EP0401693B1 - Verfahren zum Verbessern der Treffergenauigkeit eines gesteuerten Flugkörpers - Google Patents

Verfahren zum Verbessern der Treffergenauigkeit eines gesteuerten Flugkörpers Download PDF

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Publication number
EP0401693B1
EP0401693B1 EP90110415A EP90110415A EP0401693B1 EP 0401693 B1 EP0401693 B1 EP 0401693B1 EP 90110415 A EP90110415 A EP 90110415A EP 90110415 A EP90110415 A EP 90110415A EP 0401693 B1 EP0401693 B1 EP 0401693B1
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EP
European Patent Office
Prior art keywords
path
missile
target
disturbances
extrapolation
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 - Lifetime
Application number
EP90110415A
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German (de)
English (en)
French (fr)
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EP0401693A1 (de
Inventor
Peter Dr. Sundermeyer
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.)
Diehl Verwaltungs Stiftung
Original Assignee
Diehl GmbH and Co
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Filing date
Publication date
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Publication of EP0401693A1 publication Critical patent/EP0401693A1/de
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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

Definitions

  • the invention relates to a method according to the preamble of claim 1.
  • a missile which is intended to fly to a specific target will be equipped with a seeker head which is capable of identifying the target itself and generating guide signals for the pursuit of this target after the target perception, as in DE-A1- 33 03 763, described in DE-A1-15 78 299 or in DE-A1-28 30 502.
  • This has the advantage of tracking the missile into the target position of the target point by regulating the influences of path disturbances, in particular air currents acting transversely to the trajectory, even if the target performs evasive maneuvers.
  • a path advance specified in the control program can be provided by switching the squint angle during the remaining time of the target approach.
  • the target point is determined by reconnaissance means arranged outside the missile with transmission of target and / or correction information to the projectile already in the approach.
  • Fixed orbital data for stationary targets can also be corrected as a function of the missile-related path deviations of the missile.
  • Such an autonomous missile with control that does not seek a target along a preprogrammed or externally predetermined trajectory is equipped for navigation with inertial systems or corresponding sensors which provide the current actual position and thus the deviation from the known target trajectory in order to provide the missile's autopilot with this error information Food. This causes a real trajectory to the specified target point via the missile positioning system, despite disturbances acting transversely to the trajectory (such as air currents in particular).
  • an additional engine acting in the longitudinal direction is fired or activated, for example, only shortly before the target hits.
  • the invention has for its object to provide a method of the type mentioned, with which a target control of a fixed or a movable target with high accuracy is possible without the missile is equipped with a seeker head, a high accuracy is also achieved , if the programmed flying missile is affected by path disturbances such as strong ground winds.
  • the final phase path reserve provided according to this solution is therefore of a different nature than the previously known squint angle change in order to achieve a more favorable hit position, controlled from the sensor-based approach to the target. Rather, in the present solution it is a question of compensating the lateral forces acting on the trajectory, which can be determined on board the missile via the control deviation of the target trajectory, in their influence on the changed longitudinal velocity of the missile in such a way that before or at least during the final phase acceleration the missile is forced to change orbit contrary to the resulting path shift.
  • the flight path ahead can be calculated in advance in an orbital extrapolation model operated on board the missile in accordance with the respective ideal target position and the current actual position of the missile, taking into account also the influences of other flight condition variables.
  • the target path correction in the sense of reducing this error is then derived from the resultant hit error.
  • a path extrapolation can expediently be repeated in a plurality of iterations.
  • the trajectory extrapolation carried out in several iterations preferably takes into account the future acceleration profile of the missile, so that, including future trajectory disturbances and taking current external trajectory disturbances into account, a target trajectory results with a minimal hit error.
  • the target path optimized in this way serves as a reference or target specification for an autopilot of the missile.
  • a missile does not have a seeker head because, for example, this should be saved for cost reasons, or because the seeker head would not be suitable for recognizing the target to be combated, or because the geodetic location of the target to be combated is known from prior clarification, which is particularly important for stationary targets such as bridges, buildings or the like. the case is, the missile can only move along a programmed trajectory to the target to be fought. It is assumed that the programmed flying missile both its ideal target path, which leads it to the target to be fought, from pre-programmed data or by transmission via a so-called. Data-link knows, and also has sensors and / or an inertial navigation unit that delivers the actual position to the missile. This situation is shown schematically in a block diagram in FIG.
  • a web extrapolation model 10 is closed with a control unit 12 a self-contained system connected, which is indicated by the two arrows 14 and 16.
  • the web extrapolation model 10 has two inputs 18 and 20 and one output 22.
  • the input 18 is connected to the output 24 of a reference unit 26, which is indicated by the arrow 28.
  • the reference unit 26 has an input 30 through which data preprogrammed into the reference unit 26 is input.
  • the output 22 of the orbit extrapolation model 10 is connected to an input 32 of an autopilot 34, which is illustrated by the connecting line 36.
  • the autopilot 34 has a second input 38 and an output 40, the output 40 of the autopilot 34 being connected to an actuating system 42.
  • the control system 42 is connected to the missile dynamics illustrated by block 44.
  • the output 46 of the missile dynamics 44 represents the trajectory of the missile. This trajectory is characterized by the trajectory disturbances indicated by the arrow 48, which are, for example, gusts of wind, ground wind or the like. acts, influences.
  • Sensors 50 serve to detect the flight path or the flight path disturbances, the output 52 of the sensors 50 being connected to the second input 38 of the autopilot 34.
  • the output 52 of the sensors 50 is connected to an inertial navigation unit 54, at the output 56 of which the actual position of the missile is given.
  • the actual position of the missile is entered through the input 20 of the orbital extrapolation model 10 and the ideal target path of the missile is entered through the input 18 of the orbital extrapolation model 10.
  • the output 22 of the orbit extrapolation model 10 represents the target path of the missile, while the arrow 14 between the orbit extrapolation model 10 and the control unit 12 represents the hit error.
  • the autopilot 34 and the positioning system can be used 42 to influence the missile dynamics so that the real trajectory of the missile despite the external disturbances - which are indicated by the arrow 48 - leads to the target to be combated.
  • the target path of the missile which is indicated by the connecting line 36 between the orbit extrapolation model 10 and the autopilot 34 in FIG. 1
  • a path reserve is provided, which compensates for the error sketched for the horizontal plane in FIG. 2 by trajectory disturbances (see arrow 48 in FIG. 1).
  • the flight path ahead is calculated in advance according to the ideal target position (input 18 of the rail extrapolation model 10 in FIG. 1) and according to the current actual position (input 20 of the rail extrapolation model 10 in FIG. 1), and according to further flight state variables.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
EP90110415A 1989-06-08 1990-06-01 Verfahren zum Verbessern der Treffergenauigkeit eines gesteuerten Flugkörpers Expired - Lifetime EP0401693B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3918701 1989-06-08
DE3918701A DE3918701A1 (de) 1989-06-08 1989-06-08 Verfahren zur verbesserung der treffgenauigkeit eines programmiert fliegenden flugkoerpers

Publications (2)

Publication Number Publication Date
EP0401693A1 EP0401693A1 (de) 1990-12-12
EP0401693B1 true EP0401693B1 (de) 1994-11-17

Family

ID=6382343

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90110415A Expired - Lifetime EP0401693B1 (de) 1989-06-08 1990-06-01 Verfahren zum Verbessern der Treffergenauigkeit eines gesteuerten Flugkörpers

Country Status (3)

Country Link
EP (1) EP0401693B1 (enrdf_load_stackoverflow)
DE (2) DE3918701A1 (enrdf_load_stackoverflow)
ES (1) ES2064529T3 (enrdf_load_stackoverflow)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4300761A1 (de) * 1993-01-14 1994-07-21 Erno Raumfahrttechnik Gmbh Vorrichtung zur Steuerung
DE10030036B4 (de) * 2000-06-17 2014-07-17 Eads Deutschland Gmbh Fahrzeug-Steuerungssystem zur Bahnsteuerung unter Berücksichtigung einer das Fahrzeug beeinflussenden Strömung sowie ein Verfahren zur Erzeugung einer Bahn-Trajektorie
DE102010032281A1 (de) * 2010-07-26 2012-01-26 Diehl Bgt Defence Gmbh & Co. Kg Verfahren zum Steuern eines durch ein Triebwerk angetriebenen Lenkflugkörpers

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3303763A1 (de) * 1983-02-04 1984-08-09 Diehl GmbH & Co, 8500 Nürnberg Verfahren zur zielansteuerung eines projektils und zum bestimmen dessen ballistischer flugbahn sowie vorrichtungen zum ausueben der verfahren
US4522356A (en) * 1973-11-12 1985-06-11 General Dynamics, Pomona Division Multiple target seeking clustered munition and system
DE1815727C1 (de) * 1968-12-19 1985-10-31 Fried. Krupp GmbH Krupp Atlas-Elektronik Bremen, 2800 Bremen Verfahren zur Zielsteuerung von Fernlenkkoerpern,insbesondere Torpedos und Vorrichtungen zum Ausueben des Verfahrens
DE3522154A1 (de) * 1985-06-21 1987-01-02 Diehl Gmbh & Co Suchzuender-submunition

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1578299B2 (de) * 1967-10-14 1976-03-11 Licenti a Patent-Verwaltung s-GmbH, 6000 Frankfurt Verfahren zur treffpunktvorverlegung fuer passiv ortende in der eigenlenkphase mittels proportionalnavigation gelenkte geschosse
DE2543606C2 (de) * 1975-09-30 1986-11-06 Deutsch-Französisches Forschungsinstitut Saint-Louis, Saint-Louis Anordnung zur Flugbahnkorrektur eines rotierenden Geschosses
DE2830502C3 (de) * 1978-07-12 1981-10-08 Bodenseewerk Gerätetechnik GmbH, 7770 Überlingen Steuervorrichtung für Flugkörper
US4277038A (en) * 1979-04-27 1981-07-07 The United States Of America As Represented By The Secretary Of The Army Trajectory shaping of anti-armor missiles via tri-mode guidance
DE2951941C2 (de) * 1979-12-22 1988-01-21 Diehl GmbH & Co, 8500 Nürnberg Optische Fernlenkvorrichtung für ein Geschoß

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1815727C1 (de) * 1968-12-19 1985-10-31 Fried. Krupp GmbH Krupp Atlas-Elektronik Bremen, 2800 Bremen Verfahren zur Zielsteuerung von Fernlenkkoerpern,insbesondere Torpedos und Vorrichtungen zum Ausueben des Verfahrens
US4522356A (en) * 1973-11-12 1985-06-11 General Dynamics, Pomona Division Multiple target seeking clustered munition and system
DE3303763A1 (de) * 1983-02-04 1984-08-09 Diehl GmbH & Co, 8500 Nürnberg Verfahren zur zielansteuerung eines projektils und zum bestimmen dessen ballistischer flugbahn sowie vorrichtungen zum ausueben der verfahren
DE3522154A1 (de) * 1985-06-21 1987-01-02 Diehl Gmbh & Co Suchzuender-submunition

Also Published As

Publication number Publication date
ES2064529T3 (es) 1995-02-01
EP0401693A1 (de) 1990-12-12
DE3918701C2 (enrdf_load_stackoverflow) 1992-04-09
DE3918701A1 (de) 1990-12-13
DE59007711D1 (de) 1994-12-22

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