US20080124513A1 - Moldable fabric with unidirectional tape yarns - Google Patents
Moldable fabric with unidirectional tape yarns Download PDFInfo
- Publication number
- US20080124513A1 US20080124513A1 US11/519,134 US51913406A US2008124513A1 US 20080124513 A1 US20080124513 A1 US 20080124513A1 US 51913406 A US51913406 A US 51913406A US 2008124513 A1 US2008124513 A1 US 2008124513A1
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- US
- United States
- Prior art keywords
- sheets
- core
- unidirectional
- impact resistant
- resistant component
- Prior art date
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- Abandoned
Links
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Images
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
- F41H5/0471—Layered armour containing fibre- or fabric-reinforced layers
- F41H5/0478—Fibre- or fabric-reinforced layers in combination with plastics layers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
- B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
- B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
- B32B7/04—Interconnection of layers
- B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
-
- 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.]
- Y10T428/24132—Structurally defined web or sheet [e.g., overall dimension, etc.] including grain, strips, or filamentary elements in different layers or components parallel
-
- 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
- Y10T428/249921—Web or sheet containing structurally defined element or component
- Y10T428/249924—Noninterengaged fiber-containing paper-free web or sheet which is not of specified porosity
- Y10T428/24994—Fiber embedded in or on the surface of a polymeric matrix
Definitions
- the present invention generally relates to impact resistant components, anti-ballistics panels and methods for making the components and panels.
- the invention relates to impact resistant components incorporating at least two composite sheets fused together, each composite sheet comprising an adhesive layer between two unidirectional sheets of aligned fiber elements or tape elements.
- tape structures from polypropylene film that is coated with a layer of propylene copolymer including ethylene units such that the coating has a lower softening point than the core.
- Such tape structures are disclosed, for example, in U.S. Pat. No. 5,578,370 the teachings of which are hereby incorporated by reference in their entirety.
- U.S. Patent Application 2004/0242103A1 (incorporated by reference) has also proposed to form monoaxially drawn tape structures characterized by substantial draw ratios and incorporating a central layer of a polyolefin with one or two surface layers of a polyolefin from the same class as the central layer. The DSC melting point of the outer layers is lower than that of the central layer to facilitate heat bonding.
- Such drawn tape elements may be interwoven so as to form a mat structure which is then subjected to heat thereby fusing the tape elements in place.
- Multiple layers of such interwoven mat structures may be combined to form moldable structures of substantial thickness that may be shaped to three-dimensional configurations.
- a core/shell fiber generally consists of a core of one type of polymer, with a surface layer (also called a shell or cladding) of a different polymer.
- the fiber's mechanical properties are mainly a result of the core material, whereas the surface layer determines the external properties (e.g., adhesion, friction, softness).
- One advantage of a core/shell fiber is the ability to achieve a combination of such properties that would be impossible in a simple, homogeneous fiber.
- One type of core/shell fiber has a polyester core and a polyolefin shell (e.g., polypropylene). A typical application for this fiber is in nonwoven fabrics where the lower melting point of the polypropylene surface layer allows these strong polyester core fibers to be bonded together without losing their strength.
- Anti-ballistics fibers and yarns tend to be expensive, leading to expensive anti-ballistics panels and impact resistant components made from the anti-ballistics yarns.
- the anti-ballistics panels made from unidirectional Kevlar and aramid fibers are typically embedded in a matrix. There is a need to produce a unidirectional anti-ballistics component or panel of fiber or tape elements using a lower amount of matrix material.
- FIG. 1 illustrates schematically a cross-section of one embodiment of the monoaxially drawn tape element
- FIG. 2 illustrates schematically a cross-section of one embodiment of the monoaxially drawn tape element
- FIGS. 3A-C illustrate schematically cross-sections of embodiments of core/shell fibers elements.
- FIGS. 3D-E illustrate schematically additional cross-sections of fiber elements.
- FIG. 4A illustrates schematically a unidirectional sheet made up of monoaxially drawn tape elements.
- FIG. 4B illustrates schematically a unidirectional sheet made up of core/shell fiber elements.
- FIG. 5A illustrates schematically a cross-section of one embodiment of the composite sheet
- FIG. 5B illustrates schematically a cross-section of one embodiment of the composite sheet
- FIG. 6 illustrates schematically a cross-section of one embodiment of the composite sheet
- FIGS. 7A and B illustrate schematically a cross-section of one embodiment of the impact resistant component
- FIGS. 8A and B illustrate schematically a cross-section of one embodiment of the impact resistant component
- FIGS. 9A and B illustrate schematically a cross-section of one embodiment of the impact resistant component
- FIGS. 10A-B illustrate schematically an anti-ballistics panel
- FIG. 11 illustrates schematically a molded article.
- a fiber element having a core of a strain oriented polymer and at least one surface layer of a heat fusible polymer covering at least a portion of the core, wherein the at least one surface layer is characterized by a softening temperature below that of the core to permit fusion bonding upon application of heat.
- the core and/or the surface layer are an olefin polymer.
- the fiber element is a monoaxially drawn tape element 10 made up of a surface layer 14 disposed on a core 12 .
- the core is a tape shaped core layer having an upper and lower surface and the surface layer 14 covers one side (upper or lower surface) of the core layer 12 .
- the tape element 10 may be formed by any conventional means of extruding multilayer polymeric films and then slitting the films into tape elements 10 .
- FIG. 2 there is shown another embodiment of the tape elements 10 made up of a core layer 12 disposed between two surface layers 14 and 14 ′ (the surface layers being disposed on the upper and lower surface of the core layer 12 ).
- the film may be formed by blown film or cast film extrusion.
- the film is then cut into a multiplicity of longitudinal strips of a desired width by slitting the film in a direction transverse to the layered orientation of core layer 12 and surface layer 14 to form tape elements 10 with cross-sections as shown in FIG. 1 .
- the tape elements 10 are then drawn in order to increase the orientation of the core layer 10 so as to provide increased strength and stiffness of the material.
- the surface layer(s) may be added after the drawing step. After the drawing process is complete, the resulting tape elements are in the range of about 1.0 to about 5 millimeters wide.
- the tape elements 10 have a width to thickness ratio of between about 10 and 1000.
- the tape elements have a modulus of between 5 and 200.
- a fiber element being a core/shell type fiber element 15 made up of a surface layer 17 disposed on a core 16 covering at least a portion of the core.
- the surface layer 17 covers the core 16 surface area completely.
- the core 16 is typically a fiber with a circular, oblong, elliptical, elongated or other cross-section.
- the cross-section of the core has a major to minor axis aspect ratio of between 1 and 30.
- the core 16 and surface layer 17 may be co-extruded together, or the surface layer 17 may be applied to the core 16 after the core 16 has been formed.
- the fiber element 15 is oriented before or after the surface layer 17 is formed in order to increase the orientation of the core 16 so as to provide increased strength and stiffness.
- FIG. 3D there is shown an additional embodiment of a number of fiber elements being of a core/shell type fiber elements together (each made up of a surface layer 17 disposed on a core 16 covering at least a portion of the core). While it is shown that the shape grouping or cluster of fibers elements is a circular, the group shape may also be elongated or other shapes. Additionally, each fiber element 15 may have the same or different cross-sectional shapes. Once in the composite, the shape of the grouping may also change.
- FIG. 3E shows a number of fiber elements with cores 16 surrounded by a surface layer 17 . In this embodiment, the surface layer 17 surrounds all of the cores 16 . In one embodiment, the core 16 has a major axis diameter of between 1 and 1000 micrometers (preferably between 50 and 500 micrometers) and the surface layer has a thickness of between about 5 and 30% of the total.
- the core 12 , 16 of the tape and fiber elements 10 , 15 are preferably made up of a molecularly-oriented thermoplastic polymer, the core 12 , 16 being fusible to each of surface layers 14 , 14 ′, 17 at their respective intersections.
- the core 12 , 16 is compatibly bonded to each of surface layers 14 , 14 ′, 17 between their contiguous surfaces. It is further contemplated that the surface layers 14 , 14 ′, 17 have a softening temperature, or melting temperature, lower than that of the core 12 , 16 .
- the core 12 , 16 is a polyolefin polymer such as polypropylene, polyethylene, polyester such as polyethylene terephthalate, or polyamide such as Nylon 6 or Nylon 6,6 (polyester and polyurethane are common core materials with low-melt polyester, polypropylene or polyethylene shells).
- Core-wrap yarns are also common materials and include elastomeric yarns wrapped with fibers of other materials to impart different aesthetics, hand, color, UV resistance, etc.
- the preferred core/shell materials for this invention are polyolefin in nature where a highly drawn and therefore highly oriented polypropylene or polyethylene has a lower softening point polyolefin surface layer commonly comprised of homopolymers or copolymers of ethylene, propylene, butene, 4-methyl-1-pentene, and/or like monomers.
- the core 12 , 16 may be polypropylene or polyethylene.
- the core 12 , 16 may account for about 50-99 wt. % of the tape or fiber element, while the surface layers 14 , 14 ′, 17 account for about 1-50 wt. % of the tape or fiber element.
- the core 12 , 16 and surface layers 14 , 14 ′, 17 being made up of the same class of materials to provide an advantage with regard to recycling, as the core 12 , 16 may include production scrap.
- the material of surface layers 14 , 14 ′, 17 is preferably a copolymer of propylene and ethylene or an ⁇ -olefin.
- the surface layers 14 , 14 ′, 17 comprise a random copolymer of propylene-ethylene with an ethylene content of about 1-25 mol. %, and a propylene content of about 75-99 mol. %. It may be further preferred to use said copolymer with a ratio of about 95 mol. % propylene to about 5 mol. % ethylene.
- a polyolefin preferably a polypropylene homopolymer or polypropylene copolymer, prepared with a metallocene catalyst, may be used for the surface layers 14 , 14 ′, 17 .
- materials such as poly(4-methyl-1-pentene) (PMP) and polyethylene may be useful as a blend with such copolymers in the surface layers 14 , 14 ′, 17 .
- the surface layer material should be selected such that the softening point of the surface layer 14 , 14 ′, 17 is at least about 10° C. lower than that of the core layer 12 , and preferably between about 15-40° C. lower.
- Softening point for this application, is defined as the Vicat softening temperature (ASTM D1525). It is desirable to minimize the amount of adhesive used to maximize the amount of fiber elements in a composite.
- one tape element 10 that may be particularly useful is believed to be marketed under the trade designation PURE by Lankhorst/Indutech having a place of business in Sneek, The Netherlands.
- FIG. 4A illustrates a unidirectional sheet 50 formed from a multiplicity of fiber elements being tape elements 10 .
- the tape elements are aligned parallel along a common fiber direction of the unidirectional sheet 50 .
- the tape elements 10 in the unidirectional sheet 50 do not overlap one another, and may have gaps between the tape elements 10 .
- the tape elements overlap one another up to 90% in the unidirectional sheet 50 .
- the unidirectional sheet 50 is preferably able to be bent to a radius of about 1 cm without affecting its physical performance.
- One approach for aligning the tape elements is to align the tape elements into a sheet by pulling yarn from a creel. Using a roll-off creel is helpful to reduce twist in the yarn.
- FIG. 4B illustrates a unidirectional sheet 52 formed from a multiplicity of core/shell type fiber elements 15 .
- the fiber elements 15 are aligned parallel along a common fiber direction of the unidirectional sheet 52 .
- the fiber elements 15 in the unidirectional sheet 52 do not overlap one another, and may have gaps between the fiber elements 15 .
- the fiber elements may overlap one another up to 90% in the unidirectional sheet 52 .
- the unidirectional sheet 52 may additionally have a polymer matrix.
- the unidirectional sheet 52 is preferably able to be bent to a radius of about 1 cm without affecting its physical performance.
- One approach for aligning the fiber elements is to align the tape elements into a sheet by pulling yarn from a creel. Using a roll-off creel is helpful to reduce twist in the yarn.
- FIGS. 5 and 5B illustrate composite sheets, each made up of two unidirectional sheets 50 and one adhesive layer 60 .
- the composite sheets are easier to handle than the unidirectional sheets, as the unidirectional sheets are composed of the tape elements 10 not bound in any way to one another.
- the adhesive layer 60 is adjacent and sandwiched between the core layers 12 of the tape elements 10 in the unidirectional sheet 50 .
- the unidirectional sheets are made up of tape elements 10 with a core layer 12 and two surface layers 14 and 14 ′ (shown in FIG.
- the adhesive layer 60 is adjacent to and sandwiched between the surface layers 14 ′ of the tape elements 10 .
- the common fiber direction of the unidirectional sheets 50 may be aligned, or rotated relative to each other, for example 90 degrees.
- the common fiber direction of the unidirectional sheets 50 in the composite sheet 100 are the same.
- FIG. 6 illustrates composite sheets, each made up of two unidirectional sheets 52 formed from fiber elements 15 and one adhesive layer 60 .
- the composite sheets are easier to handle than the unidirectional sheets, as the unidirectional sheets are composed of the fiber elements 15 not bound in any way to one another.
- the adhesive layer 60 is adjacent and sandwiched between the surface layers 17 of the fiber elements 15 .
- the common fiber direction of the unidirectional sheets 52 may be aligned, or rotated relative to each other, for example 90 degrees.
- the common fiber direction of the unidirectional sheets 52 in the composite sheet 102 are the same.
- the adhesive layer 60 preferably comprises a material which is compatible with the unidirectional material and fuses the unidirectional material into a unidirectional sheet 52 .
- the adhesive layer may be activated to fuse the unidirectional material by pressure, heat, UV, other activation methods, or any combination thereof.
- the adhesive is a pressure sensitive adhesive.
- the adhesive has a softening point less than that of the surface layer of the fiber elements.
- the softening point of the adhesive is at least 10° C. less than that of the surface layer of the fiber elements.
- a melting point of less than 130° C. is preferred.
- the adhesive layer 60 may be, but is not limited to EVA, LLDPE, LDPE, HDPE, copolymers of polypropylene, and the like.
- the adhesive layer 60 preferably has a lower softening temperature than the layer of the tape or fiber element 10 , 15 adjacent to the adhesive layer 60 . This corresponds to the core layer 12 for the tape element 10 having a core layer 12 and one surface layer 14 (as shown in FIG. 5A ), the surface layer 14 ′ for the tape element 10 having a core layer 12 and surface layers 14 and 14 ′ (as shown in FIG. 5B ), and the surface layer 17 for a fiber element 15 (as shown in FIG. 6 ).
- the adhesive layer 60 preferably has a thickness of between about 10 ⁇ m and 100 ⁇ m. For pressure sensitive adhesives, the amount of tack is preferably high enough to stabilize the unidirectional sheets for handling.
- the adhesive layer may be applied to the unidirectional sheets 50 , 52 by any method known in the art. Preferred methods include any well known coating method such as air knife coating, gravure coating, hopper coating, roller coating, spray coating, and the like.
- the coating composition can be based on water or organic solvent(s) or a mixture of water and organic solvent(s).
- the adhesive layer 60 can be formed by thermal processing such as extrusion and co-extrusion with and without stretching, blow molding, injection molding, lamination, etc.
- the adhesive layer 60 may also be an adhesive scrim, powder coating, or the like.
- the impact resistant component 200 there is shown different embodiments of the impact resistant component 200 . While the impact resistant components 200 shown in FIG. 7A-B and 8 A-B are formed from 2 composite sheets 100 , additional composites sheets 100 may be added to the top or bottom of the impact resistant component 200 shown.
- the adhesive layers 60 are in an amount of about 0.2 to 20%, more preferably about 2-10% of the weight of the impact resistant component.
- the tape elements and the adhesive layer comprise polypropylene. This creates an impact resistant component that is essentially polypropylene increasing the recycleability of the component.
- FIGS. 9A-B there is shown another embodiment of the impact resistant component 202 formed from shell/core type fiber elements 15 . While the impact resistant components 202 shown in FIG. 9A-B are formed from 2 composite sheets 102 , additional composites sheets 102 may be added to the top or bottom of the impact resistant component 202 shown.
- the adhesive layers 60 are in an amount of about 0.2 to 20%, more preferably about 2-10% of the weight of the impact resistant component.
- the fiber elements and the adhesive layer comprise polypropylene. This creates an impact resistant component that is completely or essentially polypropylene increasing the recycleability of the component.
- FIGS. 7A and B there is shown impact resistant components formed from tape elements 10 with a core layer 12 and one surface layer 14 .
- the impact resistant component 200 is formed when the surface layers 14 from the composite sheets 100 are fused using heat and optionally pressure. There are no additional layers, adhesives, or treatments added to the surface layers 14 of the tape elements 10 .
- FIG. 7A the common fiber direction of the unidirectional sheets 50 in one composite sheet 100 is the same (parallel to) as the common fiber direction of the unidirectional sheets 50 of the adjacent composite sheet 100 .
- FIG. 7A the common fiber direction of the unidirectional sheets 50 in one composite sheet 100 is the same (parallel to) as the common fiber direction of the unidirectional sheets 50 of the adjacent composite sheet 100 .
- the common fiber direction of the unidirectional sheets 50 in one composite sheet 100 is the perpendicular (rotated 90 degrees) to the common fiber direction of the unidirectional sheets 50 of the adjacent composite sheet 100 . While in FIGS. 7A and B, 0 and 90 degree rotations have been shown; any rotation angle is feasible and contemplated.
- the structure of the impact resistant component of FIGS. 7A and B in written form is as follows:
- the impact resistant components shown in FIGS. 8A and B are formed from tape elements 10 with a core layer 12 and two surface layers 14 and 14 ′.
- the impact resistant component 200 is formed when the surface layers 14 from the composite sheets 100 are fused using heat and optionally pressure. There are no additional layers, adhesives, or treatments added to the surface layers 14 of the tape elements 10 .
- the common fiber direction of the unidirectional sheets 50 in one composite sheet 100 is the same (parallel to) as the common fiber direction of the unidirectional sheets 50 of the adjacent composite sheet 100 .
- FIG. 8A the common fiber direction of the unidirectional sheets 50 in one composite sheet 100 is the same (parallel to) as the common fiber direction of the unidirectional sheets 50 of the adjacent composite sheet 100 .
- the common fiber direction of the unidirectional sheets 50 in one composite sheet 100 is the perpendicular (rotated 90 degrees) to the common fiber direction of the unidirectional sheets 50 of the adjacent composite sheet 100 . While in FIGS. 8A and B, 0 and 90 degree rotations have been shown, any rotation angle is contemplated.
- the structure of the impact resistant component of FIGS. 8A and B in written form is as follows:
- the impact resistant components 202 shown in FIGS. 9A and B are formed from fiber elements 15 with a core 16 and a surface layer 17 .
- the impact resistant component 202 is formed when the surface layers 17 from the composite sheets 102 are fused using heat and optionally pressure. There are no additional layers, adhesives, or treatments added to the surface layers 17 of the fiber elements 15 .
- the common fiber direction of the unidirectional sheets 52 in one composite sheet 102 is the same (parallel to) as the common fiber direction of the unidirectional sheets 52 of the adjacent composite sheet 102 .
- FIG. 9A the common fiber direction of the unidirectional sheets 52 in one composite sheet 102 is the same (parallel to) as the common fiber direction of the unidirectional sheets 52 of the adjacent composite sheet 102 .
- the common fiber direction of the unidirectional sheets 52 in one composite sheet 102 is the perpendicular (rotated 90 degrees) to the common fiber direction of the unidirectional sheets 52 of the adjacent composite sheet 102 . While in FIGS. 9A and B, 0 and 90 degree rotations have been shown, any rotation angle is contemplated.
- FIG. 10A illustrates an anti-ballistics panel 300 , according to one embodiment of the invention.
- the anti-ballistics panel 300 is made up of at least 10 composite sheets 100 formed from tape elements 10 fused together, more preferably 20 to 100.
- the core/shell nature of the fiber elements 15 has not been shown to reduce the complexity of the illustration. It has been shown that 10 composite sheets 100 fused together resist penetration by objects. While the anti-ballistics panel 300 is shown with the common fiber direction of each unidirectional sheet 50 parallel to the adjacent sheets, each unidirectional sheet 50 may be rotated any amount with respect to the adjacent unidirectional sheets 50 .
- FIG. 10B illustrates an anti-ballistics panel 302 , according to one embodiment of the invention.
- the anti-ballistics panel 302 is made up of at least 10 composite sheets formed from fiber elements 15 fused together, more preferably 20 to 100. It has been shown that 10 composite sheets 102 fused together resist penetration by objects. While the anti-ballistics panel 302 is shown with the common fiber direction of each unidirectional sheet 52 rotated 90 degrees with respect to the adjacent layers, each unidirectional sheet 52 may be rotated any amount with respect to the adjacent unidirectional sheets 52 .
- the impact resistant component 200 , 202 and the anti-ballistics panel 300 , 302 are adapted for three dimensional thermo-molding.
- One example is shown in FIG. 11 of a molded helmet 400 .
- Other articles of the impact resistant component 200 , 202 and the anti-ballistics panel 300 , 302 may be molded into include chest plates, extremity protection, vehicle panels, or other applications where anti-ballistic properties are required with a light weight panel.
- the process for forming an impact resistant component comprises:
- the fiber elements ( 10 or 15 ) comprising a core ( 12 or 16 ) of a strain oriented polymer and at least one surface layer ( 14 or 17 ) of a heat fusible polymer surface at least a portion of the core ( 12 or 16 ), wherein the at least one surface layer ( 14 or 17 ) is characterized by a softening temperature below that of the core ( 12 or 16 ) to permit fusion bonding upon application of heat.
- Forming an anti-ballistics panel ( 300 and 302 ) follows the same steps as above, except that at least 10 composite sheets ( 100 , 102 ) are stacked together.
- the method discloses the tape elements 10 comprising a core layer 12 and surface layers 14 and 14 ′, the method also applies for impact resistant components 200 and anti-ballistics panels 300 made from tape elements 10 having a core layer 12 and one surface layer 14 .
- the surface layers 14 between the composite sheets fuse to form the component 200 or panel 300 .
- the layers of composite sheets 100 or 102 may be formed from a single composite sheet 100 or 102 that is repeatedly folded over itself, or from several discrete overlaid composite sheets 100 or 102 .
- the impact resistant component 200 or 202 may be formed by reheating several previously fused composite sheets 100 or 102 .
- the anti-ballistics panel 300 or 302 may be formed by reheating several previously fused composite sheets 100 or 102 or impact resistant components 200 or 202 . When such previously fused material is subjected to a temperature above the softening point of the surface layers 14 , 14 ′ or 17 and below that of the core 12 , 17 , the matrix will again melt while the core layers remain substantially solid.
- a component or panel may be made with a mixture of unidirectional sheets 50 with tape and elements and unidirectional sheets 52 with core/shell fiber elements.
- Consolidation of composite sheets 100 , 102 are preferably carried out at suitable temperature and pressure conditions to facilitate both interface bonding fusion and partial migration of the melted surface layer material between the layers.
- Heated batch or platen presses may be used for multi-layer consolidation. However, it is contemplated that any other suitable press may likewise be used to provide appropriate combinations of temperature and pressure. According to a potentially preferred practice, heating is carried out at a temperature of about 130-160° C. and a pressure of about 0.5-70 bar. When exposed to such an elevated temperature and pressure, the surface layers 14 , 14 ′, 17 will soften or even melt while the core layer 12 , 16 will remain substantially solid.
- cooling is carried out under pressure to a temperature less than about 115° C. It is contemplated that maintaining pressure during the cooling step tends to inhibit shrinkage. Without wishing to be limited to a specific theory, it is believed that higher pressures may facilitate polymer flow at lower temperatures. Thus, at the higher end of the pressure range, (greater than about 20 bar) the processing temperature may be about 90-135° C. Moreover, the need for cooling under pressure may be reduced or eliminated when these lower temperatures are utilized. The temperature operating window to fuse the sheets is wide allowing for various levels of consolidation to occur thus achieving either a more structural panel or one that would delaminate more with impact. This delamination helps in the energy absorption of an impact such as a bullet.
- the tape elements used in each of the examples were fusible mono-axially drawn tape elements having dimensions of 2.2 mm wide ⁇ 65 microns thick sold under the trade designation PURE by Lankhorst/Indutech having a place of business in Sneek, The Netherlands.
- the tape elements had a polypropylene core layer surrounded by two polypropylene copolymer surface layers. The surface layers comprised about 15% by thickness of the total tape element.
- the adhesive layer was a 0.00035 in (approximately 8 ⁇ m) polyethylene film having a melting point of about 115° C.
- the composite sheets were formed by loading a roll of creel with 224 packages of yarn and creating two unidirectional sheets with 11.2 yarns per inch.
- the low melt polyethylene film was sandwiched between the sheets, heating the composite up to the melt pointing of the film, pressing the composite together, and cooling to lock the yarns together into a unidirectional sheet.
- the composite was heated to a temperature of about 220° F. and run through a nip with about 90 pli (pounds per linear inch).
- the common fiber directions of the two unidirectional sheets were aligned.
- the yarn spacing was 11.2 ends/inch.
- Each composite sheet was then cut into 10 ⁇ 12 inch pieces and stacked so that the common fiber direction in the unidirectional sheets alternated from 0 degrees to 90 degrees from composite sheet to adjacent composite sheet.
- This alternating cross plying process continued until the weight equaled 1.5 pounds per square foot (psf and 2.3 psf to form the impact resistant unidirectional component examples.
- the weight of the adhesive layer was 8% of the total weight of the example.
- This stack of cross plied unidirectional sheet was then placed in to a cold platen press. Pressure was applied to achieve 300 psi and the platens were then heated to 300° F. After the temperature reached 290° F. in the center of the stack (measured by a thermocouple), cooling was initiated. This process was completed on several panels so that ballistic testing could be completed.
- the standard twill fabric samples (comparison examples) were formed from the tape elements as described woven into a twill weave mat fabric with 11 picks and ends per inch. The layers were stacked until the weight equaled 1.5 pounds per square foot (psf) and 2.3 psf for the testing examples. The stacked layers were placed in a platen press at 300° F. where 300 psi pressure was applied until the core reached 290° F. The examples were then cooled to 150° F., had the pressure released and were removed from the press.
- psf pounds per square foot
- V 50 is the calculated speed in feet per second that the projectile travels during testing. This speed represents the speed in which the bullet would pass through the panel 50% of the time and be stopped by the panel 50% of the time.
- the unidirectional panels had approximately 8% by weight of the adhesive layer.
- the normalized areal density is the density of the tape elements in the panel (therefore, for the unidirectional panels, the normalized areal density is 8% less than the actual density).
- the V50 of these unidirectional panels is expected to be 5% better than the panel made from twill fabric.
- the reduction in V 50 as the unidirectional panel is compared to the panel made from twill fabric in both cases was approximately 2.6%.
- the unidirectional panel had 8% less by weight of the tape elements (the reinforcing elements), but the resultant panel had a reduction in V 50 performance of only 2.6%.
Abstract
The invention relates to an impact resistant component comprising at least two composite sheets fused together, each composite sheet comprising an adhesive layer fused between two unidirectional sheets, wherein each unidirectional sheet comprises a plurality of monoaxially drawn fibers arranged substantially parallel to one another along a common fiber direction, the fibers comprising a base layer of a strain oriented polymer disposed between surface layer(s) of a heat fusible polymer, wherein the surface layer(s) are characterized by a melting temperature below that of the base layer to permit fusion bonding upon application of heat, and wherein the adhesive layer has a melting temperature below that of the base layer of the unidirectional sheet.
Description
- The present invention generally relates to impact resistant components, anti-ballistics panels and methods for making the components and panels. In particular, the invention relates to impact resistant components incorporating at least two composite sheets fused together, each composite sheet comprising an adhesive layer between two unidirectional sheets of aligned fiber elements or tape elements.
- It has been proposed to form tape structures from polypropylene film that is coated with a layer of propylene copolymer including ethylene units such that the coating has a lower softening point than the core. Such tape structures are disclosed, for example, in U.S. Pat. No. 5,578,370 the teachings of which are hereby incorporated by reference in their entirety. U.S. Patent Application 2004/0242103A1 (incorporated by reference) has also proposed to form monoaxially drawn tape structures characterized by substantial draw ratios and incorporating a central layer of a polyolefin with one or two surface layers of a polyolefin from the same class as the central layer. The DSC melting point of the outer layers is lower than that of the central layer to facilitate heat bonding. Such drawn tape elements may be interwoven so as to form a mat structure which is then subjected to heat thereby fusing the tape elements in place. Multiple layers of such interwoven mat structures may be combined to form moldable structures of substantial thickness that may be shaped to three-dimensional configurations.
- In addition to tape elements, there commonly exists fiber elements that are also characterized by having a lower melting surface than the main fiber component. A core/shell fiber generally consists of a core of one type of polymer, with a surface layer (also called a shell or cladding) of a different polymer. The fiber's mechanical properties are mainly a result of the core material, whereas the surface layer determines the external properties (e.g., adhesion, friction, softness). One advantage of a core/shell fiber is the ability to achieve a combination of such properties that would be impossible in a simple, homogeneous fiber. One type of core/shell fiber has a polyester core and a polyolefin shell (e.g., polypropylene). A typical application for this fiber is in nonwoven fabrics where the lower melting point of the polypropylene surface layer allows these strong polyester core fibers to be bonded together without losing their strength.
- Anti-ballistics fibers and yarns tend to be expensive, leading to expensive anti-ballistics panels and impact resistant components made from the anti-ballistics yarns. The anti-ballistics panels made from unidirectional Kevlar and aramid fibers are typically embedded in a matrix. There is a need to produce a unidirectional anti-ballistics component or panel of fiber or tape elements using a lower amount of matrix material.
- The accompanying drawings which are incorporated in and which constitute a part of this specification illustrate several exemplary constructions and procedures in accordance with the present invention and, together with the general description of the invention given above and the detailed description set forth below, serve to explain the principles of the invention wherein:
-
FIG. 1 illustrates schematically a cross-section of one embodiment of the monoaxially drawn tape element; -
FIG. 2 illustrates schematically a cross-section of one embodiment of the monoaxially drawn tape element; -
FIGS. 3A-C illustrate schematically cross-sections of embodiments of core/shell fibers elements. -
FIGS. 3D-E illustrate schematically additional cross-sections of fiber elements. -
FIG. 4A illustrates schematically a unidirectional sheet made up of monoaxially drawn tape elements. -
FIG. 4B illustrates schematically a unidirectional sheet made up of core/shell fiber elements. -
FIG. 5A illustrates schematically a cross-section of one embodiment of the composite sheet; -
FIG. 5B illustrates schematically a cross-section of one embodiment of the composite sheet; -
FIG. 6 illustrates schematically a cross-section of one embodiment of the composite sheet; -
FIGS. 7A and B illustrate schematically a cross-section of one embodiment of the impact resistant component; -
FIGS. 8A and B illustrate schematically a cross-section of one embodiment of the impact resistant component; -
FIGS. 9A and B illustrate schematically a cross-section of one embodiment of the impact resistant component; -
FIGS. 10A-B illustrate schematically an anti-ballistics panel; -
FIG. 11 illustrates schematically a molded article. - Embodiments of the present invention will now be described by reference to the accompanying drawings, in which, to the extent possible, like reference numerals are used to designate like components in the various views.
- Referring to
FIG. 1 , there is shown one embodiment of a fiber element having a core of a strain oriented polymer and at least one surface layer of a heat fusible polymer covering at least a portion of the core, wherein the at least one surface layer is characterized by a softening temperature below that of the core to permit fusion bonding upon application of heat. Preferably, the core and/or the surface layer are an olefin polymer. In one embodiment, the fiber element is a monoaxially drawntape element 10 made up of asurface layer 14 disposed on acore 12. The core is a tape shaped core layer having an upper and lower surface and thesurface layer 14 covers one side (upper or lower surface) of thecore layer 12. Thetape element 10 may be formed by any conventional means of extruding multilayer polymeric films and then slitting the films intotape elements 10. Referring toFIG. 2 , there is shown another embodiment of thetape elements 10 made up of acore layer 12 disposed between twosurface layers - By way of example, and not limitation, the film may be formed by blown film or cast film extrusion. The film is then cut into a multiplicity of longitudinal strips of a desired width by slitting the film in a direction transverse to the layered orientation of
core layer 12 andsurface layer 14 to formtape elements 10 with cross-sections as shown inFIG. 1 . Thetape elements 10 are then drawn in order to increase the orientation of thecore layer 10 so as to provide increased strength and stiffness of the material. In another embodiment, the surface layer(s) may be added after the drawing step. After the drawing process is complete, the resulting tape elements are in the range of about 1.0 to about 5 millimeters wide. In one embodiment, thetape elements 10 have a width to thickness ratio of between about 10 and 1000. In another embodiment, the tape elements have a modulus of between 5 and 200. - Referring to Figures now to 3A-C, there is shown some embodiments of a fiber element being a core/shell
type fiber element 15 made up of asurface layer 17 disposed on acore 16 covering at least a portion of the core. Preferably, thesurface layer 17 covers thecore 16 surface area completely. Thecore 16 is typically a fiber with a circular, oblong, elliptical, elongated or other cross-section. In one embodiment, the cross-section of the core has a major to minor axis aspect ratio of between 1 and 30. Thecore 16 andsurface layer 17 may be co-extruded together, or thesurface layer 17 may be applied to the core 16 after thecore 16 has been formed. Thefiber element 15 is oriented before or after thesurface layer 17 is formed in order to increase the orientation of the core 16 so as to provide increased strength and stiffness. - Referring to
FIG. 3D , there is shown an additional embodiment of a number of fiber elements being of a core/shell type fiber elements together (each made up of asurface layer 17 disposed on a core 16 covering at least a portion of the core). While it is shown that the shape grouping or cluster of fibers elements is a circular, the group shape may also be elongated or other shapes. Additionally, eachfiber element 15 may have the same or different cross-sectional shapes. Once in the composite, the shape of the grouping may also change.FIG. 3E shows a number of fiber elements withcores 16 surrounded by asurface layer 17. In this embodiment, thesurface layer 17 surrounds all of thecores 16. In one embodiment, thecore 16 has a major axis diameter of between 1 and 1000 micrometers (preferably between 50 and 500 micrometers) and the surface layer has a thickness of between about 5 and 30% of the total. - The
core fiber elements core core core core core core core - In an embodiment where the core 12 or 17 is polypropylene, the material of surface layers 14, 14′, 17 is preferably a copolymer of propylene and ethylene or an α-olefin. In one embodiment, the surface layers 14, 14′, 17 comprise a random copolymer of propylene-ethylene with an ethylene content of about 1-25 mol. %, and a propylene content of about 75-99 mol. %. It may be further preferred to use said copolymer with a ratio of about 95 mol. % propylene to about 5 mol. % ethylene. Instead of said copolymer or in combination therewith, a polyolefin, preferably a polypropylene homopolymer or polypropylene copolymer, prepared with a metallocene catalyst, may be used for the surface layers 14, 14′, 17. It is also contemplated that materials such as poly(4-methyl-1-pentene) (PMP) and polyethylene may be useful as a blend with such copolymers in the surface layers 14, 14′, 17. The surface layer material should be selected such that the softening point of the
surface layer core layer 12, and preferably between about 15-40° C. lower. The upper limit of this difference is not thought to be critical, and the difference in softening points is typically less than 70° C. Softening point, for this application, is defined as the Vicat softening temperature (ASTM D1525). It is desirable to minimize the amount of adhesive used to maximize the amount of fiber elements in a composite. - By way of example only, and not limitation, one
tape element 10 that may be particularly useful is believed to be marketed under the trade designation PURE by Lankhorst/Indutech having a place of business in Sneek, The Netherlands. -
FIG. 4A illustrates aunidirectional sheet 50 formed from a multiplicity of fiber elements beingtape elements 10. The tape elements are aligned parallel along a common fiber direction of theunidirectional sheet 50. In one embodiment, thetape elements 10 in theunidirectional sheet 50 do not overlap one another, and may have gaps between thetape elements 10. In another embodiment, the tape elements overlap one another up to 90% in theunidirectional sheet 50. Theunidirectional sheet 50 is preferably able to be bent to a radius of about 1 cm without affecting its physical performance. One approach for aligning the tape elements is to align the tape elements into a sheet by pulling yarn from a creel. Using a roll-off creel is helpful to reduce twist in the yarn. -
FIG. 4B illustrates aunidirectional sheet 52 formed from a multiplicity of core/shelltype fiber elements 15. Thefiber elements 15 are aligned parallel along a common fiber direction of theunidirectional sheet 52. In one embodiment thefiber elements 15 in theunidirectional sheet 52 do not overlap one another, and may have gaps between thefiber elements 15. In another embodiment, the fiber elements may overlap one another up to 90% in theunidirectional sheet 52. Theunidirectional sheet 52 may additionally have a polymer matrix. Theunidirectional sheet 52 is preferably able to be bent to a radius of about 1 cm without affecting its physical performance. One approach for aligning the fiber elements is to align the tape elements into a sheet by pulling yarn from a creel. Using a roll-off creel is helpful to reduce twist in the yarn. -
FIGS. 5 and 5B illustrate composite sheets, each made up of twounidirectional sheets 50 and oneadhesive layer 60. The composite sheets are easier to handle than the unidirectional sheets, as the unidirectional sheets are composed of thetape elements 10 not bound in any way to one another. In the embodiment where the unidirectional sheets are made up oftape elements 10 with acore layer 12 and one surface layer 14 (as shown inFIG. 5A ) theadhesive layer 60 is adjacent and sandwiched between the core layers 12 of thetape elements 10 in theunidirectional sheet 50. In the embodiment where the unidirectional sheets are made up oftape elements 10 with acore layer 12 and twosurface layers FIG. 5B ), theadhesive layer 60 is adjacent to and sandwiched between the surface layers 14′ of thetape elements 10. Within eachcomposite sheet 100, the common fiber direction of theunidirectional sheets 50 may be aligned, or rotated relative to each other, for example 90 degrees. Preferably, the common fiber direction of theunidirectional sheets 50 in thecomposite sheet 100 are the same. -
FIG. 6 illustrates composite sheets, each made up of twounidirectional sheets 52 formed fromfiber elements 15 and oneadhesive layer 60. The composite sheets are easier to handle than the unidirectional sheets, as the unidirectional sheets are composed of thefiber elements 15 not bound in any way to one another. Theadhesive layer 60 is adjacent and sandwiched between the surface layers 17 of thefiber elements 15. Within eachcomposite sheet 102, the common fiber direction of theunidirectional sheets 52 may be aligned, or rotated relative to each other, for example 90 degrees. Preferably, the common fiber direction of theunidirectional sheets 52 in thecomposite sheet 102 are the same. - The
adhesive layer 60 preferably comprises a material which is compatible with the unidirectional material and fuses the unidirectional material into aunidirectional sheet 52. The adhesive layer may be activated to fuse the unidirectional material by pressure, heat, UV, other activation methods, or any combination thereof. In one embodiment, the adhesive is a pressure sensitive adhesive. In another embodiment, the adhesive has a softening point less than that of the surface layer of the fiber elements. Preferably, the softening point of the adhesive is at least 10° C. less than that of the surface layer of the fiber elements. In one embodiment, a melting point of less than 130° C. is preferred. For unidirectional sheets made up of tape or fiber elements with an olefin core and surface layers, theadhesive layer 60 may be, but is not limited to EVA, LLDPE, LDPE, HDPE, copolymers of polypropylene, and the like. Theadhesive layer 60 preferably has a lower softening temperature than the layer of the tape orfiber element adhesive layer 60. This corresponds to thecore layer 12 for thetape element 10 having acore layer 12 and one surface layer 14 (as shown inFIG. 5A ), thesurface layer 14′ for thetape element 10 having acore layer 12 and surface layers 14 and 14′ (as shown inFIG. 5B ), and thesurface layer 17 for a fiber element 15 (as shown inFIG. 6 ). Theadhesive layer 60 preferably has a thickness of between about 10 μm and 100 μm. For pressure sensitive adhesives, the amount of tack is preferably high enough to stabilize the unidirectional sheets for handling. - The adhesive layer may be applied to the
unidirectional sheets adhesive layer 60 can be formed by thermal processing such as extrusion and co-extrusion with and without stretching, blow molding, injection molding, lamination, etc. Theadhesive layer 60 may also be an adhesive scrim, powder coating, or the like. - Referring now to
FIGS. 7A-B and 8A-B, there is shown different embodiments of the impactresistant component 200. While the impactresistant components 200 shown inFIG. 7A-B and 8A-B are formed from 2composite sheets 100,additional composites sheets 100 may be added to the top or bottom of the impactresistant component 200 shown. Preferably, theadhesive layers 60 are in an amount of about 0.2 to 20%, more preferably about 2-10% of the weight of the impact resistant component. In one embodiment, the tape elements and the adhesive layer comprise polypropylene. This creates an impact resistant component that is essentially polypropylene increasing the recycleability of the component. - Referring now to
FIGS. 9A-B , there is shown another embodiment of the impactresistant component 202 formed from shell/coretype fiber elements 15. While the impactresistant components 202 shown inFIG. 9A-B are formed from 2composite sheets 102,additional composites sheets 102 may be added to the top or bottom of the impactresistant component 202 shown. Preferably, theadhesive layers 60 are in an amount of about 0.2 to 20%, more preferably about 2-10% of the weight of the impact resistant component. In one embodiment, the fiber elements and the adhesive layer comprise polypropylene. This creates an impact resistant component that is completely or essentially polypropylene increasing the recycleability of the component. - Referring back to
FIGS. 7A and B, there is shown impact resistant components formed fromtape elements 10 with acore layer 12 and onesurface layer 14. The impactresistant component 200 is formed when the surface layers 14 from thecomposite sheets 100 are fused using heat and optionally pressure. There are no additional layers, adhesives, or treatments added to the surface layers 14 of thetape elements 10. InFIG. 7A , the common fiber direction of theunidirectional sheets 50 in onecomposite sheet 100 is the same (parallel to) as the common fiber direction of theunidirectional sheets 50 of the adjacentcomposite sheet 100. InFIG. 7B , the common fiber direction of theunidirectional sheets 50 in onecomposite sheet 100 is the perpendicular (rotated 90 degrees) to the common fiber direction of theunidirectional sheets 50 of the adjacentcomposite sheet 100. While inFIGS. 7A and B, 0 and 90 degree rotations have been shown; any rotation angle is feasible and contemplated. The structure of the impact resistant component ofFIGS. 7A and B in written form is as follows: -
- . . . AB-Adh-BA-AB-Adh-AB . . .
- (B being the core layer, A being a surface layer, and Adh being the adhesive layer)
- The impact resistant components shown in
FIGS. 8A and B are formed fromtape elements 10 with acore layer 12 and twosurface layers resistant component 200 is formed when the surface layers 14 from thecomposite sheets 100 are fused using heat and optionally pressure. There are no additional layers, adhesives, or treatments added to the surface layers 14 of thetape elements 10. InFIG. 8A , the common fiber direction of theunidirectional sheets 50 in onecomposite sheet 100 is the same (parallel to) as the common fiber direction of theunidirectional sheets 50 of the adjacentcomposite sheet 100. InFIG. 8B , the common fiber direction of theunidirectional sheets 50 in onecomposite sheet 100 is the perpendicular (rotated 90 degrees) to the common fiber direction of theunidirectional sheets 50 of the adjacentcomposite sheet 100. While inFIGS. 8A and B, 0 and 90 degree rotations have been shown, any rotation angle is contemplated. The structure of the impact resistant component ofFIGS. 8A and B in written form is as follows: -
- . . . ABA′-Adh-A′BA-ABA′-Adh-A′BA . . .
- (B being the core layer, A and A′ being surface layers, and Adh being the adhesive layer).
- The impact
resistant components 202 shown inFIGS. 9A and B are formed fromfiber elements 15 with acore 16 and asurface layer 17. The impactresistant component 202 is formed when the surface layers 17 from thecomposite sheets 102 are fused using heat and optionally pressure. There are no additional layers, adhesives, or treatments added to the surface layers 17 of thefiber elements 15. InFIG. 9A , the common fiber direction of theunidirectional sheets 52 in onecomposite sheet 102 is the same (parallel to) as the common fiber direction of theunidirectional sheets 52 of the adjacentcomposite sheet 102. InFIG. 9B , the common fiber direction of theunidirectional sheets 52 in onecomposite sheet 102 is the perpendicular (rotated 90 degrees) to the common fiber direction of theunidirectional sheets 52 of the adjacentcomposite sheet 102. While inFIGS. 9A and B, 0 and 90 degree rotations have been shown, any rotation angle is contemplated. -
FIG. 10A illustrates ananti-ballistics panel 300, according to one embodiment of the invention. Theanti-ballistics panel 300 is made up of at least 10composite sheets 100 formed fromtape elements 10 fused together, more preferably 20 to 100. The core/shell nature of thefiber elements 15 has not been shown to reduce the complexity of the illustration. It has been shown that 10composite sheets 100 fused together resist penetration by objects. While theanti-ballistics panel 300 is shown with the common fiber direction of eachunidirectional sheet 50 parallel to the adjacent sheets, eachunidirectional sheet 50 may be rotated any amount with respect to the adjacentunidirectional sheets 50. -
FIG. 10B illustrates ananti-ballistics panel 302, according to one embodiment of the invention. Theanti-ballistics panel 302 is made up of at least 10 composite sheets formed fromfiber elements 15 fused together, more preferably 20 to 100. It has been shown that 10composite sheets 102 fused together resist penetration by objects. While theanti-ballistics panel 302 is shown with the common fiber direction of eachunidirectional sheet 52 rotated 90 degrees with respect to the adjacent layers, eachunidirectional sheet 52 may be rotated any amount with respect to the adjacentunidirectional sheets 52. - The impact
resistant component anti-ballistics panel FIG. 11 of a moldedhelmet 400. Other articles of the impactresistant component anti-ballistics panel - The process for forming an impact resistant component comprises:
- 1) forming unidirectional sheets comprising arranging a plurality of monoaxially drawn fibers substantially parallel to one another along a common fiber direction, the fiber elements (10 or 15) comprising a core (12 or 16) of a strain oriented polymer and at least one surface layer (14 or 17) of a heat fusible polymer surface at least a portion of the core (12 or 16), wherein the at least one surface layer (14 or 17) is characterized by a softening temperature below that of the core (12 or 16) to permit fusion bonding upon application of heat.
- 2) sandwiching an
adhesive layer 60 between two unidirectional sheets (50 or 52). - 3) activating (preferably by heat) the sandwiched
adhesive layer 60 and unidirectional sheets (50 or 52) to a approximately the melting temperature of theadhesive layer 60 to form a composite sheet (100 or 102) with optional pressure. - 4) stacking at least 2 composite sheets (100 or 102).
- 5) applying heat (and optionally pressure of between about 0.5 and 150 bars) to the stacked composite sheets (100 or 102) to bond the surface layers (14 or 17) of the composite sheets (100 or 102) together.
- Forming an anti-ballistics panel (300 and 302) follows the same steps as above, except that at least 10 composite sheets (100, 102) are stacked together. The method discloses the
tape elements 10 comprising acore layer 12 and surface layers 14 and 14′, the method also applies for impactresistant components 200 andanti-ballistics panels 300 made fromtape elements 10 having acore layer 12 and onesurface layer 14. The surface layers 14 between the composite sheets fuse to form thecomponent 200 orpanel 300. - According to one contemplated practice, the layers of
composite sheets composite sheet composite sheets resistant component composite sheets anti-ballistics panel composite sheets resistant components component panel 300 or 303 with any desired thickness or number of sheets. Additionally, it is contemplated that a component or panel may be made with a mixture ofunidirectional sheets 50 with tape and elements andunidirectional sheets 52 with core/shell fiber elements. - Consolidation of
composite sheets core layer - The tape elements used in each of the examples were fusible mono-axially drawn tape elements having dimensions of 2.2 mm wide×65 microns thick sold under the trade designation PURE by Lankhorst/Indutech having a place of business in Sneek, The Netherlands. The tape elements had a polypropylene core layer surrounded by two polypropylene copolymer surface layers. The surface layers comprised about 15% by thickness of the total tape element.
- The adhesive layer was a 0.00035 in (approximately 8 μm) polyethylene film having a melting point of about 115° C.
- The composite sheets were formed by loading a roll of creel with 224 packages of yarn and creating two unidirectional sheets with 11.2 yarns per inch. The low melt polyethylene film was sandwiched between the sheets, heating the composite up to the melt pointing of the film, pressing the composite together, and cooling to lock the yarns together into a unidirectional sheet. The composite was heated to a temperature of about 220° F. and run through a nip with about 90 pli (pounds per linear inch). The common fiber directions of the two unidirectional sheets were aligned. The yarn spacing was 11.2 ends/inch. Each composite sheet was then cut into 10×12 inch pieces and stacked so that the common fiber direction in the unidirectional sheets alternated from 0 degrees to 90 degrees from composite sheet to adjacent composite sheet. This alternating cross plying process continued until the weight equaled 1.5 pounds per square foot (psf and 2.3 psf to form the impact resistant unidirectional component examples. The weight of the adhesive layer was 8% of the total weight of the example. This stack of cross plied unidirectional sheet was then placed in to a cold platen press. Pressure was applied to achieve 300 psi and the platens were then heated to 300° F. After the temperature reached 290° F. in the center of the stack (measured by a thermocouple), cooling was initiated. This process was completed on several panels so that ballistic testing could be completed.
- The standard twill fabric samples (comparison examples) were formed from the tape elements as described woven into a twill weave mat fabric with 11 picks and ends per inch. The layers were stacked until the weight equaled 1.5 pounds per square foot (psf) and 2.3 psf for the testing examples. The stacked layers were placed in a platen press at 300° F. where 300 psi pressure was applied until the core reached 290° F. The examples were then cooled to 150° F., had the pressure released and were removed from the press.
- Examples were then subjected to ballistic testing under the Department of Defense MIL-STD-662 V50 Ballistic Test for Armor. The resulting V50 measurements for each threat and conditions are below. The V50 is the calculated speed in feet per second that the projectile travels during testing. This speed represents the speed in which the bullet would pass through the
panel 50% of the time and be stopped by thepanel 50% of the time. -
Panal % Fabric Arial Normalized reduction const. Density Areal Density Bullet V50 in V50 Unidirectional 1.5 psf 1.38 psf 17 grain 1483 26% FSP Twill 1.5 psf 1.5 psf 17 grain 1522 Fabric FSP Unidirectional 2.3 psf 2.12 psf 44 1377 2.6% magnum Twill 2.3 psf 2.3 psf 44 1414 Fabric magnum - The unidirectional panels had approximately 8% by weight of the adhesive layer. The normalized areal density is the density of the tape elements in the panel (therefore, for the unidirectional panels, the normalized areal density is 8% less than the actual density). For equivalent normalized areal densities, the V50 of these unidirectional panels is expected to be 5% better than the panel made from twill fabric. The reduction in V50 as the unidirectional panel is compared to the panel made from twill fabric in both cases was approximately 2.6%. The unidirectional panel had 8% less by weight of the tape elements (the reinforcing elements), but the resultant panel had a reduction in V50 performance of only 2.6%.
- The invention has been described in detail with particular reference to certain preferred embodiments thereof, but it will be understood that variations and modifications can be effected within the spirit and scope of the invention.
Claims (22)
1. An impact resistant component comprising:
at least two composite sheets fused together, each composite sheet comprising two unidirectional sheets and an adhesive layer, wherein the adhesive layer fuses the unidirectional sheets to one another;
wherein each unidirectional sheet comprises a plurality of monoaxially drawn fiber elements arranged substantially parallel to one another along a common fiber direction, the fiber elements comprising a core of a strain oriented polymer and one surface layer of a heat fusible polymer that covers at least a portion of one side of the core, wherein the surface layer is characterized by a softening temperature below that of the core to permit fusion bonding upon application of heat and
wherein the adhesive layer has a softening point lower than the surface layer of the fiber elements, wherein the unidirectional sheets are oriented such that the adhesive layer adheres to the core layers of the fiber elements and the surface layers form the outer surface of the composite sheets, wherein the unidirectional sheets of each composite sheet have the same common fiber direction, and:
wherein the surface layers of the composite sheets fuse together to form the fused impact resistant component.
2. (canceled)
3. The impact resistant component of claim 1 , wherein the at least one surface layer of the fiber elements comprises an olefin polymer.
4. The impact resistant component of claim 1 , wherein the core of the fiber elements comprises an olefin polymer.
5-6. (canceled)
7. The impact resistant component of claim 1 , wherein the core is comprised of one or more fibers having a cross-sectional shape selected from the group consisting of circular, oblong, and elliptical and the at least one surface layer covers the entire surface area of the core.
8. The impact resistant component of claim 1 , wherein the adhesive layer is in an amount of between about 0.2 to 10% of the weight of the impact resistant component.
9. The impact resistant component of claim 1 , wherein the at least two composite sheets are fused together without additional adhesives.
10. The impact resistant component of claim 1 , wherein the unidirectional sheets of each composite sheet have the same common fiber direction.
11. The impact resistant component of claim 10 , wherein the common fiber direction of the unidirectional sheets of one composite sheet are perpendicular to the common fiber direction of the unidirectional sheets of the adjacent composite sheets.
12. The impact resistant component claim 1 , wherein the core, surface layer, and the adhesive layer comprise a polymer selected from the group consisting of polypropylene and polyethylene.
13. An impact resistant component comprising:
at least 10 composite sheets fused together, each composite sheet comprising two unidirectional sheets and an adhesive layer, wherein the adhesive layer fuses the unidirectional sheets to one another, wherein each unidirectional sheet comprises
a plurality of monoaxially drawn fiber elements arranged substantially parallel to one another along a common fiber direction, the fiber elements comprising a core of a strain oriented polymer and one surface layer of a heat fusible polymer that covers at least a portion of one side of the core, wherein the surface layer is characterized by a softening temperature below that of the core to permit fusion bonding upon application of heat and
wherein the adhesive layer fuses the unidirectional sheets together, where in the adhesive layer has a softening point lower than the surface layer of the fiber elements, wherein the unidirectional sheets are oriented such that the adhesive layer adheres to the core layers of the fiber elements and the surface layers form the outer surface of the composite sheets, and;
wherein the surface layers of the composite sheets fuse together to form the fused impact resistant component.
14. (canceled)
15. The impact resistant component of claim 13 , wherein the at least one surface layer and the core of the fiber elements comprises an olefin polymer.
16-27. (canceled)
28. An impact resistant component comprising:
at least two composite sheets fused together,
each composite sheet comprising two unidirectional sheets and an adhesive layer, wherein each unidirectional sheet comprises
a plurality of monoaxially drawn fiber elements arranged substantially parallel to one another along a common fiber direction, the fiber elements comprising a core of a strain oriented polymer and surface layers of a heat fusible polymer that covers at least a portion of each side of the core, wherein the surface layers are characterized by a softening temperature below that of the core to permit fusion bonding upon application of heat; and,
wherein the unidirectional sheets within each composite sheet have the same common fiber direction, wherein the adhesive layer fuses the unidirectional sheets together, wherein the adhesive layer has a softening point lower than the surface layer of the fiber elements, and wherein the surface layers of the composite sheets fuse together to form the fused impact resistant component.
29. The impact resistant component of claim 29 , wherein the unidirectional sheets of each composite sheet have the same common fiber direction.
30. The impact resistant component of claim 29 , wherein the at least two composite sheets are fused together without additional adhesives.
31. The impact resistant component of claim 29 , wherein the common fiber direction of the unidirectional sheets of one composite sheet are perpendicular to the common fiber direction of the unidirectional sheets of the adjacent composite sheets.
32. An impact resistant component comprising:
at least ten composite sheets fused together,
each composite sheet comprising two unidirectional sheets and an adhesive layer, wherein each unidirectional sheet comprises
a plurality of monoaxially drawn fiber elements arranged substantially parallel to one another along a common fiber direction, the fiber elements comprising a core of a strain oriented polymer and surface layers of a heat fusible polymer that covers at least a portion of each side of the core, wherein the surface layers are characterized by a softening temperature below that of the core to permit fusion bonding upon application of heat; and,
wherein the unidirectional sheets within each composite sheet have the same common fiber direction, wherein the adhesive layer fuses the unidirectional sheets together, wherein the adhesive layer has a softening point lower than the surface layer of the fiber elements, and wherein the surface layers of the composite sheets fuse together to form the fused impact resistant component.
33. The impact resistant component of claim 32 , wherein the at least two composite sheets are fused together without additional adhesives.
34. The impact resistant component of claim 32 , wherein the common fiber direction of the unidirectional sheets of one composite sheet are perpendicular to the common fiber direction of the unidirectional sheets of the adjacent composite sheets.
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
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US11/519,134 US20080124513A1 (en) | 2006-09-11 | 2006-09-11 | Moldable fabric with unidirectional tape yarns |
PCT/US2006/037572 WO2008054372A2 (en) | 2006-09-11 | 2006-09-26 | Moldable fabric with unidirectional yarns |
EP20060851889 EP2061653A2 (en) | 2006-09-11 | 2006-09-26 | Moldable fabric with unidirectional yarns |
US12/286,250 US7892379B2 (en) | 2006-09-11 | 2008-09-29 | Moldable fabric with unidirectional tape yarns |
IL197229A IL197229A (en) | 2006-09-11 | 2009-02-24 | Moldable fabric with unidirectional yarns |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/519,134 US20080124513A1 (en) | 2006-09-11 | 2006-09-11 | Moldable fabric with unidirectional tape yarns |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US12/286,250 Division US7892379B2 (en) | 2006-09-11 | 2008-09-29 | Moldable fabric with unidirectional tape yarns |
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US20080124513A1 true US20080124513A1 (en) | 2008-05-29 |
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US11/519,134 Abandoned US20080124513A1 (en) | 2006-09-11 | 2006-09-11 | Moldable fabric with unidirectional tape yarns |
US12/286,250 Expired - Fee Related US7892379B2 (en) | 2006-09-11 | 2008-09-29 | Moldable fabric with unidirectional tape yarns |
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US12/286,250 Expired - Fee Related US7892379B2 (en) | 2006-09-11 | 2008-09-29 | Moldable fabric with unidirectional tape yarns |
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US (2) | US20080124513A1 (en) |
EP (1) | EP2061653A2 (en) |
IL (1) | IL197229A (en) |
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Publication number | Priority date | Publication date | Assignee | Title |
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Citations (53)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4079161A (en) * | 1974-07-12 | 1978-03-14 | Phillips Petroleum Company | Transparent oriented polyolefin laminated armor structure |
US4213812A (en) * | 1970-03-05 | 1980-07-22 | Phillips Petroleum Company | Process for preparing crosslapped film structures |
US4309487A (en) * | 1968-08-23 | 1982-01-05 | Phillips Petroleum Co. | Laminated armor |
US4316933A (en) * | 1979-05-02 | 1982-02-23 | Fraser Ian E B | Tape for use as the warp and weft of woven fabrics particularly useful for packaging |
US4403012A (en) * | 1982-03-19 | 1983-09-06 | Allied Corporation | Ballistic-resistant article |
US4426415A (en) * | 1981-12-11 | 1984-01-17 | V&L Manufacturing Company, Inc. | Tufted carpeting, especially artificial turf, with tufts stitched through multiple layers of pre-woven backing material of differing gauge |
US4457985A (en) * | 1982-03-19 | 1984-07-03 | Allied Corporation | Ballistic-resistant article |
US4622254A (en) * | 1981-08-31 | 1986-11-11 | Toray Industries, Inc. | Fiber material for reinforcing plastics |
US4705706A (en) * | 1986-09-16 | 1987-11-10 | Avco Synthetic Turf Production Distribution, Inc. | Tufted carpeting having stitches thermally bonded to backing |
US4820568A (en) * | 1987-08-03 | 1989-04-11 | Allied-Signal Inc. | Composite and article using short length fibers |
US4916000A (en) * | 1987-07-13 | 1990-04-10 | Allied-Signal Inc. | Ballistic-resistant composite article |
US4953234A (en) * | 1987-08-03 | 1990-09-04 | Allied-Signal Inc. | Impact resistant helmet |
US4980227A (en) * | 1987-06-03 | 1990-12-25 | Diatex Co., Ltd. | Netlike sheet and method for producing multilayer yarn for producing the same |
US5112667A (en) * | 1987-08-03 | 1992-05-12 | Allied-Signal Inc. | Impact resistant helmet |
US5124195A (en) * | 1990-01-10 | 1992-06-23 | Allied-Signal Inc. | Flexible coated fibrous webs |
US5354605A (en) * | 1993-04-02 | 1994-10-11 | Alliedsignal Inc. | Soft armor composite |
US5437905A (en) * | 1994-05-17 | 1995-08-01 | Park; Andrew D. | Ballistic laminate structure in sheet form |
US5529826A (en) * | 1994-02-15 | 1996-06-25 | Tailor; Dilip K. | Fabric-faced thermoplastic composite panel |
US5578357A (en) * | 1992-02-10 | 1996-11-26 | Polyloom Corporation Of America | Carpet and techniques for making and recycling same |
US5578370A (en) * | 1990-02-02 | 1996-11-26 | Don & Low (Holdings) Limited | Molecularly interspersed thermoplastic composite mat |
US5589115A (en) * | 1987-11-16 | 1996-12-31 | Corning Incorporated | Method for making fiber-reinforced ceramic matrix composite |
US5643390A (en) * | 1995-05-04 | 1997-07-01 | The University Of Delaware | Bonding techniques for high performance thermoplastic compositions |
US5861202A (en) * | 1994-12-16 | 1999-01-19 | Nippon Petrochemicals Co., Ltd. | Laminated bodies and woven and nonwoven fabrics comprising α-olefin polymeric adhesion materials catalyzed with cyclopentadienyl catalyst |
US5879492A (en) * | 1998-04-17 | 1999-03-09 | Northrop Grumman Corporation | Z-peel sheets |
US5925434A (en) * | 1997-06-12 | 1999-07-20 | Bp Amoco Corporation | Tuftable backing and carpet construction |
US5935678A (en) * | 1994-05-17 | 1999-08-10 | Park; Andrew D. | Ballistic laminate structure in sheet form |
US5935651A (en) * | 1994-05-11 | 1999-08-10 | Raytheon Ti Systems, Inc. | High strength, high modulus continuous polymeric material for durable, impact resistant applications |
US5962101A (en) * | 1997-04-29 | 1999-10-05 | Donald A. Irwin, Sr. | Dimensionally stable tufted carpet |
US6054086A (en) * | 1995-03-24 | 2000-04-25 | Nippon Petrochemicals Co., Ltd. | Process of making high-strength yarns |
US6106924A (en) * | 1997-01-30 | 2000-08-22 | Nippon Petrochemicals Company, Limited | Laminate material and uniaxially oriented laminate |
US6156679A (en) * | 1996-12-25 | 2000-12-05 | Chisso Corporation | Heat-fusible composite fiber and non-woven fabric produced from the same |
US6312638B1 (en) * | 1996-10-04 | 2001-11-06 | Btg International | Process of making a compacted polyolefin article |
US6328923B1 (en) * | 1996-10-04 | 2001-12-11 | Btg International Limited | Process of making a compacted polyolefin article |
US6475592B1 (en) * | 1997-04-29 | 2002-11-05 | Darwin Enterprises, Inc. | Carpet backing that provides dimensional stability |
US6509105B2 (en) * | 1988-12-07 | 2003-01-21 | Laminating Technologies, Inc. | Method of making a composite of paper and plastic film and composites |
US6562435B1 (en) * | 1999-03-20 | 2003-05-13 | Survival, Incorporated | Method for forming or securing unindirectionally-oriented fiber strands in sheet form, such as for use in a ballistic-resistant panel |
US20030175474A1 (en) * | 2002-03-13 | 2003-09-18 | Higgins Kenneth B. | Textile constructions with stabilized primary backings and related methods |
US20030175475A1 (en) * | 2002-03-13 | 2003-09-18 | Higgins Kenneth B. | Textile constructions, components or materials and related methods |
US6641893B1 (en) * | 1997-03-14 | 2003-11-04 | Massachusetts Institute Of Technology | Functionally-graded materials and the engineering of tribological resistance at surfaces |
US6645610B1 (en) * | 1998-04-20 | 2003-11-11 | Northrop Grumann | Cured composite material formed utilizing Z-peel sheets |
US20030224143A1 (en) * | 2002-02-14 | 2003-12-04 | Ianniello Peter J. | Fuzzy woven layers, geocomposite laminates incorporating them, and related methods |
US6740386B2 (en) * | 2001-05-02 | 2004-05-25 | Burlington Industries, Inc. | Tufted covering for floors and/or walls |
US6824863B1 (en) * | 1999-09-30 | 2004-11-30 | Sumitomo Chemical Company, Limited | Fiber reinforced polypropylene-based composite material |
US20040242103A1 (en) * | 2001-07-19 | 2004-12-02 | Joachim Loos | Polyolefin film, tape or yarn |
US20050003727A1 (en) * | 2003-07-01 | 2005-01-06 | Chiou Minshon J. | Flexible spike/ballistic penetration-resistant articles |
US6897170B2 (en) * | 1998-12-11 | 2005-05-24 | Propex Fabrics, Inc. | Tuftable fabric with balanced construction |
US20050233107A1 (en) * | 2004-04-19 | 2005-10-20 | Hartman David R | Recyclable tufted carpet with improved stability and durability |
US20050263234A1 (en) * | 2003-10-28 | 2005-12-01 | Greener Bags, Llc | Reinforced paper product and method for making same |
US20060151104A1 (en) * | 2002-09-27 | 2006-07-13 | Jacobs Johannes A J | Method for reinforcing an article |
US20060222837A1 (en) * | 2005-03-31 | 2006-10-05 | The Boeing Company | Multi-axial laminate composite structures and methods of forming the same |
US20070071942A1 (en) * | 2005-09-27 | 2007-03-29 | Brian Callaway | Moldable construction incorporating non-olefin bonding interface |
US20070071941A1 (en) * | 2005-09-27 | 2007-03-29 | Eleazer Howell B | Moldable construction incorporating bonding interface |
US20070071960A1 (en) * | 2005-09-27 | 2007-03-29 | Eleazer Howell B | Moldable fabric with variable constituents |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS4840870A (en) | 1971-09-25 | 1973-06-15 | ||
DK161152C (en) | 1983-03-03 | 1991-11-11 | Genentech Inc | POLYPEPTIDE OF PROPERTIES AS HUMAN BETA-NERVE GROWTH FACTOR AND METHOD FOR PREPARATION THEREOF, DNA ISOLAT comprising a sequence encoding the polypeptide is replicable expression vector for DNA SEQUENCE recombinant host cell transformed with the vector, pharmaceutical composition comprising the polypeptide and be stated in. THAT INCLUDES THE APPLICATION OF THE POLYPEPTID IN FORCE. OF A PHARMACEUTICAL PREPARATION |
JPS6290317A (en) | 1985-10-11 | 1987-04-24 | Nippon Ester Co Ltd | Hot-melt type flat conjugate polyester fiber |
EP0344318A4 (en) | 1987-11-30 | 1990-05-14 | Hagihara Ind | Nonwoven fabric and apparatus for manufacturing same. |
JPH07300763A (en) | 1994-04-22 | 1995-11-14 | Nippon Petrochem Co Ltd | Nonwoven or woven fabric made of polypropylene |
CN1076282C (en) | 1995-03-02 | 2001-12-19 | 三井化学株式会社 | Polypropylene composite film |
US5888915A (en) | 1996-09-17 | 1999-03-30 | Albany International Corp. | Paper machine clothings constructed of interconnected bicomponent fibers |
CN1096510C (en) | 1996-09-18 | 2002-12-18 | 阿尔巴尼国际公司 | yarns of covered high modulus material and fabrics formed therefrom |
JPH10251956A (en) | 1997-03-11 | 1998-09-22 | Unitika Ltd | Sound-absorbing material |
IT1291580B1 (en) | 1997-04-16 | 1999-01-11 | Coatex S R L | TEXTILE MATERIAL AS A SUPPORT FOR COAGULATION AND PRODUCT OBTAINED THROUGH THE COAGULATION OF RESINS ON THIS SUPPORT |
JP2000008244A (en) | 1998-06-18 | 2000-01-11 | Hagiwara Kogyo Kk | Flat yarn cloth for reinforcement lamination |
NL1011516C2 (en) | 1999-03-10 | 2000-09-12 | Adprotech B V | Laminate of metal layers bonded with a fiber-reinforced adhesive layer. |
GB0111287D0 (en) | 2001-05-09 | 2001-06-27 | Amoco Detschland Gmbh | Polyolefin sheet |
WO2002101319A1 (en) * | 2001-06-12 | 2002-12-19 | Teijin Twaron Gmbh | Laminated ballistic structure comprising alternating unidirectional and thermoplastic layers |
GB0128405D0 (en) | 2001-11-27 | 2002-01-16 | Btg Int Ltd | Process for fabricating polyolefin sheet |
EP1650021A1 (en) | 2004-10-25 | 2006-04-26 | Lankhorst Indutech B.V. | Method for preparing a composite product of a polyolefenic article and a cloth |
-
2006
- 2006-09-11 US US11/519,134 patent/US20080124513A1/en not_active Abandoned
- 2006-09-26 WO PCT/US2006/037572 patent/WO2008054372A2/en active Application Filing
- 2006-09-26 EP EP20060851889 patent/EP2061653A2/en not_active Withdrawn
-
2008
- 2008-09-29 US US12/286,250 patent/US7892379B2/en not_active Expired - Fee Related
-
2009
- 2009-02-24 IL IL197229A patent/IL197229A/en not_active IP Right Cessation
Patent Citations (66)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4309487A (en) * | 1968-08-23 | 1982-01-05 | Phillips Petroleum Co. | Laminated armor |
US4213812A (en) * | 1970-03-05 | 1980-07-22 | Phillips Petroleum Company | Process for preparing crosslapped film structures |
US4079161A (en) * | 1974-07-12 | 1978-03-14 | Phillips Petroleum Company | Transparent oriented polyolefin laminated armor structure |
US4316933A (en) * | 1979-05-02 | 1982-02-23 | Fraser Ian E B | Tape for use as the warp and weft of woven fabrics particularly useful for packaging |
US4622254A (en) * | 1981-08-31 | 1986-11-11 | Toray Industries, Inc. | Fiber material for reinforcing plastics |
US4426415A (en) * | 1981-12-11 | 1984-01-17 | V&L Manufacturing Company, Inc. | Tufted carpeting, especially artificial turf, with tufts stitched through multiple layers of pre-woven backing material of differing gauge |
US4403012A (en) * | 1982-03-19 | 1983-09-06 | Allied Corporation | Ballistic-resistant article |
US4457985A (en) * | 1982-03-19 | 1984-07-03 | Allied Corporation | Ballistic-resistant article |
US4705706A (en) * | 1986-09-16 | 1987-11-10 | Avco Synthetic Turf Production Distribution, Inc. | Tufted carpeting having stitches thermally bonded to backing |
US4980227A (en) * | 1987-06-03 | 1990-12-25 | Diatex Co., Ltd. | Netlike sheet and method for producing multilayer yarn for producing the same |
US4916000A (en) * | 1987-07-13 | 1990-04-10 | Allied-Signal Inc. | Ballistic-resistant composite article |
US4820568A (en) * | 1987-08-03 | 1989-04-11 | Allied-Signal Inc. | Composite and article using short length fibers |
US4953234A (en) * | 1987-08-03 | 1990-09-04 | Allied-Signal Inc. | Impact resistant helmet |
US5112667A (en) * | 1987-08-03 | 1992-05-12 | Allied-Signal Inc. | Impact resistant helmet |
US5589115A (en) * | 1987-11-16 | 1996-12-31 | Corning Incorporated | Method for making fiber-reinforced ceramic matrix composite |
US6509105B2 (en) * | 1988-12-07 | 2003-01-21 | Laminating Technologies, Inc. | Method of making a composite of paper and plastic film and composites |
US5124195A (en) * | 1990-01-10 | 1992-06-23 | Allied-Signal Inc. | Flexible coated fibrous webs |
US5578370A (en) * | 1990-02-02 | 1996-11-26 | Don & Low (Holdings) Limited | Molecularly interspersed thermoplastic composite mat |
US5578357A (en) * | 1992-02-10 | 1996-11-26 | Polyloom Corporation Of America | Carpet and techniques for making and recycling same |
US5354605A (en) * | 1993-04-02 | 1994-10-11 | Alliedsignal Inc. | Soft armor composite |
US5529826A (en) * | 1994-02-15 | 1996-06-25 | Tailor; Dilip K. | Fabric-faced thermoplastic composite panel |
US5935651A (en) * | 1994-05-11 | 1999-08-10 | Raytheon Ti Systems, Inc. | High strength, high modulus continuous polymeric material for durable, impact resistant applications |
US6083583A (en) * | 1994-05-11 | 2000-07-04 | Raytheon Company | High strength, high modulus continuous polymeric material for impact resistant applications |
US5437905A (en) * | 1994-05-17 | 1995-08-01 | Park; Andrew D. | Ballistic laminate structure in sheet form |
US5635288A (en) * | 1994-05-17 | 1997-06-03 | Park; Andrew D. | Ballistic resistant composite for hard-armor application |
US5443882A (en) * | 1994-05-17 | 1995-08-22 | Park; Andrew D. | Armored garment |
US5547536A (en) * | 1994-05-17 | 1996-08-20 | Park; Andrew D. | Method for fabricating a ballistic laminate structure |
US5935678A (en) * | 1994-05-17 | 1999-08-10 | Park; Andrew D. | Ballistic laminate structure in sheet form |
US5443883A (en) * | 1994-05-17 | 1995-08-22 | Park; Andrew D. | Ballistic panel |
US5861202A (en) * | 1994-12-16 | 1999-01-19 | Nippon Petrochemicals Co., Ltd. | Laminated bodies and woven and nonwoven fabrics comprising α-olefin polymeric adhesion materials catalyzed with cyclopentadienyl catalyst |
US6127293A (en) * | 1994-12-16 | 2000-10-03 | Nippon Petrochemicals Co., Ltd. | Laminated bodies and woven and nonwoven fabrics comprising α-olefin polymeric adhesion materials catalyzed with cyclopentadienyl catalyst |
US6054086A (en) * | 1995-03-24 | 2000-04-25 | Nippon Petrochemicals Co., Ltd. | Process of making high-strength yarns |
US5643390A (en) * | 1995-05-04 | 1997-07-01 | The University Of Delaware | Bonding techniques for high performance thermoplastic compositions |
US6458727B1 (en) * | 1996-10-04 | 2002-10-01 | University Of Leeds Innovative Limited | Olefin polymers |
US6312638B1 (en) * | 1996-10-04 | 2001-11-06 | Btg International | Process of making a compacted polyolefin article |
US6328923B1 (en) * | 1996-10-04 | 2001-12-11 | Btg International Limited | Process of making a compacted polyolefin article |
US6156679A (en) * | 1996-12-25 | 2000-12-05 | Chisso Corporation | Heat-fusible composite fiber and non-woven fabric produced from the same |
US6106924A (en) * | 1997-01-30 | 2000-08-22 | Nippon Petrochemicals Company, Limited | Laminate material and uniaxially oriented laminate |
US6641893B1 (en) * | 1997-03-14 | 2003-11-04 | Massachusetts Institute Of Technology | Functionally-graded materials and the engineering of tribological resistance at surfaces |
US6475592B1 (en) * | 1997-04-29 | 2002-11-05 | Darwin Enterprises, Inc. | Carpet backing that provides dimensional stability |
US6479125B1 (en) * | 1997-04-29 | 2002-11-12 | Darwin Enterprises, Inc. | Backing for tufted carpet that imparts dimensional stability |
US5962101A (en) * | 1997-04-29 | 1999-10-05 | Donald A. Irwin, Sr. | Dimensionally stable tufted carpet |
US5925434A (en) * | 1997-06-12 | 1999-07-20 | Bp Amoco Corporation | Tuftable backing and carpet construction |
US5879492A (en) * | 1998-04-17 | 1999-03-09 | Northrop Grumman Corporation | Z-peel sheets |
US6645610B1 (en) * | 1998-04-20 | 2003-11-11 | Northrop Grumann | Cured composite material formed utilizing Z-peel sheets |
US6897170B2 (en) * | 1998-12-11 | 2005-05-24 | Propex Fabrics, Inc. | Tuftable fabric with balanced construction |
US6562435B1 (en) * | 1999-03-20 | 2003-05-13 | Survival, Incorporated | Method for forming or securing unindirectionally-oriented fiber strands in sheet form, such as for use in a ballistic-resistant panel |
US6949280B2 (en) * | 1999-03-20 | 2005-09-27 | Survival, Incorporated | Method for forming or securing unidirectionally-oriented fiber strands in sheet form, such as for use in a ballistic-resistant panel |
US6824863B1 (en) * | 1999-09-30 | 2004-11-30 | Sumitomo Chemical Company, Limited | Fiber reinforced polypropylene-based composite material |
US6740386B2 (en) * | 2001-05-02 | 2004-05-25 | Burlington Industries, Inc. | Tufted covering for floors and/or walls |
US20040242103A1 (en) * | 2001-07-19 | 2004-12-02 | Joachim Loos | Polyolefin film, tape or yarn |
US20030224143A1 (en) * | 2002-02-14 | 2003-12-04 | Ianniello Peter J. | Fuzzy woven layers, geocomposite laminates incorporating them, and related methods |
US20030175474A1 (en) * | 2002-03-13 | 2003-09-18 | Higgins Kenneth B. | Textile constructions with stabilized primary backings and related methods |
US6866912B2 (en) * | 2002-03-13 | 2005-03-15 | Milliken & Company | Textile constructions with stabilized primary backings and related methods |
US20030175475A1 (en) * | 2002-03-13 | 2003-09-18 | Higgins Kenneth B. | Textile constructions, components or materials and related methods |
US20060151104A1 (en) * | 2002-09-27 | 2006-07-13 | Jacobs Johannes A J | Method for reinforcing an article |
US20050003727A1 (en) * | 2003-07-01 | 2005-01-06 | Chiou Minshon J. | Flexible spike/ballistic penetration-resistant articles |
US20050263234A1 (en) * | 2003-10-28 | 2005-12-01 | Greener Bags, Llc | Reinforced paper product and method for making same |
US20050233107A1 (en) * | 2004-04-19 | 2005-10-20 | Hartman David R | Recyclable tufted carpet with improved stability and durability |
US7160599B2 (en) * | 2004-04-19 | 2007-01-09 | Owens Corning Fiberglas Technology, Inc. | Recyclable tufted carpet with improved stability and durability |
US20070122586A1 (en) * | 2004-04-19 | 2007-05-31 | Hartman David R | Recyclable tufted carpet with improved stability and durability |
US20060222837A1 (en) * | 2005-03-31 | 2006-10-05 | The Boeing Company | Multi-axial laminate composite structures and methods of forming the same |
US20070071942A1 (en) * | 2005-09-27 | 2007-03-29 | Brian Callaway | Moldable construction incorporating non-olefin bonding interface |
US20070071941A1 (en) * | 2005-09-27 | 2007-03-29 | Eleazer Howell B | Moldable construction incorporating bonding interface |
US20070071940A1 (en) * | 2005-09-27 | 2007-03-29 | Brian Callaway | Moldable construction incorporation non-olefin bonding interface |
US20070071960A1 (en) * | 2005-09-27 | 2007-03-29 | Eleazer Howell B | Moldable fabric with variable constituents |
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Also Published As
Publication number | Publication date |
---|---|
IL197229A0 (en) | 2009-12-24 |
WO2008054372A3 (en) | 2008-06-19 |
EP2061653A2 (en) | 2009-05-27 |
US20090025861A1 (en) | 2009-01-29 |
US7892379B2 (en) | 2011-02-22 |
IL197229A (en) | 2012-03-29 |
WO2008054372A2 (en) | 2008-05-08 |
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