EP3118565B1 - Procédé de protection d'un véhicule contre une attaque par un rayon laser - Google Patents

Procédé de protection d'un véhicule contre une attaque par un rayon laser Download PDF

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Publication number
EP3118565B1
EP3118565B1 EP16001538.4A EP16001538A EP3118565B1 EP 3118565 B1 EP3118565 B1 EP 3118565B1 EP 16001538 A EP16001538 A EP 16001538A EP 3118565 B1 EP3118565 B1 EP 3118565B1
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EP
European Patent Office
Prior art keywords
laser beam
laser
sensor
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
EP16001538.4A
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German (de)
English (en)
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EP3118565A1 (fr
Inventor
Arne Nolte
Michael Masur
Michael Gross
Nicolai Künzner
Thomas Kuhn
Norbert Stelte
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Diehl Defence GmbH and Co KG
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Diehl Defence GmbH and Co KG
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Publication of EP3118565A1 publication Critical patent/EP3118565A1/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, 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.
  • the aircraft is equipped with a laser detection and warning system that can output a warning signal.
  • a sensor detects the laser radiation of the laser beam
  • a Guided missile flies into the laser beam inside, in the laser beam incident on the laser source and thereby shading the vehicle in front of the laser beam.
  • 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 quick 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 can be at an approach to the Laser source mechanically destroy them by means of an active part, for example, by a cone-shaped forward splintering charge.
  • the guided missile uses the laser beam as a guide beam for driving the laser source.
  • the steering or navigation of the missile is done so far using sensor data obtained from a scanning of the laser beam.
  • a parameter of the laser beam for example a scattered light intensity, can be used for navigation, for example by keeping the measured scattered light intensity constant during the approach or by processing it according to a predetermined scheme.
  • 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 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 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.
  • 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 based on residual heat radiation when the laser source is switched off.
  • an image sensor is advantageously present, for example with a matrix detector.
  • the vehicle is preferably an aircraft, and may be fixed-wing aircraft or a rotorcraft, such as a helicopter.
  • the invention is also advantageously applicable for protecting a land vehicle or a watercraft.
  • the vehicle may be a manned or unmanned vehicle.
  • 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 from the vehicle. If a laser beam is not recognized as such or classified as non-threatening, the launching of the missile expediently fails.
  • the guided missile is expediently an unmanned guided missile, in particular with a rocket motor. Also possible is a missile without its own engine, for example in the form of a steering column.
  • the missile expediently comprises a control unit which directs the missile towards the laser source.
  • the guided missile flies towards the laser source and utilizes the laser beam expediently as a guide beam for driving the laser source.
  • the laser beam expediently as a guide beam for driving the laser source.
  • a sensor of the vehicle or a sensor of the missile picks up an image of the laser beam.
  • the location of the laser source of the laser beam can be determined therefrom. For example, a straight line of the laser beam in the environment is determined from the image and a defined end of the laser beam or the line is determined. This can be done by a control unit of the vehicle or a control unit of the guided missile. This end can be defined as the location of the laser source, and the missile can drive that position. From other parameters, for example, that the end is a lower end or the end is an abrupt end, whereas the laser beam in the other direction continuously becomes weaker, it can be assumed that the laser source is arranged at this beam end. Accordingly, this location can be used for the steering of the missile, which flies to the end of the laser beam or the location. The location of the laser source can be determined from the vehicle and transferred to the guided missile. The location may alternatively or additionally be determined by the guided missile.
  • the intensity of radiation emitted by the laser source in direct line to the missile is recorded as a measured variable.
  • a sensor is aimed at the laser source and picks up the laser radiation thrown directly from the laser source onto the sensor.
  • 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.
  • a sideways sensor is understood below exclusively directed in a lateral direction relative to the longitudinal axis of the missile sensor system, which is not aligned in the direction of flight, and a reverse sensor is directed exactly opposite to the direction of flight of the missile, usually also in the lateral direction, but also not Forward.
  • 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.
  • the guided missile expediently comprises a shading element, for example a fuselage projection, which shadows the sensor against laser radiation impinging from the front.
  • This shading expediently also exists in the case of an actively detecting sensor, so that it is therefore not, for example, flaps that are opened when the sensor is activated so that the sensor receives a free field of view.
  • the shading element comprises a recess in the outer housing of the missile, and the sensor is arranged in this recess.
  • the sensor can be oriented to the rear or to the side and remains in the shadow of the depression with a laser beam directed from the front onto the guided missile.
  • the shading element is expediently designed so that the entire optical input of the sensor is shaded towards the front.
  • the missile expediently flies within the laser beam parallel to the laser beam to the laser source. In this case, it generates a shading effect which at least partially protects the vehicle from the laser radiation.
  • flying in the laser beam it can be understood here that the laser beam hits the guided missile while the guided missile is flying parallel to the laser beam.
  • the sensor makes sense if the sensor not only detects a strength of the laser radiation, but also the relative position of the missile relative to the central axis of the laser beam.
  • This can be achieved in a simple and advantageous manner with several distributed over the circumference of an outer housing of the missile arranged sensors that detect laser beam during the flight.
  • the sensors can be arranged in a simple way so that a symmetrically centered in the laser beam flight, ie in the middle of the laser beam, leads to the same sensor signals of the sensors, the sensor signals thus reflect the symmetry of the position.
  • the flight of the missile is advantageously controlled so that the detected laser radiation is the same for all sensors.
  • the laser radiation intensities detected by the sensors are not equal to each other, but are in a predetermined relationship to each other.
  • the sensor system has at least three sensors distributed over the circumference of the outer housing, which are aligned, for example, obliquely backwards. By arranging four sensors each distributed 90 ° around the circumference, a right and left flight, or a flight up and down, even easier to control.
  • a detection space angle range of the sensor is free of objects. It is therefore no element of the missile in this area, ie in the field of view of the sensor. A falsification of the measurement result caused by a reflection can thereby be avoided.
  • the senor is directed to an outer scattering surface, which is illuminated, for example, in a beam radiating from the front of the missile from the latter. The sensor can thereby detect the presence of the laser beam at this scattered surface.
  • the guided missile comprises an outer housing with an outer scattering surface, which has at least two, in particular four tangentially offset regions. From the illumination of these areas, the relative position of the guided missile to the laser beam axis can be detected in a simple manner and very quickly.
  • a control of the missile is dependent on which of the areas is hit by the laser beam.
  • the strength with which several areas of the scattering surface are hit by the laser beam can be used to control the missile, in particular for a quantity of steering, so a strength of a rash of a steering rudder of the missile.
  • the Scattering intensity of the areas of the scattered surface can be used as the input variable of a flight control.
  • the regulation objective may be a predetermined, in particular uniform, distribution of the areas of the scattering surface. As a result, the missile can be kept in the middle of the laser beam.
  • the areas of the scattering surface can be distinguished into two different types of areas, namely those areas which are illuminated with a laser beam projecting exactly in front of the guided missile and those areas which are not illuminated in this parallel alignment of the laser beam with the missile axis.
  • an angular position of the guided missile axis relative to the laser axis can be determined by means of the second regions.
  • the second regions are expediently shaded or arranged such that at least one of the regions is illuminated by the laser beam when the missile axis is angled relative to the laser axis. From the strength of the illumination of the corresponding area, the angular size can additionally be suitably determined. For example, if the guided missile passes through the laser beam at an angle, the angular position of the missile relative to the laser beam can be measured.
  • a backscatter intensity of the areas of an orientation of the guided missile to the laser beam namely a displacement and / or angular position of the missile axis to the laser beam axis.
  • a quantitative determination of the angle of the missile axis to the laser beam can be achieved in a simple manner, when the missile in an outer housing has an outer scattering surface which comprises at least two radially offset regions.
  • the larger the angle the deeper the incident laser radiation extends radially into the scattering surface, so that the impact of the laser beam in a radially inner region indicates a larger angle than the impact of the laser beam exclusively on an outer region.
  • the control of the missile is dependent on which of the areas is hit by the laser beam.
  • a particularly rapid control of the missile based on the areas can be achieved if at least one sensor for each of the areas which is oriented to this area and whose view is advantageously blocked to all other areas.
  • particularly simple and fast sensors can be used so that an easily evaluable measurement result is available very quickly.
  • the protection of the vehicle by the guided missile can be achieved in two ways: the shading of the vehicle by the missile flying in the laser beam and the destruction of the laser source by the approaching missile.
  • the shading protection can be further increased if, during the flight to the laser source, an extension element, the outer housing is projecting outstanding, so that a shading surface of the missile is increased.
  • the shading surface refers to the silhouette of the missile in a plan view from the front.
  • the extension element is provided forward with a reflective layer, in particular with a retroreflective layer, so that the extension element reflects the incident laser radiation counter to the laser beam direction.
  • the extension element can be a movable element that is additional to the wings, a collar or the like.
  • a shading surface of the missile can be significantly increased if the missile emits cloud-shaped material during the flight to the laser source. Due to the fact that the missile flies parallel to the laser beam, the ejected material cylinder, or cone of material, lies parallel to the laser alignment, so that the laser has to pierce it over its entire length.
  • the material may be smoke from an engine, or a rocket engine of the guided missile, to which a smoke generator is added to the propellant. Particularly advantageously, the material comes from an existing addition to an engine opening nozzle. Engine thrust and smoke emissions can be controlled independently of each other.
  • the material is removed from the head of the missile by the incident laser radiation from an ablation layer.
  • the smoke is then automatically limited to such Zeitschreibr where the laser beam hits the missile.
  • the material is used very sparingly. To disturb, or destruction of the laser source, it is also advantageous if the material contains baubles for the reflection of laser radiation.
  • the material is ejected only in the direction of the laser beam or at least predominantly in this direction.
  • the material is ejected from a plurality of nozzles, and a control unit controls the ejection of material from the individual nozzles depending on the position of the missile to the laser beam. In this way, the material can be specifically directed in the direction of the laser beam and this targeted tarnished.
  • Laser optics and laser beam generators are usually very sensitive to collapse of the laser radiation. A reflection of the laser beam can therefore lead to the destruction of the laser source, so that the vehicle can also be protected thereby.
  • One possibility for reflection of the laser beam is that laser radiation is reflected by an element of the guided missile, in particular by a retro-reflector.
  • the reflector may be located at the tip of the missile and / or under a dome of the missile. If the reflector is behind a dome, evaporating gases which are produced when the reflector is destroyed should be led out of an interior space behind the dome through openings, ie into a surrounding area of the guided missile.
  • the missile thus expediently comprises a dome with a space arranged behind it, which is connected via openings with the surroundings of the missile for pressure equalization. In this space, a reflection element and / or an ablation layer can be arranged.
  • the invention is also directed to a missile having an outer housing, a tip, a steering system and an environmental sensor.
  • the sensor according to the invention for detecting laser radiation of a laser beam is executed, and the missile is further equipped according to the invention with a control unit which is designed using the data of the sensor system To steer steering system so that the tip of the guided missile in the laser beam is left on the laser source.
  • the guided missile comprises an active part with a detonation charge.
  • the detonation charge may contain splinter material, the Detonation charge and splinter material are expediently arranged to each other so that the splinter material is thrown in a detonation of the detonation charge in a cone forward. Ignition of the detonation charge may be by a percussion fuse or proximity detonator located in the missile head.
  • 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 placed in the embodiment shown on the ground and immovable. However, it is also possible that the laser system 6 is movable and is mounted, for example, in an aircraft. All details described below and related to the laser source 10 are then to be adapted accordingly to the mobility or height above the ground.
  • the laser system 6 is a high-energy laser system which emits the laser beam 8 predominantly in the infrared spectral range, for example, at 3.8 microns, the laser beam 8 over a distance of several kilometers transported enough energy to destroy sensitive parts of the aircraft and thereby its flying capacity acute to endanger.
  • the laser system 6 is used to combat aircraft and has a control unit which pivots the laser beam 8 on the vehicle 2 and the laser beam 8 automatically tracks the movement of the aircraft 2.
  • 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.
  • 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.
  • this mark can be disturbed, so that the attacking missile can not find the vehicle 2.
  • the following description refers to a stationary one High energy laser system 6, without this being a restriction on this system would be connected.
  • 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. In this way, an image of the laser beam 8 can be recorded in the environment, and from this further information about the laser beam 8 can be determined, such as geometry, position and intensity of the laser beam.
  • the control unit 18 of the sensor system 14 From the geometry recognizes the control unit 18 of the sensor system 14, in particular by means of image processing methods, the laser beam 8 as such.
  • 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. 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.
  • 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 an altitude of the aircraft and conveniently a topography of the overflown landscape 4, the distance between the aircraft and the laser source 10 can also 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 guided missile 12 is powered by a rocket motor 28, in particular a solid fuel motor, which is arranged behind an active part 30 having an explosive charge and a fragment part, which is at a blasting of the explosive charge is thrown cone-shaped forward.
  • the ignition of the active part 30 is effected by a proximity fuse, which is arranged 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 in the detection region, which comprises two mutually movable shell elements, which are moved spring-driven against each other. They completely cover the detection area of the sensor 32 in the closed state and shield the sensor 32 from incident laser radiation so far that the sensor 32 remains functional for a period of at least 10 seconds behind the cover 40 when the condition is directly illuminated by the laser beam 8.
  • FIG. 2 shows the two elements of the cover 40 in the open position, which is shown dotted. The detection area or the field of view of the sensor 32 passes through the two open elements, so that an image of the ahead of the missile 12 scenery can be made.
  • the filter 38 is an intensity-dependent filter which 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 12, each of the sensors 44 being 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.
  • the protection of the shadowing of the vehicle 2 from the laser beam 8 by the guided missile 12 is enhanced by the ejection of material 66 from four nozzles 68. These are also distributed tangentially over the circumference of the outer shell of the guided missile 12 and arranged at the rear end of the missile 12, as in FIG. 2 is shown.
  • material 66 smoke is expelled with baubles that cause a retro-reflective effect.
  • Laser radiation incident on particles is mirrored back to the laser source 10 in a direction reversed by 180 °, so that a not inconsiderable input of energy into the laser source 10 takes place. This can be disturbed or even destroyed.
  • the nozzles 68 are controlled by the control unit 26 according to the position of the missile 12 to the laser beam 8.
  • the guided missile 12 can carry ablation material 72 on its front side. If the laser beam 8 strikes the ablation material 72, it burns or dissolves in smoke. The smoke has the same effect as the material 66 and may also be provided with tinsel material incorporated into the ablation material 72.
  • the front portion of the missile 12 may be provided with a reflective layer applied to, for example, the ablation layer 72, a dome 74, or other forward-facing location of the missile 12.
  • This expediently retroreflective layer throws the laser light in the opposite direction and thus back to the laser source 10 to disrupt or destroy it.
  • the ablation layer 72 is expediently provided as an alternative to the sensor 32 so as not to obstruct the field of view to the front.
  • Ablation layer 72 may alternatively include ablation material and / or a reflective layer below dome 74 of missile 12, such as on the outside of cover 40. In this case, ablation material 72 on cover 40 and sensor 32 may be combined. However, vaporizing the ablation material 72 below the dome 74 would result in increased internal pressure within the missile 12. To dissipate the overpressure, the missile 12 therefore contains openings 76 from which the resulting smoke is removed.
  • 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.
  • This switching off is through the sensors 42 - 48 detected.
  • the cover 40 opens and allows the sensor 32 to look forward.
  • 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 assigned to a stored image of a laser source 10, the position of the heat source is recorded as a new target, and the guided missile 12 controls the heat source to destroy it.
  • 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)
  • Optical Radar Systems And Details Thereof (AREA)

Claims (16)

  1. Procédé de protection d'un véhicule (2) contre une attaque par un faisceau laser (8) provenant d'une source laser (10), dans lequel un capteur (16, 42, 44, 46, 48) détecte le rayonnement laser du faisceau laser (8), un missile guidé (12) vole dans le faisceau laser (8), se rapproche de la source laser (10) dans le faisceau laser (8) et forme ainsi une ombre sur le véhicule (2) vis-à-vis du faisceau laser (8).
  2. Procédé selon la revendication 1, caractérisé en ce qu'un capteur (16, 42, 44, 46, 48) se trouvant dans l'ombre vis-à-vis du faisceau laser (8) détecte le rayonnement laser diffusé dans l'air ambiant.
  3. Procédé selon la revendication 1 ou 2, caractérisé en ce qu'une pluralité de capteurs (42, 44, 46, 48) répartis sur la circonférence d'une enveloppe extérieure du missile guidé (12) détectent le rayonnement laser et en ce que le vol du missile guidé (12) est commandé de manière à ce que le rayonnement laser détecté soit identique pour tous les capteurs (42, 44, 46, 48).
  4. Procédé selon l'une des revendications précédentes, caractérisé en ce que le missile guidé (12) comporte une enveloppe extérieure dotée d'une surface extérieure diffusante (58) comprenant au moins deux régions (52, 60, 62) décalées tangentiellement l'une par rapport à l'autre, et en ce que le vol du missile guidé (12) est commandé en fonction de la région (52, 60, 62) qui est atteinte par le faisceau laser (8) .
  5. Procédé selon l'une des revendications précédentes, caractérisé en ce que le missile guidé (12) comporte une enveloppe extérieure dotée d'une surface extérieure diffusante (58) comprenant au moins deux régions décalées radialement (52, 60, 62) l'une par rapport à l'autre, et en ce que la commande du missile guidé (12) dépend de la région (52, 60, 62) qui est atteinte par le faisceau laser (8).
  6. Procédé selon la revendication 4 ou 5, caractérisé en ce qu'une orientation du missile guidé (12) par rapport au faisceau laser (8) est déterminée à partir d'une intensité de rétrodiffusion des régions (52, 60, 62).
  7. Procédé selon l'une des revendications 4 à 6, caractérisé en ce qu'il est prévu pour chacune des régions (52, 60, 62) au moins un capteur (44, 46, 48) qui est orienté vers ladite région (52, 60, 62) et dont la vue vers l'autre région (60, 62, 52) est masquée.
  8. Procédé selon l'une des revendications précédentes, caractérisé en ce que le missile guidé (12) éjecte un matériau (66) sous forme de nuage vers la source laser (10) pendant le vol, de manière à agrandir ainsi une surface de formation d'ombre.
  9. Procédé selon la revendication 8, caractérisé en ce que le matériau (66) est éjecté à partir d'une pluralité de buses (68), et en ce qu'une unité de commande (26) commande l'éjection du matériau à partir des buses (68) individuelles en fonction de la position du missile guidé (12) par rapport au faisceau laser (8).
  10. Procédé selon l'une des revendications précédentes, caractérisé en ce que le rayonnement laser est réfléchi par un réflecteur disposé sous un dôme (74) du missile guidé (12).
  11. Missile guidé (12) comportant une enveloppe extérieure, une pointe, un système de guidage (22, 24), un capteur (42, 44, 46, 48) destiné à détecter un rayonnement laser provenant d'un faisceau laser (8) et une unité de commande (26) conçue pour commander le système de guidage (22, 24) en utilisant les données du capteur de manière à ce que la pointe soit dirigée vers la source laser (8) en restant dans le faisceau laser.
  12. Missile guidé selon la revendication 11, caractérisé par un élément de formation d'ombre qui protège le capteur (42, 44, 46, 48) effectuant activement la détection contre un rayonnement laser incident par l'avant,
    dans lequel l'élément de formation d'ombre comprend en particulier un évidement (50) dans l'enveloppe extérieure dans lequel le capteur (42, 44, 46, 48) est disposé et orienté vers l'arrière.
  13. Missile guidé selon l'une des revendications 11 ou 12, caractérisé en ce qu'un système de capteurs (14) comporte au moins trois capteurs (42, 44, 46, 48) répartis sur la périphérie de l'enveloppe extérieure du missile guidé (12) et orientés obliquement vers l'arrière.
  14. Missile guidé selon l'une des revendications 11 à 13, caractérisé en ce qu'une région d'angle solide de détection du capteur est dépourvue d'objets et/ou en ce qu'une région d'angle solide de détection d'un capteur (44, 46, 48) de l'unité à capteurs est dirigée vers une surface diffusante (54, 58).
  15. Missile guidé selon l'une des revendications 11 à 14, caractérisé par un dôme (74) présentant un espace disposé à l'arrière de celui-ci et relié au voisinage du missile guidé (12) par des ouvertures (76) destinées à effectuer une égalisation de pression.
  16. Missile guidé selon l'une des revendications 11 à 15, caractérisé par une partie active (30) comportant une charge détonante et un matériau de fragmentation disposés l'un par rapport à l'autre de telle manière que le matériau de fragmentation soit projeté vers l'avant à l'intérieur d'un cône lors de la détonation de la charge détonante.
EP16001538.4A 2015-07-17 2016-07-12 Procédé de protection d'un véhicule contre une attaque par un rayon laser Active EP3118565B1 (fr)

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DE102015009358.4A DE102015009358A1 (de) 2015-07-17 2015-07-17 Verfahren zum Schützen eines Fahrzeugs vor einem Angriff durch einen Laserstrahl

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Publication number Priority date Publication date Assignee Title
US4471683A (en) * 1982-08-26 1984-09-18 The United States Of America As Represented By The Secretary Of The Air Force Voice command weapons launching system
SE519866C2 (sv) * 2000-08-17 2003-04-15 Celsiustech Electronics Ab Förfarande för att störa och eventuellt skada en laseranordning, samt ett skyddssystem
US9134174B2 (en) * 2013-01-07 2015-09-15 The Boeing Company Laser detection and warning system
US9383170B2 (en) * 2013-06-21 2016-07-05 Rosemount Aerospace Inc Laser-aided passive seeker
US9970811B2 (en) * 2013-08-30 2018-05-15 Torrey Pines Logic, Inc. Passive, wide-spectral-band laser threat sensor

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DE102015009358A1 (de) 2017-01-19

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