WO2010068342A2 - A composite laminate structure - Google Patents
A composite laminate structure Download PDFInfo
- Publication number
- WO2010068342A2 WO2010068342A2 PCT/US2009/062569 US2009062569W WO2010068342A2 WO 2010068342 A2 WO2010068342 A2 WO 2010068342A2 US 2009062569 W US2009062569 W US 2009062569W WO 2010068342 A2 WO2010068342 A2 WO 2010068342A2
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- WO
- WIPO (PCT)
- Prior art keywords
- skin
- composite laminate
- laminate structure
- partition
- core sections
- Prior art date
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 58
- 238000005192 partition Methods 0.000 claims abstract description 78
- 239000000835 fiber Substances 0.000 claims abstract description 66
- 239000006260 foam Substances 0.000 claims description 41
- 239000000463 material Substances 0.000 claims description 24
- 239000011347 resin Substances 0.000 claims description 12
- 229920005989 resin Polymers 0.000 claims description 12
- 239000003365 glass fiber Substances 0.000 claims description 3
- 239000007788 liquid Substances 0.000 claims 2
- 238000003780 insertion Methods 0.000 description 25
- 230000037431 insertion Effects 0.000 description 25
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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
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- 229910000831 Steel Inorganic materials 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
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- 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
- B32B5/02—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 structural features of a fibrous or filamentary layer
- B32B5/12—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 structural features of a fibrous or filamentary layer characterised by the relative arrangement of fibres or filaments of different layers, e.g. the fibres or filaments being parallel or perpendicular to each other
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B32B17/00—Layered products essentially comprising sheet glass, or glass, slag, or like fibres
- B32B17/02—Layered products essentially comprising sheet glass, or glass, slag, or like fibres in the form of fibres or filaments
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
- B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
- B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
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- 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
- B32B5/18—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 features of a layer of foamed material
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- 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
- B32B5/245—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 being a foam layer
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- 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
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- 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
- B32B2250/00—Layers arrangement
- B32B2250/40—Symmetrical or sandwich layers, e.g. ABA, ABCBA, ABCCBA
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- 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
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/101—Glass fibres
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- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2266/00—Composition of foam
- B32B2266/02—Organic
- B32B2266/0214—Materials belonging to B32B27/00
- B32B2266/0221—Vinyl resin
- B32B2266/0235—Vinyl halide, e.g. PVC, PVDC, PVF, PVDF
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- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2266/00—Composition of foam
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- B32B2266/0278—Polyurethane
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- 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
- B32B2307/00—Properties of the layers or laminate
- B32B2307/50—Properties of the layers or laminate having particular mechanical properties
- B32B2307/542—Shear strength
-
- 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
- B32B2607/00—Walls, panels
-
- 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
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- Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
- Y10T428/24008—Structurally defined web or sheet [e.g., overall dimension, etc.] including fastener for attaching to external surface
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- 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.]
- Y10T428/24033—Structurally defined web or sheet [e.g., overall dimension, etc.] including stitching and discrete fastener[s], coating or bond
-
- 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
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- 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
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- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/249921—Web or sheet containing structurally defined element or component
- Y10T428/249953—Composite having voids in a component [e.g., porous, cellular, etc.]
-
- 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
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- Y10T428/249986—Void-containing component contains also a solid fiber or solid particle
-
- 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
- Y10T428/31504—Composite [nonstructural laminate]
Definitions
- the present invention relates to an improvement in the field of composite laminate structures known as sandwich structures formed with outside skins of a polymer matrix composite and an internal core of either foam, end-grain balsa wood, or honeycomb, and more specifically to the field of these sandwich structures which additionally have some type of Z-axis fiber reinforcement through the composite laminate and normal to the plane of the polymer matrix composite skins.
- U.S. Patent No. 7,217,453 discloses a composite laminate sandwich structure including outside skins of a polymer matrix composite, an internal core, and a Z-axis fiber reinforcement through the composite laminate and normal to the plane of the polymer matrix composite skins.
- the composite laminate sandwich structure disclosed in U.S. Patent No. 7,217,453 is excellent for many applications.
- the inventors of the present invention some of who are the same as the inventors of U.S. Patent No. 7,217,453, have developed a new composite laminate sandwich structure that is ideal for applications where a higher shear modulus, greater stiffness, less deflection, and higher load-carrying capability are required.
- aspects of the invention involve a method and an apparatus for forming continuously and automatically a 3-D Z-axis reinforced composite laminate structure that has a higher shear modulus, greater stiffness, less deflection, and higher load-carrying capability than the composite laminate sandwich structure disclosed in U.S. Patent No. 7,217,453.
- the 3-D Z-axis reinforced composite laminate structure includes a sandwich panel combining high-shear Z-Y partitions and 3D-fiber insertions.
- the composite laminate structure includes a first skin; a second skin; a core between the first skin and the second skin, the core including adjacent core sections and a Z-Y partition separating the adjacent core sections; and a plurality of distinct groupings of Z-axis fibers that extend from the first skin to the second skin through the adjacent core sections and the Z-Y partition separating the adjacent core sections.
- FIG. 1 is a schematic illustration of a method and apparatus for forming continuously and automatically the subject 3-D Z-axis reinforced composite laminate structure
- FIG. 2 is a schematic vertical cross sectional view of a pultruded composite laminate panel in a preferred embodiment, in which the clinched 3-D Z- axis fibers have been cured on the fly, showing side details.
- This panel would be used as a new lightweight matting surface for temporary military aircraft runway use;
- FIG. 3 is a magnified view taken along lines 3-3 of FIG. 2;
- FIG. 4 is a magnified view taken along lines 4-4 of FIG. 3.
- FIG. 5 is a schematic vertical cross-sectional view of the pultruded sandwich panel of the preferred embodiment, just prior to entering the pultrusion die, wherein the 3D Z-axis groupings of fiber filaments have been deposited and they are prepared for clinching and riveting in the die;
- FIG. 6 is a magnified view taken along lines 6-6 of FIG. 5;
- FIG. 7 is a magnified view taken along lines 7-7 of FIG. 6;
- FIG. 8 is a magnified view taken along lines 8-8 of FIG. 2;
- FIG. 9 is a schematic illustration of a method and an apparatus for forming continuously and automatically an embodiment of a 3-D Z-axis reinforced composite laminate structure including a sandwich panel combining high-shear Z- Y partitions and 3D-fiber insertions;
- FIG. 10 is a vertical cross-sectional view of an embodiment of a 3-D Z- axis reinforced composite laminate structure including a sandwich panel combining high-shear Z-Y partitions and 3D-fiber insertions;
- FIG. 11 is a vertical cross-sectional view of an embodiment of a trapezoidal foam member of the 3-D Z-axis reinforced composite laminate structure of FIG. 10;
- FIG. 12 is a vertical cross-sectional view of an embodiment of a half- trapezoidal foam member of the 3-D Z-axis reinforced composite laminate structure of FIG. 10;
- FIG. 1 illustrates a method and apparatus for forming a pultruded and clinched 3-D Z-axis fiber reinforced composite laminate structure.
- the pultrusion direction is from left-to-right in FIG. 1 as shown by the arrows.
- the key components of the apparatus will become evident through the following description.
- FIG. 1 Shown in FIG. 1 are the ghppers 34 and 35. These are typically hydraulically actuated devices that can grip a completely cured composite laminate panel 32 as it exits pultrusion die 26. These grippers operate in a handover-hand method. When gripper 34 is clamped to the panel 32, it moves a programmed speed in the direction of the pultrusion, pulling the cured panel 32 from the die 26. Gripper 35 waits until the gripper 34 has completed its full stroke and then takes over.
- the fiber 20 can be glass fiber, either in roving rolls with continuous strand mat or it can be fabric such as x-y stitched fabric or woven roving. Besides glass, it can be carbon or aramid or other reinforcing fiber.
- a core material 22 is fed into the initial forming of the sandwich preform. The skins of the sandwich will be formed from the layers of fiber 20 on both the top and bottom of the sandwich preform 30. The core 22 will be the central section of the sandwich.
- the core can be made of urethane or PVC foam, or other similar foams in densities from 2 lbs. per cubic foot to higher densities approaching 12 lbs. per cubic foot.
- core 22 could be made of end-grain balsa wood having the properties of 6 Ib. per cubic foot density to 16 Ib. per cubic foot.
- the raw materials are directed, automatically, in the process to a guidance system in which resin from a commercial source 21 is directed to a primary wet-out station within resin tank 23.
- the wetted out preform 30 exits the resin tank and its debulking station in a debulked condition, such that the thickness of the panel section 30 is very nearly the final thickness of the ultimate composite laminate.
- These panels can be any thickness from 0.25 inches to 4 inches, or more.
- the panels can be any width from 4 inches wide to 144 inches wide, or more.
- Preform 30 is then directed to the Z-axis fiber deposition machine 24 that provides the deposition of 3-D Z-axis groupings of fiber filaments. The details as to how Z-axis filter deposition machine 24 functions is the subject of U.S. Pat.
- Modified preform 31 of FIG. 1 now automatically enters a secondary wet- out station 39.
- Station 39 can be the primary wet-out, eliminating station 23, as an alternative method.
- This station helps in the completion of the full resin wet-out of the composite laminate structure, including the 3-D Z-axis groupings of fiber filaments.
- Preform 31 then enters pultrusion die 26 mentioned earlier and through heat preform 31 is brought up in temperature sufficiently to cause catalyzation of the composite laminate panel. Exiting die 26 is the final cured panel section 32 which is now structurally strong enough to be gripped by the grippers 34 and 35.
- the sandwich structure of FIG. 1 can then be made any length practicable by handling and shipping requirements.
- the preform 32 Downstream of the grippers 34 and 35, the preform 32 is actually being “pushed” into the downstream milling machine system, 36 and 37.
- a multi-axis CNC machine (computer numerical control) moves on a gantry synchronous with the gripper pull speed, and can machine details into the composite laminate structure/panel on the fly. These can be boltholes, edge routing, milling, or cut-off.
- the machine 36 is the multi-axis head controlled by the computer 37. After cut-off, the part 33 is removed for assembly or palletizing and shipping.
- FIG. 2 illustrates a vertical cross-section of one preferred embodiment. It is a cross-section of a panel 40 that is 1.5 inches thick and 48 inches wide and it will be used as a temporary runway/taxiway/ or ramp for military aircraft. In remote locations, airfields must be erected quickly and be lightweight for transporting by air and handling. Panel 40 of FIG. 2 achieves these goals. Because it has been reinforced with the Z-axis groupings of fiber filaments, the panel can withstand the weight of aircraft tires, as well as heavy machinery. Since panel 40 is lightweight, at approximately 3 lbs. per square foot, it achieves a goal for the military, in terms of transportation and handling. Because 40 is pultruded automatically by the process illustrated in FIG.
- FIG. 3 is a magnified view taken along lines 3-3 of FIG. 2.
- FIG. 3 shows the cross section of the composite laminate structure, including the upper and lower skins 51 a and 51 b respectfully.
- Core 52 which is shown as foam, clearly could be other core material such as end-grain balsa wood.
- the several 3-D Z-axis groupings of fiber filaments 53 which are spaced in this embodiment every 0.25 inches apart and are approximately 0.080 inches in diameter.
- FIG. 4 is a magnified view taken along lines 4-4 of FIG. 3.
- FIG. 4 shows core material 52 and the upper skin section 51 a and lower skin section 51 b. These skin sections are approximately 0.125 inches thick in this embodiment and consists of 6 layers of X- Y stitched glass material at 24 oz. per square yard weight.
- the Z-axis groupings of fiber filaments 53 can be clearly seen in FIG. 4.
- the clinching or riveting of these filaments, which lock the skin and core together, can clearly be seen. [0029] FIGS.
- FIGS. 2, 3, and 4 show the runway matting material as it would be produced in the method and apparatus of FIG. 1.
- the schematic section 40 in FIG. 2 is fully cured as it would be leaving pultrusion die 26. Similar drawings of these same sections are shown for the preform of the runway matting material as it would look just prior to entering pultrusion die 26 by FIGS. 5, 6, and 7.
- FIGS. 5, 6 and 7 correlate with the preform 31 of FIG. 1.
- FIGS. 2,3, and 4 correlate with the perform 32 and the part 33 of FIG. 1.
- FIG. 5 schematically illustrates the entire matting panel 61 as a preform.
- the end of the panel 62 does not show the details 42, of FIG. 2 for clarity.
- the lines 6-6 indicate a magnified section that is shown in FIG. 6.
- FIG. 6 shows the skins 71 a and 71 b, the core 72 and the 3-D groupings of Z-axis fiber filaments 73.
- the lines 7-7 indicate a further magnification which is illustrated in FIG. 7.
- FIG. 7 shows the preform with the core 72 and upper skin material 71a and a single group of Z-axis fiber filaments 73. Note the egressed position of the fiber filaments, which after entering the pultrusion die will be bent over and riveted, or clinched, to the composite skin. Because the skins 71 a and 71 b are made of X- Y material and the grouping of fiber filaments are in the normal direction to X-Y, or the Z-direction, the composite skin in the region of the 3-D grouping of fiber filaments is said to be a three dimensional composite. [0033] FIG. 8 is a magnified view taken along lines 8-8 of FIG.
- the 3-D groupings of Z- axis fiber filaments 84 are deposited by the newly developed Z-axis deposition machine 24 in FIG. 1 , and are operated independent of the density of the material.
- the 3-D groupings of fiber Z-axis filaments can be easily deposited through either the core material 87 or the higher density X-Y material 89.
- the interlocking connecting joint 85 can be either machined into the shape of 85 in FIG.
- FIG. 8 illustrates embodiments of a method and an apparatus for forming continuously and automatically an embodiment of a 3-D Z-axis reinforced composite laminate structure including a sandwich panel combining high-shear Z- Y partitions and 3D-fiber insertions.
- the pultrusion direction is from left-to-right (front end of line to rear end of line) in FIG. 9 as shown by the arrows.
- Rolls 6b of Z-Y partition material fabric 8b are shown at one end of the apparatus (e.g., left/front end of apparatus/line).
- the Z-Y partition material fabric 8b is shown coming off of the rolls 6b as an unrolled flat fabric 6b.
- the fabric 8b is unrolled by the automatic pultrusion process, which includes pulling of a cured panel 32b at ghppers 22b near an opposite end of the apparatus (e.g., right/rear end of apparatus/line).
- the grippers 22b are hand-over-hand grippers 22b that sequentially clamp the cured panel 32b and pull the panel 32b from a curing die 26b.
- the raw material upstream gets pulled at the same speed as the cured panel 32b.
- the Z-Y partition fabric 8b gets pulled into a forming station 37b.
- the forming station 37b includes tooling that orients the Z-Y partition fabric 8b into a generally Z-Y orientation (roughly 45 degrees relative to, and in between a pure Z- direction and a pure Y-direction; see, for example, element 60b, FIG. 13, element 70b, FIG. 14).
- the Z-Y partition fabric 8b runs consistently in the pultrusion direction, in the direction of the arrows shown.
- Angulated foam sections 15b are inserted and nestled on opposite sides of the Z-Y partitions, either above or below the formed Z-Y partitions 20b that are exiting the forming station 37b. These sections of foam 15b may be 4 ft.
- foam trapezoidal section 53b shown in Fig.11.
- the foam trapezoidal section 53b of Fig. 11 is oriented correctly to be the foam section 15b that is above the Z-Y partitions 20b (in the +Z Direction).
- Foam trapezoidal section 53b has its longest edge directly under the upper skins 55b of the sandwich. If foam trapezoidal section 53b is rotated 180 degrees along its X- Axis, it becomes the foam trapezoidal section 54b of Figure 10, and is thus the lower foam section 15b of Fig. 9.
- the foam sections 15b thus are inserted to fill the interior space above and below the Z-Y partition fabric 8b such that the sum total of the foam 15b and the Z-Y partition fabric 8b form a generally rectangular interior space of the sandwich panel 32b (See, for example, FIG. 10).
- Upper and lower skins are formed by fabric material 12b that is unrolled by the pultrusion process from rolls 10b.
- the entire combination of raw material (upper skins 12b, foam section 15b-combined-with-Z-Y partitions 20b, and lower skins 12b) is pulled into forming tooling/tray 38b, and exits as dry preform material 29b.
- Dry preform material 29b then enters the 3D insertion process/assembly 9b, where discrete bundles of 3D fiber are inserted through the dry preform material 29b.
- the discrete bundles of 3D fiber are deposited through upper skins 55b (FIG. 10), combined foam/Z-Y partitions 60b and 70b, and bottom skins 56b in one movement, ending in a severing of the bundles which results in the deposition of discrete bundles.
- the 3D insertion process/assembly 9b is synchronized with the pultrusion speed of the grippers 22b.
- the 3D insertion assembly 9b is preferably on a synchronous gantry such that there is no relative motion between the dry preform 29b and the 3D insertion assembly 9b; however in alternative embodiment, relative motion between the 3D insertion assembly 9b and the dry preform 29b is allowed.
- An example 3D insertion process/assembly used as the 3D insertion process/assembly 9b is shown and described in U.S. Patent 7,105,071 , which is incorporated by reference herein as though set forth in full.
- Exiting the 3D insertion assembly 9b is a package after insertions 30b, which then enters resin injection tooling 23b.
- the package of preform becomes fully wetted out in the resin injection tooling 23b and exits as wetted-out package 31 b.
- Key to the wet-out performance in the resin injection tooling 23b is the fact that the discrete bundles of 3D fiber act as straws, or wicking mechanisms, drawing resin to internal Z-Y partition material and internal 3D fiber bundles.
- the fully wetted-out package 31 b then enters pultrusion die 26b where the sandwich panel is cured into an exiting cured panel 32b.
- a cut-off mechanism which is preferably also synchronous, cuts the cured panel 32b into predetermined lengths such that a finished panel 33b is stacked and palletized for shipping.
- FIGS. 10-14 an embodiment of a 3-D Z-axis reinforced composite laminate structure including a sandwich panel 40b combining high- shear Z-Y partitions and 3D-fiber insertions (e.g., finished panel 33b, FIG. 9) will be described.
- FIG. 10 shows an embodiment of the sandwich panel 40b, which in an exemplary application is about 3 inches thick and 48 inches wide.
- Bubble circles 12, 13 and 11 , 14 show two features of the panel cross section. Shown in bubble circle 11 , 14 are foam trapezoidal sections 53b and 54b. Foam trapezoidal section 53b is also shown in FIG. 11. Note that foam trapezoidal section 53b and foam trapezoidal section 54b are identical foam trapezoidal sections, with foam trapezoidal section 54b being an inverted relative to foam trapezoidal section 53b.
- Shown in bubble 12, 13 is a half foam trapezoidal section 83b, which is also shown in FIG. 12.
- Also shown in bubble 12, 13 is a Z-Y partition 60b, which is also shown in FIG. 13.
- the foam trapezoidal sections 53b, 54b, and 83b are longitudinally elongated foam members. Although trapezoidal sections are shown, in alternative embodiments, one or more polygonal, rectilinear, and/or curvilinear sections are used in the sandwich panel 40b. For example, but not by way of limitation, triangular sections (e.g., solid foam, hollow) such as those shown and described in U.S. Patent No. 4,223,053 may be used. [0041] FIG. 10 also shows an upper skin 55b and a lower skin 56b forming the outside surfaces of the sandwich panel 40b. Additionally, 3D fiber bundles/insertions 58b are shown tying all materials (skins, foam sections, and Z- Y partitions).
- FIG. 11 is a vertical cross-sectional view of an embodiment of the trapezoidal foam cross section 53b, which by example may be 48 inches long, or 96 inches long, but in each case with the cross section shown in FIG. 11.
- FIG. 12 is a vertical cross-sectional view of an embodiment of the half- trapezoidal foam member 83b, which as the name implies is exactly a section 53b cut in half.
- FIG. 13 is a vertical cross-sectional view of an embodiment of a Z-Y partition 60b that is oriented in the +Z-direction and -Y-direction at substantially 45 degrees relative to horizontal.
- the Z-Y partitions will be shown and described here as being oriented in the Z-direction and Y direction at substantially 45 degrees relative to horizontal, in alternative embodiments, the Z-Y partitions are oriented in the Z-direction and Y direction at an angle between 0 degrees and 90 degrees relative to horizontal.
- Upper mating portion 61 b is that portion of the Z-Y partition that mates with the interior of the upper skin 55b.
- lower mating portion 62b is that portion of the Z-Y partition that mates with the interior of the lower skin 56b.
- FIG. 14 is a vertical cross-sectional view of another embodiment of a Z-Y partition 70b.
- the Z-Y partition 60b is repeated again in FIG. 14, and is shown with the Z-Y partition 70b, which is oriented in the +Z-direction and +Y-direction at substantially 45 degrees relative to horizontal.
- Upper mating portion 71 b is that portion of the Z-Y partition that mates with the interior of the upper skin 55b.
- the lower mating portion 72 b is that portion of the Z-Y partition that mates with the interior of the lower skin 56b.
- FIG. 14 A slight gap between an end portion 71 b, 72b of Z-Y partition 70b and an end portion 61 b, 62b of Z-Y partition 60b is shown in FIG. 14 for clarity.
- the end portions 71 b, 72b and 61 b, 60b of the two Z-Y partitions 70b and 60b may be butt-jointed, overlapped, or otherwise joined/mated to form a better connection to the skins 55b, 56b and the 3D fiber insertions 58b.
- a butt-jointed configuration is shown in FIG. 10 as butt joint 80b.
- the end portions 71 b, 72b and 61 b, 60b of the two Z-Y partitions 70b and 60b are overlapped adjacent to the first/upper skin 55b and the second/lower skin 56b to form a localized thicker skin.
- This localized thicker skin can have a positive structural effect as stress concentrations of a panel under load may find one of the first mode of failures being the connection, or node, of the Z-Y partitions and the skins.
- overlapping these partitions a localized increase in cross sectional area is provided, thus minimizing the effect of the aforementioned stress concentration.
- the insertion of Z-axis fibers at this location, or node help tie the entire localized region together, further retarding any separation under load.
- the sandwich panel 40b combines a series of Z-Y partitions and a 3D fiber deposition process to create the 3-D Z-axis reinforced composite laminate structure.
- the Z-Y partitions, along with the skin materials and the interior foam, are fed continuously at the front end of a pultrusion line via the use of unique dispensing tooling.
- These preforms are then subjected to computerized, deposition of discrete bundles of 3D fiber, the bundles being deposited through upper skins, combined foam/Z-Y partitions, and bottom skins in one movement, ending in a severing of the bundles which results in the deposition of discrete bundles.
- the new preform is then subjected to resin impregnation (in an alternative embodiment, the resin may already be "attached” or “prepregged” to the fiber bundles) and then cured in a die system.
- resin impregnation in an alternative embodiment, the resin may already be "attached” or “prepregged” to the fiber bundles
- the entire process is automated and requires very little supervision by operators of the machinery.
- the 3D fiber insertions provide significant benefits to the Z-Y partitions in that both have enhanced structural properties due to the presence of the other. Previous art in pultrusion has included examples of forms of Z-Y partitions, pultruded with either foam or mandrels (resulting in hollow interior sections where the foam would otherwise be located).
- each 3D fiber bundle can exhibit 160 lbs. of compressive force resistance before buckling. At 4 bundles per square inch (or 576 per square foot), this represents 92,160 pounds-per-square-foot buckling resistance of the panel, wherein the Z-Y partitions and the foam do not have to be the only internal elements resisting through-thickness buckling.
- the failure -separation at the intersection of Z-Y partitions and the skins is virtually eliminated.
- the 3D bundle connections which are extremely effective in eliminating delamination of the skins from foam, now provide delamination resistance between the connecting points of the Z-Y partitions and the skins.
- the Z-Y partition may want to buckle due to "long-column-buckling" phenomena, as described by Euler's buckling formulae.
- the critical buckling of a section is inversely proportional to the length 2 and this length gets effectively reduced at many locations due to the connection with stabilizing 3D fiber bundles.
- the 3D fiber is also enhanced by the Z-Y partitions.
- the long column buckling of the 3D fiber are improved as the effective length of the 3D fibers are lowered due to the connection with the Z-Y partitions.
- the core shear modulus of 3D fiber bundles, in combination with foam and skins is traditionally low. Many applications require the panel to be significantly stiffer (more resistant to bending and deflections) and the addition of the Z-Y partitions enhances the panels significantly.
- the shear modulus of the panel is increased to 35,000 to 50,000 psi, depending on the thickness and ply schedule of the Z-Y partitions themselves.
- An advantage of the present 3-D Z-axis reinforced composite laminate structure including a sandwich panel combining high-shear Z-Y partitions and 3D- fiber insertions includes, but not by way of limitation, a higher shear modulus and a stiffer panel with less deflection and higher load-carrying capability. This is important when the sandwich panel is used as a replacement for other high stiffness materials (that are much heavier) such as steel and concrete.
- sandwich panel applications for the sandwich panel include, but not by way of limitation, bridge decks (pedestrian and vehicular), mud mats (used as temporary landing mats in fields, temporary aircraft runways, temporary roads for oil and gas rigging traveling over sensitive areas, tundra, and the like), walls requiring low deflections, and floors of trucks/trailers and the like, replacements where sandwich panels use balsa as a core or high-shear-honeycomb, aircraft pallets, and containers.
- Another advantage of the sandwich panel is that the use of the Z-Y partition does not add significantly to the weight of a traditional panel nor to the automated production capability (either complexity or speed of the pultrusion process). The sandwich panel also has a longer fatigue life than a traditional panel.
- a further advantage of the sandwich panel is the enhancement of both Z- Y partitions and 3D fiber insertions, above the performance of either by themselves, as explained above.
- each Z-Y partition has one more layers/plies (e.g., 2 layers, 3 layers).
- the Z-Y partition is made of a quadraxial fiber fabric material, having orientation of fiber in the 0 degree/90 degree and +/- 45 degree directions, when the fiber material is laid flat on a horizontal surface.
- the same material is placed in the disclosed Z-Y direction, there are fiber elements in the X-direction, the Z-Y direction, and the Z- Y-X direction.
Landscapes
- Moulding By Coating Moulds (AREA)
- Laminated Bodies (AREA)
Abstract
Description
Claims
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AU2009325025A AU2009325025B8 (en) | 2008-12-11 | 2009-10-29 | A composite laminate structure |
CA2746636A CA2746636C (en) | 2008-12-11 | 2009-10-29 | A composite laminate structure |
JP2011540736A JP2012511452A (en) | 2008-12-11 | 2009-10-29 | Composite laminated structure |
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US12/333,155 | 2008-12-11 | ||
US12/333,155 US7785693B2 (en) | 2001-04-06 | 2008-12-11 | Composite laminate structure |
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WO2010068342A2 true WO2010068342A2 (en) | 2010-06-17 |
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Families Citing this family (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9782951B2 (en) * | 2007-07-18 | 2017-10-10 | The Boeing Company | Composite structure having ceramic truss core and method for making the same |
US8431214B2 (en) | 2007-07-31 | 2013-04-30 | The Boeing Company | Composite structure having reinforced core and method of making same |
US8512853B2 (en) | 2007-07-31 | 2013-08-20 | The Boeing Company | Composite structure having reinforced core |
US8123510B1 (en) * | 2008-03-24 | 2012-02-28 | Ebert Composite Corporation | Thermoplastic pultrusion die system and method |
US8747098B1 (en) | 2008-03-24 | 2014-06-10 | Ebert Composites Corporation | Thermoplastic pultrusion die system and method |
US8641848B2 (en) | 2011-03-14 | 2014-02-04 | Milliken & Company | Method and apparatus for combining elongated strips |
US9248958B2 (en) | 2011-12-27 | 2016-02-02 | Advanced Composite Structures, Llc | Air cargo container |
US8776698B2 (en) | 2012-10-08 | 2014-07-15 | Advanced Composite Structures, Llc | Composite air cargo pallet |
US9735466B2 (en) * | 2013-07-18 | 2017-08-15 | Ebert Composites Corporation | Advanced composite radome and method of manufacturing |
US10449737B2 (en) | 2015-03-04 | 2019-10-22 | Ebert Composites Corporation | 3D thermoplastic composite pultrusion system and method |
US9616623B2 (en) | 2015-03-04 | 2017-04-11 | Ebert Composites Corporation | 3D thermoplastic composite pultrusion system and method |
US10124546B2 (en) | 2015-03-04 | 2018-11-13 | Ebert Composites Corporation | 3D thermoplastic composite pultrusion system and method |
US9657762B2 (en) | 2015-03-12 | 2017-05-23 | Northrop Grumman Systems Corporation | Thermally activated, shape configurable mechanical locking Z-pin |
US9963978B2 (en) | 2015-06-09 | 2018-05-08 | Ebert Composites Corporation | 3D thermoplastic composite pultrusion system and method |
US10773881B2 (en) * | 2015-10-05 | 2020-09-15 | Advanced Composite Structures, Llc | Air cargo container and curtain for the same |
CN105459314B (en) * | 2015-11-17 | 2018-06-26 | 浙江双友物流器械股份有限公司 | A kind of manufacturing process of plank |
WO2019074864A1 (en) | 2017-10-10 | 2019-04-18 | Advanced Composite Structures, Llc | Latch for air cargo container doors |
EP3720709A4 (en) | 2017-12-04 | 2021-06-16 | Annexair Inc. | Composite panel, composite material, impregnator and method for manufacturing a composite panel |
WO2019111036A1 (en) | 2017-12-04 | 2019-06-13 | Annexair Inc. | Composite panel, composite material, impregnator and method for manufacturing a composite panel |
WO2019111037A1 (en) | 2017-12-04 | 2019-06-13 | Annexair Inc. | Composite panel, composite material, impregnator and method for manufacturing a composite panel |
US11981498B2 (en) * | 2019-06-28 | 2024-05-14 | Advanced Composite Structures, Llc | Thermally insulated air cargo container |
CN114502868A (en) * | 2019-10-07 | 2022-05-13 | 三菱电机株式会社 | Glass wool and method for manufacturing vacuum heat insulation material |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20010031350A1 (en) | 1999-12-28 | 2001-10-18 | Day Stephen W. | Fiber reinforced composite cores and panels |
US20040234742A1 (en) | 2001-04-06 | 2004-11-25 | Johnson David W. | 3D fiber elements with high moment of inertia characteristics in composite sandwich laminates |
US7217453B2 (en) | 2001-04-06 | 2007-05-15 | Ebert Compoistes Corporation | Composite laminate structure |
Family Cites Families (119)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2641561A (en) * | 1949-09-08 | 1953-06-09 | Eric A Black | Sandwich-type radome panel |
US2692219A (en) * | 1951-07-05 | 1954-10-19 | Owens Corning Fiberglass Corp | Structural panel |
US2762739A (en) | 1953-11-19 | 1956-09-11 | Alexander C H Weiss | Fiber-reinforced structural panel and method of making same |
US2954001A (en) | 1957-05-03 | 1960-09-27 | Luxenburg Julius | Automatic eyelet attachment |
US3230995A (en) | 1960-12-29 | 1966-01-25 | Owens Corning Fiberglass Corp | Structural panel and method for producing same |
FR1315844A (en) | 1961-12-12 | 1963-01-25 | Rhodiaceta | Method and apparatus for sewing fabrics based on thermoplastic threads |
US3328218A (en) | 1962-04-09 | 1967-06-27 | Noyes Howard | Process of making a structural element |
FR1359354A (en) | 1963-03-15 | 1964-04-24 | Rhodiaceta | Apparatus for sewing flat elements based on thermoplastic threads |
US3761345A (en) | 1969-04-03 | 1973-09-25 | R Smith | Nonwoven structure for reinforcing resinous material |
NL7008333A (en) | 1969-06-30 | 1971-12-13 | ||
US3647606A (en) | 1969-11-21 | 1972-03-07 | Union Carbide Corp | Semirigid multilayer thermal insulation and method of making same |
US3870580A (en) | 1971-02-25 | 1975-03-11 | Jack T Belcher | Method of manufacturing of a fiber reinforced structure and method of manufacture |
FR2129931B1 (en) | 1971-03-22 | 1973-12-28 | Vidal Benjamin | |
US3837985A (en) | 1972-02-24 | 1974-09-24 | Whittaker Corp | Multi-directional reinforced composite and method of making the same |
US4218276A (en) | 1972-03-31 | 1980-08-19 | Avco Corporation | Method for making 3-D structures |
US3948194A (en) | 1973-07-23 | 1976-04-06 | Heinz Gunold | Sewing machine accessory apparatus |
US3993523A (en) | 1975-03-10 | 1976-11-23 | Booz Allen & Hamilton, Inc. | Method and apparatus for adhesively joining a plurality of superimposed material layers by a needling operation |
FR2315562A1 (en) | 1975-06-26 | 1977-01-21 | Commissariat Energie Atomique | METHOD AND DEVICES FOR MANUFACTURING BODIES OR PARTS FROM THREE-DIMENSIONAL FABRICS |
DE2544165C3 (en) | 1975-10-03 | 1978-08-10 | Pfaff Industriemaschinen Gmbh, 6750 Kaiserslautern | Equipment on sewing machines for prepunching the sewing material |
US4032383A (en) | 1975-11-04 | 1977-06-28 | Mcdonnell Douglas Corporation | Fiber insertion device for continuous 3d foaming machine and method |
FR2355936A1 (en) | 1976-02-03 | 1978-01-20 | Commissariat Energie Atomique | PROCESS FOR MANUFACTURING PARTS IN THREE-DIMENSIONAL FABRICS |
US4256790A (en) | 1978-01-19 | 1981-03-17 | Rockwell International Corporation | Reinforced composite structure and method of fabrication thereof |
US4206895A (en) | 1978-03-30 | 1980-06-10 | Olez Nejat A | Loop-tension joint |
US4223053A (en) | 1978-08-07 | 1980-09-16 | The Boeing Company | Truss core panels |
US4196251A (en) | 1979-04-16 | 1980-04-01 | International Harvester Company | Rigidized resinous foam core sandwich structure |
US4291081A (en) | 1979-07-26 | 1981-09-22 | Northrop Corporation | Laced composite structure |
US4299871A (en) | 1979-09-04 | 1981-11-10 | Grumman Aerospace Corporation | Stitch bond fastening of composite structures |
US4331091A (en) | 1979-10-22 | 1982-05-25 | Hitco | Three-dimensional thick fabrics and method and apparatus for making same |
US4506611A (en) | 1979-10-22 | 1985-03-26 | Hitco | Three-dimensional thick fabrics and methods and apparatus for making same |
US4335176A (en) | 1980-11-24 | 1982-06-15 | Ppg Industries, Inc. | Bonded needled fiber glass thermoplastic reinforced mats |
IL66104A0 (en) | 1981-07-27 | 1982-09-30 | Tesch G H | Preparation of fiber reinforced flat bodies containing a hardenable binder |
US4402778A (en) | 1981-08-05 | 1983-09-06 | Goldsworthy Engineering, Inc. | Method for producing fiber-reinforced plastic sheet structures |
US4498941A (en) | 1981-08-05 | 1985-02-12 | Goldsworthy Engineering, Inc. | Method for producing fiber reinforced sheet structures |
US4420359A (en) | 1981-08-05 | 1983-12-13 | Goldsworthy Engineering, Inc. | Apparatus for producing fiber-reinforced plastic sheet structures |
JPS5898077U (en) | 1981-12-24 | 1983-07-04 | 株式会社井上ジャパックス研究所 | sewing machine equipment |
US4495231A (en) | 1982-09-29 | 1985-01-22 | Avco Corporation | Fiber composite |
DE3246803A1 (en) | 1982-12-17 | 1984-06-20 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | METHOD FOR PRODUCING COMPONENTS FROM LAYERS OF FIBER REINFORCED PLASTIC |
FR2565262B1 (en) | 1984-05-29 | 1986-09-26 | Europ Propulsion | METHOD FOR MANUFACTURING A MULTI-DIRECTIONAL FIBROUS TEXTURE AND DEVICE FOR CARRYING OUT THIS METHOD |
US4571355A (en) | 1984-11-28 | 1986-02-18 | The Boeing Company | Fiber reinforced resin composites formed of basic ply blankets |
DE3508252A1 (en) | 1985-03-08 | 1986-09-11 | Johann 2212 Brunsbüttel Götz | METHOD FOR PULLING LIGHT FIBER FIBERS THROUGH TEXTILES AND A DEVICE FOR CARRYING OUT THE METHOD |
GB8602003D0 (en) | 1986-01-28 | 1986-03-05 | Lawton P G | Carbonisable fibre assembly |
US4761871A (en) | 1986-11-21 | 1988-08-09 | Phillips Petroleum Company | Method of joining two thermoplastic articles |
FR2612950B1 (en) | 1987-03-25 | 1989-06-09 | Aerospatiale | METHOD FOR MANUFACTURING THREE-DIMENSION WOVEN COMPOSITE REINFORCING ELEMENTS, MACHINE FOR IMPLEMENTING SAME AND PRODUCT OBTAINED |
US4752513A (en) | 1987-04-09 | 1988-06-21 | Ppg Industries, Inc. | Reinforcements for pultruding resin reinforced products and novel pultruded products |
GB2205374B (en) | 1987-05-19 | 1991-03-27 | Rockwell International Corp | Composite fasteners & method for fastening structural components therewith |
US4983453A (en) | 1987-09-04 | 1991-01-08 | Weyerhaeuser Company | Hybrid pultruded products and method for their manufacture |
JPH01110944A (en) * | 1987-10-26 | 1989-04-27 | Toyota Motor Corp | Frp structure |
GB2284031B (en) | 1987-11-27 | 1995-11-08 | Gen Electric | Composite fastener |
US4808461A (en) | 1987-12-14 | 1989-02-28 | Foster-Miller, Inc. | Composite structure reinforcement |
US4913937A (en) | 1988-02-17 | 1990-04-03 | Xerkon Inc. | Composite articles using meltable resin holding threads |
US4963408A (en) | 1988-06-13 | 1990-10-16 | Mono-Lite Corporation | Structural unitary composite laminate structure and method for making same |
GB8822521D0 (en) | 1988-09-26 | 1988-11-02 | Tech Textiles Ltd | Method of producing formable composite material |
GB8822520D0 (en) | 1988-09-26 | 1988-11-02 | Tech Textiles Ltd | Process for continuously forming reinforced plastics articles |
FR2658841B1 (en) | 1990-02-26 | 1993-06-11 | Aerospatiale | METHOD AND DEVICE FOR PRODUCING REINFORCING ELEMENTS COMPOSED OF RESISTANT FIBERS. |
US5186776A (en) | 1990-05-07 | 1993-02-16 | Foster-Miller, Inc. | Composite laminate translaminar reinforcement apparatus and method |
GB9014770D0 (en) | 1990-07-03 | 1990-08-22 | Short Brothers Plc | Manufacture of a composite material |
CA2089507C (en) | 1990-08-16 | 1996-11-26 | Lawrence W. Davies | Pultrusion method including transverse fibers |
US5778806A (en) | 1990-12-26 | 1998-07-14 | Ralph's Industrial Sewing Machine Company | Sewing and material removal assembly |
US5286320A (en) | 1991-11-18 | 1994-02-15 | Owens-Corning Fiberglas Technology Inc. | Method for making a pultruded panel |
FR2686627B1 (en) | 1992-01-24 | 1995-06-16 | Aerospatiale | METHOD FOR STITCHING A FIBROUS PIECE, FIBROUS PIECE THUS OBTAINED AND FIBER-MATRIX COMPOSITE PIECE OBTAINED FROM SAID FIBROUS PIECE. |
FR2687173B1 (en) | 1992-02-11 | 1995-09-08 | Aerospatiale | PROCESS FOR THE PRODUCTION OF A FIBER REINFORCEMENT FOR A COMPOSITE MATERIAL, AND A COMPOSITE PIECE COMPRISING SUCH A REINFORCEMENT. |
DE4203988A1 (en) | 1992-02-12 | 1993-08-19 | Will E C H Gmbh & Co | METHOD AND DEVICE FOR BINDING PAPER LAYERS |
US5327621A (en) | 1992-03-23 | 1994-07-12 | Kabushiki Kaisha Toyoda Jidoshokki Seisakusho | Method of producing fabric reinforcing matrix for composites |
US5834082A (en) | 1992-05-04 | 1998-11-10 | Webcore Technologies, Inc. | Reinforced foam cores and method and apparatus of production |
US5589243A (en) | 1992-05-04 | 1996-12-31 | Webcore Technologies, Inc. | Reinforced foam cores and method and apparatus of production |
GB9212697D0 (en) | 1992-06-15 | 1992-07-29 | Short Brothers Plc | Composite structure manufacture |
US5445861A (en) | 1992-09-04 | 1995-08-29 | The Boeing Company | Lightweight honeycomb panel structure |
US6106646A (en) | 1992-09-14 | 2000-08-22 | General Electric Company | Method for joining composite materials |
US5466506A (en) | 1992-10-27 | 1995-11-14 | Foster-Miller, Inc. | Translaminar reinforcement system for Z-direction reinforcement of a fiber matrix structure |
US5445860A (en) | 1992-12-29 | 1995-08-29 | Gff Holding Company | Tufted product having an improved backing |
US5364681A (en) | 1993-02-05 | 1994-11-15 | Gencorp Inc. | Acoustic lamina wall covering |
EP0703837B1 (en) | 1993-04-30 | 2002-12-18 | Foster Miller, Inc. | A reinforced joint for composite structures and method of joining composite parts |
WO1995003170A1 (en) | 1993-05-04 | 1995-02-02 | Foster-Miller, Inc. | Truss reinforced foam core sandwich structure |
GB9406537D0 (en) | 1994-03-31 | 1994-05-25 | British Aerospace | Blind stitching apparatus and composite material manufacturing methods |
FR2718757B1 (en) | 1994-04-18 | 1996-06-14 | Aerospatiale | Method and machine for producing a plate-shaped reinforcement for a piece of composite material. |
FR2718758B1 (en) | 1994-04-18 | 1996-06-14 | Aerospatiale | Method and machine for producing a frame for a piece of composite material. |
US5470649A (en) | 1994-06-24 | 1995-11-28 | The United States Of America As Represented By The Adminstrator Of The National Aeronautics And Space Administration | Composite with through the thickness reinforcement |
US6090465A (en) | 1994-08-29 | 2000-07-18 | Spectrum Solutions, Ltd. | Reinforced composite structure |
JP3584065B2 (en) | 1994-09-12 | 2004-11-04 | 住友化学工業株式会社 | Manufacturing apparatus and manufacturing method for long fiber reinforced resin structure |
US5549771A (en) | 1994-12-23 | 1996-08-27 | Brooker; David A. | Fabrication of body containing lengths of fiber embedded therein |
US5873973A (en) | 1995-04-13 | 1999-02-23 | Northrop Grumman Corporation | Method for single filament transverse reinforcement in composite prepreg material |
KR0151780B1 (en) * | 1995-07-18 | 1998-10-01 | 조계찬 | Method for manufacturing adiabatic and enhanced panel |
AU3411395A (en) | 1995-08-21 | 1997-03-12 | Foster-Miller Inc. | System for inserting elements in composite structure |
FR2740068B1 (en) | 1995-10-20 | 1998-01-09 | Aerospatiale | PART OF REINFORCED LOW DENSITY THERMAL PROTECTION MATERIAL AND PROCESS FOR OBTAINING SAME |
US6027798A (en) | 1995-11-01 | 2000-02-22 | The Boeing Company | Pin-reinforced sandwich structure |
US5885020A (en) | 1995-11-15 | 1999-03-23 | Spartan Felt Company, Inc. | Marker pen having improved fibrous nib |
US5836715A (en) | 1995-11-19 | 1998-11-17 | Clark-Schwebel, Inc. | Structural reinforcement member and method of utilizing the same to reinforce a product |
US5770155A (en) | 1995-11-21 | 1998-06-23 | United Technologies Corporation | Composite structure resin cure monitoring apparatus using an optical fiber grating sensor |
US5868886A (en) | 1995-12-22 | 1999-02-09 | Alston; Mark S. | Z-pin reinforced bonded composite repairs |
US6151439A (en) | 1995-12-29 | 2000-11-21 | Ani-Motion, Inc. | Apparatus and method for implanting optical fibers in fabric panels and the like |
US5789061A (en) | 1996-02-13 | 1998-08-04 | Foster-Miller, Inc. | Stiffener reinforced assembly and method of manufacturing same |
US5862975A (en) | 1996-03-20 | 1999-01-26 | The Boeing Company | Composite/metal structural joint with welded Z-pins |
US5876652A (en) | 1996-04-05 | 1999-03-02 | The Boeing Company | Method for improving pulloff strength in pin-reinforced sandwich structure |
US5980665A (en) | 1996-05-31 | 1999-11-09 | The Boeing Company | Z-pin reinforced bonds for connecting composite structures |
US5876540A (en) | 1996-05-31 | 1999-03-02 | The Boeing Company | Joining composites using Z-pinned precured strips |
US5832594A (en) | 1996-05-31 | 1998-11-10 | The Boeing Company | Tooling for inserting Z-pins |
US5916469A (en) | 1996-06-06 | 1999-06-29 | The Boeing Company | Susceptor integration into reinforced thermoplastic composites |
FR2752640B1 (en) | 1996-08-21 | 1998-11-06 | Jolly Andre Jean | METHOD FOR MANUFACTURING A SANDWICH PANEL WITH HIGH RESILIENCE CONDUCTIVE CORES AND PANEL OBTAINED |
US5809805A (en) | 1996-09-03 | 1998-09-22 | Mcdonnell Douglas Corporation | Warp/knit reinforced structural fabric |
US6187411B1 (en) | 1996-10-04 | 2001-02-13 | The Boeing Company | Stitch-reinforced sandwich panel and method of making same |
US6139942A (en) | 1997-02-06 | 2000-10-31 | Cytec Technology, Inc. | Resin composition, a fiber reinforced material having a partially impregnated resin and composites made therefrom |
US6051089A (en) | 1997-02-07 | 2000-04-18 | Mcdonnell Douglas Corporation | Reinforcing member for composite workpieces and associated methods |
US5941185A (en) | 1997-08-25 | 1999-08-24 | Selbach Machinery L.L.C. | Optical filament insertion apparatus |
JPH11151772A (en) * | 1997-11-21 | 1999-06-08 | Hitachi Zosen Corp | High strength frp laminated material and its production |
US6151089A (en) | 1998-01-20 | 2000-11-21 | Sony Corporation | Reflection type display with light waveguide with inclined and planar surface sections |
US6190602B1 (en) | 1998-03-13 | 2001-02-20 | Aztex, Inc. | Method of manufacturing a perforated laminate |
US6128998A (en) | 1998-06-12 | 2000-10-10 | Foster Miller, Inc. | Continuous intersecting braided composite structure and method of making same |
US6291049B1 (en) | 1998-10-20 | 2001-09-18 | Aztex, Inc. | Sandwich structure and method of making same |
US6196145B1 (en) | 1998-11-17 | 2001-03-06 | Albany International Techniweave, Inc. | Yarn insertion mechanism |
US6808142B2 (en) | 2000-06-06 | 2004-10-26 | Mitsubishi Heavy Industries, Ltd. | Aircraft with a plurality of upper and lower cabins functioning as cargo compartments or passenger cabins and method of loading cargos for aircraft |
US20020014302A1 (en) | 2000-07-13 | 2002-02-07 | Kazak Composites, Incorporated | Method for incorporating rigid elements into the core of composite structural members in a pultrusion process |
US6467149B2 (en) | 2000-12-07 | 2002-10-22 | The Goodyear Tire & Rubber Company | Apparatus for injecting materials into a composite |
US6645333B2 (en) * | 2001-04-06 | 2003-11-11 | Ebert Composites Corporation | Method of inserting z-axis reinforcing fibers into a composite laminate |
US20050025948A1 (en) * | 2001-04-06 | 2005-02-03 | Johnson David W. | Composite laminate reinforced with curvilinear 3-D fiber and method of making the same |
US7105071B2 (en) * | 2001-04-06 | 2006-09-12 | Ebert Composites Corporation | Method of inserting z-axis reinforcing fibers into a composite laminate |
EP1642702B1 (en) * | 2001-08-02 | 2016-03-23 | Ebert Composites Corporation | A composite laminate with a core and Z-axis oriented fibers clinched into the respective top and bottom surfaces |
JP3768170B2 (en) * | 2002-05-09 | 2006-04-19 | 山一電機株式会社 | Cable connector |
US6797397B1 (en) * | 2003-03-20 | 2004-09-28 | Exxonmobil Oil Corporation | Lamination structure with a starch to plastic bond |
ES2465579T3 (en) * | 2003-03-28 | 2014-06-06 | Milliken & Company | Fiber reinforced composite cores and panels |
-
2008
- 2008-12-11 US US12/333,155 patent/US7785693B2/en not_active Expired - Fee Related
-
2009
- 2009-10-29 CA CA2746636A patent/CA2746636C/en not_active Expired - Fee Related
- 2009-10-29 AU AU2009325025A patent/AU2009325025B8/en not_active Ceased
- 2009-10-29 EP EP09832283.7A patent/EP2365907B1/en not_active Not-in-force
- 2009-10-29 JP JP2011540736A patent/JP2012511452A/en active Pending
- 2009-10-29 MX MX2011006202A patent/MX2011006202A/en active IP Right Grant
- 2009-10-29 WO PCT/US2009/062569 patent/WO2010068342A2/en active Application Filing
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20010031350A1 (en) | 1999-12-28 | 2001-10-18 | Day Stephen W. | Fiber reinforced composite cores and panels |
US20040234742A1 (en) | 2001-04-06 | 2004-11-25 | Johnson David W. | 3D fiber elements with high moment of inertia characteristics in composite sandwich laminates |
US7217453B2 (en) | 2001-04-06 | 2007-05-15 | Ebert Compoistes Corporation | Composite laminate structure |
Non-Patent Citations (1)
Title |
---|
See also references of EP2365907A4 |
Also Published As
Publication number | Publication date |
---|---|
AU2009325025B8 (en) | 2014-07-31 |
US7785693B2 (en) | 2010-08-31 |
CA2746636A1 (en) | 2010-06-17 |
AU2009325025A8 (en) | 2014-07-31 |
EP2365907A2 (en) | 2011-09-21 |
JP2012511452A (en) | 2012-05-24 |
MX2011006202A (en) | 2011-10-11 |
WO2010068342A3 (en) | 2010-08-12 |
AU2009325025A1 (en) | 2011-07-07 |
AU2009325025B2 (en) | 2014-03-27 |
EP2365907B1 (en) | 2018-03-07 |
US20090214849A1 (en) | 2009-08-27 |
EP2365907A4 (en) | 2014-05-07 |
CA2746636C (en) | 2017-03-07 |
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