EP0296309A2 - Projectile sous-calibré stabilisé par ailettes - Google Patents

Projectile sous-calibré stabilisé par ailettes Download PDF

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Publication number
EP0296309A2
EP0296309A2 EP19880102359 EP88102359A EP0296309A2 EP 0296309 A2 EP0296309 A2 EP 0296309A2 EP 19880102359 EP19880102359 EP 19880102359 EP 88102359 A EP88102359 A EP 88102359A EP 0296309 A2 EP0296309 A2 EP 0296309A2
Authority
EP
European Patent Office
Prior art keywords
projectile
wing
projectile body
flange strip
wings
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.)
Withdrawn
Application number
EP19880102359
Other languages
German (de)
English (en)
Other versions
EP0296309A3 (fr
Inventor
Frank Dipl.-Ing. Achilles
Bernhard Dipl.-Ing. Bisping
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 Industrie AG
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 Industrie AG, Rheinmetall GmbH filed Critical Rheinmetall Industrie AG
Publication of EP0296309A2 publication Critical patent/EP0296309A2/fr
Publication of EP0296309A3 publication Critical patent/EP0296309A3/fr
Withdrawn legal-status Critical Current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
    • F42B10/02—Stabilising arrangements
    • F42B10/04—Stabilising arrangements using fixed fins
    • F42B10/06—Tail fins

Definitions

  • the invention relates to a sub-caliber wing-stabilized projectile according to the features in the preamble of claim 1.
  • the projectile body has structural measures, such as, for example, Steps, shoulders, recesses, protrusions, longitudinal grooves, ring grooves or the like such as Threaded teeth for attaching an annular sleeve on which the wings of the tail unit are arranged.
  • structural measures such as, for example, Steps, shoulders, recesses, protrusions, longitudinal grooves, ring grooves or the like such as Threaded teeth for attaching an annular sleeve on which the wings of the tail unit are arranged.
  • the rear part of the penetrator can tear off, but more frequently, the rear area can be broken off at the notched points when it hits a armored target by superimposing continuous shock waves and the resulting voltage peaks.
  • the stabilizer attachment according to the invention even very thin wings can advantageously be used, in particular in the case of small penetrators with a penetrator diameter of e.g. 10 mm can be securely attached to the projectile body.
  • This is easily possible for sash thicknesses of up to approximately 0.25 mm, since the fastening flange strip and the respective sash element are made in one piece from one material.
  • the flange strips are expediently provided with at least one incision and bent on both sides of the wing element or placed around the penetrator.
  • penetrators or balancing projectiles whose tail elements are very thin with a low dead load component, but are nevertheless very stably designed or fastened, result in higher penetration rates at the target; armored vehicles with special armor, which today mainly consist of several bulkhead armor made of different hard materials.
  • the wing elements according to the invention are not only suitable for soldering but also for gluing.
  • the flange strips are expedient depending on the number of wings dimensioned so wide that they abut the adjacent wing element or the adjacent flange strips.
  • the width of the flange strip is expediently adapted to the number of wings correspondingly wide, and the flange strip forms a middle piece between two adjacent wing elements, so that a coherent one-piece wing unit consisting of two wing elements and one flange strip is formed.
  • the wing elements preferably consist of a heat-resistant steel sheet which is punched out of the corresponding flat starting material by a punching process and is already finished in a further punching or pressing process, the flange strip of a wing element or the middle piece between two wing elements depending on the diameter of the associated one Projectile body viewed in cross section is formed into a circular arc.
  • reference number 10 denotes a projectile body in which four wing elements 12 are provided in the fastening area of the tail unit.
  • Each wing element 12 has a flange strip 14, which is bent at the side and is bent to suit the cylindrical peripheral surface of the projectile body 10. If the wing element is designed as a thin steel part, soldering is suitable as a connection to the projectile body; if the wing element is made of fiber-reinforced plastic, gluing is preferred.
  • the flange strip 14 is dimensioned so wide that it abuts the adjacent wing element or the adjacent flange strip; this results in a seen in cross section over the entire circumference of the penetrator closed fastening region with low c W -Beiwert or good flight characteristics of the projectile body.
  • This closed circumferential area can be achieved in that the flange strips 14 of the wing elements 12 are bent over their entire length to one side (to the right or left), as can be understood from FIG. 1, or in that each flange strip of the wing elements 12.1; 12.2; 12.3 is provided with an incision 15 and in each case one flange strip part 14.11; 14.31 in the circumferential direction of the projectile body 10 to the right and the other flange strip 14.12; 14.22 is bent to the left, as is clear from Fig. 3.
  • FIG. 4 Another embodiment in this respect is shown in FIG. 4, the flange strip of each wing element 12.9 having two incisions 45, 47 and the first flange strip part 14.41 to the left, the second flange strip part 14.42 to the right and the third flange strip part 14.43 again being bent to the left around the penetrator body. It can also be seen that the rear wing ends 49 are flush with the rear end 10.4 of the projectile body 10.
  • the projectile body 10 is advantageously notched in the fastening region of the wing elements and here has the same outer diameter as in the central projectile body region.
  • FIG. 5 A further advantageous embodiment of the invention is shown in FIG. 5, according to which the projectile body 10 is conically tapered towards the rear in the entire fastening area 50 of the tail unit, the deviation from the longitudinal-axial course of the peripheral surface being between 3 ° and 6 °; the flange strips are cut accordingly.
  • This results in an improvement in the air flow conditions when the projectile is in flight and an easier detachment of the tail unit when the projectile body hits the target.
  • the projectile body 10 is designed such that the rear wing ends 59 protrude rearward about a length of the projectile body diameter beyond the rear end 10.5 of the projectile body 10.
  • FIG. 2 Another advantageous embodiment is shown in FIG. 2.
  • two adjacent wing elements 12.5 and 12.7 form a coherent, one-piece wing unit with the flange strips 14.5 formed as a common central piece.
  • the exemplary embodiment shown has four wing units with a total of eight wing elements.
  • Tail units consisting of two, three, five or six wing units can also be created with advantage from two wing elements connected via the center piece.
  • the middle third of the middle piece remains between the two wing elements, while the halves of the front and rear third of the middle piece are bent outwards and abut flush with corresponding middle piece parts of the adjacent wing units.
  • the front edges of the wing elements and the flange strips or the center pieces are beveled in a streamlined manner.
  • the front edges as well as the rear edges of the individual wing elements can be inclined on one side (all to the right or to the left; opposite in the opposite direction, ie diamond-shaped in plan view).

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)
EP19880102359 1987-06-13 1988-02-18 Projectile sous-calibré stabilisé par ailettes Withdrawn EP0296309A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19873719770 DE3719770A1 (de) 1987-06-13 1987-06-13 Unterkalibriges fluegelstabilisiertes geschoss
DE3719770 1987-06-13

Publications (2)

Publication Number Publication Date
EP0296309A2 true EP0296309A2 (fr) 1988-12-28
EP0296309A3 EP0296309A3 (fr) 1991-10-23

Family

ID=6329629

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19880102359 Withdrawn EP0296309A3 (fr) 1987-06-13 1988-02-18 Projectile sous-calibré stabilisé par ailettes

Country Status (2)

Country Link
EP (1) EP0296309A3 (fr)
DE (1) DE3719770A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2651311A1 (fr) * 1989-08-24 1991-03-01 Rheinmetall Gmbh Projectile stabilise par ailettes.
DE3933442A1 (de) * 1989-10-06 1991-04-18 Rheinmetall Gmbh Fluegelstabilisiertes geschoss

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3927798A1 (de) * 1989-08-23 1991-03-14 Rheinmetall Gmbh Fluegelstabilisiertes geschoss
DE4128054A1 (de) * 1991-08-23 1993-02-25 Rheinmetall Gmbh Treibkaefig fuer ein unterkalibergeschoss

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE713343C (de) * 1938-12-20 1941-11-06 Deutsches Reich Vertreten Durc Verfahren zum Anschweissen von Fluegelblechen an Wurfgeschossen u. dgl.
US3152545A (en) * 1961-09-20 1964-10-13 Jr James H Potts Mid-fin
GB1201488A (en) * 1967-10-10 1970-08-05 Senlac Metal Casements Ltd Improvements in or relating to externally finned cylindrical articles
DE3038087A1 (de) * 1980-10-09 1982-05-27 Rheinmetall GmbH, 4000 Düsseldorf Pfeilstabilisiertes wuchtgeschoss (penetrator)
DE3508053A1 (de) * 1985-03-07 1986-09-18 Rheinmetall GmbH, 4000 Düsseldorf Wuchtgeschoss

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE713343C (de) * 1938-12-20 1941-11-06 Deutsches Reich Vertreten Durc Verfahren zum Anschweissen von Fluegelblechen an Wurfgeschossen u. dgl.
US3152545A (en) * 1961-09-20 1964-10-13 Jr James H Potts Mid-fin
GB1201488A (en) * 1967-10-10 1970-08-05 Senlac Metal Casements Ltd Improvements in or relating to externally finned cylindrical articles
DE3038087A1 (de) * 1980-10-09 1982-05-27 Rheinmetall GmbH, 4000 Düsseldorf Pfeilstabilisiertes wuchtgeschoss (penetrator)
DE3508053A1 (de) * 1985-03-07 1986-09-18 Rheinmetall GmbH, 4000 Düsseldorf Wuchtgeschoss

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2651311A1 (fr) * 1989-08-24 1991-03-01 Rheinmetall Gmbh Projectile stabilise par ailettes.
DE3933442A1 (de) * 1989-10-06 1991-04-18 Rheinmetall Gmbh Fluegelstabilisiertes geschoss

Also Published As

Publication number Publication date
DE3719770A1 (de) 1988-12-22
EP0296309A3 (fr) 1991-10-23

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