Adhesive bonding and miscellaneous chemical manufacture – Methods – Surface bonding and/or assembly therefor
Reexamination Certificate
2011-08-16
2011-08-16
Aftergut, Jeff H (Department: 1746)
Adhesive bonding and miscellaneous chemical manufacture
Methods
Surface bonding and/or assembly therefor
C156S191000
Reexamination Certificate
active
07998299
ABSTRACT:
A composite truss structure employs a sandwich-in-sandwich construction in which a composite fluted core is sandwiched between two facesheets, and at least one structural foam stiffener is sandwiched within the core or between the facesheets and/or the core.
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PCT Report US 2009/059290, The Boeing Company, Jan. 14, 2010.
Published article entitled: “An Update on Composite Tanks for Cryogens”, By Sara Black, Technical Editor | Nov. 2005, which can be found at http://www.compositesworld.com/hpc/issues/2005/November/1069.
Lockheed Martin: (X-34)—in situ fiber placement (ISFP)—preheat, no debulking, oven cure, unlined composite (IM7/8552, IM&/F650 BMI and IM&/5250-4 BMI).
Northrop Grumman: Next Generation Launch Technology—ultrasonic tape lamination (UTL) 2.5 mil material used on inner skin, debulking, oven cure, permeation barrier (epoxy adh, AL. foil, epoxy adh.), perforated aramid core.
Wilson Composites: U.S. Air Force Contracts—no liner, material patent pending microcrack resistant fiber/resin system, RTM bosses.
XCOR Aerospace: NASA's Exploration Systems Research and Technology program—filament wound Teflon/S2, Rohacell PMI foam .25-several inches, ouer shell material as needed.
HyPerComp::NASA SBIR—filament wound Zylon/polyurethane and HEI 535 epoxy/T1000, aluminum liner, oven cure.
Guzman Juan C.
Hand Michael L.
McCarville Douglas A.
Robinson Michael J.
Aftergut Jeff H
The Boeing Company
Tung & Associates
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