Launch device and method for discharging active elements

Abstract

The invention relates to a launch device (10) for discharging active elements (12) for protecting an object (O) and / or vehicle from missiles (P), wherein the launch device (10) has a launcher unit (16) for discharging fireable active elements (12), wherein the launcher unit (12) has multiple launcher segments (30) arranged adjacent to one another and pivotable relative to one another, wherein the launcher segments (30) each have a receiving space (38) extending along a discharge axis (36) for receiving and firing in each case at least one active element (12), wherein the launcher unit (16) has an actuating drive (46) by means of which the launcher segments (30) can be pivoted relative to one another such that the angle (α) enclosed by the discharge axes (36) of in each case adjacent launcher segments (30) can be set. The invention also relates to a method for discharging active elements (12) for protecting an object (O) and / or vehicle from missiles (P).

Description

[0001] Title: Launching device and method for distributing

[0002] active ingredients

[0003] Description

[0004] The invention relates to a throwing device for dispensing active agents having the features of the preamble of claim 1. Furthermore, the invention relates to a method for dispensing active agents having the features of the independent claim.

[0005] Launch systems or decoy launchers are used to protect vehicles or objects (protective object) against threats such as incoming enemy missiles by releasing agents that, for example, create a smoke screen or form a decoy target that appears more attractive to the enemy missile's homing system than the protective object (actual target) itself. Launch systems of this type are known from the state of the art and are available on the market. For example, the applicant can supply the MASS decoy system, which is usually used on ships, or the Rosy smoke protection system, which can be used on boats or land vehicles. These are so-called soft-kill systems, which are defense systems that neutralize a threat without destroying it.

[0006] Depending on the incoming threat (e.g., a sensor-guided missile, ballistic rocket, or projectile), launch systems fire single shots or so-called patterns of weapons to combat the incoming threat, i.e., to disrupt, distract, mask, or otherwise render harmless. To deliver a weapon, it is usually fired from the launch system using a propellant charge. Upon reaching a target position in space, the weapon then disassembles, explodes, or detonates.

[0007] A pattern, which is often aligned orthogonally to the incoming threat, can be composed of a row or array (rows and columns) of two or more weapons or munitions that must be deployed at a defined distance from each other. Gaps or overlapping effects must be avoided.

[0008] The effective area of ​​such a pattern can be viewed as a geometric shape made up of individual circular areas (one circular area per agent). These circular areas are created at the desired (target) position in space, depending on the agent, during disassembly, explosion, or detonation. In order to provide an effective pattern or decoy, the circular areas must, on the one hand, overlap slightly to prevent gaps between the circular areas elsewhere. Such gaps can reduce the protective effect. On the other hand, the overlap of the circular areas should not be too large to avoid unnecessarily reducing the overall effective area of ​​a pattern.

[0009] There are launching devices available on the market in which the chambers or receiving spaces in which the agents are arranged and from which the agents are fired are oriented parallel to each other (deployment axes of the receiving spaces parallel to each other). As a result, such launching devices must be readjusted when deploying agents (alignment in azimuth and / or elevation) in order to align a pattern of agents according to the incoming threat. In this case, each shot must usually be launched individually. Since the time available to combat a threat is very short (usually only a few seconds), each

[0010] Alignment process the time available to combat the threat .

[0011] In the MASS decoy system, the chambers or receptacles in which the active agents are arranged and from which the active agents are fired are angled to one another (deployment axes of the receptacles are angled to one another; "fanning"). This reduces the number and time required for alignment processes. Alignment processes cannot be avoided entirely because the fanning is optimized for a defined target distance of the active agents. At this distance, the overlap of the above-mentioned circular areas is optimal. At a shorter distance, the total effective area of ​​the pattern is reduced because the individual circular areas overlap too much. At greater distances, gaps form between the circular areas, which reduces the protective effect.To counteract this, the launching device must be realigned (aligned in azimuth and / or elevation) to deliver the missile into the gaps mentioned. Similar alignment procedures are necessary to optimally align the pattern at shorter distances.

[0012] The invention is based on the object of reducing aiming movements in launching devices and optimising the effect of weapons or ammunition such as decoys.

[0013] The invention solves this problem by a throwing device having the features of claim 1.

[0014] The launching device is designed and / or intended for deploying active agents to protect an object and / or vehicle from missiles, in particular for providing a decoy target from the deployed active agents. The launching device has a launcher unit for deploying fireable active agents (launched active agents).

[0015] The launcher unit has a plurality of launcher segments arranged adjacent to one another, in particular in a row, and pivotable relative to one another. The launcher segments, in turn, each have a receiving space extending along a deployment axis for receiving and firing at least one active agent. The launcher unit further has an actuator by means of which the launcher segments can be pivoted relative to one another, so that the angle formed by the deployment axes of adjacent launcher segments can be adjusted by driving the actuator.

[0016] The proposed launch system allows for a reduced time (time savings) to be achieved for deploying effective means against incoming threats, such as incoming enemy missiles. This is made possible by the fact that adjacent launcher segments or their deployment axes are not oriented in a fixed arrangement relative to one another, but can be pivoted relative to one another by means of an actuator. The orientation of the launcher segments relative to one another can thus be adjusted using the actuator ("variable fanning of the launcher segments").

[0017] If a specific distance is required between the missile, such as a decoy, and a protective object, a continuous concealing advance shot can be achieved with a single salvo of missiles by adjusting the angle of the launcher segments relative to each other ("variable fanning"). This is particularly useful against laser-guided threats (quick and reliable interruption of the line of sight between the approaching missile and the protective object is necessary).

[0018] If a range-adjustable munition is used as the active agent, the proposed launching device can be used to build up a decoy cloud with a salvo that is orthogonal to a specific aspect angle (direction of approach of the incoming missile), without the active agents or munitions that are furthest to the sides of the decoy cloud being in an area that is no longer relevant for the incoming missile or are outside the munitions range.

[0019] If the launch system has multiple launcher units, the adjustable launcher segments (variable fanning) can compensate for the different distances of the individual launcher segments from the target point of the decoy cloud. The resulting redundancies can, for example, compensate for partial loads of launcher units (complete construction of a decoy cloud is possible even if one of the launcher units is not fully loaded with ammunition).

[0020] The launcher segments of the launcher unit are designed to accommodate at least one active agent in the receiving space and to fire it along the deployment axis (only one active agent in the receiving space) or parallel to the deployment axis (several active agents arranged parallel to one another in one receiving space, e.g. in a magazine).

[0021] Within the scope of one embodiment, it is conceivable that the adjustable angle between adjacent thrower segments can also be 0 °, meaning that the thrower segments can therefore also be oriented parallel to one another in one alignment. This allows a large adjustment range to be achieved. In addition, the parallel alignment can be used to achieve a basic or starting position of the thrower segments in relation to one another (calibration). Within the scope of one possible embodiment, the actuator can be set up in such a way that the angles between adjacent thrower segments are identical in the deployment position. In other words, when the thrower segments are aligned in a deployment position, adjacent thrower segments can each enclose an identical angle with one another. Alternatively, the actuator can be set up in such a way that the angles between adjacent thrower segments in the deployment position differ from one another. For example, this is conceivable.that the angles between adjacent launcher segments increase outwards (i.e. towards edge launcher segments).

[0022] The actuator can have at least one electric, pneumatic or hydraulic motor that drives the launcher segments directly (gearless design) or each through a gear such that the launcher segments are pivotable or can be pivoted relative to one another (adjustment of the angle that adjacent launcher segments enclose with one another). The actuator can be designed such that one motor can drive all the launcher segments of a launcher unit. Alternatively, one motor can be provided per launcher segment, which drives the relevant launcher segment (number of motors and launcher segments per launcher unit identical).

[0023] Measures for controlling motors and for calculating optimal angles to one another are known to the person skilled in the art. For example, reference is made to DE 10 2015 002 737 A1. Within the scope of a preferred embodiment, the launcher segments can be pivoted or can be pivoted by a drive of the actuator from a starting position, in which the deployment axes of adjacent launcher segments are oriented parallel to one another or enclose a first angle with one another, into a deployment position in which the deployment axes of adjacent launcher segments enclose a second angle with one another. This enables a targeted transfer of the launcher segments from a starting position

[0024] (Ready position) into a deployment position in which active agents are deployed. Typically, the first angle and the second angle differ from one another. For example, the second angle can be greater than the first angle. The first angle can also be a = 0° (parallel orientation of the deployment axes in the starting position).

[0025] Advantageously, the launcher segments can each be mounted on the launcher unit, in particular on a support element of the launcher unit or the actuator, so as to be pivotable about a pivot axis, wherein the pivot axes are each oriented parallel to one another. This facilitates precise alignment of the launcher segments, since the pivot axes each have the same orientation. Specifically, the launcher unit can have a support element on which the launcher segments are each mounted so as to be pivotable about a pivot axis. The support element can also form an interface to a directional drive of the launching device, as will be explained further below.

[0026] The throwing device advantageously has a

[0027] Launcher base with a directional drive, wherein the launcher unit is coupled to the launcher base via a mechanical interface, in particular the above-mentioned carrier element of the launcher unit, in such a way that the launcher unit can be directionalized in azimuth and / or elevation relative to the launcher base by driving the directional drive. This enables targeted directional or alignment of the launcher unit in accordance with an approaching missile.

[0028] In a preferred embodiment, the launching device can be configured in such a way, in particular by configuring a control unit of the launching device which controls the aiming drive and the actuator, that the aiming drive and the actuator can be driven simultaneously or in an overlapping manner. This enables particularly time-efficient alignment of the launcher unit, since the launcher segments can also be pivoted relative to one another (adjusting the fanning of the launcher segments) simultaneously or in an overlapping manner with the aiming of the launcher unit. For example, a salvo of two or more active agents can be emitted, in particular a number of active agents which corresponds to the number of launcher segments present in the launcher unit, wherein no aiming process (no drive of the aiming drive) and / or no adjustment process (no drive of the actuator) takes place during the discharge of the salvo.

[0029] Specifically, the receiving chamber can be configured to directly accommodate the active agent to be fired. This contributes to a compact design of the launching device with a small number of components. The active agent can be accommodated or stored directly in the receiving chamber, in particular without a magazine. The central longitudinal axis of the active agent and the deployment axis of the receiving chamber can be congruent with one another. The proposed design makes it possible to provide a compact smoke protection system with fireable smoke grenades (e.g., with a caliber of 40 mm) as the active agent.

[0030] In a preferred embodiment, the receiving space can be configured to accommodate a magazine in which two or more fireable active agents can be or are arranged. This makes it possible to provide a launcher unit with a higher capacity for active agents. In addition, the use of magazines makes handling easier (no need to handle individual active agents). Furthermore, faster reloading of the launcher unit is promoted. The magazines can, for example, be configured to accommodate two to four active agents. The deployment axis and the central longitudinal axis of the active agents, which are preferably arranged parallel to one another in the magazine, are oriented parallel or congruent to one another. The proposed embodiment makes it possible to provide a decoy launcher with fireable grenades (e.g. caliber 81 mm), in particular smoke grenades, as the active agent.

[0031] The launcher unit can advantageously have four to twelve, preferably six to ten, more preferably eight or ten, launcher segments. In principle, a different number of launcher segments is conceivable on one launcher unit. In order to be able to deploy several active agents simultaneously, at least four launcher segments should be present. For large objects and / or vehicles to be protected, six, eight, ten or twelve launcher segments per launcher unit are suitable. As already indicated above, the launcher segments are preferably arranged adjacent to one another in a row.

[0032] The mechanical interface of the launcher unit can expediently define a reference plane, with the pivot axes of the launcher segments being oriented orthogonal or parallel to the reference plane. This makes it possible to provide the ideal fanning depending on the intended use. The reference plane can in particular be arranged on the underside of the launcher unit. With an orthogonal orientation of the pivot axes to the reference plane, the launcher segments can be pivoted parallel to the azimuth axis ("azimuth fanning"). The launcher segments are then arranged next to one another with respect to the reference plane. Alternatively, with a parallel orientation of the pivot axes to the reference plane, the launcher segments can be pivoted parallel to the elevation axis ("elevation fanning"). The launcher segments are then arranged one above the other with respect to the reference plane.

[0033] As already explained above, the active agents in question are fired active agents (firing active agents). These active agents are, in particular, cartridge-loaded ammunition from which a projectile or missile can be fired from the receiving chamber after initiation of a propellant charge.

[0034] Specifically, the effective means can be designed as grenades (e.g., smoke grenades), decoys (multispectral decoys), or launchable drones (e.g., multicopters enclosed in a transport case). These can achieve the desired protective effects depending on the intended use.

[0035] The problem mentioned at the outset is also solved by a method having the features of the independent claim.

[0036] The method is designed and intended for deploying active agents to protect an object and / or vehicle from missiles, in particular by means of a launching device having one or more of the aspects described above.

[0037] The method provides that following detection of an approaching enemy missile, a launcher unit of a launch device is directed in azimuth and / or elevation (directing process for setting a deployment orientation). Overlapping in time or simultaneously with this directing process (directing from a starting position if necessary), launcher segments of the launcher unit are pivoted relative to one another in order to set an angle which the deployment axes of adjacent launcher segments enclose with one another (setting a deployment position). A salvo of two or more active agents is then deployed, for example to create a smoke screen or to form a decoy target which appears more attractive to the homing system of an enemy missile than the object and / or vehicle to be protected (actual target) itself.

[0038] To avoid repetition, reference is made to the relevant information on the launching device regarding the advantages achievable with the method. The measures described in connection with the launching device and / or those explained below may serve to further refine the method.

[0039] In a preferred embodiment, the salvo of two or more agents can be fired without any directional movement of the launcher unit and / or without any angle adjustment of the launcher segments. This promotes rapid deployment of agents, increasing the likelihood that the deployed agents will achieve the intended protective effect.

[0040] Specifically, the missiles can be deployed simultaneously or sequentially during the salvo. This allows for targeted deployment of the missiles to deploy a protective measure, such as a smokescreen or decoy, depending on the approach direction of the enemy missile.

[0041] Optionally, after deploying a salvo of missiles, the launcher unit can return to its initial orientation (azimuth and / or elevation) and / or to its initial position (angle of adjacent launcher segments relative to each other). If another approaching missile is detected, it can be aimed again and the angles of adjacent launcher segments (fanning) can be adjusted.

[0042] The invention is explained in more detail below with reference to the figures, wherein identical or functionally similar elements are provided with identical reference numerals, but possibly only once. They show: Fig. 1 shows an embodiment of a throwing device with a launcher unit in a schematic front view;

[0043] Fig. 2 is a schematic, partially sectioned view of the launcher unit along the section axis I I- II in Figure 1, with the launcher segments in the starting position;

[0044] Fig. 3 is a schematic, partially sectioned view of the launcher unit analogous to Fig. 2, with the launcher segments now in deployment position;

[0045] Fig. 4a shows a schematic plan view of a possible arrangement of deployed agents at different firing distances with a launching device according to the state of the art (rigid fanning);

[0046] Fig. 4b is a schematic view of a possible arrangement of active agents along an axis with a throwing device according to the prior art (rigid fanning);

[0047] Fig. 5a shows a schematic plan view of a possible arrangement of deployed agents at different firing distances with a launching device according to the invention (variable fanning); and

[0048] Fig. 5b shows a schematic view of a possible arrangement of active agents along an axis with a launching device according to the invention (variable fanning). Figure 1 shows an embodiment of a launching device in a schematic front view, the launching device being designated overall by reference numeral 10.

[0049] The launching device 10 is used to deploy launchable active agents 12 to protect an object or vehicle from enemy missiles. The launching device 10 has a launcher base 14 and a launcher unit 16 for deploying the active agents 12. The launcher base 14 is attached to the object and / or vehicle to be protected, e.g., to a ship's deck 20, by fastening elements 18.

[0050] The launcher unit 16 is coupled to the launcher base 14 via a mechanical interface 22. The mechanical interface 22 can, for example, be designed as a support element 23. The launcher base 14 also has a directing drive 24. The launcher unit 16 is coupled to the launcher base 14 via the mechanical interface 22 such that the launcher unit 16 can be directed in azimuth (pivot axis 26) and / or elevation (pivot axis 28) relative to the launcher base 14 by driving the directing drive 24. The design of a directing drive 24 is known to the person skilled in the art and is only indicated here.

[0051] The launcher unit 16 has a plurality of launcher segments 30 arranged adjacent to one another in a row and pivotable relative to one another. In the present case, the launcher unit 16 has six launcher segments 30 purely by way of example. As explained above, the launcher unit 16 can however also have more than six launcher segments 30, for example eight, ten or twelve launcher segments 30. The launcher segments 30 are each mounted on the launcher unit 16 so as to be pivotable about a pivot axis 32, wherein the pivot axes 32 are each oriented parallel to one another. Specifically, the launcher segments 30 can each be pivotably mounted on the support element 23. Alternatively, the launcher segments 30 can each be pivotably mounted on the actuator 46.

[0052] The mechanical interface 22 defines a reference plane 34, wherein the pivot axes 32 of the launcher segments 30 in the example are oriented orthogonally to the reference plane 34. Relative to the reference plane 34, the launcher segments 30 are arranged side by side (cf. Fig. 1).

[0053] The launcher segments 30 each have a receiving space 38 extending along a deployment axis 36 for receiving and firing at least one active agent 12 (cf. Fig. 2). The receiving space 38 is along the

[0054] The deployment axis 36 is opened at the front in the firing direction so that an active agent 12 can be fired out of the receiving space 38.

[0055] In principle, direct accommodation of an active agent 12 in the accommodation space 38 is conceivable, as explained above. In the present case, however, the accommodation space 38 is designed to accommodate a magazine 40 in which, in the example, two fireable active agents 12 are arranged. The central longitudinal axes 42 of the active agents 12 are oriented parallel to one another (central longitudinal axis 42 is shown together with dispensing axis 36 for reasons of clarity). As explained above, the accommodation space 38 and the magazine 40 can be designed to accommodate more than two active agents 12, for example three or four active agents 12.

[0056] The launcher unit 16 has an actuator 46 by means of which the launcher segments 30 can be pivoted relative to one another, so that the angle a, which the deployment axes 36 of the launcher segments 30 respectively enclose with one another, can be adjusted.

[0057] As explained above, various configurations are conceivable for the actuator 46. In the example, the actuator 46 comprises an electric motor 48 that drives a gear 50, via which the individual launcher segments 30 can be pivoted relative to one another.

[0058] The launcher segments 30 can be pivoted by a drive of the actuator 46 from an initial position, in which the deployment axes 36 of adjacent launcher segments 30 each enclose a first angle α with one another (cf. Fig. 2), into a deployment position in which the deployment axes 36 of adjacent launcher segments 30 enclose a second angle α with one another (cf. Fig. 3). This provides a variable or adjustable fanning of the launcher segments 30.

[0059] In the example, the launcher segments 30 in the starting position (cf. Fig. 2) each enclose an angle a of a = 0 ° with one another. In other words, the launcher segments 30 are oriented parallel to one another in the starting position. However, the angle a can also be a > 0 ° in the starting position (deployment axes 36 enclose an angle of a > 0 ° with one another in the starting position). In the deployment position (cf. Fig. 3), in which the active means 12 are fired, the deployment axes 36 of adjacent launcher segments 30 enclose a (second) angle cd with cd > 0 ° with one another. The angle cd and the angle a differ from one another in the present case, with the angle cd being greater in absolute value than the angle a (also conceivable in the reverse constellation).

[0060] In order to launch an agent in the direction of an approaching enemy missile, a pointing process (driving the pointing drive 24) and an adjustment process (driving the actuator 46) are usually required.

[0061] In the example, the launching device 10 is configured such that the driving of the directional drive 24 and the actuating drive 46 can occur in an overlapping or simultaneous manner. This can be achieved, for example, by appropriately configuring a control system of the launching device 10 that controls the directional drive and the actuating drive.

[0062] As explained above, various active agents 12 can be used. In this example, the active agents 12 to be fired are designed as multispectral decoys. Multispectral decoys allow all relevant spectral ranges (radar, infrared, ultraviolet, electro-optical, laser, and visible light) to be covered with a single system.

[0063] The throwing device works as follows:

[0064] The method provides that, as a result of detection of an approaching enemy missile, the launcher unit 16 of the launching device 10 is directed in azimuth and / or elevation, in particular starting from an initial orientation (direction process by driving the direction drive 24 to set a deployment orientation).

[0065] Overlapping in time or simultaneously with this straightening process, in particular starting from a starting position (cf. Fig. 2), the launcher segments 30 of the launcher unit 16 are pivoted relative to one another in order to set an angle cd which the deployment axes 36 of adjacent launcher segments 30 enclose with one another (setting a deployment position; cf. Fig. 3).

[0066] After this, a salvo of two or more active agents or decoys 12 is deployed, for example to create a smoke screen or to form a decoy target which appears more attractive to the targeting system of an enemy missile than the object and / or vehicle to be protected (actual target) itself.

[0067] The deployment of the salvo of two or more active agents 12 preferably takes place without any directional movement of the launcher unit 16 and / or without any angular adjustment of the launcher segments 30. When deploying the salvo, the active agents 12 can be deployed simultaneously or sequentially.

[0068] Optionally, the launcher unit 16 can return to an initial orientation and / or initial position after deploying the salvo of missiles 12. If another approaching missile is detected, another alignment process and adjustment of the angles of adjacent launcher segments can be performed. As explained above, the actuator 46 can pivot the launcher segments 30 relative to one another. The fanning of the launcher segments 30 relative to one another is thus adjustable (variable fanning).

[0069] Figure 4a shows in a schematic plan view a possible arrangement of deployed active agents 12' at different firing distances A, B, C, D with a launching device according to the prior art, in which the orientation of the launcher segments to one another is fixed (rigid fanning).

[0070] Figure 4a shows an object 0 to be protected, which in the example is a ship. The arrow T indicates the direction of flight of an approaching enemy missile P. The reference axis R is aligned orthogonal to the direction of flight T of the missile P, and therefore forms an angle of 90° with it. A launcher unit (not shown in detail) is arranged on the ship, which can launch a salvo of missiles 12', wherein no communication is sent from the launcher unit during the launch of the salvo.

[0071] Also shown is a possible arrangement of deployed active means 12' at different firing distances A, B, C, D, wherein the respective firing distances are marked by lines parallel to the reference axis R. The deployed active means 12' can, in their entirety, form a decoy target or a smoke screen at the respective firing distance.

[0072] At firing distance A, the deployed weapons 12' are arranged sufficiently close together so that there are no gaps that could jeopardise the effectiveness of the decoy or the smoke screen.

[0073] Due to the fixed orientation of the launcher segments relative to each other (rigid fanning), gaps become increasingly larger with increasing firing distances B, C, and D. Introducing 12' active devices into these gaps would require communication from the launcher unit (which requires additional time). There is a risk that the 12' active devices' protective measures (smoke screen or decoy) will be reduced or that the protective measures may be ineffective.

[0074] Figure 4b shows a schematic view of a possible arrangement of deployed active agents 12' along an axis with a launching device according to the prior art, in which the orientation of the launcher segments to one another is fixed (rigid fanning).

[0075] Figure 4b symbolically shows a launcher unit 16' according to the prior art, by means of which eight active agents 12' can be deployed in a row and as a salvo, each of which is shown by means of the firing lines 1 to 8.

[0076] The arrow T indicates the direction of flight of an approaching enemy missile P. The decoy line X is aligned orthogonal to the direction of flight T of the missile P and therefore forms an angle of 90° with it. The decoy line X is a line which represents the width of the desired decoy effective against the missile P. The point M symbolizes the center of the decoy. As a result of the rigid fanning out, the deployed active agents 12' on lines of fire 6, 7 and 8 would be outside the desired decoy or outside the desired cloud. Thus, as a result of the rigid fanning out around the direction of fire, only a limited number of active agents 12' can be deployed with their range perpendicular to an aspect angle (direction of the approaching missile). In addition, considerable gaps already arise between lines of fire 4 and 5, which jeopardize the effectiveness of the protective measure.

[0077] Figure 5a shows, in a schematic view which largely corresponds to the representation in Figure 4a, a possible arrangement of deployed active agents 12' at different firing distances A, B, C, D with a launching device 10 according to the invention, in which the orientation of the launcher segments 30 relative to one another is adjustable (variable fanning).

[0078] Due to the variable fanning of the launcher segments 30, any gaps can be kept small at all firing distances A, B, C, D. Due to the adjustable fanning (narrower compared to the embodiment in Figure 4a), a sufficient number of deployed active agents 12' are located next to one another at each firing distance A, B, C, D, so that a cloud of deployed active agents 12' or a decoy target can be built up at each of these firing distances.

[0079] Figure 5b shows, in a schematic view which largely corresponds to the representation in Figure 4b, a possible arrangement of deployed active agents 12' along an axis with a throwing device 10 according to the invention, in which the orientation of the throwing segments 30 relative to one another is adjustable (variable fanning).

[0080] Due to the variable fanning of the launcher segments 30, gaps between deployed active agents 12' can be kept small. Due to the adjustable fanning (narrower compared to the embodiment in Figure 4b), all firing lines 1-8 form intersection points with the apparent target line X, so that all deployed active agents 12' corresponding to firing lines 1-8 would be located within the desired apparent target or within the desired cloud.

Claims

Patent claims 1. Launching device (10) for deploying active agents (12) for protecting an object (0) and / or vehicle from missiles (P), wherein the launching device (10) has a launcher unit (16) for deploying fireable active agents (12), characterized in that the launcher unit (12) has a plurality of launcher segments (30) arranged adjacent to one another and pivotable relative to one another, wherein the launcher segments (30) each have a receiving space (38) extending along a deployment axis (36) for receiving and firing at least one active agent (12), wherein the launcher unit (16) has an actuator (46) by means of which the launcher segments (30) can be pivoted relative to one another, so that the angle (α) which the deployment axes (36) of adjacent launcher segments (30) each enclose with one another is adjustable.

2. Throwing device (10) according to claim 1, characterized in that the thrower segments (30) can be pivoted by a drive of the actuator (46) from an initial position in which the deployment axes (36) of adjacent thrower segments (30) are each oriented parallel to one another or enclose a first angle (α) with one another, into a deployment position in which the deployment axes (36) of adjacent thrower segments (30) enclose a second angle (α') with one another.

3. Throwing device (10) according to claim 1 or 2, characterized in that the launcher segments (30) are each mounted on the launcher unit (16), in particular a carrier element (23) of the launcher unit (16) or the actuator (46), so as to be pivotable about a pivot axis (32), wherein the pivot axes (32) are each oriented parallel to one another.

4. Throwing device (10) according to one of the preceding claims, characterized by a launcher base (14) with a directional drive (24), wherein the launcher unit (16) is coupled to the launcher base (14) via a mechanical interface (22) such that the launcher unit (16) is driven by the directional drive (24) can be directed in azimuth and / or elevation relative to the launcher base (14).

5. Throwing device (10) according to the preceding claim, characterized in that the throwing device (10) is designed such that driving of the directional drive (24) and driving of the actuator (46) can occur in a temporally overlapping manner or simultaneously.

6. Throwing device (10) according to one of the preceding claims, characterized in that the receiving space (38) is arranged to directly receive the active agent (12) to be fired.

7. Throwing device (10) according to one of claims 1 to 5, characterized in that the receiving space (38) is designed to receive a magazine (40) in which two or more fireable active means (12) can be or are arranged.

8. Throwing device (10) according to one of the preceding claims, characterized in that the launcher unit (16) has four to twelve, preferably eight or ten, launcher segments (30).

9. Throwing device (10) according to claim 3 and one of claims 4 to 8, characterized in that the mechanical interface (22) defines a reference plane (34), wherein the pivot axes (32) of the launcher segments (30) are oriented orthogonally or parallel to the reference plane (34).

10. Throwing device (10) according to one of the preceding claims, characterized in that the active means (12) designed as decoys, grenades or launchable drones.

11. Method for deploying active agents (12) to protect an object (0) and / or vehicle from missiles (P), characterized in that as a result of detection of an approaching missile (P), a launcher unit (16) of a launching device (10) is directed in azimuth and / or elevation, wherein launcher segments (30) of the launcher unit (16) are pivoted relative to one another in a temporally overlapping or simultaneous manner in order to set an angle (α) which is enclosed by deployment axes (36) of adjacent launcher segments (30) with one another, after which a salvo of two or more active agents (12) is deployed.

12. Method according to the preceding claim, characterized in that the salvo of two or more active means (12) is fired without directional movement of the launcher unit (16) and / or without angle adjustment of the thrower segments (30).

13. Procedure according to one of the two preceding Claims, characterized in that when the salvo is deployed, the active agents (12) are deployed simultaneously or sequentially.

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