EP0240819B1 - Procédé de détournement de missiles à guidage radar ou infrarouge, en particulier pour la défense des navires et unités navales, et dispositif pour la mise en oeuvre du procédé - Google Patents

Procédé de détournement de missiles à guidage radar ou infrarouge, en particulier pour la défense des navires et unités navales, et dispositif pour la mise en oeuvre du procédé Download PDF

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Publication number
EP0240819B1
EP0240819B1 EP87104219A EP87104219A EP0240819B1 EP 0240819 B1 EP0240819 B1 EP 0240819B1 EP 87104219 A EP87104219 A EP 87104219A EP 87104219 A EP87104219 A EP 87104219A EP 0240819 B1 EP0240819 B1 EP 0240819B1
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EP
European Patent Office
Prior art keywords
missile
deflection
projectiles
deflection curve
curve
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.)
Expired - Lifetime
Application number
EP87104219A
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German (de)
English (en)
Other versions
EP0240819A2 (fr
EP0240819A3 (en
Inventor
Rolf Herbst
Johannes Grundler
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.)
Buck Werke GmbH and Co
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Buck Werke GmbH and Co
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Publication date
Application filed by Buck Werke GmbH and Co filed Critical Buck Werke GmbH and Co
Publication of EP0240819A2 publication Critical patent/EP0240819A2/fr
Publication of EP0240819A3 publication Critical patent/EP0240819A3/de
Application granted granted Critical
Publication of EP0240819B1 publication Critical patent/EP0240819B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F41G7/224—Deceiving or protecting means
    • 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

Definitions

  • the invention relates to a method for deflecting missiles guided by radar and / or infrared radiation, in particular for the protection of seagoing vessels and ship groups, in which projectiles producing mock targets are ignited in or in front of the target area of the missile.
  • a deflection system corresponding to the preamble of claims 1 and 6 is known from FR-A-2 383 419 in connection with "radio systems for location and navigation", Kramar, publishers Hopkins Union and Kohlcro, pp. 18 u. 25, known.
  • Radar the deflection of missiles guided by radar and / or infrared radiation in or in front of the target area of the missile.
  • the approaching missile should align itself with the apparent target in order to be distracted by the threatened ship or ship association.
  • this type of distraction is not always sufficient, especially in ship associations. It is possible and likely that the missile will switch from one ship to another and hit the ship after it has been deflected, particularly in the case of relatively tightly spaced ship groups.
  • the object underlying the invention was to develop a method of the type mentioned in the preamble of claim 1 in such a way that the approaching missile is deflected in a predetermined deflection direction, which can be determined so that the missile no longer moves after its deflection is able to switch to an alternative destination.
  • the invention further relates to a device for carrying out the method according to the invention with the features from patent claim 6, an advantageous embodiment of this device being described in patent claim 7.
  • the method according to the invention is primarily intended to protect ship groups, but it can also be used to protect individual ships, for example in the form that ships in crisis areas, for example tankers, can be equipped with a device according to the invention in order to counteract the To be protected by missiles and to protect other tankers traveling in a convoy.
  • the device according to the invention When using the method according to the invention for the protection of ship groups, it can also be advantageous to install the device according to the invention on unmanned escort ships, so that the diversion can be carried out at a relatively great distance from the ship group, where there is sufficient space for fixing the direction of deflection is available.
  • Conventional throwing bodies can be used as throwing bodies, which, for example, for generating an infrared glow target contain a certain effective mass known per se, due to which after ignition of the throwing body an infrared radiation-imitating cloud arises which has a low sinking speed with a large radiation area and thus has a ship-like characteristic.
  • Throwing bodies can be used to deflect radar-controlled missiles which contain a so-called "double active mass" which is released after the firing body has been ignited.
  • double active mass a so-called "double active mass" which is released after the firing body has been ignited.
  • the method according to the invention can be used in a wide variety of ways.
  • the device according to the invention can be used both to protect the association and to protect the support boat itself.
  • the device for carrying out a method for deflecting missiles guided by radar and / or infrared radiation basically has the following individual devices: A device 1 for locating a missile and for determining its location, its flight direction and flight speed and, if appropriate, its type.
  • This locating device can contain a radar device and additional devices such as a periscope, a night vision device and / or an optical distance measuring device in a manner known per se. Furthermore, it contains devices known per se for generating electrical data representing the determined values.
  • This data is fed to a data processing system 2, which is also constructed in a manner known per se and, based on corresponding programs, calculates a deflection curve for the missile from the determined data based on a predetermined deflection direction, in the manner in which this is explained in more detail below.
  • the data processing system 2 also generates electrical control signals which are fed to a control device 3 to which a throwing pillar 4 is connected, which is also explained in more detail below.
  • Throwing pillars 4 are fired by means of the throwing pillar 4, specifically with respect to the firing direction and the firing sequence in such a way that at the end of the trajectory of the throwing body, after firing, apparent targets appear which lie at predetermined points of the calculated deflection curve. The conditions that occur here are explained in more detail below with reference to FIGS.
  • a device according to FIG. 1 is installed on a ship S, for example an escort boat of a ship association.
  • a missile FK controlled, for example, by infrared radiation is located, the direction of flight FB1 of which is determined together with the flight speed and possibly the type of missile.
  • a deflection direction FB2 is specified and a deflection curve AK is calculated, which can be part of a parabola, for example, one branch of which connects to the approach path FB1 and the other branch to the deflection direction FB2.
  • corresponding throwing bodies On the basis of the evaluated data, corresponding throwing bodies have to be fired from the ship S on ballistic tracks P1, P2, P3, P4, P5 and P6 in such directions and in a predetermined time sequence that the apparent targets Z1, Z2, Z3, Z4 are successively on the deflection curve AK , Z5 and Z6 arise so that the missile FK is successively oriented towards these apparent targets and thereby changes its trajectory overall in such a way that it continues to fly on the deflection curve AK and is finally deflected in the deflection direction FB2.
  • the throwing bodies are preferably shot in such a way that the ballistic tracks P1 to P6 are all the same Have an elevation angle of 45 °.
  • the clouds emitting infrared radiation representing the apparent targets Z1 to Z6 lie essentially in a horizontal plane, so that the missile FK is deflected on a horizontal path.
  • the missile FK is deflected by approximately 90 ° from its approach direction.
  • six apparent targets are sufficient in the described method, for example.
  • the deflection curve AK to be built up by the six apparent targets Z1 to Z6 is designed in such a way that the missile FK can follow this curve in any case, taking into account its own maneuverability and viewing window size.
  • the deflection curve AK can also be constructed mirrored on the approach direction FB1, so that the deflection in FIG. 4 does not take place to the right but to the left.
  • FIG. 1 the launching column 4 shown in FIG. 1 is shown in somewhat more detail.
  • the throwing pillar 4 shown has a basic device 4.1, which is connected to the control device 3 in the manner shown in FIG. 1.
  • a base plate 4.2 is arranged above the basic device, on which a two-part column 4.3-4.4 is rotatably arranged in a controllable manner.
  • twelve throwing devices are arranged at an elevation angle of 45 ° in six rows arranged one above the other on the circumference.
  • On the upper part 4.4 of the column there are twelve throwing devices in three rows arranged on the circumference, which are also at an elevation angle of 45 °.
  • the throwing devices 4.31 to 4.36 arranged in the lower part 4.3 of the column serve to produce deflection curves which are intended to protect a ship's association, while the throwing bodies arranged in the upper part 4.4 of the column are intended for the self-protection of the escort ship.
  • Rows 4.31 to 4.36 and 4.41 to 4.43 can each be equipped with combined IR and radar dummy targets, which have different ranges and disassembly times. With the help of these different ranges and dismantling times, the predicted deflection curves can be produced in connection with the side-aiming of the throwing pillar and a certain firing rate by the dummy targets.
  • the deflection measure can be carried out twelve times with the lower part of the launcher column 4.3 before it is necessary to reload the launcher column.
  • the twelve groups of throwing devices, each with six different throwing bodies, are loaded from top to bottom in row 4.36 with the throwing body that has the shortest range and ending in row 4.31 with the throwing body that has the greatest range (recoil) and therefore to avoid large ones Moments close to the turntable of the thrower column is arranged.
  • the upper part 4.4 of the launcher column can be used correspondingly equipped rows 4.41 to 4.43 missiles are fired, which create false targets, which are intended to protect the escort boat itself.
  • the creation of a certain deflection curve may be dispensed with, and it is only intended to prevent the escort ship itself from being hit by the apparent targets generated.

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

Claims (7)

  1. Procédé pour dévier des engins (FK) guidés par radar et/ou par rayonnement infrarouge, notamment pour la protection de navires (S) et de groupes de navires, dans lequel on allume des éléments lancés ou projectiles générant des leurres (Z1 à Z6) dans le, ou en avant du, domaine de cible de l'engin, et dans lequel la direction, l'emplacement et la vitesse de vol d'un engin (FK) arrivant sont déterminés et, à chaque fois à des instants prédéterminés, des éléments lancés sont placés dans des régions de l'espace prédéterminées et sont allumés de manière telle que les leurres produits (Z1 à Z6) se trouvent dans des intervalles de temps et d'espace prédéterminés et que l'engin soit ainsi dévié de sa trajectoire de vol accomplie jusqu'alors,
    caractérisé
    par le fait qu'en se basant sur une direction de déviation donnée à l'avance (FB2), on calcule une courbe de déviation ouverte (AK) et, avec ses données de position on la place dans une région prédéterminée de l'espace en avant du domaine de cible de l'engin (FK), une première branche de cette courbe se raccordant à la trajectoire de vol d'arrivée (FB1) et son autre branche se raccordant à la direction de déviation de l'engin (FK), et les leurres produits (Z1 à Z6) se trouvant sur la courbe de déviation, de façon que l'engin mette successivement le cap sur eux de manière que sa trajectoire de vol se raccorde à la courbe de déviation et prenne finalement la direction de déviation (FB2).
  2. Procédé selon revendication 1, caractérisé par le fait que la courbe de déviation (AK) est une parabole.
  3. Procédé selon revendications 1 et 2, caractérisé par le fait que la courbe de déviation (AK) se trouve sensiblement dans un plan horizontal et les éléments lancés ou projectiles sont mis sur des trajectoires balistiques dans un ordre prédéterminé, sur des points individuels de la courbe de déviation et y sont allumés.
  4. Procédé selon revendication 3, caractérisé par le fait que les éléments lancés sont tirés depuis un point, sous un angle d'élévation de 45°.
  5. Procédé selon l'une des revendications 1 à 4, pour la protection de groupes de navires, caractérisé par le fait que les éléments lancés ou projectiles sont lancés depuis un navire d'accompagnement (S) sans équipage.
  6. Dispositif de mise en oeuvre du procédé selon l'une des revendications 1 à 5, comportant un dispositif de commande (3) auquel au moins une colonne de lancement (4), pouvant être commandée pour ce qui est de la direction et de la séquence de tir, est raccordée pour lancer des projectiles, un dispositif (1) pour la localisation d'un engin et la détermination de son emplacement, de sa direction de vol et de sa vitesse de vol, ainsi que pour produire des données électriques représentant les valeurs déterminées, et une installation (2) de traitement de données reliée au dispositif (1), laquelle envoie au dispositif de commande (3) des signaux de commande tels que la colonne de lancement envoie les projectiles ou élements lancés de manière que les leurres produits par lesdits projectiles ou éléments se trouvent à des intervalles déterminés dans le temps et dans l'espace et que l'engin (FK) soit ainsi dévié de sa trajectoire, caractérisé par le fait que l'installation de traitement de données (2) élabore, à partir des données déterminées, une courbe de déviation (AK) dont une branche se raccorde à la trajectoire de vol d'approche de l'engin et dont l'autre branche se raccorde à la direction de déviation de cet engin, et par le fait que la colonne de lancement (4) lance les éléments ou projectiles de façon que les leurres (Z1 à Z6) se trouvent sur la courbe de déviation (AK) et que l'engin mette successivement le cap sur eux, de manière que sa trajectoire se raccorde géométriquement à la courbe de déviation et finalement à la direction de déviation (FB2).
  7. Dispositif selon revendication 6, caractérisé par le fait que la colonne de lancement tournante (4) présente, sur son pourtour, un nombre prédéterminé d'appareils de lancement (W) qui sont disposés sur plusieurs rangées (4.31 à 4.36, 4.41 à 4.43), et présentent chacun un angle d'élévation de 45°, le pointage latéral de la colonne de lancement (4) s'effectuant par une rotation qui, ainsi que la cadence de lancement, est déterminée par le dispositif de commande (3), et la portée de chaque projectile ou élément lancé étant fixée par sa charge propulsive, et le temps de fractionnement étant réglé à chaque fois sur ledit élément ou projectile.
EP87104219A 1986-04-11 1987-03-21 Procédé de détournement de missiles à guidage radar ou infrarouge, en particulier pour la défense des navires et unités navales, et dispositif pour la mise en oeuvre du procédé Expired - Lifetime EP0240819B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3612183 1986-04-11
DE19863612183 DE3612183A1 (de) 1986-04-11 1986-04-11 Verfahren zur ablenkung von durch radar- und/oder infrarotstrahlung gelenkten flugkoerpern, insbesondere zum schutz von seeschiffen und schiffsverbaenden sowie einrichtung zur durchfuehrung des verfahrens

Publications (3)

Publication Number Publication Date
EP0240819A2 EP0240819A2 (fr) 1987-10-14
EP0240819A3 EP0240819A3 (en) 1989-03-22
EP0240819B1 true EP0240819B1 (fr) 1993-09-15

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EP87104219A Expired - Lifetime EP0240819B1 (fr) 1986-04-11 1987-03-21 Procédé de détournement de missiles à guidage radar ou infrarouge, en particulier pour la défense des navires et unités navales, et dispositif pour la mise en oeuvre du procédé

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EP (1) EP0240819B1 (fr)
DE (2) DE3612183A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2611259A1 (fr) * 1987-02-23 1988-08-26 Buck Chem Tech Werke Unite lance-fusees pour la protection d'objets mobiles ou fixes, en particulier de vehicules blindes
EP0512202A2 (fr) * 1991-05-10 1992-11-11 Buck Werke GmbH & Co Procédé pour protéger un objet émettant un rayonnement infrarouge et projectile pour la mise en oeuvre d'un tel procédé
EP0708305A2 (fr) 1994-10-21 1996-04-24 Buck Werke GmbH & Co Procédé pour protéger des objets rayonnants contre des missiles, en particulier des objets émettant un rayonnement dans l'infrarouge comme des navires

Families Citing this family (16)

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DE3835887C2 (de) * 1988-10-21 1997-10-02 Rheinmetall Ind Ag Patrone zur Scheinzielerzeugung
DE4238038C1 (de) * 1992-11-11 1994-06-16 Buck Chem Tech Werke Verfahren zum Bereitstellen eines Scheinzielkörpers
FR2749669B1 (fr) * 1996-06-07 1998-07-31 France Etat Procede de conduite et de protection d'un navire
FR2780774B1 (fr) * 1998-07-03 2001-03-09 Alkan Sa Dispositif d'autoprotection passive pour engin mobile tel qu'un helicoptere
DE10008198A1 (de) * 2000-02-23 2001-08-30 Krauss Maffei Wegmann Gmbh & C An einem Kampffahrzeug angeordnete Wurfanlage für Nebelkerzen, Sprengkörper u. dgl.
DE10117007A1 (de) * 2001-04-04 2002-10-17 Buck Neue Technologien Gmbh Verfahren und Vorrichtung zum Schutz von mobilen militärischen Einrichtungen
DE10213691B4 (de) * 2002-03-27 2004-11-25 Diehl Munitionssysteme Gmbh & Co. Kg Verfahren zum Schützen eines Objekts
US6662700B2 (en) * 2002-05-03 2003-12-16 Raytheon Company Method for protecting an aircraft against a threat that utilizes an infrared sensor
FR2840977B1 (fr) 2002-06-12 2004-09-03 Giat Ind Sa Dispositif et munition de protection d'un vehicule ou d'une plate-forme fixe contre une menace
DE10346001B4 (de) * 2003-10-02 2006-01-26 Buck Neue Technologien Gmbh Vorrichtung zum Schützen von Schiffen vor endphasengelenkten Flugkörpern
DE102004005105A1 (de) * 2004-02-02 2005-09-01 Buck Neue Technologien Gmbh Objektschutzsystem und Verfahren zum Schützen von Objekten
DE102005034613B3 (de) 2005-07-18 2007-03-29 Deutsches Zentrum für Luft- und Raumfahrt e.V. Abwehrvorrichtung gegen Flugkörper, Verfahren zur Abwehr gegen Flugkörper und Verwendung einer Laservorrichtung
DE102006017107A1 (de) 2006-04-10 2007-10-11 Oerlikon Contraves Ag Schutzeinrichtung und Schutzmaßnahme für eine Radaranlage
DE102011014599B4 (de) * 2011-03-22 2016-12-08 Diehl Bgt Defence Gmbh & Co. Kg Verfahren zum Schützen eines Objekts vor einem Angriff eines anfliegenden Flugobjekts
DE102011052616A1 (de) * 2011-03-28 2012-10-04 Peter Huber Vorrichtung und Verfahren zur Verteidigung eines Zielobjekts gegen mindestens einen angreifenden Flugkörper
DE102020119231B4 (de) 2020-07-21 2022-07-21 Krauss-Maffei Wegmann Gmbh & Co. Kg Militärische Wurfanlage

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US3126544A (en) * 1964-03-24 Method of deception for an aircraft
FR1006376A (fr) * 1948-01-05 1952-04-22 Déviation de la trajectoire d'une bombe, qui est dirigée à l'aide des photo-cellules
US3150848A (en) * 1961-06-28 1964-09-29 Samuel E Lager Method of decoying a missile from its intended target
FR2383419A1 (fr) * 1977-03-07 1978-10-06 Lacroix E Valise lance-leurres pour la deception des systemes de guidage d'armes

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Title
E.KRAMAR,FUNKSYSTEME FÜR ORTUNG UND NAVIGATION,VERLAG BERLINER UNION,SEITEN 18 und 25. *

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2611259A1 (fr) * 1987-02-23 1988-08-26 Buck Chem Tech Werke Unite lance-fusees pour la protection d'objets mobiles ou fixes, en particulier de vehicules blindes
EP0512202A2 (fr) * 1991-05-10 1992-11-11 Buck Werke GmbH & Co Procédé pour protéger un objet émettant un rayonnement infrarouge et projectile pour la mise en oeuvre d'un tel procédé
EP0512202A3 (en) * 1991-05-10 1993-09-01 Buck Werke Gmbh & Co Method for protecting an ir-radiation emitting object and projectile for putting this method in practice
US5291818A (en) * 1991-05-10 1994-03-08 Buck Werke Gmbh & Co. Process for defending objects emitting an infrared radiation, and droppable bodies to carry out the process
EP0708305A2 (fr) 1994-10-21 1996-04-24 Buck Werke GmbH & Co Procédé pour protéger des objets rayonnants contre des missiles, en particulier des objets émettant un rayonnement dans l'infrarouge comme des navires

Also Published As

Publication number Publication date
DE3612183A1 (de) 1987-10-22
EP0240819A2 (fr) 1987-10-14
EP0240819A3 (en) 1989-03-22
DE3787391D1 (de) 1993-10-21

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