EP0561163A1 - Image pickup system - Google Patents

Image pickup system Download PDF

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Publication number
EP0561163A1
EP0561163A1 EP93102363A EP93102363A EP0561163A1 EP 0561163 A1 EP0561163 A1 EP 0561163A1 EP 93102363 A EP93102363 A EP 93102363A EP 93102363 A EP93102363 A EP 93102363A EP 0561163 A1 EP0561163 A1 EP 0561163A1
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EP
European Patent Office
Prior art keywords
missile
image
axis
rows
recording system
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.)
Granted
Application number
EP93102363A
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German (de)
French (fr)
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EP0561163B1 (en
Inventor
Wladimir Sardanowsky
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Airbus Defence and Space GmbH
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Deutsche Aerospace AG
Daimler Benz Aerospace AG
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Publication of EP0561163A1 publication Critical patent/EP0561163A1/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
    • F41G7/22—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
    • F41G7/222—Homing guidance systems for spin-stabilized missiles
    • 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 invention relates to an image recording system for a missile rotating about a main axis, according to the preamble of claim 1.
  • Infrared image recording systems for missiles which consist of a missile-fixed recording optics and an opto-electrical detector mosaic which is likewise firmly connected to the missile and which is composed of detector elements which are distributed across the image plane of the recording optics and are scanned line by line.
  • Such recording systems require a very high number of detector elements for satisfactory image resolution and are accordingly expensive.
  • infrared recording devices are known (DE 30 07 893 A1; DE 30 48 496 C1) in which the field of view of the recording optics is pivoted mechanically, for example with the aid of an oscillating deflecting mirror or a gyroscopic drive, over the visual scene of interest and thereby linear or circular image scanning is achieved with a single row of detectors extending over the image field of the recording optics.
  • the mechanical effort for an exact control of the image movement and the computing effort for the correlation of the individual image signals to the corresponding pixels are considerable.
  • the object of the invention is to design the image recording system of the type mentioned at the outset in such a way that in a structurally and signal-technically simple manner and with comparatively few detector elements, perfect image quality with high image resolution is achieved.
  • a complicated mechanical image control is dispensed with through a targeted use of the self-rotation of the missile in connection with the detector arrangement which is radial to the missile axis and consists of comparatively few individual elements in a structurally very simple manner with continuous image rotation in the manner with a polar image scan with respect to the missile axis achieved that a non-rotating image of the visual scene of interest is obtained from the image signals in accordance with the respective rotational position of the missile and the radial distance of the individual detector elements from the missile axis of rotation with little computation effort and a high image resolution.
  • the image recording device according to the invention is outstandingly suitable for rotating missiles, but of course also for other moving carrier systems which carry out a continuous rotation about a main axis.
  • each angularly offset with respect to the missile axis are provided, as a result of which a frequency-selective selection is very simple, namely by appropriate selection of the frequency sensitivity of the individual rows of detectors Image scanning (claim 2) and / or an image scanning frequency increased compared to the rotational frequency of the missile can be achieved.
  • the latter can preferably be pivotably moved with respect to the missile axis, while the rows of detectors are expediently rigidly connected to the missile for reasons of structural simplification, and in the case of a pivotable fastening of the imaging optics preferably according to claim 6 are each formed in a circular arc with the center of curvature in the swivel center of the receiving optics.
  • the detector arrangement according to the invention consisting of one or at most a few missile-fixed detector rows, is provided for infrared image scanning, then it is a further advantage of the invention that complex cooling measures, such as are otherwise used for infrared imaging devices with large or rotating surfaces Detector arrangements are required.
  • infrared imaging optics 6 which is coaxial with its optical axis to the missile axis and consists of individual elements fixed to the missile. which has a variable focal length in the manner of a multi-lens zoom lens, and an infrared detector arrangement 8 which is likewise fixed in the missile in the image plane of the recording optics 6 and which is connected to electronics 10 for processing the electrical image signals generated by the detector arrangement 8 and a central cyrostatic cooling Owns 12.
  • the detector arrangement 8 consists of a single, linear row 14 of individual detector elements 16, which extends radially outward from the missile axis A to the edge of the image field of the imaging optics 6, that is to say in terms of its length and number of elements, approximately half a line of the image field covering detector mosaic corresponds to the same image resolution. Since the row of detectors 14 rotates in the same direction as the missile 2 around the missile axis A (in the direction of rotation R), there is a rotary image movement of the fixed scene image relative to the detector row 14 with a polar image scan such that the scene image is scanned by the individual detector elements 16 on circles which are concentric with one another .
  • the assigned image points can be determined on the basis of a polar coordinate representation in a very simple manner in terms of signal processing technology in accordance with the radial distance of the respective detector element 16 from the missile axis A and the rotational position of the missile 2 and thus the detector row 14 at the time of reading.
  • an image reproduction of the visual scene of interest, unaffected by the missile rotation - shown in detail in FIG. 2 - is achieved, for example in visual form on a screen or by data transmission to an automatic image monitoring device.
  • the receiving optics 6 are arranged on a missile-fixed carrier 18 such that they can be adjusted in an angularly movable manner about a swivel axis 20 lying on the missile axis A, while the row of detectors (s) continue to be rigidly connected to the missile, but is designed to be circular in shape concentrically to the swivel axis 20 and are extended so far in the pivoting direction S of the receiving optics 6 that they extend to the outer edge of the image field in each setting position of the receiving optics 6.
  • the scanned visual scene can be changed or a target area once sighted can be kept in the field of view of the optical system 6 by a swivel position adjustment of the optical system 6, even if the flight direction and / or the spatial orientation of the missile axis A changes during the flight.
  • the image recording system according to the invention is not necessarily tied to rotating missiles, but equally also for other carrier systems that continuously rotate about a main axis, e.g. Torpedoes, usable.

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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)

Abstract

In the case of an image recording system for a missile (2) which rotates about a major axis (A) and has recording optics (6) and a detector arrangement (8), which is located in the imaging plane of the recording optics, for producing electrical image signals which are processed taking into account the respective rotation position of the missile (2), in order to achieve a high image resolution in a manner which is very simple mechanically and in terms of signal processing, the detector arrangement (8) and the recording optics (6) are arranged such that they rotate about the missile major axis (A) with their optical axis moving identically to the missile (2), and the detector arrangement (8) consists of one or more rows of detectors which extend from the edge of the imaging area of the recording optics (6) to the missile axis (A). <IMAGE>

Description

Die Erfindung bezieht sich auf ein Bildaufnahmesystem für einen um eine Hauptachse rotierenden Flugkörper, nach dem Oberbegriff des Patentanspruchs 1.The invention relates to an image recording system for a missile rotating about a main axis, according to the preamble of claim 1.

Es sind Infrarot-Bildaufnahmesysteme für Flugkörper bekannt, die aus einer flugkörperfesten Aufnahmeoptik und einem ebenfalls mit dem Flugkörper fest verbundenen, opto-elektrischen Detektormosaik bestehen, welches aus flächig in der Bildebene der Aufnahmeoptik verteilten, zeilenweise abgetasteten Detektorelementen zusammengesetzt ist.
Derartige Aufnahmesysteme erfordern für eine zufriedenstellende Bildauflösung eine sehr hohe Anzahl von Detektorelementen und sind dementsprechend kostspielig.Infrared image recording systems for missiles are known which consist of a missile-fixed recording optics and an opto-electrical detector mosaic which is likewise firmly connected to the missile and which is composed of detector elements which are distributed across the image plane of the recording optics and are scanned line by line.
Such recording systems require a very high number of detector elements for satisfactory image resolution and are accordingly expensive.

Ferner sind Infrarot-Aufnahmegeräte bekannt (DE 30 07 893 A1; DE 30 48 496 C1) bei denen das Sehfeld der Aufnahmeoptik mechanisch, etwa mit Hilfe eines oszilierenden Umlenkspiegels oder eines gyroskopischen Antriebs, über die interessierende Sehszene verschwenkt und dadurch eine lineare oder zirkulare Bildabtastung mit einer einzigen, sich über das Bildfeld der Aufnahmeoptik erstreckenden Detektorreihe erreicht wird. Der mechanische Aufwand für eine exakte Steuerung der Bildbewegung und der Rechenaufwand für die Korrelation der einzelnen Bildsignale zu den entsprechenden Bildpunkten sind erheblich.Furthermore, infrared recording devices are known (DE 30 07 893 A1; DE 30 48 496 C1) in which the field of view of the recording optics is pivoted mechanically, for example with the aid of an oscillating deflecting mirror or a gyroscopic drive, over the visual scene of interest and thereby linear or circular image scanning is achieved with a single row of detectors extending over the image field of the recording optics. The mechanical effort for an exact control of the image movement and the computing effort for the correlation of the individual image signals to the corresponding pixels are considerable.

Aufgabe der Erfindung ist es, das Bildaufnahmesystem der eingangs genannten Art so auszubilden, daß auf baulich und signaltechnisch einfache Weise und mit vergleichsweise wenigen Detektorelementen eine einwandfreie Bildqualität mit einer hohen Bildauflösung erzielt wird.The object of the invention is to design the image recording system of the type mentioned at the outset in such a way that in a structurally and signal-technically simple manner and with comparatively few detector elements, perfect image quality with high image resolution is achieved.

Diese Aufgabe wird erfindungsgemäß durch das im Patentanspruch 1 gekennzeichnete Bildaufnahmesystem gelöst.This object is achieved by the image recording system characterized in claim 1.

Erfindungsgemäß wird unter Verzicht auf eine komplizierte, mechanische Bildsteuerung durch eine gezielte Ausnutzung der Eigenrotation des Flugkörpers in Verbindung mit der zur Flugkörperachse radialen, aus vergleichsweise wenigen Einzelelementen bestehenden Detektoranordnung auf konstruktiv sehr einfache Weise eine kontinuierliche Bilddrehung mit einer hinsichtlich der Flugkörperachse polaren Bildabtastung in der Weise erreicht, daß aus den Bildsignalen nach Maßgabe der jeweiligen Drehlage des Flugkörpers sowie des radialen Abstands der einzelnen Detektorelemente von der Flugkörper-Rotationsachse mit geringem Rechenaufwand und einer hohen Bildauflösung eine nicht-rotierende Abbildung der interessierenden Sehszene erhalten wird. Das erfindungsgemäße Bildaufnahmegerät ist wegen seiner einfachen Bauweise und seiner hohen Bildqualität hervorragend für rotierende Flugkörper, aber natürlich auch für andere bewegte Trägersysteme geeignet, die eine kontinuierliche Rotation um eine Hauptachse ausführen.According to the invention, a complicated mechanical image control is dispensed with through a targeted use of the self-rotation of the missile in connection with the detector arrangement which is radial to the missile axis and consists of comparatively few individual elements in a structurally very simple manner with continuous image rotation in the manner with a polar image scan with respect to the missile axis achieved that a non-rotating image of the visual scene of interest is obtained from the image signals in accordance with the respective rotational position of the missile and the radial distance of the individual detector elements from the missile axis of rotation with little computation effort and a high image resolution. Because of its simple construction and its high image quality, the image recording device according to the invention is outstandingly suitable for rotating missiles, but of course also for other moving carrier systems which carry out a continuous rotation about a main axis.

In weiterer vorteilhafter Ausgestaltung der Erfindung sind gemäß den Ansprüchen 2 und 3 anstatt einer einzigen, vorzugsweise mehrere, jeweils bezüglich der Flugkörperachse winkelig versetzt zueinander angeordnete Detektorreihen vorgesehen, wodurch sich auf sehr einfache Weise, nämlich durch entsprechende Wahl der Frequenzempfindlichkeit der einzelnen Detektorreihen, eine frequenzselektive Bildabtastung (Anspruch 2) und/oder eine gegenüber der Rotationsfrequenz des Flugkörpers erhöhte Bildabtastfrequenz erzielen läßt.In a further advantageous embodiment of the invention, instead of a single, preferably a plurality of rows of detectors, each angularly offset with respect to the missile axis, are provided, as a result of which a frequency-selective selection is very simple, namely by appropriate selection of the frequency sensitivity of the individual rows of detectors Image scanning (claim 2) and / or an image scanning frequency increased compared to the rotational frequency of the missile can be achieved.

Um das Sehfeld der Aufnahmeoptik verändern zu können, ist diese gemäß Anspruch 4 vorzugsweise bezüglich der Flugkörperachse schwenkbeweglich einstellbar, während die Detektorreihen aus Gründen einer baulichen Vereinfachung gemäß Anspruch 5 zweckmäsßigerweise starr mit dem Flugkörper verbunden und im Falle einer schwenkbaren Befestigung der Aufnahmeoptik vorzugsweise gemäß Anspruch 6 jeweils kreisbogenförmig mit dem Krümmungsmittelpunkt im Schwenkzentrum der Aufnahmeoptik ausgebildet sind.In order to be able to change the field of view of the imaging optics, the latter can preferably be pivotably moved with respect to the missile axis, while the rows of detectors are expediently rigidly connected to the missile for reasons of structural simplification, and in the case of a pivotable fastening of the imaging optics preferably according to claim 6 are each formed in a circular arc with the center of curvature in the swivel center of the receiving optics.

Ist, wie gemäß Anspruch 7 bevorzugt, die erfindungsgemäße, aus einer oder allenfalls wenigen flugkörperfesten Detektorreihen bestehende Detektoranordnung zur Infrarot-Bildabtastung vorgesehen, so zeigt sich als weiterer Vorteil der Erfindung, daß aufwendige Kühlmaßnahmen, wie sie sonst für Infrarot-Bildgeräte mit großflächigen oder rotierenden Detektoranordnungen erforderlich sind, entfallen.If, as preferred according to claim 7, the detector arrangement according to the invention, consisting of one or at most a few missile-fixed detector rows, is provided for infrared image scanning, then it is a further advantage of the invention that complex cooling measures, such as are otherwise used for infrared imaging devices with large or rotating surfaces Detector arrangements are required.

Um sowohl die Gesamtszene wie auch interessierende Szenenausschnitte mit hoher Bildauflösung abbilden zu können, empfiehlt es sich schließlich gemäß Anspruch 8, eine Aufnahmeoptik mit kontinuierlich veränderlicher Brennweite zu verwenden.In order to be able to depict both the entire scene as well as scene sections of interest with high image resolution, it is finally recommended according to claim 8 to use a recording optics with a continuously changing focal length.

Die Erfindung wird nunmehr anhand mehrerer Ausführungsbeispiele in Verbindung mit den Zeichnungen näher erläutert. Es zeigen in stark schematisierter Darstellung

Fig. 1
einen Längsschnitt eines am Bugende eines Flugkörpers angeordneten Bildaufnahmesystems;
Fig. 2
eine einzelne Detektorreihe des Bildaufnahmesystems gemäß Fig. 1 mit polarer Bildabtastung sowie einen Ausschnitt einer sich hieraus ergebenden Abbildung;
Fig. 3
eine Anordnung mehrerer, im gleichen Frequenzbereich empfindlicher Detektorreihen zur Erhöhung der Bildabtastfrequenz;
Fig. 4
eine der Fig. 3 entsprechende Darstellung einer sowohl zur Erhöhung der Bildabtastfrequenz als auch zur Bildabtastung in unterschiedlichen Freuqenzbereichen aus mehreren Detektorreihen bestehenden Detektoranordnung; und
Fig. 5
eine Modifikation des Bildaufnahmesystems gemäß Fig. 1 mit einer schwenkbeweglich einstellbaren Aufnahmeoptik.
The invention will now be explained in more detail using several exemplary embodiments in conjunction with the drawings. They show in a highly schematic representation
Fig. 1
a longitudinal section of an imaging system arranged at the bow end of a missile;
Fig. 2
a single row of detectors of the image recording system according to FIG 1 with polar image scanning and a section of a resulting image.
Fig. 3
an arrangement of several, in the same frequency range sensitive detector rows to increase the image sampling frequency;
Fig. 4
3 a representation corresponding to FIG. 3 of a detector arrangement consisting of several detector rows both for increasing the image sampling frequency and for image sampling in different frequency ranges; and
Fig. 5
a modification of the image recording system according to FIG. 1 with a pivoting adjustable recording optics.

Das Bildaufnahmesystem gemäß Fig. 1, welches am vorderen Ende eines um seine Längsachse A-A rotierenden Flugkörpers 2 im Schutze einer Infrarot-Kuppel 4 angeordnet ist, enthält als Hauptbestandteile eine mit ihrer optischen Achse zur Flugkörperachse koaxiale, aus flugkörperfesten Einzelelementen bestehende Infrarot-Aufnahmeoptik 6, die nach Art eines mehrlinsigen Zoomobjektivs eine veränderliche Brennweite besitzt, sowie eine in der Bildeebene der Aufnahmeoptik 6 ebenfalls flugkörperfest angeordnete Infrarot-Detektoranordnung 8, die an eine Elektronik 10 zur Verarbeitung der von der Detektoranordnung 8 erzeugten, elektrischen Bildsignale angeschlossen ist und eine zentrale kyrostatische Kühlung 12 besitzt.1, which is arranged at the front end of a missile 2 rotating about its longitudinal axis AA in the protection of an infrared dome 4, contains the main components of an infrared imaging optics 6 which is coaxial with its optical axis to the missile axis and consists of individual elements fixed to the missile. which has a variable focal length in the manner of a multi-lens zoom lens, and an infrared detector arrangement 8 which is likewise fixed in the missile in the image plane of the recording optics 6 and which is connected to electronics 10 for processing the electrical image signals generated by the detector arrangement 8 and a central cyrostatic cooling Owns 12.

Gemäß Fig. 2 besteht die Detektoranordnung 8 aus einer einzigen, linearen Reihe 14 aus einzelnen Detektorelementen 16, die sich von der Flugkörperachse A radial nach außen bis zum Bildfeldrand der Aufnahmeoptik 6 erstreckt, also in ihrer Länge und Elementenanzahl etwa einer Halbzeile eines das Bildfeld flächig abdeckenden Detektormosaiks gleicher Bildauflösung entspricht. Da die Detektorreihe 14 bewegungsgleich zum Flugkörper 2 um die Flugkörperachse A (in Drehrichtung R) umläuft, entsteht eine rotative Bildbewegung des raumfesten Szenenbildes relativ zur Detektorreihe 14 mit einer polaren Bildabtastung derart, daß das Szenenbild von den einzelnen Detektorelementen 16 auf zueinander konzentrischen Kreisen abgetastet wird. Aus dem von den Detektorelementen 16 erzeugten Bildsignalen lassen sich auf der Basis einer Polarkoordinatendarstellung auf signalverarbeitungstechnisch sehr einfache Weise die zugeordneten Bildpunkte nach Maßgabe des Radialabstandes des jeweiligen Detektorelements 16 von der Flugkörperachse A und der Drehlage des Flugkörpers 2 und damit der Detektorreihe 14 im Ablesezeitpunkt ermitteln. Auf diese Weise wird eine von der Flugkörperrotation unbeeinflußte - in Fig. 2 ausschnittweise dargestellte - Bildwiedergabe der interessierenden Sehszene, etwa in visueller Form auf einem Bildschirm oder durch Datenübermittlung an ein automatisches Bildüberwachungsgerät, erreicht.2, the detector arrangement 8 consists of a single, linear row 14 of individual detector elements 16, which extends radially outward from the missile axis A to the edge of the image field of the imaging optics 6, that is to say in terms of its length and number of elements, approximately half a line of the image field covering detector mosaic corresponds to the same image resolution. Since the row of detectors 14 rotates in the same direction as the missile 2 around the missile axis A (in the direction of rotation R), there is a rotary image movement of the fixed scene image relative to the detector row 14 with a polar image scan such that the scene image is scanned by the individual detector elements 16 on circles which are concentric with one another . From the image signals generated by the detector elements 16, the assigned image points can be determined on the basis of a polar coordinate representation in a very simple manner in terms of signal processing technology in accordance with the radial distance of the respective detector element 16 from the missile axis A and the rotational position of the missile 2 and thus the detector row 14 at the time of reading. In this way, an image reproduction of the visual scene of interest, unaffected by the missile rotation - shown in detail in FIG. 2 - is achieved, for example in visual form on a screen or by data transmission to an automatic image monitoring device.

Während bei Anordnung einer einzelnen Detektorreihe 14 das Bildfeld der Aufnahmeoptik 6 bei jedem Umlauf des Flugkörpers 2 je einmal abgetastet wird, ist es ohne weiteres auch möglich, die Bildabtastrate gegenüber der Rotationsfrequenz zu vervielfachen, etwa gemäß Fig. 3 dadurch zu verdreifachen, daß anstelle einer einzigen drei radial zur Flugkörperachse A mit gleichförmigem Winkelabstand verlaufende Detektorreihen 14 A, B und C vorgesehen sind. Wahlweise oder gemäß Fig. 4 zusätzlich kann die Bildabtastung auch in unterschiedlichen Frequenzbereichen erfolgen, wobei für jeden Frequenzbereich eine oder - bei einer gegenüber der Rotationsfrequenz erhöhten Bildabtastrate gemäß Fig. 4 - mehrere Detektorreihen 14, nämlich die Detektorreihen 14.1 A ... C für einen ersten und die Detektorreihen 14.2 A ... C für einen zweiten Frequenzbereich vorgesehen sind.While the arrangement of a single row of detectors 14 scans the image field of the optical system 6 once each time the missile 2 rotates, it is also easily possible to multiply the image sampling rate compared to the rotation frequency, for example by tripling it according to FIG. 3, by using instead of one only three detector rows 14 A, B and C running radially to the missile axis A with a uniform angular distance are provided. Optionally or in accordance with FIG. 4, the image can also be scanned in different frequency ranges, one for each frequency range or, in the case of an image scanning rate as shown in FIG. 4, which is higher than the rotation frequency, several detector rows 14, namely the detector rows 14.1 A ... C for one first and the detector rows 14.2 A ... C are provided for a second frequency range.

Gemäß der in Fig. 5 gezeigten Modifikation ist die Aufnahmeoptik 6 an einem flugkörperfesten Träger 18 um eine auf der Flugkörperachse A liegende Schwenkachse 20 winkelbeweglich einstellbar angeordnet, während die Detektorreihe(n) weiterhin starr mit dem Flugkörper verbunden, aber konzentrisch zur Schwenkachse 20 kreisbogenförmig ausgebildet und in Schwenkrichtung S der Aufnahmeoptik 6 soweit verlängert sind, daß sie in jeder Einstellage der Aufnahmeoptik 6 bis zum äußeren Bildfeldrand reichen. Durch eine Schwenklagenverstellung der Aufnahmeoptik 6 kann die abgetastete Sehszene verändert oder ein einmal anvisiertes Zielgebiet weiter im Sehfeld der Aufnahmeoptik 6 gehalten werden, selbst wenn sich die Flugrichtung und/oder die räumliche Ausrichtung der Flugkörperachse A während des Fluges verändert.According to the modification shown in FIG. 5, the receiving optics 6 are arranged on a missile-fixed carrier 18 such that they can be adjusted in an angularly movable manner about a swivel axis 20 lying on the missile axis A, while the row of detectors (s) continue to be rigidly connected to the missile, but is designed to be circular in shape concentrically to the swivel axis 20 and are extended so far in the pivoting direction S of the receiving optics 6 that they extend to the outer edge of the image field in each setting position of the receiving optics 6. The scanned visual scene can be changed or a target area once sighted can be kept in the field of view of the optical system 6 by a swivel position adjustment of the optical system 6, even if the flight direction and / or the spatial orientation of the missile axis A changes during the flight.

Das erfindungsgemäße Bildaufnahmesystem ist nicht unbedingt an rotierende Flugkörper gebunden, sondern gleichermaßen auch für andere, kontinuierlich um eine Hauptachse rotierende Trägersysteme, z.B. Torpedos, verwendbar.The image recording system according to the invention is not necessarily tied to rotating missiles, but equally also for other carrier systems that continuously rotate about a main axis, e.g. Torpedoes, usable.

Claims (8)

Bildaufnahmesystem für einen um eine Hauptachse rotierenden Flugkörper,
mit einer Aufnahmeoptik und einer in der Bildebene der Aufnahmeoptik befindlichen Detektoranordnung zur Erzeugung von elektrischen, unter Berücksichtigung der jeweiligen Drehlage des Flugkörpers verarbeiteten Bildsignalen,
dadurch gekennzeichnet, daß die Detektoranordnung (8) und die Aufnahmeoptik (6) mit ihrer optischen Achse bewegungsgleich zum Flugkörper (2) um die Flugkörper-Hauptachse (A) rotierend angeordnet sind und die Detektoranordnung aus einer oder mehreren, sich zur Flugkörperachse hin erstreckenden Detektorreihen (14) besteht.Image acquisition system for a missile rotating around a main axis,
with an optical system and a detector arrangement located in the image plane of the optical system for generating electrical image signals processed taking into account the respective rotational position of the missile,
characterized in that the detector arrangement (8) and the receiving optics (6) are arranged with their optical axis in rotation with the missile (2) rotating about the main missile axis (A) and the detector arrangement consists of one or more rows of detectors extending towards the missile axis (14) exists. Bildaufnahmesystem nach Anspruch 1,
dadurch gekennzeichnet, daß zur frequenzselektiven Bildabtastung mehrere, jeweils auf unterschiedliche Frequenzbereiche ansprechende, bezüglich der Flugkörperachse (A) winkelig versetzt zueinander angeordnete Detektorreihen (14.1 und 14.2) vorgesehen sind (Fig. 4).Image recording system according to claim 1,
characterized in that a plurality of detector rows (14.1 and 14.2) are arranged for frequency-selective image scanning, each responding to different frequency ranges and angularly offset with respect to the missile axis (A) (FIG. 4). Bildaufnahmesystem nach Anspruch 1 oder 2,
dadurch gekennzeichnet, daß zur Erzielung einer gegenüber der Rotationsfrequenz erhöhten Bildabtastrate mehrere, auf den gleichen Frequenzbereich ansprechende, bezüglich der Flugkörper-Achse (A) winkelig versetzt zueinander angeordnete Detektorreihen (14 A, 14 B, 14 C) vorgesehen sind (Fig. 3).Image recording system according to claim 1 or 2,
characterized in that, in order to achieve an image sampling rate that is higher than the rotation frequency, several detector rows (14 A, 14 B, 14 C), which respond to the same frequency range and are angularly offset with respect to one another with respect to the missile axis (A), are provided (FIG. 3) . Bildaufnahmesystem nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, daß die Aufnahmeoptik (6) bezüglich der Flugkörperachse (A) schwenkbeweglich einstellbar ist (Fig. 5).Image recording system according to one of the preceding claims,
characterized in that the receiving optics (6) can be pivoted with respect to the missile axis (A) (Fig. 5). Bildaufnahmesystem nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, daß die Detektorreihen (14) starr am Flugkörper (2) befestigt sind.Image recording system according to one of the preceding claims,
characterized in that the rows of detectors (14) are rigidly attached to the missile (2). Bildaufnahmesystem nach den Ansprüchen 4 und 5,
dadurch gekennzeichnet, daß die Detektorreihen (14) jeweils kreisbogenförmig mit dem Krümmungsmittelpunkt im Schwenkzentrum (20) der Aufnahmeoptik (6) ausgebildet sind (Fig. 5).Image recording system according to claims 4 and 5,
characterized in that the rows of detectors (14) are each formed in a circular arc with the center of curvature in the pivot center (20) of the optical system (6) (FIG. 5). Bildaufnahmesystem nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, daß als Detektorreihen (14) Infrarotdetektoren vorgesehen sind.Image recording system according to one of the preceding claims,
characterized in that infrared detectors are provided as rows of detectors (14). Bildaufnahmesystem nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, daß die Aufnahmeoptik (6) eine kontinuierlich veränderliche Brennweite aufweist.Image recording system according to one of the preceding claims,
characterized in that the taking optics (6) have a continuously variable focal length.
EP93102363A 1992-03-17 1993-02-16 Image pickup system Expired - Lifetime EP0561163B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4208516A DE4208516C2 (en) 1992-03-17 1992-03-17 Imaging seeker system
DE4208516 1992-03-17

Publications (2)

Publication Number Publication Date
EP0561163A1 true EP0561163A1 (en) 1993-09-22
EP0561163B1 EP0561163B1 (en) 1997-05-28

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US (1) US5333815A (en)
EP (1) EP0561163B1 (en)
DE (2) DE4208516C2 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2863079A1 (en) * 2003-12-01 2005-06-03 Sagem Tomography image reconstruction process for use in medical field, involves reconstructing image vector from signal vectors output from detector bars, where coefficient of matrix for detector bars are constructed
EP3546879A1 (en) * 2018-03-26 2019-10-02 Simmonds Precision Products, Inc. Imaging seeker for a spin-stabilized projectile
CN112114472A (en) * 2020-08-24 2020-12-22 中国科学院长春光学精密机械与物理研究所 Focal plane image rotating flexible heat conduction device and focal plane image rotating mechanism

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5529262A (en) * 1993-06-23 1996-06-25 Horwath; Tibor G. Guidance seeker for small spinning projectiles
US5669581A (en) * 1994-04-11 1997-09-23 Aerojet-General Corporation Spin-stabilized guided projectile
US6079665A (en) * 1996-11-04 2000-06-27 Trw Inc. Hyperspectral air-to-air missile seeker
DE19706958C2 (en) * 1997-02-21 2001-11-08 Lfk Gmbh Swiveling viewfinder
US6622100B2 (en) 2001-06-07 2003-09-16 Northrop Grumman Corporation Hyperspectral analysis tool
FR2852697B1 (en) * 2003-03-21 2005-06-03 COMPACT DEVICE FOR INFRARED MATRIX IMAGING
IL162032A (en) * 2004-05-17 2009-05-04 Rafael Advanced Defense Sys Projectile optical seeker

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0028966A1 (en) * 1979-11-09 1981-05-20 Thomson-Brandt Armements Method of piloting and guiding missiles in terminal flight
EP0033283A2 (en) * 1980-01-29 1981-08-05 SOCIETE EUROPEENNE DE PROPULSION (S.E.P.) Société Anonyme dite: Simplified self-steering system for a missile such as a shell or rocket
DE3300709A1 (en) * 1983-01-11 1984-07-12 Friedrich Dr. 8890 Aichach Schäff Missile for combatting air targets
US4537370A (en) * 1983-11-02 1985-08-27 Ford Aerospace & Communications Corporation Optical growth compensator
EP0233080A2 (en) * 1986-02-11 1987-08-19 Raytheon Company Infrared seeker
US4703179A (en) * 1987-04-02 1987-10-27 Ford Aerospace & Communications Corporation Sensor for hemispherical applications

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3007893C2 (en) * 1980-03-01 1983-10-13 Eltro GmbH, Gesellschaft für Strahlungstechnik, 6900 Heidelberg Thermal imaging device
DE3048496C1 (en) * 1980-12-22 1985-07-25 Eltro GmbH, Gesellschaft für Strahlungstechnik, 6900 Heidelberg DF system
DE3435634A1 (en) * 1984-09-28 1986-04-10 Diehl GmbH & Co, 8500 Nürnberg TARGET DETECTING DEVICE FOR missile
DE3609774A1 (en) * 1986-03-22 1987-09-24 Diehl Gmbh & Co TARGET DETECTING DEVICE FOR missile
US4717822A (en) * 1986-08-04 1988-01-05 Hughes Aircraft Company Rosette scanning surveillance sensor

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0028966A1 (en) * 1979-11-09 1981-05-20 Thomson-Brandt Armements Method of piloting and guiding missiles in terminal flight
EP0033283A2 (en) * 1980-01-29 1981-08-05 SOCIETE EUROPEENNE DE PROPULSION (S.E.P.) Société Anonyme dite: Simplified self-steering system for a missile such as a shell or rocket
DE3300709A1 (en) * 1983-01-11 1984-07-12 Friedrich Dr. 8890 Aichach Schäff Missile for combatting air targets
US4537370A (en) * 1983-11-02 1985-08-27 Ford Aerospace & Communications Corporation Optical growth compensator
EP0233080A2 (en) * 1986-02-11 1987-08-19 Raytheon Company Infrared seeker
US4703179A (en) * 1987-04-02 1987-10-27 Ford Aerospace & Communications Corporation Sensor for hemispherical applications

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2863079A1 (en) * 2003-12-01 2005-06-03 Sagem Tomography image reconstruction process for use in medical field, involves reconstructing image vector from signal vectors output from detector bars, where coefficient of matrix for detector bars are constructed
EP1538416A1 (en) * 2003-12-01 2005-06-08 Sagem SA Method and device for reconstruction of images on detector bars
EP3546879A1 (en) * 2018-03-26 2019-10-02 Simmonds Precision Products, Inc. Imaging seeker for a spin-stabilized projectile
US10877489B2 (en) 2018-03-26 2020-12-29 Simmonds Precision Products, Inc. Imaging seeker for a spin-stabilized projectile
CN112114472A (en) * 2020-08-24 2020-12-22 中国科学院长春光学精密机械与物理研究所 Focal plane image rotating flexible heat conduction device and focal plane image rotating mechanism

Also Published As

Publication number Publication date
EP0561163B1 (en) 1997-05-28
DE4208516C2 (en) 1994-03-03
US5333815A (en) 1994-08-02
DE4208516A1 (en) 1993-09-23
DE59306549D1 (en) 1997-07-03

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