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EP1088199A1 - Missile guidance method - Google Patents

Missile guidance method

Info

Publication number
EP1088199A1
EP1088199A1 EP99929139A EP99929139A EP1088199A1 EP 1088199 A1 EP1088199 A1 EP 1088199A1 EP 99929139 A EP99929139 A EP 99929139A EP 99929139 A EP99929139 A EP 99929139A EP 1088199 A1 EP1088199 A1 EP 1088199A1
Authority
EP
European Patent Office
Prior art keywords
missile
target
steering method
projectile
distance
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.)
Ceased
Application number
EP99929139A
Other languages
German (de)
French (fr)
Inventor
Rainer Schöffl
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.)
Dynamit Nobel Defence GmbH
Original Assignee
Dynamit Nobel AG
Dynamit Nobel GmbH Explosivstoff und Systemtechnik
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 Dynamit Nobel AG, Dynamit Nobel GmbH Explosivstoff und Systemtechnik filed Critical Dynamit Nobel AG
Publication of EP1088199A1 publication Critical patent/EP1088199A1/en
Ceased legal-status Critical Current

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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/007—Preparatory measures taken before the launching of the guided missiles

Definitions

  • the invention relates to a missile guidance method according to the preamble of claim 1 and a missile for carrying out the guidance method.
  • Guided missiles are available in a wide variety of designs and with a variety of steering methods, such as. B. in the book “Guided Weapons", R.G. Lee et al, published by Brassey's.
  • a steering method is proposed, which is characterized in that
  • the missile has one or more sensors which are switched on after a predetermined flight time
  • the sensor or sensors determine whether the missile will fly past the target at a short distance and -
  • the missile may perform a one-time orbit correction by a fixed amount.
  • the data transmission from the range finder into the missile is advantageously contactless and wireless. This means that no wiring is necessary, which prevents possible damage.
  • the one or more sensors are expediently rigidly connected to the missile.
  • the search area of the at least one sensor should be selected so that the target is detected as long as it is in the path correction area of the missile.
  • An essential feature is that the at least one sensor detects the direction in which the path correction has to take place.
  • a missile according to the invention for carrying out this method is characterized in that at least one rocket engine which acts briefly laterally is used to control (correct shortly before it hits) the missile.
  • the at least one sensor and the at least one rocket engine can be retrofitted to existing missiles.
  • Fig. 1a shows the result of a hit simulation for an anti-tank shoulder weapon that fires an unguided missile. It can be seen that out of 13 shots 8 shots would have hit the target, one tank, 4 shots would have missed the target and 1 shot would have missed the target. The reasons for the misses are made up of several individual influencing factors, such as. B. Accuracy of the missile, mistake of the shooter, incorrect sighting or crosswind. 1 b shows the improvement of the hit positions aimed at by a suitable steering method, in which scarce misses are avoided and hits in the peripheral areas are shifted towards the center of the target. However, the miss far behind the target is not corrected. Compared to FIG. 1a, the probability of hit increases from 61.5% to 92.3% in FIG. 1b, ie 1 miss in 13 shots.
  • FIG. 2 shows the features of the steering method according to the invention.
  • a missile 1 fired at the time t 0 flies along the line 2 in the direction of the tank 3.
  • a sensor is switched on in the missile 1, the field of vision 4 of which detects the tank 3 and its near surroundings 5.
  • the missile 1 would just fly past the tank 3.
  • the trajectory 6 is therefore offset by the amount X, so that the tank 3 can be hit.
  • FIG. 3 shows a block diagram of the steering method used in FIG. 2.
  • a laser rangefinder attached to the launcher measures the distance to the tank, calculates the flight time to there based on the theoretical trajectory and passes this value on to a timer in the missile. This switches on the target sensor (s) at a predetermined time before the target. Signal processing electronics determine whether the target is hit or not. In the latter case, a trigger signal is given to the control element depending on the roll position of the missile.
  • Fig. 4 shows the execution of a weapon with which the steering method according to the invention is applied.
  • a laser range finder 8 with a telescopic sight 9.
  • the weapon has two handles 10, 11 and a shoulder rest 12.
  • a firing lever 13 and a trigger lever 14 are used for firing.
  • a transmission antenna 15 which is connected to the laser range finder 8 by cable.
  • the warhead 16 of the missile 1, which is otherwise inserted in the launch tube 7, consists of a shaped charge 17 and a steering / control part 18, which contains the target sensor, a roll position sensor and contains the control mechanism.
  • the flight time determined by the laser range finder 8 is transmitted to the steering / control part 18 without contact via the antenna 15.

Landscapes

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

Abstract

The invention relates to a missile guidance method, more particularly for anti-armor projectiles fired directly at a target. In order to avoid missing a target by a narrow margin, the invention provides that the distance to the target (3) be measured with a range finder (8) before the projectile is fired. The flying time previously calculated on the basis of target distance is inputted to the projectile (1). The projectile (1) has one or several sensors which are activated after a predetermined flying time, said sensor or sensors determining whether the projectile (1) will fly over the target at a minimum distance. Optionally, the projectile (1) conducts a single trajectory adjustment with a fixed value.

Description

Lenkverfahren für Flugkörper Guiding procedures for missiles

Die Erfindung betrifft ein Lenkverfahren für Flugkörper nach dem Oberbegriff des Anspruchs 1 und einen Flugkörper zur Durchführung des Lenkverfahrens.The invention relates to a missile guidance method according to the preamble of claim 1 and a missile for carrying out the guidance method.

Gelenkte Flugkörper gibt es in den unterschiedlichsten Ausführungen und mit einer Vielzahl von Lenkverfahren, wie z. B. im Buch „Guided Weapons", R. G. Lee et al, Verlag Brassey's, beschrieben.Guided missiles are available in a wide variety of designs and with a variety of steering methods, such as. B. in the book "Guided Weapons", R.G. Lee et al, published by Brassey's.

Neben Flugkörpern, die vom Start an gelenkt werden, gibt es noch sogenannte „endphasengelenkte" Flugkörper, die erst gegen Ende ihrer Flugzeit mit Hilfe eines Suchkopfes oder mit Hilfe von Sensoren das Ziel suchen und ansteuern (siehe NATO's Sixteen Nations, Special Edition, 1990).In addition to missiles that are guided from the start, there are also so-called "final phase-guided" missiles, which only search for and target the end of their flight time with the aid of a seeker head or with the aid of sensors (see NATO's Sixteen Nations, Special Edition, 1990) .

Bei Flugkörpern, wie z. B. ungelenkten Panzerabwehrgeschossen, die ihr Ziel nur in wenigen Fällen verfehlen, sind derartige Lenkverfahren zu aufwendig, um die an sich geringe Anzahl von Fehlschüssen zu vermeiden. Es wird deshalb ein Lenkverfahren benötigt, das mit einfachen Methoden Fehlschüsse, die das Ziel nur knapp verfehlen, vermeidet.For missiles, such as B. unguided anti-tank missiles that miss their target in only a few cases, such steering methods are too expensive to avoid the small number of misses per se. A steering process is therefore required that uses simple methods to avoid misses that only just miss the target.

Es wird ein Lenkverfahren vorgeschlagen, welches dadurch gekennzeichnet ist, daßA steering method is proposed, which is characterized in that

- vor dem Abschuß die Entfernung zum Ziel mit einem Entfernungsmesser gemessen wird,- the distance to the target is measured with a range finder before firing,

- aus dem Zielabstand die vorausberechnete Flugzeit in den Flugkörper eingegeben wird,- the predicted flight time is entered into the missile from the target distance,

- der Flugkörper über einen Sensor oder mehrere Sensoren verfügt, die nach vorbestimmter Flugzeit eingeschaltet werden,the missile has one or more sensors which are switched on after a predetermined flight time,

- der oder die Sensoren feststellen, ob der Flugkörper in geringem Abstand am Ziel vorbeifliegen wird und - der Flugkörper gegebenenfalls eine einmalige Bahnkorrektur um einen feststehenden Betrag durchführt. Vorteilhafterweise erfolgt die Datenübertragung vom Entfernungsmesser in den Flugkörper kontakt- und drahtlos. Hierdurch ist keine Verdrahtung notwendig, wodurch mögliche Beschädigungen vermieden werden.- The sensor or sensors determine whether the missile will fly past the target at a short distance and - The missile may perform a one-time orbit correction by a fixed amount. The data transmission from the range finder into the missile is advantageously contactless and wireless. This means that no wiring is necessary, which prevents possible damage.

Weiterhin sind zweckmäßigerweise der eine Sensor oder die mehreren Sensoren starr mit dem Flugkörper verbunden. Der Suchbereich des wenigstens einen Sensors sollte so gewählt sein, daß das Ziel erfaßt wird, so lange es sich im Bahnkorrekturbereich des Flugkörpers befindet.Furthermore, the one or more sensors are expediently rigidly connected to the missile. The search area of the at least one sensor should be selected so that the target is detected as long as it is in the path correction area of the missile.

Ein wesentliches Merkmal ist, daß der wenigstens eine Sensor die Richtung feststellt, in der die Bahnkorrektur zu erfolgen hat.An essential feature is that the at least one sensor detects the direction in which the path correction has to take place.

Ein erfindungsgemäßer Flugkörper zur Durchführung dieses Verfahrens zeichnet sich dadurch aus, daß zur Steuerung (Korrektur kurz vor dem Auftreffen) des Flugkörpers wenigstens ein kurzzeitig seitlich wirkendes Raketentriebwerk verwendet wird.A missile according to the invention for carrying out this method is characterized in that at least one rocket engine which acts briefly laterally is used to control (correct shortly before it hits) the missile.

Vorteilhafterweise sind der wenigstens eine Sensor und das wenigstens eine Raketentriebwerk an vorhandene Flugkörper nachträglich anbaubar.Advantageously, the at least one sensor and the at least one rocket engine can be retrofitted to existing missiles.

Weitere Merkmale der Erfindung ergeben sich aus den Figuren, die nachfolgend beschrieben sind.Further features of the invention emerge from the figures, which are described below.

Fig. 1a zeigt das Ergebnis einer Treffersimulation für eine Panzerabwehr- Schulterwaffe, die einen ungelenkten Flugkörper verschießt. Man sieht daraus, daß von 13 Schüssen 8 Schüsse das Ziel, einen Panzer, getroffen hätten, 4 Schüsse das Ziel knapp verfehlt und 1 Schuß das Ziel weit verfehlt hätte. Die Gründe für die Fehlschüsse setzen sich aus mehreren einzelnen Einflußgrößen zusammen, wie z. B. Genauigkeit des Flugkörpers, Zielfehler des Schützen, falsche Visiereinstellung oder Seitenwind. Fig. 1 b zeigt die durch ein geeignetes Lenkverfahren angestrebte Verbesserung der Trefferlagen, bei dem knappe Fehlschüsse vermieden und Treffer in den Randbereichen in Richtung Zielmitte verschoben werden. Der weit hinter dem Ziel liegende Fehlschuß wird dagegen nicht korrigiert. Im Vergleich zu Fig. 1a steigt in Fig. 1 b die Treffwahrscheinlichkeit von 61 ,5 % auf 92,3 %, d. h. 1 Fehlschuß bei 13 Schüssen.Fig. 1a shows the result of a hit simulation for an anti-tank shoulder weapon that fires an unguided missile. It can be seen that out of 13 shots 8 shots would have hit the target, one tank, 4 shots would have missed the target and 1 shot would have missed the target. The reasons for the misses are made up of several individual influencing factors, such as. B. Accuracy of the missile, mistake of the shooter, incorrect sighting or crosswind. 1 b shows the improvement of the hit positions aimed at by a suitable steering method, in which scarce misses are avoided and hits in the peripheral areas are shifted towards the center of the target. However, the miss far behind the target is not corrected. Compared to FIG. 1a, the probability of hit increases from 61.5% to 92.3% in FIG. 1b, ie 1 miss in 13 shots.

Fig. 2 zeigt die Merkmale des erfindungsgemäßen Lenkverfahrens. Ein zum Zeitpunkt t0 abgefeuerter Flugkörper 1 fliegt entlang der Linie 2 in Richtung Panzer 3. Zum Zeitpunkt ty wird im Flugkörper 1 ein Sensor eingeschaltet, dessen Blickfeld 4 den Panzer 3 sowie sein näheres Umfeld 5 erfaßt. In dem in Fig. 2 dargestellten Beispiel würde der Flugkörper 1 knapp am Panzer 3 vorbeifliegen. Mit Hilfe eines Steuermechanismus wird deshalb die Flugbahn 6 um den Betrag X versetzt, so daß der Panzer 3 getroffen werden kann.2 shows the features of the steering method according to the invention. A missile 1 fired at the time t 0 flies along the line 2 in the direction of the tank 3. At the time t y , a sensor is switched on in the missile 1, the field of vision 4 of which detects the tank 3 and its near surroundings 5. In the example shown in FIG. 2, the missile 1 would just fly past the tank 3. With the help of a control mechanism, the trajectory 6 is therefore offset by the amount X, so that the tank 3 can be hit.

Fig. 3 zeigt ein Blockschaltbild des in Fig. 2 angewandten Lenkverfahrens. Ein am Abschußgerät angebrachter Laserentfernungsmesser mißt den Abstand zum Panzer, errechnet anhand der theoretischen Flugbahn die Flugzeit bis dorthin und gibt diesen Wert an einen Zeitgeber im Flugkörper weiter. Dieser schaltet zu einem vorgegebenen Zeitpunkt vor dem Ziel den oder die Zielsensoren ein. In einer Signalverarbei- tungselektronik wird festgestellt, ob das Ziel getroffen wird oder nicht. In letzterem Fall wird ein Auslösesignal abhängig von der Rolllage des Flugkörpers an das Steuerelement gegeben.FIG. 3 shows a block diagram of the steering method used in FIG. 2. A laser rangefinder attached to the launcher measures the distance to the tank, calculates the flight time to there based on the theoretical trajectory and passes this value on to a timer in the missile. This switches on the target sensor (s) at a predetermined time before the target. Signal processing electronics determine whether the target is hit or not. In the latter case, a trigger signal is given to the control element depending on the roll position of the missile.

Fig. 4 zeigt die Ausführung einer Waffe mit der das erfindungsgemäße Lenkverfahren angewandt wird. An einem Abschußrohr 7 befindet sich ein Laserentfernungsmesser 8 mit aufgesetztem Zielfernrohr 9. Die Waffe verfügt über zwei Handgriffe 10, 11 und eine Schulterstütze 12. Zum Abfeuern dient ein Sicherungshebel 13 und ein Abzugshebel 14. Ebenfalls am Abschußrohr 7 angebracht ist eine Sendeantenne 15, die mit dem Laserentfernungsmesser 8 durch Kabel verbunden ist. Der Gefechtskopf 16 des ansonsten im Abschußrohr 7 steckenden Flugkörpers 1 besteht aus einer Hohlladung 17 und einem Lenk-/Steuerteil 18, das den Zielsensor, einen Rolllagesensor sowie den Steuermechanismus enthält. Über die Antenne 15 wird die vom Laserentfernungsmesser 8 ermittelte Flugzeit berührungslos in das Lenk-/Steuerteil 18 übertragen. Fig. 4 shows the execution of a weapon with which the steering method according to the invention is applied. On a launch tube 7 there is a laser range finder 8 with a telescopic sight 9. The weapon has two handles 10, 11 and a shoulder rest 12. A firing lever 13 and a trigger lever 14 are used for firing. Also attached to the launch tube 7 is a transmission antenna 15 which is connected to the laser range finder 8 by cable. The warhead 16 of the missile 1, which is otherwise inserted in the launch tube 7, consists of a shaped charge 17 and a steering / control part 18, which contains the target sensor, a roll position sensor and contains the control mechanism. The flight time determined by the laser range finder 8 is transmitted to the steering / control part 18 without contact via the antenna 15.

Claims

Ansprüche Expectations 1. Lenkverfahren für Flugkörper (1 ), insbesondere Panzerabwehrgeschosse, die direkt gegen ein Ziel (3) geschossen werden, dadurch gekennzeichnet, daß - vor dem Abschuß die Entfernung zum Ziel (3) mit einem Entfernungsmesser (8) gemessen wird,1. Steering method for missiles (1), in particular anti-tank projectiles which are shot directly at a target (3), characterized in that - before the launch, the distance to the target (3) is measured with a range finder (8), - aus dem Zielabstand die vorausberechnete Flugzeit in den Flugkörper (1 ) eingegeben wird,- the predicted flight time is entered into the missile (1) from the target distance, - der Flugkörper (1 ) über einen Sensor oder mehrere Sensoren verfügt, die nach vorbestimmter Flugzeit eingeschaltet werden,- The missile (1) has one or more sensors that are switched on after a predetermined flight time, - der oder die Sensoren feststellen, ob der Flugkörper (1 ) in geringem Abstand am Ziel vorbeifliegen wird und- The or the sensors determine whether the missile (1) will fly past the target at a short distance and - der Flugkörper (1 ) gegebenenfalls eine einmalige Bahnkorrektur um einen feststehenden Betrag durchführt.- The missile (1) may perform a one-time orbit correction by a fixed amount. 2. Lenkverfahren nach Anspruch 1 , dadurch gekennzeichnet, daß die Datenübertragung vom Entfernungsmesser (8) in den Flugkörper (1 ) kontakt- und drahtlos erfolgt.2. Steering method according to claim 1, characterized in that the data transmission from the range finder (8) in the missile (1) is contact and wireless. 3. Lenkverfahren nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß der eine Sensor oder die mehreren Sensoren starr mit dem Flugkörper (1 ) verbunden sind.3. Steering method according to claim 1 or 2, characterized in that the one or more sensors are rigidly connected to the missile (1). 4. Lenkverfahren nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß der Suchbereich des wenigstens einen Sensors so gewählt ist, daß das Ziel erfaßt wird, so lange es sich im Bahnkorrekturbereich des Flugkörpers (1 ) befindet.4. Steering method according to one of claims 1 to 3, characterized in that the search range of the at least one sensor is selected so that the target is detected as long as it is in the path correction area of the missile (1). 5. Lenkverfahren nach Anspruch 1 , dadurch gekennzeichnet, daß der wenigstens eine Sensor die Richtung feststellt, in der die Bahnkorrektur zu erfolgen hat. 5. Steering method according to claim 1, characterized in that the at least one sensor determines the direction in which the path correction has to take place. 6. Flugkörper zur Durchführung des Lenkverfahrens nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß zur Steuerung des Flugkörpers (1 ) wenigstens ein kurzzeitig seitlich wirkendes Raketentriebwerk verwendet wird.6. Missile for performing the steering method according to one of claims 1 to 5, characterized in that for controlling the missile (1) at least one briefly laterally acting rocket engine is used. 7. Flugkörper nach Anspruch 6, dadurch gekennzeichnet, daß der wenigstens eine Sensor und das wenigstens eine Raketentriebwerk an vorhandene Flugkörper (1 ) nachträglich anbaubar sind. 7. Missile according to claim 6, characterized in that the at least one sensor and the at least one rocket engine can be retrofitted to existing missiles (1).
EP99929139A 1998-06-18 1999-06-04 Missile guidance method Ceased EP1088199A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19827168.9A DE19827168B4 (en) 1998-06-18 1998-06-18 Steering method for missiles
DE19827168 1998-06-18
PCT/EP1999/003872 WO1999066283A1 (en) 1998-06-18 1999-06-04 Missile guidance method

Publications (1)

Publication Number Publication Date
EP1088199A1 true EP1088199A1 (en) 2001-04-04

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EP99929139A Ceased EP1088199A1 (en) 1998-06-18 1999-06-04 Missile guidance method

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US (1) US6488231B1 (en)
EP (1) EP1088199A1 (en)
AU (1) AU4605699A (en)
DE (1) DE19827168B4 (en)
WO (1) WO1999066283A1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7185844B2 (en) * 2004-04-30 2007-03-06 Technology Service Corporation Methods and systems for guiding an object to a target using an improved guidance law
IL203983A (en) * 2010-02-16 2014-08-31 Oren Aharon Launching a projectile from a platform
US20170307334A1 (en) * 2016-04-26 2017-10-26 Martin William Greenwood Apparatus and System to Counter Drones Using a Shoulder-Launched Aerodynamically Guided Missile
US12416474B2 (en) 2022-04-29 2025-09-16 Bae Systems Information And Electronic Systems Integration Inc. Guidance kit with variable angular offset for undetected ground suppression and methods thereof

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3013405A1 (en) * 1980-04-05 1981-10-08 GRS Gesellschaft für Raketen-Systeme mbH, 5300 Bonn METHOD FOR AVOIDING MESSAGE FROM LAUNCHERS FOR BALLISTIC missiles

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2538665A1 (en) * 1975-08-30 1977-03-10 Messerschmitt Boelkow Blohm PROCEDURE AND EQUIPMENT FOR LETTERING BOMBS
US4492166A (en) * 1977-04-28 1985-01-08 Martin Marietta Corporation Submunition having terminal trajectory correction
DE2738266A1 (en) * 1977-08-25 1979-03-01 Licentia Gmbh Ballistic missile with automatic guidance - uses stored target image and trajectory for detection of deviations
US4238090A (en) * 1978-09-22 1980-12-09 The United States Of America As Represented By The Secretary Of The Army All-weather intercept of tanks from a helicopter
DE2846962C2 (en) * 1978-10-27 1981-02-05 Precitronic Gesellschaft Fuer Feinmechanik Und Electronic Mbh, 2000 Hamburg Laser light shot simulator for guided missiles
FR2514884B1 (en) * 1981-10-20 1985-07-12 Sfim METHOD AND DEVICE FOR GLOBALLY CORRECTING, FROM ONE SHOOTING TO THE NEXT, THE SHOOTING OF A TENSIONED WEAPON
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
SE445952B (en) * 1983-03-25 1986-07-28 Bofors Ab DEVICE FOR REDUCING PROJECT DISTRIBUTION
US4657208A (en) * 1985-06-10 1987-04-14 The United States Of America As Represented By The Secretary Of The Army Rotating warhead
DE3522154A1 (en) * 1985-06-21 1987-01-02 Diehl Gmbh & Co SEARCH SUBMUNITION
DE4401315B4 (en) * 1994-01-19 2006-03-09 Oerlikon Contraves Gmbh Device for trajectory correction
JPH08278098A (en) * 1995-04-04 1996-10-22 Mitsubishi Heavy Ind Ltd Missile guiding system
DE19543048A1 (en) * 1995-11-06 1997-08-28 Bodenseewerk Geraetetech Apparatus for generating steering signals for target tracking projectile

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3013405A1 (en) * 1980-04-05 1981-10-08 GRS Gesellschaft für Raketen-Systeme mbH, 5300 Bonn METHOD FOR AVOIDING MESSAGE FROM LAUNCHERS FOR BALLISTIC missiles

Also Published As

Publication number Publication date
WO1999066283A1 (en) 1999-12-23
DE19827168B4 (en) 2019-01-17
US6488231B1 (en) 2002-12-03
AU4605699A (en) 2000-01-05
DE19827168A1 (en) 1999-12-23

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