US3496869A - Sabot projectile - Google Patents

Sabot projectile Download PDF

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Publication number
US3496869A
US3496869A US656856A US3496869DA US3496869A US 3496869 A US3496869 A US 3496869A US 656856 A US656856 A US 656856A US 3496869D A US3496869D A US 3496869DA US 3496869 A US3496869 A US 3496869A
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US
United States
Prior art keywords
jacket
rear part
projectile
sabot
core
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
US656856A
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English (en)
Inventor
Walter Engel
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.)
OC Oerlikon Corp AG Pfaeffikon
Original Assignee
Oerlikon Buehrle Holding AG
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 Oerlikon Buehrle Holding AG filed Critical Oerlikon Buehrle Holding AG
Application granted granted Critical
Publication of US3496869A publication Critical patent/US3496869A/en
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 sabot of a sabot projectile has a rear part, a jacket and a driving band.
  • Jacket and driving band are made in a single piece, and the connection between the rear part and the driving band with jacket is formed by adjacent cone surfaces whose apices point rearwards, so that the driving band is pressed against the rear part by the gas pressure.
  • the outside diameter of the driving band is preferably greater than the greatest inside diameter of the gun bore from which the sabot projectile is fired.
  • the present invention concerns a sabot projectile and a gun bore from which the projectile is fired.
  • An object of the invention is to provide a sabot projectile wherein the sabot is not destroyed by the gas pressure when the projectile is fired.
  • a further object of the invention is to provide a sabot projectile wherein the connection between the driving band of the sabot and the jacket and also the connection between the rear part and the driving band are so designed that they are not destroyed by the gas pressure when the projectile is fired.
  • FIG. 1 shows a sectional view with parts in elevation through a sabot projectile taken along section line II in FIG. 2;
  • FIG. 2 shows a cross-sectional view along section line IIII in FIG. 1;
  • FIG. 3 shows a cross-sectional view along section line IIIIII in FIG. 1;
  • FIG. 4 shows a partial sectional view through a gun bore
  • FIG. 5 shows a partial sectional view through a cartridge chamber of a gun bore and the jacket of the sabot, along section line V-V in FIG. 4;
  • FIG. 6 is a partial sectional view through a modified sabot projectile illustrating a modified core support system
  • FIG. 7 is a similar view showing a further modification.
  • the subcaliber core 1 shown in FIG. 1 consists preferably wholly or partly of tungsten carbide and has a substantially cylindrical shape with an ogive 2.
  • the rear of the core 1 rests with its forward-opening cone surface 7 on a similarly shaped bore surface 8 of a sabot rear part 4.
  • This rear part 4 has a sleeve-shaped extension 5 into which the rear of the core 1 extends.
  • a small space is provided between the rear end face 9 of the core 1, which is perpendicular to the longitudinal axis, and the base surface 11 terminating the bore 8 of the rear part 4.
  • the rear part 4 consists preferably of an aluminium alloy, such as Perunal.
  • the outside diameter of the core 1 is smaller than the inside diameter of the extension 5. 70
  • the core 1 is provided in its rear portion with an annular groove 12.
  • a locking ring 14 consisting of three segments.
  • This locking ring 14 rests on 3,495,869 Patented Feb. 24, 1970 a groove flank 13 perpendicular to the projectile axis.
  • the outside diameter of the locking ring is greater than the diameter of the core 1.
  • a sleeve rests on the surface 52 of the locking ring 14 extending beyond the core 1.
  • This sleeve 15 consists of three equal segments.
  • the outside diameter of the sleeve 15 is equal to the inside diam eter of the extension 5.
  • the sleeve 15 has a flange 16 which extends into an enlargement of the extension 5 and projects slightly beyond the forward end of the extension 5.
  • the extension 5 is provided with annular ridges 17 which are spaced at regular intervals measured in axial direction and which are bounded forwardly by a rearwardopening cone surface 10 and rearwardly by a surface 46 intersecting the said cone surface 10.
  • the surface 46 is substantially perpendicular to the axis of the extension 5.
  • six radial slots 18 arranged at regular angular intervals extend into the extension 5 (FIG. 3).
  • the slots 18 extend behind the ridges 17 as far as a rearward-opening cone surface 20 of the rear part 4.
  • This surface 20 is intersected by another cone surface 21, extending rearwardly and opening forwardly, the arrangement being such that the diameter of the intersection line of these two surfaces 20 and 21 is smaller than the outside diameter of the rear sleeve-shaped portion 22 of the rear part 4 which, until the projectile is fired, remains inside the mouth of a carriage, not shown.
  • the cone surface 21 intersects another rearwardly extending and opening cone surface 23, which is intersected by a cone surface 24 which encloses substantially the same angle with the forwardpointing projectile axis as does the cone surface 21.
  • This surface 24 intersects the jacket surface of the portion 22 of the rear part 4.
  • the cylindrical portion of the core 1 not extending into the extension 5 is encompassed by a full-caliber jacket 25 made of plastic material and extending to a point forward of the rear end of the ogive 2.
  • the jacket is preferably made of a thermoplastic material designated nylon 6.6, having the following properties: tensile strength 8 kp/ mm. modulus of elasticity E 17,000 kp./cm. compressive strength 11 kp./mm. notch impact strength 130 cm.kp./crn. elongation to rupture 200%.
  • the forward portion of the jacket 25 is cylindrical; the rear portion is a truncated cone slightly tapering forwardly. The diameter of the forward edge of the truncated cone is greater than the diameter of the cylindrical jacket portion so that the rear portion clearing the cylindrical surfaces forms a collar-shaped extension 26 of the jacket.
  • This extension 26 represents the driving band intended to transmit to the jacket the spin imparted by the surfaces of the lands 28 bounding the grooves 29 of the gun bore 27.
  • the jacket surface of the driving band 26 rests against a cone surface 31 of the gun bore 27, which forms the rear termination of the lands 28 and into which the bottoms of the grooves 29 extend.
  • the cylindrical jacket portion is centered and guided by the lands 28.
  • the rear portion 33 of the bore of the jacket 25 is enlarged, and the bore step forming a shoulder 34 rests on the end face of the sleeve flange 16.
  • the ridges 17 of the extension 5 have a larger diameter than the portion 35 of the bore of the jacket 25 and engage it in barb-like fashion,
  • the rear portion of the bore of the jacket is so designed that it rests against the surfaces 20, 21, 23, 24 of the rear part 4, so that its rearmost portion touching the surfaces 23 and 24 forms a ring 47 of tongue-shaped cross-section.
  • radial grooves 36 are cut into the jacket 25 at regular angular intervals from the bore wall and extend from the end face to the level of the rear end of the extension 5.
  • the surfaces of the jacket 25 terminating the grooves 36 at the rear are arranged in the same plane as a groove 37 running round the whole periphery of the jacket and provided with a rounded bottom.
  • the jacket 25 is provided on the outside with recesses 38, which serve weight-reducing purposes and whose bottoms are rounded in circular fashion and whose flanks 39 enclose a substantially right angle.
  • the symmetry planes of these recesses 38 forming radial planes are arranged between the symmetry planes of the grooves 36 (FIG. 2).
  • a plastic hood 40 extending forwardly from the jacket 25 is formed as a hollow body having a tapering forward portion and a rear portion widening rearwardly in bell fashion to the outside diameter of the jacket 25 of the sabot 3.
  • the hood 40 ends forward of the ogive 2 of the core 1, enclosing the ogive and spaced therefrom and is connected with the jacket 25 by a flange 41 which terminates it at the rear which protrudes inwardly to engage a groove 42 cut round the whole circumference of the jacket 25.
  • the hood 40 is closed forwardly by a thin cover 44 arranged across its longitudinal axis and located at a short distance rearward of the end face 43 and made integral with the rest of the hood.
  • the circular junction 45 of the cover 44 with the hood 40 forms a place of intended rupture. This cover 44 increases the strength of the hood-40 and also prevents any foreign matter from penetrating between it and the ogive 2 of the core 1.
  • the shocks directed towards the ogive 2 of the core 1, often consisting of a thin ballistic hood, are absorbed by the hood 40, but, owing to the stiffness of the latter, are not transmitted to the ogive 2.
  • This coupling action between jacket 25 and rear part 4 can be improved by knurling 48 of the cone surface 21 as indicated by a dash-dotted line on the right of FIG. 1, causing the jacket 25 to mesh with the rear part 4 under the external pressure acting on the jacket,
  • the radial prestressing of the driving band 26 offers the further advantage that the projectile will still be properly guided and set spinning even when the bore 27 is worn and thus has an excessive inside diameter, as this diameter difference is made good by the elastic expansion of the driving band 26.
  • the core 1 In the acceleration of the sabot projectile, the core 1 is pushed with such force rearwards against the chamber formed by the supporting surface 8 of the rear part 4 that the latter undergoes plastic deformation. As a result the subcaliber core 1 moves relatively to the rear part 4 rearwards and is then no longer held free of clearance in axial direction. Further, the core 1 is set spinning by the frictional force acting between it and the rear part 4.
  • the force acting on the jacket 25 in axial direction forwardly is determined by the size of its surface exposed to the gas.
  • this surface is composed of the rear annular surface 49 and, as the gas can penetrate between the surface 24 of the rear part and the jacket surface 50, of the surface which is determined by the projection of this jacket surface 50 on to a plane perpendicular to the projectile axis.
  • the relations are such that the acceleration which can be imparted to the light jacket 25 by this gas power is at least equal to the acceleration sustained by the projectile relieved of the weight of the jacket 25 and the hood 40.
  • the danger of any displacement of the jacket 25 with respect to the rear part 4 is countered by the anchoring of the jacket in the rear part.
  • the rearmost portion of the jacket 25 is designed as a forward-closing key ring which is clamped between the surface 31 or between the lands 28 and the groove bottoms 29 on the one side and the surface 21 of the rear part 4.
  • a gas force acting on the surface 50 of the jacket forces the ring 47 with sealing effect against the surface 23 of the rear part 4.
  • This arrangement prevents the gas from penetrating between ring 47 and surface 23 and thus unduly enlarging the gas hit area of the jacket and, accordingly, the gas force acting on the jacket in axial direction.
  • the centrifugal force causes the jacket 25 to disintegrate into segments moving radially outwards, and this is aided by places of intended rupture formed by the webs 51 bounded by the bottoms of the grooves 36 and the surface of the jacket 25.
  • the said segments detach themselves from the rearmost portion of the jacket 25 anchored in the rear part 4 substantially along a plane perpendicular to the projectile axis and containing the ring groove 37.
  • the foremost portion of the extension 5 of the rear part 4 is curled inwardly (53) and rests against the flange 16 of the sleeve 15.
  • the inertia force acting on the core 1 when the cartridge is fed into the cartridge chamber is transmitted not to the jacket 25, but direct to the extension 5, i.e. to the rear part 4, thus dispensing with the need for ridges 17 on the extension 5.
  • FIG. '7 wherein the sleeve 54 is screwed up with the extension 5 bearing the thread 56. From the end face, slots 55 are cut into the sleeve 54 at regular angular intervals. These slots form the boundaries of segments into which the sleeve 54 disintegrates at firing under the action of the centrifugal force.
  • the elements 14 and 15 in FIGS. 1 and 6 for the support of the core .1 can also be united to form a single securing body.
  • Such a body has substantially the same cross-section as the two elements 14 and 15 together and is also split into several segments of equal size.
  • Sabot projectile comprising a projectile core (1) which extends along an axis, a sabot (3), (4, 25) with an approximately cylindrical rear part (4) having on its circumference a groove (21, 23, 24), said groove defined by two spaced substantially parallel side walls (21, 24) and a flat bottom surface (23) connecting said side walls (21, 24), said side walls being annular portions of imaginary cones having apices pointing rearwards in relation to the direction of flight, said sabot (3), (4, 25) having a jacket (25) encompassing the projectile core (1) and fitting into said groove (21, 23, 24) to form a gas tight connection between said jacket (25) and said rear part (4) and a driving band (26) integral with said jacket (25) located in the area of said groove (21, 23, 24) in the rear part (4) to improve the tightness between said jacket (25 and said rear part 4).
  • Sabot projectile comprising a projectile core (1) extending along an axis, a sabot (3, 4, 25) with an approximately cylindrical rear part (4) having a groove (21, 23, 24) on its circumference, said groove defined by two spaced substantially parallel side walls (21, 24) and a flat bottom surface (23) connecting said side walls (21, 24) said side walls being annular portions of imaginary cones having apices pointing rearwards in relation to the direction of flight, said sabot (3), (4, 25) having a jacket (25) encompassing the projectile core (1) said jacket (25) having on its rear part pointing in the flight direction of the projectile two spaced substantially parallel surfaces being annular portions of imaginary cones having apices pointing rearwards, both of said surfaces contacting the side walls (21, 24) of the groove (21, 23, 24) of the rear part (4), said jacket (25) having a driving band (26) located in the area of the groove (21, 23, 24) of the rear part (4) to improve the tightness between said jacket (25) and the
  • Sabot projectile according to claim 2 comprising a locking ring (14) an annular groove (12) in the projectile core (1) Where the locking ring (14) fits in, a frnt surface (52) on said locking ring (14) whereby said front surface (52) serves as a first resting surface, and with a second surface (34) on said jacket (25) which is parallel to said first resting surface (52) of the locking ring (14) and set at a distance from said first resting surface (52), a sleeve (15) resting on one hand on said first resting surface (52) of said locking ring (14) and on the other hand on said second resting surface (34) of said jacket (25) to prevent the axially displacement of the projectile core (1) in relation to the jacket (25) in one direction.
  • Sabot projectile according to claim 4 wherein said rear part (4) of the sabot has an extension (5) and said extension has a shoulder (53) which constitutes said second resting surface of the sabot (3, 4, 25).

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Testing Of Engines (AREA)
  • Adornments (AREA)
  • Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
  • Portable Nailing Machines And Staplers (AREA)
US656856A 1967-07-28 1967-07-28 Sabot projectile Expired - Lifetime US3496869A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US65685667A 1967-07-28 1967-07-28

Publications (1)

Publication Number Publication Date
US3496869A true US3496869A (en) 1970-02-24

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US656856A Expired - Lifetime US3496869A (en) 1967-07-28 1967-07-28 Sabot projectile

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US (1) US3496869A (xx)
BE (1) BE718414A (xx)
CH (1) CH494389A (xx)
DE (1) DE1703816B2 (xx)
FR (1) FR1576031A (xx)
GB (1) GB1224362A (xx)
NL (2) NL6810720A (xx)
SE (1) SE347813B (xx)

Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3714900A (en) * 1969-08-29 1973-02-06 Pacific Technica Corp Discarding sabot projectiles
US3724377A (en) * 1969-05-07 1973-04-03 Brevets Aero Mecaniques Shell cartridges
US3747533A (en) * 1970-12-08 1973-07-24 Oerlikon Buehrle Ag Short trajectory missile
US3847082A (en) * 1969-08-29 1974-11-12 Pacific Technica Corp Spin stabilized, discarding sabot projectile
US3927618A (en) * 1971-03-29 1975-12-23 Oerlikon Buehrle Ag Sabot projectile
US4000698A (en) * 1974-10-29 1977-01-04 General Dynamics Corporation Pomona Division Self-separating sabot
US4142467A (en) * 1976-07-09 1979-03-06 Dynamit Nobel Aktiengesellschaft Projectile with sabot
US4296687A (en) * 1979-07-16 1981-10-27 The United States Of America As Represented By The Secretary Of The Army Segmented sabot projectile
US4326464A (en) * 1979-12-10 1982-04-27 The United States Of America As Represented By The Secretary Of The Army Gusset discarding sabot munition
US4444114A (en) * 1978-08-24 1984-04-24 Rheinmetall Gmbh Munitions round for barrel-type weapons
US4574703A (en) * 1984-03-01 1986-03-11 Olin Corporation High velocity ammunition sabot
US4651649A (en) * 1983-09-06 1987-03-24 Helmut Nussbaum Sabot for subcaliber projectiles
WO1987005386A1 (en) * 1986-03-10 1987-09-11 Olin Corporation High velocity ammunition sabot
US4709638A (en) * 1981-09-24 1987-12-01 Honeywell Inc. Discarding sabot projectile
US4735147A (en) * 1984-03-01 1988-04-05 Olin Corporation Ammunition sabot and projectile
US4735148A (en) * 1986-03-18 1988-04-05 United Technologies Corporation Plastic composite sabot
US4833995A (en) * 1985-07-19 1989-05-30 Mauser-Werke Oberndorf Gmbh Fin-stabilized projectile
US4854242A (en) * 1987-05-21 1989-08-08 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Sabot projectile containing a projectile core and a sabot jacket
US4860661A (en) * 1987-11-06 1989-08-29 Diehl Gmbh & Co. Saboted projectile with propellant cage
US4881466A (en) * 1988-12-23 1989-11-21 General Electric Company High velocity sabot for spin stabilized penetrator
US5025731A (en) * 1978-06-21 1991-06-25 Rheinmetall Gmbh Segmented, discardable sabot having polygonal cross-section for sub-caliber projectile
US5090328A (en) * 1990-08-25 1992-02-25 Rheinmetall Gmbh Spin stabilized projectile unit
US5239930A (en) * 1990-02-08 1993-08-31 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland Hypervelocity sabot
US5404816A (en) * 1993-09-24 1995-04-11 Oerlikon-Contraves Pyrotec Ag Releasable sabot for a subcaliber projectile
US5969289A (en) * 1996-12-06 1999-10-19 Rhienmetall W& M Gmbh Subcaliber projectile
US20090064887A1 (en) * 2005-10-13 2009-03-12 Udo Winter Cartridge
US8550434B1 (en) * 2012-01-17 2013-10-08 Kai Hsiang Traffic Appliance Co. Ltd. Cylinder jack stand
US20130312631A1 (en) * 2010-09-16 2013-11-28 Rheinmetall Waffe Munition Gmbh Projectile having a discardable sabot
RU2717857C1 (ru) * 2019-06-18 2020-03-26 Акционерное общество "Центральный научно-исследовательский институт точного машиностроения" (АО "ЦНИИТОЧМАШ") Ведущее устройство оперенного бронебойно-подкалиберного снаряда
US11293730B1 (en) * 2016-06-14 2022-04-05 Douglas Burke Bullet projectile with enhanced mechanical shock wave delivery for warfare
US20220412706A1 (en) * 2017-06-23 2022-12-29 Douglas Burke Bullet projectile with internal hammer and post for enhanced mechanical shock wave delivery for demolition
US20230116071A1 (en) * 2020-06-15 2023-04-13 Rheinmetall Waffe Munition Gmbh Sabot

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3151525C1 (de) * 1981-12-24 1991-10-10 Rheinmetall Gmbh Munitionseinheit
SE444984B (sv) * 1982-05-28 1986-05-20 Bofors Ab Drivorgan for underkalibrig rotationsstabiliserad projektil
EP0104587A1 (en) * 1982-09-23 1984-04-04 Honeywell Inc. Subcaliber munition
DE3761061D1 (de) * 1986-03-07 1990-01-04 Oerlikon Buehrle Ag Verbindung zwischen dem treibspiegelmantel und dem treibspiegelheck eines treibspiegelgeschosses.
NO163425C (no) * 1987-04-30 1990-05-23 Oerlikon Buehrle Ag Utformning av et oenskebruddsted ved hekkdelen av et drivspeil for et drivspeilprosjektil.
ES2032496T3 (es) * 1987-07-20 1993-02-16 Oerlikon-Contraves Ag Proyectil de calibre reducido estabilizado por aletas.
DE3827739A1 (de) * 1988-08-16 1990-02-22 Rheinmetall Gmbh Treibkaefig fuer ein drallstabilisiertes geschoss

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB573914A (en) * 1943-08-06 1945-12-12 Frantisek Karel Janecek Improvements in or relating to armour piercing projectiles
US2669930A (en) * 1946-01-05 1954-02-23 Remington Arms Co Inc Sabot projectile
GB752448A (en) * 1954-12-13 1956-07-11 Bofors Ab Improvements relating to projectiles
CH351522A (de) * 1957-05-08 1961-01-15 Oerlikon Buehrle Ag Hartkern für Panzergeschosse
FR1298756A (fr) * 1960-09-12 1962-07-13 United Kingdom Government Projectiles
US3096715A (en) * 1959-01-19 1963-07-09 Brevets Aero Mecaniques Armor-piercing projectiles
US3349712A (en) * 1965-07-22 1967-10-31 Oerlikon Buhrle Holding A G Sabot projectile

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB573914A (en) * 1943-08-06 1945-12-12 Frantisek Karel Janecek Improvements in or relating to armour piercing projectiles
GB586174A (en) * 1943-08-06 1947-03-10 Frantisek Karel Janecek Improvements in or relating to armour-piercing projectiles
US2669930A (en) * 1946-01-05 1954-02-23 Remington Arms Co Inc Sabot projectile
GB752448A (en) * 1954-12-13 1956-07-11 Bofors Ab Improvements relating to projectiles
CH351522A (de) * 1957-05-08 1961-01-15 Oerlikon Buehrle Ag Hartkern für Panzergeschosse
US3096715A (en) * 1959-01-19 1963-07-09 Brevets Aero Mecaniques Armor-piercing projectiles
FR1298756A (fr) * 1960-09-12 1962-07-13 United Kingdom Government Projectiles
US3349712A (en) * 1965-07-22 1967-10-31 Oerlikon Buhrle Holding A G Sabot projectile

Cited By (38)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3724377A (en) * 1969-05-07 1973-04-03 Brevets Aero Mecaniques Shell cartridges
US3847082A (en) * 1969-08-29 1974-11-12 Pacific Technica Corp Spin stabilized, discarding sabot projectile
US3714900A (en) * 1969-08-29 1973-02-06 Pacific Technica Corp Discarding sabot projectiles
US3747533A (en) * 1970-12-08 1973-07-24 Oerlikon Buehrle Ag Short trajectory missile
US3927618A (en) * 1971-03-29 1975-12-23 Oerlikon Buehrle Ag Sabot projectile
US4000698A (en) * 1974-10-29 1977-01-04 General Dynamics Corporation Pomona Division Self-separating sabot
US4142467A (en) * 1976-07-09 1979-03-06 Dynamit Nobel Aktiengesellschaft Projectile with sabot
US5025731A (en) * 1978-06-21 1991-06-25 Rheinmetall Gmbh Segmented, discardable sabot having polygonal cross-section for sub-caliber projectile
US4444114A (en) * 1978-08-24 1984-04-24 Rheinmetall Gmbh Munitions round for barrel-type weapons
US4542696A (en) * 1978-08-24 1985-09-24 Rheinmetall Gmbh Munitions round for barrel-type weapons
US4296687A (en) * 1979-07-16 1981-10-27 The United States Of America As Represented By The Secretary Of The Army Segmented sabot projectile
US4326464A (en) * 1979-12-10 1982-04-27 The United States Of America As Represented By The Secretary Of The Army Gusset discarding sabot munition
US4709638A (en) * 1981-09-24 1987-12-01 Honeywell Inc. Discarding sabot projectile
US4651649A (en) * 1983-09-06 1987-03-24 Helmut Nussbaum Sabot for subcaliber projectiles
US4574703A (en) * 1984-03-01 1986-03-11 Olin Corporation High velocity ammunition sabot
US4735147A (en) * 1984-03-01 1988-04-05 Olin Corporation Ammunition sabot and projectile
US4833995A (en) * 1985-07-19 1989-05-30 Mauser-Werke Oberndorf Gmbh Fin-stabilized projectile
JPS63502922A (ja) * 1986-03-10 1988-10-27 オリン　コ−ポレ−ション 高速度兵器送弾筒
WO1987005386A1 (en) * 1986-03-10 1987-09-11 Olin Corporation High velocity ammunition sabot
JP2587820B2 (ja) 1986-03-10 1997-03-05 オリン コーポレーション 高速度兵器送弾筒
US4735148A (en) * 1986-03-18 1988-04-05 United Technologies Corporation Plastic composite sabot
US4854242A (en) * 1987-05-21 1989-08-08 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Sabot projectile containing a projectile core and a sabot jacket
US4860661A (en) * 1987-11-06 1989-08-29 Diehl Gmbh & Co. Saboted projectile with propellant cage
US4881466A (en) * 1988-12-23 1989-11-21 General Electric Company High velocity sabot for spin stabilized penetrator
US5239930A (en) * 1990-02-08 1993-08-31 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland Hypervelocity sabot
US5090328A (en) * 1990-08-25 1992-02-25 Rheinmetall Gmbh Spin stabilized projectile unit
US5404816A (en) * 1993-09-24 1995-04-11 Oerlikon-Contraves Pyrotec Ag Releasable sabot for a subcaliber projectile
US5969289A (en) * 1996-12-06 1999-10-19 Rhienmetall W& M Gmbh Subcaliber projectile
US20090064887A1 (en) * 2005-10-13 2009-03-12 Udo Winter Cartridge
US8037830B2 (en) * 2005-10-13 2011-10-18 Udo Winter Cartridge
US20130312631A1 (en) * 2010-09-16 2013-11-28 Rheinmetall Waffe Munition Gmbh Projectile having a discardable sabot
US9528806B2 (en) * 2010-09-16 2016-12-27 Rwm Schweiz Ag Projectile having a discardable sabot
US8550434B1 (en) * 2012-01-17 2013-10-08 Kai Hsiang Traffic Appliance Co. Ltd. Cylinder jack stand
US11293730B1 (en) * 2016-06-14 2022-04-05 Douglas Burke Bullet projectile with enhanced mechanical shock wave delivery for warfare
US20220412706A1 (en) * 2017-06-23 2022-12-29 Douglas Burke Bullet projectile with internal hammer and post for enhanced mechanical shock wave delivery for demolition
US11841214B2 (en) * 2017-06-23 2023-12-12 Douglas Burke Bullet projectile with internal hammer and post for enhanced mechanical shock wave delivery for demolition
RU2717857C1 (ru) * 2019-06-18 2020-03-26 Акционерное общество "Центральный научно-исследовательский институт точного машиностроения" (АО "ЦНИИТОЧМАШ") Ведущее устройство оперенного бронебойно-подкалиберного снаряда
US20230116071A1 (en) * 2020-06-15 2023-04-13 Rheinmetall Waffe Munition Gmbh Sabot

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FR1576031A (xx) 1969-07-25
DE1703816C3 (xx) 1973-12-20
NL137889C (xx)
NL6810720A (xx) 1969-01-30
SE347813B (xx) 1972-08-14
BE718414A (xx) 1968-12-31
DE1703816A1 (de) 1972-02-10
GB1224362A (en) 1971-03-10
DE1703816B2 (de) 1973-06-07
CH494389A (de) 1970-07-31

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