Guidance assembly concept for a penetrator

Abstract

The invention relates to a penetrator (10) for a projectile (100), comprising a main part (12), which has a terminal ballistic effect and extends along a longitudinal axis (L), and a guidance assembly (18). The main part (12) has a front part (14) at the front in the firing direction (S) and a rear part (16) at the rear in the firing direction (S). A plurality of grooves (22) are formed on the main part (12), each of the grooves having a respective open end (26) at the rear in the firing direction (S) and a respective groove profile which extends along a groove longitudinal direction (NL) oriented parallel to the longitudinal axis (L). The guidance assembly (18) has a plurality of fins (20), each of which has, on the fin edge (24) facing the main part (12), a counter profile, preferably a complementary counter profile, which corresponds to the groove profile, and the fin edge (24) of each of the fins (20) which faces the main part (12) is introduced into one of the grooves (22) and is secured therein. The invention further relates to a projectile (100) having such a penetrator (10) and to cartridge ammunition.

Description

[0001] Applicant:

[0002] Rheinmetall Waffe Munition GmbH Heinrich-Ehrhardt-Straße 2 29345 Südheide

[0003] General Power of Attorney: 723130.1

[0004] 30800059WO 19.09.2025

[0005] ELL / VBU

[0006] Title: Tail assembly concept for a penetrator

[0007] Description

[0008] 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.

[0009] A penetrator is a component 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 penetrator). Modern penetrators for main battle tanks are usually sub-caliber fletched rounds fired from smoothbore cannons with the aid of a sabot and aerodynamically stabilized by means of a fin. Such ammunition is generally referred to as APFSDS (Armor Piercing Fin Stabilized Discarding Sabot).

[0010] 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, i.e., 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, which can be determined with regard to cost and available manufacturing processes (e.g., fiber-reinforced composites can only be used with extremely high effort).

[0011] 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 have a comparatively 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 the aerodynamic and thermal loads and would erode during flight. After a short flight distance, the projectile's flight stability would be compromised.

[0012] 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 (the radially protruding tail sleeve on the penetrator), which is difficult to eliminate during manufacturing. This limits both the external and terminal ballistic performance of the penetrator.

[0013] 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.

[0014] The invention solves this problem by means of a penetrator having the features of claim 1.

[0015] The penetrator is designed and / or intended for one projectile.

[0016] 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. Several grooves are formed on the main body, each with an open end at the rear in the direction of fire, and each groove profile extends along a longitudinal direction oriented parallel to the longitudinal axis.

[0017] 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 slots with their wing edge facing the main body (inner wing edge) and fastened therein.

[0018] In the proposed penetrator, the tail fins are directly attached 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 from the tail fin sleeve to the main body of the penetrator is also eliminated.

[0019] By attaching the wings directly to the main body, materials specifically designed for the thermal and mechanical loads of the wings can be used for the tail assembly, rather than being a compromise due to the required compatibility with a tail section. 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 direction of travel, or in other words, are open to the rear in the direction of travel, contributes to simpler manufacturing, as the wings can be inserted into the slots via the open end, regardless of whether undercuts are provided on the slot profile and / or the mating profile.

[0020] 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.

[0021] 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, can be fitted with a wing, e.g., every second 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).

[0022] 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. As indicated 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, the grooves can be formed at the rear (penetrator rear) of the main body, in particular in a main body section that closes off the main body to the rear in the firing direction.

[0023] In a preferred embodiment, the grooves can each have a closed end at the front in the direction of travel. This facilitates 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.

[0024] Advantageously, the wings can be securely fastened with respect to the longitudinal direction of the groove and / or along the longitudinal direction of the groove. This allows for a stable and reliable fixing 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 advancement.

[0025] According to an advantageous embodiment, a mounting section can be formed at the rear of the main body, to which a corresponding mounting element can be attached. When attached to the mounting section, the mounting element closes the grooves and / or engages the wings in the firing direction. This allows the wings to be secured along the longitudinal direction of the groove by a positive locking mechanism.

[0026] The fastening element is reliably secured in the grooves. This contributes to simple manufacturing, as the wings can be inserted into the grooves from the rear via their open ends and secured in the grooves using the fastening element (which is applied from the rear). Optionally, the fastening element can be designed so that it can be reversibly detached from the fastening section.

[0027] 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 or screwed onto this thread. In the position attached or screwed onto 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 in the firing direction. This allows the wings to be reliably secured in the grooves along the longitudinal direction of the groove by means of a positive-locking fastening. If the locking element bears against the wings and exerts a force on them, the fastening can also include a force-locking component. The locking element can be designed as a cylindrical body with an internal thread formed therein, preferably centrally, e.g., as a nut.The internal thread corresponds to the external thread on the main body and can therefore be screwed into the external thread. The external thread can be formed 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. Alternatively, a threaded bore (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 bore is formed partly in the main body (inner circumference of the bore) and partly in the wing edges facing the main body (of the wings inserted into the respective grooves). A threaded bolt can be screwed into the threaded bore (as a fastening element), and when screwed into the threaded bore, 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.

[0028] 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 force-locking component. The threaded bolt with a head can be designed as a screw.

[0029] An advantageous embodiment provides that a retaining ring, in particular a retaining ring, is 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 a 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.

[0030] The contact surface of the retaining ring is, in particular, a radially inward-facing surface or inner surface. The corresponding counter-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 at the front in the direction of firing (cone). The corresponding counter-surface can also have a conical shape, with the counter-surface tapering conically at the rear in the direction of firing (counter-cone).

[0031] The retaining ring can, especially following the

[0032] The contact surface and, extending radially inwards from the contact surface, a stop surface with which the retaining ring, in the installed state, rests against an end face at the rear of the main body. A shoulder, preferably circumferential, can be formed on the head of the threaded bolt, which surrounds the retaining ring from the radial outside, or in other words, on the outer surface of the ring.

[0033] Advantageously, the main body can have one or more plastic deformations at the rear that 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. This allows the wings to be secured in the grooves by crimping. This provides a sole or supplementary means of securing the wings in the grooves along their longitudinal direction. Crimping eliminates the need for additional fasteners such as threaded bolts or nuts, potentially reducing the number of components.

[0034] Advantageously, the groove profile of each groove can be 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. Advantageously, the wings can each be bonded tightly into 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 bonded connection can be achieved by gluing or an adhesive bond (wings glued into the grooves). The bonded connection or the adhesive bond can extend along the longitudinal direction of the groove over a predominant part or over its entire length. Welding or brazing can also be used to create a bonded connection.

[0035] 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 when moving orthogonally to the longitudinal direction. 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.

[0036] 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 slit-shaped (rectangular) ("keyhole groove").The opposite profile of the wing edges facing the main body is designed to be complementary to this (first complementary cross-section and second complementary cross-section).

[0037] The wings of the empennage 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 its overall size).

[0038] Specifically, the wings can each be made of titanium, carbon fiber reinforced plastic (CFRP), or (technical) ceramics, in particular aluminum oxide (A12O3), 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 acting on the wings during launch, the mass of the tail assembly can be reduced. This allows for an increase in the external and terminal ballistic performance of the penetrator.

[0039] 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.

[0040] Regarding the advantages achievable with the projectile, reference is made to the relevant explanations concerning the penetrator. The measures described in connection with the penetrator and / or those discussed below can be used for further development of the projectile.

[0041] 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. Regarding the advantages achievable with the cartridge-loaded ammunition, reference is made to the relevant explanations concerning the penetrator. The measures described in connection with the penetrator and / or the projectile, and / or those discussed below, can be used for further development of the projectile.

[0042] The invention is explained in more detail below with reference to the figures, where identical or functionally identical elements are provided with identical reference numerals. The figures show:

[0043] Fig. l of a embodiment of a penetrator in a simplified schematic and partially cutaway view;

[0044] Fig. 2 shows one possible embodiment of the penetrator from Figure 1 in a partial perspective exploded view;

[0045] Fig. 3 shows a possible embodiment of the penetrator from Figure 1 in a partial sectional view;

[0046] Fig. 4 shows a modification of the possible design of the penetrator from Figure 3 in a partial sectional view;

[0047] Fig. 5 shows a possible embodiment of the main body of the penetrator from Figure 1 in a sectional view;

[0048] Fig. 6 shows another possible embodiment of the main body of the penetrator from Figure 1 in a sectional view; and Fig. 7 shows another possible embodiment of the main body of the penetrator from Figure 1 in a sectional view.

[0049] Figure 1 shows a simplified schematic representation of a penetrator 10 for use in engaging an armored target. Together with a sabot 102 indicated in Figure 1, the penetrator forms a projectile 100, which is specifically designed as a sub-caliber kinetic energy projectile. The projectile 100, in turn, together with other elements not shown in Figure 1 for clarity, in particular a propellant charge and a cartridge case, is part of a cartridge munition.

[0050] The penetrator 10 achieves its target-attack effect solely through kinetic energy. For this purpose, the penetrator 10 has a cylindrical or rod-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 wolfram heavy metal.

[0051] The main body 12 has a front 14 at the front in the direction of firing S, which is tapered or conical in shape (penetrator tip). At the other end, at the rear in the direction of firing S, the main body 12 has a tail 16.

[0052] (Penetrator tail). The penetrator 10 also has a tail assembly 18 with wings 20, which in this example is arranged 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. Figure 2 shows one possible configuration of the penetrator.

[0053] 10 , which further describes the penetrator 10 .

[0054] 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 the 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 towards the rear in the firing direction S. The six grooves 22 are evenly distributed around the circumference of the main body section 12'.

[0055] 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 (inner wing edge) facing the main body 12. 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 (Figure 2 shows an exploded view for illustrative purposes). The wings 20 are attached directly to the main body 12. A tail assembly sleeve is not provided.

[0056] In this example, the opposing profile extends along the entire inner wing edge 24. The wings 20 in this example are tapered towards the leading edge 25 and are pointed.

[0057] 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).

[0058] In the example, the wings are 20 with respect to the groove longitudinal direction N. L The main body 12 is securely and positively fastened. 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 (forming a fastening element) equipped with a corresponding internal thread 32 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 (Figure 2 shows the exploded view for clarity).

[0059] 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.

[0060] Figure 3 shows one possible design of the penetrator 10 from Figure 1 in a partial sectional view.

[0061] The present penetrator 10 largely corresponds to the embodiment described in connection with Figures 1 and 2, so that reference is made to the descriptions there to avoid repetition. In contrast, the present penetrator 10 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 formed partly in the main body 12 (see internal thread section 42' in Figure 3 below) and partly in the wing edges 24 facing the main body 12 (see internal thread section 42'' in Figure 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.

[0062] The threaded bolt 44 has a head 46 that closes the grooves 22 in the firing direction S at the rear 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 is formed in the head 46, for example, an internal hexagon socket. 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.

[0063] Figure 4 shows a modification of the possible design of the penetrator 10 from Figure 3.

[0064] In contrast to the penetrator 10 described in Figure 3, a retaining ring or hold-down ring 50 is provided here as a further separate component, which is arranged between the head 46 and the rear 16 of the main body 12. The retaining ring 50 surrounds the main body 12 at the rear 16 over an axial section to the outside, wherein the retaining ring 50 is connected to a corresponding contact surface 52.

[0065] The counter surface 54 of the main body 12 is in contact with the contact surface 52. 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).

[0066] 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, abuts an end face 58 at the rear 16 of the main body 12. A circumferential shoulder 60 is formed on the head 46 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.

[0067] Figure 5 shows one possible embodiment of the main body 12 of the penetrator 10 from Figure 1 in a sectional view through the main body section 12 ' in which the grooves 22 are formed.

[0068] In this case, the groove profile of the grooves 22j is rectangular. The grooves 22 extend straight (radially) outwards from the groove base 23j. 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 20j can each be butt-fitted in one of the grooves 22, as described above, e.g., by gluing. Figure 6 shows another possible embodiment of the main body 12 of the penetrator 10 from Figure 1 in a sectional view through the main body section 12' in which the grooves 22 are formed.

[0069] In this case, the groove profile of the grooves 22 tapers radially outwards 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.

[0070] Figure 7 shows another possible design of the main body 12 of the penetrator 10 from Figure 1 in a sectional view.

[0071] In this case, 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''). In the penetrator 10 shown in Figures 2 and 3, the grooves 22 and the inner wing edges 24 are configured as described here.

Claims

Patent claims 1. 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), characterized in that 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 (N). L ) extends, which is oriented parallel to the longitudinal axis (L), wherein the tail assembly (18) has several wings (20) which each have a corresponding, preferably complementary, counter-profile corresponding to the groove profile on a wing edge (24) facing the main body (12), wherein the wings (20) are each inserted into and fastened in one of the grooves (22) with the wing edge (24) facing the main body (12).

2. Penetrator (10) according to claim 1, characterized in that the grooves (22) in the firing direction (S) each have a closed end (28) at the front.

3. Penetrator (10) according to claim 1 or 2, characterized in that the wings (20) are arranged with respect to the longitudinal direction of the groove (N) L ) are each securely fastened and / or form-fitting.

4. Penetrator (10) according to one of the preceding claims, characterized in that at the rear (16) of the The main body (12) has a fastening section (30, 40) on which a corresponding fastening section (30, 40) is attached. Fastening element (34, 44) can be attached, wherein the fastening element (34, 44) in the state attached to the fastening section (30, 40) closes the grooves (22) at the rear in the direction of firing (S) and / or engages behind the wings (20).

5. Penetrator (10) according to one of the preceding claims, characterized in that an external thread (30) is formed at the rear (16) of the main body (12), onto which a locking element (34) equipped with an internal thread (32) can be applied, wherein the locking element (34) in the applied state closes the grooves (22) and / or engages behind the wings (20) in the firing direction (S).

6. Penetrator (10) according to one of claims 1 to 4, characterized in that a threaded bore (40) is formed at the rear (16) of the main body (12), the internal thread (42) of which is formed partly in the main body (12) and partly in the wing edges (24) facing the main body (12), wherein a threaded bolt (44) can be screwed into the threaded bore (40), wherein the threaded bolt (44) secures the wings (20) to the main body (12) when screwed in.

7. Penetrator (10) according to the preceding claim, characterized in that the threaded bolt (44) has a head (46) which extends in the firing direction (S) at the rear the grooves (22) are closed and / or the wings (20) are engaged behind.

8. Penetrator (10) according to the preceding claim, characterized in that a retaining ring (50) is arranged between the head (46) and the rear (16) of the main body (12), which surrounds the main body (12) at the rear (16), wherein the retaining ring (50) bears against a corresponding counter surface (54) of the main body (12) with a contact surface (52).

9. Penetrator (10) according to one of the preceding claims, characterized in that the main body (12) has one or more plastic deformations at the rear (16) which reduce the cross-section of the grooves (22) and / or close the grooves (22) in the firing direction (S).

10. Penetrator (10) according to one of the preceding claims, characterized in that the groove profile of the grooves (22) is rectangular in each case.

11. Penetrator (10) according to one of the preceding claims, characterized in that the wings (20) are each materially bonded in one of the grooves (22).

12. Penetrator (10) according to one of claims 1 to 9 or 11, characterized in that the groove profile of the grooves (22) is tapered outwards from the groove base (23).

13. Penetrator (10) according to one of the preceding claims, characterized in that the groove profile is trapezoidal.

14. Penetrator (10) according to one of claims 1 to 12, characterized in that the groove profile 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.

15. Penetrator (10) according to one of the preceding claims, characterized in that the wings (20) of the tail assembly (18) have different wing geometries.

16. Penetrator (10) according to one of the preceding claims, characterized in that the wings (20) are each made of titanium, carbon fiber reinforced plastic or ceramic.

17. Projectile (100) with a penetrator (10) according to one of the preceding claims and a driving cage (102) .

18. Cartridge ammunition comprising a projectile (100) according to the preceding claim and a propellant charge.

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