EP2930460B1 - Überschallflugprojektil für eine waffe mit glattem lauf - Google Patents

Überschallflugprojektil für eine waffe mit glattem lauf Download PDF

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Publication number
EP2930460B1
EP2930460B1 EP15160232.3A EP15160232A EP2930460B1 EP 2930460 B1 EP2930460 B1 EP 2930460B1 EP 15160232 A EP15160232 A EP 15160232A EP 2930460 B1 EP2930460 B1 EP 2930460B1
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EP
European Patent Office
Prior art keywords
projectile
cone
cylindrical shaft
tail
projectile according
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.)
Active
Application number
EP15160232.3A
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English (en)
French (fr)
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EP2930460A1 (de
Inventor
Roxan Cayzac
Jean-Roch Adam
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.)
Nexter Munitions SA
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Nexter Munitions SA
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Publication date
Application filed by Nexter Munitions SA filed Critical Nexter Munitions SA
Priority to PL15160232T priority Critical patent/PL2930460T3/pl
Publication of EP2930460A1 publication Critical patent/EP2930460A1/de
Application granted granted Critical
Publication of EP2930460B1 publication Critical patent/EP2930460B1/de
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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

Definitions

  • the technical field of the invention is that of projectiles with supersonic flight fired by a smooth-tube gun, and in particular that of the projectiles fired by the tank guns with a caliber of between 90 mm and 130 mm.
  • the supersonic flight projectiles for smooth tube gun are generally stabilized by a tail.
  • projectiles Two main types of projectiles are known for smooth-arm weapons: sub-calibrated projectiles (or arrow projectiles) and caliber projectiles.
  • the sub-calibrated projectiles have a bar whose diameter is much smaller than the caliber of the tube, which bar is pulled using a caliper shoe.
  • These projectiles comprise a stabilizer formed of several radial fins.
  • Projectiles with caliber are most often explosive projectiles. They have a body that is extended at its rear by a tail tail with a stabilizer stabilizer.
  • Exercise projectiles are also known to be associated with each type of war projectile.
  • a caliber exercise projectile has almost the same proportions as an explosive projectile but it is made of inert material. It carries a rear tail substantially to the diameter of the projectile body and located at a substantial distance from the body. The length of the projectile, the belt to the rear of the empennage, is thus substantially half of the total length of the projectile. The scope of this projectile is the same as that of the explosive projectile.
  • Licences US2006 / 065149 and US5328130 forming a starting point for the present invention, also describe shots drawn by smooth tube and whose stabilization is provided by a rear cylindrical stabilizer which carries a split flange to give a moderate rotation to compensate for asymmetries.
  • the feathered projectiles with caliber as described by the patent DE4132659 have a long tail tail that penetrates deeply into the case containing the propellant charge. These projectiles reduce the mass of propellant powder that can be housed in the case. The length of the empennage also hinders the placement of the projectile in a loaded socket and impose either a loading of the case from the rear and after mounting the projectile, or a load in two burdens, a first burden attached to the projectile and a second burden located in the holster.
  • the invention can thus be used more particularly to produce an exercise projectile.
  • the subject of the invention is a projectile with a supersonic flight that can be fired by a smooth-tube gun, a projectile comprising a body of the caliber of the barrel tube and an aerodynamic stabilization means disposed behind the body, a projectile characterized in that the means of aerodynamic stabilization is formed by a cone whose largest diameter is substantially equal to the diameter of the body, the cone being connected to the body by a cylindrical surface, the body having an annular rear face perpendicular to the axis of the projectile and on which connects the cylindrical surface, the height of the annular face and the length of the cylindrical surface being defined so as to ensure separation of the aerodynamic flow behind the annular face, and then the bonding of this flow directly on the conical stabilizing element .
  • the ratio between the length of the cylindrical surface and the height of the annular rear face will be between 1.5 and 3.5.
  • the length of the tail tail formed by the cone and the cylindrical bearing may be less than 40% of the total length of the projectile.
  • the cone may have an apex angle between 10 ° and 40 °.
  • the cone may comprise a cylindrical rear portion followed by a conical necking.
  • the cylindrical scope may comprise radial bores connecting the outer surface of the cylindrical seat with a volume internal to the tail tail.
  • the tail tail may be integral with a ring, the diameter of the body and having the annular rear face, which ring will be a rear portion of the body and which will attach to a front portion of the body.
  • the front part of the body may be made of steel and the tail tail and the rear part of the body may be made of aluminum alloy.
  • the projectile according to the invention may constitute an inert exercise projectile, or an explosive projectile.
  • a projectile 1 fired by a smooth tube gun comprises a body 2 to the caliber of the tube and aerodynamic stabilization means 3 disposed behind the body 2.
  • the projectile 1 is a projectile d inert exercise.
  • the socket according to the caliber may be metallic or combustible.
  • This bushing of conventional type is not part of the invention and is not shown.
  • the aerodynamic stabilization means 3 is formed by a cone of revolution whose largest diameter D3 is substantially equal to the diameter D2 of the body 2.
  • the diameter D3 may be slightly less than the diameter D2 but the diameter D3 will be chosen sufficient for the recollement of the aerodynamic flow is done on the cone.
  • the cone 3 is connected to the body 2 by a cylindrical bearing surface 4 of diameter D1.
  • the body 2 has an annular rear face 5 which is perpendicular to the axis 6 of the projectile and on which is connected the cylindrical seat 4.
  • the cone 3 has an apex angle of between 10 ° and 40 ° (and preferably between 15 ° and 30 °). This choice of the angle of the cone makes it possible to ensure a sufficient increase of the aerodynamic pressure on the cone.
  • the cone 3 may carry on its periphery grooves or notches 16 which will be inclined relative to the axis 6 of the projectile. Such an arrangement will allow (in known manner) a rotation of the projectile 1 on trajectory which improves the stability and avoids a roll-pitch resonance phenomenon.
  • the assembly constituted by the cone 3 and the cylindrical bearing surface 4 constitutes a tail tail 7 which has a length L1.
  • the empennage tail 7 is secured to a ring 8 of the caliber of the body 2 and which carries the annular rear face 5.
  • the empennage tail 7 and the ring 8 are formed here in one piece.
  • the ring 8 constitutes a rear portion of the body 2 and it is fixed to a front portion 2a of the body 2 by a thread 9.
  • the body 2 also carries a sealing belt 10.
  • the front portion 2a of the body 2 is made of steel while the empennage tail 7 and the rear portion 8 of the body are made of aluminum alloy. This results in a positioning of the center of gravity C of the projectile substantially halfway between the front and the rear of the projectile 1.
  • the empennage tail 7 comprises an internal cylindrical volume 11 which can receive, for example, a tracer (not shown).
  • the bonding of the flow then intervenes directly on the cone 3 (of angle between 10 ° and 40 °) and makes it possible to exert on it the greatest possible pressure, by recompression of the flow, thus ensuring a maximum stabilizing efficiency of the cone 3.
  • the pressure at the level of the impact on the cone 3 is multiplied approximately by 2 with respect to the initial pressure at the annular face 5.
  • This strong pressure exerted on the stabilizing cone 3 causes a stabilizing effect of the cone much higher than that which would be obtained with a projectile of the same geometry but in which there would be a more progressive variation of the aerodynamic flow without detachment of the boundary layer (for example with a projectile having a conical profile surface between the gauge body and the cylindrical bearing surface 4).
  • the projectile may have a length L1 of the tail tail 7 which is less than 40% of the total length L of the projectile.
  • a projectile will be stable (empirically) if its static margin is about one caliber.
  • the skilled person will define the geometry of the projectile providing stability by acting on the position of the center of gravity C which can be positioned in front of the projectile by adopting a material for the front portion 2a of the body which will be denser than the material of the empennage tail 7 and the rear portion 8 of the body.
  • a ballast may be attached to the front of the body to advance the center of gravity.
  • the focus of the aerodynamic forces will be positioned by playing both on the height H of the step formed by the annular rear face 5 (half gap between D1 and D2), the length L3 of the cylindrical scope (retaining the relative proportions between H and L3 mentioned previously) and on the angle of the cone 3.
  • the essential point is that the ratio between the length L3 of the cylindrical bearing surface 4 and the height H of the rear face 5 is between 1.5 and 3.5 and that the angle of the cone 3 is between 10 ° and 40 °. °.
  • the figure 2 shows another embodiment of an exercise projectile according to the invention, projectile which differs from the previous one in that the cone 3 has a rear portion 17 which is cylindrical and which is followed by a narrowing of conical base 13.
  • This device allows in the case of an exercise projectile to adjust the aerodynamic drag of the projectile to ensure better ballistic similarity.
  • the cone 3 may carry peripheral notches (not shown).
  • the internal volume 11 at the cone 3 communicates with the external surface of the cylindrical seat 4 by radial bores 12.
  • the propellant gases that enter the internal volume 11 can radially out of this volume through the holes 12.
  • the internal volume 11 of the tail tail communicates here with a cavity 14 internal to the body 2 of the projectile.
  • This cavity makes it possible to receive a tracer or an impact marking load (not shown).
  • the figure 3 shows another embodiment of the invention wherein the projectile 1 is an explosive projectile. Note that the length L2 of the body 2 of the projectile is longer than that of the exercise projectiles described above.
  • the body 2 carries the belt 10 and also a front guide ring 15.
  • the internal structure of the body 2 is not shown because it is not part of the object of the present invention. It is similar to that of known projectiles and may for example comprise an explosive charge associated with a hollow charge coating.
  • the body 2 has an annular rear face 5 on which the tail tail 7 has the cylindrical bearing surface 4.
  • the empennage tail 7 may thus have a reduced length L1 which does not exceed 40% of the total length of the tail. projectile and is virtually non-intrusive in the propellant charge of the bushing.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)

Claims (10)

  1. Überschallflugprojektil (1) für eine Kanone mit glattem Lauf, mit einem Körper (2) mit dem Kaliber des Rohrs der Kanone und einem aerodynamischen Stabilisierungsmittel (3) hinter dem Körper, wobei das Projektil dadurch gekennzeichnet ist, dass das aerodynamische Stabilisierungsmittel durch einen Kegel (3) gebildet ist, dessen größter Durchmesser (D3) gleich dem Durchmesser (D2) des Körpers (2) ist, wobei der Kegel (3) mit dem Körper (2) durch eine zylindrische Fläche (4) verbunden ist und der Körper (2) senkrecht zur Achse (6) des Projektils eine ringförmige Rückseite (5) umfasst, mit der die zylindrische Fläche (4) verbunden ist, wobei die Höhe (H) der ringförmigen Seite (5) und die Länge (L3) der zylindrischen Fläche (4) definiert sind, um einen Abbruch der aerodynamischen Strömung hinter der ringförmigen Seite (5) zu sichern und dann die Wiederherstellung dieser Strömung direkt auf dem konischen Stabilisierungselement (3).
  2. Projektil nach Anspruch 1, gekennzeichnet dadurch, dass das Verhältnis zwischen der Länge (L3) der zylindrischen Fläche (4) und der Höhe (H) der ringförmigen Rückseite (5) zwischen 1,5 und 3,5 beträgt.
  3. Projektil nach einem der Ansprüche 1 oder 2, gekennzeichnet dadurch, dass die Länge (L1) des Leitwerkschwanzes (7), der durch den Kegel (3) und die zylindrische Fläche (4) gebildet wird, weniger als 40% der Gesamtlänge (L) des Projektils beträgt.
  4. Projektil nach einem der Ansprüche 1 bis 3, gekennzeichnet dadurch, dass der Kegel (3) einen Scheitelwinkel zwischen 10° und 40° hat.
  5. Projektil nach Anspruch 4, gekennzeichnet dadurch, dass der Kegel (3) ein zylindrisches hinteres Teil (17) umfasst, gefolgt von einer konischen Einschnürung (13).
  6. Projektil nach einem der Ansprüche 3 bis 5, gekennzeichnet dadurch, dass die zylindrische Fläche (4) radiale Bohrungen (12) umfasst, die die Außenfläche der zylindrischen Fläche (4) mit einem Volumen (11) im Innern des Leitwerkschwanzes (7) verbinden.
  7. Projektil nach einem der Ansprüche 3 bis 6, gekennzeichnet dadurch, dass der Leitwerkschwanz (7) mit einem Ring (8) verbunden ist, der den Durchmesser des Körpers (2) und eine ringförmige Rückseite (5) hat, wobei der Ring (8) ein hinteres Teil des Körpers bildet und an einem Vorderteil (2a) des Körpers befestigt ist.
  8. Projektil nach Anspruch 7, gekennzeichnet dadurch, dass das Vorderteil (2a) des Körpers aus Stahl ist und der Leitwerkschwanz (7) und das hintere Teil (8) des Körpers in Aluminiumlegierung sind.
  9. Projektil nach einem der Ansprüche 1 bis 8, gekennzeichnet dadurch, dass es ein träges Übungsprojektil bildet.
  10. Projektil nach einem der Ansprüche 1 bis 8, gekennzeichnet dadurch, dass es ein Sprenggeschoss bildet.
EP15160232.3A 2014-04-08 2015-03-23 Überschallflugprojektil für eine waffe mit glattem lauf Active EP2930460B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL15160232T PL2930460T3 (pl) 2014-04-08 2015-03-23 Naddźwiękowy pocisk do działa gładkolufowego

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1400879A FR3019642B1 (fr) 2014-04-08 2014-04-08 Projectile a vol supersonique pour canon a tube lisse

Publications (2)

Publication Number Publication Date
EP2930460A1 EP2930460A1 (de) 2015-10-14
EP2930460B1 true EP2930460B1 (de) 2018-03-07

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ID=51225592

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Application Number Title Priority Date Filing Date
EP15160232.3A Active EP2930460B1 (de) 2014-04-08 2015-03-23 Überschallflugprojektil für eine waffe mit glattem lauf

Country Status (5)

Country Link
EP (1) EP2930460B1 (de)
ES (1) ES2667689T3 (de)
FR (1) FR3019642B1 (de)
NO (1) NO2930460T3 (de)
PL (1) PL2930460T3 (de)

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US463922A (en) * 1891-11-24 Philip g
US2494026A (en) * 1945-03-28 1950-01-10 Anderson Nelson Projectile
USH112H (en) * 1984-03-30 1986-08-05 The United States Of America As Represented By The Secretary Of The Army Projectile stabilizer
DE4132659A1 (de) 1991-10-01 1993-04-08 Rheinmetall Gmbh Fluegelstabilisiertes uebungsgeschoss
US5328130A (en) * 1993-01-04 1994-07-12 The United States Of America As Represented By The Secretary Of The Army Stabilizer for a cannon projectile
US7150234B2 (en) * 2004-09-30 2006-12-19 The United States Of America As Represented By The Secretary Of The Army Finless training projectile with improved flight stability over an extended range
DE102005036574A1 (de) 2005-08-01 2007-02-08 Rheinmetall Waffe Munition Gmbh Projektil mit einem Kegelleitwerk
DE102012006892B3 (de) 2012-04-05 2013-01-24 Rheinmetall Waffe Munition Gmbh Leitwerkstabilisiertes Vollkaliber-Übungsgeschoss und Verfahren zu seiner Herstellung

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
FR3019642A1 (fr) 2015-10-09
ES2667689T3 (es) 2018-05-14
EP2930460A1 (de) 2015-10-14
FR3019642B1 (fr) 2018-08-31
PL2930460T3 (pl) 2018-08-31
NO2930460T3 (de) 2018-08-04

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