US 12,220,890 B2
Methods for fabricating solid laminate stringers on a composite panel
Jiangtian Cheng, Mukilteo, WA (US)
Assigned to THE BOEING COMPANY, Arlington, VA (US)
Filed by The Boeing Company, Chicago, IL (US)
Filed on Feb. 18, 2020, as Appl. No. 16/793,559.
Prior Publication US 2021/0252817 A1, Aug. 19, 2021
Int. Cl. B29D 99/00 (2010.01); B29C 70/34 (2006.01); B29C 70/44 (2006.01); B64C 1/06 (2006.01); B64C 3/18 (2006.01); B29L 31/30 (2006.01); B64C 1/00 (2006.01)
CPC B29D 99/0014 (2013.01) [B29C 70/342 (2013.01); B29C 70/44 (2013.01); B29D 99/0003 (2013.01); B29D 99/001 (2013.01); B64C 1/064 (2013.01); B64C 3/182 (2013.01); B29L 2031/3082 (2013.01); B64C 2001/0072 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A method of fabricating a solid laminate stringer on a composite panel, comprising:
unspooling one or more composite layers onto the composite panel, comprising aligning at least one of edges and centerlines of the one or more composite layers unspooled onto the composite panel to form the solid laminate stringer;
compacting the one or more composite layers unspooled onto the composite panel;
cutting the one or more composite layers unspooled onto the composite panel; and
curing the one or more composite layers unspooled onto the composite panel,
wherein a length of the solid laminate stringer corresponds to a length of the composite panel, and wherein the one or more composite layers are unspooled continuously along a length corresponding to the length of the solid laminate stringer and are stacked lengthwise onto the composite panel to form the solid laminate stringer.