Abstract:
A method for determining a location of a flying target included identifying and measuring the target by at least two seeker systems disposed at a distance from one another. The position of the target relative to at least one of the two seeker systems is determined from measurement data derived therefrom. The position of the target is measured inconspicuously and without active radiation, in that the seeker systems are data-networked, passive target tracking systems for missiles, which autonomously track the target and align the missile with the target. The measurement data determined by the data-networked seeker systems are combined, and the location of the target is determined from the combined data.

Description:
CROSS-REFERENCE TO RELATED APPLICATION 
       [0001]    This application claims the priority, under 35 U.S.C. §119, of German patent application DE 10 2010 005 199.3, filed Jan. 21, 2010; the prior application is herewith incorporated by reference in its entirety. 
       BACKGROUND OF THE INVENTION 
     Field of the Invention 
       [0002]    The invention relates to a method for determining the location of a flying target, in which the target is identified and measured by at least two seeker systems which are at a distance from one another, and the position of the target relative to at least one of the two seeker systems is determined from measurement data derived therefrom. 
         [0003]    Guided missiles having a seeker head which is aligned with the target to be attacked are used to attack airborne targets, for example guided missiles, artillery rockets or aircraft. To do this, the seeker head normally produces an image of the target and its surrounding area, and an operator of the missile or of its carrier platform for launching the missile uses the image to manually search for the target, and passes the selected image area to the process means of the missile. The missile, to be precise its seeker system, uses the image characteristics of the target to detect the target, and tracks it autonomously, in order to make it possible for the missile to fly autonomously to the target, and to hit it, after it has been launched. 
         [0004]    For complete alignment of a guided missile, it is worthwhile to also signal information relating to the range to the target to be attacked to the guided missile. This information is typically determined using an active sensor system, for example radar or a laser rangefinder. However, active sensor systems can themselves be detected easily and are therefore undesirably exposed in the battlefield. This considerably increases the potential danger to the sensor system and the operators of the sensor system. 
       SUMMARY OF THE INVENTION 
       [0005]    It is accordingly an object of the invention to provide a method and a device for determining the location of a flying target which overcome the above-mentioned disadvantages of the heretofore-known devices and methods of this general type and which provides for an apparatus that is less conspicuous. 
         [0006]    With the foregoing and other objects in view there is provided, in accordance with the invention, a method of determining a location of a flying target, which comprises: 
         [0007]    providing at least two seeker systems positioned at a distance from one another, the seeker systems being data-networked, passive target tracking systems for missiles; 
         [0008]    identifying and measuring the target with the at least two seeker systems, and autonomously tracking the target and aligning a missile with the target; 
         [0009]    combining the measurement data determined by the seeker systems and determining a position of the target relative to at least one of the two seeker systems from the measurement data. 
         [0010]    In other words, the objects relating to the method are achieved by a novel method in which the seeker systems are data-networked, passive target tracking systems for missiles, and the measurement data determined by them are combined, and the location of the target is determined from the combined data. The target tracking systems are passive, that is to say they are not able themselves to transmit any directional electromagnetic radiation when in a silent operating mode. In this case, the term passivity is not affected by normal thermal radiation or detector-specific signals or the like. 
         [0011]    The range to the target can be determined by triangulation from the measurement data. Since the two seeker systems and the target form a triangle, it is sufficient to know the distance between the seeker systems and the angle between the flying target and the respective other seeker system, from the view of each seeker system. To do this, the two seeker systems have to find the bearing of the same target, and have to measure the line of sight to it at the same time. Both seeker systems expediently track the target, which is moving relative to them, while they are measuring the target. The measurement data can be combined at each location, for example at one of the locations of the passive seeker systems, or at some other suitable location. Furthermore, if the locations of the seeker systems and the alignment of the seeker systems are known in three dimensions, then the precise location of the flying target can be determined. 
         [0012]    In order to determine the location, it is sufficient to determine the distance between the flying target and one of the seeker systems. In addition to range determination, location determination expediently also includes determination of the three-dimensional coordinates of the flying target at a predetermined point in space. The flying target can be measured by determining at least one three-dimensional information item of the flying target relative to both seeker systems, for example angle information. Target tracking systems are expediently systems which can autonomously track the target and, in particular, can align a missile with the target, in which case, it is sufficient for alignment to align any element of the missile with the target, for example seeker optics. 
         [0013]    The seeker systems can expediently move with respect to one another and, for example, are distributed between two vehicles. The vehicles may be ground vehicles, watercraft or aircraft. It is likewise possible for one seeker system to be positioned on the ground and for the second seeker system to be in the air, for example in an aircraft, a guided missile or the like. 
         [0014]    In one advantageous embodiment of the invention, at least one of the seeker systems is part of a carrier platform from which at least one missile is launched. Systems for ground-based air defense can be distributed between a number of vehicles, which are positioned distributed in the terrain. If at least two seeker systems are available on different vehicles, this allows the location of the flying target to be determined in a “silent mode”. In this case, the carrier platforms, that is to say the launches, can be located precisely anywhere in the battlefield. 
         [0015]    It is also advantageous for the seeker system on the carrier platform to be provided in addition to a seeker system in the missile to be launched. This embodiment has the advantage that the missile can be aligned with the target even when it itself has no view of the target. In this case, the seeker system in the carrier platform can detect and track the target, and can transfer target data to the missile. If the data is suitably selected, the seeker system in the missile can detect the target as such on the basis of the transferred target data, while it has no view of the target. For example, it is possible to simulate the missile itself being able to view the target to be tracked, such that the missile can at this stage carry out preparatory actions for launching—even when it cannot itself view the target since, for example, it is stored in a closed container. The seeker system in the missile can in this way detect the target even when in a closed container, thus providing a lock-on before launch capability (LOBL capability). 
         [0016]    The target data must adequately describe the target, and may be any desired data which satisfies this requirement. The target data may be image data or data from image processing. Image data from a seeker system on the carrier platform is particularly suitable, in particular an image of the target recorded by the seeker system in the carrier platform. Alternatively or additionally, the target data may be data which was determined from evaluation of an image recorded by the seeker system in the carrier platform. Data can be used relating to the direction and/or movement of the target, and/or image data of the target, such as an intensity, shape or an extent of the target. The target data transferred to the missile from the carrier platform is expediently the same data which the seeker system in the missile would produce if it were at the same point as the seeker system in the carrier platform. 
         [0017]    The carrier platform may be a ground-based launch site for the missile, for example a goods-vehicle trailer, or an aircraft in which the missile is mounted such that it can be launched, in order to provide good aircraft camouflage. 
         [0018]    It is also advantageous for a missile to be launched from a carrier platform, and for one of the two seeker systems to be part of the missile, and for the second seeker system to be part of the carrier platform. This allows the location of the target to be determined from just a single vehicle, once the missile has been launched from that vehicle. This provides the necessary distance between the two seeker systems to allow the location to be determined by triangulation. The measurement data from the seeker system on the carrier platform is expediently transmitted to the seeker system in the missile, thus allowing data fusion to be carried out at the location of the missile, as a result of which the missile knows the range to the target being aimed at. 
         [0019]    The location of the target can be determined at an early stage, if both seeker systems are each part of a carrier platform from which missiles are in each case launched. An approaching target can be identified, measured and attacked at an early stage, for example by a group of vehicles. 
         [0020]    In order to improve the defense success probability, it is advantageous to use both seeker systems to determine a flight path and an impact point on the target. If the impact point is at a location which is not dangerous, then the attack can be cancelled, while a dangerously approaching target can be attacked with priority, for example simultaneously from a plurality of carrier platforms. In this case, it is advantageous to use the flight path to determine which of the two carrier platforms will be used for defense against the flying target. It is advantageous to use that carrier platform for defense against the flying target which is closest to the impact point on the target. Since the line-of-sight angle relative to this carrier platform changes least, it is best to carry out the attack from this carrier platform. 
         [0021]    A further advantageous embodiment of the invention provides for these seeker systems to be part of a group of vehicles comprising at least three vehicles each having a carrier platform for launching missiles, which are linked to one another via a data network, and for the location to be determined locally in at least two of the vehicles. The central data fusion, evaluation and determination of the location of the target mean that the network will remain functional even if individual network nodes fail, for example because they have been hit. It is possible to access one of the nodes at any time, such that the determined position of the target or its range to each node point can be known. 
         [0022]    With the above and other objects in view there is also provided, in accordance with the invention, an apparatus for determining a location of a flying target, comprising: 
         [0023]    at least two passive seeker systems disposed at a distance from one another; and 
         [0024]    at least one processing device connected to the seeker systems, configured to measure a position of the target from measurement data acquired by the seeker systems, and configured to determine the position of the target relative to the at least two seeker systems from the measurement data; 
         [0025]    wherein the seeker systems are data-networked, passive target tracking systems for missiles configured to autonomously track the target and to align the missiles with the target. 
         [0026]    In other words, the objects relating to the apparatus are achieved by an apparatus for determining the location of a flying target having at least two passive seeker systems which are at a distance from one another, and having at least one process means which is provided to measure the position of the target from data from both seeker systems, and to determine the position of the target relative to the two seeker systems from the measurement data. It is proposed that, according to the invention, the seeker systems are data-networked, passive target tracking systems for missiles which are provided to autonomously track the target and to align the missiles with the target. Passive location determination can be achieved by simple means, such that the apparatus remains well concealed. 
         [0027]    Other features which are considered as characteristic for the invention are set forth in the appended claims. 
         [0028]    Although the invention is illustrated and described herein as embodied in a method and apparatus for determining the location of a flying target, it is nevertheless not intended to be limited to the details shown, since various modifications and structural changes may be made therein without departing from the spirit of the invention and within the scope and range of equivalents of the claims. 
         [0029]    The construction and method of operation of the invention, however, together with additional objects and advantages thereof will be best understood from the following description of specific embodiments when read in connection with the accompanying drawings. The drawing and the description contain numerous features in combination, which a person skilled in the art will expediently also consider individually, and will combine to form worthwhile further combinations. 
     
    
     
       BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWING 
         [0030]      FIG. 1  is a diagram of a plurality of vehicles, distributed over a terrain, each having a carrier platform for launching missiles; 
           [0031]      FIG. 2  shows a missile that has been launched from an aircraft; 
           [0032]      FIG. 3  shows the missile still within the aircraft; and 
           [0033]      FIG. 4  is a schematic diagram of seeker systems, linked to one another, in the aircraft and in the missile. 
       
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
       [0034]    Referring now to the figures of the drawing in detail and first, particularly, to  FIG. 1  thereof, there is shown a group of vehicles which each have a carrier platform  2 ,  4 ,  6  for launching a plurality of missiles. Each carrier platform  2 ,  4 ,  6  is fitted with 16 containers, in each of which one missile is completely enclosed, such that it is protected against external influences, such as dirt or radiation, and cannot view the outside world. Each of the missiles has a seeker head with a passive seeker system, which is sensitive in the infrared spectral range and is prepared for detection and tracking of a target  8 . The seeker system is illustrated in more detail in  FIG. 4  and will be described in greater detail with reference to  FIG. 4 . The same seeker system  10 ,  12 ,  14  as that on each missile is additionally provided on each carrier platform  2 ,  4 ,  6 . 
         [0035]    The seeker systems  10 ,  12 ,  14  are all networked with one another for signalling purposes, such that they can interchange their position and target data. Furthermore, the carrier platforms  2 ,  4 ,  6  are equipped with receivers to receive position data, for example GPS data, as a result of which their positions are known. 
         [0036]    If at least one of the seeker systems  10 ,  12 ,  14  identifies a target  8 —the target  8  in  FIG. 1  is an approaching artillery rocket—then it signals this to the other seeker systems  10 ,  12 ,  14 . The seeker systems  10 ,  12 ,  14  direct their seeker optics at the target  8 , and track it. In order to determine the range between the target  8  and a predetermined location, for example one of the seeker systems  10 ,  12 ,  14 , the target  8  is measured by the seeker systems  10 ,  12 ,  14 . For this purpose, the seeker systems  10 ,  12 ,  14  each measure the relative angle  16  between their line of sight to the target  8  and a further predetermined direction, for example an absolute direction or to an adjacent seeker system  10 ,  12 ,  14 , as is indicated in  FIG. 1 . The relative angles  16  are solid angles in three-dimensional space, and each consist of a two-dimensional unit vector with two polar coordinate elements. 
         [0037]    The range  20  between the target  8  and at least two seeker systems  10 ,  12 ,  14  is determined from the relative angles  16  from at least two seeker systems  10 ,  12 ,  14  and the distance  18  between them. The process of alignment of the missiles from the corresponding carrier platforms  2 ,  4 ,  6  with the target  8  now includes not only the direction of the target  8  but also the distance from the carrier platforms  2 ,  4 ,  6  and the target. In another embodiment of the invention, the location coordinates of the seeker systems  10 ,  12 ,  14  are also used to determine the position of the target  8 . The network therefore knows the absolute location of the target  8 , in addition to the range. 
         [0038]    The velocity of the target  8 , its flight trajectory and, therefrom, its predicted impact point  22  are calculated from the change in the location of the target  8  over time. In  FIG. 1 , the impact point  22  is close to the carrier platform  4  which is that one of all the carrier platforms  2 ,  4 ,  6  which is closest to the impact point  22 . This carrier platform  4  is therefore assigned to attack the target  8 . The carrier platform  4  aligns one of its missiles with the target  8 , for example by passing control commands to the missile to align its flight with the target  8 . It is likewise possible to align the seeker optics of the seeker system in the missile with the target  8  even before the missile has been launched from the closed container. Before, during or after alignment, the missile is launched, flies to the target  8 , and attacks it. The selection of the carrier platform  2 ,  4 ,  6  to attack the target  8 , and the determination of the location of the target  8 , can be carried out centrally in one vehicle, or locally in all or a number of the vehicles. 
         [0039]      FIG. 2  illustrates a further exemplary embodiment. A missile  26  has been launched from an aircraft which is used as a carrier platform  24  for the missile  26 . Its seeker head includes a seeker system  28  which is aligned with the target  30 . A seeker system  32  which is arranged on the nose of the carrier platform  24  is likewise aligned with the target  30 . The target  30  is measured from both seeker systems  28 ,  32 , analogously to the description relating to  FIG. 1 . The carrier platform  24  transmits its measuring results to the missile  26 , as is indicated in  FIG. 2 , and the missile  26  calculates the range from it to the target  30 , and in particular to the absolute location of the target  30 , by data fusion from both measurement data items. 
         [0040]    In a further exemplary embodiment, the location of the target  8 ,  30  can also be determined using only one of the carrier platforms  2 ,  4 ,  6  from  FIG. 1 , by viewing the target  8 ,  30 , launching the missile  26  and measuring the target  8 ,  30  as described with reference to  FIG. 2 . 
         [0041]      FIG. 3  shows the missile  26  still in a closed container  34  on the aircraft, even before the missile  26  has been launched.  FIG. 4  shows the seeker systems  28 ,  32  in the aircraft and the missile  26 , which is still located in the aircraft, in more detail. The description relating to  FIGS. 3 and 4  can be applied analogously to a missile in a carrier platform  2 ,  4 ,  6  as shown in  FIG. 1 . 
         [0042]    The seeker systems  28 ,  32  each contain seeker optics  36 ,  38  with lenses and/or mirrors, a detector  40 ,  42 , seeker image processing  44 ,  46 , and a process means  48 ,  50  for target detection, target tracking and for controlling actions. The seeker systems  28 ,  32  are each connected to one another by a respective interface  52 ,  54  for signalling purposes. The link is provided, for example, via a cable  56  with a weak point, while the cable  56  is torn off the carrier platform  24  when the missile  26  is launched. 
         [0043]    In a first embodiment, the seeker optics  36 ,  38  are identical, as are the detectors  40 ,  42 . This results in identical images being formed on the detectors  40 ,  42 —assuming the same position and alignment in three dimensions—and being processed by the seeker image processing means  44 ,  46 , which can likewise be the same. This results in the same image data and/or the same data being output from the image processing from the seeker image processing means  44 ,  46 , and being supplied to the process means  48 ,  50 . The image processing means  46  passes its data to the process means  50  which, for example, passes on the image recorded by the seeker system  32  to a pilot of the carrier platform  24 , to be precise to a display means for the pilot. However, the image or the image data can also be transferred via the interfaces  52 ,  54  to the process means  48  as target data, which process means  48  has two, for example symmetrical, inputs. The images or to be precise the image data, from both seeker image processing means  44 ,  46 , are or is therefore available to the processing means  48 , in which case the images and/or image data may be identical. In this embodiment, the target data is therefore image data, that is to say data which contains information relating to an image. In other embodiments, the target data may be other data, for example data which has been obtained from image processing. In any case, the target data is data which describes the target. 
         [0044]    As is illustrated in  FIG. 3 , the missile  26  is enclosed in the container  34 , such that its seeker head and its seeker optics  36  contained therein has no visual contact with the target  30 . Nevertheless, an image is available to the processing means  48 , which image the seeker system  28  in the missile  26  would itself produce if it had a free view of the target  30 , apart from a possible small image offset resulting from the different positions of the seeker systems  28 ,  32  on or in the carrier platform  24 . The free view of the target  30  is therefore simulated for the seeker system  28 , as a result of which the seeker system  28  reacts in precisely the same way as if it itself has a free view of the target  30 . 
         [0045]    One of these reactions is for the processing means  48  to detect the target  30  on the basis of the image data or images from the seeker system  32 . This results in the target being detected by the missile  2 , to be precise its seeker system  12 , even before it has a free view of the target  8  for the first time. A further action is for the target  30  to be tracked by the seeker system  28  in the missile  26  during the movement of said target  30  relative to the carrier platform  24 . For this purpose, the target  30  is tracked in the image by the process means  48 , which passes control commands to the seeker optics  36 , as a result of which the latter is aligned with the target  30 . The control data is obtained analogously to the way in which the control data for the seeker optics  38  is obtained by the process means  50  in the carrier platform  24 . The seeker optics  36  in the missile  26  are therefore simultaneously slaved with the seeker optics  38  in the carrier platform  24 . The simulation of the free view of the target  30  allows the missile  26  to carry out all actions which it will carry out itself if it has a free view of the target. For example, it can control an actuator  58  in order to carry out a movement. 
         [0046]    After successful target detection, the missile  26  is launched from the carrier platform  24  and now autonomously tracks the target  30 , as is illustrated schematically in  FIG. 2 . In order to launch the missile  26 , it is ejected downwards out of the carrier platform  24 , with the data link between the missile  26  and the carrier platform  24  being torn off. This initiates the process of unfolding the wings and starting of the rocket motor in the missile  26 , as a result of which the latter now flies to the target  30  autonomously. The target tracking is in this case carried out with the aid of the seeker optics  36 , which now have a free view of the target  30  and are therefore no longer aligned with the external target data from the carrier platform  24 , with the target being tracked by its own target data from images of the target  30  that it has itself recorded. 
         [0047]    The time for switching from the processing of external target data, for example external images, to the processing of the seeker system&#39;s  28  own target data is selected by the process means  48 . In this case, it possible to choose the time at which the data link is torn off, or an earlier or later time. Independently of this, the target tracking by the process means  48  at the time of switching is carried out in error-tolerant mode in the same way as before and after switching, in order not to lose the target in the event of any possible image offset or changes in the target characteristics in the image. For example, it can be operated in the same mode which is chosen when the target  30  is concealed for a short time, and is then reacquired. 
         [0048]    In a further embodiment of the invention, the seeker systems  28 ,  32  are not identical. This is worthwhile if different missiles  26 , which have different seeker systems  28 , are fired from the carrier platform  2 ,  4 ,  6 ,  24 . In order to ensure the LOBL capability for all missiles  26  within the carrier platform  2 ,  4 ,  6 ,  24 , that is to say when still in the “blind” state, the process means  50  in the aircraft or the carrier platform  2 ,  4 ,  6  selects appropriate data forms for transfer to the corresponding seeker system in the selected missile  26 , thus resulting in sight simulation for each missile  26 . After a missile  26  which is intended to be the next to be launched has been selected, the process means  50  knows the data relating to the seeker system  28  of the selected missile  26 . In this case, the seeker system  32  is designed, in particular with respect to its seeker optics  38  and the detector  42  as well as the seeker image processing  46 , such that target data, for example an image or image data, can be made available to each of the missiles  26 , which the corresponding missile  26 , to be precise its seeker system  28 , would itself have produced if it had had a free view of the target  8 ,  30 . In this case, each missile  26  is provided with an appropriate interface  52  for data coupling to the seeker system  32  of the carrier platform  2 ,  4 ,  6 ,  24 . Before a missile  26  is launched, data is now made available to each missile  26  providing the process means  48  in the missile  26  with the capability to use the simulation of the view of the target  8 ,  30  to carry out the corresponding actions which it would have carried out if it as itself had a free view of the target  8 ,  30 .