EP2336711B1 - Dispositif de lancement pour projectile d'artillerie sous calibré - Google Patents

Dispositif de lancement pour projectile d'artillerie sous calibré Download PDF

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Publication number
EP2336711B1
EP2336711B1 EP10290641.9A EP10290641A EP2336711B1 EP 2336711 B1 EP2336711 B1 EP 2336711B1 EP 10290641 A EP10290641 A EP 10290641A EP 2336711 B1 EP2336711 B1 EP 2336711B1
Authority
EP
European Patent Office
Prior art keywords
tooth
projectile
launching device
base
hinge
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
EP10290641.9A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2336711A1 (fr
Inventor
Lionel Caillat
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
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 PL10290641T priority Critical patent/PL2336711T3/pl
Publication of EP2336711A1 publication Critical patent/EP2336711A1/fr
Application granted granted Critical
Publication of EP2336711B1 publication Critical patent/EP2336711B1/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
    • 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

Definitions

  • the technical field of the invention is that launching devices for firing sub-calibrated artillery projectiles from a weapon tube.
  • the solution of the pyrotechnic ejector is complex since the firing must be done accurately and reliably.
  • the ejector pulse can disturb the trajectory of the projectile if this pulse is not perfectly coaxial with the trajectory.
  • the maintenance of the hoof sectors on the projectile requires machining on the projectile to be able to place cutting pieces at the start of the stroke. These pieces require accurate calibration at break.
  • Calibrated projectiles of medium caliber which comprise a shoe integral with a base and which bursts at the exit of the barrel of the weapon by the effect of the centrifugal force.
  • Such projectiles are described for example by patents US 4419796 , DE-1262830 and US 4476785 .
  • hooves are generally integral with the pellet and include rupture primers to facilitate the release of the projectile.
  • Such solutions are not transferable to an artillery projectile whose rotation is reduced by the effect of a slipping belt.
  • the patent GB-123501 succinctly describes a calibrated projectile of large caliber (406 mm) having joints of its hoof sectors on the base. These joints open by the action of centrifugal force. However, the joints are not clearly defined by this patent. These articulations make it possible to push the pellet towards the rear, clearing the projectile. It even seems that the sectors remain attached to the base at the level of their joints as the figure 3 suggest it.
  • the invention proposes to improve the release of the projectile by connecting the shoe sectors to the base by a joint having a particular geometry not causing interference between the shoe sectors and the base.
  • the spacing of the sectors is done symmetrically so as not to disturb the trajectory of the projectile and the base is also removed from the projectile by the support of the sectors on the base combined with the effort generated by its own aerodynamic drag .
  • the subject of the invention is a device for launching a sub-calibrated artillery projectile, launch device comprising at its rear part a base comprising on its periphery a slipping belt, base containing a rear part of the projectile and having a thrust surface cooperating with a complementary surface of the rear of the projectile, launching device characterized in that it comprises at least two sectors of cylinder surrounding the projectile and intended to provide guidance by means of bands of outer annular bearing surfaces, sectors in contact by at least one form of internal support with the projectile, launching device comprising for each sector at least one articulation embodying an instantaneous axis of rotation, detachable articulation in flight and connecting the base to the sector considered, the articulation being constituted by at least one notch on the base, which cooperates with a tooth connected to the sector, the notch being bounded at the front by a sloped flat surface and at the back by a surf a stop perpendicular to the longitudinal axis of the projectile and cooperating
  • the notch comprises an inclined surface forming an angle ⁇ , greater than or equal to 90 degrees with a notional plane F passing through the instantaneous axis of rotation and by a point of contact between the tooth and the inclined surface, any part of the tooth placed between the imaginary plane F and the abutment surface being at a distance from the instantaneous axis of rotation which is less than the distance separating the latter axis and the point of contact between the tooth and inclined surface.
  • the articulation may comprise at least one means for adjusting the axial backlash between the base and the sector.
  • This means of adjusting the axial backlash may comprise at each joint at least one integral pressure screw by a tapping of the tooth and bearing on the inclined surface of the notch.
  • the device may comprise at least one clamping means of the hinge opposing the radial spacing between the base and the sectors when they are in contact with the projectile.
  • This clamping means may thus comprise at each articulation at least one clamping screw traversing with a tapping the tooth, clamping screw oriented so as to penetrate towards the rear of the launching device and penetrating into a clearance made in the notch of the base, release in contact with the clamping screw so as to prevent any radial movement of the tooth with respect to the base.
  • the surfaces of the clearance will be selected with dimensions such that they escape any interference with the clamping screw when the latter operates a rotation about the instantaneous axis of rotation in the direction of the opening of the sectors.
  • the launching device 1 contains a projectile 2.
  • This device is formed of a base 3 on its rear part.
  • the base is equipped with a slip belt 4.
  • the base is connected to three sectors 5 forming a shoe, only two of which are visible in the drawing.
  • the connection is provided by an articulation 6 between each shoe sector 5 and the base 3.
  • the outer part of the shoe sectors 5 is in contact with the inside of the weapon tube by means of bands 5b, 5c forming annular bearings (Tapes made for example of plastic).
  • the device as shown in this drawing is in the configuration where it is once set up in the chamber of a weapon and on its entire trajectory in the barrel of the weapon.
  • the fins 2a of the projectile 2 are contained in the base 3.
  • the base 3 comprises a thrust surface 3a bears with a corresponding rear surface of the projectile 2.
  • the base 3 has not shown grooves opening on this thrust surface 3a so let the fins 2a pass during the separation base 3 / projectile 2.
  • the hoof sectors 5 comprise flared inner support forms 5a in contact with the projectile 2 to center it on the longitudinal axis of the launching device.
  • the device 1 will open in the following manner.
  • the pressure of the air exerted on the flared support forms 5a of each sector 5 will cause a symmetrical spacing (arrows 11) of the sectors 5 with breaking annular bearing bands 5b and 5c.
  • These sectors 5 resting on the base 3 via the joints 6 will push the base 3 towards the rear, causing it to deviate from the rear of the projectile 2 and to release the fins 2a.
  • no radial force on the projectile 2 will have been produced.
  • the articulations 6 (which are not integral with the base) will become detached from the base 3 and each piece of the device 1 will be projected out of the trajectory of the projectile 2.
  • each hinge 6 comprises a tooth 6a inserted in a corresponding notch 3b, made in the base 3.
  • the notch 3b of a width substantially equal to the width of the tooth 6a, is delimited at the front by a flat surface inclined 3c and rear by a 3d surface, said abutment surface, perpendicular to the longitudinal axis of the launcher 1.
  • the tooth 6a has at its base an edge 6b placed towards the rear of the device. This edge 6b brought into contact with the abutment surface 3d constitutes an instantaneous axis of rotation 7 of the tooth 6a during the opening of the sector 5.
  • any part of the tooth located behind the plane F must be at a distance less than R from the instantaneous axis of rotation 7.
  • a needle screw 9 (or clamping screw) is inclined so that it has a penetration angle facing the rear of the launching device 1.
  • This clamping screw 9 passes through the tooth 6 by a tapping 6g to enter
  • This clamping screw 9 will provide a clamping function by penetrating into the clearance 10 until it contacts the chamfer 10d of the clearance 10 but only on the part of the most oriented chamfer 10d. towards the rear of the launching device 1 (upper part of the clearance 10 on the figure 6 ).
  • the interference between the clamping screw 9 and the chamfer 10d does not allow the tooth 6a to deviate radially from the base 3 in the direction Z.
  • the clearance 10 is chosen with a sufficiently large diameter so that, during the rotation of the tooth 6a around the instantaneous axis of rotation 7, due to the opening of the sectors 5, the clearance 10 does not interfere with the screw 9.
  • the clearance 10 may be an oblong grooving.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Pivots And Pivotal Connections (AREA)
EP10290641.9A 2009-12-21 2010-12-06 Dispositif de lancement pour projectile d'artillerie sous calibré Active EP2336711B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL10290641T PL2336711T3 (pl) 2009-12-21 2010-12-06 Wyrzutnia artyleryjskiego pocisku podkalibrowego

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0906206A FR2954485B1 (fr) 2009-12-21 2009-12-21 Dispositif de lancement pour projectile d'artillerie sous calibre.

Publications (2)

Publication Number Publication Date
EP2336711A1 EP2336711A1 (fr) 2011-06-22
EP2336711B1 true EP2336711B1 (fr) 2013-06-05

Family

ID=42313522

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10290641.9A Active EP2336711B1 (fr) 2009-12-21 2010-12-06 Dispositif de lancement pour projectile d'artillerie sous calibré

Country Status (5)

Country Link
US (1) US8333153B2 (pl)
EP (1) EP2336711B1 (pl)
ES (1) ES2426471T3 (pl)
FR (1) FR2954485B1 (pl)
PL (1) PL2336711T3 (pl)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101730664B1 (ko) 2009-02-02 2017-04-26 에어로바이론먼트, 인크. 멀티모드 무인 항공기
DK3133019T3 (en) 2009-09-09 2019-02-18 Aerovironment Inc NOISE DEVICE FOR A DRONE PROTECTION PIPE
JP5886201B2 (ja) 2009-09-09 2016-03-16 エアロバイロメント, インコーポレイテッドAerovironment, Inc. エレボン制御システム
AU2013309464B2 (en) * 2012-06-07 2016-08-04 Aerovironment, Inc. System for detachably coupling an unmanned aerial vehicle within a launch tube
KR101295318B1 (ko) * 2013-01-09 2013-08-09 국방과학연구소 플레어가 장착된 탄두용 이탈피
US8931416B2 (en) * 2013-03-07 2015-01-13 The United States Of America As Represented By The Secretary Of The Navy Inert and pressure-actuated submunitions dispensing projectile
US10502515B2 (en) * 2017-01-17 2019-12-10 Raytheon Company Launch piston brake
US10996037B2 (en) * 2018-09-04 2021-05-04 The United States Of America As Represented By The Secretary Of The Army Obturator for robust and uniform discard
US10443993B1 (en) * 2018-11-29 2019-10-15 The United States Of America As Represented By The Secretary Of The Army Spin discarding multiple projectile sabot
CN112611273B (zh) * 2020-11-27 2022-08-23 江苏科技大学 一种多破片同步高速发射弹托及其使用方法
FR3116894B1 (fr) * 2020-12-02 2022-10-28 Nexter Munitions Projectile gyrostabilisé

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB123501A (en) * 1918-02-12 1919-02-27 John William Rooney Improvements in Shells used in Warfare.
DE1262830B (de) * 1964-09-02 1968-03-07 Bundesrep Deutschland Treibspiegel fuer Unterkalibergeschosse
DE2738121A1 (de) * 1977-08-24 1979-03-01 Rheinmetall Gmbh Gewehrpatrone mit einem das unterkalibergeschoss umschliependen kunststoffmantel
US4296687A (en) * 1979-07-16 1981-10-27 The United States Of America As Represented By The Secretary Of The Army Segmented sabot projectile
DE3131540C2 (de) * 1981-08-08 1986-02-13 Mauser-Werke Oberndorf Gmbh, 7238 Oberndorf Treibspiegelgeschoß
US4419796A (en) * 1981-09-24 1983-12-13 Honeywell Inc. Method of making spin stabilized discarding sabot projectile
US4841867A (en) * 1987-12-28 1989-06-27 Ford Aerospace Corporation Discarding sabot projectile
FR2653873B1 (fr) * 1989-10-26 1992-01-03 France Etat Armement Projectile sous-calibre comportant un noyau, un sabot et une chemise.
AT399583B (de) * 1991-07-17 1995-06-26 Steyr Daimler Puch Ag Unterkalibriges geschoss mit abwerfbarem käfig
AT399582B (de) * 1991-07-17 1995-06-26 Steyr Daimler Puch Ag Unterkalibriges geschoss mit treibspiegel
DE19650739C2 (de) * 1996-12-06 1999-12-16 Rheinmetall W & M Gmbh Unterkalibriges Geschoß
FR2768809B1 (fr) * 1997-09-24 1999-10-15 Giat Ind Sa Projectile d'artillerie de campagne de gros calibre a longue portee
EP0918209B1 (de) * 1997-11-19 2002-12-18 Oerlikon Contraves Ag Geschoss mit programmierbarem Zeitzünder

Also Published As

Publication number Publication date
US8333153B2 (en) 2012-12-18
ES2426471T3 (es) 2013-10-23
PL2336711T3 (pl) 2013-10-31
FR2954485A1 (fr) 2011-06-24
US20110146525A1 (en) 2011-06-23
FR2954485B1 (fr) 2012-05-11
EP2336711A1 (fr) 2011-06-22

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