EP0149713A2 - Practice projectile - Google Patents

Abstract

The invention relates to a training projectile for large-caliber barrel weapons, in which the flight should be changed in the supersonic range after reaching variably adjustable practice shooting ranges such that a further shortening of the distance behind the target and thus also the respective total flight range can be achieved compared to known training projectiles. The object is achieved in that, with unchanged outer geometry 2, the practice floor 3 contains a further body 5 which can be adjusted to the position of the center of the training floor 4, by means of which the center of the training floor 4 extends in a range between a position 7.1 of the air attack point 6 at high initial speed and one towards the tip 8 Position 7.2 taken can be variably adjusted at a slower bullet speed, whereby an early interruption of a stable flight phase and the beginning of an unstable flight is achieved already around the supersonic speed range in that a variable distance a between position 7.1 of the air attack point is proportional to a stable flight phase corresponding to the range of the projectile floor 6 and the practice floor focus 4 is adjustable and the practice floor 3 becomes unstable with congruence of the air attack point 6 and the practice floor focus 4 and reinforced early is braked.

Description

The invention relates to a training projectile according to the preamble of claim 1.

Such a practice floor is known from DE-OS 32 33 045. The practice range can be variably adjusted on this practice floor by changing the outer geometry. Long cone-shaped projectile tips are used to set large flight distances and correspondingly short projectile points are used to set shorter flight distances. The shortening of the flight range of this rotation-stabilized practice projectile is achieved in comparison to a combat projectile having the same ballistic values within a limited range, in that an increased air resistance is generated when the flight speed decreases in the subsonic speed range on the front face of the projectile body.

Because this rotation-stabilized practice projectile does not leave the stable position it occupies during the entire flight, the shortening of the flight distance is therefore essentially determined only by the air resistance acting on the front face and only occurring at subsonic speed. The result of this is that, with the same ballistic requirements, within a same range of practice range, there is a further shortening of the distance behind the target and thus also of the entire flight range of practice range of the same caliber; especially because the practice floors can only be braked when the subsonic speed is reached.

In contrast, the invention has for its object to improve the practice projectile of the type mentioned in the preamble of claim 1 in such a way that immediately after reaching variably adjustable practice range, the flight of the practice projectile also undergoes such a change of direction in the supersonic speed range that a further shortening of the distance behind the Target and thus also the respective total flight distance compared to known practice projectiles.

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

According to the invention, the non-spin-stabilized practice floor has the decisive advantage that the stable flight phase of the training floor can be interrupted and the training floor can become unstable in the supersonic range after reaching the training range, whereby the high air resistance which forms in the transverse position or rotation of the training floor causes an immediate strong resistance Braking can take place. As a result, compared to known practice projectiles that slow down in a stable flight position, a significantly larger effective area causing the braking effect is produced for the air resistance and, with the same ballistic requirements within a same range of practice range, the distance behind the target is significantly shortened, whereby the practice level can also be used in the smallest security areas.

The point in time of becoming unstable and thus the range of practice range of the practice level can be set particularly advantageously independently of the external geometry by means of a further body which can change the position of the center of focus of the projectile level, so that different aerodynamic influences in the range of the range of practice range are avoided when using different projectile projectile tips.

The possibility of adjusting particularly small distances between the training floors is difficult in the invention point and the air attack point at high initial speed from the fact that the practice projectiles flying at supersonic speed are braked early on a comparatively short distance after reaching the practice range.

Advantageous refinements and developments emerge from the subclaims.

Because the outer geometric shape of the practice floor including the top of the floor remains essentially unchanged, this area of the training floor is suitable for simple, preferably serial, non-cutting production.

The position of the center of gravity of the practice floor can be adjusted either by exchanging another body with a different mass at the rear or within the floor of the floor gradually or continuously by a body that is longitudinally adjustable inside the floor of the floor, the stepless adjustment of the center of gravity and thus the stable flight phase, in especially . is advantageous, even in the finished laboratory state of the practice floor by rotating the top of the floor about its longitudinal axis.

Preferred embodiments of the invention are described in detail with reference to the figures shown.

• Fig. 1 ein fertiglaboriertes Übungsgeschoß in einer Seitenansicht;
• Fig. 2 das Übungsgeschoß in einer Seitenansicht, mit Geschoßkörper, Geschoßspitze und einem zur Einstellung des Geschoßschwerpunktes austauschbaren Heck,
• Fig. 3 das Übungsgeschoß in einer teilweise geschnittenen Seitenansicht,mit einem zur Geschoßschwerpunkteinstellung im Inneren des Geschoßkörpers befindlichen austauschbaren Körper;
• Fig. 4 das Übungsgeschoß in einer teilweise geschnittenen Seitenansicht mit einem im Inneren des Geschoßkörpers angeordneten stufenlos den Schwerpunkt verstellbaren Körper;
• Fig. 5 in einem Längsschnitt das Übungsgeschoß mit einer stufenlosen Verstellmöglichkeit des im Innenraum des Geschoßkörpers angeordneten Körpers durch die Geschoßspitze;
• Fig. 6 in einem Längsschnitt eine weitere Anordnung der stufenlosen Verstellmöglichkeit des im Innenraum des Geschoßkörpers angeordneten Körpers durch die Geschoßspitze;
• Fig. 7 in einer Seitenansicht des Übungsgeschosses die schematische Darstellung einer Veränderung des Übungsgeschoßschwerpunktes gegenüber dem Luftangriffspunkt;
• Fig. 8 in einem Funktionsdiagramm die stabilen und instabilen Flugbereiche des Übungsgeschosses bei zwei verschiedenen Schwerpunkteinstellungen in Abhängigkeit von der Entfernung des Luftangriffspunktes und von der Geschoßgeschwindigkeit;
• Fig. 9 in einem Diagramm den Geschwindigkeitsverlauf während des stabilen und instabilen Fluges bei zwei verschiedenen Übungsschußweiten;
• Fig. 10 den Verlauf einer Flugbahn eines auf eine Ubungsschußweite vorher eingestellten Ubungsgeschosses und eines entsprechenden normalen Gefechtsgeschosses.

It shows:

• Figure 1 shows a finished laboratory training floor in a side view.
• 2 shows the practice floor in a side view, with the floor body, floor tip and a replaceable rear for setting the floor center of gravity,
• 3 shows the training projectile in a partially sectioned side view, with an interchangeable body located in the interior of the projectile body for center of gravity adjustment;
• Figure 4 shows the training projectile in a partially sectioned side view with a body which is arranged in the interior of the projectile body and which is infinitely adjustable the center of gravity.
• 5 shows in a longitudinal section the exercise projectile with a stepless adjustment of the body arranged in the interior of the projectile body through the projectile tip;
• 6 shows in a longitudinal section a further arrangement of the stepless adjustment possibility of the body arranged in the interior of the projectile body through the projectile tip;
• 7 is a side view of the training floor, the schematic representation of a change in the center of gravity of the training floor compared to the air attack point;
• 8 shows in a functional diagram the stable and unstable flight areas of the training floor with two different center of gravity settings depending on the distance of the air attack point and on the floor speed;
• 9 shows a diagram of the speed profile during the stable and unstable flight with two different practice shooting ranges;
• 10 shows the course of a trajectory of a practice projectile set to an exercise range and a corresponding normal combat projectile.

In Fig. 1, a non-spin-stabilized practice floor 3 is shown ready labored. It consists essentially of a projectile body 1, a projectile tip 8 and a combustible propellant charge sleeve 29 connected at the rear to the projectile body 1. The cylindrical projectile body 1 is preferably suitable for smooth-tube bombardment of large-caliber barrel weapons, although it is also not shown on the projectile body jacket 30 when used slipping guide bands, can be fired from drawn tubes of large-caliber barrel weapons. To seal the projectile jacket 30 is provided with known seals, which are not relevant to the invention and therefore, like the bottom of the projectile body 1, are not shown. The front area of the projectile body 1 contains a cone-shaped tip 8 which is substantially smaller in diameter and transversely cut off at the front. Even if it is possible to set different practice shot ranges and achieve shorter flight distances, the practice projectile center of gravity 4 (FIG. 2) according to different methods ( Fig. 2 to 6) to adjust, the outer geometry 2 of the projectile body 1 and the projectile tip 8 remains unchanged in all exemplary embodiments, in order to maintain essentially equally favorable external ballistic influences.

2 shows the center of gravity of the practice floor 4, the position 7.1 of the air attack point 6 at a high initial speed and the position 7.2 of the air attack point 6 assumed on the projectile axis 15 towards the tip 8 at a slower floor speed. If the air attack point 6 is in an area a between the rear 11 and the practice floor center of gravity 4, the practice floor 3 flies in a stable flight position, whereby the same ballistic requirements are achieved during this flight as with normal combat missiles (Fig. 10).

If the projectile slows down, so that the air attack point on the projectile axis 15 shifts towards the tip in front of the practice projectile center of gravity 4 or overlaps the practice projectile center of gravity 4, the practice projectile 3 becomes unstable and the large areas of the projectile shell 30, 31 can also be due to the large air resistance , which occurs in the transverse position of the floor 3 or in the case of a training floor 3 rotating about the floor center of gravity 4 perpendicular to the floor axis 15, have a braking effect.

Not changing the outer geometry of the practice floor 3, the floor body 1 contains a further interchangeable body 5.1 on the rear side. The body 5.1 designed as a cylinder 10 forms the rear 11 of the training floor 3 and can preferably be screwed into the floor body 1. The exchangeable bodies 5.1 have the same shape, but have different densities and therefore also different masses. By exchanging the bodies 5.1, it is possible to vary the distance a variably and in stages, so that an exercise range corresponding to the stable flight phase can be set and a short projectile range can be achieved behind the target. For bodies 5.1 with a higher density, due to the increased mass of the body 5.1, the distance a between the center of gravity 4 and the position 7.1 of the air attack point 6 inevitably decreases, while the distance a would increase with a lower mass of the body 5.1.

FIG. 3 illustrates the use of a body 5.2 which is designed and exchangeable as a body 5. The interchangeable bodies 5.2 point to one another with the same density and outer geometry 13 has a different inner geometry 9 for producing different masses. The bodies 5. 2 are interchangeably fastened within a cavity 12 of the exercise floor 3 which is open at the rear, the cavity 12 preferably being designed as a bore. The body 5.2 contains at least one cavity 14 which is open at the rear and which can be varied in cross section A and / or in length 1, as a result of which different masses 5.2 can be produced in different bodies and the center of gravity of the exercise floor 4 can also be adjusted in stages.

The outer geometric shapes of the interchangeable 5.1 (Fig. 2) or 5.2 each have the same dimensions, whereby the manufacturing effort remains essentially the same, so that series production can also be carried out as in the case of the projectile body 1.

In Fig. 4 the body 5 of the practice floor 3 is shown as the position of the training floor center of gravity 4 adjustable body 5.3 on the floor axis 15. The body 5.3 is designed as a cylinder 16 provided with a thread on the jacket 18, which is arranged in a threaded bore 17 open towards the rear 11 and its position on the rear side of the projectile axis 15 is adjustable. A displacement of the body 5.3 in the direction of the stern 11 would reduce the distance a between the center of gravity 4 and the position 7.1 of the air attack point 6, while an adjustment of the body 5.3 in the direction of the tip 8 would increase the distance a. This embodiment variant of the practice floor 3 is also particularly advantageous for series production with unchanged outer geometry 2 and unchanged inner bore 17 of the projectile body 1 and the same bodies 5.3.

A possibility of setting the inside of the projectile body 1, which can also be carried out in the finished laboratory state Continuously adjustable body 5.3 (FIG. 4) clarifies FIG. 5. Here, the body 5.3 can be continuously changed in position from the outside by the cylindrical pin 19 forming the projectile tip 8. The pin 19 is rotatably mounted on the front end wall 20 of the practice floor 3 in a bearing 21 and fixed in the longitudinal direction of the floor axis 15. The pin 19 is in the interior 22.1 of the threaded bore as guide 17.1 _- 26 of the formed provided with a corresponding guide bore 27 and a driving groove 28 and driving body 5.3 bar. By rotating the pin 19 in the direction 32 about the projectile axis 15, the body 5.3 also experiences the same rotation via the driving groove 28, so that the axial displacement of the body 5.3 on the guide rod 26 takes place due to the rotating body 5.3 guided by the threaded bore 17.1 can. Rotation of the pin 19 is at the same time a measure of the range to be adjusted.

FIG. 6 shows a further embodiment variant of an external adjustment possibility of the body 5.3 (FIG. 5). The pin 19 rotatably fastened in the front end wall 20 in the bearing point 21 is formed as a threaded rod 23 in the interior 22.2 of a smooth bore 17.2. The body 5.3 (FIG. 5) is designed as a body 5.4 which is continuously displaceable longitudinally in the bore 17.2, wherein it contains an anti-rotation device 25 and a threaded bore 24 corresponding to the threaded rod 23 in the axial direction. The anti-rotation device 25, which preferably consists of a groove 33 in the body 5.4 and a spring 34 fastened within the bore 17.2, allows the body 5.4 to be locked in the circumferential direction and displaced in the direction of the projectile axis 15. This embodiment variant is particularly advantageous in terms of production technology with regard to a non-cutting production of the inner bore 17 of the practice floor 3 and the outer contours of the body 5.4.

The influencing of the stable and unstable area within the flight of the practice floor 3 by the center of gravity 4 will be explained in more detail with the aid of two different settings of the center of gravity in FIGS. 7 to 10.

In FIG. 7, position 35.1 shows the center of gravity 4 once at a distance a ₁ and position 35.2 at a distance a ₂ from position 7.1 of the air attack point 6. The distance of the practice projectile axis 4 to the tail 11 has in the position of the 35.1 _M ate 11 and in the position 35.2 the level 1. ₂ With f ₁ the distance of the air attack point in position 7.1 to the stern 11 and with f ₂ the distance in position 7.2 to the stern 11 is indicated.

From Fig. 8 it is clearly visible that the distance f of the air attack point 6 increases with decreasing speed. This behavior is achieved by the shape of the projectile tip 8 (FIG. 2), whereby it can be used in the invention in comparison with known spin and wing-stabilized practice projectiles and is advantageously used in practice projectile 3 (FIG. 2). With a larger distance 1 _{1 of} the center of gravity 4, the area 36.1 of the stable flight phase is therefore necessarily larger than the area 36.2 of the stable flight phase at a smaller distance l ₂ . However, after the smaller stable flight phase 36.2, the region 37.2 of the unstable flight is reached earlier in the setting 1 ₂ compared to the setting l ₁ . When the distance f reaches the same distance 1, the practice floor 3 becomes unstable; the speed in this area is called critical.

Correspondingly, the increased speed drop when the critical speed is reached can be seen from FIG. With a smaller distance 12 or a ₂ , the critical speed is reached sooner than with the larger distance 1 ₁ or a ₁ . FIG. 9 particularly illustrates the variability of the stable and unstable flight distances and thus on the one hand the range of the practice range during the stable flight and on the other hand the entire flight range of the training floor 3.

10 illustrates a matching ballistic flight behavior of the practice floor 3 compared to a comparable battle floor 38 to achieve the critical flight distance x _crit . (Fig. 9). The total flight distances x ₁ or x ₂ of the training floor show the very short braking distances after reaching the destination due to the unstable flight behavior of the training floor. For example, with a range x ₃ = 5000 m of a combat floor 38, it is advantageously possible to set 3 total flight ranges of, for example, x ₁ = 3000 m or only of x ₂ = 1000 m with the training floor.

Reference symbol list

• 1. projectile body
• 2, outer geometry
• 3 practice floor
• 4 Practice floor focus
• 5 bodies
• 5.1, body
• 5.2, body
• 5.3, body
• 5.4 body
• 6 air attack point
• 7.1 position
• 7.2 position
• 8 top
• 9 internal geometry
• 10 cylinders
• 11 stern
• 12 cavity
• 13 outer geometry
• 14 cavity
• 15 projectile axis
• 16 cylinders
• 17 hole
• 18 coat
• 19 cones
• 20 end wall
• 21 depository
• 22 interior
• 22.1, interior
• 22.2 Interior
• 23 threaded rod
• 24 threaded hole
• 25 anti-rotation lock
• 26 Guide and drive rod
• 27 guide bore
• 28 driving groove
• 29 propellant charge case
• 30 coat
• 31 coat
• 32 direction
• 33 groove
• 34 spring
• 35.1 position
• 35.2 Position
• 36.1 area, stable flight
• 36.2 area, stable flight
• 37.1 Area, unstable flight
• 37.2 Area, unstable flight
• 38 battle floor
• a distance
• A cross section
• 1 length
• x ₁ flight distance
• x ₂ flight distance
• f ₁ distance
• f ₂ distance
• l ₁ distance
• 1 ₂ distance
• v speed
• v _o initial speed

Claims (11)

1st practice projectile, the flight distance of which can be adjusted for shooting in variable safety areas, consisting of a full-caliber projectile body which can be closed at supersonic speed and a cone-shaped tip which is considerably smaller in diameter than the projectile body, characterized by the following features: a) the projectile body (1) contains an unchanged external geometry (2) of the practice floor (3), the position of the center of the practice floor (4) adjustable further body (5); b) the body (5) sets the practice floor center of gravity (4) in a region between a rear-facing position (7.1) of the air attack point (6) at a high initial speed of the practice floor (3) and a position ( ₇ ) towards the top (8) 2) of the air attack point (6) at a slower bullet speed, which means an early interruption of a stable flight even in the supersonic range phase and the beginning of an unstable flight is achieved in that a variable distance (a) between the position (7.1) of the air attack point (6) and the center of the practice floor (4) can be set proportionally to a stable flight phase corresponding to the range of the practice range and the practice floor ( 3) becomes unstable when the air attack point (6) and the practice floor center of gravity (4) are congruent and is decelerated early. 2. training projectile, according to claim 1, characterized in that the body (5) as replaceable each having a different mass body (5.1, 5.2) of the projectile body (1) is ausgebil det, whereby the location of the practice floor center of gravity (4). can be set in individual stages coordinated with the desired flight distance 3. Training projectile according to claim 1 and 2, characterized in that the exchangeable body (5.1) having a different mass are of the same shape, but have a different density from one another. 4. training projectile according to one of claims 1 to 3, characterized in that the body (5.1) as a with the outer geometry (2) of the projectile body (1) matching cylinder (10) forms the rear (11) of the training projectile (3). 5. exercise projectile according to claim 1 and 2, characterized in that the exchangeable and each having a different mass body (5.2) have the same density and outer geometry (13), but have a different inner geometry (9). 6. Training floor according to one of the features 1, 2 and 5, characterized in that the body is arranged by (5.2) within a cavity (12) of the practice floor (3) which is open at the rear and contains at least one cavity (14) which can be varied in cross section (A) and / or in length (1). 7. Exercise floor according to claim 1, characterized in that the position of the practice floor center of gravity (4) is continuously adjustable by a position-changing body (5.3) formed on the floor axis (15) of the practice floor (3) as a body (5). 8. Practice projectile according to claim 1 and 7, characterized in that the body (5.3) is arranged as a cylinder (16) provided with a thread on the jacket (18) within a threaded bore (17) which is open towards the rear (11). 9. training projectile according to one of claims 1, 7 and 8, characterized in that the body (5.3) from the outside through the projectile tip (8) forming cylindrical pin (19) is infinitely variable in position, thereby changing the distance determining the stable flight phase (a) is also possible in the finished laboratory state of the practice floor (3). 10. Practice projectile according to one of claims 1 and 7 to 9, characterized in that the pin (19) on the front end wall (20) of the practice projectile (3) is rotatably mounted in a bearing point (21) and in the longitudinal direction of the projectile axis (15 ) is fixed and in the interior (22.1) of the bore (17.1) is designed as a guide and driving rod (26) of the body (5.3) provided with an associated guide bore (27) and a driving groove (28). 11. Training floor according to one of claims 1, 7, 9 and 10, characterized in that the in the front end wall (20) in the bearing (21) rotatably fastened pin (19) in the interior (22.2) of the bore (17.2) is designed as a threaded rod (23), and that the body (5.3) as in the bore (17.2 ) steplessly longitudinally displaceable body (5.4) contains an anti-rotation device (25) and in the axial direction a threaded hole (24) corresponding to the threaded rod (23).

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