US 11,772,360 B2
Filament fastener that cures with composite part
Jerry Chungbin, Kenmore, WA (US); Mark Rogalski, Sammamish, WA (US); and Everette Gray, Mukilteo, WA (US)
Assigned to The Boeing Company, Chicago, IL (US)
Filed by The Boeing Company, Chicago, IL (US)
Filed on Jun. 16, 2022, as Appl. No. 17/807,229.
Application 17/807,229 is a division of application No. 16/508,144, filed on Jul. 10, 2019, granted, now 11,446,900.
Prior Publication US 2022/0305758 A1, Sep. 29, 2022
Int. Cl. B32B 7/08 (2019.01); B29C 70/08 (2006.01); B32B 5/22 (2006.01); B32B 38/18 (2006.01); B32B 38/08 (2006.01); B32B 37/12 (2006.01); B32B 38/00 (2006.01); B32B 37/18 (2006.01)
CPC B32B 7/08 (2013.01) [B29C 70/08 (2013.01); B32B 5/22 (2013.01); B32B 37/18 (2013.01); B32B 38/08 (2013.01); B32B 38/1808 (2013.01); B32B 2037/1253 (2013.01); B32B 2038/008 (2013.01); B32B 2260/046 (2013.01); B32B 2305/10 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A composite laminate comprising:
layers of reinforcement fibers forming a stack of composite material to be cured with a first resin; and
a filament fastener including bundled fibers with one or more texture elements around the bundled fibers, and a second resin chemically compatible with the first resin, wherein the one or more texture elements spiral around the bundled fibers to form a helical shape, wherein the helical shape of the filament fastener has a pitch that corresponds with a thickness of each layer of the composite laminate,
wherein the filament fastener is configured to insert into the stack through a plurality of the layers of reinforcement fibers, and to cure within the stack to bind the layers of the stack with the one or more texture elements of the filament fastener via bonding of the first resin and the second resin to form the composite laminate with delamination resistance.