EP0265369B1 - Sabot à masse réduite pour un projectile sous-calibré à vitesse élevée - Google Patents

Sabot à masse réduite pour un projectile sous-calibré à vitesse élevée Download PDF

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Publication number
EP0265369B1
EP0265369B1 EP87710017A EP87710017A EP0265369B1 EP 0265369 B1 EP0265369 B1 EP 0265369B1 EP 87710017 A EP87710017 A EP 87710017A EP 87710017 A EP87710017 A EP 87710017A EP 0265369 B1 EP0265369 B1 EP 0265369B1
Authority
EP
European Patent Office
Prior art keywords
sabot
projectile
receiver
fact
accordance
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.)
Expired - Lifetime
Application number
EP87710017A
Other languages
German (de)
English (en)
Other versions
EP0265369A2 (fr
EP0265369A3 (en
Inventor
Peter Dipl.-Ing. Rwth Wallow
Karl Wilhelm Dipl.-Ing. Rwth Bethmann
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 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 GmbH filed Critical Rheinmetall GmbH
Publication of EP0265369A2 publication Critical patent/EP0265369A2/fr
Publication of EP0265369A3 publication Critical patent/EP0265369A3/de
Application granted granted Critical
Publication of EP0265369B1 publication Critical patent/EP0265369B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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 invention relates to a sabot according to the preamble of claim 1.
  • a front-side first part of the sabot is essentially collar-shaped from four identical segments, which in the area of parting lines in a respective receptacle has a prestressed compression spring that can be relieved against the neighboring parting surface for detachment from the flight floor.
  • a rear part of the sabot is provided with a projecting receptacle of an annular cross-section for the missile in such a way that the projection engages in the center of a rear opening of the missile.
  • This known sabot has a number of disadvantages.
  • forces acting frontally against the direction of acceleration must interact with the forces from the compression springs in an essentially equilibrium manner. This results in an unmistakable sensitivity of the arrangement, which greatly affects the handling.
  • wedging may occur in the first part in such a way that subsequent acceleration of the overall arrangement cannot be achieved.
  • the usability under conditions given by a combat mission is impaired until it is completely lost and is not given at all for use in connection with barrel weapons.
  • the invention has for its object to provide a generic object, the handling and usability is guaranteed even with indispensable cadence and thereby also allows use in a barrel weapon with trouble-free detachment from the missile.
  • the fulfillment of these requirements is regarded as an essential prerequisite for the suitability for use against fast-moving targets, e.g. missiles and fighter jets, even at a great distance, whereby a carrier system can be opaque both at earth-bound and at a greater height above the earth's surface under different conditions .
  • combating fast targets close to the ground also plays an important role in ground-air operations.
  • the carrier should be considered to have a corresponding aircraft with operational mobility as well as a satellite.
  • DE-OS 29 51 904 is a sabot for a sub-caliber missile is known, which is also designed with the goal of having only a comparatively low dead weight, but it requires elements above the floor circumference to ensure a mutual positive locking in the acceleration direction, which is essential for the passage of the pipe.
  • Such or a comparable measure would, however, in the context given here, lead to such a drastic increase in the drag coefficient that the associated drop in speed of the missile would result in the inability to use the latter to combat fast flight targets at great distances.
  • a sabot according to DE-OS 33 18 972 is also unsuitable for solving the problems on which the invention is based, since apart from the considerable weight, a trouble-free detachment from the missile designed for resistance stabilization cannot be guaranteed.
  • FIGS. 1, 3 and 5 essentially being simplified longitudinal-axial sections and in FIGS. 2 and 4 being cross-sections according to the respective line II - II and IV-IV in Figures 2 and 3 respectively. Substantially identical elements are provided with the same reference symbols.
  • a conical, rotationally symmetrical missile 10.1 with a large length / diameter ratio is arranged in a thin-walled, essentially sleeve-shaped sabot 20.
  • the outer wall of the sabot 20 is essentially circular-cylindrical and (see FIG. 2) has longitudinal slots 50 and 52, so that profiled elements surrounding the missile 10.1 form.
  • brackets 40 projecting radially inwards lie in the area of a center of gravity of the missile 18 of the peripheral surface 14 of the missile 10.1 in a holding area 41 and form a front centering receptacle 20.3.
  • a second centering receptacle 20.4 on the rear is provided in the region of the missile rear part 16 by a central pin 32 which engages on the rear in a cavity 17 of the missile 10.1.
  • the sabot 20 is bounded at the back by a closed surface 54, in the vicinity of which the surrounding surface 28 has a radially deformable band-shaped element 68.
  • radially compressible elements 66 which can be connected to form a band for the purpose of better handling.
  • brackets 40 are provided with relatively small inflow surfaces 46 which are inclined inwards against the longitudinal axis A of the floor and which form the part of an air pocket 48, but at the same time passages (not specified in more detail) into a storage space 49 which is formed between the peripheral surface 14 and the inner surface 30 extends.
  • a front part 10.10 of the flight projectile 10.1 is made of a high-density material, preferably thanks to a high proportion of tungsten, which is followed by a rear part 10.11 of comparatively lower apparent density. In this way, the missile center of gravity 18 lies sufficiently far in front of an air attack point (not shown) in the acceleration direction S. 3 differs from that according to FIG.
  • a screw-in element 60 with an external thread 62 has a circular-shaped receptacle for a rear surface 19 of the missile 10.3 on the front side, not designated in more detail, and is delimited on the rear side by a rear surface 58.
  • a thread circle shown in the rear surface 58 is covered by a compressible element 68, which extends on the front side beyond the centering and fixing area 36 and thus provides for a possibly required seal and for a sufficient radial contact pressure.
  • the radially compressible elements 66 assigned on the front side of the receptacle 24.3 can, as already described in connection with the first exemplary embodiment, be connected to one another and formed in the manner of a band.
  • a front cone surface 76 on each of the drive cages shown facilitates the axial insertion of the respective arrangement in the starting position in a high-acceleration device.
  • the materials of the respective sabot are adapted in such a way that pressure forces due to acceleration, which are exerted by the respective missile, can be safely absorbed with the lowest possible dead load. If the arrangement according to the invention leaves the high-acceleration device in question, the interior 49 is already filled with air in such a way that under the effect of the air now flowing in from outside, it passes through the longitudinal slots 50 and 52 from the drive cage formed elements are pivoted lever-like in the direction of arrows K.
  • a region 37 of the sabot 24 advantageously proves to be a predetermined breaking point in such a way that the missile 10.3 can continue its movement in the S direction unhindered.
  • a smooth outer surface 14 of the missile 10.2 can be realized again, for example by an inertial body, not shown, which can move along the longitudinal axis A of the floor, or with the aid of fillers 72 which can be moved radially by springs.
  • Such frictional engagement elements 41 although not shown in the drawing, can also be arranged in the region of the first centering receptacle 24.3 in the exemplary embodiment according to FIG. 5. Since there is already a positive fit between the missile 10.3 and the sabot 24 in the centering receptacle 24.2 on the rear side, overdetermination can be avoided if the projection 44 is rigid due to its rigidity.
  • an opening path K assigned to the elements 71 (FIG. 3) is an arc with a large radius, an impairment of the behavior of the missile can be excluded.
  • the screw-in element 60 shown in FIG. 5 can advantageously have the outside diameter of the sabot 24 in its rear area.
  • the area in question, with its rear boundary surface - in particular in the case of barrel weapons - can absorb the entire gas pressure and carries the sabot 24. This can significantly increase the strength behavior during high acceleration.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Accessories Of Cameras (AREA)
  • Buildings Adapted To Withstand Abnormal External Influences (AREA)
  • Toys (AREA)

Claims (8)

  1. Cage de propulsion (20; 22; 24) pour un projectile de forme conique (10.1; 10.2; 10.3) comportant une partie avant segmentée (20.1; 22.1; 24.1) avec un premier logement de centrage (20.3; 22.3; 24.3) de la cage de propulsion (20; 22; 24) et une partie arrière (20.2; 22.2; 24.2) entourant le projectile (10.1; 10.2; 10.3) à l'extérieur comportant un deuxième logement de cent rage (20.4; 22.4; 24.4) et une surface fermée (54; 56; 58) limitant du côté du fond la partie arrière (20.2; 22.2; 24.2) caractérisée en ce que la partie avant (20.1; 22.1; 24.1) de la cage de propulsion (20; 22; 24) est reliée fixement à la partie arrière (20.2; 22.2; 24.2) de la cage de propulsion (20; 22; 24), en ce que la partie avant (20.1; 22.1; 24.1) présente en tant que premier logement de cent rage (20.3; 22.3; 24.3) un support (40; 42; 44) avec une poche d'air (48), et en ce que le premier logement de centrage (20.3; 22.3; 24.3) sert d'appui au projectile (10.1; 10.2; 10.3) dans la zone de son centre de gravité (18).
  2. Cage de propulsion selon la revendication 1, caractérisée en ce que le deuxième logement de centrage (24.4) constitue une liaison avec concordance de forme, vis à vis d'un mouvement relatif axial du projectile (10.3) dans la direction de l'accélération (S), entre la partie arrière (24.2) et le projectile (10.3).
  3. Cage de propulsion selon la revendication 1, caractérisée en ce que des éléments de liaison par concordance de forme (71) sollicitables par des forces transversales sont disposés entre la partie avant (20.1; 22.1 ; 24.1) et une première zone (10.20) du projectile (10.2).
  4. Cage de propulsion selon la revendication 1, caractérisée par un élément de liaison par frottement (41), compressible radialement, disposé dans le premier logement (20.3 ; 22.3).
  5. Cage de propulsion selon la revendication 1 ou 2, caractérisée en ce que la cage de propulsion (24) présente dans sa partie arrière (24.2) une ouverture (59), pourvue d'un taraudage (59.1), qui sert de logement à un élément à visser en forme de cylindre circulaire (60) et dont le diamètre est plus important que le diamètre le plus grand (D) du projectile (10.3).
  6. Cage de propulsion selon l'une des revendications 1 à 5, caractérisée en ce que le premier logement (20. 3; 22.3; 24.3) est formée par des saillies (40; 42; 44) s'étendant radialement contre la première zone.
  7. Cage de propulsion selon l'une des revendications 1 à 6, caractérisée en ce que la partie arrière (20.2; 22.2; 24.2) est pourvue extérieurement d'un élément en forme de ruban (68) compressible radialement.
  8. Cage de propulsion selon l'une des revendications 1 à 7, caractérisée en ce que la partie avant (20.1; 22.1; 24.1) est pourvue extérieurement, au voisinage du premier logement (20.3; 22.3; 24.3), d'un élément (66) en forme de ruban compressible radialement.
EP87710017A 1986-10-21 1987-10-20 Sabot à masse réduite pour un projectile sous-calibré à vitesse élevée Expired - Lifetime EP0265369B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19863635738 DE3635738A1 (de) 1986-10-21 1986-10-21 Treibkaefig-fluggeschoss-anordnung
DE3635738 1986-10-21

Publications (3)

Publication Number Publication Date
EP0265369A2 EP0265369A2 (fr) 1988-04-27
EP0265369A3 EP0265369A3 (en) 1989-01-25
EP0265369B1 true EP0265369B1 (fr) 1991-09-11

Family

ID=6312129

Family Applications (2)

Application Number Title Priority Date Filing Date
EP87109633A Withdrawn EP0264546A3 (fr) 1986-10-21 1987-07-04 Ensemble d'un projectile et son sabot
EP87710017A Expired - Lifetime EP0265369B1 (fr) 1986-10-21 1987-10-20 Sabot à masse réduite pour un projectile sous-calibré à vitesse élevée

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP87109633A Withdrawn EP0264546A3 (fr) 1986-10-21 1987-07-04 Ensemble d'un projectile et son sabot

Country Status (3)

Country Link
US (1) US4850280A (fr)
EP (2) EP0264546A3 (fr)
DE (2) DE3635738A1 (fr)

Families Citing this family (20)

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DE3843188C1 (de) * 1988-12-22 1993-10-14 Rheinmetall Gmbh Geschoßeinheit für großkalibrige Rohrwaffe
FR2651570B1 (fr) * 1989-09-07 1991-11-22 France Etat Armement Dispositif de liaison pour sabot de projectile sous-calibre.
AT399583B (de) * 1991-07-17 1995-06-26 Steyr Daimler Puch Ag Unterkalibriges geschoss mit abwerfbarem käfig
DE4330418A1 (de) * 1993-09-08 1995-03-09 Rheinmetall Gmbh Unterkalibriges Pfeilgeschoß
DE4330417C2 (de) * 1993-09-08 1998-02-26 Rheinmetall Ind Ag Treibkäfig für ein unterkalibriges Geschoß
WO1996041113A1 (fr) * 1995-06-07 1996-12-19 Lockheed Martin Energy Systems, Inc. Projectiles a densite et repartition de masse modulables
RU2256145C2 (ru) * 2002-11-20 2005-07-10 Радченко Михаил Юрьевич Способ изготовления пули, пуля, изготовленная по способу, и боеприпас с пулей
US20130213376A1 (en) * 2007-01-24 2013-08-22 Bill Whistler Kenworthy Apparatus for launching subcaliber projectiles at propellant operating pressures including the range of pressures that may be supplied by human breath
DE102007037738A1 (de) 2007-08-09 2009-02-12 Rheinmetall Waffe Munition Gmbh Geschoss mit einem Führungskäfig und Pusherplatte mit beschleunigungsoptimierter Öffnung
DE102007038486A1 (de) 2007-08-14 2009-02-19 Rheinmetall Waffe Munition Gmbh Verfahren zur Herstellung eines Geschosses sowie Geschoss
US20090308274A1 (en) * 2008-06-11 2009-12-17 Lockheed Martin Corporation Integrated Pusher Plate for a Canister- or Gun-Launched Projectile and System Incorporating Same
DE102008029396A1 (de) * 2008-06-23 2009-12-24 Rheinmetall Waffe Munition Gmbh Treibkäfiggeschoss
DE102008029395A1 (de) 2008-06-23 2009-12-24 Rheinmetall Waffe Munition Gmbh Treibkäfiggeschoss
US8291828B2 (en) 2010-03-04 2012-10-23 Glasser Alan Z High velocity ammunition round
US8096243B2 (en) * 2010-03-04 2012-01-17 Glasser Alan Z High velocity ammunition round
US9488455B1 (en) * 2015-01-22 2016-11-08 Consolidated Nuclear Security, LLC Sabot assembly
KR101661242B1 (ko) * 2015-07-15 2016-09-29 국방과학연구소 표적충돌 후 분리되는 이탈피
CN105737692B (zh) * 2016-04-13 2017-10-10 北京理工大学 一种无尾翼弹体加速弹托及方法
KR101916360B1 (ko) * 2018-05-18 2018-11-09 국방과학연구소 발사체의 접힘식 꼬리날개 보호 덮개
CN113865439B (zh) * 2021-10-25 2022-06-10 中国科学院力学研究所 一种气体爆轰驱动超高速发射装置用抗高过载弹丸

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Also Published As

Publication number Publication date
DE3772927D1 (de) 1991-10-17
EP0265369A2 (fr) 1988-04-27
EP0264546A2 (fr) 1988-04-27
EP0265369A3 (en) 1989-01-25
US4850280A (en) 1989-07-25
DE3635738C2 (fr) 1990-08-16
EP0264546A3 (fr) 1989-01-11
DE3635738A1 (de) 1988-05-19

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