ES3013736T3 - Projectile and method - Google Patents

Abstract

Projectile 1 with an active agent arrangement, wherein the active agent arrangement has a precharge 6 and a main charge 7, where the precharge 6 and the main charge 7 are separated along a flight direction 3 and the precharge 6 is arranged in front of the main charge 7 in the flight direction 3, where the main charge 7 is designed as a shaped charge and the precharge 6 is designed as a projectile-forming charge. (Automatic translation with Google Translate, no legal value)

Description

DESCRIPTION

Projectile and procedure

The invention relates to a projectile with the features of the preamble of claim 1. The invention also relates to an arrangement of effective means, in particular for the projectile, and to a method for bombarding a target.

The bombardment of hardened targets, particularly targets with reactive armor, is often carried out with multi-stage charges, for example, with tandem shaped charges. State-of-the-art ATGMs are known in this case, for example.

In tandem shaped charges, the time interval between the initiation of both charges is specified by the geometric distance, since a shaped charge (HL) requires a fixed distance to the target (Stand Off). For optimal effectiveness, the time interval is less than 1 millisecond. During this time, the protective plates of enemy reactive armor cannot leave the projectile's flight path quickly enough, resulting in interaction with the main shaped charge and a loss of performance.

EP 0249 678 A2 discloses an active body comprising a hollow charge with a jacket at the rear and a charge with a flat, projectile-forming jacket at an axial distance in front. Upon approaching a target to be engaged, the charges are fired one after the other, so that a projectile formed from one jacket becomes effective before a spike formed from the other jacket.

From document FR 2552870 A1, the following is known: Its technical field is warheads with multiple shaped charges. The warhead consists of a plate charge arranged in the front part of the warhead and capable of generating a longitudinal projectile with high velocity, and a shaped charge of the same caliber arranged along an axis behind the plate charge. This shaped charge ignites after the plate charge with a predetermined delay. Application: piercing simple, laminated, composite, or active armor.

An objective of the present invention is to provide a projectile that exhibits improved effect with respect to hardened targets and/or targets with reactive armor.

The objective is solved by a projectile with the characteristics of claim 1 and a method for bombarding a target with reactive armor with the characteristics of claim 12. Preferred or advantageous embodiments of the invention result from the dependent claims, from the following description, as well as from the attached figures.

A projectile with an effective means arrangement is proposed. The projectile is specifically designed for cannon weapons. For example, the projectile can be designed for firing by an automatic cannon or tank gun. In particular, the projectile forms a tank ammunition, for example a 120 mm, a 130 mm, or a 140 mm ammunition. The projectile is specifically designed for use against heavily armored targets, targets with reactive armor, and/or targets with an active protection system. The effective means arrangement is specifically designed as a tandem charge.

The effective means arrangement comprises a precharge and a main charge. The main charge and the precharge are arranged at a distance from each other in a flight direction of the projectile. The precharge is arranged in the flight direction in front of the main charge so that, during use and/or in the event of a projectile being fired, the precharge is directed toward the target. For example, the projectile has a nose and a tail, the nose being arranged forward in the flight direction and the tail rearward in the flight direction, with the precharge in particular being arranged in the nose region and the main charge in the tail region. In particular, the precharge and the main charge each comprise a detonating explosive, the detonating explosives being chemically and/or physically identical or different.

The main charge is designed as a hollow charge. In particular, the hollow charge has a conical or hemispherical metal casing, with the detonating explosive arranged around the metal casing. The metal casing is also specifically referred to as a jacket. The main charge is designed, for example, to penetrate armor. The metal casing is preferably made of a high-density, moldable material, for example, copper or uranium. The main charge is designed in particular to emit a spike from the metal casing during detonation, the main charge being arranged such that a flight direction of the spike is oriented in the same direction as the flight direction of the projectile. For example, the tip of the conical or hemispherical metal casing points in the opposite direction to the flight direction of the projectile. The main charge is specifically designed as a high-performance main charge. A special embodiment provides that instead of a hollow charge as the main charge, a projectile-forming main charge is used.

The precharge is designed as a projectile-forming charge. A projectile-forming charge is also called a P charge or EEP (explosively formed projectile). In particular, a projectile-forming charge forms armor-piercing ammunition. The precharge designed as a projectile-forming charge is designed to emit a projectile upon and/or by detonation of the precharge. The projectile is emitted, in particular, in the flight direction of the projectile. The projectile emitted by the projectile-forming charge is designed as an elongated yet compact projectile, in particular as a rifle projectile. The projectile-forming charge particularly has a metal jacket, the metal jacket preferably being designed in a parabolic or spherical shape. The metal jacket is specifically made of a high-density metal, for example, copper, tantalum, or steel.

The shaped charge is preferably configured to ignite at a distance of less than 4 caliber lengths in front of the target, while the projectile-forming charge is preferably configured to ignite at a distance of at least 50 caliber lengths in front of the target. In particular, the projectile is configured to ignite the precharge before the main charge, or the main charge and precharge are staggered over time.

The invention provides a projectile that can effectively engage heavily armored targets, for example, targets protected by reactive armor. The proposed projectile can be fired as a tandem charge, with the target's reactive armor being activated and neutralized by the projectile-forming precharge, and the main charge being used to penetrate the main armor. Using a projectile-forming charge as a precharge offers the advantage that the distance to the target can be increased. This makes it possible to position the projectile of the projectile-forming charge before an active target protection system can take effect. Attacks with two very fast, successive threats—a fast-moving projectile from the projectile-forming precharge and the ballistic residual projectile with the main charge—are difficult to defend against for an active protection system.

In particular, the invention is based on the practical application of using a projectile-forming precharge and a shaped charge in a projectile instead of two shaped charges as tandem charges. This has the advantage that the precharge can release potential reactive armor regardless of the distance from the target, so that the protective plates of the reactive armor cannot cause any reduction in penetration performance upon subsequent impact of the main charge.

The projectile has a support structure. The support structure is arranged in the flight direction between the main charge and the pre-charge. The support structure is designed, for example, to be screwed into and/or pinned to a casing of the projectile. The support structure can be designed as a metal and/or plastic support structure. Preferably, the pre-charge is connected to a front end of the support structure, while the main charge is preferably connected to a rear end of the support structure. One or more fuses can be arranged in particular on the support structure and/or in the region of the support structure. The purpose of the support structure is to protect the main charge from a bursting and/or fragmentation effect of the pre-charge. Furthermore, the purpose of the support structure is to partially absorb loads and/or acceleration forces from the forward portion of the projectile that occur when the projectile is fired and to relieve the outer shell.

For example, the support structure has a cone open toward the preload, with one tip of the cone directed in the direction of the main load. Preferably, an elongated tube is connected to the tip of the cone in the direction of the main load. Tubes are also referred to as tubular sections. In particular, an additional open cone can be connected to a rear end of the elongated tube, this cone being open toward the main load. In particular, the structures for forming the cone, the tubes, and/or the additional cone are part of the support structure.

It is particularly preferred when the support structure has through openings. The through openings are arranged, in particular, on the side of the support structure facing the preload. Specifically, the through openings are located in the region of the cone that is open to the preload. For example, the cone has a cone sleeve, with the through openings being arranged in the cone sleeve. Preferably, the through openings are arranged in the circumferential direction in the cone sleeve. The through openings are, for example, perforations, through holes, and/or holes. The through openings are designed and/or arranged to discharge and/or allow escape of a detonation pressure arising during detonation. In particular, the through openings are arranged to radially discharge the detonation pressure. This configuration is based on the idea of protecting the main charge by discharging the detonation pressure of the preload.

The projectile has a casing. The effective means arrangement is arranged in the casing. For example, the support structure is bolted or pinned to the casing. The casing has openings for the release of the detonation pressure in the event of a precharge detonation. In particular, the openings are arranged in the region of the support structure, especially in the region of the through openings in the support structure. The openings are preferably arranged in the circumferential direction around the direction of flight. The openings are, for example, bores, holes, and/or perforations in the casing. Preferably, the openings in the direction of flight are configured as slots.

In particular, the housing comprises closure elements. The closure elements are designed, in particular, in a first state to close the openings provided for the escape of the detonation pressure in the housing. The first state is, in this sense, the state before detonation and/or ignition of the precharge. The closure elements can be designed, for example, as a layer of plastic, in particular fiber-reinforced plastic, over the openings. Preferably, a controlled breaking point is provided between the closure elements and the housing, for example, a connection of the closure elements to the housing has perforations. The closure elements are designed, secured, and/or arranged such that the closure elements, through detonation pressure upon detonation of the precharge, release the openings in the housing and/or are ejected.

The projectile preferably has at least one detonation waveguide. The detonation waveguide is arranged, for example, in and/or within the region, also known as the front section, of the precharge. The detonation waveguide is designed and/or arranged to shape, influence, and/or adjust the projectile shape and/or projectile velocity of the projectile ejected from the precharge. In particular, the main charge may also have a detonation waveguide.

The projectile preferably has a target detection device. The target detection device is preferably arranged in a forward region of the projectile, in particular before the pre-charge, for example at the nose. In particular, the target detection device is configured to determine an ignition time of the main charge and/or pre-charge, and/or the target detection device is configured to ignite the main charge and/or pre-charge and/or initiate their ignition, for example in conjunction with an ignition device. In particular, the target detection device is configured to initiate the pre-charge for ignition at a distance of at least 50 caliber lengths.

In particular, the target detection equipment is configured to initiate ignition of the main charge at a distance of less than four caliber lengths. The target detection equipment comprises, for example, radar-based sensors and/or radar-based sensors.

The projectile comprises, in particular, an ignition device, the ignition device being designed as a central ignition device. The central ignition device is arranged between the main charge and the pre-charge. The central ignition device is designed, for example, as a mechanical, electromechanical, or electric fuse. The central ignition device is designed to ignite the pre-charge and the main charge, in particular to ignite them with a delay, in particular to ignite the main charge with a delay relative to the pre-charge. For example, the central ignition device has a pusher designed to release an auxiliary detonator on the tail side of the main charge for ignition.

One embodiment of the invention provides that the projectile has an ignition device, the ignition device having a first and a second fuse. The first fuse is designed for igniting the pre-charge, while the second fuse is designed for igniting the main charge. The first and second fuses are connected via a communication line, the communication line being, for example, an electric wire or cable. An ignition signal can be transmitted between the first and second fuses and/or vice versa via the communication line. The ignition signal is, for example, a current and/or voltage pulse.

A further embodiment of the invention provides that the projectile has an ignition device, the ignition device having an ignition control, a first and a second fuse. The first fuse is designed to ignite the pre-charge, the second fuse is designed to ignite the main charge. The first and second fuses are each connected to the ignition device. The ignition device is designed to ignite the first and second fuses. The ignition control is specifically designed as an electronic control system and comprises, for example, a processor and/or microchip. Preferably, the ignition control is coupled and/or connected via data transmission to the target detection device, the ignition control being designed to determine an ignition time for the first and/or second fuse.

The projectile preferably comprises a pyrotechnic separation system. The pyrotechnic separation system is arranged in particular between the main charge and the precharge, especially in the area of the support structure. The separation system is designed, based on a pyrotechnic detonation, to separate the projectile into at least, preferably exactly, two parts, one part comprising the precharge and one part the main charge.

The separation system is, for example, annular in design. In particular, the separation system forms a ring, in particular a ring section of the casing and/or around the casing. The separation system has a multitude of ignition points, the ignition points being designed specifically for the pyrotechnic separation of the projectile into at least two parts. The ignition points are arranged, in particular, in a circumferential direction around the direction of flight of the projectile.

Particularly preferably, the projectile has a warhead, wherein the target detection device, the pre-charge and/or the main charge are arranged wholly or partially in the warhead.

An effective means arrangement is designed specifically for and/or similar to the projectile described above. The effective means arrangement specifically forms a tandem charge. The effective means arrangement comprises a precharge and a main charge. The precharge is designed as a projectile-forming charge. The main charge is designed as a hollow charge. Alternatively, the main charge may be designed as a projectile-forming charge.

A further object of the invention is a method for bombarding a target, in particular an active target and/or a target with reactive armor. The method provides, in particular, bombarding the target with the projectile described above and/or with the effective means arrangement described above. The projectile is fired toward and/or in the direction of the target. The projectile has a flight direction. The method provides that a precharge designed as a projectile-forming charge is released and/or ignited, with a projectile emerging from this releasing and/or neutralizing reactive armor of the target. The release and/or ignition takes place, in particular, at a distance from the target of at least 50 caliber lengths. According to the method, the main charge is released, in particular with a time delay, with the ignited and/or released main charge penetrating the main armor of the target.

Other features, effects, and advantages of the invention are evident from the following description of a preferred embodiment of the invention, as well as from the accompanying figures. They show:

Figure 1 a sectional view of a projectile fragment;

Figure 2 schematic view of an example of a preload implementation;

Figure 3 schematic view of a further embodiment of a preload;

Figure 4 schematic example of a projectile;

Figure 5 detailed fragment of the projectile in Figure 4;

Figure 6 detailed fragment of a projectile with openings;

Figure 7 detailed fragment of a projectile with passage openings;

Figure 8 schematic embodiment of a 130 mm projectile;

Figure 9 projectile from Figure 8 after firing;

Figures 10, 11 and 12 examples of the implementation of ignition equipment;

Figure 1 schematically shows an exemplary embodiment of a fragment of a projectile 1 in a sectional view. The projectile 1 comprises a housing 2, the housing 2 being designed as a continuous envelope. In the fragment shown, the housing 2 is designed as a hollow metallic cylinder. The projectile 1 can be fired at a target by means of a cannon weapon. In this case, the projectile 1 follows a flight path, where a tangential vector in the flight path can characterize the flight speed. The projectile 1 in use flies along a flight direction 3; the flight direction 3 can define a front section 4 and a rear section, e.g., tail 5, of the projectile 1.

A preload 6 is arranged in the front section 4 and a main load 7 is arranged in the rear section 5. A support structure 8 is arranged between the preload 6 and the main load 7. The preload 6, the support structure 8 and the main load 7 are arranged within the housing 2.

The precharge 6 is designed as a projectile-forming charge. In this regard, the precharge 6 is arranged such that, if the precharge 6 is detonated, the resulting projectile is ejected in the flight direction 3, i.e., forward. For this purpose, for example, the precharge 6 has a parabolic shell 9, the parabola being open forward. When the precharge 6 is ignited, the armored target is first struck by the separated projectile, so that its active armor is released. It cannot leave the flight path of the projectile 1 until the main charge 7 impacts or this active armor is released.

The main charge 7 is designed as a hollow charge. In particular, the main charge 7 forms a high-performance charge. The main charge 7 is arranged such that upon detonation of the main charge 7, an ejected spike is ejected in the direction of the target, i.e., in the flight direction 3. For example, the main charge 7 has a conical casing, the cone being open in the flight direction.

The support structure 8 has two cone sections 10a, b, wherein the cone section 10a is open towards the precharge 6 and the cone 10b is open towards the main charge 7. The cones, in particular the cone apexes are connected by a tube section 11. The support structure 8 has the purpose on the one hand to support the projectile 1, but also to protect the main charge 7 before detonation and the detonation pressure of the precharge 6. For this purpose, through openings 12a are arranged on the lateral surface of the cone 10a, which guide a detonation pressure during detonation of the precharge 6 into an area between the tube section 11 and the casing 2 so that the detonation pressure cannot act completely on the main charge. The conical lateral surface of the cone 10b does not have any through openings 12a so that the detonation pressure discharged into the casing cannot pass through the main charge 7. In the casing 2 in the region of the tubular section 11 of the support structure 8, openings 12b are provided, where these are configured in the form of a slot and divert the detonation pressure diverted from the precharge 6 radially outside the projectile 1.

Figure 2 shows a fragment of an exemplary embodiment of a precharge 6. The precharge 6 is designed, for example, as a 120 mm charge P. The precharge 6 has a spherical or parabolic shell 9, which is surrounded by a detonating explosive. In addition, the precharge has a detonation waveguide 13. The detonation waveguide 13 is designed to optimize and/or improve the projectile shape and the projectile velocity. The detonation waveguide 13 is designed to generate an elongated, yet compact, projectile with a very high velocity, in particular to avoid low angles of attack during interaction with the target. For the 120 mm charge, the detonation waveguide 13 is designed as an isosceles trapezoid, the trapezoid widening in the flight direction.

Figure 3 shows an exemplary embodiment of a preload 6, where this preload 6 is configured as a 50 mm P charge. This preload, unlike the exemplary embodiment in Figure 2, has a detonation waveguide 13 which is not cut like a trapezoid in the direction of the support structure 8, but rather ends in a point against the direction of flight.

Figure 4 shows a schematic representation of a 120 mm ammunition as a tandem concept 14 with projectile 1. The dimensions and/or geometry are similar, for example, to multipurpose 120 HE projectiles with warhead 15. The projectile 1 can be fired in this case by means of a propelling charge 20 towards a target. By igniting the propelling charge 20, the projectile 1 is fired as a warhead itself.

The projectile 1 of Figure 4 is shown in a detailed fragment in Figure 5. A target detection device 16 is arranged on the warhead 15. The target detection device 16 is designed as a radar device for detecting the target and/or determining a distance to the target. For example, an ignition control is designed to determine an ignition time based on the distance and/or initiate ignition of the precharge 6 and/or main charge 7. Behind the target detection device 16 is the precharge 6, which is designed as a projectile-forming charge. The precharge 6 is designed with a caliber of 80 mm. Behind the precharge 6, the support structure 8 is connected, and an ignition device 17 is arranged in the region of the support structure 8. The ignition device 17 comprises a first fuse 18a and a second fuse 18b. The first fuze 18a forms an ignition chain in the direction of the precharge 6 for ignition of the precharge 6. The second fuze 18b comprises a pusher which is configured to release the auxiliary detonator 19 or the main charge 7.

Figure 6 shows a fragment of a projectile 1 in the region between the main charge 7 and the precharge 6. The casing or shell 2 is designed as a hollow cylinder in this region. Openings 12b are arranged in the region between the precharge 6 and the main charge 7 for discharging a detonation pressure from the precharge 6. The openings 12b are arranged in the circumferential direction around the hollow cylinder and are designed as slots in the flight direction 3.

Figure 7 shows the same section as in Figure 5, in which the housing 2 is shown transparently so that the support structure 8 and in particular the tubular section 11 and the conical section 10a are visible. Through openings 12a are provided in the cone sleeve of the cone 10a, which are arranged in the circumferential direction and conduct a detonation pressure arising from the detonation of the precharge 6 to an area between the tubular section 11 and the housing 2. From this area, the detonation pressure is discharged through the openings 12b.

Figure 8 shows an example of an ammunition concept in calibre 130. In contrast to the 120 mm calibre, in which the projectile 1 flies in one piece to the point of detonation, the 130 mm variant provides for a separation of the projectile 1 before the detonation of the pre-charge 6 in order to create sufficient distance between the impact of the projectile of the pre-charge 6 and the main charge 7. The ammunition concept provides for a propelling charge case in which a propelling charge 20 is arranged. By igniting the propelling charge 20 the projectile 1 is ejected and fired at the target.

Figure 9 shows the fired projectile 1 shown in Figure 7. A radar device is arranged on the nose of the projectile 1 as a target detection device 16. For reasons of radiation permeability, this part is made of foamed laminated material at the rear. Behind it is the preload 6, in this case an 80 mm preload, which is secured at the rear by a bolted support cage 21. A free space between the reinforcing ribs of the support body 8 is used to position and accommodate the ignition device. The firing of the front projectile part 22, or the separation of the front projectile part 22 from the rear projectile part 23, takes place by means of a separation unit 24. The separation unit 24 is annular in design and comprises four symmetrically distributed ignition points. When the ignition points are ignited, the inner ring is pushed out of the device like a piston against the front edge of the rear projectile casing until the outer casing of the front projectile part 22 finally tears at a defined separation point behind the casing connection point. The projectile parts 22, 23 are then accelerated away from each other by the ejection movement of the ring, guided by the circumference of the projectile heights, until the projectile 1 splits.

Figure 10 shows an exemplary embodiment of an ignition device 17 for the precharge 6 and the main charge 7. To save as much installation space as possible, the ignition device 17 is positioned between the two charges 6, 7. This essentially corresponds to a basic idea of projectile design: to separate the two charges as widely as possible, so that there is as little interaction as possible in the event of a detonation of the charges. This is important in particular so as not to destroy the tail end of the main charge when the precharge detonates, and to ensure the flight stability of the residual projectile. To initiate ignition, the ignition device 17 is configured to initiate ignition via an ignition signal generated, for example, by a proximity sensor. In the event of a fly-by or a malfunction of the proximity fuse, an impact switch is integrated into the fuse itself, which initiates ignition in the event of a mechanical collision.

The ignition device 17 in the charges 6 and 7 is to be ignited in a phased manner, with initiation taking place via a single central detonator. In the concept shown here, the pre-charge 6 is ignited via a conventional ignition chain 25. The main charge 7 in the tail region is initiated via an auxiliary detonator 26, which is activated by a shock coupling of a pusher element 27. With the aid of the pusher 27, the shaped charge can be positioned as far back as possible in the rear region such that no triggering element is required behind the shaped charge.

Figure 11 shows a further embodiment of an ignition device 17. The ignition device 17 has two independent mechanical fuses 18a and 18b. The fuse 18a is configured to initiate the pre-charge 6 and the fuse 18b is configured to initiate the main charge 7. Both fuses 18a, b are connected via a communication line 28, an ignition signal being able to be transmitted via this. For example, an ignition signal is transmitted to the fuse 18b for initiating the ignition of the fuse 18a via the communication line 28.

Figure 12 shows a third embodiment of an ignition device 17. The ignition device 17 has two fuses 18a, b and an ignition control 34. The ignition control 34 is designed as an intelligent fuse. The two fuses 18a, b can be set independently of the ignition control 29. The ignition control 29 is connected to the fuses 18a, b to initiate ignition. In particular, the ignition control 29 can be designed to ignite the fuses 18a, b in a phased manner.

List of reference symbols

1 Projectile

2 Housing

3 Flight direction

4 Front section

5 Tail

6 Preload

7 Main load

8 Support structure

9 Coating

10a, b Conic section

10 Tubular section

12th Passage opening

12b Opening

13 Detonation waveguide

14 Tandem Concept Munitions

15 Nose head

16 Target Detection Equipment

17 Ignition equipment

18a, b Wishbone

19 Auxiliary detonator

20 Propellant charge

21 Support cage

22 Front projectile part

23 Rear projectile part

24 Separation equipment

25 Ignition chain

26 Auxiliary detonator

27 Pusher

28 Line of communication

29 Ignition control

Claims (12)

1. Projectile (1) with an effective medium arrangement, wherein the effective means arrangement has a preload (6) and a main load (7), wherein the preload (6) and the main load (7) are spaced apart along a flight direction (3) and the preload (6) is arranged in the flight direction (3) before the main load (7), where the main charge (7) is configured as a hollow charge and the precharge (6) is configured as a projectile-forming charge, with a housing (2), wherein the effective means arrangement is arranged in the housing (2), wherein the housing (2) in an area between main charge (7) and precharge (6) has openings (12b) for the radial escape of a detonation pressure in case of detonation of the precharge (6), with a support structure (8) arranged in the flight direction (3) between the main charge (7) and the preload (6), wherein the support structure (8) distances the main charge (7) and the preload (6) from each other in the flight direction (3), the support structure (8) being arranged to protect the main charge (7) against a bursting and/or fragmentation effect of the preload (6) and to partially absorb the loads and/or acceleration forces of the front projectile part that occur when the projectile (1) is fired and to relieve the casing (2). 2. Projectile (1) according to claim 1, characterized in that the support structure (8) at one end directed towards the precharge (6) has passage openings (12a) for the escape of a detonation pressure in the event of a detonation of the precharge (6). 3. Projectile (1) according to one of the preceding claims, characterized in that the casing (2) has closing elements, the closing elements being designed and/or arranged to close the openings (12b) in a first state before the detonation of the pre-charge (6) and in a second state after the detonation of the pre-charge (6) are removed from the openings (12b) by a detonation pressure of the detonation of the pre-charge (6). 4. Projectile (1) according to one of the preceding claims, characterized in that the precharge has a detonation waveguide (13) for adjusting a projectile shape and/or a projectile velocity. 5. Projectile (1) according to one of the preceding claims, characterized by a target detection device (16), in particular for communication with an ignition device (17). 6. Projectile (1) according to one of the preceding claims, characterized by an ignition device (17), wherein the ignition device (17) is configured as a central ignition device (17) between main charge (7) and precharge (6). 7. Projectile (1) according to one of claims 1 to 5, characterized by an ignition system (17), where the ignition equipment (17) has a first fuse (18a) for the precharge (6) and a second fuse (18b) for the main charge (7), wherein the first fuse (18a) and the second fuse (18b) are connected by a communication line (28) to transmit an ignition signal. 8. Projectile (1) according to one of claims 1 to 5, characterized by an ignition system (17), wherein the ignition equipment (17) has an ignition control (29), a first fuse (18a) for the pre-charge (6) and a second fuse (18b) for the main charge (7), wherein the ignition control (29) for the ignition of the precharge (6) is connected to the first fuse (18a) and for the ignition of the main charge (7) to the second fuse (18b). 9. Projectile (1) according to one of the preceding claims, characterized by a pyrotechnic separation system (24) between main charge (7) and precharge (6). 10. Projectile (1) according to claim 9, characterized in that the pyrotechnic separation system (24) is configured to be annular and has distributed ignition points in the circumferential direction. 11. Projectile (1) according to one of the preceding claims, characterized by a warhead (15), wherein the effective means arrangement is arranged in the warhead (15). 12. Method for bombarding a target with reactive armor, wherein a projectile (1) is fired according to one of claims 1 to 11 in the direction of and/or towards the target, wherein the projectile-forming precharge (6) is released to activate and/or neutralize reactive armor of the target, wherein the main charge (7) is released to penetrate main armor of the target.