EP3495762A1 - Système et procédé de localisation de cible coordonnée par une personne d'un missile guidé - Google Patents

Système et procédé de localisation de cible coordonnée par une personne d'un missile guidé Download PDF

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Publication number
EP3495762A1
EP3495762A1 EP18210869.6A EP18210869A EP3495762A1 EP 3495762 A1 EP3495762 A1 EP 3495762A1 EP 18210869 A EP18210869 A EP 18210869A EP 3495762 A1 EP3495762 A1 EP 3495762A1
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EP
European Patent Office
Prior art keywords
target object
guided missile
antenna
missile
coordination terminal
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.)
Withdrawn
Application number
EP18210869.6A
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German (de)
English (en)
Inventor
Christian Tristl
Thomas Löb
Manuel Kleinke
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MBDA Deutschland GmbH
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MBDA Deutschland GmbH
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by MBDA Deutschland GmbH filed Critical MBDA Deutschland GmbH
Publication of EP3495762A1 publication Critical patent/EP3495762A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • F41G7/2206—Homing guidance systems using a remote control station
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/14—Indirect aiming means
    • F41G3/16—Sighting devices adapted for indirect laying of fire
    • F41G3/165—Sighting devices adapted for indirect laying of fire using a TV-monitor
    • 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
    • F41G7/2253—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
    • F41G7/226—Semi-active homing systems, i.e. comprising a receiver and involving auxiliary illuminating means, e.g. using auxiliary guiding missiles
    • 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
    • F41G7/20—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
    • F41G7/2286—Homing guidance systems characterised by the type of waves using radio waves
    • 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 present invention relates to a system and a method for person-coordinated target finding of a guided missile.
  • a conventional course of flight during the destination determination of a target-seeking missile emitted by a platform often consists of two phases, a so-called induction phase and a steering phase.
  • induction phase a target object is trained, that is, the target object is defined in a sensor image of a missile seeker head, and the associated data is transmitted to a seeker of the seeker.
  • the target tracking device tracks the target object in the sensor image.
  • a signature can be generated by reflection or scattering of an illumination of the target by means of laser radiation (semi-active laser-based target illumination or target search guidance, English: "semi-active laser", SAL) or a signature infrared radiation of the target can be used (passive target search)
  • Search heads are already known from the prior art, which have optics which are dual-mode or multi-mode functionality.
  • Such seekers are for example in the publications DE 10 2007 006 710 B3 .
  • EP 2 957 854 A1 or DE 10 2012 017 452 A1 discloses and can detect both infrared radiation and laser radiation.
  • the induction phase can take place before or during a target approach. This can be done in the so-called Man-In-The-Loop (MITL) method by so-called Foward Air Controllers (FAC) using radio communication through user intervention to provide high precision targeting with simultaneous responsiveness in the case to allow for rapidly changing situation conditions, eg in a confusing destination area with difficult friend-enemy separation.
  • the FAC may request a change of destination and / or a mission termination at any time by communication with a command post and / or a firing position.
  • More recent technical solutions such as Remotely Operated Video Enhanced Receiver (ROVER) or Persistent Close Air Support (PCAS), aim to improve the FAC's deployment by providing a digital data link to the automated one Information transmission between the launching platform and a terminal of the FAC is provided.
  • the publication DE 10 2010 011 256 A1 moreover proposes imparting, in addition to the steering information, further information to a laser beam of a laser target illumination device, which information is important for the optimal effect of the laser steering ammunition in the target.
  • the present invention has the object to find solutions for person-coordinated target finding of a missile, which allow increased responsiveness in case of situation changes and a reduced susceptibility to errors.
  • a system for person-coordinated target determination of a missile includes a portable mobile destination instruction device configured to mark a destination object; a guided missile comprising a first antenna, a control unit and a seeker head, the seeker head configured to detect and track the marked target object; and a portable mobile co-ordination terminal formed with a second antenna, wherein the first antenna and the second antenna are adapted to transmit targeting data between the control unit of the guided missile and the co-ordination terminal, the co-ordination terminal for displaying the targeting data and controlling the targeting of the missile is formed via the control unit during the tracking of the marked target object.
  • a method for person-coordinated target determination of a guided missile includes tagging a target object with a portable mobile targeting device; Instructing a seeker head of a missile to detect and track the marked target object; Exchanging targeting data between a portable mobile coordination terminal and a control unit of the guided missile via a first antenna of the missile and a second antenna of the coordination terminal; Displaying the goal finding data on the coordination terminal; and controlling the targeting of the missile via the control unit by means of the co-ordination terminal during the tracking of the tagged target object by the missile.
  • One idea underlying the present invention is to provide a bidirectional direct data link between a missile and a FAC via a terminal carried by it, which enables an active, direct influence of the FAC on the destination of the missile. This not only improves the precision of the target instruction by avoiding or correcting false toggling of targets. In addition, depending on the situation, in particular the slow and cumbersome communication channel can be bypassed via the command post or the fireplace. On the contrary, the coordinating person, in particular a FAC, can access the guided missile at all times and responsively. The response times for a change of destination or a mission termination can thus be significantly minimized.
  • the invention provides antennas with a corresponding emission characteristic, which enables a data connection between the terminal and the guided missile.
  • the second antenna may be coupled to a transceiver as a corresponding tactical data link (directional) antenna, wherein the overall system may be dimensioned to be accommodated in, for example, a backpack or the like can be transported.
  • the coordination terminal itself, for example, a robustified laptop or the like may be designed as an input and control device, which includes appropriate software for coordinating the Zieleinlitz and goal setting and the general mission planning.
  • the targeting of the targeting device can hereby be transmitted, as usual, via a tactical data link of the coordinator or the coordination terminal to a command post, a fire pit and / or a launching platform or the like, which then instructs detection and tracking of the marked target object by the guided missile.
  • the target instruction can also be conveyed directly between the coordination terminal and the guided missile, for example in the event that the guided missile is already in flight.
  • the coordination terminal can be designed to correct and / or change the target determination data.
  • the control may include correcting and / or changing the target determination data. Accordingly, when the situation at the destination changes, the FAC can intervene quickly and efficiently and communicate necessary changes directly and immediately with the missile. For example, the trajectory or configuration of the missile can also be changed in a Endanflugphase (English: “Cruise Phase” or “Terminal Phase”), which would no longer be possible in known system due to the Zeitdringige and the lengthy coordination with a command post or platform ,
  • the coordination terminal can be designed to stop the tracking of the marked target object.
  • the control may include canceling the tracking of the marked target object.
  • the guided missile can, for example, be redirected, defused and / or destroyed shortly before the impact.
  • the coordination terminal can be designed to replace the marked target object with another marked target object.
  • the control can include replacing the marked target object with another marked target object. For example, a wrongly activated target can still be corrected until shortly before the arrival of the guided missile and replaced by the actual target.
  • the system may be configured to transmit a marking of a target object through the targeting device directly via the coordination terminal to the guided missile and to instruct the latter to record the tracking.
  • the destination determination data may include at least one of current navigation data, steering signals and environment data of the seeker.
  • the destination finding data may include a current seeker image of the destination approach.
  • the targeting data may include current target and environmental coordinates, such as data from local and / or global positioning systems, e.g. of navigation satellite systems or the like.
  • the targeting data may include targeting data, such as laser spot and / or IR information from a targeting system and / or from a sensor within the seeker.
  • At least one of the first antenna and the second antenna can be designed with a communication range of less than 10 km, in particular less than 6 km.
  • the system may provide a short-range communication and control connection between the co-ordination terminal and the serving FAC and the missile, which will provide the FAC with direct interaction with the missile, particularly in a final propulsion phase of the missile.
  • the coordination terminal may be a portable computer such as a laptop, notebook and / or subnotebook or another mobile device, such as a tablet computer, a pocket computer, a personal digital assistant, a mobile phone, an interface device for the satellite communications etc.
  • the co-ordination terminal can be a robust laptop.
  • the destination instruction device can be a target illumination system, in particular a laser-based target illumination system.
  • the Zielbeleuchtungssytem but also be radar-based or use a combination of laser and radar.
  • the target lighting system may be an SAL system.
  • the seeker head can be designed as a dual-mode viewfinder with a semi-active target search steering mode and a passive target search steering mode.
  • the seeker head can also be designed as a multi-mode viewfinder with a plurality of semi-active and / or passive target search steering modes.
  • Such a search head with multiple modes is particularly advantageous in combination with the direct communication between missile and coordination terminal or FAC, since the used mode of the seeker head on the specific, current situation is quickly adaptable and each optimal for the current conditions control variants are selectable.
  • the semi-active Zielsuchlenkmodus at least one of laser-based and radar-based and the passive Zielsuchlenkmodus be at least one of optical and infrared based formed.
  • the semi-active Zielsuchlenkmodus based on the SAL technology and the passive Zielsuchlenkmodus TV or video-based formed with an optical camera English: "Television guidance”
  • a combination of different technologies is conceivable, eg a SAL & TV / IR seeker.
  • Such a seeker head would make it possible to utilize the most advantageous technology for the current situation.
  • a laser mode can serve align the seeker with the sighting line to the target, ie instruct the guided missile.
  • a TV and / or IR sensor can take over the final destination tracking. The discovery and identification of the target can thus be assigned to the laser mode, while the IR mode is used only for the final approach.
  • the guided missile may have a weight of less than 100 kg.
  • guided missiles include all guided missiles that can move on determinable trajectories in and outside of the airspace.
  • Missiles according to the present invention include in particular light drones, guided missiles, steering grenades, cruise missiles, ground target missiles, air-to-surface missiles, antitank missiles, anti-ship missiles, air target missiles such as air-to-air missiles or anti-aircraft missiles, anti-missile missiles and anti-satellite rockets.
  • FIG. 1 shows a schematic illustration of a system 1 for person-coordinated target finding of a homing missile 2 according to an embodiment of the invention.
  • the system 1 comprises a guided missile 2, which is emitted by a launching platform 10 and with it via a tactical data connection 22 communicated.
  • the launching platform 10 may be movable or immobile.
  • the launching platform 10 may be a flying, floating or moving vehicle, eg a helicopter.
  • the launching platform 10 may also be permanently installed.
  • the guided missile 2 may be, for example, a steering rocket in a weight class of less than 100 kg.
  • the guided missile 2 comprises a first antenna 5, a control unit 6 and a seeker head 7.
  • the seeker head 7 is for detecting and tracking a marked target object 4 as a dual-mode viewfinder with a laser-based semi-active Zielsuchlenkmodus 12 (SAL) and a TV and / or IR-based passive homing control mode 13 is formed.
  • SAL laser-based semi-active Zielsuchlenkmodus 12
  • the system 1 further comprises a portable mobile destination instruction device 3, which is formed with a laser illumination functionality for marking the target object 4.
  • a person eg a FAC
  • Laser scattered light 20 is reflected and / or scattered by the targeted target point X, whereby the seeker head 7 of the guided missile 2 can detect and track the marked target object 4 via the laser-based semi-active target search steering mode 12.
  • the passive Zielsuchlenkmodus 13 of the guided missile 2 can be used for target finding.
  • the targeting semi-active steering mode 12 may be used only for targeting and for a first phase of the target approaches.
  • Such a laser-based target search steering mode 12 has the disadvantage that the reflected or scattered laser light 20 may under certain circumstances be registered, as a result of which it is possible to infer both an imminent attack and the presence and possibly even the position of a FAC.
  • the semi-active target search steering mode 12 may be switched off in a final approach phase and instead switched to a passive target search steering mode 13 be, which does not use active radiation, but only exploits existing visual and / or infrared information of the target object 4 anyway.
  • the aiming device 3 is coupled to a portable mobile coordination terminal 8, which is formed with an input device 18 and a screen 14.
  • the co-ordination terminal 8 may be a laptop or other portable computer that is transportable by a FAC in a backpack or the like along with the targeting device 3.
  • the coordination terminal is further formed with a second antenna 9.
  • the first and second antennas 5, 9 are within a range of a few kilometers, e.g. less than 6 km, adapted to transmit destination finding data between the control unit 6 of the guided missile 2 and the coordination terminal 8 via a direct tactical data link 21.
  • the coordination terminal 8 is hereby designed to display the target determination data and to control the target determination of the guided missile 2 via the control unit 6 during the tracking of the marked target object 4.
  • the destination finding data include, for example, current navigation data, steering signals, environment data of the seeker head 7, etc.
  • the coordination terminal 8 can be used by the FAC for controlling and / or monitoring the guided missile 2. For example, via the coordination terminal 8, the FAC may correct and / or change the targeting data, abort the tracking of the tagged target 4, or replace, for example, the tagged target 4 with another tagged target 4 ', e.g. in case the target object 4 is wrongly targeted.
  • Fig. 2 shows an exemplary representation of the screen 14 of the coordination terminal 8, which is divided into two sections.
  • An upper section is used for Representation of a trajectory 16 of the guided missile 2 on an environment map 15, in particular, the current position and speed of the missile 2 is displayed.
  • a search header 17 is displayed on the lower section, which summarizes the information relevant to the FAC regarding the targeting and destination finding of the guided missile 2.
  • an indirect tactical data connection 22 is provided, via which the launching platform 10, the guided missile 2 and the coordination terminal 8 are connected.
  • the overall mission planning and mission coordination is regulated by a command post 11 or the like, which also communicates via the indirect tactical data link 22 with the individual components.
  • Fig. 3 shows a schematic flow diagram of a method M for the use of the system 1 from Fig. 1 .
  • a target approach of the guided missile 2 will be explained with reference to the figures.
  • the guided missile 2 is launched from the launching platform 10 and then guided on its trajectory by an inertial navigation system or the like.
  • a target object 4 is marked with the portable mobile Zieleinouslysvorraum 3 via the laser beam 19 and the reflected laser scattered light 20 is registered by the semi-active Zielsuchlenkmodus 12 of the seeker 7 (see. Fig. 1 )
  • the guided missile 2 under M2 is instructed to detect and track the marked target object 4.
  • the guided missile 2 for example, operate on the principle of proportional navigation.
  • a corresponding laser sensor of the seeker head 7 detects and identifies the target object 4 and centers it in a field of view by controlling a sighting line which is aligned approximately with the aid of a gimbal or the like.
  • the flight trajectory 16 is in this phase of flight in Fig. 2 marked with a dash-dotted line.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP18210869.6A 2017-12-11 2018-12-06 Système et procédé de localisation de cible coordonnée par une personne d'un missile guidé Withdrawn EP3495762A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102017011407.2A DE102017011407A1 (de) 2017-12-11 2017-12-11 System und verfahren zur personenkoordinierten zielfindung eines lenkflugkörpers

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EP3495762A1 true EP3495762A1 (fr) 2019-06-12

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EP (1) EP3495762A1 (fr)
DE (1) DE102017011407A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110596470A (zh) * 2019-09-09 2019-12-20 西北工业大学 一种利用无人机和差分gnss定位的天线测试方法
CN113091513A (zh) * 2021-03-03 2021-07-09 上海机电工程研究所 舰载导弹武器系统的实时动态标定方法、系统及介质

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113359813B (zh) * 2021-05-11 2022-08-05 西北工业大学 一种多领弹多从弹群组协同制导方法

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EP2957854A1 (fr) * 2014-06-17 2015-12-23 MBDA Italia Chercheur bi-mode
US20170314891A1 (en) * 2016-04-29 2017-11-02 Airbus Helicopters Aiming-assistance method and device for laser guidance of a projectile

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US4442431A (en) * 1971-07-12 1984-04-10 Hughes Aircraft Company Airborne missile guidance system
US20120211589A1 (en) * 2005-06-20 2012-08-23 Burak Uzman Remotely-guided vertical take-off system and method for delivering an ordnance to a target
US20100320312A1 (en) * 2006-08-16 2010-12-23 Rafael Advanced Defense Systems Ltd. Miniature missile
US20100259614A1 (en) * 2009-04-14 2010-10-14 Honeywell International Inc. Delay Compensated Feature Target System
KR101483064B1 (ko) * 2014-02-21 2015-01-21 엘아이지넥스원 주식회사 유도 비행체 발사 시스템을 위한 휴대용 발사통제 장비 및 운용 방법
EP2957854A1 (fr) * 2014-06-17 2015-12-23 MBDA Italia Chercheur bi-mode
US20170314891A1 (en) * 2016-04-29 2017-11-02 Airbus Helicopters Aiming-assistance method and device for laser guidance of a projectile

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110596470A (zh) * 2019-09-09 2019-12-20 西北工业大学 一种利用无人机和差分gnss定位的天线测试方法
CN110596470B (zh) * 2019-09-09 2021-01-05 西北工业大学 一种利用无人机和差分gnss定位的天线测试方法
CN113091513A (zh) * 2021-03-03 2021-07-09 上海机电工程研究所 舰载导弹武器系统的实时动态标定方法、系统及介质
CN113091513B (zh) * 2021-03-03 2023-02-28 上海机电工程研究所 舰载导弹武器系统的实时动态标定方法、系统及介质

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