EP3118566B1 - Method for protecting a vehicle against an attack by a laser beam - Google Patents

Description

The invention relates to a method for protecting a vehicle from attack by a laser beam emanating from a laser source.

High-energy lasers can transmit very high power over several kilometers and over a longer period of time. With such services, sensitive parts of vehicles can be so severely damaged or destroyed within a few seconds that the functioning of the vehicles is jeopardized. Thus, for example, aircraft can be attacked from the ground, in particular slow-moving commercial aircraft with relatively low maneuverability are particularly vulnerable.

To protect objects and to warn against laser radiation, various methods and systems are known from the prior art. The WO 02/14777 A1 describes a method for protecting an object from a laser device, wherein upon detection of a laser radiation of the laser device retroreflectors are ejected or fired from the object to be protected or from an environment thereof, to disturb the laser device or possibly damage. According to the EP 2 752 681 A1 To alert a pilot of an aircraft from impinging laser radiation, the aircraft is equipped with a laser detection and warning system, with which, inter alia, the location of a laser source can be determined.

It is therefore an object of the present invention to provide an effective method for protecting a vehicle from attack by a laser beam.

This object is achieved by a method according to the features of claim 1, wherein the position of the laser source is determined and a guided missile is launched and directed to the laser source. The missile can approach and combat the laser source and shade the vehicle during the approach to the laser source. This is done expediently so quickly that the laser energy deposited on the vehicle has not yet led to threatening damage. A fast protection can be achieved by starting the missile from the vehicle, since then the missile is already on site and dive into the laser beam for shading and can quickly fly to combat the laser source on this. For this purpose, the missile is expediently equipped with a rocket motor. The guided missile may approach the laser source mechanically destroy by means of an active part, for example, by a cone-shaped forward splintering charge.

The method is particularly suitable for use against a high energy laser source or a high energy laser beam. Also advantageous is a defense of a sturgeon laser. For this purpose, a sensor of a sensor system of the vehicle and / or the missile is expediently sensitive in a radiation spectrum which is usually used for high-energy laser or interfering laser. To facilitate detection of stray radiation, the spectrum in which the sensor is sensitive may be limited to a band about one laser wavelength commonly used for high energy lasers. For example, the band is at most ± 100 nm around the wavelength of 3800 nm. In addition, the sensor expediently recognizes characteristics typical of laser radiation, such as the presence of coherent radiation. Further, it is advantageous if by means of image processing methods, a laser source is recognized as such, for example, based on an image of the laser beam in the air or by residual heat radiation when the laser source is turned off. For this purpose, an image sensor is advantageously present, for example with a matrix detector.

The vehicle is preferably an aircraft, and the invention is also advantageously applicable for protecting a land vehicle or a watercraft. A control unit of the vehicle may have one or more computing units, which may be arranged in the vehicle at a location or distributed over the vehicle. The control unit expediently recognizes the laser beam as such and initiates a start of the missile as a function of the recognition result. If a laser beam is recognized as such and it is also classified as threatening to the vehicle, the missile is launched, in particular from the vehicle. If a laser beam is not recognized as such or classified as non-threatening, the launching of the missile expediently fails.

The guided missile is expediently an unmanned guided missile, in particular with a rocket motor. Also possible is a missile without its own engine, for example in the form of a steering column. The missile expediently comprises a control unit which directs the missile towards the laser source.

The position of the laser source can be determined in various ways. In a first possibility, a sensor of the sensor system of the vehicle and / or the missile captures an image of the laser beam. By means of image processing methods, the location of the laser source of the laser beam can be determined therefrom, for example because the laser source is visible from the image as such. Another possibility is that from the image a straight line of the laser beam in the environment and a defined end of the laser beam or the line is determined. This can be done by a control unit of the vehicle or a control unit of the guided missile. This end can be defined as the location of the laser source, and the missile can drive that position. From other parameters, for example, that the end is a lower end or the end is an abrupt end, whereas the laser beam in the other direction is continuously weaker, it can be assumed that the laser source is arranged at this beam end. Accordingly, this location can be used for the steering of the missile, which flies to the end of the laser beam or the location. Another possibility is that the location of the laser source is determined by means of a non-optical sensor, such as a radar sensor or the like.

The position of the laser source can be determined from the vehicle and transferred to the missile. The location may alternatively or additionally be determined by the guided missile. The position of the laser source may be determined as absolute, geographical coordinates or relative to the vehicle and / or missile.

The guided missile flies towards the laser source and expediently uses the laser beam as a guide beam for driving the laser source. In general, there are several options for this.

In a first possibility, a control unit of the missile determines the position of the laser source and controls it. The determination can take place by means of image processing, as described above, wherein the guided missile independently determines the position or the position is determined by the vehicle and is transmitted to the missile.

In a second possibility, the intensity of radiation emitted by the laser source in direct line to the missile is recorded as a measured variable. A sensor will open directed the laser source and receives the laser radiation thrown by the laser source in a direct line on the sensor. By diffraction and scattering in the laser source of the laser beam is widened to a small extent, the detected laser intensity increases with increasing proximity to the laser beam, ie with decreasing angle to the spatial direction of the laser beam. An increase in the measured intensity of the laser radiation is therefore a sign of an approach to the laser beam. This method requires a forward sensor, which has the disadvantage that it can be hit and destroyed directly by the laser beam. Immersion in the laser beam should therefore be avoided.

This disadvantage can be circumvented by a third possibility, which is based on the measurement in the air scattered laser radiation. The laser radiation is spatially scattered on its way through the air to a small extent, so that the laser beam is visible as a line in the landscape. This intensity of the scattered radiation can be measured and increases with decreasing distance to the laser beam. The intensity can be used as a control variable for steering the missile. This method has the advantage that laser radiation scattered in the ambient air can be detected with sideways or backward sensor systems, which can both be protected towards the front. In the following, sideways sensor technology is understood as meaning a sensor system which is oriented exclusively in a lateral direction relative to the longitudinal axis of the missile and which is therefore not oriented in the direction of flight, and a rearward sensor is directed precisely opposite to the direction of flight of the missile, generally also in the lateral direction, but likewise not Forward.

The measurement of the scattered radiation has the further advantage that it can take place both from outside the laser beam and from within the laser beam and in both cases is suitable for steering the guided missile.

In an advantageous embodiment of the invention, a distance of the laser source to the vehicle is determined. For this purpose, the direction of the laser beam is expediently determined, which may be an absolute direction, for example in geographical coordinates, or a relative direction to the orientation or direction of flight of the vehicle. The determination of the distance of the laser source can be done particularly easily using a flying height of the vehicle and the direction. For this purpose, topographical data of a landscape overflown by the vehicle are expediently included. Alternatively or additionally, the Distance by triangulation using a plurality of spaced sensors done. For example, the vehicle is equipped with a plurality of sensors that detect the laser beam and / or the laser source. From the orientation of the laser source to a reference direction of the respective sensors and the alignment of the reference directions of the sensors to each other can be calculated using triangulation, the distance in a simple manner.

The missile expediently flies in the laser beam and is in this case controlled so that it remains in the laser beam, so that in this way the vehicle remains at least partially shaded by the laser beam during this flight. For this purpose, the guided missile can fly at least substantially parallel to the laser beam, which can also be understood to mean swaying in the laser beam, so that the laser beam at least partially remains directed at the guided missile. As directed to the guided missile laser beam can be understood the missile laser beam core whose power per cross-sectional area is at least for example 30% of the maximum power per cross-sectional area, the maximum power per cross-sectional area is to be seen at the location of the missile, since the power per cross-sectional area with increasing distance decreases to the laser source.

Furthermore, it is advantageous if the position of a shading corridor between the laser source and the vehicle is determined. The location of the shading corridor can be calculated from the location of the laser source and the location of the vehicle. The shading corridor may include all points at which the missile may be to shade the vehicle. The end of the shading corridor at the laser source remains fixed in space or moves along with the movement of the laser source. The other end moves with the moving vehicle. If the position of the shading corridor is known, then the guided missile can be controlled as a function of its position relative to the shading corridor. For example, the missile is held within the Abschattungskorridors so that it always shields the vehicle here.

The shading corridor may range from the laser source to the vehicle and be configured in geometry to include all of the imaginary lines from the laser source to all points of the vehicle. Lines from the laser source to areas other than in the vehicle or more than a predetermined distance from the vehicle are not within the shading corridor.

The areas of a vehicle are usually different laser hard, and also less laser-hard points are present whose destruction does not lead to a critical condition of the vehicle in general. It is therefore advantageous if a shading protection is limited to one or more laser-sensitive points of the vehicle. This allows these sites to be protected more effectively. A laser-sensitive location may be such a location or area whose irradiation with a high energy laser for a period of less than 5 seconds generally results in a critical condition of the vehicle

Accordingly, it is advantageous if the shading corridor is limited to a space between a laser-sensitive location of the vehicle and the laser source. In this case, not only a geometric point is to be understood as a point, but a spatially extended area which is to be protected from irradiation by high-energy laser radiation. The sum of the laser-sensitive points of the vehicle is expediently limited to a maximum of 25% of the silhouettes of the vehicle visible from the laser source.

One way of defending a laser system against an approaching guided missile is to pivot the laser beam so that following the missile deflects the missile from the shadowing corridor. By quickly swinging back the laser beam onto the vehicle and the inertia of the guided missile, the vehicle can be re-irradiated without the missile being able to shade the vehicle. To thwart this defense as possible, it is proposed that a flight space is determined within which the missile moves. The flight space is determined, for example, from the distance between the laser source and the vehicle. The guided missile is now controlled to remain within the flight space.

The space can be confined to a very thin corridor with a small area to be protected, which moves with the movement of the vehicle through the room. However, control inaccuracies and inaccuracies in determining the position of the laser source, the vehicle, and / or the missile may result in inaccuracies in steering control of the missile. This uncertainty can be greatest where the distance to the laser source and to the vehicle is greatest, thus in an area in the middle between the vehicle and the laser source. It is therefore advantageous if one Flight of the missile between the laser source and the vehicle is determined, which is tapered to both the laser source and to the vehicle. Generally, the flight space is expediently rotationally symmetrical and may, for example, have the shape of a football ice.

The flight space is suitably determined using the shading corridor. In this case, the flying space expediently extends beyond the shading corridor, in particular in such a way that it extends furthest beyond the shading corridor in a middle region between the vehicle and the laser source. The shading corridor can hereby be limited to shading of the entire vehicle or only one or more laser-sensitive points. In the case of several laser-sensitive areas, a space between the corresponding shading corridors is expediently used as the entire shading corridor, so that a single shading corridor is created. This can be used to determine the flight envelope.

In order to achieve an undesirable deflection of the guided missile from a shading position, the guided missile expediently remains in a predetermined flying space when the laser beam disappears from a shading corridor. The disappearance may in this case be a pivoting of the laser beam from the shading space or flying space or a shutdown. The guided missile follows only partially a laser beam pivoted out of the shading corridor and expediently always remains in the flying space or is controlled accordingly.

Further, it is advantageous if the vehicle monitors the position of the flying missile. A misdirection of the missile by a control error or a destroyed sensor can be avoided. The monitoring is not only useful when the control of the missile is done completely from the vehicle. In particular, when the flight control of the missile is carried out by a control unit of the missile itself, intervention of the vehicle in the steering control can be advantageous. If, for example, the guided missile leaves the flight space, so that shading of the vehicle is endangered, intervening in the flight control can retrieve the guided missile into the flight space, so that the vehicle can be reliably shadowed.

The missile is conveniently controlled using the position of the vehicle and the position of the laser source in its flight. This control can originate from the vehicle and / or from a control unit of the guided missile. If the steering system is based solely on the guided missile, then the position of the missile should be constantly known to the missile. The position can, for example, be transmitted continuously or periodically from the vehicle to the guided missile by data link. It is also possible that the position of the vehicle is derived from an inertial position, for example a position of the vehicle at the start of the guided missile, expediently using the direction of flight and the speed of flight of the vehicle. If the position of the laser source is known, a shading corridor or flight space can be calculated by the guided missile and used for the control.

To control the missile is provided according to the invention that the missile detects the laser beam and controls its flight path as a function of its position to the laser beam. The guided missile uses the laser beam as a beacon and flies in this way towards the laser source. This flight control is conveniently combined with flight control using a shading corridor and / or flight space. In this way, in particular, a rough navigation based on shading corridor or flight space can take place and a detailed navigation can be carried out on the basis of the laser beam itself.

For the detection of the laser beam and the control of the flight path as a function of the position to the laser beam, the guided missile expediently comprises one or more sensors, which are sensitive in particular to stray radiation of the laser radiation in the air.

In a rapid pivoting or turning off the laser beam, the laser beam disappears from a sensor of the missile and / or the vehicle. In order to be able to reliably continue an approach of the guided missile to the laser source, it is advantageous for the guided missile to fly onto the laser beam when the laser beam has disappeared by means of inertial navigation. The disappearance may in this case be characterized in that the laser beam is no longer or not sufficiently detected by one or more sensors of the missile.

Another possibility is that the laser beam detects a disappearance of the laser beam and then activates a previously shaded by the laser beam sensor. The flight control is then conveniently continued using this newly activated sensor. The sensor may be a forward sensor, which expediently recognizes the laser source, for example based on thermal radiation, as such.

Even if the laser beam is present, it may be advantageous for the guided missile to activate a forward sensor which was previously shaded by the laser beam in order to be able to carry out flight control with great precision. This is particularly advantageous in the endgame of the flight, ie within the last section of the flight of the missile from the vehicle to the laser source. An activation of a forward sensor, which is usually very sensitive to laser radiation or heat radiation, should, however, only take place if the risk of direct irradiation by the laser beam is low. It is therefore advantageous if the guided missile detects a danger of the laser beam and activates a forward sensor at a danger below a limit value and uses its data for a flight to the laser source.

Since a forward sensor can be very sensitive to high energy laser radiation, this is advantageously under a hood, which is blasted off, for example, at the beginning of Endgames. Also possible and advantageous is a movable mechanical cover of the forward sensor, which opens and thus releases the view of the forward sensor forward.

In order to disturb a fight by the guided missile, the laser beam can be switched off so that it disappears and a line along the laser beam is no longer possible. An optical guidance of the guided missile can also be maintained in this situation if the missile detects a heat source of the laser source when the laser beam is switched off. Since the laser source is warm shortly after switching off the laser beam, the heat source can be detected with an infrared sensor. The guided missile can take the heat source to the target and this drive. In order to avoid confusion with another heat target, it is advantageous to compare the pattern of the heat source with data from a database. In the database, infrared patterns of post-radiation laser sources can be deposited. Fits the sensed pattern with one deposited patterns sufficiently, so the heat source can be classified as a laser source, so that the heat source can serve as a target.

The invention is also directed to a system of a vehicle and a missile having a control system according to the features of claim 10. Effective protection against irradiation of the vehicle by a high energy laser can be achieved when the control system is prepared to position to determine the laser source to start the missile and to direct this to the laser source. The control system may be present in common in the vehicle, in the missile or in both units, for example by a control unit in the vehicle and a control unit in the guided missile. Here, a task distribution is advantageous in that the determination of the laser source is advantageously carried out by a control unit in the vehicle and the steering of the missile to the laser source out through a control unit of the missile.

The description of advantageous embodiments of the invention given so far contains numerous features that are summarized in several dependent claims in several groups. However, these features may conveniently be considered individually and grouped together into meaningful further combinations, in particular when reclaiming claims, so that a single feature of a dependent claim can be combined with a single, several or all features of another dependent claim. In addition, these features can be combined individually and in any suitable combination both with the method according to the invention and with the device according to the invention according to the independent claims. Thus, process features can also be formulated formally as properties of the corresponding device unit and functional device features also as corresponding process features.

The above-described characteristics, features, and advantages of this invention, as well as the manner in which they are achieved, will become clearer and more clearly understood in connection with the following description of the embodiments, which will be described in detail in conjunction with the drawings. The embodiments serve to illustrate the invention and do not limit the invention to the combination of features specified therein, not even with respect to functional features. In addition, suitable features of each embodiment can also be considered explicitly isolated from a Embodiment away, incorporated in another embodiment to supplement it and / or combined with any of the claims.

FIG 1

ein Luftfahrzeug mit Lenkflugkörpern zur Verteidigung gegen einen Angriff durch ein Lasersystem,

FIG 2

einen der Lenkflugkörper mit mehreren Sensoren zum Detektieren von Laserstrahlung,

FIG 3

eine Verteidigung des Fahrzeugs durch einen Lenkflugkörper,

FIG 4

den Lenkflugkörper aus FIG 2 in einem Querschnitt,

FIG 5

einen Flugraum eines Lenkflugkörpers vom Fahrzeug zu einer Laserquelle und

FIG 6

einen Lenkflugkörper mit einer abwerfbaren Haube vor einer Vorwärtssensorik.

Show it:

FIG. 1

an aircraft with guided missiles for defense against attack by a laser system,

FIG. 2

one of the missiles with several sensors for detecting laser radiation,

FIG. 3

a defense of the vehicle by a guided missile,

FIG. 4

the guided missile FIG. 2 in a cross section,

FIG. 5

a flight space of a missile from the vehicle to a laser source and

FIG. 6

a guided missile with a drop-off hood in front of a forward sensor.

FIG. 1 shows a vehicle 2 in the form of an aircraft, which is designed in this example as a commercial aircraft for the transport of passengers or air freight. In a landscape 4, over which the vehicle 2 flies, a laser system 6 is positioned, which in the in FIG. 1 represented moment a laser beam 8, which is generated by a laser source 10, directed into the sky. The laser system 6 is a high-energy laser system that emits the laser beam 8 predominantly in the infrared spectral range, for example, at 3.8 microns, the laser beam 8 over a distance of several kilometers transported enough energy to destroy sensitive parts of the aircraft and thereby its flying capacity acute to endanger. The laser system 6 is used to combat aircraft and has a control unit which pivots the laser beam 8 on the vehicle 2 and the laser beam 8 automatically tracks the movement of the aircraft 2. In the control unit, a laser-sensitive point of the vehicle 2 is deposited, to which the laser beam 8 is automatically directed by means of image processing methods to the irradiate in the laser system 6 pictorially deposited location of the aircraft 2 over a period of a few seconds and thereby destroy.

To protect the vehicle 2, this has at least one missile 12, wherein in FIG. 1 to illustrate several missiles 12 are shown. Furthermore, the aircraft has a sensor system 14 with a plurality of sensors 16, which are each signaled by a control unit 18. In the embodiment shown, the aircraft is equipped with five sensors 16, one in the rear half of the fuselage, one in the front half of the fuselage, one on each wing of the aircraft and one upward sensor 16 on the upper half of the fuselage of the aircraft ,

To protect the aircraft, the sensors 16 of the sensor system 14 actively monitor the airspace for laser radiation. The sensors 16 each comprise an image sensor behind a 180 ° optics, so that the scene of a hemisphere of the surrounding space is imaged onto a laser-sensitive element. In this way, an image of the laser beam 8 can be recorded in the environment, and from this further information about the laser beam 8 can be determined, such as geometry, position and intensity of the laser beam. From the geometry recognizes the control unit 18 of the sensor system 14, in particular by means of image processing methods, the laser beam 8 as such. As geometrical features it can be used that the laser beam 8 is seen as a straight line in the landscape. In addition, it has a sharply defined end on the laser source 10. At its other end, however, the laser beam becomes weaker, as long as it does not strike an object FIG. 1 is shown, so that a defined end is not readily determinable. This feature of the upper attenuation of the laser radiation can also be used for laser detection.

From the geometric data of the laser beam 8 and its spectrum and radiation intensity, the control unit 18 first classifies the laser beam 8 in the three stages harmless, potentially dangerous and dangerous. In a harmless classification, the laser beam 8 is further observed, but the laser source 10 is not controlled. Classification in one of the other two levels will prepare for shading and / or combat. For this purpose, a canister 20, which accommodates at least one of the missiles 12, is pivoted in the direction of the laser source 10. This pivoting is in FIG. 1 indicated by the curved double arrow on the canister 20. In a classification in the highest of the Threat classes will initiate combat. For this purpose, for example, a release of an operator of the aircraft 2, such as a pilot, necessary. However, this has already been given in advance, for example because it is known that the aircraft is flying through a potentially dangerous region.

For controlling the laser source 10, it is advantageous if the position of the laser source 10 is known. This determines the control unit 18, for example, from the geometry of the laser beam 8. Thus, at the location of the abrupt end of the laser beam 8, the laser source 10 can be suspected. In addition, the laser beam 8 can be given a direction, at least a rough direction at the top and bottom, wherein the laser source 10 is positioned only at a lower end of the laser beam 8. In this way, a direction of the laser source 10 relative to the aircraft 2 can be determined. From the direction and a flight altitude of the aircraft and expediently a topography of the overflown landscape, the distance between aircraft and laser source 10 can be determined, in particular the absolute geographic coordinates of the laser source 10 are determined. The detection of the laser beam 8 takes place insofar by a recording of the laser beam 8 from the side, wherein from the laser beam 8 scattered in the atmosphere laser radiation is recorded.

In the event that the laser beam 8 is already directed at the aircraft 2 and thus the undefined upper end is no longer recognizable as such and the laser beam 8 has an abrupt end both above and below, the determination of the position of the laser source 10 by another of the sensors 16 of the sensor system 14, for example by a sensor 16 on a wing of the aircraft 2. This detects the laser beam 8 per se and both abrupt ends, the control unit 18, the lower abrupt end of the laser beam 8 as the location of Laser source 10 selects. Also possible is a position determination of the laser source 10 by means of triangulation. Once three or more sensors 16 have detected the laser beam 8 and determined its lower abrupt end, in addition to the direction of the laser source 10 and its distance can be determined by the known orientation of the sensors 16 on the aircraft 2 to each other.

To protect the aircraft, at least one missile 12 is now started by the aircraft. The control of the start takes over the control unit 18 of the Sensor system 14, which may also be part of a central vehicle control of the vehicle 2.

FIG. 2 shows one of the missile 12, which are stored in the canister 20 in the vehicle 2. The guided missile 12 has guide vanes 22 that are moved by actuators 24 for steering the missile 12. The control of the actuators 24 is carried out by a control unit 26 of the missile 12. The missile is powered by a rocket motor 28, in particular a solid fuel motor, which is disposed behind an active part 30 having an explosive charge and a fragmentary part which is conical when blasting the explosive charge is thrown forward. The ignition of the active part 30 may be effected by an impact fuse or a proximity fuse located in the missile head.

In the missile head, a sensor 32 is arranged, which is an imaging infrared sensor. The sensor 32 comprises an optical system 34 and a matrix detector 36. A filter 38 is used to shadow the detector 36. The detector 36 is arranged on a cooling unit, not shown, and connected to the control unit 26 by signal technology. For further protection of the sensor 32 whose detection area a cover 40 is arranged, which comprises two mutually movable shell elements, which are spring-driven against each other. They completely cover the detection area of the sensor 32 in the closed state and shield the sensor 32 from incident laser radiation so far that the sensor 32 remains functional for a period of at least 10 seconds behind the cover 40 when the condition is directly illuminated by the laser beam 8. FIG. 2 shows the two elements of the cover 40 in the open position, which is shown dotted. The detection area or the field of view of the sensor 32 passes through the two open elements, so that an image of the ahead of the missile 12 scenery can be made.

The filter 38 is an intensity-dependent filter which shadows automatically as a function of the intensity of the incident laser radiation. If the intensity exceeds a limit value, the filter 38 automatically becomes impermeable and thereby protects the underlying detector 36 very quickly. In addition, the filter 38 sends a signal to the control unit 26, which then immediately closes the cover 40 and thus also causes additional mechanical protection of the sensor 32.

In addition or as an alternative to the sensor 32, the guided missile comprises one or more of the sensors 42, 44, 46, 48 described below, which in FIG FIG. 2 and FIG. 4 are shown schematically.

First, the guided missile 12 includes four sensors 42 which are arranged over the circumference of the missile 12 at a distance of 90 ° to each other. In FIG. 2 For the sake of clarity, only two of these sensors 42 are shown. The sensors 42 serve to find the laser beam 8 and to stein it into the laser beam 8. The sensors 42 form a sideways sensor with a field of view to the side of the missile 12, which is indicated by dotted lines. Within the field of view, there are no elements of the missile 12, so that the sensors 42 sense only in the air surrounding the laser beam 8 scattered laser radiation. The intensity of the laser radiation thus sensed is a measure of the distance of the guided missile 12 from the laser beam 8. The tangential arrangement of the four sensors 42 on the circumference of the missile 12 can also determine the direction in which the laser beam is relative to the missile 12.

According to the sensor signals of the sensor 42, the control unit 26 causes the flight of the guided missile 12 to the laser beam 8 out. The direction results from a combination of the direction of those sensors 42 which receive the strongest scattered light signal of the laser radiation.

As soon as the guided missile 12 is immersed in the laser beam 8 and thus hit directly by the laser beam 8, a fine control is performed on the basis of the sensors 44, 46 and / or 48, which are present together or only individually in the guided missile 12. The sensors 44 form - like the sensors 42, 46 and 48 - a group of a plurality of sensors, in the embodiment shown four sensors, which are arranged uniformly tangentially spaced from each other in the periphery of the missile 12 on the outer shell of the missile. In the exemplary embodiment shown, a sensor group has four sensors 42, 44, 46, 48, which are tangentially 90 ° apart. All sensors 42, 44, 46, 48 are arranged in one or more recesses 50 in the outer shell of the missile 12 and are thus shaded forward. A laser beam 8 impinging on the guided missile 12 from the front can thus not reach the sensors 42-48. Even with a tilt of up to 30 ° of the missile axis to the axis of the laser beam 8, the sensors 42 - 48 remain shaded by the laser beam 8.

The sensors 44 have a field of view 52, which in FIG. 2 by dashed lines and in FIG. 4 is realized by a respective dashed line indicated area. A field of view of a sensor 44 is directed to a leading edge of a fin 54 of the missile, with each of the sensors 44 directed to another fin 54. On the representation of the wings 22 was in FIG. 4 omitted for clarity. If the front edge of the fin 54 is hit by the laser beam 8, this is detected by the corresponding sensor 44, so that the offset of the laser beam 8 relative to the guided missile 12 can be determined. By a quantitative measurement of the sensors 44 is also measured how far the fin 54 dips into the laser beam 8, so that in addition to the direction of the offset and the size of the offset of the laser beam 8 to the missile 12 can be detected.

The flight of the guided missile 12 is controlled so that it dives as deeply as possible in the laser beam 8, so in particular lies centrally in the laser beam 8. The guided missile 12 in this case flies parallel to the laser beam 8 in this direction to the laser source 10. As a result, the vehicle 2 is shadowed by the missile 12 from the laser beam 8 and thus protected.

By directed onto the fins 54 fields 52 of the sensors 44 of the missile can be kept centered in the laser beam 8. This is done by the sensor signals of the sensors 44 are used as a control input for steering control of the missile 12. As Lenk target the signals of the sensors 44 should be the same, so that all fins 54 are illuminated equally strong. This is a sign of a central or centered flight of the guided missile 12 in the laser beam 8.

By transverse wind, steering error, Verschwenkungsbewegungen of the laser beam 8 and the like, the missile axis is tilted during the flight again to the axis of the laser beam 8. Such tilting is not immediately recognizable by the illumination of the fins 54. To detect such a tilt serve the sensors 46. Each of the sensors 46 has a field of view 56 which in FIG. 4 is indicated by a dashed rectangular area. The field of view 56 is directed to a slope 58 in the outer wall of the missile 12, which is divided into two areas 60, 62. Here, the inner region 60 is provided with a different surface than the outer region 62. The surfaces differ for example by a roughness and / or a coating, such as a color and / or a scattering layer. While the fields of view 56 of the sensors 46 on the outer area 62 are directed, the fields of view 64 of the sensors 48 are directed to the inner portion 60 of the slope 58. At the in FIG. 4 In the embodiment shown, the regions 60, 62 are coated with different colors, and the sensors 46, 48 are sensitive only in a narrow spectral window of the color of their field of view 56, 64.

Now, if the guided missile 12 is tilted to the laser beam 8 and is hit by this, the laser beam 8 will illuminate at least the outer region 62 directly. This is detected by the sensors 46. From the tangential arrangement to each other, the direction can be determined in which the missile axis is tilted to the laser beam 8 and its axis. In addition, the tilt increases with increasing intensity of the sensor signal of the respective sensors 46.

With still increasing tilting of the laser beam 8 hits the inner portion 60 of the slope 58, whereby the sensors 48 output a corresponding signal. Again, the tilt increases with increasing sensor signal. From the signals of the sensors 46, 48, therefore, the direction of the tilt and the magnitude of the tilting of the missile axis for the alignment of the laser beam 8 can be determined. The steering or the guide vanes 22 are controlled using the sensor signals and the tilting is thereby reduced, in particular until a parallel flight of the steering missile 12 to the laser beam 8 is achieved.

Several methods for protecting the vehicle 2 are described below FIG. 3 and FIG. 5 explained. After detecting the laser beam 8 and the localization of the laser source 10 by the sensor system 14 of the vehicle 2 and the classification of the laser beam 8 as threatening the missile 12 is started from the canister 20 in the direction of the laser source 10 out. Before, during or after take-off, a target transfer or instruction of the vehicle 2 to the guided missile 12 takes place. The control unit 18 transfers both the coordinates of the target and the position and orientation of the laser beam 8 to the control unit 26 of the guided missile 12 by means of wireless data transmission. The coordinates here are absolute, geostationary coordinates, wherein the coordinate errors in the indication of the position of the laser source 10 can be quite large, as these could not be detected by the vehicle 2 itself. Based on this coarse instruction, the guided missile 12 flies toward the laser beam 8 whose position and orientation is roughly known to it.

During the approach, the incident radiation in the wavelength of the laser beam 8 is monitored by the sensor 42. The closer the guided missile 2 moves to the laser beam 8, the greater the detected radiation intensity. The guided missile 12 is guided into the laser beam 8, wherein the control is now carried out on the basis of the signals of directed exclusively in the rear half-space backward sensor 44 - 48. The guided missile 12 is held in the laser beam 8 and flies parallel to it to the laser source 10 out. If the laser beam 8 remains still and does not disappear, the guided missile 12 can fly exclusively to the laser source 10 under the guidance of the laser beam 8.

The guided missile 12 flies toward the laser source 10 using the laser beam 8 as a guide beam. When approaching below a predetermined distance of the steering missile 12 to the laser source 10 of the active part 30 of the Lenklugkörpers triggers and the fragmentation charge is thrown cone-shaped to the laser source 10 and destroys them. An approach of the missile 12 to the laser system 6 can be detected by this, and the laser system 6 can initiate action. A countermeasure may include that the laser beam 8 is pivoted and the steering missile 12 following the laser beam 8 is deflected so far that it no longer shades the vehicle 2. To avoid this, the guided missile 12 is controlled so that it remains within its flight to the laser source 10 within a Abschattungskorridors 66 which in FIG. 3 indicated by two solid lines. The shading corridor 66 extends from the laser source 10 to the vehicle 2 and is configured in its geometry to include all imaginary lines from the laser source to all points of the vehicle 2. However, lines from the laser source 10 to spatial points which are more than a predetermined distance laterally from the vehicle 2 are not within the shading corridor, as in FIG FIG. 3 is indicated. This distance serves to compensate for computing inaccuracies and is expediently less than 50 m, in particular less than 10 m. The shading corridor 66 is calculated by the control unit 18 from the positions of the laser source 10 and the vehicle 2 as well as the dimensions, the orientation and / or the direction of movement and speed of the vehicle 2 in space. The position of the shading corridor 66, in particular its geometry and position in space, can be determined in absolute, earth-fixed coordinates or in relative coordinates which refer to a reference space moved with the vehicle 2.

Further, in the control unit 18 of the vehicle 2, a plurality of laser-sensitive points 68, 70 deposited, which in FIG. 3 are indicated. These laser-sensitive areas 68, 70 include those areas on the vehicle whose irradiation by a high-energy laser within a predetermined period of, for example, less than 10 s lead to damage to the vehicle 2, which affects its overall functioning. Shading passages 72, 74, which are calculated in FIG. 2, are also calculated for these laser-sensitive points 68, 70 FIG. 3 dotted, or dashed, are indicated. Corresponding to the shading corridor 66, the shading corridors 72, 74 exclusively comprise all the imaginary lines from the laser source 10 to all possible points of the laser-sensitive spots 68, 70.

The flight of the missile 12 is controlled so that the missile 12 always within the Abschattungskorridors 66, or 72, 74 remains, depending on how the flight control was deposited in the control unit 18 and passed to the control unit 26 of the guided missile 12. Leaves the laser beam 8 the Abschattungskorridor 66, so he no longer applies to the vehicle 2, the missile 12 still remains within the Abschattungskorridors 66 to a renewed pivoting of the laser beam 8 on the vehicle 2, that can shadow vehicle 2 as quickly as possible , In particular, the guided missile 12 remains within one of the special shading corridors 72, 74 for the protection of the laser-sensitive point 68, 70. If the laser beam 8 leaves one of the shading corridors 72, 74, it remains in the shading corridor 66, thus striking the vehicle 2 at a non-laser-sensitive location , so the guided missile 12 still remains within its Abschattungskorridors 72, or 74 in order to protect the respective laser-sensitive point 68, or 70 swiftly when the laser beam 8 pivots renewed on this.

The control of the missile 12 within the Abschattungskorridore 66, 72, 74 can be done by a control system that includes both the control unit 18 in the vehicle 2 and the control unit 26 in the guided missile 12. The control unit 26 assumes the fine control and the control unit 18 the coarse control. The control of the vehicle 2 engages in the control by the missile 12 itself and serves as a higher-level control. For this purpose, the current position of the missile 12 is monitored by the vehicle 2. If the guided missile 12 is flying in the desired shadowing corridor 66, 72, 74 within the laser beam, the control unit 18 will not intervene and the flight control will become only taken from the missile 12 itself. If, however, the laser beam 8 is swiveled from a currently irradiated sensitive point 66 to another laser-sensitive point 70, then the control unit 18 can intervene in the flight control in order to accelerate a flight correction. The guided missile 12 is instructed on the new to the laser-sensitive point associated Abschattungskorridor 74 and flown there. The fine control for immersion in the laser beam 8 and for holding the guided missile 12 can in turn be performed by the missile 12, or its control unit 26.

If the laser beam swivels within the shading corridor 66, 72, 74, then the guided missile 12 will follow this pivoting in order to stay within the laser beam 8 and shade the vehicle. If this is not desired, because the guided missile 12, for example, in a Abschattungskorridor 72, 74 should remain so engages the control unit 18 corrective and keeps the missile 12 in the desired Abschattungskorridor 72, 74. The same applies to the situation in which the laser beam 8 is pivoted out of the large shading corridor 66. Flying over of the guided missile 12 is prevented by the control unit 18 of the vehicle 2 and the missile 12 is held within the desired Abschattungskorridors 66, 72, 74.

In an alternative or additional possibility, the guided missile 12 determines a shading corridor 66, 72, 74 itself and also controls the rough navigation itself, so that intervention by the vehicle 2 is not necessary or can be limited to exceptions. For this purpose, the guided missile 2 determines its own position during its flight to the laser source 10 out, for example, using the interior navigation. In addition, it determines the position of the vehicle 2, for example by estimating the position of the vehicle 2 from an initial position, for example a position at a start of the guided missile 12, and an update of the flight based on the speed and direction of the vehicle 2. It is also possible that he receives the position of the vehicle 2 by a data link from this. From the three positions of the laser source 10, the guided missile 12 and the vehicle 2, the guided missile 12 calculates the corresponding shading corridor 66, 72, 74 and keeps its flight therein. If the vehicle 2 detects that the guided missile 12 erroneously controls, for example, because it leaves the rejected shading corridor 66, 72, 74, then the control unit 18 can intervene to correct and steer the guided missile 12 back into the desired trajectory.

FIG. 5 shows a further possibility of controlling the guided missile 12. Shown is the laser beam 8, which runs within the Abschattungskorridors 74 and thus illuminates the laser-sensitive point 70 of the vehicle 2. At a first time, the guided missile 12 flies within the shadowing corridor 74 towards the laser source 10. This is based on the uppermost position of the missile 12 in FIG. 5 indicated.

In a subsequent moment, the laser beam 8 is swiveled out of the shading corridor 66, as shown in FIG FIG. 5 indicated by the dotted line. As a result, the guided missile 12 would be led out of a shading position in which he could shade the vehicle 2. In the embodiment shown, the guided missile 12 follows the slowly pivoted laser beam 8 and remains within the laser beam 8, as in FIG. 5 indicated by the middle position of the missile 12 in the dotted line.

This is also permitted by the control unit 18 of the vehicle 2 in order to restrict interference from the outside in the flight of the guided missile 12, or the flight control by the control unit 26 of the guided missile 12 to exceptions. For this purpose, a flight 76 is calculated by the vehicle 2 and / or the guided missile 12, within which the guided missile 12 has to remain. This flying space 76 is tapered towards both the vehicle 2 and the laser source 10, so that the largest cross-sectional dimension is approximately in the middle between the vehicle 2 and the laser source 10, as in FIG FIG. 5 is shown. With this flight space determination inaccuracies is carried out, which are connected to the position determination of the guided missile 12. Again, because the guided missile 12 is still capable of accurately determining the position of the missile 12, the flying space 76 allows for a tolerance around the shadowing corridor 74, within which the coarse flight control from the side of the vehicle 2 is not in the fine flight control of the guided missile 12 engages. Since the position of the missile in the vicinity of the vehicle 2 is known in more detail, it is tapered toward the vehicle 2. Since the guided missile 12 has to hit the laser source 10, the flying space 76 tapers off towards the laser source 10. At the in FIG. 5 In the exemplary embodiment shown, the guided missile 12 flies in its position shown in the middle at the edge of the flight space 76 within the laser beam 8. The flight control from the control unit 18 therefore does not intervene in the flight and the flight is carried out exclusively by the guided missile itself.

At a later moment, the laser beam pivots into an in FIG. 5 direction shown in a wide dotted line. In this respect, the guided missile 12 does not follow the laser beam 8 and remains within the flying space 76. Since the guided missile 12 can not maintain its fine control within the laser beam 8 in this situation, the guided missile 12 becomes based on a coarse control controlled by the guided missile 12 itself or the control unit 18 of the vehicle 2 can perform. Here, the guided missile 12 is again guided in the calculated Abschattungskorridor 74, as based on the lower position of the missile 12 in FIG. 5 is shown. This is to the determination and thus can come to steering inaccuracies, is not critical, since the missile 12 remains in any case within the flight envelope 76. When the guided missile 12 leaves the flight space 76, the flight control of the vehicle 2 intervenes and corrects the flight of the missile 12. This is analogous to the correction using the shadowing corridor 66, 72, 74 as well FIG. 3 described.

Another way to defend the laser system 6 against the approaching guided missile 12 is that the laser beam 8 is turned off. Although the guided missile 12 can now be roughly controlled in the direction of the laser source, missing this target is not unlikely without the laser beam 8. For direct finding of the target, or the laser source 10, in particular in the Endgame, the forward sensor in the form of the "forward" sensor 32 with the imaging detector or the matrix detector 36. Since this is not laser-resistant, it must during the flight in the laser beam 8 are adequately shaded. This is done in a first embodiment with reference to the cover 40 and in a second embodiment that in FIG. 6 is shown by means of a blow-off hood 78. The hood 78 consists of several parts, which have several predetermined breaking points in the FIG. 6 are indicated by a serrated line, are connected together. Within the hood 78 is a small explosive charge, which is ignited by the control unit 26. The hood 78 breaks apart and exposes behind in the dome 80, which is permeable to infrared radiation, so that the sensor 32 has a clear view to the front.

Is the laser beam 8 switched off or wasted from the sensor of the missile 12, for example, because he is far förtgeschwenkt, as in FIG. 5 is indicated by the wide-dotted line, the cover 40 can be opened, or the hood 78 are blasted off. To such a situation too recognize, the control unit 26 in conjunction with the sensor system of the missile 12 is prepared to detect a danger of the laser beam 8. This happens, for example, based on a measured intensity of the laser radiation. If the danger is below a limit value, the cover 40 can be opened or the hood 78 can be blown off and the forward sensor 32 can be activated.

In this case, for example, the far-swung laser beam 8 and its end is recorded pictorially on the laser source 10 and the position of the laser source 10 in the image of the forward sensor 32 is determined. From this, the approach direction to the laser source 10 can be determined, so that a point accurate approach to the laser source 10 without the line through the laser beam 8, or a flight can take place within the laser beam 8. An image acquisition time of 50 ms is sufficient to find the laser source, identify it and determine its direction.

If the laser beam 8 disappears because the laser system 6 switches off the laser source 10, the sensor 32 searches for heat sources in its field of view. Detected heat sources are compared with data stored in a database, in particular images of known heat sources. Here, the time that has elapsed since the switching off of the laser beam 8, taken into account. If the image of a heat source detected by the sensor 32 can be associated with a stored image of a laser source 10, the location of the heat source is recorded as a new target, and the missile 12 controls the heat source to destroy it.

Since a very small Zeitfester of about 15 ms is sufficient to identify the laser source 10, or the heat source, it is harmless if the laser beam 8 after this period again radiates on the approaching guided missile 8 and destroys the sensor 32, for example. However, to make the target approach control even firmer, there is a possibility that the forward sensor 32 may be protected by the filter 38 and / or the cover 40. If the laser beam 8 hits the open forward sensor 32, the radiated intensity increases sharply, and the intensity-dependent filter 38 closes or becomes opaque. However, the filter 38 stops direct irradiation by the laser beam 8 for only a few milliseconds. Therefore, at the same time the cover 40 is actuated, the spring-drawn their two lids from the in FIG. 2 dashed lines shown Expense position pulls in the solid closed position and thus covers the sensor 32. Now, the sensor 44 may begin blinking and release opening of the cover 40 at a sufficiently long non-irradiation of the missile 12 by the laser beam 8.

In order to disturb or avoid a fight by the guided missile 12, it may be that the laser system 6, the laser source 10 turns off, so that the laser beam 8 disappears. A line of the flight of the missile 12 along the laser beam 8 is no longer possible. However, this switching off is detected by the sensors 42-48. The cover 40 opens and allows the sensor 32 to look forward. The sensor 32 searches for heat sources in its field of view. Found heat sources are compared with data stored in a database, in particular images of known heat sources. In this case, the duration of time that has elapsed since the laser beam 8 was turned off is taken into account. If the image of a heat source can be assigned to a stored image of a laser source 10, the position of the heat source is recorded as a new target and guided missile 12 controls the heat source to destroy it.

In order to prevent destruction of the sensor 32, the cover 40 opens only for a short period of time and then closes again to protect the sensor 32. An opening period of 50 ms is sufficient to find the laser source 10, identify it and determine its direction. The guided missile 12 can now fly into the laser source 10 on the basis of this data. In order to avoid destruction of the sensor 32 by only briefly switching off the laser source 10, the cover 40 opens after a preset time after switching off the laser source 10. This preset time may be different from guided missile 12 to missile 12 so that the laser system 6 the Opening time after switching off the laser source 10 does not know. After expiration of the waiting time, the cover 40 opens for the preset time, for example 50 ms and closes again. The sensor 32 is protected against re-ignition of the laser beam 8.

Activation of the sensor 32 is also possible if the laser beam 8 is sufficiently far away from the missile 12, for example because the laser beam 8 has been widely pivoted. As a result, the laser source 10 can be detected directly and thus controlled more easily. The distance of the missile 12 to the laser beam 8 is estimated by the sensors 42, and the control unit 26 opens the cover 40 in response to the sensor signal.

LIST OF REFERENCE NUMBERS

2

vehicle

4

landscape

6

laser system

8th

laser beam

10

laser source

12

Missile

14

sensor system

16

sensor

18

control unit

20

canister

22

steering wings

24

actuator

26

control unit

28

rocket engine

30

active part

32

sensor

34

optics

36

matrix detector

38

filter

40

cover

42

sensor

44

sensor

46

sensor

48

sensor

50

deepening

52

Facial field

54

fin

56

Facial field

58

slope

60

Area

62

Area

64

Facial field

66

Abschattungskorridor

68

laser-sensitive point

70

laser-sensitive point

72

Abschattungskorridor

74

Abschattungskorridor

76

airspace

78

Hood

80

cathedral

Claims (14)

1. Method for protecting a vehicle (2) from an attack by a laser beam (8) emanating from a laser source (10), wherein the position of the laser source (10) is determined and a guided missile (12) is launched and steered to words the laser source (10),
   characterized
   in that the guided missile (12) detects the laser beam (8) and controls its trajectory depending on its position in relation to the laser beam (8).
2. Method according to Claim 1,
   characterized
   in that a distance of the laser source from the vehicle (2) is determined using the flight altitude and the direction of the laser beam (8).
3. Method according to Claim 1 or 2,
   characterized
   in that the guided missile (12) flies parallel to the laser beam (8) in the laser beam (8) and thereby shadows the vehicle (2) from the laser beam (8).
4. Method according to any one of the preceding claims, characterized
   in that the position of a shadowing corridor (66, 72, 74) between the laser source (10) and the vehicle (2) is determined and the guided missile (12) is controlled depending on its position in relation to the shadowing corridor (66, 72, 74), wherein
   the shadowing corridor (72, 74) is restricted, in particular, to a space between a laser-sensitive point (68, 70) of the vehicle (2) and the laser source (10).
5. Method according to any one of the preceding claims, characterized
   in that the distance between the laser source (10) and the vehicle (2) is determined and a flight space (76) is determined therefrom and the guided missile (12) is controlled in such a way that it remains within the flight space (76).
6. Method according to any one of the preceding claims, characterized
   in that a flight space (76) of the guided missile (12) is determined between the laser source (10) and the vehicle (2), said flight space tapering both towards the laser source (10) and towards the vehicle (2).
7. Method according to any one of the preceding claims, characterized
   in that the guided missile (12) remains in a predetermined flight space (76) when the laser beam (8) disappears from a shadowing corridor (66).
8. Method according to any one of the preceding claims, characterized
   in that the vehicle (2) monitors the position of the flying guided missile (12), wherein
   the vehicle (2), in particular, intervenes in a flight control of the guided missile (12) if the guided missile (12) departs from the flight space (76).
9. Method according to any one of the preceding claims, characterized
   in that the guided missile (12) controls its trajectory using the position of the vehicle (2) and the position of the laser source (10), wherein
   the guided missile (12), in particular during its flight, determines the position of the vehicle (2) from an inertial position and the flight direction and the flight speed of the vehicle (2).
10. Method according to any one of the preceding claims, characterized
    in that the guided missile (12) flies towards the laser source (10) by means of inertial navigation if the laser beam (8) has disappeared.
11. Method according to any one of the preceding claims, characterized
    in that the guided missile (12) identifies a disappearance of the laser beam (8) and, following this, activates a sensor (32, 42, 44, 46, 48) that was previously shadowed from the laser beam (8).
12. Method according to any one of the preceding claims, characterized
    in that the guided missile (12) identifies a danger level of the laser beam (8) and, should a danger lie below a limit value, said guided missile activates a forward sensor and uses the data thereof for a flight towards the laser source (10).
13. Method according to any one of the preceding claims, characterized
    in that, if the laser beam (8) is deactivated, the guided missile (12) detects a heat source of the laser source (10), compares the pattern of the heat source to data in a database and approaches the heat source in the case of a successful comparison.
14. System made of a vehicle (2) and a guided missile (12), said system comprising a control system configured to determine the position of the laser source (10), launch the guided missile (12) and steer the latter towards the laser source (10),
    characterized
    in that the guided missile (12) is designed to detect the laser beam (8) and control its trajectory depending on its position in relation to the laser beam (8).

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