Penetrator projectiles

Abstract

A nose unit for a discarding sabot penetrator having a bolt in a bore of the pointed nose which is temporarily displaced on firing due to acceleration and against a restoring spring. This produces a circular edge and a break in the contour of the nose to define a limit surface between a zone of supersonic airflow and a zone of subsonic airflow, at least during the separation of the sabot segments. This facilitates the uniformed detachment of the segments.

Description

BACKGROUND OF THE INVENTION

This invention relates to a pointed nose unit for a penetrator projectile.

In penetrator projectiles with discarding sabots, such as are described in U.S. Pat. No. 3,899,978, the sabot is provided with an air dam which surrounds it in the vicinity of the front of the penetrator and serves to initiate detachment of the sabot segments though incident air flow after it has left the barrel of a weapon. The detachment of the sabot segments from the penetrator body during firing has been found to frequently take place unevenly. This can impart oscillations to the projectile. The oscillations may reduce not only the aiming accuracy but also the penetrative power which is particularly relevant when used against modern targets which require penetrators of considerable length which must be substantially free of any tendency to oscillate.

Experiments carried out on the behavior of penetrators and sabot systems have shown that in the zone around the front part of the projectile unstable air flow conditions may occur which prevent the sabot from seaprating evenly.

An object of this invention is to provide a pointed nose unit for a penetrator projectile.

According to the present invention a penetrator projectile is provided with a pointed nose having a high ratio of length to diameter and constructed to be at least transitionally variable in shape to improve the separation of discardable sabot segments after emerging from the barrel of a weapon.

BRIEF DESCRIPTION OF THE DRAWINGS

The invention is further described in more detail with reference to the two preferred embodiments shown in the accompanying drawings. In the drawings the nose end of a penetrator is shown in longitudinal section, and

FIG. 1 is a first embodiment in the initial position,

FIG. 2 shows the embodiment of FIG. 1 in a position after the firing acceleration phase,

FIG. 3 is a second embodiment in the initial position, and

FIG. 4 shows the embodiment of FIG. 3 in an intermediate position during flight.

DETAILED DESCRIPTION OF THE DRAWINGS

Referring to the drawings, FIG. 1 shows a penetrator projectile 10 with a peripheral surface 12 and a front stud 14 extending beyond an annular shoulder 16. The stud 14 serves to secure a pointed nose body 18 which has a rear cylindrical portion with an outer peripheral surface 20, an inner peripheral surface 22 and a rear circular annular face 24 which bears against the annular shoulder 16. The outer peripheral surface 20 extends as far as an edge 26 which forms a juncture with a conical surface 28 extending to a front edge 30. The part of the pointed nose body 18 which is associated with the conical surface 28 has coaxial bores 32, 34, and 36 of different diameters. An annular shoulder 38 delimits the front end of coaxial bore 32 which has a greater diameter then coaxial bore 36. A bolt 40 has a piston 42 fitted to the bore 32 and a front part 44 with a conical point 46 fitted to the bore 36. This assembly is mounted in the pointed body 18 in such a way as to be axially movable. A stub 48 extending toward the rear beyond the piston 42 is embraced by a coil compression spring 50. A rear abutment 52 for the spring is secured by a screw threading 54 in the bore 34 and has a blind hole 56 for the free end of stub 48.

FIG. 1 shows the pointed body in the initial position. When the penetrator 10 is fired and accelerated in the direction 100, as shown in FIG. 2, bolt 40, owing to its mass, assumes the position shown in FIG. 2. The conical point 46 retracts into the bore 36. When the projectile 10 emerges from the barrel of a weapon a limit zone between a zone with a supersonic flow and a zone with a subsonic flow is formed at the edge 30. This facilitates the even separation of sabot segments (not shown). For this purpose a c.sub.w coefficient (drag coefficient) greater than that occurring in the initial position is temporarily accepted. After the firing acceleration has reduced, bolt 40 moves forward and the point 46 is restored to the forward projecting position by the force of spring 50. The c.sub.w coefficient (drag coefficient) is thereby reduced to the value associated with the initial position. (For a definition of c.sub.w see Rheinmetall Handbook of Weaponry, pp. 144-147, Broenners Druckerei Breidenstein GmbH, frankfurt a.M., Second English Edition 1982.)

In FIG. 3 a penetrator 60 has a cylindrical body 62 with an axial bore 64 which, at an annular face 67, reduces to a blind hole 65 of smaller diameter. At the front of penetrator 60, a shoulder 66 is provided with a screw threading. The screw threading secures a bushing 68 with an outer annular end face 70, a corresponding inner face 71, and a central bore 72. The axial bore 64 accommodates an insert 74 with a shouldered front part 76 and a piston 78. The piston 78 is adapted to the bore 64 and has a rear face 77. A packing 80 embraces a shoulder 81 and extends from rear face 77 to an end face 79. In the vicinity of the corresponding inner face 71 is a packing 82 which embraces the shouldered front part 76. This latter part extends as a cylinder to a front edge 86 and then continues in the form of a conical nose 88. The insert 74 has an axial through bore 90 with a front end 94 defining an annular edge 92. The rear end 96 of insert 74, in the initial state, terminates in blind hole 65.

In the initial state the insert 74 takes up a position as shown in FIG. 3. On the emergence of the penetrator 60 from the barrel of a weapon (not shown) the fron annular face 70 forms a step in the contour and provides a limiting surface between a supersonic airflow and a subsonic zone. This assists the uniform separation of sabot segments (not shown) from the penetrator 60 and, for this purpose, a less favorable c.sub.w coefficient has to be expected. During the flight of the projectile air flows through the bore 90 and causes an accumulation of pressure behind the rear end face 79. As a result of this the insert is moved in the direction 100 (FIG. 4) to provide improved c.sub.w coefficient in comparison with that shown in FIG. 3. FIG. 4 shows the insert 74 in an intermediate position. A terminal position will be reached when the face 84 of the piston 78 bears against face 83 of the packing 82.

The subcaliber projectiles described herein have a length to diameter ratio ranging from 10/1 to 30/1.

Although the invention is described and illustrated with reference to a plurality of embodiments thereof, it is to be expressly understood that it is in no way limited to the disclosure of such preferred embodiments but is capable of numerous modifications within the scope of the appended claims.

Claims

1. A nose unit for a penetrator projectile having a high ratio of length to diameter and constructed to be at least transitionally variable in shape to improve the separation of discardable sabot segments after emerging from the barrel of a weapon, wherein

the nose unit is axially movably mounted in a central axial bore of said penetrator projectile;

said bore receiving said nose unit which has a frusto-conical front end, formed in such way, that in the initial position prior to firing of the projectile, the front end of said nose unit is in a retracted position in said bore;

said nose unit being moved forward out of said bore during firing acceleration such that said nose unit, on leaving said barrel projects forwardly in said bore of said projectile, the nose unit having a second central axial through-bore,

said bore of the projectile forming a guide for said nose;

said nose unit being slidably mounted in said first bore so as to form a piston fitting the first bore; the rear end surface of said nose unit abuts in the initial position against an annular confronting surface of said first bore, a blind hole is disposed at the rear of the first central axial bore, after the projectile has left the barrel of the weapon airflow through said second central axial through bore of said nose unit causes pressure to build up in the blind hole to displace the nose unit in the direction of flight of the projectile.

2. A nose unit as set forth in claim 1, wherein the front end of the projectile has disposed on an outer annular surface a threaded bush; and comprising

a first packing embracing said nose unit in the vicinity of an inner annular surface associated with the bush and opposed to the outer annular surface; and

a second packing embracing a shoulder on the rear of said nose unit and extending to the diameter of the first central axial bore.