EP0777100A2 - Système d'arme missile - Google Patents

Système d'arme missile Download PDF

Info

Publication number
EP0777100A2
EP0777100A2 EP96119417A EP96119417A EP0777100A2 EP 0777100 A2 EP0777100 A2 EP 0777100A2 EP 96119417 A EP96119417 A EP 96119417A EP 96119417 A EP96119417 A EP 96119417A EP 0777100 A2 EP0777100 A2 EP 0777100A2
Authority
EP
European Patent Office
Prior art keywords
target
image
seeker head
weapon system
correlation
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
EP96119417A
Other languages
German (de)
English (en)
Other versions
EP0777100B1 (fr
EP0777100A3 (fr
Inventor
Mafred Dipl.-Phys. Hiebl
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.)
LFK Lenkflugkoerpersysteme GmbH
Original Assignee
Daimler Benz Aerospace AG
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 Daimler Benz Aerospace AG filed Critical Daimler Benz Aerospace AG
Publication of EP0777100A2 publication Critical patent/EP0777100A2/fr
Publication of EP0777100A3 publication Critical patent/EP0777100A3/fr
Application granted granted Critical
Publication of EP0777100B1 publication Critical patent/EP0777100B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F41G7/2273—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
    • F41G7/2206—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
    • F41G7/2213—Homing guidance systems maintaining the axis of an orientable seeking head pointed at the target, e.g. target seeking gyro
    • 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
    • F41G7/2226—Homing guidance systems comparing the observed data with stored target data, e.g. target configuration data
    • 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

Definitions

  • the invention relates to a missile weapon system with seeker head optics and an instruction processor according to claim 1.
  • Such weapon systems are known per se.
  • the missile is completely on its own after the target search.
  • he is equipped with a gimbal-mounted seeker head camera and with a tracker which, by successive image comparison using a correlation process, pursues its assigned goal until the hit, the seeker head moving completely autonomously after the launch and being uninfluenced.
  • the missile - or its "instruction processor” (alignment processor) - must be given the target to be approached prior to departure, or it must be briefed on this target.
  • a so-called image comparison is used, in which images of the rifle sight are compared and correlated with those of the seeker head.
  • the seeker head now has a considerably smaller field of view than the rifle sight, so it only sees a section of the larger sight image.
  • the alignment processor continuously matches the two images, the comparison being carried out by querying line by line and column by column in the sighting image from the top left corner of the search header image and determining the correlation coefficient or a related criterion for each position . Where the correlation coefficient is at a maximum, the probability that both images are congruent is greatest.
  • the focal length of the viewfinder optics is dimensioned so that a normal tank target at 500 m distance - this is the minimum distance - still fits fully into the picture.
  • this has the disadvantage that the target appears relatively very small in the maximum distance of approximately 4.5 km. (approx. 4 samples).
  • the optical axis of the sight has a distance from the optical axis of the seeker head caused by the carrier (helicopter), that is to say a parallax which is approximately 5 m in height and width. This means that the perspective from the seeker head to the target is different from that from the sight.
  • the alignment processor it is essential that the seeker head and sight optics see the same thing. However, this is not the case if there are foreground or background objects in the image (figure), which is to be addressed as a normal case. However, this significantly worsens the image comparison and leads to a large mistake in the introduction.
  • a missile weapon system is known from US Pat. No. 3,986,682, in which a target is continuously pursued by comparing sight and seeker head images that have been covered by means of a correlation method, the image size of the seeker head optics being chosen to be small from the start.
  • DE 33 34 729 A1 discloses a method for aligning a target seeker head of a self-guided missile, in which an image containing the target and an image generated by the target seeker head are matched to one another with the aid of an image correlation.
  • the present invention has for its object to provide a weapon system of the type mentioned, in which the instruction probability of at least 85% is achieved and guaranteed and the alignment processor is almost undisturbed by residual stabilization errors, the harmonization close to the ground and the search head image in the resolution is improved.
  • an optimal instruction probability can only be achieved if parallax-free images are available. This can be achieved by minimizing the target environment, ie the target environment is not included or is only slightly included in the image comparison.
  • the marker box must be adapted to the size of the target, that is to say reduced or enlarged to such an extent that as little background as possible is contained in the marker box.
  • the marking box is a rectangular frame from the display, which is generated by the processor, and is not fully extended with indicated corners. This is currently square and its size is preset. The shooter can now either enlarge or reduce the marker box using the operator controls, so to speak zoom.
  • the operational status - ie "enlarge” or “reduce” - is communicated to the fire control computer (FCC) on the MIL bus.
  • the FCC Firing Control Computer
  • the FCC calculates the current marking box size from the time the shooter holds the zoom button and the zoom speed, which the FCC communicates to the tracker to set the track box size.
  • the FCC is in the Able to calculate the respective focal length of the seeker head optics and to inform the ammunition on the bus or enter them.
  • the seeker head adjusts its current actual value to the setpoint commanded by the FCC and returns the currently achieved field of view to the FCC for each frame until the FCC determines that the fields of view match.
  • the control loop can be maintained as long as the shooter in turn adjusts the "Operator Controls".
  • the seeker head image is rotationally symmetrical and only the part that lies within an inscribed square can be compared with the sight image section.
  • the sensor ratio must be taken into account geometrically by a factor ⁇ 2
  • this image section must be compared with an section of the search head image of the same size.
  • FCC Fire Control Computer
  • Image filling does not mean that the target must fill the entire image at maximum distance. It is sufficient if a good image comparison is also guaranteed for long-range targets and also the increased vibration levels, to which long-range optics are exposed, in contrast to short-range optics, still permit sufficient detection.

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)
  • Telescopes (AREA)
EP96119417A 1995-12-09 1996-12-04 Système d'arme missile Expired - Lifetime EP0777100B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19546017 1995-12-09
DE19546017A DE19546017C1 (de) 1995-12-09 1995-12-09 Flugkörper-Waffensystem

Publications (3)

Publication Number Publication Date
EP0777100A2 true EP0777100A2 (fr) 1997-06-04
EP0777100A3 EP0777100A3 (fr) 1999-09-01
EP0777100B1 EP0777100B1 (fr) 2002-07-24

Family

ID=7779680

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96119417A Expired - Lifetime EP0777100B1 (fr) 1995-12-09 1996-12-04 Système d'arme missile

Country Status (4)

Country Link
US (1) US5785275A (fr)
EP (1) EP0777100B1 (fr)
DE (2) DE19546017C1 (fr)
ES (1) ES2179146T3 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999051931A1 (fr) * 1998-04-07 1999-10-14 Raytheon Company Systeme de guidage muni d'un autodirecteur a corps fixe et possedant un angle d'observation reglable
FR2830078A1 (fr) * 2001-09-25 2003-03-28 Sagem Procede de guidage d'une roquette
US11965714B2 (en) 2007-02-28 2024-04-23 Science Applications International Corporation System and method for video image registration and/or providing supplemental data in a heads up display

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19828644C2 (de) * 1998-06-26 2001-12-06 Lfk Gmbh Verfahren zum ferngesteuerten Bekämpfen bodennaher und/oder bodengebundener Ziele
DE10158666A1 (de) * 2001-11-28 2003-06-18 Lfk Gmbh Vorrichtung und Verfahren zur autarken Zielführung eines Flugkörpers mit Hilfe außerhalb des Zielpunktes liegender Orientierungsmerkmale
EP1913557B1 (fr) * 2005-06-23 2016-06-01 Israel Aerospace Industries Ltd. Systeme et procede de poursuite d'objets mobiles
IL219639A (en) 2012-05-08 2016-04-21 Israel Aerospace Ind Ltd Remote object tracking
US10212396B2 (en) 2013-01-15 2019-02-19 Israel Aerospace Industries Ltd Remote tracking of objects
IL224273B (en) 2013-01-17 2018-05-31 Cohen Yossi Delay compensation during remote sensor control
DE102022000723A1 (de) * 2022-03-01 2023-09-07 Diehl Defence Gmbh & Co. Kg Vorrichtung zur Zielübergabe

Citations (2)

* 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
DE3334729A1 (de) 1983-09-26 1985-04-11 Siemens AG, 1000 Berlin und 8000 München Verfahren zur ausrichtung eines zielsuchkopfes eines selbstgesteuerten flugkoerpers

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3923273A (en) * 1967-01-30 1975-12-02 Us Navy Aim point correlator
GB1568058A (en) * 1975-11-21 1980-05-21 Emi Ltd Tracking and/or huidance systems
GB2148465B (en) * 1983-10-20 1987-05-28 Nader Dadabhoy Daroga Missile control systems
DE3435634A1 (de) * 1984-09-28 1986-04-10 Diehl GmbH & Co, 8500 Nürnberg Zielerfassungseinrichtung fuer flugkoerper
US5341142A (en) * 1987-07-24 1994-08-23 Northrop Grumman Corporation Target acquisition and tracking system
USH796H (en) * 1989-11-27 1990-07-03 The United States Of America As Represented By The Secretary Of The Army Open loop seeker aiming guiding system
US5274236A (en) * 1992-12-16 1993-12-28 Westinghouse Electric Corp. Method and apparatus for registering two images from different sensors
US5323987A (en) * 1993-03-04 1994-06-28 The Boeing Company Missile seeker system and method

Patent Citations (2)

* 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
DE3334729A1 (de) 1983-09-26 1985-04-11 Siemens AG, 1000 Berlin und 8000 München Verfahren zur ausrichtung eines zielsuchkopfes eines selbstgesteuerten flugkoerpers

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999051931A1 (fr) * 1998-04-07 1999-10-14 Raytheon Company Systeme de guidage muni d'un autodirecteur a corps fixe et possedant un angle d'observation reglable
FR2830078A1 (fr) * 2001-09-25 2003-03-28 Sagem Procede de guidage d'une roquette
WO2003027599A1 (fr) * 2001-09-25 2003-04-03 Sagem Sa Procede de guidage d'une roquette
US11965714B2 (en) 2007-02-28 2024-04-23 Science Applications International Corporation System and method for video image registration and/or providing supplemental data in a heads up display
US12455140B2 (en) 2007-02-28 2025-10-28 Science Applications International Corporation System and method for video image registration and/or providing supplemental data in a heads up display

Also Published As

Publication number Publication date
DE19546017C1 (de) 1997-04-24
US5785275A (en) 1998-07-28
DE59609477D1 (de) 2002-08-29
EP0777100B1 (fr) 2002-07-24
EP0777100A3 (fr) 1999-09-01
ES2179146T3 (es) 2003-01-16

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