EP3679314B1 - Missile de lutte anti-drone - Google Patents

Missile de lutte anti-drone Download PDF

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Publication number
EP3679314B1
EP3679314B1 EP18758540.1A EP18758540A EP3679314B1 EP 3679314 B1 EP3679314 B1 EP 3679314B1 EP 18758540 A EP18758540 A EP 18758540A EP 3679314 B1 EP3679314 B1 EP 3679314B1
Authority
EP
European Patent Office
Prior art keywords
drive
missile
drone
housing
active body
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP18758540.1A
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German (de)
English (en)
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EP3679314A1 (fr
Inventor
René FRETER
Martin Walzer
Peter Gerd Fisch
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Diehl Defence GmbH and Co KG
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Diehl Defence GmbH and Co KG
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Publication date
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Publication of EP3679314A1 publication Critical patent/EP3679314A1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
    • F41H13/00—Means of attack or defence not otherwise provided for
    • F41H13/0006—Ballistically deployed systems for restraining persons or animals, e.g. ballistically deployed nets
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2253—Passive homing systems, i.e. comprising a receiver and do not requiring an active illumination of the target
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2273—Homing guidance systems characterised by the type of waves
    • F41G7/2293—Homing guidance systems characterised by the type of waves using electromagnetic waves other than radio waves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
    • F41H11/00—Defence installations; Defence devices
    • F41H11/02—Anti-aircraft or anti-guided missile or anti-torpedo defence installations or systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/20—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type
    • F42B12/22—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type with fragmentation-hull construction
    • F42B12/32—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type with fragmentation-hull construction the hull or case comprising a plurality of discrete bodies, e.g. steel balls, embedded therein or disposed around the explosive charge
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
    • F42B12/62—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected parallel to the longitudinal axis of the projectile

Definitions

  • the invention relates to a missile for fighting drones with a drive and a housing around the drive and an active body for damaging the drone.
  • Remote-controlled small aircraft are becoming more and more powerful, both in terms of their payload and in terms of their control and flight capabilities.
  • model building drones can easily be remote-controlled over long distances without the pilot standing on the ground having to keep an eye on them.
  • Such a defense device is from the DE 10 2016 211 371 A1 known.
  • An arrow-like missile is shot from a launcher, which has a net launcher at its front end. If the missile comes close to the drone to be intercepted, the net is thrown forward, the drone is caught and the drone, which is entangled in the net, falls to the ground on a parachute.
  • Another defense device is also from the DE 10 2015 008 255 A1 known. It is a defense drone to ward off small drones.
  • the defense drone comprises a motor connected to its fuselage for driving propellers and a throwable effector provided on the fuselage.
  • the invention is based on the consideration that small and light drones can only be hit with difficulty by a directed launch.
  • capturing with the aid of a net requires a high level of accuracy for the approaching missile.
  • the missile With the seeker head with the optical viewfinder, the missile can be tracked in a targeted manner to the movements of an agile drone, so that a target approach can be carried out precisely and the active body can be triggered in sufficient proximity to the drone.
  • a drone can be understood to mean an unmanned aircraft such as a remote-controlled aircraft, in particular up to a total weight of twenty kilograms, for example from the hobby area of model aircraft building. It can be a so-called Small Unmaned Aircraft (SUA) or a Micro Air Vehicle (MAV).
  • a drone can be a rotary wing aircraft, in particular with a plurality of rotors, for example a quadrocopter or a hexacopter. However, a fixed wing or only wing is also possible.
  • the control unit is prepared for drone detection, in particular on the basis of data from the seeker or a detector of the seeker head.
  • a drone detection can be understood to mean holding a given target as well as autonomous recognition of the target as such. If, for example, a missile launcher for launching the missile is equipped with optics or another target acquisition system with which the target is detected and transferred to the missile, it is sufficient for drone detection if the control unit is prepared to target the transferred target in this way to keep that this steers the missile to the target. A faster launch is possible, however, if the drone is detected by the missile itself.
  • image processing algorithms can be used by the control unit with which the target is recognized as such. To identify the target, it is sufficient to classify the target into one of several different classes of different missiles.
  • the control unit can compare properties of the missile, for example optical properties, with class properties and divide the missile into one or more of the classes on the basis of the comparison result.
  • a classification of the missile expediently includes a distinction between missiles to be attacked and missiles not to be attacked. In this way, an incorrect attack on a missile that is not to be combated can be avoided.
  • the detection of unmanned small missiles is particularly useful.
  • the drone can be recognized as such among several objects visible in the sky, which counteracts incorrect combat becomes.
  • the control unit is expediently able to differentiate between rotary-wing and fixed-wing aircraft or to classify the drone as a rotary-wing or fixed-wing aircraft.
  • the active body is at least prepared to damage the drone. Damage can be a reduction or cessation of the drone's ability to fly. This can be done mechanically and / or electronically, for example by radiation to disrupt radio traffic and / or to impair, in particular destroy, electronic components of the drone.
  • the active body can contain a microwave transmitter or a transmitter in a different frequency range which, in response to a combat command, emits active radiation to damage the drone. Of course, complete destruction is also possible, for example parts of the drone being broken off causing a crash.
  • the active body can have an explosive charge, a shot charge or the like, for example rubber shot.
  • the control unit is used to control the approach of the missile to the detected drone. Appropriately, this is an autonomous approach to the drone without the need for continuous control by an operator.
  • the seeker head can be an artillery seeker, i.e. a seeker as it is used in artillery shells.
  • a rocket engine is advantageous as the drive, a propeller drive with a battery and a rechargeable battery also being possible.
  • the missile is advantageously shot down by a hand launcher or battery launcher, referred to in the following simply as a launcher.
  • a launcher for 40 mm caliber projectiles or rockets is particularly cheap.
  • the drive is releasably held in the housing in such a way that it can be ejected in flight.
  • a rear space of the missile that was previously occupied by the drive can now be used for other purposes.
  • the active body is arranged in relation to the drive in such a way that it gains a degree of active freedom when it is released. A degree of freedom of action is obtained when the effective body can achieve an effect through the drop that is not or not yet possible before the drop.
  • the drive can be detachably arranged in the housing so that it can be ejected in flight and is thus ejected from the housing. It is also possible that the drive is held releasably to the housing in such a way that it can be ejected together with the housing part surrounding it in flight.
  • the drive and a rear housing part are detachably held in relation to a front housing part, so that, for example, a rear part of the missile is dropped as a whole. The rear space is then the area behind the front, remaining part of the missile, and it is free for the active body to be deployed through this space.
  • the drone and / or the missile glides down while floating on a parachute.
  • the missile has a parachute which is arranged in a payload chamber of the missile.
  • the arrangement can be in front of the drive in the direction of flight, in particular directly in front of the drive.
  • the parachute can be ejected to the rear through a drive compartment, which is open through the release of the drive. Ejection to the rear is considerably easier and entails much smaller risks of the parachute becoming entangled on the missile than a lateral ejection, for example through a side flap.
  • a trigger can be provided which, together with the parachute, is designed such that when it is triggered it throws the parachute backwards through a drive space.
  • the drive space which houses the drive before and during the launch of the missile, is free after the drive has been dropped so that the parachute can be ejected through the drive space to the rear.
  • the missile is expediently launched from a tube from which the missile is ejected either by a cartridge, but in particular by its own drive.
  • steering blades are advantageous, which are expediently arranged at the rear of the missile.
  • a wing has at least one control surface which can be moved relative to the housing of the missile as an outer surface, the movement of which is expediently controlled by the control unit.
  • several control vanes are expediently available, which are designed as folding vanes. Folding wings can be folded in the tube and, after the tube is closed or after leaving the missile, can be opened out of the tube and thereby protrude, for example, vertically radially from the housing and enable the missile to be controlled through the corresponding control surface.
  • a drive lock is expediently provided for this purpose, which locks the drive in the housing or drive space in such a way that it cannot fall out.
  • a simple drive lock can be achieved if it is connected to a folding wing in such a way that unfolding the folding wing mechanically moves the drive lock in such a way that it releases the drive for ejection. A mechanical form fit can be released so that the drive can now be ejected.
  • the drive and housing are expediently designed in such a way that the drive can be freely ejected to the rear after being pushed. If, for example, the folding wings are unfolded and the drive lock is brought into such a position that the drive is released, it can still push the missile for a while after its take-off and thereby remain pressed into the housing. If the pushing slows down, is stopped or otherwise diverted, the drive can be ejected to the rear.
  • a particularly simple release of the drive can be achieved if the drive lock is rigidly connected to a folding sash. By unfolding, for example, a formation can be moved into a release position, so that a form fit that was previously blocked by the nose is released.
  • a simple ejection of the drive from the housing or a drive space can be achieved if the drive is designed such that it is ejected from the housing by its thrust reversal. It is also advantageous if the drive and the housing are designed in such a way that the drive, which is designed to drive over a predetermined period of time, develops a pressure in the housing towards the end of the period which drives the drive out of the housing. For example, towards the end of the period of time, the drive can cause a forward gas ejection which, before the drive, generates a gas pressure that ejects the drive from the housing.
  • a drone to be intercepted is usually small and therefore only visible to the naked eye over short distances. If a drone is seen by an operator, for example, and the decision to intercept the drone has been made, it may be that it is already relatively close, i.e. only a few hundred meters, from the operator. The same applies to automatic drone detection and launching the missile from an automated battery. If the drive is to be dropped, for example to enable a parachute to be ejected backwards, the drive must be switched off or burned out before reaching the drone to be intercepted.
  • the weight and aerodynamics of the missile are characterized by the fact that the drive is designed to drive over a predetermined period of time, and this period, in conjunction with weight and aerodynamics, is dimensioned so that the drive can thrust after end of the predetermined maximum distance after the start.
  • the maximum drive distance can be adjusted accordingly.
  • the active body is an active body that is also used in another context, for example a ballistic projectile, so that it then only has to be inserted into a payload chamber of the missile, for example.
  • the missile has a payload chamber in which the active body is arranged, expediently together with an ignition trigger for igniting the active body.
  • the ignition trigger can be adapted to the type of ignition of the active body, so that when different active bodies are used, only the corresponding ignition trigger has to be adapted.
  • the active body has an impact fuse
  • the ignition trigger contains a mechanism which simulates an impact of the active body when triggered.
  • the ignition trigger is connected to the control unit by a signal line, expediently via a mechanical interface.
  • a composite body consisting of an ignition trigger and an active body can be pushed into the payload chamber, electrical contact with the control unit being established through the mechanical interface, expediently by engaging a mechanical locking unit, so that a reliable signal connection between the ignition trigger and control unit is ensured.
  • a drone usually comprises rotating parts, such as a rotor, a propeller or even a turbine, which can be brought to a standstill by a network or, more generally, a thread. In this way, the drone can be prevented from continuing its flight and thus damaged, but it does not have to be destroyed.
  • the missile has a thread load and an ejector for ejecting the thread load.
  • the thread load contains a multitude of threads.
  • a thread is an elongated and flexible element, the material of which is of minor importance, so it can be a plastic, a natural material, a composite, metal or other material.
  • the ejector may contain a detonating agent which, when exploded, ejects the threads. The ejection can take place to the rear, in particular through a drive space, or to the side, for example by breaking off a housing part.
  • the filament charge may include loose filaments that are not attached to the missile and / or not attached to each other.
  • the threads become entangled in a rotating element of the drone, which then crashes.
  • the threads can be connected at least indirectly to the housing of the missile at at least one end. They can create a web of threads that can be used to capture the drone.
  • the threads In order to keep the weight of the missile as low as possible, the threads also have a low weight, which could have a negative impact when they are distributed in the area around the missile, since they are not scattered far around the area even if detonated.
  • weights are attached to the threads, which are also thrown away during casting. The weights can pull the threads apart and thus spread them over a wide radius, which means that the missile has a wider radius of action to catch the drone. It is possible to provide a separate weight for each thread, or to attach several threads to a weight so that several threads with one weight fly through the air like tufts.
  • the weights are housing elements.
  • the housing can be broken open and the individual housing elements can pull the threads into the surrounding area.
  • the housing expediently contains predetermined breaking points or predetermined breaking lines which divide it into individual housing elements. At least one thread is expediently attached to one, to several or to each housing element divided in this way.
  • the housing elements can be tubular parts, in particular tubular strips. The threads on the housing elements advantageously form a network, in particular when the housing elements are driven apart.
  • the threads are at least indirectly attached to the seeker head.
  • the threads can be fastened to the housing or to a fastening element provided for this purpose in a payload compartment.
  • the missile and drone remain connected to one another and can slide down on a parachute, for example.
  • the threads can be fastened to a housing element in order to achieve a high degree of waste, for example to a part of the housing around the payload space and / or the drive space.
  • the ejector and the housing are designed such that the housing is moved apart first and / or more apart in a front area than in a further rear area when being ejected. It can be achieved in this way that the wind prevailing around the housing Drives housing elements apart. If threads are attached to the housing elements, the thread load can be driven far apart.
  • a detonation means and the housing are designed in such a way that, when the detonation means detonates, the housing bursts open first and / or more in a front area than in a further rear area.
  • the invention is also directed to a system comprising one or more missiles according to the invention and a grenade launcher.
  • a favorable production of the missile or the entire system can be achieved if the grenade launcher is equipped as ammunition with a cartridge with a propellant and an active body and the missile has an identical active body.
  • the active body which is, for example, a detonation body, can be used both in the grenade launcher and in the missile, or active bodies already known from a known grenade launcher can be used for the missile.
  • the active body can be made particularly simple and the system can be cost-effective if the active body is equipped with an impact fuse and the missile has an ignition trigger that contains a mechanism that simulates an impact of the active body when triggered so that it detonates in the missile.
  • the invention is further directed to a missile launcher with a missile as described above for the invention.
  • the missile launcher is used to launch the missile, for example in the form of a barrel.
  • the invention is also directed to a system of several missiles in accordance with the above description of the invention and several different active bodies.
  • a cost-effective system can be achieved if the missiles all have an identical payload chamber in which the various active bodies can be inserted and locked without tools.
  • the active bodies can expediently be ignited by the control unit.
  • Such a modular structure allows identical missile fuselages to be equipped with different active bodies, so that a high degree of versatility in use can be achieved at low costs.
  • the active bodies advantageously have an identical outer circumference.
  • the tool-free insertion of the active body is advantageously possible with existing neighboring modules, such as a drive of the missile and a control unit or control electronics.
  • An advantageous embodiment variant of the invention provides that an ignition trigger for igniting the active body is arranged in each of the payload chambers and the ignition triggers are different and adapted to the respective active body.
  • a simple insertion of the active body into the missile fuselage can be achieved if a firing trigger with its active body together form a firmly connected package, which can be inserted into the payload chamber as a whole - expediently without tools - and assembled there as a whole ready for use.
  • the packages are expediently all uniform in their external shape. Uniform interfaces to the control unit are also advantageous.
  • the invention is directed to a method for fighting drones according to claim 15.
  • a precise control of the missile to the drone can be achieved if, according to the invention, a seeker head of the missile detects the drone with an optical viewfinder.
  • a control unit of the missile can steer it to the target using the viewfinder data, even if the missile performs its own flight movements during the approach of the missile.
  • the predefined position in which the active body of the missile is triggered can be established by predetermining the distance and / or direction of the missile to the drone.
  • a drive of the missile is thrown from a housing of the missile before the active body is triggered, and the active body acts through a drive space in which the drive was stored before it was released.
  • This can also be understood to mean a discharge of the active body wholly or partially through the drive space.
  • the drive can be ejected from the housing and ejected or, together with a housing part surrounding it, can be separated from a front housing part and ejected.
  • the seeker head detects the drone autonomously during the approach and the active body is triggered if the drone is located within a given space.
  • a check is expediently carried out by the control unit during the Approach made to determine whether the drone is in a specified position, for example within a specified lounge area.
  • a target is expediently categorized as a target to be approached only if it lies within a predetermined range voltage.
  • the distance voltage expediently extends up to a maximum normal optical detection of the drone in question by a human eye. This maximum distance can be specified in advance or result from a categorization of the drone during the approach.
  • FIG 1 shows a missile 2 for combating drones, which is designed as a rocket missile with a rocket motor as drive 4.
  • a propeller drive with an electric motor fed by a battery or a rechargeable battery is also possible.
  • the missile 2 is a guided missile with steering blades 6, which are rotatable in their entire outer surface by an actuator (not shown), which is arranged between a housing 8 and the drive 4.
  • the four steering drives are controlled by a control unit 10, which is arranged behind a seeker head 12, which has an optical viewfinder 14 and an image detector (not shown) for capturing images of a drone to be intercepted.
  • the missile 2 is also equipped with a gliding wing 16, which has a lift profile similar to that of aircraft.
  • the missile 2 is designed to prevent a drone to be intercepted from continuing to fly and for this purpose comprises an active body 18 in a payload chamber 20 FIG 1
  • the active body 18 is a high-explosive grenade with rubber shot and a front impact fuse.
  • the active body 18 is arranged with its front impact fuse on an ignition trigger 22 which, when triggered, simulates an impact of the active body 18, so that it detonates.
  • the ignition trigger 22 contains a mechanism which strikes the percussion fuse of the active body 18 from the front.
  • the entire active body package comprising active body 18 and ignition trigger 22 is arranged at an interface 24 for signal transmission to control unit 10, so that ignition trigger 22 can be triggered by control unit 10.
  • the payload chamber 20 further contains a parachute 26, which enables the missile 2 to float downward after its mission has been completed, held on the parachute 26, so that injury to persons by the falling missile 2 is counteracted.
  • FIG 2 shows the missile 2 after it has been launched from a missile launcher 28.
  • the missile launcher 28 comprises a plurality of canisters, in each of which a missile 2 is stored.
  • a control unit 30 of the missile launcher 28 can launch one or more missiles 2 one after the other.
  • a plurality of such missile launchers 28 are arranged, for example, around a large event in such a way that the missile 2 can be launched without danger.
  • the event site is monitored, for example, from the air or from an elevated location by one or more operators or automatically by means of one or more cameras.
  • an operator or a control unit transmits a command to start a missile 2 to the control unit 30 of the missile launcher 28.
  • a missile 2 starts from a tube of the missile launcher 28, for example vertically upwards.
  • the missile 2 has a diameter of about 5 cm along its housing 8, and a tube of the missile launcher 28 has an outer diameter of about 7 cm. It is thus very easily possible to have a missile launcher with a single tube carried by an operator and shoot the missile 2 by hand, for example by pointing the missile launcher at the drone 32 and pulling a trigger, whereupon the missile 2 comes out of the missile launcher starts. For example, several operators in and around an event site can be equipped with such a missile launcher and shoot the missile 2 by hand in the event of a potential threat from a drone 32.
  • a third possibility consists in aligning the missile launcher 28 in the direction of the drone 32 before a missile 2 is launched, so that the drone 32 in the Seeker 14 of missile 2 appears visible. All three variants are briefly described below.
  • the missile 2 is intended to approach the drone 32 and either hit it directly or trigger its active body 18 in the immediate vicinity of it. Instead of a drone 32, it is generally also possible to fight or intercept another aircraft. In order to be able to approach the drone 32, it makes sense if the control unit 10 recognizes the drone 32 as such or classifies it as an object to be approached. If the viewfinder 14 is a rigid viewfinder, it is necessary for the missile 2 to be at least substantially aligned with the drone 32 in order to image it through the viewfinder 14 onto the detector. With a vertical start, as in FIG 2 In this respect, a preliminary instruction is necessary, which is transferred by the control unit 30 or another control unit to the missile 2 or its control unit 10. For example, a start trajectory is specified, along which the missile 2 flies until it automatically detects the drone 32. The launch trajectory can be calculated in a simple manner from the positions of the missile launcher 28 and the drone 32 as well as missile data.
  • Pre-instruction can be simplified if the missile launcher 28 is aimed at the drone 32 to be intercepted before the missile 2 is launched.
  • the drone 32 can be recognized by the viewfinder 14 of the missile 2 even without a change in direction of the missile 2 and the missile 2 can independently control the drone 32 immediately after take-off.
  • the same also applies to a launch from a missile launcher carried by the operator, which is aimed at the drone 32 before the launch.
  • the drone 32 can, for example, be targeted by optics of the missile launcher 28 or the manual missile launcher, and a marking can be logged on the image of the drone 32.
  • the image marked in this way is transferred to the control unit 10 of the missile 2, which then independently searches for a comparable image through its viewfinder 14 and, once it is found, follows the corresponding image and thus the drone 32.
  • a preliminary instruction can be dispensed with entirely if the control unit 10 is set up to independently find a drone 32 to be intercepted.
  • the control unit 10 can expediently classify a drone 32 as such and expediently also decide whether it should be intercepted.
  • a A suitable decision criterion is a distance from the missile launcher 28 or a manual missile launcher to the drone 32. If no distance measurement is available, the distance can be estimated from the optical size of the drone 32 in the search image. If the drone 32 is closer than an interception distance 34 to the missile launcher 28, the drone 32 is intercepted.
  • the control unit 10 If the actual or estimated distance is greater than the interception distance 34, for example greater than 800 m, the drone 32 is not intercepted since the control unit 10 assumes that this is not the drone 32 to be intercepted recognized by an operator, since this is hardly visible due to the great distance. The control unit 10 will now search for another drone 32 to be intercepted with the aid of the seeker head 12.
  • the mission is ended and the parachute 26 is ejected. Suspended on the parachute 26, the missile 2 slides downward, so that injury to people by a rapidly falling missile 2 is counteracted.
  • the missile 2 flies directly to or in the vicinity of the drone 32 and triggers the active body 18 if it is located closer than an interception distance to the drone 32.
  • the distance of the missile 2 to the drone 32 is estimated here by the control unit 10 on the basis of optical data from the seeker head 12, and the triggering of the active body 18 is also controlled by the control unit 10.
  • the active body 18 is triggered with its rubber shot and the drone 32 is destroyed as a result.
  • the parachute 26 is ejected and the missile 2 slides hanging on the parachute 26 to the ground.
  • FIG 1 it can be seen that the parachute 26 is accommodated within the housing 8 in front of the drive 4 in the direction of flight of the missile 2.
  • the drive 4 is held detachably in or on the housing 8. After the burn-up of the drive 4 or towards the end of the burn-up, the drive 4 is ejected to the rear, and a drive space 36 in which the drive 4 was positioned during take-off becomes free.
  • the drive can be designed in such a way that, towards the end of its burn-up, it ejects combustion gases to the front, so that a high overpressure arises in front of the drive 4, through which the Drive 4 is ejected to the rear.
  • an explosive device is possible, which is located in front of the drive 4 and pushes the drive 4 to the rear through the deployment of explosion gases.
  • the burn-off gases can unfold freely or be held in a cushion, analogous to an airbag that ejects the drive 4 towards the rear. It is also possible to throw off the drive 4 together with the housing part surrounding it. Ejection of the drive 4 is shown schematically in FIG FIG 2 shown.
  • the drive space 36 is now free and the parachute 26 can be ejected to the rear through the drive space 36 by igniting or triggering an ejection element. This is shown schematically and by way of example in FIG 3 shown. Tangling of the parachute 26 on the steering blades 6 can be avoided in this way.
  • the missile 2 can be reliably braked and gently brought back to the surface of the earth.
  • the active body 18, which can also include the parachute 26 receives an additional degree of freedom of action, since it can now be dropped to the rear through the drive space 36, which previously would not have been possible with the drive 4 placed there.
  • a safety net 40 can be attached to the parachute 26, which is driven even further radially outward by a corresponding aerodynamic configuration than the parachute 26 itself.
  • a safety net 40 is in FIG 3 indicated only schematically by dashed lines.
  • parachute 26 Another possibility is to make the parachute 26 very large so that it extends radially very far around the missile 2. For this purpose, it can have a multiplicity of openings 42 in order to reduce its air resistance to a size appropriate for the missile 2.
  • FIG 4 shows a missile 2, which is essentially analogous to the missile 2 from FIG 1 is constructed, but contains a different active body 18.
  • the following description is essentially limited to the differences from the exemplary embodiment in FIG Figures 1 to 3 , to which reference is made for features and functions that remain the same.
  • all features of a previous exemplary embodiment are generally adopted in each of the following exemplary embodiments without being described again, unless features are described as differences from the previous exemplary embodiment.
  • the missile 2 from FIG 4 comprises a thread load 44 with a multiplicity of threads 46.
  • the threads 46 are fastened at their front end to the seeker head 12 either directly or indirectly and are connected at their rear end to a weight 48, in this exemplary embodiment housing parts of the housing 8
  • the housing 8 - controlled by the control unit 10 at the time at which the missile 2 is in the vicinity of the drone 32 - was blown up in the area around the payload chamber 20.
  • the housing 8 has predetermined breaking lines in the area of the payload chamber 20, along which the housing 8 breaks apart when the ejector is triggered into a multiplicity of housing elements that serve as weights 48.
  • Each of the housing elements defined by the predetermined breaking lines is connected to at least one thread 46 and, due to its high kinetic energy gained during the explosion, carries this far radially outward, so that a large radius of action of the missile 2 is achieved.
  • the drone 32 to be intercepted can be hit by threads 46 that are entangled in at least one rotor of the drone 32 even if the control is only relatively imprecise.
  • the drone 32 which is thereby tied to the missile 2, is carried along by the missile 2 and crashes in order to then, bound to the missile 2, float down with it on the parachute 26.
  • a holding element 50 for example a holding rod, can prevent the missile 2 from breaking when the housing 8 explodes and the front part with the seeker head 12 falls down in an uncontrolled manner.
  • the detonation of the housing 8 can take place in such a way that it is pushed outward first or more at the front than further back.
  • the air flowing around the missile 2 from the front engages the bursting housing elements and additionally drives them radially outward.
  • the threads 46 can also be thrown out loosely, that is to say not attached to the missile 2.
  • weights 48 for example as housing elements, can pull the threads 46 outward, alternatively without the weights 48, and the threads are only driven outward by a corresponding detonation charge.
  • the drone 32 becomes entangled in the threads 46 with one or more rotors and crashes.
  • the threads can form a thread network, that is to say they can be linked to one another several times, so that the threads 46 counteract the drone 32 slipping through.
  • the net wraps around the drone 32 and holds it in place.
  • the thread load 44 or the threads 46 can be ejected to the rear through the drive space 36.
  • the parachute 26 - if present - is placed in front of the thread load in the payload chamber 20 so that the threads 46 can first be ejected and then the parachute 26 can then be ejected through the drive space 36.
  • FIG 5 shows a possibility for locking and releasing the drive 4 in the drive space 36.
  • the rear part of the missile 2 is shown with schematically drawn steering wings 6. If the missile 2 is still in a tube of the missile launcher 28, the steering wings 6 are folded in around a compact one To enable arrangement in the missile launcher 28. This is in the top drawings of FIG 5 shown, from the side (left illustration) and from behind (right illustration). The steering wings 6 are folded in against a spring force and unfold as soon as the rear part of the missile 2 has left the tube or the missile launcher 28. The steering wings fold out, as in the illustrations below FIG 5 is shown.
  • each steering wing 6 carries a drive lock 52, for example in the form of a nose, which is rigidly connected to the rest of the steering wing 6. If the steering wing 6 folds out, the position of the drive lock 52 of the steering wing 6 also changes. If the steering wings 6 are folded in, the drive locks 52 grip radially inward and form a form fit behind the drive 4, as shown in FIG FIG 5 , upper right illustration can be seen. The drive 4 cannot fall out to the rear and is held securely in the missile launcher 28 during its storage. After the missile 2 has taken off, the steering wings fold out and the drive locks 52 fold radially outwards, as in the lower right-hand part of FIG FIG 5 is shown.
  • the drive 4 is now released to the rear and can fall out. During its push or burn, however, the drive 4 pushes forward to a sufficient extent to reliably prevent it from falling out.
  • the drive 4 is only ejected when it finishes its advance or by an ejection unit, as described above, or when it ejects itself through its thrust reversal.
  • the drive 4 only drives very briefly and the missile 2 flies the rest of the distance sailing and without drive in the direction of the drone 32.
  • the drive 4 and the weight and aerodynamics of the missile 2 are coordinated with one another in such a way that the drive 4 only drives or burns over a maximum predetermined period of time.
  • a pushing distance 54 or burnout distance is expediently less than 200 m, in particular less than 100 m.
  • a pushing or burning time of the drive 4 is a maximum of 3 seconds, in particular a maximum of 2 seconds.
  • the drive 4 is ejected early and the missile 2 is available for intercepting the drone 32 after a short time.
  • Drones 32 are simple units that can be obtained from a model shop with little money. In order to combat a drone 32 efficiently, the manufacture of a missile 2 for combating drones should therefore also be as inexpensive as possible respectively. FIG 6 shows several measures with which inexpensive production is facilitated.
  • FIG 6 shows three missiles 2, which are identical except for the contents of the payload chamber 20.
  • the missile 2a shown at the top carries, as active body 18a, a grenade 56 with an impact fuse, such as a rubber shot grenade, which, for example, leads to FIG 1 is described.
  • a parachute 26 how to FIG 1 described can be present, but does not have to be present.
  • the active body 18 can be a projectile, in particular a grenade 56.
  • the active body 18 is a grenade 56, as it is fired by a conventional grenade launcher 58.
  • the grenade 56 is in a cartridge 60, which houses a propellant for firing the grenade 56 from the grenade launcher 58.
  • the ammunition of the grenade launcher 58 can now be used as an active body 18a in the missile 2a.
  • the grenade 56 for example, is separated from the cartridge 60 and inserted into the payload chamber 20. In-house production of an active body 18 for use in a missile 2 for combating drones can be dispensed with.
  • the active body 18b consists of a thread load 44 with a corresponding ejector and possibly also a parachute 26.
  • the active body 18c is a parachute 26 with a safety net 40. All three active bodies 18a-c are designed the same in such a way that they can be tool-free can be inserted through an opening in the housing 8 into the payload chamber 20 and fastened there, touching the interface 24 of the control unit 10 with a signal interface, so that a signal connection between the control unit 10 and the active body 18 is achieved.
  • the active bodies 18 are all designed with the same maximum outer radius, which is matched to the capacity or the dimensions of the payload chamber 20.
  • a missile 2 can be provided with the corresponding active charge 18 depending on the application, so that a very simple and inexpensive production of the missile 2 is made possible. For example, it is possible to deliver a large number of missiles 2 without active bodies 18 and to add a variation of active bodies. Before use, a decision can be made - possibly even on site - as to how the drone 32 is to be intercepted and which active body 18 is to be used in this respect. The active body can easily be inserted into the missile 2 or its payload chamber 20 without tools, and the missile 2 is ready for use.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Claims (15)

  1. Missile (2) de lutte contre les drones, comprenant un mécanisme de propulsion (4) et un boîtier (8) autour du mécanisme de propulsion (4) et un corps actif (18) destiné à endommager un drone (32), une tête chercheuse (12) comprenant un viseur optique (14) et une unité de commande (10) servant à la reconnaissance de drone, destinée à commander un vol d'approche vers le drone (32) reconnu et à déclencher le corps actif (18),
    caractérisé en ce
    que le mécanisme de propulsion (4) est maintenu détachable par rapport au boîtier (8) de telle sorte qu'il peut être éjecté pendant le vol, et le corps actif (18) est disposé par rapport au mécanisme de propulsion (4) de telle sorte que l'éjection lui procure un degré de liberté d'action.
  2. Missile (2) selon la revendication 1, caractérisé par un parachute (26), qui est disposé dans une chambre à charge utile (20) devant le mécanisme de propulsion (4) dans la direction du vol et qui est réalisé conjointement avec un déclencheur de telle sorte que lors du déclenchement, il est éjecté vers l'arrière à travers un espace de propulsion (36).
  3. Missile (2) selon la revendication 1 ou 2, caractérisé par au moins une aile articulée (6) destinée à être déployée après le lancement et à guider le vol, et un mécanisme de verrouillage de la propulsion (52), qui est relié à l'aile articulée (6) de telle sorte qu'un déploiement de l'aile articulée (6) déplace mécaniquement le mécanisme de verrouillage de la propulsion (52) de telle sorte qu'il libère le mécanisme de propulsion (4) en vue de l'éjection, un mécanisme de verrouillage de la propulsion (52) étant relié de manière rigide à l'aile articulée (6).
  4. Missile (2) selon l'une des revendications précédentes, caractérisé en ce que le mécanisme de propulsion (4) et le boîtier (8) sont configurés de telle sorte que le mécanisme de propulsion (4) peut être éjecté librement vers l'arrière après une poussée lors du lancement.
  5. Missile (2) selon l'une des revendications précédentes, caractérisé en ce que le mécanisme de propulsion (4) est réalisé de telle sorte qu'il est éjecté hors du boîtier (8) par une inversion de poussée, le mécanisme de propulsion (4) et le boîtier (8) étant configurés de telle sorte que le mécanisme de propulsion (4), lequel est conçu pour appliquer une propulsion pendant une période prédéterminée, développe vers la fin de la période une pression dans le boîtier (8) qui expulse le mécanisme de propulsion (4) hors du boîtier (8).
  6. Missile (2) selon l'une des revendications précédentes, caractérisé par un poids et un aérodynamisme et en ce que le mécanisme de propulsion (4) est conçu pour appliquer une propulsion pendant une période prédéterminée qui, en collaboration avec le poids et l'aérodynamisme, est dimensionnée de telle sorte que le mécanisme de propulsion (4) met fin normalement à sa poussée après le lancement après un parcours de vol maximum de 200 m, notamment après un maximum de 100 m.
  7. Missile (2) selon l'une des revendications précédentes, caractérisé par une chambre à charge utile (20), dans laquelle sont disposés le corps actif (18) et un déclencheur d'allumage (22) destiné à allumer le corps actif (18), le corps actif (18) possédant un allumeur à percussion et le déclencheur d'allumage (22) contenant un mécanisme qui simule une frappe du corps actif (18) lors du déclenchement.
  8. Missile (2) selon l'une des revendications précédentes, caractérisé par une charge à fils (44) et un éjecteur destiné à éjecter la charge à fils (44) contenant une pluralité de fils (46).
  9. Missile (2) selon la revendication 8, caractérisé en ce que la charge à fils (44) forme des fils (46) détachés ou un réseau de fils, des poids (48) sont montés sur les fils (46), lesquels sont accélérés lors de l'éjection, et les poids (48) sont des éléments de boîtier.
  10. Missile (2) selon la revendication 8 ou 9, caractérisé en ce que l'éjecteur et le boîtier (8) sont réalisés de telle sorte que les éléments de boîtier du boîtier (8), lors de l'éjection, sont tout d'abord et/ou davantage écartés les uns des autres dans une zone avant que dans une zone qui se trouve plus à l'arrière, de sorte que le vent de déplacement qui règne autour du boîtier (8) entraîne les éléments de boîtier les uns à l'écart des autres.
  11. Système composé de plusieurs missiles selon l'une des revendications précédentes et de plusieurs corps actifs (18) différents,
    caractérisé en ce
    que les missiles (2) possèdent tous une chambre à charge utile (20) identique, dans laquelle les différents corps actifs (18) peuvent être introduits et verrouillés sans outils de telle sorte qu'ils peuvent être allumés depuis l'unité de commande (10).
  12. Système selon la revendication 11, caractérisé en ce qu'un déclencheur d'allumage (22) destiné à allumer le corps actif (18) est respectivement disposé dans les chambres à charge utile (20), les déclencheurs d'allumage (22) sont différents et adaptés aux corps actifs (18) respectifs, et les déclencheurs d'allumage (22) et les corps actifs (18) forment ensemble, dans chaque missile (2), respectivement un paquet assemblé de manière fixe et les paquets sont tous homogènes au niveau de leur forme extérieure et de leur interface avec l'unité de commande (10).
  13. Système composé d'un ou de plusieurs missiles (2) selon l'une des revendications précédentes et d'un lance-grenade (58), caractérisé en ce que le lance-grenade (58) est équipé, comme munition, d'une cartouche (60) pourvue d'un bloc de propergol et d'un corps actif (18), et le missile (2) possède un corps actif (18) identique.
  14. Système selon la revendication 13, caractérisé en ce que le corps actif (18) est équipé d'un allumeur à percussion et le missile (2) possède un déclencheur d'allumage (22), lequel contient un mécanisme qui simule une frappe du corps actif (18) lors du déclenchement, de sorte que celui-ci détone dans le missile (2).
  15. Procédé de lutte contre les drones, avec lequel un missile (2) et lancé et un corps actif (18) du missile (2) est déclenché dès que le missile (2) vole dans une position prédéfinie par rapport à un drone (32) et endommage au moins le drone (32), une tête chercheuse (12) du missile (2) détectant le drone (32) avec un viseur optique (14),
    caractérisé en ce
    qu'un mécanisme de propulsion (4) du missile (2) est éjecté d'un boîtier (8) avant un déclenchement du corps actif (18) et le corps actif (18) agit à travers un espace de propulsion (36) dans lequel était logé le mécanisme de propulsion (4) avant l'éjection.
EP18758540.1A 2017-09-09 2018-08-09 Missile de lutte anti-drone Active EP3679314B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102017008489.0A DE102017008489A1 (de) 2017-09-09 2017-09-09 Flugkörper zur Drohnenbekämpfung
PCT/EP2018/000397 WO2019048074A1 (fr) 2017-09-09 2018-08-09 Missile de lutte anti-drone

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Publication Number Publication Date
EP3679314A1 EP3679314A1 (fr) 2020-07-15
EP3679314B1 true EP3679314B1 (fr) 2021-06-16

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DE (1) DE102017008489A1 (fr)
WO (1) WO2019048074A1 (fr)

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Publication number Priority date Publication date Assignee Title
GB201905128D0 (en) * 2019-04-11 2019-05-29 Secr Defence Entanglement device and method of use
CN110553548A (zh) * 2019-08-30 2019-12-10 江西洪都航空工业集团有限责任公司 一种基于固定翼平台的反无人机***
DE102020003043A1 (de) 2020-05-20 2021-11-25 SDT Industrial Technology UG (haftungsbeschränkt) Das Luftraum-Schutz-System gegen die Flugobjekte
CN111998730A (zh) * 2020-09-10 2020-11-27 邯郸元一无人机科技有限公司 一种电动火箭装置
CN116902246B (zh) * 2023-09-12 2023-12-12 成都庆龙航空科技有限公司 一种无人机侦查识别装置

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5750918A (en) * 1995-10-17 1998-05-12 Foster-Miller, Inc. Ballistically deployed restraining net
US8387540B2 (en) * 2008-08-11 2013-03-05 Raytheon Company Interceptor projectile and method of use
US10399674B2 (en) * 2014-07-28 2019-09-03 Insitu, Inc. Systems and methods countering an unmanned air vehicle
GB2538826B (en) * 2015-04-22 2021-06-23 Openworks Eng Ltd System for deploying a first object for capturing, immobilising or disabling a second object
US9476677B1 (en) * 2015-06-04 2016-10-25 Raytheon Company Long range KV-to-KV communications to inform target selection of follower KVS
JP2017009244A (ja) 2015-06-25 2017-01-12 株式会社ディスコ 小型無人飛行機撃退装置
DE102015008255B4 (de) * 2015-06-26 2017-10-19 Diehl Defence Gmbh & Co. Kg Abwehrdrohne zur Abwehr einer Kleindrohne
US20170059692A1 (en) * 2015-08-28 2017-03-02 Laufer Wind Group Llc Mitigation of Small Unmanned Aircraft Systems Threats
US10005556B2 (en) * 2015-11-25 2018-06-26 Mohammad Rastgaar Aagaah Drone having drone-catching feature
DE202016105223U1 (de) * 2016-09-19 2016-12-05 Wood-Flame Gmbh Munition für eine Schussvorrichtung zur Drohnenabwehr, Schussvorrichtung und Abfangdrohne

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DE102017008489A1 (de) 2019-03-14
WO2019048074A1 (fr) 2019-03-14

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