EP2482025B1 - Procédé et dispositif de défense contre l'attaque d'un missile - Google Patents

Procédé et dispositif de défense contre l'attaque d'un missile Download PDF

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Publication number
EP2482025B1
EP2482025B1 EP12000173.0A EP12000173A EP2482025B1 EP 2482025 B1 EP2482025 B1 EP 2482025B1 EP 12000173 A EP12000173 A EP 12000173A EP 2482025 B1 EP2482025 B1 EP 2482025B1
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Prior art keywords
missile
defensive
strategy
defense
irradiation
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German (de)
English (en)
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EP2482025A2 (fr
EP2482025A3 (fr
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Diehl Defence GmbH and Co KG
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Diehl Defence GmbH and Co KG
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    • 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
    • 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
    • F41H13/0043—Directed energy weapons, i.e. devices that direct a beam of high energy content toward a target for incapacitating or destroying the target
    • 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
    • F41H13/0043—Directed energy weapons, i.e. devices that direct a beam of high energy content toward a target for incapacitating or destroying the target
    • F41H13/005—Directed energy weapons, i.e. devices that direct a beam of high energy content toward a target for incapacitating or destroying the target the high-energy beam being a laser beam
    • F41H13/0062—Directed energy weapons, i.e. devices that direct a beam of high energy content toward a target for incapacitating or destroying the target the high-energy beam being a laser beam causing structural damage to the target

Definitions

  • the invention relates to a method for repelling a missile by means of defense radiation.
  • the invention relates to a device for repelling a missile by means of defense radiation.
  • the invention is based on the consideration that it is crucial in the defense of the attacking missile to deposit as much radiant energy in selected, function-sensitive missile elements of the missile for their safe damage.
  • missile elements can the Seeker head, a warhead, the rocket motor, electronics and / or be important for aerodynamic stability guiding elements. It is therefore important to hit the selected missile element at a proper angle of radiation to damage it. If the selected missile element is a seeker head, then one will want to hit the missile as possible from the front in order to hit and damage the detector within the limits of the visual field of the missile. If the selected missile element is a warhead lying behind a seeker head, it will be wanted to hit it from the side where it is least likely to penetrate. If the beam strikes non-optical structures, it is advantageous that it impinges as perpendicularly as possible in order to deposit as much radiant energy as possible in the element hit.
  • the recognition of the attacking missile as such happens by the fact that the missile is first recognized as a missile and then recognized whether it is classified as attacking.
  • the classification may be according to one or more predetermined parameters used for classification, such as a distance of an anticipated trajectory of the missile to a defense system, to a predetermined point, to a protected area around a vehicle or to another object or to another spatial one Range, in particular a minimum distance.
  • the method for averting an attacking missile is expediently carried out by a defense system on a vehicle.
  • a defense vehicle can be a land, air or sea vehicle. It expediently includes a defense system for warding off the attacking missile, which is in particular a distance-effective defense system.
  • the defense system can automatically respond to the clearance, for example, as soon as it falls below a specified level and / or the missile is likely to enter a protected area.
  • the specified value may be determined by one or more parameters that are predetermined and / or situational.
  • the defense strategy can be selected from a plurality of predetermined defense strategies. It is also possible to calculate the defense strategy from a number of parameters and thus to rebuild it. It is also advantageous to select parts of the defense strategy from existing strategies and to use these based on predetermined parameters, eg. B. using Enlightenment results, to modify or expand and thus form the entire defense strategy. All of these options for establishing the defense strategy take into account the angle of irradiation, which can be an angle between an irradiation direction and a direction of flight of the missile.
  • the irradiation direction and the flight direction may be instantaneous or assumed future quantities at a future time, so that the irradiation angle may also be a current or assumed future angle.
  • the irradiation angle is an angle between 0 ° and 180 °, with the missile at 0 ° exactly incident on the radiation source and at 180 ° away from it.
  • the defense radiation is expediently laser radiation, wherein the frequency or the frequency range of the laser radiation can be any suitable frequency or any suitable frequency range. Also suitable and advantageous is microwave radiation, although other electromagnetic radiation is possible.
  • the type of missile is determined and used in the preparation of the defense strategy. Since the existence, arrangement and sensitivity of missile elements may differ from missile to missile, it is advantageous to know the type of attacking missile so that the defense strategy may be determined by consideration of the species.
  • the species may be a missile type or a missile class comprising several types of missiles.
  • the missile is expediently an unmanned missile, in particular a missile missile with a warhead provided for detonation, such as an air-to-surface missile, a ground-to-surface missile, or a steerable artillery missile.
  • a type-dependent vulnerability property of the missile is deposited in the defense system as a function of different irradiation angles and, in particular, irradiation energies.
  • the deposit can take place in the form of several or a multi-dimensional table in which, for example, a control success depending on several parameters is deposited.
  • the parameters may be type of missile, irradiation angle, irradiation energy, distance of the missile from the defense system and / or the irradiation time.
  • a replacement strategy is followed. This may involve making an assumption about the type of missile based on at least one predetermined parameter.
  • a suitable parameter is the airspeed of the missile. From this it can usually be distinguished whether the attacking missile is a apelooka, an artillery shell or a missile.
  • the defense strategy specifies a missile element to be irradiated, which was selected in the preparation of the defense strategy as a function of the irradiation angle. Equivalent to this is the selection of a storage point on the missile, for example in the form of coordinates. If the irradiation angle is very acute or very small, it is expedient to select a forwardly located missile element, for example the seeker head, as the missile element to be irradiated when creating the defense strategy. However, if the irradiation angle is large, for example, greater than 45 °, so that the missile can be irradiated from the side, it is expedient to select a laterally accessible missile element, for example a warhead, a rocket motor or a guide element.
  • an irradiation angle or radiation angle range is selected as a function of a missile element to be irradiated. For example, if a laterally accessible missile element is provided for irradiation, the irradiation of this missile element can be postponed until a favorable irradiation angle is reached. The time until then can be used to irradiate another missile element. In the presence of more than one straightening device for blasting, that straightening device can be selected whose irradiation angle is more favorable for the irradiation of the selected missile element, so that in this way the irradiation angle is selected.
  • a future trajectory of the missile is determined and taken into account in the determination of the defense strategy.
  • This can be a Irradiation angle can be determined as a function of time, so that, for example, to be irradiated missile elements can be selected depending on each of an irradiation angle or irradiation angle range.
  • the particular trajectory may range from the missile to a point of impact, or may include only part of that distance.
  • the defense strategy provides that a plurality of flying body elements are irradiated in succession, the sequence and duration of the irradiation being set as a function of the temporal course of the irradiation angle. In this way, an available radiant energy can be used effectively.
  • the invention is particularly advantageous applicable if at least two straightening devices are available for emitting radiation. Since the straightening devices are usually in a mutually different irradiation angle to the attacking missile, the defense strategy expediently includes different sub-strategies for each straightening device.
  • the defense strategy can specify a missile element to be irradiated and at least one of the straightening devices can be selected as a function of its irradiation angle taking into account the missile element. Conversely, it is expedient to make the selection of the missile element to be irradiated dependent on the available irradiation angles.
  • the defense strategy may provide for irradiating a spot on the missile by a selected directional device. Additionally or alternatively, it is possible that the defense strategy indicates a simultaneous irradiation of different points with a plurality of straightening devices, optionally with different intensities, and / or provides an irradiation sequence with one or more straightening devices over different points of the missile.
  • a weaker defense beam from a first aiming device can briefly aim at the seeker head and a stronger jet from a second aiming device can attack the warhead. If both defense beams are fed from the same energy source, after switching off the first beam, the energy of the second defense beam is increased accordingly.
  • the dosage of the first jet is expediently chosen so that the irradiated missile element, in this example the seeker, is destroyed with high probability. Since the Missile but also without a functioning seeker depending on the encounter situation can still hit his target, the warhead is attacked for safety's sake.
  • the plurality of straightening devices may be disposed on a vehicle, for example, on opposite sides of an armored land vehicle. However, it is advantageous if the multiple straightening devices are mounted on several vehicles. In this way, a large distance between the straightening devices can be achieved and a wide range of irradiation angles can be made possible. It can be developed as a variant-rich defense strategy.
  • the straightening devices are arranged on at least two signal-technically interconnected vehicles, wherein one vehicle informs the other at least details of the defense strategy.
  • the defense strategy can be developed only partially in total on one vehicle, on several vehicles or on several vehicles, so that the combination of defense strategy parts creates an overall defense strategy.
  • the defense strategy for each vehicle may include its own strategy part assigned to the vehicle.
  • the irradiation powers can be available irradiation powers, for example maximum powers of the straightening devices, or temporarily adjusted irradiation powers, for example when an irradiation power is distributed from a laser source to several straightening devices.
  • a further advantageous embodiment of the invention provides that the two vehicles each have a detection means, the detection means are networked with each other and detection data of the detection means for detecting the missile are fused.
  • detection means can form a detection system by which an attacking missile is simultaneously observed from several directions, for example.
  • the data fusion facilitates detection of the missile, for example its type.
  • Data fusion can be accomplished by processing recognition data from multiple recognition means together to produce a recognition result.
  • a defense strategy is determined from the type of missile, its prospective trajectory, the coordinates of the available directional devices and the available radiant energy devices.
  • the creation or calculation of the defense strategy can be based on a weighted table of radiation-sensitive parts and / or associated optimal irradiation locations and / or angles.
  • a defense system on a vehicle may include a directional device and a detection device for detecting the missile.
  • a defense system operates without detection means and the detection means is arranged separately, for. B. on another vehicle.
  • the defense system and the detection means are arranged on different units, eg. B. on different vehicles, so for example, a recognition already take place when a missile for a defense vehicle is not or not yet visible, so that a not or not yet visible attack can be fended off early.
  • the object directed to the device is achieved by a device of the aforementioned type, in which the process agent according to the invention is prepared to create the defense strategy as a function of an irradiation angle between the direction of irradiation and the direction of flight of the missile.
  • Defense radiation can be used energy-efficiently and effectively defend a vehicle.
  • the process means is prepared for controlling one, several or all of the method steps described hitherto and in the drawing description. Such a preparation may be provided by a corresponding control program of the process means, the sequence of which - such as in conjunction with suitable input signals, such as sensor signals - causes such a control.
  • the process means expediently comprises electronic elements, such as a processor and data memory, which are necessary for the execution of the control program.
  • Fig. 1 shows a group of four vehicles 2, 4, 6, 8 in a convoy, of which vehicle 2 is a car, vehicle 4 is a transport tank, vehicle 6 is a person transporting flatbed truck and vehicle 8 is a main battle tank.
  • the vehicles 4, 6, 8 are designed as defense vehicles and each comprise at least one defense system 10 and a recognition means 12.
  • the defense systems 10 serve both to defend the respective vehicle 4, 6, 8 and to mutually defend the vehicles 4, 6, 8
  • each defense system 10 cooperates with at least one detection means 12, which is prepared on the basis of predetermined criteria to first recognize an approaching missile 14 as such and further to recognize whether the Missile 14 is classified as attacking.
  • the defense vehicles 4, 6, 8 include one or more processing means 16, 18, as they are, for example, in Fig. 2 are indicated.
  • Fig. 2 shows, for example, the defense vehicle 8 in a highly simplified and schematic representation. It contains a device for repelling an attacking missile 14, briefly referred to as a defense system 10, which comprises two alignment devices 20 for directing a laser beam into the environment, a laser source 22 and the processing means 16.
  • the defense vehicle 8 includes the detection means 12 with two cameras 26, each protected by a dome and connected to the processing means 18.
  • the defense system 10 may also include the detection means 12.
  • both process means 16, 18 may be referred to as common process means, which may in particular be a central processing means of the defense vehicle 8 or a part thereof.
  • the two processing means 16, 18, as well as the cameras 26, optionally a An horrtorik the straightening devices 20 and a data interface 28 are interconnected by data lines, such as a bus system, such as a CAN-BUS system.
  • the detection means 12 comprise means for detecting different missiles, for example an image processing program which evaluates image data from the cameras 26 and detects a missile 14 as such.
  • the detection means 12 include means for detecting the type of the missile 14 and means for calculating the future trajectory 30 up to a possible impact of the missile 14.
  • the means for detecting the type of missile 14 include a database with a variety of missile features, on the basis of which the nature of the missile 14 can be detected by image processing.
  • the missile features include optical features taking into account an observation angle, ie the angle between the line of sight from the detection means 12 to the missile 14 and its flight direction, which is characterized by its trajectory 30.
  • the missile features include data on speeds and maneuvering characteristics of different missiles.
  • a missile 14 If a missile 14 is recognized as such, it is decided whether it is harmless or potentially dangerous. This decision, as well as further decisions, can be taken jointly by each recognition means 12 individually or by the combination of several or all recognition means 12, for example by a leading recognition means 12 or processing means 18.
  • the discrimination of harmless and potentially dangerous missiles 14 takes place via a speed threshold in which a missile 14 whose speed is below the speed threshold is classified as harmless.
  • the speed threshold is suitably above 100 km / h to exclude at least most bird flights. If the missile 14 is identified as being potentially dangerous, the probable flight path 30 is next calculated and decided whether it is likely to reach at least one guard 32 around a vehicle 2, 4, 6, 8 protected by the defensive vehicles 4, 6, 8 is.
  • each vehicle 2, 4, 6, 8 is provided with at least one protective area 32 whose size depends on the type of vehicle 2, 4, 6, 8, the load, such as the people on the bed of the vehicle 6, after Type of the detected missile 14, terrain features and further can judge.
  • These parameters, which determine the size of the protection area 32 can be predetermined or time-variable. As a rule, the protected area will be hemispherical above the corresponding vehicle 2, 4, 6, 8.
  • the calculated trajectory 30 is within a protected area, it is next checked to see which missile 14 it is, so it is the nature of the missile, in particular determines its type.
  • the four detection means 12 of the vehicle convoy are networked together, for example by data interfaces 28.
  • the detection means 12 operate autonomously, however, exchange their detection data with each other.
  • a detection means 12 or its process means 18 can be determined as leading the decision, for example, the decision as to whether an approaching object is a missile 14, what type of missile 14 is and / or if the missile 14 at least one of the vehicles 2, 4 , 6, 8 of the group to be protected is likely to be dangerous, ie penetrates into its protected area 32.
  • Fig. 1 a possible concrete combat situation of the missile 14 is described.
  • the missile 14 is approaching the group of vehicles 2, 4, 6, 8 and is shown for better depictability rather close to this, where he also occupy more distant positions to the group and there recognized and can also be fought.
  • this is detected by the detection means 12 of the vehicles 4, 6.
  • the two detection means 12 of the main battle tank 8 do not recognize the missile 14, as it is shadowed by the truck 6 so that it is not visible to the rear detection means 12 of the main battle tank 8 and with respect to the front detection means 12 behind the tower of the main battle tank is lying and therefore also not visible.
  • the missile 14 is recognized, for example, first by the detection means 12 of the vehicle 4. This transmits the recognition data to the two further defense vehicles 6, 8, so that their detection means 12 also search for the missile 14 in the indicated position. Then the missile 14 is also recognized by the detection means 12 of the vehicle 6 as such.
  • the recognition data of the plurality of recognition means 12 are fused to recognize the missile 14 or its type.
  • the detection means 12 thus form a networked total sensor system which determines the current position, the current speed and at least part of the future trajectory 30 of the attacking missile 14.
  • the next step is now a detection of the type of missile 14.
  • Both detection means 12 process this task independently, but exchange Recognition data with each other, so that a detection is simplified.
  • the detection angle is the angle between the observation direction, which in Fig. 1 is indicated by dotted lines, with the determined flight direction on the trajectory 30 of the missile 14. Since it is generally easier to recognize the type of the missile 14 with blunt detection means, the recognition means 12 of the vehicle 4 is assigned decision-making power, the type of missile Missile 14 to decide. Therefore, in the case of a plurality of recognition means 12, the decision-making competence for recognition as a function of the recognition angle is allocated to a recognition means 12.
  • the detection means 12 of the defense vehicle 4 is of course supported by detection data of the detection means 12 of the other vehicle, in this case the truck 6.
  • an assumption about the type of missile is made 14 made.
  • the assumption may be a fixed default or a default that depends on the velocity of the missile 14.
  • the protective areas 32 around the vehicles 2, 4, 6, 8 can be adapted in size and shape to the missile 14 and it is checked again whether its prospective flight path 30 touches a protective area 32. If this is the case, - provided that automatic missile defense is set in the defense systems 10 - the combat of the missile 14 is automatically initiated.
  • these defense systems are switched to a stand-by mode, which allows an immediate combat recording.
  • the straightening devices 20 are aligned to a predetermined location, expediently to the location where the missile 14 emerges behind the obstacle, in this case behind the vehicle. 6
  • the two defense systems 10 of the vehicles 4, 6 are available in this embodiment initially. Their control directions are in Fig. 1 indicated by narrow dashed lines.
  • the angle of attack of the defense system 10 of the defense vehicle 4 is greater than the control angle of the defense system 10 of the vehicle 6 and this embodiment is around 70 °.
  • a defense strategy is developed which takes into account these different angles of attack and, in particular, their course over time or their change with the movement of the missile 14 relative to the vehicles 4, 6.
  • the determination of the defense strategy is in this case carried out by the processing means 16 of the defense system 10, wherein each defense system 10 can work autonomously and work out its own defense strategy.
  • a defense system 10 takes over the lead and determines a defense strategy, which informs the other defense systems 10 in whole or in part.
  • the processing means 16 are networked in such a way that defense data are fused and processed into a common defense strategy.
  • the two defense systems 10 of the defense vehicle 8 which are located very close to one another also receive different partial strategies, since their control angles to the missile 14, in particular in the final phase of the flight of the missile 14, also differ sufficiently to justify a separate partial strategy. This is especially true in a slow-flying missile, such as an approaching apelooka.
  • a defense system 10 it is possible for a defense system 10 to illuminate only one irradiation target point during the entire combat, for example a warhead of the missile 14, or to illuminate sequentially different missile elements in order to optimally utilize different irradiation angles.
  • the irradiation obstacles in this example, the vehicle 6 and the tower of the main battle tank 8, are taken into account, so that a fight against the two defense systems 10 of the main battle tank 10 is taken only when the missile 14 penetrates into the field of view of the defense systems 10, as shown by the dashed Line from the defense system 10 of the vehicle 8 to the flight path 30 in Fig. 1 is indicated.
  • the straightening devices 20 are aligned with the predetermined target point on the missile 14 and laser energy is applied to the straightening devices 20, in accordance with the defense strategy.
  • the maximum energy can be switched.
  • the energy of the laser source 24 according to the Defense strategy can be given to a straightening device 20 alone or both with distributed energy.
  • the irradiation of the missile 14 is recorded and, if necessary, changed at predetermined times, and the missile 14 is thus repelled.

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  • Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Optics & Photonics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Catching Or Destruction (AREA)

Claims (10)

  1. Procédé de défense contre un missile (14) au moyen d'un rayonnement de défense, avec lequel le missile (14) est reconnu en tant que tel et il est ensuite reconnu si le missile (14) est à classifier comme attaquant, et avec lequel une stratégie de défense est établie et le rayonnement de défense est dirigé sur le missile (14) conformément à la stratégie de défense,
    la stratégie de défense étant établie en fonction d'un angle d'irradiation entre la direction de l'irradiation et la direction de vol du missile (14) pour, lors de la défense contre le missile (14), appliquer autant d'énergie de rayonnement que possible dans des éléments de missile choisis, fonctionnellement sensibles du missile (14) pour les endommager avec certitude, et
    la stratégie de défense indiquant un élément de missile à irradier qui a été choisi en fonction de l'angle d'irradiation lors de l'établissement de la stratégie de défense.
  2. Procédé selon la revendication 1, caractérisé en ce que la nature du missile (14) est déterminée et prise en compte lors de l'établissement de la stratégie de défense.
  3. Procédé selon la revendication 2, caractérisé en ce qu'en cas d'échec de la détermination de la nature du missile (14), une supposition de la nature du missile (14) est effectuée à partir de la vitesse de vol du missile (14).
  4. Procédé selon l'une des revendications précédentes, caractérisé en ce qu'une future trajectoire de vol (30) du missile (14) est déterminée et prise en compte lors de la définition de la stratégie de défense.
  5. Procédé selon l'une des revendications précédentes, caractérisé en ce que la stratégie de défense prévoit d'irradier plusieurs éléments de missile les uns après les autres et la séquence ainsi que la durée de l'irradiation dépendent de la courbe dans le temps de l'angle d'irradiation.
  6. Procédé selon l'une des revendications précédentes, caractérisé en ce qu'au moins deux dispositifs de pointage (20) destinés à émettre le rayonnement de défense et leurs angles d'irradiation sont pris en compte dans la stratégie de défense.
  7. Procédé selon la revendication 6, caractérisé en ce que la stratégie de défense indique un élément de missile à irradier et au moins l'un des dispositifs de pointage (20) est sélectionné en fonction de son angle d'irradiation en tenant compte de l'élément de missile.
  8. Procédé selon la revendication 6 ou 7, caractérisé en ce que les deux dispositifs de pointage (20) sont disposés sur deux véhicules (4, 6, 8) connectés mutuellement en réseau par signalétique et un véhicule (4, 6, 8) communique aux autres au moins des détails de la stratégie de défense.
  9. Procédé selon l'une des revendications 6 à 8, caractérisé en ce que les deux véhicules (4, 6, 8) disposent respectivement d'un moyen de reconnaissance (12), les moyens de reconnaissance (12) sont connectés mutuellement en réseau et les données de reconnaissance des moyens de reconnaissance sont fusionnées en vue de reconnaître le missile (14).
  10. Dispositif de défense contre un missile (14) au moyen d'un rayonnement de défense, lequel comprend au moins un moyen de reconnaissance (12) comportant des moyens pour reconnaître différents missiles afin de reconnaître le missile en tant que tel, le moyen de reconnaissance (12) étant préparé pour décider si le missile (14) reconnu est potentiellement dangereux, et lequel comprend au moins un dispositif de pointage (20) destiné à diriger et à émettre un rayonnement de défense sur le missile (14) attaquant ainsi qu'un moyen de traitement (16), lequel est préparé pour définir une stratégie de défense,
    le moyen de traitement (16) étant préparé pour établir la stratégie de défense en fonction d'un angle d'irradiation entre la direction de l'irradiation et la direction de vol du missile (14) pour, lors de la défense contre le missile (14), appliquer autant d'énergie de rayonnement que possible dans des éléments de missile choisis, fonctionnellement sensibles du missile (14) pour les endommager avec certitude, et la stratégie de défense indiquant un élément de missile à irradier qui a été choisi en fonction de l'angle d'irradiation lors de l'établissement de la stratégie de défense.
EP12000173.0A 2011-01-26 2012-01-13 Procédé et dispositif de défense contre l'attaque d'un missile Active EP2482025B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102011009459.8A DE102011009459B4 (de) 2011-01-26 2011-01-26 Verfahren und Vorrichtung zum Abwehren eines angreifenden Flugkörpers

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EP2482025A2 EP2482025A2 (fr) 2012-08-01
EP2482025A3 EP2482025A3 (fr) 2015-04-15
EP2482025B1 true EP2482025B1 (fr) 2017-04-12

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EP (1) EP2482025B1 (fr)
DE (1) DE102011009459B4 (fr)
IL (1) IL217145A (fr)
ZA (1) ZA201200565B (fr)

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EP4107468A4 (fr) * 2020-02-17 2024-03-13 Bae Systems Bofors Ab Procédé de commande de tir d'un pistolet anti-aérien

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DE102014014117A1 (de) * 2014-09-24 2016-03-24 Diehl Bgt Defence Gmbh & Co. Kg Abwehrvorrichtung zum Bekämpfen eines unbemannten Luftfahrzeugs, Schutzeinrichtung zum Bekämpfen eines unbemannten Luftfahrzeugs und Verfahren zum Betrieb einer Schutzeinrichtung
DE102015011579A1 (de) * 2015-09-03 2017-03-09 Mbda Deutschland Gmbh Abwehrsystem und Drohnenabwehranlage zum Abwehren von Fremddrohnen
DE102016121698A1 (de) 2016-11-11 2018-05-17 Rheinmetall Waffe Munition Gmbh Verfahren und Abwehrsystem zur Bekämpfung von Zielen und Bedrohungen
CN115479504B (zh) * 2022-10-31 2023-08-15 航天科工微电子系统研究院有限公司 一种针对带电粒子束武器的防御方法

Citations (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3623808A1 (de) 1986-07-15 1988-01-28 Diehl Gmbh & Co Verfahren und anordnung zum nachfuehren eines hochenergie-laserstrahles
US5198607A (en) 1992-02-18 1993-03-30 Trw Inc. Laser anti-missle defense system
DE4402855A1 (de) 1994-01-31 1995-08-03 Diehl Gmbh & Co Einrichtung zur Abwehr eines angreifenden Luftziel-Flugkörpers
DE4444636A1 (de) 1994-12-15 1996-06-20 Sepp Gunther Waffensystem für einen Blendlaser
EP0800095A2 (fr) 1996-04-02 1997-10-08 Trw Inc. Système et procédé de poursuite laser transversale
US5780839A (en) 1996-04-02 1998-07-14 Trw Inc. Laser crossbody and feature curvature tracker
US6343766B1 (en) 1997-08-27 2002-02-05 Trw Inc. Shared aperture dichroic active tracker with background subtraction
US6653971B1 (en) 1999-05-14 2003-11-25 David L. Guice Airborne biota monitoring and control system
DE10229273A1 (de) 2002-06-28 2004-01-29 Diehl Munitionssysteme Gmbh & Co. Kg Objekt-Selbstschutzvorrichtung
DE10230939A1 (de) 2002-07-09 2004-02-12 Buck Neue Technologien Gmbh Verfahren und Vorrichtung zum Schutz von Gefechtsfeldfahrzeugen
US20040069927A1 (en) 2002-07-19 2004-04-15 Lockheed Martin Corporation Method and system for wavefront compensation
US20040118270A1 (en) 2002-12-20 2004-06-24 Barrett John L. Method for deflecting fast projectiles
WO2004109251A2 (fr) 2003-05-30 2004-12-16 Bae Systems Information And Electronic Systems Integration Inc. Procede de retro-eclairage pour des contre-mesures de missiles guides ir
US20060000987A1 (en) 2002-11-19 2006-01-05 Weber Jonathan L Active sensor receiver detector array for countermeasuring shoulder-fired missiles
US20060028374A1 (en) 2004-08-06 2006-02-09 Time Domain Corporation System and method for ultra wideband subarray beam steering
WO2006076043A1 (fr) 2004-07-29 2006-07-20 Raytheon Company Systeme de commande de faisceau comprenant une balise etendue et procede associe
WO2006096190A2 (fr) 2004-06-03 2006-09-14 Bae Systems Information And Electronic Systems Integration, Inc. Systeme pour diriger un faisceau laser et sa methode d'utilisation dans un systeme directionnel infrarouge de contre mesures
WO2006134050A1 (fr) 2005-06-17 2006-12-21 Thales Procede de protection antimissiles de vehicules et dispositif de mise en oeuvre
US20070201015A1 (en) 2004-05-26 2007-08-30 Gidseg Ronald A System And Method For Transitioning From A Missile Warning System To A Fine Tracking System In A Directional Infrared Countermeasures System
US20080018519A1 (en) 2005-12-06 2008-01-24 Russell Berg Anti-missile system and method
WO2008062401A1 (fr) 2006-11-21 2008-05-29 Rafael - Armament Development Authority Ltd. Système et procédé de contre-mesures à base de laser
FR2909441A1 (fr) 2006-12-04 2008-06-06 Nexter Munitions Sa Dispositif de defense d'une plate-forme contre une menace
US7411543B1 (en) 2004-08-13 2008-08-12 Lockheed Martin Corporation Maximum-likelihood rocket identifier
WO2009038843A2 (fr) 2007-06-14 2009-03-26 Raytheon Company Procédés et appareil pour contrer un projectile
DE102008020959A1 (de) 2008-04-25 2009-11-05 Eurocopter Deutschland Gmbh Verfahren und Apparatur zur Erkennung und Vermeidung von Beschusssituationen beim Betrieb von Luftfahrzeugen
US20090296070A1 (en) 2008-05-30 2009-12-03 The Boeing Company Systems and Methods for Targeting Directed Energy Devices
WO2010138226A2 (fr) 2009-05-08 2010-12-02 Raytheon Company Système directeur de faisceau laser de haute énergie et procédé

Patent Citations (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3623808A1 (de) 1986-07-15 1988-01-28 Diehl Gmbh & Co Verfahren und anordnung zum nachfuehren eines hochenergie-laserstrahles
US5198607A (en) 1992-02-18 1993-03-30 Trw Inc. Laser anti-missle defense system
DE4402855A1 (de) 1994-01-31 1995-08-03 Diehl Gmbh & Co Einrichtung zur Abwehr eines angreifenden Luftziel-Flugkörpers
DE4444636A1 (de) 1994-12-15 1996-06-20 Sepp Gunther Waffensystem für einen Blendlaser
EP0800095A2 (fr) 1996-04-02 1997-10-08 Trw Inc. Système et procédé de poursuite laser transversale
US5780839A (en) 1996-04-02 1998-07-14 Trw Inc. Laser crossbody and feature curvature tracker
US6343766B1 (en) 1997-08-27 2002-02-05 Trw Inc. Shared aperture dichroic active tracker with background subtraction
US6653971B1 (en) 1999-05-14 2003-11-25 David L. Guice Airborne biota monitoring and control system
DE10229273A1 (de) 2002-06-28 2004-01-29 Diehl Munitionssysteme Gmbh & Co. Kg Objekt-Selbstschutzvorrichtung
DE10230939A1 (de) 2002-07-09 2004-02-12 Buck Neue Technologien Gmbh Verfahren und Vorrichtung zum Schutz von Gefechtsfeldfahrzeugen
US20040069927A1 (en) 2002-07-19 2004-04-15 Lockheed Martin Corporation Method and system for wavefront compensation
US20060000987A1 (en) 2002-11-19 2006-01-05 Weber Jonathan L Active sensor receiver detector array for countermeasuring shoulder-fired missiles
US20040118270A1 (en) 2002-12-20 2004-06-24 Barrett John L. Method for deflecting fast projectiles
WO2004109251A2 (fr) 2003-05-30 2004-12-16 Bae Systems Information And Electronic Systems Integration Inc. Procede de retro-eclairage pour des contre-mesures de missiles guides ir
US20070201015A1 (en) 2004-05-26 2007-08-30 Gidseg Ronald A System And Method For Transitioning From A Missile Warning System To A Fine Tracking System In A Directional Infrared Countermeasures System
WO2006096190A2 (fr) 2004-06-03 2006-09-14 Bae Systems Information And Electronic Systems Integration, Inc. Systeme pour diriger un faisceau laser et sa methode d'utilisation dans un systeme directionnel infrarouge de contre mesures
WO2006076043A1 (fr) 2004-07-29 2006-07-20 Raytheon Company Systeme de commande de faisceau comprenant une balise etendue et procede associe
US20060028374A1 (en) 2004-08-06 2006-02-09 Time Domain Corporation System and method for ultra wideband subarray beam steering
US7411543B1 (en) 2004-08-13 2008-08-12 Lockheed Martin Corporation Maximum-likelihood rocket identifier
WO2006134050A1 (fr) 2005-06-17 2006-12-21 Thales Procede de protection antimissiles de vehicules et dispositif de mise en oeuvre
US20080018519A1 (en) 2005-12-06 2008-01-24 Russell Berg Anti-missile system and method
WO2008062401A1 (fr) 2006-11-21 2008-05-29 Rafael - Armament Development Authority Ltd. Système et procédé de contre-mesures à base de laser
FR2909441A1 (fr) 2006-12-04 2008-06-06 Nexter Munitions Sa Dispositif de defense d'une plate-forme contre une menace
WO2009038843A2 (fr) 2007-06-14 2009-03-26 Raytheon Company Procédés et appareil pour contrer un projectile
DE102008020959A1 (de) 2008-04-25 2009-11-05 Eurocopter Deutschland Gmbh Verfahren und Apparatur zur Erkennung und Vermeidung von Beschusssituationen beim Betrieb von Luftfahrzeugen
US20090296070A1 (en) 2008-05-30 2009-12-03 The Boeing Company Systems and Methods for Targeting Directed Energy Devices
WO2010138226A2 (fr) 2009-05-08 2010-12-02 Raytheon Company Système directeur de faisceau laser de haute énergie et procédé

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4107468A4 (fr) * 2020-02-17 2024-03-13 Bae Systems Bofors Ab Procédé de commande de tir d'un pistolet anti-aérien

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DE102011009459B4 (de) 2015-08-20
ZA201200565B (en) 2012-10-31
EP2482025A2 (fr) 2012-08-01
DE102011009459A1 (de) 2012-07-26
IL217145A0 (en) 2012-06-28
IL217145A (en) 2017-05-29
EP2482025A3 (fr) 2015-04-15

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