EP0392086B1 - Flügelstabilisiertes Geschoss - Google Patents

Flügelstabilisiertes Geschoss Download PDF

Info

Publication number
EP0392086B1
EP0392086B1 EP89122526A EP89122526A EP0392086B1 EP 0392086 B1 EP0392086 B1 EP 0392086B1 EP 89122526 A EP89122526 A EP 89122526A EP 89122526 A EP89122526 A EP 89122526A EP 0392086 B1 EP0392086 B1 EP 0392086B1
Authority
EP
European Patent Office
Prior art keywords
projectile
sensor unit
target
fin
warhead
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
EP89122526A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0392086A3 (de
EP0392086A2 (de
Inventor
Wilfried Becker
Gerhard Dr. Glotz
Helmut Dr. Peller
Josef Dr. Osthues
Hans-Peter Opitz
Heinz-Josef Dr. Kruse
Jutta Peters
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.)
Rheinmetall Industrie AG
Original Assignee
Rheinmetall GmbH
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 Rheinmetall GmbH filed Critical Rheinmetall GmbH
Publication of EP0392086A2 publication Critical patent/EP0392086A2/de
Publication of EP0392086A3 publication Critical patent/EP0392086A3/de
Application granted granted Critical
Publication of EP0392086B1 publication Critical patent/EP0392086B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/01—Arrangements thereon for guidance or control
    • 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
    • F42B10/66—Steering by varying intensity or direction of thrust

Definitions

  • the invention relates to a wing-stabilized projectile, in particular a tank ammunition, with the features of the preamble of claim 1.
  • bullets are such.
  • bullets that can be steered by a shooter or purely ballistic bullets that autonomously detect their target during their flight are used for this purpose.
  • steerable projectiles require visual contact with the target and to control the projectile towards the target require a connection between a control unit, for example a fire control system in a vehicle, and the projectile.
  • a control unit for example a fire control system in a vehicle
  • the effort involved in control elements and their complex structure is considerable in such controlled projectiles.
  • An autonomous projectile looking for its target is known for example from DE 33 37 873-A1.
  • a sensor seeker head is to correct the trajectory of the projectile by means of a thrust jet control device towards the target after detection of a target.
  • a wing-stabilized projectile with a shaped charge warhead and a pulse control arranged in the projectile tip is also known.
  • corresponding pulse engines are located on the circumference of the floor, evenly distributed.
  • the invention is therefore based on the object of creating a simply constructed wing-stabilized projectile, in particular tank ammunition, which is distinguished by a high probability of being hit when combating slow flight targets.
  • the great advantage of the wing-stabilized projectile according to the invention is that it has advantages of conventional armored projectiles, such as. B. large warhead, combined with the advantages of steerable projectiles and thus a compensation of ballistic errors and target movements during the flight time of the projectile without requiring a direct connection between the projectile and a control unit in an armored vehicle.
  • the projectile according to the invention can be used to combat hidden targets, for example by activating an ignition chain in the projectile at a preselectable attachment angle above the target, using time detectors or distance detonators.
  • a wing-stabilized projectile 10 according to the invention with a longitudinal axis 12 is shown during its flight in the target area.
  • the projectile 10 is stabilized by the stabilizer wing 14 and contains in its projectile tip 22 a sensor unit 16 and a warhead 18 arranged behind it with a spherical plate 20, which is preferably designed as a spherical fragment plate.
  • Sensor electronics can be accommodated anywhere in the floor 10.
  • the scanning of the target area, indicated in the drawing by an area shown in broken lines, is carried out with the sensor unit 16, which can be, for example, a single sensor or a sensor line.
  • a rotation required for scanning can be achieved according to the invention either with a rigid sensor in the sensor unit 16 in that the projectile 10 as a whole rotates about its longitudinal axis 12 as a result of a corresponding adjustment of the tail wings 14, for example in the direction of an arrow 26, or in that the sensor unit 16 itself, as a rotating sensor, executes a relative rotational movement with respect to the projectile 10.
  • the projectile 10 As soon as a flight target, illustrated here by a helicopter 24, has been detected by the projectile 10, in particular its sensor unit 16, to compensate for ballistic errors and target movements during its flight time, the projectile 10 shortly before the target 24 about its vertical axis (axis transverse to the longitudinal axis of the projectile 10) is rotated and the entire projectile tip 22 including the sensor unit 16 is blasted off and the warhead 18 now directed towards the target 24 with the spherical plate 20 is initiated.
  • a flight target illustrated here by a helicopter 24
  • the projectile 10 shortly before the target 24 about its vertical axis (axis transverse to the longitudinal axis of the projectile 10) is rotated and the entire projectile tip 22 including the sensor unit 16 is blasted off and the warhead 18 now directed towards the target 24 with the spherical plate 20 is initiated.
  • a possible detection of wrong targets can be avoided by transmitting route or time information from a fire control system in an armored vehicle before the shot is broken.
  • a transceiver device according to the invention also provided on floor 10 with a corresponding electronics unit is used, which has not been described in the drawing for the sake of clarity.
  • microreaction engines or a detachable mass in the projectile tip 22 are provided in the projectile, which serve for the exact alignment of the projectile 10, in particular the spherical plate 20, with the target 24.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP89122526A 1989-04-08 1989-12-06 Flügelstabilisiertes Geschoss Expired - Lifetime EP0392086B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3911576A DE3911576A1 (de) 1989-04-08 1989-04-08 Fluegelstabilisiertes geschoss
DE3911576 1989-04-08

Publications (3)

Publication Number Publication Date
EP0392086A2 EP0392086A2 (de) 1990-10-17
EP0392086A3 EP0392086A3 (de) 1991-05-02
EP0392086B1 true EP0392086B1 (de) 1993-09-22

Family

ID=6378260

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89122526A Expired - Lifetime EP0392086B1 (de) 1989-04-08 1989-12-06 Flügelstabilisiertes Geschoss

Country Status (2)

Country Link
EP (1) EP0392086B1 (enrdf_load_stackoverflow)
DE (2) DE3911576A1 (enrdf_load_stackoverflow)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19505791C1 (de) * 1995-02-20 1996-08-14 Daimler Benz Aerospace Ag Verfahren und Vorrichtung zur Bekämpfung verdeckt operierender Hubschrauber
DE19847218A1 (de) * 1998-10-13 2000-04-20 Bodenseewerk Geraetetech Suchkopf, insbesondere für Hochgeschwindigkeits-Flugkörper
DK1767893T3 (en) 2005-09-23 2017-03-06 Saab Ab Missile Transfer System

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE683586A (enrdf_load_stackoverflow) * 1966-07-04 1966-12-16
US3674227A (en) * 1970-03-23 1972-07-04 Hughes Aircraft Co Fragmenting cover
US4492166A (en) * 1977-04-28 1985-01-08 Martin Marietta Corporation Submunition having terminal trajectory correction
GB2129103A (en) * 1982-10-18 1984-05-10 Raytheon Co Mortar round
US4519315A (en) * 1982-12-20 1985-05-28 The United States Of America As Represented By The Secretary Of The Army Fire and forget missiles system
DE3300709C2 (de) * 1983-01-11 1985-12-19 Friedrich Dr. 8890 Aichach Schäff Rotierender Flugkörper zum Bekämpfen von Luftzielen
FR2590973B1 (fr) * 1985-11-29 1988-02-12 France Etat Armement Dispositif de basculement de projectile sur trajectoire

Also Published As

Publication number Publication date
DE3911576C2 (enrdf_load_stackoverflow) 1991-09-05
DE3911576A1 (de) 1990-10-11
EP0392086A3 (de) 1991-05-02
DE58905698D1 (de) 1993-10-28
EP0392086A2 (de) 1990-10-17

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