EP0392086A2 - Projectile à stabilisation par ailettes - Google Patents

Projectile à stabilisation par ailettes Download PDF

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Publication number
EP0392086A2
EP0392086A2 EP19890122526 EP89122526A EP0392086A2 EP 0392086 A2 EP0392086 A2 EP 0392086A2 EP 19890122526 EP19890122526 EP 19890122526 EP 89122526 A EP89122526 A EP 89122526A EP 0392086 A2 EP0392086 A2 EP 0392086A2
Authority
EP
European Patent Office
Prior art keywords
projectile
wing
target
stabilized
sensor unit
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
EP19890122526
Other languages
German (de)
English (en)
Other versions
EP0392086B1 (fr
EP0392086A3 (fr
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/fr
Publication of EP0392086A3 publication Critical patent/EP0392086A3/fr
Application granted granted Critical
Publication of EP0392086B1 publication Critical patent/EP0392086B1/fr
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 tank ammunition.
  • Known generic wing-stabilized projectiles of this type are used as ballistic projectiles for combating slow-flying flight targets, for example helicopters.
  • a disadvantage of these projectiles is their poor probability of being hit, since after they have been fired there is no possibility of compensating for ballistic errors and target movements during the flight time of the projectile.
  • Steerable projectiles are also known, which can be directed towards the target after direct firing and visual contact with the target.
  • a control unit for example a fire control system in a vehicle
  • a disadvantage of such guided projectiles is their complex controls and their complex structure.
  • floors with automatic target tracking (autonomous) a high level of technical effort is also required.
  • a relatively large coverage of your search head is necessary.
  • the invention is therefore based on the object of creating a simply constructed wing-stabilized projectile, in particular a tank ammunition, which is distinguished by a high probability of being hit when fighting 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 rotary movement with respect to the projectile 10.
  • the projectile 10 As soon as a flight target, here illustrated 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 is rotated about its vertical axis shortly before the target 24 and the entire projectile tip 22 including the sensor unit 16 is blown off and the warhead 18 now directed with the spherical plate 20 toward the target 24 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 the floor 10 with a corresponding electronics unit is used, which for the sake of clarity has not been specified in the drawing.

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 Projectile à stabilisation par ailettes Expired - Lifetime EP0392086B1 (fr)

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 true EP0392086A2 (fr) 1990-10-17
EP0392086A3 EP0392086A3 (fr) 1991-05-02
EP0392086B1 EP0392086B1 (fr) 1993-09-22

Family

ID=6378260

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89122526A Expired - Lifetime EP0392086B1 (fr) 1989-04-08 1989-12-06 Projectile à stabilisation par ailettes

Country Status (2)

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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0994326A3 (fr) * 1998-10-13 2001-07-11 Bodenseewerk Gerätetechnik GmbH Tête chercheuse, en particulier pour un missile à grande vitesse
EP1767893A1 (fr) * 2005-09-23 2007-03-28 Saab Ab Système de guidage de missile

Families Citing this family (1)

* 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

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2074186A5 (fr) * 1970-03-23 1971-10-01 Hughes Aircraft Co
DE3337873A1 (de) * 1982-10-18 1984-04-19 Raytheon Co., 02173 Lexington, Mass. Geschoss fuer granatwerfersysteme
US4492166A (en) * 1977-04-28 1985-01-08 Martin Marietta Corporation Submunition having terminal trajectory correction
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
EP0229541A1 (fr) * 1985-11-29 1987-07-22 ETAT-FRANCAIS représenté par le DELEGUE GENERAL POUR L'ARMEMENT (DPAG) Dispositif de basculement de projectile sur trajectoire

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE683586A (fr) * 1966-07-04 1966-12-16
DE3300709C2 (de) * 1983-01-11 1985-12-19 Friedrich Dr. 8890 Aichach Schäff Rotierender Flugkörper zum Bekämpfen von Luftzielen

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2074186A5 (fr) * 1970-03-23 1971-10-01 Hughes Aircraft Co
US4492166A (en) * 1977-04-28 1985-01-08 Martin Marietta Corporation Submunition having terminal trajectory correction
DE3337873A1 (de) * 1982-10-18 1984-04-19 Raytheon Co., 02173 Lexington, Mass. Geschoss fuer granatwerfersysteme
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
EP0229541A1 (fr) * 1985-11-29 1987-07-22 ETAT-FRANCAIS représenté par le DELEGUE GENERAL POUR L'ARMEMENT (DPAG) Dispositif de basculement de projectile sur trajectoire

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0994326A3 (fr) * 1998-10-13 2001-07-11 Bodenseewerk Gerätetechnik GmbH Tête chercheuse, en particulier pour un missile à grande vitesse
EP1767893A1 (fr) * 2005-09-23 2007-03-28 Saab Ab Système de guidage de missile
US7675011B2 (en) 2005-09-23 2010-03-09 Saab Ab Missile guidance system

Also Published As

Publication number Publication date
DE3911576A1 (de) 1990-10-11
EP0392086B1 (fr) 1993-09-22
DE3911576C2 (fr) 1991-09-05
EP0392086A3 (fr) 1991-05-02
DE58905698D1 (de) 1993-10-28

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