EP4113052A1 - Selbstlenkende vorrichtung für rakete - Google Patents

Selbstlenkende vorrichtung für rakete Download PDF

Info

Publication number
EP4113052A1
EP4113052A1 EP22181184.7A EP22181184A EP4113052A1 EP 4113052 A1 EP4113052 A1 EP 4113052A1 EP 22181184 A EP22181184 A EP 22181184A EP 4113052 A1 EP4113052 A1 EP 4113052A1
Authority
EP
European Patent Office
Prior art keywords
phase
target
active
missile
assembly
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.)
Granted
Application number
EP22181184.7A
Other languages
English (en)
French (fr)
Other versions
EP4113052B1 (de
Inventor
Lina MESSAOUDI
Eric Chamouard
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.)
Thales SA
Original Assignee
Thales SA
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 Thales SA filed Critical Thales SA
Publication of EP4113052A1 publication Critical patent/EP4113052A1/de
Application granted granted Critical
Publication of EP4113052B1 publication Critical patent/EP4113052B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • F41G7/2246—Active homing systems, i.e. comprising both a transmitter and a receiver
    • 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
    • F41G7/2206—Homing guidance systems using a remote control station
    • 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
    • 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
    • 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

Definitions

  • the invention relates to missiles equipped with active seekers, that is to say having the ability to transmit and receive a signal.
  • the mission of the seekers can be anti-aircraft or anti-ship, and the present invention requires that the target have an active radar carried.
  • the purpose of a seeker integrated into a missile is to allow the missile 1 to guide itself on its target 2 in order to be able to intercept it, as illustrated in [ Fig. 1 ].
  • the missile 1 is based on the information delivered by a fire control radar, placed on the ground or on a nearby aircraft.
  • missile 1 uses the information delivered by seeker 3, which is integrated into the front of missile 1, as shown in [ Fig.2 ].
  • the missile 1 relies on the information from the fire control radar (ground radar 4 and/or radar carried 5 on the firing plane of the missile 1).
  • This radar emits a wave and, by receiving the latter's reflection on the target 2, can estimate the information concerning the target 2, i.e. distance, speed and angular direction.
  • This information will be transmitted to the missile 1, via a data link or at the time of firing, and constitute the target designation, denoted DO.
  • DO the target designation
  • the latter will be delivered with more or less good precision, depending on the quality of the fire control radar (range of uncertainty of the DO).
  • This target designation can be refreshed during the flight.
  • the target designation includes parameters representative of the range of target 2 from missile 1, the relative velocity of target 2 relative to missile 1, and the angular direction of target 2 relative to the direction of travel. of missile 1.
  • the fire control radar is jammed which implies that the missile can be fired without a DO target designation or with a degraded DO target designation, i.e. without information on the distance and/or the speed of the target.
  • the missile is guided using information from the homing device.
  • the operation of a seeker device 3 comprises three phases, as follows.
  • a first so-called standby phase during which the homing device 3 is deactivated, and therefore does not emit a signal.
  • a second phase during which the homing device 3 is activated and scans the area of the target designation (distance/relative speed/angular direction of the target, or the targets, 2 to be detected. At the end of the second phase, it selects target 2 to pursue.
  • missile 1 is fired without distance information from target 2, the seeker is activated as soon as possible and remains so until impact, which leads to a long operating time which may be greater than that for which it is dimensioned, implying a risk of its deactivation when approaching target 2.
  • this may also have the consequence of increasing the time taken by the seeker 3 to scan the target designation DO, which depends on the magnitude of the uncertainties of the domain of the target designation DO. Also, the duration of this scanning or research phase can potentially be dimensioning.
  • the seeker 3 must be activated for a long time, which poses problems of energy consumption, the cell or battery of the missile 1 being limited.
  • An object of the invention is to overcome the problems cited above, and in particular to make it possible to improve the duration of use of a seeker, by limiting its consumption.
  • Such a system makes it possible to improve the duration of use of a seeker, by limiting its consumption, and to guarantee the full performance of the missile, including when the DO is degraded.
  • the use of the passive assembly makes it possible to reduce the operating time of the active part, this being likely to reduce the warning to the target defense system (electronic system of the detector type and jammer, defensive manoeuvre, etc. if equipped.
  • the computer is configured to, during the third tracking phase, when the power of the signal received by the active assembly is greater than an autoguiding threshold, transmit guidance information to a control unit of the missile, for terminal guidance on target.
  • the missile has information on the direction, speed and acceleration of the target which are refreshed at a very high rate (of the order of ten ms).
  • the active assembly comprises at least one transmitter/receiver RF antenna.
  • this active RF device will make it possible to estimate the direction, speed and acceleration of the target
  • the passive assembly includes at least one receiver RF antenna and/or one electro-optical sensor.
  • this passive set will make it possible to estimate the direction of the target.
  • the passive assembly is arranged around the periphery of the seeker device.
  • the passive set not being positioned on the same volume as the active device
  • the seeker device 3 comprises an active assembly 6 comprising at least one active sensor 6a configured to transmit and receive signals to detect a target 2, with active radar carried, in a target designation domain DO corresponding to intervals of values of distance of target 2 from homing device 3, speed of target 2 from device 3, and angular direction of target 2 from the direction of movement of device 3.
  • the seeker device 3 also comprises a passive assembly 7 comprising at least one passive sensor 7a configured to receive detection signals from the target 2, and a transmission/reception module 8 of high-frequency signals.
  • the seeker device 3 is also provided with a module 9 for transposition of a high frequency signal into a low frequency signal, and with a module 10 for analog/digital conversion and digital/analog conversion.
  • the homing device 3 measures the elevation and bearing deviations of the target 2, among others, which it delivers to the missile 1.
  • the uncertainty distance associated with these deviation measurements is defined by a standard deviation.
  • the autoguiding distance corresponds to the distance between the missile 1 and the target 2 from which this standard deviation is less than a threshold.
  • This threshold is defined by the missile manufacturer, to ensure, from this distance, the capacity of the missile 1 to reach the target 2 and which depends on its time constant and on the relative speed of the missile/target.
  • the missile self-tests correspond to the electronic operations aimed at ensuring that the functions of the missile are operational ("Built In Test" in English).
  • the homing device 3 comprises conventional elements 15 such as a waveform generation device, power supplies, a pointing management device for the active assembly.
  • Fig.5 represents the passive assembly 7, comprising at least one passive sensor 7a, arranged either in the plane of the active assembly 6, or around the periphery of the envelope of the seeker device 6.
  • the coverage of the antennas is not optimal in the missile axis.
  • trajectory formation a maneuver, for example aimed at pointing the missile axis in another direction
  • trajectory formation is necessary in order to increase the coverage of the active set 6 in the direction of target 2.
  • this trajectory formation consists in maintaining the direction of the speed vector of the missile 1 such that the target 2 is in the coverage of the active set 6.
  • Fig.7 illustrates the operation of the passive assembly which makes it possible to estimate the angular direction of target 2, from the reception of the wave emitted by the active radar carried by target 2.
  • the passive sensors 7a of the passive assembly 7 which can have an angular precision greater than that of the angular direction of the objective designation DO.
  • the passive sensors 7a deliver information on the angular direction of the target 2 associated with an angular precision domain.
  • the passive set 7 (grey rectangle) will give a domain where the target 2 is located that is more precise than that which was provided by the fire control device (white rectangle). This reduced area can be traveled from faster (or more efficient) way by the antenna of the homing device 3.
  • this range of angular precision is less than or equal to the instantaneous angular aperture of the active assembly 6, which avoids sweeping angularly .
  • the passive assembly 7 may have processing enabling it to estimate the distance of the target 2 (pseudo-distance) with greater or lesser precision (depending on the quality of the passive sensors 7a). This distance can be estimated when the power level received from target 2 is greater than a defined threshold.
  • Fig.10 illustrates the operation of the active assembly 6 which makes it possible to estimate the distance, the relative speed and the angular direction of the target 2.
  • the active assembly 6 is configured to scan the angular domain and thus cover an area of the space greater than its instantaneous angular aperture which is the aperture it would have in the absence of scanning means.
  • the emission of signals by the active assembly 6 causes thermal heating of the active assembly 6, and therefore of the seeker device 3, which has no cooling source.
  • the use of the active set 6 is therefore limited.
  • the computer 11 deactivates the active assembly 6, the first standby phase being between the firing of the missile 1 and a first distance D from the target equaling an autoguiding distance Dautoguiding of the missile increased of a maximum uncertainty distance value Dmax, or between the firing of missile 1 and the end of the self-tests of seeker device 3.
  • the autoguiding device 3 has a domain of uncertainty of the distance from the target 2, in which the real distance from the target 2 is found. research phase, is done when the distance separating the missile 1 from the target 2 becomes less than the first distance D.
  • FIG.11 schematically illustrates the operation of the homing device 3 during the transition between the first standby phase and the second search phase, according to one aspect of the invention.
  • the computer 11 alternately activates and deactivates the active assembly 6, the second phase succeeding the first phase, and ending when the power of the signal received by the active assembly 6, when it is activated, is greater than a target detection power threshold.
  • the duration Da of an activation of the active assembly 6, also called recurrence, is defined as the period during which the seeker 3 emits an impulse and receives the signal coming from the target 2 to analyze it and estimate the characteristics (distance, speed, angular direction).
  • the computer 11 is configured to, during the third so-called tracking phase, when the power of the signal received by the active assembly 6 is greater than an autoguiding threshold, transmit guidance information to a control unit of the missile 1, for terminal guidance on target 1.
  • the active assembly 6 comprises at least one transmitter/receiver RF antenna, and/or comprises at least one receiver RF antenna and/or one electro-optical sensor.

Landscapes

  • 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)
EP22181184.7A 2021-07-01 2022-06-27 Selbstlenkende vorrichtung für rakete Active EP4113052B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR2107141A FR3124855B1 (fr) 2021-07-01 2021-07-01 Dispositif autodirecteur pour missile.

Publications (2)

Publication Number Publication Date
EP4113052A1 true EP4113052A1 (de) 2023-01-04
EP4113052B1 EP4113052B1 (de) 2024-02-14

Family

ID=77913218

Family Applications (1)

Application Number Title Priority Date Filing Date
EP22181184.7A Active EP4113052B1 (de) 2021-07-01 2022-06-27 Selbstlenkende vorrichtung für rakete

Country Status (2)

Country Link
EP (1) EP4113052B1 (de)
FR (1) FR3124855B1 (de)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2590359A1 (fr) * 1985-11-18 1987-05-22 Aerospatiale Systeme pour le guidage automatique d'un missile et missile pourvu d'un tel systeme
US6806823B1 (en) * 2003-10-20 2004-10-19 The United States Of America As Represented By The Secretary Of The Army Passive radar detector for dualizing missile seeker capability
US20170268852A1 (en) * 2016-03-16 2017-09-21 Diehl Defence Gmbh & Co. Kg Method for steering a missile towards a flying target

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2590359A1 (fr) * 1985-11-18 1987-05-22 Aerospatiale Systeme pour le guidage automatique d'un missile et missile pourvu d'un tel systeme
US6806823B1 (en) * 2003-10-20 2004-10-19 The United States Of America As Represented By The Secretary Of The Army Passive radar detector for dualizing missile seeker capability
US20170268852A1 (en) * 2016-03-16 2017-09-21 Diehl Defence Gmbh & Co. Kg Method for steering a missile towards a flying target

Also Published As

Publication number Publication date
FR3124855A1 (fr) 2023-01-06
FR3124855B1 (fr) 2023-10-06
EP4113052B1 (de) 2024-02-14

Similar Documents

Publication Publication Date Title
EP2092366B1 (de) Verfahren zur schätzung der höhe eines ballistischen projektils
US20200064443A1 (en) Method of identifying and neutralizing low-altitude unmanned aerial vehicle
US6770865B2 (en) Systems, methods, and devices for detecting light and determining its source
FR2728333A1 (fr) Dispositif d'autodefense contre des missiles
EP0485253A1 (de) Millimeterwellenradarsystem zur Führung eines mobilen bodengebundenen Roboters
FR2607585A1 (fr) Mine a tir indirect d'attaque de vehicule blinde
WO2021089938A1 (fr) Procede de poursuite d'un objet spatial a l'aide de systemes radar et lidar embarques
FR2729764A1 (fr) Radar a champ angulaire instantane important et haut pouvoir instantane de resolution angulaire, notamment pour autodirecteur de missile
EP1108970A1 (de) Vorrichtung zur eindeutigen Messung des Rollwinkels eines Geschosses und Verwendung zur Korrektur der Flugbahn eines Geschosses
FR2514486A1 (fr) Dispositif de combat contre des buts, tels que blindes ou analogues, au moyen d'une munition pointable sur le but
US7044044B2 (en) Radio frequency triggered directed energy munition
EP4113052B1 (de) Selbstlenkende vorrichtung für rakete
EP2472285B1 (de) Verfahren zur Verbesserung der Leistungen eines Radars bei Vorhandensein von diffusen zurückgestreuten Echos
FR2969305A1 (fr) Procede et systeme de detection d'un train d'impulsions electromagnetiques, dispositif de guidage electromagnetique d'une munition vers une cible comprenant un tel systeme de detection
US11435165B2 (en) Narrow band antenna harmonics for guidance in multiple frequency bands
FR2781043A1 (fr) Procede et dispositif de brouillage d'une munition guidee en phase finale
USH205H (en) Wide bandwidth radar having improved signal to clutter response characteristics
EP3654057B1 (de) Optimierungsverfahren zum ausrichten einer antenne eines flugzeug-radarsystems
Paleologue Active infrared systems: possible roles in ballistic missile defense?
EP0809084B1 (de) Vorrichtung zur Rollwinkelbestimmung eines Flugkörpers, insbesondere einer Munition
WO1996039611A1 (en) Range determination apparatus
EP2161591A1 (de) Verfahren und System zur Erkennung von Schussabfeuerungen
EP0650026B1 (de) Verfahren zum Betrieb eines im Vergleich zum Zielerfassungssystem versetzten Waltensystems und Gesamtheit dieser Systeme zur Durchführung des Verfahrens
EP0013195A1 (de) Luft-Boden-Entfernungsradar für ein Bordfeuerleitsystem und Verwendung eines solchen Radars bei einem Feuerleitsystem
EP1260785B1 (de) Passiver Doppler-Annäherungszünder

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20230421

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230529

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

RIC1 Information provided on ipc code assigned before grant

Ipc: F41G 7/00 20060101ALI20230822BHEP

Ipc: F41G 7/22 20060101AFI20230822BHEP

INTG Intention to grant announced

Effective date: 20230912

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

RAP3 Party data changed (applicant data changed or rights of an application transferred)

Owner name: THALES

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602022001937

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D