EP3028002B1 - Verfahren zur steigerung der reichweite von drallstabilisierten projektilen und ebensolches projektil - Google Patents

Verfahren zur steigerung der reichweite von drallstabilisierten projektilen und ebensolches projektil Download PDF

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Publication number
EP3028002B1
EP3028002B1 EP14744849.2A EP14744849A EP3028002B1 EP 3028002 B1 EP3028002 B1 EP 3028002B1 EP 14744849 A EP14744849 A EP 14744849A EP 3028002 B1 EP3028002 B1 EP 3028002B1
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EP
European Patent Office
Prior art keywords
projectile
transverse channels
tail
longitudinal channel
projectile according
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Active
Application number
EP14744849.2A
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German (de)
English (en)
French (fr)
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EP3028002A1 (de
Inventor
Martin Ziegler
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.)
Alpha Velorum AG
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Alpha Velorum AG
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    • 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

Definitions

  • the invention relates to a method for increasing the range of spin-stabilized projectiles and a similar projectile.
  • the projectile must have a high initial velocity, preferably supersonic velocity, and the resistance forces must be minimized so that the energy loss of the projectile is minimized along the trajectory.
  • the bow of the projectile is shaped resistance optimized, preferably as an ogive, and the tail pulled something what is known as boat tail or "boat tail", so that the cross section of the pressure reduction is reduced at the base of the projectile.
  • a further increase of the base pressure can be achieved by additional outflow of gas at the projectile base as so-called “base bleed", whereby the range can be considerably increased.
  • base bleed so-called “base bleed”
  • a spin stabilized projectile 1 according to the prior art with ogivalem bug and projectile tip 1a, cylindrical middle part 1b and retracted projectile tail 1c is shown, as is also typical for smaller caliber ammunition up to caliber .50 BMG, ie 12.7x99 mm.
  • the swirl stabilization is usually by achieved the shooting of drawn runs, but can also be achieved by other means, such as inclined aerodynamically effective surfaces. With regard to the effect according to the invention, only the occurrence of a rotation is necessary with a sufficiently large angular frequency, depending on the specific projectile design.
  • Projectiles or projectiles of the prior art often have a shape whose associated total length 10 in the in Fig. 1 illustrated three areas front part of the length 11 with bow and projectile tip 1a, center section 1b of length 12 and projectile tail 1c or projectile base of length 13 can divide.
  • boat tail of the rear diameter d3 is reduced relative to the caliber or center part diameter d1, so that there is a streamlined shape.
  • the resistance forces caused by movement in the space filled with air as the medium to be penetrated lead to a loss of kinetic energy.
  • each part of the projectile 1 with bow, center and tail contributes a specific share, its energy loss due to the energy conservation must correspond to an energy gain of its flow around.
  • Fig.2 Based on the flow field around a supersonic range at about 1.8 Mach flying projectile 1 with bow-Mach cone 2 and Heck-Mach-cone 3, energy transfer e to the boundary layer 8, NachstromMechkontur 4 with so-called dead water 5 as immediately behind the projectile existing aerodynamic shadow and turbulent wake 6 shown schematically.
  • the energy flow e is explained in the boundary layer 8 of the projectile 1, which forms a non-linear velocity profile near the wall and after a laminar start-up phase grows turbulently until it peels off the dull rear of the projectile.
  • the boundary layer 8 is shown in ground-fixed coordinates, wherein air or fluid particles are entrained near the wall in the direction of flight.
  • the energy loss of the projectile 1 along its path can be reduced by filling the velocity profile of the boundary layer 8 by feeding medium already moving at projectile velocity, which is the result Wall friction reduced.
  • the rotation of the projectile 1 and the radial or centrifugal acceleration generated thereby is used to convey fluid particles or particles of the medium from the dead water 5 of the projectile 1 into the boundary layer 8.
  • the range of a spin stabilized projectile can be increased or the projectile waste per distance interval can be reduced, so that a flatter trajectory with increased hit probability and a higher energy result in the target.
  • the spin-stabilized projectile 1 with an outer surface, a projectile tip and a projectile tail will be so formed, that the outer surface has at least one circumferential groove 9, which are connected via radial transverse channels 10 with at least one longitudinal channel 11 in the interior of the projectile 1, which in turn is connected to an opening in the rear projectile.
  • this longitudinal channel 11 is, for example, formed as an axial or longitudinal bore from the base or the projectile tail to the height of the circumferential groove 9 in its outer wall, from which the transverse channels 10 substantially at right angles, ie in the radial direction branch off, which can also be realized by appropriate drilling.
  • other types of manufacturing method according to the invention can be used.
  • the groove is in this case as close as possible to the bow region, so that a large part of the outer surface can be influenced by the generated flow with respect to the flow field.
  • the groove 9 can be arranged directly on the front part of the substantially cylindrical central part of the projectile.
  • the transition of the longitudinal channel 11 to the projectile base or the projectile tail is aerodynamically shaped, for example by a rounding r4 of the transition edge.
  • the flow that forms there increases the base pressure at the rear of the projectile, which reduces its resistance.
  • the diameter d4 of the longitudinal channel depends on various factors, such as the dimensions of the projectile, its internal structure and the expected Mach number or flight or muzzle velocity.
  • the cross section of the longitudinal channel 11 can be formed round and constant in the simplest case be, according to the invention, however, other geometries are used.
  • the channel can also be performed polygonal or star-shaped and with a length-dependent variable cross-section. Due to the swirl stabilization, however, a symmetrical mass distribution is to be ensured with respect to the swirl axis.
  • a multiplicity or multiplicity of such channels can also be formed.
  • the longitudinal channel 11 is in contact with a plurality of uniformly radially distributed transverse channels 10, which connect the longitudinal channel 11 as an inner conveyor channel with the outer wall of the projectile 1 and terminate in the circumferential groove 9.
  • transverse forces 10 which are executed as bores, produce a centrifugal force and therefrom the desired conveying effect, which conveys the fluid or surrounding medium from the dead water into the longitudinal channel 11 and finally into the boundary layer.
  • the number of transverse channels 10 can be adapted to the corresponding projectile geometries and flow conditions and can be both even and odd, eg 2, 3, 4, 5, 6 or 8.
  • the transverse channels 10 are uniform, ie distributed equidistantly over the circumference or with the same angle division.
  • the longitudinal channel 11 and the transverse channels 10 may have the various and mentioned in the local context geometries to take into account the production and fluidic conditions.
  • the radial transverse channels 10 can be a sickle-shaped or curved in or against the Have direction pointing in the direction of twist, so that the flow behavior of the conveyed medium can be influenced by a component acting in or counter to the direction of rotation.
  • the length of the radial transverse channels 10 and thus the proportion of the projectile diameter available for the centrifugal acceleration of the medium depends on the specific configuration of the projectile 1 and its flight or rotation speed. In particular, however, this can amount to at least one third of the diameter of the projectile 1 in each case.
  • the transverse channels 10 terminate in a circumferential groove 9 as a collecting channel for the fluid flowing out of the transverse channels 10, wherein the flowing surrounding medium or its boundary layer is relined out of the groove 9. It is advantageous to perform the groove 9 forward relatively sharp-edged to force a stall of the inflowing boundary layer, and provided at the rear with a shallow transition to promote the pumped fluid evenly under the front inflowing boundary layer flow and the velocity profile wall side fill.
  • the circumferential groove 9 has a profile whose projectile tip facing edge 9a is steeper than the projectile tail facing edge 9b is formed.
  • the projectile 1 according to the invention can be designed both as a full storey, but also as a jacketed projectile or as a projectile with a more complex internal structure, as is the case, for example, with artillery projectiles. Accordingly, the method according to the invention and the projectiles according to the invention are also not restricted to specific projectile types or calibers. In particular, small or medium calibers, e.g. common sports or hunting ammunition or anti-aircraft gun ammunition in the caliber 35mm or 40mm, but also artillery shells in the caliber 155mm, 175mm or 203mm are designed according to the invention.
  • small or medium calibers e.g. common sports or hunting ammunition or anti-aircraft gun ammunition in the caliber 35mm or 40mm, but also artillery shells in the caliber 155mm, 175mm or 203mm are designed according to the invention.
  • a projectile 1 according to the invention can have a sabot or a sabot or can also be designed as a flange projectile.
  • FIG. 5 shows the schematic representation of the flow at supersonic speed for the first embodiment of the projectile according to the invention. From the opposite Fig. 2 changed flow field around the projectile is seen that a portion of the fluid from the dead water circulates around the rear of the projectile and does not enter the turbulent wake. As a result, the energy loss of the projectile along the trajectory decreases.
  • the circulation leads to a detachment bladder 12 in the middle region, which there reduces the wall shear stress, and to an increase in pressure in the inflow of the base or the projectile tail, which reduces the resistance component from the flow around the blunt stern.
  • the reduction of the resistance forces corresponds to the reduction of energy loss. As a result, range and target energy or target effect of the projectile are increased.
  • a second embodiment of the projectile according to the invention which in particular has manufacturing advantages, is in the 6a-c shown.
  • a projectile according to the invention is thus composed in this case of at least two parts 13 and 14, wherein at least one of the two parts 13 and 14 has a plurality of evenly distributed on the circumference of hollow webs 15, preferably two to eight, wherein these after assembly in the interaction of the two Parts 13 and 14, the radial transverse channels 10 ' and / or the at least one longitudinal channel 11 'form.
  • the several recesses can be uniformly let into the circumference.
  • the projectile tip forming part 13 peg-shaped projecting into the projectile tail forming part 14.
  • the at least two parts 13 and 14 centered by conical seat and joined by friction, positive engagement, gluing, soldering or welding and connected to each other, wherein the parts 13 and 14 may also consist of different materials.
  • the channels are formed as a depression in one of the first of the two parts 13 and 14, wherein the second part 14 during assembly covers the open channel side, so that a total again longitudinally effetströmbare tubes and thus the inventive channels 10 'and 11' are formed.
  • the second embodiment of the projectile according to the invention consists of two parts 13 and 14, which can be centered over a conical seat and joined by frictional engagement in a press fit.
  • the parts may be joined together by positive locking, gluing, welding, soldering or another joining method.
  • Particularly advantageous here are the aerodynamic rounding of the channels, ie the transition from the longitudinal channel 11 'to the transverse channels 10' and the transition to the lateral wall opening gestaltbar, whereby the radial transverse channels 10 'and the at least one longitudinal channel 11 'have a common curved course. This allows a continuous and streamlined course of the entire channel can be realized.
  • the hollow paths required in front of the channels can be embedded both alone in the first part 13 and only in the second part 14 or in both parts 13 and 14. They may be parallel to the longitudinal axis or spiral, wherein at least two channels are required to avoid imbalance, but preferably, depending on the caliber two to eight channels evenly distributed around the circumference.
  • the two parts 13 and 14 can be made from cylindrical solid material and from tubes by cold forming, which allows a simple and cost-effective production. It is also advantageous here that the two parts can be made of different materials.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Earth Drilling (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Powder Metallurgy (AREA)
EP14744849.2A 2013-07-31 2014-07-30 Verfahren zur steigerung der reichweite von drallstabilisierten projektilen und ebensolches projektil Active EP3028002B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH01342/13A CH708412A2 (de) 2013-07-31 2013-07-31 Projektil mit verbesserter Reichweite.
PCT/EP2014/066341 WO2015014877A1 (de) 2013-07-31 2014-07-30 Verfahren zur steigerung der reichweite von drallstabilisierten projektilen und ebensolches projektil

Publications (2)

Publication Number Publication Date
EP3028002A1 EP3028002A1 (de) 2016-06-08
EP3028002B1 true EP3028002B1 (de) 2018-08-29

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP14744849.2A Active EP3028002B1 (de) 2013-07-31 2014-07-30 Verfahren zur steigerung der reichweite von drallstabilisierten projektilen und ebensolches projektil

Country Status (7)

Country Link
US (1) US10094644B2 (tr)
EP (1) EP3028002B1 (tr)
CH (1) CH708412A2 (tr)
ES (1) ES2699433T3 (tr)
HU (1) HUE040260T2 (tr)
TR (1) TR201816455T4 (tr)
WO (1) WO2015014877A1 (tr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE538646C2 (sv) * 2015-04-01 2016-10-11 Nammo Vanäsverken Ab Spårljusprojektil och förfarande för applicering av en spårljusanordning i en spårljusprojektil
US10317178B2 (en) * 2015-04-21 2019-06-11 The United States Of America, As Represented By The Secretary Of The Navy Optimized subsonic projectiles and related methods
US10928168B2 (en) * 2017-11-10 2021-02-23 Curtis E. Graber Noise control system and method for small caliber ammunition
US10119780B1 (en) * 2018-01-12 2018-11-06 David Wayne Bergeron Light gas gun projectile
CN114692318B (zh) * 2022-06-01 2022-08-26 中国飞机强度研究所 飞机冲击动力学测试用格栅式燃油箱结构抗毁伤评估方法

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB374091A (en) * 1929-12-24 1932-05-30 Hermann Gerlich Improvements in or relating to fire-arms or other projectile propelling apparatus and projectiles therefor
US2507878A (en) * 1943-10-16 1950-05-16 Jr Thomas A Banning Projectile
US2624281A (en) * 1947-09-10 1953-01-06 James A Mcnally Projectile
US2793592A (en) * 1952-02-28 1957-05-28 William J Kroeger Reaction means for rotating ammunition projectiles at low speeds
FR1246710A (fr) 1957-04-08 1960-11-25 Mobile aéronautique
GB1019061A (en) 1961-03-29 1966-02-02 Herbert Harry Pearcey Improvements relating to control of fluid flow past bodies and to reduction of drag of such bodies
US4176487A (en) * 1970-11-18 1979-12-04 Manis John R Firearm barrels and projectiles
US4379531A (en) * 1970-11-18 1983-04-12 Manis John R Projectile
US3890902A (en) * 1973-12-04 1975-06-24 Us Army Projectile
US3913489A (en) * 1973-12-19 1975-10-21 Us Army Projectile
PT77697B (fr) * 1982-11-24 1986-02-12 Ladriere Serge Projectile perfectionne destine a etre decharge par des armes a feu
US5381736A (en) * 1994-01-24 1995-01-17 Kalcic; Frank Recoil reducing bullet
US8082850B2 (en) * 2005-10-21 2011-12-27 Liberty Ammunition, Inc. Synchronized spin multi-component projectile
US8267015B2 (en) * 2005-10-21 2012-09-18 Liberty Ammunition, Inc. Multi-component projectile rotational interlock
AU2013101363B4 (en) * 2013-07-31 2014-03-13 Techventure Investments Pty Ltd A projectile body and corresponding ammunition round for small arms or a light firearm

Also Published As

Publication number Publication date
US20160169644A1 (en) 2016-06-16
US10094644B2 (en) 2018-10-09
TR201816455T4 (tr) 2018-11-21
HUE040260T2 (hu) 2019-02-28
WO2015014877A1 (de) 2015-02-05
CH708412A2 (de) 2015-02-13
EP3028002A1 (de) 2016-06-08
ES2699433T3 (es) 2019-02-11

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