EP2392890B1 - Procédé de guidage d'un corps volant vers une cible - Google Patents

Procédé de guidage d'un corps volant vers une cible Download PDF

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Publication number
EP2392890B1
EP2392890B1 EP11004429.4A EP11004429A EP2392890B1 EP 2392890 B1 EP2392890 B1 EP 2392890B1 EP 11004429 A EP11004429 A EP 11004429A EP 2392890 B1 EP2392890 B1 EP 2392890B1
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EP
European Patent Office
Prior art keywords
target
missile
data
reconnaissance
detection
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EP11004429.4A
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German (de)
English (en)
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EP2392890A1 (fr
Inventor
Michael Dr. Gross
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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 EP2392890A1 publication Critical patent/EP2392890A1/fr
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/007—Preparatory measures taken before the launching of the guided missiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/008—Combinations of different guidance systems
    • 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
    • F41G7/22—Homing guidance systems
    • F41G7/2226—Homing guidance systems comparing the observed data with stored target data, e.g. target configuration data
    • 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
    • F41G7/22—Homing guidance systems
    • F41G7/2253—Passive homing systems, i.e. comprising a receiver and do not requiring an active illumination of the target
    • 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
    • F41G7/22—Homing guidance systems
    • F41G7/2273—Homing guidance systems characterised by the type of waves
    • F41G7/2293—Homing guidance systems characterised by the type of waves using electromagnetic waves other than radio waves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/34—Direction control systems for self-propelled missiles based on predetermined target position data
    • F41G7/343—Direction control systems for self-propelled missiles based on predetermined target position data comparing observed and stored data of target position or of distinctive marks along the path towards the target

Definitions

  • the invention relates to a method for instructing a missile on a target, in which target data, by means of which the missile is controllable on the target, assembled and given to the missile for driving to the target, wherein reconnaissance data from a reconnaissance sensor by a missile homing system to detection assistance data , which contain information about the target data beyond the target data, processed and given to the missile.
  • the coordinates of the target or other target data describing the target are collected and passed to the missile which is to fight the target.
  • the missile or its seeker head detects the target during the approach to the target and is thus instructed to the target.
  • the US 6 157 875 A describes, for example, an image-guided weapon system: After determining a target area, an image of the target area is generated and a target point within the target area is selected and its GPS coordinates are determined. By means of image processing software, a reference image is generated using flight direction data, the image of the target area and the GPS coordinates of the target, which is transferred to the weapon. The images generated by the gun's viewfinder are compared to the reference image, and once there is sufficient correlation, the GPS coordinates are updated and the weapon is brought to the target.
  • From the DE 37 34 758 A1 is an antitank missile system known.
  • a helicopter used for the collection of reconnaissance data, it takes cover after target acquisition.
  • the target data obtained via the sensor system or its reconnaissance sensors as well as a Target reference image are transmitted to the missile system.
  • a rocket follows a predefined flight profile and then activates its sensors and identifies the target by comparing its sensor image with the target reference image.
  • the invention is based on the consideration that if a target is attacked using target data alone, such as target coordinates, collateral damage may under certain circumstances not be reliably prevented.
  • target data alone such as target coordinates
  • collateral damage may under certain circumstances not be reliably prevented.
  • the detection of the target can be made more reliable if, in addition to the target data, the missile is provided with additional information that supports a target acquisition.
  • acquisition support data may include how the target may be detected at the time the missile approaches the target, such as which type of sensor, in which spectrum, and / or by which optical features.
  • the acquisition support data may also include information about how well the target is recognizable. If, for example, the target is only recognizable very late because of atmospheric turbidity, a high-weighting can be given to a coordinate-based instruction without the target initially being detected as such.
  • the missile can be reliably trained on the target based on the detection assistance data.
  • the missile may be a missile with or without its own drive. It expediently comprises a seeker head with a sensor for detecting target properties, for example an optical sensor.
  • the target data is data by which the missile is controllable to the target. They can be target coordinates, coordinates of a target area and / or the target in such far determining data, so that the target can be detected as such by the target data.
  • the missile is expediently equipped with a process unit that is prepared to control the missile based on the target data into the target, in particular to detect the target based on the target data. The detection can be done optically, so that the target is recognized as such, and the use of any suitable frequency, for example in the visual, infrared or radar range, is possible.
  • the reconnaissance sensor may be any suitable sensor. It is expediently part of a reconnaissance network consisting of a large number of, in particular, different reconnaissance sensors.
  • the enlightenment data are expediently data about the destination and / or the destination area. They can be retrieved from a database by the Missile Injection System and desirably describe the target or target area at a historical time so that they can be referred to as archive information.
  • the reconnaissance data are expediently available to a large number of retrievers, for example several missiles or missile instruction systems.
  • the missile registration system may include a ground-based process unit that is connected to the missile via remote data transmission.
  • the detection assistance data is expediently output to the missile before the missile sensor contacts the target.
  • the missile may be controlled to the target depending on the detection assist data, that is, using the detection assist data, so that the detection assist data may be used directly or indirectly as control information for controlling the missile.
  • the missile is controlled to the target using the detection assistance data before the missile detects the target.
  • the reconnaissance data contain information about a recognizability of the target.
  • Such information may be data on visibility over the target, an atmospheric transmittance or visibility, conveniently depending on the sensor used.
  • the reconnaissance data may be data on objects obscuring the target so that the target may not be recognizable.
  • a further embodiment of the invention provides that the reconnaissance data contain information about an environmental feature in the environment of the target. From this, as a detection support data, a relationship information, for example, a relative position of the destination to the environmental feature is advantageously determined.
  • the reconnaissance information may be a terrain and / or topography feature that is conveniently well visible, such as a tower, mast, hall, intersection, or the like. In this way, the target can be controlled even if its absolute position is unknown, as long as the relative position is known.
  • the missile may first be controlled using the reconnaissance information, eg, coordinates of a tower, and then guided into the target using the detection assist data, eg, the relative position of the target to the tower.
  • the detection support data may include a relative position and / or optical data, conveniently as viewed from a proximity of the environmental feature, such that the missile may be first applied to the environmental feature and then to the target.
  • the reconnaissance data include image information of an environment of the destination, and the detection support data includes a terrain model of an environment of the destination. Due to the terrain model, which is conveniently a topographical model or a radiation model, in two or three dimensions, the missile may receive additional information about the nature of the environment, conveniently relative to the target. Visibility of the target depending on the surrounding topography can be determined. It is also possible to detect from a radiation model that the target is first faded by another object, so that target detection is only possible if the object is optically separable from the target.
  • the reconnaissance data include image information of an environment of the destination, and the detection assist data includes a synthetic image of the destination and / or an environment of the destination.
  • a missile parameter is suitably taken into account, such as an approach direction of the missile to the target or target area, an anticipated missile velocity, atmospheric information such as ambient brightness, atmospheric transparency, and / or the like, thereby providing a particularly suitable image is attainable for the capture of the goal.
  • the image represents the target and / or the target area from the point of view of the approaching missile.
  • the synthetic image is an image of the target from the direction and the distance of a maximum detection distance of the missile / or atmospheric parameters can be considered.
  • the synthetic image is created and expediently provided to the missile before it can detect the target, in particular before the target is visible to the approaching missile. In this way, the missile, or its seeker, adjust detection parameters depending on characteristics of the image, even before the target has been detected by the missile or is visible. If the missile reaches the maximum detection range, it may have already evaluated the synthetic image and set the detection parameters to quickly detect the target.
  • the reconnaissance data includes visibility on the approach route of the missile to the target.
  • the synthetic image is created taking into account the visibility.
  • the vision may be a sensorial detection of the target according to the sensitivity of a sensor of the missile.
  • the reconnaissance data include a pre-image of the target created before the approach of the missile and the detection assistance data contain information on a relationship of the pre-image with the visual image of the target approaching the target
  • Missile offers a missile.
  • the pre-image may be a captured image or a synthetic image and is useful as a reference image.
  • the relationship may be a comparison and, in particular, information about how to compare the pre-image with the visual image.
  • the comparison can be done by an image correlation method.
  • the relationship may include information about which direction to look at the target when the missile is approaching the target.
  • the pre-image is created taking into account a maximum possible detection distance so that the pre-image shows the target and / or an environment of the target from a view in which the missile can actually detect the target, e.g. the maximum possible detection distance.
  • the reliability of proper targeting can be further enhanced if the reconnaissance data includes information about a view of the target, and the detection assistance data provides information on which of several possible missile targeting methods is most appropriate. For example, among several different sensors of the missile for detecting the target can be selected and / or an image correlation method based on a pre-image can be selected.
  • Detection of a false target can be counteracted if the reconnaissance data includes information about a view of the target and the detection assistance data contains information as to whether the missile is sufficient can be easily brought to the target via its own sensors or whether it has to be guided to the target with the aid of another method and expediently to where, so that its own sensor system can detect the target. In this way, it is possible to prevent the missile from searching for a target which is not recognizable to it and to interrupt an operation or to select a wrong target. If it is decided that a foreign guidance is necessary, for example, with the aid of another missile, which is in the vicinity or above the target, it can be decided from when or at what distance the guidance of the missile with the help of its own sensors.
  • the reconnaissance data includes a plurality of target features of visual information of the target and the capture support data includes information as to which of the target features the intended target must have.
  • the optical information may be information about a target signature, such as radiation that emits the target, information about radiation outlines, for example, four people on a pickup appearing as four luminous spots in an infrared image, a contrast between ambient radiation and a vehicle a certain paint and the like.
  • the information may be recorded or modeled destination information. Using feature-based algorithms and / or probability analysis, the missile can determine the target from a set of interchangeable objects.
  • the invention is further directed to a missile instruction system having processing means prepared to assemble target data by which a missile is controllable to a target and to deliver to the missile for targeting, and reconnaissance data from a reconnaissance sensor to capture assistance data; include, beyond the target data, information for detecting the target to process and hand over to the missile and in particular to control the missile using the detection support data to the target.
  • the reconnaissance data includes image information of an environment of the target and includes visibility on the approach route of the missile to the target.
  • the detection assistance data according to the invention contain a synthetic image of the target from the point of view of the approaching missile, the synthetic image was created taking into account the visibility.
  • the process agent is also suitably prepared to perform one, several or all of the previously mentioned process steps.
  • the process means comprises a ground-based first process unit and a second process unit in the missile, wherein the first
  • Process unit is prepared to process the reconnaissance data to detection assistance data and the second processing unit is prepared to control the missile on the target using the detection support data.
  • the second processing unit may generate flight control data and in particular data for a process unit of a seeker head of the missile for detecting the target.
  • Fig. 1 shows a landscape with mountains 2 and two valleys 4, 6 separated by a mountain saddle 8. Above the saddle 8 and the second valley 6 hangs a low-lying cloud 10, which obscures the view from the saddle 8 or from above to a target area 12.
  • a village 14 In the target area 12 is a village 14 and a plurality of objects 16, 18, 20 to be controlled, one of which has been selected as the target 20 to be fought by a missile 22.
  • the missile 22 is to be launched from a carrier platform 24, which in this embodiment is a ground-based carrier platform 24. In alternative embodiments, a sea-bound or flying support platform is possible.
  • the carrier platform 24 is technically connected to a missile guidance system 26, which comprises a ground-based process unit in the form of a data processing system in a building, and which may be part of a guidance system or weapon deployment system.
  • the Missile Injection System 26 is in turn linked to the missile 22 for data-logging purposes so that it can transmit to it detection support data prior to launch from the carrier platform 24 and during approach to the target 20.
  • a reconnaissance sensor 28 in a reconnaissance unit which in the illustrated embodiment is an aircraft that flies in the vicinity of the target area 12.
  • the target area 12 Before the launch of the missile 22, the target area 12 is informed by the reconnaissance unit and reconnaissance data resulting from the reconnaissance are transmitted to the missile guidance system 26.
  • the reconnaissance data in this embodiment include several aerial photographs of the target area 12 as well as information about the cloud cover 10, its thickness and position, in particular its lower edge.
  • the target 20 is selected.
  • the further objects 16, 18, the village 14 and in particular a landmark 30 are identified as such.
  • acquisition assistance data is developed by the missile registration system 26 used to instruct the missile 22 to target.
  • the acquisition support data may include some or all of the data described below.
  • An approach route 34 is calculated from the topography of the two valleys 4, 6 and the mountain saddle 8 located therebetween and a hill 32 in front of the destination area 12. This may not be too shallow, since the missile 22, or its seeker, the target 20 can detect optically only after flying over the hill 32. Since the distance from the hill 32 to the target 20 is too small to be able to determine its exact location due to detection of the movable target 20, the missile 22 must fly so that it has enough time to detect the correct target 20 and Distinguishing the target 20 from the objects 16, 18 is available. Thus, as part of the detection support data, the approach route 34 is determined to be directed toward the target 20 from above, so that the destination 20 can be sufficiently detected before being reached as such. Since the approach route 34 is an integral part of a reliable detection of the target 20, it belongs to the detection support data.
  • An approach route 34 directed from above onto the destination 20 requires that the missile 22 must fly through the cloud 10 in which the view of the destination 20 is blocked. It is therefore established as further detection support data, how long the missile 22 is controlled on its approach route 34 with extraneous information, for example, with target coordinates and / or the coordinates of the approach route 34, and from when he can use his own sensors for flight control or target detection. Thus, it is defined as acquisition support data that the missile 22 is only controlled with the help of its own sensors when it has exited the cloud 10, ie has passed its lower edge from above, as in FIG Fig. 1 is indicated. Since the approach route 34 and the position of the cloud 10 and its lower edge is known, the exit point of the missile 22 from the cloud 10 is known. Thus, a control mode change point is set, in which a control mode of the missile 22 is switched from a first mode to a second mode, in this embodiment, from a coordinate control to a visual control.
  • the missile instruction system 26 creates a synthetic image of the target area 12 as detection assistance data.
  • This synthetic image is created from the aerial photographs of the target area 12 of the reconnaissance sensor 28 and is transmitted to the missile 22 before it has sight of the target 20, ie before it is even able to detect the target 20.
  • the synthetic image is transferred to the missile 22 before it starts from the carrier platform 24.
  • the synthetic image of the target area 12 represents the target area 12 or a part thereof from the point of view of the approaching missile at the location from which the missile 22 can first detect the target 20. In the embodiment of Fig. 1 this is the point where the approach route 34 passes down the cloud deck 10.
  • the synthetic image includes, in particular, the landmark 30 and the target 20 designated as such, as well as the further objects 16, 18 that are subject to confusion for better discrimination from the target 20. Further objects, for example the village 14 or other landscape features, may be included in the synthetic image.
  • the missile 22 or its process unit can compare an image taken of the missile 22 image of the target area 12 with the synthetic image and, for example, in this way important in the synthetic image marked objects 16, 18, 20, 30 find in a simple manner in the captured real image and identify.
  • the detection assistance data includes information about a detection performance of the target 20.
  • this information implies that at the time the missile 22 first has a clear view of the target 20, detection of the target 20 using optical sensors of the target Missile 22 is possible only with a low quality, since the target 20 is relatively well camouflaged against the background and a distinction is possible only with insufficient reliability. Therefore, the detection support data further recognizes that although the flight control is visual, it is not oriented to the target 20 but to another point, such as the landmark 30. Thus, in an optically controlled flight phase, the flight control will be oriented at that point until one in the detection support data specified detection quality is sufficiently high, for example, over a predetermined quality value.
  • the distance or point on the approach route 34, from which the coverage quality is sufficiently good, is also included in the detection assistance data. From this moment, a further and thus later phase or mode of flight control can begin, from which the visual orientation on the target 20 controls the flight of the missile 22.
  • the direction and distance information between landmark 30 and target 20 can be given as an approximation, so that the missile 22 must target the target 20 as directly as possible and not first the landmark 30 and the target 20.
  • the acquisition support data may also include a number of features of the target 20 characterizing the target 20.
  • the features include visual features, which may be understood to include features that are recognizable only in the infrared or in another spectral range.
  • the features include, among other things, that the target 20 from the viewpoint of the approaching missile 22 along the approach route 34 has an extension of about 3 m x 6 m, the target has a dark green to ocher URL color design and stands against a light brown background. The background is from above the sandy or loamy soil on which the target 20 stands.
  • the missile 22 For measuring individual objects, such as the houses and vehicles, the missile 22 is provided with a scale as detection assistance data.
  • the scale may consist in an optical detail easily recognizable by the missile 22 in the target area 12, for example a house whose dimensions are indicated in the detection support data. By comparing the Objects with the optical detail, the missile 22 can easily determine the dimensions of the objects.
  • the missile 22 may distinguish the target 20 from, for example, houses of the village 14. It can not distinguish the target 20 from the objects 16, 18.
  • the detection support data includes relationship information about at least one surrounding point, in this case, the landmark 30.
  • the detection assistance data in this case include the distance 36 and the direction of the target 20 to the landmark 30, the direction being given as a geographical direction or as a direction to another landmark, so that triangulation is possible. From this information, the missile 22 can distinguish the target 20 from the other two objects 16, 18 which are at a different distance and direction from the landmark 30.
  • the target 20 is at the time of approach of the missile 22 in the vicinity of a vehicle 38, which is not included in the reconnaissance by the reconnaissance sensor 28, since it has retracted recently in the target area 12.
  • the vehicle 38 stops near the target 20 has approximately the same dimensions and suitcases on the roof of a similar color and piebald structure.
  • the infrared signature is approximately equal to the target 20.
  • the detection assistance data includes the information that the target 20 is positioned in front of a light brown background.
  • the vehicle 38 travels on a medium gray road so that the background feature on the vehicle 38 does not apply.
  • the feature of the background may be deposited as a binding feature in the detection support data without the target 20 not being identified or combated as such. Since the target 20 fulfills all visual features, it can be recognized by the vehicle 38 through this visual feature and thus identified as a target 20.
  • a direction of travel and travel speed of the target 20 are used, so that from a reconnaissance time and a target detection time by the missile 22 of the direction of travel and travel speed a current location is calculated, at which the target 20 can be positioned assuming the enlightened direction and speed would.
  • tolerance information may be part of the detection support data, eg, allowable positional inaccuracy, color inaccuracy, inaccuracy in size, radiation signature inaccuracy, or the like.
  • a terrain model as a three-dimensional model is also advantageous, which is made available to the missile 22 before a first possible detection time. From this three-dimensional terrain model, the missile 22 can transform the view of the target area 12 from any perspective into a two-dimensional theoretical vision image that facilitates location of the objects of interest 16, 18, 20, 30 that are conveniently marked as such in the three-dimensional terrain model. It is also possible that the three-dimensional terrain model is used by the missile guidance system 26 to create the synthetic and especially two-dimensional image that simulates the missile 22's view of the target area from its approach route 34. By means of an advance image, for example the synthetic image and / or the three-dimensional terrain model, the missile 22 can easily find objects 16, 18, 20, 30 of interest by image correlation with an image of the target area 12 taken by the missile 22.
  • the missile 22 is informed of a detection method among several possible detection methods with which it should detect the target 20.
  • a visual detection method directed at the landmark 30 is specified in a former flight phase.
  • a detection method is specified in which the target 20 is detected by means of an infrared sensor in order to be able to distinguish it from similar rocks surrounding the target 20.
  • a third and later flight phase is characterized in that the detection method again takes place in the visible frequency range in order to be able to detect and check the visual characteristics of the target color and the background color.
  • the detection support data comprises a plurality of recognition methods that are used in succession or simultaneously and with which the missile 22 is to detect the target 20.
  • the detection support data includes at least one location point from which to change a detection method.
  • Fig. 2 2 shows a flow diagram of a method for instructing the missile 22 on the target 20.
  • a first database that contains the knowledge base of a guidance system, for example an insert situation image
  • superordinate position information 40 is retrieved and transferred to a process unit 42 of the missile guidance system 26.
  • reconnaissance data 44 are retrieved, for example via the application area, the target area 12 contained therein and / or features of the destination 20.
  • the superordinate knowledge base from the database 40 can also contain reconnaissance data here ,
  • target data 46 is generated by the missile homing system 26 or other system, such as the coordinates of the target area 12 and, if applicable, the target 20 transmitted to the missile 22 before or after launch from the carrier platform 24. On the basis of this data, the missile 22 can be started and guided in the direction of the target area.
  • detection support data 48 is also generated by the process unit 42 of the missile instruction system 26. These can - depending on the data - the missile 22 also be handed over after its launch, since they support the later capture later.
  • missile information 50 will also be included via the missile 22. This missile information 50 conveniently contains information about the type of missile 22 and its sensors, its process unit and its capabilities, about the seeker head and its optics, about the warhead of the missile 22 and its uses and the like.
  • the derived detection support data 48 which may include target features, a target behavior, a target position, a target context, a steering strategy for the missile 22, and / or detection conditions, are provided to another process unit 52 that is part of the missile 22.
  • the ground-based process unit 42 and the process unit 52 of the missile 22 in this case form a process means of the missile homing system 26.
  • the reconnaissance data 44 are transferred to the missile 22, and the process unit 52 of the missile 22 derives therefrom capture support data 48, according to which the missile 22 detects the target 20.
  • acquisition support data 48 directly to the Missiles 22 are transferred together with reconnaissance data from which the missile 22 further detection assistance data 48 generated and the target detection and / or missile control from the entirety of the detection support data 48 takes place.
  • the process unit 52 Based on the detection support data 48, the process unit 52 performs the control 54 of the missile 22.
  • the controller 54 may include the control of actuators for steering the missile 22, actuators for controlling the seeker head, further actuators for triggering a warhead, the control of a triggering mode of the warhead and / or the selection of a detection mode for detecting the target 20 and others control actions.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Radar Systems Or Details Thereof (AREA)

Claims (10)

  1. Procédé de pointage d'un missile (22) sur une cible (20), procédé dans lequel des données de cible (46), au moyen desquelles le missile (22) peut être guidé vers la cible (20), sont assemblées et transmises au missile (22) pour le guider vers la cible (20), des données de reconnaissance (44) en provenance d'un capteur de reconnaissance (28) étant traitées par un système de pointage de missile (26) pour obtenir des données d'aide à la détection (48) contenant des informations de détection de la cible (20) allant au-delà des données de cible (46) et étant transmises au missile (22),
    a) les données de reconnaissance (44) contenant des informations d'image d'un environnement de la cible (20) et comprenant des conditions de visibilité sur la route d'approche (34) du missile (22) sur la cible (20) et
    b) les données d'aide à la détection (48) comprenant une image de synthèse de la cible (20) telle que vue par le missile (22) en approche et
    c) l'image de synthèse étant créée avec prise en compte des conditions de visibilité.
  2. Procédé selon la revendication 1,
    les données de reconnaissance (44) comprenant des informations sur la capacité de reconnaissance de la cible (20) et les données d'aide à la détection (48) comprenant des informations sur les conditions actuelles de détection de la cible (20).
  3. Procédé selon la revendication 1 ou 2,
    les données de reconnaissance (44) comprenant des informations sur une caractéristique environnementale (30) dans l'environnement de la cible (20), et les données d'aide à la détection (48) comprenant une information relationnelle entre la cible (20) et la caractéristique environnementale (30).
  4. Procédé selon l'une des revendications précédentes,
    les données d'aide à la détection (48) comprenant un modèle de terrain d'un environnement de la cible (20).
  5. Procédé selon l'une des revendications précédentes,
    les données de reconnaissance (44) comprenant une pré-image de la cible (20) qui est réalisée avant l'approche du missile (20) vers la cible (20) et les données d'aide à la détection (48) comprenant des informations sur une relation de pré-image avec une image visuelle de la cible (20) qui s'offre au missile (22) approchant de la cible (20).
  6. Procédé selon l'une des revendications précédentes,
    les données de reconnaissance (44) comprenant des informations sur une vue de la cible (20), et les données d'aide à la détection (48) comprenant des informations sur lequel parmi une pluralité de procédés de détection de cible possibles du missile (22) est le plus approprié.
  7. Procédé selon l'une des revendications précédentes,
    les données de reconnaissance (44) comprenant des informations sur une vue de la cible (20) et des données d'aide à la détection (48) indiquant si le missile (22) présente une approche suffisamment bonne de la cible (20) par ses propres capteurs ou s'il doit être guidé vers la cible (20) à l'aide d'un autre procédé.
  8. Procédé selon l'une des revendications précédentes,
    les données de reconnaissance (44) contenant une pluralité de caractéristiques de cible constituées d'informations optiques de la cible (20), et les données d'aide à la détection (48) contenant des informations relatives aux caractéristiques de cible que la cible détectée (20) doit posséder.
  9. Système de pointage de missile (26) comprenant un agent de traitement préparé pour
    a) rassembler des données de cible (46) au moyen desquelles un missile (22) peut être guidé vers une cible (20) et les transmettre au missile (22) afin de le piloter vers la cible (20), et
    b) traiter des informations (44) en provenance d'un capteur de reconnaissance (28) pour obtenir des données d'aide à la détection (48) contenant des informations de détection de la cible (20) au-delà des données de cible (46) et pour les transférer au missile (22),
    c) les données de reconnaissance (44) contenant des informations d'image d'un environnement de la cible (20) et comprenant des conditions de visibilité sur la route d'approche (34) du missile (22) vers la cible (20),
    d) les données d'aide à la détection (48) comprenant une image de synthèse de la cible (20) telle que vue par le missile en approche, et
    e) l'image de synthèse ayant été créée avec prise en compte de conditions de visibilité.
  10. Système de pointage de missile selon la revendication 9,
    le moyen de traitement comprenant une première unité de traitement au sol (42) et une deuxième unité de traitement (52) dans le missile (22), la première unité de traitement (42) étant préparée pour traiter les données de reconnaissance (44) pour obtenir des données d'aide à la détection (48) et la deuxième unité de traitement (52) étant préparée pour guider le missile (22) vers la cible (20) à l'aide des données d'aide à la détection (48).
EP11004429.4A 2010-06-04 2011-05-31 Procédé de guidage d'un corps volant vers une cible Active EP2392890B1 (fr)

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DE201010022728 DE102010022728A1 (de) 2010-06-04 2010-06-04 Verfahren zum Einweisen eines Flugkörpers auf ein Ziel

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Publication number Priority date Publication date Assignee Title
DE3734758A1 (de) * 1987-10-14 1989-05-03 Messerschmitt Boelkow Blohm Panzerabwehr-raketensystem
US5881969A (en) * 1996-12-17 1999-03-16 Raytheon Ti Systems, Inc. Lock-on-after launch missile guidance system using three dimensional scene reconstruction
US6072889A (en) * 1997-12-03 2000-06-06 The Raytheon Company Method and system for imaging target detection
DE19828644C2 (de) * 1998-06-26 2001-12-06 Lfk Gmbh Verfahren zum ferngesteuerten Bekämpfen bodennaher und/oder bodengebundener Ziele
US6157875A (en) * 1998-07-17 2000-12-05 The United States Of America As Represented By The Secretary Of The Navy Image guided weapon system and method
GB2430722B (en) * 2001-09-26 2007-08-22 Mbda Uk Ltd A guidance system
US7040570B2 (en) * 2003-09-29 2006-05-09 The United States Of America As Represented By The Secretary Of The Army Weather-agile reconfigurable automatic target recognition system
DE10356157B4 (de) * 2003-12-02 2006-06-14 Michael Grabmeier Verfahren und Vorrichtungen für den Marschflugkörper-Verschuß mittels Booster-Plattform
DE102008054264B4 (de) * 2008-10-31 2012-09-13 Lfk-Lenkflugkörpersysteme Gmbh Multifunktionale Service- und Testeinrichtung für unbemannte Flugkörper

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