing (1) and comprises axial separation points (15) along the covering (10). According to the invention, the propellant cup (4) comprises at least one open pocket (9) which extends in a cavity between the projectile (5) and the cartridge bushing (1) and/or in the cavity of the projectile, counter to the base (2) of the cartridge bushing (1) and which is used to receive one part of the propellant charge, in order for the projectile to have an advantageous length.

Description

cartridge

Technical area

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 plastic Treibbecher that separates the projectile from the propellant in the cartridge case and along its shell has axial separation points.

State of the art

In order to be able to shoot subcaliber projectiles from, for example, shotgun barrels, it is known, inter alia (US Pat. No. 4,434,718 A), to use the missile-provided projectile in a propellant bucket which is received by a cartridge case together with the projectile. The Treibbecher has a reinforced by a metal disc bottom and a shell enclosing the shell, which is provided with axial predetermined breaking points. If the intended between the bottom of the cartridge case and the propellant cup propellant ignited such introduced into a cartridge chamber of a shotgun cartridge, the resulting propellant gases propel the propellant cup with the projectile from the cartridge case into the barrel barrel in which the subcaliber projectile is guided over the propellant cup , When leaving the gun barrel the mantle of the propellant cup is spread by the air resistance and dissolves from the flying projectile. The disadvantage of these known cartridges is, above all, that with a given length of the cartridge case and a predetermined amount of propellant charge, the length of the lower-caliber projectile is limited, which, despite the tail of the projectile, adversely affects the accuracy of the trajectory. In addition, that the seal between the Treibbecher and the shotgun barrel exclusively over a can be done by the bottom of the blowing cup formed sealing ring, which brings a tolerance dependence with it. Despite axial guide ribs of the shell of the driving cup therefore a centric guidance of the projectile in shotgun barrel can not always be ensured.

Presentation of the invention

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 invention solves this problem by the fact that 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.

Since 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.

Particularly advantageous conditions arise in this context, when the pockets of the driving cup extend between axial guide vanes of the projectile. The gusset space between the guide vanes allows the provision of the projectile rotationally symmetrical surrounding pockets which are closed by the mantle of Treibbechers radially outward, so that the pressure of the propellant gases presses the mantle of Treibbechers radially outward against the barrel from which the projectile is launched. This means an advantageous seal of the propellant bowl over the barrel regardless of manufacturing tolerances. In addition, the projectile in the propellant cup is additionally centered by the propellant gas pressure within the surrounding surrounding the projectile pockets of the propellant cup, which has an advantageous effect on the guidance accuracy of the projectile. In addition, 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. Although on such a bag no sealing effect improving forces can be exerted on the propellant gases on the mantle of the driving cup, there is an improvement in the projectile leadership, because the projectile is centered in this pocket positively against the Treibbecher.

If the projectile tapers conically towards its bottom, then 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.

For runs with a narrowed orifice, a largely unobstructed passage of the propellant bucket through this choke opening is to be ensured. For this purpose, 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 Treibbechers within the barrel by the circumferentially distributed longitudinal ribs that leak in a conical part of the shell of the Treibbechers to the seal between the Treibbecher 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. In addition, 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.

If the propellant cup is provided with at least one membrane closing off the projectile through the propellant gases, 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.

As already stated, the shape of the driving cup is dependent on the configuration of the projectile, which can be designed differently. Thus, for a simple production of 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. übrigt. 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 the Treibbechers. 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. In order to increase the projectile weight, in this embodiment, 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.

To seal the propellant bowl relative to the barrel, 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.

If the inner walls bounding the pockets of the propellant cup run counter to the propellant charge in a cutting edge, the penetration of the propellant cup into the propellant charge is facilitated if the propellant cup with the projectile is inserted into the cartridge case filled with the propellant charge. In addition, a tion of these cutting cause an axial tolerance compensation between bullet and cartridge case.

The mantle of the propellant cup need not extend beyond the axial length of the propellant cup. In order to provide a larger volume for the propellant charge, 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. However, such an embodiment of the propellant bucket requires a shorter guide length for the propellant cup, which makes disadvantageous especially when leaving the barrel. For this reason, 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.

Thus, 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. However, 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.

Short description of the drawing

In the drawing, the subject invention is shown, for example. 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,

3 is a section along the line III - III of Fig. 2,

4 is a section along the line IV - IV of FIG. 3,

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,

7 shows an additional embodiment of a projectile with a driving cup in a representation corresponding to FIG. 4, FIG.

8 shows a further construction form of a projectile in a driving cup in a longitudinal section corresponding to FIG. 4, FIG.

9 shows a further modification of a projectile with an associated driving cup in a longitudinal section,

10 is a section along the line X - X of FIG. 9,

11 shows a further embodiment of a projectile with an associated driving cup in a longitudinal section,

12 is a section along the line XII - XiI of Fig. 11,

13 is a projectile with a tail in a partially torn side view,

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 and

16 is a section along the line XVI - XVI of FIG. 15.

Way to carry out the invention

According to the embodiment of FIGS. 1 to 4, 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. 6 having a tail unit 7 in the form of radially projecting guide vanes 8, and forms in the gusset region between the guide vanes 8 extending, against the bottom 2 of the cartridge case 1 open pockets 9, on the one hand by a jacket 10 of the propellant bowl 4 and on the other hand by inner walls 11th limited to abut the projectile 5 and separate the projectile from a propellant charge, which is provided in the cartridge case 1 between the bottom 2 and the driving cup 4 and the pockets 9 fills. However, this propellant charge is not shown in the drawing for reasons of clarity. So that the drive cup 4 can penetrate better into the propellant charge when it is pressed into the cartridge case 1, the inner walls 11 bounding the pockets 9 run out in a cutting edge 12.

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. Through these longitudinal ribs 14, a good guidance of the propellant gases driven out of a barrel, for example, a shotgun 4 is ensured despite the forward tapered lateral surface 13, which facilitates the passage of the propellant can 4 and the projectile 5 by a possibly narrowed mouth opening of the barrel , Since after the expulsion of the propellant can 4 from the barrel, the propellant 4 is to separate from the flying projectile 5, 4 distributed over the circumference separating points 15 are provided in the form of axial slots in the shell 10 of the propellant cup, so that the jacket 10 after exiting due to the air resistance, the barrel is spread umbrella-like and braked. These 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 Haiterung 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. In this context, it should be noted that 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.

So that the propellant gas pressure can be transmitted to the projectile 5 with an advantageous damping via the propellant cup 4, 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.

The embodiment of 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 Aufnahmevolumenε 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. According to FIGS. 1 to 4 wear for this purpose, the inner walls 11 in the axial direction In the embodiment shown, these guide ribs 23 also serve as sealing sections 17. The projectile 5 according to FIG. 5 is likewise equipped with a tail unit 7 forming a guide wing 8. However, 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. To ignite the tracer unit 25, 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. Thus, 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. In addition, in the bottom-side cavity of the projectile projecting an approach 31 of the propellant can 4 with an overflow 27, which opens into the cavity 30 of the projectile 5. Since the overflow is closed again with a membrane 26, the diaphragm 26 is broken by a pressurization of the propellant cup 4 by the propellant gases, so that in the cavity 30 during the expulsion of the projectile 5 from a run a corresponding gas pressure can build up after Outlet of the propellant can 4 from the barrel, the detachment of the propellant can 4 from the flying projectile 5 supports. - -

According to FIG. 8, 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. Since due to the cylindrical shell of the projectile 5 between the shell 10 of the propellant can 4 and the projectile 5 in the circumferential direction is only a frictional engagement, which is not sufficient for a swirl transmission from the propellant cup 4 to the projectile 5, the projectile 5 with a circumferentially be provided extending axial ribbing.

The embodiment of 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. However, 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 matching Treibbecher 4. In order to increase the weight of the existing only from the folded tubular body projectile 5, 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. In the FIG 14, 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. However, particularly simple construction conditions result if such 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. To connect the head 18 with the tail unit 7, only the head 18 in the Zwickeibereich between the guide vanes 8 need to be folded by clamping, with a projectile from the projectile head 18 to the tail 7 continuous shape of the guide vanes 8 results. This two-part design of the projectile 5 allows the use of different bullet heads 18 at each matching tail 7th

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.

So that 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.

Claims

Patent claim:

1. Cartridge with a cartridge case and with a cartridge inserted into the cartridge case, a Unterkalibriges bullet form-fitting, made of plastic Treibbecher which separates the projectile from the propellant charge in the cartridge case and along its shell axial separation points, characterized in that the Treibbecher ( 4) at least one pocket (9) extending into a cavity between the projectile (5) and the cartridge case (1) and / or into a cavity of the projectile (5), open against the bottom (2) of the cartridge case (1) Receiving a portion of the propellant charge.

2. Cartridge according to claim 1, characterized in that the pockets (9) of the driving cup (4) between axial guide vanes (8) of the projectile (5) erstrek- ken.

3. Cartridge according to claim 1 or 2, characterized in that the driving cup (4) in a central recess (32) in the projectile bottom erstrek- kende pocket (9) forms.

4. Cartridge according to claim 1 or 3, characterized in that the driving cup (4) has a conically tapering to its bottom projectile (5) enclosing annular chamber as a receiving pocket (9) for a portion of the propellant charge.

5. Cartridge according to one of claims 1 to 4, characterized in that the driving cup (4) has a forwardly tapering lateral surface (13) distributed over the circumference of longitudinal ribs (14), the envelope surface of a Hüllzylin- the drive cup (4 ) corresponds.

6. Cartridge according to one of claims 1 to 5, characterized in that the projectile (5) at its head (18) forms a re-entrant, by the driving cup (4) overlapped annular shoulder (19).

7. Cartridge according to one of claims 1 to 6, characterized in that the propellant cup (4) has at least one overflow channel (27) to the projectile (5) closing, by the propellant gas breakthrough membrane (26).

8. Cartridge according to claim 7, characterized in that the projectile (5) forms a to the overflow channel (27) adjoining cavity (30).

9. Cartridge according to one of claims 1 to 8, characterized in that the projectile (5) consists of a head (18) and in the hollow head (18) used tail unit (7) whose guide vanes (8) up in extend the head region, and that the head (18) is folded into the gusset area between the guide vanes (8) in a clamping manner.

10. Cartridge according to one of claims 1 to 8, characterized in that the projectile (5) forms a against the driving cup (4) open hollow body, which is folded into guide vanes (8).

11. Cartridge according to one of claims 1 to 8, characterized in that the projectile (5) has a star-shaped cross-section.

12. Cartridge according to claim 11, characterized in that the projectile (5) consists of a tubular body which is folded radially to form axial wings (33).

13. Cartridge according to one of claims 1 to 12, characterized in that the driving cup (4) has at least one circumferential sealing ring (16).

14. Cartridge according to one of claims 1 to 13, characterized in that the pockets (9) of the driving cup (4) delimiting inner walls (11) leak against the propellant charge in a cutting edge (12).

15. Cartridge according to one of claims 1 to 14, characterized in that the pockets (9) of the driving cup (4) delimiting inner walls (11) in the axial direction over the jacket (10) of the driving cup (4) against the bottom (2 ) of the cartridge case (1) and in the extension of the jacket (10) carry axial guide ribs (23).

16. Cartridge according to one of claims 1 to 15, characterized in that the projectile (5) in the axial direction via damping elements (21) preferably at the bottom of the driving cup (4) is supported.

17. Cartridge according to claim 16, characterized in that the damping elements (21) provided at the bottom of the driving cup (4), against the projectile (5) projecting damping ribs (22).

18. Cartridge according to one of claims 1 to 17, characterized in that the pockets (9) of the driving cup (4) are partially filled with a damping mass.