EP1090263B1 - Method for remote controlled combat of near-surface and/or surface targets - Google Patents
Method for remote controlled combat of near-surface and/or surface targets Download PDFInfo
- 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
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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.
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- 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)
Description
Die Erfindung betrifft ein Verfahren zum Bekämpfen bodennaher und/oder bodengebundener Ziele, wie Panzer oder dergleichen, mittels eines einen Suchkopf, eine Wirkladung und mindestens ein Triebwerk aufweisenden Flugkörpers, bei dem der Flugkörper nach einer im wesentlichen vertikalen Startphase in eine im wesentlichen horizontale Marsch- und Suchphase umgelenkt wird, in welcher der Flugkörper mittels des Suchkopfs das vor ihm liegende Gelände abtastet, woraufhin sich schließlich nach Aufschalten des Suchkopfes auf ein erkanntes Ziel eine im wesentlichen nach abwärts gerichtete Anflugphase anschließt, wobei ein externes Aufklärungssystem in einem geeigneten Luft- und/oder Raumfahrzeug, wie einem Hubschrauber, einer Drohne oder einem Satelliten, Informationen zur Lenkung des Flugkörpers aufnimmt.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.
In der DE 196 26 975 C1 ist ein Flugkörper beschrieben, der hinsichtlich seines Aufbaus zur Steigerung der Trefferwahrscheinlichkeit auf kostengünstige Weise kaum noch verbesserbar ist. Jedoch fordern insbesondere neue Panzerschutzsysteme, wie sogenannte aktive Schutzsysteme, weitere Verbesserungen.DE 196 26 975 C1 describes a missile which, with regard to its Structure to increase the probability of hits in a cost-effective manner can hardly be improved. However, especially new ones Armor protection systems, such as so-called active protection systems, others Improvements.
So ist, beispielsweise, in der DE 42 17 185 C1 bereits vorgeschlagen worden, daß ein Flugkörper aufteilbar ist, so daß ein von einem Körperteil mit dem Gefechtskopf abtrennbarer Täuschkörper von Sensoren eines Panzerfahrzeugs anstelle des den Gefechtskopf enthaltenden Körperteils erfaßt und bekämpft wird. For example, it has already been proposed in DE 42 17 185 C1 that a missile is divisible, so that one of a body part with the Warhead detachable decoy from sensors of an armored vehicle instead of the body part containing the warhead is detected and fought.
Als autonomer Flugkörper ist ferner in der DE 42 23 531 C2 ein Flugkörper offenbart, der ein Trägheitsreferenzsystem zur Verringerung von Initialisierungsfehlern umfaßt.DE 42 23 531 C2 also describes a missile as an autonomous missile which discloses an inertial reference system for reducing Initialization errors included.
Anstelle von autonomen Flugkörpern, insbesondere mit Suchköpfen und/oder Trägheitsreferenzsystemen, sind auch Flugkörper bekannt, die gänzlich über eine externe Einrichtung auf ein Ziel hin gelenkt werden. So offenbart, beispielsweise, die DE 44 16 885 A1 ein Verfahren zur Lenkung eines Flugkörpers mit mindestens einer Strahlungsquelle, die von zwei in einer Abschußrampe zueinander versetzt angeordneten Sensoren geortet werden kann. Aus den Ortungssignalen werden dabei an eine Lenkeinrichtung des Flugkörpers übertragene Lenkkommandos abgeleitet, die den Flugkörper in der Visierlinie zumindest eines ein Ziel erfassenden Sensors halten. Solch eine Steuerung eines Flugkörpers ist bereits bei LOS-Verfahren, also im Falle eines Direktschußverfahrens, kompliziert, wenn zwischen der Abschußrampe und dem Ziel eine Störung auftritt. Gänzlich versagt das bekannte Verfahren jedoch, wenn das Ziel nicht in einer Sichtverbindung zu der Abschußrampe steht, wie im Falle von NLOS-Verfahren.Instead of autonomous missiles, especially with search heads and / or Inertial reference systems, missiles are also known, which have a complete external device can be directed towards a goal. For example, 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. 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. However, the known method fails completely if the target is not in line of sight to the launcher as in the case of NLOS procedures.
Aus der GB-A-2 148 465 ist ein gattungsgemäßes Verfahren bekannt, bei dem die Flugkörpertrajektorie in Abhängigkeit von von dem Aufklärungssystem empfangenen Zielinformationen über Justierung einer Starteinrichtung einstellbar ist und vom Aufklärungssystem aufgenommene Fotos noch vor dem Start in einen Speicher des Flugkörpers eingegeben werden.From GB-A-2 148 465 a generic method is known in which the Missile trajectory depending on the received from the reconnaissance system Target information is adjustable via adjustment of a starting device and from Photos taken before the start into a memory of the reconnaissance system Missile can be entered.
Aus der EP 0 797 068 A2, der US 5,458,041 sowie der DE 37 15 909 C1 sind Verfahren zum Lenken von Flugkörpern bekannt, die von Flugzeugen aus gestartet werden. From EP 0 797 068 A2, US 5,458,041 and DE 37 15 909 C1 Method for guiding missiles known from aircraft be started.
Die DE 31 45 374 A1 sowie die DE 33 03 763 A1 beschreiben Verfahren zur Bekämpfung von Bodenzielen mittels Flugkörpern, wobei diese Flugkörper jedoch nicht aufgrund von Informationen, die über ein externes Aufklärungssystem erhalten werden können, gelenkt werden können.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.
Aufgabe der Erfindung ist es daher, das gattungsgemäße Verfahren derart weiterzuentwickeln, daß die Nachteile des Stands der Technik überwunden werden, das heißt insbesondere eine genauere Zielaufschaltung und höhere Treffgenauigkeit erreicht wird.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.
Diese Aufgabe wird erfindungsgemäß dadurch gelöst, daß die von dem Aufklärungssystem aufgenommenen Information zur Lenkung des Flugkörpers zu dem Flugkörper übertragen werden, und während der Suchphase der Suchwinkel des Suchkopfs des Flugkörpers laufend in Abhängigkeit von dem Flugkörper durch das Aufklärungssystem übermittelten Zieldaten im Hinblick auf das Erkennen des Ziels optimiert wird.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.
Dabei kann nach der Erfindung vorgesehen sein, daß das Aufklärungssystem statisch oder fliegend das mögliche Zielgebiet während einer Mission abtastet ein externes Aufklärungssystem Informationen zur Steuerung des Flugkörpers aufnimmt und überträgt.It can be provided according to the invention that 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.
Erfindungsgemäß wird auch vorgeschlagen, daß der Flugkörper nach Erkennen eines zu bekämpfenden Zieles durch das Aufklärungssystem, insbesondere hinsichtlich Zielart, Zielort und/oder Zielbewegung, unter Steuerung von durch das Aufklärungssystem an eine Starteinrichtung für den Flugkörper übermittelte Signale so gestartet wird, daß seine quasi-ballistische Flugbahn im wesentlichen zum durch das Aufklärungssystem aufgefaßten Ziel führt. According to the invention it is also proposed that 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.
Nach der Erfindung ist weiterhin bevorzugt, daß nach Erkennen des Ziels und Aufschalten des Suchkopfes des Flugkörpers auf dieses in der Zielanflugsphase der Suchwinkel des Suchkopfes des Flugkörpers weitestgehend unter entsprechender Auflösungserhöhung verkleinert und auf das Erkennen von dem Flugkörper durch das Aufklärungssystem übermittelten Details des zu bekämpfenden Ziels, wie Motorbereich eines Panzers oder dergleichen, minimiert wird.According to the invention it is further preferred that after recognizing the target and Activation of the missile's search head on this in the target approach phase 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.
Ferner kann erfindungsgemäß vorgesehen sein, daß das Aufklärungssystem aufgenommene Informationen an eine Übertragungsstation weiterleitet, und über die Übertragungsstation der Flugkörper zum Ziel gelenkt wird.It can further be provided according to the invention that the reconnaissance system forwards recorded information to a transmission station, and via the missile transfer station is directed to the target.
Schließlich wird nach der Erfindung dabei auch vorgeschlagen, daß der Flugkörper Informationen an die Übertragungsstation liefert, die zusammen mit den von dem Aufklärungssystem übermittelten Informationen zur Lenkung des Flugkörpers in der Übertragungsstation bearbeitet werden.Finally, it is also proposed according to the invention that 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.
Der Erfindung liegt somit die überraschende Erkenntnis zugrunde, daß herkömmlicherweise mittels eines Suchkopfs autonom arbeitende Flugkörper zusätzlich über ein Aufklärungssystem ferngesteuert werden und dem Flugkörper permanent Informationen von dem externen Aufklärungssystem übermittelt werden können, um die Zielrichtung des Flugkörpers während der Suchphase ständig zu optimieren, so daß es im Prinzip zur Kombination zweier herkömmlicher Suchverfahren kommt, was die Fehlerausschaltung erheblich erhöht und die Treffergenauigkeit im Vergleich zum Stand der Technik bei weitem übertrifft. Über die erfindungsgemäße Datenverbindung zwischen dem Flugkörper und dem Aufklärungssystem, sei es direkt oder indirekt über eine Übertragungsstation, können somit dem Flugkörper noch während seines Fluges aktuelle Zieldaten zur Erhöhung der Bekämpfungseffektivität übermittelt werden. 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.
Weitere Merkmale und Vorteile der Erfindung ergeben sich aus der nachfolgenden Beschreibung, in der ein Ausführungsbeispiel der Erfindung anhand einer schematischen Zeichnung im einzelnen erläutert ist. Dabei zeigt die aus einer einzigen Figur bestehende Zeichnung ein Kampfszenario in perspektivischer Ansicht.Further features and advantages of the invention result from the following Description in which an embodiment of the invention using a schematic drawing is explained in detail. The shows from a single figure existing drawing a combat scenario in perspective View.
In der Figur ist ein Kampfszenario dargestellt, bei dem ein Panzer 1 von einem
Flugkörper 2 anzugreifen ist. Zu diesem Zweck überfliegt ein Hubschrauber 3 das
mögliche Zielgebiet und tastet selbiges innerhalb eines Sichtkegels I ab. Sobald
von dem Hubschrauber 3 der Panzer 1 als Ziel, sowohl hinsichtlich Zielart, Zielort
und Zielbewegung, erkannt worden ist, werden Signale von dem Hubschrauber 3
zu einer nicht gezeigten Starteinrichtung des Flugkörpers 2 am Startpunkt A
übersendet. Diese Signale können dabei von dem Hubschrauber 3 zu einer
Übertragungsstation 4 und dann zur Starteinrichtung übermittelt werden und
enthalten Informationen, die es ermöglichen, daß der Flugkörper 2 vom Startpunkt
A auf eine quasi-ballistische Flugbahn a gebracht wird, die im wesentlichen zum
durch den Hubschrauber 3 erfaßten Panzer 1 führt.In the figure, a combat scenario is shown in which a tank 1 by one
Missile 2 is to be attacked. For this purpose, a
Während der Suchphase fliegt der Flugkörper 2 im wesentlichen horizontal und
mit Überschall. Dabei wird der Suchwinkel des Suchkopfs, also der Sichtkegel b
des Lenkflugkörpers 2, während der Suchphase laufend in Abhängigkeit von dem
Flugkörper 2 durch den Hubschrauber 3 übermittelten Zieldaten im Hinblick auf
das Erkennen des Panzers 1 optimiert. In der Figur ist beispielhaft die Bahn c des
Mittelpunkts des Lichtkegels b des Flugkörpers 2 dargestellt, wie sie sich durch
die Fernsteuerung mittels der von dem Hubschrauber 3 erfaßten, bearbeiteten und
übermittelten Daten ergibt.During the search phase, 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, during the search phase continuously depending on the
Missile 2 transmitted by the
Nachdem der Suchkopf des Flugkörpers 2 den Panzer 1 erkannt hat und der
Flugkörper 2 auf den Panzer 1 aufgeschaltet hat, also in der Zielanflugphase, wird
der Winkel des Lichtkegels b des Lenkflugkörpers 2 ständig verkleinert, in
Abhängigkeit von Details des zu bekämpfenden Panzers 1, die der Hubschrauber 3
erfaßt hat, um die Auflösung innerhalb des Sichtkegels b des Flugkörpers 2 zu
erhöhen, was gleichzeitig die Zielgenauigkeit steigert So ist es, beispielsweise,
möglich, genau auf den Motorbereich des Panzers 1 zu zielen, so daß sich die
Wirkladung des Flugkörpers 1 im Motorbereich entfaltet, wie in der Figur
symbolisiert.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
Die in der vorstehenden Beschreibung, in der Zeichnung sowie in den Ansprüchen offenbarten Merkmale der Erfindung können sowohl einzeln als auch in jeder beliebigen Kombination für die Verwirklichung der Erfindung in ihren verschiedenen Ausführungsformen wesentlich sein.The in the above description, in the drawing and in the claims Disclosed features of the invention can be used individually as well as in each any combination for realizing the invention in their different embodiments may be essential.
Claims (6)
- A method of combating ground-based or near-ground targets such as armoured vehicles or the like, by means of a missile containing a homing head, an active charge and at least one engine, wherein the missile, after a substantially vertical starting phase, is deflected into a substantially horizontal cruising and homing phase in which the missile, via the homing head, scans the ground in front, followed finally by a substantially downward directed approach phase after the homing head has recognised and locked on to a target, wherein an external reconnaissance system in a suitable air and/or space vehicle such as a helicopter, drone or satellite receives information for guiding the missile, characterised in that the information for guiding the missile received by the reconnaissance system is transmitted to the missile, and during the homing phase the angle of the missile homing head is continuously improved for recognising the target in dependence on data transmitted by the reconnaissance system to the missile.
- A method according to claim 1, characterised in that the reconnaissance system, either static or flying, scans the possible target area during a mission.
- A method according to claim 1 or 2, characterised in that after a target for combating has been recognised by the reconnaissance system, particularly as regards nature, position and/or movement of the target, the missile is started under control of signals transmitted by the reconnaissance system to a missile-starting device so that the quasi-ballistic flight path of the missile leads substantially to the target picked up by the reconnaissance system.
- A method according to any of the preceding claims, characterised in that after the target has been recognised and the homing head of the missile has locked on to it in the target approach phase, the homing angle of the missile head is substantially reduced with corresponding increase of resolution and restricted to recognising details of the target communicated to the missile by the reconnaissance system, such as the engine area of an armoured vehicle or the like.
- A method according to any of the preceding claims, characterised in that the reconnaissance system transmits received information to a transmission station, via which the missile is guided towards the target.
- A method according to claim 5, characterised in that the missile supplies information to the transmission station for processing therein together with the information transmitted by the reconnaissance system for guiding the missile.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19828644 | 1998-06-25 | ||
| DE19828644A DE19828644C2 (en) | 1998-06-26 | 1998-06-26 | Process for remote control of ground-based and / or ground-based targets |
| PCT/DE1999/001862 WO2000000779A1 (en) | 1998-06-26 | 1999-06-25 | Method for remote controlled combat of near-surface and/or surface targets |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1090263A1 EP1090263A1 (en) | 2001-04-11 |
| EP1090263B1 true EP1090263B1 (en) | 2002-05-22 |
Family
ID=7872185
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP99927726A Expired - Lifetime EP1090263B1 (en) | 1998-06-26 | 1999-06-25 | Method for remote controlled combat of near-surface and/or surface targets |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US6455828B1 (en) |
| EP (1) | EP1090263B1 (en) |
| JP (1) | JP4262889B2 (en) |
| CA (1) | CA2334373C (en) |
| DE (2) | DE19828644C2 (en) |
| WO (1) | WO2000000779A1 (en) |
Families Citing this family (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1142912C (en) | 1998-08-04 | 2004-03-24 | 阿斯特拉曾尼卡有限公司 | Amide derivs. useful as inhibitors of production of cytokines |
| IL138831A (en) * | 2000-10-03 | 2007-07-24 | Rafael Advanced Defense Sys | Gaze-actuated information system |
| DE10060090A1 (en) * | 2000-12-02 | 2002-06-13 | Lfk Gmbh | Procedure for handing over a target to a missile |
| JP4087104B2 (en) * | 2001-11-20 | 2008-05-21 | シャープ株式会社 | Group robot system |
| 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 |
| EP1767893B1 (en) * | 2005-09-23 | 2016-12-28 | Saab Ab | Missile guidance system |
| DE102005054776A1 (en) * | 2005-11-15 | 2007-05-24 | Lfk-Lenkflugkörpersysteme Gmbh | Steering method for missiles |
| DE102007021112B3 (en) * | 2007-05-05 | 2008-07-31 | Lfk-Lenkflugkörpersysteme Gmbh | Reconnaissance radius enlarging method for combat helicopter, involves carrying unmanned reconnaissance drones in combat helicopters, and launching reconnaissance drones into operational area from flying combat helicopters |
| DE102010022728A1 (en) * | 2010-06-04 | 2011-12-08 | Diehl Bgt Defence Gmbh & Co. Kg | Method for instructing a missile on a target |
| US11947349B2 (en) | 2012-03-02 | 2024-04-02 | Northrop Grumman Systems Corporation | Methods and apparatuses for engagement management of aerial threats |
| 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 |
| DE102012218746A1 (en) * | 2012-10-15 | 2014-04-17 | Cassidian Airborne Solutions Gmbh | Weapon composite system and method of controlling the same |
| FR3010180B1 (en) * | 2013-09-04 | 2016-10-21 | Dcns | METHOD FOR USING A MISSILE AND ASSOCIATED MISSILE EMPLOYMENT SYSTEM |
| DE102014007456B3 (en) * | 2014-05-21 | 2015-01-22 | Mbda Deutschland Gmbh | Modular guided missile system |
| CN114152251A (en) | 2015-03-25 | 2022-03-08 | 威罗门飞行公司 | Machine-to-machine targeting with positive identification maintained |
| KR101745853B1 (en) * | 2017-03-03 | 2017-06-09 | 국방과학연구소 | Automatic target designation device using space virtual image and method thereof |
| CN112461059B (en) * | 2020-10-30 | 2022-12-13 | 彩虹无人机科技有限公司 | Image homing guided missile ground launching method |
Family Cites Families (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3131089C2 (en) * | 1981-08-06 | 1985-06-13 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Reconnaissance and fire control system |
| DE3145374C2 (en) * | 1981-11-14 | 1984-12-20 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Method and device for combating ground targets by means of missiles |
| DE3303763A1 (en) | 1983-02-04 | 1984-08-09 | Diehl GmbH & Co, 8500 Nürnberg | METHOD FOR TARGETING A PROJECTILE AND DETERMINING ITS BALLISTIC FLIGHT TRACK AND DEVICES FOR EXECUTING THE METHOD |
| 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 (en) | 1987-05-13 | 1998-05-14 | Daimler Benz Aerospace Ag | Target seeking method for missile |
| US5131602A (en) * | 1990-06-13 | 1992-07-21 | Linick James M | Apparatus and method for remote guidance of cannon-launched projectiles |
| DE4132233C2 (en) * | 1990-11-22 | 2003-03-06 | Rheinmetall W & M Gmbh | Antitank missile system |
| 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 (en) | 1992-05-23 | 1993-10-21 | Deutsche Aerospace | Anti-tank projectile - has detaching head to accelerate ahead and trigger defence systems, to give clear zone for projectile to strike |
| DE4223531C2 (en) | 1992-07-17 | 1994-10-20 | Bodenseewerk Geraetetech | Device for guiding a powered missile shot from a launcher |
| DE4416885C2 (en) | 1994-05-13 | 1998-04-09 | Daimler Benz Aerospace Ag | Missile guidance device |
| US5458041A (en) * | 1994-08-02 | 1995-10-17 | Northrop Grumman Corporation | Air defense destruction missile weapon system |
| DE19546017C1 (en) * | 1995-12-09 | 1997-04-24 | Daimler Benz Aerospace Ag | Missile weapon system |
| IL117589A (en) | 1996-03-21 | 2001-10-31 | Israel Aircraft Ind Ltd | Guidance system for air-to-air missiles |
| DE19626075C1 (en) | 1996-06-28 | 1998-01-15 | Buck Chem Tech Werke | Missiles to combat moving targets |
| 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/en not_active Expired - Fee Related
-
1999
- 1999-06-25 US US09/720,426 patent/US6455828B1/en not_active Expired - Lifetime
- 1999-06-25 JP JP2000557108A patent/JP4262889B2/en not_active Expired - Fee Related
- 1999-06-25 DE DE59901512T patent/DE59901512D1/en not_active Expired - Lifetime
- 1999-06-25 CA CA002334373A patent/CA2334373C/en not_active Expired - Fee Related
- 1999-06-25 WO PCT/DE1999/001862 patent/WO2000000779A1/en active IP Right Grant
- 1999-06-25 EP EP99927726A patent/EP1090263B1/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| EP1090263A1 (en) | 2001-04-11 |
| WO2000000779B1 (en) | 2000-04-27 |
| CA2334373A1 (en) | 2000-01-06 |
| DE19828644C2 (en) | 2001-12-06 |
| JP4262889B2 (en) | 2009-05-13 |
| WO2000000779A1 (en) | 2000-01-06 |
| DE19828644A1 (en) | 2000-01-20 |
| DE59901512D1 (en) | 2002-06-27 |
| CA2334373C (en) | 2006-03-14 |
| JP2002519619A (en) | 2002-07-02 |
| US6455828B1 (en) | 2002-09-24 |
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