WO2019048074A1 - Missile de lutte anti-drone - Google Patents

Missile de lutte anti-drone Download PDF

Info

Publication number
WO2019048074A1
WO2019048074A1 PCT/EP2018/000397 EP2018000397W WO2019048074A1 WO 2019048074 A1 WO2019048074 A1 WO 2019048074A1 EP 2018000397 W EP2018000397 W EP 2018000397W WO 2019048074 A1 WO2019048074 A1 WO 2019048074A1
Authority
WO
WIPO (PCT)
Prior art keywords
missile
drive
drone
housing
active body
Prior art date
Application number
PCT/EP2018/000397
Other languages
German (de)
English (en)
Inventor
René FRETER
Martin Walzer
Peter Gerd Fisch
Original Assignee
Diehl Defence Gmbh & Co. Kg
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Diehl Defence Gmbh & Co. Kg filed Critical Diehl Defence Gmbh & Co. Kg
Priority to EP18758540.1A priority Critical patent/EP3679314B1/fr
Publication of WO2019048074A1 publication Critical patent/WO2019048074A1/fr

Links

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 drone control 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 efficient, both in terms of their payload and in terms of their control and flight capabilities.
  • model drones can be easily remotely controlled over long distances, without the need to keep an eye on the ground-based pilot.
  • Such a defense device is known from DE 10 2016 211 371 A1. From a launcher, an arrow-like missile is launched, which includes a net thrower at its front end. If the missile comes close to the
  • the drone is captured and the drone entangled with the missile falls to the ground on a parachute.
  • a missile of the aforementioned type which according to the invention has a seeker with an optical viewfinder and a control unit for drone detection and for controlling a approach to the recognized drone and to trigger the active body.
  • the invention is based on the consideration that small and light drones are difficult to hit only by a directed launch. In particular, the capture by means of a network requires a high accuracy of the approaching missile.
  • the missile can specifically
  • Movements of an agile drone tracked so that a target approach can be precise and the triggering of the active body in sufficient proximity to the drone.
  • an unmanned aerial vehicle such as a remote-controlled aircraft, in particular up to twenty kilograms total weight, to be understood, for example, from the hobby field of model aircraft construction. It can be a so-called
  • a drone may be a rotorcraft, in particular with a plurality of rotors, for example a quadrocopter or a hexacopter. However, it is also possible a fixed wing or only wing.
  • the control unit is prepared for drone detection, in particular based on data from the viewfinder or a detector of the seeker head.
  • a drone recognition can be understood as both the holding of a given goal and an autonomous recognition of the target as such.
  • a missile launcher for firing the missile with an optic or another
  • Target detection system equipped with which the target is detected and to the
  • Control unit is prepared to hold the transferred target in such a way that thereby the missile is controlled to the destination. However, a more rapid launch is possible if the drone detection is done by the missile itself.
  • image processing algorithms can be used by the control unit, with which the target is recognized as such.
  • identify the target classify the target into one of several different classes of different missiles.
  • the control unit may have characteristics of the missile, such as optical
  • a classification of the missile includes a
  • the control unit is able to distinguish between rotorcraft and fixed-wing aircraft or classify the drone as rotorcraft or fixed-wing aircraft.
  • the active body is at least prepared to damage the drone.
  • Damage may be a reduction or termination of the drone's flying capacity. This can be done by mechanical and / or electronic means, for example by radiation to disrupt radio communications and / or
  • the active body may contain a microwave transmitter or a transmitter in a different frequency range, which points to a control command
  • Active radiation emits to damage the drone.
  • a complete destruction is possible, for example, a crash causing breaking off parts of the drone.
  • the active body may have an explosive charge, a shot load or the like, for example rubber.
  • the control unit is used to control the approach of the missile to the recognized drone. Conveniently, this is an autonomous approach to the drone, without the need for a continuous control of an operator.
  • the seeker can be an artillery seeker, so a seeker, as in artillery projectiles
  • the drive is a rocket engine advantageous, with a propeller drive with a battery and a battery is possible.
  • the missile is fired by a hand launcher or battery launcher, hereinafter referred to simply as a launcher.
  • a launcher for 40 mm caliber missiles or missiles.
  • Controllability can be facilitated if the active body has an ejection of a
  • Acting element can cause to the rear, if possible without destroying the
  • the drive is releasably held in the housing in such a way that it can be dropped in flight.
  • the active body is arranged to drive so that he wins by the ejection a degree of freedom of action. A degree of freedom of action is then obtained if, due to the ejection, an effect of the active body can be achieved which is not or not yet possible before the ejection.
  • the drive may be detachably mounted in the housing so that it can be dropped in flight and thus ejected from the housing. It is also possible that the drive is releasably held to the housing in such a way that it can be dropped together in flight with the surrounding housing part. Drive and a rear one
  • Housing part are releasably held to a front housing part, so that
  • the drone and / or the missile glides down on a parachute.
  • the missile has a parachute, which is arranged in a payload chamber of the missile. The arrangement may be in the direction of flight before the drive, in particular immediately before the drive. If the drive is abwerfbär, so the parachute can be ejected by a drive space, which is consistent by the dropping of the drive, to the rear. Ejecting backwards is much easier and involves much less risk of tangling
  • a trigger may be present, which is designed together with the parachute so that it throws the parachute back through a drive space when triggered.
  • the drive space which houses the drive before and at the start of the missile, is free to the extent that the parachute can be ejected through the drive space to the rear after dropping the drive.
  • a starting of the missile is expediently made of a tube from which the missile is ejected either by a cartridge, but in particular by its own drive.
  • For a steerable control of the missile to the target steering wings are advantageous, which are advantageously arranged at the rear of the missile.
  • a wing has at least one to the housing of the missile movable control surface as an outer surface whose movement is suitably controlled by the control unit.
  • control wings are present, which are designed as folding wings. Folding wings can be folded in the tube and unfold after Rohrverschuss or leaving the missile from the tube and thereby protrude, for example, vertically radially from the housing and allow control of the missile by the corresponding control surface.
  • the drive If the drive is to be dropped, then it makes sense if it is locked in the housing or its drive space before and during the start in such a way that it does not fall out of the housing or drive space erroneously. Conveniently, this is a drive lock available that locks the drive so in the housing or drive compartment that falling out is blocked.
  • a simple drive lock can be achieved when it is so connected to a folding wing that folding the flap mechanically moves the drive lock so that it releases the drive for dropping.
  • a mechanical positive connection can be released, so that the drive is now ejectable.
  • the drive and housing are designed so that the drive is freely ejectable after a push at a start to the rear. If, for example, 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 start and thus remain pressed into the housing. If the push-in latches, is stopped or otherwise deflected, 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 wing. By unfolding, for example, a molding can be moved into a release position, so that a previously performed by the nose blocking positive engagement is solved.
  • a simple ejection of the drive from the housing or a drive space can be achieved if the drive is designed so that it is ejected by its thrust reverser from the housing. It is also advantageous if the drive and the housing are designed so that the drive to the
  • Driving is carried out over a predetermined period, towards the end of the
  • the drive may cause a forward gas discharge that creates a gas pressure prior to driving that ejects the drive from the housing.
  • a drone to be intercepted is usually small and thus only over short
  • the weight and aerodynamics of the missile characterized in that the drive is designed to drive over a predetermined period of time, and this period in conjunction with weight and aerodynamics is such that the drive his thrust after predetermined maximum distance after starting regularly finished.
  • the maximum drive range can be adjusted appropriately.
  • the used active body is, for example, a ballistic projectile, so this then, for example, must be used only in a payload chamber of the missile.
  • the missile has a payload chamber in which the active body is arranged, expediently together with a
  • the detonator can be adapted to the ignition of the active body, so that when using different active body only the appropriate detonator must be adjusted. If, for example, the active body has an impact fuze, then it is advantageous if the detonation release contains a mechanism which, when triggered, simulates an impact of the active body. In general, it is expedient if the ignition trigger is connected by a signal line to the control unit, expediently via a mechanical interface. For example, a composite of detonator and active body can be inserted into the payload chamber, wherein an electrical contact with the
  • Control unit is manufactured by the mechanical interface
  • a drone usually includes rotating parts, such as a rotor, a propeller or even a turbine, which can be brought to a stop by a net, or more generally a thread. In this way, while the drone may be prevented from flying on and thus damaged, it does not have to be destroyed. To achieve this, it is advantageous if the missile has a thread load and an ejector for ejecting the thread load.
  • the thread load contains a multiplicity of threads.
  • a thread is an elongated and flexible element whose material is of minor importance, so it can be insofar as a plastic, a natural material, a composite material, metal or other material.
  • the ejector may contain a detonating agent, by the explosion of the threads are ejected. The ejection can be done to the rear, in particular by a drive space or laterally, for example, by blowing off a
  • the thread load may include loose threads that are not attached to the missile and / or not attached to each other.
  • the threads become entangled in a rotating one
  • the threads may be connected at least one end at least indirectly to the housing of the missile. They can form a thread network with which the drone can be captured. In order to keep the weight of the missile as low as possible, the threads have only a low weight, which could be negatively noticeable in their distribution in the surrounding space around the missile, as they are not scattered even in a detonative deployment not far in the area. To this disadvantage too
  • weights are attached to the threads that are squandered with the ejection.
  • the weights can be the threads
  • each thread with its own weight or to attach several threads to one weight so that several threads of a weight fly tuft-like through the air.
  • the weights are housing elements.
  • the housing can be broken and the individual housing elements can pull the threads into the enclosure.
  • the housing contains predetermined breaking points or predetermined breaking lines, which divide it into individual housing elements. At one, several or each so divided housing element expediently at least one thread is attached.
  • Housing elements can insofar be pipe parts, in particular pipe strips.
  • the threads on housing elements in particular when the housing elements are driven apart, form a net.
  • the threads are at least indirectly attached to the seeker.
  • the threads may be attached to the case or attached to it
  • the missile and the drone remain connected to each other and can, for example, slide down a parachute.
  • the threads may be attached to a housing member to achieve a large amount of sling, for example on a part of the housing around the payload space and / or the drive space.
  • the ejector and the housing are designed so that the
  • a detonation means and the housing are designed such that the housing bursts first and / or more in a front area on detonation of the detonation means than in a region located further back.
  • the invention is also directed to a missile system
  • Grenade launcher as ammunition with a cartridge with a propellant and a
  • Active body is equipped 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 can be used for the missile already known active body from a known grenade launcher.
  • the active body can be made particularly simple and insofar the system be inexpensive if the active body is equipped with an impact fuse and the missile has a detonator containing a mechanism that simulates an impact of the active body when triggered, so that it detonates in the missile.
  • the invention is directed to a missile launcher having a missile as described above for the invention.
  • the missile launcher is used to fire the missile, for example in the form of a pipe shot.
  • the invention is also directed to a multi-missile system according to the above description of the invention and several different active bodies.
  • An inexpensive system can be achieved if the missiles all have an identical payload chamber in which the various
  • Active body can be used without tools and locked. Conveniently, the active body of the control unit are ignited.
  • identical missile fuselages can be equipped with different active bodies, so that a high deployment variability can be achieved at low cost.
  • the active bodies have an identical outer circumference.
  • the tool-free insertion of the active body is advantageously possible at existing neighboring modules, such as a propulsion of the missile and a
  • Control unit or control electronics are control unit or control electronics.
  • Payload chambers each have a detonator for igniting the active body is arranged and the detonators are different and adapted to the respective active body.
  • a simple insertion of the active body in the missile fuselage can be achieved if in each case a detonator with its active body together form a firmly connected package that can be used in particular as a whole - conveniently tool-free - in the payload chamber and assembled there as a whole ready for use.
  • the packages are all uniform in their outer shape. Uniform interfaces to the control unit are also advantageous.
  • the invention is directed to a method for drone control in which a missile is launched and an active body of the missile is triggered as soon as the missile flies in a predetermined position to the drone and at least damaged the drone.
  • 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 control this using the viewfinder data to the destination, even if this own
  • Flight movements during the approach of the missile performs.
  • Predetermination of distance and / or direction of the missile to the drone be set.
  • a drive of the missile is before triggering the
  • the drive can be ejected from the housing and dropped or separated and discarded together with a surrounding housing part of a front housing part.
  • the seeker autonomously detects the drone during the approach and the active body is triggered if the drone is within a predetermined common room.
  • a check by the control unit during the Anflugs made whether the drone is in a predetermined position, for example, within a given lounge.
  • the missile can thereby be shot down very quickly, without a previous target acquisition is necessary.
  • a target is expediently only as
  • the distance voltage expediently extends to a maximum to a normal optical detection of the drone in question by a human eye. This maximum distance may be predetermined or result from a categorization of the drone during the approach.
  • Device features also as corresponding process characteristics.
  • Embodiments serve to illustrate the invention and do not limit the invention to the combination of features specified therein, not even with regard to functional features.
  • suitable features of each embodiment can also be considered explicitly isolated from a
  • FIG 2 shows the missile launched from a launcher of FIG 1 on the
  • FIG. 3 shows a schematic representation of a missile for drone combat with a parachute
  • FIG. 5 shows a drive lock at the rear of a missile in locked and in releasing position
  • the missile 2 is a guided missile with guide vanes 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 image capturing a drone to be intercepted.
  • the missile 2 is also equipped with a sliding wing 16, which has a lift profile analogous to aircraft.
  • the missile 2 is designed to prevent a drone to be intercepted from flying on to it and for this purpose comprises an active body 18 in a payload chamber 20.
  • the active body 18 is an explosive grenade with rubber shot and a front impact fuze. Accordingly, the
  • the ignition trigger 22 includes a mechanism which strikes the impact detonator of the active body 18 from the front.
  • Packing body of active body 18 and ignition trigger 22 is arranged at an interface 24 for signal transmission to the control unit 10, so that the ignition trigger 22 can be triggered by the control unit 10.
  • the payload chamber 20 includes a parachute 26 that allows the missile 2 to float down after completion of its mission on the parachute 26, thereby preventing injury to persons from falling
  • the missile launcher 28 comprises a multiplicity of canisters, in each of which a missile 2 is mounted.
  • a control unit 30 of the missile launcher 28 one or more missiles 2 can be started in succession.
  • Several such missile launcher 28 are arranged, for example, around a major event around so that a launch of the missile 2 can safely take place.
  • 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. If a drone 32 approaches and it is decided that the drone 32 is to be intercepted, an instruction for starting a missile 2 is transmitted to the control unit 30 of the missile launcher 28 by an operator or a control unit.
  • a missile 2 takes off from a tube of the
  • Aircraft launchers 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 so far very easy to let a missile launcher with a single pipe by an operator wear and the missile 2 by hand
  • the missile launcher is directed to the drone 32 and a trigger is actuated, whereupon the missile 2 from the
  • Missile launcher starts. For example, in and around one
  • a third possibility is to align the missile launcher 28 in front of a launch of a missile 2 in the direction of the drone 32, so that the drone 32 in Viewfinder 14 of the missile 2 appears visible. All three variants are briefly described below.
  • the missile 2 is supposed 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 can generally be fought or intercepted another aircraft. In order to be able to fly to the drone 32, it makes sense if the control unit 10 recognizes the drone 32 as such or as
  • the viewfinder 14 is a rigid viewfinder, then it is necessary that the missile 2 is at least substantially aligned with the drone 32 in order to image it through the viewfinder 14 onto the detector.
  • a pre-instruction is necessary, which is passed by the control unit 30 or another control unit to the missile 2 and its control unit 10.
  • a start trajectory is given, along which the missile 2 flies until it detects the drone 32 autonomously.
  • the starting trajectory can be determined from the positions of the
  • Aircraft launcher 28 and the drone 32 and missile data are calculated in a simple manner. A pre-briefing can be simplified if the missile launcher 28 before the
  • Missile Launcher Aligned to Drone 32 Prior to Launch The drone 32 may be targeted, for example, by an optical system of the missile launcher 28 or the manual missile launcher, and a marker may be logged on the image of the drone 32. The thus marked image is transferred to the control unit 10 of the missile 2, which now independently a comparable image through his
  • Seeker 14 searches and after finding the corresponding image and thus the drone 32 pursued.
  • a pre-instruction can be dispensed with altogether if the control unit 10 is set up to find a drone 32 to be intercepted independently.
  • the control unit 10 expediently classify a drone 32 as such and expediently also decide whether it should be intercepted.
  • a suitable decision criterion is a distance from the missile launcher 28 or a manual missile launcher to drone 32. If no distance measurement is present, the distance can be determined by the optical size of the drone 32 in the
  • Search image can be estimated. If the drone 32 is closer than a trapping distance 34 to the missile launcher 28, the drone 32 is intercepted. If the actual or estimated distance is greater than the intercept distance 34, for example greater than 800 m, the drone 32 will not be intercepted because the control unit 10 assumes that this is not the drone 32 to be intercepted by an operator This is hardly visible due to the high distance.
  • the intercept distance 34 for example greater than 800 m
  • Control unit 10 is now using the seeker 12 after another
  • Parachute 26 slides the missile 2 down so that injury to persons by a rapidly falling missile 2 is counteracted.
  • the missile 2 will fly directly to or near the drone 32 and will trigger the active body 18 if closer than one
  • Catching distance to the drone 32 is located.
  • the distance of the missile 2 to the drone 32 is in this case by the control unit 10 based on optical data of the
  • Triggering of the active body 18 of the parachute 26 is ejected and the missile 2 slides on the parachute 26 hanging to the ground.
  • the parachute 26 is housed in the direction of flight of the missile 2 in front of the drive 4 within the housing 8.
  • the drive 4 is detachably held in or on the housing 8. After burnup of the drive 4 or towards the end of the burnup, the drive 4 is ejected to the rear, and a drive space 36, in which the drive 4 was positioned during the start, is released.
  • the drive 4 is detachably held in or on the housing 8. After burnup of the drive 4 or towards the end of the burnup, the drive 4 is ejected to the rear, and a drive space 36, in which the drive 4 was positioned during the start, is released.
  • Drive be designed so that it expels exhaust gases towards the end of its combustion, so that in front of the drive 4, a high pressure is created by the Drive 4 is ejected to the rear.
  • an explosive is possible, which is located in front of the drive 4 and expresses the drive 4 to the rear by the development of explosive gases.
  • the burn-off gases can unfold freely or be held in a cushion, analogously to an airbag which ejects the drive 4 to the rear. It is also possible to drop the drive 4 together with the surrounding housing part. Ejecting the drive 4 is shown schematically in FIG.
  • the drive space 36 is now free and the parachute 26 can be ignited
  • Drive space 36 are ejected. This is shown schematically and by way of example in FIG. Tangling of the parachute 26 on the steering wings 6 can be avoided thereby.
  • the missile 2 can be reliably braked and gently brought back to the earth's surface.
  • the active body 18, which may also include the parachute 26 receives an additional degree of freedom of action, since now a discharge to the rear is made possible by the drive space 36, which would not be the case with the drive 4 placed there.
  • a safety net 40 may be attached to the parachute 26, which is driven by a corresponding aerodynamic design even further radially outward than the parachute 26 itself.
  • a safety net 40 is indicated only schematically by dashed lines in FIG.
  • Another possibility is to make the parachute 26 very large so that it expands radially very far around the missile 2. For this purpose, it can carry a multiplicity of openings 42 in order to reduce its air resistance to an appropriate size for the missile 2.
  • FIG. 4 shows a missile 2, which is constructed essentially analogously to the missile 2 from FIG. 1, but contains a different active body 18. The following
  • the missile 2 of FIG 4 comprises a thread charge 44 with a plurality of threads 46.
  • the threads 46 are attached at its front end to the seeker 12 either directly or indirectly and are connected at its rear end with a weight 48, in this embodiment, housing parts of Housing 8.
  • a weight 48 in this embodiment, housing parts of Housing 8.
  • the housing 8 - controlled by the control unit 10 at the time when the missile 2 is in the vicinity of the drone 32 - blown up in the area around the payload chamber 20.
  • the housing 8 in the region of the payload chamber 20 predetermined breaking lines, along which the housing 8 upon release of the
  • Auswerfers breaks up into a variety of housing elements, which as
  • Weights 48 serve. Each of the housing elements defined by the predetermined breaking lines is connected to at least one thread 46 and carries it by its high kinetic energy gained during the explosion far radially outward, so that a large radius of action of the missile 2 is achieved. This allows the
  • intercept drone 32 are also taken in a relatively imprecise control of threads 46, which entangle in at least one rotor of the drone 32.
  • the thereby attached to the missile 2 drone 32 is entrained by the missile 2 and crashes, then tied to the missile 2 with this on the parachute 26 float down.
  • a holding element 50 for example a
  • Holding rod can prevent the missile 2 breaks when blowing the housing 8 and the front part with the seeker 12 falls uncontrollably down.
  • the blasting of the housing 8 can be carried out in such a way that it is pressed forward or more at the front than at the rear. The air flowing around the missile 2 from the front engages in the bursting housing elements and additionally drives them radially outwards.
  • the threads 46 can also be ejected loosely, ie not fastened to the missile 2. Also with this
  • Embodiments may draw weights 48, for example as housing elements, which pull threads 46 outwardly, alternatively without the weights 48, and the threads are driven outwards only by a corresponding detonation charge.
  • the drone 32 entangles with one or more rotors in the threads 46 and crashes.
  • the threads can form a thread network, that is to say be repeatedly linked to one another, so that the drone 32 is prevented from slipping through the threads 46.
  • the net wraps around the drone 32 and holds it tight.
  • the thread charge 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 first the threads 46 can 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 FIG.
  • FIG 5 Drawings of FIG 5 shown, from the side (left view) and from behind (right view).
  • the guide vanes 6 are folded against a spring force and unfold as soon as the missile 2 with its rear part of the tube
  • 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 flips out, the position of the drive lock 52 of the steering wing 6 also changes
  • the drive locks 52 engage radially inwardly and form a positive connection behind the drive 4, as shown in FIG 5, upper right view can be seen.
  • the drive 4 can not fall out to the rear and is held securely during its storage in the missile launcher 28.
  • the steering vanes fold out and the drive locks 52 fold radially outward, as shown in the lower right part of FIG.
  • the drive 4 is now released to the rear and can fall out.
  • the drive 4 pushes forward sufficiently to reliably prevent it from falling out.
  • the drive 4 is ejected only when it stops its feed or through an ejector unit, as described above, or when it ejects its own power by its thrust reverser.
  • the drive 4 drives only very briefly and the missile 2 flies the remaining distance sailing and unpowered in the direction of the drone 32.
  • a start-up distance 54 or burn-out distance is expediently less than 200 m, in particular less than 100 m.
  • a startup or burnup time of the drive 4 is a maximum of 3 seconds, in particular only a maximum of 2 seconds.
  • the drive 4 is ejected early and it is the missile 2 after a short time to intercept the drone 32 available.
  • Drones 32 are simple units that can be obtained with little resources from a model shop. For the efficient combat of a drone 32, therefore, the production of a missile 2 for drone control should be as favorable as possible respectively. 6 shows several measures with which a favorable production is facilitated.
  • the missile 2a which is shown at the top in FIG. 6, carries an active body 18a
  • Grenade 56 with impact fuze such as a rubber crumb grate, which is described for example to FIG 1.
  • a parachute 26, as described for FIG. 1, may be present, but need not be present.
  • the active body 18 may be a projectile, in particular a shell 56.
  • the active body 18 is a grenade 56, as by a conventional
  • Grenade launcher 58 is fired.
  • 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 active body 18a in the missile 2a.
  • the grenade 56 is separated from the cartridge 60 and in the
  • Payload chamber 20 used.
  • the own production of an active body 18 for use in a missile 2 for drone control can be dispensed with.
  • the active body 18b consists of a thread charge 44 with a corresponding ejector and possibly also a parachute
  • the active body 18c is a parachute 26 with a safety net 40. All three active body 18a - c are executed the same way that they are used without tools through an opening in the housing 8 in the payload chamber 20 and can be attached there , wherein they touch the interface 24 of the control unit 10 with a signal interface, so that a signal connection between
  • Control unit 10 and 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. In this way, a missile 2 can be provided depending on the application with the corresponding active charge 18, so that a very simple and cost-effective production of
  • Missile 2 is enabled. Thus, it is possible, for example, to deliver a plurality of missiles 2 without active body 18 and to add a variation of active bodies. Before the mission can - possibly even on the spot - be decided in what way the drone 32 is to be intercepted and which
  • Active body 18 insofar applies.
  • the active body can be used without tools in a simple manner in the missile 2 or its payload chamber 20, and the missile 2 is ready for use. LIST OF REFERENCE NUMBERS

Landscapes

  • 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)

Abstract

L'invention concerne un missile (2) de lutte anti-drone, comportant un système de propulsion (4) et un carter (8) qui entoure ledit système de propulsion (4) ainsi qu'un corps actif (18) destiné à endommager un drone (32). Un vol d'approche précis sur le drone (32) peut être obtenu si le missile (2) comporte un autodirecteur (12) équipé d'un capteur optique (14) et le missile comprend également une unité de commande (10) de reconnaissance de drone, destinée à commander un vol d'approche sur le drone (32) identifié et à déclencher le corps actif (18).
PCT/EP2018/000397 2017-09-09 2018-08-09 Missile de lutte anti-drone WO2019048074A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP18758540.1A EP3679314B1 (fr) 2017-09-09 2018-08-09 Missile de lutte anti-drone

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102017008489.0 2017-09-09
DE102017008489.0A DE102017008489A1 (de) 2017-09-09 2017-09-09 Flugkörper zur Drohnenbekämpfung

Publications (1)

Publication Number Publication Date
WO2019048074A1 true WO2019048074A1 (fr) 2019-03-14

Family

ID=63294188

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2018/000397 WO2019048074A1 (fr) 2017-09-09 2018-08-09 Missile de lutte anti-drone

Country Status (3)

Country Link
EP (1) EP3679314B1 (fr)
DE (1) DE102017008489A1 (fr)
WO (1) WO2019048074A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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系统
WO2020208330A1 (fr) * 2019-04-11 2020-10-15 The Secretary Of State For Defence Dstl Dispositif d'enchevêtrement et son procédé d'utilisation
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
DE102020003043A1 (de) 2020-05-20 2021-11-25 SDT Industrial Technology UG (haftungsbeschränkt) Das Luftraum-Schutz-System gegen die Flugobjekte
RU2823620C1 (ru) * 2023-04-27 2024-07-25 Алексей Игоревич Васильев Боеприпас для гранатомета против беспилотных летательных аппаратов

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2979979A1 (fr) * 2014-07-28 2016-02-03 Insitu, Inc. Systèmes et procédés destinés à contrer un véhicule aérien sans pilote
DE102016211371A1 (de) 2015-06-25 2016-12-29 Disco Corporation Abwehrvorrichtung für kleine, unbemannte luftfahrzeuge
DE102015008255A1 (de) * 2015-06-26 2016-12-29 Diehl Bgt Defence Gmbh & Co. Kg Abwehrdrohne zum Abfangen einer Kleindrohne
US20170059692A1 (en) * 2015-08-28 2017-03-02 Laufer Wind Group Llc Mitigation of Small Unmanned Aircraft Systems Threats

Family Cites Families (6)

* 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
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
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

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2979979A1 (fr) * 2014-07-28 2016-02-03 Insitu, Inc. Systèmes et procédés destinés à contrer un véhicule aérien sans pilote
DE102016211371A1 (de) 2015-06-25 2016-12-29 Disco Corporation Abwehrvorrichtung für kleine, unbemannte luftfahrzeuge
DE102015008255A1 (de) * 2015-06-26 2016-12-29 Diehl Bgt Defence Gmbh & Co. Kg Abwehrdrohne zum Abfangen einer Kleindrohne
US20170059692A1 (en) * 2015-08-28 2017-03-02 Laufer Wind Group Llc Mitigation of Small Unmanned Aircraft Systems Threats

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020208330A1 (fr) * 2019-04-11 2020-10-15 The Secretary Of State For Defence Dstl Dispositif d'enchevêtrement et son procédé d'utilisation
GB2584782B (en) * 2019-04-11 2023-04-19 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系统
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
RU2823620C1 (ru) * 2023-04-27 2024-07-25 Алексей Игоревич Васильев Боеприпас для гранатомета против беспилотных летательных аппаратов

Also Published As

Publication number Publication date
DE102017008489A1 (de) 2019-03-14
EP3679314B1 (fr) 2021-06-16
EP3679314A1 (fr) 2020-07-15

Similar Documents

Publication Publication Date Title
EP3679314B1 (fr) Missile de lutte anti-drone
EP3548833B1 (fr) Dispositif de lancement avec missile pour intercepter des drones hostiles
DE2809497C2 (de) Vorrichtung zum Ausbringen eines Scheinzieles
EP3341674B1 (fr) Système de défense contre les menaces
EP3070429B1 (fr) Projectile destiné a intercepter un petit drone
EP2213975A2 (fr) Projectile cargo
DE69523064T2 (de) Verfahren und vorrichtung zur verwendung eines von einem trägerflugzeug gestarteten gefechtskopfes zur bekämpfung von an der flugbahn des trägerflugzeuges entlang identifizierten zielen
EP3014213B1 (fr) Détonateur pour grenade de mortier et grenade de mortier pouvant être tirée par un mortier à ergot équipée d'un tel détonateur
DE102015015938A1 (de) Autonome, unbemannte Fluggeräte zur Begleitung, Eskortierung und Absicherung von Lutffahrzeugen wie Starr- und Drehflügler
EP3931087A1 (fr) Drone et procédé de lutte contre des cibles
DE69810879T2 (de) Projektil mit radialer Wirkrichtung
EP3376154B1 (fr) Procédé de protection d'un missile de croisière
DE102019135246B4 (de) Fluggerät und Verfahren zum Abfangen einer Drohne
DE102014115721A1 (de) Aktive Bremsung eines Ausstoßtriebwerkes
DE19831645A1 (de) Geschoßzünder
EP3698097B1 (fr) Leurre
DE102011089584B4 (de) Waffensystem, insbesondere Verfahren zur effektiven Bekämpfung von Schiffszielen
DE102019109360A1 (de) Inventionssystem zur Abwehr von RAM-Zielen und/oder UAVs sowie Verfahren zur Abwehr von RAM-Zielen und/oder UAVs
RU2815562C1 (ru) Устройство экранной сетевой защиты летательного аппарата
DE3924352C1 (de) Flugkörper zur Bekämpfung von Bodenzielen
DE102017002262B4 (de) Verfahren zum Verteidigen eines U-Boots gegen einen Angriff durch einen unter Wasser befindlichen Sprengkörper
DE4225233A1 (de) Abwehreinrichtung
DE102022130560A1 (de) Verfahren und Vorrichtung zur Abwehr von Luftfahrzeugen, insbesondere von unbemannten Luftfahrzeugen
WO2013020911A1 (fr) Dispositif et procédé de protection d'objets
WO2020164869A1 (fr) Procédé de lutte contre des cibles aériennes au moyen de corps volants dirigeables

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 18758540

Country of ref document: EP

Kind code of ref document: A1

WWE Wipo information: entry into national phase

Ref document number: 2018758540

Country of ref document: EP

ENP Entry into the national phase

Ref document number: 2018758540

Country of ref document: EP

Effective date: 20200409