EP4587780A1 - Système de missile tactique électro-optique - Google Patents

Système de missile tactique électro-optique

Info

Publication number
EP4587780A1
EP4587780A1 EP23864859.6A EP23864859A EP4587780A1 EP 4587780 A1 EP4587780 A1 EP 4587780A1 EP 23864859 A EP23864859 A EP 23864859A EP 4587780 A1 EP4587780 A1 EP 4587780A1
Authority
EP
European Patent Office
Prior art keywords
missile
image sensor
image
seeker
target
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.)
Pending
Application number
EP23864859.6A
Other languages
German (de)
English (en)
Other versions
EP4587780A4 (fr
Inventor
Shimon ZEIERMAN
Tzachi LEVIN
Barak TUR
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.)
Rafael Advanced Defense Systems Ltd
Original Assignee
Rafael Advanced Defense Systems Ltd
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 Rafael Advanced Defense Systems Ltd filed Critical Rafael Advanced Defense Systems Ltd
Publication of EP4587780A1 publication Critical patent/EP4587780A1/fr
Publication of EP4587780A4 publication Critical patent/EP4587780A4/fr
Pending legal-status Critical Current

Links

Classifications

    • 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
    • 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
    • F41G7/20—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
    • F41G3/00—Aiming or laying means
    • F41G3/06—Aiming or laying means with rangefinder

Definitions

  • the present invention relates to missile systems and, in particular, it concerns an electro-optical tactical missile system.
  • the present invention is an electro-optical tactical missile system.
  • a missile system comprising: (a) a sight having a targeting image sensor with a first iFOV, the sight being configured to employ the targeting image sensor to obtain a reference image including a target, and to receive an input from an operator designating the target within the reference image, thereby defining a desired point of impact; (b) a missile for launching towards the target, the missile having a seeker image sensor having a second iFOV that is at least three times wider in each of two dimensions than the iFOV of the targeting image sensor, the missile further having a processing system including at least one processor and data storage, the processing system being in data communication with the seeker image sensor, and in data communication prior to launch with the sight, the processing system being configured to: (i) receive the reference image sampled by the targeting image sensor and the desired point of impact within the reference image; (ii) receive sampled images from the seeker image sensor during flight of the missile; (iii) perform image registration between the reference image and the
  • the data communication between the processing system and the sight is through a wireless communications link prior to launch of the missile.
  • the targeting image sensor has an angular pixel resolution at least one order of magnitude higher than the seeker image sensor.
  • the seeker image sensor is rigidly mounted to a body of the missile.
  • the seeker image sensor is mounted with a gimbal to a body of the missile.
  • the second iFOV is at least three times wider in each dimension than the first iFOV.
  • an angular field of view of the seeker image sensor is at least twice the angular field of view of the targeting image sensor.
  • a method of operating a missile system comprising the steps of: (a) employing a sight associated with a missile launching system, the sight having a targeting image sensor with a first iFOV, to obtain a reference image including a target and designating the target within the reference image, thereby defining a desired point of impact; (b) launching a missile towards the target, the missile having a seeker image sensor having a second iFOV that is at least three times wider in each of two dimensions than the iFOV of the targeting image sensor; (c) during flight of the missile, sampling images from the seeker image sensor; (d) employing a processing system to perform image registration between the reference image and the sampled image, the image registration including down- sampling of the reference image so as to substantially match a resolution of the sampled images; (e) employing the image registration to determine the desired point of impact within the sampled images; and (f) continuously steering the missile towards the desired point of impact.
  • the second iFOV is at least three times wider in each dimension than the first iFOV.
  • the seeker image sensor is rigidly mounted to a body of the missile.
  • the sight is located at the launch location of the missile.
  • FIG. 1 is a schematic representation of an electro- optic al missile according to an embodiment of the present invention
  • FIG. 2 is a schematic representation of an electro-optical missile system including the missile of FIG. 1, constructed and operative according to an embodiment of the present invention
  • FIG. 3 is a flow diagram illustrating operation of the missile of FIG. 1 according to an aspect of the present invention
  • FIGS. 4B (i)-(iv) are a sequence of image from a seeker image sensor of the missile of FIG. 1 from the launch location and from a sequence of subsequent positions during flight of the missile;
  • FIGS. 5A-5D are image pairs showing (ii) a tile generated from a targeting sensor reference image by down sampling, and (i) a corresponding image from FIG. 4B illustrating the result of image registration marked with a dashed line;
  • Each missile also has a processing system 22 including at least one processor 24 and data storage 26, the processing system being in data communication, typically a wired connection, with the seeker image sensor 20, and in data communication, prior to launch, with the sight 14.
  • a processing system 22 including at least one processor 24 and data storage 26, the processing system being in data communication, typically a wired connection, with the seeker image sensor 20, and in data communication, prior to launch, with the sight 14.

Landscapes

  • 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)

Abstract

Un système de missile comprend un viseur ayant un capteur d'image de ciblage pour obtenir une image de référence et recevoir une entrée définissant un point d'impact souhaité, et un missile. Le missile a un capteur d'image autodirecteur ayant un IFOV qui est au moins trois fois plus large dans chaque dimension qu'un IFOV du capteur d'image de ciblage. Un système de traitement du missile reçoit l'image de référence, reçoit des images échantillonnées en provenance du capteur d'image autodirecteur pendant le vol, et effectue un recalage d'images entre l'image de référence et l'image échantillonnée. Le recalage d'images comprend le sous-échantillonnage de l'image de référence de sorte qu'elle corresponde à une résolution des images échantillonnées. Le recalage d'images est utilisé pour déterminer le point d'impact souhaité au sein des images échantillonnées, et le missile est dirigé vers le point d'impact souhaité.
EP23864859.6A 2022-09-13 2023-06-04 Système de missile tactique électro-optique Pending EP4587780A4 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IL296458A IL296458A (en) 2022-09-13 2022-09-13 Electro-optical tactical missile system
PCT/IB2023/055742 WO2024057102A1 (fr) 2022-09-13 2023-06-04 Système de missile tactique électro-optique

Publications (2)

Publication Number Publication Date
EP4587780A1 true EP4587780A1 (fr) 2025-07-23
EP4587780A4 EP4587780A4 (fr) 2025-12-24

Family

ID=90274360

Family Applications (1)

Application Number Title Priority Date Filing Date
EP23864859.6A Pending EP4587780A4 (fr) 2022-09-13 2023-06-04 Système de missile tactique électro-optique

Country Status (3)

Country Link
EP (1) EP4587780A4 (fr)
IL (1) IL296458A (fr)
WO (1) WO2024057102A1 (fr)

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3986682A (en) * 1974-09-17 1976-10-19 The United States Of America As Represented By The Secretary Of The Navy Ibis guidance and control system
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
US7444002B2 (en) * 2004-06-02 2008-10-28 Raytheon Company Vehicular target acquisition and tracking using a generalized hough transform for missile guidance
US7463753B2 (en) * 2004-09-15 2008-12-09 Raytheon Company FLIR-to-missile boresight correlation and non-uniformity compensation of the missile seeker
IL227982B (en) * 2013-08-15 2018-11-29 Rafael Advanced Defense Systems Ltd Missile system with navigation capability based on image processing
US10077972B1 (en) * 2017-07-11 2018-09-18 Bae Systems Information And Electronic Systems Integration Inc. SAL seeker with spatial and temporal sensors
US10663260B2 (en) * 2017-11-20 2020-05-26 Bae Systems Information And Electronic Systems Integration Inc. Low cost seeker with mid-course moving target correction

Also Published As

Publication number Publication date
IL296458A (en) 2024-12-01
WO2024057102A1 (fr) 2024-03-21
EP4587780A4 (fr) 2025-12-24

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