EP4589243A1 - Leitwerkstabilisiertes artilleriegeschoss mit einer leitwerkschutzverkleidung, die durch entnahme von treibladungsgasen abgeworfen werden kann - Google Patents

Leitwerkstabilisiertes artilleriegeschoss mit einer leitwerkschutzverkleidung, die durch entnahme von treibladungsgasen abgeworfen werden kann

Info

Publication number
EP4589243A1
EP4589243A1 EP25152113.4A EP25152113A EP4589243A1 EP 4589243 A1 EP4589243 A1 EP 4589243A1 EP 25152113 A EP25152113 A EP 25152113A EP 4589243 A1 EP4589243 A1 EP 4589243A1
Authority
EP
European Patent Office
Prior art keywords
projectile
base
cowling
tail
volume
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.)
Pending
Application number
EP25152113.4A
Other languages
English (en)
French (fr)
Inventor
Sylvain PINOTEAU
Quentin Morvan
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.)
KNDS Ammo France SA
Original Assignee
KNDS Ammo France SA
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 KNDS Ammo France SA filed Critical KNDS Ammo France SA
Publication of EP4589243A1 publication Critical patent/EP4589243A1/de
Pending legal-status Critical Current

Links

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
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F42B10/16—Wrap-around fins
    • 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
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F42B10/18—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel using a longitudinally slidable support member
    • 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
    • F42B10/20—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel deployed by combustion gas pressure, or by pneumatic or hydraulic forces
    • 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
    • F42B10/26—Stabilising arrangements using spin
    • F42B10/28—Stabilising arrangements using spin induced by gas action
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B14/00—Projectiles or missiles characterised by arrangements for guiding or sealing them inside barrels, or for lubricating or cleaning barrels
    • F42B14/06—Sub-calibre projectiles having sabots; Sabots therefor

Definitions

  • the field of the invention is that of field artillery projectiles stabilized by tail.
  • a tail is commonly used to stabilize a projectile fired from a large or medium caliber smoothbore or rifled gun. Fixed tails and deploying tails are known.
  • the deploying tail has the advantage of being less cumbersome in length than the fixed tail, which, to be effective, must be pushed far back from the body of the projectile. In fact, for a smaller footprint, the deploying tail allows for better stabilization, and therefore greater accuracy. In addition, the deploying tail allows firing using a tube of the same caliber as the projectile.
  • the French patent is known FR3094475 B1 a projectile which has a shroud covering the sides and bottom of the projectile base, and therefore covering the pivoting fins housed by the base.
  • This shroud has an annular bulge or ferrule which is located at the front edge of the shroud and which is sized so that it can be applied radially tight against the base of the projectile.
  • the centrifugal force applied to the ferrule and the lack of support by the tube will cause the ferrule, which has been weakened by the passage through the tube, and the front edge of the shroud to burst, which will cause the shroud to separate from the base, favorable to the deployment of the fins.
  • the empennage comprises several deployable fins and the cowling is divided into several segments, each segment covering a fin in the folded position, a borrow volume being arranged axially between each segment and the base.
  • the borrowing volume 6 has at least one filling opening 7 opening into the volume delimited by the tube 10 at the rear AR of the base 3, thus making it possible to put the internal volume of the tube 10 at the rear AR of the projectile 1 and the borrowing volume 6 into fluid communication.
  • a single filling opening 7 is provided through the cowling 5. This is an axial opening passing through the annular plate 500.
  • the gas borrowed during the firing phase and therefore contained in the borrowed volume 6 will find itself under overpressure relative to the atmospheric air.
  • This overpressure gas will then generate a thrust force P (represented on the Figure 3 ) at the rear of the borrow volume 6, in particular an axial thrust on the thrust face 52 of the cowling 5.
  • This thrust force P causes the cowling 5 to separate by relative to the base 3, in particular a separation of the collar 511 relative to the groove 310, and the displacement of the cover 5 along the base 3.
  • the cover 5 is therefore ejected, as can be seen in the Figure 2 , like a piston in a cylinder which moves under the effect of the pressure which is present in the chamber.
  • the present invention makes it possible to protect the deploying tail 4 of the projectile 1 during the firing phase by means of the cowling 5 ( Figure 1 ) while allowing efficient ejection of the cowling 5 on the trajectory at the exit of the tube 10 ( Figure 2 ), using the pressure of the firing gas G used during the propulsion phase of the projectile 1 in the gun tube 10.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Toys (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP25152113.4A 2024-01-17 2025-01-15 Leitwerkstabilisiertes artilleriegeschoss mit einer leitwerkschutzverkleidung, die durch entnahme von treibladungsgasen abgeworfen werden kann Pending EP4589243A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR2400357A FR3158359A1 (fr) 2024-01-17 2024-01-17 Projectile d'artillerie stabilisé par emprennage comportant un capotage de protection d'empennage éjectable par emprunt de gaz de tir.

Publications (1)

Publication Number Publication Date
EP4589243A1 true EP4589243A1 (de) 2025-07-23

Family

ID=91247400

Family Applications (1)

Application Number Title Priority Date Filing Date
EP25152113.4A Pending EP4589243A1 (de) 2024-01-17 2025-01-15 Leitwerkstabilisiertes artilleriegeschoss mit einer leitwerkschutzverkleidung, die durch entnahme von treibladungsgasen abgeworfen werden kann

Country Status (3)

Country Link
EP (1) EP4589243A1 (de)
KR (1) KR20250112711A (de)
FR (1) FR3158359A1 (de)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2221707B1 (de) 1973-03-14 1976-04-30 France Etat
EP1321737A2 (de) 2001-12-18 2003-06-25 Diehl Munitionssysteme GmbH & Co. KG Aus einem Rohr zu verschiessender Flugkörper mit überkalibrigem Leitwerk
US7226016B2 (en) 2000-07-03 2007-06-05 Bae Systems Bofors Ab Method and arrangement for low or non-rotating artillery shells
FR3094475B1 (fr) 2019-03-27 2022-08-12 Nexter Munitions Capotage et projectile comportant un tel capotage

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2221707B1 (de) 1973-03-14 1976-04-30 France Etat
US7226016B2 (en) 2000-07-03 2007-06-05 Bae Systems Bofors Ab Method and arrangement for low or non-rotating artillery shells
EP1321737A2 (de) 2001-12-18 2003-06-25 Diehl Munitionssysteme GmbH & Co. KG Aus einem Rohr zu verschiessender Flugkörper mit überkalibrigem Leitwerk
FR3094475B1 (fr) 2019-03-27 2022-08-12 Nexter Munitions Capotage et projectile comportant un tel capotage

Also Published As

Publication number Publication date
FR3158359A1 (fr) 2025-07-18
KR20250112711A (ko) 2025-07-24

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