EP1538417B1 - Mehrschichtiges Panzerschutzmaterial und Verfahren zu seiner Herstellung - Google Patents

Mehrschichtiges Panzerschutzmaterial und Verfahren zu seiner Herstellung 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
Authority
EP
European Patent Office
Prior art keywords
ceramic
layer
support layer
protection material
carbon
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.)
Revoked
Application number
EP03027995A
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German (de)
English (en)
French (fr)
Other versions
EP1538417A1 (de
Inventor
Eugen Pfitzmaier
Bodo Dipl.-Ing. Benitsch
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.)
SGL Carbon SE
Original Assignee
SGL Carbon SE
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
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First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=34442970&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP1538417(B1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by SGL Carbon SE filed Critical SGL Carbon SE
Priority to DE50309268T priority Critical patent/DE50309268D1/de
Priority to AT03027995T priority patent/ATE387618T1/de
Priority to EP03027995A priority patent/EP1538417B1/de
Priority to ES03027995T priority patent/ES2302526T3/es
Priority to US10/999,438 priority patent/US20090324966A1/en
Publication of EP1538417A1 publication Critical patent/EP1538417A1/de
Application granted granted Critical
Publication of EP1538417B1 publication Critical patent/EP1538417B1/de
Anticipated expiration legal-status Critical
Revoked legal-status Critical Current

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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.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Ceramic Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Laminated Bodies (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Professional, Industrial, Or Sporting Protective Garments (AREA)
EP03027995A 2003-12-05 2003-12-05 Mehrschichtiges Panzerschutzmaterial und Verfahren zu seiner Herstellung Revoked EP1538417B1 (de)

Priority Applications (5)

Application Number Priority Date Filing Date Title
DE50309268T DE50309268D1 (de) 2003-12-05 2003-12-05 Mehrschichtiges Panzerschutzmaterial und Verfahren zu seiner Herstellung
AT03027995T ATE387618T1 (de) 2003-12-05 2003-12-05 Mehrschichtiges panzerschutzmaterial und verfahren zu seiner herstellung
EP03027995A EP1538417B1 (de) 2003-12-05 2003-12-05 Mehrschichtiges Panzerschutzmaterial und Verfahren zu seiner Herstellung
ES03027995T ES2302526T3 (es) 2003-12-05 2003-12-05 Material de blindaje-proteccion multicapa y procedimiento para su fabricacion.
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 (de) 2003-12-05 2003-12-05 Mehrschichtiges Panzerschutzmaterial und Verfahren zu seiner Herstellung

Publications (2)

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

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EP03027995A Revoked EP1538417B1 (de) 2003-12-05 2003-12-05 Mehrschichtiges Panzerschutzmaterial und Verfahren zu seiner Herstellung

Country Status (5)

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US (1) US20090324966A1 (es)
EP (1) EP1538417B1 (es)
AT (1) ATE387618T1 (es)
DE (1) DE50309268D1 (es)
ES (1) ES2302526T3 (es)

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RU2560444C2 (ru) * 2013-05-31 2015-08-20 Российская Федерация, от имени которой выступает Государственная корпорация по атомной энергии "Росатом"-Госкорпорация "Росатом" Теплобронезащитная слоистая система
KR101683511B1 (ko) * 2015-03-16 2016-12-07 현대자동차 주식회사 자동차용 범퍼 백 빔
KR102263817B1 (ko) * 2019-10-08 2021-06-14 한국과학기술연구원 방검 하이브리드 복합 구조체의 제조방법
CN111038045A (zh) * 2019-12-12 2020-04-21 中国建筑材料科学研究总院有限公司 透明装甲板及透明装甲板制造方法
CN113936548B (zh) * 2020-06-29 2024-01-19 云谷（固安）科技有限公司 显示模组、折弯垫块及显示模组的制作方法
CN114923368A (zh) * 2022-06-21 2022-08-19 福建泉城特种装备科技有限公司 一种防弹墙体复合材料以及防弹墙
CN116001382B (zh) * 2022-12-07 2024-06-25 北京理工大学 一种抗破片群舰船防护结构及其设计方法

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Also Published As

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

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