EP1072858A1 - Method and apparatus for guiding a missile towards a target by means of laser scanning - Google Patents

Method and apparatus for guiding a missile towards a target by means of laser scanning Download PDF

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Publication number
EP1072858A1
EP1072858A1 EP00402039A EP00402039A EP1072858A1 EP 1072858 A1 EP1072858 A1 EP 1072858A1 EP 00402039 A EP00402039 A EP 00402039A EP 00402039 A EP00402039 A EP 00402039A EP 1072858 A1 EP1072858 A1 EP 1072858A1
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EP
European Patent Office
Prior art keywords
missile
field
scanning
laser
laser beam
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Granted
Application number
EP00402039A
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German (de)
French (fr)
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EP1072858B1 (en
Inventor
Maurice Adda
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Aerospatiale Matra Missiles SA
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Aerospatiale Matra Missiles SA
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Publication of EP1072858A1 publication Critical patent/EP1072858A1/en
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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
    • F41G7/30—Command link guidance systems
    • F41G7/301—Details
    • F41G7/303—Sighting or tracking devices especially provided for simultaneous observation of the target and of the missile

Definitions

  • the present invention relates to a method and a device for laser scanning guidance from a missile to a target.
  • the invention applies more particularly guiding a missile from a firing station, including the laser beam projector, an optical receiver being on board said missile.
  • the laser beam projector emits a radial scanning pattern, intended to cover the entire guidance field of the missile. It is associated with a direct optical channel (or any other optical channel televisual or thermal observation).
  • This procedure has the drawback, the laser beam scanning the whole field, that said beam is likely to be then detected, and the shooting post possibly destroyed by the opponent.
  • the object of the invention is to reduce the possibility of detecting the laser beam.
  • the method of laser scanning guidance of a missile towards a target, according to which a field is observed, in which is susceptible to evolve said missile, to locate the latter in said field is remarkable, according to the invention, in that, in said field, it is determined an area around the instantaneous position of said missile thus located, and in that the laser scanning is carried out only in said zone.
  • the probability of detection of the laser beam is reduced by function of the reduction of the "surface” swept by said beam.
  • scanning continues to be performed throughout the field, essentially with the laser beam off, the latter being on, and therefore possibly identifiable, only in the determined area (significantly reduced compared to said field) around the instantaneous position of the missile, and the extent of which will depend on different parameters, variables depending on the missile's firing conditions.
  • said means for activating the laser beam are means for igniting said beam in phase with the means for scanning of said field, so as to make the ignition of said beam coincide with the scanning of said area.
  • the reduction in detectability of the laser beam is thus obtained by switching on the laser so as to cover only the part of the guidance field in which the missile is located.
  • said observation means comprise a video camera, a semi-transparent blade which can then be inserted in the optical path between the viewfinder and the camera.
  • a monitor allows the visualization of said area in said field.
  • a switch allows switching from laser scanning from said area to scanning of said field, on operator's order, this in order to locate the missile again in case it comes out of said zoned.
  • Figure 1 is a block diagram of an exemplary embodiment of the laser scanning guidance device of a missile towards a target according to the invention.
  • Figure 2 shows the field of observation in which is defined an area around the missile.
  • FIGS 3 to 5 illustrate different means of imaging said device of the invention.
  • the activation means 10 are connected to the generator of the laser beam 3 via a link 12, and the scanning means 6 aux determination means 7 by a link 13.
  • the activation means 10 of the laser beam 2 are means for igniting said beam (via the link 12) in phase with the scanning means 6 of the field 5, so as to coincide (via link 13) switching on the beam with the scanning of zone 8.
  • the laser is switched on and off in phase with the scanning of the beam so as to make the laser ignition coincide when the beam scans the "position" (in the broad sense of "area", as used previously) of the missile.
  • the firing station detects the position of the missile in the guiding field by a video repeat, coupled to a box of image processing (generally designated by the numerical reference 7 on Figure 1).
  • this optical structure can be supplemented by a micromonitor 17 in order to allow the visualization of the lighting window (or zone 8).
  • This optical organization allows obtain, over the scene (field 5), a visualization of the missile guidance window (zone 8). It is thus possible to envisage, in the event that the “missile location” would lose the missile (the latter then being outside the window) to send to the means of location 7 (on operator's order) a return command (symbolized by entry 19 in Figure 1) of the full scan of the field 5 by the laser beam allowing to "hang” again the missile.

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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)
  • Optical Radar Systems And Details Thereof (AREA)

Abstract

The method of guiding a missile (M) to its target (T) involves using an observation field (5) in which the missile is guided. A missile guidance zone (8) is defined to localize the laser guidance area. The illumination of the laser beam coincides with the guidance zone. An Independent claim is included for a guidance system using the above method.

Description

La présente invention concerne un procédé et un dispositif de guidage à balayage laser d'un missile vers une cible.The present invention relates to a method and a device for laser scanning guidance from a missile to a target.

Quoique non exclusivement, l'invention s'applique plus particulièrement au guidage d'un missile à partir d'un poste de tir, comportant le projecteur de faisceau laser, un récepteur optique étant embarqué sur ledit missile.Although not exclusively, the invention applies more particularly guiding a missile from a firing station, including the laser beam projector, an optical receiver being on board said missile.

Le projecteur de faisceau laser émet une figure de balayage radiale, destinée à couvrir l'ensemble du champ de guidage du missile. Il est associé à une voie directe optique (ou tout autre canal optique d'observation télévisuelle ou thermique).The laser beam projector emits a radial scanning pattern, intended to cover the entire guidance field of the missile. It is associated with a direct optical channel (or any other optical channel televisual or thermal observation).

Cette façon de faire présente l'inconvénient, le faisceau laser balayant l'ensemble du champ, que ledit faisceau est susceptible d'être alors détecté, et le poste de tir éventuellement détruit par l'adversaire.This procedure has the drawback, the laser beam scanning the whole field, that said beam is likely to be then detected, and the shooting post possibly destroyed by the opponent.

L'invention a pour but de réduire l'éventualité de détection du faisceau laser.The object of the invention is to reduce the possibility of detecting the laser beam.

A cet effet, le procédé de guidage à balayage laser d'un missile vers une cible, selon lequel on observe un champ, dans lequel est susceptible d'évoluer ledit missile, pour localiser ce dernier dans ledit champ, est remarquable, selon l'invention, en ce que, dans ledit champ, on détermine une zone autour de la position instantanée dudit missile ainsi localisé, et en ce qu'on effectue le balayage laser uniquement dans ladite zone.For this purpose, the method of laser scanning guidance of a missile towards a target, according to which a field is observed, in which is susceptible to evolve said missile, to locate the latter in said field, is remarkable, according to the invention, in that, in said field, it is determined an area around the instantaneous position of said missile thus located, and in that the laser scanning is carried out only in said zone.

Ainsi, la probabilité de détection du faisceau laser est réduite en fonction de la réduction de la « surface » balayée par ledit faisceau.Thus, the probability of detection of the laser beam is reduced by function of the reduction of the "surface" swept by said beam.

Bien que l'on puisse envisager de ne plus balayer que ladite zone (laser allumé) en excluant le reste du champ, il est avantageux (essentiellement pour des raisons pratiques d'adaptation des systèmes existants) que, le balayage proprement dit étant effectué dans tout ledit champ, l'allumage dudit faisceau laser coïncide avec le balayage de ladite zone.Although it can be envisaged to scan only said area (laser on) excluding the rest of the field, it is advantageous (essentially for practical reasons of adaptation of existing systems) that, the actual scanning being carried out throughout said field, the ignition of said laser beam coincides with the scanning of said zoned.

Dans ce cas, le « balayage » continue à être effectué dans tout le champ, pour l'essentiel avec le faisceau laser éteint, ce dernier n'étant allumé, et donc éventuellement repérable, que dans la zone déterminée (notablement réduite par rapport audit champ) autour de la position instantanée du missile, et dont l'étendue dépendra de différents paramètres, variables en fonction des conditions de tir du missile.In this case, "scanning" continues to be performed throughout the field, essentially with the laser beam off, the latter being on, and therefore possibly identifiable, only in the determined area (significantly reduced compared to said field) around the instantaneous position of the missile, and the extent of which will depend on different parameters, variables depending on the missile's firing conditions.

Pour la mise en oeuvre du procédé ci-dessus, l'invention concerne également un dispositif de guidage à balayage laser d'un missile vers une cible comportant :

  • des moyens d'émission d'un faisceau laser destiné à transmettre des ordres de pilotage audit missile,
  • des moyens d'observation d'un champ, dans lequel est susceptible d'évoluer ledit missile, pour localiser ce dernier dans ledit champ, et
  • des moyens de balayage dudit champ par ledit faisceau laser, reliés auxdits moyens d'émission,
remarquable selon l'invention, par :
  • des moyens pour définir une zone autour de la position instantanée dudit missile dans ledit champ, reliés auxdits moyens d'observation, et
  • des moyens d'activation dudit faisceau laser dans ladite zone, reliés auxdits moyens définissant ladite zone.
For the implementation of the above method, the invention also relates to a device for laser scanning guidance of a missile towards a target comprising:
  • means for emitting a laser beam intended to transmit piloting orders to said missile,
  • means for observing a field, in which said missile is capable of evolving, for locating the latter in said field, and
  • means for scanning said field by said laser beam, connected to said emission means,
remarkable according to the invention, by:
  • means for defining an area around the instantaneous position of said missile in said field, connected to said observation means, and
  • means for activating said laser beam in said zone, connected to said means defining said zone.

Avantageusement, lesdits moyens d'activation du faisceau laser sont des moyens d'allumage dudit faisceau en phase avec les moyens de balayage dudit champ, de manière à faire coïncider l'allumage dudit faisceau avec le balayage de ladite zone. Advantageously, said means for activating the laser beam are means for igniting said beam in phase with the means for scanning of said field, so as to make the ignition of said beam coincide with the scanning of said area.

Plus particulièrement, la réduction de détectabilité du faisceau laser est ainsi obtenue par allumage du laser de manière à ne couvrir que la partie du champ de guidage dans laquelle se trouve le missile.More specifically, the reduction in detectability of the laser beam is thus obtained by switching on the laser so as to cover only the part of the guidance field in which the missile is located.

Avantageusement, lesdits moyens d'observation comprennent une caméra vidéo, une lame semi-transparente pouvant être alors intercalée dans le chemin optique entre le viseur et la caméra.Advantageously, said observation means comprise a video camera, a semi-transparent blade which can then be inserted in the optical path between the viewfinder and the camera.

De préférence, un moniteur permet la visualisation de ladite zone dans ledit champ.Preferably, a monitor allows the visualization of said area in said field.

Soit ledit moniteur partage, avec ladite caméra, la même lame semi-transparente intercalée dans ledit chemin optique, soit ladite caméra et ledit moniteur sont décalés, et sont associés, chacun, à une lame semi-transparente propre.Either said monitor shares, with said camera, the same blade semi-transparent inserted in said optical path, ie said camera and said monitor are offset, and are each associated with a semi-transparent blade clean.

De préférence, un commutateur permet de passer du balayage laser de ladite zone au balayage dudit champ, sur ordre de l'opérateur, cela afin de localiser à nouveau le missile au cas où celui-ci sortirait de ladite zone.Preferably a switch allows switching from laser scanning from said area to scanning of said field, on operator's order, this in order to locate the missile again in case it comes out of said zoned.

Les figures du dessin annexé feront bien comprendre comment l'invention peut être réalisée. Sur ces figures, des références identiques désignent des éléments semblables.The figures in the accompanying drawing will make it clear how the invention can be realized. In these figures, identical references denote similar elements.

La figure 1 est un schéma synoptique d'un exemple de réalisation du dispositif de guidage à balayage laser d'un missile vers une cible selon l'invention.Figure 1 is a block diagram of an exemplary embodiment of the laser scanning guidance device of a missile towards a target according to the invention.

La figure 2 montre le champ d'observation dans lequel est définie une zone autour du missile.Figure 2 shows the field of observation in which is defined an area around the missile.

Les figures 3 à 5 illustrent différents moyens d'imagerie dudit dispositif de l'invention.Figures 3 to 5 illustrate different means of imaging said device of the invention.

Il est représenté, sur la figure 1, un exemple de réalisation du dispositif 1 de guidage à balayage laser d'un missile M vers une cible T (figure 2). There is shown, in Figure 1, an embodiment of the device 1 of laser scanning guidance from a missile M to a target T (figure 2).

Le dispositif 1 comprend :

  • des moyens d'émission d'un faisceau laser 2 destiné à transmettre des ordres de pilotage au missile M, comprenant un générateur de faisceau laser 3,
  • des moyens d'observation 4 (notamment une caméra vidéo, à effet thermique, ou autre) d'un champ 5 (figure 2), également symbolisé par la flèche 5A sur la figure 1 (image reçue par la caméra), dans lequel est susceptible d'évoluer le missile M, pour localiser ce dernier dans le champ 5, et
  • des moyens de balayage 6, comportant un miroir fixe 6A et un miroir mobile 6B, du champ 5 par le faisceau laser 2, reliés au générateur 3.
The device 1 includes:
  • means for emitting a laser beam 2 intended to transmit piloting orders to the missile M, comprising a laser beam generator 3,
  • observation means 4 (in particular a video camera, with thermal effect, or other) of a field 5 (FIG. 2), also symbolized by the arrow 5A in FIG. 1 (image received by the camera), in which is likely to evolve missile M, to locate it in field 5, and
  • scanning means 6, comprising a fixed mirror 6A and a movable mirror 6B, of the field 5 by the laser beam 2, connected to the generator 3.

Plus particulièrement, selon l'invention, le dispositif 1 comprend en outre :

  • des moyens 7 pour définir une zone 8 (figure 2) autour de la position instantanée du missile M dans le champ 5, reliés aux moyens d'observation 4 par une liaison 9, et
  • des moyens d'activation 10 du faisceau laser 2 dans la zone 8, reliés aux moyens 7 définissant la zone 8 par une liaison 11.
More particularly, according to the invention, the device 1 further comprises:
  • means 7 for defining an area 8 (FIG. 2) around the instantaneous position of the missile M in the field 5, connected to the observation means 4 by a link 9, and
  • means 10 for activating the laser beam 2 in the zone 8, connected to the means 7 defining the zone 8 by a link 11.

Par ailleurs, les moyens d'activation 10 sont reliés au générateur du faisceau laser 3 par une liaison 12, et les moyens de balayage 6 aux moyens de détermination 7 par une liaison 13.Furthermore, the activation means 10 are connected to the generator of the laser beam 3 via a link 12, and the scanning means 6 aux determination means 7 by a link 13.

Dans cet exemple, les moyens d'activation 10 du faisceau laser 2 sont des moyens d'allumage dudit faisceau (via la liaison 12) en phase avec les moyens de balayage 6 du champ 5, de manière à faire coïncider (via la liaison 13) l'allumage du faisceau avec le balayage de la zone 8.In this example, the activation means 10 of the laser beam 2 are means for igniting said beam (via the link 12) in phase with the scanning means 6 of the field 5, so as to coincide (via link 13) switching on the beam with the scanning of zone 8.

On réduit ainsi l'intégralité du balayage radial (suivant les axes Y-Y ; Z-Z, en supposant l'axe X-X celui « reliant» le poste de tir à la cible) à la seule partie (zone 8) du champ 5 de guidage dans laquelle se trouve le missile M. This reduces the entire radial scan (along the axes Y-Y ; Z-Z, assuming the X-X axis that "connecting" the shooting station to the target) to the only part (zone 8) of guide field 5 in which is located the missile M.

A cet effet, on allume et on éteint le laser en phase avec le balayage du faisceau de manière à faire coïncider l'allumage du laser lorsque le faisceau balaie la « position » (au sens large de « zone », comme utilisé précédemment) du missile. Le poste de tir détecte la position du missile dans le champ de guidage par une reprise vidéo, couplée à un boítier de traitement d'image (globalement désigné par la référence numérique 7 sur la figure 1).For this purpose, the laser is switched on and off in phase with the scanning of the beam so as to make the laser ignition coincide when the beam scans the "position" (in the broad sense of "area", as used previously) of the missile. The firing station detects the position of the missile in the guiding field by a video repeat, coupled to a box of image processing (generally designated by the numerical reference 7 on Figure 1).

Dans le cas d'un poste de tir ne comportant qu'une voie optique directe (viseur 14 sur les figures 3 à 5, la référence numérique 15 désignant l'oeil de l'observateur), l'ajout d'une caméra 4 de reprise d'image est nécessaire, en intercalant de plus dans le chemin optique une lame semi-transparente 16 (figure 3).In the case of a shooting station comprising only one optical channel direct (viewfinder 14 in FIGS. 3 to 5, the reference numeral 15 designating the observer's eye), the addition of a camera 4 for image capture is necessary, by further inserting in the optical path a blade semi-transparent 16 (Figure 3).

Comme on le voit sur la figure 4, cette structure optique peut être complétée par un micromoniteur 17 afin de permettre la visualisation de la fenêtre (ou zone 8) d'éclairage.As seen in Figure 4, this optical structure can be supplemented by a micromonitor 17 in order to allow the visualization of the lighting window (or zone 8).

La figure 4 est un schéma de principe dans lequel la lame semi-transparente 16 permet :

  • la double observation de la scène par l'oeil 15 de l'observateur et par la caméra 4,
  • la double observation, par l'oeil 15, de la scène et de l'image du micromoniteur 17.
FIG. 4 is a block diagram in which the semi-transparent blade 16 allows:
  • double observation of the scene by the eye 15 of the observer and by the camera 4,
  • the double observation, by the eye 15, of the scene and the image of the micromonitor 17.

Toutefois, l'observation parasite du micromoniteur 17 par la caméra 4 n'est pas exclue dans un tel schéma. Il peut être avantageusement remplacé par un schéma (figure 5), dans lequel les deux fonctions précitées sont dissociées, avec une lame semi-transparente 18 supplémentaire (associée uniquement au micromoniteur 17), permettant d'éviter toute observation parasite.However, the parasitic observation of micromonitor 17 by the camera 4 is not excluded in such a scheme. It can be advantageously replaced by a diagram (figure 5), in which the two functions above are dissociated, with an additional semi-transparent blade 18 (associated only with micromonitor 17), making it possible to avoid any spurious observations.

L'avantage de cette organisation optique est qu'elle permet d'obtenir, en surimpression de la scène (champ 5), une visualisation de la fenêtre de guidage du missile (zone 8). Il est ainsi possible d'envisager, dans l'hypothèse où la « localisation missile» perdrait le missile (ce dernier se trouvant alors en dehors de la fenêtre) d'envoyer aux moyens de localisation 7 (sur ordre de l'opérateur) une commande de restitution (symbolisée par l'entrée 19 sur la figure 1) du balayage complet du champ 5 par le faisceau laser permettant d'«accrocher » à nouveau le missile.The advantage of this optical organization is that it allows obtain, over the scene (field 5), a visualization of the missile guidance window (zone 8). It is thus possible to envisage, in the event that the “missile location” would lose the missile (the latter then being outside the window) to send to the means of location 7 (on operator's order) a return command (symbolized by entry 19 in Figure 1) of the full scan of the field 5 by the laser beam allowing to "hang" again the missile.

Claims (10)

Procédé de guidage à balayage laser d'un missile (M) vers une cible (T), selon lequel on observe un champ (5), dans lequel est susceptible d'évoluer ledit missile (M), pour localiser ce dernier dans ledit champ (5),
caractérisé en ce que, dans ledit champ (5), on détermine une zone (8) autour de la position instantanée dudit missile (M) ainsi localisé, et en ce qu'on effectue le balayage laser uniquement dans ladite zone (8).Method for laser scanning guidance of a missile (M) towards a target (T), in which a field (5) is observed, in which said missile (M) is capable of evolving, in order to locate the latter in said field (5),
characterized in that, in said field (5), a zone (8) is determined around the instantaneous position of said missile (M) thus located, and in that laser scanning is carried out only in said zone (8). Procédé selon la revendication 1, dans lequel le balayage proprement dit est effectué dans tout ledit champ (8),
caractérisé en ce que l'allumage dudit faisceau laser (2) coïncide avec le balayage de ladite zone (8).Method according to claim 1, in which the actual scanning is carried out throughout said field (8),
characterized in that the lighting of said laser beam (2) coincides with the scanning of said area (8). Dispositif de guidage à balayage laser d'un missile vers une cible, pour la mise en oeuvre du procédé selon la revendication 1 ou 2, comportant : des moyens d'émission (3) d'un faisceau laser (2) destiné à transmettre des ordres de pilotage audit missile (M), des moyens d'observation (4) d'un champ (5), dans lequel est susceptible d'évoluer ledit missile (M), pour localiser ce dernier dans ledit champ (5), et des moyens (6) de balayage dudit champ (5) par ledit faisceau laser (2), reliés auxdits moyens d'émission (3), caractérisé par : des moyens (7) pour définir une zone (8) autour de la position instantanée dudit missile (M) dans ledit champ (5), reliés auxdits moyens d'observation (4), et des moyens d'activation (10) dudit faisceau laser (2) dans ladite zone (8), reliés auxdits moyens (7) définissant ladite zone (8). Device for laser scanning guidance of a missile towards a target, for implementing the method according to claim 1 or 2, comprising: means for emitting (3) a laser beam (2) intended to transmit piloting orders to said missile (M), means of observation (4) of a field (5), in which said missile (M) is capable of evolving, to locate the latter in said field (5), and means (6) for scanning said field (5) by said laser beam (2), connected to said emission means (3), characterized by : means (7) for defining an area (8) around the instantaneous position of said missile (M) in said field (5), connected to said observation means (4), and means for activating (10) said laser beam (2) in said zone (8), connected to said means (7) defining said zone (8). Dispositif selon la revendication 3,
caractérisé en ce que lesdits moyens d'activation du faisceau laser (2) sont des moyens d'allumage (10) dudit faisceau (2) en phase avec les moyens de balayage (6) dudit champ (5), de manière à faire coïncider l'allumage dudit faisceau (2) avec le balayage de ladite zone (8).Device according to claim 3,
characterized in that said means for activating the laser beam (2) are means for igniting (10) said beam (2) in phase with the scanning means (6) for said field (5), so as to coincide the ignition of said beam (2) with the scanning of said area (8). Dispositif selon la revendication 3 ou 4,
caractérisé en ce que lesdits moyens d'observation comprennent une caméra vidéo (4).Device according to claim 3 or 4,
characterized in that said observation means comprise a video camera (4). Dispositif selon la revendication 5,
caractérisé en ce qu'une lame semi-transparente (16) est intercalée dans le chemin optique entre le viseur (14) et la caméra (4).Device according to claim 5,
characterized in that a semi-transparent plate (16) is interposed in the optical path between the viewfinder (14) and the camera (4). Dispositif selon l'une quelconque des revendications 3 à 6,
caractérisé en ce qu'un moniteur (17) permet la visualisation de ladite zone (8) dans ledit champ (5).Device according to any one of Claims 3 to 6,
characterized in that a monitor (17) allows the visualization of said area (8) in said field (5). Dispositif selon la revendication 7,
caractérisé en ce que ledit moniteur (17) partage, avec ladite caméra (4), la même lame semi-transparente (16) intercalée dans ledit chemin optique.Device according to claim 7,
characterized in that said monitor (17) shares, with said camera (4), the same semi-transparent plate (16) interposed in said optical path. Dispositif selon la revendication 7,
caractérisé en ce que ladite caméra (4) et ledit moniteur (17) sont décalés, et sont associés, chacun, à une lame semi-transparente propre (16,18).Device according to claim 7,
characterized in that said camera (4) and said monitor (17) are offset, and are each associated with a clean semi-transparent plate (16,18). Dispositif selon l'une quelconque des revendications 3 à 9,
caractérisé par un commutateur (19) permettant de passer du balayage laser de ladite zone (8) au balayage dudit champ (5), sur ordre de l'opérateur.Device according to any one of Claims 3 to 9,
characterized by a switch (19) for switching from laser scanning of said area (8) to scanning of said field (5), on the operator's order.
EP00402039A 1999-07-30 2000-07-18 Method and apparatus for guiding a missile towards a target by means of laser scanning Expired - Lifetime EP1072858B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9909916A FR2797042B1 (en) 1999-07-30 1999-07-30 LASER SCANNING GUIDING METHOD AND DEVICE FROM A MISSILE TO A TARGET
FR9909916 1999-07-30

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EP1072858A1 true EP1072858A1 (en) 2001-01-31
EP1072858B1 EP1072858B1 (en) 2004-03-31

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AT (1) ATE263355T1 (en)
BR (1) BR0003426A (en)
DE (1) DE60009403T2 (en)
ES (1) ES2215584T3 (en)
FR (1) FR2797042B1 (en)
IL (1) IL137507A (en)
NO (1) NO319311B1 (en)

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* Cited by examiner, † Cited by third party
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US20060000925A1 (en) * 2004-06-30 2006-01-05 Maher Colin G Reduced sized micro-fluid jet nozzle structure
FR2885213B1 (en) * 2005-05-02 2010-11-05 Giat Ind Sa METHOD FOR CONTROLLING A MUNITION OR SUB-MUNITION, ATTACK SYSTEM, MUNITION AND DESIGNER EMPLOYING SUCH A METHOD
US7714989B1 (en) 2007-11-28 2010-05-11 The United States Of America As Represented By The Secretary Of The Navy Micropulse laser guidance
RU2477866C1 (en) * 2011-10-27 2013-03-20 Виктор Прович Семенков Method for shaping of information field of laser teleorientation system
RU2497062C2 (en) * 2011-12-08 2013-10-27 Виктор Прович Семенков Combined optic-electronic instrument
RU2504906C1 (en) * 2012-05-29 2014-01-20 Открытое акционерное общество "Государственный Рязанский приборный завод" Method for laser remote orientation of object and apparatus for realising said method
US9012822B2 (en) * 2012-07-18 2015-04-21 Thales Holdings Uk Plc Missile guidance
CN103121135A (en) * 2013-02-01 2013-05-29 河南新能光伏有限公司 Thin film solar cell bus bar intersection automatic hot welding device
RU2674563C1 (en) * 2018-03-07 2018-12-11 АО "Пространственные системы информации" (АО "ПСИ") Air targets coordinates optoelectronic measuring instrument
RU2750810C1 (en) * 2020-01-22 2021-07-05 Общество с ограниченной ответственностью "СМАРТС-Кванттелеком" Device for quantum communication at side frequencies with radiation registration at the central frequency

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3104318A1 (en) * 1980-12-23 1982-08-26 Eltro GmbH, Gesellschaft für Strahlungstechnik, 6900 Heidelberg Aiming method and associated apparatus arrangement
GB2146450A (en) * 1983-08-24 1985-04-17 Messerschmitt Boelkow Blohm Optical-mechanical scanning system having periodic beam switch
FR2593291A1 (en) * 1982-04-26 1987-07-24 Trt Telecom Radio Electr DEVICE FOR INFRARED DETECTION OF A LANDSCAPE POINT AND SYSTEM COMPRISING SAID DEVICE FOR GUIDING A MISSILE ON A TARGET

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3954228A (en) * 1965-11-16 1976-05-04 The United States Of America As Represented By The Secretary Of The Army Missile guidance system using an injection laser active missile seeker
US3695555A (en) * 1970-06-12 1972-10-03 Us Navy Gun-launched glide vehicle with a mid-course and terminal guidance control system
US4324491A (en) * 1973-02-12 1982-04-13 The United States Of America As Represented By The Secretary Of The Navy Dual mode guidance system
US4383663A (en) * 1976-06-01 1983-05-17 The United States Of America As Represented By The Secretary Of The Navy Active optical terminal homing
FR2688317B1 (en) * 1987-03-09 1994-08-05 Thomson Csf LASER WAVE SPATIAL ANALYSIS DEVICE, PARTICULARLY FOR MISSILE SELF-DIRECTING.
DE4007712A1 (en) * 1990-03-10 1991-09-12 Tzn Forschung & Entwicklung FLOOR WITH AN IR DETECTING SYSTEM ARROWED ON THE BOW SIDE

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3104318A1 (en) * 1980-12-23 1982-08-26 Eltro GmbH, Gesellschaft für Strahlungstechnik, 6900 Heidelberg Aiming method and associated apparatus arrangement
FR2593291A1 (en) * 1982-04-26 1987-07-24 Trt Telecom Radio Electr DEVICE FOR INFRARED DETECTION OF A LANDSCAPE POINT AND SYSTEM COMPRISING SAID DEVICE FOR GUIDING A MISSILE ON A TARGET
GB2146450A (en) * 1983-08-24 1985-04-17 Messerschmitt Boelkow Blohm Optical-mechanical scanning system having periodic beam switch

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EP1072858B1 (en) 2004-03-31
FR2797042B1 (en) 2002-09-06
DE60009403D1 (en) 2004-05-06
IL137507A (en) 2003-06-24
NO20003883D0 (en) 2000-07-28
FR2797042A1 (en) 2001-02-02
NO319311B1 (en) 2005-07-11
ES2215584T3 (en) 2004-10-16
DE60009403T2 (en) 2005-03-03
BR0003426A (en) 2001-03-13
US6357694B1 (en) 2002-03-19
NO20003883L (en) 2001-01-31
ATE263355T1 (en) 2004-04-15
IL137507A0 (en) 2001-07-24

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