EP0036232A1 - Training projectile - Google Patents

Training projectile Download PDF

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Publication number
EP0036232A1
EP0036232A1 EP81200252A EP81200252A EP0036232A1 EP 0036232 A1 EP0036232 A1 EP 0036232A1 EP 81200252 A EP81200252 A EP 81200252A EP 81200252 A EP81200252 A EP 81200252A EP 0036232 A1 EP0036232 A1 EP 0036232A1
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EP
European Patent Office
Prior art keywords
warhead
bullet
conical point
flight
ammunition
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.)
Granted
Application number
EP81200252A
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German (de)
French (fr)
Other versions
EP0036232B1 (en
Inventor
Joris De Brant
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.)
FN Herstal SA
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FN Herstal SA
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 FN Herstal SA filed Critical FN Herstal SA
Priority to AT81200252T priority Critical patent/ATE4940T1/en
Publication of EP0036232A1 publication Critical patent/EP0036232A1/en
Application granted granted Critical
Publication of EP0036232B1 publication Critical patent/EP0036232B1/en
Expired legal-status Critical Current

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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
    • F42B10/52—Nose cones

Definitions

  • the present invention relates to a training ammunition, particularly for weapons of war.
  • a .50 machine gun has a maximum range of around 7,000 m and a useful range of around 3,000 m.
  • a shooting range must have dimensions that comfortably take into account the maximum range, while the targets are only located at 500 or 600 meters. Huge spaces are thus lost, which is particularly annoying, especially in countries with high population density.
  • the object of the invention is to overcome these drawbacks by providing a training munition giving rise to a fair and precise shot up to a certain distance from the weapon (in principle to the place where the targets are located ) under the same shooting conditions and with the same flight time as war ammunition but having a very reduced range and maximum arrow.
  • the invention is based on the fact that following the oblique shock wave created by a projectile at supersonic speed, the pressure, the specific mass and the temperature of the air rise suddenly with the passage of the wave. It follows that the surface of the projectile warhead is subjected to high pressures and temperatures, this warhead absorbing heat during flight.
  • the principle of the invention is to use these factors to bring about a notable change in the shape of the projectile from a point on its trajectory corresponding to the useful range, so as to obtain a sudden deceleration and, consequently, a shortening. important of the total reach and the maximum deflection.
  • a driving ammunition according to the invention is therefore characterized in that at least part of the projectile warhead is made of a material eroding under the action of heat and pressures present on the surface of the warhead in flight so as to cause a modification of the shape of said warhead after a certain flight time, modification causing a notable increase in its aerodynamic coefficient, the remainder or body of the bullet being metallic.
  • Figure 1 shows a ball according to the invention, consisting of a body 1 having, in its front part, an annular flat face 2 and a central stud 3.
  • the body 1 receives a warhead 4 made in this example of high density polyethylene , having a softening temperature fixed by the useful range of the projectile, for example of the order of 120-130 ° C.
  • the warhead 4 is glued to the body 1 at the level of the face 2.
  • the plane of the front face 5 of the post 3 is situated clearly in front of the zone of greatest heating of the warhead in flight, except for the point.
  • the constituent material of the warhead 4 located between the planes 2 and 5 will have disappeared, while the tip of the warhead will have been partially and gradually eroded, which ensures the precision of the shoot.
  • the dimensions of the warhead in the plane of the face 5 are calculated so as to ensure the adhesion of said point or tenon 3 during the first flight time. Then, the material in contact with the face 5 erodes very quickly under the action of heat and pressure, which leads to the separation of the remainder of the point of the warhead of the post 3.
  • the front face 5 of the stud 3 is situated in a plane passing through a zone of lesser heating than those situated behind this plane when the projectile is in flight.
  • the dimensions of the ogival head in the plane of the face 5 are calculated so as to ensure that it adheres to the stud during the first phase of the flight, while allowing a slow and gradual change of the warhead, which ensures a fair and precise shot.
  • the choice of the constituent material of the warhead 4, its shape and that of the body 1 will be chosen in such a way that said sudden drop in speed is located at the end of the projectile's useful range or just beyond the latter. In this way, the ballistic characteristics of the above-described projectile will be, during the first phase of the flight (useful range), in all respects comparable to those of a real projectile.
  • the post 3 has the advantage of facilitating the centering and the maintenance of the warhead 4. It could however be omitted and replaced by a simple recess, as indicated in 6 in FIG.
  • an ammunition according to the invention exhibits, in the first phase of its flight, the same characteristics as an actual ammunition.
  • the increase in the aerodynamic resistance coefficient at the end of this first phase results solely from physical phenomena, the proper functioning of the ammunition is guaranteed.

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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)
  • Steroid Compounds (AREA)
  • Glass Compositions (AREA)
  • Lasers (AREA)
  • Liquid Crystal Substances (AREA)
  • Primary Cells (AREA)
  • Radar Systems Or Details Thereof (AREA)

Abstract

1. Training ammunition of the type comprising a case, an explosive charge and a bullet, having a body (1) and a conical point (4), one part at least of the conical point being made of a synthetic material bringing about an anti-aerodynamic modification of the bullet under the action of the heat and pressures acting o, the conical point in the course of the flight, the aforesaid conical point (4) having an axial recessed bore extending from its rear face, characterized in that the body of the (metallic) bullet has a tenon (3) intended for completely filling the aforesaid recessed bore of the conical point, the shape and dimensions of the bore and tenon (3) being such that in the course of the flight, the conical point (4) becomes progressively eroded through flowing of its constituent material towards the body (1) until the insufficiency of material at the tenon (3) level results in the separation of the remaining part of the conical point (4) of the body (1).

Description

La présente invention concerne une munition d'entraînement, particulièrement pour armes de guerre.The present invention relates to a training ammunition, particularly for weapons of war.

On sait que la portée maximum d'une arme est un multiple de sa portée utile. Une mitrailleuse .50 a une portée maximum de l'ordre de 7.000 m et une portée utile d'environ 3.000 m. Pour des raisons évidentes de sécurité, un champ de tir doit avoir des dimensions tenant confortablement compte de la portée maximum, alors que les cibles ne sont situées qu'à 500 ou 600 mètres. D'énormes espaces sont ainsi perdus, ce qui est particulièrement gênant, surtout dans les pays à haute densité de population.We know that the maximum range of a weapon is a multiple of its useful range. A .50 machine gun has a maximum range of around 7,000 m and a useful range of around 3,000 m. For obvious security reasons, a shooting range must have dimensions that comfortably take into account the maximum range, while the targets are only located at 500 or 600 meters. Huge spaces are thus lost, which is particularly annoying, especially in countries with high population density.

On a proposé, en vue de réduire la portée maximum, de diminuer la charge propulsive des munitions et/ou d'utiliser des balles ayant un coefficient aérodynamique élevé.In order to reduce the maximum range, it has been proposed to reduce the propellant charge of the ammunition and / or to use bullets having a high aerodynamic coefficient.

Cette dernière solution pose des difficultés, car la munition doit répondre à des impératifs de forme afin de pouvoir être accomodée normalement par le système d'alimentation et de chargement de l'arme.This last solution poses difficulties, because the ammunition must meet form requirements in order to be able to be accommodated normally by the supply and loading system of the weapon.

Pour contourner cette difficulté, on a proposé de munir une tête de balle anti-aérodynamique d'une coiffe ogivale de forme classique, destinée à être soufflée, lors du tir, dans l'âme même du canon de l'arme. Une telle solution est par exemple décrite dans le brevet belge n° 744.993.To circumvent this difficulty, it has been proposed to provide an anti-aerodynamic bullet head with a ogival cap of conventional shape, intended to be blown, when fired, into the very core of the gun barrel. Such a solution is for example described in Belgian patent n ° 744.993.

Ces solutions connues présentent le désavantage important de s'écarter des conditions de tir réel, qu'elles ne peuvent reproduire.These known solutions have the significant disadvantage of deviating from the real shooting conditions, which they cannot reproduce.

En effet, ces projectiles d'entraînement ont une vitesse de départ de beaucoup inférieure à celle d'un projectile réel correspondant. Il s'ensuit que pour atteindre une cible située dans la zone utile, il faut nécessairement plus de hausse. La précision du tir est également moindre et il est en outre souvent nécessaire de modifier le réglage du mécanisme d'armement de l'arme.Indeed, these training projectiles have a starting speed much lower than that of a corresponding real projectile. It follows that to reach a target located in the useful area, it is necessarily necessary more increase. The accuracy of the shot is also less and it is also often necessary to modify the setting of the weapon's weapon mechanism.

Le but de l'invention est de pallier ces inconvénients en fournissant une munition d'entraînement donnant lieu à un tir juste et précis jusqu'à une certaine distance de l'arme (en principe jusqu'à l'endroit ou se trouvent les cibles) sous les mêmes conditions de tir et avec le même temps de vol que la munition de guerre mais ayant une portée et une flèche maximale fort réduites.The object of the invention is to overcome these drawbacks by providing a training munition giving rise to a fair and precise shot up to a certain distance from the weapon (in principle to the place where the targets are located ) under the same shooting conditions and with the same flight time as war ammunition but having a very reduced range and maximum arrow.

L'invention repose sur le fait que suite à l'onde de choc oblique créée par un projectile à vitesse supersonique, la pression, la masse spécifique et la température de l'air s'élèvent brusquement au passage de l'onde. Il s'ensuit que la surface de l'ogive du projectile est soumise à de hautes pressions et températures, cette ogive absorbant de la chaleur en cours de vol.The invention is based on the fact that following the oblique shock wave created by a projectile at supersonic speed, the pressure, the specific mass and the temperature of the air rise suddenly with the passage of the wave. It follows that the surface of the projectile warhead is subjected to high pressures and temperatures, this warhead absorbing heat during flight.

Le principe de l'invention est d'utiliser ces facteurs pour entraîner une modification notable de la forme du projectile à partir d'un point de sa trajectoire correspondant à la portée utile, de manière à obtenir un brusque ralentissement et, partant, un raccourcissement important de la portée totale et de la flèche maximale.The principle of the invention is to use these factors to bring about a notable change in the shape of the projectile from a point on its trajectory corresponding to the useful range, so as to obtain a sudden deceleration and, consequently, a shortening. important of the total reach and the maximum deflection.

Une munition d'entraînement selon l'invention se caractérise dès lors en ce qu'une partie au moins de l'ogive du projectile est réalisée en un matériau s'érodant sous l'action de la chaleur et des pressions présentes à la surface de l'ogive en vol de manière à entraîner une modification de la forme de ladite ogive après un certain temps de vol, modification causant une notable augmentation de son coefficient aérodynamique, le restant ou corps de la balle étant métallique.A driving ammunition according to the invention is therefore characterized in that at least part of the projectile warhead is made of a material eroding under the action of heat and pressures present on the surface of the warhead in flight so as to cause a modification of the shape of said warhead after a certain flight time, modification causing a notable increase in its aerodynamic coefficient, the remainder or body of the bullet being metallic.

Deux exemples de réalisation de projectiles selon l'invention sont décrits ci-après avec référence aux figures 1 et 2 annexées, représentant chacune une réalisation différente.Two exemplary embodiments of projectiles according to the invention are described below with reference to Figures 1 and 2 attached, each representing a different embodiment.

La figure 1 représente une balle conforme à l'invention, constituée par un corps 1 présentant, en sa partie avant, une face plane annulaire 2 et un tenon central 3. Le corps 1 reçoit une ogive 4 réalisée dans cet exemple en polyéthylène haute densité, ayant une température de ramollissement fixée par la portée utile du projectile, par exemple de l'ordre de 120-130°C. L'ogive 4 est collée sur le corps 1 au niveau de la face 2.Figure 1 shows a ball according to the invention, consisting of a body 1 having, in its front part, an annular flat face 2 and a central stud 3. The body 1 receives a warhead 4 made in this example of high density polyethylene , having a softening temperature fixed by the useful range of the projectile, for example of the order of 120-130 ° C. The warhead 4 is glued to the body 1 at the level of the face 2.

Le plan de la face avant 5 du tenon 3 est situé nettement en avant de la zone de plus grand échauffement de l'ogive en vol, pointe exceptée. Ainsi, après un premier temps calculé de vol, la matière constitutive de l'ogive 4, située entre les plans 2 et 5 aura disparu, tandis que la pointe de l'ogive aura été partiellement et progressivement érodée, ce qui assure la précision du tir.The plane of the front face 5 of the post 3 is situated clearly in front of the zone of greatest heating of the warhead in flight, except for the point. Thus, after a first calculated flight time, the constituent material of the warhead 4, located between the planes 2 and 5 will have disappeared, while the tip of the warhead will have been partially and gradually eroded, which ensures the precision of the shoot.

A remarquer que les dimensions de l'ogive dans le plan de la face 5 sont calculées de façon à assurer l'adhésion de ladite pointe ou tenon 3 durant le premier temps de vol. Ensuite, la matière en contact avec la face 5 s'érode très rapidement sous l'action de la chaleur et de la pression, ce qui entraîne la séparation du restant de la pointe de l'ogive du tenon 3.Note that the dimensions of the warhead in the plane of the face 5 are calculated so as to ensure the adhesion of said point or tenon 3 during the first flight time. Then, the material in contact with the face 5 erodes very quickly under the action of heat and pressure, which leads to the separation of the remainder of the point of the warhead of the post 3.

La face avant 5 du tenon 3 est situé dans un plan passant par une zone d'échauffement moindre que celles situées derrière ce plan lorsque le projectile est en vol. Les dimensions de la tête ogivale dans le plan de la face 5 sont calculées de façon à assurer l'adhésion de celle-ci au tenon pendant la première phase du vol, tout en permettant un changement lent et progressif de l'ogive, ce qui assure un tir juste et précis.The front face 5 of the stud 3 is situated in a plane passing through a zone of lesser heating than those situated behind this plane when the projectile is in flight. The dimensions of the ogival head in the plane of the face 5 are calculated so as to ensure that it adheres to the stud during the first phase of the flight, while allowing a slow and gradual change of the warhead, which ensures a fair and precise shot.

Dans la deuxième phase, la matière se trouvant dans le plan de la face 5 du tenon s'érode très vite sous l'action de la chaleur et de la pression résultant dans la séparation de la tête (reste) du tenon (voir figures en annexe). Il ne reste dès lors plus qu'un projectile à coefficient aérodynamique élevé, ce qui se traduit par une chute brutale de la vitesse et une diminution importante de la portée totale.In the second phase, the material lying in the plane of the face 5 of the post erodes very quickly under the action of heat and pressure resulting in the separation of the head (rest) of the post (see figures in Annex). There therefore remains only one projectile with a high aerodynamic coefficient, which results in a sudden drop in speed and a significant reduction in the total range.

Le choix du matériau constitutif de l'ogive 4, sa forme et celle du corps 1 seront choisis de manière telle que ladite chute brutale de vitesse se situe en fin de portée utile du projectile ou juste au-delà de cette dernière. De cette manière, les caractéristiques balistiques du projectile sus- décrit seront, durant la première phase du vol (portée utile), en tous points comparables à celles d'un projectile réel.The choice of the constituent material of the warhead 4, its shape and that of the body 1 will be chosen in such a way that said sudden drop in speed is located at the end of the projectile's useful range or just beyond the latter. In this way, the ballistic characteristics of the above-described projectile will be, during the first phase of the flight (useful range), in all respects comparable to those of a real projectile.

Le tenon 3 a pour avantage de faciliter le centrage et le maintien de l'ogive 4. Il pourrait toutefois être omis et remplacé par un simple évidement, comme indiqué en 6 à la figure 2.The post 3 has the advantage of facilitating the centering and the maintenance of the warhead 4. It could however be omitted and replaced by a simple recess, as indicated in 6 in FIG.

Il est clair de ce qui précède qu'une munition selon l'invention présente, dans la première phase de son vol, les mêmes caractéristiques qu'une munition réelle. Comme l'augmentation du coefficient de résistance aérodynamique au terme de cette première phase résulte uniquement de phénomènes physiques, le bon fonctionnement de la munition est garanti.It is clear from the above that an ammunition according to the invention exhibits, in the first phase of its flight, the same characteristics as an actual ammunition. As the increase in the aerodynamic resistance coefficient at the end of this first phase results solely from physical phenomena, the proper functioning of the ammunition is guaranteed.

Il est évident que d'autres formes de réalisation que celles décrites ci-dessus peuvent être envisagées, sans pour autant sortir du cadre de l'invention.It is evident that other embodiments than those described above can be envisaged without departing from the scope of the invention.

Claims (5)

1.- Munition d'entraînement du type constitué principalement par une douille, une charge propulsive et une balle à ogive de forme identique à celle d'une balle réelle, caractérisée en ce qu'une partie au moins de ladite ogive (4) est réalisée en un matériau s'érodant sous l'action de la chaleur et des pressions présentes à la surface de l'ogive en vol de manière à entraîner une modification de la forme de ladite ogive après un certain temps de vol, modification causant une notable augmentation de son coefficient aérodynamique, le restant ou corps (1) de la balle étant métallique.1.- Training ammunition of the type mainly consisting of a cartridge case, a propellant charge and a bullet with a warhead of identical shape to that of a real bullet, characterized in that at least part of said warhead (4) is made of a material eroding under the action of heat and pressure present on the surface of the warhead in flight so as to cause a change in the shape of said warhead after a certain flight time, modification causing a notable increase in its aerodynamic coefficient, the remainder or body (1) of the ball being metallic. 2.- munition selon la revendication l, caractérisée en ce que ladite ogive (4) est réalisée en une matière synthétique ayant une température de ramollissement de l'ordre de 120-130°C, cette ogive étant solidarisée à la balle (1) par collage.2.- ammunition according to claim l, characterized in that said warhead (4) is made of a synthetic material having a softening temperature of the order of 120-130 ° C, this warhead being secured to the bullet (1) by collage. 3.- Munition selon la revendication 2, caractérisée en ce que ladite ogive (4) présente un alésage borgne axial s'étendant à partir de sa face arrière.3. Ammunition according to claim 2, characterized in that said warhead (4) has an axial blind bore extending from its rear face. 4.- Munition selon la revendication 3, caractérisée en ce que le corps de la balle (1) présente un tenon (3) destiné à remplir complètement ledit alésage.4. Ammunition according to claim 3, characterized in that the body of the bullet (1) has a stud (3) intended to completely fill said bore. 5.- Munition selon la revendication 4, caractérisée en ce que les longueurs et diamètres desdits alésage et tenon (3) sont tels que, durant le vol du projectile, la partie de l'ogive située entre le corps de la balle et l'extrémité avant (5) du tenon (3) s'érode complètement avant que ne disparaisse la partie restante ou pointe de l'ogive.5. Ammunition according to claim 4, characterized in that the lengths and diameters of said bore and tenon (3) are such that, during the flight of the projectile, the part of the warhead situated between the body of the bullet and the front end (5) of the post (3) completely erodes before the remaining part or tip of the warhead disappears.
EP81200252A 1980-03-18 1981-03-05 Training projectile Expired EP0036232B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT81200252T ATE4940T1 (en) 1980-03-18 1981-03-05 PRACTICE BULLET.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
BE58460 1980-03-18
BE2/58460A BE882272A (en) 1980-03-18 1980-03-18 TRAINING AMMUNITION

Publications (2)

Publication Number Publication Date
EP0036232A1 true EP0036232A1 (en) 1981-09-23
EP0036232B1 EP0036232B1 (en) 1983-10-05

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EP81200252A Expired EP0036232B1 (en) 1980-03-18 1981-03-05 Training projectile

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EP (1) EP0036232B1 (en)
AT (1) ATE4940T1 (en)
BE (1) BE882272A (en)
DE (1) DE3161078D1 (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0123978A2 (en) * 1983-04-23 1984-11-07 Rheinmetall GmbH Nose cap for a projectile with an armour-piercing core
FR2547407A1 (en) * 1983-06-08 1984-12-14 Mecanique Ste Nle Et Practise projectile for artillery with trajectory retardation and impact marking
GB2154713A (en) * 1981-09-22 1985-09-11 Herstal Sa Improved ammunition
EP0346779A1 (en) * 1988-06-14 1989-12-20 DIEHL GMBH & CO. Projectile for practice
EP0385129A1 (en) * 1989-03-03 1990-09-05 Werkzeugmaschinenfabrik Oerlikon-Bührle AG Short-trajectory projectile having means for reducing the range
US9157713B1 (en) 2013-03-15 2015-10-13 Vista Outdoor Operations Llc Limited range rifle projectile
US9952024B2 (en) 2014-03-10 2018-04-24 Nostromo Holdings, Llc Ammunition cartridge with induced instability at a pre-set range

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2114879A5 (en) * 1970-12-08 1972-06-30 Oerlikon Buehrle Ag

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE734429C (en) * 1939-07-20 1943-04-15 Ing Bohdan Pantoflicek Practice bullet with shortened trajectory
US4140061A (en) * 1977-06-06 1979-02-20 The United States Of America As Represented By The Secretary Of The Army Short-range discarding-sabot training practice round and self-destruct subprojectile therefor
DE2756420C2 (en) * 1977-12-17 1985-02-07 Rheinmetall GmbH, 4000 Düsseldorf Bullet with automatic splitting effect

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2114879A5 (en) * 1970-12-08 1972-06-30 Oerlikon Buehrle Ag

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2154713A (en) * 1981-09-22 1985-09-11 Herstal Sa Improved ammunition
EP0123978A2 (en) * 1983-04-23 1984-11-07 Rheinmetall GmbH Nose cap for a projectile with an armour-piercing core
EP0123978A3 (en) * 1983-04-23 1985-05-15 Rheinmetall Gmbh Nose cap for a projectile with an armour-piercing core
FR2547407A1 (en) * 1983-06-08 1984-12-14 Mecanique Ste Nle Et Practise projectile for artillery with trajectory retardation and impact marking
EP0346779A1 (en) * 1988-06-14 1989-12-20 DIEHL GMBH & CO. Projectile for practice
EP0385129A1 (en) * 1989-03-03 1990-09-05 Werkzeugmaschinenfabrik Oerlikon-Bührle AG Short-trajectory projectile having means for reducing the range
US5001986A (en) * 1989-03-03 1991-03-26 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Short-range projectile containing means for producing a short flight path
US9157713B1 (en) 2013-03-15 2015-10-13 Vista Outdoor Operations Llc Limited range rifle projectile
US9952024B2 (en) 2014-03-10 2018-04-24 Nostromo Holdings, Llc Ammunition cartridge with induced instability at a pre-set range

Also Published As

Publication number Publication date
BE882272A (en) 1980-09-18
EP0036232B1 (en) 1983-10-05
ATE4940T1 (en) 1983-10-15
DE3161078D1 (en) 1983-11-10

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