DE2245353A1 - BULLET - Google Patents

Description

Patent attorneys,

Dipl. -InG. H. Weickmann, D1PL.-PHYS. Dr.E. Fincke Dipl.-Ing. FA Weickmann, Dipl.-Chem. B. Huber

8 MUNICH 86, POST BOX 860 820

MÖHLSTRÄSSE 22, CALL NUMBER 483,921 / 22

<98 3921/22>

Abraham Flatau, 2003 Stocktort Road, Jappa, Maryland, USA

Bullet

The invention relates to significant improvements in this regard the flight range of an ammunition projectile and sees here a relatively flat trajectory compared to the usual ballistic trajectories.

In order to achieve a greater flight range, common projectiles ranging from shells fired from the shoulder to artillery shells using a rocket engine added to the basement. The rocket engine assembly has roughly the flight range enlarged by a third, based on the trajectory without Rocket.

The aim of the invention is to increase the flight distance without the additional weight and costs of a rocket engine ",

-2- 2 2 4 5 3 b

Another object of the invention is to provide a projectile whose limit flight capability is related to lethality per unit weight of ammunition, shows a considerable increase compared to conventional projectiles.

This invention is directed to a body of revolution that forms a ring-wing warhead with a hollow ring, which surrounds a central opening and rotates about an axis which extends generally in the direction of the flight path on the impact surface. The hollow ring takes the payload and the ignition device.

This invention relates to a new projectile design based on a streamlined ring or ring wing formed by the rotation of a wing profile or wing cross-section, about an axis lying below and parallel to the longitudinal direction of the wing cross-section.

The main aim of this invention is to provide ammunition which is more effective at reducing the resistance of the enemy to overcome.

Another object of the invention is to provide ammunition or a To create a projectile that better than before uses a trajectory lying in the direct line of fire.

Furthermore, the projectile according to the invention should be a larger

309886/0328

OFWGfNAL INSPECTED

22A5353

Destruction of the target area can be achieved without increasing the payload. Furthermore, it is the aim of the invention that the warhead according to the invention can be fired from a conventional launching device which has a projectile casing guide ring used. Another object of the invention is to provide an annular wing projectile with a small angle of climb for the initial flight path.

Various developments have taken place in the field of military equipment to kill people and material with bullets, Destroy mortars and grenades. These means have a flight range that is limited due to their ballistic properties. Many of these funds have the use of “ Launcher made necessary, which require that the projectile an angle of climb relative to the ground up to 45 has in order to achieve the maximum flight distance. In most cases, the usual projectiles can be used to achieve the maximum flight distance are not shot in the direct line or with a small angle of climb of about 6.

The usual bullets have a fundamental shortcoming, the consists in the fact that medium and maximum flight distances cannot be achieved without the aid of the normal high flight paths, the. result from high climbing angles of, for example, 30 to 45.

The one used in the army to be shot from the shoulder

309880/0320

Grenade launcher (l ί-79) and the 40 mm (i i-40o) from the shoulder Grenades to be fired cannot shoot or be fired with small angles of incline.

With a heavy overhanging jungle canopy, the Soldier trying to hit a target at medium or long range with a normal bow or shoot a high trajectory. In many cases this leads to the projectile hitting or grazing the foliage and thus is diverted from the desired trajectory. In other words, a relatively flat trajectory would be desirable to avoid the influence of this environment.

The ballistic design of the present warhead overcomes the previous limitations of the high flight path and allows a climb angle of 5 to / from the launcher for essentially the same flight distance as with a climb angle of 35, that of the 40 mm - M-39 grenade system was required. In addition, the warhead according to the invention can also be shot with a high trajectory, if this is desirable.

The warhead of the present invention offers great improvements in trajectory performance in conjunction with an enhanced one Flight range, by a factor of 2 or more for the same launch speed and weight of the projectile in relation to the M-406 shell, The warhead according to the invention has a considerable increase

309886/0328 ~ ⁵ ~

in terms of dangerousness for the same amount of highly explosive Explosives shown used in the standard 40mm grenade (M-406).

The exceptional aerodynamic properties of the ring wing training allow the soldier on one Shoot essentially a direct line into the target area.

The embodiment of the present invention has aerodynamic properties that are common to conventional ballistic Shots were not reachable. In flight, the projectile rotates around its axis of symmetry, which is in the center of the body of revolution which is formed by rotating the wing cross-section about this axis. The turning speed should be exceed about 2,000 rpm, and preferably far exceed this limit. The rotary motion creates gyroscopic Stability, so that despite the fact that the projectile tends to maintain a relatively constant attitude, the angle of the Ring wing generates a lift force along the flight path, which partially cancels the influence of gravity. this will achieved by using an essentially neutral static aerodynamic moment or dynamic equilibrium property, C., i \. In addition, the ring wing bolt has a lower air resistance than the usual M-406 grenade. In this way, the combination of the buoyancy and the low air resistance to a relatively flat one

309886/0328 - ⁶ "

Flight path and an extended flight range for any given launch speed when firing at low angles.

The ring wing design leads to a more even distribution of splinters over a larger area than with the 11-406 grenade could be achieved. The ring wing design can therefore be used for a tactical function, with the Explosion can occur either in the air near the target or on impact at the target.

The IL-406 shell's fragmentation pattern is generally limited to the rearward direction only and is approximately 135. The field tests show directly the fragmentation pattern and the distribution that results from the embodiment according to the invention in the case of a warhead with a notched wire mesh gravel charge. The dead effect, as it is derived from the terrain measurement data, results in a substantial increase for the warhead according to the invention compared to the M-406 shell. This is partly due to both the increase in the number of available fragments resulting from the ring wing geometry and the absence of a child effect in the design, resulting in a considerable increase in the distribution of fragments for the ammunition according to the invention H-406 results. Figures 1 and 3 show scattering patterns and the distribution of splinters resulting from the field trials.

- 7 -309886/0328

OFUGINAL INSPECTED

• Further details, features and advantages of the invention emerge from the following description in conjunction with the claims and the drawing. In this shows? '

1 shows a longitudinal section through a projectile according to FIG. 2; Fig. 2 is a view of a known grenade;

3 shows a diagrammatic, partially broken away and cross-section showing the representation according to the invention Design;

4 shows a cross section through a projectile according to the invention with a guide ring or sabot;

5 shows a cross section of the sabot with a projectile aid;

6 shows a schematic representation of an inventive Floor;

7 shows an enlarged cross section through the embodiment according to the invention;

Figures G and 9 are diagrammatic representations of projectiles according to the invention with an inner detonating ring and a detonating sector, respectively.

3098 8 6/0328

BATH ORIGINAL

In Figs. 1, 2, 3 and 6, the straight arrows show the direction of the flight. In Fig. 6, the curved arrow indicates the direction of rotation.

The warhead is a self-contained unit and the external design is particularly suitable for the various military filling materials that are used in warfare are usable. Furthermore, the warhead according to the invention is, as is the case with conventional military equipment is, according to FIGS. 3 and 7, provided in the interior with an igniter 7 which is provided in the ignition ring 5 arranged at the rear and the ignition line 11 ignites, whereupon the igniter 13 ignites the explosive filling 15, which in turn generates a force which breaks up the outer surface 1 and the splinters formed flung away. The internal functional elements mentioned above correspond to the state of the art and the purpose and the The way in which these parts work are well known to those skilled in the art. Other ignition points are planned, for example one inner ignition ring - for example according to FIG. 8 - or an ignition sector according to FIG. 9.

It is within the scope of the invention that other internal known elements for the ignition of military equipment can be used in the embodiment according to the invention.

In this invention, various other types of ignition are dependent on time, impact, approach or

309886/0328

scheduled a command that ensures a safe separation from the Ensure launch device before arming in flight.

The present invention is better suited than prior art destruction or incapacitation devices of military objects through highly explosive fragmentation or projectile fragmentation, incendiary materials or one other substance for rendering harmless.

The projectile can be filled with chemical materials that provide a vapor when released from the projectile will. Examples of known agents are phosgene gas, mustard gas, "v -chloroazetophenone. Other bullet filling components can deliver a smoke, for example phosphorus, sulfuric acid with chlorosulphonic acid or a fire material, like thermite, which is black and non-oxidic and mixed with aluminum, or white phosphorus.

The streamlined cross-section used in the ring-wing grenade is quite thick, ie on the order of 25 to 35 JO of the sight dimension and preferably about 40 % at the point of greatest thickness. The emphasis on the extent of the thickness is made in order to be able to contain sufficient explosives in the ring-wing warhead and to obtain a large charge-to-mass ratio. This is the ratio by which the basic blasting properties and fragmentation velocity properties can be predicted and which is a basis for implementation

309886/0328 - ¹⁰ -

a comparison with other warheads. The front and rear edges of the ring wing are like this designed that the radius of the front edge is substantially larger than the radius of the rear edge, which is part of the rear arranged ignition ring corresponding to the ignition arrangement shown in Fig. 7 forms.

The manufacture and field testing of explosive devices using colored wire mesh charges has shown that an overall diameter of 5 to 6.5 cm and a tendon dimension of 2.5 to 3.5 cm produce the desired results. Small wing extensions, i.e. wingspan or diameter to the Chord values that are close to one do not give good aerodynamic properties.

Fig. 2 is a view of a known grenade, (40 mm 41-406), in which the reference number 2 is the outer housing, the reference number 4 is the notched wire mesh ball for the fragmentation and the Numeral 6 denotes the fragments scattered after the projectile exploded.

Fig. 1, the longitudinal section through Fig. 2, shows the fragment litter pattern of the outer housing 2, the detonator 8, the explosive charge 10 and the notched wire mesh ball 4 for fragmentation, the shielding effect being over at least 60 /? the shattering ball is indicated. The shielding effect reduces both the fragmentation speed, the radius of death and the area of destruction of the projectile outside of the

en zone of 135.

309886/0328

- 11 -

ORIGINAL INSPECTED

unshielded zone of 135.

In Fig. 3, the reference numeral 27 denotes the warhead, the internal structure of which is shown in cross section. Fig. 3 shows the scattering pattern extending over 360, i.e. there is no shielding effect and the entire outer surface of the warhead drives the fragments formed in all directions.

F.g. 7 is an enlarged cross section to make it more clear shows the inner parts and the three main parts that make up the Form warhead and that disintegrating into fragments outer unit 1, the inner unit 3 and the post-ignition ring 5, the is arranged in the rear of the warhead. The outer unit is inside for a more precise fragmentation prepared accordingly. The three parts are connected in the usual way such as by epoxy glue or other metal glue, which cause these parts to stick together during use. Rails desired, the warhead can through Can be combined into a unit using a conventional metal joining process.

8 and 9 show a ring and sector ignition which can be used in the warhead, the structural parts of the warhead always to the selected ignition system and of course in accordance with the fit aerodynamic stability requirements.

Fig. 5 is a cross section of a projectile case and a guide ring, the one in a common guide ring launcher

- 12 309886/0328

is used with appropriate dimensions for this floor. The circular projectile case guide ring has an outer housing 20, a housing 21 and an annular scale 22 which is aligned with the firing pin of the trigger mechanism of the firing device, not shown, and ignites the circular propellant charge 23, which develops sufficient force to keep the annular piston 24 moving which drives the ring 25, which is connected to the guide ring or projectile ring 26, which receives the warhead 27 according to the invention. The inner part 31 of the housing encloses the igniter, the propellant charge and part of the piston, so that when the piston moves forward, the warhead does not rotate within the guide ring when it moves in the barrel of the launching device (not shown). The guide ring has projections 29 and 28 (Fig. 4) - of _# which cooperate with the rifling portion of the barrel of the launcher as the sabot is propelled towards the muzzle of the launcher.

In use, the firing pin will hit the detonator directly, which in turn ignites the propellant powder. The lündpulver moves the piston forward, which gives the guide ring, which receives the projectile 27, the initial forward thrust * The guide ring engages in the swirl area along the barrel of the launcher * whereby the guide ring and the projectile be rotated. When the rotating guide ring leaves the launcher, act through the Swirl generated centrifugal forces on the in several places

309886/0328 - I ³ -

partially slotted front guide ring section and separate the guide ring together with the air resistance quickly from the projectile, which allows it to fly on its predetermined trajectory.

Although the guide ring has been shown and described, it should be noted that the present invention relates entirely to the projectile; other means of attainment the desired launch speed and the speed of rotation are envisaged and indicate, for example, anen integrated swirl area in the area of the maximum projectile diameter, this area being the streamlined cross-section is adapted. Other methods can have incised or grooved surfaces in the area of the maxiamlen Swirl surfaces are provided.

In that case, the projectile becomes according to the present invention Fired with a conventional propellant charge at subsonic speeds of more than ol m / sec and with rotational speeds that significantly exceed those of known comparable projectiles. The initial speed of rotation is always above 2,000 rpm lie. For specific sizes and applications, an optimal Spin based on flight dynamics analysis can be selected which includes parameters such as projectile mass, launch speed, flight range and deviation. While of the bullet's flight along its trajectory, the rotational movement creates a gyroscopic stability. The attitude of the Create the projectile along the trajectory and the wing shape

309888/6320

14 -

a buoyancy to partially counterbalance the force of gravity. This results in a flatter trajectory compared to the usual ballistic trajectory, if the projectile explodes, the forces occurring within the destructible surfaces cause the pre-notched outer surfaces to be split up Housing wall, resulting in an expulsion or ejection of small splinters with a high initial speed and to a Distribution of splinters leads. Destroy when using means as a payload for incapacitation this means the military target.

Assembly of the complete streamlined warhead illustrated in Figure 7 includes the connection of units 1 and 3, thereby forming a front part of hollow cross-section which is part of the streamlined Forms shape. This is followed by the filling of the cavity with the appropriate filling material 15, the arrangement of the ignition system, which includes the ignition amplifier, an ignition amplifier line, a striker and an igniter, and the attachment of the rear cross-section in the form of the post-ignition ring 4, whereby the rear end of the streamlined body is completed. So you get an integrated unit. Other structural arrangements and assembly techniques are of course for other ignition arrangements, e.g. for the types of ignition according to Figures 8 and 9.

The projectile can mean in the direction of the impact area a hand-held weapon, one off the shoulder or

309886/0328

- 15 -

vehicle-mounted weapon system or from a Airborne vehicle moving at low speed can be shot down.

The warhead is made of materials common to military equipment, such as steel, aluminum, magnesium, or alloys thereof. For use with certain substances such as o-chlorobenzylidene, malonitrile, a soft lidterial such as rubber or Weichplastiek be used to form the warhead * the guide GeschoßhUlse can of high-strength polytnerem material such as polyethylene or polypropylene "the GeschößhUlse can such as high-strength polyethylene or i ^J consist ölypröpylen of aluminum or other light .. material *.

It is also within the scope of the invention that the fragmentation part of the warhead has a spiral wound and notched wire, as is found in the known H-406 shell. It is found, however, that the use of the notched wire results in an outer surface of the inventive streamlined grenade which has the surface irregularities, whereby the aerodynamic properties are detected. The pre-formed fragments of the warhead are formed by pre-notching or engraving the inner surface of the unit 1 as shown in FIGS. whereby a smooth outer surface is obtained j to the desired aerodynamic properties leads>which; the required stability and flight range arise while getting the desired

988 6/0323 - io -

The size and shape of the fragments are determined.

The above description, including, for example, sizes and ranges, has essentially been directed to what is meant names ammunition directed against persons. As part of the Invention, however, is the use of these ammunition for the destruction of material, larger dimensions may be preferred. The invention also includes the use of the projectile as specific warheads, adapted for this as tiassenhercl or highly explosive plastic. line warheads do not have to be better than ordinary projectiles, such as shaped charges. To provide significant armor penetration capability for a warhead with shaped charge within a To obtain ring wing it would be necessary to have ring wing units with an outside diameter greater than 20 cm which leads to bulky sizes and increased weight. In comparison, this large circular wing project could not have the same penetration capacity as a regular projectile with shaped charge and the same weight.

- patent claims -

- 17 309886/0328

Claims (10)

PATENT CLAIMS Ij projectile characterized by a hollow closed, circular ring (27) surrounding a central open area, an ignition device (5,11,13) within the ring and filler material (15) in the ring which contacts the ignition device and is out of the group Highly explosive substances, incendiary materials and substances to be incapacitated are comprehensively selected, 2. A projectile according to claim 1 / characterized in that the closed circular ring (27) AASS during the flight to rotate about its axis of symmetry, this rotary body in the center of the axis of rotation. 3. Projectile according to claim 1, characterized gekennzd. chnet that the circular ring (27) a wing-shaped or streamlined body-shaped Has cross-section with a front and a rear section (1/3) and 5). 4. Projectile according to claim 3, characterized in that the front portion (l, 3) has a larger radius than the rear section (5). 5. Projectile according to claim 3 or 4, characterized in that that an inner surface (l) of the front section (l, 3) is preformed. - 18 309836/0 323 6. Projectile according to one of claims 1 to 5, characterized in that the ignition device has an igniter (7), one Detonator, a detonator line (II) and an ignition amplifier (13). 7. Projectile according to claim 6, characterized in that the front section (1,3) the detonator, the Zunderleitung (ll) and the ignition amplifier (13) and the rear section (5) accommodates the igniter (7). 8. Projectile according to one of claims 1 to 7, characterized in that the ring as a buoyancy body (in the form of a Ring wing formed with a thickness cross-sectional shape and after the conclusion of a launcher to achieve gyroscopic stability at a speed rotates at over 2000 rpm. 9. Projectile according to claim 8, characterized in that it has, in addition to a neutral stability, aerodynamic performance data that allow definable, repeatable, flat trajectories and a large flight range. 10. Projectile according to claim 8, characterized in that the wing cross-section makes up at least 25 % of the dimensions of the leg, so that there is an effective warhead. 309886/0328 L β e'rs e i t e