EP3118564B1 - 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.

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, in which, 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 in order to disturb and possibly damage the laser device. According to the EP 2 752 681 A1 To warn a pilot of an aircraft from impinging laser radiation, the aircraft is equipped with a laser detection and warning system that can output a warning signal.

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 aforementioned type, in which according to the invention a sensor system detects laser radiation of the laser beam and a guided missile flies into the laser beam and thereby shading the vehicle. The laser beam can no longer or only weakly penetrate the vehicle and the shadow protects the vehicle. If the vehicle has already been illuminated, an already warmed point of the vehicle can cool down. The shading is expediently done so quickly that the laser energy deposited on the vehicle has not yet led to threatening damage to the vehicle.

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 sensor system comprises at least one sensor sensitive to laser radiation, which detects the laser radiation of the laser beam. For this purpose, the sensor or the sensor system 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 system 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 system advantageously contains an image sensor, for example a matrix detector.

The sensor system may be part of the vehicle and the sensor may be permanently installed in the vehicle. The sensor system detects laser radiation of the laser beam, ie radiation directly emitted by the laser source and / or laser radiation scattered from the laser beam, for example by the scattering of the laser beam in the air, on particles and / or on an object. The sensor system absorbs the radiation and converts it into a measuring signal. From the measurement signal, a control unit expediently determines a threat level of the laser radiation, for example by a classification in at least the levels threatening or harmless. This can be done, for example, via the measured scattered light intensity in the atmosphere, an energy input into the sensor system, a spread spectrum and / or over a temporal characteristic of the radiation, such as a pulsation.

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.

The missile is expediently a guided missile and in particular an unmanned missile. It may be equipped with a rocket engine and / or an air-breathing engine, such as a turbine engine. in this connection is an air-breathing engine at a collision protection of the vehicle by the missile advantageous. A suitably additional rocket motor is advantageous for a quick start and the rapid achievement of a shading position. Also possible is a missile without its own engine, for example in the form of a steering column. Conveniently, the missile is provided with a shading sail, which is extendable during the flight of the missile, so that a shading surface of the missile is increased.

Advantageously, the guided missile accompanies the vehicle and keeps the vehicle from being shaded by the laser beam. The guided missile is thus advantageously a loiterable missile capable of moving at substantially the same speed as the vehicle is moving. The loiterfähige guided missile can remain between the vehicle and a laser source of the laser beam and protects the vehicle by shading in this way, at least over a predetermined period of time and / or as long as a classified as threatening laser beam is detected.

In an advantageous embodiment of the invention, the missile is launched from the vehicle. In this way, a particularly rapid protection of the vehicle from the laser beam can be achieved because the missile is already on site and can dive into the laser beam for shading.

Depending on the carrying capacity of the vehicle, a light guided missile is favorable. Also in terms of cost, a lighter and easier missile is advantageous. Cost and weight can be saved if the missile is drive-free, so has no own drive motor. In such a case, the guided missile can be launched from the vehicle, expediently forward, including a direction obliquely forward to be understood. The Loiterfähigkeit of the missile is created by a Mitsegeln the missile below the vehicle, suitably obliquely down to keep a sufficient speed. Such a missile can be shot down, sail down towards the laser source of the laser beam and thereby shade the vehicle flying higher up. This can be understood below that the missile reduces its distance from the laser source and increases its distance from the vehicle: the closer the missile comes to the laser source, the slower he must fly forward compared to the vehicle flying above.

One way to control the missile is to determine the location of the laser source of the laser beam. From this location and the position of the vehicle a shading corridor can be calculated in which the missile must remain in order 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, and the other end moves with the moving vehicle. If the position of the shading corridor is known, the missile can be held in it for shading the vehicle.

The flight of the missile may be controlled by a control unit of the missile and / or a control unit of the vehicle. One of the control units expediently recognizes the laser beam as such, for example on the basis of scattered radiation of the laser beam and in particular with the aid of image processing methods or on detection of a luminous light spot on the vehicle.

In this respect, it is advantageous if the control unit determines from the data of the sensor system the position of a laser source which emits the laser beam. In this case, a radiation end of the laser beam can be detected, and from the position of the beam, the position of the laser source can be determined. Alternatively or additionally, the position from triangulation can be determined from the data of several sensors. The position of the laser source can be detected as a direction, for example as an absolute direction or as a direction relative to the direction of flight of the aircraft. It is also possible to determine the direction as an absolute, ie geographical, direction.

Furthermore, a determination of a distance of the laser source from the sensor system is advantageous. This can be done particularly easily using a flying height of the vehicle. If the direction of the laser source and the altitude are known, the distance to the laser source can be calculated from this in a simple manner, in particular taking into account topographical data of an overflown landscape.

The control unit initiates a start of the missile expediently in dependence on the recognition result. If a laser beam is recognized as such and it is also classified as threatening to the vehicle, the missile is started. If a laser beam is not recognized as such or classified as non-threatening, the launching of the missile expediently fails.

The flight of the missile can be controlled independently by a control unit of the missile. Additionally or alternatively, it is possible that the remaining in the vehicle control unit controls the flight of the missile or mitsteuert. For example, the self-controlling missile an escape or Abschattungsanweisung be issued by the vehicle, which is then taken into account by the control unit of the missile.

A control of the missile from the vehicle is also advantageous if the position of the laser beam or the laser source is accurately determined by the vehicle or the vehicle detects an impact of the laser beam. The missile can be directed from the vehicle into a shading position or into the shading corridor.

For this purpose, it is advantageous if a control unit, in particular that of the vehicle, determines both the position of the vehicle and the position of a laser source of the laser beam. The control unit can control the flight of the missile and hold it between the laser source and the vehicle. Conveniently, the control unit also determines the position of the missile and takes into account this in the control of the missile. The positions may be absolute positions, for example with respect to an earth coordinate system, or relative positions of the vehicle and the laser source and in particular the steering missile to each other.

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. Accordingly, it is advantageous if the flight of the missile is controlled so that it remains between the laser source and a predetermined, to be protected laser-sensitive point of the vehicle. Thus, for example, a laser-sensitive point of the vehicle can be deliberately shadowed by the corresponding flight control of the missile. The missile remains between the laser source and the predetermined location, that is, at a position such that the location is shadowed by the laser beam or would shadow it as the laser beam illuminates the location.

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. As a laser-sensitive body is not only a geometric point on the vehicle to understand, but a spatially extended area that 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.

A further possibility for controlling the guided missile is that a spot illuminated by the laser beam of the vehicle is detected and localized. If the position of the laser source is known, a shading corridor can be calculated and the missile can remain held within the shading corridor. However, even if the position of the laser source is not known, a lighted spot on the vehicle may be shaded, especially if the missile is held relatively close to the vehicle. For example, the missile flies directly under the vehicle and shadows the illuminated spot. It is advantageous in this case if the position of a lighting location at which the laser beam hits the vehicle is determined and the guided missile is controlled as a function of the position of the lighting location.

Detecting a spot illuminated by the laser beam on the vehicle is possible in a particularly simple manner from a missile flying in the vicinity, in particular the guided missile. For this purpose, it can have a vehicle-oriented sensor which is prepared for the detection of a laser light spot. The sensor senses the illuminated location at which the laser beam hits the vehicle, and a control unit, advantageously a control unit of the guided missile, determines the position of the lighting location, for example relative to a position of the missile and or a reference point of the vehicle. The control unit can now control the flight of the guided missile so that the illuminated spot disappears on the vehicle. The illuminated spot can be used with or without recognition of their relative position to the guided missile as a control variable, in particular as a controlled variable, for steering the missile. If the illuminated spot is recognizable on the vehicle, the flight of the guided missile is controlled so that the illuminated spot disappears.

Appropriately, it is detected whether the illuminated spot covers a laser-sensitive point of the vehicle. The detection can be performed by a control unit of the missile. The detection can be based on stored sensitivity data of the vehicle. If a laser-sensitive point of the vehicle is illuminated, the flight of the guided missile is expediently controlled so that the Light spot disappears. If the illuminated spot is not a laser-sensitive spot, the illumination of the spot does not lead to critical damage to the spot even with a longer illumination, so that shading of this sufficiently laser-hard spot can be dispensed with. The missile can be controlled so that it shaded another - especially laser-sensitive - spot, so it remains between the laser source and this laser-sensitive point even if it is not illuminated.

For determining the position of the illuminated location on the vehicle, it is advantageous if a control unit determines the position of the lighting location on the vehicle on the basis of characteristic image features of the vehicle. For this purpose, the characteristic image features are expediently at least partially stored in a database to which the control unit has access.

For the protection of a laser sensor, it is advantageous if this is arranged on a side facing away from the laser source side of the missile and, for example, is oriented upward. Upwards here can be understood that the center of gravity of the recording orientation of the sensor is directed into the upper half-space, whose zenith is in the opposite direction to the center of the earth. This may also be the case with a guided missile parked on the ground in regular parking position, so that the sensor is arranged on top of the guided missile. The missile can observe the vehicle from below and monitor it for lighting.

A protection of the vehicle by the guided missile can be detected from an attacking point and a control of the laser beam can be changed accordingly. For example, the laser beam is aligned in rapid succession on several laser-sensitive points, so that in each case a large amount of laser energy is deposited. Due to the inertia of the guided missile, this may not be able to follow the rapid change of destination. Nevertheless, in order to achieve sufficient protection of the vehicle, it is advantageous if the flight of the missile is controlled so that the missile casts its shadow on several areas of the vehicle to be protected so that none of the points illuminated by the laser beam for more than a predetermined time duration becomes. For example, the lighting of a second location is accepted without the missile being controlled to shadow this second location. Only when this second location is illuminated so long that the predetermined time period is reached threatened, the position of the missile is changed relative to the aircraft and the second location is shaded to cool it.

The predetermined amount of time may depend on a laser sensitivity of the locations, so that the longer the time the laser hardens the location in question, the greater the time duration. The time period may also depend on a laser power that has been calculated, for example, by a control unit of the vehicle. Further, the time period may be dependent upon the number of illuminated locations on the vehicle in the past. In addition, the predetermined period of time can be dependent on a distance of the illuminated locations from each other, so that an alternating duration, which assumes a change of the missile from one shading position to the other, is taken into account. Furthermore, the period of time may depend on the amount of laser energy previously deposited at that location and a cooling time. If the points have already been illuminated before and the cooling time was low, then the predetermined period of time is shorter than if the cooling time had been greater.

For example, an irradiated point on the vehicle is determined. Now, a temperature, a deposited amount of energy, a degree of deterioration and / or the like of this location can be determined. Furthermore, a laser hardness of the site can be taken into account, for example a destruction period from which further irradiation of the site leads to destruction of the site. Furthermore, an alternating duration, which takes a change in the shading position of the guided missile from a shadowed to an irradiated point, can be determined. Depending on one or more of the above variables, a changeover time may be determined at which the missile is controlled to a new shading position. At the time of change, the missile will now be directed to the new location to be shaded.

It is advantageous if the flight of the guided missile is controlled such that a shadow of the missile changes from the momentarily shaded point to a momentarily irradiated point as a function of a cooling time of the momentarily shaded point. Furthermore, it is expedient to take into account a laser hardness or damage time of the point currently irradiated and an alternating duration which takes the movement of the shadow between the points.

Another possibility of shading is that the guided missile ejects a shading means. Such a shading means may include smoke, flicker elements or the like. The shading means is expediently ejected in addition to the drive exhaust gas of the missile, so that the ejection can be independent of a thrust control of the missile. For this purpose, the guided missile expediently comprises a shading means nozzle, which is provided in addition to the engine jet opening.

Further, it is advantageous if the flight of the missile is controlled so that the ejected shading shadows a predetermined, laser-sensitive point of the vehicle at least partially. In particular, it is advantageous if the shading means is ejected as a function of the position of a lighting spot on the vehicle and the position of the guided missile. For example, if the lighting point behind the missile so that shading must be achieved by the missile by a deceleration of the missile, so the shading means can be first ejected to achieve shading in addition or earlier before the missile with its solid structures, the shading of this Job can begin.

When using tinsel elements, it is advantageous if they have a retroreflective property. The laser beam is reflected at the bauble elements in the opposite direction, so that a part of the laser radiation is reflected back to the laser source. Their function can be impaired as a result.

In order to achieve fast maneuverability for rapid shadowing, it is advantageous if the missile has a braking means, such as a brake flap or a brake sail, for reducing the speed of flight. This is expediently extended during the flight and brakes the missile depending on the degree of extension. The airspeed can be draughty reduced and a falling back of the missile can be reached quickly.

Moreover, it is advantageous if the missile extends after its launch a shading element and thereby increases its shadow area, in particular to at least 1.5 times the shading surface of the missile at the start. This can cause inaccuracies in flight control be compensated for the missile and / or it can be shadowed several laser-sensitive points at the same time.

To disrupt the function of the laser source, it is also advantageous if the missile has a reflector, in particular a retroreflector. The reflector may for example be seconded to a shading element, which is extended after the start of the missile.

In addition, the invention is directed to a missile for protecting a vehicle from attack by a laser beam. In order to achieve effective protection of the vehicle from the attack, the guided missile according to the invention comprises a sensor system for sensing laser radiation of the laser beam and a control unit which is designed to fly the guided missile into the laser beam and to shadow the vehicle from the laser beam. Conveniently, the control unit is also prepared to keep the shadow of the missile on the vehicle.

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 in Reference to functional characteristics. 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 unmittelbar vor einem Angriff durch ein Lasersystem,

FIG 2

das Luftfahrzeug, das von einem loiternden Lenkflugkörper gegen einen Laserstrahl des Lasersystems abgeschattet wird,

FIG 3

das Luftfahrzeug, das von einem auf die Laserquelle zu fliegenden Lenkflugkörper gegen einen Laserstrahl abgeschattet wird,

FIG 4

das Luftfahrzeug in einer Ansicht von unten mit drei von Laserstrahlen beleuchteten Stellen, von denen eine durch einen Lenkflugkörper teilweise abgeschattet wird, und

FIG 5

den Lenkflugkörper beim Abschatten einer beleuchteten Stelle durch seine festen Strukturen und dem teilweisen Abschatten einer anderen beleuchteten Stelle durch ein gasförmiges Abschattungsmittel.

Show it:

FIG. 1

an aircraft immediately before an attack by a laser system,

FIG. 2

the aircraft, which is shaded by a loitering guided missile against a laser beam from the laser system,

FIG. 3

the aircraft being shaded by a guided missile aimed at the laser source against a laser beam,

FIG. 4

the aircraft in a view from below with three laser-illuminated areas, one of which is partially shaded by a guided missile, and

FIG. 5

the missile when shadowing a lit spot by its solid structures and the partial shading of another illuminated spot by a gaseous shading means.

FIG. 1 shows a vehicle 2 in the form of an aircraft, which is designed in this case 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, wherein the Laser beam 8 over a distance of several kilometers transported enough energy to destroy sensitive parts of the aircraft and thereby endangering its flying capacity acutely. 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 missile 12, 14, wherein in FIG. 1 to illustrate several protection methods three missiles 12 and a missile 14 are shown. Furthermore, the aircraft has a sensor system 16 with a plurality of sensors 18, which are each signaled by a control unit 20. In the illustrated embodiment, the aircraft is equipped with five sensors 18, 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 18 on the upper half of the fuselage of the aircraft , To protect the aircraft, the sensors 18 of the sensor system 16 actively monitor the airspace for laser radiation. The sensors 18 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 on the laser beam 8 can be determined. In this way, an image of the laser beam 8 is recorded, from whose wavelength or spectrum and whose geometry the control unit 20 of the sensor system 16 recognizes the laser beam 8 as such, in particular by means of image processing methods. When Geometrical features can be used to see the laser beam 8 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 20 first classifies the laser beam 8 in the three stages harmless, potentially dangerous and dangerous. In a classification harmless in the level of the laser beam 8 is further observed, however, neither the laser beam 8 is shadowed nor the laser source 10 is combated. Classification in one of the other two levels will prepare for shading and / or combat. For this purpose, a canister 22, 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 22. Alternatively or additionally, the ejection of the missile 14 from the fuselage of the aircraft 2 is prepared. Classification into the highest of the threat classes will initiate combat and / or shadowing. 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.

Both for shading and for controlling the laser source 10, it is advantageous if the position of the laser source 10 is known. This determines the control unit 20, 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. This can also be done by the upward sensor 18 whose view is adjusted to the laser source 10. On the basis of the orientation of the visible part of the laser beam 8, a further course of the laser beam 8 can also be extrapolated in the environment.

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 is detected by another of the sensors 18 of the sensor system 16, for example by a sensor 18 on a wing of the aircraft 2. This recognizes the laser beam 8 per se and both abrupt ends, the control unit 20, 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 18 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 18 on the aircraft 2 to each other.

To protect the aircraft, at least one missile 12, 14 is now started by the aircraft. The control of the start takes over the control unit 20 of the sensor system 16, which may also be part of a central vehicle control of the vehicle 2.

FIG. 2 and FIG. 3 show two embodiments for protecting the aircraft, which can be performed individually or in combination. In the first embodiment FIG. 2 The missile 14 is dropped from the fuselage of the aircraft, and this begins its Loiterflug, which is substantially parallel to the flight of the aircraft. The purpose of this flight is to shade the aircraft, in particular at least laser-sensitive points of the aircraft, from the laser beam 8. The missile 14 is driven with an air-breathing internal combustion engine, such as a turbine, so that a long flight in the company of the vehicle 2 is possible. Alternatively or additionally, a rocket motor is possible, in particular a solid fuel motor, which is tuned in terms of its performance on the airspeed of the aircraft. The missile 14 is equipped with large wings for large-scale shading of the aircraft. At least the entire lower side of the missile 14 is laser-hardened, so that an irradiation of at least three minutes by the high-energy laser beam 8 does not produce damage to the missile 14 which interferes with the flight. Part of the underside is equipped with retroreflectors, which reflect a part of the laser radiation back to the laser source 10.

For holding the missile 14 in the laser beam 8 there are several possibilities. For example, the position of the laser beam 8 in the space or its end on the vehicle 2 can be determined by sensors 18 of the sensor system 16. Corresponding control signals are given by the control unit 20 to a control unit 24 of the missile 14.

An alternative or additional possibility is that the missile 14 determines the shading itself and controls its flight from this. Thus, the missile 14 on an upward laser-sensitive sensor 26 which monitors the aircraft 2 from below. An impact of the laser beam 8 on the aircraft 2 is detected, and the missile 14 is controlled so that the irradiation spot of the laser beam 8 on the aircraft 2 disappears. For this purpose, the flight is controlled so that the controlled variable, namely the visibility of the laser spot on the aircraft 2, disappears or at least reduced. On the other hand, if the laser beam 8 is moved away from the aircraft, the laser spot also disappears. In this case, the missile 14 continues to accompany the aircraft for a predetermined distance or time duration in order to maintain protection against the potentially again dangerous laser beam 8.

Especially with a missile 14 with a rocket engine, it may be that the solid fuel of the rocket motor is consumed after a while. In this case, a second missile 14 can be started, which further shadows the vehicle 2. Even if in FIG. 1 only one missile 14 is shown in the vehicle 2, but several may be present and be started in succession.

An additional or alternative method for shading the vehicle 2 by a missile 12 is based on the drawing FIG. 3 shown. In a threat scenario as described above, a missile 12 is launched in the form of a steering rocket. Alternatively, the missile 2 may be designed as a steering floor, which is designed without its own drive, but is steerable and for the purpose sailable on a long flight. This missile 12 is started from the canister 22, for example, by a drop, a launch and / or a launch of a missile engine of the missile 12. Since the missile 12 by the alignment of the canister 22 on the laser source 10 and / or forward and down already aligned starts, detours can be avoided and the missile 12 can be quickly brought into a favorable shading position. This is particularly advantageous when using a steerable projectile, which also has a control unit for controlling the steered flight and a steering system for performing the steering.

The methods described below can be carried out with the guided missile 12 and / or with the guided missile 14. For controlling the guided missile 12 and / or the missile 14 from FIG. 2 a shading corridor 28 is first determined by the control unit 20. This shading corridor 28 extends from the laser source 10 to the vehicle 2 and is designed in its geometry so that it includes all the imaginary lines from the laser source 10 to all points of the vehicle 2. However, lines from the laser source 10 to spatial points which are more than a predetermined distance away from the vehicle 2 are not within the shading corridor 28. This distance serves to compensate for calculation inaccuracies and is expediently less than 50 m, in particular less than 10 m. The shading corridor 28 is calculated by the control unit 20 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 28, in particular its geometry and position in space, may be determined in absolute, earth-fixed coordinates or in relative coordinates which relate to a reference space moved with the vehicle 2.

Further, in the control unit 20, a plurality of laser-sensitive points 30, 32 of the vehicle 2 are deposited, which in FIG. 4 are illustrated by a front dotted area 30 and a rear dotted area 32. These laser-sensitive points 30, 32 include those areas on the vehicle whose irradiation by a high-energy laser within a predetermined period of, for example, less than 10 seconds lead to damage to the vehicle 2, which impairs its functionality. Shading corridors 34, 36, which are calculated in FIG. 2, are also calculated for these laser-sensitive points 30, 32 FIG. 3 dotted or dashed lines are indicated. According to the shading corridor 28 include the Shadowing corridor 34, 36 exclusively all imaginary lines from the laser source 10 to all possible points of the laser-sensitive points 30, 32nd

At the in FIG. 3 In the embodiment shown, the guided missile 12 was launched forward and obliquely downwards, so that its distance from the laser source 10 is reduced by the flight and its distance from the vehicle 12 is simultaneously increased. The flight of the guided missile 12 is in this case controlled by the control unit 20 of the aircraft 2, wherein the control unit 20 is connected via a radio link with the control unit of the missile 12 in connection. The flight of the missile 12 is controlled so that the missile 12 always within the Abschattungskorridors 28 and 34, 36 remains. Leaves the laser beam 8 the shading corridor 28, so he no longer applies to the vehicle 2, the missile 12 still remains within the Abschattungskorridors 28 in order to shade the vehicle 2 as quickly as possible with a renewed pivoting of the laser beam 8 on the vehicle 2. In particular, the guided missile 12 remains within one of the special shading passages 34, 36 for protecting a laser-sensitive point 30, 32 of the vehicle 2. The laser beam 8 leaves one of the shading passages 34, 36, but remains in the shading corridor 28, that is to say at a non-laser-sensitive point the vehicle 2, so the missile 12 still remains within one of the Abschattungskorridore 34, 36 in order to protect the relevant laser-sensitive point 30, or 32 swiftly when the laser beam 8 pivots on this.

Based on the presentation FIG. 4 are described in the following defense strategies of the vehicle 2. The laser beam 8 is aimed at the vehicle 2 and forms a light spot 38 at a laser-sensitive point 32. The guided missile 12 or the missile 14, to which the method descriptions also refer, is directed such that it at least partially shields the laser-sensitive point 32. At the in FIG. 4 shown position of the missile 12, 14 shading the spot 38 partially. To increase its Abschattungsfläche two shading elements 40 were extended in the form of shading sails after the launch of the missile 12, 14, which more than double the shading surface of the missile 12, 14. The shading elements 40 are coated with a retroreflective layer, which in FIG. 4 is indicated by a hatching of the shading elements 40. If the laser beam 8 strikes this layer, it is partially reflected back to the laser source 10 and damages its optics or other elements there, so that the functionality of the laser source 10 is impaired.

The flight of the missile 12, 14 is now controlled, for example, by the control unit 20 or the control unit 24 of the missile 12, 14, that the missile 12, 14 completely shading the light spot 38. For this purpose, the luminous intensity of the light spot 38 is measured, either by the sensor 26 of the missile 12, 14 or by one of the sensors 18 of the aircraft 2. The light intensity can be used as a controlled variable for controlling the steering of the missile 12, 14, wherein the control target the Disappearance of the luminosity is. With the missile 14, this can be achieved very easily, since its sensor 26 can easily detect and measure the luminous intensity of the luminous spot 38 during a loiter flight. If the missile 12 is designed as a sailable projectile, it removes relatively quickly from the vehicle 12. Although the measurement of the luminous intensity of the luminous spot 38 is still possible, it is still more difficult. The measurement is therefore expediently carried out by one of the sensors 18. These are placed so that they can scan at least all the laser-sensitive points 30, 32.

If the position of the light spot 38 on the vehicle changes, for example, it moves into a non-laser-sensitive area, as in FIG FIG. 4 is indicated by the light spot 42, the missile 12, 14 so remains in the shading corridor 34, 36 so that it shaded a laser-sensitive point 30, 32. Shading of the other areas of the vehicle 2 is dispensed with. However, if the laser beam 8 is guided to another laser-sensitive point 30, as in FIG FIG. 4 is indicated by the light spot 44, the missile 12, 14 is directed into a shading position of the corresponding laser-sensitive point 30. However, this does not have to take place immediately, but can take place after a waiting period, which depends on the laser hardness of the region 30 or the amount of energy deposited there. In this way it is prevented that the light spot 38, 44 quickly jumps back and forth between the laser-sensitive points 30, 32 and the missile 12, 14 greatly reduces its shading effect by continuous tracking. After a predetermined period of time or waiting period, the guided missile 12, 14 controls the newly illuminated laser-sensitive area 30 and shadows it against the laser beam 8. If the laser beam 8 jumps to another laser-sensitive region 32, the missile 12, 14 remains in such a way that it shadows the previously irradiated laser-sensitive point 30 until it reaches a non-critical state, for example has cooled down long enough. Only then is the missile 12, 14 steered to shadowing another laser-sensitive point 32.

FIG. 5 shows a further embodiment in which the shadowing of two light spots 38, 44 is enhanced by the ejection of gaseous shading agent 46. For this purpose, the missile 12, 14 comprises a smoke generator or a flicker ejector, the baubles, such as foil pieces ejected. The shading means 46 has the purpose of shading and may also serve the purpose of retroreflection, especially when using flicker elements. At the in FIG. 5 illustrated embodiment, for example, the radiation-critical time of the laser-sensitive points 30, 32 so small that an alternating illumination of these points 30, 32 by the laser beam 8 to a critical destruction of at least one of these points 30, 32 leads.

Now the missile 12, 14 protects the points 30, 32 according to a stored priority. This priority may be the importance of elements of the aircraft 2 located at locations 30, 32. However, it is also possible that the missile 12, 14 with higher priority protects the front laser-sensitive area 30 and tries to at least partially protect the rear area 32 with the aid of the shading means 46, or shadow. At the in FIG. 5 As shown, the rear light spot 38 lies just in front of the front light spot 44, so that the two locations 30, 32 can be adequately shaded. However, this arrangement of the light spots 38, 44 is rather not the rule. If the light spot 38 lies obliquely behind the light spot 44, then the constellation is off FIG. 5 not available.

However, ejection of shading means 46 nevertheless makes sense, since the change of the shading position of the missile 12, 14 from one location 30 to another location 32 takes a while. For example, after completion of the shadowing of the front laser sensitive spot 30, the missile 32 may be steered sideways until it flies just in front of the spot 38 on the rear laser sensitive spot 32. The emission of the shading agent 46 can be started and continue until the missile 12, 14 reaches the laser-sensitive point 32 by slowing down its airspeed and immediately shades the light spot 38.

To accelerate this braking process, the missile 12, 14 is equipped with a brake flap 48, the in FIG. 5 is indicated only by a transverse line. The brake flap 48 can also be realized in an equivalent manner by a brake parachute or other extendable or ejectable element.

In a further method, a plurality of missiles 12 are started by the vehicle 2. This is in FIG. 3 indicated by the multiple existing missile 12 in canister 22. The missiles 12 are controlled in such a way that several or all of the laser-sensitive points 30, 32 of the vehicle 2 are shaded, in particular independently of the position of the light spot 38, 42, 44.

LIST OF REFERENCE NUMBERS

2

vehicle

4

landscape

6

laser system

8th

laser beam

10

laser source

12

missile

14

missile

16

sensor system

18

sensor

20

control unit

22

canister

24

control unit

26

sensor

28

Abschattungskorridor

30

laser-sensitive point

32

laser-sensitive point

34

Abschattungskorridor

36

Abschattungskorridor

38

spot

40

shading

42

spot

44

spot

46

shading

48

airbrake

Claims (15)

1. Method for protecting a vehicle (2) from an attack by a laser beam (8), wherein a sensor system (16) detects laser radiation of the laser beam (8) and a guided aerial vehicle (12, 14) flies into the laser beam (8) and shadows the vehicle (2) thereby.
2. Method according to Claim 1,
   characterized
   in that the guided aerial vehicle (12, 14) is launched from the vehicle (2) and the flight of the guided aerial vehicle (12, 14) is controlled from the vehicle (2).
3. Method according to Claim 1 or 2,
   characterized
   in that the guided aerial vehicle (12) is fired towards the front from the vehicle and said guided aerial vehicle sails in the direction of a laser source (10) of the laser beam (8).
4. Method according to any one of the preceding claims,
   characterized
   in that the positions of the vehicle (2) and also of the guided aerial vehicle (12, 14) and a laser source (10) of the laser beam (8) are established and the guided aerial vehicle (12, 14) is kept between the laser source (10) and the vehicle (2) in the laser beam (8).
5. Method according to any one of the preceding claims,
   characterized
   in that the position of a luminous spot (38, 42, 44), at which the laser beam (8) strikes the vehicle (2), is determined and the guided aerial vehicle (12, 14) is controlled depending on the position of the luminous spot (38, 42, 44).
6. Method according to any one of the preceding claims,
   characterized
   in that the guided aerial vehicle (12, 14) has a sensor (26) directed to the vehicle (2), said sensor sensing a luminous spot (38, 42, 44), at which the laser beam (8) strikes the vehicle (2).
7. Method according to Claim 6,
   characterized
   in that the sensor (26) is arranged on a side of the guided aerial vehicle (12, 14) facing away from the laser source (10) and aligned upwardly.
8. Method according to any one of the preceding claims,
   characterized
   in that a flight of the guided aerial vehicle (12, 14) is controlled in such a way that the guided aerial vehicle (12, 14) casts its shadow on a plurality of spots (30, 32) of the vehicle (2) to be protected in such a way that none of the spots (30, 32) are illuminated by the laser beam (8) for longer than a respectively predetermined time duration.
9. Method according to any one of the preceding claims,
   characterized
   in that the flight of the guided aerial vehicle (12, 14) is controlled in such a way that a aerial vehicle shadow changes from the currently shadowed spot to the currently irradiated spot depending on a cooling duration of the currently shadowed spot, a damage time of the currently irradiated spot and a change duration taken up by moving the shadow between the spots.
10. Method according to any one of the preceding claims,
    characterized
    in that the guided aerial vehicle (12, 14) ejects a shadowing means (46).
11. Method according to Claim 10,
    characterized
    in that the shadowing means (46) is ejected depending on the position of a luminous spot (38, 42, 44) on the vehicle (2) and the position of the guided aerial vehicle (12, 14).
12. Method according to any one of the preceding claims,
    characterized
    in that the guided aerial vehicle (12, 14) has an air break (48) for reducing its flight speed.
13. Method according to any one of the preceding claims,
    characterized
    in that the guided aerial vehicle (12, 14) extends a shadowing element (40) after its launch and, as result thereof, increases its shadow area to at least 1.5-times the size.
14. Method according to any one of the preceding claims,
    characterized
    in that the guided aerial vehicle (12, 14) has a retroreflector.
15. Guided aerial vehicle (12, 14) for protecting a vehicle (2) against attack by a laser beam (8), said guided aerial vehicle having a sensor (26) for sensing laser radiation of the laser beam (8) and a control unit (24), the latter being designed to fly the guided aerial vehicle (12, 14) into the laser beam (8), to shadow the vehicle (2) from the laser beam (8) and keep the shadow of the guided aerial vehicle (12, 14) on the vehicle (2).

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