EP3637039B1 - Projectile porteur de charges pour une arme à canon - Google Patents

Projectile porteur de charges pour une arme à canon Download PDF

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Publication number
EP3637039B1
EP3637039B1 EP19201711.9A EP19201711A EP3637039B1 EP 3637039 B1 EP3637039 B1 EP 3637039B1 EP 19201711 A EP19201711 A EP 19201711A EP 3637039 B1 EP3637039 B1 EP 3637039B1
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EP
European Patent Office
Prior art keywords
projectile
carrier
casing
base
flight
Prior art date
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Active
Application number
EP19201711.9A
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German (de)
English (en)
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EP3637039A1 (fr
Inventor
Benjamin SCHMITZ
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.)
Diehl Defence GmbH and Co KG
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Diehl Defence GmbH and Co KG
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Publication of EP3637039A1 publication Critical patent/EP3637039A1/fr
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Publication of EP3637039B1 publication Critical patent/EP3637039B1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
    • F42B12/62—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected parallel to the longitudinal axis of the projectile

Definitions

  • the invention relates to a carrier projectile for a barrel weapon.
  • Such a carrier projectile is, for example, the widespread "SMArt 155" projectile from GIWS mbH.
  • the missile uses a timed fuse and an ejector charge (usually pyrotechnics) to pyrotechnically eject a payload/submunition from the missile after a defined time.
  • ejector charge usually pyrotechnics
  • Other well-known projectiles are, for example, the "40mm M1001 HVCC" from General Dynamics (Flechet Munition) or classic shotgun ammunition that is fired from smoothbore weapons.
  • the pamphlet U.S. 3,802,345 A describes sabots and in particular a sabot configuration containing a bundle of elongated, sub-caliber, spin-stabilized projectiles.
  • the pamphlet U.S. 2014/251173 A1 describes a projectile for delivering submunitions without the use of energetic materials.
  • the publication describes an inert rotationally symmetrical projectile for firing from an on-board cannon and the distribution of submunitions on a target.
  • the projectile comprises a bottom wad, a sabot casing, a submunitions pack and a retaining ring.
  • the sabot casing includes a plurality of sabot leaves which are angled and attached to the plug.
  • the housing includes a payload portion and a nose portion with a walk-through corridor between these portions.
  • the pamphlet U.S. 2017/356728 A1 which constitutes the closest prior art, describes a system, apparatus and method comprising a projectile; a retroreflector assembly attached to a base of the projectile is; and a cover disposed over the retroreflector assembly and hermetically sealed to the base of the projectile; wherein the cover is positioned over the retroreflector assembly in a first position prior to launch, and wherein the cover is detached from the base of the projectile in a second position after launch.
  • a tubular projectile having a tubular body with forward and rearward ends defining opposite ends of a central opening.
  • the front end and inner surface of the central opening are configured to create preselected flow conditions within the central opening while controlling the aerodynamic drag of the projectile.
  • the object of the invention is to specify an improved carrier projectile for a barrel weapon.
  • the support floor extends along a central longitudinal axis.
  • the carrier floor includes a floor and, in particular, a leader band.
  • the guide band is arranged on the peripheral surface of the projectile base.
  • the peripheral surface or direction relates to the central longitudinal axis. The peripheral surface thus points radially outwards with respect to the central longitudinal axis.
  • the central longitudinal axis represents an axial direction of the carrier projectile.
  • the projectile is also assigned an intended firing or flight direction after firing from the barrel weapon, which is directed in the axial direction.
  • the carrier floor includes a shell that is connected to the floor in an initial state.
  • the initial state is the intended state of the carrier projectile between its manufacture and its launch.
  • the shell is detachable in the axial direction away from the floor. Release occurs only when a release force acting in the axial direction between the base of the bullet and the casing (or two opposing forces: counteracting on the base and in the direction of flight on the casing) exceeds a limit force.
  • the base and casing enclose you space for a payload.
  • the carrier bullet contains a separating device to generate the detaching force. The release force is or is generated by the separating device after leaving the barrel without using an ejection charge and/or without using an igniter.
  • the optional guide band seals the base of the bullet from the barrel.
  • the base of the projectile forms the rear and the casing the front part of the carrier projectile.
  • the carrier projectile works without pyrotechnics and/or without stored chemical energy and/or without a timer.
  • construction splinters, braids or other active elements or active means or effectors can be used as payload.
  • the casing remains connected to the base of the bullet. Only after leaving the barrel are the casing and bullet base separated from one another by applying the release force. In the initial state or in a holding state (which lasts even after firing until the casing and base are separated), the projectile base and casing are fastened or held to one another via a connecting means.
  • the release force is or is produced—in particular exclusively—aerodynamically on the carrier projectile during the flight of the carrier projectile.
  • the release force is therefore generated by the air that surrounds the fired and flying projectile or is flown through by it.
  • no further aids are required to generate the release force. Since the corresponding aerodynamics and thus the release force only occur when the carrier projectile has left the barrel of the barrel weapon, this ensures that the casing and projectile base do not become detached from one another while the weapon is barreling, thereby undesirably releasing the payload.
  • the carrier floor is thus designed to be particularly safe in this regard.
  • the separating device is therefore operated or designed aerodynamically.
  • the dissolving force is or is generated—in particular exclusively—by air pressure.
  • the "air pressure” is pneumatic pressure which is generated by the air flowing against the carrier projectile during flight, i.e. the aerodynamic pressure the flight of the carrier projectile is generated or is.
  • the pressure can be positive (overpressure, thrust) or negative (suction, underpressure) as a relative pressure to a reference pressure on the projectile.
  • the separating device is then a device operated—in particular exclusively—by this pneumatic or air pressure. Pneumatic or air pressure can be used particularly simply, reliably and safely within the carrier projectile.
  • the separator includes an opening in the shell.
  • the opening is exposed to dynamic pressure or air pressure from the air flowing in. Due to the dynamic pressure, an overpressure in the form of air pressure is or will be generated in the receiving space by means of the opening.
  • air flows through the opening into the carrier projectile or into the receiving space.
  • the overpressure is generated in the receiving space.
  • the overpressure acts on the base and casing and causes opposing axial forces on both elements, which tend to detach or push the two elements apart in the axial direction.
  • the limit force is smaller than the release force generated by the overpressure. At least the force generated by the overpressure contributes to the release force.
  • the opening is located at that end of the envelope which points forward in the intended direction of flight, ie at the front end or the tip of the envelope. Inflowing air can be absorbed particularly well there and the above-mentioned dynamic pressure can be generated.
  • the separating device contains a filling element which closes the opening in the initial state.
  • the opening and thus also the receiving space and the carrier floor are protected overall from unwanted foreign matter (dust, dirt, moisture) penetrating through the opening.
  • the filling element In order to release the opening, the filling element must be removed at the latest at the time at which air is desired to flow into the opening. In particular, this is the time when the carrier projectile leaves the barrel of the barrel weapon after firing.
  • the filling element can be realized in any way, e.g. B. starting with a wax, wood, metal or plastic plug, up to a part of the projectile casing, the z. B. can be separated from the rest of the projectile casing via a predetermined breaking point in order to release the opening.
  • the filling element can, in particular, before the firing of the carrier projectile - e.g. B. manually - be removed, for example, during or just before loading the gun.
  • the filling element can also be designed in such a way that it is automatically removed when the carrier projectile is fired.
  • the filling element can therefore be removed from the opening or is removed in this way by a firing shock that occurs when the projectile is fired.
  • Filling element and/or opening are therefore appropriately dimensioned or matched to one another in order to ensure removal during the firing shock.
  • a corresponding holding force of the filling element in the opening or a breaking force of a corresponding connection or of the filling element itself is dimensioned in such a way that the holding force is smaller than the force that acts during a firing shock as intended.
  • the releasing force is generated by the inertia of the filling element. In this way, automatic removal of the filling element can be implemented in a particularly simple manner.
  • the separating device contains a surface arranged on the floor of the floor.
  • the surface is exposed to an aerodynamically generated suction force caused by air flowing past.
  • the suction force is directed away from the envelope in the opposite direction to flight. Since the envelope itself strives to fly further in the direction of flight, the suction force causes at least part of the release force.
  • the suction force adds up to the total release force together with the above-mentioned force generated by the overpressure in the receiving space. In this way, the dissolving force can be generated particularly effectively and easily.
  • the surface is the bottom surface of the projectile base which is directed backwards with respect to the direction of flight.
  • the base and the casing are held together in the initial state by a frictional and/or positive connection or a corresponding connecting means.
  • the connection can be released when or by applying the release force (greater than or equal to the limit force). As soon as the limit force is applied, the corresponding connection is released or is then released as a result.
  • an adhesive and/or holding force of the connection caused by the connection is dimensioned to be less than or equal to the limit force.
  • the connection is dimensioned accordingly with regard to the forces.
  • the corresponding connection is therefore at least part of the connection means mentioned above.
  • the connecting means is or contains a Compressible sealing element which requires at least the limit force to be applied in order to compress and overcome a friction/form fit.
  • Alternative fasteners or parts thereof are, for example, adhesive or press connections, predetermined breaking points, tear-off seams, etc.
  • the carrier projectile is a carrier projectile for a barrel weapon with a rifled barrel.
  • the optional guide band is then used to transfer spin from the barrel to the carrier bullet.
  • the carrier projectile is suitable for the majority of available barrel weapons.
  • the general advantages of rifling also apply to the carrier projectile in question.
  • the carrier projectile has a spin transfer element.
  • the spin transmission element is arranged in the receiving space and fastened to the projectile base and/or to the casing and at least partially penetrates the receiving space for the payload for the purpose of transmitting spin. The enforcement goes so far that a designated payload is subjected to the twist in the desired manner.
  • Spin which is transferred from the barrel of the barrel weapon to the carrier projectile, is also transferred to the payload by means of the spin transfer element.
  • the spin transmission element is in particular a driver element that is connected to the projectile base and/or the casing in a rotationally fixed manner with respect to the central longitudinal axis. Grids, brackets, pins, etc. are conceivable as carrier elements.
  • the twist transmission element contains or is at least one wall that extends at least partially through the receiving space.
  • the recording space is divided into two sub-spaces, at least at the relevant point per wall. Each subspace can then accommodate at least part of the payload.
  • the twist transmission then takes place through attachment to the wall.
  • the spin transmission element contains two walls which are arranged in a cross-shape in cross section and which intersect at the central longitudinal axis of the carrier projectile.
  • the wall is designed in particular with or without recesses.
  • the wall is attached to the floor. In this way, simple possibilities for the transfer of spin to the payload are created in each case.
  • the carrier projectile contains a spin decoupling element for accommodating at least part of the payload.
  • the spin decoupling element is decoupled from the base of the projectile and the casing with respect to a rotation about the central longitudinal axis.
  • the rest of the carrier projectile can therefore execute a twisting motion without the twist decoupling element (and the payload accommodated therein) following it. It is thus possible to orient the payload or its relevant part on the spin decoupling element and thus to spin decouple it from the rotating part of the carrier projectile, in particular from the projectile base and the casing. These elements then have no twist.
  • the benefits of a spinning launcher are retained without necessarily subjecting the payload to spin.
  • the twist decoupling element contains or is a receiving body for at least part, in particular the entire payload.
  • the receiving body is rotatably mounted in the base of the projectile and in the shell about the central longitudinal axis. Since the receiving body itself is twist-decoupled, the entire payload held in this is twist-decoupled.
  • the receiving body is in particular a trough, cup or pot, the opening of which points in particular in the direction of flight and which is in particular designed axially symmetrically to the central longitudinal axis. With regard to the acceleration of the carrier projectile, the payload is thus in contact with a base of the receiving body pointing counter to the direction of flight.
  • the twist decoupling can thus be accomplished in a particularly simple manner.
  • the invention is based on the following findings, observations and considerations and also has the following embodiments.
  • the embodiments are sometimes also referred to as “the invention” for the sake of simplicity.
  • the embodiments can also contain parts or combinations of the above-mentioned embodiments or correspond to them and/or optionally also include embodiments that have not been mentioned before.
  • the invention is based on the basic idea of designing a carrier system for barrel weapons (with a rifled barrel/twist) in order to deliver a payload (construction fragments, braids, other active elements) from a rifled barrel. At the same time, disassembly during the barrel should be ruled out.
  • the invention is based on the basic idea, through the suction on the floor of the bullet (which arises aerodynamically during flight) and an air inlet, which (also aerodynamically during flight) generates an overpressure in the bullet interior (receiving space), the bullet (in the axial direction) to pull apart and open (to separate the casing from the base).
  • the carrier projectile according to the invention does not require an expensive time fuse with pyrotechnics and can also be used in particular in small calibers (medium caliber, .50/12.7 mm or larger). Furthermore, no chemical energy is stored in the projectile itself, which completely avoids the risk of explosives. The question of IM properties (insensitive ammunition) does not even arise. A premature opening and disassembly in the barrel is technically impossible. This is due to the fact that the projectile can only be opened by dynamic processes during flight; in the barrel, on the other hand, pressure is exerted on a solid floor (floor). It is technically impossible for projectile parts to remain in the barrel.
  • the invention it is possible to eject active agents (e.g. splinters or fletchlets) from a rifled barrel without opening the carrier projectile and releasing the active agents in the barrel.
  • active agents e.g. splinters or fletchlets
  • the invention allows implementation without having to resort to an (expensive) detonator or other arming devices.
  • the invention also allows a reaction without having to store chemical energy. This results in an advantage in IM issues, chemical compatibility, storage stability and storage group classification.
  • the payload is released immediately after the run (0-5 m, in particular 0.5-3 m, in particular 1-2 m).
  • the carrier system carrier projectile
  • the carrier bullet is accelerated like a classic bullet in one barrel.
  • the twist is transmitted through the guide band.
  • the sealed air inlet opening with filling element
  • the acceleration force at the rear is eliminated and is replaced by a suction (caused by the air flowing past).
  • the air flowing in through the opening/air inlet
  • the bullet to open (separation of bullet base and casing). Due to the accelerating force in the barrel, fragmentation of the bullet in the barrel is impossible.
  • spin transfer element spin transfer element
  • twist transfer element can be replaced.
  • a rotatable trough (receiving body) is used in the floor of the floor, in which the payload is located, decoupled from twisting.
  • FIG 1 shows a carrier projectile 2 according to the invention for an in Figure 2a indicated barrel weapon 20.
  • the carrier projectile 2 extends along a central longitudinal axis 4, which describes an axial direction of the carrier projectile 2.
  • the carrier projectile 2 also has an intended flight direction 6 (indicated by an arrow), which is directed in the direction of the central longitudinal axis 4 .
  • the carrier projectile 2 contains a projectile base 8 .
  • a guide band 12 is arranged on the projectile base 8 on a peripheral surface 10 pointing radially outwards (with respect to the central longitudinal axis 4 or axial direction).
  • the carrier floor 2 also includes a shell 14 in the form of an upper floor shell, which is in the figure 1 shown initial state A is connected to the floor 8.
  • the base 8 and casing 14 can be detached from one another in the axial direction by moving the casing 14 away from one another in the direction of flight 6 and/or the base 8 counter to the direction of flight 6 (consideration of the relative movements).
  • This requires the application of a detaching force L, which is only indicated in the figures, between the floor 8 and the casing 14 (acts on both elements in opposite directions) for the movement described above.
  • the release force L must be greater than a limit force G up to which the base 8 and casing 14 hold one another.
  • the floor 8 and the casing 14 are connected by an in Figure 1b only symbolically indicated frictional / form-fitting connection 36 held together, which is greater than or equal to the limit force G dissolves when a release force L is applied.
  • the corresponding friction-locking/positive-locking elements therefore form a connecting means 37 in order to hold the casing 14 and the floor 8 together until the limit force G acts on them.
  • Projectile base 8 and shell 14 surround a receiving space 16 inside the carrier projectile 2.
  • the carrier projectile 2 conveys a payload 17, here only symbolically indicated, here construction fragments.
  • the carrier projectile 2 contains a separating device 18.
  • the separator 18 When the carrier projectile 2 is used as intended, ie after it has been fired and during its flight, namely after leaving an in Figure 2a illustrated barrel 22 of the barrel weapon 20, the separator 18 generates the release force L, which eventually becomes greater than or equal to the limit force G. In this case, generation occurs without using an ejection charge and without using an igniter (neither of which are therefore shown, of course).
  • the separator 18 includes an opening 24 in the shell 14.
  • the shell 14 is thus pierced by the opening 24 which forms an air inlet opening as will be explained later.
  • the opening 24 is located at that end 26 of the carrier projectile 2 or of the casing 14 which is at the front with respect to the direction of flight 6 .
  • the opening 24 is located at the tip 28 of the carrier projectile 2 or the casing 14.
  • the opening 24 is closed by a filling element 30 .
  • the filling element 30 is removable from the opening 24 in order to free it, as will be explained later.
  • the opening 24 is therefore a sealed air inlet opening.
  • the separating device 18 further includes a surface 32 which is arranged on the floor 8 .
  • the surface 32 is formed by the end 34 of the carrier projectile 2 or the projectile base 8 , which is opposite the end 26 or the tip 28 with respect to the direction of flight 6 .
  • the guide band 12 serves to seal the carrier projectile 2 or the projectile base 8 from the barrel 22 or its inside.
  • the barrel 22 is a rifled barrel 22.
  • the guide band 12 is therefore also used to transmit spin from the barrel 22 to the base 8 and thus the entire carrier projectile 2.
  • the carrier projectile 2 When it is used, the carrier projectile 2 is introduced into the barrel weapon 20 or its barrel 22 and fired in a conventional manner.
  • Figure 2a 12 shows the carrier projectile 2 during its journey through the barrel 22 after firing.
  • the carrier projectile 2 is accelerated by a drive (propellant charge) not shown in detail.
  • the drive or the acceleration force is symbolized by an arrow 38 .
  • the corresponding force acts on the floor 8 or the surface 32 or the end 34 and acts in the direction of the flight direction 6.
  • the launch shock causes the sealed air inlet opening (opening 24, closed by filling element 30) opens inwards: the filling element 30 is thus released from the opening 24 by means of its inertia and transported in the direction of arrow 40 into the receiving space 16. If the carrier projectile 2 leaves the muzzle opening (not shown) of the barrel 22, the drive or the acceleration of the carrier projectile 2 ends.
  • Figure 2b shows the subsequent flight phase of the carrier projectile 2 in the air 40.
  • the acceleration (arrow 38 in Figure 2a ) no longer on floor 8.
  • air 40 which is traversed by the carrier floor 2 , creates a suction which causes a force against the direction of flight 6 at the floor 8 .
  • the corresponding force is indicated by an arrow 42.
  • the corresponding suction therefore acts against the direction of flight 6.
  • the envelope 14, on the other hand, strives to move further in the direction of flight 6 less or unbraked.
  • the corresponding suction and the mass inertia of the casing 14 already produce part of the detaching force L, which tends to separate the casing 14 and the base 8 of the projectile in or counter to the direction of flight 6 .
  • air 40 flows through the opening 24 or air inlet opening (indicated by the arrow 44) into the receiving space 16 or interior of the carrier projectile 2.
  • a corresponding dynamic pressure builds up in the receiving space 16 , which exceeds the ambient pressure.
  • This dynamic pressure or overpressure also causes part of the release force L.
  • the release force L is made up of exactly the two components mentioned (suction and dynamic pressure).
  • FIG. 2c shows the corresponding conditions:
  • the total detaching force L symbolized here by a double arrow, is greater than the limit force G and therefore leads to casing 14 and projectile base 8 detaching from one another in or counter to the direction of flight 6 .
  • the receiving space 16 or the carrier projectile 2 is thereby opened and the payload 17 located therein is released.
  • the resulting force (release force L) from the suction (arrow 42) and internal pressure (arrow 44) is greater than the force that the connecting means 37 in the form of the connection 36 can hold.
  • Payload 17, which is still in the shell 14 after the separation of shell 14 and floor 8, is thereby also by the air flowing through the opening 24 from the Case 14 pressed.
  • the floor 8 falls off the payload 17 anyway due to the suction on the surface 32 .
  • figure 3 shows part of an alternative carrier floor 2.
  • This contains the floor 8 from figure 1 , the in Fig. 3 a) in sectional side view according to Figure 1b and in Figure 3b ) is shown in plan view against the direction of flight 6.
  • a spin transmission element 50 (in the form of a carrier element) of the carrier projectile 2 is fastened in the projectile base 8 or firmly connected to the projectile base 8 .
  • the purpose of the spin transmission element 50 is to transmit a spin, which the base 8 has, to the payload 17 .
  • the twist transmission element 50 extends over a part of the receiving space 16 and therefore interacts with the payload 17 located therein by positive locking, as shown in FIG Figure 3b ) is indicated.
  • the twist transmission element 50 here consists of two walls 52, which each extend along the central longitudinal axis 4 and are rotated by 90° relative to one another, so that they form a cross-section in cross-section.
  • FIG figure 4 shows an alternative embodiment of the carrier floor 2. This also contains the floor 8 according to FIG figure 1 . However, a twist decoupling element 54 is arranged in the floor 8 . With regard to the central longitudinal axis 4 or the axial direction, the floor 8 and the spin decoupling element 54 can be rotated in relation to one another and are therefore decoupled from one another with regard to this rotation.
  • the twist decoupling element 54 serves to accommodate the payload 17, which is indicated here in the form of braids.
  • the spin decoupling element 54 thus forms a receiving body 56 , here in the form of a pot-shaped, circular cup that is open in the direction of flight 6 .
  • the spin decoupling element 54 is thus rotatable with respect to the entire carrier projectile 2 both in the projectile base 8 and in the shell 14 about the central longitudinal axis 4 or axial direction.
  • the spin decoupling element 54 together with the payload 17, retains its rotational rest position about the central longitudinal axis 4 due to the rotational mass inertia.
  • bucket and payload 17 “slip” relative to floor 8 and casing 14 about central longitudinal axis 4 or axial direction “through”.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Claims (9)

  1. Projectile porteur (2) pour une arme à tube (20) avec un canon (22) qui s'étend le long d'un axe longitudinal central (4),
    - avec un fond de projectile (8),
    - avec une enveloppe (14) qui, dans un état initial (A), est reliée au fond de projectile (8), et qui peut être détachée en s'éloignant du fond de projectile (8) dans une direction axiale, lorsqu'une force de détachement (L), qui dépasse une force limite (G), agit entre le fond de projectile (8) et l'enveloppe (14) dans la direction axiale,
    - le fond de projectile (8) et l'enveloppe (14) entourant un espace de réception (16) pour une charge utile (17),
    - et avec un dispositif de séparation (18), la force de détachement (L) étant produite par le dispositif de séparation (18) après avoir quitté le canon (22) sans utilisation d'une charge d'éjection et/ou sans utilisation d'un détonateur,
    la force de détachement (L) étant produite de manière aérodynamique sur le projectile porteur (2) pendant le vol du projectile porteur (2),
    - la force de détachement (L) étant produite par la pression d'air produite par le vol,
    - le dispositif de séparation (18) contenant une ouverture (24) dans l'enveloppe (14) qui est exposée à une pression dynamique d'air entrant pendant le vol, la pression dynamique produisant une surpression sous forme de pression d'air dans l'espace de réception (16),
    - le dispositif de séparation (18) contenant un élément de remplissage (30) qui ferme l'ouverture (24) dans l'état initial (A),
    - l'élément de remplissage (30) pouvant être retiré de l'ouverture (24) par un choc de tir qui se produit lors du tir du projectile (2).
  2. Projectile porteur (2) selon la revendication 1, caractérisé en ce que l'ouverture (24) se trouve à l'extrémité avant (26) de l'enveloppe (14), orientée dans la direction de vol (6).
  3. Projectile porteur (2) selon l'une quelconque des revendications précédentes, caractérisé en ce que le dispositif de séparation (18) contient une surface (32) agencée sur le fond de projectile (8), qui est exposée pendant le vol à une force d'aspiration due à l'air passant, la force d'aspiration étant dirigée à l'encontre de la direction de vol (6) en s'éloignant de l'enveloppe (14) .
  4. Projectile porteur (2) selon l'une quelconque des revendications précédentes, caractérisé en ce que le fond de projectile (8) et l'enveloppe (14) sont maintenus l'un contre l'autre dans l'état initial (A) par une liaison par friction et/ou par complémentarité de forme (36), qui peut être supprimée lors de l'application de la force limite (G).
  5. Projectile porteur (2) selon l'une quelconque des revendications précédentes, caractérisé en ce que le projectile porteur (2) est un projectile porteur (2) pour une arme à tube (20) avec un canon rayé (22).
  6. Projectile porteur (2) selon la revendication 5, caractérisé en ce que le projectile porteur (2) présente dans l'espace de réception (16) un élément de transmission de rotation (50) qui est fixé au fond de projectile (8) et/ou à l'enveloppe (14) et qui traverse au moins partiellement l'espace de réception (16) pour la transmission de rotation.
  7. Projectile porteur (2) selon la revendication 6, caractérisé en ce que l'élément de transmission de rotation (50) contient ou est au moins une paroi (52) qui s'étend au moins partiellement à travers l'espace de réception (16).
  8. Projectile porteur (2) selon l'une quelconque des revendications 5 à 7, caractérisé en ce que le projectile porteur (2) contient un élément de découplage de rotation (54) pour recevoir au moins une partie de la charge utile (17), l'élément de découplage de rotation (54) étant découplé du fond de projectile (8) et de l'enveloppe (14) par rapport à une rotation autour de l'axe longitudinal central (4).
  9. Projectile porteur (2) selon la revendication 8, caractérisé en ce que l'élément de découplage de rotation (54) contient un corps de réception (56) pour au moins une partie de la charge utile (17), qui peut tourner dans le fond de projectile (8) et dans l'enveloppe (14) autour de l'axe longitudinal central (4).
EP19201711.9A 2018-10-12 2019-10-07 Projectile porteur de charges pour une arme à canon Active EP3637039B1 (fr)

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DE102018008079.0A DE102018008079A1 (de) 2018-10-12 2018-10-12 Trägergeschoss für eine Rohrwaffe

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Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA1013197A (en) * 1973-11-16 1977-07-05 Her Majesty The Queen In Right Of Canada As Represented By The Minister Of National Defence Of Her Majesty's Canadian Government Tubular projectile

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US3024729A (en) * 1948-04-24 1962-03-13 Cornell Aeronautical Labor Inc Ram jet projectile
US3802345A (en) * 1962-05-02 1974-04-09 Aai Corp Multiple projectile sabot assembly for use in rifled barrel
US6763765B2 (en) * 2001-09-27 2004-07-20 Harold Crowson Break-away gas check for muzzle-loading firearms
US8931416B2 (en) * 2013-03-07 2015-01-13 The United States Of America As Represented By The Secretary Of The Navy Inert and pressure-actuated submunitions dispensing projectile
US9329008B1 (en) * 2013-08-08 2016-05-03 The United States Of America As Represented By The Secretary Of The Army Low collateral damage kinetic energy projectile
US9874426B2 (en) * 2016-06-09 2018-01-23 Teledyne Scientific & Imaging, Llc Retroreflector array and cover for optical bullet tracking

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA1013197A (en) * 1973-11-16 1977-07-05 Her Majesty The Queen In Right Of Canada As Represented By The Minister Of National Defence Of Her Majesty's Canadian Government Tubular projectile

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EP3637039A1 (fr) 2020-04-15

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