Bullet

Abstract

Projectile (1) with at least one projectile head (2) with a casing (3) and a tail section (4), wherein the projectile (1) has an interface for separating the projectile head (2) from the tail section (4), characterized in that locking grooves (12, 13) and inlet grooves (14, 15) are provided within the interface, and in that the locking grooves (12, 13) are designed to receive a locking cylinder (18), wherein the two inlet grooves (14, 15) stand one above the other and form a common inlet groove (17) for the locking cylinder (18).

Description

[0001] The invention relates to a strippable tail assembly, particularly for a full-caliber projectile. The invention concerns the ability to separate a tail assembly attached to the projectile head or warhead from the projectile head after or upon penetration of the warhead into the target, for example, a masonry structure. The entire tail assembly, including the tail assembly, is separated from the projectile head. The tail assembly is thus firmly anchored to the target or follows the projectile head later. The tail assembly can be a folding tail assembly or a rigid tail assembly.

[0002] In smoothbore ammunition fired from a smoothbore weapon, a full-caliber ammunition projectile has a tail fin for spin stabilization. This is usually a rigid or fixed tail fin or a folding tail fin. These are screwed into or onto a casing containing an explosive.

[0003] DE 26 23 582 C2 discloses a rocket projectile with a deployable tail assembly and sabot. The rocket projectile has a combustion chamber containing a solid propellant in its tail section, concentrically enclosed by a projectile wall. The combustion chamber opens into a nozzle with a jet outlet at the rear. In the area of ​​the jet outlet, the combustion chamber is tightly sealed with a detachable cover. Evenly distributed around the circumference of the projectile, tail assembly vanes are pivotally mounted in a pivot area around pivot axes arranged transversely to the projectile's longitudinal axis. When the cover is detachable, the tail assembly is deployed and locked in the launch position.

[0004] DE 693 06 462 T2 describes a folding tail assembly that deploys upon acceleration. The folding tail assembly, which has a folded state, can be deployed into an unfolded state solely due to the acceleration or inertial forces of the missile.

[0005] A tail-stabilized projectile can be found in DE 199 06 969 B4. The projectile is equipped with stabilizing fins whose center of gravity is radially offset from the fin pivot points when the tail is folded. The stabilizing fins are supported by sliding elements on the inner surface of the weapon barrel. After the stabilizing fins are deployed, the sliding elements are stripped off by the air forces acting on them.

[0006] A fin-stabilized projectile is known from DE 100 15 514 A1. The tail fins are arranged in a rearward-moving axial receiver in the rear of the projectile. After the projectile has left the barrel, the receiver can move rearward out of the tail section of the projectile until it reaches a stop under the pressure of the propellant gases remaining in a cavity. The fins, consisting of two fin sections, are then pivoted outward around a pivot axis mounted on the receiver.

[0007] DE 100 66 232 B4 proposes a tail-stabilized full-caliber explosive projectile with a projectile body and a tail support attached to the projectile body at the rear. In addition to a first guide strip, a second guide strip is arranged above a fuze receptacle. This measure allows the fuze to be housed in the tail section of the projectile body in a simple and cost-effective manner, preventing it from being fired.

[0008] A projectile with a fixed tail assembly is known from DE 10 2010 034 332 A1. The ammunition shown is characterized by its modular design. For this purpose, the propulsion system is equipped with a defined interface. This allows it to be used as training ammunition and as effective ammunition in real-world operations.

[0009] DE 10 2012 005 741 A1 describes a tail-stabilized full-caliber training projectile with a tubular tail assembly. The training projectile also includes a solid head section, to which the tubular tail assembly is attached at the rear. DE 10 2012 006 892 B3 also describes a tail-stabilized full-caliber training projectile.

[0010] To transfer the enormous launch forces, the rear section of the shell structure is very solid. This massive rear section prevents fragmentation in the direction of flight to the rear of the target. Even deliberately introduced structural fragments are intercepted by the solid rear section. Furthermore, in such full-caliber projectiles, the fuse is located in the rear section of the projectile head.

[0011] DE 10 2013 015 163 A1 discloses a course correction device for spin-stabilized projectiles. A connecting element and an adapter element are arranged between the projectile and a wing element.

[0012] DE 10 86 153 discloses an annular coupling element for missiles, which has an internal thread and an external thread. The coupling element is connected to the missile's payload nose via the internal thread, while the external thread is screwed to the missile's fuselage.

[0013] To secure the screw connection, a locking pin is provided to lock the screw connection between the coupling link and the fuselage in a desired position.

[0014] DE 30 17 380 A1 describes a fin-stabilized one-piece projectile with a predetermined breaking point designed as an annular groove.

[0015] FR 758 944 discloses a connection between a projectile body and a tail assembly by means of a locking pin. Further embodiments of two-part projectiles are known from DE 35 39 506 A1 and US 2004 / 0055502 A1.

[0016] The invention aims to remedy the above disadvantages.

[0017] This problem is solved by the features of patent claim 1. Advantageous embodiments are listed in the subclaims.

[0018] The invention is based on the idea of ​​separating the tail fin of a projectile from the projectile head after or upon penetration of the projectile head into the target, such as masonry. The idea is to separate the solid tail fin from the projectile head. The tail fin then remains firmly in place in the target or later follows the projectile head. This eliminates the solid tail fin after the projectile head impacts the target. The resulting structural fragments can be released unhindered to the rear.

[0019] The advantage is that when the explosive is detonated in the projectile head, the fragments are no longer intercepted to the rear. Especially during MOUT operations and the shelling of buildings, it is now possible to ensure that only a specific room or area within the building is targeted. This design minimizes the potential risk of destroying the entire building or floor.

[0020] This separation task is performed by a newly created interface. The interface can be provided between the tail section and the projectile head and is preferably implemented by a locking mechanism. When the projectile hits the target, the tail fins of a folding tail unit are deployed. If the tail unit is a rigid tail unit, its diameter is larger than the projectile diameter. After and upon penetration of the target, the solid tail unit is axially separated from the projectile head. The severed tail unit is then, for example, firmly embedded in the target. At the very least, the solid tail unit follows the projectile head in time.

[0021] Existing parts of the floor can be used to create the interface.

[0022] The projectile head comprises at least one casing, in which, in one exemplary embodiment, an explosive is stored. A detonator is preferably integrated into the tip of the projectile head and, in this embodiment, serves to initiate the explosive. A tail unit is attached to the rear of the warhead.

[0023] In a simple design, the interface can be integrated into a connecting area between the tail section and the shell of the missile head. For this purpose, a transfer part can be provided, which is located between the shell of the missile head and a tail section of the tail section.

[0024] To transmit the launch acceleration, the transmission part and the casing are preferably designed conically in their connecting zone. Locking grooves and inlet grooves are machined into this cone in both parts, for example, by milling. To create the connection, the transmission part and the casing are placed on top of each other so that the two inlet grooves are aligned. A locking cylinder, e.g., a locking bolt, is inserted or rolled over this inlet groove and inserted circumferentially into the locking grooves. Finally, this connection point is preferably cast.

[0025] When the projectile hits the target, the projectile head penetrates it. The tail section and transition section are decelerated significantly more rapidly. When the locking cylinder(s) break, the warhead and tail section, including the transfer section, separate axially. When the explosive is detonated, the energy is transferred to the bullet pack. The rearward-facing fragments of the design are no longer intercepted.

[0026] During launch acceleration, force is transferred via the two cones (transmission part, casing) of the locking mechanism in the connection zone. After leaving the barrel, the force transmissions reverse. At this point, at least one locking cylinder prevents both the transmission part from twisting toward the casing (spin absorption) and the transmission part from being stripped rearward due to aerodynamic forces.

[0027] A strippable tail assembly for a projectile, in particular for a full-caliber projectile, is proposed. In order to prevent the tail assembly or tail assembly section from reducing the rearward impact, it is proposed to provide an interface for separating the projectile head from the tail assembly section. The interface comprises a transition section. The projectile head comprises a casing for receiving the active mass, such as an explosive charge. The casing and the transition section, in turn, form the interface. The casing and the transition section are preferably conically designed or shaped in their common connection zone. Locking grooves and inlet grooves are provided within the interface. The grooves are formed on the outer circumference of the transition section or on the inside of the casing. The transition section has a thread that can be connected to a thread on the tail assembly section.The two entry grooves, positioned one above the other, form a common entry groove for a locking cylinder. The locking grooves, in turn, are congruent, so that they can accommodate the locking cylinder together. When the projectile penetrates a target, at least one of the locking cylinders breaks due to the deceleration of the rear unit or the tail section, separating the projectile head from the tail section. In the best case scenario, the tail section and transition section remain stuck in the target, while the projectile head can exert its effect in all directions.

[0028] The idea is also applicable to similarly mounted projectiles and is not limited to an explosive projectile or a training projectile with a tail unit.

[0029] The invention will be explained in more detail using an exemplary embodiment and drawing. It shows: Fig. 1 a representation of a missile with a tail unit, Fig. 2 a representation of a transition part from Fig. 1, Fig. 3 a sectional view of a shell made of Fig. 1, Fig. 4 a sectional view of Fig. 3, Fig. 5 a partial view of the shell from Fig. 1 with cutting information, Fig. 6 a sectional view BB from Fig. 5, Fig. 7 a sectional view CC from Fig. 5, Fig. 8 a sectional view DD from Fig. 6.

[0030] In Fig. 1 depicts a projectile 1, here an explosive projectile. The projectile 1 comprises at least a projectile head 2 with a casing 3 and a tail section 4. The casing 3, in turn, accommodates an explosive 19. The tail section 4 has a tail section 5 and a folding tail section 6 with tail fins 7. An interface 21 is arranged between the casing 3 and the tail section 4. The interface 21 uses a transition part 8 that connects the casing 3 of the projectile head 2 to the tail section 4. The transition part 8 has a thread 16 pointing towards the tail section 4. The transition part 8 and the tail section 5 of the tail section 4 can be mechanically connected to one another via the thread 16 ( Fig. 2).

[0031] The inner shape 11 of the casing 3 and the outer shape 10 of the transition part 8 are matched to form the interface 21. The casing 3 and the transition part 8 preferably have a conical configuration or shape in their common connection zone 9. Locking grooves 12, 13 and inlet grooves 14, 15 are provided in this connection zone 9. The grooves 12, 14 are introduced on the outer circumference of the transition part 8, the grooves 13, 15 on the inside in the casing 3 ( Fig. 2, Fig. 3). A locking cylinder 18, for example a bolt, is inserted into this.

[0032] Fig. 5 shows the inlet groove 15 in a sectional view from Fig. 4.

[0033] The Fig. 5-8 serve to better illustrate the principle of the strippable tail unit. Fig. 6 to 8 show the locking cylinder 18 in the locking position.

[0034] The transition piece 8 and the casing 3 are placed one above the other so that the two inlet grooves 14, 15 are aligned and form a common inlet groove 17, while the locking grooves 12, 13 are congruent. A locking cylinder 18 is rolled over this inlet groove 17 and inserted circumferentially into the locking grooves 12, 13. Finally, the entire assembly should be cast. Alternatively, the locking cylinder 18 can be inserted into the locking grooves 12, 13 at the beginning of assembly. Using a tool, the locking cylinder 18 can then be pushed into the locking position over the inlet grooves 14, 15.

[0035] If the projectile 1 strikes a target (not shown in detail), the projectile head 2 penetrates it. The extended tail fins 7 cause the tail section 4 to decelerate the projectile 1, with the tail section 4 and the transfer section 8 being decelerated significantly more. This force is sufficient to break the locking cylinder 18. When the locking cylinder breaks, the projectile head 2 and the tail section 4 separate with the transfer section 8. After the detonation of the explosive 19 in the projectile head 2, the energy from the detonation of the explosive is transferred to a ball pack 20. The rearward-facing structural fragments can now also act unhindered.

[0036] It goes without saying that two or more locking cylinders can also be used, provided the design is appropriate. It should be noted that all locking cylinders must be broken when penetrating the target. LIST OF REFERENCE SYMBOLS 1 floor 2 Projectile head, warhead 3 Shell bullet head 4 tail unit, tail unit part 5 Rear section 6 Folding tail unit 7 tail wings 8 Transition part 9 Connection zone 10 Outer shape transition part 11 Inner shape of cover 3 12 Locking groove, transition part 13 Locking groove, cover 14 Inlet groove, transition part (cylinder inlet) 15 Inlet groove, sleeve (cylinder inlet) 16 thread, transition part 17 Inlet groove, common 18 locking cylinders 19 Explosives 20 ball pack 21 Interface

Claims

[1] Projectile (1) with at least one projectile head (2) with a casing (3) and a tail section (4), wherein the projectile (1) has an interface for separating the projectile head (2) from the tail section (4), characterized by that locking grooves (12, 13) and inlet grooves (14, 15) are provided within the interface, and that the locking grooves (12, 13) are designed to receive a locking cylinder (18), wherein the two inlet grooves (14, 15) stand one above the other to form a common inlet groove (17) for the locking cylinder (18). [2] Projectile (1) according to claim 1, characterized by that the shell (3) and a transition part (8) form the interface (21). [3] Projectile (1) according to claim 2, characterized by that the inner shape (11) of the shell (3) and the outer shape (10) of the transition part (8) are coordinated with each other. [4] Projectile (1) according to claim 2 or 3, characterized bythat the casing (3) and the transition part (8) have a conical design in their common connection zone (9). [5] Projectile (1) according to one of claims 2 to 4, characterized by that the grooves (12, 14) are provided on the outer circumference of the transition part (8) and the grooves (13, 15) are provided on the inside of the casing (3). [6] Projectile (1) according to one of claims 2 to 5, characterized by that the transition part (8) has a thread (16). [7] Projectile (1) according to one of claims 1 to 6, characterized by that the locking grooves (12, 13) are congruent, such that they can accommodate a locking cylinder (18). [8] Projectile (1) according to one of claims 1 to 7, characterized by that it is a full caliber bullet. [9] Projectile (1) according to one of claims 1 to 8 characterized by that it is an explosive projectile. [10] Projectile (1) according to one of claims 1 to 8, characterized bythat it is a training projectile. [11] Projectile (1) according to one of claims 1 to 10, characterized by that the locking cylinder (18) can be inserted over the inlet grooves (14,15) and can be pushed into the locking grooves (12,13) in the circumferential direction.

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