EP1090263A1 - Verfahren zum ferngesteuerten bekämpfen bodennaher und/oder bodengebundener ziele - Google Patents
Verfahren zum ferngesteuerten bekämpfen bodennaher und/oder bodengebundener zieleInfo
- Publication number
- EP1090263A1 EP1090263A1 EP99927726A EP99927726A EP1090263A1 EP 1090263 A1 EP1090263 A1 EP 1090263A1 EP 99927726 A EP99927726 A EP 99927726A EP 99927726 A EP99927726 A EP 99927726A EP 1090263 A1 EP1090263 A1 EP 1090263A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- missile
- target
- reconnaissance system
- phase
- search
- 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.)
- Granted
Links
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 combating near-ground and / or ground-based targets, such as tanks or the like, by means of a missile having a seeker head, an active charge and at least one engine, in which the missile, after an essentially vertical starting phase, moves into an essentially horizontal march. and the search phase is diverted, in which the missile scans the area lying in front of it by means of the seeker head, whereupon finally after switching on the
- Seeker head connects to a recognized target an essentially downward approach phase.
- Missiles which are suitable for carrying out this method are described, for example, in DE 196 26 975 Cl. Such missiles can hardly be improved in terms of their construction to increase the probability of hits in a cost-effective manner. However, new armor protection systems, such as so-called active protection systems, call for further improvements.
- a missile can be split so that a decoy body that can be separated from a body part with the warhead is detected and fought by sensors of an armored vehicle instead of the body part containing the warhead.
- DE 42 23 531 C2 also discloses a missile which has an inertial reference system for reducing Initialization errors included.
- DE 44 16 885 A1 discloses a method for guiding a missile with at least one radiation source, which can be located by two sensors arranged offset in a launch ramp. Steering commands transmitted to a steering device of the missile are derived from the location signals and hold the missile in the sight line of at least one sensor that detects a target.
- Such control of a missile is already complicated with the LOS method, that is to say in the case of a direct-fire method, if a fault occurs between the launch ramp and the target.
- the known method completely fails if the target is not in line of sight to the launcher, as in the case of NLOS methods.
- the object of the invention is therefore to further develop the generic method in such a way that the disadvantages of the prior art are overcome, that is to say in particular a more precise targeting and higher accuracy is achieved.
- an external reconnaissance system in a suitable aircraft and / or spacecraft such as a helicopter, a drone or a satellite, receives information for guiding the missile, which are transmitted to the missile.
- the reconnaissance system scans the possible target area statically or flying during a mission.
- External reconnaissance system provides information for controlling the missile records and transmits.
- the missile be recognized by the reconnaissance system after detection of a target to be combated, in particular with regard to the type of target, target location and / or target movement, under the control of signals transmitted by the reconnaissance system to a launch device for the missile so that its quasi ballistic trajectory essentially leads to the goal understood by the reconnaissance system.
- a further development according to the invention is characterized in that during the search phase the search angle of the missile's seeker head is continuously optimized as a function of the missile transmitted by the reconnaissance system with a view to recognizing the target.
- the search angle of the missile's search head is largely reduced with a corresponding increase in resolution and on the detection of the missile transmitted by the reconnaissance system details of the target to be combated such as the engine area of a tank or the like is minimized.
- the reconnaissance system forwards information recorded to a transmission station, and the missile is directed to the target via the transmission station.
- the missile delivers information to the transmission station, which is processed together with the information transmitted by the reconnaissance system for guiding the missile in the transmission station.
- the invention is therefore based on the surprising finding that conventionally, missiles operating autonomously by means of a seeker head are additionally controlled remotely via a reconnaissance system, so that in principle there is a combination of two conventional search methods, which considerably increases the error elimination and the accuracy in comparison to the prior art by far exceeds.
- the data connection according to the invention between the missile and the reconnaissance system be it directly or indirectly via a transmission station, current target data can thus be transmitted to the missile during its flight in order to increase the effectiveness of the combat.
- the figure shows a combat scenario in which a tank 1 is to be attacked by a missile 2.
- a helicopter 3 flies over the possible target area and scans the same within a viewing cone I.
- signals are sent from the helicopter 3 to a launching device of the missile 2 at the starting point A, not shown.
- These signals can be transmitted from the helicopter 3 to a transmission station 4 and then to the launching device and contain information which enables the missile 2 to be brought from the starting point A to a quasi-ballistic trajectory a, which is essentially that of the helicopter 3 captured tanks 1 leads.
- the missile 2 flies essentially horizontally and with supersonic.
- the search angle of the seeker head ie the viewing cone b of the guided missile 2
- the search angle of the seeker head is continuously optimized during the search phase as a function of the missile 2 transmitted by the helicopter 3 with respect to the detection of the tank 1.
- the path c of the center of the light cone b of the missile 2 is shown as an example, as it results from the remote control by means of the data acquired, processed and transmitted by the helicopter 3.
- the angle of the light cone b of the guided missile 2 is continuously reduced, depending on details of the tank 1 to be combated, which the helicopter 3 has detected to increase the resolution within the viewing cone b of the missile 2, which at the same time increases the accuracy.
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)
Abstract
Description
Claims
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19828644 | 1998-06-26 | ||
DE19828644A DE19828644C2 (de) | 1998-06-26 | 1998-06-26 | Verfahren zum ferngesteuerten Bekämpfen bodennaher und/oder bodengebundener Ziele |
PCT/DE1999/001862 WO2000000779A1 (de) | 1998-06-26 | 1999-06-25 | Verfahren zum ferngesteuerten bekämpfen bodennaher und/oder bodengebundener ziele |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1090263A1 true EP1090263A1 (de) | 2001-04-11 |
EP1090263B1 EP1090263B1 (de) | 2002-05-22 |
Family
ID=7872185
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP99927726A Expired - Lifetime EP1090263B1 (de) | 1998-06-26 | 1999-06-25 | Verfahren zum ferngesteuerten bekämpfen bodennaher und/oder bodengebundener ziele |
Country Status (6)
Country | Link |
---|---|
US (1) | US6455828B1 (de) |
EP (1) | EP1090263B1 (de) |
JP (1) | JP4262889B2 (de) |
CA (1) | CA2334373C (de) |
DE (2) | DE19828644C2 (de) |
WO (1) | WO2000000779A1 (de) |
Families Citing this family (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1102750A1 (de) | 1998-08-04 | 2001-05-30 | AstraZeneca AB | Amid-derivate verwendbar als inhibitoren der cytokinproduktion |
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 |
ES2619597T3 (es) * | 2005-09-23 | 2017-06-26 | Saab Ab | Sistema de guiado de misil |
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 |
US9170070B2 (en) | 2012-03-02 | 2015-10-27 | Orbital Atk, Inc. | Methods and apparatuses for active protection from aerial threats |
US11313650B2 (en) | 2012-03-02 | 2022-04-26 | Northrop Grumman Systems Corporation | Methods and apparatuses for aerial interception of aerial threats |
US11947349B2 (en) | 2012-03-02 | 2024-04-02 | Northrop Grumman Systems Corporation | Methods and apparatuses for engagement management 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 |
AU2016238311B2 (en) * | 2015-03-25 | 2021-07-08 | 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 |
JP7535282B1 (ja) | 2024-03-16 | 2024-08-16 | 株式会社共伸 | レーザ加工用治具及びこれを有するレーザ加工装置、レーザ加工方法 |
Family Cites Families (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3131089C2 (de) * | 1981-08-06 | 1985-06-13 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Aufklärungs- und Feuerleitsystem |
DE3145374C2 (de) * | 1981-11-14 | 1984-12-20 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Verfahren und Einrichtung zur Bekämpfung von Bodenzielen mittels Flugkörper |
DE3303763A1 (de) * | 1983-02-04 | 1984-08-09 | Diehl GmbH & Co, 8500 Nürnberg | Verfahren zur zielansteuerung eines projektils und zum bestimmen dessen ballistischer flugbahn sowie vorrichtungen zum ausueben der verfahren |
GB2148465B (en) * | 1983-10-20 | 1987-05-28 | Nader Dadabhoy Daroga | Missile control systems |
US5379966A (en) * | 1986-02-03 | 1995-01-10 | Loral Vought Systems Corporation | Weapon guidance system (AER-716B) |
DE3715909C1 (de) | 1987-05-13 | 1998-05-14 | Daimler Benz Aerospace Ag | Zielanflugverfahren |
US5131602A (en) * | 1990-06-13 | 1992-07-21 | Linick James M | Apparatus and method for remote guidance of cannon-launched projectiles |
DE4132233C2 (de) * | 1990-11-22 | 2003-03-06 | Rheinmetall W & M Gmbh | Panzerabwehrraketensystem |
US5260709A (en) * | 1991-12-19 | 1993-11-09 | Hughes Aircraft Company | Autonomous precision weapon delivery using synthetic array radar |
US5186414A (en) * | 1992-04-20 | 1993-02-16 | The United States Of America As Represented By The Secretary Of The Navy | Hybrid data link |
DE4217185C1 (de) | 1992-05-23 | 1993-10-21 | Deutsche Aerospace | Flugkörper |
DE4223531C2 (de) | 1992-07-17 | 1994-10-20 | Bodenseewerk Geraetetech | Einrichtung zur Führung eines aus einem Werfer abgeschossenen, angetriebenen Flugkörpers |
DE4416885C2 (de) | 1994-05-13 | 1998-04-09 | Daimler Benz Aerospace Ag | Vorrichtung zur Lenkung eines Flugkörpers |
US5458041A (en) | 1994-08-02 | 1995-10-17 | Northrop Grumman Corporation | Air defense destruction missile weapon system |
DE19546017C1 (de) * | 1995-12-09 | 1997-04-24 | Daimler Benz Aerospace Ag | Flugkörper-Waffensystem |
IL117589A (en) * | 1996-03-21 | 2001-10-31 | Israel Aircraft Ind Ltd | Air-to-air missile guidance system |
DE19626075C1 (de) | 1996-06-28 | 1998-01-15 | Buck Chem Tech Werke | Flugkörper zur Bekämpfung beweglicher Ziele |
US5917442A (en) * | 1998-01-22 | 1999-06-29 | Raytheon Company | Missile guidance system |
US6318667B1 (en) * | 1999-03-31 | 2001-11-20 | Raymond C. Morton | Stealth weapon systems |
-
1998
- 1998-06-26 DE DE19828644A patent/DE19828644C2/de not_active Expired - Fee Related
-
1999
- 1999-06-25 US US09/720,426 patent/US6455828B1/en not_active Expired - Lifetime
- 1999-06-25 EP EP99927726A patent/EP1090263B1/de not_active Expired - Lifetime
- 1999-06-25 JP JP2000557108A patent/JP4262889B2/ja not_active Expired - Fee Related
- 1999-06-25 CA CA002334373A patent/CA2334373C/en not_active Expired - Fee Related
- 1999-06-25 DE DE59901512T patent/DE59901512D1/de not_active Expired - Lifetime
- 1999-06-25 WO PCT/DE1999/001862 patent/WO2000000779A1/de active IP Right Grant
Non-Patent Citations (1)
Title |
---|
See references of WO0000779A1 * |
Also Published As
Publication number | Publication date |
---|---|
US6455828B1 (en) | 2002-09-24 |
JP4262889B2 (ja) | 2009-05-13 |
CA2334373A1 (en) | 2000-01-06 |
CA2334373C (en) | 2006-03-14 |
JP2002519619A (ja) | 2002-07-02 |
DE59901512D1 (de) | 2002-06-27 |
EP1090263B1 (de) | 2002-05-22 |
DE19828644C2 (de) | 2001-12-06 |
DE19828644A1 (de) | 2000-01-20 |
WO2000000779B1 (de) | 2000-04-27 |
WO2000000779A1 (de) | 2000-01-06 |
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