EP3118566B1 - Procede de protection d'un vehicule contre une attaque par un rayon laser - Google Patents

Procede de protection d'un vehicule contre une attaque par un rayon laser Download PDF

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Publication number
EP3118566B1
EP3118566B1 EP16001539.2A EP16001539A EP3118566B1 EP 3118566 B1 EP3118566 B1 EP 3118566B1 EP 16001539 A EP16001539 A EP 16001539A EP 3118566 B1 EP3118566 B1 EP 3118566B1
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EP
European Patent Office
Prior art keywords
laser beam
vehicle
laser
guided missile
missile
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP16001539.2A
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German (de)
English (en)
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EP3118566A1 (fr
Inventor
Arne Nolte
Michael Masur
Michael Gross
Nicolai Künzner
Thomas Kuhn
Norbert Stelte
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Diehl Defence GmbH and Co KG
Original Assignee
Diehl Defence GmbH and Co KG
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Publication of EP3118566A1 publication Critical patent/EP3118566A1/fr
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
    • F41H11/00—Defence installations; Defence devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/30—Command link guidance systems
    • F41G7/301—Details
    • F41G7/303—Sighting or tracking devices especially provided for simultaneous observation of the target and of the missile
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
    • F41H13/00—Means of attack or defence not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/01—Arrangements thereon for guidance or control

Definitions

  • 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.
  • the WO 02/14777 A1 describes a method for protecting an object from a laser device, wherein upon detection of a laser radiation of the laser device retroreflectors are ejected or fired from the object to be protected or from an environment thereof, to disturb the laser device or possibly damage.
  • the aircraft is equipped with a laser detection and warning system, with which, inter alia, the location of a laser source can be determined.
  • the position of the laser source is determined and a guided missile is launched and directed to the laser source.
  • the missile can approach and combat the laser source and shade the vehicle during the approach to the laser source. This is done expediently so quickly that the laser energy deposited on the vehicle has not yet led to threatening damage.
  • a fast protection can be achieved by starting the missile from the vehicle, since then the missile is already on site and dive into the laser beam for shading and can quickly fly to combat the laser source on this.
  • the missile is expediently equipped with a rocket motor.
  • the guided missile may approach the laser source mechanically destroy by means of an active part, for example, by a cone-shaped forward splintering charge.
  • the method is particularly suitable for use against a high energy laser source or a high energy laser beam. Also advantageous is a defense of a sturgeon laser.
  • a sensor of a sensor system of the vehicle and / or the missile is expediently sensitive in a radiation spectrum which is usually used for high-energy laser or interfering laser.
  • 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.
  • the sensor expediently recognizes characteristics typical of laser radiation, such as the presence of coherent radiation.
  • a laser source is recognized as such, for example, based on an image of the laser beam in the air or by residual heat radiation when the laser source is turned off.
  • an image sensor is advantageously present, for example with a matrix detector.
  • the vehicle is preferably an aircraft, and the invention is also advantageously applicable for protecting a land vehicle or a watercraft.
  • a control unit of the vehicle may have one or more computing units, which may be arranged in the vehicle at a location or distributed over the vehicle.
  • the control unit expediently recognizes the laser beam as such and initiates a start of the missile as a function of the recognition result. If a laser beam is recognized as such and it is also classified as threatening to the vehicle, the missile is launched, in particular from the vehicle. If a laser beam is not recognized as such or classified as non-threatening, the launching of the missile expediently fails.
  • the guided missile is expediently an unmanned guided missile, in particular with a rocket motor. Also possible is a missile without its own engine, for example in the form of a steering column.
  • the missile expediently comprises a control unit which directs the missile towards the laser source.
  • the position of the laser source can be determined in various ways.
  • a sensor of the sensor system of the vehicle and / or the missile captures an image of the laser beam.
  • the location of the laser source of the laser beam can be determined therefrom, for example because the laser source is visible from the image as such.
  • Another possibility is that from the image a straight line of the laser beam in the environment and a defined end of the laser beam or the line is determined. This can be done by a control unit of the vehicle or a control unit of the guided missile. This end can be defined as the location of the laser source, and the missile can drive that position.
  • 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 is determined by means of a non-optical sensor, such as a radar sensor or the like.
  • the position of the laser source can be determined from the vehicle and transferred to the missile.
  • the location may alternatively or additionally be determined by the guided missile.
  • the position of the laser source may be determined as absolute, geographical coordinates or relative to the vehicle and / or missile.
  • the guided missile flies towards the laser source and expediently uses the laser beam as a guide beam for driving the laser source. In general, there are several options for this.
  • a control unit of the missile determines the position of the laser source and controls it. The determination can take place by means of image processing, as described above, wherein the guided missile independently determines the position or the position is determined by the vehicle and is transmitted to the missile.
  • the intensity of radiation emitted by the laser source in direct line to the missile is recorded as a measured variable.
  • a sensor will open directed the laser source and receives the laser radiation thrown by the laser source in a direct line on the sensor.
  • the detected laser intensity increases with increasing proximity to the laser beam, ie with decreasing angle to the spatial direction of the laser beam.
  • An increase in the measured intensity of the laser radiation is therefore a sign of an approach to the laser beam.
  • This method requires a forward sensor, which has the disadvantage that it can be hit and destroyed directly by the laser beam. Immersion in the laser beam should therefore be avoided.
  • This disadvantage can be circumvented by a third possibility, which is based on the measurement in the air scattered laser radiation.
  • the laser radiation is spatially scattered on its way through the air to a small extent, so that the laser beam is visible as a line in the landscape.
  • This intensity of the scattered radiation can be measured and increases with decreasing distance to the laser beam.
  • the intensity can be used as a control variable for steering the missile.
  • This method has the advantage that laser radiation scattered in the ambient air can be detected with sideways or backward sensor systems, which can both be protected towards the front.
  • sideways sensor technology is understood as meaning a sensor system which is oriented exclusively in a lateral direction relative to the longitudinal axis of the missile and which is therefore not oriented in the direction of flight, and a rearward sensor is directed precisely opposite to the direction of flight of the missile, generally also in the lateral direction, but likewise not Forward.
  • the measurement of the scattered radiation has the further advantage that it can take place both from outside the laser beam and from within the laser beam and in both cases is suitable for steering the guided missile.
  • a distance of the laser source to the vehicle is determined.
  • the direction of the laser beam is expediently determined, which may be an absolute direction, for example in geographical coordinates, or a relative direction to the orientation or direction of flight of the vehicle.
  • the determination of the distance of the laser source can be done particularly easily using a flying height of the vehicle and the direction.
  • topographical data of a landscape overflown by the vehicle are expediently included.
  • the Distance by triangulation using a plurality of spaced sensors done.
  • the vehicle is equipped with a plurality of sensors that detect the laser beam and / or the laser source. From the orientation of the laser source to a reference direction of the respective sensors and the alignment of the reference directions of the sensors to each other can be calculated using triangulation, the distance in a simple manner.
  • the missile expediently flies in the laser beam and is in this case controlled so that it remains in the laser beam, so that in this way the vehicle remains at least partially shaded by the laser beam during this flight.
  • the guided missile can fly at least substantially parallel to the laser beam, which can also be understood to mean swaying in the laser beam, so that the laser beam at least partially remains directed at the guided missile.
  • the guided missile laser beam can be understood the missile laser beam core whose power per cross-sectional area is at least for example 30% of the maximum power per cross-sectional area, the maximum power per cross-sectional area is to be seen at the location of the missile, since the power per cross-sectional area with increasing distance decreases to the laser source.
  • the position of a shading corridor between the laser source and the vehicle is determined.
  • the location of the shading corridor can be calculated from the location of the laser source and the location of the vehicle.
  • the shading corridor may include all points at which the missile may be to shade the vehicle.
  • the end of the shading corridor at the laser source remains fixed in space or moves along with the movement of the laser source. The other end moves with the moving vehicle.
  • the guided missile can be controlled as a function of its position relative to the shading corridor. For example, the missile is held within the Abschattungskorridors so that it always shields the vehicle here.
  • the shading corridor may range from the laser source to the vehicle and be configured in geometry to include all of the imaginary lines from the laser source to all points of the vehicle. Lines from the laser source to areas other than in the vehicle or more than a predetermined distance from the vehicle are not within the shading corridor.
  • 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
  • the shading corridor is limited to a space between a laser-sensitive location of the vehicle and the laser source.
  • a geometric point is to be understood as a point, but a spatially extended area which is to be protected from irradiation by high-energy laser radiation.
  • the sum of the laser-sensitive points of the vehicle is expediently limited to a maximum of 25% of the silhouettes of the vehicle visible from the laser source.
  • One way of defending a laser system against an approaching guided missile is to pivot the laser beam so that following the missile deflects the missile from the shadowing corridor.
  • the vehicle By quickly swinging back the laser beam onto the vehicle and the inertia of the guided missile, the vehicle can be re-irradiated without the missile being able to shade the vehicle.
  • a flight space is determined within which the missile moves. The flight space is determined, for example, from the distance between the laser source and the vehicle.
  • the guided missile is now controlled to remain within the flight space.
  • the space can be confined to a very thin corridor with a small area to be protected, which moves with the movement of the vehicle through the room.
  • control inaccuracies and inaccuracies in determining the position of the laser source, the vehicle, and / or the missile may result in inaccuracies in steering control of the missile.
  • This uncertainty can be greatest where the distance to the laser source and to the vehicle is greatest, thus in an area in the middle between the vehicle and the laser source. It is therefore advantageous if one Flight of the missile between the laser source and the vehicle is determined, which is tapered to both the laser source and to the vehicle.
  • the flight space is expediently rotationally symmetrical and may, for example, have the shape of a football ice.
  • the flight space is suitably determined using the shading corridor.
  • the flying space expediently extends beyond the shading corridor, in particular in such a way that it extends furthest beyond the shading corridor in a middle region between the vehicle and the laser source.
  • the shading corridor can hereby be limited to shading of the entire vehicle or only one or more laser-sensitive points. In the case of several laser-sensitive areas, a space between the corresponding shading corridors is expediently used as the entire shading corridor, so that a single shading corridor is created. This can be used to determine the flight envelope.
  • the guided missile expediently remains in a predetermined flying space when the laser beam disappears from a shading corridor.
  • the disappearance may in this case be a pivoting of the laser beam from the shading space or flying space or a shutdown.
  • the guided missile follows only partially a laser beam pivoted out of the shading corridor and expediently always remains in the flying space or is controlled accordingly.
  • the vehicle monitors the position of the flying missile. A misdirection of the missile by a control error or a destroyed sensor can be avoided.
  • the monitoring is not only useful when the control of the missile is done completely from the vehicle.
  • intervention of the vehicle in the steering control can be advantageous. If, for example, the guided missile leaves the flight space, so that shading of the vehicle is endangered, intervening in the flight control can retrieve the guided missile into the flight space, so that the vehicle can be reliably shadowed.
  • the missile is conveniently controlled using the position of the vehicle and the position of the laser source in its flight.
  • This control can originate from the vehicle and / or from a control unit of the guided missile. If the steering system is based solely on the guided missile, then the position of the missile should be constantly known to the missile. The position can, for example, be transmitted continuously or periodically from the vehicle to the guided missile by data link. It is also possible that the position of the vehicle is derived from an inertial position, for example a position of the vehicle at the start of the guided missile, expediently using the direction of flight and the speed of flight of the vehicle. If the position of the laser source is known, a shading corridor or flight space can be calculated by the guided missile and used for the control.
  • the missile detects the laser beam and controls its flight path as a function of its position to the laser beam.
  • the guided missile uses the laser beam as a beacon and flies in this way towards the laser source.
  • This flight control is conveniently combined with flight control using a shading corridor and / or flight space. In this way, in particular, a rough navigation based on shading corridor or flight space can take place and a detailed navigation can be carried out on the basis of the laser beam itself.
  • the guided missile expediently comprises one or more sensors, which are sensitive in particular to stray radiation of the laser radiation in the air.
  • the laser beam disappears from a sensor of the missile and / or the vehicle.
  • the guided missile In order to be able to reliably continue an approach of the guided missile to the laser source, it is advantageous for the guided missile to fly onto the laser beam when the laser beam has disappeared by means of inertial navigation.
  • the disappearance may in this case be characterized in that the laser beam is no longer or not sufficiently detected by one or more sensors of the missile.
  • the laser beam detects a disappearance of the laser beam and then activates a previously shaded by the laser beam sensor.
  • the flight control is then conveniently continued using this newly activated sensor.
  • the sensor may be a forward sensor, which expediently recognizes the laser source, for example based on thermal radiation, as such.
  • the guided missile may be advantageous for the guided missile to activate a forward sensor which was previously shaded by the laser beam in order to be able to carry out flight control with great precision. This is particularly advantageous in the endgame of the flight, ie within the last section of the flight of the missile from the vehicle to the laser source.
  • An activation of a forward sensor which is usually very sensitive to laser radiation or heat radiation, should, however, only take place if the risk of direct irradiation by the laser beam is low. It is therefore advantageous if the guided missile detects a danger of the laser beam and activates a forward sensor at a danger below a limit value and uses its data for a flight to the laser source.
  • a forward sensor can be very sensitive to high energy laser radiation, this is advantageously under a hood, which is blasted off, for example, at the beginning of Endgames. Also possible and advantageous is a movable mechanical cover of the forward sensor, which opens and thus releases the view of the forward sensor forward.
  • the laser beam can be switched off so that it disappears and a line along the laser beam is no longer possible.
  • An optical guidance of the guided missile can also be maintained in this situation if the missile detects a heat source of the laser source when the laser beam is switched off. Since the laser source is warm shortly after switching off the laser beam, the heat source can be detected with an infrared sensor. The guided missile can take the heat source to the target and this drive. In order to avoid confusion with another heat target, it is advantageous to compare the pattern of the heat source with data from a database. In the database, infrared patterns of post-radiation laser sources can be deposited. Fits the sensed pattern with one deposited patterns sufficiently, so the heat source can be classified as a laser source, so that the heat source can serve as a target.
  • the invention is also directed to a system of a vehicle and a missile having a control system according to the features of claim 10.
  • Effective protection against irradiation of the vehicle by a high energy laser can be achieved when the control system is prepared to position to determine the laser source to start the missile and to direct this to the laser source.
  • the control system may be present in common in the vehicle, in the missile or in both units, for example by a control unit in the vehicle and a control unit in the guided missile.
  • a task distribution is advantageous in that the determination of the laser source is advantageously carried out by a control unit in the vehicle and the steering of the missile to the laser source out through a control unit of the missile.
  • 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.
  • a laser system 6 is positioned, which in the in FIG. 1 represented moment a laser beam 8, which is generated by a laser source 10, directed into the sky.
  • the laser system 6 is a high-energy laser system that emits the laser beam 8 predominantly in the infrared spectral range, for example, at 3.8 microns, the laser beam 8 over a distance of several kilometers transported enough energy to destroy sensitive parts of the aircraft and thereby its flying capacity acute to endanger.
  • the laser system 6 is used to combat aircraft and has a control unit which pivots the laser beam 8 on the vehicle 2 and the laser beam 8 automatically tracks the movement of the aircraft 2.
  • a laser-sensitive point of the vehicle 2 is deposited, to which the laser beam 8 is automatically directed by means of image processing methods to the irradiate in the laser system 6 pictorially deposited location of the aircraft 2 over a period of a few seconds and thereby destroy.
  • this has at least one missile 12, wherein in FIG. 1 to illustrate several missiles 12 are shown.
  • the aircraft has a sensor system 14 with a plurality of sensors 16, which are each signaled by a control unit 18.
  • 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 ,
  • 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.
  • 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.
  • the control unit 18 of the sensor system 14 in particular by means of image processing methods, the laser beam 8 as such.
  • the laser beam 8 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.
  • the control unit 18 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.
  • 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.
  • a classification in the highest of the Threat classes will initiate combat. For this purpose, for example, a release of an operator of the aircraft 2, such as a pilot, necessary. However, this has already been given in advance, for example because it is known that the aircraft is flying through a potentially dangerous region.
  • the position of the laser source 10 is known. This determines the control unit 18, for example, from the geometry of the laser beam 8. Thus, at the location of the abrupt end of the laser beam 8, the laser source 10 can be suspected.
  • 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.
  • 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.
  • a position determination of the laser source 10 by means of triangulation.
  • At least one missile 12 is now started by the aircraft.
  • the control of the start takes over the control unit 18 of the Sensor system 14, which may also be part of a central vehicle control of the vehicle 2.
  • FIG. 2 shows one of the missile 12, which are stored in the canister 20 in the vehicle 2.
  • the guided missile 12 has guide vanes 22 that are moved by actuators 24 for steering the missile 12.
  • the control of the actuators 24 is carried out by a control unit 26 of the missile 12.
  • the missile is powered by a rocket motor 28, in particular a solid fuel motor, which is disposed behind an active part 30 having an explosive charge and a fragmentary part which is conical when blasting the explosive charge is thrown forward.
  • the ignition of the active part 30 may be effected by an impact fuse or a proximity fuse located in the missile head.
  • a sensor 32 is arranged, which is an imaging infrared sensor.
  • the sensor 32 comprises an optical system 34 and a matrix detector 36.
  • a filter 38 is used to shadow the detector 36.
  • the detector 36 is arranged on a cooling unit, not shown, and connected to the control unit 26 by signal technology.
  • a cover 40 is arranged, which comprises two mutually movable shell elements, which are spring-driven against each other. They completely cover the detection area of the sensor 32 in the closed state and shield the sensor 32 from incident laser radiation so far that the sensor 32 remains functional for a period of at least 10 seconds behind the cover 40 when the condition is directly illuminated by the laser beam 8.
  • FIG. 2 shows the two elements of the cover 40 in the open position, which is shown dotted. The detection area or the field of view of the sensor 32 passes through the two open elements, so that an image of the ahead of the missile 12 scenery can be made.
  • the filter 38 is an intensity-dependent filter which shadows automatically as a function of the intensity of the incident laser radiation. If the intensity exceeds a limit value, the filter 38 automatically becomes impermeable and thereby protects the underlying detector 36 very quickly. In addition, the filter 38 sends a signal to the control unit 26, which then immediately closes the cover 40 and thus also causes additional mechanical protection of the sensor 32.
  • the guided missile comprises one or more of the sensors 42, 44, 46, 48 described below, which in FIG. 2 and FIG. 4 are shown schematically.
  • the guided missile 12 includes four sensors 42 which are arranged over the circumference of the missile 12 at a distance of 90 ° to each other. In FIG. 2 For the sake of clarity, only two of these sensors 42 are shown.
  • the sensors 42 serve to find the laser beam 8 and to stein it into the laser beam 8.
  • the sensors 42 form a sideways sensor with a field of view to the side of the missile 12, which is indicated by dotted lines. Within the field of view, there are no elements of the missile 12, so that the sensors 42 sense only in the air surrounding the laser beam 8 scattered laser radiation.
  • the intensity of the laser radiation thus sensed is a measure of the distance of the guided missile 12 from the laser beam 8.
  • the tangential arrangement of the four sensors 42 on the circumference of the missile 12 can also determine the direction in which the laser beam is relative to the missile 12.
  • the control unit 26 causes the flight of the guided missile 12 to the laser beam 8 out.
  • the direction results from a combination of the direction of those sensors 42 which receive the strongest scattered light signal of the laser radiation.
  • the sensors 44 form - like the sensors 42, 46 and 48 - a group of a plurality of sensors, in the embodiment shown four sensors, which are arranged uniformly tangentially spaced from each other in the periphery of the missile 12 on the outer shell of the missile.
  • a sensor group has four sensors 42, 44, 46, 48, which are tangentially 90 ° apart. All sensors 42, 44, 46, 48 are arranged in one or more recesses 50 in the outer shell of the missile 12 and are thus shaded forward.
  • a laser beam 8 impinging on the guided missile 12 from the front can thus not reach the sensors 42-48. Even with a tilt of up to 30 ° of the missile axis to the axis of the laser beam 8, the sensors 42 - 48 remain shaded by the laser beam 8.
  • the sensors 44 have a field of view 52, which in FIG. 2 by dashed lines and in FIG. 4 is realized by a respective dashed line indicated area.
  • a field of view of a sensor 44 is directed to a leading edge of a fin 54 of the missile, with each of the sensors 44 directed to another fin 54.
  • the flight of the guided missile 12 is controlled so that it dives as deeply as possible in the laser beam 8, so in particular lies centrally in the laser beam 8.
  • the guided missile 12 in this case flies parallel to the laser beam 8 in this direction to the laser source 10. As a result, the vehicle 2 is shadowed by the missile 12 from the laser beam 8 and thus protected.
  • each of the sensors 46 has a field of view 56 which in FIG. 4 is indicated by a dashed rectangular area.
  • the field of view 56 is directed to a slope 58 in the outer wall of the missile 12, which is divided into two areas 60, 62.
  • the inner region 60 is provided with a different surface than the outer region 62.
  • the surfaces differ for example by a roughness and / or a coating, such as a color and / or a scattering layer.
  • the fields of view 56 of the sensors 46 on the outer area 62 are directed, the fields of view 64 of the sensors 48 are directed to the inner portion 60 of the slope 58.
  • the regions 60, 62 are coated with different colors, and the sensors 46, 48 are sensitive only in a narrow spectral window of the color of their field of view 56, 64.
  • the laser beam 8 will illuminate at least the outer region 62 directly. This is detected by the sensors 46. From the tangential arrangement to each other, the direction can be determined in which the missile axis is tilted to the laser beam 8 and its axis. In addition, the tilt increases with increasing intensity of the sensor signal of the respective sensors 46.
  • the sensors 48 output a corresponding signal.
  • the tilt increases with increasing sensor signal. From the signals of the sensors 46, 48, therefore, the direction of the tilt and the magnitude of the tilting of the missile axis for the alignment of the laser beam 8 can be determined.
  • the steering or the guide vanes 22 are controlled using the sensor signals and the tilting is thereby reduced, in particular until a parallel flight of the steering missile 12 to the laser beam 8 is achieved.
  • FIG. 3 and FIG. 5 Several methods for protecting the vehicle 2 are described below FIG. 3 and FIG. 5 explained.
  • a target transfer or instruction of the vehicle 2 to the guided missile 12 takes place.
  • the control unit 18 transfers both the coordinates of the target and the position and orientation of the laser beam 8 to the control unit 26 of the guided missile 12 by means of wireless data transmission.
  • the coordinates here are absolute, geostationary coordinates, wherein the coordinate errors in the indication of the position of the laser source 10 can be quite large, as these could not be detected by the vehicle 2 itself.
  • the guided missile 12 flies toward the laser beam 8 whose position and orientation is roughly known to it.
  • the incident radiation in the wavelength of the laser beam 8 is monitored by the sensor 42.
  • the guided missile 12 is guided into the laser beam 8, wherein the control is now carried out on the basis of the signals of directed exclusively in the rear half-space backward sensor 44 - 48.
  • the guided missile 12 is held in the laser beam 8 and flies parallel to it to the laser source 10 out. If the laser beam 8 remains still and does not disappear, the guided missile 12 can fly exclusively to the laser source 10 under the guidance of the laser beam 8.
  • the guided missile 12 flies toward the laser source 10 using the laser beam 8 as a guide beam.
  • the laser system 6 can initiate action.
  • a countermeasure may include that the laser beam 8 is pivoted and the steering missile 12 following the laser beam 8 is deflected so far that it no longer shades the vehicle 2.
  • the guided missile 12 is controlled so that it remains within its flight to the laser source 10 within a Abschattungskorridors 66 which in FIG. 3 indicated by two solid lines.
  • the shading corridor 66 extends from the laser source 10 to the vehicle 2 and is configured in its geometry to include all imaginary lines from the laser source to all points of the vehicle 2. However, lines from the laser source 10 to spatial points which are more than a predetermined distance laterally from the vehicle 2 are not within the shading corridor, as in FIG FIG. 3 is indicated. This distance serves to compensate for computing inaccuracies and is expediently less than 50 m, in particular less than 10 m.
  • the shading corridor 66 is calculated by the control unit 18 from the positions of the laser source 10 and the vehicle 2 as well as the dimensions, the orientation and / or the direction of movement and speed of the vehicle 2 in space.
  • the position of the shading corridor 66 in particular its geometry and position in space, can be determined in absolute, earth-fixed coordinates or in relative coordinates which refer to a reference space moved with the vehicle 2.
  • a plurality of laser-sensitive points 68, 70 deposited, which in FIG. 3 are indicated.
  • These laser-sensitive areas 68, 70 include those areas on the vehicle whose irradiation by a high-energy laser within a predetermined period of, for example, less than 10 s lead to damage to the vehicle 2, which affects its overall functioning.
  • Shading passages 72, 74, which are calculated in FIG. 2, are also calculated for these laser-sensitive points 68, 70 FIG. 3 dotted, or dashed, are indicated.
  • the shading corridors 72, 74 exclusively comprise all the imaginary lines from the laser source 10 to all possible points of the laser-sensitive spots 68, 70.
  • the flight of the missile 12 is controlled so that the missile 12 always within the Abschattungskorridors 66, or 72, 74 remains, depending on how the flight control was deposited in the control unit 18 and passed to the control unit 26 of the guided missile 12. Leaves the laser beam 8 the Abschattungskorridor 66, so he no longer applies to the vehicle 2, the missile 12 still remains within the Abschattungskorridors 66 to a renewed pivoting of the laser beam 8 on the vehicle 2, that can shadow vehicle 2 as quickly as possible , In particular, the guided missile 12 remains within one of the special shading corridors 72, 74 for the protection of the laser-sensitive point 68, 70.
  • the laser beam 8 leaves one of the shading corridors 72, 74, it remains in the shading corridor 66, thus striking the vehicle 2 at a non-laser-sensitive location , so the guided missile 12 still remains within its Abschattungskorridors 72, or 74 in order to protect the respective laser-sensitive point 68, or 70 swiftly when the laser beam 8 pivots renewed on this.
  • the control of the missile 12 within the Abschattungskorridore 66, 72, 74 can be done by a control system that includes both the control unit 18 in the vehicle 2 and the control unit 26 in the guided missile 12.
  • the control unit 26 assumes the fine control and the control unit 18 the coarse control.
  • the control of the vehicle 2 engages in the control by the missile 12 itself and serves as a higher-level control. For this purpose, the current position of the missile 12 is monitored by the vehicle 2. If the guided missile 12 is flying in the desired shadowing corridor 66, 72, 74 within the laser beam, the control unit 18 will not intervene and the flight control will become only taken from the missile 12 itself.
  • the control unit 18 can intervene in the flight control in order to accelerate a flight correction.
  • the guided missile 12 is instructed on the new to the laser-sensitive point associated Abschattungskorridor 74 and flown there.
  • the fine control for immersion in the laser beam 8 and for holding the guided missile 12 can in turn be performed by the missile 12, or its control unit 26.
  • the guided missile 12 will follow this pivoting in order to stay within the laser beam 8 and shade the vehicle. If this is not desired, because the guided missile 12, for example, in a Abschattungskorridor 72, 74 should remain so engages the control unit 18 corrective and keeps the missile 12 in the desired Abschattungskorridor 72, 74. The same applies to the situation in which the laser beam 8 is pivoted out of the large shading corridor 66. Flying over of the guided missile 12 is prevented by the control unit 18 of the vehicle 2 and the missile 12 is held within the desired Abschattungskorridors 66, 72, 74.
  • the guided missile 12 determines a shading corridor 66, 72, 74 itself and also controls the rough navigation itself, so that intervention by the vehicle 2 is not necessary or can be limited to exceptions.
  • the guided missile 2 determines its own position during its flight to the laser source 10 out, for example, using the interior navigation.
  • it determines the position of the vehicle 2, for example by estimating the position of the vehicle 2 from an initial position, for example a position at a start of the guided missile 12, and an update of the flight based on the speed and direction of the vehicle 2. It is also possible that he receives the position of the vehicle 2 by a data link from this.
  • the guided missile 12 calculates the corresponding shading corridor 66, 72, 74 and keeps its flight therein. If the vehicle 2 detects that the guided missile 12 erroneously controls, for example, because it leaves the rejected shading corridor 66, 72, 74, then the control unit 18 can intervene to correct and steer the guided missile 12 back into the desired trajectory.
  • FIG. 5 shows a further possibility of controlling the guided missile 12. Shown is the laser beam 8, which runs within the Abschattungskorridors 74 and thus illuminates the laser-sensitive point 70 of the vehicle 2. At a first time, the guided missile 12 flies within the shadowing corridor 74 towards the laser source 10. This is based on the uppermost position of the missile 12 in FIG. 5 indicated.
  • the laser beam 8 is swiveled out of the shading corridor 66, as shown in FIG FIG. 5 indicated by the dotted line.
  • the guided missile 12 would be led out of a shading position in which he could shade the vehicle 2.
  • the guided missile 12 follows the slowly pivoted laser beam 8 and remains within the laser beam 8, as in FIG. 5 indicated by the middle position of the missile 12 in the dotted line.
  • a flight 76 is calculated by the vehicle 2 and / or the guided missile 12, within which the guided missile 12 has to remain.
  • This flying space 76 is tapered towards both the vehicle 2 and the laser source 10, so that the largest cross-sectional dimension is approximately in the middle between the vehicle 2 and the laser source 10, as in FIG FIG. 5 is shown. With this flight space determination inaccuracies is carried out, which are connected to the position determination of the guided missile 12.
  • the flying space 76 allows for a tolerance around the shadowing corridor 74, within which the coarse flight control from the side of the vehicle 2 is not in the fine flight control of the guided missile 12 engages. Since the position of the missile in the vicinity of the vehicle 2 is known in more detail, it is tapered toward the vehicle 2. Since the guided missile 12 has to hit the laser source 10, the flying space 76 tapers off towards the laser source 10. At the in FIG. 5 In the exemplary embodiment shown, the guided missile 12 flies in its position shown in the middle at the edge of the flight space 76 within the laser beam 8. The flight control from the control unit 18 therefore does not intervene in the flight and the flight is carried out exclusively by the guided missile itself.
  • the guided missile 12 does not follow the laser beam 8 and remains within the flying space 76. Since the guided missile 12 can not maintain its fine control within the laser beam 8 in this situation, the guided missile 12 becomes based on a coarse control controlled by the guided missile 12 itself or the control unit 18 of the vehicle 2 can perform.
  • the guided missile 12 is again guided in the calculated Abschattungskorridor 74, as based on the lower position of the missile 12 in FIG. 5 is shown. This is to the determination and thus can come to steering inaccuracies, is not critical, since the missile 12 remains in any case within the flight envelope 76.
  • the flight control of the vehicle 2 intervenes and corrects the flight of the missile 12. This is analogous to the correction using the shadowing corridor 66, 72, 74 as well FIG. 3 described.
  • the laser beam 8 is turned off.
  • the guided missile 12 can now be roughly controlled in the direction of the laser source, missing this target is not unlikely without the laser beam 8.
  • the forward sensor in the form of the "forward" sensor 32 with the imaging detector or the matrix detector 36. Since this is not laser-resistant, it must during the flight in the laser beam 8 are adequately shaded. This is done in a first embodiment with reference to the cover 40 and in a second embodiment that in FIG. 6 is shown by means of a blow-off hood 78.
  • the hood 78 consists of several parts, which have several predetermined breaking points in the FIG.
  • hood 78 Within the hood 78 is a small explosive charge, which is ignited by the control unit 26.
  • the hood 78 breaks apart and exposes behind in the dome 80, which is permeable to infrared radiation, so that the sensor 32 has a clear view to the front.
  • the cover 40 can be opened, or the hood 78 are blasted off.
  • the control unit 26 in conjunction with the sensor system of the missile 12 is prepared to detect a danger of the laser beam 8. This happens, for example, based on a measured intensity of the laser radiation. If the danger is below a limit value, the cover 40 can be opened or the hood 78 can be blown off and the forward sensor 32 can be activated.
  • the far-swung laser beam 8 and its end is recorded pictorially on the laser source 10 and the position of the laser source 10 in the image of the forward sensor 32 is determined. From this, the approach direction to the laser source 10 can be determined, so that a point accurate approach to the laser source 10 without the line through the laser beam 8, or a flight can take place within the laser beam 8.
  • An image acquisition time of 50 ms is sufficient to find the laser source, identify it and determine its direction.
  • the sensor 32 searches for heat sources in its field of view. Detected heat sources are compared with data stored in a database, in particular images of known heat sources. Here, the time that has elapsed since the switching off of the laser beam 8, taken into account. If the image of a heat source detected by the sensor 32 can be associated with a stored image of a laser source 10, the location of the heat source is recorded as a new target, and the missile 12 controls the heat source to destroy it.
  • the laser source 10 turns off, so that the laser beam 8 disappears. A line of the flight of the missile 12 along the laser beam 8 is no longer possible. However, this switching off is detected by the sensors 42-48.
  • the cover 40 opens and allows the sensor 32 to look forward.
  • the sensor 32 searches for heat sources in its field of view. Found heat sources are compared with data stored in a database, in particular images of known heat sources. In this case, the duration of time that has elapsed since the laser beam 8 was turned off is taken into account. If the image of a heat source can be assigned to a stored image of a laser source 10, the position of the heat source is recorded as a new target and guided missile 12 controls the heat source to destroy it.
  • the cover 40 opens only for a short period of time and then closes again to protect the sensor 32.
  • An opening period of 50 ms is sufficient to find the laser source 10, identify it and determine its direction.
  • the guided missile 12 can now fly into the laser source 10 on the basis of this data.
  • the cover 40 opens after a preset time after switching off the laser source 10. This preset time may be different from guided missile 12 to missile 12 so that the laser system 6 the Opening time after switching off the laser source 10 does not know. After expiration of the waiting time, the cover 40 opens for the preset time, for example 50 ms and closes again.
  • the sensor 32 is protected against re-ignition of the laser beam 8.
  • Activation of the sensor 32 is also possible if the laser beam 8 is sufficiently far away from the missile 12, for example because the laser beam 8 has been widely pivoted. As a result, the laser source 10 can be detected directly and thus controlled more easily.
  • the distance of the missile 12 to the laser beam 8 is estimated by the sensors 42, and the control unit 26 opens the cover 40 in response to the sensor signal.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Claims (14)

  1. Procédé de protection d'un véhicule (2) contre une attaque par un faisceau laser (8) provenant d'une source laser (10), dans lequel la position de la source laser (10) est déterminée et un missile guidé (12) est lancé et dirigé vers la source laser (10), caractérisé en ce que le missile guidé (12) détecte le faisceau laser (8) et commande sa trajectoire de vol en fonction de sa position par rapport au faisceau laser (8).
  2. Procédé selon la revendication 1,
    caractérisé en ce qu'une distance de la source laser au véhicule (2) est déterminée par utilisation de l'altitude de vol et de la direction du faisceau laser (8).
  3. Procédé selon la revendication 1 ou 2,
    caractérisé en ce que le missile guidé (12) vole parallèlement au faisceau laser (8) à l'intérieur du faisceau laser (8) et de ce fait, projette une ombre sur le véhicule (2) vis-à-vis du faisceau laser (8).
  4. Procédé selon l'une des revendications précédentes, caractérisé en ce que la position d'un couloir d'ombre (66, 72, 74) entre la source laser (10) et le véhicule (2) est déterminée et en ce que le missile guidé (12) est commandé en fonction de sa position par rapport au couloir d'ombre (66, 72, 74),
    dans lequel le couloir d'ombre (72, 74) est limité en particulier à un domaine compris entre un point sensible au laser (68, 70) du véhicule (2) et la source laser (10).
  5. Procédé selon l'une des revendications précédentes, caractérisé en ce que la distance entre la source laser (10) et le véhicule (2) est déterminée, en ce qu'un domaine de vol (76) est déterminé à partir de celle-ci et en ce que le missile guidé (12) est commandé de manière à rester à l'intérieur de le domaine de vol (76).
  6. Procédé selon l'une des revendications précédentes, caractérisé en ce qu'un domaine de vol (76) du missile guidé (12) est déterminé entre la source laser (10) et le véhicule (2), lequel domaine de vol se rétrécit à la fois vers la source laser (10) et vers le véhicule (2).
  7. Procédé selon l'une des revendications précédentes, caractérisé en ce que le missile guidé (12) reste dans un domaine de vol prédéterminé (76) lorsque le faisceau laser (8) disparaît d'un corridor d'ombre (66).
  8. Procédé selon l'une des revendications précédentes, caractérisé en ce que le véhicule (2) surveille la position du missile guidé (12),
    dans lequel le véhicule (2) intervient notamment dans la commande de vol du missile guidé (12) lorsque le missile guidé (12) quitte le domaine de vol (76).
  9. Procédé selon l'une des revendications précédentes, caractérisé en ce que le missile guidé (12) commande sa trajectoire de vol par utilisation de la position du véhicule (2) et de la position de la source laser (10),
    dans lequel le missile guidé (12) détermine la position du véhicule (2) à partir d'une position inertielle et de la direction et de la vitesse de vol du véhicule (2), en particulier pendant son vol.
  10. Procédé selon l'une des revendications précédentes, caractérisé en ce que le missile guidé (12) vole vers la source laser (10) par navigation inertielle lorsque le faisceau laser (8) a disparu.
  11. Procédé selon l'une des revendications précédentes, caractérisé en ce que le missile guidé (12) détecte une disparition du faisceau laser (8) et active un capteur (32, 42, 44, 46, 48) préalablement occulté vis-à-vis du faisceau laser (8).
  12. Procédé selon l'une des revendications précédentes, caractérisé en ce que le missile guidé (12) identifie un niveau de risque du faisceau laser (8) et active un capteur orienté vers l'avant lorsque le niveau de risque est inférieur à une valeur limite et utilise ses données pour un vol effectué vers la source laser (10).
  13. Procédé selon l'une des revendications précédentes, caractérisé en ce que le missile guidé (12) détecte une source de chaleur de la source laser (10) lorsque le faisceau laser (8) est désactivé, compare le motif de la source de chaleur à des données provenant d'une base de données et vole vers la source de chaleur si la comparaison est positive.
  14. Système constitué d'un véhicule (2) et d'un missile guidé (12) comportant un système de commande conçu pour déterminer la position de la source laser (10), lancer le missile guidé (12) et le diriger vers la source laser (10),
    caractérisé en ce que le missile guidé (12) est conçu pour détecter le faisceau laser (8) et pour commander sa trajectoire de vol en fonction de sa position par rapport au faisceau laser (8).
EP16001539.2A 2015-07-17 2016-07-12 Procede de protection d'un vehicule contre une attaque par un rayon laser Active EP3118566B1 (fr)

Applications Claiming Priority (1)

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DE102015009365.7A DE102015009365B4 (de) 2015-07-17 2015-07-17 Verfahren zum Schützen eines Fahrzeugs vor einem Angriff durch einen Laserstrahl

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EP3118566A1 EP3118566A1 (fr) 2017-01-18
EP3118566B1 true EP3118566B1 (fr) 2018-09-19

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Family Cites Families (7)

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Publication number Priority date Publication date Assignee Title
DE19724080A1 (de) 1997-06-07 1998-12-10 Bodenseewerk Geraetetech Infrarot-Suchkopf für zielsuchende Flugkörper
SE519866C2 (sv) 2000-08-17 2003-04-15 Celsiustech Electronics Ab Förfarande för att störa och eventuellt skada en laseranordning, samt ett skyddssystem
DE10230939A1 (de) 2002-07-09 2004-02-12 Buck Neue Technologien Gmbh Verfahren und Vorrichtung zum Schutz von Gefechtsfeldfahrzeugen
US7540227B2 (en) 2003-05-06 2009-06-02 Bae Systems Technology Solutions & Services Inc. Air based vertical launch ballistic missile defense
IT1391858B1 (it) * 2008-09-09 2012-01-27 Alenia Aeronautica Spa Disposizione di collaudo per un sistema di riconoscimento di minacce laser per un velivolo
US9134174B2 (en) 2013-01-07 2015-09-15 The Boeing Company Laser detection and warning system
US9970811B2 (en) * 2013-08-30 2018-05-15 Torrey Pines Logic, Inc. Passive, wide-spectral-band laser threat sensor

Non-Patent Citations (1)

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Title
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EP3118566A1 (fr) 2017-01-18
DE102015009365B4 (de) 2023-07-27

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