EP0561163A1 - Système de prise de vues - Google Patents

Système de prise de vues 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
Authority
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
Other languages
German (de)
English (en)
Other versions
EP0561163B1 (fr
Inventor
Wladimir Sardanowsky
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.)
Airbus Defence and Space GmbH
Original Assignee
Deutsche Aerospace AG
Daimler Benz Aerospace AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Deutsche Aerospace AG, Daimler Benz Aerospace AG filed Critical Deutsche Aerospace AG
Publication of EP0561163A1 publication Critical patent/EP0561163A1/fr
Application granted granted Critical
Publication of EP0561163B1 publication Critical patent/EP0561163B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F41G7/222—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.

Landscapes

  • 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)
EP93102363A 1992-03-17 1993-02-16 Système de prise de vues Expired - Lifetime EP0561163B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4208516A DE4208516C2 (de) 1992-03-17 1992-03-17 Bilderzeugendes Suchkopfsystem
DE4208516 1992-03-17

Publications (2)

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

Family

ID=6454278

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93102363A Expired - Lifetime EP0561163B1 (fr) 1992-03-17 1993-02-16 Système de prise de vues

Country Status (3)

Country Link
US (1) US5333815A (fr)
EP (1) EP0561163B1 (fr)
DE (2) DE4208516C2 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2863079A1 (fr) * 2003-12-01 2005-06-03 Sagem Procede et dispositif de reconstitution d'image sur des barrettes de detecteurs
EP3546879A1 (fr) * 2018-03-26 2019-10-02 Simmonds Precision Products, Inc. Chercheur d'imagerie pour projectile gyrostabilisé
CN112114472A (zh) * 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 一种焦面像旋柔性导热装置及焦面像旋机构

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 (de) * 1997-02-21 2001-11-08 Lfk Gmbh Schwenkbarer Sucher
US6622100B2 (en) 2001-06-07 2003-09-16 Northrop Grumman Corporation Hyperspectral analysis tool
FR2852697B1 (fr) * 2003-03-21 2005-06-03 Dispositif compact d'imagerie matricielle infrarouge
IL162032A (en) * 2004-05-17 2009-05-04 Rafael Advanced Defense Sys Optical target search accessory for bullet

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0028966A1 (fr) * 1979-11-09 1981-05-20 Thomson-Brandt Armements Procédé de pilotage et de guidage de projectiles en phase terminale de vol
EP0033283A2 (fr) * 1980-01-29 1981-08-05 SOCIETE EUROPEENNE DE PROPULSION (S.E.P.) Société Anonyme dite: Système d'auto-guidage simplifié pour engin du type obus ou roquette
DE3300709A1 (de) * 1983-01-11 1984-07-12 Friedrich Dr. 8890 Aichach Schäff Flugkoerper zum bekaempfen von luftzielen
US4537370A (en) * 1983-11-02 1985-08-27 Ford Aerospace & Communications Corporation Optical growth compensator
EP0233080A2 (fr) * 1986-02-11 1987-08-19 Raytheon Company Autodirecteur infrarouge
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 (de) * 1980-03-01 1983-10-13 Eltro GmbH, Gesellschaft für Strahlungstechnik, 6900 Heidelberg Wärmebildgerät
DE3048496C1 (de) * 1980-12-22 1985-07-25 Eltro GmbH, Gesellschaft für Strahlungstechnik, 6900 Heidelberg Peilsystem
DE3435634A1 (de) * 1984-09-28 1986-04-10 Diehl GmbH & Co, 8500 Nürnberg Zielerfassungseinrichtung fuer flugkoerper
DE3609774A1 (de) * 1986-03-22 1987-09-24 Diehl Gmbh & Co Zielerfassungseinrichtung fuer flugkoerper
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 (fr) * 1979-11-09 1981-05-20 Thomson-Brandt Armements Procédé de pilotage et de guidage de projectiles en phase terminale de vol
EP0033283A2 (fr) * 1980-01-29 1981-08-05 SOCIETE EUROPEENNE DE PROPULSION (S.E.P.) Société Anonyme dite: Système d'auto-guidage simplifié pour engin du type obus ou roquette
DE3300709A1 (de) * 1983-01-11 1984-07-12 Friedrich Dr. 8890 Aichach Schäff Flugkoerper zum bekaempfen von luftzielen
US4537370A (en) * 1983-11-02 1985-08-27 Ford Aerospace & Communications Corporation Optical growth compensator
EP0233080A2 (fr) * 1986-02-11 1987-08-19 Raytheon Company Autodirecteur infrarouge
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 (fr) * 2003-12-01 2005-06-03 Sagem Procede et dispositif de reconstitution d'image sur des barrettes de detecteurs
EP1538416A1 (fr) * 2003-12-01 2005-06-08 Sagem SA Procédé et dispositif de reconstruction d'image sur des barrettes de détecteurs
EP3546879A1 (fr) * 2018-03-26 2019-10-02 Simmonds Precision Products, Inc. Chercheur d'imagerie pour projectile gyrostabilisé
US10877489B2 (en) 2018-03-26 2020-12-29 Simmonds Precision Products, Inc. Imaging seeker for a spin-stabilized projectile
CN112114472A (zh) * 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 一种焦面像旋柔性导热装置及焦面像旋机构

Also Published As

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

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