EP0137106B1 - Jacket for sabot projectile - Google Patents

Description

The invention relates to positive locking means according to the preamble of claim 1 and a method for arranging the positive locking means.

Form-locking means are known which, in a predeterminable circumferential area of a sub-caliber missile core for connecting a throwable sabot, consist of form-locking means in the form of a thread arranged on the missile core or of grooves, which can disadvantageously result in undesirable notch effects in the missile core and impairment of the penetration performance cannot be ruled out. In order to avoid these notch effects, which are disadvantageous in the fight against armored targets, according to FR-A-2523715 (published on 23-09-83) a further form-locking means has been proposed on a balancing projectile consisting of a heavy metal core, in which the thread required for transmission in the outer area of a mantle connected to the missile is arranged. However, this jacket, which is metallurgically connected to the missile core, consists of light metal, preferably of an aluminum alloy.

In contrast, the invention has for its object to design the positive locking means in a missile core according to the preamble of claim 1, in order to achieve a high performance level, in such a way that undesirable notch effects on the missile core are avoided and the cross-sectional load capacity of the positive locking means is significantly increased.

This object is achieved by the invention specified in claim 1.

According to the invention, the positive locking means have the decisive advantage that, in addition to a high firing durability, a high penetration rate of the missile core is achieved. The high firing durability is achieved on the one hand by a comparatively high strength of the support sheath, which can be dimensioned relatively small in height, and on the other hand the profiles formed by the overlapping individual cross-sectional areas are highly resilient for positive engagement with the sabot without noteworthy notch effects. The high penetration performance of the missile core is achieved in particular when lateral forces occur in armored targets in that the positive locking means do not cause any notches on the missile core.

Advantageous refinements and developments emerge from the subclaims.

According to a special feature of the invention, the carrier jacket consists of a band wrapped around the missile core, which means that a thin-walled carrier jacket with a large UD (length / diameter) ratio can be connected to the missile core in a simple manner, in particular by thermoforming and a subsequent shrinking process. This arrangement allows a continuous and individual shrinking process, the winding of a tape wound, thereby avoiding in particular throwing of the carrier jacket, which is characteristic of long, thin-walled and tight-tolerance bushings during the shrinking process, and producing a carrier jacket with a uniformly high shear strength. The fact that the form-fitting profiles of the carrier jacket for the sabot on the one hand do not require any after-treatment or on the other hand are hot-formed without cutting results in a high-strength jacket structure which is not weakened by separation of the material fibers in the launch durability due to the notch effect.

A comparatively advantageous long and slender support jacket can also be produced from individual partially overlapping rings by hot forming, but preferably in the cold state by extrusion with simultaneous connection to the missile core. The extrusion simultaneously produces a carrier jacket with increased strength properties and the processing effort for producing the carrier jacket is kept low.

The invention is explained below with reference to the preferred exemplary embodiments of the details shown in the drawings, largely without details that are not essential to the invention.

• Figur 1 in einem schematisch dargestellten Halbschnitt einen Teilbereich des Fluggeschosses in Längsrichtung mit einem auf dem Umfang angeordneten Trägermantel für einen abwerfbaren Treibkäfig ;
• Figur 2 in einer vergrößerten Schnittdarstellung von Fig. 1 einen Teilbereich des Trägermantels mit überlappten Einzelquerschnitten ohne vorgefertigte Außenprofilierung ;
• Figur 3 in einer vergrößerten Schnittdarstellung von Fig. 1 einen Teilbereich des Trägermantels mit überlappten Einzelquerschnitten, die weitere v-förmige Außenprofile enthalten ;
• Figur 4 in einer vergrößerten Schnittdarstellung von Fig. 1 einen Teilbereich des Trägermantels mit überlappten Einzelquerschnitten, die gerundete Außenprofile enthalten ;
• Figur 5 in einer schematischen Darstellung ein in einem Teilbereich des Fluggeschoßkernes als Trägermantel aufgewickeltes Band und einer Einrichtung zum Befestigen des Bandes ;
• Figur 6 in einer Schnittdarstellung einer in Fig. 2 dargestellten Einzelquerschnitt ;
• Figur 7 in einer Schnittdarstellung einen in Fig. 3 dargestellten Einzelquerschnitt mit vorgefertigtem Außenprofil ;
• Figur 8 in einer Schnittdarstellung einen in den Fig. 3 order 4 dargestellten Einzelquerschnitt ohne vorgefertigtes Außenprofil;
• Figur 9 in einer Schnittdarstellung einen Ring, dessen Querschnitt einem in den Fig. 3 order 4 dargestellten Einzelquerschnitt ohne zusätzliches Außenprofil entspricht.

It shows:

• Figure 1 in a schematically illustrated half section of a portion of the missile in the longitudinal direction with a circumferential support jacket for a droppable sabot;
• Figure 2 is an enlarged sectional view of Figure 1, a portion of the support jacket with overlapped individual cross-sections without prefabricated outer profile.
• Figure 3 is an enlarged sectional view of Figure 1, a portion of the support jacket with overlapped individual cross-sections that contain other V-shaped outer profiles.
• Figure 4 is an enlarged sectional view of Figure 1, a portion of the support shell with overlapped individual cross-sections that contain rounded outer profiles.
• Figure 5 is a schematic representation of a tape wound in a portion of the missile core as a carrier jacket and a device for fastening the tape;
• FIG. 6 shows a sectional illustration of an individual cross section shown in FIG. 2;
• Figure 7 is a sectional view of a single cross section shown in Figure 3 with a prefabricated outer profile.
• Figure 8 is a sectional view of a single cross section shown in Figures 3 or 4 without a prefabricated outer profile;
• Figure 9 is a sectional view of a ring, the cross section of which corresponds to an individual cross section shown in Figures 3 or 4 without an additional outer profile.

In Fig. 1, a partial area of a sub-caliber missile core 5 consisting of heavy metal is shown parallel to the projectile axis 28, on the circumference of which a support jacket 2 is arranged as an intermediate area for the positive locking of a droppable sabot 17. The cross-sectional area 3 of the carrier jacket 2 consists of individual overlapped cross-sectional areas 4 shown in FIGS. 2, 3 and 4, the inner sides 16 of which form a coherent inner surface 18 for a non-positive connection with the jacket surface 19.

The cross-sectional areas 4 shown in FIGS. 2, 3 and 4 illustrate either overlapped cross-sectional areas of a wound band 6 (FIG. 5) or of endless rings 7 placed on them (FIG. 9). In both cases, the cross-sectional area 4 according to FIGS. 6 to 9 has on the end faces 8 and 8 's-shaped profiles 9 for a positive connection of the bands 6 or rings 7. The profiles 9 are arranged on the end faces 8, 8 'in the overlapped area parallel to one another, whereby one position of the overlap of adjacent cross sections 4 results in such a way that the area of the overlapped area from an inner end face 8 of an adjacent cross-sectional area 4 Face 8 ', the inside 16 of the cross-sectional area 4 formed by the face 8' opposite. The inner end face 8 can be shortened to the outside 10 by an inclined surface 11 or fillet 12. This results in 13 or v-shaped 14 grooves 14, 15 on the outer end face 8 'or with the outer fillet 13 of adjacent cross-sectional areas 4, post-treatment-free, rounded 13 or v-shaped 14 grooves 14, 15 as positive locking means 1 for positive locking to the sabot 17 (FIG. 1). The acceleration forces introduced by the sabot 17 (FIG. 1) onto the carrier jacket 2 are transmitted in the direction 21 to the missile core 5 (FIG. 1). For the transfer of high acceleration forces, the is made of thermoformable.

Steel or cold-formable steel existing carrier jacket 2 either non-positively connected to the jacket surface 19 (FIG. 1) by hot forming of the strips 6 (FIG. 5) or by hot forming or cold forming of the rings 7 (FIG. 9).

The carrier jacket 2 composed of a band 6 is warmly joined according to FIG. 5 with the winding process with the carrier jacket 2 centered and the completion or production of new grooves 20 by rolling or rolling, whereby further methods such as forging or hammering are also possible . The tape 6 is wound obliquely around the rotating missile core 5 in the direction of rotation 22 in the direction 23, then heated to forging temperature by a heat source 24, for example by a ring burner or a magnetic coil etc., so that it is radially through to the projectile axis 28 in Direction 25 pressurized and rotating in the direction of rotation 26 roller 27 can be formed into a bushing of high radial strength. The subsequent, successive cooling of the individual turns of the strip formed into a bushing forms a notch-free shrink connection with the missile core 5, producing a high shot durability. Before the winding process, the cross-sectional area 4 of the band 6 according to FIG. 7 can be designed with a groove 20 prefabricated on the outside 10 or without an outer groove according to FIG. 8.

The endless rings 7 shown in FIG. 9 can likewise be formed by their cross-sectional areas 4 pre-shaped on the end faces 8, 8 'with S-shaped profiles 9 to form a support jacket 2 (which can be varied in length and parallel to the projectile axis 28 (FIG. 1)). Fig. 1). For example, forging or rolling processes or, in the case of completely prefabricated form-locking means (FIGS. 2, 3 and 4), extrusion may be considered as the joining process. During cold forming, the surface of the profiles 9 of the carrier jacket 2 (FIG. 1) is solidified in such a way that a high-strength connection is created between it and the missile core 5 (FIG. 1) due to internal stresses. The binding of the carrier jacket 2 (Fig. 1) to the missile core 5 (Fig. 1) can, but also in all other manufacturing processes, be reinforced by an acceptable surface roughness or by fine toothing or wave formation between the carrier jacket 2 and missile core 5 without breaking points .

The missile core 5 can either be equipped with an outer ballistic hood, not shown, to avoid external ballistic influences of the carrier shell 2, or it can be provided in the front area of the missile core 5, which is also not shown, with a front part enlarged notch-free to the diameter of the outside 10 of the thin-walled carrier shell 2.

Claims (10)

1. Interlocking engagement means of metal for a sabot and positioned in a predetermined peripheral zone of a sub-calibre projectile core preferably comprising a heavy metal, characterized by the fact that the engagement means (1) comprises a jacket (2) of comparatively high strength of which the cross section area (3) is made up of overlapping individual cross-sectional areas (4) forming a profile extending in an axial direction.

2. Interlocking engagement means in accordance with Claim 1, characterized by the fact that the jacket (2) comprises a strip (6) having a cross sectional area (4) wound around the projectile core (5) and overlapping.

3. Interlocking engagement means in accordance with Claims 1 and 2, characterized by the fact that the jacket (2) is made up of endless rings (7) overlapping with the cross section surface (4).

4. Interlocking engagement means in accordance with any one of Claims 1 to 3, characterized by the fact that the material of the jacket (2) comprises a hot-workable or malleable steel.

5. Interlocking engagement means in accordance with any one of Claims 1 to 3, characterized by the fact that both ends (8, 8') of the cross section area (4) are formed with S-shaped profiles (9) in such a way that wound bands (6) are interconnected via endless rings (7) with interlocking engagement.

6. Interlocking engagement means in accordance with any one of Claims 1 to 5, characterized by the fact that end (8) of the cross section area (4) of a strip (6) or ring (7) which faces towards the inside (16) is provided with an oblique surface (11) or rounded portion (12) terminating on the outside (10) whereby grooves (14, 15) either rounded, (14) or V-shaped (15), for interlocking with the sabot (17) are formed when the system is assembled and without re-treatment.

7. Interlocking engagement means in accordance with any one of Claims 1 to 6, characterized by the fact that the insides (16) of the cross section areas (4) form a cohesive internal surface (18) of the jacket (2), the internal surface (18) being connected with positive engagement and by the hot working or cold working of the strips (6) or rings (7) to the jacket surface (19) of the projectile core (5).

8. Interlocking engagement means in accordance with any one of Claims 1 to 7, characterized by the fact that the outside (10) of the cross section area (4) contains at least one further groove (20) which has been preformed or which is hot-worked.

9. Method for the arrangement of the interlocking engagement means described in Claim 1, characterized by the fact that the strips of the jacket according to Claim 2 are combined in a hot state in parallel or simultaneously with the winding process, accompanied by the centering of the jacket and the preparation or production of new grooves in accordance with Claim 8 by laminating or by rolling, forging, hammering etc. the jacket forming a shrunk-fitted assembly with the projectile core on cooling down.

10. Method for the arrangement of the interlocking engagement means described in Claim 1, characterised by the fact that the jacket made up of rings according to Claim 3 is subject to cold- working by flow-pressing and strengthening under contact pressure from profile surfaces according to Claim 5, such that the jacket is firmly connected by internal stressing to the core of the shell.

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