DE102022134714A1 - Device for defence against an aircraft - Google Patents

Abstract

Device for defense against an aircraft, preferably for defense against an unmanned aircraft, the device (1) comprising: a rotor magazine (2) with at least one projectile chamber (3) in which a projectile (20) can be arranged, wherein the rotor magazine (2) can be rotated about an axis of rotation (D) in such a way that a rotational movement of the rotor magazine (2) about the axis of rotation (D) generates a centrifugal force (F) acting on the projectile (20) in the projectile chamber (3), and the device (1) has a retaining device (5) which can be transferred from a retaining position to a firing position, wherein the retaining device (5) in the retaining position is designed to prevent the projectile (20) from emerging from the projectile chamber (3) when the rotor magazine (2) rotates about the axis of rotation (D), and the device (1) is designed to fire the projectile (20) when the rotor magazine (2) rotates about the axis of rotation (D) and the retaining device (5) is in the firing position.

Description

Technical area

The invention relates to a device for defending against an aircraft, in particular for defending against an unmanned aircraft. The device is preferably designed to be attached to an aircraft, in particular to an unmanned aircraft, preferably to be connected to the aircraft as a payload in order to defend against another aircraft, in particular another unmanned aircraft.

Accordingly, the present invention also relates to an aircraft, in particular an unmanned aircraft, with a device according to the invention.

A missile, in particular a rocket missile, with a device mentioned above is also the subject of the present invention.

State of the art

As the popularity of unmanned aircraft (hereinafter also referred to as drones) increases, so does the danger posed by unmanned aircraft. For example, drones that operate within the flight path of airports can pose a significant threat to aircraft taking off and landing. Drones can also be used to spy on sensitive areas, such as military restricted areas or industrial facilities. In this respect, there is a need for a device to defend against unmanned aircraft.

It is known from the state of the art to provide ground-based firing devices. The firing devices can be used to fire projectiles or nets at unwanted drones. This can permanently prevent the unwanted, unmanned aircraft from continuing to fly. However, such firing devices have the disadvantage that the firing devices must have very complex targeting devices and sufficient firepower to be able to guarantee the necessary accuracy even at greater distances. Accordingly, the known firing devices are very expensive to manufacture and unsuitable for use on drones. In addition, several firing devices must be provided in a dislocated arrangement to secure larger areas. This also increases costs.

Another approach known in the state of the art is to use jammers. The jammers are intended to disrupt and/or prevent the reception of radio signals, such as the reception of control signals or GPS signals. However, the use of jammers is ineffective on autonomously operating unmanned aircraft, such as drones, which fly a prescribed flight route based on speed and direction. On the other hand, the jammers also disrupt other radio systems whose operation is expressly desired.

Description of the invention

It is therefore an object of the present invention to provide a device for defense against aircraft, preferably for defense against unmanned aircraft, which overcomes the aforementioned problems and disadvantages of the prior art. It is a particular object of the present invention to provide a device that can be manufactured inexpensively, can be used as mobile as possible and is at the same time highly effective.

This object is achieved with a device according to claim 1. Advantageous developments of the invention are the subject of the dependent claims and/or are explained in the following description.

The solution according to the invention consists in providing a device that is suitable for defense against an aircraft, preferably for defense against an unmanned aircraft. Preferably, the device can be attached to an aircraft, in particular to an unmanned aircraft, and/or connected to the aircraft, in particular to the unmanned aircraft. For example, the device can be designed as a payload for an aircraft, in particular for an unmanned aircraft.

The term "aircraft" in the sense of this invention includes all aircraft, such as fixed-wing aircraft (e.g. aircraft with rigid and/or pivoting wings), rotary-wing aircraft (e.g. helicopters) and/or airships. The term "aircraft" also includes in particular unmanned and/or autonomously flying aircraft.

For the purposes of this invention, “defense against an aircraft” is understood to mean the active influencing, preferably the deterioration and particularly preferably the destruction, of the flight capability of the aircraft to be defended against. For example, the device is designed to to cause the aircraft to be defended from terminating its flight. This can be achieved in particular by influencing and/or eliminating the propulsion and/or lift-generating components of the aircraft to be defended from.

According to the invention, the device comprises a rotor magazine. The rotor magazine has at least one projectile chamber in which a projectile can be arranged, in particular stowed.

The term "projectile chamber" in the sense of this invention refers to a storage space, for example a cavity, in and/or on the rotor magazine. Alternatively, the projectile chamber can also have any other shape or structure, as long as the projectile chamber is designed so that a projectile can be stowed at least partially in and/or on the rotor magazine or at least partially stored with the projectile chamber.

The rotor magazine can be a one-piece component. This means that the rotor magazine can be molded in its entirety. For example, the rotor magazine can be an injection-molded component that is manufactured in a single injection molding process. Alternatively, the rotor magazine can be a cast component or an additively manufactured component.

According to the invention, the rotor magazine is rotatable about a rotation axis. Preferably, the rotor magazine is rotatable in one direction of rotation, for example in a single predefined direction of rotation, about the rotation axis. When the rotor magazine rotates about the rotation axis, i.e. performs a rotational movement, the rotational movement of the rotor magazine generates a centrifugal force which acts on the projectile in the projectile chamber.

In order to prevent the projectile from exiting the projectile chamber due to centrifugal force, the device according to the invention has a retaining device. The retaining device can be transferred from a retaining position to a firing position. The retaining device can preferably be transferred back and forth between the retaining position and the firing position. The retaining device prevents the projectile from exiting the projectile chamber when the retaining device is in the retaining position. In other words, the retaining device is preferably designed to hold the projectile in the projectile chamber when the rotor magazine rotates about the axis of rotation and the retaining device is in the retaining position. The retaining device can delimit the projectile chamber at least in sections radially on the outside with respect to the axis of rotation when the retaining device is in the retaining position.

According to the invention, the device is designed to fire the projectile when the rotor magazine rotates about the axis of rotation and the retaining device is in the firing position. In other words, the projectile can exit the projectile chamber due to the centrifugal force acting on the projectile when the retaining device is in the firing position. Preferably, the centrifugal force causes the projectile to accelerate to a predefined relative speed when the projectile exits the projectile chamber.

The device according to the invention advantageously ensures that at least one projectile can be ejected effectively with a relatively simple and correspondingly cost-effective structure. Due to the small number of components required, the device according to the invention can also be designed to be relatively light and compact. This means that the device can also be used as a payload on an aircraft. The centrifugal force acting on the projectile can be influenced particularly well via the rotational speed of the rotor magazine. Accordingly, the relative speed of the fired projectile can also be influenced particularly effectively. The device according to the invention has the advantage that the device can be manufactured inexpensively, can be used as mobile as possible and is at the same time highly effective.

In an exemplary development of the device, the projectile chamber has a muzzle opening. The muzzle opening is preferably provided radially on the outside of the projectile chamber with respect to the axis of rotation. The muzzle opening is designed in particular so that the projectile can exit the projectile chamber via the muzzle opening when the device fires the projectile. The muzzle opening is preferably arranged and designed in such a way that the projectile can be ejected from the projectile chamber due to the centrifugal force acting on the projectile. This is particularly the case when the rotor magazine rotates about the axis of rotation and the retaining device is in the firing position.

The muzzle opening can be closed by the retaining device when the retaining device is in the retaining position. When the retaining device is in the firing position, the muzzle opening can be released by the retaining device.

The retaining device can, for example, have a muzzle cover. The muzzle cover preferably closes the muzzle opening when the retaining device is in the retaining position. When the retaining device is in the firing position, the muzzle opening can be opened by the muzzle cover. The muzzle cover is preferably arranged on the rotor magazine so that it can pivot, in particular pivot about a pivot axis. The muzzle cover can pivot from the retaining position to the firing position. The muzzle cover can preferably pivot back and forth between the retaining position and the firing position.

A device with a mouth opening and a mouth cover advantageously means that simple structural means can be used to produce the desired functionality of the device. This has the advantage that the device can be manufactured particularly easily and inexpensively without negatively affecting the functionality.

In an exemplary embodiment of the device, the retaining device comprises a pre-tensioning means. The pre-tensioning means can in particular be designed to be spring-elastic. For example, the pre-tensioning means can be a spring, in particular a spiral spring.

Preferably, the pre-tensioning means is designed to exert a pre-tensioning force, in particular to exert a pre-tensioning force on the muzzle cover. The pre-tensioning force can promote a movement of the muzzle cover from the retaining position to the firing position. For example, the pre-tensioning force can push and/or pull the muzzle cover from the retaining position to the firing position. In other words, the pre-tensioning force can push and/or pull the muzzle cover away from the muzzle opening.

A retaining device with a pre-tensioning means advantageously means that simple constructional means can be used to produce the desired functionality of the device. This has the advantage that the device can be produced particularly simply and inexpensively without negatively affecting the functionality.

In a further exemplary embodiment, the device comprises a drive. The drive is preferably designed to drive the rotor magazine, in particular to rotate it about the axis of rotation. The drive can be designed as an electric drive.

For example, the drive can be an electric motor. Preferably, the drive can be electrically connected to an aircraft, in particular an unmanned aircraft. For example, the drive can be designed to be connected to the on-board power supply of the aircraft to which the device is attached. Independently of the above, the electric drive can be connected to an aircraft, in particular an unmanned aircraft, in a signal-communicating manner. This allows the drive to be controlled, for example, via the aircraft.

A device having a drive advantageously ensures that the rotor magazine can be driven independently of the aircraft to which the device is attached. As a result, the device can be connected to different aircraft in a modular manner and operated with different aircraft.

The device is preferably designed to fire the projectile precisely when the projectile chamber, in particular the muzzle opening of the projectile chamber, is in a predefined angular position with respect to the axis of rotation and/or reaches a predefined angular position. For example, the device can be designed to fire the projectile precisely when the projectile chamber, in particular the muzzle opening of the projectile chamber, is in a 90° position and/or reaches a 90° position.

In an exemplary development, the device comprises a triggering device. The triggering device is preferably designed to bring about, in particular to release or at least to facilitate, a transfer of the retaining device from the retaining position to the firing position. This is preferably the case when the projectile chamber, in particular the muzzle opening of the projectile chamber, is in a predefined angular position with respect to the axis of rotation and/or reaches a predefined angular position. The triggering device can be transferred from a safety position to a release position. The triggering device can preferably be transferred back and forth between the safety position and the release position.

Preferably, the triggering device secures the retaining device, in particular the mouth cover of the retaining device, in the retaining position when the triggering device is in the securing position. For example, the triggering device can secure the retaining device, in particular the mouth cover of the retaining device, in relation to the rotor magazine lock. The triggering device can counteract the pre-tensioning force of the pre-tensioning means. In other words, the triggering device can be designed to prevent a movement of the retaining device, in particular a movement of the mouth cover of the retaining device, in relation to the rotor magazine when the triggering device is in the securing position.

When the triggering device is in the release position, the retaining device, in particular the muzzle cover of the retaining device, is preferably released by the triggering device. This enables the retaining device to switch from the retaining position to the firing position. For example, the retaining device, in particular the muzzle cover of the retaining device, is no longer locked to the rotor magazine by the triggering device when the triggering device is in the release position. As a result, the pre-tensioning means, in particular the pre-tensioning force of the pre-tensioning means, can then push and/or pull the muzzle cover from the retaining position to the firing position. This preferably results in the projectile in the projectile chamber being fired by the device.

The triggering device advantageously ensures that the retaining device can be or is transferred from the retaining position to the firing position precisely when the projectile chamber, in particular the muzzle opening of the projectile chamber, reaches a predefined angular position in relation to the axis of rotation. This allows the projectile to be fired particularly effectively and efficiently in a predefined direction by the device.

In an exemplary development of the triggering device, the triggering device has a lever arm mechanism. The lever arm mechanism is preferably designed to release the retaining device, in particular the mouth cover of the retaining device, when the lever arm mechanism is actuated by an actuator of the triggering device described below. The lever arm mechanism can be pivotably connected to the rotor magazine, in particular connected to the rotor magazine via a joint. The lever arm mechanism is preferably connected to the rotor magazine in such a way that the lever arm mechanism rotates with the rotor magazine when the rotor magazine rotates about the axis of rotation.

The lever arm mechanism can be transferred from the securing position to the release position in relation to the rotor magazine, in particular can be pivoted, particularly preferably pivoted via the joint between the lever arm mechanism and the rotor magazine. The lever arm mechanism advantageously secures the retaining device, in particular the mouth cover of the retaining device, in the retaining position when the lever arm mechanism is in the securing position. In the release position, the lever arm mechanism enables the retaining device, in particular the mouth cover of the retaining device, to be transferred.

A lever arm mechanism advantageously means that the triggering device can be implemented using simple constructional means and is therefore relatively inexpensive. This has the advantage that the device can be manufactured particularly inexpensively without negatively affecting its functionality.

In a further embodiment, the triggering device comprises an actuator. The actuator can be arranged in a fixed position, in particular immobile, with respect to the axis of rotation. The actuator is preferably designed to move the lever arm mechanism from the securing position to the release position. This is particularly the case when the lever arm mechanism is guided past the actuator at least in sections by the rotary movement of the rotor magazine and the actuator is advantageously in an actuating position. For example, the actuator can be arranged and designed in such a way that at least part of the actuator protrudes into the circular path of the lever arm mechanism. This is preferably ensured when the actuator is in the actuating position. Because part of the actuator protrudes into the circular path of the lever arm mechanism, the lever arm mechanism must give way to the actuator when the lever arm mechanism is guided past the actuator due to the rotary movement of the rotor magazine. This evasive movement of the lever arm mechanism causes the lever arm mechanism to move from the safety position to the release position. This allows the retention device to change from the retention position to the locking position. This preferably has the consequence that the projectile exits the projectile chamber and is fired by the device.

When the actuator is in a run-through position, the lever arm mechanism can preferably be guided past the actuator without there being any interaction, in particular contact, between the lever arm mechanism and the actuator. Accordingly, the lever arm mechanism remains in the securing position and the retaining device remains in the retaining position. This preferably has the consequence that the rotor magazine can rotate about the axis of rotation without the projectile in the projectile chamber being fired by the device.

Due to the fixed arrangement of the actuator, the lever arm mechanism can only be actuated by the actuator in a predefined angular position or moved from the safety position to the release position. This advantageously means that the triggering device transfers the retention device from the retention position to the firing position precisely when the projectile chamber, in particular the muzzle opening of the projectile chamber, reaches or passes through a predefined angular position in relation to the axis of rotation. Accordingly, the projectile can be fired particularly effectively and efficiently in a predefined direction by the device.

The actuator can be designed in several parts. For example, the actuator can have an actuator and an actuating means. The actuator can be an electric motor actuator, for example a servo. The actuator is preferably designed to drive the actuating means, in particular to move the actuating means from the run-through position into the actuating position. The actuating means can be an actuating pin and/or an actuating lever.

The lever arm mechanism can comprise a plurality of lever arms. Preferably, the individual lever arms are immovably connected to one another. The plurality of lever arms can each be aligned obliquely and/or orthogonally to one another. In an advantageous embodiment of the lever arm mechanism, the lever arm mechanism comprises a first lever arm, an optional second lever arm and a third lever arm.

The first lever arm can be designed as a force introduction means. This means that, for example, the force for adjusting the lever arm mechanism from the locking position to the release position can be introduced into the lever arm mechanism via the first lever arm. For example, the first lever arm comes into contact with the actuator, in particular the actuating means of the actuator, at least in sections when the lever arm mechanism is rotated past the actuator due to the rotary movement of the rotor magazine and the actuator is advantageously in the actuating position. Preferably, the first lever arm is connected to the second lever arm. In alternative embodiments, however, the first lever arm can also be connected directly to the third lever arm.

The optional second lever arm can be designed as a force transmission means. This means that the second lever arm can transmit the movement of the first lever arm to the third lever arm. The second lever arm can be connected to the first lever arm at a first end. Preferably, the second lever arm is connected to the third lever arm at a second end.

The third lever arm can be designed as a securing means. This means that the third lever arm is preferably in direct or indirect contact with the retaining device, in particular the mouth cover of the retaining device. This can be the case in particular when the lever arm mechanism is in the securing position and the lever arm mechanism secures the retaining device, in particular the mouth cover of the retaining device, in the retaining position.

In a further exemplary embodiment of the device, the rotor magazine comprises several projectile chambers. The rotor magazine can have, for example, between five and fifty, preferably between twenty and thirty and particularly preferably twenty-four projectile chambers. The projectile chambers can be distributed in the circumferential direction in and/or on the rotor magazine, in particular evenly distributed. For example, the projectile chambers can be arranged next to one another in the circumferential direction and/or each have the same dimensions or design.

Preferably, each of the multiple projectile chambers is assigned a respective retaining device. The device can therefore also comprise multiple retaining devices, in particular mutually independent retaining devices. Each of the multiple projectile chambers and/or the multiple retaining devices can be assigned a lever arm mechanism. The device can therefore also comprise multiple, in particular mutually independent, lever arm mechanisms.

An embodiment of the device with several projectile chambers advantageously means that several projectiles can be carried and/or fired by the device. Preferably, one projectile is stored or can be stored in each of the several projectile chambers. Alternatively or additionally, several projectiles can be provided per projectile chamber. Several projectile chambers have the advantage that the device can be particularly effective.

The projectile can be a bola projectile, for example. The bola projectile can have several projectile bodies, preferably two projectile bodies, which can be connected to one another via a flexible connecting means. The projectile bodies can be metal balls, for example. The flexible connecting means can be a nylon band, for example. The connecting means is preferably designed in such a way that the several projectile bodies can be a maximum distance from one another of between 2m and 14m, preferably between 6m and 10m and particularly preferably 8m.

A bola projectile advantageously means that there is a very high probability that the bola projectile will become caught in and/or on the propulsion means and/or the buoyancy means of the aircraft being fired at when the bola projectile is fired through the device. Accordingly, the flight capability of the aircraft being fired at can be at least reduced, and at best eliminated. A bola projectile therefore has the advantage that the effectiveness of the device can be further increased.

Alternatively or additionally, the projectile can also be a safety net. It is also conceivable that different types of projectiles, such as a mix of bola projectiles and safety nets, can be fired with the device.

In a further exemplary embodiment, the device comprises a connecting device. The connecting device is preferably designed so that the device can be connected to an aircraft, in particular to an unmanned aircraft, via the connecting device. For example, the device can be connected to the aircraft, in particular to the unmanned aircraft, via the connecting device in a form-fitting manner, for example via a latching and/or snap connection, in a force-fitting manner, for example via a screw connection, and/or in a material-fitting manner, for example via an adhesive connection. The connecting device is preferably a mounting plate that can be screwed to the aircraft, in particular to the unmanned aircraft. Independently of the above, the actuator, the drive and/or the rotor magazine can be arranged on the connecting device.

The object of the invention mentioned at the outset is also achieved according to the invention with an aircraft according to claim 10. The aircraft according to the invention is preferably an unmanned aircraft.

The aircraft according to the invention comprises a device according to one of the aforementioned embodiments. All of the aforementioned features, combinations of features and advantages therefore also apply in analogous application to the aircraft according to the invention. Due to the device, the aircraft is advantageously designed to fend off another aircraft, in particular another unmanned aircraft. This is the case, for example, if the aircraft with the device shoots at the other aircraft.

In an advantageous development of the aircraft, the aircraft comprises several of the aforementioned devices. Preferably, the firing direction of the several devices is different.

The object of the invention mentioned at the outset is also achieved according to the invention with a missile according to claim 11. The missile according to the invention can in particular be a rocket missile, that is to say a missile with a rocket propulsion system.

The missile according to the invention comprises at least one device according to one of the aforementioned embodiments. Preferably, the missile comprises several devices according to the aforementioned embodiments.

All of the aforementioned features, combinations of features and advantages therefore also apply to the missile in an analogous application. The missile is designed to repel an aircraft, in particular an unmanned aircraft, due to the one or more devices. This is the case, for example, when the missile fires at the aircraft with the one or more devices.

Short description of the drawings

• 1 eine perspektivische Darstellung eines Ausführungsbeispiels einer Vorrichtung zur Abwehr von Luftfahrzeugen, vorzugsweise zur Abwehr von unbemannten Luftfahrzeugen,
• 2 eine schematische Schnittdarstellung des Ausführungsbeispiels gemäß 1, und
• 3 eine perspektivische Darstellung eines Verwendungsbeispiels der Vorrichtung zur Abwehr von Luftfahrzeugen in einem Raketenflugkörper.

The different and exemplary features described above can be combined with one another according to the invention, as long as this is technically reasonable and suitable. Further combinable features, advantages and embodiments of the invention emerge from the following description of an embodiment and from the figures. They show:

• 1 a perspective view of an embodiment of a device for defence against aircraft, preferably for defence against unmanned aircraft,
• 2 a schematic sectional view of the embodiment according to 1 , and
• 3 a perspective view of an example of use of the device for defence against aircraft in a missile.

Ways to implement the invention

1 shows a perspective view of an embodiment of a device 1 for defense against aircraft. The device 1 is designed in particular to defend against unmanned aircraft, such as quadrocopters, octocopters and/or unmanned vertical take off and landing (VTOL) aircraft. The device 1 can terminate the flight of the unmanned aircraft by firing at it with a 1 projectile 20 (not shown).

The device 1 can be connected to an aircraft, in particular to an unmanned aircraft, via a connecting device 19. In the 1 In the embodiment shown, the connecting device 19 is designed as a connecting plate 19, which has several passages for screws. In other words, the device 1 can be screwed to an aircraft by means of the connecting device 19. The device 1 can then be transported as a payload by the aircraft and preferably during the flight other aircraft, in particular other unmanned aircraft with the projectiles 20 (in 1 not shown).

As in the 1 As shown in the embodiment shown, the device 1 comprises a rotor magazine 2. The rotor magazine 2 is rotatable about a rotation axis D. In order for the rotor magazine 2 to be able to rotate, for example, in the 1 drawn direction of rotation R ₁ rotates around the axis of rotation D, the rotor magazine 2 is driven by a drive 8 via a drive shaft 9 (see also 2 ).

The rotor magazine 2 has a total of twenty-four projectile chambers 3. For the sake of better representation, 1 not each of the projectile chambers 3 is provided with a reference symbol. The projectile chambers 3 are arranged evenly distributed in the circumferential direction with respect to the axis of rotation D. In each of the projectile chambers 3 there is a 1 not shown, projectile 20 is provided. This structural design causes a centrifugal force to act on the projectiles 20 in the projectile chambers 3 when the rotor magazine 2 rotates about the axis of rotation D. This means that the projectiles 20 in the projectile chambers 3 are pressed radially outwards due to the rotational movement of the rotor magazine 2 in relation to the axis of rotation D.

Each of the projectile chambers 3 has a respective retaining device 5. Each retaining device 5 is provided radially outwardly on the corresponding projectile chamber 3 with respect to the axis of rotation D. Each of the retaining devices 5 is movable from a retaining position (in 1 shown) into a firing position (in 1 not shown). In the retention position, the retention device 5 is designed to retain a projectile 20 in the projectile chamber 3, i.e. to prevent the projectile 20 from escaping from the corresponding projectile chamber 3 when the rotor magazine 2 rotates about the axis of rotation D. In the firing position, the retention device 5 is designed to release the projectile. In other words, the projectile 20 can exit the projectile chamber 3 due to the centrifugal force acting on the projectile 20 when the retention device 5 is in the firing position and the rotor magazine 2 rotates about the axis of rotation D.

Each retaining device 5 comprises a muzzle cover 6 and a pre-tensioning means 7. The muzzle cover 6 is pivotally connected to the rotor magazine 2. As a result, the muzzle cover 6 can be moved in relation to the rotor magazine 2 from the retaining position (in 1 shown) into the firing position (in 1 not shown). The pre-tensioning means 7 is in the 1 illustrated embodiment is designed as a spring 7, in particular as a spiral spring 7. The pre-tensioning means 7 generates a pre-tensioning force which presses the muzzle cover 6 into the firing position.

In order for the device 1 to 1 In order to fire projectiles 20 (not shown) into the projectile chamber 3, the device 1 comprises a trigger device 10. The trigger device 10 can be operated from a safety position (in 1 shown) into a release position (in 1 not shown). In the release position, the trigger device 10 is designed to release a transfer of the retaining device 5, in particular a pivoting of the muzzle cover 6, from the retaining position to the firing position. In the securing position, the retaining device 5, in particular the muzzle cover 6, is secured in the retaining position by the trigger device 10. With regard to the specific functionality of the device 1, in particular the trigger device 10, reference is made to the description for the representation of 2 referred to.

In structural terms, the triggering device 10 comprises a lever arm mechanism 11 and an actuator 16. The actuator 16 is designed to to actuate the lever arm mechanism 11 - relative to the axis of rotation D - at a predefined angular position. For this purpose, the actuator 16 is provided in a fixed position at a specific location of the device 1. In the 1 In the embodiment shown, the actuator 16 comprises an actuator 17, namely an electric servo 17, and an actuating means 18, namely an actuating arm 18. The actuating means 18 is moved by the actuator 17 from a through position (in 1 shown) into an actuating position (in 1 not shown) adjustable.

Each restraint device 5 and thus also each projectile chamber 3 is assigned a lever arm mechanism 11. Each lever arm mechanism 11 comprises in the 1 illustrated embodiment, three lever arms 12, 13, 14, namely a first lever arm 12, a second lever arm 13 and a third lever arm 14. The lever arm mechanism 11 is pivotally mounted on the rotor magazine 2 with respect to the rotor magazine 2. The lever arm mechanism 11 is particularly designed to be able to move from the securing position (in 1 shown) to the release position (in 1 not shown).

If the actuating means 18 is in the 1 shown through-run position, the rotor magazine 2 can rotate completely freely about the axis of rotation D without the actuating means 18 coming into contact with the lever arm mechanism 11. This means that the rotor magazine 2 can rotate at least one complete revolution about the axis of rotation D without the lever arm mechanism 11 being moved from the safety position to the release position. As a result, the retaining devices 5 also keep the projectile chambers 3 fired. Accordingly, no projectile 20 can exit the projectile chambers 3. The rotor magazine 2 can rotate without a projectile 20 being fired by the device 1.

This is different when the release device 10 changes from the locking position to the release position.

2 shows a schematic sectional view of the embodiment of the device 1 of 1 .

The rotor magazine 2 rotates in the 2 shown illustration in the direction of rotation R, around the axis of rotation D. In contrast to the 1 , was in the 2 the actuating means 18 is moved by the actuator 17 into the actuating position. For this purpose, the actuating means 18 was rotated by the actuator 17 by 90° in the direction of rotation R _2. In the actuating position, the actuating means 18 protrudes at least in sections into the circular path of the lever arm mechanism 11, in particular into the circular path of the first lever arm 12 of the lever arm mechanism 11. The technical effect of this is described further below. First, however, the projectile chamber 3 shown on the left will be discussed, which has obviously not yet passed the triggering device 10 or which has not yet been guided past the triggering device 10.

In the 2 The projectile chamber 3 shown on the left is closed radially outward by the retaining device 5. This means that the projectile 20, which is described in more detail below and is arranged within the left projectile chamber 3, cannot leave the projectile chamber 3. The exit of the projectile 20 radially outward (relative to the axis of rotation D) is prevented by the retaining device 5, in particular by the muzzle cover 6 of the retaining device 5. Nevertheless, a centrifugal force acts on the projectile 20 due to the rotational movement of the rotor magazine 2, which pushes the projectile 20 radially outward.

In the state of the left projectile chamber 3, the retaining device 5, in particular the muzzle cover 6 of the retaining device 5, is held or locked in the retaining position by the lever arm mechanism 11, in particular the third lever arm 14. In other words, pivoting of the muzzle cover 6 about a pivot axis S from the retaining position into the firing position is mechanically prevented by the lever arm mechanism 11, in particular the third lever arm 14 of the lever arm mechanism 11, although the muzzle cover 6 is pressed into the firing position by the pre-tensioning means 7. The 2 The lever arm mechanism 11 shown on the left is in the locking position.

If the 2 If the projectile chamber 3 shown on the left now continues to rotate in the direction of rotation R due to the rotation of the rotor magazine 2, the projectile chamber 3 will inevitably assume the angular position of the 2 reach the chamber 3 shown on the right.

Since at this angular position the actuating means 18 of the actuator 16 extends into the circular path of the first lever arm 12 of the lever arm mechanism 11 and the rotor magazine 2 continues to rotate in the direction of rotation R, the first lever arm 12 of the lever arm mechanism 11 strives to avoid the actuating means 18. This is made possible by the fact that the entire lever arm mechanism 11 is pivotally connected to the rotor magazine 2 via a joint 15. In other words, the first lever arm 12 is moved by the actuating means tel 18 is pressed downwards when the first lever arm 12 is guided past the actuator 16 due to the rotary movement of the rotor magazine 2. In the illustrated embodiment, the joint 15 is provided between the first lever arm 12 and the second lever arm 13.

A force is introduced into the lever arm mechanism 11 via the first lever arm 12, which moves the entire lever arm mechanism 11 from the safety position (left lever arm mechanism 11 in 2 ) can be swivelled into the release position (right lever arm mechanism 11 in 2 ). The first lever arm 12 can accordingly also be referred to as force introduction means 12.

The evasive movement of the first lever arm 12 is transmitted via the second lever arm 13 to the third lever arm 14. As a result, the retaining device 5, in particular the muzzle cover 6, is released from the trigger device 10, in particular the lever arm mechanism 11. As shown on the right in 2 As shown, the retaining device 5 is then transferred from the retaining position to the firing position. This means that the muzzle cover 6 pivots from the retaining position to the firing position, in particular pivots about the pivot axis S.

In the firing position, a muzzle opening 4 of the projectile chamber 3 is released by the muzzle cover 6. The projectile 20 can thus exit the projectile chamber 3 via the muzzle opening 4 due to the centrifugal force acting on the projectile 20. Accordingly, the projectile 20 is fired by the device 1.

The projectile 20 fired by the device 1 is a bola projectile 20. The projectile 20 has two projectile bodies 21. In the embodiment shown, the projectile bodies 21 are designed as metal balls 21. Independently of this, the projectile bodies 21 are connected to one another by a flexible connecting means 22. The flexible connecting means 22 can be, for example, a nylon band 22. If the two projectile bodies 21 are spaced apart from one another as far as possible, the distance can be limited to 8 m by the flexible connecting means.

3 shows a schematic, perspective view of a missile 30 with a rocket engine. In other words, in 3 a rocket missile 30 is shown.

The missile 30 comprises several of the devices 1 of the aforementioned type, in particular 3 devices 1. The devices 1 are arranged in the missile 30 such that all axes of rotation D of the devices 1 are coaxial with the longitudinal axis L of the missile 30. This has the advantage that all devices 1 can be driven by a single drive 8, thus saving installation space and weight.

Preferably, the devices 1 each fire the projectiles 20 in different directions. In other words, the devices 1 are rotated in relation to the longitudinal axis L of the missile 30 in such a way that the retaining device 5 is released by the triggering device 10 in different angular positions, for example always with a 90° offset, in order to fire the projectiles 20. This increases the scattering effect and consequently also the probability of hitting.

In alternative examples of use not shown in the figures, one or more devices 1 of the 1 and 2 The embodiment shown can be provided on an aircraft, preferably an unmanned aircraft.

List of reference symbols

1

contraption

2

Rotor magazine

3

Bullet chamber

4

Muzzle opening

5

Restraint device

6

Muzzle cover

7

Preloading device

8th

drive

9

drive shaft

10

Release device

11

Lever arm mechanism

12

first lever arm

13

second lever arm

14

third lever arm

15

joint

16

Actuator

17

Actuator

18

Actuators

19

Connecting device

20

bullet

21

Projectile body

22

flexible connecting element

30

Missile missiles

D

Rotation axis

S

Swivel axis

L

Longitudinal axis of the rocket

R1

Direction of rotation of the rotor magazine

R2

Direction of rotation of the actuating device

Claims (11)

Device for defense against an aircraft, preferably for defense against an unmanned aircraft, the device (1) comprising: - a rotor magazine (2) with at least one projectile chamber (3) in which a projectile (20) can be arranged, wherein - the rotor magazine (2) can be rotated about an axis of rotation (D) in such a way that a rotational movement of the rotor magazine (2) about the axis of rotation (D) generates a centrifugal force (F) acting on the projectile (20) in the projectile chamber (3), and - the device (1) has a retaining device (5) which can be transferred from a retaining position to a firing position, wherein - the retaining device (5) in the retaining position is designed to prevent the projectile (20) from escaping from the projectile chamber (3) when the rotor magazine (2) rotates about the axis of rotation (D), and - the device (1) is designed to fire when the rotor magazine (2) rotates about the rotation axis (D) and the retaining device (5) is in the firing position. Device (1) according to Claim 1 , characterized in that the projectile chamber (3) has a muzzle opening (4) arranged radially outward with respect to the axis of rotation (D) and the retaining device (5) comprises a muzzle cover (6), wherein the muzzle opening (4) is closed by the muzzle cover (6) when the retaining device (5) is in the retaining position, and the muzzle cover (6) releases the muzzle opening (4) when the retaining device (5) is in the firing position. Device (1) according to Claim 2 , characterized in that the retaining device (5) has a prestressing means (7), wherein the prestressing means (7) exerts a prestressing force on the mouth cover (6), and the prestressing force pushes and/or pulls the mouth cover (6) away from the mouth opening (4). Device (1) according to one of the preceding claims, characterized in that the device (1) has a drive (8), preferably an electric motor drive (8), and the drive (8) is designed to rotate the rotor magazine (2) in at least a first direction of rotation (R ₁ ) about the axis of rotation (D). Device (1) according to one of the preceding claims, characterized in that the device (1) has a triggering device (10), and the triggering device (10) is designed to cause the retaining device (5) to be transferred from the retaining position to the firing position when the projectile chamber (3) has reached a predefined angular position with respect to the axis of rotation (D). Device (1) according to Claim 5 , characterized in that the triggering device (10) has a lever arm mechanism (11) which can be moved from a securing position, in which the lever arm mechanism (11) secures the retaining device (5) in the retaining position, into a release position, in which the lever arm mechanism (11) enables the retaining device (5) to be transferred from the retaining position to the firing position. Device (1) according to Claim 6 , characterized in that the lever arm mechanism (11) is connected to the rotor magazine (2), preferably via a joint (15) to the rotor magazine (2), and the triggering device (10) has an actuator (16) which is stationary with respect to the axis of rotation (D), wherein the actuator (16) is designed to move the lever arm mechanism (11) from the securing position into the release position when the lever arm mechanism (11) is guided past the actuator (16) at least in sections by the rotary movement of the rotor magazine (2). Device (1) according to one of the preceding claims, characterized in that the rotor magazine (2) has a plurality of projectile chambers (3), preferably 24 projectile chambers (3), and each projectile chamber (3) is assigned a respective retaining device (5). Device (1) according to one of the preceding claims, characterized in that the projectile (20) is a bola projectile (20) with several projectile bodies (21) which are connected to one another by a flexible connecting means (22). Aircraft, preferably unmanned aircraft, with a device (1) according to one of the Claims 1 until 9 , wherein the aircraft is protected by the device (1) for defence against another aircraft, preferably for defence against a other unmanned aircraft. Missile (30) with several devices (1) according to one of the Claims 1 until 9 .

Images