Classifications

• • H—ELECTRICITY
  • H04—ELECTRIC COMMUNICATION TECHNIQUE
  • H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
  • H04N7/00—Television systems
  • H04N7/18—Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast
  • H04N7/181—Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast for receiving images from a plurality of remote sources
• • G—PHYSICS
  • G01—MEASURING; TESTING
  • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
  • G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
  • G01S7/003—Transmission of data between radar, sonar or lidar systems and remote stations
• • G—PHYSICS
  • G01—MEASURING; TESTING
  • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
  • G01S17/00—Systems using the reflection or reradiation of electromagnetic waves other than radio waves, e.g. lidar systems
  • G01S17/66—Tracking systems using electromagnetic waves other than radio waves
• • G—PHYSICS
  • G01—MEASURING; TESTING
  • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
  • G01S17/00—Systems using the reflection or reradiation of electromagnetic waves other than radio waves, e.g. lidar systems
  • G01S17/87—Combinations of systems using electromagnetic waves other than radio waves
• • G—PHYSICS
  • G01—MEASURING; TESTING
  • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
  • G01S17/00—Systems using the reflection or reradiation of electromagnetic waves other than radio waves, e.g. lidar systems
  • G01S17/88—Lidar systems specially adapted for specific applications
  • G01S17/89—Lidar systems specially adapted for specific applications for mapping or imaging

Definitions

• Airspace surveillance system for the detection of rockets launched within an area to be monitored and methods for
• the present invention relates to an airspace monitoring system for detecting missiles starting within an area to be monitored with at least two surveillance platforms. It further relates to a method for
• Airspace monitoring with such an airspace monitoring system is possible.
• Monitoring devices are directed from the top of the earth.
• Monitoring devices preferably operate in the infrared range from 2.6 to 4,6 pm wavelength. Due to the high background noise of a variety of on-earth heat radiation sources and sunlight reflections on cloud surfaces or water surfaces capture these known
• Radar reformstrahlquerites can measure, but are not able to make a more accurate identification of the detected object. Therefore, it is possible to make such radar systems useless by depositing decoys.
• This inventive airspace monitoring system for detecting launching within an area to be monitored rockets is provided with at least two monitoring platforms, which are positioned outside or at the edge of the area to be monitored so that the area or part of the area is located between the monitoring platforms, wherein the respective monitoring platform is configured with at least one camera system as a sensor such that the viewing directions of the camera systems (Sensors) of two opposing monitoring platforms facing each other.
• this airspace monitoring system it is possible to observe the area to be monitored or the part of the relevant area to be monitored from two viewing directions and to aim a detected object from at least two directions, whereby a position determination of the object is made possible.
• an imaging sensor in the form of a telescope camera system allows an object identification by
• Position determination of detected objects can be carried out with it.
• Airspace monitoring system is designed for detection and tracking of moving objects located at a great distance and is designed for this purpose with a camera-optics camera and a position stabilization device for the camera and the camera optics, the camera is provided with a first image sensor with a associated therewith first high-speed closure; a second image sensor having a second high speed shutter associated therewith; the
• Camera optics a device comprising optical elements for focusing incident radiation on a radiation-sensitive surface of the first image sensor and / or the second image sensor having at least one reflector telescope assembly and at least one Zielvbeforeungsaptan ever and is provided with a drive device for at least one movable element of
• the means of optical elements comprises a said first image sensor associated first subassembly of optical elements having a first focal length and the second image sensor associated second subassembly of optical elements having a second focal length which is shorter than the first focal length.
• This position-stabilized camera provided with a telescope optics which is particularly suitable for imaging distant objects is capable of using the element controlled by the control device and moved by the drive device, for example a target tracking mirror, with the latter
• Focal assigned image sensor to scan the area to be monitored, for example, that of the engine jet of a rocket launcher
• the optical beam path between the first sub-array and the second sub-array is preferably switchable, wherein the
• Switching preferably a movable, in particular pivotable, mirror is provided.
• the image sensor has a sensitivity maximum in
• Wavelength range is given by all currently known rocket fuels
• the image sensor a, preferably uncooled, indium gallium arsenide CCD sensor chip.
• a sensor chip is in
• Spectral range of 0.7 pm to 1, 7 pm is particularly sensitive and has a maximum sensitivity that is close to the theoretically possible
• Sensitivity limit is. It is particularly advantageous if this
• the respective Hochgeschwind technikverInstitut the camera is designed so that the associated image sensor can record a plurality of individual images in rapid succession, preferably at a frequency of 50 images per second, more preferably of 100 images per second.
• This fast frame sequence makes it possible, with the camera according to the invention, to scan a large search volume, that is to say a large horizontal and vertical image angle, in rapid succession, so that the camera scans carried out in this way produce a ensure high reliability for the detection of light-emitting moving objects.
• At least one of the subarrays of optical elements has a Barlow lens set, preferably combined with a field flattener.
• a Barlow lens set makes it possible to achieve high light transmission and thus high sensitivity with a large focal length.
• the Field Flattener largely eliminates the field curvature present on Dall Kirkham and Ritchey Cretien telescopes, allowing much sharper camera shots than uncorrected.
• the camera has a filter arrangement comprising a plurality of spectral filters, which can each be coupled into the beam path when required, wherein the filter arrangement is preferably designed as a filter wheel.
• a filter arrangement in particular such a fast-rotating filter wheel with, for example, three band filters which cover the entire spectral range, can be coupled into the beam path
• Sequentially false color images of the light and heat energy radiating moving object such as a burning rocket tail create.
• the images contain sufficient shape, color and spectral information to identify the target object by multispectral image correlation with known reference target images to be able to make.
• Target illumination device which has a radiation source, preferably a laser diode radiation source or a high-pressure xenon short arc lamp radiation source.
• the radiation source is preferably designed as a laser array or xenon short arc lamp with aspherical collimation optics and pinhole collimator.
• Target lighting device can continue the once detected rocket then be recognized if they no longer emits light or no heat radiation or emits only a very low radiation, as is the case for example, when the burning time of the rocket engine is completed.
• This target illuminator which is preferably formed by a near-infrared laser diode target illuminator or near-infrared high-pressure xenon short arc lamp aiming illuminator, illuminates the moving rocket once detected and the camera receives the reflected light from the illuminated moving rocket of the target illuminator.
• the target illumination device can be coupled to the camera optics in such a way that the light emitted by the target illumination device
• Target illumination radiation in the beam path of the camera optics for bundling the emitted radiation can be coupled.
• a very accurate adjustment of the illumination on the target object can be ensured, which can only be achieved with disproportionate effort by other means.
• Such a long focal length target illuminator makes it possible to produce in the target range, ie in the area of the moving rocket, a light spot with the multiple area of the rocket, which is so large that it illuminates the rocket, but still enough light back onto the rocket Image sensor of the
• Target illumination device generated radiation pulse through the camera optics to the target, so the rocket, sent while the beam path to
• the tact of this stroboscopic target illumination is chosen so that the duration of each on the target emitted illumination pulse is smaller than the time required to cover the distance from the camera system to the rocket and back.
• the duration of each light pulse sent to the rocket is at least 40%, in particular greater than 60%, which is used to cover the distance from
• the radiation source of the target illumination device is designed to emit pulsed light flashes, preferably in the infrared range, wherein the intensity of the near infrared light flashes is preferably at least 1 kW, more preferably 2 kW.
• the pulse power of about 2 kW emits enough near-infrared light to illuminate an object several hundred kilometers away, for example the rocket, so that the light reflected by the object is sufficiently strong to be detected by the sensor of the camera.
• the camera system is provided with an automatically operating image evaluation device, in particular an automatically operating one
• Multispectral image evaluation device provided or connected, to which the
• Image data of the pictures taken by the camera By means of this image evaluation device, preferably as
• Multispectral image evaluation is formed, can be identified with sufficient resolution and modulation depth of the received images automatically detected objects. Especially with multi-spectral images, this can be done by
• the monitoring platforms are air-supported and are each further preferably formed by an aircraft or provided on board an aircraft. It is particularly advantageous if the respective aircraft
• a swiveling device with which the camera system can be pivoted between a monitoring position and a navigation position and / or a communication position.
• This embodiment makes it possible to use the camera system in the navigation position for star navigation for their own position determination. Will the star navigation with the same camera system
• radiation modulated by the camera system for example a data stream, for example to a base station or to other monitoring platforms of the airspace monitoring system, can be transmitted or received from there.
• the radiation source of the target illumination device is designed to be modulatable by means of a data input device in order to be able to transmit data, for example to a base station or to other monitoring platforms of the airspace monitoring system, in the communication position with the emitted modulated radiation.
• Airspace monitoring system is characterized in that by means of at least one camera system of each monitoring platform of the airspace or an area of the airspace over the area to be monitored in a scan procedure in which the camera system operates in a scan mode, is systematically searched for objects that in relation to their environment a significant output higher heat radiation, and that the camera system is switched after detecting such a high heat radiation emitting object from the scan mode in a target tracking mode of a target tracking procedure, in which by means of a larger focal length, the detected object
• the smaller image detail is recorded by the camera and the camera is carried along with this moving detected object.
• An advantageous development of this method is characterized in that after switching the camera system to the target tracking mode by means of an image evaluation method, in particular a
• an object detection for the detected object is performed to identify the object based on stored in a database image data or multispectral reference target image data. In this way, it can be reliably determined whether the detected object is a launching rocket or possibly a decoy. Furthermore, the missile type can be identified, so that by means of its known flight performance data, a target area targeted by the missile can be determined. Also, specific control measures can be initiated due to the detected rocket type.
• a target illumination device is activated in the target tracking mode of the camera system if the heat radiation signal emitted by the detected object fails or falls below one
• the rocket can also burn after its
• Trajectory tracking and trajectory measurement is possible and deception maneuvers, such as the ejection of decoys, can be detected so early that even the taking of countermeasures is possible.
• the viewing direction of the camera system of each monitoring platform from the location of the associated Monitoring platform is directed through the monitored area of the airspace of the monitored area in the direction of space.
• Camera system of a monitoring platform information about the line of sight and thus over the sector of the monitored airspace in which the object has been detected by the capturing camera system to at least one camera system, preferably two camera systems, transmitted from at least one or two other platforms; that these further platform (s) direct their scanning activity to this sector of the airspace and if, after at least one other camera system has detected the object, from the
• This type of cooperative object tracking enables accurate orbit tracking of the object's trajectory, even when the object is at a great distance.
• the respective monitoring platform performs star bearings with the camera of its camera system for determining its own position, as a result of which, as already described, the accuracy of the position determination of the detected object and of its trajectory determination are improved.
• Airspace monitoring system provided camera system; a schematic representation of a target illumination device of the camera system of FIG. 2; a simplified perspective view of a
• FIG. 6 is a view of the airspace monitoring system of FIG. 5 in FIG.
• FIG. 1 an inventive airspace monitoring system is shown schematically in a perspective view from space.
• the thick dot-dash line B indicates the boundary of the territory of one
• the altitude aircraft may be formed, for example, in the manner as described in the unpublished German Patent Application 10 2010 053 372.6.
• Each of these altitude aircraft is equipped with at least one camera system 100, 200, 300, 400. Construction and mode of action of the respective camera system will be described in more detail below with reference to the camera system 100.
• the other camera systems 200, 300, 400 are constructed in the same way, so their description is omitted to avoid repetition.
• the viewing directions 10, 20; 30, 40 of the camera systems 100, 200; 300, 400 of two monitoring platforms 1, 2 located opposite each other; 3, 4 are facing each other, wherein the airspace to be monitored above the territory S between the two each forming a pair of monitoring platforms 1, 2 and 3, 4 extends. From the angles of view of the respective camera systems 100, 200, 300, 400, a region G to be monitored is detected in this way.
• FIG. 2 shows the airspace monitoring system of FIG. 1 in a viewing direction which corresponds to the arrow II in FIG. It can be seen how the viewing directions 10, 20 of the respective camera system 100, 200 located on board the surveillance platform 1, 2 are directed towards each other and how from the upper and lower
• a volume is defined as the airspace area V, of the on board the monitoring platforms 1, 2, 3, 4 camera systems 100, 200, 300, 400 preferably is monitored completely.
• the camera system 100 has a camera 101 provided with a camera 101, which is arranged on a camera platform 103.
• the camera platform 103 is provided with a position stabilization device 130 for the camera 101 and the camera
• Camera optics 102 provided, which is also shown only schematically in Fig. 3.
• the camera 101 has a first image sensor 110 with a
• the first image sensor 1 10 is associated with a high-frequency line stabilization and image rotation unit 1 4.
• the first image sensor 110 has an optical axis A ', which corresponds to the optical axis A of the camera optics 102.
• a second image sensor 1 12 with a second associated therewith
• Visual line stabilization and image rotation unit 115 is between the
• Camera optics 102 and the first image sensor 110 disposed at an angle to the optical axis A of the camera optics 102, wherein the angle shown in Fig. 3 of the optical axis A of the camera optics 102 and directed to the second image sensor 112 optical axis A "90 °.
• the high-frequency line stabilization and image rotation units 114, 15 detect, with the help of rotary accelerometers at the target tracking mirror 1242, high-frequency rotations of the mirror in the intertial system and therefrom calculate a correction movement for the mirror which stabilizes the line of sight of the mirror telescope 122 in space.
• the respective Jardinderotationsappel compensates for unwanted image rotation caused by movements of the target tracking mirror 1242, by counter-rotation with an auxiliary mirror system or by counter-rotation of the entire camera 101 about the optical axis A ' .
• the two image sensors 110, 112 are preferably highly sensitive in the near infrared range and formed, for example, by an InGaAs CCD chip with a preferably 30 ⁇ m pixel size and with a frame rate of 100 Hz at most.
• the sensors 110, 112 are preferably highly sensitive in the wavelength range from 0.90 ⁇ m to 1.70 ⁇ m and have a preferred image size of 250 ⁇ 320 pixels in order to achieve a high image reading frequency of 100 images per second.
• the camera optics 102 has a device 120 of optical elements for bundling incident radiation onto the radiation-sensitive surface of the image sensor 1 10 and / or the second image sensor 112. This optical
• Device 120 is provided with a reflector telescope assembly 122, a tracking mirror assembly 124, a first image sensor 110
• the second focal length f2 is shorter than the first focal length f1.
• FFC Fluorite Flatfield Corrector
• Focal length f1 of the camera optics 102 with the first sub-assembly 126, in which the captured by the camera optics 102 image is imaged on the first image sensor 110 38.1 m.
• the focal length f2 of the camera optics 102 with the second subarray 128, in which the image captured by the camera optics 102 is imaged on the second image sensor 112, is 2.54 m.
• the mirrors 1220, 222 of the reflecting telescope 122 are preferably provided with a gold surface mirroring and therefore particularly suitable for use as an infrared telescope mirror.
• the optical beam path of the camera optics 102 with its optical axis A is by means of a switchable, preferably pivotable, mirror 129 between the optical beam path of the first sub-array 126 with the directed to the first image sensor 110 optical axis A 'and the second optical
• Subarray 128 can be switched over with the optical axis A "directed to the second image sensor 112. In this way, the image captured by the camera optics 102 can be imaged either on the first image sensor 110 or on the second image sensor 112.
• the target tracking mirror arrangement 124 which is provided on the side of the mirror telescope arrangement 122 facing away from the image sensors 110, 112, has a first deflection mirror 1240 located in front of the mirror telescope arrangement 122 and a movable second deflection mirror 1242. This second one
• Deflection mirror 1242 is by means of only schematically shown in the figure
• Drive device 1244 mounted such that the second deflecting mirror 1242 is pivotable about a first axis x and a second axis y arranged at right angles thereto by means of the drive device 1244 mounted on the camera platform 103.
• a control device 1246 shown only schematically in FIG. 3 is provided.
• a filter arrangement 121 which has a plurality of spectral filters 121A, 121B, 121C. If necessary, these filters can be coupled individually into the beam path, for which purpose the filter arrangement can be designed as a filter wheel.
• the filters of the filter arrangement 121 are permeable to different wavelength ranges in the overall range from 0.90 m to 1.70 ⁇ , so that one part of the incident light from this wavelength range can be filtered out with one filter each, which acts as a blocking filter.
• a target illumination device 104 with a radiation source 140 is provided.
• the radiation source 140 is used as a laser Radiation source, preferably as a high pressure xenon short arc lamp with aspherical collimating optics and Pinholekollimator as
• High speed sector mirror 123 designed.
• the radiation source 140 emits light along an optical axis A '"which is transverse, preferably perpendicular to the optical axis A of the camera optics 102. In the region of the intersection of the optical axes A and A'" is a movable
• Mirror arrangement 123 is provided, which consists in the example shown of a rotating sector shutter whose closed sector elements are mirrored to redirect the along the optical axis A '"emitted light in the direction of the optical axis A of the camera optics 102, and whose open sector elements a light transmission from the In this way, light from the target illuminator 104 may be alternately directed by the camera optics 102 to a target T and light reflected from the target T back through the camera optics 102 to the first image sensor 110, as further below will be described.
• FIG. 4 shows an exemplary structure of the radiation source 140 of the target illuminating device 104 shown only symbolically in FIG. 3.
• This radiation source 140 is equipped with a xenon short arc lamp and has, for example, an electric power of 12 kW and a radiation power in the near
• an arc lamp 141 is arranged, which generates a short arc of about 14 mm in length and 2.8 mm thickness.
• the light emitted by this arc light is passed from the elliptical reflector 142 to a condenser 143, which is provided at its light entrance side with a sapphire crystal hollow cone 144 as condenser inlet and a pinhole block 145 has.
• the pinhole block 145 has a light passage opening 145 'tapering from the light entrance side to the light exit side
• Exit aperture 145 “has a polished gold surface.”
• the light aperture 145 is liquid cooled
• the light entrance side larger opening of the light passage opening 145 ' is the sapphire glass hollow cone 144 inserted with its light exit end, as shown in Fig. 4 can be seen.
• an illumination field lens 146 Disposed behind the pinhole block 145 is an illumination field lens 146 which images the exit aperture 145 "of the pinhole block through the fluoride flatfield corrector 127 onto the aperture 1220 'of the binocular telescope assembly 122 ( Figure 3) the deflection of the optical axis A '"of the radiation source 140 onto the optical axis A of the reflecting telescope arrangement 122, which takes place in the region of the dotted line 123' by means of the mirror arrangement 123, is not shown.
• the camera 101 is activated with the second image sensor 1 12 and in the
• Beam path A of the mirror telescope arrangement 122 Whenam path A of the mirror telescope arrangement 122.
• Deflection mirror 129 directed to the target area G to be monitored.
• the control device 1246 for the drive device 1244 of the second deflection mirror 1242 is controlled such that the tracking mirror 1242 acting as the second deflection mirror 1242 carries out a target scan area scan scanning line by line.
• the second image sensor 112 captures images of the target area with a high frame rate of 100 Hz, for example, and forwards them to an image evaluation device 105 of the superordinate monitoring device, which is provided, for example, in a control station 5.
• one of the spectral filters 121 A, 121 B, 121 C is alternately inserted into the beam path of the
• Target detection and destination identification can be performed, with false targets identified as such and marked as non-hazardous in the relevant target tracing file and the relevant target object identification file.
• the first image sensor 110 is activated, for which purpose the deflecting mirror 129 is swiveled out of the beam path A of the reflecting telescope arrangement 122 so that the light captured by the reflecting telescope arrangement 122 can reach the first image sensor 110 , At the same time, in the parent
• Control computer activates a target tracking procedure, which ensures that the deflection mirror 1242 acting as a target tracking mirror is driven in such a way that it tracks the moving target T such that the target T is always imaged on the first image sensor 110.
• the image sensor 110 also picks up the target T at a fast frame rate of, for example, 100 Hz and forwards the acquired image signals to the image evaluation device 05. There is then an object identification of the target T based on the recorded image data.
• the target T sets its own radiation activity in the wavelength range for which the camera 101 is sensitive, as is the case, for example, when the engines of a starting rocket (as target T) are at the end of their combustion, then
• Target illuminating device 104 of the camera system according to the invention and the mirror assembly 123 is activated, so that the sector shutter wheel is set in rotation.
• Target illumination device 104 emitted high-energy radiation at a mirrored sector element of the mirror assembly 123 deflected and introduced into the beam path of the reflector telescope assembly 122 and on the
• Target tracking mirror assembly 124 is directed to the target T. This
• the image sensor 110 can thus take pictures of the target T with the aid of the radiation emitted stroboscopically by the target illuminating device 104 by means of the rotating sector mirror arrangement 123, even if the target T no longer emits its own radiation.
• This camera system 100 is thus capable of a distance of up to 1 .200 km on the side facing away from the camera system
• the rocket can also be switched off after the engine has been shut down
• Target illumination device 104 are tracked on their trajectory.
• Geometry in the example in Fig. 1 only have to bridge a distance of a maximum of 500 km with the target lighting device.
• Fig. 5 is shown schematically how the cooperative search method by means of several airborne surveillance platforms 1, 2, 3, 4 works.
• the individual monitoring platforms 1, 2, 3, 4 are mutually connected with each other and with the control station 5 located in the air or on the ground
• Monitoring platform 1 is shown.
• two monitoring platforms 1, 2 and 3, 4 form a monitoring platform pair.
• the monitoring platforms 1, 2; 3, 4 of each pair are arranged so that the area to be monitored G or the part of this area to be monitored lies between them (FIG. 6).
• the volume defined by the area G and the corridor K, which determines the airspace area V, thereby forms a search volume which is completely captured by the camera systems of the surveillance platforms 1, 2, 3, 4.
• This search volume is first scanned line by line by the camera systems 100, 200, 300, 400 in monitoring mode by recording individual images arranged one after the other at short time intervals, for example at a frequency of 100 Hz.
• the monitoring time intervals are chosen so that a rocket launches on the way through the search volume is detected at least three times.
• Camera system is detected (for example, the camera system 100), the camera system 200 of the opposite second monitoring platform 2 is notified.
• the camera system 200 of this second monitoring platform 2 then directs its search area to the starting area of the rocket observed by the first monitoring platform or the part of the monitored air space volume V in which the first camera system 100 has detected the rocket T. Subsequently, by means of both camera systems 100, 200 of the pair of
• Position determination of the rocket T is carried out in succession at least three times, so that the trajectory T of the rocket is determined from the thus obtained at least three position values.
• more than three of these cooperative position determinations are performed, whereby the
• a trajectory projection in the future is calculated from the temporal position determination data of the rocket position in a control computer 50 of the control station 5 by means of a trajectory Kalman filter. Then, in at least one of the camera systems 100, 200, 300, 400, the long-focal-length target tracking procedure is activated and the camera systems in which they are activated
• Target tracking procedure has been activated, clocked synchronously in time aligned each precalculated rocket position.
• This multispectral recording and evaluation technique makes it possible to distinguish a real missile from false targets and interferers. If the engine beam of the rocket T once detected is extinguished, the target illumination device 104 of the respective camera system 100, 200, 300, 400 switches as already described, and the position determination of the rocket can thus also be effected after the engine has been shut down in the described time-sequential manner continue to be continued. Thus, even after the end of the engine of the detected rocket T further trajectory data of the rocket can be determined, so that the trajectory determination is further specified.
• the range of the target lighting device must be at a favorable distribution of camera systems a maximum of 500 km, as can be seen from the geometry of Fig. 5. Then the intensity of the illumination pulse is sufficient to generate an echo pulse that is well detectable.
• the rocket T must be in range of at least three active camera systems and it must be for one Triangulation of the missile position suitable lines of sight with sufficiently large cutting angles exist between the respective camera system and the rocket. If so, target illumination devices 104 are activated by at least three targeting camera systems. The camera systems then attempt to target the target position on the extrapolated target trajectory as synchronously as possible, so that the illumination impulses of all three camera systems arrive at the target at the same time. If a first location attempt fails, then
• Target illuminators multiplied if these
• Target lighting devices are directed to the same side of the rocket T. It is advantageous if the entire usable spectral range is recorded in onochrom images in order to achieve the highest sensitivity.
• Trajectory tracking is performed on all detected objects.
• the trajectories of different objects determined in this way are sent to the control computer 50 and stored there as different trajectory traces in a target tracking file, which is constantly updated. In this way, it can be recognized whether a missile, for example, several subsidiary missiles deposited, in addition
• the orbit data of a detected rocket can be determined fifty times more accurate than just satellite navigation.
• the airspace area where the target can be located in future measurements is much smaller, so targeting with extrapolated trajectory data can be much faster.
• the above-described combined image recognition, observed missile activity, and trajectory analysis can be used to determine the targets of the attacking missile or missile
• the attitude control device The attitude control device

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• 2011
  • 2011-02-04 DE DE102011010339A patent/DE102011010339A1/de not_active Withdrawn
• 2012
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  • 2012-02-02 WO PCT/DE2012/000093 patent/WO2012103878A2/fr active Application Filing
  • 2012-02-02 EP EP13005889.4A patent/EP2711733A3/fr not_active Withdrawn
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