EP0882941B1 - Infrarot-Suchkopf für zielsuchende Flugkörper - Google Patents
Infrarot-Suchkopf für zielsuchende Flugkörper Download PDFInfo
- Publication number
- EP0882941B1 EP0882941B1 EP98109319A EP98109319A EP0882941B1 EP 0882941 B1 EP0882941 B1 EP 0882941B1 EP 98109319 A EP98109319 A EP 98109319A EP 98109319 A EP98109319 A EP 98109319A EP 0882941 B1 EP0882941 B1 EP 0882941B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- detector
- radiation
- seeker head
- infrared seeker
- infrared
- 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
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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
- F41G7/2213—Homing guidance systems maintaining the axis of an orientable seeking head pointed at the target, e.g. target seeking gyro
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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
- F41G7/224—Deceiving or protecting means
-
- 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
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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
- F41G7/2273—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 infrared search head for target-seeking missiles, in which a field of view through an imaging optical system on a main detector is reproducible, which detects a target located in your visual field, and a second Detector is provided, which responds to the high-intensity radiation, the Seeker contains a facility to prevent interference by going from the target the missile emitted, high-intensity radiation is caused and by the second detector can be activated.
- Infrared search heads for missiles are widely known.
- An infrared search head for target-seeking missiles is, for example, by EP-B-0 538 671 known.
- the seeker head contains an optical system that gimbals over an inner and an outer frame with respect to a structure movable on all sides is stored.
- the optical system creates an image of a Field of view. Signals are obtained which are sent via two frame actuators direct the viewfinder towards a detected target.
- a gyro-stabilized viewfinder is known from DE-PS-3 925 942.
- the seeker contains an imaging optical system through which a field of view Detector means is mapped.
- the detector means generate target signals, from which Alignment signals are generated.
- the orbital axis becomes a through the alignment signals Rotors aimed at a target.
- the detector means are in a dewar arranged and are cooled.
- FR 2 740 638 A1 relates to an arrangement which is intended to prevent a Infrared detector can be detected or disturbed by enemy laser radiation.
- a second, special detector is provided which is suitable for the To detect the occurrence of such laser radiation. If such a disturbance occurs Laser radiation is e.g. the field of view scanning of the infrared detector is interrupted.
- the special detector in one version of FR 2 740 638 A1 contains one Monochromator, being the distinguishing criterion between laser radiation and thermal radiation of a target the monochromatic character of laser radiation serves.
- the laser radiation is higher as a light pulse Performance recognized.
- the invention has for its object in a seeker head of the aforementioned Kind after detection of disruptive laser radiation and appropriate shutdown or shielding the main detector to avoid losing a target.
- this object is achieved in that the second detector is on the location of the light source emitting the high-intensity radiation is more appealing
- the function of the position-sensitive detector is its high-intensity radiation is not affected.
- the devices for preventing interference from high-intensity radiation usually a laser beam directed at the search head of the missile be of different types. Different solutions, individually or in suitable Combination can be used are the subject of the subclaims.
- an infrared seeker head is shown schematically.
- the search head can be in the nose an air-to-air missile and an infrared-transmissive dome be protected.
- the infrared seeker head is rotatable on an axis 10 mounted inner frame 12 of a gimbal system.
- the inner frame 12 carries that entire opto-electronic receiving system whose optical axis through appropriate deflection of the frame axes is aimed at a target.
- a first one Detector system 14 contains infrared optics 16 as the imaging optical system. This detector system 14 forms a conventional passive infrared detector, which is based on Thermal radiation appeals.
- the infrared optics 16 form a field of view (and the target) via a scanning device arranged behind with a movable optical Deflector from an infrared detector line as the main detector.
- the one from it derived infrared data are arranged in a structure-fixed manner in the missile Signal processing forwarded.
- the second detector system On the inner frame 12 there is a second one close to the first detector system 14 Detector system arranged. Contains in the embodiment shown in Fig.1 the second detector system as "second detectors" two laser detector modules 18 and 20, which respond to laser radiation.
- the optical axes of the two laser detector modules 18 and 20 are defined to the optical axis of the first Detector system 14 aligned.
- the fields of view of the laser detector modules 18 and 20 are matched to the field of view of the first detector system 14 in such a way that Laser interference in the entire scanning range of the first detector system 14 can be detected.
- the use of two laser detector modules 18 and 20 has the advantage that second detector system can also detect laser radiation if, depending on Deflection direction of the frame axis, one or the other laser detector module 18 or 20 at high squint angles covered by the dome bracket or other parts becomes.
- the laser detector modules 18 and 20 each contain a four-quadrant detector and one entry lens 22 and 24 respectively.
- the received laser radiation is after conventional measurement method out of focus on the four-quadrant detectors.
- the electronics of the are in a housing 26 on the inner frame 12 Seeker.
- FIG 2 the signal processing of the infrared seeker head of Figure 1 in one Block diagram shown.
- the signals (infrared data) of the first detector system 14 are fed to a signal processing unit 28.
- these signals are evaluated and alignment signals are generated.
- the Alignment signals of the signal processing unit 28 are a switching logic 30 fed which tracking and steering signals for the seeker head tracking and Missile guidance delivers. This is indicated by an arrow 34.
- the signals of the four-quadrant detector of the laser detector module 18 are fed to signal processing 32. In the Signal processing 32, these signals are evaluated and alignment signals are generated. These alignment signals are also supplied to the switching logic 30.
- the seeker tracking and the missile guidance are based on the Alignment signal from the signal processing unit 28 of the first detector system 14. If the threat is detected, a laser steel is launched onto the target from the target Missile aligned, then this alignment signal, the signal processing 28 disturbed and unusable for the guidance of the missile.
- the Switchover logic 30 detected. The switching logic 30 then switches over so that the Search head tracking and missile guidance are based on the alignment signal of the Signal processing unit 32 of the second detector system supports. This can be done take place that the analog output data of the quadrant detectors in the electronics be processed and digitized if they have a predetermined threshold exceed.
- the switching logic 30 continues to turn on Protection signal 36 generated by which measures to protect the first Detector system 14 can be initiated.
- the protection signal 36 of a protective signal processing unit 38 which are connected to a Output 40 gives a protection command to the first detector system 14.
- the protection signal 36 of a protective signal processing unit 38 which are connected to a Output 40 gives a protection command to the first detector system 14.
- the field of view of the first detector system 14 with an Scanned scanner.
- a protective measure we use the movable optical one Deflector of the scanning device when the protection signal occurs in one position stopped, in which the detector line of the first detector system 14 from the Laser radiation is not applied.
- the imaging optical again System 16 forms an infinite field of vision over a moving one optical deflection device 60 in the plane of a detector line 62.
- the optical Deflection device 60 is moved by a drive 64.
- the deflector 60 is shown as an oscillating mirror in FIG. The swinging motion is through one Double arrow indicated.
- the detector line 62 is a linear arrangement of detector elements, which extends perpendicular to the paper plane in Fig.4.
- a Protection command at the output 40 (Fig.2) is the deflection device 60 by the drive 64 brought into the position shown in dashed lines in Figure 4. In this position the Deflection device 60 all radiation from the field of view captured by the system 16 past the detector line 62.
- FIG. 6 This is shown in Fig. 6.
- a deflection mirror 70 swung in, which is dashed in Figure 6 is drawn.
- FIG. 3 shows the sequence of switching between the two operating modes in one Flow chart shown: Furthermore, there is an optional process at short distance shown between search head and target.
- the Search head is switched to regular infrared mode. This is through block 42 shown.
- a query takes place (block 44) whether laser radiation is received or not. If no laser radiation is received ("NO"), then it remains Seeker head in this infrared mode. If laser radiation is received (“YES”), the protective measures for the first detector system 14 are initiated (cf. Switching logic 30 in Fig.2). This is represented by block 46.
- the Search head switched to laser-controlled operation (block 48). It finds one repeated query instead (block 50) as to whether laser radiation is still being received.
- the infrared search head can also be used to check whether the target is within a short time Distance.
- the target image is larger than the laser interference in the picture, so that at least parts of the target in the signal processing unit 28 of the first detector means 14 can be recognized and "valid" alignment signals can be generated.
- This process is shown in Figure 3 by dashed lines. If in that laser-controlled operation (block 48) when queried (block 50) continues laser radiation is detected ("YES"), in this case a query takes place as to whether the destination is within a short time Distance. This is represented by block 52. If not (“NO"), then the seeker head remains in laser controlled mode (block 48). If If the target is a short distance away (“YES”), the search head is placed in the Infrared mode switched (block 54).
- an imaging optical system 72 generates the represented by a lens, an image of the field of view on a CCD matrix detector 74.
- a pair of complementary prisms 76 and 78 arranged in the beam path.
- the prisms 76 and 78 form isosceles right-angled triangles in cross section, the hypotenuses of the triangles facing each other.
- the prism 76 has an entry surface 80 and an inclined surface 82 facing the prism 78.
- the Prism 78 has a prism 76 facing, parallel to the inclined surface 82 Inclined surface 84 and an exit surface 86 parallel to the entry surface 80.
- the Sloping surface 84 is coated with a semiconductor layer 88.
- the semiconductor layer 88 is transparent to the infrared radiation received by the CCD matrix detector 74, but shows a non-linear absorption behavior. This non-linear Absorption behavior can be caused, for example, by two-photon processes his.
- the semiconductor layer for the low intensities of the infrared radiation with which the CCD matrix detector 74 is usually acted on as the main detector has a high transmission, high intensities, such as those from a laser aimed at the missile generated, strongly absorbed.
- the two prisms 76 and 78 are mutually perpendicular by a piezo actuator 90 to the planes of the two inclined surfaces 82 and 84 between one shown in FIG first position and a second position shown in Figure 8 movable.
- the prism 76 Perpendicular to the entry surface 80, the prism 76 has an exit surface 92.
- the level of Exit surface 92 is perpendicular to the plane of exit surface 86 of prism 78.
- a second detector 94 is arranged opposite the exit surface 92.
- the second Detector 94 responds to the high-intensity radiation, namely that of the target Missile-directed laser beam.
- the second detector 94 is a detector that is less sensitive to radiation than the main detector 74.
- the second detector 94 should detect the incidence of high-intensity radiation. He doesn't need the weak To address the natural radiation of a distant target like the main detector.
- the second Detector 94 is a four quadrant detector.
- the imaging optical system 72 forms the prisms 76 and 78 in the first position (FIG. 7) the field of view through the two prisms 76 and 78 and the layer 88 sharp on the CCD matrix detector 74.
- the second position of prisms 76 and 78 (FIG. 8) is through the piezo actuator 90 between the inclined surfaces 82 of the prism 76 and the semiconductor layer 88 applied to the inclined surface 84 has a narrow air gap 96 educated.
- the width of the air gap 96 can be on the order of light wavelengths lie.
- the air gap 96 leads to that on the inclined surface 82 of the Prism 76 a total reflection takes place.
- the optical system 72 does not produce an image the CCD matrix detector 74 but on the second detector 94 essentially the source of the high-intensity radiation. This illustration is done somewhat out of focus on the detector 94 designed as a four-quadrant detector.
- the individual detector elements of the CCD matrix detector build during an "integration time” due to the light falling on analog signals, each corresponds to the time integral of the light falling on the detector element. During one After the "readout time", the detector elements are read out line by line. This change of integration and readout time takes place cyclically. Useful information of CCD matrix detectors therefore only deliver that during the integration period incident light. During the readout time, the imaging light beam from the CCD matrix detector 74, without affecting the sensitivity of the CCD matrix detector is impaired.
- the prisms 76 and 78 become during the integration time into the first position shown in FIG. 7 and during the readout time in brought the read position shown in Fig.8.
- the light thereby acts on the CCD matrix detector only during the integration period.
- the light turns on during the readout time directed to the second detector 94 by the total reflection on the inclined surface 82.
- Switching between the first position of Fig.7 and the second position of Fig.8 can be done by the piezo actuator 90 at high frequency.
- the arrangement described has another advantage: the light is periodic, namely during the readout times, also directed to the second detector 94.
- the second detector 94 detects the occurrence of high-intensity radiation. If such Radiation is detected, the prisms 76 and 78 can be in their second position being held. Then the CCD matrix detector 74 is completely against that shielded from incident radiation.
- a second detector 94 designed as a four-quadrant detector is used Image of the light source of high intensity radiation generated.
- the four quadrant detector now delivers target placement signals from the laser beam, by means of which the missile enters the Goal is led.
- the laser beam thus sets the highly sensitive CCD matrix detector 74 out of function. For this, he now provides a means by which To guide missiles into the target.
- the system is immediately switched back to normal operation: the prisms are brought into the position of Fig. 7, and the CCD matrix detector 74 takes over the observation of the target again. It also happens when the laser beam is pulsed.
- a prism arrangement with piezo actuators, as described in FIGS. 7 and 8, can also be used in place of the mirror 7 in FIG.
- the periodic switching between the positions of Fig. 7 and Fig. 8 during the integration time and the readout time of the CCD matrix detector 74 and / or the upstream of the semiconductor layer 88 with non-linear absorption behavior can u.U. the high-intensity radiation can be attenuated so far that the CCD matrix detector 74 continues to lead even without switching to a detector 94 of the missile into the source of this high-intensity radiation without being blinded or damaged.
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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)
- Optical Radar Systems And Details Thereof (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Description
- Fig.1
- ist eine schematische, perspektivische Darstellung und zeigt ein Ausführungsbeispiel des erfindungsgemäßen Infrarot-Suchkopfes.
- Fig.2
- ist ein Blockdiagramm und veranschaulicht die Signalverarbeitung bei einem erfindungsgemäßen Infrarot-Suchkopf.
- Fig.3
- ist ein Flußdiagramm und veranschaulicht die Steuerung des erfindungsgemäßen Infrarot-Suchkopfes und zusätzlich eine optionale Betriebsweise des Infrarot-Suchkopfes.
- Fig.4
- zeigt eine Ausführung, bei welcher im Normalbetrieb das Gesichtsfeld mittels einer Detektorzeile über einen Schwingspiegel abgetastet wird und bei Auftreten einer hochintensiven Störstrahlung der Schwingspiegel in eine Stellung bewegt wird, in welcher die Detektorzeile nicht von der Störstrahlung beaufschlagt ist.
- Fig.5
- zeigt eine Ausführung, bei welcher als Schutzmaßnahme zum Schutz des Haupt-Detektors vor hochintensiver Störstrahlung eine vor dem Haupt-Detektor angeordnete mechanische oder elektro-optische Blende geschlossen wird.
- Fig.6
- zeigt eine Ausführung, bei welcher als Schutzmaßnahme zum Schutz des Haupt-Detektors vor hochintensiver Störstrahlung ein Spiegel in den Strahlengang eingeschwenkt wird, der die Störstrahlung von dem Haupt-Detektor ablenkt.
- Fig.7
- zeigt eine Ausführung, zwei durch einen Piezosteller gegeneinander beweglicher Prismen in der Stellung, in welcher das von dem optischen System erfaßte Licht auf einen Haupt-Detektor geleitet wird.
- Fig.8
- zeigt die Ausführung von Fig.7 in einer Stellung, bei welcher das von dem optischen System erfaßte Licht auf einen Hilfs-Detektor geleitet wird, der zum Empfang der hochintensiven Störstrahlung ausgelegt ist.
- Das erste Detektorsystem kann durch Abblendmittel geschützt werden. Hierbei kann es sich sowohl um eine mechanische als auch um eine trägheitslose Blende (z.B. eine elektro-optische Kerr-Zelle) handeln. Das ist in Fig.5 schematisch dargestellt. Bei der Ausführung von Fig.5, die im übrigen ähnlich ausgebildet sein kann wie die Ausführung von Fig.1 bis 3, erzeugt das abbildende optische System 16 ein Bild des Gesichtsfeldes in der Ebene eines infrarotempfindlichen CCD-Matrixdetektors 66. Vor dem CCD-Matrixdetektor 66 sitzen Abblendmittel 68, die von dem Schutzbefehl am Ausgang 40 ansteuerbar sind und in Fig.5 von einer Kerrzelle gebildet werden.
- Es können auch Strahlablenkmittel vorgesehen sein, welche die Strahlung von dem Haupt-Detektor beim Auftreten des Schutzsignals ablenken. Dies kann in einfacher Weise durch einen verschwenkbaren Umlenkspiegel realisiert sein, welcher beim Auftreten des Schutzsignals so verschwenkt wird, daß die Strahlung nicht mehr auf den Haupt-Detektor fällt.
Claims (10)
- Infrarot-Suchkopf für zielsuchende Flugkörper, bei welchem ein Gesichtsfeld durch ein abbildendes optisches System (16;72) auf einem Haupt-Detektor (62;66;74) abbildbar ist, der ein in dem Gesichtsfeld befindliches Ziel erfaßt, und ein zweiter Detektor (18;94) vorgesehen ist, welcher auf die hochintensive Strahlung anspricht, wobei der Suchkopf eine Einrichtung (18,60,68,70,30,38) zur Abwehr von Störungen enthält, die durch vom Ziel auf den Flugkörper ausgesandte, hochintensive Strahlung hervorgerufen wird und die durch den zweiten Detektor aktivierbar ist, dadurch gekennzeichnet, daß der zweite Detektor (18;94) ein auf den Ort der die hochintensive Strahlung aussendenden Lichtquelle ansprechender positionsempfindlicher Detektor ist dessen Funktion durch die hochintensive Strahlung nicht beeinträchtigt ist.
- Infrarot-Suchkopf nach Anspruch 1, dadurch gekennzeichnet, daß(a) aus Signalen des ersten und des zweiten Detektors (14,18) Lenksignale für den Flugkörper ableitbar sind und(b) eine Umschalt-Vorrichtung (30) vorgesehen ist, durch welche die Erzeugung der Lenksignale bei Beaufschlagung des Infrarot-Suchkopfes mit der hochintensiven Strahlung von den Signalen des ersten Detektors (14) auf die Signale des zweiten Detektors (18) umschaltbar ist,(c) so daß der Flugkörper dann auf die Quelle der hochintensiven Strahlung gerührt wird.
- Infrarot-Suchkopf nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß als Schutzmaßnahme durch den zweiten Detektor (18) bei Beaufschlagung mit der hochintensiven Strahlung eine Abblend-Einrichtung (68) vor dem Haupt-Detektor (66) aktivierbar ist.
- Infrarot-Suchkopf nach Anspruch 1, dadurch gekennzeichnet, daß(a) das Gesichtsfeld mittels eines Zeilendetektors (62) über ein im Strahlengang angeordnetes bewegliches optisches Ablenkglied (60) periodisch abtastbar ist und(b) als Schutzmaßnahme durch den zweiten Detektor (18) bei Beaufschlagung mit der hochintensiven Strahlung ein Anhalten der Bewegung der Ablenkglied (60) in einer Stellung auslösbar ist, in welcher der Zeilendetektor (62) nicht von der Strahlung aus dem abbildenden optischen System beaufschlagt ist.
- Infrarot-Suchkopf nach Anspruch 1, dadurch gekennzeichnet, daß als Schutzmaßnahme durch den zweiten Detektor (18) bei Beaufschlagung mit der hochintensiven Strahlung eine Strahlenablenk-Einrichtung (70) vor dem Haupt-Detektor (66) aktivierbar ist.
- Infrarot-Suchkopf nach Anspruch 1, dadurch gekennzeichnet, daß(a) der Haupt-Detektor (74) ein zweidimensionaler CCD-Matrixdetektor ist, in welchem periodisch während einer Integrationszeit Pixel-Signale aufgebaut und während einer Auslesezeit ausgelesen werden,(b) vor dem Haupt-Detektor (74) eine gesteuerte optische Strahlenablenk-Einrichtung (76,78) zum Umlenken des Strahlenganges angeordnet sind und(c) die optische Strahlenablenk-Einrichtung (76,78) synchron mit der Auslesung des CCD-Matrixdetektors periodisch während der Auslesezeit aktivierbar sind.
- Infrarot-Suchkopf nach Anspruch 6, dadurch gekennzeichnet, daß die Strahlenablenk-Einrichtung ein Paar von komplementären Prismen (76,78) aufweist, zwischen denen mittels eines piezoelektrischen Hubgliedes (90) wahlweise ein Luftspalt (96) erzeugbar ist, an welchem eine Totalreflexion einfallenden Lichtes erfolgt.
- Infrarot-Suchkopf nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, daß im Abbildungs-Strahlengang vor dem Haupt-Detektor (74) eine Filterschicht (88) angeordnet ist, deren Transparenz mit zunehmender Intensität der einfallenden Stahlung abnimmt.
- Infrarot-Suchkopf nach Anspruch 8, dadurch gekennzeichnet, daß die Filterschicht (88) auf die an die den Luftspalt (96) begrenzende, einfallseitige Schrägfläche (84) des detektorseitigen Prismas (78) aufgebracht ist.
- Infrarot-Suchkopf nach Anspruch 1, dadurch gekennzeichnet, daß die Einrichtung zur Abwehr von Störungen deaktivierbar ist, wenn bei geringem Abstand zwischen Flugkörper und Ziel das Zielbild auf dem Haupt-Detektor wesentlich größer wird als das Bild der Quelle der hochintensiven Strahlung.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19724080A DE19724080A1 (de) | 1997-06-07 | 1997-06-07 | Infrarot-Suchkopf für zielsuchende Flugkörper |
DE19724080 | 1997-06-07 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0882941A1 EP0882941A1 (de) | 1998-12-09 |
EP0882941B1 true EP0882941B1 (de) | 2003-12-03 |
Family
ID=7831801
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP98109319A Expired - Lifetime EP0882941B1 (de) | 1997-06-07 | 1998-05-22 | Infrarot-Suchkopf für zielsuchende Flugkörper |
Country Status (3)
Country | Link |
---|---|
US (1) | US6196497B1 (de) |
EP (1) | EP0882941B1 (de) |
DE (2) | DE19724080A1 (de) |
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IL140232A (en) * | 2000-12-11 | 2010-04-29 | Rafael Advanced Defense Sys | Method and system for guiding active laser imaging of interceptor missiles |
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US8339580B2 (en) * | 2004-06-30 | 2012-12-25 | Lawrence Livermore National Security, Llc | Sensor-guided threat countermeasure system |
FR2882440B1 (fr) * | 2005-02-23 | 2007-04-20 | Sagem | Dispositif de contre-mesure et de poursuite d'une menace sous la forme d'un missile a autodirecteur |
US8639394B2 (en) * | 2008-12-01 | 2014-01-28 | Lockheed Martin Corporation | Dynamic optical countermeasures for ground level threats to an aircraft |
FR2942554B1 (fr) * | 2009-02-20 | 2014-08-01 | Sagem Defense Securite | Dispositif et procede de guidage d'un missile vers une cible, missile et autodirecteur associes. |
DE102010027189A1 (de) * | 2010-07-15 | 2012-01-19 | Lfk-Lenkflugkörpersysteme Gmbh | Suchkopf für einen Flugkörper |
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US9146251B2 (en) | 2013-03-14 | 2015-09-29 | Lockheed Martin Corporation | System, method, and computer program product for indicating hostile fire |
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RU2756170C1 (ru) * | 2020-11-06 | 2021-09-28 | Акционерное общество Научно-производственное предприятие "Авиационная и Морская Электроника" | Оптико-электронная многоканальная головка самонаведения |
CN114543599A (zh) * | 2020-11-24 | 2022-05-27 | 北京振兴计量测试研究所 | 一种激光目标模拟测量装置及测量方法 |
DE102021005406B4 (de) * | 2021-10-30 | 2023-06-22 | Diehl Defence Gmbh & Co. Kg | Optische Vorrichtung zur Erfassung einer Objektszene und Suchkopf |
CN114459298B (zh) * | 2022-02-25 | 2024-03-01 | 西安恒宇众科空间技术有限公司 | 一种微型弹载主动式激光导引头及其导引方法 |
DE102022000894A1 (de) * | 2022-03-15 | 2023-09-21 | Diehl Defence Gmbh & Co. Kg | Vorrichtung zur optischen Erfassung eines Zielobjekts |
CN117538961B (zh) * | 2024-01-09 | 2024-07-09 | 中天引控科技股份有限公司 | 一种用于实现红外导引头的制备方法及装置 |
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Publication number | Priority date | Publication date | Assignee | Title |
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GB1177641A (en) * | 1961-02-03 | 1970-01-14 | Emi Ltd | Improvements relating to Automatic Tracking Apparatus. |
DE2655306C3 (de) * | 1976-12-07 | 1981-07-09 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Verfahren und Vorrichtung zur Ausblendung von Störstrahlern in einer Einrichtung zur optischen Lenkung von Flugkörpern |
FR2740638B1 (fr) * | 1986-07-02 | 1998-01-02 | Trt Telecom Radio Electr | Procede pour empecher la detection et le leurrage d'une camera thermique par des moyens externes a la camera et dispositif mettant en oeuvre ce procede |
DE3925942C2 (de) | 1989-08-07 | 1996-07-25 | Bodenseewerk Geraetetech | Kreiselstabilisierter Sucher |
DE3938705C2 (de) | 1989-08-07 | 1996-09-05 | Bodenseewerk Geraetetech | Kreiselstabilisierter Sucher |
US5062586A (en) * | 1990-05-17 | 1991-11-05 | Electronics & Space Corporation | Missile tracking, guidance and control apparatus |
FR2751479B1 (fr) * | 1990-08-03 | 1998-11-06 | Thomson Csf | Procede et systeme de protection des equipements de veille ou de poursuite optroniques au regard d'une illumination |
DE4135260C1 (de) | 1991-10-25 | 1993-02-25 | Bodenseewerk Geraetetechnik Gmbh, 7770 Ueberlingen, De | |
DE4244480A1 (de) * | 1992-12-30 | 1994-07-07 | Bodenseewerk Geraetetech | Sensoranordnung mit gekühltem Sensor |
DE19520318A1 (de) * | 1995-06-02 | 1996-12-05 | Bodenseewerk Geraetetech | Sensoranordnung mit einem durch einen Joule-Thomson Kühler gekühlten Sensor und Elektronikbauteilen |
-
1997
- 1997-06-07 DE DE19724080A patent/DE19724080A1/de not_active Withdrawn
-
1998
- 1998-05-22 DE DE59810311T patent/DE59810311D1/de not_active Expired - Lifetime
- 1998-05-22 EP EP98109319A patent/EP0882941B1/de not_active Expired - Lifetime
- 1998-06-02 US US09/088,369 patent/US6196497B1/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
DE19724080A1 (de) | 1998-12-10 |
EP0882941A1 (de) | 1998-12-09 |
DE59810311D1 (de) | 2004-01-15 |
US6196497B1 (en) | 2001-03-06 |
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