EP2671094A2

EP2671094A2 - Air surveillance system for detecting missiles launched from inside an area to be monitored and air surveillance method

Info

Publication number: EP2671094A2
Application number: EP12712895.7A
Authority: EP
Inventors: Manfred Hiebl; Hans Wolfgang PONGRATZ
Original assignee: EADS Deutschland GmbH
Current assignee: Airbus Defence and Space GmbH
Priority date: 2011-02-04
Filing date: 2012-02-02
Publication date: 2013-12-11
Also published as: EP2711733A3; US20140022388A1; WO2012103878A2; DE102011010339A1; WO2012103878A3; EP2711734A2; EP2711733A2; EP2711734A3

Abstract

An airspace surveillance system for the detection of missiles launched within a space being monitored, having at least two surveillance platforms positioned outside or on the edge of the space being monitored in such a manner that the space or a part of the space is situated between the monitoring platforms. Each of the monitoring platforms is equipped with at least one camera system in such a manner that the lines of sight of the camera systems of the two monitoring platforms being positioned opposite to and facing each other.

Description

Airspace surveillance system for the detection of rockets launched within an area to be monitored and methods for

Air traffic control

TECHNICAL AREA

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.

BACKGROUND OF THE INVENTION

In particular, in order to combat armed medium-range missiles or long-range missiles in time before reaching their targets, it is necessary to know the trajectory of the rocket. In particular, if these missiles are equipped with a nuclear warhead, a fight against these missiles must be made as possible over the territory from which the rockets are launched to increase the risk of the state launching these missiles, that in the destruction of the rocket emerging radioactive fali-out your own

Territory radioactively contaminated. If such destruction over the launch territory is not possible, such missiles should be destroyed at a very high altitude in their trajectory to minimize collateral damage from concentrated radioactive fall-out. It is therefore necessary to obtain knowledge of the launch of such missiles at a very early stage, and a reliable one at a very early stage

Determine the path of the missile trajectory.

STATE OF THE ART From the general state of the art, flying satellites are known for this surveillance purpose in high orbits, the

Monitoring devices are directed from the top of the earth. These

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

Surveillance systems have a high background noise, which can lead to false alarms.

Other known monitoring devices are formed by radar stations which are stationed along an expected rocket flight route in order to be able to detect a flying rocket and track it for path determination. These

Monitoring method requires a lot of effort and is often not feasible for political reasons. In addition, such radar stations determine only the position of a flying rocket and their

Radar Rückstrahlquerschnitt 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.

BACKGROUND OF THE INVENTION It is therefore an object of the present invention to provide a

To provide an airspace surveillance system capable of detecting and identifying early-launched missiles and determining their trajectory. Furthermore, it is an object of the present invention, a corresponding method for airspace monitoring with such

To specify the airspace surveillance system.

The part of the object directed to the airspace monitoring system is solved by an airspace monitoring system having the features of

Patent claim 1.

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.

ADVANTAGES

With this airspace monitoring system according to the invention, 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. The use of an imaging sensor in the form of a telescope camera system allows an object identification by

For example, perform a multispectral image comparison, so that it can be determined by comparing the target objects with known target reference images, whether it is the detected object to a rocket or

for example, is decoy.

It is particularly advantageous if three or more monitoring platforms at spaced-apart positions outside or at the edge of

monitoring area are provided. As a result, the accuracy of the position determination of a detected object and the accuracy of the

Track tracking of this object can be significantly improved.

It is also advantageous if at least two pairs of the monitoring platforms are provided, wherein the area to be monitored or a part of the area to be monitored between the monitoring platforms of each

Paares is located. In this way, especially when two of these pairs are positioned at the "corners" of the area to be monitored, the entire Be reliably monitored and a fast and reliable

Position determination of detected objects can be carried out with it.

It is particularly advantageous if each of the camera systems of

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 Zielverfolgungsspiegelanordnung and is provided with a drive device for at least one movable element of

A tracking mirror arrangement and a control device for the

Drive means and wherein 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

to detect emitted light. If a detection of an object has taken place, an enlarged representation of the detected object can be obtained by means of the first image sensor assigned to the longer focal length, whereby the Identification of the object is facilitated. In this way it can be determined whether the detected object is a rocket, and it can also be identified on the basis of the enlarged representation. For this purpose, 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. Preferably, the image sensor has a sensitivity maximum in

Spectral range between 0.7 pm and 1, 7 pm wavelength. In this

Wavelength range is given by all currently known rocket fuels

Burn off a reliable, stable signal of over 1,000,000 watts / m ² . Furthermore, the earth's atmosphere in this wavelength range has a window with high light transmission above a height of 15 km, so that in this spectral range a large visibility is possible. In a preferred

Embodiment, the image sensor, a, preferably uncooled, indium gallium arsenide CCD sensor chip. Such 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

Sensor chip is high resolution and in the near infrared range is highly sensitive to light and low noise. Preferably, the respective Hochgeschwind igkeitverschluss 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.

It is particularly advantageous if 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.

In a further preferred embodiment, 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. Such 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. At the same time high resolution of the camera, in which it is possible to image the light source, so for example the rocket tail on multiple pixels of the sensor, 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.

It is particularly advantageous if the camera system continues with a

Target illumination device is provided, 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. By means of

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. Preferably, 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. Through this use of the same optical beam path for the target illumination and the target image, 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

Camera system is reflected.

It is particularly advantageous if the camera optics for coupling the target illumination radiation has a mirror arrangement which is configured such that the beam path of the camera optics between the first image sensor and the target illumination device synchronously with the emission of the

Lighting pulse and with the arrival of its echo pulse is switchable. In this so-called "gated view" operation, one of the

Target illumination device generated radiation pulse through the camera optics to the target, so the rocket, sent while the beam path to

assigned image sensor is interrupted. 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. Preferably, 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

Camera system to the rocket and back needed time.

Preferably, 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 energy bundling together with the high

Ideally, 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.

Further preferably, 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

Multispectral image correlation with known reference target images done.

Preferably, 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

Höhenluftfahrzeug is and in the stratosphere, preferably in about 38 km altitude, is positioned. At this altitude aircraft are difficult to locate and fight. Furthermore, there is the visibility due to the thin atmosphere, especially in the near-infrared wavelength range, very large.

It is particularly advantageous if, in addition, a swiveling device is provided, 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

performed as the position determination of an object detected by the camera, so neutralize camera system-related measurement errors, so that a higher accuracy of the position determination of the detected object is achieved. In the communication position, 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.

It is advantageous if 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.

The part of the object directed to the method is achieved by the method having the features of claim 14.

This method for airspace monitoring with an inventive

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

Multispektraibildauswertverfahrens, 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.

In a further advantageous embodiment, 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

predetermined threshold value decreases, so that the target illumination device illuminates the object. As a result, the rocket can also burn after its

Engines continue to be pursued, creating an even more reliable

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.

It is particularly advantageous if 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. The view of the camera against the dark and cold space as a background due to the reduced background noise for even more reliable detection of even the smallest sources of light or heat, so that the usable range of

Camera system over a directed to the Earth observation system is significantly improved.

It is also advantageous if after detecting an object by a

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

Camera systems that have captured the object, time-synchronized bearings are performed on the object to the current position and the

Determine movement path of the detected object with high accuracy. This type of cooperative object tracking enables accurate orbit tracking of the object's trajectory, even when the object is at a great distance.

Preferably, 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.

Preferred embodiments of the invention with additional

Design details and other advantages are described below with reference to the accompanying drawings and explained. BRIEF DESCRIPTION OF THE DRAWINGS

a simplified perspective view of a

airspace monitoring system according to the invention and an airspace monitoring method performed therewith; a view of the airspace monitoring system of Figure 1 in the direction of arrow II. a schematic representation of the optical structure and the beam paths of a in the inventive

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

Track tracking method with the inventive airspace monitoring system analogous to the representation in Fig. 1 and

FIG. 6 is a view of the airspace monitoring system of FIG. 5 in FIG

Direction of the arrow VI in Fig. 5th

PRESENTATION OF PREFERRED EMBODIMENTS

In 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

supervising state. On two opposite sides of this territory S are each spaced apart two elevator aircraft as Monitoring platforms 1, 2, 3, 4 positioned. The altitude aircraft may be formed, for example, in the manner as described in the unpublished German Patent Application 10 2010 053 372.6. Of the

The disclosure content of this German patent application is fully incorporated in the disclosure of the present application. 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

Edge beams 12, 14; 22, 24 of the respective viewing direction 10; 20 on

Monitoring corridor K of the monitored area G in the vertical direction

is spanned so that from the monitored located on the ground surface E area G and the monitoring corridor K, 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.

Before discussing the way in which airspace surveillance is carried out, the structure and operation of the aboard will be described below Monitoring platforms 1, 2, 3, 4 located camera systems 100, 200, 300, 400 described using the example of the camera system 100.

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

High-speed shutter 1 11 on. Furthermore, 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

High-speed lock 113 and a high-frequency

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 Bildderotationseinheit 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 μm 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 μm to 1.70 μm 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

associated sub-assembly 126 of optical elements having a first focal length f1 and a second image sensor 12 associated second

Subassembly 128 of optical elements with a second focal length f2. The second focal length f2 is shorter than the first focal length f1. In the radiation path of the first sub-assembly 126 is a Fluorite Flatfield Corrector (FFC) 127

intended. In the preferred embodiment shown, the

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 mirror telescope 122 is preferably formed in this embodiment of an IR Dall Kirkham or an IR Ritchey Cretien telescope with Flatfield Corrector and Bariowlinsen for focal length extension and has an aperture of 12.5 "(= 31, 75 cm) This telescope is special for the near

Infrared range suitable. 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

Mounts 1242 ', 1242 "on a movable member 1244' one

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. For controlling the drive device 1244, a control device 1246 shown only schematically in FIG. 3 is provided.

In the mirror telescope arrangement 122, a filter arrangement 121 is provided 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 μιη, 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.

In the area of the first sub-assembly 126, 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

Flash lighting device with coupling via a

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

Infrared range of 1,100 W.

In an elliptical reflector 142, 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. 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 operation of the camera system according to the invention will be explained below.

The camera 101 is activated with the second image sensor 1 12 and in the

Beam path A of the mirror telescope arrangement 122 eingeschwenktem

Deflection mirror 129 directed to the target area G to be monitored. By means of a control computer (not shown) of a monitoring device, of which the camera system 100 is part, 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. During this search operation, which scans the target area, 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. During these recordings, one of the spectral filters 121 A, 121 B, 121 C is alternately inserted into the beam path of the

Mirror telescope assembly 122 pivoted in rapid succession, so that each recorded by the second image sensor 1 12 recording of the target area with one of the spectral filters 121 A, 121 B, 121 C is exposed. Several consecutive pictures superimposed on a near-infrared false-color image of the target and at the same time an ultispectral analysis of the target area in the near infrared range. This false color image is then sent to the image evaluator 105

Evaluation forwarded, so that there is an automatic multispectral

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.

If a target T is detected, for example a heat radiation emitting rocket, 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.

If 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. As a result, the radiation from the source 140 of the

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

high-energy flash of light is reflected from the target T and hits over the The tracking mirror assembly 124 and the mirror telescope assembly 122 back to the rotating sector shutter 123, at which time there is an open sector element in the beam path so that the light reflected from the target T can pass through the open sector shutter of the mirror assembly 123 and onto the first image sensor 110 arrives. 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

Surveillance area G there is launching a rocket launching

to detect and identify the burning engine. The rocket can also be switched off after the engine has been shut down

Target illumination device 104 are tracked on their trajectory. The

Trace tracking of a detected rocket after the end of the fire is recorded by the nearest camera systems, which are then in the

Geometry in the example in Fig. 1 only have to bridge a distance of a maximum of 500 km with the target lighting device.

In 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

Communication link, as shown by the outgoing of the monitoring platform 1 double-line arrows in Fig. 5 using the example of the first

Monitoring platform 1 is shown. In the example 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. Once a starting rocket from the search scan of a first

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

Monitoring platforms 1, 2 synchronized clocked a cross-bearing on the detected rocket T carried out, as shown in Fig. 6. In this way, the current position of the rocket T is determined. This cooperative

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. Preferably, however, more than three of these cooperative position determinations are performed, whereby the

Measuring the trajectory of the rocket is even more accurate. In this case, 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. There will be

made high-resolution images of the rocket still having an engine jet. From the bearings associated with these recordings can then calculate the exact position of the rocket in space and their velocity vector. As has already been described, recordings of the rocket T in three or more different infrared wavelength ranges are taken in succession by means of the filter arrangement 121 and combined by superposing them into a multicolor false color image of the rocket. These images are then processed with a multi-spectral image evaluation program and a classification and identification of the located rocket is performed. The composite composite multi-spectral images, with a sufficient number of added frames by averaging over the many frames, have a much better signal-to-noise ratio than the raw frames, thus providing a better recognition rate by means of these composite multispectral images. 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

time synchronously the closer environment of the extrapolated target position scanned until the rocket T has been taken again. The time-synchronized illumination of the target of several target illumination devices becomes the usable one

Lighting the rocket T with the number of activated

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.

When the rocket has been picked up, it will search for more parts of it, using a camera scan around the rocket

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

are intended to attack different targets. When the trajectories of all detected objects have been stably measured, further measurements are made using the switchable spectral filters 121A, 121B, 121C. This plurality of spectra of each detected object are then combined into composite spectral images to allow identification of the detected objects by means of a multi-spectral image recognition process. In this way, single and multiple warheads, burnt rocket stages and decoys can be detected and harmless parts of the rocket can be distinguished from dangerous parts. Not only satellite navigation data (GPS satellite signals) and inertial navigation data are used for determining and determining the position of each monitoring platform 1, 2, 3, 4, but also a

Drehlagebestimmung by star observation by means of a Stellar Attitude reference Sy stems carried out, wherein the respective camera of the camera system of the monitoring platform is directed to one or more stars. By comparison with the data of a star chart carried in a database, the three attitude angles in space are determined. By using the same telescope camera system, both for attitude angle determination of the monitoring platform, as well as for the visual angle determination of the targeted target, stand out

Adjustment error of the camera optics and angle sensors of the camera system largely on, whereby the residual accuracy of the position data of the targeted targets is improved. Calculations have shown that by adding a star navigation in this way to the conventional one

Satellite navigation, the orbit data of a detected rocket can be determined fifty times more accurate than just satellite navigation. In addition, with this better survey accuracy, 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

Multiple warheads are detected early, so the time for the

Preparation of missile defense against conventional methods is increased and the attacking rocket or the attacking

Multiple warheads can be trapped far from their targets. Reference signs in the claims, the description and the drawings are only for the better understanding of the invention and are not intended to limit the scope. Mark the reference list:

monitoring platform

line of sight

upper marginal rays

line of sight

upper marginal rays

line of sight

camera system

camera

camera optics

camera platform

The attitude control device

first image sensor

High-speed shutter

second image sensor

High-speed shutter

high-frequency line stabilization and image rotation unit high-frequency line stabilization and image rotation unit

Facility

A filter assembly

A spectral filter

B spectral filter

C spectral filter 22 reflector telescope arrangement

23 mirror arrangement

23 'dot-dash line

24 target tracking mirror assembly

26 first sub-assembly

27 Fluorite Flatfield Corrector

128 second sub-assembly

129 deflecting mirror

130 position stabilization device

140 first radiation source

141 arc lamp

142 reflector

143 condenser

144 sapphire glass hollow cone

145 pinhole block

145 'light passage opening

145 "exit aperture

146 Illumination field lens

00 camera system

300 camera system

00 camera system

1220 mirrors

1220 'aperture

1222 mirrors

1240 first deflecting mirror

1242 second deflecting mirror

1242 'Bracket for deflecting mirror 1242

1242 "Bracket for deflecting mirror 1242

1244 drive device

1244 'movable element of the drive device 1244

1246 control device A optical axis

A 'optical axis

A "optical axis

A '"optical axis

B border of the territory

E earth surface

G monitored area

K surveillance corridor

S territory

T goal

T trajectory

V airspace area f1 first focal length f2 second fueling

X first axis

y second axis

Claims

claims

1. Airspace monitoring system to detect from within a

monitoring area launching rockets with at least two

Monitoring platforms (1, 2, 3, 4) positioned outside or at the edge of the area to be monitored <G) such that the area (G) or a part of the area (G) between the surveillance platforms (1, 2, 3 , 4), wherein the respective monitoring platform (1, 2, 3, 4) with at least one camera system (100, 200, 300, 400) is designed such that the viewing directions (10, 20, 30, 40) of the camera systems (100, 200, 300, 400) of two mutually opposite monitoring platforms (1, 2, 3, 4) facing each other.

2. Airspace monitoring system according to claim 1,

characterized,

in that three or more monitoring platforms (1, 2, 3, 4) are provided at spaced-apart positions outside or at the edge of the area to be monitored (G).

3. Airspace monitoring system according to claim 1 or 2,

characterized,

at least two pairs of monitoring platforms (1, 2, 3, 4) are provided, the area to be monitored or a part of the area to be monitored being located between the surveillance platforms (1, 2, 3, 4) of each pair.

4. Airspace monitoring system according to one of the preceding claims, characterized in that

in that each of the camera systems is designed for detection and tracing of moving objects at a great distance and is designed for this purpose a camera (101) provided with a camera optics (102) and a position stabilization device (130) for the camera (101) and the camera optics (102),

wherein the camera (101) is provided with

^■ a first image sensor (1 10) with a first associated high speed shutter (1 1 1);

^• a second image sensor (112) having a second high-speed shutter (1 13) associated therewith;

the camera optics (102) comprising means (120) of optical elements for collimating incident radiation on one

radiation-sensitive surface of the first image sensor (110) and / or the second image sensor (112) with at least one

Mirror telescope arrangement (122) and at least one

Has a tracking mirror assembly (124) and is provided with

^■ a drive device (244) for at least one movable

Element of the target tracking mirror assembly (124) and

^■ a control device (246) for the drive means (244) and

^■ wherein the means (120) associated with the optical elements, a first image sensor (1 10) first sub-assembly (126) associated with the optical elements having a first focal length (f1) and a second image sensor (1 12), second sub-assembly (128) from optical elements having a second focal length (f2) which is shorter than the first focal length (f1).

Airspace monitoring system according to one of the preceding claims, characterized

in that the optical beam path of the camera system (100) can be switched between the first sub-array (126) and the second sub-array (128), wherein a movable, in particular pivotable, mirror (129) is preferably provided for switching over.

6. Airspace monitoring system according to one of the preceding claims, characterized

that the respective image sensor (110, 112) of the camera system a

Sensitivity maximum in the spectral range between 0.7 pm and 1, 7 pm wavelength.

7. Airspace monitoring system according to one of the preceding claims, characterized

the camera (101) of the camera system (100) comprises one of a plurality of

Spectral filters (121A, 121B, 121 C) existing filter assembly (121), which can be coupled into the beam path, if necessary, wherein the filter assembly (121) is preferably designed as a filter wheel.

8. Airspace monitoring system according to one of the preceding claims, characterized in that

that in the camera system (100) further comprises a target illumination device (104) with a radiation source (140), preferably one, preferably as a laser array or a xenon short arc lamp with aspherical

Collimating optics and Pinholekollimator trained as a radiation source, laser radiation source, is provided, wherein the

Target illumination device (104) is preferably coupled to the camera optics (102) such that the of the target illumination device

emitted target illumination radiation in the beam path of

Camera optics (102) for bundling the emitted radiation can be coupled and wherein the camera optics (102) further preferably for coupling the target illumination radiation has a mirror arrangement (123) which is designed so that the beam path of the camera optics (102) between the first image sensor (110 ) and the target lighting device (104)

is switchable.

9. Airspace monitoring system according to one of the preceding claims, characterized in that

in that the camera system (100) is furthermore provided or connected to an automatically operating image evaluation device (105) to which the image data of the images recorded by the camera (102) are transmitted.

10. Airspace monitoring system according to one of the preceding claims, characterized in that

the surveillance platforms (1, 2, 3, 4) are airborne and each preferably formed by an aircraft or aboard a

Aircraft are provided. 1. Airspace monitoring system according to claim 10,

characterized,

that the respective aircraft is an altitude aircraft and is positioned in the stratosphere, preferably at a height of approximately 38 km.

12. Airspace monitoring system according to one of the preceding claims, characterized in that

that in addition a pivoting device is provided, with which the

Camera system (100, 200, 300, 400) is formed pivotable between a monitoring position and a navigation position and / or a communication position.

13. Airspace monitoring system according to one of claims 8 to 2,

characterized,

the radiation source (140) of the target illumination device (104) is designed to be modulatable by means of a data injection device in order to be able to transmit data in the communication position with the emitted modulated radiation.

14. Air surveillance procedure with a

Airspace monitoring system according to one of the preceding

Claims,

characterized,

in that, by means of at least one camera system (100) of each monitoring platform (1, 2, 3, 4), the airspace or an area of the airspace above the area to be monitored (G) is in a scanning procedure in which the camera system (100) is in one Scan mode works, is systematically scanned for objects that give in relation to their environment significantly higher heat radiation, and

in that the camera system (100) is switched over from the scanning mode in a target tracking mode of a target tracking procedure after detection of such a high heat radiation object, wherein a smaller image detail containing the detected object (T) is picked up by the camera by means of a larger focal length and the camera is carried along with this moving detected object (T).

15. A method for airspace monitoring according to claim 14,

characterized,

that after switching the camera system (100) in the

Target tracking mode by means of a Bildauswerteverfahrens a

Object detection for the detected object (T) is performed to the object based on image data stored in a database

identify.

16. A method for airspace monitoring according to claim 14 or 15,

characterized,

that in the target tracking mode of the camera system (100) a

Target lighting device (104) is activated when the detected Object (T) emitted heat radiation signal is absent or falls below a predetermined threshold, so that the

Target illuminating device (104) illuminates the object (T). 17. Air surveillance method according to one of claims 14 to 16, characterized

that the viewing direction of the camera system (100, 200, 300, 400) of each monitoring platform (1, 2, 3, 4) from the location of the associated

Monitoring platform (1, 2, 3, 4) is directed through the monitored area (V) of the airspace of the monitored area in the direction of space.

18. Air surveillance method according to one of claims 14 to 17, characterized

in that after the detection of an object (T) by a camera system (100, 200, 300, 400) of a surveillance platform {1, 2, 3, 4) information about the

Viewing direction 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, is transmitted from at least one or two further monitoring platforms; that these further monitoring platform (s) (1, 2, 3, 4) direct their scanning activity to this sector of the airspace and, if at least one further camera system has detected the object (T), from the camera systems comprising the Object (T) have been detected, time-synchronized bearings are performed on the object to determine the current position and the trajectory of the detected object (T).

Air surveillance method according to one of Claims 14 to 18, characterized

in that the respective monitoring platform (1, 2, 3, 4) performs star bearings with the camera of its camera system (100, 200, 300, 400) to determine its own position.