EP0099769B1 - Vorrichtung zur Analyse eines räumlichen Feldes zur Winkelortung eines strahlenden Objektes - Google Patents

Vorrichtung zur Analyse eines räumlichen Feldes zur Winkelortung eines strahlenden Objektes Download PDF

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Publication number
EP0099769B1
EP0099769B1 EP19830401158 EP83401158A EP0099769B1 EP 0099769 B1 EP0099769 B1 EP 0099769B1 EP 19830401158 EP19830401158 EP 19830401158 EP 83401158 A EP83401158 A EP 83401158A EP 0099769 B1 EP0099769 B1 EP 0099769B1
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EP
European Patent Office
Prior art keywords
plane
axis
image
optical
detector
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
Application number
EP19830401158
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English (en)
French (fr)
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EP0099769A1 (de
Inventor
Christian Pepin
Yves-Antoine Emmanuelli
Jean-Louis Beck
Christian Sez
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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Publication date
Application filed by Thomson CSF SA filed Critical Thomson CSF SA
Publication of EP0099769A1 publication Critical patent/EP0099769A1/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2253—Passive homing systems, i.e. comprising a receiver and do not requiring an active illumination of the target
    • 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
    • F41G7/22—Homing guidance systems
    • F41G7/2213—Homing guidance systems maintaining the axis of an orientable seeking head pointed at the target, e.g. target seeking gyro
    • 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
    • F41G7/22—Homing guidance systems
    • F41G7/2273—Homing guidance systems characterised by the type of waves
    • F41G7/2293—Homing guidance systems characterised by the type of waves using electromagnetic waves other than radio waves

Definitions

  • the present invention relates to a device for analyzing a spatial field for the angular localization of a radiating object in the field and in which the video image is formed by circular field scanning.
  • the invention applies more precisely to systems equipped with a detector strip as a photodetector or image sensor, and in which a circular analysis of the image of the instantaneous field observed is carried out.
  • a more particularly envisaged application is in the field of seeker for missiles, mainly infrared seeker with imaging or pseudo-imaging.
  • the axis of rotation is parallel to the axis of the receiving optics and an additional mirror is used to reflect the radiation towards the bar which is offset relative to the axis.
  • the axis of rotation is perpendicular to that of the optics and an internal mirror inclined at 45 ° on the optical axis returns the radiation towards the dihedral which reflects it towards the detector placed at the rear of an opening in the mirror.
  • the object of the invention is to provide a video image forming device in circular field scanning in which these drawbacks are avoided and which fits well in a gyro-stabilized version.
  • a self-directing missile device with four quadrant detector and equipped with anti-roll stabilization.
  • a receiving optical mirror is mounted on the gyroscopic router and is therefore driven in rotation; the connection with the center of suspen'sion is done by a ball mounting allowing the relative axial depointing.
  • the invention proposes to produce a video image formation device by circular field scanning, comprising a receiving optic which produces the image of the field observed in a plane perpendicular to the axis of the receiving optics, a photodetector device constituted a photodetector strip located in this plane and arranged along a radius of the circular field scan, and intermediate optical means for producing a circular image scan in this plane, these optical means using a straight reflective dihedral driven in rotation around an axis perpendicular to its edge and corresponding to the axis of the receiving optics, the video image forming device being characterized in that the receiving optics is constituted by means of a Cassegrain assembly comprising a main mirror which focuses the incident radiation on said photodetector strip by means of a secondary mirror mounted on the same optical axis, the secondary mirror re being constituted by said rotating dihedral.
  • FIG. 1 represents a video image forming device according to the invention, comprising a receiving optic 1 which produces the image of the field observed in a plane, a photodetector array 3 located in this plane and intermediate optical means using a right dihedron reflective 2 driven into rotation around an axis perpendicular to its edge to produce a circular scan by rotation of the image of the field in front of the bar 3 arranged radially.
  • the receiving optics is constituted by a Cassegrain assembly with a main mirror 1 which focuses the incident radiation via the secondary mirror 2 mounted on the same optical axis Z.
  • the secondary mirror is constituted by the rotating dihedron 2 , the axis of rotation of the reflecting dihedron corresponding to the optical axis Z of the Cassegrain assembly.
  • the radiation received after reflections on the mirrors 1 and 2 is focused in the plane of the bar 3.
  • the block 4 represents means for driving the reflecting dihedron in rotation 2.
  • the block 5 represents the processing and operating circuits of the SV video signal detected by the photodetector element strip 3.
  • this device has certain characteristics which are recalled with the aid of FIG. 2.
  • a longitudinal section plane called PNI non-inverting plane
  • the device forms a direct image of an object; thus the object OB has for image O'B 'of the same direction.
  • the inverting plane PI In a second longitudinal section plane, called the inverting plane PI and perpendicular to the previous one, the optical device forms an inverted image of an object; thus, the object OA will have the image O'A 'of reverse direction.
  • the growth on this diagram has not been taken into account. It appears that the device is equivalent to a symmetry with respect to a straight line in the image plane. If the optical device D is rotated by an angle 8, the image rotates in the same direction by a double angle of 26, this property being general for all these types of devices.
  • a right-angled dihedral consisting of two plane mirrors placed in an optical path thus provides a symmetrical image with respect to the line of intersection of the two faces of the dihedron, called the edge of the dihedron.
  • This property of geometric optics is well known and if we consider an axis of rotation perpendicular to the edge, we have an inverting plane containing the axis of rotation and perpendicular to the edge of the dihedral and a non-inverting plane containing the axis of rotation and the dihedral edge.
  • the mounting with right dihedral turning thus solves well the problem of the circular sweeping of the field.
  • the solution chosen which consists in replacing the secondary of the Cassegrain type optics by the dihedral whose edge takes the place of the secondary mirror is particularly advantageous in an application to a seeker with video imaging, given that the axis of rotation is finds it confused with the optical axis of the device.
  • the condition to check is that the edge of the dihedral passes through the axis of rotation and is perpendicular to this axis.
  • the dihedral is positioned symmetrically with respect to the axis of rotation but, for practical and production considerations, the symmetrical position will be the one chosen because it avoids having disadvantages on the optical plane on the one hand taking into account that the pupil would be asymmetrical, on the mechanical plane on the other hand in particular in a gyro-stabilized version as a result of the imbalance and balancing questions that this is likely to pose .
  • Figures 3 and 4 show the optical path of the light rays. It was considered that the angular field observed is between the extreme directions given by the rays R2 and R3, the radius R1 corresponding to the middle direction parallel to the optical axis Z of the system. The dihedral edge is perpendicular to the figure plane in Fig. 3 and passes through this plane in the case of FIG. 4.
  • the assembly includes additional optical elements, in particular an image recovery optic 7 which makes it possible to place the detector 3 further downstream on the Z axis. In a version according to FIG. 1 the detector would be placed at the focal plane indicated PF.
  • the Cassegrain assembly grouping the main mirror 1 and the secondary mirror formed by the rotating dihedral 2 focuses the field radiation on the focal plane PF where the image of the field will be located.
  • the optics 7 constituted by a converging lens makes it possible to take up the image of the field in the plane PF to reform it downstream in a plane where the photodetector bar 3 will be positioned.
  • This version corresponds to that of a fixed sensor carried by the missile body.
  • the lens 7 is not useful in its central part and this can possibly be hollowed out.
  • a spherical mirror 8 is provided, the center of curvature of which is located on the axis Z in the plane where the bar is positioned, so as to return the radiation reflected by the latter towards the detector.
  • the reflecting deposit is distributed on a spherical support, providing the transparent circular area necessary for the passage of useful radiation.
  • the mirror is located where a real pupil PR is formed.
  • the support can be produced using an element made of transparent material, glass for example, or using two opaque elements, metallic for example.
  • the mounting with the mirror 8 is useful in the case of a cooled infrared detector because it makes it possible to limit the noise resulting from the detection of the continuous background by the detector. This technique is described in French patent publication number 2,487,512 (filing no.
  • Fig. 5 relates to an achievement for a dihedral circular scanning seeker in which the detector or sensor is fixed, carried by the missile body.
  • the detector bar 3 is positioned on the cold table of a cooling device 10, for example a cryostat.
  • the bar is positioned at the center of suspension of the gyroscope which is indicated by the intersection of the Y axis with the Z axis, the Y axis being one of the axes of mechanical rotation of the gimbal.
  • the optical assembly 1 and 2 is driven in rotation by the gyroscopic router 11 which gives an angular speed of image analysis double the speed of rotation of the router. There is a slight difference in terms of the recovery optics vis-à-vis the representation. 3 and Fig.
  • this optic is constituted by two lenses, a lens 7A which transforms the beam coming from the focal plane into a parallel beam and a lens 7B which reconcentrates the beam at the level of the detector 3.
  • the spherical mirror 8 is constituted by a set of two mechanical parts 8A and 8B, the part 8B being integral with the transparent optics 7B which is hollowed out in its central part.
  • the bearings 12 make it possible to separate the terminal optics 7B-8A-8B from the rotation of the router.
  • the router 11 comprises an annular magnet 13 which undergoes the magnetic effects generated by the coils 14 said to be of precession and which are fixedly mounted on a mechanical support 15 which is integral with the body 16 of the missile.
  • the router 11 is decoupled from the frame 17 linked to the central gimbal by the ball bearings 12.
  • the second mechanical axis of the gimbal is perpendicular to the plane of the figure and not visible in the median plane of cut shown.
  • the rotation along the Y axis is decoupled from the body of the missile 16 by the ball bearings 18.
  • the secondary mirror 2 consisting of the right dihedron is supported by arms 19, for example two thin arms to mechanically couple it to the spinning top. Note also the presence of a diaphragm 20 which limits the entry of stray radiation.
  • Fig. 6 shows a second application to a seeker with circular dihedral scanning and in which this time the sensor is carried by the gimbal and no longer by the missile body, the detector 3 is thus secured to the angular deflection of the aiming axis Z and no longer from the longitudinal axis of the missile.
  • the detector will preferably consist of a detector strip with multiplexing integrated in the focal plane in order to minimize the number of connecting wires going to downstream processing circuits.
  • the optics are particularly simple since it comprises the main mirror of the aspheric Cassegrain, and the secondary mirror constituted by the dihedral 2. There is no dioptric element, the spectral band is therefore very wide.
  • the angular deflections of the aiming axis Z are not limited as in the case of FIG. 5 since the sensor is integral with the gyroscopic structure.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Radiation Pyrometers (AREA)

Claims (5)

1. Vorrichtung zur Erzeugung eines Videobildes durch kreisförmige Feldablenkung, mit einer Empfangsoptik (1), welche das Bild des beobachteten Feldes in einer Ebene senkrecht zur Achse (Z) der Empfangsoptik empfängt, einer Photodetektorvorrichtung, die aus einer Photodetektorzeile (3) gebildet ist, welche in dieser Ebene liegt und entlang einem Radius der kreisförmigen Feldablenkung angeordnet ist, und optischen zwischengeordneten Mitteln zur Erzeugung einer kreisförmigen Bildablenkung in dieser Ebene, wobei diese optischen Mittel ein aufrechtes reflektierendes Zweiflach (2) verwenden, welches um eine zu seiner Kante senkrechte Achse, die der Achse (Z) der Empfangsoptik entspricht, in Drehung versetzt wird, wobei die Vorrichtung zur Videobilderzeugung dadurch gekennzeichnet ist, daß die Empfangsoptik durch eine Cassegrain-Anordnung gebildet ist, welche einen Hauptspiegel (1) enthält, der die eintreffende Strahlung auf der genannten Photodetektorzeile (3) mittels eines Hilfsspiegels (2) fokussiert, welcher auf derselben optischen Achse (Z) angeordnet ist, wobei dieser Hilfsspiegel durch das rotierende Zweiflach gebildet ist.
2. Vorrichtung nach Anspruch 1, bei welcher ein zusätzliches optisches Element vorgesehen ist, um das in der Brennebene der Empfangsoptik erzeugte Feldbild einzufangen und dieses Bild in einer anderen Ebene erneut zu erzeugen, worin die Zeile liegt, wobei die Optik zum Einfangen des Bildes eine Konvergenzlinse ist, dadurch gekennzeichnet, daß diese Linse (7) mit der Cassegrain-Anordnung eine Zwischenebene zwischen der Linse und der Photodetektorzeile bestimmt, worin eine reelle kreisrunde Pupille (PR) gebildet wird, und daß sich in dieser Ebene ein sphärischer Spiegel (8) befindet, der mit einer kreisrunden transparenten Zone versehen ist, die der Pupille entspricht, um die Nutzstrahlung durchzulassen, wobei der sphärische Spiegel (8A, 8B) außerhalb dieser Zone reflektierend ist, um die von dem Detektor ausgehende Strahlung auf diesen zurückzuwerfen.
3. Vorrichtung nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, daß sie Kreiselstabilisierungsmittel für die optische Achse (Z) aufweist und daß das Zweiflach durch den Kreisel (11) der Kreiselanordnung angetrieben wird.
4. Vorrichtung nach Anspruch 3, verwendet zur Bildung eines Flugkörper-Zielsuchers mit beweglichem Fühler, der durch die Kreiselanordnung getragen wird.
5. Vorrichtung nach den kombinierten Ansprüchen 2 und 3, verwendet zur Bildung eines Flugkörper-Zielsuchers mit festem Fühler, dadurch gekennzeichnet, daß die Detektorzeile (3) in der Aufhängungsmitte der Kreiselanordnung positioniert und fest mit dem Körper des Flugkörpers verbunden ist.
EP19830401158 1982-06-18 1983-06-07 Vorrichtung zur Analyse eines räumlichen Feldes zur Winkelortung eines strahlenden Objektes Expired EP0099769B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8210708 1982-06-18
FR8210708A FR2528981B1 (fr) 1982-06-18 1982-06-18 Dispositif d'analyse d'un champ spatial pour la localisation angulaire d'un objet rayonnant

Publications (2)

Publication Number Publication Date
EP0099769A1 EP0099769A1 (de) 1984-02-01
EP0099769B1 true EP0099769B1 (de) 1987-05-20

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Application Number Title Priority Date Filing Date
EP19830401158 Expired EP0099769B1 (de) 1982-06-18 1983-06-07 Vorrichtung zur Analyse eines räumlichen Feldes zur Winkelortung eines strahlenden Objektes

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EP (1) EP0099769B1 (de)
DE (1) DE3371691D1 (de)
FR (1) FR2528981B1 (de)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2764402B1 (fr) * 1986-04-21 2003-02-21 Aerospatiale Systeme d'autoguidage pour missile
FR2688317B1 (fr) * 1987-03-09 1994-08-05 Thomson Csf Dispositif d'analyse spatiale a onde laser, notamment pour autodirecteur de missile.
FR2647540B1 (fr) * 1989-05-23 1994-03-25 Thomson Csf Dispositif de ralliement de missile
FR2670980A1 (fr) * 1990-12-20 1992-06-26 Thomson Csf Detecteur infrarouge a haute capacite d'identification, et camera thermique comportant un tel detecteur.
DE4135260C1 (de) * 1991-10-25 1993-02-25 Bodenseewerk Geraetetechnik Gmbh, 7770 Ueberlingen, De

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2418437A1 (de) * 1972-04-15 1975-10-30 Elektro Optik Gmbh & Co Kg Vorrichtung zur mittelpunkt-modulation in optischen trackern
US3927254A (en) * 1975-03-13 1975-12-16 Gen Dynamics Corp Optical seeker scanning system
US4266173A (en) * 1979-03-15 1981-05-05 The Boeing Company Roll compensated seeker head
FR2481794A1 (fr) * 1980-05-05 1981-11-06 Trt Telecom Radio Electr Dispositif optique d'analyse d'un champ spatial et de localisation angulaire d'un objet rayonnant dans ce champ

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DE3371691D1 (en) 1987-06-25
FR2528981A1 (fr) 1983-12-23
FR2528981B1 (fr) 1985-10-25
EP0099769A1 (de) 1984-02-01

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