EP0670465A1 - Sekundärziele benutzendes Flugkörperlenkungssystem - Google Patents

Sekundärziele benutzendes Flugkörperlenkungssystem Download PDF

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Publication number
EP0670465A1
EP0670465A1 EP95102659A EP95102659A EP0670465A1 EP 0670465 A1 EP0670465 A1 EP 0670465A1 EP 95102659 A EP95102659 A EP 95102659A EP 95102659 A EP95102659 A EP 95102659A EP 0670465 A1 EP0670465 A1 EP 0670465A1
Authority
EP
European Patent Office
Prior art keywords
missile
detector
target
launcher
rifle
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Withdrawn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
EP95102659A
Other languages
English (en)
French (fr)
Inventor
Itzhak Marom
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
State of Israel
Original Assignee
Rafael Advanced Defense Systems Ltd
State of Israel
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, State of Israel filed Critical Rafael Advanced Defense Systems Ltd
Publication of EP0670465A1 publication Critical patent/EP0670465A1/de
Withdrawn legal-status Critical Current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
    • F41G7/226—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

Definitions

  • the present invention relates to systems for improving the accuracy of missiles and, in particular, in improving the accuracy of short range missiles which are typically fired from a shoulder-held launcher.
  • More sophisticated missiles feature a mechanism which allows the missile trajectory to be adjusted during flight.
  • Illustrative of these guided missiles is the TOW missile which remains connected via a thin wire to the launcher throughout its flight to the target. Navigational commands transmitted through the wire make it possible to carry out trajectory corrections of the missile during flight.
  • a disadvantage of such a system is the complexity of the missiles and launchers which results from the need to accommodate the long wire connection between the missile and the launcher.
  • Other guided missile systems include a radio or electro-optical receiver in the missile which is able to receive navigational commands transmitted to it wirelessly during flight from the launch site.
  • a disadvantage of such systems is that they require the use of expensive optics and electronics to maintain communication between the missile and the launch site.
  • a missile homing system for adjusting missile trajectory during flight toward a target, comprising: (a) a missile; (b) at least one secondary target propelled toward the target; (c) detecting means located on the missile for detecting the direction of the at least one secondary target; (d) processing means located on the missile for determining trajectory adjustment based on the detection of the direction of the at least one secondary target; and (e) steering means for adjusting the trajectory of the missile toward the target based on the determined trajectory adjustment.
  • the secondary targets are bullets, or projectiles, preferably tracer bullets and the detector is a visible light detector.
  • the bullets are fired by a rifle, automatic rifle or machine gun, which is in the vicinity of, or which is connected to, the missile launcher.
  • the present invention successfully addresses the shortcomings of the presently known configurations by providing the ability of effecting mid-course trajectory corrections of a short range missile without the need for a complex aiming system and without the need for transmission of commands to the missile and without the need for a physical connection between the missile and the launcher.
  • the missile operator launches the missile in the direction of the intended target.
  • the missile operator or another person in the vicinity of the missile operator, fires secondary targets, such as tracer bullets, carefully aimed at the intended target of the missile.
  • the tracer bullets which travel at speeds which are much larger than those of the missile, are detected by a detector located in the missile. Based on the detected tracer bullets, adjustments are automatically made to the missile trajectory so as to cause the missile to home in on the destination of the secondary targets, i.e., on the intended target of the missile.
  • the present invention is of a system which can be used to increase the accuracy of missiles, especially those of the short range type which are normally fired using a shoulder-held launcher.
  • the system includes a missile 10 which is launched from a suitable missile launcher 12 in the direction of a target 14 .
  • While missile 10 is in flight, at least one, preferably a plurality of, secondary targets, such as bullets or tracer bullets 16 , aimed at target 14 , are made to pass by missile 10 .
  • Secondary targets e.g., tracer bullets 16
  • rifle 18 is physically connected in some suitable fashion to missile launcher 12 , as indicated by the broken line in the Figure.
  • Missile 10 includes detecting means 20 for detecting the direction at various times of secondary targets 16 .
  • Any suitable detecting means 20 may be used including, but not limited to, a visible light detector and/or an infrared detector, with the former being particularly useful when used in conjunction with tracer bullets serving as secondary targets 16 .
  • Detecting means 20 may, for example, be in the form of a four-quadrant detector or a matrix detector, such as a CCD detector, among others.
  • Missile 10 further includes processing means 22 for determining trajectory adjustment based on the detection of the direction at various times of secondary targets 16 .
  • missile 10 includes steering means 24 for adjusting the trajectory of missile 10 toward target 14 based on the trajectory adjustment determined by processing means 22 which, in turn, is based on the detected direction at various times of secondary targets 16 .
  • the processing of the detected direction of secondary targets 16 and the resultant trajectory corrections may be carried out in any suitable way including, but not limited to, through use of proportional navigation or pure pursuit (hound and hare) techniques.

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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)
EP95102659A 1994-03-02 1995-02-24 Sekundärziele benutzendes Flugkörperlenkungssystem Withdrawn EP0670465A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IL10883194 1994-03-02
IL10883194A IL108831A0 (en) 1994-03-02 1994-03-02 Missile homing system using secondary targets

Publications (1)

Publication Number Publication Date
EP0670465A1 true EP0670465A1 (de) 1995-09-06

Family

ID=11065874

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95102659A Withdrawn EP0670465A1 (de) 1994-03-02 1995-02-24 Sekundärziele benutzendes Flugkörperlenkungssystem

Country Status (2)

Country Link
EP (1) EP0670465A1 (de)
IL (1) IL108831A0 (de)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3116039A (en) * 1956-02-29 1963-12-31 Goldberg Michael Method of and system for guiding a missile
US3835749A (en) * 1962-10-26 1974-09-17 P Joneaux Weapon launching rockets and method to use the same
GB2029943A (en) * 1978-09-13 1980-03-26 Rheinmetall Gmbh Method of attacking ground targets
FR2657686A1 (fr) * 1990-01-26 1991-08-02 Thomson Brandt Armements Arme anti-char de courte portee et son procede d'utilisation.

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3116039A (en) * 1956-02-29 1963-12-31 Goldberg Michael Method of and system for guiding a missile
US3835749A (en) * 1962-10-26 1974-09-17 P Joneaux Weapon launching rockets and method to use the same
GB2029943A (en) * 1978-09-13 1980-03-26 Rheinmetall Gmbh Method of attacking ground targets
FR2657686A1 (fr) * 1990-01-26 1991-08-02 Thomson Brandt Armements Arme anti-char de courte portee et son procede d'utilisation.

Also Published As

Publication number Publication date
IL108831A0 (en) 1997-02-18

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