US3398918A - Optical system for guiding a projectile - Google Patents

Optical system for guiding a projectile Download PDF

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Publication number
US3398918A
US3398918A US599139A US59913966A US3398918A US 3398918 A US3398918 A US 3398918A US 599139 A US599139 A US 599139A US 59913966 A US59913966 A US 59913966A US 3398918 A US3398918 A US 3398918A
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Prior art keywords
beams
projectile
guiding
optical
missile
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Expired - Lifetime
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US599139A
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English (en)
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Girault Pierre
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Thales SA
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CSF Compagnie Generale de Telegraphie sans Fil SA
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    • 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
    • F41G7/263—Means for producing guidance beams
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01S—DEVICES USING THE PROCESS OF LIGHT AMPLIFICATION BY STIMULATED EMISSION OF RADIATION [LASER] TO AMPLIFY OR GENERATE LIGHT; DEVICES USING STIMULATED EMISSION OF ELECTROMAGNETIC RADIATION IN WAVE RANGES OTHER THAN OPTICAL
    • H01S3/00—Lasers, i.e. devices using stimulated emission of electromagnetic radiation in the infrared, visible or ultraviolet wave range
    • H01S3/0007—Applications not otherwise provided for

Definitions

  • wmobJsuwo 5b m wnSSmG N E om f n 23 sq: m3 m; 03 Ill ll.
  • an optical beam-rider guidance system for guiding a missile from a launching base to a target, wherein said launching base comprises: sighting means having an optical axis for sighting said target; laser means generating a plurality of fan-shaped light beams crossing each other, means for deflecting said beams laterally of said axis and means for modulating said beams.
  • a missile for a system as above mentioned said missile comprising means for sensing the modulated energy carried by said beams, rudder means for controlling the trajectory of said missile and guidance means coupling said rudder means to said sensing means.
  • FIG. 1 shows a first embodiment of the guiding system according to the invention
  • FIG. 2 is a block diagram of the system of FIG. 1;
  • FIG. 3 is a second embodiment of the guiding system according to the invention.
  • FIG. 4 is a block diagram of the system of FIG. 3.
  • FIG. 1 shows an optional maser or laser 1 continuously or intermittently transmitting an only slightly divergent beam of light aligned parallel with the axis oz.
  • the radiated energy is preferably within the infrared band so that it is not visible. It may be produced by a ruby or a gas laser, according to whether a pulsed or continuous emission is required.
  • the beam coming from the source 1 passes through an optical modulator comprising a pair of Efihdflld Patented Aug. 27, 1958 crossed polarizers 2 and 3 between which is located an electrically birefringent medium 4 Under the action of a modulating voltage U applied by means of electrodes to the birefringent medium, the beam is intensity modulated without its very small divergence being thereby affected.
  • This amplitude modulated beam passes then through an optical anamorphotic device, consisting of a fixed cylindrical lens 5 and a mobile cylindrical lens 6,. These two lenses cooperate in substantially increasing the divergence of the beam in the plane of curvature of the lenses, without altering it in the plane normal thereto.
  • an optical anamorphotic device consisting of a fixed cylindrical lens 5 and a mobile cylindrical lens 6,.
  • the divergence a in the plane normal to the former is controlled by modifying, by means of a servo-motor 8 the distance between the lenses 5 and 6
  • the incidence of the axis oz relative to the spread or fan shaped beam thus obtained is controlled by pivoting the optical assembly 5 6,, by means of a servomotor 9,,.
  • the projectile 16 is represented near the line of sight oz which coincides with the axis of the launching device 13. According to the invention, the projectile pro ceeds inside a corridor, centred on the line of sight, and whose walls are formed by the beams 7 and by similar beams 7 7 and 7,, which intersect one another.
  • a programmer 11 which is started at the moment the missile is launched, works out the orders which actuate the servomotors 8,, and 9,, corresponding to each beam so that the beams form continuously around the projectile 10 during its progression towards the target, a closed outline of predetermined dimensions, for example, not exceeding those of the target.
  • the projectile 10 is self-guided in such a way that it remains inside the closed outline defined by the beams 7 7, 7, and 7 This is a sort of beam-riding guidance.
  • FIG. 2 shows the block diagram of the system of FIG. 1. It consists of two parts, one located at the luanching base and the other inside the missile 10.
  • the launching base comprises the laser 1 equipped with its supply source 12; the light beam produced thereby passes, after optical division, which may be achieved, for example, as shown in FIG. 3, through the optical modulators 4,, 4 4 and 4 which are respectively controlled by the modulating voltages U U U and U from the oscillators 14 14 14 and 14
  • the beams pass then through anamorphosers 6,, 6 6 and 6, which spread them out and make them converge under the control of a programmer 11 which depends on the launching system 13.
  • the missile comprises a detecting system consisting of a collector lens 15, a filter 16, centered on the optical frequency transmitted by the laser 1, and a photo-electric element 17.
  • the photo-electric element 17 is connected to a receiver 18, having four outputs a, b, c and d at which appear separately the detection signals originating from the beams 7 7 7 and 7,
  • These signals are applied as control signals to a known system 19 comprising a gyroscope and a computer which works out orders M and N for the correction of the trajectory. These orders actuate the rudders 23 and 24 by means of servo-motors 21 and 22.
  • the launching base projects into space the four beams 7 7 7 and 7, which differ from one another by their respective modulation frequencies f,,, f f and f
  • These beams are spread out and orientated according to the programme produced by the programmer 11 and surround completely the missile as a closed contour, centered on the line of sight.
  • the missile tends to deviate from this sight line, indicated by the axis oz in FIG. 1, it encroaches, for example, on the beam 7,, which acts then on the photoelectric element 17 and causes the appearance of an 3 output voltage at the output a of the receiver 18.
  • This voltage acts on the computer 19, associated to the gyroscope 20, and supplies piloting orders M and N, which actuate the rudders 23 and 24. As a consequence, the flight direction is corrected and the projectile moves away from the beam 7 while remaining inside the corridor.
  • the projectile is guided in a by all-or-nothing manner, since the change in the trajectory is effected by interception of one or two of the beams of light forming the lateral walls of a corridor.
  • this corridor could be partitioned into a plurality of further corridors by means of intermediate beams, in order to achieve a more gradual modification of the trajectory.
  • the invention provides a proportional guidance system by means of two beams sweeping the guiding volume in directions perpendicular to each other.
  • FIG. 3 shows a laser 1 emitting a beam with only slight divergence, which beam is divided into two by means of a reflecting device 25.
  • the two reflected beams propagate respectively through polarizers 2 and 2 the birefringent media 4,, and 4 and the polarizers 3,, and 3 which cooperate so as to modulate the light intensity of the beams by means of modulating voltages U and U
  • the modulated beams are then reflected by vibrating mirrors 26,,, 26 actuated, respectively, by servo-motors 27 and 27
  • the beams reflected by the vibrating mirrors are rendered anamorphous by means of optical devices comprising, respectively, the fixed cylindrical lenses 5 and 5 and the movable cylindrical lenses 6,, and 6
  • Two beams 7 and 7 at right angles to each other and very flat, are then obtained as shown in FIG. 3.
  • the beam 7 performs a sweeping along the axis 0 and the beam 7 sweeps along the axis 0x.
  • FIG. 4 shows a block diagram of the guiding system of FIG. 3.
  • the beam emitted by the light source 1 is divided optically, by means of an optical device 25 into two beams, which pass, respectively, through the optical modulators 4,, and 4
  • These beams are respectively amplitude modulated by means of the voltage generators 29 and 29,, which are in turn frequency modulated within distinct frequency hands by a sweep generator 28.
  • Bandpass filters 31 and 31 are provided on board the projectile for separating the signals in accordance with the modulation they undergo. From the modulators 4,, and 4 the modulated beams pass through optical anamorphous devices 6,, and 6 and pass through the deviators 27 27 respectively whereby the beams perform a sweep in synchronism with the sweep signal produced by the generator 28.
  • the sweep of the beams and the amplitude of the sweep are also controlled by a programmer 11 controlled by the launching device 13.
  • the projectile On board the projectile is a collector lens 15, a filter 16 centered on the emission optical frequency of the source 1 and a photo-electric element 17 which feeds an amplifier 30.
  • the output of the amplifier 30 is connected to separating filters 31 and 31 mentioned above, which respectively feed the frequency discriminators 32 and 32
  • the position information supplied by the discriminators 32 and 32 is applied simultaneously to two computers 19 and 19,, which, by means of angular information, supplied by the gyroscope 20, work out the orders M and N for guiding the projectile.
  • the orders M and N are applied to servo-motors 21 and 22 which actuate the rudders 23 and 24.
  • the source 1 transmits a beam of light, divided into two parts which pass, respectively, through the modulators 4 and 4 to which are respectively applied two modulating voltages which are frequency modulated with different frequency bands voltages.
  • the modulation frequencies are connected with the voltage supplied by the generator 28, since the same controls the oscillators 29 and 29
  • This voltage is also applied to the deviators 27 and 27 which cause the beams issuing from the modulators 4 and 4 to perform a sweeping along the planes yoz and xoz respectively.
  • These angular sweeps are synchronized with the frequency excursion of the generators 29 and 29 so that each orientation of a beam corresponds to a certain value of the optical modulation frequency.
  • the beams available at the output of the deviators 27 and 27, are rendered anamorphous by the anamorphotic devices 6 and 6 which emit the flattened beams 7 and 7,, into space.
  • a programmer 11 controls the anamorphotic devices 6,, and 6 and the deviators 27 and 27 so as to adjust the spreading out of the beams and the amplitude of the sweep as a function of the distance through which the projectile 10 has travelled. This control is assured from the moment of launching which is determined by the launcher 13.
  • the projectile flying inside the pyramid shaped volume centred on the line of sight is swept by the two beams 7 and 7
  • Its detection system receives each time the missile is swept by the beams 7 and 7 a pair of luminous information signals which have instantaneous frequencies which determine the position of the projectile transversally relative to the line of sight oz.
  • the information items are translated by the photo-electric cell 17 and the amplifier 30 into electrical signals which are decoupled by means of filters 31 and 31
  • the AC. voltages at the outputs of the filters are then applied to the discriminators 32 and 32;, which supply, respectively, the trajectory deviations E and E as shown in FIG. 3.
  • a sweep frequency of the beams of the order of 20 c./s. and an amplitude of 2.5 in. measured at a distance of 200 m. from the launching base may be provided.
  • the minimum aperture of the light beams is of the order of milliradians.
  • Frequency modulation bands used are centred at about 20 and 30 kc./s., respectively, with a frequency excursion of 10 percent. Under these conditions the power of the laser source must be 3 milliwatt to obtain a signal-to-noise ratio of more than 12 db.
  • an optical filter 16 is used, which is centred on the transmission frequency of the source 1. This filter makes it possible to eliminate in a substantial manner disturbances caused by ambient light.
  • a gyroscope may be used as inertial guiding system.
  • the inertia axis of the gyroscope supplies the angular information for taking into account the rotation of the projectile about itself.
  • the computers which issue the piloting orders comprise, by way of example, sine-cosine potentiometers supplied by the detection signals in the case of a frequency modulation following a sinusoidal law.
  • the beams can be differentiated from each other by means of a modulation other than the frequency modulation.
  • the light energy may be pulse modulated to form trains of pulses of variable width wherein this width is a function of the instantaneous position of the beam in the space.
  • An optical beam-rider guidance system for guiding a missile from a launching base to a target, wherein said launching base comprises: sighting means having an optical axis for sighting said target; laser means generating a plurality of fan-shaped light beams crossing each other, means for deflecting said beams laterally of said axis and means for modulating said beams.
  • a missile for a system as claimed in claim 1 said missile comprising means for sensing the modulated energy carried by said beams, rudder means for controlling the trajectory of said missile and guidance means coupling said rudder means to said sensing means.
  • sensing means comprise photoelectric transducer means, means for focusing on said transducer means the light energy of said beams and, associated with said focusing means optical filtering means rejecting the radiations having a wavelength ditferent from the wavelength of said laser means.
  • said launching device further comprises means for actuating said deflecting means according to a predetermined program starting from the instant of the launching.
  • said generating means comprise at least one laser source radiating a beam of light having a small divergence and anamorphotic means for spreading said beam in a transverse direction to form a fan-shaped beam.
  • said fan shaped beam generating means includes control means for causing said fan-shaped beams to build up substantially the lateral faces of a pyramid having a symmetry axis aligned on said optical axis, said pyramid having a base smaller than the area of said target.
  • modulation means comprise a plurality of oscillators having distinct oscillation frequencies.
  • a missile for a system as claimed in claim 8 wherein said guidance means comprise a plurality of band pass filters coupled to said transducer means and respectively tuned to said frequencies, means for detecting said modulation signals at the respective outputs of said filters, computer means having first inputs coupled to said detecting means, second inputs and outputs; said second inputs being coupled to gyroscopic means and said outputs of said computer means being coupled to said rudder means.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Plasma & Fusion (AREA)
  • General Engineering & Computer Science (AREA)
  • Optics & Photonics (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Optical Radar Systems And Details Thereof (AREA)
  • Optical Communication System (AREA)
US599139A 1965-12-06 1966-12-05 Optical system for guiding a projectile Expired - Lifetime US3398918A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR41068A FR1466437A (fr) 1965-12-06 1965-12-06 Système optique de guidage d'un projectile

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DE (1) DE1481990B2 (nl)
FR (1) FR1466437A (nl)
GB (1) GB1177950A (nl)
NL (1) NL160081C (nl)

Cited By (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3614025A (en) * 1967-07-19 1971-10-19 Comp Generale Electricite Machine guiding system
US3782667A (en) * 1972-07-25 1974-01-01 Us Army Beamrider missile guidance method
US3796396A (en) * 1971-10-29 1974-03-12 C Crovella Method and apparatus for modulating a pyrotechnic tracer
US3912197A (en) * 1973-11-27 1975-10-14 Us Army Laser-guided ring airfoil projectile
FR2274887A1 (fr) * 1974-08-28 1976-01-09 Bofors Ab Appareil de regulation de la puissance d'un faisceau dit de guidage optique
DE2636926A1 (de) * 1975-09-04 1977-03-17 Hughes Aircraft Co Verfahren und vorrichtung zur bestimmung von quer zu einem strahl elektromagnetischer energie gelegenen orten
US4103260A (en) * 1977-01-03 1978-07-25 Hughes Aircraft Company Spatial polarization coding electro-optical transmitter
US4111383A (en) * 1976-04-16 1978-09-05 Texas Instruments Incorporated Laser beam transmitter system for laser beam rider guidance systems
US4111384A (en) * 1976-04-16 1978-09-05 Texas Instruments Incorporated Scanner system for laser beam rider guidance systems
US4111385A (en) * 1976-04-16 1978-09-05 Texas Instruments Incorporated Laser beam rider guidance system
EP0002576A1 (en) * 1977-12-12 1979-06-27 FORD AEROSPACE & COMMUNICATIONS CORPORATION Projector for projecting electromagnetic control signals
US4174818A (en) * 1976-01-29 1979-11-20 Elliott Brothers (London) Limited Guidance systems for mobile craft
US4189116A (en) * 1977-10-05 1980-02-19 Rockwell International Corporation Navigation system
US4215324A (en) * 1978-08-01 1980-07-29 Hughes Aircraft Company Spatial encoding of a laser beam by means of a Stark cell modulator
US4231533A (en) * 1975-07-09 1980-11-04 The United States Of America As Represented By The Secretary Of The Air Force Static self-contained laser seeker system for active missile guidance
US4234141A (en) * 1970-03-10 1980-11-18 The United States Of America As Represented By The Secretary Of The Army Range gated retroreflective missile guidance system
US4245800A (en) * 1978-06-22 1981-01-20 Hughes Aircraft Company Spatial coding of laser beams by optically biasing electro-optic modulators
US4299360A (en) * 1979-01-30 1981-11-10 Martin Marietta Corporation Beamrider guidance technique using digital FM coding
US4318591A (en) * 1980-06-10 1982-03-09 Ford Aerospace & Communications Corp. Polarization switched image rotator
US4406430A (en) * 1979-12-22 1983-09-27 Diehl Gmbh & Co. Optical remote control arrangement for a projectile
US4441669A (en) * 1981-05-05 1984-04-10 Diehl Gmbh & Co. Apparatus for the production of a guide pattern of light beams
FR2539864A1 (fr) * 1983-01-20 1984-07-27 Telecommunications Sa Systeme de guidage d'engin par faisceau lumineux
DE3511077A1 (de) * 1985-03-27 1986-10-02 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Verfahren und einrichtung zur erzeugung eines abgelenkten lichtstrahles
US4659228A (en) * 1981-11-12 1987-04-21 Canon Kabushiki Kaisha Aligning apparatus
US4709875A (en) * 1986-01-30 1987-12-01 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Apparatus for guiding a missile
US4967979A (en) * 1973-09-21 1990-11-06 The United States Of America As Represented By The Secretary Of The Navy Command guidance technique for line-of-sight missile
US5348249A (en) * 1993-01-11 1994-09-20 Hughes Missile Systems Company Retro reflection guidance and control apparatus and method
US5533692A (en) * 1979-01-30 1996-07-09 Oerlikon-Contraves Ag Beamrider guidance system using digital phase modulation encoding
US6014270A (en) * 1998-11-23 2000-01-11 Lucent Technologies Inc Cylindrical lenses for alignment of optical sources and destinations
WO2005050279A1 (en) * 2003-10-28 2005-06-02 Raytheon Company System containing an anamorphic optical system with window, optical corrector, and sensor
US20060098710A1 (en) * 2003-07-03 2006-05-11 Optris Gmbh Sighting device and additional device for measuring, working, and/or operating with or without contact
JP2007524073A (ja) * 2003-07-03 2007-08-23 オプトリス ゲーエムベーハー 照準装置及び非接触で又は接触させて使用可能な測定装置
US20070290096A1 (en) * 2005-10-13 2007-12-20 Jenkins David G Methods and apparatus for guidance systems
US20100290038A1 (en) * 2009-05-13 2010-11-18 Bae Systems Information And Electronic Systems Integration Inc. Distributed array semi-active laser designator sensor
US9279651B1 (en) * 2014-09-09 2016-03-08 Marshall Phillip Goldberg Laser-guided projectile system
CN105716471A (zh) * 2014-12-02 2016-06-29 哈尔滨新光光电科技有限公司 一种采用电磁吸附反射镜模拟目标抖动的方法
US10677565B2 (en) * 2014-12-18 2020-06-09 Israel Aerospace Industries Ltd. Guidance system and method

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4020339A (en) * 1975-05-19 1977-04-26 Aktiebolaget Bofars System for determining the deviation of an object from a sight line
NL7506079A (nl) * 1975-05-23 1976-11-25 Bofors Ab Inrichting voor het in een bundel uitzenden van straling.
GB2113939B (en) * 1981-11-19 1985-07-10 British Aerospace Angular position determination
DE4416211C2 (de) * 1994-05-07 1996-09-26 Rheinmetall Ind Gmbh Verfahren und Vorrichtung zur Flugbahnkorrektur von Geschossen

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GB441866A (en) * 1934-07-25 1936-01-27 Nicholas Sandor Improvements in and connected with the control of the flight of projectiles
US2930894A (en) * 1954-07-13 1960-03-29 Republic Aviat Corp Optical sighting and tracking device
US2950474A (en) * 1949-10-27 1960-08-23 Robert M Page Missile guiding system
US2994270A (en) * 1942-01-08 1961-08-01 Maury I Hull Anti-aircraft defense systems
US3028807A (en) * 1959-08-24 1962-04-10 Mcdonnell Aircraft Corp Guidance system
DE1168513B (de) * 1958-12-16 1964-04-23 Boelkow Entwicklungen Kg Verfahren zur Stabilisierung und Lenkung eines Flugkoerpers mit Hilfe hochfrequenter elektrischer Schwingungen
US3255984A (en) * 1963-06-13 1966-06-14 Sanders Associates Inc Beam riding guidance system
US3277396A (en) * 1962-04-23 1966-10-04 Raytheon Co Means for modulating a laser
US3297876A (en) * 1963-04-16 1967-01-10 United Aircraft Corp Amplitude modulation for lasers

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Publication number Priority date Publication date Assignee Title
GB441866A (en) * 1934-07-25 1936-01-27 Nicholas Sandor Improvements in and connected with the control of the flight of projectiles
US2994270A (en) * 1942-01-08 1961-08-01 Maury I Hull Anti-aircraft defense systems
US2950474A (en) * 1949-10-27 1960-08-23 Robert M Page Missile guiding system
US2930894A (en) * 1954-07-13 1960-03-29 Republic Aviat Corp Optical sighting and tracking device
DE1168513B (de) * 1958-12-16 1964-04-23 Boelkow Entwicklungen Kg Verfahren zur Stabilisierung und Lenkung eines Flugkoerpers mit Hilfe hochfrequenter elektrischer Schwingungen
US3028807A (en) * 1959-08-24 1962-04-10 Mcdonnell Aircraft Corp Guidance system
US3277396A (en) * 1962-04-23 1966-10-04 Raytheon Co Means for modulating a laser
US3297876A (en) * 1963-04-16 1967-01-10 United Aircraft Corp Amplitude modulation for lasers
US3255984A (en) * 1963-06-13 1966-06-14 Sanders Associates Inc Beam riding guidance system

Cited By (45)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3614025A (en) * 1967-07-19 1971-10-19 Comp Generale Electricite Machine guiding system
US4234141A (en) * 1970-03-10 1980-11-18 The United States Of America As Represented By The Secretary Of The Army Range gated retroreflective missile guidance system
US3796396A (en) * 1971-10-29 1974-03-12 C Crovella Method and apparatus for modulating a pyrotechnic tracer
US3782667A (en) * 1972-07-25 1974-01-01 Us Army Beamrider missile guidance method
US4967979A (en) * 1973-09-21 1990-11-06 The United States Of America As Represented By The Secretary Of The Navy Command guidance technique for line-of-sight missile
US3912197A (en) * 1973-11-27 1975-10-14 Us Army Laser-guided ring airfoil projectile
FR2274887A1 (fr) * 1974-08-28 1976-01-09 Bofors Ab Appareil de regulation de la puissance d'un faisceau dit de guidage optique
US4231533A (en) * 1975-07-09 1980-11-04 The United States Of America As Represented By The Secretary Of The Air Force Static self-contained laser seeker system for active missile guidance
DE2636926A1 (de) * 1975-09-04 1977-03-17 Hughes Aircraft Co Verfahren und vorrichtung zur bestimmung von quer zu einem strahl elektromagnetischer energie gelegenen orten
US4030686A (en) * 1975-09-04 1977-06-21 Hughes Aircraft Company Position determining systems
US4174818A (en) * 1976-01-29 1979-11-20 Elliott Brothers (London) Limited Guidance systems for mobile craft
US4111384A (en) * 1976-04-16 1978-09-05 Texas Instruments Incorporated Scanner system for laser beam rider guidance systems
US4111385A (en) * 1976-04-16 1978-09-05 Texas Instruments Incorporated Laser beam rider guidance system
US4111383A (en) * 1976-04-16 1978-09-05 Texas Instruments Incorporated Laser beam transmitter system for laser beam rider guidance systems
US4103260A (en) * 1977-01-03 1978-07-25 Hughes Aircraft Company Spatial polarization coding electro-optical transmitter
US4189116A (en) * 1977-10-05 1980-02-19 Rockwell International Corporation Navigation system
EP0002576A1 (en) * 1977-12-12 1979-06-27 FORD AEROSPACE & COMMUNICATIONS CORPORATION Projector for projecting electromagnetic control signals
US4186899A (en) * 1977-12-12 1980-02-05 Ford Motor Company Controlled beam projector
US4245800A (en) * 1978-06-22 1981-01-20 Hughes Aircraft Company Spatial coding of laser beams by optically biasing electro-optic modulators
US4215324A (en) * 1978-08-01 1980-07-29 Hughes Aircraft Company Spatial encoding of a laser beam by means of a Stark cell modulator
US4299360A (en) * 1979-01-30 1981-11-10 Martin Marietta Corporation Beamrider guidance technique using digital FM coding
US5533692A (en) * 1979-01-30 1996-07-09 Oerlikon-Contraves Ag Beamrider guidance system using digital phase modulation encoding
US4406430A (en) * 1979-12-22 1983-09-27 Diehl Gmbh & Co. Optical remote control arrangement for a projectile
US4318591A (en) * 1980-06-10 1982-03-09 Ford Aerospace & Communications Corp. Polarization switched image rotator
US4441669A (en) * 1981-05-05 1984-04-10 Diehl Gmbh & Co. Apparatus for the production of a guide pattern of light beams
US4659228A (en) * 1981-11-12 1987-04-21 Canon Kabushiki Kaisha Aligning apparatus
US4565339A (en) * 1983-01-20 1986-01-21 Societe Anonyme De Telecommunications System for guiding a missile by a flat light pencil beam
FR2539864A1 (fr) * 1983-01-20 1984-07-27 Telecommunications Sa Systeme de guidage d'engin par faisceau lumineux
DE3511077A1 (de) * 1985-03-27 1986-10-02 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Verfahren und einrichtung zur erzeugung eines abgelenkten lichtstrahles
US4709875A (en) * 1986-01-30 1987-12-01 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Apparatus for guiding a missile
US5348249A (en) * 1993-01-11 1994-09-20 Hughes Missile Systems Company Retro reflection guidance and control apparatus and method
US6014270A (en) * 1998-11-23 2000-01-11 Lucent Technologies Inc Cylindrical lenses for alignment of optical sources and destinations
JP4690316B2 (ja) * 2003-07-03 2011-06-01 オプトリス ゲーエムベーハー 照準装置及び非接触で又は接触させて使用可能な測定装置
US20060098710A1 (en) * 2003-07-03 2006-05-11 Optris Gmbh Sighting device and additional device for measuring, working, and/or operating with or without contact
JP2007524073A (ja) * 2003-07-03 2007-08-23 オプトリス ゲーエムベーハー 照準装置及び非接触で又は接触させて使用可能な測定装置
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Also Published As

Publication number Publication date
GB1177950A (en) 1970-01-14
NL160081B (nl) 1979-04-17
DE1481990B2 (de) 1977-05-18
NL6617149A (nl) 1967-06-07
NL160081C (nl) 1979-09-17
FR1466437A (fr) 1967-01-20
DE1481990A1 (de) 1969-05-29

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