EP0300373B1 - Projectile sous-calibré stabilisé par ailettes - Google Patents

Projectile sous-calibré stabilisé par ailettes Download PDF

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Publication number
EP0300373B1
EP0300373B1 EP88111368A EP88111368A EP0300373B1 EP 0300373 B1 EP0300373 B1 EP 0300373B1 EP 88111368 A EP88111368 A EP 88111368A EP 88111368 A EP88111368 A EP 88111368A EP 0300373 B1 EP0300373 B1 EP 0300373B1
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EP
European Patent Office
Prior art keywords
sabot
projectile
swirl
penetrator
spin
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP88111368A
Other languages
German (de)
English (en)
Other versions
EP0300373A3 (en
EP0300373A2 (fr
Inventor
Fritz K. Dr. Feldmann
Paul J. Griffith
Craig L. Christenson
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.)
Rheinmetall Air Defence AG
Original Assignee
Oerlikon Contraves AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from US07/075,818 external-priority patent/US4815682A/en
Application filed by Oerlikon Contraves AG filed Critical Oerlikon Contraves AG
Publication of EP0300373A2 publication Critical patent/EP0300373A2/fr
Publication of EP0300373A3 publication Critical patent/EP0300373A3/de
Application granted granted Critical
Publication of EP0300373B1 publication Critical patent/EP0300373B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • 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
    • F42B10/04—Stabilising arrangements using fixed fins
    • F42B10/06—Tail fins
    • 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
    • F42B14/061—Sabots for long rod fin stabilised kinetic energy projectiles, i.e. multisegment sabots attached midway on the projectile

Definitions

  • the invention relates to a wing-stabilized lower-caliber projectile with a dropping sabot according to the preamble of claim 1.
  • GB-A-2 027 855 has also disclosed a method for producing a sub-caliber projectile, in which the droppable sabot is poured directly onto the projectile body in a simple manner, the full swirl also being transferred to the projectile here.
  • the floor can be designed as an arrow floor.
  • the wing projectiles are stabilized during flight by aerodynamic forces which act on the projectile.
  • the projectile twist does not contribute to the stabilization of the wing projectiles, a low rotational speed around the longitudinal axis is desirable in order to reduce the adverse effects of the mass and design asymmetries that result from material defects and manufacturing tolerances.
  • Wing-stabilized projectiles are preferably shot down by smooth-tube cannons; thanks to the lack of swirl grooves, no swirl is generated.
  • Such weapons are located for example on front battle tanks and generally have a caliber of 60 millimeters and more.
  • Wing stabilized bullets generally consist of a sub-caliber bullet body and a set of wings of four or more individual wings attached to the rear end of the bullet.
  • the projectile structure is symmetrical to its longitudinal axis and the projectile is shot out of the weapon with the help of a dropping sabot.
  • the detachable sabot has two important tasks, it is to guide the lower-caliber floor along the center line of the weapon barrel during acceleration and it is to form a seal to keep the propellant gases in the barrel during passage. This last task is fulfilled by the swirl band, which engages in the swirl grooves of the weapon barrel and thereby the full one Swirl on the projectile transmits according to the slope of the swirl grooves and the muzzle velocity of the projectile.
  • Wing stabilized bullets contain a sliding fit between the swirl band and the sabot.
  • the sliding seat is designed so that it reduces the swirl speed of the sabot approximately by 70 to 90% of the swirl of the swirl band, which absorbs the full swirl.
  • the size of the swirl transmitted from the sliding seat in the swirl band is determined by the sliding friction.
  • the centrifugal forces acting on the parts of the sabot are very effective in initiating the immediate and symmetrical separation of the sabot from the projectile body when the projectile emerges from the muzzle of the weapon barrel.
  • the centrifugal forces which act on the parts of the sabot are also reduced, namely in the square of the swirl speed.
  • the separation of the sabot is less quick and less precise than with a non-sliding twist band and increasingly dependent on the aerodynamic forces.
  • non-sliding swirl bands allows the construction of stronger sabots. This is advantageous in the case of rapid-fire cannons and the corresponding structural loading and feeding when they are inserted into the weapon barrel.
  • the present invention aims to improve the probability of being hit by wing stabilized sub-caliber projectiles fired from gun barrels with swirl grooves by defining the projectile properties which enable the firing to be carried out at full swirl speed without the use of a swirl band to reduce the swirl. Furthermore, the avoidance of a fragile sliding swirl band enables the ammunition to improve its structural integrity, strength and reliability.
  • the invention relates in particular to wing-stabilized projectile for automatic firearms with a caliber of 12.7 to 40 millimeters.
  • a droppable sabot with rigidly attached swirl band creates a swirl during the acceleration of the projectile in the barrel according to the slope of the swirl grooves and the muzzle velocity of the barrel.
  • the resulting swirl when firing is therefore solely dependent on the muzzle velocity and can therefore be repeated precisely.
  • the swirl movement is transmitted undiminished to the lower-caliber floor.
  • the lower-caliber floor enters the atmosphere and is exposed to the aerodynamic forces.
  • the swirl speed In addition to the aerodynamic forces stabilizing the projectile in flight, they also act on the guide vanes and cause a rapid reduction in the swirl speed of the projectile. After a relatively short flight, the swirl speed reaches the constant value. This constant swirl speed is determined by the bevel angle of the wing and is also proportional to the projectile flight speed. In order to maintain stable flight conditions and to avoid deviations in trajectory, it is necessary that the constant swirl speed of the projectile is always greater than the nutation or natural frequency. This choice of constant swirl speed is intended to prevent the occurrence of resonance instabilities which lead to large angles of attack and even catastrophic fluctuations.
  • the critical swirl speed (nutation frequency) of the projectile is determined by the moment of inertia and the aerodynamic properties and represents a fixed value for a given projectile. Within certain limits, the size of the critical swirl can be influenced by the design of the projectile.
  • the wing-stabilized projectile is provided with a droppable sabot which essentially has three main parts, namely a sabot rear, one Sabot body and a protective hood.
  • the sabot tail is preferably made of light metal, in particular aluminum, which is composed of three or more identical elements and holds the penetrator in the central area in a coaxial position to the weapon barrel.
  • the sabot tail transmits the longitudinal acceleration forces and the swirl which is transmitted from the sabot to the penetrator by the swirl grooves.
  • a sabot body made of plastic is arranged in front of the sabot tail and is provided with an integrated swirl band which engages in the swirl grooves and is provided both as a seal and for transmitting the swirl movement - which is transmitted from the swirl grooves to the penetrator.
  • the sabot body further includes the three or more longitudinal grooves that extend radially from its outer cylindrical surface and leave a web of a given thickness on the inside of the longitudinal grooves. The sabot will break along these longitudinal grooves under the action of centrifugal force as it emerges from the muzzle of the weapon barrel.
  • connection there is a mechanical connection between the sabot body and the sabot rear, which anchors the front part of the sabot rear and the rear part of the sabot body.
  • This connection prevents the separation of the parts under the effect of the propellant gas pressure, which acts on the rear side of the swirl band when fired.
  • the connection transfers the swirl from the sabot body to the sabot rear.
  • the separating surfaces between the parts of the sabot rear are sealed and the connection of the The rear of the sabot tail with the penetrator is provided with an annular seal.
  • the sealing of the rear parts, the annular seal and the sabot body form a single integrated unit, preferably made of a fiber-reinforced plastic. Because of the complicated structure of the sabot body and seals, this unit is preferably produced by injection molding on the previously assembled unit of sabot tail and penetrator.
  • a protective hood is placed on the front end of the sabot body to protect the front end of the penetrator and to adapt the projectile to the automatic feeder.
  • the induced decrease of the projectile swirl to the constant projectile swirl is very quick, very precise and repeatable. This combines with the fact that the initial swirl speed at the muzzle can be controlled just as precisely as the muzzle velocity. In general, the deviation from the standard is not more than one percent and results in an exactly repeatable course of the projectile swirl during the flight.
  • the invention aims to provide a wing-stabilized projectile with a dropping sabot that is fired from a gun barrel provided with swirl grooves with full swirl according to the pitch of the swirl grooves of the gun barrel.
  • the invention also aims to provide a wing-stabilized projectile with a dropping sabot, which is launched with full swirl from a weapon barrel provided with swirl grooves and is then decelerated to a constant swirl speed in a fast, precise and precisely repeatable manner with the aid of an aerodynamic damping which results in a exactly repeatable swirl reduction during the trajectory of the projectile.
  • the invention also aims to provide a wing-stabilized projectile with a dropping sabot that is fired from a weapon barrel provided with swirl grooves, which achieves full swirl when fired and has a constant swirl speed that is greater than the nutation frequency of the projectile.
  • the invention further aims to provide a wing-stabilized projectile with a dropping sabot which is launched with full swirl from a weapon barrel provided with swirl grooves and which has a half-life of no more than 0.1 seconds, this half-life being required to bring the swirl speed to a value lower, which is halfway between the initial value at launch and the constant swirl speed.
  • the invention also aims to provide a wing-stabilized projectile that is robust Sabot, which can be separated immediately and radially-symmetrically after firing under the action of centrifugal forces.
  • the invention also aims to provide a droppable sabot for a wing-stabilized projectile, in which the sabot has three elements, namely a sabot rear, a sabot body made of plastic with an integrated swirl band and seals and a ballistic protective hood.
  • the invention also aims to provide a droppable sabot for a wing-stabilized projectile, in which sabot rear and sabot body have a mechanical connection and the sabot body has an integrated swirl band for sealing the propellant gases and for transmitting the full swirl to the projectile through the swirl grooves of the weapon barrel is produced.
  • the invention further aims to provide a detachable sabot for a wing-stabilized projectile, in which the sabot body has an integrated swirl band for sealing the propellant gases in the swirl grooves and with a seal which extends over the intermediate surfaces of the sabot rear parts and with a seal on the contact surface between Sabot tail and penetrator.
  • the invention also aims to provide a droppable sabot for a wing-stabilized projectile, which has an integrated construction of sabot body, swirl band and seal of the elements of the rear part and seal between the rear and penetrator.
  • the invention also aims to provide a sabot body for a wing-stabilized projectile which is injection-molded directly onto the sabot tail combined with the penetrator.
  • Figure 1 is a longitudinal section through the sub-caliber floor, which is in a throwable Sabot is located.
  • the sub-caliber projectile consists of a penetrator 10 and a wing arrangement 12 at its rear end.
  • a pyrotechnic lighting set 14 is provided which is generally located in the central body of the wing assembly.
  • a heavy metal in particular a tungsten alloy or an enriched uranium alloy, is used for the penetrator 10 in order to achieve a high penetration performance.
  • Either steel or aluminum is used to make the wing assembly.
  • the aluminum wings In the case of high-speed bullets, the aluminum wings must be provided with a protective layer to prevent them from burning off due to the aerodynamic heating.
  • the wing arrangement consists of 4 to 6 wings, which are arranged symmetrically around the central body. 2 shows a wing arrangement with four wings.
  • the wing span 16 must be equal to or smaller than the bore diameter of the weapon barrel.
  • the front edge of the wing is chamfered in an arrow shape, the wing being relatively thin.
  • the floor plan of the wings must be large enough to ensure aerodynamic stability in the longitudinal direction of the sub-caliber projectile with a stability range of not less than 1.5 sub-caliber projectile diameters, the stability range being defined as the distance between the aerodynamic pressure center 24 and the center of gravity 26 of the Projectile body.
  • the wing arrangement is intended to generate an aerodynamic rolling or transverse moment with respect to the longitudinal axis 20 of the projectile by a constant one To ensure swirl speed during the flight, corresponding to the propulsion.
  • the rolling moment is generated aerodynamically, either by the angle of attack of the wings, similar to the stabilizing wings on an aircraft, or by a bevelled leading edge 22 of the wings shown in FIG. 2, or by bevelled trailing edges of the wings. All wings are preferably of identical design.
  • the primary aim of the invention is that the lower-caliber projectile receives the full swirl in accordance with the gradient of the swirl grooves and the muzzle velocity of the weapon barrel.
  • the sub-caliber bullet enters the atmosphere and is immediately subjected to a swirl-reducing aerodynamic swirl damping. The rapid swirl reduction continues until a constant swirl is reached, depending on the design of the wings and the projectile speed.
  • the half-life ie the time required to bring the swirl speed of the projectile to half the value between the initial value at launch and the constant speed, should not be greater than 0.1 seconds.
  • the projectile gains dynamic stability and the half-life is greater than 0.1 seconds and is therefore too short to allow a possible increase in the precession movement due to the Magnus forces.
  • the resonance can be accompanied by rotary movements and yaws.
  • the constant swirl speed must differ from the nutation frequency of the projectile.
  • the present invention aims to have the projectile swirl speed rapidly from its initial launch value to the constant swirl speed decreases, which is greater than the nutation frequency of the projectile by at least a factor of two under all conditions in the operating area of the ammunition. This method, which is also referred to as swirl speed adjustment, is further described in a further example according to FIG. 3.
  • the illustration shows the projectile swirl speed as a function of the projectile flight distance for a wing-stabilized projectile that was shot down by an automatic 25mm cannon with a swirl groove gradient of 7.5%.
  • the corresponding swirl speed is 13'690 rad / sec.
  • the bullet speed decreases rapidly due to the aerodynamic speed damping.
  • the half-life (7505 rad / sec) is reached after 0.058 seconds and at a bullet speed of 1300 m / sec at a distance of 75 meters from the weapon.
  • the projectile has reached its constant swirl speed of approximately 1320 rad / sec.
  • This swirl speed will decrease even further in proportion to the bullet speed.
  • the bullet speed is still approx. 1200 m / sec and the constant twist is approx. 1106 rad / sec.
  • the natural frequency of the projectile is approximately 440 rad / sec.
  • the constant swirl speed is still a factor of 2.5 greater than the nutation frequency and thus the resonance instability is avoided.
  • the information provided is based on shooting tests and shows the effect of swirl tuning, which is an object of the present invention.
  • the invention also aims to provide a droppable sabot for a wing-stabilized Sub-caliber bullet.
  • the droppable sabot consists of three main components, as shown in the longitudinal section of FIG.
  • the rearmost component is a sabot rear part 28, which consists of three or more identical elements 29, which contain the penetrator 10 of the sub-caliber projectile in a coaxial position. These three elements 29 touch each other along radially directed flat surfaces 30.
  • the arrangement of the sabot rear part 28 is also described with reference to FIG. 5, which shows a view of the droppable sabot from behind.
  • the contact surface of the sabot rear part with the central part of the penetrator 10 has various tasks to be performed.
  • this surface causes the penetrator to be in a coaxial position with respect to the gun barrel axis.
  • this contact surface must be strong enough to transmit the longitudinal acceleration forces from the sabot to the projectile when fired.
  • the contact surface is to transmit the swirl without slippage, which acts through the swirl grooves of the weapon barrel from the sabot to the penetrator. The functions just described are best performed with the help of a screw surface 32 or with a number of annular grooves.
  • the plastic sabot body 34 is located in front of the sabot rear part, as can be seen in FIG.
  • the sabot body has an integrated swirl band 36, which engages in the swirl grooves of the weapon barrel when fired, and which serves both for sealing the propellant gases and for transmitting the swirl movement which occurs from the swirl grooves of the weapon barrel to the lower-caliber projectile is transmitted.
  • the sabot body 34 has three or more grooves 38 extending in the longitudinal direction, which also extend in the radial direction from the outer cylinder surface to the penetrator 10 and to the sabot base 28, so that a rib 40 remains, which has a certain thickness on the has inner limit of the groove 38.
  • the first feature relates to the design of the contact surface 42 between the front part of the sabot rear 28 and the rear part of the sabot body 34, according to FIG. 4.
  • This mechanical connection is necessary in order to anchor the sabot body 34 to the sabot tail 28 and thereby prevent separation between the two components under the action of the propellant gas forces acting on the rear end of the swirl band 36 during the launch and to prevent the swirl from the sabot body to transfer to the sabot tail.
  • the design of this connection is designed such that the effect of the gas seal between the sabot body 34 and the sabot rear 28 increases during the gas pressure on the swirl band when fired in the weapon barrel.
  • connection is given by the exterior Contour of the front two thirds of the rear surface in front of the holding groove 43 for the cartridge case, this contour being essentially below the swirl band of the sabot body.
  • the swirl band and the sabot body are compressed and form an effective gas seal along the interface, which prevents propellant gases from passing through this interface.
  • the sabot body transmits the swirl that is generated by the swirl grooves via the sabot tail without slippage to the penetrator 10 at the mechanical connection surface.
  • the second critical feature is the seal 44 which extends rearwardly through the channels 41 located in the contact surfaces of the sabot rear segments.
  • the seal which extends through the channels, projects into an annular seal 46, which is located on the rear side 37 of the sabot rear 28 and surrounds the penetrator 10.
  • the rear side 37 also comprises an annular groove 39 for anchoring the annular seal 46.
  • the seal 44 can also be seen in FIG. 7, which shows a cross section through the sabot rear 28. This seal is important: to prevent propellant gases from entering the sabot assembly during launch either through the contact surfaces 30 of the sabot tail segments or along the perimeter of the penetrator 10.
  • the seal 44 and seal 46 and sabot body form one only integral unit, which is manufactured in a single operation on the previously assembled sabot rear because of its complicated training in the injection molding process.
  • This injection molding process in place on the The sabot tail requires a special shape in which the projectile sabot subassembly is inserted and centered so that a coaxial alignment of all parts is guaranteed.
  • the cross section of the seal 44 and the corresponding channels in the contact surfaces 30 of the sabot segments 28 can be larger than shown in FIG. After all, it is necessary that the sabot body 34, the seal 44 and the seal 46 form a single unit.
  • a carbon or glass fiber reinforced plastic is preferably used, e.g. Nylon or liquid crystal polymer (LCP) suitable for the injection molding process on the spot for the sabot body as a seal and seal.
  • the third essential component of the droppable sabot is the protective hood 48 which is attached to the front end of the sabot body.
  • the outer shape must meet the requirements for the surface of the ammunition for firearms.
  • the hood is necessary to protect the sub-caliber projectile part that protrudes from the front end of the sabot body as long as the ammunition is stored, transported and fed to the weapon.
  • To reduce the weight of the protective hood it is hollow, with a thin wall and preferably made of plastic by injection molding.
  • the protective hood is preferably attached to the sabot body using a snap fit 50.
  • the stability of the projectile ie the distance S between the center of gravity 26 of the penetrator 10 and the air attack point 24 on the penetrator 10 is dependent on the design of the stabilizing wing 12.
  • the half-life of the swirl is also the same on the one hand and the size of the constant swirl depends on the design of the stabilizing wing 12.
  • this distance S between the center of gravity 26 and the air attack point 24 should be at least 1.2 times greater than the sub-caliber diameter of the penetrator 10.
  • the half-life should be 0.10 seconds and the constant swirl should be 50 percent greater than the nutation frequency or natural frequency of the penetrator 10, as can be seen from FIG.
  • the properties of the penetrator 10 are achieved only by an appropriate design of the stabilizing wing 12. Therefore, the construction of the four stabilizing wings 12 will be explained in more detail with reference to FIGS. 8 and 9.
  • the beveled guide edge 22 is inclined by, for example, 30 ° and, according to section A-A, has a second bevel of 10 ° and, according to view B, this bevel is 5 °. It is essential here that the wings 12 are chamfered on one side only, and that seen in the swirl direction of the projectile on the rear or away side. Finally, the wing length a in FIG. 8 is also important for the stability of the penetrator 10.
  • each wings 12 are evenly distributed around the circumference and are relatively thin, that is to say, for example, 0.5-1.0 millimeters.
  • view B the edge 22 is more or less sharp, ie the value b is between 0 and 70% of the thickness of the wing.
  • the following values can also be mentioned for the position of the center of gravity 26 and the air attack point 24:
  • the distance S1 between the tip of the penetrator 10 and the center of gravity 26 is, for example, 86-93 millimeters and the distance S2 between the tip of the penetrator 10 and the air attack point 24 is, for example, 100-120 Millimeter.
  • the stability of the penetrator 10 thus results from the difference S2-S1 and the diameter of the penetrator 10.

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  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
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Claims (9)

  1. Projectile sous-calibré, stabilisé par des ailettes comportant un sabot éjectable pour le départ du coup dans un canon rayé, projectile comportant un dard (10) constitué par une tige allongée dont l'extrémité arrière est munie d'un jeu d'ailettes de stabilisation (12), projectile caractérisé par un sabot pour transmettre toute la rotation en fonction du pas des rainures et de la vitesse à l'embouchure pour le projectile, les ailettes de stabilisation (12) étant fixées en un point déterminé du dard (10) et en ce que la forme aérodynamique des ailettes de stabilisation (12) est telle que le dard (10) offre un minimum de stabilité longitudinale (distance entre le centre de poussée aérodynamique (24) derrière le centre de gravité (26) du projectile sous-calibré) correspondant à 1,2 fois le diamètre du dard, un amortissement du roulis aérodynamique, présentant un demi-temps de rotation qui ne dépasse pas 0,10 seconde et une vitesse de rotation constante qui est au moins supérieure de 50 % à la fréquence de nutation donnée du projectile pendant le vol du projectile.
  2. Projectile sous-calibré, stabilisé par les ailettes selon la revendication 1, caractérisé par un amortissement aérodynamique du roulis qui donne un demi-temps de rotation inférieur au temps nécessaire à modifier la précession du projectile résultant de l'effet Magnus.
  3. Projectile sous-calibré, stabilisé par des ailettes selon la revendication 1, caractérisé en ce que le dard (10) présente un amortissement aérodynamique suffisant pour son mouvement de nutation et son mouvement de précession, donnant une stabilité dynamique croissante lorsque le mouvement de roulis du projectile diminue.
  4. Projectile sous-calibré, stabilisé par des ailettes selon la revendication 1, caractérisé par une vitesse de rotation constante pour éviter que ne se produisent des sauts de résonance ainsi que des mouvements de roulis ou des girations catastrophiques du projectile pendant tout son temps de vol.
  5. Projectile sous-calibré, stabilisé par des ailettes selon l'une des revendications 1 à 4, caractérisé en en ce que les ailettes de stabilisation (12) ont un bord d'attaque (22) incliné vers l'arrière et elles sont également en biais dans la direction de rotation de manière à obtenir la stabilité longitudinale, le demi-tempts de rotation et la vitesse de rotation constante souhaités.
  6. Projectile sous-calibré, stabilisé par des ailettes selon la revendication 5, caractérisé en ce qu'en plus la longueur des ailettes de stabilisation (12) est choisie dans la direction axiale du projectile pour obtenir la stabilité longitudinale, le demi-temps de rotation et une vitesse de rotation constante, choisis.
  7. Projectile sous-calibré, stabilisé par des ailettes selon l'une des revendications 1 à 6, caractérisé par un sabot comportant un arrière (28) métallique, segmenté ayant un certain nombre de surfaces intermédiaires (30) ainsi que des moyens pour recevoir le dard (10) solidairement en rotation au niveau de son centre de gravité (26) et le long de l'axe longitudinal (20), un corps de sabot (34) en matière synthétique, fixé à l'arrière (28), dépasse de celui-ci le long de l'axe (20) du projectile et comporte une ceinture (36) intégrée, de mise en rotation pour communiquer une rotation sans glissement, au dard (10), ainsi que des moyens (44, 46) pour assurer l'étanchéité des surfaces intermédiaires arrière (30) ainsi que celle de la liaison entre le dard (10) et la partie arrière (28).
  8. Projectile sous-calibré, stabilisé par des ailettes selon la revendication 7, caractérisé par un corps de sabot (34) fabriqué par injection, comportant un joint intégré (44, 46) qui s'étend vers l'arrière à travers des fentes (30) disposées dans la direction longitudinale et appartenant à l'arrière (28) du sabot métallique ainsi qu'un moyen d'étanchéité (46) annulaire qui entoure le dard (10) sur le côté arrière de la partie arrière (28), le moyen d'étanchéité (44, 46) évitant que les gaz de propulsion ne pénètrent dans le sabot (28, 34) entre les segments (29) de la partie arrière (28) s'étendant dans la direction longitudinale et la liaison (32) entre le dard (10) et le sabot (28, 34).
  9. Projectile sous-calibré, stabilisé par des ailettes selon la revendication 8, caractérisé en ce que la partie arrière (28) présente une surface de liaison (42) qui s'étend vers l'avant pour pénétrer dans le corps (34) du sabot qui comporte également le dard (10) en position coaxiale.
EP88111368A 1987-07-20 1988-07-15 Projectile sous-calibré stabilisé par ailettes Expired - Lifetime EP0300373B1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US7581987A 1987-07-20 1987-07-20
US07/075,818 US4815682A (en) 1987-07-20 1987-07-20 Fin-stabilized subcaliber projectile and method of spin tuning
US75819 1987-07-20
US75818 1987-07-20

Publications (3)

Publication Number Publication Date
EP0300373A2 EP0300373A2 (fr) 1989-01-25
EP0300373A3 EP0300373A3 (en) 1989-08-23
EP0300373B1 true EP0300373B1 (fr) 1992-06-17

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EP88111368A Expired - Lifetime EP0300373B1 (fr) 1987-07-20 1988-07-15 Projectile sous-calibré stabilisé par ailettes

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EP (1) EP0300373B1 (fr)
JP (1) JPS6467596A (fr)
DE (1) DE3872083D1 (fr)
ES (1) ES2032496T3 (fr)
NO (1) NO883195L (fr)

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WO2017001428A1 (fr) 2015-07-01 2017-01-05 Rwm Schweiz Ag Projectile sous-calibré empenné pouvant être tiré depuis un canon rayé et son procédé de fabrication
WO2021063613A1 (fr) 2019-10-02 2021-04-08 Rheinmetall Waffe Munition Gmbh Pénétrateur, utilisation d'un pénétrateur et projectile

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Publication number Priority date Publication date Assignee Title
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CA2121101C (fr) * 1993-05-27 1998-02-24 Walter Engel Sabot largable pour projectile sous-calibre
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US6324986B1 (en) 1998-11-06 2001-12-04 Oerlikon Contraves Ag Cartridge-case base for a sub-caliber projectile
US6843179B2 (en) 2002-09-20 2005-01-18 Lockheed Martin Corporation Penetrator and method for using same
AU2003275105A1 (en) * 2002-09-20 2004-04-08 Lockheed Martin Corporation A penetrator and method for using same
DE102020120850B4 (de) 2020-08-07 2022-06-15 Rheinmetall Waffe Munition Gmbh Verfahren zur Herstellung eines thermisch stabilen Leitwerks sowie entsprechendes Leitwerk

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Publication number Priority date Publication date Assignee Title
WO2017001428A1 (fr) 2015-07-01 2017-01-05 Rwm Schweiz Ag Projectile sous-calibré empenné pouvant être tiré depuis un canon rayé et son procédé de fabrication
DE102015110627A1 (de) 2015-07-01 2017-01-05 Rwm Schweiz Ag Aus einem gezogenen Waffenrohr verschießbares, flügelstabilisiertes Unterkalibergeschoss und Verfahren zu seiner Herstellung
WO2021063613A1 (fr) 2019-10-02 2021-04-08 Rheinmetall Waffe Munition Gmbh Pénétrateur, utilisation d'un pénétrateur et projectile
US11802755B2 (en) 2019-10-02 2023-10-31 Rheinmetall Waffe Munition Gmbh Penetrator, use of a penetrator, and projectile

Also Published As

Publication number Publication date
EP0300373A3 (en) 1989-08-23
ES2032496T3 (es) 1993-02-16
NO883195D0 (no) 1988-07-19
DE3872083D1 (de) 1992-07-23
NO883195L (no) 1989-01-23
JPS6467596A (en) 1989-03-14
EP0300373A2 (fr) 1989-01-25

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