Guide concept for a penetrator

Abstract

The invention relates to a penetrator (10) for a projectile (100), comprising a terminal ballistic main body (12) extending along a longitudinal axis (L) and a tail assembly (18), wherein the main body (12) has a front (14) at the front in the firing direction (S) and a rear (16) in the firing direction (S), wherein several grooves (22) are formed on the main body (12), each of which has an open end (26) at the rear in the firing direction (S) and whose groove profile extends along a groove longitudinal direction (NL) oriented parallel to the longitudinal axis (L), wherein the tail assembly (18) has several wings (20) which each have a counter-profile corresponding to, preferably complementary to, the groove profile on a wing edge (24) facing the main body (12), wherein the wings (20) each merge with the wing edge (24) facing the main body (12) into a the grooves (22) are inserted and fastened therein. One projectile (100) with such a penetrator (10) and one cartridged ammunition are specified.

Description

[0001] The invention relates to a penetrator with features of the preamble of claim 1. The invention further relates to a projectile and a cartridged ammunition with features of the dependent claims.

[0002] A penetrator is a part of a projectile that achieves its effect, namely at least the penetration of a target's armor and in particular the associated damage or destruction of the target, solely through kinetic energy (kinetic energy projectile).

[0003] Modern penetrators for main battle tanks are usually sub-caliber discarding sabots fired from smoothbore cannons using a sabot and aerodynamically stabilized by means of a fin. Such ammunition is generally referred to as APFSDS (Armor Piercing Fin Stabilized Discarding Sabot).

[0004] A penetrator of the type mentioned above is known, for example, from DE 40 28 409 A1, which shows, among other things, the connection of the tail assembly to the penetrator. This tail assembly, as is common in the prior art, is constructed as a single unit; that is, the interface to the main body of the penetrator (tail assembly sleeve) and the individual wings are combined into one component. This component usually has to be manufactured by machining, which entails a corresponding amount of effort. Furthermore, this limits the choice of materials in terms of cost and available manufacturing processes (e.g., fiber-reinforced composites can only be used with extremely high effort).

[0005] The interface to the penetrator is often designed as a tail fin sleeve in the form of a hollow cylinder with an internal thread. It is attached to the rear of the penetrator and screwed in place using an external thread. A lightweight metal (e.g., high-strength aluminum) would be well-suited for this tail fin body, as it would possess relatively low mass and sufficient mechanical strength. However, a tail fin made of lightweight metal is not thermally stable enough for use on a penetrator. The outer fins would quickly heat up to above the melting point of the lightweight metal due to aerodynamic and thermal loads and erode during flight. After a short flight distance, the projectile's flight stability would be compromised.

[0006] The steel tail assembly, frequently used for these reasons, is thermally stable enough, but quite heavy (high mass). Furthermore, the steel tail assembly is aerodynamically disadvantageous due to the circumferential step (a tail sleeve protruding radially from the penetrator), which is difficult to eliminate during manufacturing. This limits both the external and terminal ballistic performance of the penetrator.

[0007] The invention is based on the objective of improving the external and terminal ballistic performance of a penetrator. It is desirable to enable the use of low-mass fin materials.

[0008] The invention solves this problem by means of a penetrator having the features of claim 1.

[0009] The penetrator is designed and / or intended for one floor.

[0010] The penetrator has a terminal ballistic main body extending along a longitudinal axis and a tail assembly. The main body has a front (penetrator front or penetrator tip) at the front in the direction of fire and a rear (penetrator tail) at the rear in the direction of fire.

[0011] Several grooves are formed on the main body, each with an open end at the rear in the direction of the shot, and each groove profile extends along a groove longitudinal direction that is oriented parallel to the longitudinal axis.

[0012] The tail assembly has several wings or stabilizing surfaces, each of which has a corresponding, preferably complementary, profile on a wing edge facing the main body (inner wing edge). The wings are each inserted into one of the grooves and secured therein with their wing edge facing the main body (inner wing edge).

[0013] In the proposed penetrator, the tail fins are attached directly to the main body of the penetrator, thus eliminating the tail fin sleeve (tail finless design). This allows for a reduction in the tail fin mass and therefore also in the mass of the penetrator. As a result of the elimination of the tail fin sleeve (tail fin base), the aerodynamic drag caused by the step at the transition between the tail fin sleeve and the main body of the penetrator is also eliminated.

[0014] By attaching the wings directly to the main body, materials specifically designed for the thermal and mechanical loads of the wings can be used, rather than being compromised by the required compatibility with a tailplane sleeve. Since individual wings are inserted into the slots on the main body, there is greater freedom in shaping than with a one-piece design as in the prior art. The fact that the slots have an open end in the firing direction, or in other words, are open to the rear in the firing direction, contributes to simpler manufacturing, as the wings can be inserted into the slots via the open end, regardless of whether undercuts are provided in the slot profile and / or the mating profile.

[0015] As explained above, the main body has several grooves. In principle, it is conceivable that the main body has two to ten or two to eight grooves. For reasons of stability, a design with four, five, or six grooves is preferred.

[0016] In principle, it is conceivable that there are more slots than wings on the main body, allowing for the selection of which and how many slots are fitted with a wing. This enables individual customization of the penetrators. For example, not every slot, but only selected slots, could be fitted with a wing, e.g., every other slot. For reasons of aerodynamics and stability, it is advantageous if every slot is fitted with a wing, or—in other words—if the number of slots and the number of wings of the penetrator (inserted into the slots) correspond (e.g., six slots and six wings).

[0017] The grooves are preferably evenly distributed on the main body. If the section of the main body in which the grooves are formed has a circular cylindrical shape, the grooves can preferably be evenly distributed along the circumferential direction. Regardless, the grooves have a groove base and are open (radially) outwards.

[0018] As stated above, the groove profile of each groove extends along a longitudinal groove direction oriented parallel to the longitudinal axis. The longitudinal groove directions of the grooves are preferably also oriented parallel to each other. The grooves can extend side by side on the main body with the same length. Regardless of this, the grooves can be formed at the rear (penetrator rear) of the main body, particularly in a main body section that closes off the main body to the rear in the firing direction.

[0019] In a preferred embodiment, the grooves can each have a closed end at the front in the direction of travel. This facilitates the alignment of the wings relative to the main body, since the groove end at the front in the direction of travel defines a stop, for example, when the wings are inserted via the open end.

[0020] Advantageously, the wings can be attached by friction and / or form-fitting with respect to or along the longitudinal direction of the groove. This ensures a stable and reliable fixation of the wings along the longitudinal direction of the groove, so that the wings do not change their position relative to the main body along the longitudinal direction of the groove as much as possible during closure.

[0021] According to an advantageous embodiment, a mounting section can be formed at the rear of the main body, to which a corresponding fastening element can be attached. When attached to the mounting section, the fastening element closes the grooves and / or engages behind the wings in the firing direction. This allows the wings to be reliably secured in the grooves along the longitudinal direction of the groove by a positive-locking fastening (fastening element). This simplifies manufacturing, as the wings can be inserted into the grooves from the rear via their open ends and secured in the grooves by means of the fastening element (which is applied from the rear). Optionally, the fastening element can be designed to be reversibly detachable from the mounting section.

[0022] Specifically, an external thread can be formed at the rear of the main body (as a mounting section or part of a mounting section). A locking element, equipped with a corresponding internal thread (forming a fastening element), is attached to this thread. When attached to the external thread, this locking element closes the grooves at the rear in the firing direction and / or engages the wings at their rear end. This allows the wings to be reliably secured in the grooves along their longitudinal direction by means of a positive-locking connection. If the locking element bears against the wings and exerts a force on them, the fastening can also include a friction-locking component. The locking element can be designed as a cylindrical body with an internal thread, preferably centrally located, for example, as a nut.The internal thread corresponds to the external thread on the main body, meaning it can be screwed into the external thread. The external thread can be located on the outer surface of the main body or on a pin projecting axially from the rear of the main body, which has a tapered cross-section compared to the main body.

[0023] Alternatively, a threaded hole (bore with an internal thread) can be formed at the rear of the main body (as a mounting section or part of a mounting section). The internal thread of this hole extends partially into the main body (inner circumference of the hole) and partially into the wing edges facing the main body (the wings inserted into the respective grooves). A threaded bolt can be screwed into the threaded hole (as a fastening element). When screwed into the threaded hole, the threaded bolt secures the wings to the main body. The threaded bolt and the threaded hole, which engages the wings and the main body, ensure a uniform load distribution along the entire thread length. This contributes to a reliable fastening. The threaded bolt has an external thread that corresponds to the internal thread of the threaded hole. The threaded bolt can therefore be screwed into the threaded hole.

[0024] In a preferred embodiment, the threaded bolt can have a head that closes the grooves at the rear in the firing direction and / or engages the wings at the rear end in the firing direction. This also enables a reliable positive-locking fastening of the wings in the grooves along the longitudinal direction of the groove. If the head of the threaded bolt rests against the wings and exerts a force on them, the fastening can also have a frictional component. The threaded bolt with head can be designed as a screw.

[0025] An advantageous embodiment provides for a retaining ring, in particular a retaining ring, to be arranged between the head and the rear of the main body. This retaining ring surrounds the rear of the main body radially outwards (over an axial section), with one contact surface bearing against a corresponding mating surface of the main body. The retaining ring is a separate component located between the head of the threaded bolt and the rear of the main body. A positive fit can be established (in the radial direction) between the retaining ring and the rear end of the main body via the contact surface of the corresponding mating surface. This prevents the rear end of the main body from bending upwards, thereby significantly increasing the load-bearing capacity of this interface in the axial direction.The tendency of the end of the main body to bend upwards results from the weakening of the material due to the threaded hole and grooves introduced into the main body, which causes the tangential connection of these areas to be lost.

[0026] The contact surface of the retaining ring is, in particular, a radially inward-facing surface or inner surface. The corresponding mating surface on the main body is, in particular, a radially outward-facing surface or outer surface. The contact surface can have a conical shape, with the contact surface widening conically towards the front in the direction of the shot (cone). The corresponding mating surface can also have a conical shape, with the mating surface tapering conically towards the rear in the direction of the shot (counter-cone).

[0027] The retaining ring can have a stop surface, particularly adjacent to the contact surface and extending radially inwards from the contact surface, with which the retaining ring rests against an end face at the rear of the main body when installed. A shoulder, preferably circumferential, can be formed on the head of the threaded bolt, which engages the retaining ring from the radial outside, or in other words, on the outer surface of the ring.

[0028] Advantageously, the main body can have one or more plastic deformations at the rear, which reduce the cross-section of the grooves (into which the wings are inserted with their side facing the main body) and / or close the grooves in the firing direction. Thus, the wings can be secured in the grooves by crimping. This allows for the wings to be secured in the grooves either exclusively or additionally along the longitudinal direction of the groove. Crimping eliminates the need for other fasteners such as threaded bolts or nuts, potentially reducing the number of components.

[0029] The groove profile of each groove can be advantageously rectangular. In other words, the groove can have a rectangular profile or cross-section. A groove with a rectangular profile is relatively easy to manufacture. The grooves can extend straight (radially) outwards from the groove base. Furthermore, the cross-section of the base body is only weakened relatively slightly by the rectangular, e.g., slot-shaped, groove profile. With a rectangular groove profile, the corresponding profile of the wing edge facing the main body is also rectangular.

[0030] Advantageously, the wings can each be bonded to the material within one of the grooves. In this way, the wings (with their edges facing the main body inserted into the grooves) can be secured along the longitudinal direction of the groove as well as perpendicular to it, i.e., radially outwards. This is particularly advantageous for groove profiles that do not taper outwards or are free of undercuts, such as a rectangular groove profile. The bond can be achieved by gluing or by adhesive bonding (wings glued into the grooves). The bond or adhesive can extend along the longitudinal direction of the groove over a predominant portion or the entire length of the groove. Welding or brazing can also be used as a bond.

[0031] In a further preferred embodiment, the groove profile of the grooves can be tapered from the groove base outwards (radially). This allows the wings (with their wing edges facing the main body inserted into the grooves) to be secured orthogonally to the longitudinal direction of the groove, i.e., radially outwards (positive locking connection). The corresponding profile of the wing edge facing the main body is designed in such a way that it can be inserted into the groove along its longitudinal direction, but cannot be removed from the groove without damage. Specifically, the groove profile can be trapezoidal (trapezoidal groove). The corresponding profile of the wing edge facing the main body can be complementary to this, in particular as a counter-trapezoid.

[0032] An advantageous embodiment can also consist of the groove profile (starting from the groove base) having an inner groove profile section with a first cross-section and an adjoining outer groove profile section with a second cross-section, which is tapered compared to the first cross-section. In this way, the wings (with their wing edges facing the main body inserted into the grooves) can also be secured orthogonally to the longitudinal direction of the groove, i.e., radially outwards (positive locking connection by undercut). Specifically, the first and second cross-sections can differ in shape. The first cross-section can be circular, and the second cross-section can be rectangular (a keyhole groove).The opposing profile of the wing edges facing the main body is designed to be complementary (first complementary cross-section and second complementary cross-section).

[0033] The empennage wings can expediently have different wing geometries. In other words, one part of the wings can have a first wing geometry, and another part can have a second wing geometry that differs from the first, particularly in size and / or shape. This makes it possible to optimally adjust the empennage's aerodynamic characteristics, such as drag, pitching moment, and / or wing twist (without significantly increasing the mass of the empennage body and the empennage's overall size).

[0034] Specifically, the wings can be made of titanium, carbon fiber reinforced plastic (CFRP), or (technical) ceramics, in particular aluminum oxide (Al₂O₃), silicon nitride (Si₃N₄), zirconium oxide (ZrO₂), boron nitride (BN), or silicon carbide (SiC). By using these materials, which can withstand the thermal and mechanical loads exerted on the wings during firing, the mass of the tail assembly can be reduced. This allows for an increase in the external and terminal ballistic performance of the penetrator.

[0035] The aforementioned problem is also solved by a projectile with the features of the dependent claim. The projectile has a penetrator with one or more of the aspects described above, as well as a driving cage.

[0036] Regarding the advantages achievable with the projectile, reference is made to the relevant explanations concerning the penetrator. Further development of the projectile can be achieved using the measures described in connection with the penetrator and / or those discussed below.

[0037] The aforementioned problem is also solved by a cartridge-loaded ammunition with the features of the further subordinate claim. The cartridge-loaded ammunition comprises a projectile with the aspects described above and a propellant charge.

[0038] Regarding the advantages achievable with the cartridge-loaded ammunition, reference is made to the relevant explanations concerning the penetrator. Further modifications to the projectile can be made using the measures described in connection with the penetrator and / or the projectile itself, and / or those discussed below.

[0039] The invention is explained in more detail below with reference to the figures, where identical or functionally equivalent elements are provided with identical reference numerals. The figures show: Fig. 1 of an embodiment of a penetrator in a simplified schematic and partially cutaway view; Fig. 2 one possible design of the penetrator Fig. 1 in a partial perspective exploded view; Fig. 3. One possible design of the penetrator Fig. 1 in a partial sectional view; Fig. 4 a modification of the design possibilities of the penetrator from Fig. 3 in a partial sectional view; Fig. 5 a possible design of the main body of the penetrator made of Fig. 1 in a sectional view; Fig. 6 another possible design of the main body of the penetrator Fig. 1 in a sectional view; and Fig. 7 another possible design of the main body of the penetrator Fig. 1 in a sectional view.

[0040] Fig. Figure 1 shows a simplified schematic representation of a Penetrator 10 for use in engaging an armored target. Together with a Fig. Within the indicated firing cage 102, the penetrator forms a projectile 100, which is specifically designed as a sub-caliber kinetic energy projectile. The projectile 100, in turn, is together with in Fig. 1. Other elements not shown for clarity, in particular a propellant charge and a casing, are part of a cartridged ammunition.

[0041] The penetrator 10 achieves its target-attack effect solely through kinetic energy. For this purpose, the penetrator 10 has a cylindrical or pin-shaped main body 12 extending along a longitudinal axis L. In this example, the main body 12 is made of a heavy metal, in particular a tungsten heavy metal.

[0042] The main body 12 has a front 14 at the front in the firing direction S, which is tapered or conical (penetrator tip). At the other end, at the rear in the firing direction S, the main body 12 has a tail 16 (penetrator tail). The penetrator 10 also has a tail assembly 18 with wings 20, which in this example is located at the tail 16 of the main body 12. Optionally, the wings 20 of the tail assembly 18 can have different wing geometries, as explained above.

[0043] Fig. Figure 2 shows one possible design of the penetrator 10, which is used to further describe the penetrator 10.

[0044] Several grooves 22 are formed on the main body 12, the groove profile of which each extends along a groove longitudinal direction N. L The main body extends parallel to the longitudinal axis L. In this example, six grooves 22 are formed on the main body 12, specifically on a main body section 12' that closes off the main body 12 to the rear in the firing direction S. The six grooves 22 are evenly distributed around the circumference of the main body section 12'.

[0045] The tail assembly 18 has several wings 20, in this example six wings 20 (the number of slots 22 corresponds to the number of wings 20). Each wing 20 has a corresponding and complementary profile on a wing edge 24 facing the main body 12 (inner wing edge). The wings 20 are each inserted into one of the slots 22 with their wing edge 24 facing the main body 12 and secured therein (in Fig. Figure 2 shows an exploded view for illustrative purposes. The wings 20 are attached directly to the main body 12. A tailplane sleeve is not provided.

[0046] In the example, the opposing profile extends along the entire inner wing edge 24. In the example, the wings 20 are tapered towards the leading edge 25 and are pointed.

[0047] The grooves 22 each have an open end 26 at the rear in the direction of travel S. The wings 20 can be inserted into the grooves 22 via this open end with their inner wing edge 24. At the front in the direction of travel S, the grooves 22 have a closed end 28. This limits the insertion of the wings 20 into the grooves 22 (the closed end 28 acts as a stop).

[0048] In the example, the wings are 20 with respect to the groove longitudinal direction N. LThe device is attached by friction and form-fitting means. At the rear 16 of the main body 12, an external thread 30 is formed (as a fastening section), onto which a locking element 34, equipped with a corresponding internal thread 32 (forming a fastening element), is applied, which closes the grooves 22 at the rear in the firing direction S and / or engages the wings 20 at the rear end in the firing direction S. Fig. Figure 2 shows the exploded view for clarity).

[0049] The locking element 34 is designed in the example as a cylindrical body with a centrally formed internal thread, e.g., as a nut. The external thread 30 is formed on a pin 36 projecting axially from the rear of the main body 12, which has a tapered cross-section compared to the main body 12.

[0050] Fig. Figure 3 shows one possible design of the penetrator 10. Fig. 1 in a partial sectional view.

[0051] The present penetrator 10 largely corresponds to the one associated with Fig. 1 and Fig. 2 described embodiment, so that reference is made to the explanations therein to avoid repetition.

[0052] In contrast, the penetrator 10 in this case has a threaded bore 40 at the rear 16 of the main body 12 (as a fastening section), the internal thread 42 of which is partially embedded in the main body 12 (see internal thread section 42' in Fig. 3 below) and is partially formed in the wing edges 24 facing the main body 12 (see internal thread section 42'' in Fig. 3 above). A threaded bolt 44 with an external thread 45 is screwed into the threaded bore 40 (as a fastening element), which secures the wings 20 to the main body 12.

[0053] The threaded bolt 44 has a head 46 that closes the grooves 22 at the rear in the firing direction S and engages the wings 20 at the rear end in the firing direction S. The threaded bolt 44 is designed as a screw with a head. A tool engagement section 48, for example an internal hexagon, is formed in the head 46. In this case, the mating profile extends only along a portion of the inner wing edge 24, approximately halfway along the inner wing edge 24.

[0054] Fig. Figure 4 shows a modification of the possible design of the penetrator 10. Fig. 3.

[0055] Unlike the one in Fig. In the penetrator 10 described in Section 3, a retaining ring or hold-down ring 50 is provided as a further separate component, which is arranged between the head 45 and the tail 16 of the main body 12. The retaining ring 50 surrounds the main body 12 at the tail 16 over an axial section to the outside, with the retaining ring 50 bearing against a corresponding counter surface 54 of the main body 12 at a contact surface 52.

[0056] The contact surface 52 is a radially inward-facing surface, and the counter surface 54 is a radially outward-facing surface. The contact surface 52 has a conical shape, widening conically forward in the firing direction S (cone). The corresponding counter surface 54 also has a conical shape, tapering conically backward in the firing direction S (counter-cone).

[0057] The retaining ring 50 has a stop surface 56 extending radially inwards from the contact surface 52, with which the retaining ring 50, in the installed state, rests against an end face 58 at the rear 16 of the main body 12. A circumferential shoulder 60 is formed on the head 45 of the threaded bolt 44, which, in this example, surrounds the retaining ring radially outwards, or in other words, on the outer surface 62 of the ring.

[0058] Fig. Figure 5 shows one possible design of the main body 12 of the penetrator 10. Fig. 1 in a sectional view through the main body section 12', in which the grooves 22 are formed.

[0059] In this case, the groove profile of the grooves 22 is rectangular. The grooves 22 extend straight (radially) outwards from the groove base 23. The corresponding counter-profile of the wing edge 24 of the wings 20 facing the main body 12 is also rectangular. In this and other embodiments, the wings 20 can be bonded to one of the grooves 22, as described above, e.g., by gluing.

[0060] Fig. Figure 6 shows another possible design of the main body 12 of the penetrator 10. Fig. 1 in a sectional view through the main body section 12', in which the grooves 22 are formed.

[0061] In this case, the groove profile of the grooves 22 tapers outwards (radially) from the groove base 23. Specifically, the groove profile is trapezoidal. The corresponding counter-profile of the wing edge 24 facing the main body 12 is complementary to this, in this example as a counter-trapezoid.

[0062] Fig. Figure 7 shows another possible design of the main body 12 of the penetrator 10. Fig. 1 in a sectional view.

[0063] The groove profile (starting from the groove base 23) has an inner groove profile section 27' with a first cross-section and an adjoining outer groove profile section 27'' with a second cross-section, which is tapered compared to the first cross-section. The first and second cross-sections differ in their shape. The first cross-section is circular, and the second cross-section is slit-shaped (rectangular) ("keyhole groove"). The corresponding profile of the wing edges 24 facing the main body 12 is complementary to this (first complementary cross-section 29' and second complementary cross-section 29'').

[0064] At the penetrator 10 in the Fig. 2 and Fig. 3 the grooves 22 and the inner wing edges 24 are formed as described here. QUOTES INCLUDED IN THE DESCRIPTION

[0000] This list of documents cited by the applicant was automatically generated and is included solely for the reader's convenience. The list is not part of the German patent or utility model application. The DPMA accepts no liability for any errors or omissions. Cited patent literature

[0000] DE 40 28 409 A1

[0004]

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