EP3118567A1 - Method for protecting a vehicle against an attack by a laser beam - Google Patents

Abstract

The invention is based on a method for protecting a vehicle (2) against attack by a laser beam (8) emanating from a laser source (10). Effective protection can be achieved when a missile (12) starts from the vehicle (2), a sensor (42, 44, 46, 48) of the missile (12) scans the laser beam (8) and directs the missile (12) from the laser beam (8) to the laser source (10).

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.

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 of the type mentioned, in which according to the invention a guided missile starts from the vehicle, a sensor of the missile scans the laser beam, in particular scans from the outside, and the guided missile guided by the laser beam to the laser source zufährt. The missile can shade the vehicle and / or approach and combat 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 / or can quickly fly to combat the laser source on this. Especially in the latter case, the missile is expediently equipped with a rocket motor. The guided missile can be at an approach to the Laser source mechanically destroy them by means of an active part, for example, by a cone-shaped forward splintering charge.

The guided missile uses the laser beam as a guide beam for driving the laser source. The steering or navigation of the missile is done so far using sensor data obtained from a scanning of the laser beam. In particular, the laser beam is detected as such, and the missile controls toward the lower end of the laser beam. Alternatively or additionally, a parameter of the laser beam, for example a scattered light intensity, can be used for navigation, for example by the measured scattered light intensity being kept constant during the approach or being processed according to a predetermined scheme.

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. The guided missile comprises at least one sensor sensitive to laser radiation, which detects the laser radiation of the laser beam. For this purpose, the sensor is expediently sensitive in a radiation spectrum which is usually used for high-energy lasers or interfering lasers. 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 the sensor detects by means of image processing methods a laser beam as such in the environment, for example on the basis of scattered radiation. For this purpose, the sensor is advantageously an image sensor with, for example, a matrix detector.

The vehicle is preferably an aircraft, and may be fixed-wing aircraft or a rotorcraft, such as a helicopter. However, the invention is also advantageously applicable for protecting a land vehicle or a watercraft. The vehicle may be a manned or unmanned vehicle.

It may include a control unit having one or more computing units that may be distributed in the vehicle at a location or over the vehicle. The control unit expediently detects the laser beam as such and initiates a start of the missile as a function of the recognition result. Is a laser beam recognized as such and he is also classified as threatening to the vehicle, the missile is launched 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 guided missile flies towards the laser source and utilizes the laser beam expediently as a guide beam for driving the laser source. In general, there are several options available.

In a first possibility, a sensor of the vehicle or a sensor of the missile picks up 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, a straight line of the laser beam in the environment is determined from the image 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. The location of the laser source can be determined from the vehicle and transferred to the guided missile. The location may alternatively or additionally be determined by the guided missile.

This former possibility is particularly suitable for instructing the guided missile in a first phase of flight towards the laser source. For this purpose, in an advantageous embodiment of the invention, a sensor of the vehicle or a sensor of the missile on an image of the laser beam. From the image, a straight line of the laser beam in the environment can be determined. In particular, a defined End of the laser beam or the line determined. Accordingly, the missile can approach the end of the laser beam.

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 is aimed at the laser source and picks up the laser radiation thrown directly from the laser source onto 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.

A third possibility is based on the measurement of scattered laser radiation. The laser radiation is partially spatially scattered in the air, on particles and / or on an object, so that the laser beam is visible 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 a sideways or backward sensor system, both of which can be protected towards the front and then blind to the front. Under a sideways sensor is understood below exclusively directed in a lateral direction relative to the longitudinal axis of the missile sensor system, which is not aligned in the direction of flight, and a reverse sensor is directed exactly opposite to the direction of flight of the missile, usually also in the lateral direction, but also not Forward.

In order to measure laser radiation scattered in the air, a sensor which is blind to the front detects the laser beam from a side view in a further advantageous embodiment of the invention. Control of the guided missile expediently takes place on the basis of the sensor results recorded in this way, for example on the basis of a radiation intensity.

The guided missile may have a forward sensor, that is one or more sensors whose direction of view forward, ie in the direction of flight of the missile is directed or judged. A flown object can be scanned sensory and a detected target can be approached exactly. The sensor may be a center of gravity sensor which detects a radiating object with respect to its orientation relative to the longitudinal axis of the missile, but does not resolve the object in an image. Steering signals can be generated particularly easily from a center of gravity sensor. Also possible is an image sensor, ie a two-dimensionally resolving sensor, for example with a matrix detector. With this, the detected object can be figuratively resolved and determined not only in terms of its location but also in terms of its geometry.

A forward sensor is particularly vulnerable to a laser beam incident directly into the sensor. In order to obtain sensory properties even when the missile hits the laser beam directly, the missile advantageously has a sideways sensor system and / or a backward sensor system. In the case of a front-blind sensor, which can not be directed forward in the direction of flight or in the direction of the longitudinal axis of the guided missile, no laser radiation striking the missile from the front can reach the sensor directly. He is thereby at least largely protected from front incident laser radiation. Also possible is a forward-fading forward sensor, which can be covered, for example, by a screening means or pivoted out of the forward direction, so that it is protected by the pivoting forward.

Particularly advantageously, the guided missile comprises a forward sensor and an additional sideways and / or backward sensor. In this way, not only a large space around the missile can be monitored by sensors, but the sensors can be used sequentially, so that one of the sensors is only used sensorially when the other sensor is turned off or destroyed.

Advantageously, the guided missile comprises a first sensor on a missile head and a second sensor on a fuselage region of the missile. By "an" is meant here also "in". The sensor on the missile head is expediently part of a forward sensor system and the second sensor part of a sideways or backward sensor system. It is also advantageous if the second sensor in the trunk area is also part of a forward sensor, since then both sensors used, for example, one after the other for forward detection can be. Thus, for example, first the trunk sensor detect laser radiation, whereas the head sensor is shaded. If the fuselage sensor is destroyed by a laser strike, the head sensor can be activated forward so that the onward flight can also be controlled by the sensor. It is also possible and advantageous if the head sensor is activated only in the endgame to the front, so if a particularly accurate direction control for accurate steering of the missile to the target is necessary. Before the Endgame, which may be determined by a predetermined distance to the destination, for example, 500 m to the target, only a trunk sensor is expediently active, so that damage to the head sensor is prevented by a laser hit. The trunk sensor may be positioned, for example, on a fin of the missile.

Further, it is advantageous if the missile has two sensors arranged one behind the other in a missile head. First, the front sensor can detect laser radiation, and after a defect of the front sensor, the rear sensor can be activated. For this purpose, for example, the front sensor is moved to the side, so that the view of the rear sensor is released forward, or the front sensor is dropped with a head element, so that the view of the second sensor is released forward. The two sensors do not have to be arranged exactly one behind the other in the direction of flight. It is sufficient if the front sensor is farther forward and the rear farther back than the front sensor.

A good protection of a sensor against incident laser radiation can also be achieved if the sensor is located during a flight phase within the missile and is extended during the flight in a viewing position, in particular by an outer shell of the missile is extended, so thus thereby the visual profile of the missile is enlarged from the front. The sensor may be attached to a fin, a bracket, a flap, or the like that extends out of the fuselage or head of the missile.

In a further advantageous embodiment of the invention, a sensor of the missile is brought by a cover from a visual state in a blind or covered state. Threatened by an incident laser beam, the sensor can be protected by this. Expediently, the covering takes place as a function of the distance of the laser beam to the guided missile. If the laser beam, for example, in the direction of Steering missile pivoted, and this is detected early, so the sensor can be covered and thereby protected. The distance can be determined as an absolute distance or as a relative distance, for example by increasing a scattered radiation intensity to above a predetermined value. If, for example, the scattered radiation intensity more than doubles in less than 500 ms, this can be assessed as the laser beam approaches the missile and the sensor is covered.

The pivoting of a laser beam on the missile can be extremely fast. There is thus the danger that the laser beam hits a sensor before the sensor is covered. A particularly rapid protection of the sensor can be achieved if the cover has a particular intensity-dependent filter and a mechanical cover. The filter has the advantage that it can be activated very quickly, but does not sufficiently protect against strong incident laser radiation. However, the protection may be large enough to ensure the survival of the sensor for such a period of time that the mechanical cover closes. In this way, the sensor is first protected by the filter and then by the closing mechanical cover. In this respect, it is advantageous that the filter is first shaded to generate the sensor and then the cover is moved into the detection range of the sensor.

In order to facilitate the steering of a continuation, it is advantageous if the sensor unit blinks during the flight with covered sensor. This can be done by the cover partially or at least indirectly releasing the detection area of the sensor. This can be done by partially opening the cover, so that a partial view area is released forward. Although the opening does not allow a viewing area to be forward, incident laser radiation is directed indirectly to the sensor so that it can be determined whether the laser is still aimed at the guided missile. A particularly safe option is that a front-covered Blinzelsensor measures incident energy to a cover, for example, by a change in temperature of the cover, and from a direct irradiation is detected by the laser beam or it is closed.

A defense option of the laser system is that an approaching guided missile is detected and the laser is turned off. The missile loses its guidance and if necessary flies past the laser system. Once activated, however, the laser source will turn off even after the laser beam is turned off Heat source that can be detected by an infrared sensor. Subsequent navigation can be assisted in that the guided missile detects a heat source of the laser source when the laser beam is switched off. In order to avoid confusion of objectives at least largely, it is also advantageous if the pattern of the heat source is compared with data of a database, so that the heat source is identified as a laser source. If successful, the missile can approach the heat source. The comparison is successful if the pattern of the heat source coincides with the data to a predetermined extent.

Likewise, the protection of the missile or its sensor, it is beneficial if the missile keeps a distance from the laser beam, which is at least a predetermined safety distance, and flies in minimal distance to the laser beam along. The safety distance is expediently always exceeded, until the missile has reached a predetermined distance from the laser source and can now control it directly. The safety margin may be predetermined in advance and be absolutely predetermined or depend on parameters, for example laser power, and determined during the flight.

For dimming a sensor or for controlling evasive movements, it is advantageous if a distance or a change in the distance from the guided missile to the laser beam is detected. The strength of the detected scattered radiation can be used as a measure of the distance. In this respect, the guided missile can detect an approach of the laser beam from an increase in the detected radiation intensity. In general, a radiation intensity can be correlated with the distance to the laser beam or, more precisely, to its longitudinal axis. For example, a stray radiation edge is detected in which the radiation intensity increases sharply. From this it can be determined that the guided missile moves in the vicinity of the axis of symmetry of the laser beam.

To protect the missile or its sensor, it is advantageous if the missile evades the laser beam. For example, if this approaches closer to the guided missile than a safety distance, an evasive control can be started. In this case, it is expediently also determined from which direction the laser beam approaches the guided missile. The Evasive movement is expediently carried out as a function of the approach direction.

Even with a highly agile guided missile, the agility of a laser beam in space can not be achieved. An escape from the laser beam can be favored if an evasion direction of the guided missile is dependent on the distance and / or the approaching speed of the laser beam to the guided missile. So it makes sense, for example, that the guided missile escapes at a rapid approach, ie at a closing speed above a threshold, transversely to the direction of approach. This must first be detected by the laser system before the laser can be tracked. On a slow approach, however, it may make sense that the missile dives through the laser beam. It deflects expediently towards the laser beam, so that a residence time in the laser beam is shortened.

In order to avoid unnecessary evasive maneuvers, it is advantageous that a start of an evasive flight is made dependent on the movement of the laser beam. Thus, the laser source can be approached directly with a quiet laser beam, without an evasive maneuver delays the arrival at the laser source.

While steering movements of the guided missile are subject to a certain inertia, a laser beam with negligible inertia of the laser system can be swung back and forth in space. However, an evasive movement of the missile must be pictorially recorded for tracking the laser beam and the tracking motion must be calculated. This results in a certain time delay from the steering movement to the tracking of the laser beam. This time delay can be kept high when the missile flies in an erratic trajectory relative to the orientation of the laser beam. An erratic trajectory may have random steering motions, that is, performed using a random generator, and which are expediently free of common geometric patterns. Instead of or in addition to the erratic trajectory, a helix trajectory around the laser beam is advantageous. The helical path - possibly distorted or trembled by the erratic flight - requires complex pivoting movements of the laser beam relative to the steering movement of the guided missile.

Depending on the radiance and computational capabilities of the laser system, it is advantageous if this is attacked with several missiles. These will expediently all started from the same vehicle and fly the laser source. In order to achieve a concerted attack as possible, it is advantageous if the missile exchanges data with other, the laser source approaching guided missiles. For example, the position of the laser source and / or an approach direction to the laser source can be exchanged. In this way, a solid angle distance from the perspective of the laser source between the missiles can be increased, so that alignment of the laser beam is made difficult to the missile.

A reliable arrival of the missile at the laser source can be favored if the laser source is illuminated by a radiator. The guided missile can detect the beam spot at the laser source or in the vicinity of the laser source, and the missile can orient itself in its flight at the beam spot. One possibility is, for example, a semi-active laser method, also called SAL method. The radiator can be arranged in the vehicle, which leads the guided missile thereby. Another possibility is that the radiator is arranged in a missile, which is arranged, for example, behind another missile, the sensory capabilities, for example, different or less. For example, the laser source is illuminated by a missile, and one or more other missiles are oriented at the Anstrahlstelle.

The invention is also directed to a guided missile having a steering system and a sensor for detecting laser radiation of a laser beam. In order to effectively protect a vehicle against attack by a laser beam, the guided missile according to the invention comprises a control unit which is prepared to direct the guided missile using the laser beam as a guide to the laser source.

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 are each individually and in any suitable Combination both with the inventive method and with the inventive device according to the independent claims combined. 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 may also be explicitly considered isolated, removed from one embodiment, incorporated into another embodiment to complement 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

ein Diagramm der Intensität der von einem Sensor des Lenkflugkörpers gemessenen Laserstrahlung in Abhängigkeit von der Entfernung des Flugkörpers vom Laserstrahl,

FIG 5

eine konzertierte Verteidigung des Fahrzeugs durch mehrere Lenkflugkörper und

FIG 6

einen Revolversensor des Lenkflugkörpers.

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

a diagram of the intensity of the laser radiation measured by a sensor of the missile as a function of the distance of the missile from the laser beam,

FIG. 5

a concerted defense of the vehicle by several guided missiles and

FIG. 6

a revolver sensor of the guided missile.

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 placed in the embodiment shown on the ground and immovable. However, it is also possible that the laser system 6 is movable and is mounted, for example, in an aircraft. All details described below and related to the laser source 10 are then to be adapted accordingly to the mobility or height above the ground.

The laser system 6 is a high-energy laser system which 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 irradiate the laser system 6 pictorially deposited point of the aircraft 2 over a period of a few seconds and thereby destroy.

Instead of the high-energy laser system 6, a designator laser system or marker laser system can be fought or disturbed, which illuminates the vehicle 2 in order to control a guided missile into the vehicle 2. By shading the vehicle 2 and / or destroying the laser source 10, this mark can be disturbed, so that the attacking missile can not find the vehicle 2. The following description refers to a stationary high energy laser system 6 without being limited to this system.

To protect the vehicle 2, this has at least one guided missile 12, wherein in FIG. 1 to explain several guided missiles 12 are shown. Furthermore, the aircraft has a sensor system 14 with a plurality of sensors 16, each of which is signal-connected to a control unit 18 are. 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. Classification into 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 may 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 guided 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 effected by a control unit 26 of the guided missile 12. The guided missile 12 is driven by a rocket motor 28, in particular a Solid fuel motor, which is arranged behind a knitting member 30 having an explosive charge and a fragment part which is thrown in a bursting of the explosive charge in a cone shape 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 detector 36 in the form of a matrix detector. Further, a filter 38 for shading the detector 36 is provided. 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, a cover 40 is arranged in the detection region, which comprises two mutually movable shell elements, which are moved 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 automatically becomes opaque depending on 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. The sensor 42 is fastened to the fuselage of the guided missile 12 and in particular to a fin. The field of view of the sensor 42 points forward, so it is a forward sensor. The sensor 42 is not an imaging sensor, but measures the intensity of the incident laser radiation and is on a frequency band of 50 nm limited by the laser wavelength of 3.8 microns. If the laser source 10 lies in the field of view of the sensor 42, then the intensity of the incident laser light and thus an angular distance of the guided missile 12 from the orientation of the laser beam 8 is measured. With increasing intensity, the guided missile 12 approaches the laser beam 8 and vice versa. The intensity is given as a sensor signal to the control unit 26, which generates therefrom steering signals for steering the guided missile 12.

The sensor 44 is a flash sensor that measures a heating history. If the laser beam 8 hits the guided missile 12 fully, the sensor 42 is destroyed. However, the sensor 44 is designed to withstand the direct laser irradiation for a period of at least 30 seconds and to measure the course of a heating of a front part of the sensor 44. If the guided missile 12 leaves the laser beam 8, then the corresponding cooling of the sensor 44 is detected very quickly, so that the exit of the laser beam 8 can be detected by the control unit 26 as such. The cover 40 can be opened, for example, and the sensory view can be taken forward again.

The sensor 46 is another optional sensor that is similar to the sensor 42. However, the sensor 46 is not fixedly mounted to the missile fuselage, but can be moved out of the fuselage on a fin 50. In FIG. 2 the retracted position of the sensor 46 is pulled through and the extended position shown in phantom. The sensor 46 is extended when, for example, the sensor 42 is destroyed. The sensor 46 is alternatively or additionally extended only when the sensor 44 indicates the absence of the laser beam 8.

The sensor 48 is a sideways sensor, ie blind to the front, the field of view is shown with two dashed lines. The sensor 48 is seated in a recess 52 of the fuselage of the guided missile 12 and is shaded towards the front. The sensor 48 also remains functional when the laser beam 8 hits the guided missile 12 from the front over a period of maximum 60 seconds. The sensor 48 measures the intensity of the laser radiation scattered in the air of the laser beam 8. The closer the laser beam 8 to the missile 12, the greater the measured intensity, analogous to the sensors 42, 46. As in the two aforementioned sensors are the Signals from the sensor 48 for steering the missile processed by the control unit 26.

FIG. 3 shows a flight of the missile 12 for protecting the vehicle 2, which can be performed individually or in combination. In a first embodiment, a missile 12 is started in the form of a steering rocket. This missile 12 is started from the canister 20, for example, by a drop, a launch and / or a launch of Raketenmotors the missile 12. Since the missile 12 is aligned by the alignment of the canister 20 on the laser source 10 already to the laser source 10, detours can be avoided and the missile 12 can be started in direct line to the laser source 10. As an alternative to the guided missile, other guided missiles may also be used, for example steerable projectiles. These are also a control unit 26 for controlling the steered flight and a steering system 22, 24 to perform the steering.

The control of the missile 12 can be done independently by the control unit 26 of the missile 12. It is also possible that the control is carried out by the control unit 18 of the vehicle 2, either in addition or independently by the specification of appropriate commands to the control unit 26 of the missile 12. In this way, the missile 12 is controlled on or in the laser source 10, so this is destroyed. Shortly before the missile 12 reaches the laser source 10, the active part 30 can be ignited, which hurls a splinter charge cone forward and thereby destroys the laser source 10.

The flight of the missile 12 is suitably guided by the laser beam 8. For this purpose, it can be further observed by the sensor system 14 of the aircraft, and in the missile 12 corresponding control signals can be given. Alternatively or additionally, it is possible that the missile 12 independently uses the laser beam 8 as flight guidance and steers its own flight depending on its orientation in space. The missile 12 thus flies guided by the laser beam 8 independently into the laser source 10. In this case, the flight is guided along the laser beam 8 along or in a suitably predetermined spacing band along the laser beam 8.

In particular, in an independent control of the missile 12 to the laser source 10, the transfer of a target instruction from the control unit 18 to the control unit 26 is advantageous. As a result, at least a rough navigation in the first part of the approach can be considerably facilitated.

Several methods for protecting the vehicle 2 are described below with reference to 3 to 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, since they could not be recognized 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 12 moves to the laser beam 8, the greater the detected radiation intensity.

FIG. 4 shows an idealized radiation pattern in which the radiation intensity I over the distance φ to the laser beam 8, which is indicated in degrees, is plotted. The angle refers to the angle between the laser beam 8 and a straight line from the laser source 10 to the missile 12, or its sensor 42. An angle of 0 ° means here that the missile 12 is flying within the laser beam 8, or directly from it is taken. The intensity I of the incident on the sensor 42 laser radiation is then extremely high as by the asymptote of FIG. 4 reproduced intensity function is indicated.

Plotted are further three distances d ₁ , d ₂ , d ₃ , which are relevant to the control of the missile 12, as well as a distance band or flight band D. If the missile 12 flies closer than the distance d ₃ on the laser beam 12, this has a destruction of the open sensor 32, in particular also of the sensor 42, within a predetermined period of time, for example 500 ms. Falls below the distance d ₂ , the filter 38 fades and the cover 40 closes. The distance d ₁ is the safety distance, outside of which the missile 2 has its regular distance from the laser beam 8. The distance band D indicates the corridor around the laser beam 8, in which the guided missile 12 in regular flight and under the direction of the laser beam 8 stops. The distance band D and in particular the distances d _i are calculated from the measured course of the radiation intensity I by the control unit 26.

The behavior of the intensity I over the time of flight is monitored by the sensor 42 in conjunction with the control unit 26, and the missile 12 controls the laser beam 8 until it is within the air band D. If the flight band D is reached, then the guided missile 12 flies around the laser beam in a helical path 54, which in FIG. 3 is indicated. Depending on the movement of the laser beam 8 through the space, or its pivoting speed, the control unit 26 controls an erratic trajectory additively on the helical path, so that a lighting of the missile 12 by the laser beam 8 is significantly more difficult. However, if the laser beam 8 only tracks the movement of the vehicle 2, this erratic path can be omitted. Instead of the helical track, a path to the laser beam 8 can be selected, which runs at least substantially parallel to the laser beam 8 and can additionally comprise erratic web components for laser defense. Here, the distance to the laser beam 8 between a first approach phase and the final Endgame at least substantially constant. Or the web is continuously approaching the laser beam 8, for example, so that the angle between the web and the laser beam 8 - from the perspective of the laser source 8 - remains constant, so that the guided missile in a straight line on this.

When the guided missile 12 reaches the endgame 56, which begins at a predetermined distance from the laser source 10, for example at a distance of 300 meters, the helix path 54 is terminated and a direct approach to the laser source 10 is controlled. Alternatively to the predetermined distance, successful target detection by the sensor 32 may be used. This opens, or begins its detection, when the guided missile 12 has reached a predetermined flight stage, the beginning of which can mark a distance to the laser source 10, a position relative to the laser source 10 or another size, which is for example predetermined by the vehicle 2. If, for example, it is clear that the laser source 10 would have to be recognizable very quickly by the guided missile 12, since it is barely camouflaged or hidden, this flight status can be achieved very quickly. Detects the vehicle 2 and its sensor system 14, however, that the laser source 10 is difficult to detect, for example, because it is still covered by a terrain survey and the laser beam, the vehicle 2 while still not true, but can already be recognized as in FIG. 1 is indicated, then this flight status is set later by the vehicle 2.

At the appropriate time or upon reaching the appropriate position, the cover 40 opens and the sensor 32 has a clear view of the laser source 10. The position of the laser source 10 is determined to be absolute or relative to the missile 12 and the control unit 26 determines when Endgame 56 begins. If the guided missile 12 reaches a blasting distance of a few meters to the laser source 10, the active part 30 is ignited and the explosive charge is thrown in the form of a conical fragment charge to the laser source 10, and this is thereby destroyed.

An approach of the guided missile 12 to the laser system 6 can be detected by the laser system 6 itself, and the laser system 6 can control defensive measures. For example, the laser beam 8 is aimed directly at the missile 12 to destroy control-relevant units of the missile 12. If, for example, by such a laser defense of the sensor 42 destroyed, the sensor 44 monitors the illumination of the missile 12 by the laser beam 8. By a certain inertia of the sensor 44, it releases the sensor system of the guided missile 12 only when the guided missile 12 or the sensor 44 has not been illuminated by the laser beam 8 for a while. In this way, a sensor release can be avoided by a brief emergence and re-entering the guided missile 12 in the laser beam 8.

If the sensor 44 releases the sensor, then the fin 50 extends with the sensor 46 and takes over the monitoring task of the destroyed sensor 42. Incidentally, the method can be continued as described above.

Another possibility is that, in addition to or as an alternative to the sensor 46, the sensor 48 monitors stray radiation from the laser beam 8. These also behave in their intensity analogous to the intensity curve FIG. 4 so that the distance of the guided missile 12 to the laser beam 8 can also be determined from the scattered radiation intensity. For example, if the sensor 48 is used instead of the sensor 42, the risk of destruction of the sensor 48 by the laser beam 8 is lower, and the sensor 46 can be dispensed with. Incidentally, the method may proceed as described above.

If the laser beam 8 strikes 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, pulls the spring-pulled their two covers from the dashed open position in the solid closed position and thus covers the sensor 32. The sensor 44 may begin blinking and release opening of the cover 40 as described above, with the laser beam 8 sufficiently non-irradiating the missile 12.

The guided missile 12 uses the laser beam 8 as a guide beam for driving the laser source 10. An adequate defense of the laser source 10 may accordingly consist in that the laser beam 8 is pivoted quickly and thus the laser beam 8 following guided missile 12 is misleading. In order to avoid this, tracking the laser beam 8 by the guided missile 12 depends on its pivoting speed and / or its orientation relative to the vehicle 2. In addition, tracing depends on the current position of the missile 12 relative to the laser source 10. If the guided missile 12 is already in Endgame 56, it flies the laser source 10 independently of a pivoting movement of the laser beam 8 at. If the guided missile 12 is still in front of the endgame 56, it expediently remains in a flying cone whose tip lies in the laser source 10 and in whose volume the vehicle 2 is positioned, in particular on its axis of symmetry. The size of the cone may be predetermined or determined by the vehicle 2 or the missile 12 during the flight of the missile 12. When the laser beam 8 swivels only within the flying cone, the guided missile 12 follows the laser beam 8 in order to be guided by it. However, when the laser beam 8 swings out of the flying cone, the guided missile 12 does not follow the laser beam 8 and remains within the flying cone.

A sensor support of the missile 12 by sensors 16 of the vehicle 2 is also possible. If the sensor system 14 detects that the laser beam 8 is swung to deceive the missile 12, then the control unit 18 can intervene in the flight of the missile 12 and bring it back in the direction Swing to the laser source 10, for example, bring in the flying cone. Such recognition can be done, for example, by the fact that the laser beam 8 exceeds a predetermined distance to a straight line intended between vehicle 2 and laser source 10.

In order to avoid a direct meeting of the guided missile 12 by the laser beam 8, this can avoid an approaching laser beam 8. If the distance between the laser beam 8 and the guided missile 12 drops below the distance d ₁ , the guided missile 12 starts an evasive maneuver. If a laser approach occurs slowly, for example by pivoting the laser beam 8 with the movement of the vehicle 2, the movement of the steering missile 12 is carried along with the movement of the laser beam 8, so that the missile 2 remains within the flight band D. If the approach exceeds a predetermined speed, the guided missile 12 deviates transversely to the approach direction of the laser beam 8 relative to the guided missile 12. The irradiation intensity of the laser radiation is monitored so that the cover 40 is closed and / or the fin 50 is retracted when the distance d ₂ is exceeded. Depending on the approach speed, it may also be appropriate for the guided missile 12 to dive through the laser beam 8. Again, the sensors 32, 46 are protected as described above.

Another way to defend the laser system 6 is to turn off the laser source 10 so that the laser beam 8 disappears. This can be detected by an abrupt drop in the intensity I by the sensor system of the guided missile 12. The cover 40 is - if not already done - opened and the sensor 32 looks for heat sources in his field of view. Found 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 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 the guided missile 12 controls the heat source to destroy it.

Another way to defend the vehicle 2 against a laser beam 8 is based on FIG. 5 explained. Several guided missiles 12 are started from the canister 20 and attack the laser source 10 in concert. They operate here a data exchange with each other, so that information on their own position and the position of the laser source 10 and the laser beam 8 are interchanged. For example, a front steering missile 12 can detect the detected position the laser source 10 tell a rear missile. In addition, based on the own and the position of the other guided missile 12 an approach direction of the missile 12 is controlled so that they drive the laser source 10 from different directions. For example, one of the guided missiles 12 flies a helical track 54, a second guided missile 12 flies at a greater distance d an erratic path and another missile 12 flies at a very large distance from the laser beam 8, the laser source 10 at.

With or without a swarm of guided missiles 12, the illumination of the laser source 10 by a semi-active system is possible and useful. Such an SAL method can be carried out by a laser of the vehicle 2, which marks the laser source 10 with a radiation spot which is controlled by the missile or the missiles 12. It is also possible that one of the missile 12 has an SAL system and during its approach, expediently from a greater distance from the laser beam 8, the laser source 10 marked with a beam spot. The remaining missiles 12 now control this aerial spot. A line through the laser beam 8 can be omitted here. At the in FIG. 5 shown embodiment, the advancing missile 12 is struck by the laser beam 8 and its sensor is largely destroyed. This guided missile 12 now continues to fly blindly in accordance with the last determined position information of the laser source 10 and its own flight direction. The underlying guided missile 12 attempts to remain at a large distance d to the laser beam 8 and performs appropriate evasive movements in an attack by the laser beam 8. It follows a marking of the laser source 10 by an irradiation point, which is generated by the most distant flying missile 12 by a marking laser. The position of the laser source 10 was in this case detected by the frontmost flying missile 12 and passed on to the other missile 12, so that the marker missile uses this position to align its marking laser.

FIG. 6 shows in a further embodiment, one of the sensors 42, 46 of the missile 12 in an alternative embodiment. The sensor 42, 46 comprises six sensor heads 58, five of which are covered by a cover element 60, for example a metal plate. One of the sensor heads 58 lies behind an opening 62 of the cover element 60, is thus oriented in the environment and can look into the environment and detect laser radiation.

The sensor heads 58 are pivotable about a common axis, as in FIG FIG. 6 indicated by the curved arrow. If the currently active sensor head 58 is destroyed, the turret can be further rotated by 60 °, so that the next sensor head 58 comes to lie behind the opening 62 and can detect the detection.

Arranged in the middle and also behind the cover element 60 is the sensor 44, which has the task of detecting when a high-energy laser beam 8 is directed onto the sensor 42, 46.

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

fin

52

deepening

54

helical path

56

endgame

58

sensor head

60

cover

62

opening

D

flight band

d _i

distance

φ

Angle to the laser beam

Claims (16)

Method for protecting a vehicle (2) from attack by a laser beam (8) emanating from a laser source (10), in which a guided missile (12) starts from the vehicle (2), a sensor (42, 44, 46, 48 ) of the guided missile (12) scans the laser beam (8) and the guided missile (12) guided by the laser beam (8) incident on the laser source (10). Method according to claim 1,
characterized,
in that a sensor (32, 16) takes an image of the laser beam (8), from the image a straight line of the laser beam (8) in the vicinity and a defined end of the laser beam (8) is determined, and the guided missile (12) determines the end of the laser beam (8) flies. Method according to claim 1 or 2,
characterized,
in that a forwardly blind sensor (48) of the guided missile (12) detects the laser beam (8) from a side view. Method according to one of the preceding claims,
characterized,
that the guided missile (12) a first sensor (32, 46, 48) on a guided missile head and a second sensor (42) to a body portion of the guided missile (12), the first, the second sensor (48) detects the laser radiation and after a defect of the second sensor (48), the first sensor (32, 46, 48) begins to detect laser radiation. Method according to one of the preceding claims,
characterized,
that the guided missile has two sensors arranged one behind the other in a missile head and initially the front sensor laser radiation detected and after a defect of the front sensor this is dropped with a head element and then detects the rear sensor laser radiation. Method according to one of the preceding claims,
characterized,
in that a sensor (46) of the guided missile (12) is extended out of the fuselage of the guided missile (12) during the flight of the guided missile (12). Method according to one of the preceding claims,
characterized,
in that a sensor (32, 46) of the guided missile (12) is brought into a covered state from a visual state by a cover (40) and the masking is effected as a function of the distance of the laser beam (8) from the guided missile (12)
the cover (40) has, in particular, an intensity-dependent filter (38) and a mechanical cover (40), the filter only (38) causing the sensor (32) to be shaded, and then the mechanical cover (40) to the detection area of the sensor Sensor (32) is moved. Method according to claim 7,
characterized,
in that the guided missile (12) blinks during the flight when the sensor (32, 46) is dimmed, in that a sensor (44) senses direct irradiation by the laser beam (8) and detects a swiveling of the laser beam (8) from the guided missile (12). Method according to one of the preceding claims,
characterized,
when the laser missile (8) is turned off, the guided missile (12) detects a heat source of the laser source (10), compares the pattern of the heat source with data from a database and flies the heat source upon successful comparison. Method according to one of the preceding claims,
characterized,
in that the guided missile (12) flies along the laser beam (8) in at least one predetermined safety distance (d ₁ ) from the laser beam (8). Method according to one of the preceding claims,
characterized,
in that the guided missile (12) detects an approach of the laser beam (8) from an increase in a detected radiation intensity. Method according to one of the preceding claims,
characterized,
that the guided missile (12) evades the laser beam (8) when approaching the missile (12) closer than a safety distance (d ₁ ), wherein the deflecting direction of the missile (12) depends in particular on the distance and the approach speed of the laser beam (8 ) to the guided missile (12) and / or being
a start of an avoidance flight is made, in particular depending on the movement of the laser beam (12). Method according to one of the preceding claims,
characterized,
in that the guided missile (12) flies in an erratic trajectory relative to the orientation of the laser beam (8). Method according to one of the preceding claims,
characterized,
in that the guided missile (12) exchanges data with further guided missiles (12) approaching the laser source (10). Method according to one of the preceding claims,
characterized,
in that the laser source (10) is illuminated by a radiator, a sensor (32) detects the radiating point on the laser source (10) and the guided missile (12) is oriented in its flight at the radiating point. Guided missile (12) having a steering system (22, 24) and a sensor (42, 44, 46, 48) for detecting laser radiation of a laser beam (8) and a control unit (26), which is prepared for guiding the missile (12) under use of the laser beam (8) as a guide beam to a laser source (10) of the laser beam (8) to direct.

Images