EP0482987B1 - Compact sighting system with large angular sweep capability for optronic target acquisition and localisation equipment - Google Patents
Compact sighting system with large angular sweep capability for optronic target acquisition and localisation equipment Download PDFInfo
- Publication number
- EP0482987B1 EP0482987B1 EP19910402785 EP91402785A EP0482987B1 EP 0482987 B1 EP0482987 B1 EP 0482987B1 EP 19910402785 EP19910402785 EP 19910402785 EP 91402785 A EP91402785 A EP 91402785A EP 0482987 B1 EP0482987 B1 EP 0482987B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- azimuth
- assembly
- elevation
- sighting device
- sight
- 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 - Lifetime
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G3/00—Aiming or laying means
- F41G3/06—Aiming or laying means with rangefinder
- F41G3/065—Structural association of sighting-devices with laser telemeters
Definitions
- the invention relates to the field of optronic equipment on board an aircraft, in particular intended for three-dimensional localization and / or for the acquisition of targets for example, and more particularly to a compact aiming device with large angular movement for a such equipment.
- An installation of the optronic equipment under the airplane does not allow the orientation of the line of sight towards the positive elevation angles with respect to the horizontal reference of the airplane fuselage.
- a lateral implantation would present an important mask, in deposit, due to the presence of the nose, unless using two systems placed symmetrically, which then significantly increases the cost.
- the installation of localization or optronic acquisition equipment, in particular on a weapon plane, at the foot of the canopy then creates a mask for the visibility of the pilot, mask all the greater as the field of acquisition of the localization equipment is important: as shown in FIG. 1, to allow the orientation of the line of sight downwards, according to elevation angles by compared to the horizontal reference of the negative and possibly large RHF fuselage, the localization equipment must indeed exceed relative to the skin of the PA aircraft, and the pilot P in his cockpit then has his low visibility line LVB, in the direction (in field) of the optronic equipment, limited by this equipment.
- the low line of sight of the Lvb optronic equipment is itself limited by the fuselage or "skin" of the PA aircraft.
- the main devices for orienting the line of sight mounted on existing devices currently do not generally allow a large angular movement of the line of sight, or else when the angular movement is almost suitable, the device creates a large concealment for the visibility of the pilot and harmful disturbances for stability and piloting due to aerodynamic drag.
- the subject of the invention is a device for optronic on-board location and acquisition equipment, which allows access to large angular deflections of the line of sight, in particular an unlimited field deflection, while clearing the visibility of the pilot. and limiting the aerodynamic effects.
- the proposed device is compact, in the sense that it makes it possible to limit the volume external to the skin of the aircraft, and has an external structure which can rotate freely along the bearing axis.
- the invention relates to a compact aiming device with large angular movement for optronic target location and acquisition equipment on board an aircraft comprising an optomechanical set of orientation in elevation and in bearing of the line of sight and mirrors. forming an optical image shifting assembly, in which the optomechanical assembly comprises a bearing structure which can rotate 360 ° supported by bearings and a site structure mounted on the bearing structure using two bearings arranged at one side and on the other side of the optical offset assembly.
- the optomechanical assembly comprises a bearing structure which can rotate 360 ° supported by bearings and a site structure mounted on the bearing structure using two bearings arranged at one side and on the other side of the optical offset assembly.
- This sighting device is characterized according to the invention in that the field device comprises an inlet porthole crossed by the useful incident beam and forms the envelope of the aiming device, and in that the entry porthole has a overall rectangular shape in two dimensions and covers the elevated field on 90 ° in positive and at least 20 ° in negative compared to the horizontal reference of the fuselage according to a first dimension and has a reduced width at the entrance pupil according to the second dimension.
- the document FR-A-1 452 061 describes a device for pointing the telescope in which the dome of the telescope is orientable in bearing.
- the device for orienting the line of sight is located in the plane of symmetry of the aircraft.
- the principle adopted is the use of a Poggendorf mirror M (called 1 ⁇ 2), that is to say that the line of sight rotates by 2 ⁇ when a mirror undergoes a rotation of ⁇ .
- a type of device does not allow the orientation of the line of sight LV towards high elevation angles relative to the horizontal reference of the RHF fuselage, due to the principle adopted and the limited size of the mirror.
- the low visibility of the pilot is very obscured in the axis since the system is arranged in the plane of symmetry of the aircraft.
- the principle used is the same, rotation of a mirror M equal to half the viewing angle relative to the RHF, but the device for orienting the line of sight comprises a lens at the head to reduce the diameter of the beam at the level of the mirror M.
- This device is more complex than the previous one, because the angle of rotation of the head lens is equal to twice that of the mirror M, the 2 axes of rotation being confused.
- the same limitation occurs with regard to the orientation of the line of sight towards very high elevation angles, and the concealment of the low visibility of the pilot still exists.
- a third type of device shown in Figure 3 also mounted laterally, the concealment of the low line of sight is of the same order; on the other hand the accessible angular range is more important because the system provides for a coupling of axes making it possible to orient the line of sight at the same time in elevation and in bearing.
- Such a device consists of a sphere S rotating around a fixed point C which is the center of the sphere and which is the intersection of the two axes of rotation.
- Such a device makes it possible to obtain smaller external dimensions, but has a major drawback for monitoring, because if it is easy to position the various elements of the device to obtain a line of sight in a given direction, a servo-control of the whole to get a continuous scan is much more difficult.
- the line of sight accesses a large angular range to perform either a pursuit or a target search by exploring a large volume around the aircraft according to a scanning law; on the other hand, the servos of the line of sight along the axes site and deposit are planned to be fully decoupled;
- the optomechanical site / deposit architecture proposed allows the aiming device to occupy only a small volume, with a spherical entry porthole of very simplified construction.
- the sighting device 1 is shown in Figures 4a and 4b according to two orthogonal sections, Figure 4a being in the plane of symmetry of the aircraft.
- This device comprises a deposit structure 2 which forms the envelope of the device 1, a spherical part of this envelope emerging from the skin of the aircraft.
- This structure 2 rotates around the Y′0Y bearing axis over 360 °, bearing on the frame of the aircraft thanks to the bearings R1 and R2 arranged between this frame and a cylindrical part of the structure 2; the deposit structure 2 supports image transfer mirrors M2, M3 and M4.
- a site structure 3 defines the site angle of the line of sight around a site axis X′OX orthogonal to the axis of deposit Y′0Y; for this purpose, two rolling bearings A and B ensure the rotation of the site structure 3 independently of the deposit structure 2; the site structure 3 supports the deflection mirror M1 from the line of sight towards the site axis X′OX.
- the sighting device 1 also includes a spherical porthole 10 mounted in the reservoir structure 2; the large dimension of this window covers the field in site (see Figure 4b) over 90 ° in positive site and at least 20 ° in negative site compared to RHF; the small dimension or width of the window is reduced to the dimension of the entrance pupil (widened to the instantaneous field of observation in cone of the equipment).
- This configuration makes it possible to limit the dimensions of the window without limiting the angular movement.
- the optical equipment is completed by an afocal optical assembly composed of two groups, a front group, symbolized by the input lens 11, and a rear group, symbolized by the output lens 12, the lens 11 being secured to the site structure 3 and the lens 12 secured to the reservoir structure 2.
- the useful incident beam defined by the entrance pupil and oriented along the line of sight, passes through the entrance window 10, is focused by the lens 11, after reflection on the mirrors M1 and M2, in a plane located between mirrors M2 and M3 to form an intermediate image there, and is returned along the bearing axis thanks to mirrors M3 and M4 to reform a collimated beam on this axis through group 12, the latter forming an afocal arrangement with group 11; the collimated beam is then focused in a detection plane.
- an afocal assembly for example with converging-converging diopters, makes it possible to have a beam of reduced diameter, in particular at the level of the mirrors M2 and M3. This makes it possible to reduce the dimensions of the return mirrors M1 to M4, in particular of the mirrors M2 and M3 situated before and after the plane of formation of the intermediate image.
- the site structure 2 has an opening ⁇ because the rolling bearing B is located behind the mirror M2.
- the seal between the moving part in the deposit and the fixed frame, at the level of the bearing R1 can be ensured by gaskets of loaded polytetrafluoroethylene (more commonly known under the trade name "TEFLON").
- TEFLON loaded polytetrafluoroethylene
- the window in order to no longer be exposed to aerodynamic flow, can be turned 180 ° along the deposit axis so as to be protected, for example rain-erosion, when crossing hostile areas; the opening of the site structure can be used to embed a diaphragm and / or a collecting lens so as to improve the quality of the image formed in the detection plane; for safety reasons, the window can be doubled.
- thermokinetic heating In order to completely avoid sealing problems, it can also be envisaged to use a fixed spherical porthole, of suitable dimensions; but, in this case, most of the advantages of the mobile structure disappear, in particular the reduced size of the window and the variable stopping point of the incident aerodynamic flow, a fixed stopping point causing localized thermokinetic heating.
Landscapes
- Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Telescopes (AREA)
Description
L'invention se rapporte au domaine des équipements optroniques embarqués à bord d'avion, notamment destinés à la localisation tridimensionnelle et/ou à l'acquisition de cibles par exemple, et plus particulièrement à un dispositif de visée compact à grand débattement angulaire pour un tel équipement.The invention relates to the field of optronic equipment on board an aircraft, in particular intended for three-dimensional localization and / or for the acquisition of targets for example, and more particularly to a compact aiming device with large angular movement for a such equipment.
Un paramètre important pour les systèmes optroniques de localisation tridimensionnelle et/ou d'identification embarqués est le débattement angulaire de la ligne de visée. En effet, il est tout à fait important que ce type d'équipements embarqués permette la localisation et l'identification dans les secteurs les plus grands possibles. L'implantation idéale consisterait à mettre l'équipement optronique directement en bout de nez de l'avion. Ceci n'est généralement pas possible du fait de la présence du radar à cet endroit.An important parameter for optronic three-dimensional localization and / or on-board identification systems is the angular displacement of the line of sight. Indeed, it is very important that this type of on-board equipment allows localization and identification in the largest possible sectors. The ideal location would be to put the optronic equipment directly at the nose of the aircraft. This is generally not possible due to the presence of the radar at this location.
Une implantation de l'équipement optronique sous l'avion ne permet pas l'orientation de la ligne de visée vers les angles de site positifs par rapport à la référence horizontale du fuselage de l'avion.An installation of the optronic equipment under the airplane does not allow the orientation of the line of sight towards the positive elevation angles with respect to the horizontal reference of the airplane fuselage.
Une implantation latérale présenterait un masque important, en gisement, du fait de la présence du nez, à moins d'utiliser deux systèmes placés symétriquement, ce qui augmente alors notablement le coût.A lateral implantation would present an important mask, in deposit, due to the presence of the nose, unless using two systems placed symmetrically, which then significantly increases the cost.
L'implantation dite "en pied de verrière", entre le pare-brise du cockpit et le radôme, permet d'obtenir les champs d'acquisition les plus importants et les plus intéressants du point de vue opérationnel.The so-called "canopy" installation, between the cockpit windshield and the radome, provides the most important and most interesting fields of acquisition from an operational point of view.
Or l'implantation d'un équipement de localisation ou d'acquisition optronique, notamment sur un avion d'arme, en pied de verrière crée alors un masque pour la visibilité du pilote, masque d'autant plus grand que le champ d'acquisition de l'équipement de localisation est important : comme le montre la figure 1, pour permettre l'orientation de la ligne de visée vers le bas, selon des angles de site par rapport à la référence horizontale du fuselage RHF négatifs et éventuellement importants, l'équipement de localisation doit en effet dépasser par rapport à la peau de l'avion PA, et le pilote P dans son cockpit a alors sa ligne de visibilité basse LVB, dans la direction (en gisement ) de l'équipement optronique, limitée par cet équipement. La ligne de visée basse de l'équipement optronique Lvb est, elle, limitée par le fuselage ou "peau" de l'avion PA.However, the installation of localization or optronic acquisition equipment, in particular on a weapon plane, at the foot of the canopy then creates a mask for the visibility of the pilot, mask all the greater as the field of acquisition of the localization equipment is important: as shown in FIG. 1, to allow the orientation of the line of sight downwards, according to elevation angles by compared to the horizontal reference of the negative and possibly large RHF fuselage, the localization equipment must indeed exceed relative to the skin of the PA aircraft, and the pilot P in his cockpit then has his low visibility line LVB, in the direction (in field) of the optronic equipment, limited by this equipment. The low line of sight of the Lvb optronic equipment is itself limited by the fuselage or "skin" of the PA aircraft.
Les principaux dispositifs d'orientation de la ligne de visée montés sur les appareils existants actuellement ne permettent généralement pas un grand débattement angulaire de la ligne de visée, ou bien lorsque le débattement angulaire est à peu près convenable, le dispositif crée une occultation importante pour la visibilité du pilote et des perturbations néfastes pour la stabilité et le pilotage dues à la traînée aérodynamique.The main devices for orienting the line of sight mounted on existing devices currently do not generally allow a large angular movement of the line of sight, or else when the angular movement is almost suitable, the device creates a large concealment for the visibility of the pilot and harmful disturbances for stability and piloting due to aerodynamic drag.
L'invention a pour objet un dispositif pour équipement optronique de localisation et d'acquisition embarqué, qui permet d'accéder à de grands débattements angulaires de la ligne de visée, en particulier un débattement en gisement illimité, tout en dégageant la visibilité du pilote et en limitant les effets aérodynamiques. Pour cela le dispositif proposé est compact, en ce sens qu'il permet de limiter le volume externe à la peau de l'avion, et possède une structure externe pouvant tourner librement selon l'axe de gisement.The subject of the invention is a device for optronic on-board location and acquisition equipment, which allows access to large angular deflections of the line of sight, in particular an unlimited field deflection, while clearing the visibility of the pilot. and limiting the aerodynamic effects. For this, the proposed device is compact, in the sense that it makes it possible to limit the volume external to the skin of the aircraft, and has an external structure which can rotate freely along the bearing axis.
L'invention concerne un dispositif de visée compact à grand débattement angulaire pour équipement optronique de localisation et d'acquisition de cible embarqué à bord d'avion comportant un ensemble optomécanique d'orientation en site et en gisement de la ligne de visée et des miroirs formant un ensemble optique de déport d'image, dans lequel l'ensemble optomécanique comporte une structure gisement pouvant tourner sur 360° en appui sur des roulements et une structure site montée sur la structure gisement à l'aide de deux paliers disposés de part et d'autre de l'ensemble optique de déport. Un tel dispositif de visée est décrit dans le document FR-A-167 432.The invention relates to a compact aiming device with large angular movement for optronic target location and acquisition equipment on board an aircraft comprising an optomechanical set of orientation in elevation and in bearing of the line of sight and mirrors. forming an optical image shifting assembly, in which the optomechanical assembly comprises a bearing structure which can rotate 360 ° supported by bearings and a site structure mounted on the bearing structure using two bearings arranged at one side and on the other side of the optical offset assembly. Such an aiming device is described in document FR-A-167,432.
Ce dispositif de visé est caractérisé selon l'invention en ce que le dispositif de gisement comporte un hublot d'entrée traversé par le faisceau incident utile et forme l'enveloppe du dispositif de visée, et en ce que le hublot d'entrée présente une forme globalement rectangulaire selon deux dimensions et couvre le champ en site sur 90° en positif et au moins 20° en négatif par rapport à la référence horizontale du fuselage selon une première dimension et possède une largeur réduite à la pupille d'entrée selon la seconde dimension.This sighting device is characterized according to the invention in that the field device comprises an inlet porthole crossed by the useful incident beam and forms the envelope of the aiming device, and in that the entry porthole has a overall rectangular shape in two dimensions and covers the elevated field on 90 ° in positive and at least 20 ° in negative compared to the horizontal reference of the fuselage according to a first dimension and has a reduced width at the entrance pupil according to the second dimension.
Dans le domaine technique des telescopes astronomiques, le document FR-A-1 452 061 décrit un dispositif de pointage du télescope dans lequel la coupole du télescope est orientable en gisement.In the technical field of astronomical telescopes, the document FR-A-1 452 061 describes a device for pointing the telescope in which the dome of the telescope is orientable in bearing.
L'invention sera mieux comprise et d'autres caractéristiques et avantages apparaîtront à l'aide de la description qui suit en référence aux figures annexées représentant, respectivement :
- La figure 1, un schéma général permettant de montrer l'occultation de la ligne de visibilité basse du pilote, occasionnée par un équipement d'acquisition optronique en secteur frontal ;
- Les figures 2 et 3 sont des schémas illustrant des dispositifs selon l'art antérieur ;
- Les figures 4a et 4b illustrent le dispositif compact selon l'invention en coupe dans deux positions différentes ;
- FIG. 1, a general diagram making it possible to show the concealment of the pilot's low visibility line, occasioned by optronic acquisition equipment in the frontal sector;
- Figures 2 and 3 are diagrams illustrating devices according to the prior art;
- Figures 4a and 4b illustrate the compact device according to the invention in section in two different positions;
Pour mieux comprendre les caractéristiques essentielles de l'invention et mieux en mesurer les avantages, une description succincte est donnée ci-après de dispositifs d'orientation de la ligne de visée connus.In order to better understand the essential characteristics of the invention and to better measure the advantages thereof, a brief description is given below of known devices for orienting the line of sight.
Selon un premier type de dispositif représenté sur la figure 2, le dispositif d'orientation de la ligne de visée est situé dans le plan de symétrie de l'avion. Le principe retenu est l'utilisation d'un miroir M de Poggendorf (dit en ½), c'est-à-dire que la ligne de visée tourne de 2 α lorsqu'un miroir subit une rotation de α . Un tel type de dispositif ne permet pas l'orientation de la ligne de visée LV vers des angles en site élevés par rapport à la référence horizontale du fuselage RHF, du fait du principe retenu et de la dimension limitée du miroir. De plus la visibilité basse du pilote est très occultée dans l'axe puisque le système est disposé dans le plan de symétrie de l'avion.According to a first type of device shown in FIG. 2, the device for orienting the line of sight is located in the plane of symmetry of the aircraft. The principle adopted is the use of a Poggendorf mirror M (called ½), that is to say that the line of sight rotates by 2 α when a mirror undergoes a rotation of α. Such a type of device does not allow the orientation of the line of sight LV towards high elevation angles relative to the horizontal reference of the RHF fuselage, due to the principle adopted and the limited size of the mirror. In addition the low visibility of the pilot is very obscured in the axis since the system is arranged in the plane of symmetry of the aircraft.
Selon un autre type de dispositif, le principe utilisé est le même, rotation d'un miroir M égale à la moitié de l'angle de visée par rapport à la RHF, mais le dispositif d'orientation de la ligne de visée comporte une lentille en tête pour réduire le diamètre du faisceau au niveau du miroir M. Ce dispositif est plus complexe que le précédent, car l'angle de rotation de la lentille de tête est égal à deux fois celui du miroir M, les 2 axes de rotation étant confondus. La même limitation intervient quant à l'orientation de la ligne de visée vers des angles en site très élevés, et l'occultation de la visibilité basse du pilote existe toujours.According to another type of device, the principle used is the same, rotation of a mirror M equal to half the viewing angle relative to the RHF, but the device for orienting the line of sight comprises a lens at the head to reduce the diameter of the beam at the level of the mirror M. This device is more complex than the previous one, because the angle of rotation of the head lens is equal to twice that of the mirror M, the 2 axes of rotation being confused. The same limitation occurs with regard to the orientation of the line of sight towards very high elevation angles, and the concealment of the low visibility of the pilot still exists.
Selon un troisième type de dispositif représenté sur la figure 3 également monté latéralement, l'occultation de la ligne de visée basse est du même ordre ; par contre le domaine angulaire accessible est plus important car le système prévoit un couplage d'axes permettant d'orienter la ligne de visée en même temps en site et en gisement. Un tel dispositif est constitué d'une sphère S tournant autour d'un point fixe C qui est le centre de la sphère et qui est l'intersection des deux axes de rotation. Un tel dispositif permet d'obtenir des dimensions extérieures plus faibles, mais a un inconvénient majeur pour effectuer une veille, car s'il est facile de positionner les différents éléments du dispositif pour obtenir une ligne de visée dans une direction donnée, un asservissement de l'ensemble pour obtenir un balayage continu est beaucoup plus difficile.According to a third type of device shown in Figure 3 also mounted laterally, the concealment of the low line of sight is of the same order; on the other hand the accessible angular range is more important because the system provides for a coupling of axes making it possible to orient the line of sight at the same time in elevation and in bearing. Such a device consists of a sphere S rotating around a fixed point C which is the center of the sphere and which is the intersection of the two axes of rotation. Such a device makes it possible to obtain smaller external dimensions, but has a major drawback for monitoring, because if it is easy to position the various elements of the device to obtain a line of sight in a given direction, a servo-control of the whole to get a continuous scan is much more difficult.
Selon l'invention, d'une part la ligne de visée accède à un grand domaine angulaire pour effectuer soit une poursuite soit une recherche de cible par exploration d'un volume important autour de l'avion selon une loi de balayage ; d'autre part, les asservissements de la ligne de visée selon les axes site et gisement sont prévus pour être totalement découplés ; enfin l'architecture optomécanique site/gisement proposée permet au dispositif de visée de n'occuper qu'un faible volume, avec un hublot d'entrée sphérique de réalisation très simplifiée.According to the invention, on the one hand the line of sight accesses a large angular range to perform either a pursuit or a target search by exploring a large volume around the aircraft according to a scanning law; on the other hand, the servos of the line of sight along the axes site and deposit are planned to be fully decoupled; Finally, the optomechanical site / deposit architecture proposed allows the aiming device to occupy only a small volume, with a spherical entry porthole of very simplified construction.
Le dispositif de visée 1 selon l'invention est représenté sur les figures 4a et 4b selon deux coupes orthogonales, la figure 4a étant dans le plan de symétrie de l'avion. Ce dispositif comporte une structure gisement 2 qui forme l'enveloppe du dispositif 1, une partie sphérique de cette enveloppe émergeant de la peau de l'avion. Cette structure 2 tourne autour de l'axe gisement Y′0Y sur 360°, en appui sur le bâti de l'avion grâce aux roulements R1 et R2 disposés entre ce bâti et une partie cylindrique de la structure 2 ; la structure gisement 2 supporte des miroirs de déport d'image M2, M3 et M4. Une structure site 3 définit l'angle de site de la ligne de visée autour d'un axe de site X′OX orthogonal à l'axe de gisement Y′0Y ; dans ce but, deux paliers à roulement A et B assurent la rotation de la structure site 3 indépendamment de la structure gisement 2 ; la structure site 3 supporte le miroir de renvoi M1 de la ligne de visée vers l'axe de site X′OX. Le dispositif de visée 1 comporte également un hublot sphérique 10 monté dans la structure gisement 2 ; la grande dimension de cet hublot couvre le champ en site (voir figure 4b) sur 90° en site positif et au moins 20° en site négatif par rapport à la RHF ; la petite dimension ou largeur du hublot est réduite à la dimension de la pupille d'entrée (élargie au champ d'observation instantané en cône de l'équipement). Cette configuration permet de limiter les dimensions du hublot sans limiter le débattement angulaire.The
L'équipement optique est complété par un ensemble optique afocal composé de deux groupes, un groupe avant, symbolisé par la lentille 11 d'entrée, et un groupe arrière, symbolisé par la lentille 12 de sortie, la lentille 11 étant solidaire de la structure site 3 et la lentille 12 solidaire de la structure gisement 2.The optical equipment is completed by an afocal optical assembly composed of two groups, a front group, symbolized by the
Dans ces conditions, le faisceau incident utile, défini par la pupille d'entrée et orienté selon la ligne de visée, traverse le hublot d'entrée 10, est focalisé par la lentille 11, après réflexion sur les miroirs M1 et M2, dans un plan situé entre les miroirs M2 et M3 pour y former une image intermédiaire, et est renvoyé selon l'axe de gisement grâce aux miroirs M3 et M4 pour reformer un faisceau collimaté sur cet axe à travers le groupe 12, ce dernier formant un montage afocal avec le groupe 11 ; le faisceau collimaté est ensuite focalisé dans un plan de détection.Under these conditions, the useful incident beam, defined by the entrance pupil and oriented along the line of sight, passes through the
L'intégration d'un ensemble afocal, par exemple à dioptres convergent-convergent, permet de disposer d'un faisceau de diamètre réduit, en particulier au niveau des miroirs M2 et M3. Ceci permet de diminuer les dimensions des miroirs de renvoi M1 à M4, en particulier des miroirs M2 et M3 situés avant et après le plan de formation de l'image intermédiaire. Pour permettre la formation de cette image intermédiaire et le passage du faisceau entre les miroirs M2 et M3, la structure site 2 présente une ouverture ⌀ du fait que le palier de roulement B se trouve derrière le miroir M2.The integration of an afocal assembly, for example with converging-converging diopters, makes it possible to have a beam of reduced diameter, in particular at the level of the mirrors M2 and M3. This makes it possible to reduce the dimensions of the return mirrors M1 to M4, in particular of the mirrors M2 and M3 situated before and after the plane of formation of the intermediate image. To allow the formation of this intermediate image and the passage of the beam between the mirrors M2 and M3, the
Une solution aurait pu être de placer le palier B entre les miroirs M1 et M2 pour permettre un débattement angulaire en site illimité. Cependant, l'éventail des valeurs utiles du débattement en site est compris entre +60° et -20° (voir figure 4b) lorsque le dispositif est implanté en pied de verrière ; en effet, l'angle en site bas (ligne de visée basse Lvb) est alors limité par la présence du radôme et, d'autre part, le système présente un point singulier pour les angles en site positif d'environ 90°, la rotation autour de l'axe gisement n'ayant alors plus aucun effet. En revanche, en plaçant le palier B derrière le miroir M2 et en inclinant ce dernier pour rendre globalement parallèles les faisceaux incidents sur M1 et émergeant de M2, il s'ensuit une réduction du diamètre hors tout du dispositif.One solution could have been to place the bearing B between the mirrors M1 and M2 to allow angular movement on an unlimited site. However, the range of useful values for on-site clearance is between + 60 ° and -20 ° (see Figure 4b) when the device is installed at the foot of the canopy; indeed, the low elevation angle (low line of sight Lvb) is then limited by the presence of the radome and, on the other hand, the system presents a singular point for the angles in positive elevation of approximately 90 °, the rotation around the deposit axis then having no effect. On the other hand, by placing the bearing B behind the mirror M2 and by tilting the latter to make the incident beams on M1 generally parallel and emerging from M2, there follows a reduction in the overall diameter of the device.
L'invention n'est pas limitée au mode de réalisation décrit et représenté ; en particulier, l'étanchéité entre la partie mobile en gisement et la bâti fixe, au niveau du roulement R1, peut être assurée par des joints en polytétrafluoroéthylène (plus communément connu sous la dénomination commerciale "TEFLON") chargé. Dans certaines conditions, notamment en phase de poursuite de cible, lorsqu'il est nécessaire de stabiliser la ligne de visée, le couple de frottement risque de s'avérer trop important pour ce type de joints ; il est alors plus intéressant au niveau des performances d'adapter un joint de type ferrofluide. D'autres aménagements et avantages sont également à considérer dans le cadre de l'invention : notamment, pour ne plus être exposé au flux aérodynamique, le hublot peut être retourné de 180° selon l'axe gisement de façon à être protégé, par exemple de la pluvio-érosion, lors de la traversée de zones hostiles ; l'ouverture de la structure site peut servir à enchâsser un diaphragme et/ou une lentille collectrice de façon à améliorer la qualité de l'image formée dans le plan de détection ; pour des raisons de sécurité, le hublot peut être doublé .The invention is not limited to the embodiment described and shown; in particular, the seal between the moving part in the deposit and the fixed frame, at the level of the bearing R1, can be ensured by gaskets of loaded polytetrafluoroethylene (more commonly known under the trade name "TEFLON"). Under certain conditions, in particular during the target tracking phase, when it is necessary to stabilize the line of sight, the friction torque may prove to be too great for this type of joint; it is therefore more advantageous in terms of performance to adapt a ferrofluid type seal. Other arrangements and advantages are also to be considered in the context of the invention: in particular, in order to no longer be exposed to aerodynamic flow, the window can be turned 180 ° along the deposit axis so as to be protected, for example rain-erosion, when crossing hostile areas; the opening of the site structure can be used to embed a diaphragm and / or a collecting lens so as to improve the quality of the image formed in the detection plane; for safety reasons, the window can be doubled.
Afin de se soustraire totalement des problèmes d'étanchéité, il peut également être envisagé d'utiliser un hublot sphérique fixe, de dimensions adaptées ; mais, dans ce cas, la plupart des avantages que présente la structure mobile disparaissent, en particulier la dimension réduite du hublot et le point d'arrêt variable du flux aérodynamique incident, un point d'arrêt fixe entraînant un échauffement thermocinétique localisé.In order to completely avoid sealing problems, it can also be envisaged to use a fixed spherical porthole, of suitable dimensions; but, in this case, most of the advantages of the mobile structure disappear, in particular the reduced size of the window and the variable stopping point of the incident aerodynamic flow, a fixed stopping point causing localized thermokinetic heating.
Claims (4)
- Compact sighting device with large angular displacement for optoelectronic target locating and acquisition equipment installed on board an aircraft, including an optomechanical assembly for orienting the line of sight in elevation and in azimuth, and mirrors forming an optical image-shifting assembly, in which the optomechanical assembly includes an azimuth structure (2) capable of turning over 360° supported on bearings (R1) and (R2) and an elevation structure (3) mounted on the azimuth structure (2) with the aid of two bearings (A) and (B) arranged on either side of the optical shifting assembly, characterized in that the azimuth device includes an entry window traversed by the useful incident beam and forms the casing of the sighting device (1), and in that the entry window (10) exhibits an overall rectangular shape along two dimensions and covers the field in elevation over 90° in the positive direction and at least 20° in the negative direction with respect to the longitudinal fuselage datum along a first dimension, and possesses a reduced width at the entry pupil along the second dimension.
- Sighting device according to Claim 1, characterized in that it includes an afocal optical assembly consisting of a front group (11) integral with the elevation structure (3) and arranged upstream of the optical assembly for shifting the image in order to form an intermediate image and of a rear group (12) integral with the azimuth structure (2) and arranged downstream of this shifting assembly in order to reform a beam collimated along the azimuth axis Y′OY.
- Sighting device according to Claim 1, characterized in that the azimuth structure comprises a cylindrical part, the sealing of which with (2) and the frame of the aircraft is provided by a ferrofluid joint.
- Sighting device according to one of the preceding claims, characterized in that the elevation structure has an aperture (ø) for letting through the light beam, the aperture (ø) holding image correction means.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR9013278 | 1990-10-26 | ||
| FR9013278A FR2668614B1 (en) | 1990-10-26 | 1990-10-26 | COMPACT SIGHTING DEVICE WITH LARGE ANGLE TRAVEL FOR OPTRONIC TARGET LOCATION AND ACQUISITION EQUIPMENT. |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0482987A1 EP0482987A1 (en) | 1992-04-29 |
| EP0482987B1 true EP0482987B1 (en) | 1995-04-12 |
Family
ID=9401583
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP19910402785 Expired - Lifetime EP0482987B1 (en) | 1990-10-26 | 1991-10-18 | Compact sighting system with large angular sweep capability for optronic target acquisition and localisation equipment |
Country Status (3)
| Country | Link |
|---|---|
| EP (1) | EP0482987B1 (en) |
| DE (1) | DE69108845T2 (en) |
| FR (1) | FR2668614B1 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4331259C1 (en) * | 1993-09-15 | 2003-07-10 | Bodenseewerk Geraetetech | Seeker for guided missile has electro-optical seeker mounted in Cardan frame with actuators to align seeker onto target |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1452061A (en) * | 1965-05-12 | 1966-02-25 | Spherical dome for space or astronomical observation instruments | |
| FR2565698B1 (en) * | 1984-06-06 | 1987-09-04 | Thomson Csf | AIRPORT OPTOELECTRIC DETECTION, LOCATION AND OMNIDIRECTIONAL TARGET TRACKING SYSTEM |
| US4900117A (en) * | 1989-02-21 | 1990-02-13 | Chen Linus T | Rotary optical coupler utilizing cylindrical ringshaped mirrors and method of making same |
-
1990
- 1990-10-26 FR FR9013278A patent/FR2668614B1/en not_active Expired - Fee Related
-
1991
- 1991-10-18 DE DE1991608845 patent/DE69108845T2/en not_active Expired - Fee Related
- 1991-10-18 EP EP19910402785 patent/EP0482987B1/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| FR2668614A1 (en) | 1992-04-30 |
| EP0482987A1 (en) | 1992-04-29 |
| DE69108845D1 (en) | 1995-05-18 |
| DE69108845T2 (en) | 1995-09-14 |
| FR2668614B1 (en) | 1993-10-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA1232164A (en) | Reconnaissance system using an aerial vehicle spinning about its lengthwise axis | |
| EP0628780A1 (en) | Aiming system for aircraft | |
| EP0482987B1 (en) | Compact sighting system with large angular sweep capability for optronic target acquisition and localisation equipment | |
| EP0702246B1 (en) | Portable device for measuring the backscattering of light | |
| FR2944594A1 (en) | SELF-DIRECTING HEAD WITH TWO DETECTION WAYS, AND MISSILE COMPRISING SUCH A HEAD | |
| WO1996007120A1 (en) | Orientation locating system for an observation instrument | |
| EP0353138A1 (en) | Multispectral mirror device | |
| EP0068932B1 (en) | Sighting devices for periscopic arrangements, particulary for submarines | |
| EP0425365B1 (en) | System for correction of optical aberrations caused by non axial use of spherical cupolas | |
| FR2764710A1 (en) | MULTISPECTRAL STABILIZED SIGHT DEVICE | |
| FR2530009A1 (en) | Stabilised periscope and aiming device with IR detector | |
| EP1635485B1 (en) | Optical transmission method between an on-board spacecraft terminal and a distant terminal, and spacecraft adapted for said method | |
| FR2584202A1 (en) | IMPROVEMENTS ON STABILIZED MOUNTING DEVICES | |
| WO2022012824A1 (en) | Optronic pod | |
| EP0099769B1 (en) | Device for analyzing a spatial field for the angular localization of a radiating object | |
| FR2525761A1 (en) | Stabilised optical sighting system with gyroscope - has infrared camera aligned with input in order to generate position signals for aligning motors | |
| EP0071492A1 (en) | Apparatus for panorama-optical surveillance | |
| EP0196980A1 (en) | View finder for optical ranging | |
| EP0438336B1 (en) | Self rotating sighting device for on board optoelectronic localisation and identification equipment | |
| WO2020127688A1 (en) | Optical detection device of a self-guided flying vehicle | |
| FR2690532A1 (en) | Pointing, or aiming, device for optical equipment e.g. for satellite communication using modulated laser beam - has system of two mirrors rotating about axes perpendicular to each other with fine tuning of first mirror | |
| FR2944593A1 (en) | SELF-DIRECTING HEAD COMPRISING AT LEAST TWO DISTINCT DETECTION WAYS, AND MISSILE COMPRISING SUCH A HEAD | |
| US20240168276A1 (en) | On-Gimbal Telescope Pointing Assembly | |
| FR2530831A1 (en) | Variable optical deflector device, application to a homing-head optical system. | |
| US20210033750A1 (en) | Compact Star Tracker with Photonic Crystal Pointing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
| AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): DE FR GB IT |
|
| 17P | Request for examination filed |
Effective date: 19920818 |
|
| RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: THOMSON-CSF |
|
| 17Q | First examination report despatched |
Effective date: 19940715 |
|
| GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
| AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): DE FR GB IT |
|
| ITF | It: translation for a ep patent filed |
Owner name: JACOBACCI & PERANI S.P.A. |
|
| REF | Corresponds to: |
Ref document number: 69108845 Country of ref document: DE Date of ref document: 19950518 |
|
| GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) |
Effective date: 19950427 |
|
| PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
| STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
| 26N | No opposition filed | ||
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20010918 Year of fee payment: 11 |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20010919 Year of fee payment: 11 |
|
| REG | Reference to a national code |
Ref country code: GB Ref legal event code: IF02 |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: CD |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20021018 |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20030501 |
|
| GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20021018 |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IT Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED. Effective date: 20051018 |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20101020 Year of fee payment: 20 |