EP1757899A1 - Projectile plein calibre pour canon à alésage lisse - Google Patents

Projectile plein calibre pour canon à alésage lisse Download PDF

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Publication number
EP1757899A1
EP1757899A1 EP06016077A EP06016077A EP1757899A1 EP 1757899 A1 EP1757899 A1 EP 1757899A1 EP 06016077 A EP06016077 A EP 06016077A EP 06016077 A EP06016077 A EP 06016077A EP 1757899 A1 EP1757899 A1 EP 1757899A1
Authority
EP
European Patent Office
Prior art keywords
projectile
caliber
lateral surface
full
projectile body
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
EP06016077A
Other languages
German (de)
English (en)
Other versions
EP1757899B1 (fr
Inventor
Michael Dr. Imdahl
Rosemarie Meuer
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 Waffe Munition GmbH
Original Assignee
Rheinmetall Waffe Munition 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 Waffe Munition GmbH filed Critical Rheinmetall Waffe Munition GmbH
Publication of EP1757899A1 publication Critical patent/EP1757899A1/fr
Application granted granted Critical
Publication of EP1757899B1 publication Critical patent/EP1757899B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/04—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type
    • F42B12/10—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type with shaped or hollow charge
    • F42B12/105—Protruding target distance or stand-off members therefor, e.g. slidably mounted
    • 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
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • 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
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/38—Range-increasing arrangements
    • F42B10/42—Streamlined projectiles
    • F42B10/46—Streamlined nose cones; Windshields; Radomes

Definitions

  • the invention relates to a far-reaching, shootable from a smooth tube full caliber projectile.
  • projectiles are preferably designed as full-caliber projectiles.
  • Missiles fired from smoothbore guns require special structural measures for a stable flight behavior and a small compensatory swirl to compensate for unavoidable manufacturing deviations.
  • Missiles designed for low velocity decay usually have an ogival tip contour. However, these projectiles are sensitive to disturbances due to high buoyancy and low stability.
  • a full-caliber projectile with a cylindrical guide area and an ogive-shaped projectile nose is the DE 101 57 563 A1 removable.
  • this projectile outer shape causes a relatively low velocity drop of the projectile, so that for full-caliber Tank ammunition, since they have the greatest possible combat distances, this ogival bullet exterior geometry is used. It is further stated that this geometry is unfavorable for low combat distances in such wing-stabilized full-caliber projectiles with fold-out or swing-out tail wings. Therefore, it is proposed to provide a projectile with a hood-shaped adapter part, which has an outer contour, which is optimally designed to combat targets of short combat distance. On this adapter part is located on the front side a fastening device to which an ogival projectile nose is placed, if the projectile targets large combat distances are to be achieved.
  • wing stabilized practice bullets with a substantially identical caliber bullet casing and a peg-shaped bullet tip of the DE 198 34 395 C2 known. Such spikes significantly reduce the flow resistance, which is very important at high speeds of a projectile.
  • Wing stabilized full caliber bullets require either a folding mechanism or a rigid tail with a relatively large distance from the actual projectile body for sufficient effectiveness.
  • rigid tail units limit the available usable space due to the necessary distance, while folding tail units have only a slight aerodynamic stability during the unfolding process, so that disturbances acting during this phase lead to considerable flight path deviations.
  • Shape-stabilized full-caliber ammunition has a relatively high velocity drop.
  • the aerodynamic stability decreases with decreasing speed.
  • the covered by the spike area is usually not available for the payload to be transported.
  • the object of the invention is to disclose a wing-stabilized tank projectile of the abovementioned type designed as a full-caliber projectile, which can transport a specific payload volume with sufficient accuracy and a maximum end speed over distances> 2500 m.
  • the invention is based essentially on the idea to connect the three aforementioned structural elements shape stabilization, wing stabilization and ogival tip contour with each other.
  • a spike with a sub-caliber impact surface ensures the necessary stability in the first flight phase.
  • the sub-caliber impact surface reduces the velocity drop of previously known full-caliber solutions.
  • the subsequent ogival tip area ensures sufficient payload volume and low loss of speed, and a folding mechanism ensures aerodynamic stability even at low projectile speeds.
  • the outer diameter of the impact surface is chosen to be much smaller than the projectile caliber and thus caused by the abutment velocity drop compared to known comparable projectiles is substantially reduced, in such a way that for the development of the folding tail necessary bullet stability is achieved with the lowest possible flow resistance ,
  • the lateral surface of the cylindrical projectile body within a second portion is selected such that it has a constantly decreasing, preferably ogival, course up to the outer edge of the abutting surface.
  • the projectile according to the invention also has a greater aerodynamic stability than the latter because of the reduced speed compared with known projectiles.
  • a conically configured external geometry can also be used, although an increase in the flow resistance must be expected.
  • 1 denotes an inventive tank projectile, which comprises a substantially cylindrical projectile body 2 for receiving a payload, not shown, for example, of explosives.
  • a payload not shown, for example, of explosives.
  • a tailstock 4 At the rear end 3 of the projectile body 2 is followed by a tailstock 4 with a folding tail unit 5.
  • the wings 5 'of the folding tail unit 5 already in its unfolded position.
  • a sub-caliber, spike-shaped projectile nose 7 which is connected on its projectile body 2 side facing a perpendicular to the longitudinal axis 100 of the projectile 1 extending abutment surface 8 with the lateral surface 9 of the projectile body 2 and the projectile tip side has a known per se annular thickening 10 to improve the flow separation.
  • the lateral surface 9 of the projectile body 2 comprises, seen in the direction of the longitudinal axis 100 of the projectile 1, two subregions 11 and 12.
  • the first, relatively long portion 11 of the lateral surface 9 has a substantially same caliber outer diameter D0
  • the front side subsequent smaller second portion 12, which extends to the abutting surface 8, according to the invention has an approximately ogival outer contour, so that the diameter D1 of the outer edge of the abutment surface 8 is smaller than the projectile caliber D0.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Footwear And Its Accessory, Manufacturing Method And Apparatuses (AREA)
  • Ceramic Products (AREA)
  • Luminescent Compositions (AREA)
EP06016077A 2005-08-24 2006-08-02 Projectile plein calibre pour canon à alésage lisse Active EP1757899B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102005039900A DE102005039900A1 (de) 2005-08-24 2005-08-24 Weitreichendes Vollkalibergeschoss

Publications (2)

Publication Number Publication Date
EP1757899A1 true EP1757899A1 (fr) 2007-02-28
EP1757899B1 EP1757899B1 (fr) 2008-04-02

Family

ID=37440637

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06016077A Active EP1757899B1 (fr) 2005-08-24 2006-08-02 Projectile plein calibre pour canon à alésage lisse

Country Status (4)

Country Link
EP (1) EP1757899B1 (fr)
AT (1) ATE391281T1 (fr)
DE (2) DE102005039900A1 (fr)
ES (1) ES2301120T3 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113865443A (zh) * 2021-09-23 2021-12-31 西安近代化学研究所 一种定末速度减速装置

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE202009016713U1 (de) 2009-12-04 2010-04-08 Lehnen, Frank Widerstandsstabilisiertes, flügelloses und angetriebenes Wuchtgeschoss
DE102009057682A1 (de) 2009-12-04 2011-06-09 Frank Lehnen Widerstandsstabilisiertes, flügelloses und angetriebenes Wuchtgeschoss
DE102013010356B3 (de) * 2013-06-21 2014-06-05 Rheinmetall Waffe Munition Gmbh Leitwerkstabilisiertes Vollkalibergeschoss

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3713607A (en) * 1968-08-15 1973-01-30 Us Navy Load reducing spike for supersonic missiles
GB2060143A (en) * 1979-10-09 1981-04-29 Bofors Ab Projectile with extendable fin
GB2105444A (en) * 1981-09-09 1983-03-23 Bofors Ab Practice projectile
GB2105445A (en) * 1981-09-09 1983-03-23 Bofors Ab Ammunition unit
DE19906969A1 (de) * 1999-02-19 2000-08-31 Rheinmetall W & M Gmbh Aus einem Waffenrohr verschießbares leitwerkstabilisiertes Geschoß
DE19834395C2 (de) 1998-07-30 2000-12-07 Rheinmetall W & M Gmbh Geschosskopf
DE10115088A1 (de) * 2001-03-27 2002-10-02 Rheinmetall W & M Gmbh Flugkörper
DE10157563A1 (de) 2001-11-23 2003-06-12 Rheinmetall W & M Gmbh Vollkalibriges Geschoss
DE10312717A1 (de) 2003-03-21 2004-10-07 Rheinmetall W & M Gmbh Flügelstabilisiertes Vollkaliber-Sprenggeschoß

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3713607A (en) * 1968-08-15 1973-01-30 Us Navy Load reducing spike for supersonic missiles
GB2060143A (en) * 1979-10-09 1981-04-29 Bofors Ab Projectile with extendable fin
GB2105444A (en) * 1981-09-09 1983-03-23 Bofors Ab Practice projectile
GB2105445A (en) * 1981-09-09 1983-03-23 Bofors Ab Ammunition unit
DE19834395C2 (de) 1998-07-30 2000-12-07 Rheinmetall W & M Gmbh Geschosskopf
DE19906969A1 (de) * 1999-02-19 2000-08-31 Rheinmetall W & M Gmbh Aus einem Waffenrohr verschießbares leitwerkstabilisiertes Geschoß
DE10115088A1 (de) * 2001-03-27 2002-10-02 Rheinmetall W & M Gmbh Flugkörper
DE10157563A1 (de) 2001-11-23 2003-06-12 Rheinmetall W & M Gmbh Vollkalibriges Geschoss
DE10312717A1 (de) 2003-03-21 2004-10-07 Rheinmetall W & M Gmbh Flügelstabilisiertes Vollkaliber-Sprenggeschoß

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
MIKHAIL A G: "SPIKE-NOSED PROJECTILES: COMPUTATIONS AND DUAL FLOW MODES IN SUPERSONIC FLIGHT", JOURNAL OF SPACECRAFT AND ROCKETS, AMERICAN INSTITUTE OF AERONAUTICS AND ASTRONAUTICS,REASTON,VA, US, vol. 28, no. 4, 1 July 1991 (1991-07-01), pages 418 - 424, XP000233302, ISSN: 0022-4650 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113865443A (zh) * 2021-09-23 2021-12-31 西安近代化学研究所 一种定末速度减速装置
CN113865443B (zh) * 2021-09-23 2023-03-24 西安近代化学研究所 一种定末速度减速装置

Also Published As

Publication number Publication date
DE502006000564D1 (de) 2008-05-15
ATE391281T1 (de) 2008-04-15
EP1757899B1 (fr) 2008-04-02
DE102005039900A1 (de) 2007-03-08
ES2301120T3 (es) 2008-06-16

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