EP3489617A1 - Projektil - Google Patents

Projektil Download PDF

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Publication number
EP3489617A1
EP3489617A1 EP18207856.8A EP18207856A EP3489617A1 EP 3489617 A1 EP3489617 A1 EP 3489617A1 EP 18207856 A EP18207856 A EP 18207856A EP 3489617 A1 EP3489617 A1 EP 3489617A1
Authority
EP
European Patent Office
Prior art keywords
projectile
flange
cup
edge
seal
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
EP18207856.8A
Other languages
English (en)
French (fr)
Other versions
EP3489617B1 (de
Inventor
Sylvain PINOTEAU
Quentin Morvan
Hervé Vacher
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
Original Assignee
Nexter Munitions 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 Nexter Munitions SA filed Critical Nexter Munitions SA
Priority to PL18207856T priority Critical patent/PL3489617T3/pl
Publication of EP3489617A1 publication Critical patent/EP3489617A1/de
Application granted granted Critical
Publication of EP3489617B1 publication Critical patent/EP3489617B1/de
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
    • 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
    • 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
    • F42B14/064—Sabots enclosing the rear end of a kinetic energy projectile, i.e. having a closed disk shaped obturator base and petals extending forward from said base
    • 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
    • F42B10/44—Boat-tails specially adapted for drag reduction
    • 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
    • F42B14/02—Driving bands; Rotating bands
    • 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
    • F42B14/067—Sealing aspects in sabots, e.g. sealing between individual segments of the sabots or sealing between the outer surface of the sabot and the inner surface of the barrel

Definitions

  • the technical field of the invention relates to projectiles comprising a belt and a rear cup which is intended to be dropped on trajectory.
  • a known projectile 1 of this type is shown in FIGS. 1a to 1c. It comprises a cup 5 which is intended to contain and protect a stabilizer of the projectile 1 during the storage operations, transport and especially during the barrel firing phase of the projectile.
  • a belt 3 of the projectile is there to seal the gas between the projectile and the barrel when firing the projectile.
  • a flange 4 which is centered by an annular portion 4a on the projectile.
  • the cup 5 comprises a wall 5b which extends from the bottom of the cup to under the flange 4.
  • An O-ring 8 is centered on the body 2 of the projectile 1 and it pinches the edge of the wall 5b against the inside of the collar 4.
  • the firing gases can not enter the cup 5 at the edge 5c of the wall 5b.
  • the cup 5 is separated from the rest of the projectile by means known to those skilled in the art and as disclosed in the patent EP1297292 for example.
  • the belt 3 is dislocated by the rotation of the projectile which improves the overall aerodynamics of the projectile by reducing the surface opposite the advancement.
  • the bulge comprises a groove 7 which accommodates the O-ring 8, this groove causes a discontinuity in the flow of air ( figure 1c ) which forms a second aerodynamic brake and therefore limits the scope of the projectile.
  • the invention aims to improve the scope of the projectile by reducing sources of aerodynamic braking.
  • the invention relates to a projectile comprising an ejectable cup for protecting during firing a base of the projectile vis-à-vis the propellant gas, the cup having a bottom located at the rear of the projectile and a wall surrounding the base and extending longitudinally to a position where the edge of the wall is clamped between a seal surrounding the body of the projectile and a flange also surrounding the projectile, flange comprising an annular portion centered on a first cylindrical surface of the body of the projectile having a first diameter, the collar being located behind a projectile belt which is centered on a second cylindrical bearing surface of the body having a second diameter, projectile characterized in that the first bearing is separated from the second bearing by a shoulder whose face is directed towards the rear of the projectile, a clamping means pressing the seal against the annular portion of the collar this causes the radial expansion of the seal which is thus pressed against the edge of the cup, itself pressed against the inside of the collar.
  • the clamping means comprises a nut screwed onto a thread centered on the projectile body, Thread whose outer diameter is less than or equal to the first diameter, the nut being fragmentable by the action of the centrifugal forces developed during firing.
  • the seal comprises at least one axial stack of elastic rings.
  • each elastic ring is composed of the assembly of a plurality of contiguous sectors whose junctions are angularly distributed in an equal manner and such that for a first ring the junction zones are angularly offset relative to the junction zones of a second neighboring ring.
  • the flange is composed of the assembly of a plurality of contiguous sectors whose junctions are angularly distributed equally, the annular portion of the flange is located opposite the inside of the flange thus forming a chute adapted to correspond with the edge of the cup and is located partly between the edge of the cup and the projectile body which prevents the radial disunion of the collar.
  • Figures 1a, 1b and 1 C show a projectile according to the state of the art.
  • a projectile 1 comprises a projectile body 2 surrounded by a belt 3 disposed in a groove 3a.
  • the rear of the body 2 of the projectile 1 is contained in a cup 5 which has a bottom 5a and a wall 5b which surrounds the rear of the projectile body 2 and extends from the bottom 5a to a flange 4 situated behind the the belt 3.
  • the flange 4 comprises an annular portion 4a centered on the body of the projectile 1 and leaning against the belt 3. It is recalled that the belt 3 serves to seal the connection between the projectile 1 and the inner wall of a barrel 100 so that the propellant gases remain behind the projectile and do not leak around the projectile.
  • the projectile thus comprises a circular bulge 6 having a groove 7 which accommodates an O-ring 8.
  • the edge 5c of the wall 5b of the cup 5 passes under the flange 4 and is clamped between the O-ring 8 and the inner face of the flange 4.
  • the gases can not infiltrate inside the cup 5 by crossing the edge 5c.
  • the cup 5 is released by means known to those skilled in the art such as those disclosed in the patent EP1297292 and which are not the subject of the present invention.
  • the belt 3 is no longer maintained either by the barrel of the weapon and it is dislocated by the rotation of the projectile 1.
  • the flange 4 remains in place as visible in FIG. figure 1c behind the throat 3a which received the belt.
  • the rear of the projectile 1 is then released and the fins 200 to increase the range of the projectile 1 can be deployed (here fins formed of sheets wound around the rear of the projectile and which expand elastically).
  • FIGS. 2a , 2b and 2c show a projectile according to one embodiment of the invention.
  • the projectile 1 comprises a cup 5, the edge 5c of the wall 5b is located under a flange 4 and between a gasket 8 centered on the projectile body.
  • the flange 4 comprises an annular portion 4a centered on a first cylindrical surface of the body 2 of the projectile which has a first diameter D1 and is leaned against a belt 3 itself centered on a second cylindrical surface of the body 2 of the projectile which has a second diameter D2.
  • the first diameter D1 is smaller than the second diameter D2 so as to form a shoulder 10 whose annular face is directed towards the rear AR of the projectile 1.
  • the elastic rings 11 and 12 are crushed against the annular portion 4a of the flange 4 by a clamping means 13 comprising a nut screwed onto a thread 14 made on the first diameter D1 of the projectile body, a clamping means comprising a nut 13.
  • the pressure exerted by the clamping means 13 causes the radial expansion of the elastic rings 11 and 12 which are compressed against the edge 5c of the cup 5, itself pressed against the inside of the collar 4.
  • the elastic rings 11 and 12 may be replaced by an O-ring.
  • the seal thus produced prevents the propellant gases from crossing the edge 5c of the cup.
  • the flange 4 and its annular portion 4a are composed of several sectors joined two by two whose junctions are distributed angularly in an equal manner.
  • the annular portion 4a of the flange 4 is located facing the inside of the flange 4 thereby forming a chute 4c adapted to correspond with the edge 5c of the cup 5.
  • This annular portion 4a is thus located partly between the edge 5c of the cup 5 and the projectile body 2 which prevents the radial disunion of the flange 4 by the edge 5c of the cup 5 which opposes any radial movement of the part
  • the elastic rings 11 and 12 comprise two-to-two contiguous sectors whose junctions are distributed angularly in an equal manner. Thanks to the edge 5c of the cup, any radial movement of the ring sectors 11 and 12 is blocked, which maintains the integrity of the elastic rings.
  • each ring sector of the same first ring 11 are offset axially relative to the junctions of the sectors of a second ring 12 adjacent so that each junction is facing a sector adjacent ring to improve the sealing provided by the ring sectors 11 and 12.
  • the clamping means 13 comprises fragmentation lines which allow it to burst by the centrifugal force once the flange 4 has been released.
  • the fins 200 are deployed. Note that the projectile body 2 exposes, in the air flow order P along its profile, the second bearing having a second diameter D2 greater than the first diameter D1 of the first bearing and that all the changes in diameter D following towards the rear AR of the projectile 1 are of decreasing dimensions which makes it possible not to oppose frontal resistance to the flow P of the air and thus to the penetration of the projectile 1 in the air.
  • the invention therefore makes it possible not to reduce the range unlike the solution according to the state of the art and the rear part of the projectile nevertheless remains protected from the gases during the firing phase.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP18207856.8A 2017-11-24 2018-11-22 Projektil Active EP3489617B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL18207856T PL3489617T3 (pl) 2017-11-24 2018-11-22 Pocisk

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1701228A FR3074282B1 (fr) 2017-11-24 2017-11-24 Projectile

Publications (2)

Publication Number Publication Date
EP3489617A1 true EP3489617A1 (de) 2019-05-29
EP3489617B1 EP3489617B1 (de) 2020-07-29

Family

ID=61913213

Family Applications (1)

Application Number Title Priority Date Filing Date
EP18207856.8A Active EP3489617B1 (de) 2017-11-24 2018-11-22 Projektil

Country Status (5)

Country Link
US (1) US10520290B2 (de)
EP (1) EP3489617B1 (de)
ES (1) ES2818049T3 (de)
FR (1) FR3074282B1 (de)
PL (1) PL3489617T3 (de)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11674782B1 (en) * 2020-08-28 2023-06-13 The United States Of America As Represented By The Secretary Of The Army Piston actuated extended range projectile with segmented slip band
US11402188B1 (en) * 2020-08-28 2022-08-02 The United States Of America As Represented By The Secretary Of The Army Pyrotechnic delayed extended range shotgun munition

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1297292A1 (de) * 2000-07-03 2003-04-02 Bofors Defence AB Verfahren und vorrichtung für artilleriegeschosse
US20130284045A1 (en) * 2011-02-01 2013-10-31 Korea Nuclear Engineering Co., Ltd. Ammunition
US20150330755A1 (en) * 2014-04-30 2015-11-19 Bae Systems Land & Armaments L.P. Gun launched munition with strakes

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3738279A (en) * 1970-07-24 1973-06-12 Us Navy Sabot for sub-calibre projectile
US3927618A (en) * 1971-03-29 1975-12-23 Oerlikon Buehrle Ag Sabot projectile
DE2407220A1 (de) * 1974-02-15 1980-09-04 Rheinmetall Gmbh Unterkalibergeschoss
DE102008029395A1 (de) * 2008-06-23 2009-12-24 Rheinmetall Waffe Munition Gmbh Treibkäfiggeschoss

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1297292A1 (de) * 2000-07-03 2003-04-02 Bofors Defence AB Verfahren und vorrichtung für artilleriegeschosse
US20130284045A1 (en) * 2011-02-01 2013-10-31 Korea Nuclear Engineering Co., Ltd. Ammunition
US20150330755A1 (en) * 2014-04-30 2015-11-19 Bae Systems Land & Armaments L.P. Gun launched munition with strakes

Also Published As

Publication number Publication date
US10520290B2 (en) 2019-12-31
ES2818049T3 (es) 2021-04-09
US20190162512A1 (en) 2019-05-30
FR3074282B1 (fr) 2019-10-11
EP3489617B1 (de) 2020-07-29
FR3074282A1 (fr) 2019-05-31
PL3489617T3 (pl) 2020-11-02

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