EP1399706A1 - Artillery projectile comprising an interchangeable payload - Google Patents

Artillery projectile comprising an interchangeable payload

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Publication number
EP1399706A1
EP1399706A1 EP02754685A EP02754685A EP1399706A1 EP 1399706 A1 EP1399706 A1 EP 1399706A1 EP 02754685 A EP02754685 A EP 02754685A EP 02754685 A EP02754685 A EP 02754685A EP 1399706 A1 EP1399706 A1 EP 1399706A1
Authority
EP
European Patent Office
Prior art keywords
section
projectile
projectile according
tip section
wall
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP02754685A
Other languages
German (de)
French (fr)
Other versions
EP1399706B1 (en
Inventor
Karl Kautzsch
Klaus Bär
Jürgen Bohl
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 BGT Defence GmbH and Co KG
Original Assignee
Diehl Munitionssysteme GmbH and Co KG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Diehl Munitionssysteme GmbH and Co KG filed Critical Diehl Munitionssysteme GmbH and Co KG
Publication of EP1399706A1 publication Critical patent/EP1399706A1/en
Application granted granted Critical
Publication of EP1399706B1 publication Critical patent/EP1399706B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/04—Stabilising arrangements using fixed fins
    • F42B10/06—Tail fins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B14/00—Projectiles or missiles characterised by arrangements for guiding or sealing them inside barrels, or for lubricating or cleaning barrels
    • F42B14/02—Driving bands; Rotating bands
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F42B10/16—Wrap-around fins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/62—Steering by movement of flight surfaces
    • F42B10/64—Steering by movement of flight surfaces of fins
    • 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 an artillery projectile according to the preamble of claim 1.
  • the generic device is known as the MLRS 1/2 artillery missile system.
  • Its continuous rocket shell can be equipped with canisters from the still open rear behind the ogive equipped with a time fuse, which in turn are equipped with distribution units for ejecting different armor-piercing active bodies such as, in particular, bomblets or tank mines. Behind this axial stack of canisters, the rocket is then equipped with its motor, the housing of which in the rear area is equipped with fold-out rudders that are bent parallel to the system axis.
  • the flexibility of such a system is limited, however, because the rocket shell is in one piece from the ogive to the point of separation for the connection of the ejectable rocket motor.
  • the present invention is based on the technical problem of creating a system which is more open with regard to the interchangeability of the warheads and which is characterized above all by a large range with, nevertheless, precise delivery runs of the payload.
  • the payload space is the entire central section of an artillery projectile to be fired ballistically and after apogee turns into a controlled gliding flight; whereby this very different payload-absorbing section lies between a standard tail section that remains the same for all payloads, which determines the outer ballistics immediately after leaving the weapon barrel, and a standard tip section that also remains the same for all payloads, which in turn has canard oars for controllable gliding flight and with navigation devices like
  • Inertia and / or satellite navigation is equipped for the most precise possible payload delivery.
  • the center section which can be inserted interchangeably between these two standard end sections, contains at least one warhead in the form of a target-seeking submunition, a bundle of bomblets to be spread, a high-energy warhead or a post-accelerated rod penetrator in its hollow cylindrical shell.
  • An appropriately labored shell of the middle section is then flanged to the standard bottom section and the standard tip section, for example by radial pins or a type of bayonet coupling.
  • the projectile has a uniform airframe for very different payloads and, because of the unchanged external ballistics, can therefore be handled without any problems regardless of the payload to be deployed from the artillery gun.
  • FIG. 1 shows in axial longitudinal section a ballistic-to-be-extended, extended-range sliding floor with an exchangeable payload section between standard end sections.
  • the schematic diagram shows in longitudinal section a projectile 11 to be brought out of an artillery gun, that is to say ballistically, and divided into three parts in the axial direction, namely a load section 14 which can be inserted between a rear section 12 and a tip section 13.
  • the load section 14 is therefore no longer a load space that can be loaded in a continuous floor envelope, but rather embodies the completely exchangeable center area of the floor 11 together with its wall 15.
  • the useful space 16 within the wall 15 of the middle or load section 14 of the projectile 11 can, as explained at the outset, be equipped with different warheads, in particular those against hard-armored target objects.
  • a correspondingly labored load section 14 can then be equipped on the production side with the rear section 12 and with the tip section 13 in order to complete the projectile 11.
  • the projectile 11 is equipped with stabilizing fins 17 which are oriented parallel to the axis and are approximately made of sheet steel and which are applied to the cylindrical outer surface area of the rear section 12 under spring tension until they are fired from the weapon barrel.
  • stabilizing fins 17 which are oriented parallel to the axis and are approximately made of sheet steel and which are applied to the cylindrical outer surface area of the rear section 12 under spring tension until they are fired from the weapon barrel.
  • a pot-shaped hood 18 is placed over the rear
  • a circumferential guide band 21 is inserted into a radially flat, axially wide groove 20 embedded in the outer lateral surface of the annular wall 19. This is designed as a so-called slipping guide band 21, i.e. not connected to the projectile 11 in a rotationally fixed manner, in order to reduce the stabilizing twist caused by its trains when it is fired from the barrel of the weapon to approximately 10% of the natural value, because the projectile 11 is external ballistic, i.e. after leaving the
  • Muzzle of the gun barrel not fly stabilized twist but to be aerodynamically stabilized by the then approximately radially emerging fins 17.
  • the tip section 13 is designed as standard regardless of the equipment of the load section 14. She is with
  • Canard sliding wings 23 equipped, which emerge from the contour of the ogive 24, for example by a pivoting movement, as soon as the projectile 11 has flown through its apogee on its initially ballistic launch trajectory.
  • the Canards 23 are used both for gliding and for target control. There is a transition - initially from the ballistic descent path adjoining the apogee - to a stretch-controlled gliding flight in order to achieve a correspondingly greater range as a result of the significantly flatter descent path.
  • the specified target point is controlled with the aid of inertial or satellite navigation.
  • This flight guidance takes place by swiveling the sliding wings 23 out of the neutral position, parallel to the generatrix of the ogive 24, by means of a steering transmitter 25, which in turn is controlled via a navigation device 26, so that the projectile 11 then flies over shortly before the predetermined target point is flown over to change from the flat slideway into a steep attack path.
  • a steering transmitter 25 which in turn is controlled via a navigation device 26, so that the projectile 11 then flies over shortly before the predetermined target point is flown over to change from the flat slideway into a steep attack path.
  • an ejection device 28 is activated in order to separate the tip section 13 from the load section 14 and to empty the useful space 16 directly into the narrower target area via this separation point.
  • an inexpensive artillery ammunition that can be steered in the final phase has a significantly increased range and acquisition accuracy for universal use with regard to variable payloads while always maintaining the same aerodynamic behavior because the external ballistic projectile coefficients are maintained if, in the case of an aerodynamically stabilized sliding projectile 11, the external ballistics initially determining, standardized tail section 12 and in the final phase range and precision determining, likewise standardized tip section 13, a load section 14 connecting their two contours is inserted, which can be equipped with very different warheads, in particular optimized against hard targets is.
  • the rear section 12 is equipped with over-calibrated stabilizing fins 17, which are placed in the weapon barrel, in the position in which it is placed, on the lateral surface of the rear section 12, overlapped by a ring wall 19, which is slid with a slipping guide band 21 is already equipped in the gun barrel for the first swirl reduction.
  • 13 canard sliding vanes 23 are issued from the tip section, by means of which a transition from the descending branch of the ballistic trajectory to a flatter and therefore more extensive slideway is controlled via a steering transmitter 25, from which - exclusively a steeper descent into a narrowly specified one, controlled by navigation
  • Target area takes place in which the load section 14 delivers its payload.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Braking Arrangements (AREA)
  • Pharmaceuticals Containing Other Organic And Inorganic Compounds (AREA)
  • Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)

Abstract

An inexpensive artillery munition of great range and acquisition accuracy for universal use while maintaining the external-ballistic coefficients is afforded when inserted between a standardized tail section (12) and also standardized tip section (13) is a load section (14) which connects the two contours of said sections together and which can be equipped with very different warheads which in particular are optimized against hard targets. For launch into an aerodynamically stabilized ballistic trajectory the tail section (12) is provided with super-calibre stabilization fins (17).

Description

Artillerie-Projektil mit austauschbarer Nutzlast Artillery projectile with interchangeable payload
Die Erfindung betrifft ein Artillerie-Projektil gemäß dem Oberbegriff des Anspruches 1.The invention relates to an artillery projectile according to the preamble of claim 1.
Die gattungsgemäße Einrichtung ist als das Artillerie-Raketensystem MLRS 1/2 bekannt. Dessen durchgehende Raketenhülle kann vom noch offenen Heck her hinter der mit einem Zeitzünder bestückten Ogive mit Kanistern bestückt werden, die ihrerseits mit Verteileinheiten zum Auswerfen von unterschiedlichen panzerbrechenden Wirkkörpern wie insbesondere von Bomblets oder von Panzerminen ausgestattet sind. Hinter diesem axialen Stapel von Kanistern wird die Rakete dann mit ihrem Motor bestückt, dessen Gehäuse im Heckbereich mit ausklappbaren, parallel zur Systemachse gebogenen Steuerrudern ausgestattet ist. Die Flexibilität eines solchen Systems ist aber eingeschränkt, weil die Raketenhülle von der Ogive bis zur Trennstelle für den Anschluß des abwerfbaren Raketenmotors einstückig ist. Auch sind die Lenkeigenschaften dieser Artillerie-Rakete nur mäßig gut, weil die Rakete mit nach dem Verlassen des Startrohres nur kurzzeitig aktivem Motor eine hohe Beschleunigung in eine vergleichsweise flache Flugbahn erfährt. Die rein zeitabhängige Missionsbeendigung über den Zeitzünder in der Ogive läßt keine punktgenaue Zielakquisition erwarten, so daß beim Ansprechen des Zeitzünders mit Absprengen des dann längst ausgebrannten Motors nur Streuwirkkörper sinnvoll auszubringen sind.The generic device is known as the MLRS 1/2 artillery missile system. Its continuous rocket shell can be equipped with canisters from the still open rear behind the ogive equipped with a time fuse, which in turn are equipped with distribution units for ejecting different armor-piercing active bodies such as, in particular, bomblets or tank mines. Behind this axial stack of canisters, the rocket is then equipped with its motor, the housing of which in the rear area is equipped with fold-out rudders that are bent parallel to the system axis. The flexibility of such a system is limited, however, because the rocket shell is in one piece from the ogive to the point of separation for the connection of the ejectable rocket motor. The steering characteristics of this artillery rocket are also only moderately good, because the rocket experiences a high acceleration in a comparatively flat trajectory when the engine is only briefly active after leaving the launch tube. The purely time-dependent mission termination via the time fuse in the ogive does not make it possible to expect precise target acquisition, so that when the time fuse responds with the then long-burned-out engine blasting, only scattering active bodies can be expediently deployed.
Vorliegender Erfindung liegt die technische Problemstellung zugrunde, ein hinsichtlich der Austauschbarkeit der Gefechtsköpfe offeneres System zu schaffen, das sich vor allem auch durch große Reichweite mit dennoch zielgenauer Abliefe - runs der Nutzlast auszeichnet. Diese Aufgabe ist nach vorliegender Erfindung dadurch gelöst, daß gemäß der Merksmalskombination des Hauptanspruches der Nutzlastraum die gesamte mittlere Sektion eines ballistisch zu verschießenden und nach dem Apogäum in einen gesteuerten Gleitflug übergehenden ArtiUerie-Projektiles ist; wobei diese sehr unterschiedliche Nutzlasten aufnehmende Sektion zwischen einem für alle Nutzlasten gleichbleibenden Standard-Hecksektion, das die Außenballistik unmittelbar nach Verlassen des Waffenrohres bestimmt, und einem ebenfalls für alle Nutzlasten gleichbleibenden Standard-Spitzensektion liegt, die ihrerseits mit Canard- Rudern für einen steuerbaren Gleitflug und mit Navigationseinrichtungen wieThe present invention is based on the technical problem of creating a system which is more open with regard to the interchangeability of the warheads and which is characterized above all by a large range with, nevertheless, precise delivery runs of the payload. This object is achieved according to the present invention in that, according to the combination of features of the main claim, the payload space is the entire central section of an artillery projectile to be fired ballistically and after apogee turns into a controlled gliding flight; whereby this very different payload-absorbing section lies between a standard tail section that remains the same for all payloads, which determines the outer ballistics immediately after leaving the weapon barrel, and a standard tip section that also remains the same for all payloads, which in turn has canard oars for controllable gliding flight and with navigation devices like
Trägheits- und/oder Satellitennavigation für eine möglichst punktgenaue Nutzlastablieferung ausgestattet ist.Inertia and / or satellite navigation is equipped for the most precise possible payload delivery.
Die zwischen diesen beiden Standard-Endsektionen austauschbar einfügbare Mit- ten-Sektion beinhaltet in ihrem hohlzylindrischen Mantel wenigstens einen Gefechtskopf nach Art zielsuchender Submunition, ein Bündel von auszustreuenden Bomblets, einen Hochenergie-Gefechtskopf oder einen nachbeschleunigbaren Stab-Penetrator. Eine entsprechend laborierte Geschoßhülle der Mitten-Sektion wird dann mit der Standard-Bodensektion und der Standard-Spitzensektion ver- flanscht, etwa durch radiale Stifte oder durch eine Art von Bajonett-Kupplung miteinander verbunden. Jedenfalls weist das Geschoß einen einheitlichen Airframe für sehr unterschiedliche Nutzlasten auf und ist deshalb, wegen unveränderter Außenballistik, zum Verbringen aus dem Artillerie-Geschütz unabhängig von der gerade zu verbringenden Nutzlast problemfrei zu handhaben.The center section, which can be inserted interchangeably between these two standard end sections, contains at least one warhead in the form of a target-seeking submunition, a bundle of bomblets to be spread, a high-energy warhead or a post-accelerated rod penetrator in its hollow cylindrical shell. An appropriately labored shell of the middle section is then flanged to the standard bottom section and the standard tip section, for example by radial pins or a type of bayonet coupling. In any case, the projectile has a uniform airframe for very different payloads and, because of the unchanged external ballistics, can therefore be handled without any problems regardless of the payload to be deployed from the artillery gun.
Hinsichtlich weiterer Einzelheiten, Weiterbildungen und Vorteile der erfindungsgemäßen Losung wird außer auf die Unteransprüche auch auf nachstehende Beschreibung eines in der Zeichnung unter Beschränkung auf das Wesentliche nicht maßstabsgerecht skizzierten bevorzugten Realisierungsbeispiels zur erfindungsgemäßen Lösung verwiesen. Die einzige Figur der Zeichnung zeigt im Axial-Längsschnitt ein ballistisch zu verbringendes, reichweitengesteigertes Gleitgeschoß mit einer austauschbaren Nutzlast-Sektion zwischen Standard- Endsektionen. Die Prinzipskizze zeigt im Längsschnitt ein aus einem Artillerie-Geschütz, also ballistisch zu verbringendes Geschoß 11, das in axialer Richtung dreigeteilt ist, nämlich eine zwischen einer Heck-Sektion 12 und einer Spitzen-Sektion 13 einfügbare Last-Sektion 14 aufweist. Die Last-Sektion 14 ist also nicht mehr ein be- schickbarer Lastraum in einer durchgehenden Geschoßhülle, sondern sie verkörpert den komplett austauschbaren Mittenbereich des Geschosses 11 mitsamt seiner Wandung 15.With regard to further details, developments and advantages of the solution according to the invention, reference is made not only to the subclaims but also to the description below of a preferred exemplary embodiment of the solution according to the invention which is not outlined to scale in the drawing, but limited to the essentials. The only figure in the drawing shows in axial longitudinal section a ballistic-to-be-extended, extended-range sliding floor with an exchangeable payload section between standard end sections. The schematic diagram shows in longitudinal section a projectile 11 to be brought out of an artillery gun, that is to say ballistically, and divided into three parts in the axial direction, namely a load section 14 which can be inserted between a rear section 12 and a tip section 13. The load section 14 is therefore no longer a load space that can be loaded in a continuous floor envelope, but rather embodies the completely exchangeable center area of the floor 11 together with its wall 15.
Der Nutzraum 16 innerhalb der Wandung 15 der mittleren oder Last-Sektion 14 des Geschosses 11 kann wie eingangs erläutert mit unterschiedlichen Gefechtsköpfen bestückt sein, insbesondere mit solchen gegen hartgepanzerte Zielobjekte. Ein entsprechend laborierte Last-Sektion 14 kann dann fertigungsseitig mit der Heck-Sektion 12 und mit der Spitzen-Sektion 13 bestückt werden, um das Geschoß 11 zu komplettieren.The useful space 16 within the wall 15 of the middle or load section 14 of the projectile 11 can, as explained at the outset, be equipped with different warheads, in particular those against hard-armored target objects. A correspondingly labored load section 14 can then be equipped on the production side with the rear section 12 and with the tip section 13 in order to complete the projectile 11.
Das Geschoß 11 ist mit starr-achsparallel orientierten, etwa aus Stahlblech bestehenden Stabilisierungsflossen 17 ausgestattet, die bis zum Abschuß aus dem Waffenrohr unter Federvorspannung an die zylindrische Außenmantelfläche der Heck-Sektion 12 angelegt sind. Um sie in dieser leicht unterkalibrigen Verbrin- gungsstellung zu halten, ist von rückwärts eine topfförmige Haube 18 über dieThe projectile 11 is equipped with stabilizing fins 17 which are oriented parallel to the axis and are approximately made of sheet steel and which are applied to the cylindrical outer surface area of the rear section 12 under spring tension until they are fired from the weapon barrel. In order to keep them in this slightly sub-calibrated transfer position, a pot-shaped hood 18 is placed over the rear
Heck-Sektion 12 mit diesen peripher sie umschlingenden Stabilisierungsflossen 17 geschoben. Deren hohlzylindrische Ringwand 19 hindert die angelegten Stabilisierung Os-flossen 17 am Aufrichten.Rear section 12 with these peripherally wrapping stabilizing fins 17 pushed. Their hollow cylindrical ring wall 19 prevents the stabilization Os-fins 17 from erecting.
In eine in die Außenmantelfläche der Ringwand 19 eingelassene radial flache, axial breite Nut 20 ist ein umlaufendes Führungsband 21 eingelegt. Das ist als sog. durchrutschendes Führungsband 21 ausgelegt, also nicht drehfest mit dem Geschoß 11 verbunden, um den beim Abschuß aus dem Waffenrohr von dessen Zügen hervorgerufenen Stabilisierungsdrall auf etwa 10 % des natürlichen Wertes herabzusetzen, weil das Geschoß 11 außenballistisch, also nach Verlassen derA circumferential guide band 21 is inserted into a radially flat, axially wide groove 20 embedded in the outer lateral surface of the annular wall 19. This is designed as a so-called slipping guide band 21, i.e. not connected to the projectile 11 in a rotationally fixed manner, in order to reduce the stabilizing twist caused by its trains when it is fired from the barrel of the weapon to approximately 10% of the natural value, because the projectile 11 is external ballistic, i.e. after leaving the
Mündung des Waffenrohres, nicht drallstabilisiert fliegen sondern von den dann etwa radial sich ausstellenden Flossen 17 aerodynamisch stabilisiert werden soll. Für diesen Drallabbau im Waffenrohr kann grundsätzlich zwar auch vorgesehen sein, die Ringwand 19 gegenüber dem Geschoß 11, also gegenüber seiner Heck-Sektion 12 sich verdrehen zu lassen: konstruktiv einfacher ist es jedoch, die Haube 18 mit der Ringwand 19 drehfest auf der Heck-Sektion 12 festzulegen und das Führungsband 21 in seiner Nut 20 durchrutschen zu lassen.Muzzle of the gun barrel, not fly stabilized twist but to be aerodynamically stabilized by the then approximately radially emerging fins 17. For this swirl reduction in the weapon barrel, it is in principle also possible to provide the ring wall 19 with respect to the projectile 11, that is to say with respect to it To allow the rear section 12 to be rotated: it is structurally simpler, however, to fix the hood 18 with the ring wall 19 in a rotationally fixed manner on the rear section 12 and to let the guide band 21 slip through its groove 20.
Wenn die Heck-Sektion 12 die Mündung des Waffenrohres verläßt, bewirken derWhen the rear section 12 leaves the mouth of the gun barrel, the effect
Bodensog hinter der Haube 18 und die auf seine Ringwand 19 achsparallel einwirkenden Komponenten der Staudruckkräfte, daß die Ringwand 19 axial nach rückwärts verschoben und schließlich ganz von der Heck-Sektion 12 abgezogen wird und dadurch die noch an die Außenperipherie der Heck-Sektion 12 ange- schmiegten Stabilisierungsflossen 17 zum radialen Ausstellen freigibt. DiesesBottom suction behind the hood 18 and the components of the dynamic pressure forces acting axially parallel on its ring wall 19, that the ring wall 19 is displaced axially backwards and is finally completely pulled off the rear section 12 and as a result is still attached to the outer periphery of the rear section 12. nestled stabilizing fins 17 releases for radial exposure. This
Aufrichten kann fliehkraftbedingt um achsparallele Scharniere erfolgen; zweckmäßiger ist es jedoch, die Stabilisierungsflossen 17 wie schon erwähnt aus Federblechen zu erstellen, die jeweils längs eines Randes starr mit der Heck-Sektion 12 verbunden (beispielsweise vernietet) sind und sich unter Entspannung, eventuell auch von einer auch Biegefeder unterstützt, aus der von der Ringwand 19 gehalterten Anlage in eine parallel zur Projektil-Längsachse 22 gebogen radial-abstehende Stellung entspannen.Due to centrifugal force, it can be erected around hinges parallel to the axis; It is more expedient, however, to create the stabilizing fins 17, as already mentioned, from spring plates, each of which is rigidly connected to the rear section 12 (for example riveted) along one edge and is supported with relaxation, possibly also by a spiral spring, from which the ring wall 19 held system relax in a radially protruding position bent parallel to the longitudinal axis 22 of the projectile.
Wie die Heck-Sektion 12 so ist auch die Spitzen-Sektion 13 unabhängig von der Ausstattung der Last-Sektion 14 standardmäßig ausgelegt. Sie ist mitLike the rear section 12, the tip section 13 is designed as standard regardless of the equipment of the load section 14. She is with
Canard-Gleitflügeln 23 ausgestattet, die aus der Kontur der Ogive 24 beispielsweise durch eine Schwenkbewegung heraustauchen, sobald das Geschoß 11 auf seiner zunächst ballistischen Abschußbahn dessen Apogäum durchflogen hat. Die Canards 23 dienen sowohl dem Gleitflug wie auch der Zielansteuerung. Es erfolgt - zunächst aus der an das Apogäum sich anschließenden ballistischen Abstiegsbahn heraus ein Übergang in einen gestreckt gesteuerten Gleitflug, um so infolge deutlich flacherer Abstiegsbahn eine entsprechend größere Reichweite zu erzielen. Zugleich wird mit Hilfe einer Inertial- oder Satellitennavigation der vorgegebene Zielpunkt angesteuert. Diese Flugführung erfolgt durch Verschwenken der Gleit- flügel 23 aus der neutralen Stellung, parallel zur Erzeugenden der Ogive 24, heraus mittels eines Lenkgebers 25, der seinerseits über eine Navigationseinrichtung 26 angesteuert wird, um mit dem Geschoß 11 dann kurz vor Überfliegen des vorgegebenen Zielpunktes noch aus der flachen Gleitbahn in eine steile Angriffsbahn überzugehen. Aus dieser heraus wird schließlich, dicht über dem Ziel, von einem beispielsweise gegenüber dem umgebenden Gelände abstandsorientiert wirkenden Zünder 27 eine Ausstoßeinrichtung 28 aktiviert, um die Spitzen-Sektion 13 von der Last-Sektion 14 abzutrennen und über diese Trennstelle den Nutzraum 16 unmittelbar ins engere Zielgebiet zu entleeren.Canard sliding wings 23 equipped, which emerge from the contour of the ogive 24, for example by a pivoting movement, as soon as the projectile 11 has flown through its apogee on its initially ballistic launch trajectory. The Canards 23 are used both for gliding and for target control. There is a transition - initially from the ballistic descent path adjoining the apogee - to a stretch-controlled gliding flight in order to achieve a correspondingly greater range as a result of the significantly flatter descent path. At the same time, the specified target point is controlled with the aid of inertial or satellite navigation. This flight guidance takes place by swiveling the sliding wings 23 out of the neutral position, parallel to the generatrix of the ogive 24, by means of a steering transmitter 25, which in turn is controlled via a navigation device 26, so that the projectile 11 then flies over shortly before the predetermined target point is flown over to change from the flat slideway into a steep attack path. Out of this, one becomes, just above the goal For example, in relation to the surrounding area of detonator 27 which acts in a distance-oriented manner, an ejection device 28 is activated in order to separate the tip section 13 from the load section 14 and to empty the useful space 16 directly into the narrower target area via this separation point.
Eine preisgünstige endphasenlenkbare Artillerie-Munition deutlich gesteigerter Reichweite und Akquisitionsgenauigkeit für hinsichtlich variabler Nutzlast universellen Einsatz unter immer gleichem aerodynamischem Verhalten wegen Beibehaltene der außenballistischen Geschoß-Beiwerte ergibt sich also erfindungs- gemäß, wenn bei einem aerodynamisch stabilisierten Gleit-Geschoß 11 zwischen einer anfangs die Außenballistik bestimmenden, standardisierten Heck-Sektion 12 und einer in der Endphase Reichweite und Präzision bestimmenden, ebenfalls standardisierten Spitzen-Sektion 13 eine deren beiden Konturen miteinander verbindende Last-Sektion 14 eingefügt ist, die mit sehr unterschiedlichen, insbeson- dere gegen harte Ziele optimierten Gefechtsköpfen bestückbar ist. Zum Abschuß in eine aerodynamisch stabilisiert ballistische Bahn ist die Heck-Sektion 12 mit überkalibrigen Stabilisierungsflossen 17 ausgestattet, die im Waffenrohr, in Ver- bringungsstellung an die Mantelfläche der Heck-Sektion 12 angelegt, von einer Ringwand 19 übergriffen sind, die mit einem durchrutschenden Führungsband 21 zu erstem Drallabbau bereits im Waffenrohr ausgestattet ist. Vorzugsweise alsbald nach Passieren des Apogäums der ballistischen Bahnkurve werden aus der Spitzen-Sektion 13 Canard-Gleitflügel 23 ausgestellt, mittels derer über einen Lenkgeber 25 ein Übergang aus dem absteigenden Ast der ballistischen Bahnkurve in eine flachere und deshalb weiterreichende Gleitbahn gesteuert wird, aus der her- aus schließlich navigationsgesteuert ein steilerer Abstieg in ein eng vorgegebenesAccording to the invention, an inexpensive artillery ammunition that can be steered in the final phase has a significantly increased range and acquisition accuracy for universal use with regard to variable payloads while always maintaining the same aerodynamic behavior because the external ballistic projectile coefficients are maintained if, in the case of an aerodynamically stabilized sliding projectile 11, the external ballistics initially determining, standardized tail section 12 and in the final phase range and precision determining, likewise standardized tip section 13, a load section 14 connecting their two contours is inserted, which can be equipped with very different warheads, in particular optimized against hard targets is. To launch it into an aerodynamically stabilized ballistic track, the rear section 12 is equipped with over-calibrated stabilizing fins 17, which are placed in the weapon barrel, in the position in which it is placed, on the lateral surface of the rear section 12, overlapped by a ring wall 19, which is slid with a slipping guide band 21 is already equipped in the gun barrel for the first swirl reduction. Immediately after passing the apogee of the ballistic trajectory, 13 canard sliding vanes 23 are issued from the tip section, by means of which a transition from the descending branch of the ballistic trajectory to a flatter and therefore more extensive slideway is controlled via a steering transmitter 25, from which - exclusively a steeper descent into a narrowly specified one, controlled by navigation
Zielgebiet erfolgt, in das die Last-Sektion 14 ihre Nutzlast abgibt. Target area takes place in which the load section 14 delivers its payload.

Claims

Patentansprüche claims
1. Artillerie-Projektil mit austauschbarer Nutzlast, dadurch gekennzeichnet, daß bei einem Geschoß (11) zwischen einer standardisierten Heck-Sektion (12) und einer standardisierten Spitzen-Sektion (13) die Außenkonturen die- ser beiden Standard-Sektionen (12,13) miteinander verbindend eine austauschbare, mit unterschiedlichen Nutzlasten bestückbare Last-Sektion (14) angeordnet ist.1. Artillery projectile with interchangeable payload, characterized in that the outer contours of these two standard sections (12, 13.) On a projectile (11) between a standardized rear section (12) and a standardized tip section (13) ) connecting an interchangeable load section (14) which can be equipped with different payloads.
2. Projektil nach Anspruch 1, dadurch gekennzeichnet, daß die Heck-Sektion (12) den Geschoß-Boden und überkalibrig radial ausstellbare Stabilisierungsflossen (17) enthält.2. Projectile according to claim 1, characterized in that the rear section (12) contains the floor and over-calibrated radially deployable stabilizing fins (17).
3. Projektil nach Anspruch 2, dadurch gekennzeichnet, daß die Heck-Sektion (12) bei an deren Außenmantelfläche angelegten Stabilisierungsflossen (17) von einer Ringwand (19) umgeben ist, die sich beim Abschuß aus dem Waffenrohr unter Freigabe des Aufstellens der Stabilisierungsflossen (17) achsparallel nach rückwärts vom Heck des Geschosses (11) abzieht.3. Projectile according to claim 2, characterized in that the rear section (12) is surrounded by stabilizing fins (17) applied to the outer lateral surface thereof by an annular wall (19) which, when fired from the weapon barrel, releases the setting up of the stabilizing fins ( 17) pulls backwards axially parallel from the rear of the projectile (11).
4. Projektil nach Anspruch 3, dadurch gekennzeichnet, daß die Ringwand (19) von einem Führungsband (21) umgeben ist.4. Projectile according to claim 3, characterized in that the ring wall (19) is surrounded by a guide band (21).
5. Projektil nach Anspruch 4, dadurch gekennzeichnet, daß das Führungsband (21) in eine die Ringwand (19) umgebenden Nut (20) kontrolliert durchrutschbar eingelegt ist. 5. Projectile according to claim 4, characterized in that the guide band (21) in a ring wall (19) surrounding groove (20) is inserted in a controlled slip.
6. Projektil nach einem der Ansprüche 3 bis 5, dadurch gekennzeichnet, daß die Ringwand (19) die Wandung einer topfförmigen Haube (18) ist, die heckseitig auf die Heck-Sektion (12) mit an deren Wandung angeklappten6. Projectile according to one of claims 3 to 5, characterized in that the annular wall (19) is the wall of a cup-shaped hood (18), the rear of the rear section (12) with the wall folded
Stabilisierungsflossen (17) aufgeschoben ist.Stabilizing fins (17) is pushed on.
7. Projektil nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, daß die Spitzen-Sektion (13) mit aus der Kontur der Ogive (24) ausstellbaren Gleitflügeln (23) ausgestattet ist.7. Projectile according to one of the preceding claims, characterized in that the tip section (13) is equipped with sliding wings (23) which can be extended from the contour of the ogive (24).
8. Projektil nach Anspruch 7, dadurch gekennzeichnet, daß in der Spitzen-Sektion (13) ein navigationsgeführter Lenkgeber (25) für8. Projectile according to claim 7, characterized in that in the tip section (13) a navigation-guided steering sensor (25) for
Canard-Gleitflügel (23) vorgesehen ist.Canard sliding wing (23) is provided.
9. Projektil nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, daß in der Spitzen-Sektion (13) eine von einem Zünder (27) aktivierbare9. Projectile according to one of the preceding claims, characterized in that in the tip section (13) one of an igniter (27) can be activated
Trenneinrichtung (28) zum Freigeben einer Auswurföffnung unter Aufsprengen einer Verbindung zwischen der Last-Sektion (14) und der Spitzen- Sektion (13) vorgesehen ist. Separating device (28) for releasing an ejection opening by blowing open a connection between the load section (14) and the tip section (13) is provided.
EP02754685A 2001-06-23 2002-06-15 Artillery projectile comprising an interchangeable payload Expired - Lifetime EP1399706B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE10130383A DE10130383A1 (en) 2001-06-23 2001-06-23 Artillery projectile with interchangeable payload
DE10130383 2001-06-23
PCT/EP2002/006623 WO2003001141A1 (en) 2001-06-23 2002-06-15 Artillery projectile comprising an interchangeable payload

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EP1399706A1 true EP1399706A1 (en) 2004-03-24
EP1399706B1 EP1399706B1 (en) 2005-09-21

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US (1) US20040200375A1 (en)
EP (1) EP1399706B1 (en)
KR (1) KR100796706B1 (en)
AT (1) ATE305128T1 (en)
DE (2) DE10130383A1 (en)
IL (1) IL159502A0 (en)
WO (1) WO2003001141A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7506587B1 (en) 2007-02-20 2009-03-24 The United States Of Americas As Represented By The Secretary Of The Navy Modular projectile system

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6978967B1 (en) * 2003-04-25 2005-12-27 The United States Of America As Represented By The Secretary Of The Army Space saving fin deployment system for munitions and missiles
WO2006088687A1 (en) * 2005-02-07 2006-08-24 Bae Systems Information And Electronic Systems Integration Inc. Optically guided munition
SE528624C2 (en) * 2005-11-15 2007-01-09 Bae Systems Bofors Ab Increasing a range of trajectory shells for explosive substances by utilizing folding/fixed rear guide fins with specified radial extent range and folding/fixed front steerable so-called canard fins with aerodynamic bearing surfaces
FR2910122B1 (en) * 2006-12-15 2009-03-06 Thales Sa DEPLOYABLE CARRIER EMPLOYING DEVICE FOR OBUS
EP2109752B1 (en) 2007-01-12 2014-03-05 Raytheon Company Methods and apparatus for weapon fuze
DK2391863T3 (en) 2009-02-02 2020-08-24 Aerovironment Inc MULTIMODAL DRIVERLESS AIRCRAFT
US20120068002A1 (en) * 2009-05-19 2012-03-22 Unger Michael P Guided missile
KR101098114B1 (en) * 2009-07-06 2011-12-26 주식회사 풍산 Dual Warhead Bombshell
CN105151275B (en) * 2009-09-09 2017-05-31 威罗门飞行公司 Elevon control system
CA2789722C (en) 2009-09-09 2018-08-28 Aerovironment, Inc. Systems and devices for remotely operated unmanned aerial vehicle report-suppressing launcher with portable rf transparent launch tube
US8671839B2 (en) 2011-11-04 2014-03-18 Joseph M. Bunczk Projectile and munition including projectile
US9593922B2 (en) * 2013-03-14 2017-03-14 Bae Systems Land & Armaments L.P. Fin deployment system
US9194677B1 (en) * 2013-03-26 2015-11-24 Raytheon Company Projectile with aft obturating device
DE102017105565A1 (en) * 2017-03-15 2018-09-20 Rheinmetall Waffe Munition Gmbh Ammunition and logistics concept for in particular artillery projectiles
FR3080912B1 (en) 2018-05-02 2020-04-03 Nexter Munitions PROJECTILE POWERED BY STATOREACTOR
KR102081885B1 (en) 2018-06-19 2020-02-26 주식회사 풍산 Unfolding wings apparatus of folding blade
JP7456371B2 (en) * 2020-12-23 2024-03-27 三菱電機株式会社 Radome for flying objects, manufacturing method of radome for flying objects

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5439188A (en) * 1964-09-04 1995-08-08 Hughes Missile Systems Company Control system
US4364530A (en) * 1980-09-08 1982-12-21 The United States Of America As Represented By The Secretary Of The Navy Propulsion/control modular booster
DE3334023A1 (en) * 1983-09-21 1985-04-04 Mauser-Werke Oberndorf Gmbh, 7238 Oberndorf BULLET BODY WITH PLASTIC GUIDE BAND
FR2654822B1 (en) * 1987-03-17 1993-04-23 Thomson Brandt Armements DISPENSER OF SUB-PROJECTILES.
US4899956A (en) * 1988-07-20 1990-02-13 Teleflex, Incorporated Self-contained supplemental guidance module for projectile weapons
GB9225589D0 (en) * 1992-12-08 2003-04-16 Royal Ordnance Plc Improvements in or relating to general purpose bombs
EP0794405B1 (en) * 1996-03-08 2001-09-05 Diehl Stiftung & Co. Method and device for dispersing a large caliber payload above a target
US6126109A (en) * 1997-04-11 2000-10-03 Raytheon Company Unlocking tail fin assembly for guided projectiles
DE19740888C2 (en) * 1997-09-17 1999-09-02 Rheinmetall W & M Gmbh Method for autonomously steering a spin-stabilized artillery projectile and autonomously guided artillery projectile for carrying out the method
US6408762B1 (en) * 1997-12-11 2002-06-25 Lockheed Martin Corporation Clamp assembly for shrouded aerial bomb
US6227119B1 (en) * 1998-10-30 2001-05-08 Lockheed Martin Corporation Lightweight warhead assembly
DE19917189A1 (en) * 1999-04-16 2000-10-19 Diehl Stiftung & Co Warhead comprises submunition stacked in a chamber, and an expulsion system located between the submunition chambers.
US6227096B1 (en) * 1999-06-22 2001-05-08 The Boeing Company Universal warhead adapter, and missile and method incorporating same
DE19944379B4 (en) * 1999-09-16 2007-05-16 Rheinmetall Waffe Munition cartridge
SE518665C2 (en) * 2000-03-21 2002-11-05 Bofors Weapon Sys Ab Fine stabilized artillery grenade
SE518654C2 (en) * 2000-07-03 2002-11-05 Bofors Defence Ab Methods and apparatus for artillery projectiles
SE518656C2 (en) * 2000-07-03 2002-11-05 Bofors Defence Ab Fine stabilized artillery grenade
SE519757C2 (en) * 2000-08-15 2003-04-08 Bofors Defence Ab Controllable artillery projectile with extremely long range
US6502786B2 (en) * 2001-02-01 2003-01-07 United Defense, L.P. 2-D projectile trajectory corrector

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO03001141A1 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7506587B1 (en) 2007-02-20 2009-03-24 The United States Of Americas As Represented By The Secretary Of The Navy Modular projectile system

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WO2003001141A1 (en) 2003-01-03
IL159502A0 (en) 2004-06-01
US20040200375A1 (en) 2004-10-14
EP1399706B1 (en) 2005-09-21
KR20040011552A (en) 2004-02-05
KR100796706B1 (en) 2008-01-21
DE50204329D1 (en) 2006-02-02
DE10130383A1 (en) 2003-01-09
ATE305128T1 (en) 2005-10-15

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