US20070243408A1 - Formed core sandwich structure and method and system for making same - Google Patents
Formed core sandwich structure and method and system for making same Download PDFInfo
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- US20070243408A1 US20070243408A1 US11/702,884 US70288407A US2007243408A1 US 20070243408 A1 US20070243408 A1 US 20070243408A1 US 70288407 A US70288407 A US 70288407A US 2007243408 A1 US2007243408 A1 US 2007243408A1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/0008—Soldering, e.g. brazing, or unsoldering specially adapted for particular articles or work
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/0008—Soldering, e.g. brazing, or unsoldering specially adapted for particular articles or work
- B23K1/0014—Brazing of honeycomb sandwich structures
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/008—Soldering within a furnace
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/20—Preliminary treatment of work or areas to be soldered, e.g. in respect of a galvanic coating
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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
- B32B15/00—Layered products comprising a layer of metal
- B32B15/01—Layered products comprising a layer of metal all layers being exclusively metallic
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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
- B32B15/00—Layered products comprising a layer of metal
- B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
- B32B15/043—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of metal
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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
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products 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 form; Layered products 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 form; Layered products 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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- 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
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
- B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
- B32B3/30—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by a layer formed with recesses or projections, e.g. hollows, grooves, protuberances, ribs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K2101/00—Articles made by soldering, welding or cutting
- B23K2101/02—Honeycomb structures
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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
- B32B2307/00—Properties of the layers or laminate
- B32B2307/70—Other properties
- B32B2307/718—Weight, e.g. weight per square meter
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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
- B32B2605/00—Vehicles
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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
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12201—Width or thickness variation or marginal cuts repeating longitudinally
- Y10T428/12208—Variation in both width and thickness
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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
- Y10T428/12—All metal or with adjacent metals
- Y10T428/1234—Honeycomb, or with grain orientation or elongated elements in defined angular relationship in respective components [e.g., parallel, inter- secting, etc.]
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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
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12347—Plural layers discontinuously bonded [e.g., spot-weld, mechanical fastener, etc.]
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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
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12993—Surface feature [e.g., rough, mirror]
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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.]
- Y10T428/24628—Nonplanar uniform thickness material
- Y10T428/24669—Aligned or parallel nonplanarities
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
A method and apparatus for producing a metal core sandwich structure that is lightweight and many times stiffer than regular sheet metal, and which is easily formable into curved structures as well as structures having compound curves. In one embodiment, a formed metal core includes a plurality of cells comprising alternating front and rear projections extending outwardly in front of and behind a median plane, with each projection having a bonding surface area or land configured to be brazed or bonded with corresponding external metal sheets on both sides of the formed metal core. A plurality of micro-abrasions or indentations are formed on the bonding lands, allowing stronger brazing or bonding joints to be formed between the metal core and the external metal sheets by facilitating improved capillary action by the metal core during the brazing or bonding process.
Description
- The present application is a continuation-in-part of U.S. application Ser. No. 11/285,096, filed on Nov. 22, 2005, entitled “Formed Metal Core Sandwich Structure and Method and System for Making Same” and the disclosures of which are herein incorporated by reference in their entirety.
- 1. Technical Field
- The present invention relates to metal sandwich sheet structures and, more particularly, to formable metal core sandwich sheet structures and methods and systems for manufacturing same.
- 2. Description of Related Art
- Metal core sandwich structures are known in the art. For example, U.S. Pat. No. 3,525,663 to Hale and U.S. Pat. No. 4,035,536 to Morrison both disclose metal sandwich structures having a formed metal core brazed to two outer metal sheets. However, it is believed that the structures disclosed by Hale and Morrison, and other similar conventional formed metal core sandwich structures, cannot be easily formed into compound curves and other complex shapes without delaminating, wrinkling and/or otherwise losing its structural integrity. Therefore, prior metal core sandwich structures are not well-suited for applications that require formation of compound curves, for example, without delaminating or wrinkling during the forming process.
- Other types of metal core sandwich structures, such as honeycomb sandwich structures, are described in U.S. Pat. No. 6,544,623 to Straza, for example. Although this honeycomb core sandwich structure provides improved formability when compared to other metal core sandwich structures, it is relatively expensive to manufacture and, therefore, not well-suited for many commercial, cost-sensitive applications (e.g., automobile bodies).
- Therefore, there is a need for an improved metal core sandwich structure that is more economical to manufacture and which exhibits improved formability characteristics without sacrificing structural integrity and strength.
- The invention addresses the above and other needs by providing an improved metal sandwich sheet structure that includes a formed metal core that is brazed or bonded to two outer flat metal sheets. This improved metal sandwich structure is capable of being formed into complex shapes while retaining its structural integrity. This improved metal sandwich structure is also easier and more economical to manufacture than prior honeycomb core sandwich structures, while providing similar strengths and characteristics as the honeycomb core structures.
- In one embodiment of the invention, a method of producing a metal core sandwich structure includes providing a formed metal core that is lightweight and many times stiffer than regular sheet metal, and which is easily formable into curved structures as well as structures having compound curves that curve in two or more directions simultaneously, for example. In one embodiment, a metal core sheet is rolled, stamped or pressed into a corrugated shape having a plurality of cells comprising alternating front and rear projections extending outwardly in front of and behind a median plane, with each projection having a bonding surface area or land configured to be brazed or bonded with corresponding external metal sheets on both sides of the formed metal core sheet. A plurality of micro-abrasions or indentations are formed on the bonding lands, allowing stronger brazing joints to be formed between the metal core and the external metal sheets by facilitating improved capillary action by the metal core during the brazing process. The improved brazing joints provide better bonds so the resulting multi-layer sheet structure will not fracture or delaminate during forming. The resulting sandwich structure is easier to form into complex curves and shapes while maintaining its structural integrity. Thus, the improved metal sandwich structure is well suited for various applications where formability and structural integrity are important (e.g., automotive body applications).
- In another embodiment of the invention, an apparatus for forming an improved core metal sheet is provided. The apparatus includes a press or mold that presses (via stretching and/or gathering) the core metal sheet to form a desired corrugated core structure. At desired locations on the surface of the press, micro-protrusions and/or micro-ridges and/or micro-lines (collectively referred to herein as “micro-protrusions”) extend outwardly from the press surfaces so that during forming of the core metal sheet, micro-abrasions and/or micro-grooves and/or micro-channels (collectively referred to herein as “micro-abrasions”) are formed to extend inwardly on desired surface areas of the formed metal core. These micro-abrasions allow for improved brazing between the formed metal core and the two outer metal sheets through improved capillary action by the metal core during brazing.
- In a further embodiment, the outer layer sheets are electro-tacked to the formed core prior to brazing or bonding, which allows for improved subsequent brazing and an improved quality sandwich structure. In one embodiment, the invention provides a novel electro-tacking apparatus for tack welding the formed core to the outer metal sheets prior to brazing.
- In various embodiments of the invention, various cell shapes and geometries such as hexagonal, square, octagonal or other shape may be formed in the core sheet as well as different cell sizes in accordance with desired formability, stiffness and crush characteristics. For example, it may be desirable for some zones of the sandwich structure to be more easily crushed (e.g., to provide “crush zones” in an automobile body frame) or to be more rigid or more flexible. For example, if crush zones are desired, the sandwich structure (or at least designated areas of the sandwich structure) can be designed to be more easily crushed which may help avoid automobile impact injuries while other areas of the automobile body (e.g., roofs) will be stiffer, allowing for more protection from metal crushing into passenger compartments.
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FIG. 1 illustrates a perspective view of a metal core sheet after it has been formed, in accordance with one embodiment of the invention. -
FIG. 2A illustrates a top view of the formed metal core sheet ofFIG. 1 . -
FIG. 2B illustrates a cross-sectional side view of the formed metal sheet ofFIGS. 1 and 2 A, taken along a cross-section indicated bylines 2B-2B ofFIG. 2A . -
FIG. 3A illustrates a top view of a metal core sheet formed in a corrugated checker-board pattern, in accordance with another embodiment of the invention. -
FIG. 3B illustrates a cross-section side view of the formed metal core ofFIG. 3A taken alonglines 3B-3B ofFIG. 3A . -
FIG. 4 illustrates a side view of a metal core sheet being formed between two press plates or molds, in accordance with one embodiment of the invention. -
FIG. 5 illustrates an exploded side view of a metal core sandwich structure prior to brazing, in accordance with one embodiment of the invention. -
FIG. 6 illustrates the metal core sandwich structure ofFIG. 4 after brazing. -
FIG. 7 illustrates a perspective view of an electro-tack welding apparatus used to tack weld the metal core sandwich structure prior to brazing, in accordance with a further embodiment of the invention. -
FIG. 8 illustrates a cross-sectional side view of one embodiment of a double cell sandwich structure. -
FIG. 9 illustrates a top view of a press plate used to form a core sheet used in the embodiment ofFIG. 8 . -
FIG. 10 is cross-sectional side of the embodiment ofFIG. 8 showing exemplary dimension. -
FIG. 11 illustrates a cross-sectional side view of a further embodiment of a double cell sandwich structure. -
FIG. 12 a illustrates a top view of an upper press used to form a first core sheet used in the embodiment shown inFIG. 11 . -
FIG. 12 b is a cross-sectional side view of the upper press ofFIG. 12 and a lower press used for forming a first core sheet, in accordance with one embodiment of the present invention. -
FIG. 13 a illustrates top view a top view of an upper press used to form a second core sheet used in the embodiment shown inFIG. 11 . -
FIG. 13 b is a cross-sectional side view of the upper press ofFIG. 13 a, taken along the lines 13 b-13 b of that figure, and a lower press for forming a second core sheet, in accordance with one embodiment of the present invention. -
FIG. 14 illustrates a cross-sectional side view of an exemplary embodiment of a double cell sandwich structure having a middle sheet, in accordance with one embodiment of the present invention. -
FIG. 15 illustrates a cross-sectional side view of another exemplary embodiment of a double cell sandwich structure having a middle sheet, in accordance with one embodiment of the present invention. - Preferred embodiments of the invention are described in detail below with reference to the figures wherein like elements are referenced with like numerals throughout. It is understood that the figures are not necessarily drawn to scale but intended to merely illustrate some of the novel aspects, features and processes of the invention.
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FIG. 1 illustrates a perspective view of a formedmetal core 10 made in accordance with one embodiment of the invention. In this embodiment, themetal core 10 is formed in a corrugated pattern having a plurality ofcells 12 comprising alternating front and rear projections extending outwardly in front of and behind amedian plane 14, with each projection having a bonding surface area orland 16 configured to be brazed or bonded with corresponding external metal sheets (not shown) on both sides of themedian plane 14. As shown inFIG. 1 , a plurality of micro-abrasions orindentations 18 are formed on the bonding lands 16. As explained in further detail below, the micro-abrasions 18 provide stronger brazing joints to be formed between themetal core 10 and the external metal sheets by facilitating improved capillary action by themetal core 10 during the brazing process. -
FIG. 2A illustrates a top view of the formedmetal core 10 ofFIG. 1 . Themetal core 10 includes a plurality of upwardly projecting cells 12A and a plurality of downwardly projectingcells 12B. The bonding lands 16 of the upwardly projecting cells 12A are also shown while the bonding lands 16 of the downwardly projectingcells 12B are located on the opposite side of thecore 10 and, hence, not shown inFIG. 2A . A plurality of micro abrasions orindentions 18 are formed on the bonding lands 16 of eachcell 12A and 12B to facilitate improved capillary action of themetal core 10 during brazing. -
FIG. 2B illustrates a cross-sectional side view of themetal core 10 taken alongperspective lines 2B-2B ofFIG. 2A . As shown inFIGS. 1, 2A and 2B, in one embodiment, eachcell 12A and 12B is formed in the shape of an octagon. However, it is understood that the invention is not limited to any particular shape, size and/or configuration of thecells 12A, 12B. Any desired shape, size and configuration of cells may be utilized to achieve various desired physical characteristics of the resulting metal core sandwich structure, in accordance with the present invention. -
FIG. 3A illustrates a top view of an alternative, exemplary formedmetal core 30 having a plurality of square-shaped cells 32A and 32B in a checkerboard configuration. The cells 32A represent upwardly projecting cells and the cells 32B represent downwardly projecting cells. Each cell 32A and 32B has acorresponding bonding land 34 and a plurality of micro-abrasions 36 on the surface of each bondingland 34.FIG. 3B illustrates a cross-sectional side view of the formedmetal core 30 ofFIG. 3A , taken alonglines 3B-3B of that figure. -
FIG. 4 illustrates a cross-sectional side view of themetal core 30 as it is formed between twopresses metal core 30 into a desired shape and configuration. During forming, a flat sheet ofmetal material 30 is placed between the top and bottom presses 42 and 44, respectively. As the top and bottom presses 42 and 44 are pressed together themetal core 30 is formed via stretching and/or gathering of themetal sheet material 30 to form the cells 32A and 32B in a checkerboard configuration. It is understood that thepresses - In one embodiment, the micro-abrasions 36 illustrated in
FIG. 3A , for example, are formed during pressing of themetal core 30. A plurality of micro-protrusions, ridges and/or lines (collectively referred to herein as “micro-protrusions”) (not shown) are provided on selectedsurfaces metal core 30, the micro-protrusions form the plurality of micro-abrasions 36 on the bonding lands 34 of the cells 32A, 32B of the formedmetal core 30. In one embodiment, the micro-protrusions are formed on the surfaces of thepresses metal core 30. In one embodiment, the micro-protrusions are formed on the corresponding press surfaces by fine etching of press surfaces using known means and techniques (e.g., electrical metal etching, chemical etching, sand blasting, grit blasting, etc.). In one embodiment, the micro-protrusions are formed so as to providemicro-abrasions 36 having a depth and/or width of 0.0005 inches to 0.002 inches and cover approximately 50-80% of the surface area of the bonding lands 34. In various embodiments, theabrasions 36 may be substantially parallel channels, criss-cross configurations, or channels traveling in random directions and/or curved channels. In alternative embodiments, the micro-abrasions may be formed by electronic discharge machining (EDM) processes, which are well-known in the art. In other embodiments, the micro-abrasions 36 may be formed on the bonding lands 34 of themetal core 30 after themetal core 30 has been pressed and formed. It is appreciated, however, that providing presses 42 and 44 with preformed micro-protrusions that automatically form micro-abrasions 36 on themetal core 30 during pressing can save substantial time and work when compared to forming the micro-abrasions 36 manually or individually for eachmetal core 30 subsequent to pressing. - In alternative embodiments, the
metal core presses metal core material 50 on either side of the core sheet to be formed. With the proper amount of pressure during forming, the brazing material will be embedded into the core sheet. This facilitates the subsequent brazing process by evenly distributing the braze material across the surface of the core sheet to be formed. In these embodiments, the micro-abrasions 18, 36 are formed and pass through the brazing material onto the bonding lands 16, 34 of the formedmetal core metal core -
FIG. 5 illustrates an exploded cross-sectional side view of an exemplary formed metal core 10 (FIG. 1 ) sandwiched between two sheets of brazingmaterial 50, which are in turn sandwiched between twoexternal metal sheets 60. In this embodiment, thebrazing material sheets 50 have not been pressed and formed with themetal core 10, as described above.FIG. 6 illustrates a cross-section side view of the resulting metalcore sandwich structure 70 after brazing of themetal core 10 to theexternal metal sheets 60 has been completed. The micro-abrasions 18 (FIG. 2A ) allow for an improved capillary effect so that thebrazing material 50, upon melting, flows into the pores of the bonding lands 16 (FIGS. 1 and 2 A) more easily and thereby provides a stronger braze joint between the closely fitted surfaces of the bonding lands 16 and theexternal metal sheets 60. The improved capillary effect and, hence, improved brazing joint provided by the micro-abrasions 18 produce a stronger metalcore sandwich structure 70 that can be formed into compound curves, and other shapes and forms, more easily without delaminating, wrinkling or otherwise losing its structural integrity. In further embodiments, micro-abrasions may also be formed on the interior surface of theexternal metal sheets 60 in order to improve the capillary effect of theexternal metal sheets 60 during brazing. - In a further embodiment of the invention, prior to brazing, all of the layers of the
metal sandwich structure 70, comprising a formedmetal core 10,brazing material sheets 50 and twoouter metal sheets 60, are electro-tack-welded together so as to secure the multiple layers to one another and prevent relative movements during the brazing process. This further improves the strength of the braze joints formed between the bonding lands 16 of thecore 10 and theexternal metal sheets 60 to provide a higher quality finished product. -
FIG. 7 illustrates a perspective view of a noveltack welding apparatus 100 that may be used in conjunction with the present invention. Theapparatus 100 includes a computer and/or electronically controlledactuator box 102 that contains standard electronics and mechanical components (e.g., gears, switches, power supply, etc.) to control movement of anactuator arm 104 that controls movement of atop plate 106. The metal core sandwich structure 70 (FIGS. 5 and 6 ) is positioned between thetop plate 106 and abottom ground plate 108. As shown inFIG. 7 , the top tack-welding plate 106 comprises a plurality ofsubsections 110 that are electrically insulated from each other. In one embodiment, thesubsections 110 can be made from copper or copper-alloy and are insulated from one another by an insulating material (e.g., ceramic). Each of thesubsections 110 are electrically coupled to a correspondingconductive wire 112 via correspondingcontacts 114. Theconductive wires 112 are coupled to apower switch box 116 that controls when electrical current is supplied to eachindividual wire 112. Thepower switch box 116 can be controlled by a computer or processor (not shown). - In one embodiment, a high energy, low voltage current is sequentially applied to each
subsection 110 to tack-weld a corresponding portion of the metalcore sandwich structure 70 located between thecorresponding subsection 110 and thebottom ground plate 108. In one embodiment, the top andbottom plates sandwich structure 70. A sequence of tack welds are rapidly performed in different areas of thesandwich structure 70 by sequentially applying an electrical current to eachsubsection 110 of thetop plate 106. By sequentially tack-welding only portions of thesandwich structure 70 at any one time, this tack-welding process allows for controlled heating and cooling throughout thesandwich structure 70, which in turn allows for improved tack welds. Thus, portions of thesandwich structure 70 following tack-welding are allowed to cool while other portions are being tack-welded. This cooling process provides better tack-welds and the resultingsandwich structure 70 has a lower tendency to delaminate at individual tack welds. In other words, letting thestructure 70 heat up and cool in different areas as it is being tack welded helps prevent individual tack welds from separating. After the metalcore sandwich structure 70 has been tack welded together, as described above, thestructure 70 is then placed in a furnace for brazing. - The metal
core sandwich structure 70 may incorporate any type of metal and/or metal alloys as the formedcore external metal sheets 60, such as A1 or D2 steel, for example. It is understood that any metals, metal alloys, or combinations thereof, that are suitable for brazing are contemplated to be within the scope of the present invention (e.g., copper, aluminum, titanium, etc.). Additionally, any type of known brazing material in the form of sheets, foils, sprays , powders, paste or slurries, for example, may be utilized in accordance with the present invention. Furthermore, it is contemplated that some embodiments of the invention may utilize non-metal core materials and non-metal external sheets. For example, known synthetic and/or polymer materials (e.g., Kevlar) may be used to form an injection-molded core and thereafter bonded (e.g., sonically welded and/or vibration welded) to synthetic and/or polymer outer sheets. Micro-abrasions are formed on the bonding lands of the non-metal core which facilitate gripping between the core and the external sheets during and after welding. - Further embodiments of metal core sandwich structures may include using a double cell sandwich core. These embodiments also have two external sheets defining a central core; but, instead of using a single core sheet (such as
sheet 10 ofFIG. 6 ), exemplary embodiments of double cell sandwich structures may use two core sheets. - One embodiment of a double
cell sandwich structure 800 is shown inFIG. 8 . Doublecell sandwich structure 800 can compriseexternal sheets first core sheet 806 a and asecond core sheet 806 b.External sheets sheets 60 shown inFIG. 6 .First core sheet 806 a andsecond core sheet 806 b may be made of the same materials as detailed above with reference tocore sheet 10. In theembodiment 800, thefirst core sheet 806 a and thesecond core sheet 806 b comprise a plurality of pyramid-shapedcells - Further to
FIG. 8 , inwardly projectinglands 834 a of thefirst sheet 806 a contact corresponding inwardly projectinglands 834 b of thesecond sheet 806 b. In addition, outwardly extendinglands 836 a of thefirst sheet 806 a contact an interior side of theexternal sheet 802 and outwardly extendinglands 836 b of thesecond sheet 806 b contact an interior side theexternal sheet 804. The inwardly projectinglandings 834 a of the first sheet can be configured to be brazed or bonded with corresponding inwardly facinglandings 834 b of the second sheet. Moreover, outwardly facinglandings external metal sheets external sheets -
FIG. 9 illustrates a top view of apress 900 configured to press ormold core sheets Press 900 has corresponding molded patterns, such aspunch 902, and configurations to form thecores sheets top press 900 and a corresponding bottom press (not shown). As thetop press 900 and the bottom press are pressed together, a core sheet is formed via stretching and/or gathering of the metal sheet. It is understood thatpress 900 is exemplary only and that presses having other desired molded patterns and configurations may be used to form metal core sheets having cells of various shapes, sizes and configurations. -
FIG. 10 is a cross-sectional view ofstructure 800 showing exemplary dimensions of thestructure 800. The exemplary dimensions are as follows: an inwardly projecting landing thickness A=0.0040″; an inside radii B=0.0006″; an outside radii C=0.010″; a cell diameter D=0.050″; a cell incline E=70°; an outwardly projecting landing thickness F=0.0040″; an external sheet thickness G=0.0060″; a core sheets width H=0.0300″; and a sandwich cell structure width I=0.0720″. It is understood that the above dimensions are exemplary only and that a sandwich core structure having other sizes and configurations may be used as desired to fit the needs of a particular application. -
FIG. 11 is a cross-sectional side view of a further embodiment of a doublecell sandwich structure 1100.Structure 1100 hasexternal sheets second core sheet 1108. The first core sheet 1006 has a generally sinusoidal cross-sectional shape with abulge 1110 located at a tip of each inwardly projectingpeak 1112. Thesecond core sheet 1108 also has a generally sinusoidal cross-sectional shape, but has adimple 1114 located at a tip of each inwardly projecting peak 1116. As seen inFIG. 11 , thebulges 1110 sit in the correspondingdimples 1114. - The
bulges 1110 anddimples 1114, as well as area near the bulges and dimples, may be brazed or bonded to facilitate gripping with a corresponding surface. Moreover, outwardly facing landings 1118 a and 1118 b of thefirst sheet 1106 and thesecond sheet 1108, respectively, can be configured to be brazed or bonded with the interior surface of correspondingexternal metal sheets - Similar to embodiments described above, the
first core sheet 1106 and thesecond core sheet 1108 may be formed between two presses having corresponding molded patterns and configurations to form a flat metal sheet into the desired shape and configuration. -
FIG. 12 a is a top view of anupper press 1202 having a plurality ofpins 1206 for forming the first core sheet 1006. In one embodiment, pins 1206 are spaced an equal distance away from eachadjacent pin 1206. In a further embodiment, partial pins that would otherwise be located at edges of thepress 1202 are eliminated. This is believed to help avoid sharp edges which could cut the material being formed. Only fivepins 1206 are shown inFIG. 12 a for ease of understanding for the reader. As is appreciated, there is no limit as to the number ofpins 1206 that can be used. -
FIG. 12 b illustrates the cross-sectional side view of theupper press 1202, taken along thelines 12 b-12 b ofFIG. 12 a, andlower press 1204 forming thefirst core sheet 1106 in accordance with one embodiment of the present invention. As can be seen, pins 1206 a, 1206 b, 1206 c have a generally conical shape and extend outwardly from a baseline 1208 of theupper press 1202. Located at a tip of eachpin projection 1210. Thelower press 1204 has a plurality of conically-shapedcavities indentation 1214 located at a central bottom area of each cavity 1212.Pins respective cavities upper press 1202 andlower press 1204 are pressed together to form thefirst core sheet 1106. -
FIG. 13 a is a top view of anupper press 1302 having a plurality ofpins 1306 for forming thesecond core sheet 1108. As with theupper press 1202, pins 1306 may be spaced an equal distance away from eachadjacent pin 1306 and partial pins that would otherwise be located at edges of the press may be eliminated. Eliminating partial pins on the edges of a press is believed to help avoid sharp edges which could cut the material being formed. Also, only fivepins 1306 are shown inFIG. 13 for ease of understanding for the reader. As is appreciated, however, there is no limit as to the number ofpins 1306 that can be used. -
FIG. 13 b illustrates a cross-sectional side view ofupper press 1302, taken along the lines 13 b-13 b ofFIG. 13 a, andlower press 1304 forming asecond core sheet 1108 in accordance with an embodiment of the present invention. Theupper press 1302 andlower press 1304 can be similar to theupper press 1202 andlower press 1204, respectively, with an exception being that that theupper press 1302 hasindentations 1306 instead ofprojections 1210 and thelower press 1304 hasprojections 1308 instead ofindentations 1214. In other words, the placement on respective presses of the projections and indentations for forming thefirst core sheet 1106 is reversed for forming thesecond core sheet 1108. Also, theindentations 1306 andprojections 1308 are preferably larger than theindentations 1214 andprojections 1210 to permit thebulges 1110 formed in thefirst sheet 1106 to sit in thedimples 1114 formed in thesecond sheet 1108, as shown inFIG. 11 . -
FIG. 14 illustrates a cross-sectional side view of a double cell sandwich structure 1600 having a middle sheet in accordance with another embodiment of the present invention. Some parts of thestructure 1400 are identical to those of the previously described embodiments, and like reference numerals have been used for like parts as appropriate. As shown inFIG. 14 , amiddle sheet 1450 is positioned between thefirst core sheet 806 a and thesecond core sheet 806 b. -
FIG. 15 illustrates a cross-sectional side view of a further embodiment of a doublecell sandwich structure 1500 having a middle sheet, in accordance with another embodiment of the present invention. Some parts of thestructure 1500 are identical to those of the previously described embodiments, and like reference numerals have been used for like parts as appropriate. As shown inFIG. 15 , adimpled middle sheet 1550 is positioned between thefirst core sheet 1106 and thesecond core sheet 1108. Thedimpled middle sheet 1550 hasdimples 1552 formed at locations corresponding to the locations of thebulges 1110 of thefirst core sheet 1106 and thedimples 1114 of thesecond core sheet 1108. - It is understood that sheets forming the
respective structures - The double cell sandwich structures provide many advantages. For example, it is believed that embodiments of double cell sandwich structures provide many of the advantages of the single cell structures; yet double cell structures can provide even more strength and further reduce dimpling and wrinkling on the surface of the structure during and after forming of the sandwich structure. Embodiments using of a middle sheet between the core sheets can strengthen the structure even further.
- Various preferred embodiments of the invention have been described above. However, it is understood that these various embodiments are exemplary only and should not limit the scope of the invention as recited in the claims below. Various modifications of the preferred embodiments described above can be implemented by those of ordinary skill in the art, without undue experimentation. These various modifications are contemplated to be within the spirit and scope of the invention as set forth in the claims below.
Claims (24)
1. A method of manufacturing a metal core sandwich structure, comprising:
forming a first metal core having a plurality of inwardly and outwardly projecting bonding lands;
forming a second metal core having a plurality of inwardly and outwardly projecting bonding lands;
forming micro-abrasions on a plurality of the bonding lands of each metal core;
placing the inwardly projecting bonding lands of the first metal core in contact with the inwardly projecting bonding lands of the second metal core;
placing a first metal sheet in contact with the outwardly projecting bonding lands of the first metal core and placing a second metal sheet in contact with the outwardly projecting bonding lands of the second metal core, thereby forming a sandwich structure; and
heating the sandwich structure to braze the first metal core, the first metal sheet, the second metal core and the second metal sheet together, wherein the micro-abrasions allow for improved capillary action at the bonding lands.
2. The method of claim 1 , further comprising forming a bulge on each inwardly projecting land of the first metal core and forming a dimple on each inwardly projecting land of the second metal core, wherein the bulges are configured to be received at least partially within corresponding dimples when the first and second metal cores contact each other.
3. The method of claim 1 wherein the first and second metal cores are formed with a press.
4. The method of claim 1 wherein first metal sheet and the second metal sheet comprise a plurality of cells, each of the cells having a pyramid-like shape.
5. The method of claim 1 wherein the micro-abrasions comprise grooves that are approximately 0.0005 to 0.002 inches in depth.
6. The method of claim 1 wherein the micro-abrasions cover approximately 50-80% of the surface area of the bonding lands.
7. The method of claim 1 wherein the micro-abrasions are formed on the bonding lands during the forming of the first metal core and second metal core.
8. The structure of claim 1 further comprising tack welding the first metal core, the second metal core, the first metal sheet and the second metal sheet together.
9. A metal core sandwich structure comprising:
first and second metal cores each having a plurality of inwardly and outwardly projecting bonding lands, a plurality of the inwardly projecting lands of the first metal core brazed to a plurality of the inwardly projecting lands of the second metal core; and
a first metal sheet brazed to a plurality of the outwardly projecting bonding lands of the first metal core and a second metal sheet brazed to a plurality of the outwardly projecting lands of the second metal core, wherein a plurality of micro-abrasions are formed on the plurality of bonding lands prior to brazing so as to allow for improved capillary action at the bonding lands.
10. The structure of claim 9 further comprising a bulge on each inwardly projecting land of the first metal core and a dimple on each inwardly projecting land of the second metal core, wherein the bulges are received at least partially within corresponding dimples.
11. The structure of claim 9 wherein the first metal core is tack welded to the second metal core and the first metal sheet, and the second metal core is tack welded to the second metal sheet.
12. The structure of claim 9 wherein the first and second metal cores each have a generally sinusoidal cross-sectional shape.
13. The structure of claim 9 wherein the first and second metal cores each comprise a plurality of pyramid-like shaped cells.
14. The structure of claim 9 wherein the micro-abrasions comprise grooves that are approximately 0.0005 to 0.002 inches in depth.
15. The structure of claim 9 wherein the micro-abrasions cover approximately 50-80% of the surface area of the bonding lands.
16. The structure of claim 9 wherein the micro-abrasions are formed on the bonding lands during forming of the respective first and second metal cores.
17. A metal core sandwich structure comprising:
first and second metal cores each having a plurality of inwardly and outwardly projecting bonding lands;
a first metal sheet brazed to a plurality of the outwardly projecting bonding lands of the first metal core;
a second metal sheet brazed to a plurality of the outwardly projecting lands of the second metal core; and
a third metal sheet brazed, on one side, to a plurality of the inwardly projecting lands of the first metal core and, on the other side, brazed to a plurality of the inwardly projecting lands of the second metal core,
wherein a plurality of micro-abrasions are formed on a plurality of the bonding lands prior to brazing so as to allow for improved capillary action at the bonding lands.
18. The structure of claim 17 further comprising a bulge on each inwardly projecting land of the first metal core and a dimple on each inwardly projecting land of the second metal core, wherein the bulges are received at least partially within corresponding dimples.
19. The structure of claim 18 wherein the third metal sheet comprises a plurality of bulges, at least some of the bulges of the third metal sheet receiving one of the corresponding bulges of the first metal core and positioned in one of the corresponding dimples of the second metal core.
20. The structure of claim 17 wherein the first and second metal cores each have a generally sinusoidal cross-sectional shape.
21. The structure of claim 17 wherein the first and second metal cores each comprise a plurality of pyramid-like shaped cells.
22. The structure of claim 17 wherein the micro-abrasions comprise grooves that are approximately 0.0005 to 0.002 inches in depth.
23. The structure of claim 17 wherein the micro-abrasions cover approximately 50-80% of the surface area of the bonding lands.
24. The structure of claim 17 wherein the micro-abrasions are formed on the bonding lands during forming of the first and second metal core.
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US12/180,466 US7753254B2 (en) | 2005-11-22 | 2008-07-25 | Formed core sandwich structure and method and system for making same |
US12/249,097 US7757931B2 (en) | 2005-11-22 | 2008-10-10 | Formed core sandwich structure and method and system for making same |
US12/249,095 US20090123709A1 (en) | 2005-11-22 | 2008-10-10 | Formed core sandwich structure and method and system for making same |
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US11/702,884 US20070243408A1 (en) | 2005-11-22 | 2007-02-05 | Formed core sandwich structure and method and system for making same |
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Publication number | Priority date | Publication date | Assignee | Title |
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US11737818B2 (en) * | 2018-08-14 | 2023-08-29 | Biosense Webster (Israel) Ltd. | Heat transfer during ablation procedures |
US10507875B1 (en) | 2018-12-21 | 2019-12-17 | Celltech Metals Inc. | Trailer wall including logistics post |
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CA3196470C (en) * | 2020-10-23 | 2024-02-13 | Yan Zheng | Roofing membrane with protrusions |
Citations (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3068565A (en) * | 1958-10-16 | 1962-12-18 | Nat Distillers Chem Corp | Method of making honeycomb laminate |
US3071853A (en) * | 1955-10-17 | 1963-01-08 | Solar Aircraft Co | Method and apparatus for making brazed honeycomb |
US3086899A (en) * | 1956-05-04 | 1963-04-23 | Dow Chemical Co | Constructional lamina |
US3525663A (en) * | 1967-03-09 | 1970-08-25 | Jesse R Hale | Anticlastic cellular core structure having biaxial rectilinear truss patterns |
US3834487A (en) * | 1973-03-08 | 1974-09-10 | J Hale | Sandwich core panel with structural decoupling between the outer face sheets thereof |
US3876492A (en) * | 1973-05-21 | 1975-04-08 | Lawrence A Schott | Reinforced cellular panel construction |
US4035536A (en) * | 1975-03-03 | 1977-07-12 | Mcdonnell Douglas Corporation | Sandwich panel core |
US4374886A (en) * | 1979-06-06 | 1983-02-22 | Formica Corporation | Color registered decorative laminates |
US4530197A (en) * | 1983-06-29 | 1985-07-23 | Rockwell International Corporation | Thick core sandwich structures and method of fabrication thereof |
US4618152A (en) * | 1983-01-13 | 1986-10-21 | Thomas P. Mahoney | Honeycomb seal structure |
US4676843A (en) * | 1984-02-23 | 1987-06-30 | Bbc Brown, Boveri & Company Limited | Process for joining component workpieces made of a superalloy employing the diffusion bonding process |
US4759994A (en) * | 1983-12-12 | 1988-07-26 | Hugues Lesourd | Sandwich-type stampable, metallic structure |
US5316863A (en) * | 1992-05-18 | 1994-05-31 | Alcan International Limited | Self-brazing aluminum laminated structure |
US6138898A (en) * | 1998-12-22 | 2000-10-31 | The Boeing Company | Corner gap weld pattern for SPF core packs |
US6419146B1 (en) * | 1996-01-12 | 2002-07-16 | The Boeing Company | Metal sandwich structure with integral hardpoint |
US6544623B1 (en) * | 2000-11-29 | 2003-04-08 | George C. P. Straza | Honeycomb cell structure and method of manufacture |
US6689328B1 (en) * | 1997-05-09 | 2004-02-10 | Nippon Steel Corporation | Metal honeycomb body for exhaust gas purification catalyst and method for producing the same |
US20040154252A1 (en) * | 2002-06-06 | 2004-08-12 | Sypeck David J. | Multifunctional periodic cellular solids and the method of making same |
US20060199031A1 (en) * | 1999-04-23 | 2006-09-07 | The Boeing Company | Multisheet sandwich panel using superplastic forming and adhesive bonding |
Family Cites Families (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2481046A (en) * | 1947-11-13 | 1949-09-06 | Western Engineering Associates | Panel structure |
US3011602A (en) * | 1959-07-13 | 1961-12-05 | Lockheed Aircraft Corp | Panel construction |
US3151712A (en) * | 1960-11-30 | 1964-10-06 | Budd Co | Insulating structure |
US3376684A (en) * | 1963-10-16 | 1968-04-09 | Gen Dynamics Corp | Double reverse corrugated material |
US3888531A (en) * | 1973-03-21 | 1975-06-10 | Straza Enterprises Ltd | Frangible shock absorbing bumper |
DE2518683C3 (en) * | 1975-04-26 | 1981-04-09 | 4P Verpackungen Gmbh, 8960 Kempten | Heat exchanger made from two aluminum sheets connected to one another |
US4346904A (en) * | 1980-11-26 | 1982-08-31 | Watkins Jr Shelton | Honeycomb structure for use in abradable seals |
US4409274A (en) * | 1982-02-24 | 1983-10-11 | Westvaco Corporation | Composite material |
US4495237A (en) * | 1983-06-10 | 1985-01-22 | Patterson Fred R | Pyramidal core structure |
CA1280268C (en) * | 1988-09-30 | 1991-02-19 | Jobst Ulrich Gellert | Injection molding nozzle having nose portion with heating element encircling the bore and method |
US5258087A (en) * | 1989-03-28 | 1993-11-02 | Plascon Technologies (Proprietary) Limited | Method of making a composite structure |
US5173471A (en) * | 1990-05-25 | 1992-12-22 | Usui Kokusai Sangyo Kabushiki Kaisha | Exhaust gas cleaning device |
DE4430428B4 (en) | 1994-08-26 | 2005-12-01 | Bayerische Motoren Werke Ag | layer body |
DE19729566C2 (en) | 1997-07-08 | 2000-09-14 | Daimler Chrysler Ag | Metal composite plate |
JPH1147980A (en) | 1997-07-29 | 1999-02-23 | Kobe Steel Ltd | Method for joining applying sprayed coating and joined body, and thermal spraying material used for said method |
US6221463B1 (en) * | 1998-07-08 | 2001-04-24 | Eugene W. White | Three-dimensional film structures and methods |
AU2002323407A1 (en) * | 2001-08-24 | 2003-03-10 | University Of Virginia Patent Foundation | Reversible shape memory multifunctional structural designs and method of using and making the same |
US20070243408A1 (en) | 2005-11-22 | 2007-10-18 | Straza George C P | Formed core sandwich structure and method and system for making same |
-
2007
- 2007-02-05 US US11/702,884 patent/US20070243408A1/en not_active Abandoned
-
2008
- 2008-02-05 WO PCT/US2008/053067 patent/WO2008097984A1/en active Application Filing
- 2008-07-25 US US12/180,466 patent/US7753254B2/en active Active
- 2008-10-10 US US12/249,095 patent/US20090123709A1/en not_active Abandoned
- 2008-10-10 US US12/249,097 patent/US7757931B2/en active Active
Patent Citations (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3071853A (en) * | 1955-10-17 | 1963-01-08 | Solar Aircraft Co | Method and apparatus for making brazed honeycomb |
US3086899A (en) * | 1956-05-04 | 1963-04-23 | Dow Chemical Co | Constructional lamina |
US3068565A (en) * | 1958-10-16 | 1962-12-18 | Nat Distillers Chem Corp | Method of making honeycomb laminate |
US3525663A (en) * | 1967-03-09 | 1970-08-25 | Jesse R Hale | Anticlastic cellular core structure having biaxial rectilinear truss patterns |
US3834487A (en) * | 1973-03-08 | 1974-09-10 | J Hale | Sandwich core panel with structural decoupling between the outer face sheets thereof |
US3876492A (en) * | 1973-05-21 | 1975-04-08 | Lawrence A Schott | Reinforced cellular panel construction |
US4035536A (en) * | 1975-03-03 | 1977-07-12 | Mcdonnell Douglas Corporation | Sandwich panel core |
US4374886A (en) * | 1979-06-06 | 1983-02-22 | Formica Corporation | Color registered decorative laminates |
US4618152A (en) * | 1983-01-13 | 1986-10-21 | Thomas P. Mahoney | Honeycomb seal structure |
US4530197A (en) * | 1983-06-29 | 1985-07-23 | Rockwell International Corporation | Thick core sandwich structures and method of fabrication thereof |
US4759994A (en) * | 1983-12-12 | 1988-07-26 | Hugues Lesourd | Sandwich-type stampable, metallic structure |
US4676843A (en) * | 1984-02-23 | 1987-06-30 | Bbc Brown, Boveri & Company Limited | Process for joining component workpieces made of a superalloy employing the diffusion bonding process |
US5316863A (en) * | 1992-05-18 | 1994-05-31 | Alcan International Limited | Self-brazing aluminum laminated structure |
US6419146B1 (en) * | 1996-01-12 | 2002-07-16 | The Boeing Company | Metal sandwich structure with integral hardpoint |
US6689328B1 (en) * | 1997-05-09 | 2004-02-10 | Nippon Steel Corporation | Metal honeycomb body for exhaust gas purification catalyst and method for producing the same |
US6138898A (en) * | 1998-12-22 | 2000-10-31 | The Boeing Company | Corner gap weld pattern for SPF core packs |
US20060199031A1 (en) * | 1999-04-23 | 2006-09-07 | The Boeing Company | Multisheet sandwich panel using superplastic forming and adhesive bonding |
US6544623B1 (en) * | 2000-11-29 | 2003-04-08 | George C. P. Straza | Honeycomb cell structure and method of manufacture |
US20040154252A1 (en) * | 2002-06-06 | 2004-08-12 | Sypeck David J. | Multifunctional periodic cellular solids and the method of making same |
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Also Published As
Publication number | Publication date |
---|---|
US20080292898A1 (en) | 2008-11-27 |
US7757931B2 (en) | 2010-07-20 |
US20090123776A1 (en) | 2009-05-14 |
US20090123709A1 (en) | 2009-05-14 |
WO2008097984A1 (en) | 2008-08-14 |
US7753254B2 (en) | 2010-07-13 |
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Owner name: CELLTECH METALS, INC., CALIFORNIA Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:STRAZA, GEORGE C.P.;REEL/FRAME:019524/0306 Effective date: 20070612 |
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