EP1090263B1 - Procede pour combattre a distance des cibles proches du sol et/ou sur le sol - Google Patents

Procede pour combattre a distance des cibles proches du sol et/ou sur le sol Download PDF

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Publication number
EP1090263B1
EP1090263B1 EP99927726A EP99927726A EP1090263B1 EP 1090263 B1 EP1090263 B1 EP 1090263B1 EP 99927726 A EP99927726 A EP 99927726A EP 99927726 A EP99927726 A EP 99927726A EP 1090263 B1 EP1090263 B1 EP 1090263B1
Authority
EP
European Patent Office
Prior art keywords
missile
target
reconnaissance system
homing
information
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
EP99927726A
Other languages
German (de)
English (en)
Other versions
EP1090263A1 (fr
Inventor
Roland Gauggel
Michael Arnold
Reinhard KRÜGER
Norbert TRÄNAPP
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.)
LFK Lenkflugkoerpersysteme GmbH
Original Assignee
LFK Lenkflugkoerpersysteme GmbH
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 LFK Lenkflugkoerpersysteme GmbH filed Critical LFK Lenkflugkoerpersysteme GmbH
Publication of EP1090263A1 publication Critical patent/EP1090263A1/fr
Application granted granted Critical
Publication of EP1090263B1 publication Critical patent/EP1090263B1/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
    • F41G7/2206—Homing guidance systems using a remote control station
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/02—Aiming or laying means using an independent line of sight
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/14—Indirect aiming means
    • F41G3/16—Sighting devices adapted for indirect laying of fire
    • F41G3/165—Sighting devices adapted for indirect laying of fire using a TV-monitor

Definitions

  • the invention relates to a method for controlling ground level and / or ground-based targets, such as tanks or the like, by means of a one Seeker head, a real load and at least one engine Missile, in which the missile is essentially vertical Starting phase redirected into a substantially horizontal marching and searching phase in which the missile uses the seeker head to find the one in front of it Terrain scans, whereupon finally after opening the search head a recognized target an essentially downward approach phase connected, whereby an external reconnaissance system in a suitable air and / or spacecraft, such as a helicopter, a drone or one Satellite that receives missile guidance information.
  • a suitable air and / or spacecraft such as a helicopter, a drone or one Satellite that receives missile guidance information.
  • DE 42 23 531 C2 also describes a missile as an autonomous missile which discloses an inertial reference system for reducing Initialization errors included.
  • DE 44 16 885 A1 uses a method for guiding a missile at least one radiation source from two in a launcher sensors can be located offset from one another. From the Location signals are sent to a missile guidance device transmitted steering commands derived, the missile in the line of sight hold at least one sensor detecting a target.
  • a missile guidance device transmitted steering commands derived, the missile in the line of sight hold at least one sensor detecting a target.
  • Such a control of a Missile is already in the LOS process, so in the case of a Direct shot procedure, complicated when between the launch pad and the If a malfunction occurs.
  • the known method fails completely if the target is not in line of sight to the launcher as in the case of NLOS procedures.
  • DE 31 45 374 A1 and DE 33 03 763 A1 describe methods for Combat ground targets using missiles, these missiles however not based on information coming from an external Reconnaissance system can be maintained, can be directed.
  • the object of the invention is therefore the generic method in such a way further develop that overcomes the disadvantages of the prior art become, that means in particular a more precise target activation and higher Accuracy is achieved.
  • This object is achieved in that the Reconnaissance system recorded information to control the missile transmitted to the missile, and the search angle during the search phase of the missile's seeker head depending on the missile target data transmitted by the reconnaissance system with regard to the Recognizing the goal is optimized.
  • the reconnaissance system static or flying scans the possible target area during a mission external reconnaissance system information to control the missile records and transmits.
  • the missile after detection of a goal to be combated by the reconnaissance system, in particular in terms of target type, target location and / or target movement, under the control of transmitted the reconnaissance system to a missile launch facility Signals are started so that its quasi-ballistic trajectory essentially leads to the goal understood by the reconnaissance system.
  • the search angle of the missile's search head largely below corresponding increase in resolution and reduced to the recognition of that Missiles through the reconnaissance system transmitted details of the target, such as the engine area of a tank or the like becomes.
  • the reconnaissance system forwards recorded information to a transmission station, and via the missile transfer station is directed to the target.
  • the Missile provides information to the transfer station along with the information transmitted by the reconnaissance system to control the Missile are processed in the transfer station.
  • the invention is therefore based on the surprising finding that conventionally, missiles operating autonomously by means of a seeker head can also be controlled remotely via a reconnaissance system and the missile permanently transmitted information from the external reconnaissance system can be used to determine the target direction of the missile during the search phase constantly optimize, so that it is in principle a combination of two conventional search method comes, which eliminates the error considerably increases and the hit accuracy compared to the prior art far exceeds.
  • About the data connection between the Missile and the reconnaissance system be it directly or indirectly via a Transfer station, the missile can still during its flight current target data to increase the effectiveness of the control are transmitted.
  • a combat scenario is shown in which a tank 1 by one Missile 2 is to be attacked.
  • a helicopter 3 flies over it possible target area and scans the same within a viewing cone I.
  • These signals can from the helicopter 3 to one Transfer station 4 and then transmitted to the starter and contain information that enables the missile 2 from the starting point A is brought to a quasi-ballistic trajectory a, which is essentially to leads through the helicopter 3 captured tank 1.
  • the missile 2 flies essentially horizontally and with supersonic.
  • the search angle of the seeker head i.e. the viewing cone b of the guided missile 2
  • the path c of the is exemplary
  • the center of the light cone b of the missile 2 is shown as it passes through the remote control by means of the detected, edited and by the helicopter 3 transmitted data results.
  • the seeker head of the missile 2 After the seeker head of the missile 2 has recognized the tank 1 and the Missile 2 has been connected to the tank 1, i.e. in the target approach phase the angle of the light cone b of the guided missile 2 is constantly reduced, in Dependence on details of the tank 1 to be fought, which the helicopter 3 has detected the resolution within the cone b of the missile 2 increase, which at the same time increases the target accuracy.
  • the helicopter 3 For example, possible to aim precisely at the engine area of the tank 1, so that the Active charge of the missile 1 unfolds in the engine area, as in the figure symbolizes.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Claims (6)

  1. Procédé pour combattre des cibles proches du sol ou liées au sol, telles que des chars d'assaut ou analogues, à l'aide d'un mobile aérien présentant une tête chercheuse, une charge active et au moins un propulseur, dans lequel le propulseur est dévié d'une phase de départ sensiblement verticale, en une phase de fonctionnement et de recherche sensiblement horizontale, dans lequel le mobile aérien balaye le paysage situé devant lui à l'aide de la tête chercheuse, suite à quoi, l'intrusion de la tête chercheuse sur une cible reconnue est finalement suivie d'une phase d'approche sensiblement dirigée vers le bas, un système de reconnaissance externe dans un véhicule aérien et/ou spatial adapté, tel qu'un hélicoptère, un bourdon ou un satellite relevant des informations pour le guidage du mobile aérien, caractérisé en ce que les informations relevées par le système de reconnaissance pour le guidage du mobile aérien sont transmises au mobile aérien et pendant la phase de recherche, l'angle de recherche de la tête chercheuse du mobile aérien est constamment optimisé en fonction des données concernant la cible, transmises par le système de reconnaissance, en conséquence de la détection de la cible.
  2. Procédé selon la revendication 1, caractérisé en ce que, au cours d'une mission, le système de reconnaissance balaye la zone cible envisageable de manière statique ou volante.
  3. Procédé selon l'une quelconque des revendications 1 ou 2, caractérisé en ce qu'après la détection par le système de reconnaissance d'une cible qui doit être combattue, particulièrement au niveau du type, du lieu et/ou du déplacement de ladite cible, sous la commande de signaux transmis par le système de reconnaissance à un dispositif de lancement du mobile aérien, le mobile aérien est lancé de manière à ce que sa trajectoire de vol quasi-balistique conduise sensiblement vers la cible enregistrée par le système de reconnaissance.
  4. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que, après la détection de la cible et l'intrusion de la tête chercheuse du mobile aérien sur cette dernière, dans la phase d'approche de la cible, l'angle de recherche de la tête chercheuse du mobile aérien est rapetissé au possible, sous augmentation conséquente de la résolution et après la détection du détail de la cible à combattre transmis par le système de reconnaissance, par exemple la zone moteur d'un char d'assaut ou analogue, il est minimisé.
  5. Procédé selon l'une quelconque des revendications précédentes, caractérise en ce que le système de reconnaissance transmet les informations recueillies à un poste de transmission et en ce que le mobile aérien est dirigé vers la cible, par l'intermédiaire du poste.de transmission.
  6. Procédé selon la revendication 5, caractérisé en ce que le mobile aérien fournit au poste de transmission des informations qui, parallèlement aux informations transmises par le système de reconnaissance, sont traitées dans le poste de transmission, pour le guidage du mobile aérien.
EP99927726A 1998-06-26 1999-06-25 Procede pour combattre a distance des cibles proches du sol et/ou sur le sol Expired - Lifetime EP1090263B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19828644 1998-06-25
DE19828644A DE19828644C2 (de) 1998-06-26 1998-06-26 Verfahren zum ferngesteuerten Bekämpfen bodennaher und/oder bodengebundener Ziele
PCT/DE1999/001862 WO2000000779A1 (fr) 1998-06-26 1999-06-25 Procede pour combattre a distance des cibles proches du sol et/ou sur le sol

Publications (2)

Publication Number Publication Date
EP1090263A1 EP1090263A1 (fr) 2001-04-11
EP1090263B1 true EP1090263B1 (fr) 2002-05-22

Family

ID=7872185

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99927726A Expired - Lifetime EP1090263B1 (fr) 1998-06-26 1999-06-25 Procede pour combattre a distance des cibles proches du sol et/ou sur le sol

Country Status (6)

Country Link
US (1) US6455828B1 (fr)
EP (1) EP1090263B1 (fr)
JP (1) JP4262889B2 (fr)
CA (1) CA2334373C (fr)
DE (2) DE19828644C2 (fr)
WO (1) WO2000000779A1 (fr)

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IL138831A (en) * 2000-10-03 2007-07-24 Rafael Advanced Defense Sys An information system is operated by Mabat
DE10060090A1 (de) * 2000-12-02 2002-06-13 Lfk Gmbh Verfahren zur Übergabe eines Zieles an einen Flugkörper
JP4087104B2 (ja) * 2001-11-20 2008-05-21 シャープ株式会社 群ロボットシステム
IL163450A (en) * 2004-08-10 2009-12-24 Rafael Advanced Defense Sys Guided missile with distributed guidance mechanism
US7328644B2 (en) * 2005-07-12 2008-02-12 Scv Quality Solutions, Llc System and method for intercepting a projectile
DK1767893T3 (en) 2005-09-23 2017-03-06 Saab Ab Missile Transfer System
DE102005054776A1 (de) * 2005-11-15 2007-05-24 Lfk-Lenkflugkörpersysteme Gmbh Lenkverfahren für Flugkörper
DE102007021112B3 (de) * 2007-05-05 2008-07-31 Lfk-Lenkflugkörpersysteme Gmbh Verfahren zur Vergrößerung des Aufklärungsradius eines Kampfhubschraubers, sowie Aufklärungsflugkörper und Kampfhubschrauber zur Durchführung des Verfahrens
DE102010022728A1 (de) * 2010-06-04 2011-12-08 Diehl Bgt Defence Gmbh & Co. Kg Verfahren zum Einweisen eines Flugkörpers auf ein Ziel
US11947349B2 (en) 2012-03-02 2024-04-02 Northrop Grumman Systems Corporation Methods and apparatuses for engagement management of aerial threats
US11313650B2 (en) 2012-03-02 2022-04-26 Northrop Grumman Systems Corporation Methods and apparatuses for aerial interception of aerial threats
DE102012218746A1 (de) * 2012-10-15 2014-04-17 Cassidian Airborne Solutions Gmbh Waffenverbundsystem und Verfahren zur Steuerung desselben
FR3010180B1 (fr) * 2013-09-04 2016-10-21 Dcns Procede d'utilisation d'un missile et systeme d'emploi de missile associe
DE102014007456B3 (de) * 2014-05-21 2015-01-22 Mbda Deutschland Gmbh Modulares Lenkflugkörpersystem
US11112787B2 (en) * 2015-03-25 2021-09-07 Aerovironment, Inc. Machine to machine targeting maintaining positive identification
KR101745853B1 (ko) * 2017-03-03 2017-06-09 국방과학연구소 공간가상영상을 이용한 자동 표적 지정장치 및 그 방법
CN112461059B (zh) * 2020-10-30 2022-12-13 彩虹无人机科技有限公司 一种图像寻的制导导弹地面发射方法

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Also Published As

Publication number Publication date
WO2000000779B1 (fr) 2000-04-27
CA2334373C (fr) 2006-03-14
DE19828644A1 (de) 2000-01-20
EP1090263A1 (fr) 2001-04-11
DE59901512D1 (de) 2002-06-27
WO2000000779A1 (fr) 2000-01-06
US6455828B1 (en) 2002-09-24
JP2002519619A (ja) 2002-07-02
DE19828644C2 (de) 2001-12-06
CA2334373A1 (fr) 2000-01-06
JP4262889B2 (ja) 2009-05-13

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