Missile and method of operating a missile

Abstract

The present invention relates to a missile (10) with a firing device (20) having several barrels (11) extending in the direction of a longitudinal axis (A) of the missile (10) and arranged inclined or skew relative to the longitudinal axis (A), wherein projectiles (12) provided with propellant charges (13) for ejection from the barrels (11) can be loaded into the barrels (20) and a method for operating such a missile (10).

Description

TECHNICAL AREA OF INVENTION

[0001] The present invention relates to a missile and a method for operating a missile. BACKGROUND OF THE INVENTION

[0002] Missiles designed to engage static or mobile targets can be equipped with fragmentation warheads. These have a poorly defined destructive range. Therefore, the use of fragmentation warheads carries the risk of collateral damage in the vicinity of the intended target area and thus does not allow for the spatially limited engagement of individual targets. SUMMARY OF THE INVENTION

[0003] Accordingly, it is an object of the present invention to provide a means of limiting the effect of a missile to a defined area of ​​effect.

[0004] The present problem is solved by a missile having the features of claim 1 and by a method for operating such a missile having the features of claim 9.

[0005] According to a first aspect of the present invention, a missile is provided which has a firing device comprising several barrels extending in the direction of a longitudinal axis of the missile and arranged inclined or skew relative to the longitudinal axis. The barrels can be loaded with projectiles which are provided with propellant charges for ejecting the projectiles from the barrels.

[0006] The term "skew" in the sense of the present invention is defined geometrically by the fact that the barrels are arranged in the firing device in such a way that the straight lines extending the barrels in three-dimensional space neither intersect nor run parallel to each other.

[0007] According to a further aspect of the present invention, a method for operating a missile according to the invention is provided. The method comprises: determining at least one target effective area of ​​the missile; determining an actual impact time of the missile in the target effective area; determining target impact points of the projectiles in the target effective area; calculating target ignition times of the propellant charges based on the actual impact time of the missile in the target effective area, the target impact points of the projectiles in the target effective area, geometric data of the firing device and / or ejection parameters of the projectiles; deriving target ignition time-dependent ignition signals; providing the target ignition time-dependent ignition signals in the control unit; and controlling the ignition of the propellant charges of the projectiles based on the target ignition time-dependent ignition signals.

[0008] It is an aspect of the present invention to provide a missile with a firing device that functions like a volley gun and comprises several barrels, each containing multiple projectiles that can be electronically detonated sequentially or simultaneously. The firing device thus enables a high rate of fire. It is provided that, during the missile's approach to a predetermined target or one detected during flight, the projectiles are fired shortly before impact. Thus, in operation according to the invention, the missile allows the effect of the missile and the projectiles to be limited to a defined area. If target objects are located within this area, they will be hit by at least one projectile with a certain probability. The smaller the target area and the more projectiles are fired, the higher the probability of a hit.The probability of a hit can be increased depending on the size of the target object, the size of the target area, and the number of projectiles. The missile according to the invention is suitable, among other things, for engaging individuals, groups of people, unmanned aerial vehicles (UAVs), naval drones, and other unarmored targets. Compared to conventional fragmentation warheads, the missile according to the invention allows for a local limitation of the effect, thus significantly reducing the risk of unintended collateral damage. Furthermore, the method according to the invention allows for scaling of the effect during missile operation by appropriately determining the spatial extent of the target effective area and deriving the target detonation times of the projectiles.The latter can be achieved by considering only the distance of the missile from the target area or by including flight-specific parameters of the missile as well as the geometric parameters of the firing device that influence the potential target area of ​​the projectiles. This allows the projectiles to be distributed in a small spatial area with high intensity or in a larger area with lower intensity. For example, when targeting a small, individual target within a small target area, the firing signals can be issued in such a way that all projectiles within a small radius around the targeted position are dispersed only shortly before the missile impacts the target area, with the target being hit by one or more projectiles.However, it is also possible to combat a group of targets in a larger area by appropriately defining the target effective area and deriving ignition signals for earlier projectile ejection, whereby the probability of hitting each individual target is lower, but overall there is a high probability that at least one of the targets will be hit.

[0009] According to one embodiment of the missile, the barrels are aligned at an angle of inclination of between 10° and 80° relative to the longitudinal axis, with the barrels being aligned at the same or different angles of inclination relative to the longitudinal axis. This advantageously ensures that the projectile leaves the barrel at an angle inclined to its flight path and, even when the missile is moving and its flight speed is taken into account, travels along a straight line defining the projectile's trajectory towards the intended point of impact after exiting the barrel.

[0010] According to one embodiment, the barrels can be arranged in several rows, in a ring-like fashion, around the longitudinal axis of the missile, and the projectiles can be ejected from the barrels sequentially or simultaneously. In addition to the aforementioned inclination, the barrels are thus also arranged rotated by a certain angle around the longitudinal axis of the missile, thereby achieving a high rate of fire, since the projectiles can be moved faster from the ring-like arranged barrels and along the same or closely spaced straight lines.

[0011] According to one embodiment, the barrels are arranged offset from each other in a circumferential direction of the missile. This advantageously supports better utilization of the installation space within the missile, resulting in benefits with regard to the missile's aerodynamics.

[0012] According to further training, the projectiles may have the same or different calibers. This allows for better utilization of space within the missile, resulting in advantages regarding the missile's aerodynamics. Furthermore, the resulting ability to select projectile calibers in a targeted manner improves the projectiles' accuracy and effectiveness.

[0013] According to one embodiment, the barrels have a cover that is designed to be lifted or pierced, particularly by the projectile. This protects the muzzle from dirt ingress and also provides aerodynamic advantages for the entire missile, as the closed barrels do not impair the missile's stability during approach to the target area. The cover can be designed as a simple film applied to the muzzle. Alternatively, the cover can be optimized for the missile's aerodynamics, for example, as a cap or sleeve, so that it further enhances the missile's flight stability during approach to the target.

[0014] According to one embodiment, the propellant charge of each projectile has a propellant quantity that defines the projectile's exit velocity from the barrel. This has the advantage that, by appropriately adjusting the propellant quantity and the type of the corresponding projectile, as well as its position relative to the missile's longitudinal axis, it is achieved that all projectiles, viewed across the entire firing device, exhibit an approximately identical exit or muzzle velocity upon exiting the barrel.

[0015] In a preferred embodiment, several projectiles can be grouped together, with each projectile or projectile group having its own propellant charge. Grouping individual projectiles together allows for the use of a single propellant charge to power several projectiles positioned in succession. This has the advantage that, as the number of available projectiles increases, the required installation space within the missile can be reduced.

[0016] According to one embodiment, the projectiles have a fragmenting charge or are designed as cluster ammunition. The cluster ammunition design has the advantage that the projectiles disperse, similar to a shotgun blast, and a large number of moving or stationary targets can be engaged more effectively. The feature that the projectiles split in flight, i.e., fan out similarly to the sabot of kinetic energy penetrators, intensifies the effect on the target. This is particularly advantageous for engaging single targets, as mentioned above.

[0017] According to one embodiment, the firing device includes a control unit for time-controlled ignition of the propellant charges. The control unit advantageously enables the sequential or simultaneous ignition of the propellant charges, allowing the projectiles to be precisely controlled in accordance with the missile's trajectory and its reaching the effective area, and enabling the corresponding control signals to be implemented in a manner consistent with operational requirements.

[0018] According to further training, the propellant charges have electronically controlled detonators, and the control unit is configured to issue time-controlled ignition signals to the detonators. This advantageously simplifies the integration of the propellant charge control into the overall missile control system.

[0019] In one embodiment of the method, determining the actual impact time of the missile within the target effective area is additionally or alternatively carried out by recording the actual flight path of the missile relative to the target effective area, the actual flight speed of the missile, and / or the actual geometric position of the missile relative to the target effective area. This enables a more accurate determination of the actual impact time of the missile within the target effective area and, from this, the derivation of more precise target ignition times and ignition signals, allowing for improved delimitation and focusing of the point of impact and the effect of the projectiles within the effective area.

[0020] In one embodiment of the method, the calculation of the target ignition times of the propellant charges is additionally based on the actual trajectory and the actual flight speed of the missile. This enables a more precise calculation of the target ignition times of the propellant charges and the derivation of the ignition signals, and allows for a further narrowing down of the target impact point of the projectiles within the effective area, thus focusing the projectile effect within that area.

[0021] In one embodiment of the method, the geometry data of the firing device include values ​​for an inclination of the barrels and an arrangement of the barrels relative to the missile longitudinal axis, and the ejection parameters include values ​​for a projectile-specific exit velocity from the barrels.

[0022] From the inclination of the barrels relative to the missile's longitudinal axis, the trajectory of each projectile ejected from the respective barrel can be calculated during target acquisition and with respect to impact on the effective area, and the respective ignition signal can be derived individually. This ensures that the projectiles' trajectories are aligned in such a way that they form curves of possible impact points within the effective area and, viewed from the outside of the missile, converge on the missile's point of impact. Based on the values ​​for the exit velocity and exit angle of the projectiles from the barrels, as well as their trajectory, the ignition point for each projectile can be calculated, so that each projectile from a barrel is fired when the missile reaches a specific distance from the effective area, in order to strike a specific point on this curve or within the effective area along the same trajectory.

[0023] According to one embodiment of the method, the at least one target effective area of ​​the missile is determined either before launch or during flight. This has the advantage that, knowing the type and area of ​​the target object, the approach angle and the missile's trajectory for reaching the effective area or an impact point located within the effective area can be predetermined. The effective area can be defined as the position of a stationary target object before the missile's flight begins, and the firing signals can be derived accordingly. Alternatively, the missile can detect the target area, for example, if it is equipped with an image processing device, with the at least one effective area being defined during flight to derive appropriate firing signals.

[0024] According to one embodiment of the method, the missile's trajectory and orientation relative to at least one target area are adjusted during flight. This has the advantage that the missile can perform flight maneuvers to assume an ideal position relative to the target area or the target object. This is particularly advantageous when engaging multiple targets sequentially along a trajectory, where, for example, projectiles have already been fired from individual barrels or barrel arrays, or when multiple targets are to be engaged in a flyby and not all barrels are pointing in the required direction, the missile's orientation is adjusted. For example, several distributed ground targets with multiple target areas defined by this method can be engaged sequentially in a flyby if the missile fires several projectiles in salvos and adjusts its flight attitude between each shot.By rolling, the missile aligns the still-loaded barrels towards the effective surfaces. The missile's movement is controlled either before flight or autonomously during flight, depending on the situation, either by the missile itself or remotely.

[0025] According to one embodiment of the method, at least one effective surface is congruent with a physical impact surface, or one or more effective surfaces can be defined offset relative to the physical impact surface. This advantageously allows the firing signals for multiple firing sequences or from multiple barrels to be coordinated when more than one effective surface is defined, ensuring that projectiles impact one or more of the effective surfaces. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The invention will now be explained with reference to the figures in the drawings. The figures show: Fig. 1 a schematic representation of a missile according to an embodiment of the present invention approaching a detected target; Fig. 2 a schematic representation of a section of a firing device of a missile according to an embodiment of the present invention; Fig. 3 a schematic representation of the projectile distribution in an effective area during operation of the missile according to an embodiment of the present invention; and Fig. 4 a flowchart of a method for operating a missile according to an embodiment of the present invention.

[0027] In the figures, the same reference symbols denote identical or functionally equivalent components, unless otherwise stated. DETAILED DESCRIPTION OF EXAMPLES OF THE INVENTION

[0028] Fig. 1 Figure 1 shows a schematic representation of a missile 10 according to an embodiment of the present invention approaching a detected target 15. The missile 10 comprises a firing device 20 equipped with a plurality of barrels 11 loaded with projectiles 12 and propellant charges 13 associated with the projectiles 12. The firing device 20 is shown in section in Figure 1. Fig. 2 A more detailed presentation.

[0029] The projectiles 12 are fired during the flight phase of the missile 10. Due to the missile 10's inherent velocity, a single projectile 12 does not leave the missile 10 at the angle at which the barrel 11 is inclined to the missile's longitudinal axis A (roll axis), but rather the muzzle velocity and the missile velocity add vectorially. The missile 10 generally strikes the target object 15 at a specific angle to the effective area 14. Fig. 1 In the illustrated embodiment, a vehicle to be struck is located. The projectiles 12 leave the missile 10 at an angle to the missile's trajectory 17. The barrels 11 are arranged in a ring around the circumference U of the missile 10 and simultaneously rotated by a specific angle about the missile's longitudinal axis A. Each projectile 12 has a curve 18 in which Figuren 1 and 3 represented as a straight line, which indicates the projectile trajectory 16 relative to the missile 10. For the projectiles 12 of a missile 10, this results in a family of curves that includes the individual curves of each projectile 12 and thus indicates the points of impact 19 of the projectiles 12 in the effective area 14.

[0030] In calculating the impact points 19 of the individual projectiles 12 on the target object 15 or on the effective area 14 defined by it, the inventive method for operating the missile 10 transforms a missile coordinate system, which is moved due to the flight motion of the missile 10, and a coordinate system of the target object 15 at the impact point 19' of the missile 10 into each other, and from this transformation determines the curves 18 of the projectiles 12. The curves 18 indicate at which points each projectile 12 can potentially hit the effective area 14. From this, an ignition signal for the propellant charges 13 is derived, which results from the distance from the launch point of the projectile 12 to the impact point 19 in the effective area 14. During the missile 10's approach, the distance of the missile 10 from the target object 15 decreases over time.By coordinating the ignition times of the projectiles 12, the possible impact points 19 of several projectiles 12 within the effective area 14 are arranged along a defined, identical curve 18. This ensures that, taking into account the flight path of the missile 10, several projectiles 12 strike different impact points 19 of the target object 15 within the target area. Each barrel 11 of the firing device 20 provided in the missile 10, and each projectile 12 loaded therein, thus results in a curve 18. All curves 18 lie within the effective area 14 and converge on the impact point of the missile 19'.

[0031] The geometric data of the firing device 20, which includes values ​​for the inclination of the barrels 11 and their arrangement relative to the missile's longitudinal axis A, and the projectile exit parameters 12, which include values ​​for propellant-charge-dependent and thus projectile-specific exit velocities, determine the respective ignition time of the propellant charges 13. From this, a corresponding ignition signal for the time-controlled ignition of the individual propellant charges 13 can be derived. The ignition signal determines at what time, i.e., at what distance from the point of impact 19, one or more projectiles 12 are fired simultaneously or sequentially from the same or different barrels 11 in order to strike a specific point on this trajectory 18 and thus the target object 15.

[0032] Fig. 2 shows a schematic representation of a section of a firing device 20 of a missile 10 (cf. Fig. 1 ) according to an embodiment of the present invention. The firing device 20 comprises several barrels 11, each loaded with projectiles 12 and the associated propellant charges 13. The barrels 11 are arranged in a ring or ring-like pattern around the circumference U of the missile 10. The barrels 11 extend in the direction of a longitudinal axis A of the missile 10 and may exhibit an inclination or geometrically defined skew with respect to the longitudinal axis A. The angle of inclination may, for example, be in the range of between 10° and 80° relative to the longitudinal axis A of the missile 10. Individual barrels 11 may be arranged such that they are aligned with the same or different angles of inclination relative to the longitudinal axis A.The missile 10, equipped with the barrel configuration shown here, thus has a firing device 20 that functions like a volley gun and enables the firing of multiple projectiles 12 from several barrels 11 by igniting the respective propellant charges 13 sequentially or simultaneously (electronically). A control unit 21 for outputting the ignition signals is associated with the firing device 20, the ignition signals being derived according to the invention and made available to the control unit 21. The firing device 20 thus enables a high rate of fire, the maximum rate being determined in particular by the time required for a projectile 12 and the subsequent combustion gases of the propellant charge 13 to exit the respective barrel 11. After this time, the next projectile 12 can already be fired from the barrel 11.It is provided that the ignition signals are derived in such a way that, during the approach of the missile 10 to a target 15, the projectiles 12 are fired from the individual barrels 11 in a defined sequence and temporal order shortly before impact with the target 15 and depending on the flight motion and trajectory 17 of the missile 10 and / or a movement of the target 15. In addition to the previously described inclination, the barrels 11 can also be arranged rotated by a specific angle around the longitudinal axis A of the missile 10. Furthermore, in embodiments, it can be provided that the individual barrels of a circumferential row are each offset from the next circumferential row in the circumferential direction of the missile 10, thereby providing an overall slimmer missile 10 with improved aerodynamics and increased flight stability due to better utilization of installation space. In the exemplary embodiment of the... Fig. 2 All projectiles 12 have the same caliber. In further embodiments, it can be provided that the projectiles 12 have different calibers in each barrel, which further improves the utilization of space in the missile 10 and its aerodynamics. In the exemplary embodiment, the individual barrels 11 have a cover 22, which is designed as a foil that is pierced by the first projectile 12 ejected. This protects the muzzles 23 against the ingress of dirt and simultaneously improves the aerodynamic behavior of the missile 10, compared to embodiments with open muzzles 23, up to the point of exit of the first projectile 12. It is also possible, but in Fig. 2 It is not shown that several projectiles 12 are grouped into projectile groups. Each projectile group is then assigned a propellant charge 13, which propels several consecutive projectiles 12, causing all projectiles 12 of a barrel 11 to be ejected successively in quick succession from the respective barrel 11.

[0033] Fig. 3 Figure 1 shows a schematic representation of the impact points 19, 19' of the projectiles 12 and the missile 10, transformed into the effective area 14, during operation of the missile 10 according to an embodiment of the present invention. Fig. 3 The area of ​​the target object 15, which defines the effective area 14, is indicated. The trajectory 17 of the missile 10 is chosen such that it strikes centrally within the effective area 14. The firing sequence of the propellant charges 13 of the individual projectiles 12 is coordinated so that they ignite along the area 14. Fig. 3 The curves 18 shown are controlled and arrive in the effective area 14 relative to the impact point 19' of the missile 10. The ignition signals of the propellant charges 13 are derived depending on the trajectory 17 and flight speed of the missile 10 and in coordination with the geometric parameters of the firing device 20 in order to concentrate the impact points 19 of the projectiles 12 of a barrel 11 within the effective area 14 and relative to the impact point 19' of the missile 10, thereby achieving a spatially limited, but highly effective effect on the target object 15.

[0034] The projectiles 12 are fired while the missile 10 is still in flight. Due to the missile 10's inherent velocity, a single projectile 12 does not leave the missile 10 at the angle at which the barrel 11 is inclined to the missile's longitudinal axis (roll axis) A, but rather the muzzle velocity and the missile velocity add vectorially. The missile 10 generally impacts the target area at a specific angle. The individual projectiles 12 leave the missile 10 inclined at an angle to the trajectory 17. Furthermore, the barrels 11 of the firing device 20 are arranged in a ring or ring shape around the circumference U of the missile 10, i.e., simultaneously rotated by a specific angle around the missile 10's longitudinal axis A.Taking into account the aforementioned geometric parameters of the firing device 20, the missile 10, the projectiles 12, and the intended effective area 14 in the target object 15, curves 18 for the projectiles 12 are derived. The ignition signals determine the firing sequence and the ignition timing of the projectiles 12 in the respective barrels 11. By coordinating the ignition timings, it is ensured that the projectiles 12 of a barrel 11 strike impact points 19 in the effective area 14 or in the target object 15, which are distributed along the corresponding curve 18 such that the intended effect can be achieved in the target object.

[0035] The individual projectiles 12, arranged sequentially in each barrel 11, are fired sequentially by igniting their respective propellant charges 13. All projectiles 12 are fired while the missile 10 is still in flight. Based on the known geometric data of all barrels 11 of the firing device 20, a family of curves is derived along which the projectiles 12 strike the effective area 14. The impact points 19 of all projectiles 12 within the effective area 14 can thus be determined across the entire firing device 20 and controlled depending on the trajectory 17 and flight speed of the missile 10. This ensures that the projectiles 12 strike the target object 15 with uniform distribution within a limited area defined for the target object 15.The ignition of the propellant charges 13 can be coordinated in particular such that the projectiles 12 are fired simultaneously or directly one after the other from barrels 11 that are opposite each other in circumference, in order to prevent disturbances to the missile 10 caused by the recoil of the projectiles 12.

[0036] Fig. 4Figure 1 shows a flowchart of a method for operating a missile 10 according to an embodiment of the present invention. The reference numerals given below refer to the elements described in connection with the preceding figures. In the method, a target effective area 14 of the missile 10 is determined in a first step S1. This is defined by the type and area of ​​the target object 15 and specifies the approach angle and the flight path 17 of the missile 10 for reaching the effective area 14 or an impact point 19' of the missile 10 located within the effective area 14. The effective area 14 can be defined before the start of the missile 10's flight, for example, with knowledge of the position of a stationary target object 15. Alternatively, the missile 10 can also actively perform flight maneuvers to assume an ideal position relative to the effective area 14 or the target object 15.This is particularly advantageous when engaging multiple targets sequentially along a flight path 17, where projectiles 12 have already been fired from individual barrels 11 or rows of barrels, or when multiple targets are to be engaged in flight and not all barrels 11 are pointing in the required direction. For example, various distributed ground targets with multiple defined effective areas 14 can be engaged in overflight by the missile 14 firing multiple projectiles 12 in salvos and, between each firing, aligning the still-loaded barrels 11 toward the other effective areas 14 by rolling. Alternatively or additionally, the missile 10 can be equipped with an image processing device that detects the target area and defines the effective area 14 during flight in order to derive corresponding firing signals later in the flight.

[0037] In step S2, the actual impact time of the missile 10 within the target effective area 14 is determined from the target effective area 14 defined in step S1. Step S2 can also include recording the actual flight path 17 of the missile 10 relative to the predefined or flight-dependent target effective area 14, as well as determining the actual flight speed of the missile 10. Alternatively or additionally, the actual geometric position of the missile 10 relative to the target effective area 14 can also be considered.

[0038] In step S3, the target impact points of the projectiles 12 within the target effective area 14 are determined from the parameters of the missile 10 recorded in step S2. If only the actual geometric position of the missile 10 relative to the target effective area 14 was determined in step S2, predefined standard values ​​are used for the actual flight path 17 and the actual flight speed.

[0039] In step S4, the target ignition times of the propellant charges 13 of the projectiles 12 are calculated based on the previously determined actual impact time of the missile 10, the known geometric data of the launching device 20, and the ejection parameters of the projectiles 12. This ensures that the projectiles 12 are ejected in the required sequence and spatial distribution at the most favorable time during the flight of the missile 10 in order to arrive at the effective area 14. In step S4, the target ignition times of the propellant charges 13 can also be calculated based on the actual trajectory 17 and the actual flight speed of the missile 10.

[0040] In the following step S5, ignition signals dependent on the target ignition time are derived, and in step S6 the ignition signals are provided in the control unit 21 of the firing device 20.

[0041] In step S7, the ignition of the propellant charges 13 of individual projectiles 12 or of projectile groups is controlled based on the target ignition-time-dependent ignition signals, and the projectiles 12 are ejected from the barrels 11 in such a way as to be guided along a curve 18 to the respective point of impact 19 in the effective area 14, in order to impact there simultaneously or at different times. In the case of various, distributed ground targets with thus defined multiple effective areas 14, which are, for example, engaged in an overflight, specific ignition signals are derived for each individual effective area 14 in order to control the projectile ejection during flight. An interruption of the ignition or firing sequence can also occur.

[0042] The derivation of the target ignition timing-dependent ignition signals and the control of the ignition of the propellant charges 13 based thereon do not necessarily require consideration of all the parameters described above or the execution of all steps. For example, within the scope of the invention, it can also be provided that, instead of the actual flight speed and the actual impact time of the missile 10 in the target effective area 14, the distance of the missile 10 from the target effective area 14 is determined and the target ignition times are controlled based on this parameter. Any error that might arise in the calculation of the target ignition times due to the absence of the actual missile speed should be small, especially at small inclination angles of the barrels 11 to the longitudinal axis A of the missile 10 and / or when using a standard value for the missile speed. REFERENCE MARK LIST

[0043] 10 Missile 11 Barrel 12 Projectile 13 Propellant 14 Effective area 15 Target 16 Projectile trajectory 17 Trajectory 18 Curve 19, 19' Impact point 20 Firing device 21 Control device 22 Cover 23 Muzzle A Missile longitudinal axis U Circumference S1 Step S2 Step S3 Step S4 Step S5 Step S6 Step S7 Step

Claims

1. Missile (10) with a firing device (20) having several barrels (11) extending in the direction of a longitudinal axis (A) of the missile (10) and arranged inclined or skew relative to the longitudinal axis (A), wherein projectiles (12) provided with propellant charges (13) for ejection from the barrels (11) can be loaded into the barrels (20).

2. Missile (10) according to claim 1, wherein the barrels (11) are aligned at an angle of inclination of between 10° and 80° relative to the longitudinal axis (A), wherein the barrels (11) are in particular aligned at the same or at different angles of inclination relative to the longitudinal axis (A), wherein the barrels (11) are in particular arranged in several rows, in a ring-like fashion, around the longitudinal axis (A) of the missile (10) and the projectiles (12) can be ejected sequentially or simultaneously from the barrels (11), wherein the barrels (11) are in particular arranged offset from each other in a circumferential direction of the missile (10).

3. Missile (10) according to any of the preceding claims, wherein the projectiles (12) have the same or different calibers in each run.

4. Missile (10) according to one of the preceding claims, wherein the barrels (11) have a cover (22), wherein the cover (22) is designed to be liftable or pierceable by the projectile (12).

5. Missile (10) according to any of the preceding claims, wherein the propellant charge (13) of each projectile (12) has a propellant charge quantity that defines an exit velocity of the projectile (12) from the barrels (11).

6. Flying object (10) according to any one of the preceding claims, characterized by the fact that several projectiles (12) can be grouped together to form projectile groups, with each projectile (12) or projectile group being assigned a propellant charge (13).

7. Missile (10) according to one of the preceding claims, wherein the projectiles (12) have a fragmentation charge or are designed as cluster munitions.

8. Missile (10) according to one of the preceding claims, wherein the firing device (20) has a control device (21) for time-controlled control of the ignition times of the propellant charges (13), wherein the propellant charges (13) in particular have electronically controllable detonators and the control device (21) is configured for time-controlled output of ignition signals to the detonators.

9. A method for operating a missile (10) according to any of the preceding claims, comprising: - determining at least one target effective area (14) of the missile (10); - determining an actual impact time of the missile (10) in the target effective area (14); - determining target impact points of the projectiles (12) in the target effective area (14); - calculating target ignition times of the propellant charges (13) based on the actual impact time of the missile (10) in the target effective area (14), the target impact points of the projectiles (12) in the target effective area (14), geometric data of the firing device (20) and / or ejection parameters of the projectiles (12); - deriving target ignition time-dependent ignition signals; - providing the target ignition time-dependent ignition signals in the control device (21); and - Controlling the ignition of the propellant charges (13) of the projectiles (12) based on the target ignition time-dependent ignition signals.

10. Method according to claim 9, wherein, when determining an actual impact time of the missile (10) in the target effective area (14), the determination of the actual impact time of the missile (10) in the target effective area (14) is additionally or alternatively provided by detecting an actual flight path (17) of the missile (10) relative to the target effective area (14), an actual flight speed of the missile (10) and / or an actual geometric position of the missile (10) relative to the target effective area (14).

11. Method according to claim 9 or 10, wherein when calculating target ignition times of the propellant charges (13) the calculation is additionally carried out on the basis of the actual flight path (17) and the actual flight speed of the missile (10).

12. Method according to any one of claims 9 to 11, wherein the geometry data of the firing device (20) comprise values ​​for an inclination of the barrels (11) and an arrangement of the barrels (11) relative to the missile longitudinal axis (A) and the ejection parameters comprise values ​​for an exit velocity of the individual projectiles (12) from the barrels (11).

13. Method according to one of claims 9 to 12, wherein the determination of at least one target effective area (14) is carried out before a launch of the missile (10) or during the flight of the missile (10).

14. Method according to one of claims 9 to 13, wherein an adjustment of the flight path (17) and an orientation of the missile (10) relative to the at least one target effective surface (14) is provided during flight.

15. Method according to any one of claims 9 to 14, wherein the at least one target effective surface (14) is congruent with a physical impact surface of the missile (10) or one or more target effective surfaces (14) are defined offset relative to the physical impact surface.

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