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WO2009056081A1 - Projectile présentant des canaux d'écoulement générant un moment angulaire - Google Patents

Projectile présentant des canaux d'écoulement générant un moment angulaire Download PDF

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Publication number
WO2009056081A1
WO2009056081A1 PCT/DE2007/002162 DE2007002162W WO2009056081A1 WO 2009056081 A1 WO2009056081 A1 WO 2009056081A1 DE 2007002162 W DE2007002162 W DE 2007002162W WO 2009056081 A1 WO2009056081 A1 WO 2009056081A1
Authority
WO
WIPO (PCT)
Prior art keywords
projectile
core
flow channels
channels
projectile 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.)
Ceased
Application number
PCT/DE2007/002162
Other languages
German (de)
English (en)
Inventor
Andrey Sorokin
Adilbek Kagenov
Mikhail Fitisov
Vadim Pavlov
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.)
JALLCOM HOLDINGS Ltd
Original Assignee
JALLCOM HOLDINGS Ltd
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 JALLCOM HOLDINGS Ltd filed Critical JALLCOM HOLDINGS Ltd
Publication of WO2009056081A1 publication Critical patent/WO2009056081A1/fr
Anticipated expiration legal-status Critical
Ceased 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
    • F42B10/26—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
    • 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
    • F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02—Cartridges, i.e. cases with charge and missile
    • F42B5/067—Mounting or locking missiles in cartridge cases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02—Cartridges, i.e. cases with charge and missile
    • F42B5/067—Mounting or locking missiles in cartridge cases
    • F42B5/073—Mounting or locking missiles in cartridge cases using an auxiliary locking element

Definitions

  • the invention relates to a projectile with a swirl-generating flow channels.
  • the projectile is particularly suitable for firing from a smooth tube.
  • DE-OS 27 31 092 and DE-OS 27 31 093 discloses projectiles that produce with swirl Flow channels are provided, the entry side of a taper part with subsequent constriction and it then have an extension part, wherein the respective channel axis of the swirl channels in the extension part rectilinear or moderately curved, skewed runs at a distance to the projectile axis. Compression collisions should be avoided by having the channel walls of the extension part, seen in the flow direction, a convex and / or straight shape and / or a maximum slightly concave curved shape.
  • the flow channels can also be arranged in subcircular projectile bodies in spaced-apart guide rings, the outer diameter of which corresponds to the caliber of the tube or can be arranged in a cage surrounding the middle part of the projectile body.
  • These guide means are separably attached to the projectile body.
  • US 4,249,465 discloses as a further development a stabilizer for a cannon projectile.
  • the stabilizer consists of a one-piece solid cylindrical metal element with a first and different from this second diameter.
  • the metal element is arranged coaxially at the rear end of the projectile and has a flat rear portion with a plurality of longitudinal axis-angled slots with parallel side walls. The air impinging on these side walls in the flight of the projectile should impart a spin to the projectile.
  • the object of the invention is therefore to improve a projectile of the type mentioned above so that it has a high firing range with a stabilized flight and a high accuracy and impact regardless of the caliber without additional tail.
  • the object is achieved by a projectile for firing from a smooth barrel or pipe with a swirl-generating flow channels in which the swirl-generating flow channels spiral in the shaft of Projectile core are arranged in the outer wall, wherein the projectile core is rotatably mounted in a jacket, the jacket has openings for the escape of the propellant gas leaving the projectile from the barrel or pipe, in the rear end of the projectile a socket with a passage for the passage Propellant gas and a valve for closing a located in the bottom of the shell opening are provided or the swirl-generating flow channels are arranged spirally in a guide pedestal in the outer wall, the guide pedestal positively receives the projectile core and the guide pedestal with the projectile core on a piston, the channels has for the passage of the propellant gas, is rotatably mounted.
  • An embodiment of the invention provides for rotatably supporting the projectile core with its nose and its rear end by means of axes and / or bearings within the shell.
  • the valve is spring-loaded hinged to the sleeve, the piston is cup-shaped, the channels for the passage of the propellant gases are arranged radially equidistant from each other in the piston and has the guide pedestal predetermined breaking points.
  • a particular embodiment of the projectile according to the invention provides that the bottom and / or the outer wall of the projectile core and the inner wall and / or the guide pedestal are complementarily designed with a profile or whose surface has such a roughness that a common spin of guide pedestal and projectile core secured is.
  • the opening for the exit of the propellant gases are arranged circumferentially equidistant from each other in the shell, the number of openings corresponds to the number of flow channels and the openings have a diameter corresponding to the distance between the two side walls of a flow channel ,
  • Figure 1 shows a longitudinal section through a projectile with a stored in a defect projectile core in the gun barrel.
  • Fig. 3 shows the cross section of the projectile according to FIG. 1 at the moment of
  • FIG. 5 shows the longitudinal section of a projectile after leaving the gun barrel.
  • FIG. 8 shows the bottom view of the projectile core according to FIG. 7;
  • FIG. 9 shows the section A - A of the projectile core according to FIG. 7;
  • FIG. 11 shows the detail I of the projectile according to FIG. 10 in an enlarged view
  • FIG. 12 shows the section B-B of the projectile according to FIG. 10;
  • Fig. 13, 14 the detail Il with a longitudinal section and a bottom view of a socket
  • FIG. 15 shows the longitudinal section through an embodiment of a projectile according to the invention in a gun barrel;
  • Fig. 16 shows the longitudinal section through a projectile according to FIG. 15 after
  • FIG. 17 shows the side view of the projectile according to FIG. 16;
  • FIG. 18 shows the section C - C of the representation according to FIG. 17;
  • FIG. 19 shows a longitudinal section through a projectile according to FIG. 15 on leaving the gun barrel;
  • Fig. 20 shows the representation of the projectile core with the originally associated with him components.
  • Fig. 1 shows an inventive projectile after ignition.
  • the projectile is still in the cartridge 19.
  • the jacket 3 is preferably made of steel.
  • the sleeve 5 is arranged with the spring-loaded valve 7 in the jacket 3.
  • the socket 5 has the passage channels 9.
  • the valve 7 is used to open and close the provided in the bottom of the shell 3 opening 11.
  • the bush 5 has a circumferential groove in the form-fitting a bead-shaped portion of the shell 3 engages. It can be clearly seen that the projectile core 2 has flow channels 4 arranged spirally in its conical and rear cylindrical section.
  • the expanding propellant gases press against the spring-loaded valve 7, which releases the opening 11 located in the bottom of the jacket 3.
  • the propellant gas penetrates into the spirally arranged flow channels 4 of the projectile core 2 and the space formed by a gap between the projectile core 4 and the shell. 3 and there generates the pressure G.
  • the shell 3 has at its circumference in a uniformly spaced openings 10 for the exit of the propellant gas when the projectile core 2 leaves the tube 1 (FIG. 3).
  • the openings 10 are preferably designed and arranged such that they continue the course of the spirally arranged flow channels 4.
  • the number of openings 10 corresponds to the number of flow channels 4.
  • the diameter of the openings 10 preferably corresponds to the distance that occupy both side walls of a flow channel 4 at its end in the weft direction to each other.
  • the propellant gas flows with the force F through the flow channels 4 and exerts on them the lateral pressure P (FIG. 4), which the rotatably mounted projectile core 2 within the shell 3 a Lends twist.
  • the torque M is thus generated (FIG. 3).
  • the number and the diameter of the passage channels 9 be chosen differently.
  • the projectile core 2 is rotatably mounted in the shell 3, not only a very high rotational speed of this projectile core 2 can be achieved, but the projectile 2 receives at the same time required for high accuracy high stability. Since the moment the outlet of the propellant gas from the openings 10 of the shell 3, the valve 7 closes the opening 11 located at the bottom of the shell 3, lend the continuing acting propellant gases when leaving the projectile fired from the smooth barrel 1 of a rifle or pipe of a gun particularly high initial speed of 1500 m / s to 1800 m / s and a higher firing range over the known prior art solutions.
  • Fig. 15 shows a particular embodiment of a projectile according to the invention.
  • the projectile core 12 is mounted in a form-locking manner in a guide pedestal 15.
  • the guide pedestal 15 is preferably made of a wear-resistant and high-temperature-resistant plastic and may have predetermined breaking points.
  • the guide pedestal 15 is rotatably mounted with the aid of the bearing 14 on the cup-shaped piston 16, which has the channels 17 for the passage of the propellant gases.
  • the surrounding wall in the direction of the cartridge case or cartridge tion 20 of the piston 16 has at its end to the shoulder 21, with which the piston 16 is mounted on the cartridge case or the cartridge.
  • the channels 17 are preferably arranged radially in the piston 16 at the same distance from one another. After ignition of the charge, the developing propellant gases pass through the channels 17 and exert with the force F the pressure P laterally on the flow channels 13 of the guide pedestal 15 (Fig. 17, 18).
  • the bottom of the projectile core 2 and the inside of the bottom of the guide pedestal 15 have a complementary trained profile, which ensures that the projectile core 2 lossless by the offset with the propellant gases in rotation guide base 15 receives the same rotational speed as the guide pedestal 15. If necessary, sufficient it is to give the bottom of the projectile core 2 and the inner surface of the guide pedestal 15 a corresponding roughness.
  • the bearing 14 makes it possible to keep the energy losses as low as possible by the friction to be overcome during the rotation.
  • Fig. 19 and Fig. 20 show that after leaving the projectile from the gun barrel 1 of the guide base 15, the bearing 14 and the cup-shaped piston 16 by the resistance of the air flow and optionally existing predetermined breaking points slidably from the projectile core 2, which by the generated gas-dynamically generated spin and the smooth barrel / gun barrel 1 a particularly high rotational and initial speed and accuracy in stable flight.
  • the projectile according to the invention can be used for handguns as well as for guns or cannons with a caliber of up to 150 mm.
  • the smooth barrel 1 and the smooth tube 1 can also be more efficiently finished compared to drawn barrels or tubes and also make thinner walls with considerable material effects.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Toys (AREA)

Abstract

L'invention concerne un projectile destiné à être tiré à partir d'un canon ou d'un tube lisse, ce projectile présentant des canaux d'écoulement générant un moment angulaire. Lesdits canaux d'écoulement générant le moment angulaire sont disposés en forme de spirale dans la tige d'un noyau de projectile dans la paroi extérieure de celui-ci, le noyau de projectile est monté rotatif dans une enveloppe et cette enveloppe présente des ouvertures par lesquelles le gaz propulseur peut s'échapper lorsque le noyau de projectile sort du canon ou du tube. Une bague présentant des canaux pour le passage du gaz propulseur et une valve destinée à obturer une ouverture ménagée dans la base de l'enveloppe sont disposées à l'extrémité arrière du projectile. Les canaux d'écoulement générant le moment angulaire peuvent être disposés également en forme de spirale dans une base de guidage dans la paroi extérieure de celle-ci, le noyau de projectile étant logé dans cette base de guidage par complémentarité de forme et la base de guidage étant montée avec le noyau de projectile de façon rotative sur un piston qui présente des canaux pour le passage du gaz propulseur. Ce projectile présente une longue portée et une grande force de pénétration avec une vitesse initiale comprise entre 1500 m/s et 1800 m/s et une trajectoire stable. Il peut être utilisé aussi bien pour des armes de poing que pour des fusils et des canons.
PCT/DE2007/002162 2007-11-02 2007-11-29 Projectile présentant des canaux d'écoulement générant un moment angulaire Ceased WO2009056081A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007052938.6 2007-11-02
DE200710052938 DE102007052938B3 (de) 2007-11-02 2007-11-02 Geschoss mit einen Drall erzeugenden Strömungskanälen

Publications (1)

Publication Number Publication Date
WO2009056081A1 true WO2009056081A1 (fr) 2009-05-07

Family

ID=39618867

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2007/002162 Ceased WO2009056081A1 (fr) 2007-11-02 2007-11-29 Projectile présentant des canaux d'écoulement générant un moment angulaire

Country Status (2)

Country Link
DE (1) DE102007052938B3 (fr)
WO (1) WO2009056081A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2008057945A (ja) * 2006-08-30 2008-03-13 Sefa-Japan:Kk 平滑銃身またはライフリング付銃身より発射可能で命中精度のよい単体および複合体装弾筒を有する銃砲用装弾
US10591263B2 (en) * 2015-03-23 2020-03-17 Brown James F High spin projectile apparatus comprising components made by additive manufacture
CN111397536A (zh) * 2020-05-20 2020-07-10 西北核技术研究院 大尺寸钢筋混凝土靶板侵彻弹洞三维轮廓测量方法
US11867487B1 (en) 2021-03-03 2024-01-09 Wach Llc System and method for aeronautical stabilization

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT523170B1 (de) * 2020-09-02 2021-06-15 Conle Henning Schusswaffe mit Patrone

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE298588C (fr) *
GB191214431A (en) * 1912-06-20 1913-03-06 Enrico Cremonesi Improvements in and relating to Projectiles.
DE597633C (de) 1930-11-11 1934-05-28 Karl Burgsmueller Jr Geschoss fuer glatte Rohre
CA985081A (en) * 1970-11-18 1976-03-09 John R. Manis Firearms
DE2731092A1 (de) 1977-07-09 1979-01-25 Josef Prof Dr Ing Ballmann Geschoss mit drall erzeugenden stroemungskanaelen
DE2731093A1 (de) 1977-07-09 1979-01-25 Josef Prof Dr Ing Ballmann Geschoss, insbesondere zum verschiessen aus einem glatten rohr
US4314510A (en) * 1980-01-28 1982-02-09 The United States Of America As Represented By The Secretary Of The Army Kinetic sabot system
GB2259354A (en) * 1991-09-03 1993-03-10 William Wheatley Cross Spin-stabilised round for a firearm
RU2225974C1 (ru) * 2002-09-13 2004-03-20 Автономная некоммерческая организация "Центральный научно-исследовательский и опытно-конструкторский институт "Центр перспективных исследований" Способ придания вращения пулевому или иному снаряду и огнестрельный комплекс яугонена для его осуществления

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3065696A (en) * 1959-11-23 1962-11-27 Robert A Kleinguenther Projectile for firearms
US3225694A (en) * 1964-01-20 1965-12-28 Gunnar P Michelson Missile
IL37042A (en) * 1971-06-14 1976-06-30 Israel State Rear sabot for sub-calibre projectile with delayed detachment
US4709638A (en) * 1981-09-24 1987-12-01 Honeywell Inc. Discarding sabot projectile
US5164538A (en) * 1986-02-18 1992-11-17 Twenty-First Century Research Institute Projectile having plural rotatable sections with aerodynamic air foil surfaces
FR2799833B1 (fr) * 1999-10-15 2002-10-25 Tda Armements Sas Dispositif de correction de trajectoire pour projectiles guides gyroscopes

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE298588C (fr) *
GB191214431A (en) * 1912-06-20 1913-03-06 Enrico Cremonesi Improvements in and relating to Projectiles.
DE597633C (de) 1930-11-11 1934-05-28 Karl Burgsmueller Jr Geschoss fuer glatte Rohre
CA985081A (en) * 1970-11-18 1976-03-09 John R. Manis Firearms
DE2731092A1 (de) 1977-07-09 1979-01-25 Josef Prof Dr Ing Ballmann Geschoss mit drall erzeugenden stroemungskanaelen
DE2731093A1 (de) 1977-07-09 1979-01-25 Josef Prof Dr Ing Ballmann Geschoss, insbesondere zum verschiessen aus einem glatten rohr
US4249465A (en) 1977-07-09 1981-02-10 Josef Ballmann Projectile
US4314510A (en) * 1980-01-28 1982-02-09 The United States Of America As Represented By The Secretary Of The Army Kinetic sabot system
GB2259354A (en) * 1991-09-03 1993-03-10 William Wheatley Cross Spin-stabilised round for a firearm
RU2225974C1 (ru) * 2002-09-13 2004-03-20 Автономная некоммерческая организация "Центральный научно-исследовательский и опытно-конструкторский институт "Центр перспективных исследований" Способ придания вращения пулевому или иному снаряду и огнестрельный комплекс яугонена для его осуществления

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2008057945A (ja) * 2006-08-30 2008-03-13 Sefa-Japan:Kk 平滑銃身またはライフリング付銃身より発射可能で命中精度のよい単体および複合体装弾筒を有する銃砲用装弾
US10591263B2 (en) * 2015-03-23 2020-03-17 Brown James F High spin projectile apparatus comprising components made by additive manufacture
US10996033B2 (en) 2015-03-23 2021-05-04 Brown James F Projectile apparatus for smooth bore barrels
CN111397536A (zh) * 2020-05-20 2020-07-10 西北核技术研究院 大尺寸钢筋混凝土靶板侵彻弹洞三维轮廓测量方法
CN111397536B (zh) * 2020-05-20 2021-05-04 西北核技术研究院 大尺寸钢筋混凝土靶板侵彻弹洞三维轮廓测量方法
US11867487B1 (en) 2021-03-03 2024-01-09 Wach Llc System and method for aeronautical stabilization

Also Published As

Publication number Publication date
DE102007052938B3 (de) 2009-04-16

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