EP0482987B1 - Kompaktes Visiergerät mit grossem Betrachtungswinkel für optoelektronische Ausrüstung zur Lokalisierung und Erfassung eines Ziels - Google Patents

Kompaktes Visiergerät mit grossem Betrachtungswinkel für optoelektronische Ausrüstung zur Lokalisierung und Erfassung eines Ziels Download PDF

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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
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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
Application number
EP19910402785
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English (en)
French (fr)
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EP0482987A1 (de
Inventor
Olivier Dez
Vincent Vilbois
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Thales SA
Original Assignee
Thomson CSF SA
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Filing date
Publication date
Application filed by Thomson CSF SA filed Critical Thomson CSF SA
Publication of EP0482987A1 publication Critical patent/EP0482987A1/de
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Publication of EP0482987B1 publication Critical patent/EP0482987B1/de
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Expired - Lifetime legal-status Critical Current

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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.

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  • Physics & Mathematics (AREA)
  • Optics & Photonics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Telescopes (AREA)

Claims (4)

  1. Kompaktes Visiergerät mit großem Auslenkungswinkel für eine optoelektronische Ausrüstung zur Lokalisierung und Erfassung eines Ziels an Bord eines Flugzeuges mit einer optomechanischen Einheit zur Höhenwinkel- und Seitenwinkelorientierung der Visierlinie sowie mit Spiegeln, die eine optische Einheit zum Bildversatz bilden, bei der die optomechanische Einheit eine Seitenwinkelstruktur (2), die sich auf Wälzlagern (R1) und (R2) um 360° drehen kann, sowie eine Höhenwinkelstruktur (3) aufweist, die an der Seitenwinkelstruktur (2) mit Hilfe von zwei Lagern (A) und (B) angebracht ist, die beiderseits der optischen Versatzeinheit angeordnet sind, dadurch gekennzeichnet, daß die Seitenwinkeleinrichtung ein Eintrittsfenster (10) aufweist, das von dem einfallenden Nutzstrahl durchquert wird, und das Gehäuse der Visiereinrichtung (1) bildet, und daß das Eintrittsfenster (10) eine insgesamt nach zwei Dimensionen rechteckige Form aufweist und das Höhenwinkelfeld über 90° positiv und wenigstens 20° negativ bezüglich der horizontalen Bezugsachse des Rumpfes nach einer ersten Dimension abdeckt und eine auf die Eintrittspupille reduzierte Breite nach der zweiten Dimension aufweist.
  2. Visiergerät nach Anspruch 1, dadurch gekennzeichnet, daß es eine brennpunktlose optische Einheit aufweist, die aus einer vorderen Gruppe (11), die mit der Höhenwinkelstruktur (3) fest verbunden und auf der Eintrittsseite der optischen Bildversatzeinheit angeordnet ist, um ein Zwischenbild zu erstellen, sowie aus einer hinteren Gruppe (12) besteht, die mit der Seitenwinkelstruktur (2) fest verbunden und auf der Austrittsseite dieser Versatzeinheit angeordnet ist, um wieder einen entlang der Seitenwinkelachse Y′OY kollimatierten Strahl zu bilden.
  3. Visiergerät nach Anspruch 1, dadurch gekennzeichnet, daß die Seitenwinkelstruktur (2) einen zylindrischen Teil aufweist, dessen Dichtigkeit mit dem Aufbau des Flugzeugs durch eine Ferrofluiddichtung sichergestellt ist.
  4. Visiergerät nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die Höhenwinkelstruktur eine Öffnung (Φ) aufweist, um den Lichtstrahl durchzulassen, wobei die Öffnung (Φ) Mittel zur Bildkorrektur einfaßt.
EP19910402785 1990-10-26 1991-10-18 Kompaktes Visiergerät mit grossem Betrachtungswinkel für optoelektronische Ausrüstung zur Lokalisierung und Erfassung eines Ziels Expired - Lifetime EP0482987B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9013278 1990-10-26
FR9013278A FR2668614B1 (fr) 1990-10-26 1990-10-26 Dispositif de visee compact a grand debattement angulaire pour equipement optronique de localisation et d'acquisition de cible.

Publications (2)

Publication Number Publication Date
EP0482987A1 EP0482987A1 (de) 1992-04-29
EP0482987B1 true EP0482987B1 (de) 1995-04-12

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP19910402785 Expired - Lifetime EP0482987B1 (de) 1990-10-26 1991-10-18 Kompaktes Visiergerät mit grossem Betrachtungswinkel für optoelektronische Ausrüstung zur Lokalisierung und Erfassung eines Ziels

Country Status (3)

Country Link
EP (1) EP0482987B1 (de)
DE (1) DE69108845T2 (de)
FR (1) FR2668614B1 (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4331259C1 (de) * 1993-09-15 2003-07-10 Bodenseewerk Geraetetech Sucher für zielverfolgende Flugkörper

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1452061A (fr) * 1965-05-12 1966-02-25 Coupole de forme sphérique pour instruments d'observation spatiale ou astronomique
FR2565698B1 (fr) * 1984-06-06 1987-09-04 Thomson Csf Systeme aeroporte de detection optoelectrique, de localisation et de poursuite omnidirectionnelle de cible
US4900117A (en) * 1989-02-21 1990-02-13 Chen Linus T Rotary optical coupler utilizing cylindrical ringshaped mirrors and method of making same

Also Published As

Publication number Publication date
FR2668614B1 (fr) 1993-10-29
DE69108845D1 (de) 1995-05-18
DE69108845T2 (de) 1995-09-14
EP0482987A1 (de) 1992-04-29
FR2668614A1 (fr) 1992-04-30

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