EP0047479B1 - Transmission method of guide dates to a missile - Google Patents

Transmission method of guide dates to a missile Download PDF

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Publication number
EP0047479B1
EP0047479B1 EP19810106842 EP81106842A EP0047479B1 EP 0047479 B1 EP0047479 B1 EP 0047479B1 EP 19810106842 EP19810106842 EP 19810106842 EP 81106842 A EP81106842 A EP 81106842A EP 0047479 B1 EP0047479 B1 EP 0047479B1
Authority
EP
European Patent Office
Prior art keywords
missile
radio
control transmitter
radiation
signal
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
Application number
EP19810106842
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German (de)
French (fr)
Other versions
EP0047479A2 (en
EP0047479A3 (en
Inventor
Günther Dipl.-Ing. Riedl
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.)
Siemens AG
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Siemens AG
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Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Publication of EP0047479A2 publication Critical patent/EP0047479A2/en
Publication of EP0047479A3 publication Critical patent/EP0047479A3/en
Application granted granted Critical
Publication of EP0047479B1 publication Critical patent/EP0047479B1/en
Expired 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
    • F41G7/30—Command link guidance systems
    • F41G7/301—Details
    • F41G7/306—Details for transmitting guidance signals

Definitions

  • the invention relates to a method for transmitting steering data to an on-board receiver attached to a steerable missile by means of modulated electromagnetic radiation emanating from a command transmitter.
  • steering data can be transmitted from the command transmitter to the on-board receiver of the steerable missile by means of modulated electromagnetic radiation.
  • This steering method is described in DE-A-2 945 847.
  • a receiver attached to the target can receive information about the fact of the missile approach. It is known to design the radio transmission of the commands to the on-board receiver of the guided missile as far as possible in such a way that it is difficult for the opponent to recognize this transmission and the effects of enemy interference are minimized as far as possible.
  • a small transmitter power of the command transmitter is to be used for this. However, this transmitter power must be selected at least so large that the useful field strength at the on-board receiver of the guided missile does not fall below a certain value.
  • the useful field strength of the command signal is large for the receiver during the first time after the launch of the flux body and the interference / useful ratio becomes greater as the missile approaches the target. Since the radiated command transmitter power is kept constant irrespective of the respective distance between the command transmitter and the missile, but is at least so large that there is a sufficient useful / interference ratio at the target throughout the flight time of the missile, the target can be via a receive information about the fact of the missile approach for a relatively long time.
  • a radio transmission system between a fixed and a movable station is now known from US Pat. No. 2,981,943, a signal for the distance between the two stations being derived from the received signal by the receiver of the movable station and with this signal that of the transmitter power to be radiated is adapted to the current distance. In this case, only as much power should be used as is necessary for the respective task in the message transmission. This is to avoid interference from other fixed stations as much as possible.
  • this known radio transmission system is not a guidance system for the transmission of guidance data from a stationary command point to a missile that is moving away.
  • the object of the invention is to provide a method for transmitting steering data from a command transmitter to the on-board receiver of a missile, so that the target of this missile receives as little information as possible about the fact that the missile was approaching.
  • the steering wire which is undesirable for various reasons, should be avoided and modulated electromagnetic radiation should be used in its place. It should also be ensured that the guided missile, which can have a large offset to the axis between the command transmitter and the target at the start of its flight, is detected by the command transmitter's steering signal from the beginning to the end of its trajectory.
  • this object is achieved in that the beam width (angle of divergence) of the command transmitter is dependent on the distance currently existing between the missile and the command transmitter, the information of which is available from the command transmitter is controlled that the on-board receiver in the missile always receives precisely the reception power required for a sufficient signal-to-noise ratio.
  • the radiation power of the command transmitter can also be controlled as a function of the distance between the missile and the command transmitter in such a way that the receiver in the missile always receives the reception power necessary for a sufficient signal-to-noise ratio .
  • the divergence angle of the command transmitter is relatively large in the vicinity of the missile and becomes smaller as the distance between the missile and the command transmitter increases. This also ensures that the guided missile, which may initially have a large storage area to the command transmitter - target axis, is “captured”. In addition, the power density at the destination is kept as low as possible and the risk of betrayal is also kept low.
  • the range-time diagram for the missile consists in that the control of the radiation lobe width and possibly additionally the radiation power of the command transmitter is purely time-dependent.
  • the command transmitter power density can then be relatively small in the vicinity of the missile, ie if the missile is still relatively close to the command transmitter, and increases with increasing distance between the missile and the comm mando transmitter. It is pointed out in this connection that the range-time diagram for the missile is mostly known.
  • Another expedient possibility for determining the control variable for the beam width and, if applicable, the performance of the command transmitter is that a location device connected to the missile's launching system, e.g. on an infrared goniometer, by means of which the position of the guided missile relative to the line of sight of the launch system is determined, the intensity of the signal arriving from the missile (IR signal) is measured and as a signal for controlling the beam width and, if necessary, the radiation power of the Command transmitter is used.
  • IR signal the intensity of the signal arriving from the missile
  • the transmitter frequency of the command transmitter is advantageously selected such that there is a high atmospheric basic attenuation for the electromagnetic radiation emitted by the command transmitter.
  • the weather-dependent “reserve” of transmission power is kept relatively low, so that the otherwise increased risk of treachery is avoided in good weather conditions.

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  • 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)
  • Radar Systems Or Details Thereof (AREA)

Description

Die Erfindung bezieht sich auf ein Verfahren zur Übertragung von Lenkdaten zu einem an einem lenkbaren Flugkörper angebrachten Bordempfänger mittels von einem Kommandosender ausgehender, modulierter elektromagnetischer Strahlung.The invention relates to a method for transmitting steering data to an on-board receiver attached to a steerable missile by means of modulated electromagnetic radiation emanating from a command transmitter.

Es ist bekannt, die Lenkdaten von einem Kommandosender zum lenkbaren Flugkörper mittels Draht zu übermitteln. In diesem Zusammenhang wird z.B. auf den Aufsatz «Das Panzerabwehrwaffensystem MILAN» in der Zeitschrift «Internationale Wehrrevue", Sonderreihe 5, 1978, Seiten 58-62 hingewiesen. Durch die Übermittlung von Lenkdaten an einen Flugkörper mittels Lenkdraht wird erreicht, dass das Ziel dieses Flugkörpers möglichst wenig Information über die Tatsache des Anflugs des Flugkörpers erhält.It is known to transmit the steering data from a command transmitter to the steerable missile by means of wire. In this context, reference is made, for example, to the article "The anti-tank weapon system MILAN" in the magazine "Internationale Wehrrevue " , special series 5, 1978, pages 58-62 receives as little information as possible about the fact that the missile was approaching.

Um den aus mancherlei Gründen unerwünschten Lenkdraht zu vermeiden, können Lenkdaten mittels modulierter elektromagnetischer Strahlung vom Kommandosender an den Bordempfänger des lenkbaren Flugkörpers übermittelt werden. Diese Lenkmethode ist in der DE-A-2 945 847 beschrieben. Dabei kann jedoch ein am Ziel angebrachter Empfänger Information über die Tatsache des Flugkörperanflugs erhalten. Es ist zwar bekannt, die Funkübertragung der Kommandos zum Bordempfänger des ferngelenkten Flugkörpers möglichst so auszulegen, dass dem Gegner das Erkennen dieser Übertragung erschwert wird und Auswirkungen gegnerischer Störungen möglichst herabgesetzt sind. Dazu soll eine kleine Sendeleistung des Kommandosenders verwendet werden. Diese Senderleistung muss aber zumindest so gross gewählt werden, dass die Nutzfeldstärke am Bordempfänger des ferngelenkten Flugkörpers einen bestimmten Wert nicht unterschreitet. Dies bedeutet, dass während der ersten Zeit nach dem Start des Flukörpers für dessen Empfänger die Nutzfeldstärke des Kommandosignals gross ist und bei Annäherung des Flugkörpers an das Ziel das Stör/Nutz-Verhältnis immer grösser wird. Da die abgestrahlte Kommandosenderleistung unabhängig von der jeweiligen Entfernung zwischen dem Kommandosender und dem Flugkörper konstant gehalten wird und dabei aber mindestens so gross ist, dass während der gesamten Flugzeit des Flugkörpers auch am Ziel ein ausreichendes Nutz/Stör-Verhältnis vorliegt, kann das Ziel über eine relativ lange Zeit Information über die Tatsache des Flugkörperanflugs erhalten.In order to avoid the steering wire, which is undesirable for various reasons, steering data can be transmitted from the command transmitter to the on-board receiver of the steerable missile by means of modulated electromagnetic radiation. This steering method is described in DE-A-2 945 847. However, a receiver attached to the target can receive information about the fact of the missile approach. It is known to design the radio transmission of the commands to the on-board receiver of the guided missile as far as possible in such a way that it is difficult for the opponent to recognize this transmission and the effects of enemy interference are minimized as far as possible. A small transmitter power of the command transmitter is to be used for this. However, this transmitter power must be selected at least so large that the useful field strength at the on-board receiver of the guided missile does not fall below a certain value. This means that the useful field strength of the command signal is large for the receiver during the first time after the launch of the flux body and the interference / useful ratio becomes greater as the missile approaches the target. Since the radiated command transmitter power is kept constant irrespective of the respective distance between the command transmitter and the missile, but is at least so large that there is a sufficient useful / interference ratio at the target throughout the flight time of the missile, the target can be via a receive information about the fact of the missile approach for a relatively long time.

Aus der US-PS 2 981 943 ist nunmehr ein Funk- übertragungssystem zwischen einer festen und einer beweglichen Station bekannt, wobei vom Empfänger der beweglichen Station aus dem empfangenen Signal ein Signal für die Entfernung zwischen den beiden Stationen abgeleitet wird und mit diesem Signal die von der Antenne abzustrahlende Senderleistung der augenblicklichen Entfernung angepasst wird. Es soll dabei jeweils nur soviel Leistung aufgewendet werden, wie es für die jeweilige Aufgabe bei der Nachrichtenübertragung erforderlich ist. Damit soll eine Störung von anderen festen Stationen möglichst vermieden werden. Bei diesem bekannten Funkübertragungssystem handelt es sich aber nicht um ein Lenksystem zur Übertragung von Lenkdaten von einer ortsfesten Kommandostelle zu einem sich entfernenden Flugkörper.A radio transmission system between a fixed and a movable station is now known from US Pat. No. 2,981,943, a signal for the distance between the two stations being derived from the received signal by the receiver of the movable station and with this signal that of the transmitter power to be radiated is adapted to the current distance. In this case, only as much power should be used as is necessary for the respective task in the message transmission. This is to avoid interference from other fixed stations as much as possible. However, this known radio transmission system is not a guidance system for the transmission of guidance data from a stationary command point to a missile that is moving away.

Aufgabe der Erfindung ist es, ein Verfahren zur Übermittlung von Lenkdaten von einem Kommandosender an den Bordempfänger eines Flugkörpers anzugeben, so dass das Ziel dieses Flugkörpers möglichst wenig Information über die Tatsache des Anflugs des Flugkörpers erhält. Der aus mancherlei Gründen unerwünschte Lenkdraht soll vermieden und an seiner Stelle modulierte elektromagnetische Strahlung verwendet werden. Dabei soll auch sichergestellt sein, dass der Lenkflugkörper, der am Anfang seines Fluges eine grosse Ablage zur Achse zwischen dem Kommandosender und dem Ziel haben kann, vom Anfang bis zum Ende seiner Flugbahn vom Lenksignal des Kommandosenders erfasst wird.The object of the invention is to provide a method for transmitting steering data from a command transmitter to the on-board receiver of a missile, so that the target of this missile receives as little information as possible about the fact that the missile was approaching. The steering wire, which is undesirable for various reasons, should be avoided and modulated electromagnetic radiation should be used in its place. It should also be ensured that the guided missile, which can have a large offset to the axis between the command transmitter and the target at the start of its flight, is detected by the command transmitter's steering signal from the beginning to the end of its trajectory.

Gemäss der Erfindung, die sich auf ein Verfahren der eingangs genannten Art bezieht, wird diese Aufgabe dadurch gelöst, dass die Abstrahlungskeulenbreite (Divergenzwinkel) des Kommandosenders in Abhängigkeit von der zwischen dem Flugkörper und dem Kommandosender momentan bestehenden Entfernung, deren Angabe beim Kommandosender vorliegt, so gesteuert wird, dass der Bordempfänger im Flugkörper stets gerade die für ein ausreichendes Signal-Rausch-verhältnis nötige Empfangsleistung erhält.According to the invention, which relates to a method of the type mentioned at the outset, this object is achieved in that the beam width (angle of divergence) of the command transmitter is dependent on the distance currently existing between the missile and the command transmitter, the information of which is available from the command transmitter is controlled that the on-board receiver in the missile always receives precisely the reception power required for a sufficient signal-to-noise ratio.

Zusätzlich zur Steuerung der Abstrahlungskeulenbreite des Kommandosenders kann gemäss einer Weiterbildung der Erfindung auch die Abstrahlleistung des Kommandosenders in Abhängigkeit von der Entfernung zwischen dem Flugkörper und dem Kommandosender so gesteuert werden, dass der Empfänger im Flugkörper stets gerade die für ein ausreichendes Signal-Rauschverhältnis nötige Empfangsleistung erhält.In addition to controlling the radiation beam width of the command transmitter, according to a further development of the invention, the radiation power of the command transmitter can also be controlled as a function of the distance between the missile and the command transmitter in such a way that the receiver in the missile always receives the reception power necessary for a sufficient signal-to-noise ratio .

Der Divergenzwinkel des Kommandosenders ist dabei im Nahbereich des Flugkörpers verhältnismässig gross und wird mit zunehmendem Abstand zwischen Flugkörper und Kommandosender kleiner. Dadurch wird gleichermassen sichergestellt, dass der Lenkflugkörper, der am Anfang eine grosse Ablage zur Achse Kommandosender - Ziel haben kann, «eingefangen» wird. Darüber hinaus wird die Leistungsdichte am Ziel möglichst klein und ebenfalls die Verratsgefahr gering gehalten.The divergence angle of the command transmitter is relatively large in the vicinity of the missile and becomes smaller as the distance between the missile and the command transmitter increases. This also ensures that the guided missile, which may initially have a large storage area to the command transmitter - target axis, is “captured”. In addition, the power density at the destination is kept as low as possible and the risk of betrayal is also kept low.

Eine vorteilhafte Weiterbildung der Erfindung unter der Voraussetzung, dass das Entfernungs-Zeit-Diagramm für den Flugkörper bekannt ist, besteht darin, dass die Steuerung der Abstrahlungskeulenbreite und gegebenenfalls zusätzlich der Abstrahlleistung des Kommandosenders rein zeitabhängig erfolgt. Die Kommandosenderleistungsdichte kann dann im Nahbereich des Flugkörpers, d.h. wenn der Flugkörper noch relativ nahe beim Kommandosender ist, verhältnsimässig klein sein und steigt mit zunehmender Entfernung zwischen dem Flugkörper und dem Kommandosender an. Es wird in diesem Zusammenhang noch darauf hingewiesen, dass das Entfernungs-Zeit-Diagramm für den Flugkörper meistens bekannt ist.An advantageous further development of the invention, provided that the range-time diagram for the missile is known, consists in that the control of the radiation lobe width and possibly additionally the radiation power of the command transmitter is purely time-dependent. The command transmitter power density can then be relatively small in the vicinity of the missile, ie if the missile is still relatively close to the command transmitter, and increases with increasing distance between the missile and the comm mando transmitter. It is pointed out in this connection that the range-time diagram for the missile is mostly known.

Eine andere zweckmässige Möglichkeit zur Ermittlung der Steuergrösse für die Keulenbreite und gegebenenfalls die Leistung des Kommandosenders besteht darin, dass an einer mit der Abschussanlage des Flugkörpers verbundenen Ortungseinrichtung, z.B. an einem Infrarot-Goniometer, mittels welchem an sich die Lage des lenkbaren Flugkörpers relativ zur Visierlinie der Abschussanlage bestimmt wird, die Intensität des vom Flugkörper eintreffenden Signals (IR-Signal) gemessen und als Signal für die Steuerung der Abstrahlungskeulenbreite und gegebenenfalls zusätzlich der Abstrahlleistung des Kommandosenders verwendet wird. Durch diese Massnahme wird eine optimale Anpassung an die wetterabhängigen Dämpfungswerte der Atmosphäre erzielt.Another expedient possibility for determining the control variable for the beam width and, if applicable, the performance of the command transmitter is that a location device connected to the missile's launching system, e.g. on an infrared goniometer, by means of which the position of the guided missile relative to the line of sight of the launch system is determined, the intensity of the signal arriving from the missile (IR signal) is measured and as a signal for controlling the beam width and, if necessary, the radiation power of the Command transmitter is used. This measure enables an optimal adaptation to the weather-dependent attenuation values of the atmosphere.

In vorteilhafter Weise wird die Senderfrequenz des Kommandosenders so gewählt, dass sich eine hohe atmosphärische Grunddämpfung für die vom Kommandosender ausgesendete elektromagnetische Strahlung ergibt. Dadurch wird die witterungsabhängige «Reserve» an Sendeleistung relativ gering gehalten, so dass die ansonsten erhöhte Verratsgefahr bei guten Witterungsbedingungen vermieden wird.The transmitter frequency of the command transmitter is advantageously selected such that there is a high atmospheric basic attenuation for the electromagnetic radiation emitted by the command transmitter. As a result, the weather-dependent “reserve” of transmission power is kept relatively low, so that the otherwise increased risk of treachery is avoided in good weather conditions.

Claims (6)

1. A method of transmission of guide data to an air-borne receiver attached to a controllable missile, by means of modulated electromagnetic radiation from a radio-control transmitter, characterised in that the radiation lobe width of the radio-control transmitter is varied in dependence upon the instantaneous distance between the missile and the radio-control transmitter, an indication of which is present at the radio-control transmitter, such that the receiver in the missile continually receives the level of received power required for an efficient signal-to-noise ratio.
2. A method as claimed in Claim 1, characterised in that the radiation power of the radio-control transmitter is additionally controlled in dependence upon the spacing between the missile and the radio-control transmitter, such that the receiver in the missile continually receives the received power required for an efficient signal-to-noise ratio.
3. A method as claimed in Claim 1 or 2, characterised in that where the distance-time-diagram for the missile is known, the control of the radiation lobe width and possibly also of the radiation power of the radio-control transmitter is effected purely in dependence upon time.
4. A method as claimed in Claim 1 or 2, characterised in that on an orientation device, e.g. on an infrared goniometer, by means of which the position of the controllable missile relative to the line of sight of the launching point is determined per se, the intensity of the signal arriving from the missile is measured and used as a signal for control of the radiation lobe width and possibly also of the radiation power of the radio-control transmitter.
5. A method as claimed in one of the preceding Claims, characterised in that the transmitting frequency of the radio-control transmitter is selected such that the fundamental atmospheric attenuation for the transmitted electromagnetic radiation is high.
EP19810106842 1980-09-04 1981-09-01 Transmission method of guide dates to a missile Expired EP0047479B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3033357 1980-09-04
DE19803033357 DE3033357C2 (en) 1980-09-04 1980-09-04 Method for the transmission of guidance data to a missile

Publications (3)

Publication Number Publication Date
EP0047479A2 EP0047479A2 (en) 1982-03-17
EP0047479A3 EP0047479A3 (en) 1983-01-19
EP0047479B1 true EP0047479B1 (en) 1987-01-07

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP19810106842 Expired EP0047479B1 (en) 1980-09-04 1981-09-01 Transmission method of guide dates to a missile

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EP (1) EP0047479B1 (en)
DE (1) DE3033357C2 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5259568A (en) * 1984-01-17 1993-11-09 Werkzeugmaschinenfabrik Oerlikon-Buehrle Ag Command optics
GB2282734B (en) * 1989-11-13 1995-08-09 Philips Electronic Associated Communications system
US5691531A (en) * 1995-11-09 1997-11-25 Leigh Aerosystems Corporation Data insertion system for modulating the carrier of a radio voice transmitter with missile control signals
DE19618602A1 (en) * 1996-05-09 1997-11-13 Bodenseewerk Geraetetech Interface for digital data transmission between a missile and a launch device
DE102009035016A1 (en) * 2009-07-28 2011-02-03 Diehl Bgt Defence Gmbh & Co. Kg Method for the wireless transmission of information formed from data packets

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE534532A (en) * 1953-12-30
US3998406A (en) * 1964-05-28 1976-12-21 Aeronutronic Ford Corporation Guided missile system
FR1449622A (en) * 1965-02-23 1966-05-06 Labo Cent Telecommunicat Multi-mode aerial improvements for monopulse radar
FR2161775B1 (en) * 1971-11-29 1976-06-04 Labo Cent Telecommunicat
FR2441145A1 (en) * 1978-11-09 1980-06-06 Aerospatiale GUIDANCE SYSTEM FOR BURST SHOT OF REMOTE CONTROLLED MISSILES

Also Published As

Publication number Publication date
EP0047479A2 (en) 1982-03-17
DE3033357C2 (en) 1984-11-08
DE3033357A1 (en) 1982-04-01
EP0047479A3 (en) 1983-01-19

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