EP0210488B1 - Verfahren zum Ansteuern eines Zieles - Google Patents

Verfahren zum Ansteuern eines Zieles Download PDF

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Publication number
EP0210488B1
EP0210488B1 EP86109387A EP86109387A EP0210488B1 EP 0210488 B1 EP0210488 B1 EP 0210488B1 EP 86109387 A EP86109387 A EP 86109387A EP 86109387 A EP86109387 A EP 86109387A EP 0210488 B1 EP0210488 B1 EP 0210488B1
Authority
EP
European Patent Office
Prior art keywords
target
projectile
lift
yaw
horizontal
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
Application number
EP86109387A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0210488A1 (de
Inventor
Heinrich Wällermann
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
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 Diehl GmbH and Co filed Critical Diehl GmbH and Co
Publication of EP0210488A1 publication Critical patent/EP0210488A1/de
Application granted granted Critical
Publication of EP0210488B1 publication Critical patent/EP0210488B1/de
Expired legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/62—Steering by movement of flight surfaces
    • F42B10/64—Steering by movement of flight surfaces of fins

Definitions

  • the invention relates to a method according to the preamble of claim 1.
  • Such a method is known from US-A-3 695 555 for an artillery projectile which can be steered in the end phase or from GB-A-1 605 007 for a projectile in the form of a target-seeking torpedo.
  • the invention relates to projectiles which can be steered in the final phase, as are known as submunitions from DEFENSE ELEC-TRONICS, issue June 1984, page 102.
  • the maneuverability in the yaw direction (that is, in the lateral pivoting of the longitudinal axis of the projectile) is extremely limited from a currently given flight position.
  • the buoyancy vector To actuate a laterally distant target, the buoyancy vector must therefore be pivoted from the vertical towards the laterally distant target, which requires a correspondingly strong rolling movement of the projectile about its longitudinal axis.
  • any change in the roll position has repercussions on other aerodynamic influences and thus undesirable repercussions on flight behavior.
  • the invention is based on the object of modifying the control method of the generic type in such a way that hard yaw maneuvers can be carried out for rapid target control even with only one pair of horizontal sliding surfaces on the projectile, without running the risk that the flight behavior thereby becomes unstable, the projectile can no longer or at least no longer be steered towards the goal in the desired time behavior.
  • the projectile 1 sketched in a side view in FIG. 1 is equipped with crossed, that is, in pairs horizontally and vertically oriented rudders 2, 3 and with a pair of only horizontally extending, approximately symmetrical cross-sectional sliding surfaces 4. From an opposing position e.g. the horizontal rudder 2 results in a rolling movement 5 around the longitudinal axis 6 of the projectile. In the same direction, positioning components of the horizontal rudder 2 in the direction shown in full lines in FIG. 1 cause an inflow 7 of the sliding surfaces 4, from which a lift 8 of the projectile 1 leads to the center of the earth counteracting gravity results; and which is therefore the normal mode of operation for a gliding flight of the projectile 1 oriented approximately parallel to the target area 15.
  • the representation sequence in FIG. 2 above corresponds to this conventional maneuver of a bank to carry out major lateral course changes.
  • projectile 1 outlined in rear view grips out of its current slideway 18 above target area 15 by means of its pivotable search head 16 (FIG. 1) target 17 to combat.
  • the pitching movement 10 in the horizontal plane is carried out by the control of the horizontal rudder 2 to control the target 17 - preferably in the interest of the steepest possible approach approach with a delayed pitching movement 10, as described in detail in GB-A-2 134 632 of the applicant - in the case of a conventional bank slope maneuver
  • the lateral course correction according to the upper illustration in FIG.
  • the reduced required angle of the roll movement 5 'means as mentioned in the introduction, better maneuverability of the projectile 1 and thus a more manageable and yet also manageable faster transition from the slide 18 into the descent 19; This is particularly important if the horizontal target distance 20 (transversely to the plane of representation of FIG. 2; see FIG. 3) is only relatively small when aiming and switching to output 9, i.e. hard yaw maneuvers due to the high gliding speed of the projectile 1 Change of flight direction towards the destination 17 may be required.
  • the position of the horizontal rudders 2 for buoyancy 8 must still be maintained (i.e. in the control device 21 guided by the seeker head 16 for switching the horizontal rudders 2 not yet switch over to the downward slope of the output) if the target distance 20 is still very large or is changing due to an escape movement 22 of the target 17, or in any case only reduced relatively little.
  • the target distance 20 is still very large or is changing due to an escape movement 22 of the target 17, or in any case only reduced relatively little.
  • the projectile 1 would therefore sag from an initial slideway 18 and could only reach the target 17 on a flat approach or not at all, if - despite the given target perception by means of the search head 16 - the horizontal distance 20 is still too large for the desired course of the descent path 19 to be driven under the output 9.
  • a switch to output 9 is not required, or only in the very last phase of the descent path 19 - that is to say greatly delayed - if the conceived target 17 (according to FIG. 3) is almost in the vertical plane through the current slideway 18, that is, only a slight yaw course correction and, accordingly, only a small rolling movement 5 while maintaining the vectorial direction of the buoyancy 8 is required.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (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)
EP86109387A 1985-07-12 1986-07-09 Verfahren zum Ansteuern eines Zieles Expired EP0210488B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19853524925 DE3524925A1 (de) 1985-07-12 1985-07-12 Verfahren zum ansteuern eines zieles
DE3524925 1985-07-12

Publications (2)

Publication Number Publication Date
EP0210488A1 EP0210488A1 (de) 1987-02-04
EP0210488B1 true EP0210488B1 (de) 1988-10-26

Family

ID=6275607

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86109387A Expired EP0210488B1 (de) 1985-07-12 1986-07-09 Verfahren zum Ansteuern eines Zieles

Country Status (4)

Country Link
US (1) US4711412A (enrdf_load_stackoverflow)
EP (1) EP0210488B1 (enrdf_load_stackoverflow)
DE (2) DE3524925A1 (enrdf_load_stackoverflow)
SG (1) SG19589G (enrdf_load_stackoverflow)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB8129316D0 (en) * 1981-09-29 2006-07-05 British Aerospace Improvements in or relating to guidance systems
DE3738580A1 (de) * 1987-11-13 1989-06-01 Diehl Gmbh & Co Gelenktes artillerieprojektil mit flugbahnregler
DE3821218A1 (de) * 1988-06-23 1990-03-08 Diehl Gmbh & Co Verfahren zum bekaempfen eines zielobjektes von einem ueberflugprojektil aus und ueberflugprojektil zum ausueben des verfahrens
US5086422A (en) * 1989-06-19 1992-02-04 Ricoh Company, Ltd. Optical disk apparatus
DE4133405C2 (de) * 1991-10-09 1995-02-23 Deutsche Aerospace Submunition für Tiefflugeinsatz
SE511986C2 (sv) * 1995-10-06 2000-01-10 Bofors Ab Sätt att korrigera projektilbanan för rotationsstabiliserande projektiler
US8450668B2 (en) * 2005-02-07 2013-05-28 Bae Systems Information And Electronic Systems Integration Inc. Optically guided munition control system and method
US7834300B2 (en) * 2005-02-07 2010-11-16 Bae Systems Information And Electronic Systems Integration Inc. Ballistic guidance control for munitions
US20080029641A1 (en) * 2005-02-07 2008-02-07 Bae Systems Information And Electronic Systems Three Axis Aerodynamic Control of Guided Munitions
WO2006086527A1 (en) * 2005-02-07 2006-08-17 Bae Systems Information And Electronic Systems Integration Inc. Radiation homing tag
US7533849B2 (en) * 2005-02-07 2009-05-19 Bae Systems Information And Electronic Systems Integration Inc. Optically guided munition

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2824710A (en) * 1949-01-05 1958-02-25 Albert C Hall Control system for guided missiles
US2821349A (en) * 1952-11-04 1958-01-28 Glenn L Martin Co Dive control system for pilotless aircraft
GB1605007A (en) * 1969-01-08 1981-12-16 Krupp Atlas Elektronik Gmbh Method and apparatus for steering a submarine torpedo or other steerable body
US3695555A (en) * 1970-06-12 1972-10-03 Us Navy Gun-launched glide vehicle with a mid-course and terminal guidance control system
US3946968A (en) * 1974-08-02 1976-03-30 Raytheon Company Apparatus and method for aerodynamic cross-coupling reduction
DE3119185C2 (de) * 1981-05-14 1984-05-30 Messerschmitt-Bölkow-Blohm GmbH, 8000 München "Steuerbarer Flugkörper"
US4530476A (en) * 1981-08-12 1985-07-23 E-Systems, Inc. Ordnance delivery system and method including remotely piloted or programmable aircraft with yaw-to-turn guidance system
US4590567A (en) * 1982-01-04 1986-05-20 General Electric Company Large angle, gravity compensated, bank-to-turn pursuit controller
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
US4606514A (en) * 1984-08-10 1986-08-19 Martin-Marietta Corporation Method for homing a projectile onto a target and for determining the ballistic trajectory thereof as well as arrangements for implementing the method

Also Published As

Publication number Publication date
DE3524925A1 (de) 1987-01-22
EP0210488A1 (de) 1987-02-04
US4711412A (en) 1987-12-08
DE3524925C2 (enrdf_load_stackoverflow) 1988-09-29
DE3661048D1 (en) 1988-12-01
SG19589G (en) 1990-01-26

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