EP0234030A1 - Dispositif de guidage d'un engin volant - Google Patents

Dispositif de guidage d'un engin volant Download PDF

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Publication number
EP0234030A1
EP0234030A1 EP86117392A EP86117392A EP0234030A1 EP 0234030 A1 EP0234030 A1 EP 0234030A1 EP 86117392 A EP86117392 A EP 86117392A EP 86117392 A EP86117392 A EP 86117392A EP 0234030 A1 EP0234030 A1 EP 0234030A1
Authority
EP
European Patent Office
Prior art keywords
missile
guide beam
beacon
subfield
code
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
Application number
EP86117392A
Other languages
German (de)
English (en)
Other versions
EP0234030B1 (fr
Inventor
Gregor Dr. Ing. Cremosnik
Joachim Dipl.-Phys. Timper
Johann Dipl.-Phys. Holzberger
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.)
Rheinmetall Air Defence AG
Original Assignee
Werkzeugmaschinenfabrik Oerlikon Buhrle AG
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 Werkzeugmaschinenfabrik Oerlikon Buhrle AG filed Critical Werkzeugmaschinenfabrik Oerlikon Buhrle AG
Publication of EP0234030A1 publication Critical patent/EP0234030A1/fr
Application granted granted Critical
Publication of EP0234030B1 publication Critical patent/EP0234030B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/24—Beam riding guidance systems
    • F41G7/26—Optical guidance systems

Definitions

  • the invention relates to a device for guiding a missile with the aid of an electromagnetic beacon, in a path on which the missile is to move against a target, the beacon being coded so that the missile receives the information with which it is on the desired Can move web.
  • an optical guide beam is generated by a light source, with which a missile is directed against a target from a launch base.
  • Means are available to fan out the guide beam in such a way that the beam cross section consists of intersecting beams.
  • Means are also provided for modulating and deflecting the fanned out light beam, each bar being modulated differently.
  • the missile there is a receiver with photocells and control elements to steer the missile along the beacon against the target.
  • a guide beam is also generated with the aid of a light source, in a path on which the missile is to move.
  • the guide beam cross-section is broken down into a checkerboard-like area, each field of the checkerboard-like cross-sectional area having its own code, such that the receiver in the missile can recognize the field in which the guide beam cross-sectional area is located.
  • Digital frequency modulation of the beacon of a device for guiding a missile is e.g. in U.S. Patent 4,299,360.
  • two rotating coding disks are used, with passage openings which allow the guide beam to pass through and modulate the guide beam according to their arrangement on the disk.
  • the guide beam is divided into four quadrants in frequency by using four beam sources, each of which has a different frequency.
  • the modulated radiation from the four sources is combined into a single beam with the desired spatial modulation.
  • the object to be achieved with the present invention is to create a simple device for guiding a missile, in which the risk that the missile inadvertently leaves the guide beam and can no longer be guided is as small as possible.
  • the inventive device for guiding a missile, with which this object is achieved is characterized in that: - A device for the gradual deflection of the beacon and a device for coding the beacon are coupled to one another via a computer in order to generate a separate code on each subfield of a scanning field.
  • a chessboard-like scanning field is preferably generated with the aid of the device for deflecting the guide beam, and each subfield is given its own code with the aid of the device for coding the guide beam.
  • a scanning field with circles or spirals or any other pattern can also be generated.
  • the invention consists essentially in modulating a guide beam, in particular a CO2 laser beam, first by means of an acousto-optical or electro-optical crystal with a code which contains the information to be transmitted.
  • the coded guide beam is deflected by a suitable device, in particular a deflection or scanning mirror, such that it e.g. creates a checkerboard-like scanning field with eight by eight subfields.
  • the deflected guide beam remains on each subfield until the required information has been transmitted and only then jumps to the next subfield.
  • a missile 6 is to be directed to a target 4 with the aid of a beacon 3.
  • a steering device 2 which directs the steering beam 3 towards the target 4 to be combated.
  • the directional axis 5 in the middle of the beacon 3 is indicated by dashed lines.
  • the missile 6 is to be directed against the target 4 in this guide beam 3.
  • the guide beam 3 is e.g. with the aid of a target tracking device, which is not described in detail here, is constantly aimed at the moving target 4. Instead of using the target tracking device, the guide beam 3 can be guided by hand to the target 4 until the missile 6 has reached the target 4.
  • the guide beam 3 must have a sufficiently large cross section to ensure that the missile 6 cannot fly out of the guide beam 3 after it is once in the guide beam 3.
  • a guide beam 3 is generated which, compared to known guide beams, requires less power to generate it, ie the energy for generating the guide beam 3 is smaller than before, since only a subfield of the scanning beam is illuminated.
  • the coding should be able to be chosen as desired and should also be changeable as desired. This is not the case with known steering devices.
  • the data transmission performance should be high.
  • the laser 11 fed by a current source 10 generates a guide beam 3, the divergence of which is set by a device 12 for expanding the guide beam.
  • the guide beam is then encoded by a modulator 13.
  • the coded guide beam is changed by zoom optics 14 such that during the flight of the missile 6 e.g. the cross-section of the beacon is adjusted depending on the distance of the missile.
  • the focused and coded guide beam is deflected by a scanning mirror 15 and generates the checkerboard-like field 16.
  • An encoder 18 is connected to the modulator 13 via a driver 17 and a control element 20 is connected to the scanning mirror 15 via a driver 19.
  • the control element 20 is also connected to the zoom optics 14 via a driver 21. Both the encoder 18 and the control element 20 are connected to a common computer 22. Missiles 6 are indicated in different subfields 23 in the checkerboard-like scanning field 16 of the guide beam 3.
  • a frequency f a 80 Hz in the row direction, ie in the azimuth
  • each reference bit each has to be transmitted for azimuth and elevation, then 23 bits are required for each subfield 23.
  • the modulator 13 must therefore operate at a frequency of approximately 12 kHz.
  • the modulator 13 can operate at a maximum frequency of 10 MHz.
  • each piece of information is therefore transmitted to the missile 6 not only once but 10 times. Therefore the modulator has to work at 120kHz instead of 12kHz. In this way, the disturbing influence of the atmosphere can be largely eliminated. It is also possible to transmit further information.
  • the missile 6 can be directed into the center of a partial field 23 by utilizing the natural beam distribution or by additional modulation.
  • the coding of the scanning field 16 described enables several missiles 6 to be steered simultaneously in different subfields 23 without the coding having to be changed.
  • coding can be used, in particular the analog methods: amplitude, frequency and phase modulation and the digital methods: on / off keying, frequency keying and phase shift keying. In the present case, however, the digital methods, in particular the phase shift, are preferred. Keying.
  • the coding is achieved by a phase jump compared to a reference signal.
  • phase jump is 180 °
  • the logical assignment is "0" or "L” and if the phase jump is 0 °, the logical assignment "1" or "H” results.
  • the eight lines are labeled with three bits each as follows: 000, 001, 010, 011, 100, 101, 110 and 111.
  • the eight columns are labeled in the same way with three bits each: 000, 001, 010, 011, 100, 101, 110 and 111.
  • Subfield 23 thus has the code "000 000" in the first row and in the first column and the subfield in the last row and in the last column has the code "111 111".
  • a first frequency A corresponds to the logical assignment "0”
  • a second frequency B corresponds to the logical assignment "1”.
  • the rest of the coding corresponds to the phase shift keying just mentioned.
  • the encoder in the transmitter is synchronized with the decoder in the receiver before the launch of the missile.
  • the missile 30 has at its rear end a photodetector 31 with an upstream one Collecting lens and a narrow band filter, which is connected to detector electronics 32.
  • detector electronics 32 In this detector electronics 32 there is an amplifier, a filter and a decoder. Special evaluation electronics in the missile are required to determine the center of the field.
  • a computer is connected to the detector electronics 32 33 connected.
  • Control elements 35 are present for guiding the missile 30, for example pivotable wings or nozzles.
  • the payload 36 for example an explosive charge, is located in the front part of the missile 30.
  • a current source 34 is provided to supply the various elements.

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)
  • Radar Systems Or Details Thereof (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
EP86117392A 1986-01-30 1986-12-13 Dispositif de guidage d'un engin volant Expired - Lifetime EP0234030B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH34986 1986-01-30
CH349/86 1986-01-30

Publications (2)

Publication Number Publication Date
EP0234030A1 true EP0234030A1 (fr) 1987-09-02
EP0234030B1 EP0234030B1 (fr) 1990-11-28

Family

ID=4184991

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86117392A Expired - Lifetime EP0234030B1 (fr) 1986-01-30 1986-12-13 Dispositif de guidage d'un engin volant

Country Status (8)

Country Link
US (1) US4709875A (fr)
EP (1) EP0234030B1 (fr)
CA (1) CA1264842A (fr)
DE (1) DE3675926D1 (fr)
DK (1) DK48287A (fr)
ES (1) ES2019870B3 (fr)
IL (1) IL81417A (fr)
NO (1) NO165814C (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2689644A1 (fr) * 1992-03-30 1993-10-08 Saint Louis Inst Dispositif de détection et mesure de l'écart de trajectoire d'un projectile.
NL1031288C2 (nl) * 2006-03-03 2007-09-04 Thales Nederland Bv Apparaat en werkwijze voor geleiding van een projectiel.
DE102013209052A1 (de) 2013-05-15 2014-11-20 Rheinmetall Air Defence Ag Vorrichtung zur Flugbahnkorrektur eines Geschosses

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2627268B1 (fr) * 1988-02-12 1993-05-14 Thomson Brandt Armements Systeme de guidage de vecteur par faisceau laser et impulseurs pyrotechniques, et vecteur guide par un tel systeme
US5102065A (en) * 1988-02-17 1992-04-07 Thomson - Csf System to correct the trajectory of a projectile
NL8801917A (nl) * 1988-08-02 1990-03-01 Hollandse Signaalapparaten Bv Koerscorrectiesysteem voor in baan corrigeerbare voorwerpen.
IT9047709A1 (it) * 1989-03-24 1990-09-25 Thomson Csf Sistema per la guida di proietti tramite fascio direttore codificato in coordinate cartesiane.
DE4007712A1 (de) * 1990-03-10 1991-09-12 Tzn Forschung & Entwicklung Geschoss mit einem bugseitig angeordneten ir-suchsystem
US5375008A (en) * 1991-07-17 1994-12-20 Electronic Warfare Associates, Inc. Systems for distinguishing between friendly ground targets and those of a foe
DE4416211C2 (de) * 1994-05-07 1996-09-26 Rheinmetall Ind Gmbh Verfahren und Vorrichtung zur Flugbahnkorrektur von Geschossen
DE4444635C2 (de) * 1994-12-15 1996-10-31 Daimler Benz Aerospace Ag Einrichtung zur Selbstverteidigung gegen Flugkörper
US5537711A (en) * 1995-05-05 1996-07-23 Tseng; Yu-Che Electric board cleaner
US8371201B2 (en) * 2004-08-25 2013-02-12 Bae Systems Information And Electronic Systems Integration Inc. Method and apparatus for efficiently targeting multiple re-entry vehicles with multiple kill vehicles
DE102010004820A1 (de) * 2010-01-15 2011-07-21 Rheinmetall Air Defence Ag Verfahren zur Flugbahnkorrektur eines insbesondere endphasengelenkten Geschosses sowie Geschoss zur Durchführung des Verfahrens
US8237095B2 (en) * 2010-02-24 2012-08-07 Lockheed Martin Corporation Spot leading target laser guidance for engaging moving targets
EP2390616A1 (fr) * 2010-05-27 2011-11-30 Nederlandse Organisatie voor toegepast -natuurwetenschappelijk onderzoek TNO Procédé de guidage d'une salve de projectiles guidés vers une cible, système et produit de programme informatique
US8872081B2 (en) * 2011-11-01 2014-10-28 Ge Aviation Systems Llc Methods for adjusting a relative navigation system
US9012822B2 (en) * 2012-07-18 2015-04-21 Thales Holdings Uk Plc Missile guidance
US9322651B2 (en) 2012-08-29 2016-04-26 Ge Aviation Systems Llc System and method for utilizing multiple sensors
IL236338B (en) * 2014-12-18 2018-12-31 Israel Aerospace Ind Ltd Guidance system and method
US9435635B1 (en) * 2015-02-27 2016-09-06 Ge Aviation Systems Llc System and methods of detecting an intruding object in a relative navigation system
US20190004544A1 (en) * 2017-06-29 2019-01-03 Ge Aviation Systems, Llc Method for flying at least two aircraft
RU2704675C1 (ru) * 2019-04-11 2019-10-30 Акционерное общество "Научно-технический центр ЭЛИНС" Устройство формирования оптического поля для телеориентирования управляемых объектов

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1958139A1 (de) * 1969-11-19 1971-05-27 Messerschmitt Boelkow Blohm Anordnung zur optischen Leitstrahllenkung von Flugzeugen und Flugkoerpern
FR2458044A1 (fr) * 1979-06-02 1980-12-26 Messerschmitt Boelkow Blohm Procede de defense contre les engins volants ou les missiles
GB2066431A (en) * 1979-12-22 1981-07-08 Diehl Gmbh & Co Optical remote-control means for a propectile
DE3341186A1 (de) * 1982-11-13 1984-06-28 British Aerospace Plc, London Strahlgefuehrtes lenksystem
DE3311349A1 (de) * 1983-03-29 1984-10-11 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Verfahren zur vermessung eines bewegten koerpers im raum

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US3690594A (en) * 1964-05-20 1972-09-12 Eltro Gmbh Method and apparatus for the determination of coordinates
FR1466437A (fr) * 1965-12-06 1967-01-20 Csf Système optique de guidage d'un projectile
US3782667A (en) * 1972-07-25 1974-01-01 Us Army Beamrider missile guidance method
US4014482A (en) * 1975-04-18 1977-03-29 Mcdonnell Douglas Corporation Missile director
JPS5842431B2 (ja) * 1975-12-29 1983-09-20 富士重工業株式会社 飛翔体の光ビ−ム誘導装置
GB1524122A (en) * 1976-01-29 1978-09-06 Elliott Brothers London Ltd Guidance systems for mobile craft
US4186899A (en) * 1977-12-12 1980-02-05 Ford Motor Company Controlled beam projector
US4209224A (en) * 1977-12-12 1980-06-24 Ford Aerospace & Communications Corp. Prismatic beam rotator for an optical beam projector
US4245800A (en) * 1978-06-22 1981-01-20 Hughes Aircraft Company Spatial coding of laser beams by optically biasing electro-optic modulators
FR2441145A1 (fr) * 1978-11-09 1980-06-06 Aerospatiale Systeme de guidage pour tir en rafale de missiles telecommandes
US4299360A (en) * 1979-01-30 1981-11-10 Martin Marietta Corporation Beamrider guidance technique using digital FM coding
US4424944A (en) * 1980-02-07 1984-01-10 Northrop Corporation Device to spatially encode a beam of light

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1958139A1 (de) * 1969-11-19 1971-05-27 Messerschmitt Boelkow Blohm Anordnung zur optischen Leitstrahllenkung von Flugzeugen und Flugkoerpern
FR2458044A1 (fr) * 1979-06-02 1980-12-26 Messerschmitt Boelkow Blohm Procede de defense contre les engins volants ou les missiles
GB2066431A (en) * 1979-12-22 1981-07-08 Diehl Gmbh & Co Optical remote-control means for a propectile
DE3341186A1 (de) * 1982-11-13 1984-06-28 British Aerospace Plc, London Strahlgefuehrtes lenksystem
DE3311349A1 (de) * 1983-03-29 1984-10-11 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Verfahren zur vermessung eines bewegten koerpers im raum

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2689644A1 (fr) * 1992-03-30 1993-10-08 Saint Louis Inst Dispositif de détection et mesure de l'écart de trajectoire d'un projectile.
NL1031288C2 (nl) * 2006-03-03 2007-09-04 Thales Nederland Bv Apparaat en werkwijze voor geleiding van een projectiel.
WO2007099150A1 (fr) * 2006-03-03 2007-09-07 Thales Nederland B.V. Appareil et procédé de guidage de projectile
US8173945B2 (en) 2006-03-03 2012-05-08 Thales Nederland B.V. Apparatus and method for guidance of a projectile
DE102013209052A1 (de) 2013-05-15 2014-11-20 Rheinmetall Air Defence Ag Vorrichtung zur Flugbahnkorrektur eines Geschosses

Also Published As

Publication number Publication date
DE3675926D1 (de) 1991-01-10
NO870062D0 (no) 1987-01-07
EP0234030B1 (fr) 1990-11-28
NO165814B (no) 1991-01-02
DK48287D0 (da) 1987-01-29
IL81417A0 (en) 1987-08-31
DK48287A (da) 1987-07-31
NO165814C (no) 1991-04-10
IL81417A (en) 1993-06-10
NO870062L (no) 1987-07-31
CA1264842A (fr) 1990-01-23
ES2019870B3 (es) 1991-07-16
US4709875A (en) 1987-12-01

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