DE3932952A1 - BULLET STOCK - Google Patents

Description

The invention relates to a wing-stabilized Wuchtge shot with a projectile body that is a length / diameter has water ratio of greater than 10, and by means of a segmented droppable sabot from a large caliber barrel weapon can be fired, according to the characteristics in the preamble of claim 1.

The shooting of slim, rod-shaped balancing bullets rides with increasing length and slimming of penetrators ever bigger problems. Especially that Natural vibration behavior of the shot rod-shaped Long storeys with an L / D ratio greater than 10 is to be regarded as critical here. The lowest The natural bending and bending frequencies of the slim penetrators are sin decrease in frequency ranges in which suggestions by Ab gait errors, malfunctions in the sabot detachment and also Suggestions occur during the flight phase. This low frequency excitations lead to transverse vibrations of the Rod during the flight phase by the slim rod no longer adequately reset, damped and balanced can be. The vibrations can continue rock up, which on the one hand is the endballistic performance of the penetrator, and even to failure or break the penetrator before reaching its target can.

In known balancing bullets or penetrators, this takes place Problem of natural vibration behavior due to the existing those inherent rigidity of relatively squat penetrato Ren or short storey bodies (L / D less than 10) no loading consideration.

It is therefore an object of the invention, for balancing projectiles with high slenderness measures to ensure a high rigidity even during the flight phase ben, on the one hand, the natural frequencies of the penetrator increase and secondly the vulnerability to Verbie reduced.

This object is achieved with the in the character nung part of claim 1 specified features ge solves. With the application of elongated stabilization affordability on the projectile body will be shootable and the stable flight behavior of penetrators higher Slenderness ensured. The penetrator rod will thereby over a partial length or over its entire length provided with elongated stabilizing strips that on the one hand on the penetrator itself or on a transition put on the cover. The high surface area The moment of stabilization bars gives the pen trator rod a high overall rigidity over the entire Penetrator length and guaranteed even during the flight phase a low susceptibility to vibration excitation.

The penetrator can have any shape and also be of any desired slenderness. The bracing of the Projectile body is essentially broken up by the stabilization strips ensured. As special the penetrator rod with solid is advantageous strong bullet tip and tapering towards the rear Projectile body out. This version doesn't just include aerodynamic, but also endballistic advantages. The The diameter of the empennage wing can also be increased that of the full caliber are expanded so that the Leit factory wings serve as support struts and guide elements and so stabilize very long penetrators during the acceleration phase in the pipe the.  

The power transmission of the gases present to the Penetra gate is made using conventional drive cages. The An Number of sabot segments depends on the Number of stabilizing bars applied. There are three, four or more stabilization bars imaginable, which the stiffening of the penetrator rod and the aero Ensure dynamic guidance of the projectile body. For the existing stabilization bars will match de Recesses in the sabot, preferably in the Tei Levels of the sabot segments provided. About Carrying the acceleration forces in the pipe from the sabot both the penetrator can be on the penetrator rod even using conventional thread or ring grooves as well the applied stabilizing strips are also used will.

When using an additional steel shell over the breakable tungsten core of the projectile body must non-positive connection between casing and penetrator be ensured. This is a particular advantage the tapered penetrator rod. Here can one essential part of the acceleration forces z. B. over Rei exercise. In addition, the frictional connection possible connection between the shell and penetrator to strive far ahead. With this procedure, the Connection during the penetration process of the target plate and the Penetra separate from the envelope surrounding it.

The special advantages of the balancing bullet according to the invention This becomes clear during the free flight. The natural frequencies ex Penetrator rods both decrease with the growing Slenderness level as well as especially with the growing Length of the rod. This increases the vulnerability of the bars against low-frequency suggestions, to whom the System is subject to such. B. in the acceleration pro zeß in the pipe from outgoing errors or suggestions  during the flight phase. The result is increased deflection movements of the rods during the flight by the Penetra can only be insufficiently damped. By the continuous excitation of the bars in their critical The system keeps rocking natural frequencies on what causes plastic deformation and even material can cause breaks.

To increase the penetrator stiffness, which both the kri table natural frequencies, as well as the deformation availability and the restoring forces are increased according to the invention elongated stabilizers along the penetrator arranged strips. That way, both the system rigidity increases as well as the flight behavior of the penetrator rod stabilized. To relocate the Pressure application point to the rear can be the diameter of the rear part of the sta bilization strips can be widened towards the rear. On this way the distance between pressure point and System focus increased and a more stable flight behavior set. One-piece stabilizing bars with tail fins designed on the rear can also be used consistently the same wing height or rise to the rear the wing height should be formed.

The formation of a massive penetrator head with itself tapering stern also leads to a displacement of the Center of gravity towards the front and to enlarge the Distance from the air attack point to the center of gravity and thus to further stabilize the system. The magnification The wing diameter also ensures that the taper penetrator cross section for a constant or for an increase in the total area moment of inertia.

As the critical state form, the one with the lowest eigen frequency can be considered. The vibration maximum forms usually in the middle of the penetrator rod. It  care must therefore be taken that the maximum deflection by a sufficient length and Adequate bending at the height of the stabilizing bars stiffness of the system is present.

The stable flight behavior of the slim according to the invention Penetrator rod also offers we from an end ballistic point of view considerable advantages. The low-frequency vibrating rod hits the target in a less deflected state. The natural vibration behavior of the rod runs in the ver neglected right at the end of the penetration process sigbar slow. Therefore, the deflected state can be during considered the penetration phase into the target to be virtually static be tested. During the penetration process of the rod-shaped force a hydrodynamic is shot on the front of the impact Condition in which the penetrating bullet mate rial rinses out the target material and continuously digs into the target. The penetration process is there if maintained by the constant pressure, who follow through with the undiminished speed penetrating mass is caused. The longer the The longer the process is maintained, the longer the staff is and the more the penetrator penetrates into the target.

If the penetrator rod is deformed or bent and the associated lateral deflection of the pushing material there is a lateral fault orientation between the penetrating mat rial and the armored target. Furthermore can it due to the limited penetration channel and the material flowing back from the crater floor to additional material Frictions and disabilities come as a result of which kinetic energy of the penetrator is reduced or else the penetrator can be destroyed.

To prevent these effects, the stabilization of the Penetrator's essential requirement. For this purpose  according to the invention the stiffening of the penetrator attached stabilizer bars made. Hinders Lich are only in the process of penetration into the target enlarged wing. These are at the meeting braking on the target surface and thus reducing the speed of the enclosed mass of penetrator. The Forces required to shear the wings are however relatively small, so that they are in relation to the kinetic residual energy of the penetrator almost can be relaxed.

When using a cover on which the stabilizing line Most attached, the disadvantages of Shear can even be avoided almost entirely. In particular re the shape of the penetrator tapering towards the rear stabes proves to be particularly effective. At the If the KE system hits the target, the envelope will also with the wings braked by the target wall and the Penetrator picks up its external stabilization system simple way off so that the penetrator alone and unsung prevents it from entering the target. The conical taper de form also forgives small pendulum angles, under de the penetrator hits the target. Friction on Inlet channel leading to failure if cylindrical of the penetrator can be done in this way diminishes.

The massive formation of the penetrator head proves itself furthermore as advantageous for oblique impacts on the target armored plates or in the penetration of reactive Aims that place high demands on the shear ability of the Ask penetrators. In these operations, first Line claims the tips of the penetrators; the rear right area of the penetrator is used for material replenishment in the entry hole punched from the top and up maintaining the hydrodynamic process. Here too  offers the shape of the tapered penetrator rod eighth advantages. The shootable mass is based on this Way optimally used. It is compared to the cylindri the projectile shape in the conical course to the rear lengthens and thus ensures the center of the penetration process for further material replenishment, which is getting smaller which however creates a deeper hole.

Furthermore, the refluxing material can become smaller flow freely through the penetrator diameter and calls less friction effects with the subsequent penetrator body out.

With the balancing of the balancing projectiles according to the invention by means of additional external stabilizing strips created an opportunity in an advantageous way, yet longer and slimmer penetrators with a length / through Knife ratio of greater than 30 can be fired securely and with even greater penetration performance at the target design. Such a long balancing projectile is e.g. B. on Page 1809, left picture, the Intern. Military review 12/1986 shown.

For example, with the invention, it can also remain the same bender ammunition length and total floor length as well as without Shortening the central primer (inner long ignition tube) an increase in the penetrator mass and thus the performance be achieved in the goal that by eliminating the Previously usual wing stabilizer with tail sleeve Steel or aluminum at this point the penetrator body is extended and also goal-oriented Samem tungsten heavy metal.

The invention is based on in the drawing tions schematically illustrated embodiments explained and described in more detail.  

Show it:

Fig. 1 is a side view of a penetrator according to the invention,

Fig. 2 shows a cross section through a erfindungsge MAESSEN penetrator with indicated sabot,

Fig. 3 shows a cross section through the inventive penetrator according to line III-III in Fig. 1,

Fig. 4 is a side view of another erfindungsge MAESSEN penetrator,

Fig. 5, 6, 7 and 8, cross-sectional and Teilquerschnittdarstel lungs by further embodiments of the invention penetrators,

Fig. 9, 10, 11 and 12 further side views of the invention penetrators.

In Fig. 1, the reference numeral 10 denotes a wing-stabilized balancing projectile or a penetrator which has a projectile body 12 with an L / D ratio of greater than ten. The projectile body 12 has on the front a slightly enlarged diameter projectile tip 14 , in the central area a conventional positive-locking zone 16 with thread or ring grooves for transferring the acceleration forces from a segmented, droppable driving cage fig to the projectile body 12 and a conventional wing wing 18 on the rear side. To increase its flexural strength, the projectile body 12 is provided according to the invention in its central region (maximum deflection) with at least three narrow stabilizing strips 20 running in the longitudinal direction on the outer surface of the projectile body. In order to achieve an effective stabilization effect, the stabilization strips 20 should extend at least over a third of the total projectile body length.

In the specific case shown, the length of the stabilization strips 20 is slightly more than half of the total length of the projectile body.

In Fig. 2 is a cross-sectional view of a bullet body 12 according to the invention with three stabilizing strips 20 and, moreover, six tail fins 22 of the wing tail unit 18 which are visible.

In the central region of the projectile body 12 , the positive-locking zone 16 is formed on the circumferential side, in which three sabot segments 24 engage here with correspondingly designed thread or ring grooves. The caliber-sized circumferential circle represents the front flange 26 of a conventional two-flange sabot. The sabot segments 24 are designed as 120 ° segments and are each laterally delimited by a parting plane 28 . According to the invention it is provided that each of the stabilizing bars 20 is arranged for aerodynamic reasons in the longitudinal direction exactly in front of an empennage wing 22 of the wing tail unit 18 .

According to Fig. 3 it is provided that the Stabilisierungslei most 20 in cross-sectional view, a wider base 30 for attachment to the projectile body 12 and to their outer edges 32 are tapered, ie that the sheet thickness of the stabilizing strips 20 decreases from the inside to the outside.

In FIG. 4 a further inventive penetrator 10 is shown. Here, each stabilizing bar 20 is extended to the rear and simultaneously formed in one piece as an empennage wing 22 with increasing height. The sta bilization strips 20 increase from the projectile tip 14 to about the middle of the projectile body 12 slowly but ste term in diameter or its radial extent. From the middle of the projectile body 12 from the stabilization strips 20 are then formed with a constant diameter, while they have a considerable increase in diameter again to the projectile rear 34 and are thus designed as a one-piece, large-area tailplane 22 .

Fig. 5 shows again a projectile body 12 in cross-sectional view, but here four stabilization strips 20 are symmetrically distributed over the circumference of the Geschoßkör pers 12 . The stabilizing strips 20 are inserted and fastened in the longitudinal grooves 36 provided on the outer surface of the projectile body 12 . The stabilizing strips 20 are preferably attached by welding or soldering.

According to a further embodiment shown in FIG. 6, the projectile body 12 has a core 40 made of fracture-sensitive tungsten heavy metal and a thin outer steel shell 38 . The stabilizing strips 20 are now welded directly onto the ductile steel shell 38 . If appropriate, the steel casing 38 can also be provided with corresponding longitudinal grooves into which the stabilizing strips are inserted and then preferably soldered.

In a simple embodiment according to FIG. 7, the stabilizing strips 20 have a rectangular cross section; they are each soldered into a longitudinal groove 36 provided on the outer surface of the projectile body 12 .

In order to produce a small compensating rotation, the stabilization strips 20 of the projectile body 12 have a corresponding bevel 42 on one side of their lateral outer edges 32 and / or their rear outer edges 32 , as shown in FIG. 8.

Another embodiment of a penetrator 10 according to the invention is shown in FIG. 9. Here, the projectile body 12 has an essentially cylindrical shape and the stabilizing strips 20 extend with a constant width over the entire length of the cylindrical projectile body region.

Advantageously, the stabilizing strips 20 in a front section 50 made of a high temperature resistant material such. B. a steel or titanium alloy and in the rear section 52 from a light metal alloy such. B. aluminum.

According to another embodiment shown in FIG. 10, the projectile body 12 likewise has an essentially cylindrical shape, but the stabilizing strips 20 widen towards the rear, ie they extend over the entire length of the cylindrical projectile body region with a width that increases continuously towards the rear or Height.

In a further preferred exemplary embodiment shown in FIG. 11 of a penetrator 10 according to the invention, the projectile body 12 is behind its projectile tip 14 , possibly starting with an annular groove 44 as a predetermined breaking point, with a conically tapering shape to the rear, ie with a projectile body decreasing towards the rear knife trained.

A similarly designed penetrator 10 is shown in FIG. 12. Thereafter, the one-piece projectile body 12 following the projectile tip 14 via a short cylin-shaped projectile body piece 46 , approximately with a length of two to four projectile body diameters, a tapered projectile body shape 48 towards the rear, with the stabilizing strips 20 at the same time as an enlarged tailplane wing 22 are formed.

The stabilizer bars can be used for an inexpensive Series production as simple stamped sheet metal parts made of steel sheet metal or a corresponding other dimensionally stable mate rial are manufactured.

By applying stabilization according to the invention perform on the outer surface of balancing bullets with high Slenderness becomes a high inherent rigidity of the Ge lap body also guaranteed during the flight phase, wel che increases the natural frequencies of the penetrator and reduces susceptibility to bending.

Reference symbol list

10 penetrator
12 storey body
14 storey top
16 positive-locking zone
18 wing tail
20 stabilizing bars
22 empennage wings
24 telecommunications segments
26 front flange
28 parting plane
30 base ( 20 )
32 outer edge
34 bullet tail
36 longitudinal grooves
38 steel shell
40 WSM core
42 chamfer ( 32 )
44 ring groove
46 cylindrical piece
48 conical pieces
50 front section
52 rear section

Claims (14)

1. Wing-stabilized balancing projectile with a Geschoßkör by, which has a length / diameter ratio of greater than ten, which can be fired from a large-caliber Rohrwaf fe by means of a segmented sabotable sabot, and which due to its great slenderness during acceleration in the gun barrel and is subject to bending vibrations during the projectile flight, characterized in that the projectile body ( 12 ) has at least three longitudinal stabilization strips ( 20 ) on its outer surface of the projectile body to increase its flexural strength. ( Fig. 1) 2. Projectile according to claim 1, characterized in that the stabilizing strips ( 20 ) extend at least over a third of the total projectile body length. ( Fig. 1) 3. Projectile according to claim 1 or 2, characterized in that each of the stabilizing strips ( 20 ) for aerodynamic reasons in the longitudinal direction is arranged precisely in front of an empennage wing ( 22 ) of the wing tail unit ( 18 ). ( Fig. 2) 4. Projectile according to claim 1, 2 or 3, characterized in that the stabilizing strips ( 20 ) in cross-sectional view, a wider base ( 30 ) for attachment to the projectile body ( 12 ) and to their outer edges ( 32 ) are tapered ie that the sheet thickness of the stabilizing strips ( 20 ) decreases from the inside to the outside. ( Fig. 3) 5. Projectile according to claim 1, 2, 3 or 4, characterized in that each stabilization bar ( 20 ) extends to the rear and, if necessary, is formed in one piece as an empennage wing ( 22 ) with increasing height. ( Fig. 4, 11, 12) 6. Projectile according to claim 1, 2, 3, 4 or 5, characterized in that four stabilizing strips ( 20 ) are provided distributed symmetrically on the circumference of the projectile body ( 12 ). ( Fig. 5) 7. Projectile according to one of the preceding claims 1 to 6, characterized in that the projectile body ( 12 ) has a core ( 40 ) made of brittle sensitive heavy metal and a thin outer casing ( 38 ) made of a more ductile material such as, for. B. steel, on which the stabilizing strips ( 20 ) are attached. ( Fig. 6) 8. Projectile according to one of the preceding claims 1 to 7, characterized in that the stabilizing strips ( 20 ) have a rectangular cross section and are each secured in a longitudinal groove ( 36 ) provided on the outer surface of the projectile body ( 12 ). ( Fig. 7) In that the stabilizing strips (20) 9. A projectile according to one of the preceding claims 1 to 8, characterized in that for generating a low compensating rotation on one side of their since low outside edges (32) and / or its rear outer edges of a corresponding chamfer (42). ( Fig. 8) 10. Projectile according to one of the preceding claims 1 to 9, characterized in that the projectile body ( 12 ) has an essentially cylindrical shape and the stabilizing strips ( 20 ) with a constant width over the entire length of the cylindrical projectile body region. ( Fig. 9) 11. Projectile according to one of the preceding claims 1 to 9, characterized in that the projectile body ( 12 ) has a substantially cylindrical shape and the stabilizing strips ( 20 ) run with increasing width to the rear over the entire length of the cylindrical projectile body region. ( Fig. 10) 12. Projectile according to one of the preceding claims 1 to 9, characterized in that the projectile body ( 12 ) behind the projectile tip ( 14 ), optionally with an annular groove ( 44 ) as a predetermined breaking point, starting with a conically tapering shape towards the rear, ie a projectile which decreases towards the rear body diameter. ( Fig. 12) 13. Projectile according to one of the preceding claims 1 to 12, characterized in that the one-piece projectile body ( 12 ) following the projectile tip ( 14 ) via a short cylindrical piece ( 46 ) with a length of approximately two to four Ge projectile body diameters has a conically tapering shape towards the rear ( 48 ), the stabilizing strips ( 20 ) at the rear being simultaneously designed as a control wing. ( Fig. 11) 14. Projectile according to one of the preceding claims 1 to 13, characterized in that the stabilizing strips ( 20 ) in a front part ( 50 ) made of a high temperature resistant material such as. B. a steel or titanium alloy and in the rear section ( 52 ) made of a light metal alloy such. B. aluminum. ( Fig. 9)