EP1538417B1 - Multilayer armour plating material and process for making it - Google Patents

Multilayer armour plating material and process for making it Download PDF

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Publication number
EP1538417B1
EP1538417B1 EP03027995A EP03027995A EP1538417B1 EP 1538417 B1 EP1538417 B1 EP 1538417B1 EP 03027995 A EP03027995 A EP 03027995A EP 03027995 A EP03027995 A EP 03027995A EP 1538417 B1 EP1538417 B1 EP 1538417B1
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EP
European Patent Office
Prior art keywords
ceramic
layer
support layer
protection material
carbon
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Revoked
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EP03027995A
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German (de)
French (fr)
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EP1538417A1 (en
Inventor
Eugen Pfitzmaier
Bodo Dipl.-Ing. Benitsch
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SGL Carbon SE
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SGL Carbon SE
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Application filed by SGL Carbon SE filed Critical SGL Carbon SE
Priority to EP03027995A priority Critical patent/EP1538417B1/en
Priority to DE50309268T priority patent/DE50309268D1/en
Priority to ES03027995T priority patent/ES2302526T3/en
Priority to AT03027995T priority patent/ATE387618T1/en
Priority to US10/999,438 priority patent/US20090324966A1/en
Publication of EP1538417A1 publication Critical patent/EP1538417A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
    • F41H5/00—Armour; Armour plates
    • F41H5/02—Plate construction
    • F41H5/04—Plate construction composed of more than one layer
    • F41H5/0414—Layered armour containing ceramic material
    • F41H5/0428—Ceramic layers in combination with additional layers made of fibres, fabrics or plastics
    • F41H5/0435—Ceramic layers in combination with additional layers made of fibres, fabrics or plastics the additional layers being only fibre- or fabric-reinforced layers
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/23—Sheet including cover or casing
    • Y10T428/239—Complete cover or casing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24058—Structurally defined web or sheet [e.g., overall dimension, etc.] including grain, strips, or filamentary elements in respective layers or components in angular relation
    • Y10T428/24124—Fibers
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24479—Structurally defined web or sheet [e.g., overall dimension, etc.] including variation in thickness
    • Y10T428/24521—Structurally defined web or sheet [e.g., overall dimension, etc.] including variation in thickness with component conforming to contour of nonplanar surface
    • Y10T428/24529—Structurally defined web or sheet [e.g., overall dimension, etc.] including variation in thickness with component conforming to contour of nonplanar surface and conforming component on an opposite nonplanar surface
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24628—Nonplanar uniform thickness material

Definitions

  • the invention relates to a multilayer armor protection material consisting of a single or multilayer ceramic or metallic layer, seen in the direction of fire rear support layer of carbon fiber reinforced plastic (CFRP) and seen in the direction of fire front support layer of carbon fiber reinforced plastic (CFRP), according to claim 1 and a Process for its preparation according to claim 14.
  • CFRP carbon fiber reinforced plastic
  • Antitank material can protect terrestrial and airworthy vehicles such as airplanes, helicopters and satellites as well as potentially endangered persons against impact or ballistic threats.
  • armor protection materials with a favorable mass-protection ratio are particularly advantageous.
  • a bullet-resistant plate material is described, with a front layer of hexagonal ceramic plates, which, viewed in the direction of firing, is followed by a first hard laminate layer of compacted FRP material. With the interposition of an adhesive film, a second laminate layer of FRP material is provided which is softer than the first laminate layer.
  • the ceramic layer By the rear, acting as a support layer hard laminate layer, the ceramic layer should be supported when it is penetrated by a projectile or resulting from impact bullet fragments. The subordinate, softer laminate layer should catch the bullet or the bullet fragments as a catch layer without tearing it.
  • EP 1 288 607 A1 which forms a basis for claims 1 and 14, discloses a multi-layered armor protective material comprising a monolithic ceramic layer, an antiballistic backing material attached to the ceramic layer, and an outer shell of an antiballistic material enclosing the backing layer and the ceramic layer containing a curable resin.
  • the outer shell 16 which completely surrounds the composite structure of ceramic and backing, serves to enclose the backing-bonded ceramic antiballistic material in a compressed state. Thanks to this cover, the ceramic / backing composite also withstands multiple bombardment.
  • the outer shell 16, like the backing 14, is made of an antiballistic material. Suitable materials include antiballistic quality fibers, ie high extensibility, elastic deformability and relatively high modulus eg Aramid, Zylon® or special glass fibers soaked with a suitable amount of resin.
  • the solutions are based on a combination of a ceramic layer and a fabric-based backing, such as aramid or dyneema.
  • a fabric-based backing such as aramid or dyneema.
  • the minimum possible hit distance of such systems is above the desired and achievable with steel.
  • the reason for this is the limited shear strength of the adhesive between the ceramic and the fabric and, secondly, the damage to the ceramic and the associated decrease in the rigidity of the overall system in the event of repeated impact of projectiles.
  • the rigidity to projectiles with high kinetic energy and high hardness is often no longer sufficient.
  • the invention is based on the object to further develop a multi-layered armor protection material of the type mentioned in that it ensures a higher protection performance, in particular with multiple firing with the lowest possible weight.
  • a cost-effective method for its production is to be provided.
  • a front support layer of carbon fiber reinforced plastic (CFRP) is disposed upstream
  • the steel or ceramic layer between the front and the rear support layer is optimally embedded and supported in a composite.
  • this protects the ceramic or steel material from damaging vibrations caused by repeated impact of projectiles, in that the higher stiffness of the structure reduces the vibration amplitudes.
  • a particular advantage of the carbon fiber reinforced plastic (CFRP) existing support layers is also in their adaptability to curved or angled surfaces, so that the armor material of the invention can be used universally, to protect arbitrarily shaped surfaces.
  • the rear support layer made of carbon fiber reinforced plastic and / or on the surface facing away from the impact stress surface of the ceramic or metallic layer
  • the rear support layer of carbon fiber reinforced plastic is applied to the shearing stress facing surface of the ceramic or metallic layer by carbon fiber fabric to Training with binder impregnated fiber mats (prepregs or wet laminates) with a binder, in particular impregnated with a binder resin, and the impregnated prepregs or wet laminates cured during a curing period thermally and / or by electromagnetic radiation and at least during a part of the curing period against one or both surfaces of the ceramic or metallic layer are pressed.
  • the curing binder of the fibrous mats arranged on both sides provide a material bond with the surface of the ceramic or steel layer, without the need for an additional adhesive.
  • the two-sided pressing can advantageously apply both support layers, the front and rear support layers, to the ceramic or steel layer during a single process step.
  • the ceramic or metallic layer of the front support layer and the rear support layer is complete sheathed, especially at the end faces.
  • a particularly rigid and firm cohesion of the composite is given in an advantageous manner.
  • Another advantage is the use of carbon fiber reinforced plastic for the front and / or the rear support layer, even if the ceramic or metallic layer at least locally deviates from a flat plate and has a curvature and / or angling and / or if the layer thickness of the ceramic or metallic layer is variable.
  • the fiber plastics which are usually based on fibers, knitted fabrics or knitted fabrics, can easily be adapted to uneven shapes before curing.
  • the carbon fiber reinforced plastic includes a unidirectional scrim of 90 degree staggered layers of parallel fibers.
  • the front support layer and / or the rear support layer has a volume-related carbon of at least 10%.
  • the matrix of the front support layer and / or the rear support layer consists of a thermally and / or by electromagnetic radiation curable polymer, for example of a phenolic resin.
  • this may comprise a monolithic ceramic, for example of aluminum oxide or silicon carbide.
  • a fiber-reinforced ceramic can be used.
  • a sintered ceramic or a ceramic produced by infiltration with liquid silicon is used.
  • Fiber-reinforced ceramics may preferably be so-called C / SiC materials, in which preferably carbon-based fibers, in particular carbon fibers or graphite fibers are bonded in a matrix formed predominantly of SiC, Si and C.
  • the C / SiC composite ceramics may also comprise other high temperature resistant fibers which contain, in addition to carbon, other elements such as Si, B, N, O or Ti.
  • the procedure for the production of C / SiC material is characterized in that first a CFC material is formed.
  • CFRP carbon fiber reinforced plastics
  • CFRP carbon fiber reinforced plastics
  • This shaped body is manufactured in the present case as a thin plate with the desired thickness.
  • the base material is not limited to CFC materials.
  • Other temperature-stable ceramic fibers in particular those based on SiO 2 , Al 2 O 3 , ZrO 2 , or SiC, which have been coated with carbon or graphite, may likewise be used as the fiber material.
  • the carbon fiber reinforced carbon material plate material is then infiltrated with a silicon melt or silicon alloy melt at temperatures of about 1600 ° C in vacuum or under inert gas, thereby converting at least a portion of the carbon of the matrix and / or fibers into SiC.
  • a silicon melt or silicon alloy melt at temperatures of about 1600 ° C in vacuum or under inert gas, thereby converting at least a portion of the carbon of the matrix and / or fibers into SiC.
  • the metals of subgroups I to VIII can also be used as further constituents of the melt, in particular Ti, Cr, Fe, Mo, B and Ni.
  • the liquid infiltration of the CFC molded body produces a dense, solid and very hard shaped body of C / SiC material containing fibers, generally carbon fibers, with a matrix of predominantly SiC, Si and C.
  • the matrix of the molded article may be wholly or partially generated by gas phase infiltration (CVD or CVI). Then the matrix has a relatively high SiC content, typically over 95%.
  • the preparation of the matrix can be carried out by the pyrolysis of Si-containing, preceramic polymers, such as those produced by the pyrolysis of polymers containing one or more of the elements Si, B, C, N, P or Ti.
  • Preferred applications of the armor protection material according to the invention relate to ballistic protection in land, air and water vehicles, as a deposit or integral part of protective vests and as a satellite shield. In all these applications is especially the low weight of Carbon fiber reinforced plastic advantageous.
  • a satellite shield especially a ceramic based on C / SiC material because of the high temperature resistance of advantage.
  • the back support layer in particular a aluminum, aramid or Dyneema-containing collecting layer.
  • four layers, namely the front support layer, the ceramic or steel layer, the back support layer and the trap layer can be joined together with a single pressing operation, wherein in each case by the curing binder of the front and rear support layer forming prepreg of the material bond between the individual layers comes about.
  • individual or all of the layers mentioned can also be glued together by means of liquid adhesive or adhesive film.
  • an approximately 12 mm thick, reinforced with carbon fibers ceramic plate 2 in particular a plate of a C / SiC composite ceramic with the dimensions 350 mm x 400 mm on the of the attack stress facing away surface with 12 layers of a unidirectional scrim of offset by 90 degrees to each other arranged layers of parallel carbon fibers directly occupied.
  • the Beschussbe pipeung facing surface of the ceramic plate 2 layers of preferably the same unidirectional Geleges be brought directly to the plant.
  • Both scrims are impregnated prior to or simultaneously with the laying on the ceramic layer 2 with a thermally and / or by electromagnetic radiation curable polymer, in particular with a phenolic resin as a binder to form impregnated with the binder pulp mats, so-called.
  • a thermally and / or by electromagnetic radiation curable polymer in particular with a phenolic resin as a binder to form impregnated with the binder pulp mats, so-called.
  • Prepregs in which the matrix consists of the polymer.
  • Curing of the prepregs to CFK preferably takes place by means of a customary autoclave process in which the impregnated prepreg enclosing the ceramic layer 2 is hardened, for example under a curing temperature in a range between 50 ° C to 180 ° C and under pressing against the ceramic layer become.
  • a curing temperature in a range between 50 ° C to 180 ° C and under pressing against the ceramic layer become.
  • an adhesion of the prepregs with the surfaces of the ceramic layer 2 is formed by the initially viscous binder penetrating into the rough surface structure of the ceramic layer and solidifying or hardening after some time.
  • the hardened prepreg upstream of the ceramic layer in the direction of bombing forms a front support layer 4 and the hardened prepreg downstream of the ceramic layer 2 in the direction of bombardment forms a rear support layer 6.
  • the ceramic layer can be completely encased by the front support layer and the rear support layer, in particular at the end faces.
  • a catching layer 8 in particular comprising aluminum, aramid or dyneema, having a thickness of approximately 10 mm, is simultaneously applied to the surface of the rear support layer facing away from the impact stress.
  • four layers namely, the front support layer 4, the ceramic or steel layer 2, the back support layer 6 and the trap layer 8 can be joined together with a single pressing operation.
  • the pressing and curing process is restricted to the front support layer 4, the ceramic layer 2 and the back support layer 8.
  • the collecting layer 8 in the form of an approximately 10 mm thick backing of aramid fabric can also be glued onto the thus prepared laminated body.
  • the front support layer 4 and / or the rear support layer 6 and possibly also the backing 8 can also be deviated from a flat ceramic layer 2 to a curvature and / or at least locally deviating from a flat plate a ceramic layer 2 having a bend and / or varying with respect to the layer thickness can be applied.
  • the armor material had a basis weight of less than 45 kg / m 2 and was tested in bombardment tests according to the fire class FB 7.
  • the results showed a significant increase in rigidity compared to armor without front, glass or carbon fiber reinforced support layer 4.
  • the primary, but especially the secondary damage in the ceramic plate caused by the impact of the projectile were greatly reduced.
  • the stresses on the adhesive bond between the back support layer 6 and the backing 8 could be reduced so that the otherwise observed partial or full-scale detachment of the backing 8 remained, whereby the armor material 1 remained intact even with multiple firing and the multihit behavior has been greatly improved.
  • Overall not only the surface weight-related protection performance was increased by the measures mentioned, but it was also the adhesion of the backing 8 at the rest of the ballistic system can be significantly improved.
  • the carbon fiber reinforced ceramic plate 2 of the preferred embodiment has been replaced by a monolithic ceramic plate made of, for example, alumina.
  • the dimensions of the ceramic were about 250 mm x 350 mm, the thickness 8 mm.
  • a development of the embodiment described above was to replace the carbon fiber reinforced ceramic plate 2 by a plate of ballistic steel with a thickness of about 8 mm.
  • the ceramic layer 2 of the armor material 1 was constructed from individual ceramic tiles with the dimensions 20 mm x 20 mm x 8 mm, which were placed in a known manner for ballistic systems together to a ceramic structure with the dimension of 300 mm x 300 mm to build.
  • the ceramic layer 2 was curved and in particular adapted in geometry to the wheel arch of a motor vehicle, wherein the front and rear support layer 4, 6 are made of flexible fiber-readily adaptable to this curved shape before curing.
  • curved, based on a ceramic layer 2 tank material 1 was produced as a deposit of a protective or bulletproof vest.
  • the overall protection system as a combination of liner and westliner was tested as described above, with the result correspondingly positive.
  • Backing 8 a Dyneema clutch. Also conceivable is a front and / or rear support layer 4, 6 made of a hybrid fabric constructed with carbon and aramid fibers or with carbon and glass fibers.

Abstract

The multilayered armor plate for protection against impacts, projectiles and the like comprises a ceramic or metal layer (2) which is provided with a front support layer (4) consisting of glass fiber and/or carbon fiber reinforced plastic materials. Independent claims are also included for: (A) applications of the proposed armor plate in vehicles, vessels, aircraft and spacecraft, as well as in protective vests; (B) a method for producing such an armor plate.

Description

Stand der TechnikState of the art

Die Erfindung betrifft ein mehrschichtiges Panzerschutzmaterial bestehend aus einer ein- oder vielstückigen keramischen oder metallischen Schicht, einer in Beschussrichtung gesehen hinteren Stützschicht aus kohlenstofffaserverstärktem Kunststoff (CFK) und einer in Beschussrichtung gesehen vorderen Stützschicht aus kohlenstofffaserverstärktem Kunststoff (CFK), gemäß dem Anspruch 1 sowie ein Verfahren zu seiner Herstellung gemäß dem Anspruch 14.The invention relates to a multilayer armor protection material consisting of a single or multilayer ceramic or metallic layer, seen in the direction of fire rear support layer of carbon fiber reinforced plastic (CFRP) and seen in the direction of fire front support layer of carbon fiber reinforced plastic (CFRP), according to claim 1 and a Process for its preparation according to claim 14.

Durch Panzerschutzmaterial können terrestrische und flugfähige Fahrzeuge wie beispielsweise Flugzeuge, Helikopter und Satelliten sowie potentiell gefährdete Personen gegen Impact bzw. ballistische Bedrohungen geschützt werden. Im Bereich der Luft- und Raumfahrt sind vor allem Panzerschutzmaterialien mit einem günstigen Masse-Schutz-Verhältnis von Vorteil. Zur Zerstörung der Projektile sind im Bereich des zivilen terrestrischen Fahrzeugschutzes insbesondere auf speziellen Stahlsorten basierende Schichten im Einsatz, während im militärischen, wie auch im Bereich des Personenschutzes keramische Schichten verwendet werden.Antitank material can protect terrestrial and airworthy vehicles such as airplanes, helicopters and satellites as well as potentially endangered persons against impact or ballistic threats. In the field of aerospace, armor protection materials with a favorable mass-protection ratio are particularly advantageous. For the destruction of the projectiles in the field of civilian terrestrial vehicle protection in particular on special steel grades based layers in use, while in the military, as well as in the field of personal protection ceramic layers are used.

Auf Keramik basierendes Panzerschutzmaterial weist gegenüber Stahllösungen ein geringeres Flächengewicht bei gleicher Schutzleistung auf. Dem steht das bessere Multi-Hit-Verhalten des Stahls entgegen. Darunter versteht man den Erhalt der projektilstoppenden Eigenschaften bei mehrfachem Impact in geringen Trefferabständen. Bei Panzerschutzmaterial mit Stahlschicht liegen diese Abstände typischerweise im Bereich von Abständen, die dem dreifachen Durchmesser des Geschosses entsprechen. Bei Verwendung einer keramischen Schicht liegt der tolerierbare Trefferabstand etwa im Bereich des 8- bis 10-fachen des Durchmessers des Geschosses.On ceramic-based armor protection material has compared to steel solutions on a lower basis weight with the same protection performance. This is opposed by the better multi-hit behavior of the steel. By this one understands the preservation of the project stopping properties with multiple impact in small hit distances. In the case of armored steel-clad material, these distances are typically in the range of distances equal to three times the diameter of the projectile. When using a ceramic layer, the tolerable hit distance is approximately in the range of 8 to 10 times the diameter of the projectile.

Allen Lösungen, bei denen das Geschoss bzw. der Geschosskern zunächst gebrochen werden muss, ist gemein, dass sie aus mindestens zwei Schichten mit unterschiedlichen Funktionen bestehen. Dabei hat eine vordere, der Beschussbeanspruchung zugewandte Schicht, welche beispielsweise aus Stahl oder Keramik besteht, die Aufgabe, das Geschoss weitestgehend zu zersplittern. Eine weitere Schicht, das sogenannte Backing übernimmt die Funktion des Auffangens von Geschosssplittern, sowie die Absorption der restlichen kinetischen Energie. Die Schichten können einander unmittelbar kontaktieren und sind miteinander verklebt oder sie stehen in einem geschotteten System in definiertem Abstand zueinander.All solutions in which the projectile or bullet core must first be broken, have in common that they consist of at least two layers with different functions. In this case, a front, the Beschussbeanspruchung facing layer, which consists for example of steel or ceramic, has the task of splitting the projectile as far as possible. Another layer, the so-called backing, performs the function of collecting bullet fragments, as well as the absorption of the remaining kinetic energy. The layers can contact each other directly and are glued together or they are in a partitioned system at a defined distance from each other.

In der gattungsbildenden DE 41 14 809 A1 ist ein geschoßfestes Plattenmaterial beschrieben, mit einer Frontschicht aus sechseckförmigen Keramikplatten, welcher in Beschussrichtung gesehen eine erste harte Laminatlage aus verdichtetem GFK-Material nachgeordnet ist. Unter Zwischenfügung einer Klebefolie wird eine zweite Laminatlage aus GFK-Material vorgesehen, die gegenüber der ersten Laminatlage weicher ist. Durch die hintere, als Stützschicht wirkende harte Laminatlage soll die Keramikschicht abgestützt werden, wenn diese von einem Geschoss bzw. von beim Aufschlag entstehenden Geschosssplittern durchschlagen wird. Die nachgeordnete, weichere Laminatlage soll als Fangschicht das Geschoss bzw. die Geschosssplitter auffangen, ohne dabei zu zerreißen.In the generic DE 41 14 809 A1 a bullet-resistant plate material is described, with a front layer of hexagonal ceramic plates, which, viewed in the direction of firing, is followed by a first hard laminate layer of compacted FRP material. With the interposition of an adhesive film, a second laminate layer of FRP material is provided which is softer than the first laminate layer. By the rear, acting as a support layer hard laminate layer, the ceramic layer should be supported when it is penetrated by a projectile or resulting from impact bullet fragments. The subordinate, softer laminate layer should catch the bullet or the bullet fragments as a catch layer without tearing it.

EP 1 288 607 A1 , die eine Grundlage für die Ansprüche 1 und 14 bildet, offenbart ein mehrschichtiges Panzerschutzmaterial umfassend eine monolithische keramische Schicht, ein an der keramischen Schicht befestigtes antiballistisches Backing-Material und eine äußere, die Backing-Schicht und die keramische Schicht umschließende Hülle aus einem antiballistischen Material, welches ein härtbares Harz enthält. Die äußere Hülle 16, welche die Verbundstrukur aus Keramik und Backing komplett umgibt, dient dem Einschluss des mit einem Backing verbundenen keramischen antiballistischen Materials in einem verpressten Zustand. Dank dieser Hülle hält den Keramik/Backing-Verbund auch einem Mehrfachbeschuss stand. Die äußere Hülle 16 besteht -ebenso wie das Backing 14- aus einem antiballistischen Material. Geeignete Materialien umfassen Fasern mit antiballistischer Qualität, d.h. hoher Dehnbarkeit, elastischer Verformbarkeit und relativ hohem Modul z.B. Aramid, Zylon® oder spezielle Glasfasern, getränkt mit einer passenden Menge Harz. EP 1 288 607 A1 , which forms a basis for claims 1 and 14, discloses a multi-layered armor protective material comprising a monolithic ceramic layer, an antiballistic backing material attached to the ceramic layer, and an outer shell of an antiballistic material enclosing the backing layer and the ceramic layer containing a curable resin. The outer shell 16, which completely surrounds the composite structure of ceramic and backing, serves to enclose the backing-bonded ceramic antiballistic material in a compressed state. Thanks to this cover, the ceramic / backing composite also withstands multiple bombardment. The outer shell 16, like the backing 14, is made of an antiballistic material. Suitable materials include antiballistic quality fibers, ie high extensibility, elastic deformability and relatively high modulus eg Aramid, Zylon® or special glass fibers soaked with a suitable amount of resin.

Häufig basieren bei gewichtsoptimierten Ansätzen die Lösungen auf einer Kombination einer Keramikschicht und einem Backing auf Gewebebasis beispielsweise aus Aramid oder Dyneema. Der minimal mögliche Trefferabstand solcher Systeme liegt jedoch über dem angestrebten und mit Stahl realisierbaren. Grund ist zum einem die begrenzte Scherfestigkeit des Klebers zwischen Keramik und dem Gewebe und zum anderen die Schädigung der Keramik und die damit verbundene Abnahme der Steifigkeit des Gesamtsystems bei wiederholtem Auftreffen von Geschossen. Weiterhin reicht auch bei Verwendung von Stahlschichten die Steifigkeit gegenüber Geschossen mit hoher kinetischer Energie und hoher Härte oft nicht mehr aus.Often, in weight-optimized approaches, the solutions are based on a combination of a ceramic layer and a fabric-based backing, such as aramid or dyneema. However, the minimum possible hit distance of such systems is above the desired and achievable with steel. The reason for this is the limited shear strength of the adhesive between the ceramic and the fabric and, secondly, the damage to the ceramic and the associated decrease in the rigidity of the overall system in the event of repeated impact of projectiles. Furthermore, even when steel layers are used, the rigidity to projectiles with high kinetic energy and high hardness is often no longer sufficient.

Aufgabe der ErfindungObject of the invention

Der Erfindung liegt demgegenüber die Aufgabe zugrunde, ein mehrschichtiges Panzerschutzmaterial der eingangs erwähnten Art derart weiter zu entwickeln, dass es bei möglichst geringem Gewicht eine höhere Schutzleistung insbesondere bei Mehrfachbeschuss gewährleistet. Außerdem soll ein kostengünstiges Verfahren zu seiner Herstellung bereitgestellt werden.The invention is based on the object to further develop a multi-layered armor protection material of the type mentioned in that it ensures a higher protection performance, in particular with multiple firing with the lowest possible weight. In addition, a cost-effective method for its production is to be provided.

Diese Aufgabe wird erfindungsgemäß durch die kennzeichnenden Merkmale von Anspruch 1 und die kennzeichnenden Merkmale von Anspruch 14 gelöst.This object is achieved by the characterizing features of claim 1 and the characterizing features of claim 14.

Vorteile der ErfindungAdvantages of the invention

Indem gemäß Anspruch 1 der keramischen oder metallischen Schicht in Beschussrichtung gesehen eine vordere Stützschicht aus kohlenstofffaserverstärktem Kunststoff (CFK) vorgeordnet ist, wird die Stahl- oder Keramikschicht zwischen der vorderen und der hinteren Stützschicht optimal in einen Verbund eingebettet und abgestützt. Dies schützt insbesondere das Keramik- oder Stahlmaterial vor schädlichen, durch einen wiederholten Impact von Geschossen hervorgerufenen Schwingungen, indem die höhere Steifigkeit der Struktur die Schwingungsamplituden reduziert. Ein besonderer Vorteil der aus kohlenstofffaserverstärktem Kunststoff (CFK) bestehenden Stützschichten liegt außerdem in deren Anpassungsfähigkeit an gekrümmte oder abgewinkelte Flächen, so dass das erfindungsgemäße Panzermaterial universell, zum Schutz beliebig geformter Oberflächen einsetzbar ist.By according to claim 1 of the ceramic or metallic layer seen in the direction of firing a front support layer of carbon fiber reinforced plastic (CFRP) is disposed upstream, the steel or ceramic layer between the front and the rear support layer is optimally embedded and supported in a composite. In particular, this protects the ceramic or steel material from damaging vibrations caused by repeated impact of projectiles, in that the higher stiffness of the structure reduces the vibration amplitudes. A particular advantage of the carbon fiber reinforced plastic (CFRP) existing support layers is also in their adaptability to curved or angled surfaces, so that the armor material of the invention can be used universally, to protect arbitrarily shaped surfaces.

Gemäß dem Herstellungsverfahren von Anspruch 14 wird auf die der Beschussbeanspruchung zugewandte Oberfläche der keramischen oder metallischen Schicht die vordere Stützschicht aus kohlenstofffaserverstärktem Kunststoff und/oder auf die von der Beschussbeanspruchung abgewandte Oberfläche der keramischen oder metallischen Schicht die hintere Stützschicht aus kohlenstofffaserverstärktem Kunststoff aufgebracht, indem Kohlenstofffasergewebe zur Ausbildung mit Binder imprägnierter Faserstoffmatten (Prepregs bzw. Nasslaminate) mit einem Binder, insbesondere mit einem Binderharz imprägniert werden, und die imprägnierten Prepregs bzw. Nasslaminate während eines Aushärtezeitraums thermisch und/oder durch elektromagnetische Strahlung ausgehärtet und zumindest während eines Teils des Aushärtezeitraums gegen eine oder beide Oberflächen der keramischen oder metallischen Schicht gepresst werden. Hierdurch wird ein Heißpressprozess verwirklicht, bei welchem der aushärtende Binder der beidseitig angeordneten Faserstoffmatten für einen Stoffschluss mit der Oberfläche der Keramik- bzw. der Stahlschicht sorgen, ohne dass zusätzlich ein Klebstoff verwendet werden müsste. Durch das beidseitige Pressen können außerdem in vorteilhafter Weise während eines einzigen Verfahrensschritts beide Stützschichten, die vordere und die hintere Stützschicht auf die Keramik- bzw. Stahlschicht aufgebracht werden.According to the manufacturing method of claim 14, the rear support layer made of carbon fiber reinforced plastic and / or on the surface facing away from the impact stress surface of the ceramic or metallic layer, the rear support layer of carbon fiber reinforced plastic is applied to the shearing stress facing surface of the ceramic or metallic layer by carbon fiber fabric to Training with binder impregnated fiber mats (prepregs or wet laminates) with a binder, in particular impregnated with a binder resin, and the impregnated prepregs or wet laminates cured during a curing period thermally and / or by electromagnetic radiation and at least during a part of the curing period against one or both surfaces of the ceramic or metallic layer are pressed. As a result, a hot pressing process is realized, in which the curing binder of the fibrous mats arranged on both sides provide a material bond with the surface of the ceramic or steel layer, without the need for an additional adhesive. In addition, the two-sided pressing can advantageously apply both support layers, the front and rear support layers, to the ceramic or steel layer during a single process step.

Durch die in den Unteransprüchen aufgeführten Maßnahmen sind vorteilhafte Weiterbildungen und Verbesserungen der in den Patentansprüchen 1 und 14 angegebenen Erfindung möglich.The measures listed in the dependent claims advantageous refinements and improvements of the claims 1 and 14 invention are possible.

Gemäß einer bevorzugten Ausführungsform ist die keramische oder metallische Schicht von der vorderen Stützschicht und der hinteren Stützschicht vollständig ummantelt, insbesondere an den Stirnflächen. Hierdurch ist in vorteilhafter Weise ein besonders steifer und fester Zusammenhalt des Verbundes gegeben.According to a preferred embodiment, the ceramic or metallic layer of the front support layer and the rear support layer is complete sheathed, especially at the end faces. As a result, a particularly rigid and firm cohesion of the composite is given in an advantageous manner.

Von Vorteil ist die Verwendung von kohlenstofffaserverstärktem Kunststoff für die vordere und/oder die hintere Stützschicht auch, wenn die keramische oder metallische Schicht mindestens lokal von einer ebenen Platte abweicht und eine Krümmung und/oder eine Abwinkelung aufweist und/oder wenn die Schichtdicke der keramischen oder metallischen Schicht variabel ist. Denn die meist auf der Basis von Gelegen, Geweben, Gewirken oder Gestricken vorhandenen Faserkunststoffe lassen sich vor dem Aushärten leicht an unebene Formen anpassen. Besonders bevorzugt beinhaltet der kohlenstofffaserverstärkte Kunststoff ein unidirektionales Gelege aus um 90 Grad zueinander versetzt angeordneten Schichten paralleler Fasern.Another advantage is the use of carbon fiber reinforced plastic for the front and / or the rear support layer, even if the ceramic or metallic layer at least locally deviates from a flat plate and has a curvature and / or angling and / or if the layer thickness of the ceramic or metallic layer is variable. This is because the fiber plastics, which are usually based on fibers, knitted fabrics or knitted fabrics, can easily be adapted to uneven shapes before curing. More preferably, the carbon fiber reinforced plastic includes a unidirectional scrim of 90 degree staggered layers of parallel fibers.

Gemäß einer Weiterbildung weist die vordere Stützschicht und/oder die hintere Stützschicht einen auf das Volumen bezogenen Kohlenstoff- von mindestens 10 % auf.According to a development, the front support layer and / or the rear support layer has a volume-related carbon of at least 10%.

Gemäß einer weiterbildenden Maßnahme besteht die Matrix der vorderen Stützschicht und/oder der hinteren Stützschicht aus einem thermisch und/oder durch elektromagnetische Strahlung aushärtbaren Polymer, beispielsweise aus einem Phenolharz.According to a further development measure, the matrix of the front support layer and / or the rear support layer consists of a thermally and / or by electromagnetic radiation curable polymer, for example of a phenolic resin.

Bei Verwendung einer keramischen Schicht kann diese eine monolithische Keramik beispielweise aus Aluminiumoxid oder Siliziumcarbid aufweisen. Alternativ kann auch eine faserverstärkte Keramik verwendet werden. Insbesondere wird eine gesinterte, oder durch Infiltration mit flüssigem Silizium hergestellte Keramik verwendet.When using a ceramic layer, this may comprise a monolithic ceramic, for example of aluminum oxide or silicon carbide. Alternatively, a fiber-reinforced ceramic can be used. In particular, a sintered ceramic or a ceramic produced by infiltration with liquid silicon is used.

Faserverstärkte Keramiken können bevorzugt sog. C/SiC-Werkstoffe sein, bei denen vorzugsweise kohlenstoffbasierte Fasern, insbesondere Kohlenstofffasern oder Graphitfasern in einer überwiegend aus SiC, Si und C gebildeten Matrix gebunden sind. Die C/SiC-Verbundkeramiken können auch andere hochtemperaturbeständige Fasern umfassen, die neben Kohlenstoff noch weitere Elemente, wie beispielsweise Si, B, N, O oder Ti enthalten. Die Vorgehensweise zur Herstellung von C/SiC-Werkstoff ist dadurch gekennzeichnet, dass zunächst ein CFC-Werkstoff gebildet wird. Besonders bevorzugt ist die Herstellung von kurzfaserbündelverstärktem CFK (Kohlenstofffaserverstärkte Kunststoffe), bestehend aus mit einer carbonisierbaren Substanz und/oder mit Kohlenstoff beschichteten Kohlenstofffasern oder Faserbündeln und Füllstoffen und Bindern, der mit einem Kern zur gewünschten Form gepresst und ausgehärtet und hierauf carbonisiert und/oder graphitiert wird, so daß ein CFC- oder C/C- Formkörper als Zwischenprodukt entsteht. Dieser Formkörper wird im vorliegenden Fall als dünne Platte mit der gewünschten Dicke gefertigt. Das Basismaterial ist indessen nicht auf CFC-Werkstoffe beschränkt. Als Fasermaterial können ebenso auch weitere temperaturstabile Keramikfasern, insbesondere auf der Basis von SiO2, Al2O3, ZrO2, oder SiC, verwendet werden, die mit Kohlenstoff oder Graphit beschichtet wurden.Fiber-reinforced ceramics may preferably be so-called C / SiC materials, in which preferably carbon-based fibers, in particular carbon fibers or graphite fibers are bonded in a matrix formed predominantly of SiC, Si and C. The C / SiC composite ceramics may also comprise other high temperature resistant fibers which contain, in addition to carbon, other elements such as Si, B, N, O or Ti. The procedure for the production of C / SiC material is characterized in that first a CFC material is formed. Particularly preferred is the production of short fiber bundle reinforced CFRP (carbon fiber reinforced plastics) consisting of carbonizable substance and / or carbon coated carbon fibers or fiber bundles and fillers and binders pressed and cured with a core to the desired shape and then carbonized and / or graphitized is, so that a CFC or C / C-shaped body is formed as an intermediate. This shaped body is manufactured in the present case as a thin plate with the desired thickness. However, the base material is not limited to CFC materials. Other temperature-stable ceramic fibers, in particular those based on SiO 2 , Al 2 O 3 , ZrO 2 , or SiC, which have been coated with carbon or graphite, may likewise be used as the fiber material.

Das Plattenmaterial aus kohlenstofffaserverstärktem Kohlenstoffwerkstoff wird anschließend bei Temperaturen um etwa 1600 °C im Vakuum oder unter Inertgas mit einer Siliziumschmelze oder einer Siliziumlegierungsschmelze infiltriert, wodurch zumindest ein Teil des Kohlenstoffs der Matrix und/oder der Fasern in SiC umgewandelt wird. Neben Silizium können als weitere Bestandteile der Schmelze auch die Metalle der Nebengruppen I bis VIII verwendet werden, insbesondere Ti, Cr, Fe, Mo, B und Ni. Durch die Flüssiginfiltration des CFC-Formkörpers entsteht ein dichter, fester und sehr harter Formkörper aus C/SiC-Werkstoff enthaltend Fasern, im allgemeinen Kohlenstofffasern, mit einer Matrix aus überwiegend SiC, Si und C.The carbon fiber reinforced carbon material plate material is then infiltrated with a silicon melt or silicon alloy melt at temperatures of about 1600 ° C in vacuum or under inert gas, thereby converting at least a portion of the carbon of the matrix and / or fibers into SiC. In addition to silicon, the metals of subgroups I to VIII can also be used as further constituents of the melt, in particular Ti, Cr, Fe, Mo, B and Ni. The liquid infiltration of the CFC molded body produces a dense, solid and very hard shaped body of C / SiC material containing fibers, generally carbon fibers, with a matrix of predominantly SiC, Si and C.

Alternativ kann die Matrix des Formkörpers ganz oder teilweise durch eine Gasphaseninfiltration (CVD oder CVI) erzeugt werden. Dann weist die Matrix einen relativ hohen SiC-Gehalt auf, typischerweise über 95%. Weiterhin kann die Herstellung der Matrix durch die Pyrolyse von Si-haltigen, präkeramischen Polymeren erfolgen, wie sie zum Beispiel durch die Pyrolyse von Polymeren entstehen, die eines oder mehrere der Elemente Si, B, C, N, P oder Ti enthalten.Alternatively, the matrix of the molded article may be wholly or partially generated by gas phase infiltration (CVD or CVI). Then the matrix has a relatively high SiC content, typically over 95%. Furthermore, the preparation of the matrix can be carried out by the pyrolysis of Si-containing, preceramic polymers, such as those produced by the pyrolysis of polymers containing one or more of the elements Si, B, C, N, P or Ti.

Bevorzugte Anwendungen des erfindungsgemäßen Panzerschutzmaterials betreffen den ballistischen Schutz in Land-, Luft- und Wasserfahrzeugen, als Einlage oder integraler Bestandteil von Schutzwesten sowie als Satelliten-Schutzschild. Bei allen diesen Anwendungen ist besonders das geringe Gewicht von kohlenstofffaserverstärktem Kunststoff von Vorteil. Für die letzt genannte Verwendung als Satelliten-Schutzschild ist vor allem eine Keramik basierend auf C/SiC-Werkstoff wegen der hohen Temperaturbeständigkeit von Vorteil.Preferred applications of the armor protection material according to the invention relate to ballistic protection in land, air and water vehicles, as a deposit or integral part of protective vests and as a satellite shield. In all these applications is especially the low weight of Carbon fiber reinforced plastic advantageous. For the last-mentioned use as a satellite shield, especially a ceramic based on C / SiC material because of the high temperature resistance of advantage.

Gemäß einer besonders zu bevorzugenden Weiterbildung des erfindungsgemäßen Verfahrens wird durch den Pressvorgang und das Aushärten gleichzeitig auf die von der Beschussbeanspruchung weg weisende Oberfläche der hinteren Stützschicht eine insbesondere Aluminium, Aramid oder Dyneema beinhaltende Auffangschicht aufgebracht. Dann können mit einem einzigen Pressvorgang vier Schichten, nämlich die vordere Stützschicht, die Keramik- oder Stahlschicht, die hintere Stützschicht sowie die Auffangschicht miteinander verbunden werden, wobei jeweils durch den aushärtenden Binder der die vordere und hintere Stützschicht bildenden Prepregs der Stoffschluss zwischen den einzelnen Schichten zustandekommt.According to a particularly preferable development of the method according to the invention, by the pressing process and the curing at the same time applied to the pointing away from the Beschussbeanspruchung surface of the back support layer, in particular a aluminum, aramid or Dyneema-containing collecting layer. Then four layers, namely the front support layer, the ceramic or steel layer, the back support layer and the trap layer can be joined together with a single pressing operation, wherein in each case by the curing binder of the front and rear support layer forming prepreg of the material bond between the individual layers comes about.

Alternativ können einzelne oder sämtliche der genannten Schichten auch mittels Flüssigkleber oder Klebefolie miteinander verklebt werden.Alternatively, individual or all of the layers mentioned can also be glued together by means of liquid adhesive or adhesive film.

Zeichnungendrawings

Nachstehend ist ein Ausführungsbeispiel der Erfindung in den Zeichnungen dargestellt und in der nachfolgenden Beschreibung näher erläutert. Die einzige Figur zeigt eine Schnittdarstellung eines Panzermaterials gemäß einer bevorzugten Ausführungsform der Erfindung.An embodiment of the invention is illustrated in the drawings and explained in more detail in the following description. The single figure shows a sectional view of an armor material according to a preferred embodiment of the invention.

Beschreibung der AusführungsbeispieleDescription of the embodiments

Im Rahmen des Herstellungsverfahrens des in der Figur gezeigten bevorzugten Ausführungsbeispiels eines erfindungsgemäßen Panzermaterials 1 wird eine ca. 12 mm dicke, mit Kohlenstofffasern verstärkte Keramikplatte 2, insbesondere eine Platte aus einer C/SiC-Verbundkeramik mit den Abmessungen 350 mm x 400 mm auf der von der Beschussbeanspruchung weg weisenden Oberfläche mit 12 Lagen eines unidirektionales Gelege aus um 90 Grad zueinander versetzt angeordneten Schichten paralleler Kohlenstofffasern unmittelbar belegt. Auf der gegenüberliegenden, der Beschussbeanspruchung zugewandten Oberfläche der Keramikplatte werden 2 Lagen des vorzugsweise gleichen unidirektionalen Geleges unmittelbar zur Anlage gebracht.As part of the manufacturing process of the preferred embodiment of an armor material 1 according to the invention shown in the figure, an approximately 12 mm thick, reinforced with carbon fibers ceramic plate 2, in particular a plate of a C / SiC composite ceramic with the dimensions 350 mm x 400 mm on the of the attack stress facing away surface with 12 layers of a unidirectional scrim of offset by 90 degrees to each other arranged layers of parallel carbon fibers directly occupied. On the opposite, the Beschussbeanspruchung facing surface of the ceramic plate 2 layers of preferably the same unidirectional Geleges be brought directly to the plant.

Beide Gelege werden vor dem oder gleichzeitig mit dem Auflegen auf die Keramikschicht 2 mit einem thermisch und/oder durch elektromagnetische Strahlung aushärtbaren Polymer, insbesondere mit einem Phenolharz als Binder imprägniert, um mit dem Binder imprägnierte Faserstoffmatten, sog. Prepregs auszubilden, bei welchen die Matrix aus dem Polymer besteht.Both scrims are impregnated prior to or simultaneously with the laying on the ceramic layer 2 with a thermally and / or by electromagnetic radiation curable polymer, in particular with a phenolic resin as a binder to form impregnated with the binder pulp mats, so-called. Prepregs in which the matrix consists of the polymer.

Die Aushärtung der Prepregs zu CFK (Kohlenstofffaserverstärkter Kunststoff) findet vorzugsweise mittels eines üblichen Autoklavprozesses statt, bei welchem die die Keramikschicht 2 umschließenden, imprägnierten Prepregs beispielsweise unter einer Aushärtetemperatur in einem Bereich zwischen 50 °C bis 180 °C und unter Pressen gegen die Keramikschicht ausgehärtet werden. Während des Aushärtevorgangs entsteht eine Adhäsion bzw. ein Stoffschluss der Prepregs mit den Oberflächen der Keramikschicht 2, indem der anfangs noch viskose Binder in die raue Oberflächenstruktur der Keramikschicht eindringt und nach einiger Zeit erstarrt bzw. aushärtet. Dabei bildet das der Keramikschicht in Beschussrichtung vorgeordnete, ausgehärtete Prepreg eine vordere Stützschicht 4 und das der Keramikschicht 2 in Beschussrichtung nachgeordnete, ausgehärtete Prepreg eine hintere Stützschicht 6 aus. Besonders bevorzugt kann während des Herstellprozesses die Keramikschicht von der vorderen Stützschicht und der hinteren Stützschicht vollständig ummantelt werden, insbesondere an den Stirnflächen.Curing of the prepregs to CFK (carbon fiber reinforced plastic) preferably takes place by means of a customary autoclave process in which the impregnated prepreg enclosing the ceramic layer 2 is hardened, for example under a curing temperature in a range between 50 ° C to 180 ° C and under pressing against the ceramic layer become. During the curing process, an adhesion of the prepregs with the surfaces of the ceramic layer 2 is formed by the initially viscous binder penetrating into the rough surface structure of the ceramic layer and solidifying or hardening after some time. In this case, the hardened prepreg upstream of the ceramic layer in the direction of bombing forms a front support layer 4 and the hardened prepreg downstream of the ceramic layer 2 in the direction of bombardment forms a rear support layer 6. Particularly preferably, during the manufacturing process, the ceramic layer can be completely encased by the front support layer and the rear support layer, in particular at the end faces.

Vorzugsweise wird im Rahmen des Press- und Aushärtevorgangs gleichzeitig auf die von der Beschussbeanspruchung weg weisenden Oberfläche der hinteren Stützschicht eine insbesondere Aluminium, Aramid oder Dyneema beinhaltende Auffangschicht 8 mit einer Dicke von ca. 10 mm aufgebracht. Dann können mit einem einzigen Pressvorgang vier Schichten, nämlich die vordere Stützschicht 4, die Keramik- oder Stahlschicht 2, die hintere Stützschicht 6 sowie die Auffangschicht 8 miteinander verbunden werden.Preferably, in the context of the pressing and hardening process, a catching layer 8, in particular comprising aluminum, aramid or dyneema, having a thickness of approximately 10 mm, is simultaneously applied to the surface of the rear support layer facing away from the impact stress. Then, four layers, namely, the front support layer 4, the ceramic or steel layer 2, the back support layer 6 and the trap layer 8 can be joined together with a single pressing operation.

Alternativ wird der Press- und Aushärtevorgang auf die vordere Stützschicht 4, die Keramikschicht 2 und die hintere Stützschicht 8 beschränkt. Die Auffangschicht 8 in Form eines ca. 10 mm dicken Backings aus Aramidgewebe kann auch auf den derart vorbereiteten Schichtkörper aufgeklebt werden.Alternatively, the pressing and curing process is restricted to the front support layer 4, the ceramic layer 2 and the back support layer 8. The collecting layer 8 in the form of an approximately 10 mm thick backing of aramid fabric can also be glued onto the thus prepared laminated body.

Aufgrund der vor der Aushärtung flexiblen Materialeigenschaften der Prepregs können die vordere Stützschicht 4 und/oder die hintere Stützschicht 6 und evtl. auch das Backing 8 anstatt auf eine ebene Keramikschicht 2 auch auf eine mindestens lokal von einer ebenen Platte abweichende und eine Krümmung und/oder eine Abwinkelung aufweisende und/oder bezüglich der Schichtdicke variierende Keramikschicht 2 aufgebracht werden.Due to the flexible material properties of the prepregs prior to curing, the front support layer 4 and / or the rear support layer 6 and possibly also the backing 8 can also be deviated from a flat ceramic layer 2 to a curvature and / or at least locally deviating from a flat plate a ceramic layer 2 having a bend and / or varying with respect to the layer thickness can be applied.

Das Panzermaterial wies ein Flächengewicht von weniger als 45 kg/m2 auf und wurde in Beschussversuchen entsprechend der Beschussklasse FB 7 getestet. Die Ergebnisse zeigten eine deutliche Steigerung der Steifigkeit gegenüber Panzermaterial ohne vordere, glas- oder kohlenstofffaserverstärkte Stützschicht 4. Die durch das Auftreffen des Projektils entstandenen Primär-, aber vor allem die Sekundarschädigungen in der Keramikplatte wurden demgegenüber stark reduziert. Bei der Ausführungsform mit aufgeklebtem Backing 8 konnten die Belastungen auf die Klebeverbindung zwischen der hinteren Stützschicht 6 und dem Backing 8 derart verringert werden, dass die sonst zu beobachtenden teilweisen oder ganzflächigen Ablösungen des Backings 8 ausblieben, wodurch das Panzermaterial 1 auch bei Mehrfachbeschuss intakt blieb und das Multihit-Verhalten stark verbessert wurde. Insgesamt wurde durch die genannten Maßnahmen nicht nur die flächengewichtsbezogene Schutzleistung erhöht, sondern es konnte auch die Haftung des Backings 8 am Rest des ballistischen Systems wesentlich verbessert werden.The armor material had a basis weight of less than 45 kg / m 2 and was tested in bombardment tests according to the fire class FB 7. The results showed a significant increase in rigidity compared to armor without front, glass or carbon fiber reinforced support layer 4. The primary, but especially the secondary damage in the ceramic plate caused by the impact of the projectile were greatly reduced. In the embodiment with glued-on backing 8, the stresses on the adhesive bond between the back support layer 6 and the backing 8 could be reduced so that the otherwise observed partial or full-scale detachment of the backing 8 remained, whereby the armor material 1 remained intact even with multiple firing and the multihit behavior has been greatly improved. Overall, not only the surface weight-related protection performance was increased by the measures mentioned, but it was also the adhesion of the backing 8 at the rest of the ballistic system can be significantly improved.

Bei den weiteren Ausführungsformen wurden jeweils nur die im folgenden explizit beschriebenen Merkmale des Panzermaterials verändert, bei ansonsten gleichem Aufbau wie beim bevorzugten Ausführungsbeispiel.In the other embodiments, only the features of the armor material described explicitly below were changed in each case, with otherwise the same structure as in the preferred embodiment.

So wurde die kohlenstofffaserverstärkte Keramikplatte 2 der bevorzugten Ausführungsform durch eine Platte aus monolithischer Keramik ersetzt, welche beispielsweise aus Aluminiumoxid besteht. Die Abmessungen der Keramik betrugen ca. 250 mm x 350 mm, die Dicke 8 mm.Thus, the carbon fiber reinforced ceramic plate 2 of the preferred embodiment has been replaced by a monolithic ceramic plate made of, for example, alumina. The dimensions of the ceramic were about 250 mm x 350 mm, the thickness 8 mm.

Eine Fortbildung der eingangs beschriebenen Ausführungsform sah vor, die kohlenstofffaserverstärkte Keramikplatte 2 durch eine Platte aus ballistischen Stahl mit einer Dicke von ca. 8 mm zu ersetzen.A development of the embodiment described above was to replace the carbon fiber reinforced ceramic plate 2 by a plate of ballistic steel with a thickness of about 8 mm.

Gemäß einer Weiterbildung wurde die keramische Schicht 2 des Panzermaterials 1 aus einzelnen Keramikkacheln mit den Abmessungen 20 mm x 20 mm x 8 mm aufgebaut, die in für ballistische Systeme bekannter Weise aneinander gelegt wurden, um eine Keramikstruktur mit den Abmessung von 300 mm x 300 mm zu bilden.According to a development, the ceramic layer 2 of the armor material 1 was constructed from individual ceramic tiles with the dimensions 20 mm x 20 mm x 8 mm, which were placed in a known manner for ballistic systems together to a ceramic structure with the dimension of 300 mm x 300 mm to build.

Bei einer weiteren Ausführungsform war die Keramikschicht 2 gekrümmt ausgebildet und insbesondere in ihrer Geometrie dem Radlauf eines Kraftfahrzeugs angeglichen, wobei die aus flexiblen Faser-Gelegen bestehende vordere und hintere Stützschicht 4, 6 vor dem Aushärten leicht an diese gekrümmte Form anpassbar sind.In another embodiment, the ceramic layer 2 was curved and in particular adapted in geometry to the wheel arch of a motor vehicle, wherein the front and rear support layer 4, 6 are made of flexible fiber-readily adaptable to this curved shape before curing.

Weiterhin wurde auch gekrümmtes, auf einer Keramikschicht 2 basierendes Panzermaterial 1 als Einlage einer Schutz- oder Panzerweste hergestellt. Das Gesamtschutzsystem als Kombination von Einlage und Westenliner wurde wie eingangs beschrieben getestet, wobei das Resultat entsprechend positiv ausfiel.Furthermore, curved, based on a ceramic layer 2 tank material 1 was produced as a deposit of a protective or bulletproof vest. The overall protection system as a combination of liner and westliner was tested as described above, with the result correspondingly positive.

Gemäß einer weiteren Fortbildung wurde als Backing 8 ein Dyneema-Gelege eingesetzt. Denkbar ist auch eine vordere und/oder hintere Stützschicht 4, 6 aus einem mit Kohlenstoff- und Aramidfasern bzw. mit Kohlenstoff- und Glasfasern aufgebauten Hybridgewebe.According to another training was used as Backing 8 a Dyneema clutch. Also conceivable is a front and / or rear support layer 4, 6 made of a hybrid fabric constructed with carbon and aramid fibers or with carbon and glass fibers.

Claims (17)

  1. Multilayer armour protection material (1)
    consisting of a one- or multi-piece ceramic or metallic layer (2) and, viewed in the direction of fire, a rear support layer (6) of carbon-fibre-reinforced plastics material,
    and, viewed in the direction of fire, a front support layer (4) of carbon-fibre-reinforced plastics material,
    wherein the carbon-fibre-reinforced plastics material of the front and of the rear support layer (4, 6) is in the cured state and is no longer flexible and
    the protective layer forms a stiff composite structure with the two support layers.
  2. Armour protection material according to Claim 1, characterised in that
    the ceramic or metallic layer (2) is completely encased by the front support layer (4) and the rear support layer (6), in particular at the end faces.
  3. Armour protection material according to Claim 1 or 2, characterised in that
    the ceramic or metallic layer (2) diverges from a plane plate, at least locally, and comprises a curve and/or a bend.
  4. Armour protection material according to at least one of the preceding Claims, characterised in that
    the layer thickness of the ceramic or metallic layer (2) is variable.
  5. Armour protection material according to at least one of the preceding Claims, characterised in that
    the front support layer (4) and/or the rear support layer (6) have a carbon fibre proportion, related to the volume, of at least 10%.
  6. Armour protection material according to at least one of the preceding Claims, characterised in that
    the carbon fibres are present in the form of bunches, woven fabrics or knitted fabrics.
  7. Armour protection material according to Claim 6, characterised in that
    the carbon-fibre-reinforced plastics material includes a unidirectional bunch of layers, staggered by 90°, of parallel fibres.
  8. Armour protection material according to at least one of the preceding Claims, characterised in that
    the matrix of the front support layer (4) and/or of the rear support layer (6) consists of a polymer which can be cured thermally and/or through electromagnetic radiation.
  9. Armour protection material according to at least one of the preceding Claims, characterised in that,
    viewed in the direction of fire, an interception layer (8), which includes in particular aluminium, aramid or Dyneema, is disposed after the rear support layer (6).
  10. Armour protection material according to at least one of the preceding Claims, characterised in that
    the ceramic layer (2) includes a monolithic ceramic or a fibre-reinforced ceramic, in particular a sintered ceramic or one made through infiltration with liquid silicon.
  11. Use of an armour protection material according to at least one of Claims 1 to 10 as ballistic protection in land vehicles, aircraft and watercraft.
  12. Use of an armour protection material according to at least one of Claims 1 to 10 as an insert or integral component part of protective vests.
  13. Use of an armour protection material according to at least one of Claims 1 to 10 as a satellite protective shield.
  14. A method for making a multilayer armour protection material (1) according to Claim 1, characterised in that
    a front support layer (4) of carbon-fibre-reinforced plastics material is applied to the surface of the ceramic or metallic layer (2) which faces the firing load and a rear support layer (6) of carbon-fibre-reinforced plastics material is applied to the surface of the ceramic or metallic layer (2) which is remote from the firing load by impregnating carbon fibre bunches, woven fabrics or knitted fabrics with a binder, in particular with a binder resin, for forming fibrous mats impregnated with binder, and the impregnated fibrous mats are cured thermally and/or through electromagnetic radiation during a curing period and pressed against one or both surface(s) of the ceramic or metallic layer (2) at least during a part of the curing period.
  15. A method according to Claim 14, characterised in that
    the ceramic or metallic layer (2) is completely encased by the front support layer (4) and the rear support layer (6), in particular at the end faces.
  16. A method according to either of Claims 14 and 15, characterised in that
    an interception layer (8), which includes in particular aluminium, aramid or Dyneema, is simultaneously applied to the surface of the rear support layer (6) which points away from the firing load through the pressing process and the curing.
  17. A method according to at least one of Claims 14 to 16, characterised in that
    the curing temperature during thermal curing lies in a range between 50°C and 180°C.
EP03027995A 2003-12-05 2003-12-05 Multilayer armour plating material and process for making it Revoked EP1538417B1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP03027995A EP1538417B1 (en) 2003-12-05 2003-12-05 Multilayer armour plating material and process for making it
DE50309268T DE50309268D1 (en) 2003-12-05 2003-12-05 Multilayered anti-tank material and process for its production
ES03027995T ES2302526T3 (en) 2003-12-05 2003-12-05 SHIELDING MATERIAL-MULTI-PAD PROTECTION AND PROCEDURE FOR MANUFACTURING.
AT03027995T ATE387618T1 (en) 2003-12-05 2003-12-05 MULTI-LAYER ARMOR PROTECTION MATERIAL AND METHOD FOR PRODUCING IT
US10/999,438 US20090324966A1 (en) 2003-12-05 2004-11-29 Multilayer armor plating, and process for producing the plating

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03027995A EP1538417B1 (en) 2003-12-05 2003-12-05 Multilayer armour plating material and process for making it

Publications (2)

Publication Number Publication Date
EP1538417A1 EP1538417A1 (en) 2005-06-08
EP1538417B1 true EP1538417B1 (en) 2008-02-27

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP03027995A Revoked EP1538417B1 (en) 2003-12-05 2003-12-05 Multilayer armour plating material and process for making it

Country Status (5)

Country Link
US (1) US20090324966A1 (en)
EP (1) EP1538417B1 (en)
AT (1) ATE387618T1 (en)
DE (1) DE50309268D1 (en)
ES (1) ES2302526T3 (en)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7849779B1 (en) * 2006-01-23 2010-12-14 U.T. Battelle, Llc Composite treatment of ceramic tile armor
US20120055327A1 (en) * 2006-04-20 2012-03-08 Holowczak John E Armor system having ceramic matrix composite layers
US8640590B2 (en) * 2006-04-20 2014-02-04 Sikorsky Aircraft Corporation Armor system having ceramic composite with improved architecture
US8375839B2 (en) * 2007-08-29 2013-02-19 Supracor, Inc. Lightweight armor and ballistic projectile defense apparatus
GB2451357B (en) * 2008-09-04 2009-10-14 Global Composites Group Ltd Ceramic Armour
BRPI1014107A2 (en) 2009-05-04 2019-07-16 Ppg Ind Ohio Inc composite materials and their application.
US8225704B2 (en) * 2010-01-16 2012-07-24 Nanoridge Materials, Inc. Armor with transformed nanotube material
US20130180393A1 (en) * 2011-02-01 2013-07-18 Sgl Carbon Se Defensive, ceramic based, applique armor, device for providing anti-projectile armoring protection and process for producing ceramic based projectile armor with hollow geometry
WO2013002865A1 (en) * 2011-04-08 2013-01-03 Schott Corporation Multilayer armor
GB2504497B (en) 2012-07-27 2014-07-30 Np Aerospace Ltd Armour
US9458632B2 (en) 2012-10-18 2016-10-04 Ppg Industries Ohio, Inc. Composite materials and applications thereof and methods of making composite materials
WO2014200592A2 (en) * 2013-03-14 2014-12-18 Phoenix Armor, Llc Polymer and block copolymer, ceramic composite armor system
RU2560444C2 (en) * 2013-05-31 2015-08-20 Российская Федерация, от имени которой выступает Государственная корпорация по атомной энергии "Росатом"-Госкорпорация "Росатом" Heat protective armour layered system
KR101683511B1 (en) * 2015-03-16 2016-12-07 현대자동차 주식회사 bumper back-beam for vehicles
KR102263817B1 (en) * 2019-10-08 2021-06-14 한국과학기술연구원 Manufacturing method of stab proof hybrid composite structure
CN111038045A (en) * 2019-12-12 2020-04-21 中国建筑材料科学研究总院有限公司 Transparent armor plate and manufacturing method thereof
CN113936548B (en) * 2020-06-29 2024-01-19 云谷（固安）科技有限公司 Display module, bending cushion block and manufacturing method of display module
CN114923368A (en) * 2022-06-21 2022-08-19 福建泉城特种装备科技有限公司 Bulletproof wall composite material and bulletproof wall

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1142689A (en) * 1966-03-29 1969-02-12 Aerojet General Co Armour plating
US4198454A (en) * 1978-10-27 1980-04-15 American Air Filter Company, Inc. Lightweight composite panel
DE2934050C2 (en) * 1979-08-23 1983-12-08 Thiele & Co, 2800 Bremen Composite panel for armoring vehicle interiors or the like.
US5142997A (en) * 1990-10-31 1992-09-01 Westinghouse Electric Corp. Projectile resisting space dividing system
DE4114809A1 (en) 1991-05-07 1992-11-12 Gerd Dr Ing Kellner Lightweight bullet-proof plate material - comprising ceramic or metallic front layer joined by elastic bonding agent to multilayer elasticated laminate
US5214235A (en) * 1992-03-25 1993-05-25 The United States Of America As Represented By The United States Department Of Energy Shock destruction armor system
EP0582225A3 (en) * 1992-07-31 1994-06-15 Hughes Aircraft Co Low-temperature curing epoxy resin composition
US5456974A (en) * 1993-03-12 1995-10-10 Lundblad; Wayne E. Ballistic resistant article comprising a three dimensional interlocking woven fabric
US5567498A (en) * 1993-09-24 1996-10-22 Alliedsignal Inc. Textured ballistic article
KR100255413B1 (en) * 1995-03-15 2000-05-01 프리트 Ballistic grill for special purpose vehicles
US5970843A (en) * 1997-05-12 1999-10-26 Northtrop Grumman Corporation Fiber reinforced ceramic matrix composite armor
DE19746598C2 (en) * 1997-10-22 2000-12-07 Dornier Gmbh Ceramic composite and its use
EP1288607A1 (en) * 2001-08-24 2003-03-05 Israel Military Industries Ltd. Anti-ballistic ceramic articles
US6389594B1 (en) * 2001-08-30 2002-05-21 Israel Military Industries Ltd. Anti-ballistic ceramic articles
DE10157487C1 (en) * 2001-11-23 2003-06-18 Sgl Carbon Ag Fiber-reinforced composite body for protective armor, its manufacture and uses

Also Published As

Publication number Publication date
ES2302526T3 (en) 2008-07-16
DE50309268D1 (en) 2008-04-10
ATE387618T1 (en) 2008-03-15
EP1538417A1 (en) 2005-06-08
US20090324966A1 (en) 2009-12-31

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