EP0100979B1 - Système de guidage semi-actif pour un missile à tête chercheuse - Google Patents

Système de guidage semi-actif pour un missile à tête chercheuse Download PDF

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Publication number
EP0100979B1
EP0100979B1 EP83107521A EP83107521A EP0100979B1 EP 0100979 B1 EP0100979 B1 EP 0100979B1 EP 83107521 A EP83107521 A EP 83107521A EP 83107521 A EP83107521 A EP 83107521A EP 0100979 B1 EP0100979 B1 EP 0100979B1
Authority
EP
European Patent Office
Prior art keywords
target
guidance system
illuminating device
illumination
devices
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.)
Expired
Application number
EP83107521A
Other languages
German (de)
English (en)
Other versions
EP0100979A1 (fr
Inventor
Peter Dipl.-Ing. Kriegesmann
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.)
Cessione telefunken Systemtechnik GmbH
Original Assignee
Licentia Patent Verwaltungs 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 Licentia Patent Verwaltungs GmbH filed Critical Licentia Patent Verwaltungs GmbH
Publication of EP0100979A1 publication Critical patent/EP0100979A1/fr
Application granted granted Critical
Publication of EP0100979B1 publication Critical patent/EP0100979B1/fr
Expired 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
    • F41G7/226—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
    • F41G7/2286—Homing guidance systems characterised by the type of waves using radio waves

Definitions

  • the invention relates to a semi-active guidance system for a target-seeking, guided missile.
  • a target for the combat of which the missile is started, is illuminated with electromagnetic energy by an illuminator which is separate from the missile and is generally stationary.
  • the radiation hitting the target is inter alia reflected in the direction of the missile, which passively obtains information about the direction of flight to be taken from the relative direction of incidence of the radiation component reflected on it.
  • Such a semi-active missile guidance method can be used during the entire flight path or even only during shorter phases of the flight.
  • FR-A 2470357 describes a guiding method for a missile, in which a laser is provided for illuminating a target to be combated. A person operating the laser directs the sharply focused laser beam onto the target. The missile fired at the target contains receiving devices which detect the laser light back-controlled by the target and, if necessary, correct the direction of flight of the missile towards the target via control means. The operator must keep the laser beam aimed at the target throughout the flight phase of the missile and track it when the target is moving.
  • the laser illumination of the target can also be limited to a short alignment phase after the launch of the missile. For this case, an image recording device is provided in the missile, which determines the current target direction during the short illumination phase and subsequently takes over the control of the missile on the basis of the continuously recorded image.
  • systems which have a search radar or a comparable device for a first target detection. Since the antenna of the search radar only points at the target for a short time and the radar signal is usually pulse-shaped, the search radar is not suitable for illuminating the target. A discovered target is therefore illuminated by a target tracking radar with a very narrow, approximately pencil-shaped directional diagram. The current target location can be determined continuously from the echo component reflected from the target to the illuminated target tracking radar, and this information can be used to precisely align the narrow antenna lobe of the illuminator to the target.
  • the object of the present invention is to provide a semi-active guidance system for guided missiles which can also be constructed with little effort, in particular for the simultaneous guidance of several missiles.
  • the lighting device is designed only to emit signals, but not to receive echoes, and therefore does not have the possibility of independent target tracking.
  • Such a lighting device without its own reception and evaluation facility is much simpler in construction and therefore cheaper than an autonomous target tracking device. This has a particularly advantageous effect when extending a control system to a plurality of lighting devices. Since the destination cannot be determined with the lighting device, the destination information of the destination device is used for the alignment of the directional diagram.
  • setting variables for the illuminating device are derived from the target information and transmitted to the illuminating device.
  • the semi-active guidance of a missile to the discovered target by illumination takes place from the illumination device.
  • the target location devices are free to examine the entire surveillance area for the presence of further targets.
  • the directional diagram of the lighting device is aligned according to the determined target location or the transmitted setting variables by means of conventional adjusting devices.
  • the entire surveillance area is usually periodically swept by the target location devices, in particular in the case of a search radar.
  • the target illuminated by the lighting device is therefore again detected by the target locating devices after a certain information renewal time.
  • a new target location of the target, which has moved on in the meantime, is determined and the directional diagram of the lighting device is reset in accordance with the new target location.
  • the solid angle illuminated by the directional diagram i. H. the azimuthal and elevational latitude of the directional lobe is selected so that it is greater than or at least as large as the maneuvering space of the target within the information renewal time.
  • the limits of this maneuvering space result from the length of the information renewal time, the current target data and assumptions about the maneuverability of the target.
  • the technique of working with a confined maneuvering space is known from radar systems with tracking.
  • an advantageous further development of the invention provides for the shape of the directional diagram of the lighting device, i.e. the width in elevation and azimuth, to be changeable so that the solid angle illuminated via the directional diagram is adapted to the current target data can be.
  • the invention is particularly advantageous for supplementing and expanding known systems, which comprise a search radar for room surveillance and one or more target tracking devices with a narrow, approximately pencil-shaped directional diagram.
  • the search radar and the target tracking devices essentially assume the function of the target locating devices.
  • a favorable embodiment provides that after the discovery of a target by the search radar, a target tracking device is aimed at the target and determines its exact target location.
  • the target tracking device can also be used to determine the target height, while the search radar often only allows the target azimuth to be determined.
  • the target tracking device can advantageously also carry out target illumination in the initial phase.
  • the lighting device takes over the target lighting.
  • the target tracking device is thereby released (after changing frequency) for a new target.
  • the target tracking device perceives the illumination of the target until the target of the lighting device has approached a maximum distance, which could clearly be referred to as the range of the lighting device.
  • the target tracking device perceives the illumination of the target until the target of the lighting device has approached a maximum distance, which could clearly be referred to as the range of the lighting device.
  • the target tracking device if there is only one target, it is advantageous to carry out the target illumination by the target tracking device during the entire flight time (or the semi-active phase) of the missile, and the illumination to the illumination device only if there is another target to transfer and use the target tracking device to determine the destination and possibly illuminate the new target.
  • a further advantageous embodiment provides that when there are several targets, each target is illuminated by one lighting device each, and the target tracking device determines the target locations of the illuminated targets in a cyclical sequence independently of other target positioning devices. This can significantly reduce the information renewal time.
  • the individual operating modes and the coordination of the various system components are advantageously controlled via a central computer.
  • this also provides the missile-specific setting of e.g. Frequency, time of transmission and modulation of the lighting signal.
  • the lighting devices can perform deceptive transmitter tasks during breaks in which they are not required for missile guidance and are controlled accordingly by the head office.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Sampling And Sample Adjustment (AREA)
  • Measuring Pulse, Heart Rate, Blood Pressure Or Blood Flow (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Claims (13)

1. Système de guidage semi-actif pour un missile ou un autre projectile guidé et à dispositif chercheur de cible, comprenant
- des dispositifs de localisation de cible,
- au moins un dispositif d'illumination de cible, et
- des moyens d'asservissement pour l'orientation du diagramme directionnel du dispositif d'illumination sur une position de cible détectée par les dispositifs de localisation,
caractérisé en ce que
- le dispositif d'illumination est réalisé pour agir seulement comme un dispositif émetteur,
- des dispositifs de commande sont prévus pour, à chaque renouvellement de l'information fournie sur une cible par les dispositifs de localisation, produire un nouveau réglage des moyens d'asservissement dans le sens d'un nouveau pointage du diagramme directionnel du dispositif d'illumination sur la cible et
- les largeurs de valeur moyenne en hauteur et en direction du diagramme directionnel du disposition d'illumination ont au moins une grandeur telle que l'angle solide illuminé englobe l'espace d'évolution de la cible à l'intérieur du temps de renouvellement de l'information des dispositifs de localisation.
2. Système selon la revendication 1, caractérisé en ce que les dispositifs de localisation comportent une installation radar panoramique.
3. Système selon la revendication 1 ou 2, caractérisé en ce que les dispositifs de localisation comportent un dispositif de poursuite de cible ayant un diagramme à peu près en forme de pinceau très fin.
4. Système selon la revendication 3, caractérisé en ce qu'il comprend des moyens de commande qui assurent l'illumination de la cible par le dispositif de localisation dans une phase initiale et par le dispositif d'illumination ensuite.
5. Système selon la revendication 4, caractérisé en ce que le dispositif d'illumination prend la relève pour illuminer la cible lorsque celle-ci s'approche à une distance inférieure à une distance maximale du dispositif d'illumination.
6. Système selon la revendication 4, caractérisé en ce que le dispositif d'illumination prend la relève, pour illuminer la cible, en cas de présence d'une autre cible.
7. Système selon la revendication 4 ou 5, caractérisé en ce que les moyens de commande sont réalisés de manière qu'en cas de changement du dispositif illuminant, pour la même cible, le nouveau dispositif illuminant respecte, sans changement, les paramètres d'illumination appliqués précédemment et qui sont spécifiques au missile.
8. Système selon une des revendications 1 à 7, caractérisé par plusieurs dispositifs d'illumination utilisables indépendamment les uns des autres.
9. Système selon la revendication 8, caractérisé en ce que les zones illuminées par les dispositifs d'illumination se complètent et chevauchent.
10. Système selon une des revendications 3 à 9, caractérisé en ce que, en cas de présence de plusieurs cibles, un dispositif d'illumination individuel est prévu pour chaque cible et que le dispositif de poursuite est commandé de manière qu'il détermine, indépendamment d'autres dispositifs de localisation de cible, de façon cyclique, dans l'ordre, les positions actuelles des cibles illuminées.
11. Système selon une des revendications précédentes, caractérisé par un calculateur de commande pour dériver des grandeurs de réglage pour le ou les dispositifs d'illumination à partir des informations fournies sur la ou les cibles par les dispositifs de localisation.
12. Système selon une des revendications précédentes, caractérisé en ce que la forme du diagramme directionnel est variable.
13. Système selon une des revendications précédentes, caractérisé en ce que le dispositif d'illumination remplit des tâches d'émetteur leurre dans des pauses d'illumination.
EP83107521A 1982-08-14 1983-07-30 Système de guidage semi-actif pour un missile à tête chercheuse Expired EP0100979B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19823230267 DE3230267A1 (de) 1982-08-14 1982-08-14 Halbaktives leitsystem fuer einen zielsuchenden, lenkbaren flugkoerper
DE3230267 1982-08-14

Publications (2)

Publication Number Publication Date
EP0100979A1 EP0100979A1 (fr) 1984-02-22
EP0100979B1 true EP0100979B1 (fr) 1988-06-22

Family

ID=6170862

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83107521A Expired EP0100979B1 (fr) 1982-08-14 1983-07-30 Système de guidage semi-actif pour un missile à tête chercheuse

Country Status (7)

Country Link
US (1) US4558836A (fr)
EP (1) EP0100979B1 (fr)
DE (2) DE3230267A1 (fr)
DK (1) DK159860C (fr)
ES (1) ES8404504A1 (fr)
GR (1) GR77566B (fr)
NO (1) NO156389C (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6145784A (en) * 1997-08-27 2000-11-14 Trw Inc. Shared aperture dichroic active tracker with background subtraction
DE102004029343B4 (de) * 2004-06-17 2009-04-30 Diehl Bgt Defence Gmbh & Co. Kg Zielführungsvorrichtung für ein Fluggerät
FR2885213B1 (fr) * 2005-05-02 2010-11-05 Giat Ind Sa Procede de commande d'une munition ou sous-munition, systeme d'attaque, munition et designateur mettant en oeuvre un tel procede
US7767945B2 (en) 2005-11-23 2010-08-03 Raytheon Company Absolute time encoded semi-active laser designation
US7575191B2 (en) * 2006-01-27 2009-08-18 Lockheed Martin Corporation Binary optics SAL seeker (BOSS)
US8390802B2 (en) * 2009-05-13 2013-03-05 Bae Systems Information And Electronic Systems Intergration Inc. Distributed array semi-active laser designator sensor
US8344302B1 (en) * 2010-06-07 2013-01-01 Raytheon Company Optically-coupled communication interface for a laser-guided projectile
FR3050814B1 (fr) * 2016-04-29 2019-06-07 Airbus Helicopters Procede et dispositif d'aide a la visee pour le guidage laser d'un projectile

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2162983A1 (de) * 1971-12-18 1973-06-20 Fusban Ulrich Mit zielsucheinrichtung ausgestattetes lenkflugkoerpersystem

Family Cites Families (13)

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Publication number Priority date Publication date Assignee Title
US3001186A (en) * 1951-08-17 1961-09-19 Otto J Baltzer Missile guidance system
US3116039A (en) * 1956-02-29 1963-12-31 Goldberg Michael Method of and system for guiding a missile
GB1064150A (en) * 1963-01-07 1967-04-05 British Aircraft Corp Ltd Improvements relating to target acquisition systems
GB1021867A (en) * 1963-10-28 1966-03-09 English Electric Aviat Ltd Improvements relating to visual identification of aircraft
DE1249124B (de) * 1965-03-26 1967-08-31 Albiswerk Zurich A G Zurich (Schweiz) Verfahren und Einrichtung zum Lenken eines ersten bewegten Korpers m Bezug auf einen zweiten bewegten Korper
FR1454451A (fr) * 1965-08-04 1966-02-11 Comp Generale Electricite Dispositif de pointage combiné radar-laser
US3799676A (en) * 1972-05-26 1974-03-26 Us Air Force Optical tracking system
GB1406707A (en) * 1972-07-03 1975-09-17 British Aircraft Corp Ltd Object recognition
US4143835A (en) * 1972-09-12 1979-03-13 The United States Of America As Represented By The Secretary Of The Army Missile system using laser illuminator
US3974383A (en) * 1975-02-03 1976-08-10 Hughes Aircraft Company Missile tracking and guidance system
US4406429A (en) * 1978-04-13 1983-09-27 Texas Instruments Incorporated Missile detecting and tracking unit
DE2922592C2 (de) * 1979-06-02 1981-11-26 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Verfahren zur Abwehr von Flugkörpern
DE2947492C2 (de) * 1979-11-24 1983-04-28 Licentia Patent-Verwaltungs-Gmbh, 6000 Frankfurt Lenkverfahren für Flugkörper

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2162983A1 (de) * 1971-12-18 1973-06-20 Fusban Ulrich Mit zielsucheinrichtung ausgestattetes lenkflugkoerpersystem

Also Published As

Publication number Publication date
DK159860C (da) 1991-05-13
EP0100979A1 (fr) 1984-02-22
US4558836A (en) 1985-12-17
NO156389B (no) 1987-06-01
ES524887A0 (es) 1984-05-01
GR77566B (fr) 1984-09-24
DK159860B (da) 1990-12-17
DE3377155D1 (en) 1988-07-28
NO156389C (no) 1987-09-09
DK355783A (da) 1984-02-15
ES8404504A1 (es) 1984-05-01
DE3230267A1 (de) 1984-02-16
DK355783D0 (da) 1983-08-04
NO832910L (no) 1984-02-15

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