EP3637039B1 - Carrier projectile for a gun - Google Patents

Carrier projectile for a gun 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
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.)
Active
Application number
EP19201711.9A
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German (de)
French (fr)
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EP3637039A1 (en
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 date
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Publication of EP3637039A1 publication Critical patent/EP3637039A1/en
Application granted granted Critical
Publication of EP3637039B1 publication Critical patent/EP3637039B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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)

Description

Die Erfindung betrifft ein Trägergeschoss für eine Rohrwaffe.The invention relates to a carrier projectile for a barrel weapon.

Ein derartiges Trägergeschoss ist zum Beispiel das weit verbreitete Geschoss "SMArt 155" der Fa. GIWS mbH. Das Geschoss verwendet einen Zeitzünder und eine Ausstoßladung (in der Regel Pyrotechnik), um eine Nutzlast/Submunition aus dem Geschoss nach einem definierten Zeitpunkt pyrotechnisch auszustoßen. Weitere bekannte Geschosse sind zum Beispiel das "40mm M1001 HVCC" der Fa. General Dynamics (Flechet Munition) oder klassische Schrotmunition, die aus Glattrohrwaffen verschossen wird.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. 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.

Die Druckschrift US 3 802 345 A beschreibt Treibkäfige und insbesondere eine Treibkäfigkonfiguration, die ein Bündel länglicher, unterkalibriger, drallstabilisierter Geschosse enthält.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.

Die Druckschrift US 2014/251173 A1 beschreibt ein Geschoss zur Abgabe von Submunition ohne Einsatz von energetischen Materialien. Die Druckschrift beschreibt ein inertes rotationssymmetrisches Geschoss für den Abschuss aus einer Bordkanone und die Verteilung von Submunitionen auf ein Ziel. Das Geschoss umfasst einen Bodenpfropfen, ein Treibspiegelgehäuse, ein Submunitionspaket und einen Haltering. Das Treibkäfiggehäuse umfasst eine Vielzahl von Treibkäfigblättern, die im Winkel angeordnet und am Stopfen befestigt sind. Das Gehäuse umfasst einen Nutzlastteil und einen Nasenteil mit einem Durchgangskorridor zwischen diesen Teilen.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.

Die Druckschrift US 2017/356728 A1 , die den nächstkommenden Stand der Technik bildet, beschreibt ein System, eine Vorrichtung und Verfahren, umfassend ein Geschoss; eine Retroreflektoranordnung, die an einer Basis des Geschosses befestigt ist; und eine Abdeckung, die über der Retroreflektoranordnung angeordnet und an der Basis des Geschosses hermetisch abgedichtet ist; wobei die Abdeckung über der Retroreflektoranordnung in einer ersten Position vor dem Abfeuern angeordnet ist, und wobei die Abdeckung von der Basis des Geschosses in einer zweiten Position nach dem Abfeuern gelöst wird.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.

Aus dem Patent CA 1013197 ist ein Röhrenprojektil mit einem Röhrenkörper mit einem vorderen und einem hinteren Ende bekannt, die gegenüberliegende Enden einer zentralen Öffnung definieren. Das vordere Ende und die innere Oberfläche der zentralen Öffnung sind eingerichtet und vorgewählte Strömungsbedingungen innerhalb der zentralen Öffnung zu schaffen und dabei den aerodynamischen Widerstand des Projektils zu steuern.From the patent CA1013197 discloses 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.

Aufgabe der Erfindung ist es, ein verbessertes Trägergeschoss für eine Rohrwaffe anzugeben.The object of the invention is to specify an improved carrier projectile for a barrel weapon.

Die Aufgabe wird gelöst durch ein Trägergeschoss gemäß Patentanspruch 1 für eine Rohrwaffe mit einem Lauf. Bevorzugte oder vorteilhafte Ausführungsformen der Erfindung sowie anderer Erfindungskategorien ergeben sich aus den weiteren Ansprüchen, der nachfolgenden Beschreibung sowie den beigefügten Figuren.The object is achieved by a carrier projectile according to patent claim 1 for a barrel weapon with a barrel. Preferred or advantageous embodiments of the invention and other categories of the invention result from the further claims, the following description and the attached figures.

Das Trägergeschoss erstreckt sich entlang einer bzw. seiner Mittellängsachse. Das Trägergeschoss enthält einen Geschossboden und insbesondere ein Führungsband. Das Führungsband ist in der Regel an der Umfangsfläche des Geschossbodens angeordnet. Die Umfangsfläche bzw. -richtung bezieht sich auf die Mittellängsachse. Die Umfangsfläche weist also radial auswärts bezüglich der Mittellängsachse. Die Mittellängsachse stellt eine Axialrichtung des Trägergeschosses dar. Dem Geschoss ist außerdem eine bestimmungsgemäße Abschuss- bzw. Flugrichtung nach dem Abfeuern aus der Rohrwaffe zugeordnet, die in Axialrichtung gerichtet ist.The support floor extends along a central longitudinal axis. The carrier floor includes a floor and, in particular, a leader band. As a rule, 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.

Das Trägergeschoss enthält eine Hülle, die in einem Ausgangszustand mit dem Geschossboden verbunden ist. Der Ausgangszustand ist der bestimmungsgemäße Zustand des Trägergeschosses zwischen dessen Fertigung und dessen Abschuss. Die Hülle ist in Axialrichtung vom Geschossboden weg lösbar. Das Lösen erfolgt nur, wenn in Axialrichtung eine Lösekraft zwischen Geschossboden und Hülle (bzw. zwei gegensätzliche Kräfte: am Boden entgegen und an der Hülle in Flugrichtung) wirkt, die eine Grenzkraft übersteigt. Der Geschossboden und die Hülle umschließen einen Aufnahmeraum für eine Nutzlast. Das Trägergeschoss enthält eine Trennvorrichtung zur Erzeugung der Lösekraft. Die Lösekraft ist bzw. wird von der Trennvorrichtung nach Verlassen des Laufes ohne Verwendung einer Ausstoßladung und/oder ohne Verwendung eines Zünders erzeugt.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.

Das optionale Führungsband bewirkt beim Einsetzen bzw. Verwenden des Trägergeschosses in einer bestimmungsgemäßen Rohrwaffe eine Abdichtung des Geschossbodens zum Lauf hin. Bezüglich der bestimmungsgemäßen Abschuss- bzw. Flugrichtung bildet der Geschossboden den hinteren, die Hülle den vorderen Teil des Trägergeschosses. Mit anderen Worten arbeitet das Trägergeschoss also ohne Pyrotechnik und/oder ohne gespeicherte chemische Energie und/oder ohne Zeitzünder. Als Nutzlast kommen beispielsweise Konstruktionssplitter, Flechets oder andere Wirkelemente bzw. Wirkmittel bzw. Effektoren in Frage.When inserting or using the carrier bullet in a gun that is intended for use, the optional guide band seals the base of the bullet from the barrel. With regard to the intended firing or flight direction, the base of the projectile forms the rear and the casing the front part of the carrier projectile. In other words, the carrier projectile works without pyrotechnics and/or without stored chemical energy and/or without a timer. For example, construction splinters, braids or other active elements or active means or effectors can be used as payload.

Solange sich das Trägergeschoss nach dem Abschuss noch im Lauf der Rohrwaffe befindet, bleibt die Hülle mit dem Geschossboden verbunden. Erst nach dem Verlassen des Laufes werden Hülle und Geschossboden durch Aufbringung der Lösekraft voneinander getrennt. Geschossboden und Hülle sind also im Ausgangszustand bzw. in einem Haltezustand (der auch noch nach dem Abschuss bis zum Trennen von Hülle und Boden andauert) über ein Verbindungsmittel aneinander befestigt bzw. gehalten.As long as the carrier bullet is still in the barrel of the barrel weapon after firing, 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.

Der Erfindung entsprechend ist bzw. wird die Lösekraft - insbesondere ausschließlich - aerodynamisch am Trägergeschoss während des Fluges des Trägergeschosses erzeugt. Die Erzeugung der Lösekraft erfolgt also durch die Luft, die das abgefeuerte und fliegende Geschoss umgibt bzw. von diesem durchflogen wird. Für die Erzeugung der Lösekraft sind somit diesbezüglich keine weiteren Hilfsmittel (Zünder, Ausstoßladung, ...) erforderlich. Da eine entsprechende Aerodynamik und somit die Lösekraft erst auftritt, wenn das Trägergeschoss den Lauf der Rohrwaffe verlassen hat, ist hierdurch sichergestellt, dass sich Hülle und Geschossboden nicht bereits im Lauf der Waffe voneinander lösen und somit ein unerwünschtes Freisetzen der Nutzlast erfolgt. Das Trägergeschoss ist damit diesbezüglich besonders sicher ausgeführt. Die Trennvorrichtung ist also aerodynamisch betrieben bzw. ausgeführt.According to the invention, 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. In this regard, no further aids (igniters, ejector charges, etc.) 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.

Erfindungsgemäß ist bzw. wird die Lösekraft - insbesondere ausschließlich - durch Luftdruck erzeugt. Der "Luftdruck" ist dabei pneumatischer Druck, der durch die im Flug am Trägergeschoss anströmende Luft erzeugt ist, der also aerodynamisch durch den Flug des Trägergeschosses erzeugt wird bzw. ist. Der Druck kann hierbei als Relativdruck zu einem Referenzdruck an Geschoss positiv (Überdruck, Schub) oder negativ (Sog, Unterdruck) sein. Die Trennvorrichtung ist dann eine - insbesondere ausschließlich - durch diesen pneumatischen bzw. Luftdruck betriebene Vorrichtung. Pneumatischer bzw. Luftdruck kann besonders einfach, zuverlässig und sicher innerhalb des Trägergeschosses verwendet werden.According to the invention, 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.

Erfindungsgemäß enthält die Trennvorrichtung eine Öffnung in der Hülle. Während des Fluges ist die Öffnung einem Staudruck bzw. Luftdruck anströmender Luft ausgesetzt. Durch den Staudruck ist bzw. wird vermittels der Öffnung ein Überdruck in Form von Luftdruck im Aufnahmeraum erzeugt. Durch die Öffnung strömt beim bestimmungsgemäßen Flug des Trägergeschosses also Luft in das Trägergeschoss bzw. in den Aufnahmeraum ein. Hierdurch wird der Überdruck im Aufnahmeraum erzeugt. Der Überdruck wirkt auf Geschossboden und Hülle und bewirkt gegeneinander gerichtete Axialkräfte an beiden Elementen, die bestrebt sind, die beiden Elemente in Axialrichtung voneinander zu lösen bzw. auseinander zu drücken. Insbesondere ist in diesem Fall die Grenzkraft kleiner als die durch den Überdruck erzeugte Lösekraft. Zumindest trägt die durch den Überdruck erzeugte Kraft zur Lösekraft bei.According to the invention, the separator includes an opening in the shell. During flight, 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. During normal flight of the carrier projectile, air flows through the opening into the carrier projectile or into the receiving space. As a result, 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. In particular, in this case 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.

In einer bevorzugten Variante dieser Ausführungsform befindet sich die Öffnung an demjenigen Ende der Hülle, das in der bestimmungsgemäßen Flugrichtung nach vorne weist, also am vorderen Ende bzw. der Spitze der Hülle. Dort kann einströmende Luft besonders gut aufgenommen werden bzw. der oben genannte Staudruck erzeugt werden.In a preferred variant of this embodiment, 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.

Gemäß der Erfindung enthält die Trennvorrichtung ein die Öffnung im Ausgangszustand verschließendes Füllelement. Somit ist im Ausgangszustand die Öffnung und damit auch der Aufnahmeraum und das Trägergeschoss insgesamt davor geschützt, dass unerwünschte Fremdstoffe (Staub, Schmutz, Feuchtigkeit) durch die Öffnung eindringen. Um die Öffnung freizugeben ist das Füllelement spätestens zu dem Zeitpunkt zu entfernen, an dem ein Einströmen von Luft in die Öffnung gewünscht ist. Dies ist insbesondere der Zeitpunkt, wenn das Trägergeschoss nach dem Abfeuern den Lauf der Rohrwaffe verlässt. Das Füllelement kann in beliebiger Weise realisiert sein, z. B. beginnend bei einem Wachs-, Holz-, Metall- oder Kunststoffpfropfen, bis hin zu einem Teil der Geschosshülle, der z. B. über eine Sollbruchstelle von der restlichen Geschosshülle trennbar ist, um die Öffnung freizugeben.According to the invention, the separating device contains a filling element which closes the opening in the initial state. Thus, 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. 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.

Das Füllelement kann insbesondere vor dem Abfeuern des Trägergeschosses - z. B. händisch - entfernt werden, zum Beispiel während oder kurz vor dem Laden der Rohrwaffe. Alternativ kann das Füllelement aber auch derart ausgeführt sein, dass es beim Abschuss des Trägergeschosses automatisch entfernt wird.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. Alternatively, the filling element can also be designed in such a way that it is automatically removed when the carrier projectile is fired.

Gemäß der Erfindung ist das Füllelement daher durch einen beim Abfeuern des Geschosses auftretenden Abschussschock aus der Öffnung entfernbar bzw. wird derart entfernt. Füllelement und/oder Öffnung sind daher entsprechend dimensioniert bzw. aufeinander abgestimmt, um das Entfernen beim Abschussschock sicherzustellen. Zum Beispiel ist eine entsprechende Haltekraft des Füllelements in der Öffnung oder eine Bruchkraft einer entsprechenden Verbindung oder des Füllelement selbst derart dimensioniert, dass die Haltekraft kleiner derjenigen Kraft ist, die bei einem bestimmungsgemäßen Abschussschock wirkt. Die lösende Kraft ist durch die Massenträgheit des Füllelements erzeugt. So kann eine automatische Entfernung des Füllelements besonders einfach realisiert werden.According to the invention, 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. For example, 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.

In einer bevorzugten Variante der oben genannten Ausführungsform enthält die Trennvorrichtung eine am Geschossboden angeordnete Fläche. Die Fläche ist während des Fluges des Trägergeschosses einer aerodynamisch erzeugten Sogkraft durch vorbeiströmende Luft ausgesetzt. Die Sogkraft ist entgegen der Flugrichtung von der Hülle weg gerichtet. Da die Hülle an sich bestrebt ist, in Flugrichtung weiter zu fliegen, bewirkt die Sogkraft zumindest einen Teil der Lösekraft. Insbesondere addiert sich die Sogkraft zusammen mit der oben genannten durch den Überdruck im Aufnahmeraum erzeugten Kraft zur gesamten Lösekraft. So kann die Lösekraft besonders effektiv und einfach erzeugt werden. Insbesondere ist die Fläche die bezüglich der Flugrichtung rückwärts gerichtete Bodenfläche des Geschossbodens.In a preferred variant of the embodiment mentioned above, the separating device contains a surface arranged on the floor of the floor. During the flight of the carrier projectile, 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. In particular, 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. In particular, the surface is the bottom surface of the projectile base which is directed backwards with respect to the direction of flight.

In einer bevorzugten Ausführungsform der Erfindung sind der Geschossboden und die Hülle im Ausgangszustand durch eine Reibschluss- und/oder Formschluss-Verbindung bzw. ein entsprechendes Verbindungsmittel aneinander gehalten. Die Verbindung ist bei bzw. durch Aufbringen der Lösekraft (größer/gleich der Grenzkraft) lösbar. Sobald die Grenzkraft anliegt, wird die entsprechende Verbindung also gelöst bzw. ist in der Folge dann gelöst. Insbesondere ist eine entsprechend durch die Verbindung bewirkte Haft- und/oder Haltekraft der Verbindung kleiner oder gleich der Grenzkraft dimensioniert. Die Verbindung ist hinsichtlich der Kräfte entsprechend dimensioniert. Die entsprechende Verbindung ist damit zumindest Teil des oben genannten Verbindungsmittels. Insbesondere ist bzw. enthält das Verbindungsmittel ein komprimierbares Dichtelement, welches zur Komprimierung und Überwindung eines Reib-/Formschlusses das Aufbringen mindestens der Grenzkraft benötigt. Alternative Verbindungsmittel oder Teile davon sind zum Beispiel Klebe-oder Pressverbindungen, Sollbruchstellen, Abreißnähte usw.In a preferred embodiment of the invention, 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. In particular, 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. In particular, 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.

In einer bevorzugten Ausführungsform der Erfindung ist das Trägergeschoss ein Trägergeschoss für eine Rohrwaffe mit einem gezogenen Lauf. Das optionale Führungsband ist dann ein solches zur Drallübertragung vom Lauf auf das Trägergeschoss. Somit ist das Trägergeschoss einerseits für den Großteil verfügbarer Rohrwaffen geeignet. Außerdem ergeben sich die generellen Vorteile eines Dralls auch für das vorliegende Trägergeschoss.In a preferred embodiment of the invention, 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. Thus, on the one hand, the carrier projectile is suitable for the majority of available barrel weapons. In addition, the general advantages of rifling also apply to the carrier projectile in question.

In einer bevorzugten Variante dieser Ausführungsform weist das Trägergeschoss ein Drallübertragungselement auf. Das Drallübertragungselement ist im Aufnahmeraum angeordnet und am Geschossboden und/oder an der Hülle befestigt und durchsetzt zur Drallübertragung den Aufnahmeraum für die Nutzlast zumindest teilweise. Die Durchsetzung reicht dabei so weit, dass eine bestimmungsgemäße Nutzlast in gewünschter Weise mit dem Drall beaufschlagt wird. Drall, der vom Lauf der Rohrwaffe auf das Trägergeschoss übertragen wird, wird vermittels des Drallübertragungselements auch auf die Nutzlast übertragen. Das Drallübertragungselement ist insbesondere ein Mitnahmeelement, dass bezüglich der Mittellängsachse drehfest mit dem Geschossboden und oder der Hülle verbunden ist. Als Mitnahmeelement denkbar sind zum Beispiel Gitter, Bügel, Stifte etc.In a preferred variant of this embodiment, 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.

In einer bevorzugten Variante dieser Ausführungsform enthält oder ist das Drallübertragungselement mindestens eine sich zumindest teilweise durch den Aufnahmeraum erstreckende Wand. So wird der Aufnahmeraum zumindest an der betreffenden Stelle pro Wand in zwei Teilräume aufgeteilt. Jeder Teilraum kann dann zumindest einen Teil der Nutzlast aufnehmen. Die Drallübertragung findet dann durch Anlage an der Wand statt. Insbesondere enthält das Drallübertragungselement zwei im Querschnitt kreuzförmig angeordnete Wände, die sich an der Mittellängsachse des Trägergeschosses schneiden. Die Wand ist insbesondere mit oder ohne Aussparungen ausgeführt. Insbesondere ist die Wand am Geschossboden befestigt. So sind jeweils einfache Möglichkeiten zur Drallübertragung auf die Nutzlast geschaffen.In a preferred variant of this embodiment, the twist transmission element contains or is at least one wall that extends at least partially through the receiving space. In this way, 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. In particular, 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. In particular, 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.

In einer bevorzugten Variante der oben genannten Ausführungsform, die insbesondere eine Alternative zum Drallübertragungselement darstellt, enthält das Trägergeschoss ein Drallentkopplungselement zur Aufnahme zumindest eines Teils der der Nutzlast. Das Drallentkopplungselement ist vom Geschossboden und der Hülle bezüglich einer Rotation um die Mittellängsachse entkoppelt. Das restliche Trägergeschoss kann also eine Drallbewegung ausführen, ohne dass das Drallentkopplungselement (und die darin aufgenommene Nutzlast) dieser folgt. So ist es möglich, die Nutzlast bzw. deren betreffenden Teil am Drallentkopplungselement zu orientieren und so vom drallenden Teil des Trägergeschosses, insbesondere vom Geschossboden und der Hülle, drallzuentkoppeln. Diese Elemente weisen dann keinen Drall auf. Die Vorteile eines drallenden Trägergeschosses bleiben erhalten, ohne zwangsweise die Nutzlast auch einem Drall auszusetzen.In a preferred variant of the above-mentioned embodiment, which in particular represents an alternative to the spin transmission element, 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.

In einer bevorzugten Variante dieser Ausführungsform enthält oder ist das Drallentkopplungselement ein Aufnahmekörper für zumindest einen Teil, insbesondere die gesamte Nutzlast. Der Aufnahmekörper ist im Geschossboden und in der Hülle um die Mittellängsachse rotierbar gelagert. Da der Aufnahmekörper selbst drallentkoppelt ist, ist auch die gesamte in diesem gehaltene Nutzlast drallentkoppelt. Der Aufnahmekörper ist insbesondere eine Wanne, Becher oder Topf, dessen Öffnung insbesondere in Flugrichtung weist und der insbesondere axialsymmetrisch zur Mittellängsachse ausgeführt ist. Hinsichtlich der Beschleunigung des Trägergeschosses steht somit die Nutzlast an einem entgegen der Flugrichtung weisenden Boden des Aufnahmekörpers an. Die Drallentkopplung kann so besonders einfach bewerkstelligt werden.In a preferred variant of this embodiment, 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.

Die Erfindung beruht auf folgenden Erkenntnissen, Beobachtungen bzw. Überlegungen und weist noch die nachfolgenden Ausführungsformen auf. Die Ausführungsformen werden dabei teils vereinfachend auch "die Erfindung" genannt. Die Ausführungsformen können hierbei auch Teile oder Kombinationen der oben genannten Ausführungsformen enthalten oder diesen entsprechen und/oder gegebenenfalls auch bisher nicht erwähnte Ausführungsformen einschließen.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.

Die Erfindung beruht auf der grundlegenden Idee, ein Trägersystem für Rohrwaffen (mit gezogenem Lauf/Drall) zu entwerfen, um eine Nutzlast (Konstruktionssplitter, Flechets, andere Wirkelemente) aus einem gezogenen Lauf zu verbringen. Gleichzeitig soll eine Zerlegung im Lauf ausgeschlossen sein.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.

Die Erfindung beruht auf der grundlegenden Idee, durch den Sog am Geschossboden (der aerodynamisch während des Fluges entsteht) und einen Lufteinlass, der (ebenfalls aerodynamisch während des Fluges) einen Überdruck im Geschoss-Innenraum (Aufnahmeraum) erzeugt, das Geschoss (in Axialrichtung) auseinander zu ziehen und zu öffnen (die Hülle vom Geschossboden zu trennen).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).

Gegenüber klassischen Cargo-Geschossen mit Zeitzünder und Ausstoßladung benötigt das erfindungsgemäße Trägergeschoss keinen teuren Zeitzünder mit Pyrotechnik und kann auch insbesondere in kleinen Kalibern (Mittelkaliber, .50/12,7mm oder größer) eingesetzt werden. Des Weiteren ist im Geschoss selbst keine chemische Energie gespeichert, was die Gefährdung durch Explosivstoffe völlig vermeidet. Die Frage nach IM-Eigenschaften (insensitive Munition) stellt sich so erst gar nicht. Eine vorzeitige Öffnung und Zerlegung im Lauf ist technisch ausgeschlossen. Dies ist dadurch begründet, dass das Öffnen des Geschosses erst durch dynamische Vorgänge während des Fluges bewerkstelligt werden kann; im Lauf wird dagegen Druck auf einen massiven Boden (Geschossboden) ausgeübt. Das Verbleiben von Geschossteilen im Lauf ist technisch ausgeschlossen.Compared to classic cargo projectiles with a time fuse and ejector charge, 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.

Gemäß der Erfindung ist es möglich, Wirkmittel (z. B. Splitter oder Flechets) aus einem gezogenen Lauf zu verbringen, ohne dass dabei ein Öffnen des Trägergeschosses und eine Freigabe der Wirkmittel im Lauf möglich ist. Die Erfindung erlaubt dabei eine Umsetzung, ohne dabei auf einen (teuren) Zünder oder andere Entsicherungseinrichtungen zurückgreifen zu müssen. Die Erfindung erlaubt dabei ebenfalls eine Umsetzung, ohne chemische Energie speichern zu müssen. Dies führt zu einem Vorteil bei IM-Fragen, chemischer Kompatibilität, Lagerstabilität und Lagergruppeneinstufung.According to 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. 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.

Gemäß der Erfindung erfolgt eine Freigabe der Nutzlast unmittelbar nach dem Lauf (0-5m, insbesondere 0,5-3m, insbesondere 1-2m). Das Trägersystem (Trägergeschoss) ermöglicht die Verbringung ähnlich zu Schrot oder Kanistermunition aus gezogenen Läufen, bei gleichzeitigem (optionalem) Drallübertrag auf die Nutzlast.According to the invention, 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) allows the movement similar to shot or canister ammunition from rifled barrels, with simultaneous (optional) spin transfer to the payload.

Das Trägergeschoss wird wie ein klassisches Geschoss in einem Lauf beschleunigt. Im Falle eines gezogenen Laufes wird durch das Führungsband der Drall übertragen. Durch den anstehenden Druck auf das Heck des Geschosses, wird es beschleunigt und der versiegelte Lufteinlass (Öffnung mit Füllelement) geöffnet (Entfernen des Füllelements aus der Öffnung durch Abschussschock). In der folgenden Flugphase (nach Verlassen des Laufes) entfällt die Beschleunigungskraft am Heck und wird durch einen Sog (verursacht durch die vorbeiströmende Luft) ersetzt. Gleichzeitig sorgt die (durch die Öffnung/Lufteinlass) einströmende Luft für einen Überdruck im Geschoss-Innenraum (Aufnahmeraum). Sog und Überdruck sorgen für ein Öffnen des Geschosses (Trennung von Geschossboden und Hülle). Durch die beschleunigende Kraft im Lauf ist eine Zerlegung des Geschosses im Lauf ausgeschlossen.The carrier bullet is accelerated like a classic bullet in one barrel. In the case of a rifled barrel, the twist is transmitted through the guide band. Due to the applied pressure on the tail of the projectile, it is accelerated and the sealed air inlet (opening with filling element) is opened (removing the filling element from the opening by launch shock). In the following flight phase (after leaving the run) the acceleration force at the rear is eliminated and is replaced by a suction (caused by the air flowing past). At the same time, the air flowing in (through the opening/air inlet) creates overpressure in the interior of the projectile (receiving space). Suction and overpressure cause 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.

Wenn eine Drallübertragung auf die Nutzlast gewünscht ist, kann ein optionales Drallübertragungssystem (Drallübertragungselement) eingesetzt werden. Ein Grund für eine gewünschte Drallübertragung auf die Nutzlast wäre eine größere Auffächerung der Nutzlast (in der Regel Effektoren), um den Wirkbereich (kegelförmig vor der Waffenmündung) zu vergrößern.If a spin transfer to the payload is desired, an optional spin transfer system (spin transfer element) can be used. One reason for a desired spin transfer to the payload would be a greater fanning out of the payload (usually effectors) in order to increase the effective range (cone-shaped in front of the weapon muzzle).

Wenn eine Drallübertragung nicht gewünscht ist, um den Wirkbereich zu strecken und mehr in die Tiefe zu wirken, kann das Drallübertragungselement ersetzt werden. In diesem Fall ist im Geschossboden eine drehbare Wanne (Aufnahmekörper) eingesetzt, in dem sich die Nutzlast drallentkoppelt befindet.If a twist transfer is not desired in order to stretch the effective area and work more in depth, the twist transfer element can be replaced. In this case, a rotatable trough (receiving body) is used in the floor of the floor, in which the payload is located, decoupled from twisting.

Gemäß der Erfindung ist es also möglich, Drall auf die Nutzlast zu übertragen oder diese vom Drall zu entkoppeln.According to the invention, it is therefore possible to transfer spin to the payload or to decouple it from spin.

Weitere Merkmale, Wirkungen und Vorteile der Erfindung ergeben sich aus der nachfolgenden Beschreibung eines bevorzugten Ausführungsbeispiels der Erfindung sowie der beigefügten Figuren. Dabei zeigen in einer schematischen Prinzipskizze:

Figur 1
ein Trägergeschoss in a) Außenansicht und b) im Querschnitt (Linie Ib-Ib in Fig. 1a),
Figur 2
eine Darstellung der Funktionsweise des Trägergeschosses aus Figur 1 in den Phasen a) Abschuss, b) Flug und c) Öffnung (Darstellung gemäß Fig. 1b),
Figur 3
den Geschossboden des Trägergeschosses aus Figur 1 mit Drallübertragungselement a) im Schnitt gemäß Fig. 1b und b) in Draufsicht entgegen der Richtung des Pfeils 6 in Fig. 3a,
Figur 4
den Geschossboden des Trägergeschosses aus Figur 1 mit Drallentkopplungselement im Schnitt gemäß Fig. 1b.
Further features, effects and advantages of the invention result from the following description of a preferred exemplary embodiment of the invention and the attached figures. A schematic principle sketch shows:
figure 1
a carrier floor in a) external view and b) in cross-section (line Ib-Ib in Fig. 1a ),
figure 2
an illustration of how the carrier floor works figure 1 in the phases a) launch, b) flight and c) opening (representation according to Fig. 1b ),
figure 3
the floor of the carrier floor figure 1 with twist transmission element a) in section according to Fig. 1b and b) in plan view against the direction of arrow 6 in Figure 3a ,
figure 4
the floor of the carrier floor figure 1 with twist decoupling element in section according to Fig. 1b .

Figur 1 zeigt ein erfindungsgemäßes Trägergeschoss 2 für eine in Figur 2a angedeutete Rohrwaffe 20. Das Trägergeschoss 2 erstreckt sich entlang einer Mittellängsachse 4, die eine Axialrichtung des Trägergeschosses 2 beschreibt. Das Trägergeschoss 2 weist außerdem eine bestimmungsgemäße Flugrichtung 6 (durch einen Pfeil angedeutet) auf, die in Richtung der Mittellängsachse 4 gerichtet ist. Das Trägergeschoss 2 enthält einen Geschossboden 8. An einer (bezüglich der Mittellängsachse 4 bzw. Axialrichtung) radial auswärts weisenden Umfangsfläche 10 ist am Geschossboden 8 ein Führungsband 12 angeordnet. figure 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).

Das Trägergeschoss 2 enthält außerdem eine Hülle 14 in Form einer oberen Geschosshülle, die in dem in Figur 1 dargestellten Ausgangszustand A mit dem Geschossboden 8 verbunden ist. Geschossboden 8 und Hülle 14 sind jedoch in Axialrichtung voneinander lösbar, indem die Hülle 14 in Flugrichtung 6 und/oder der Geschossboden 8 entgegen der Flugrichtung 6 voneinander weg bewegt werden (Betrachtung der Relativbewegungen). Hierzu ist die Aufbringung einer in den Figuren nur angedeuteten Lösekraft L zwischen Geschossboden 8 und Hülle 14 (greift in entgegengesetzten Richtungen an beiden Elementen an) für die oben beschriebene Bewegung notwendig. Die Lösekraft L muss hierbei größer einer Grenzkraft G sein, bis zu der Geschossboden 8 und Hülle 14 aneinander halten. Im Beispiel sind der Geschossboden 8 und die Hülle 14 durch eine in Figur 1b lediglich symbolisch angedeutete Reibschluss- / Formschluss-Verbindung 36 aneinandergehalten, die sich beim Aufbringen einer Lösekraft L größer gleich der Grenzkraft G löst. Die entsprechenden Reibschluss- / Formschlusselemente (nicht dargestellt) bilden daher ein Verbindungsmittel 37, um Hülle 14 und Geschossboden 8 bis zum Einwirken der Grenzkraft G aneinander zu halten.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. However, 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. In this case, the release force L must be greater than a limit force G up to which the base 8 and casing 14 hold one another. In the example, 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 (not shown) 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.

Geschossboden 8 und Hülle 14 umgeben einen Aufnahmeraum 16 im Inneren des Trägergeschosses 2. Im Aufnahmeraum 16 befördert das Trägergeschoss 2 eine hier nur symbolisch angedeutete Nutzlast 17, hier Konstruktionssplitter.Projectile base 8 and shell 14 surround a receiving space 16 inside the carrier projectile 2. In the receiving space 16, the carrier projectile 2 conveys a payload 17, here only symbolically indicated, here construction fragments.

Das Trägergeschoss 2 enthält eine Trennvorrichtung 18. Bei der bestimmungsgemäßen Benutzung des Trägergeschosses 2, d. h. nach dessen Abschuss und während dessen Fluges, nämlich nach Verlassen eines in Figur 2a dargestellten Laufs 22 der Rohrwaffe 20, erzeugt die Trennvorrichtung 18 die Lösekraft L, die schließlich größer gleich der Grenzkraft G wird. Die Erzeugung geschieht hierbei ohne Verwendung einer Ausstoßladung und ohne Verwendung eines Zünders (beides daher selbstverständlich nicht dargestellt).The carrier projectile 2 contains a separating device 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).

Die Trennvorrichtung 18 enthält eine Öffnung 24 in der Hülle 14. Die Hülle 14 ist also von der Öffnung 24 durchbrochen, die eine Lufteinlassöffnung bildet, wie später erläutert wird. Die Öffnung 24 befindet sich an demjenigen Ende 26 des Trägergeschosses 2 bzw. der Hülle 14, welches bezüglich der Flugrichtung 6 vorne liegt. Hier befindet sich die Öffnung 24 an der Spitze 28 des Trägergeschosses 2 beziehungsweise der Hülle 14.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 . Here the opening 24 is located at the tip 28 of the carrier projectile 2 or the casing 14.

In Figur 1a, b ist die Öffnung 24 durch ein Füllelement 30 verschlossen. Das Füllelement 30 ist jedoch aus der Öffnung 24 entfernbar, um diese freizugeben, wie später erläutert wird. Im Ausgangszustand A ist die Öffnung 24 also eine versiegelte Lufteinlassöffnung.In Figure 1a, b the opening 24 is closed by a filling element 30 . However, the filling element 30 is removable from the opening 24 in order to free it, as will be explained later. In the initial state A, the opening 24 is therefore a sealed air inlet opening.

Die Trennvorrichtung 18 enthält weiterhin eine Fläche 32, die am Geschossboden 8 angeordnet ist. Hier ist die Fläche 32 durch das Ende 34 des Trägergeschosses 2 bzw. des Geschossbodens 8 gebildet, welches dem Ende 26 bzw. der Spitze 28 bezüglich der Flugrichtung 6 gegenüberliegt.The separating device 18 further includes a surface 32 which is arranged on the floor 8 . Here 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 .

Das Führungsband 12 dient zur Abdichtung des Trägergeschosses 2 bzw. des Geschossbodens 8 gegenüber dem Lauf 22 bzw. dessen Innenseite. Der Lauf 22 ist ein gezogener Lauf 22. Das Führungsband 12 dient daher auch zur Drallübertragung vom Lauf 22 auf den Geschossboden 8 und damit das gesamte Trägergeschoss 2.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.

Die Funktionsweise des Trägergeschosses 2 wird wie folgt erläutert:
Bei seiner Benutzung wird das Trägergeschoss 2 in die Rohrwaffe 20 bzw. deren Lauf 22 eingebracht und in herkömmlicher Weise abgeschossen. Figur 2a zeigt das Trägergeschoss 2 während seines Weges durch den Lauf 22 nach dem Abschuss.The functioning of the carrier floor 2 is explained as follows:
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.

Während dieses Abschussvorgangs im Lauf 22 wird das Trägergeschoss 2 durch einen nicht näher dargestellten Antrieb (Treibladung) beschleunigt. Der Antrieb bzw. die Beschleunigungskraft ist durch einen Pfeil 38 symbolisiert. Die entsprechende Kraft greift am Geschossboden 8 bzw. der Fläche 32 bzw. dem Ende 34 an und wirkt in Richtung der Flugrichtung 6. Gleichzeitig wird durch den Abschussschock die versiegelte Luft-Einlassöffnung (Öffnung 24, verschlossen durch Füllelement 30) nach innen geöffnet: das Füllelement 30 wird also vermittels seiner Massenträgheit aus der Öffnung 24 gelöst und in Richtung des Pfeils 40 in den Aufnahmeraum 16 befördert. Verlässt das Trägergeschoss 2 die nicht dargestellte Mündungsöffnung des Laufs 22, endet der Antrieb bzw. die Beschleunigung des Trägergeschosses 2.During this firing process in the barrel 22, 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. At the same time, 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.

Figur 2b zeigt die sich nun anschließende Flugphase des Trägergeschosses 2 in der Luft 40. Im Flug nach dem Verlassen des Laufes 22 steht die Beschleunigung (Pfeil 38 in Figur 2a) am Geschossboden 8 nicht mehr an. Stattdessen entsteht durch Luft 40, welche vom Trägergeschoss 2 durchquert wird, aufgrund der Aerodynamik am Geschossboden 8 ein Sog, der eine Kraft entgegen der Flugrichtung 6 am Geschossboden 8 bewirkt. Die entsprechende Kraft ist durch einen Pfeil 42 angedeutet. Der entsprechende Sog wirkt also entgegen der Flugrichtung 6. Die Hülle 14 ist dagegen bestrebt, sich weniger bzw. ungebremst in Flugrichtung 6 weiterzubewegen. Bereits durch den entsprechenden Sog und die Massenträgheit der Hülle 14 entsteht somit ein Teil der Lösekraft L, die bestrebt ist, Hülle 14 und Geschossboden 8 in bzw. entgegen der Flugrichtung 6 voneinander zu trennen. Figure 2b shows the subsequent flight phase of the carrier projectile 2 in the air 40. In flight after leaving the barrel 22, the acceleration (arrow 38 in Figure 2a ) no longer on floor 8. Instead, due to the aerodynamics at the 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 .

Gleichzeitig findet ein zweiter Effekt statt: durch die Öffnung 24 bzw. Lufteinlassöffnung strömt (angedeutet durch den Pfeil 44) Luft 40 in den Aufnahmeraum 16 bzw. Innenraum des Trägergeschosses 2. Mit anderen Worten baut sich aufgrund der Aerodynamik ein entsprechender Staudruck im Aufnahmeraum 16 auf, der den Umgebungsdruck übersteigt. Somit entsteht ein Überdruck im Trägergeschoss 2 bzw. Aufnahmeraum 16 gegenüber der umgebenden Luft 40. Auch dieser Staudruck bzw. Überdruck bewirkt einen Teil der Lösekraft L. Im Beispiel setzt sich die Lösekraft L genau aus den beiden genannten Komponenten (Sog und Staudruck) zusammen.At the same time, a second effect takes place: 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. In other words, due to the aerodynamics, a corresponding dynamic pressure builds up in the receiving space 16 , which exceeds the ambient pressure. This creates an overpressure in the carrier floor 2 or receiving space 16 compared to the surrounding air 40. This dynamic pressure or overpressure also causes part of the release force L. In the example, the release force L is made up of exactly the two components mentioned (suction and dynamic pressure).

Figur 2c zeigt die entsprechenden Verhältnisse: Die gesamte Lösekraft L, hier durch einen Doppelpfeil symbolisiert, ist größer der Grenzkraft G und führt daher dazu, Hülle 14 und Geschossboden 8 in bzw. entgegen der Flugrichtung 6 voneinander zu lösen. Der Aufnahmeraum 16 bzw. das Trägergeschoss 2 wird dadurch geöffnet und die darin befindliche Nutzlast 17 freigegeben. Mit anderen Worten ist die resultierende Kraft (Lösekraft L) aus Sog (Pfeil 42) und Innendruck (Pfeil 44) größer, als diejenige Kraft, die das Verbindungsmittel 37 in Form der Verbindung 36 halten kann. Nutzlast 17, die sich nach der Trennung von Hülle 14 und Geschossboden 8 noch in der Hülle 14 befindet, wird dabei auch durch die Luft, die durch die Öffnung 24 einströmt, aus der Hülle 14 gedrückt. Der Geschossboden 8 fällt durch den Sog an der Fläche 32 dabei ohnehin von der Nutzlast 17 ab. Figure 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. In other words, 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 .

Figur 3 zeigt einen Teil eines alternativen Trägergeschosses 2. Dieses enthält den Geschossboden 8 aus Figur 1, der in Fig. 3 a) in Schnitt-Seitenansicht gemäß Figur 1b und in Fig. 3b) in Draufsicht entgegen der Flugrichtung 6 dargestellt ist. Im Geschossboden 8 ist ein Drallübertragungselement 50 (in Form eines Trägerelements) des Trägergeschosses 2 befestigt bzw. fest mit dem Geschossboden 8 verbunden. Das Drallübertragungselement 50 dient dazu, einen Drall, welchen der Geschossboden 8 aufweist, auf die Nutzlast 17 zu übertragen. Das Drallübertragungselement 50 erstreckt sich über einen Teil des Aufnahmeraums 16 und tritt daher mit der hierin befindlichen Nutzlast 17 durch Formschluss in Wechselwirkung, wie in Figur 3b) angedeutet ist. Das Drallübertragungselement 50 besteht hier aus zwei Wänden 52, die sich jeweils entlang der Mittellängsachse 4 erstrecken und um 90° gegeneinander verdreht sind, sodass diese im Querschnitt eine Kreuzstruktur bilden. 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.

Figur 4 zeigt eine alternative Ausführungsform des Trägergeschosses 2. Dieses enthält ebenfalls den Geschossboden 8 gemäß Figur 1. Im Geschossboden 8 ist jedoch ein Drallentkopplungselement 54 angeordnet. Bezüglich der Mittellängsachse 4 bzw. der Axialrichtung sind Geschossboden 8 und Drallentkopplungselement 54 gegeneinander rotierbar und somit bezüglich dieser Rotation voneinander entkoppelt. Das Drallentkopplungselement 54 dient zur Aufnahme der Nutzlast 17, die hier in Form von Flechets angedeutet ist. Das Drallentkopplungselement 54 bildet somit einen Aufnahmekörper 56, hier in Form eines in Flugrichtung 6 offenen topfförmigen kreisrunden Bechers. Das Drallentkopplungselement 54 ist somit bezüglich des gesamten Trägergeschosses 2 sowohl im Geschossboden 8 als auch in der Hülle 14 um die Mittellängsachse 4 bzw. Axialrichtung rotierbar. Im Falle einer Drallübertragung vom Lauf 22 auf das Trägergeschoss 2 behält das Drallentkopplungselement 54 zusammen mit der Nutzlast 17 aufgrund der rotatorische Massenträgheit seine rotatorische Ruheposition um die Mittellängsachse 4 bei. Becher und Nutzlast 17 "rutschen" mit anderen Worten gegenüber Geschossboden 8 und Hülle 14 um die Mittellängsachse 4 bzw. Axialrichtung "durch". 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. In the event of a spin being transferred from the barrel 22 to the carrier projectile 2, 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. In other words, bucket and payload 17 “slip” relative to floor 8 and casing 14 about central longitudinal axis 4 or axial direction “through”.

BezugszeichenlisteReference List

22
Trägergeschosscarrier floor
44
Mittellängsachsecentral longitudinal axis
66
Flugrichtungflight direction
88th
Geschossbodenfloor
1010
Umfangsflächeperipheral surface
1212
Führungsbandguide band
1414
HülleCovering
1616
Aufnahmeraumrecording room
1717
Nutzlastpayload
1818
Trennvorrichtungseparator
2020
Rohrwaffepipe weapon
2222
Laufrun
2424
Öffnungopening
2626
EndeEnd
2828
SpitzeGreat
3030
Füllelementfilling element
3232
FlächeArea
3434
EndeEnd
3636
VerbindungConnection
3737
Verbindungsmittellanyard
3838
PfeilArrow
4040
LuftAir
4242
PfeilArrow
4444
PfeilArrow
5050
Drallübertragungselementtwist transmission element
5252
WandWall
5454
Drallentkopplungselementtwist decoupling element
5656
Aufnahmekörperrecording body
AA
Ausgangszustandinitial state
LL
Lösekraftsolvent power
GG
Grenzkraftlimit force

Claims (9)

  1. Carrier projectile (2) for a gun (20) having a barrel (22) which extends along a longitudinal centre axis (4),
    - having a projectile base (8),
    - having a casing (14) which in an initial state (A) is connected to the projectile base (8), and which can be released in an axial direction away from the projectile base (8) when a release force (L) which exceeds a limit force (G) acts between the projectile base (8) and casing (14) in an axial direction,
    - wherein the projectile base (8) and the casing (14) surround a receiving space (16) for a useful load (17),
    - and having a separation apparatus (18), wherein the release force (L) is produced by the separation apparatus (18) after leaving the barrel (22) without the use of an ejection charge and/or without the use of a detonator, wherein the release force (L) is produced aerodynamically on the carrier projectile (2) during the flight of the carrier projectile (2),
    - wherein the release force (L) is produced by means of air pressure which is produced by the flight,
    - wherein the separation apparatus (18) contains an opening (24) in the casing (14) which during the flight is exposed to a dynamic pressure of incoming air, wherein, as a result of the dynamic pressure, an excess pressure in the form of air pressure is produced in the receiving space (16),
    - wherein the separation apparatus (18) contains a filling element (30) which closes the opening (24) in the initial state (A),
    - wherein the filling element (30) can be removed from the opening (24) by means of a firing shock which occurs when the projectile (2) is fired.
  2. Carrier projectile (2) according to Claim 1,
    characterized in that
    the opening (24) is located at the front end (26), facing in the flight direction (6), of the casing (14).
  3. Carrier projectile (2) according to either of the preceding claims,
    characterized in that
    the separation apparatus (18) contains a face (32) which is arranged on the projectile base (8) and which during the flight is exposed to a suction force as a result of air flowing past it, wherein the suction force is directed away from the casing (14) counter to the flight direction (6).
  4. Carrier projectile (2) according to any one of the preceding claims,
    characterized in that
    the projectile base (8) and the casing (14) in the initial state (A) are held on each other by means of a frictionally engaging and/or positive-locking connection (36) which can be released upon application of the limit force (G).
  5. Carrier projectile according to any one of the preceding claims,
    characterized in that
    the carrier projectile (2) is a carrier projectile (2) for a gun (20) having a rifled barrel (22).
  6. Carrier projectile (2) according to Claim 5,
    characterized in that
    the carrier projectile (2) has in the receiving space (16) a torsion transmission element (50) which is secured to the projectile base (8) and/or to the casing (14) and which at least partially extends through the receiving space (16) in order to transmit torsion.
  7. Carrier projectile (2) according to Claim 6,
    characterized in that
    the torsion transmission element (50) contains or is at least one wall (52) which extends at least partially through the receiving space (16).
  8. Carrier projectile (2) according to any one of Claims 5 to 7,
    characterized in that the carrier projectile (2) contains a torsion decoupling element (54) for receiving at least a portion of the useful load (17), wherein the torsion decoupling element (54) is decoupled from the projectile base (8) and the casing (14) with respect to a rotation about the longitudinal centre axis (4).
  9. Carrier projectile (2) according to Claim 8,
    characterized in that
    the torsion decoupling element (54) contains for at least a portion of the useful load (17) a receiving member (56) which can be rotated in the projectile base (8) and in the casing (14) about the longitudinal centre axis (4).
EP19201711.9A 2018-10-12 2019-10-07 Carrier projectile for a gun Active EP3637039B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102018008079.0A DE102018008079A1 (en) 2018-10-12 2018-10-12 Carrier bullet for a barrel weapon

Publications (2)

Publication Number Publication Date
EP3637039A1 EP3637039A1 (en) 2020-04-15
EP3637039B1 true EP3637039B1 (en) 2023-09-06

Family

ID=68172109

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19201711.9A Active EP3637039B1 (en) 2018-10-12 2019-10-07 Carrier projectile for a gun

Country Status (2)

Country Link
EP (1) EP3637039B1 (en)
DE (1) DE102018008079A1 (en)

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

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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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Publication number Publication date
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EP3637039A1 (en) 2020-04-15

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