US3800706A - Projectile for training ammunition - Google Patents

Projectile for training ammunition Download PDF

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Publication number
US3800706A
US3800706A US00203401A US20340171A US3800706A US 3800706 A US3800706 A US 3800706A US 00203401 A US00203401 A US 00203401A US 20340171 A US20340171 A US 20340171A US 3800706 A US3800706 A US 3800706A
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United States
Prior art keywords
projectile
central bore
discharge channels
training ammunition
ammunition
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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
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US00203401A
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English (en)
Inventor
H Gawlick
A Schatz
H Mothes
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Dynamit Nobel AG
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Dynamit Nobel AG
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Priority claimed from DE19712149977 external-priority patent/DE2149977A1/de
Application filed by Dynamit Nobel AG filed Critical Dynamit Nobel 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
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
    • F42B10/54—Spin braking means

Definitions

  • the spin braking means includes a central bore extending from the tip of the projectile partially therethrough with the rear portion of the central bore being in communication with the outer surface of the projectile via discharge channels arranged about the central bore.
  • the rear portion of the central bore is provided with a deflecting lobe having a cross section which increases rearwardly for directing the air flow into the discharge channels in order to minimize turbulence in the air flow.
  • the central bore and discharge channels operate in the manner of a rotary compressor with radial rotors in that air flow therethrough during the flight of a spin stabilized projectile effects braking of the projectile in a predetermined manner to reduce the flight range of the projectile. With known flight characteristics of a projectile, the cross-sectional size of the central bore and discharge channels can be selected to produce a predetermined braking effect and a predetermined flight range for the projectile.
  • the present invention relates to training ammunition having a reduced flight range and capable of being utilized on small firing ranges.
  • the projectile is formed in the manner of live ammunition and is provided with a continuous central axial bore.
  • the bore has an inside cross section which can be up to one third or more of the caliber cross section, and which can additionally be of a special configuration for the purpose of effecting an axial braking of the projectile.
  • the present invention provides a training ammunition having a reduced range wherein the projectile is controlled in an exactly predetermined manner by braking the spin to below the minimum spin required to maintain the stable flight of the projectile.
  • the use of the training ammunition constructed in accordance with the present invention is possible on small firing ranges.
  • An initial consideration is that the firing of the ammunition from the original weapon takes place at a known spin angle, and a prerequisite is that the projectile leaves the barrel of the weapon at a spin speed which is so far above the minimum speed necessary for a stable flight that a stably traversed flight path of a desired length is the result, with a continuous braking of the spin starting at the instant of departure. This is accomplished, according to this invention, by providing the tip portion of the ammunition with a spin-braking means.
  • the spin-braking device it is possible by appropriate configuration and dimensioning of the spin-braking device to brake the rotation of the projectile during its flight in such a manner that this rotation, after a flight path which is predetermined within certain limits, falls below the minimum rotation requi'red for spin stabilization.
  • the projectile begins to tumble, finally is pivoted by 180 vertically to its axis of rotation, and continues its flight with the rear of the projectile pointing forward.
  • this is connected with an increase in the air resistance or drag which can be influenced by the configuration of the rear of the projectile, such that a shortened maximum range of the projectile is provided.
  • the training ammunition is usable in a similar manner to that of live ammunition and exhibits initially the same behavior with respect to external ballistics and consequently also the same flight path as the live projectile. Therefore, the same sighting adjustment can be utilized for firing the training ammunition as that for live ammunition.
  • the maximum firing range is smaller than in case of live ammunition, so that the practice projectile can be utilized with great versatility on firing ranges having a smaller safety zone.
  • the spin-braking means is formed as a bore of the blind-hole type starting at the tip of the projectile with the rear of the bore ending within the projectile and being in communication with bores at the jacket of the projectile via preferably radially disposed channels.
  • the air entering the central bore and dammed up therein flows via the channels and communicating bores toward the outside. Due to appropriate arrangement and configuration of the mouths of the bores, the projectile imparts to the exiting air an impulse which is in opposition to the spin direction such that the rotation of the projectile is braked by the amount of the impulse.
  • this spin-braking means basically has the effect of a rotary compressor, the energy requirement of which is covered by the rotational energy of the projectile, the central bore and the dis charge channels are formed in accordance with the known principles of rotary compressors with radial rotors.
  • the discharge channels and central bore of the spin braking means may be designed to have the effect of a radial rotor, initially, i.e. without lengthy experiments, in such a manner that the decrease in rotational energy and thus also the passing of the stability limit of the projectile toward instability take place in a predetermined manner.
  • the inside diameter of the central bore is selected to be between approximately 10 and 40% of the caliber of the projectile. This diameter range is preferable since a smaller inside diameter could provide an insufficient flow of air through the central bore and a larger inside diameter with correspondingly shorter discharge channels could undesirably reduce the energy transfer to the exiting air.
  • the discharge channels may be positioned at least approximately in the zone of the cross-sectional plane defined by the center of gravity of the projectile. In this manner, the resultant of any uncompensated lateral flow forces within the discharge channels, which are disposed, for example, in a plane or also on a conical surface, is arranged to be effective at least approximately in the center of gravity of the projectile,
  • the projectile which can be formed in one piece, for example by casting, is formed of different mating portions in order to keep the manufacturing expenses as low as possible.
  • the projectile is divided in the region of the discharge channels in such a manner that one part having a lug engages into a corresponding recess of the other part, and the discharge channels are each formed as two partial bores which are preferably inclined toward each other and arranged in the lug and in the wall of the recess.
  • the discharge channels are formed in separate components as a radial rotor member.
  • the discharge channels can be joined to the projectile in the zone of the rear end of the central bore. That is, the central bore extends completely through the front part of the projectile and the radial rotor is attached at the rear of the projectile to close off the central bore.
  • the rigid connection of the two parts of the projectile with each other, or of the individually manufactured radial rotor with the projectile divided in the zone of the rear end of the central bore can be effected in a conventional manner, depending on the particular situation, for example depending on the materials employed or on the forces effective on the projectile, by frictional contact in the manner of a press fit, or also by means of a threaded, plug-in, glue, weld, or solder connection, or the like.
  • a deflecting lobe with a cross section that increases in the flow direction is suitably disposed at the rear end of the central bore in order to minimize turbulence in the air flow from the central bore to the discharge channels.
  • This lobe can have a conical configuration, for example, wherein the diameter of the base corresponds to the diameter of the central bore.
  • the design ofthe deflecting lobe is such that it has a concave surface in its part under the effect of the air flow.
  • FIG. 1 is a longitudinal sectional view of a projectile exiting from a barrel of a weapon in accordance with the present invention
  • FIG. 2 is a longitudinal sectional view of another embodiment of a projectile in accordance with the present invention.
  • FIG. 3 is a cross-sectional view taken along line III- ---III of the projectile of FIG. 2,
  • FIG. 4 is a fragmentary longitudinal sectional view of another projectile embodiment wherein the radial rotor is formed as a separate component
  • FIGS. 5a and 5b are plan and elevational views, respectively, of the radial rotor of FIG. 4, and
  • FIG. 6 is a cross-sectional view of another radial rotor in accordance with the present invention.
  • FIG. I shows a training projectile l which is integrally formed, for example by casting, and having a caliber D exiting from the barrel 25 of a weapon.
  • the projectile is provided with a central bore 2 having an inside diameter D, and discharge channels 3 extending therefrom.
  • the discharge channels have a height h, at the entrance and a height h at the exit.
  • a rotationally symmetrical deflecting lobe 4 is integrally formed with the projectile.
  • the discharge channels 3 are disposed approximately in the zone of the cross-sectional plane determined by the center of gravity of the projectile, so that any transverse forces due to the air flow indicated by the arrows A exert only a minor influence on the projectile.
  • the projectile l is constructed in a conventional manner of steel, brass, aluminum, or like materials.
  • the projectile 1 is shown as being divided in the region of the discharge channels 3, only one channel being shown for reasons of clarity, in such a manner that the rear part 5 having a lug 6 engages a corresponding recess of the front part 7. Both parts are connected with each other by means of a threaded joint.
  • the surface 15 of the deflecting lobe 8 which is under the effect of the air flow, is concave and formed to be rotationally symmetrical.
  • An annular guide band 11 of, for example, copper, brass, or lead is secured about the rear part 5 and serves to provide a better seal in the barrel of the firearm.
  • the projectile is also provided with a signal flare cartridge 12 which is inserted in the bottom section 10 and a target marking charge 13 is arranged in the front part 7. It would, of .course, be possible to provide, in place of the signal flare cartridge 12 and/or the target marking charge 13, an impact bursting charge or the like.
  • the tip 14 of the projectile can be produced, for example, of a synthetic resin, aluminum, or also of steel. The selection of the material depends on the weight to be imparted to the projectile, and whether a pyrotechnic target marking is desired. In this case, the tip of the projectile is suitably made of a readily deformable material, preferably polyethylene or aluminum.
  • the cross section taken along line IIIIII of FIG. 2, illustrated in FIG. 3, shows the distribution of the discharge channels 3 between the lug 6 and the front part 7 into two mutually inclined partial bores 16 and 17.
  • the spin-stabilized projectile rotates, in accordance with the arrow B, in the counterclockwise direction, the mutual inclination of the partial bores 16 and 17, provided in the same direction, effects the largest possible spin-braking, in that a rotational force in the opposite direction is effected.
  • a rotor 18 which is formed as a separate component is inserted into the projectile 1 which is divided into a rear part 5 and a front part 7.
  • the radial rotor 18 is secured by means of pins 19 in the rear part 5 with the rear and front parts being connected by means of the thread 20.
  • perforations 21 are provided, which are associated with the discharge channels 3 formed in the radial rotor 18, in order to make it possible for the air to exit laterally.
  • the front part 7, as distinguished from FIG. 2, is manufactured integrally with the tip of the projectile, which portion is not shown.
  • the radial rotor 18 of FIG. 4 which is illustrated in top plan and elevation views in FIGS. 5a and 5b is provided with six radially disposed vanes 22 in a uniform distribution such that the discharge channels 3 are formed between these vanes. As shown in FIG. 5b, the height of the vanes 22 decreases in the outward radial direction with the mutual distance between vanes increasing in this direction. Both parameters are adapted to each other in such a manner that the cross-sectional modification of the discharge channels 3 obtained thereby makes it exactly possible to achieve the desired effect on the air flow.
  • the radial rotor 18 is preferably manufactured from a metal which can be processed by means of the die-casting method, such as, for example, aluminum, zinc alloys, or like materials.
  • FIG. 6 there is shown another embodiment of a radial rotor 23 in a cross-sectional view with the section taken close to the lower end of the deflecting lobe 4.
  • the vanes 24 are curved in the manner of turbine vanes.
  • the connection with the projectile parts can be effected in the same manner as shown in FIG. 4, but, of course, can also be accomplished in another conventional manner.
  • a spin-stabilized training projectile having a desired shortened range may be produced.
  • An example of such a projectile is a projectile having the caliber D 105 mm., a muzzle velocity of approximately 800 m./sec., and a peripheral speed at the muzzle of the weapon of approximately 30 m./sec. which is in the same order of magnitude as a rotary compressor.
  • the pressure difference between the tip of the projectile and the cylindrical zone of the jacket of the projectile has, depending on the configuration of the tip, an upper limit of approximately 1kp./cm This projectile was designed to fall below the stability limit after approximately 1,500 meters of firing range and then to descend to the ground as quickly as possible.
  • the projectile was constructed in accordance with FIGS. 2 and 3 to have four bores for the discharge channels 16, 17. Each channel had a diameterof 12.5 mm. and a bend angle of 45 with the inside diameter D, of the central bore 2 being 30 mm.
  • photographic records of the flight path of the projectile disclosed deviations after approximately 1,500 meters as a result of the projectile becoming unstable in flight, thereby providing the required shortening of the maximum range of the projectile.
  • Training ammunition comprising a projectile having a spin stabilized flight upon launching from a barrel of a weapon and spin-braking means arranged in said projectile serving as a rotary compressor with radial rotors for braking the spin stabilized flight of said projectile to reduce the maximum flight range thereof, said spin-braking means including a central bore extending from the tip of said projectile partially therethrough, said central bore having the rear portion thereof in communication with the outer surface of said projectile via discharge channels arranged about said central bore, whereby the spin stabilized flight of said projectile is braked by the flow of air through said central bore and said discharge channels.
  • said projectile includes at least a first and second part joined together in the region of said discharge channels, said first part being provided with a lug portion and said second part being provided with a recess portion for receiving said lug portion, each of said discharge channels being formed as two partial bores, one of said bores being provided in the lug portion of said first part and the other bore being provided in the wall of said recess portion of said second part.
  • said projectile includes at least a first and second part joined together in the region of said discharge channels, said first part being provided with a lug portion and said second part being provided with a recess portion for receiving said lug portion, each of said discharge channels being formed as two partial bores, one of said bores being provided in the lug portion of said first part and the other bore being provided in the wall of said recess portion of said second part.
  • said projectile includes at least a first and second part joined together in the region of said discharge channels, said first part being provided with a lug portion and said second part being provided with a recess portion for receiving said lug portion, each of said discharge channels being formed as two partial bores, one of said bores being provided in the lug portion of said first part and the other bore being provided in the wall of said recess portion of said second part.
  • said projectile includes at least a first and second part joined together in the region of said discharge channels, said first part being provided with a lug portion and said second part being provided with a recess portion for receiving said lug portion, each of said discharge channels being formed as two partial bores, one of said bores being provided in the lug portion of said first part and the other bore being provided in the wall of said recess portion of said second part.
  • said projectile includes at least a first and second part joined together in the region of said discharge channels, said first part being provided with a lug portion and said second part being provided with a recess portion for receiving said lug portion, each of said discharge channels being formed as two partial bores, one of said bores being provided in the lug portion of said first part and the other bore being provided in the wall of said recess portion of said second part.
  • Training ammunition as defined in claim 40 wherein said second part is provided with a deflecting lobe having a cross section which increases rearwardly in the flow direction, said deflecting lobe being disposed on said part at the junction of said discharge channels and adapted to be arranged along the axis of the central bore at the rear end thereof.
  • Training ammunition as defined in claim 1 wherein said projectile is provided with a first part having said central bore therein, said first part having a cylindrical portion with apertures arranged in the region ofthe rear end of said central bore and extending to the outer cylindrical surface of said projectile, and a second part having discharge channels adapted for connection with said first part in the region of the rear end of said central bore, each of said discharge channels being arranged for communication with a corresponding aperture of said first part for directing the air flow from said central bore into said corresponding aperture.
  • Training ammunition as defined in claim 46 wherein said second part is provided with a deflecting lobe having a cross section which increases rearwardly in the flow direction, said deflecting lobe being disposed on said part at the junction of said discharge channels and adapted to be arranged along the axis of the central bore at the rear end thereof.
  • said projectile includes a first part having said central bore therein, said first part having a cylindrical portion having apertures arranged about the periphery thereof in the region of the rear end of said central bore, a second part connected to said first part, and a third part forming said discharge channels being positioned on said second part in the region of the rear end of said central bore and arranged for communication with said apertures of said first part for directing the air flow from said central bore into said apertures.
  • An arrangement for training ammunition comprising a projectile, a weapon for launching said projectile and imparting a rotation to said projectile so as to provide a spin stabilized flight of said projectile, said projectile including braking means for applying rotation retarding forces to said spin stabilized projectile so as to brake the spin stabilized flight of said projectile and making said projectile unstable thereby limiting the maximum flight range of said projectile.
  • said braking means is arranged within said projectile and includes a central bore extending from the tip of said projectile partially therethrough, said central bore having the rear portion thereof in communication with the outer surface of said projectile via discharge channels arranged about said central bore, whereby the spin stabilized flight of said projectile is retarded by the flow of air through the central bore and the discharge channels.
  • a method for controlling the flight range of spin stabilized projectiles for training purposes comprising the steps of launching a projectile, imparting a rotation to the projectile so as to provide a spin stabilized flight for the projectile, and applying a spin retarding force to the spin stabilized projectile to break the rotation of ill projectile includes a central bore extending from the tip of the projectilepartially therethrough, the central bore having the rear portion thereof in communication with the outer surface of the projectile via discharge channels arranged about the central bore, the step of applying a retarding force including the directing of the air flow through the central bore and the discharge channels to brake the spin stabilized flight of the projectile.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Toys (AREA)
US00203401A 1971-10-07 1971-11-30 Projectile for training ammunition Expired - Lifetime US3800706A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19712149977 DE2149977A1 (de) 1968-01-02 1971-10-07 Geschoss fuer uebungsmunition

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US3800706A true US3800706A (en) 1974-04-02

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US00203401A Expired - Lifetime US3800706A (en) 1971-10-07 1971-11-30 Projectile for training ammunition

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US (1) US3800706A (enrdf_load_stackoverflow)
BE (1) BE775978A (enrdf_load_stackoverflow)
FR (1) FR2155174A5 (enrdf_load_stackoverflow)
GB (1) GB1351666A (enrdf_load_stackoverflow)
NL (1) NL7116088A (enrdf_load_stackoverflow)
NO (1) NO130495C (enrdf_load_stackoverflow)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4128060A (en) * 1976-04-13 1978-12-05 Dynamit Nobel Aktiengesellschaft Short-range projectile for practice ammunition
US4208968A (en) * 1976-09-04 1980-06-24 Dynamit Nobel Aktiengesellschaft Projectile for practice ammunition
US4520972A (en) * 1981-06-05 1985-06-04 Dynamit Nobel Aktiengesellschaft Spin-stabilized training missile
US4653405A (en) * 1985-09-27 1987-03-31 Duchossois Industries, Inc. Self-destructing projectile
DE102010006164A1 (de) * 2010-01-29 2011-08-04 Lödding, Jutta, 31275 Geschoss
US8640624B1 (en) * 2011-12-21 2014-02-04 The United States Of America As Represented By The Secretary Of The Army Low collateral damage air defense projectile
US9851186B2 (en) * 2015-03-23 2017-12-26 James F. Brown High spin projectile apparatus for smooth bore barrels
US9885553B2 (en) * 2014-01-02 2018-02-06 Keith Allen Langenbeck Hollow tube projectiles and launch systems thereof
US10591263B2 (en) * 2015-03-23 2020-03-17 Brown James F High spin projectile apparatus comprising components made by additive manufacture
US11156442B1 (en) 2018-10-11 2021-10-26 U.S. Government As Represented By The Secretary Of The Army Dynamic instability reduced range round
US20230184524A1 (en) * 2021-09-07 2023-06-15 True Velocity Ip Holdings, Llc Vented hollow point projectile

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2557293A1 (de) * 1975-12-19 1977-06-30 Dynamit Nobel Ag Uebungsgeschoss
FR2551196B1 (fr) * 1976-06-02 1986-06-06 France Etat Armement Projectile d'exercice a portee reduite pour un champ de tir a gabarit reduit
FR2547407B1 (fr) * 1983-06-08 1990-09-28 Mecanique Ste Nle Et Projectile d'exercice pour artillerie a freinage de trajectoire et marquage d'impact
DE3376451D1 (en) * 1983-09-01 1988-06-01 France Etat Training projectile
EP4264169A1 (en) 2020-12-16 2023-10-25 BAE SYSTEMS plc Energy harvesting assemblies
GB2602050B (en) * 2020-12-16 2023-06-07 Bae Systems Plc Energy harvesting assemblies
US12398986B2 (en) * 2023-09-25 2025-08-26 Thomas Martin Firearm projectile device

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US33746A (en) * 1861-11-19 Improvement in projectiles for fire-arms
US35103A (en) * 1862-04-29 Improvement in projectiles for ordnance
US40142A (en) * 1863-09-29 Improvement in projectiles for ordnance
US40538A (en) * 1863-11-03 Improvement in explosive shells
US962482A (en) * 1910-01-28 1910-06-28 George E Wells Projectile.
US1892158A (en) * 1931-05-26 1932-12-27 Matthews John Short range bullet
US3713386A (en) * 1970-06-22 1973-01-30 Colt Ind Operating Corp Range limited projectile system

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US33746A (en) * 1861-11-19 Improvement in projectiles for fire-arms
US35103A (en) * 1862-04-29 Improvement in projectiles for ordnance
US40142A (en) * 1863-09-29 Improvement in projectiles for ordnance
US40538A (en) * 1863-11-03 Improvement in explosive shells
US962482A (en) * 1910-01-28 1910-06-28 George E Wells Projectile.
US1892158A (en) * 1931-05-26 1932-12-27 Matthews John Short range bullet
US3713386A (en) * 1970-06-22 1973-01-30 Colt Ind Operating Corp Range limited projectile system

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4128060A (en) * 1976-04-13 1978-12-05 Dynamit Nobel Aktiengesellschaft Short-range projectile for practice ammunition
US4208968A (en) * 1976-09-04 1980-06-24 Dynamit Nobel Aktiengesellschaft Projectile for practice ammunition
US4520972A (en) * 1981-06-05 1985-06-04 Dynamit Nobel Aktiengesellschaft Spin-stabilized training missile
US4653405A (en) * 1985-09-27 1987-03-31 Duchossois Industries, Inc. Self-destructing projectile
DE102010006164A1 (de) * 2010-01-29 2011-08-04 Lödding, Jutta, 31275 Geschoss
DE102010006164B4 (de) * 2010-01-29 2012-04-05 Jutta Lödding Geschoss
US8640624B1 (en) * 2011-12-21 2014-02-04 The United States Of America As Represented By The Secretary Of The Army Low collateral damage air defense projectile
US9885553B2 (en) * 2014-01-02 2018-02-06 Keith Allen Langenbeck Hollow tube projectiles and launch systems thereof
US9851186B2 (en) * 2015-03-23 2017-12-26 James F. Brown High spin projectile apparatus for smooth bore barrels
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
US11156442B1 (en) 2018-10-11 2021-10-26 U.S. Government As Represented By The Secretary Of The Army Dynamic instability reduced range round
US20230184524A1 (en) * 2021-09-07 2023-06-15 True Velocity Ip Holdings, Llc Vented hollow point projectile
US11859954B2 (en) * 2021-09-07 2024-01-02 True Velocity Ip Holdings, Llc Vented hollow point projectile

Also Published As

Publication number Publication date
BE775978A (fr) 1972-03-16
NO130495C (enrdf_load_stackoverflow) 1974-12-18
NO130495B (enrdf_load_stackoverflow) 1974-09-09
FR2155174A5 (enrdf_load_stackoverflow) 1973-05-18
NL7116088A (enrdf_load_stackoverflow) 1973-04-10
GB1351666A (en) 1974-05-01

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