US 12,350,892 B2
Co-cured UV/visible light-resistant fiberglass coated composite material for aircraft fuselage assembly
Alain A. Adjorlolo, Shoreline, WA (US); Patrice K. Ackerman, Kent, WA (US); and Jason A. Bolles, Kent, WA (US)
Assigned to THE BOEING COMPANY, Arlington, VA (US)
Filed by The Boeing Company, Chicago, IL (US)
Filed on Mar. 30, 2022, as Appl. No. 17/708,404.
Prior Publication US 2023/0311427 A1, Oct. 5, 2023
This patent is subject to a terminal disclaimer.
Int. Cl. B29C 70/06 (2006.01); B29C 70/28 (2006.01); B64C 1/00 (2006.01); B29K 63/00 (2006.01); B29K 309/08 (2006.01); B29L 31/30 (2006.01)
CPC B29C 70/06 (2013.01) [B29C 70/28 (2013.01); B64C 1/00 (2013.01); B29K 2063/00 (2013.01); B29K 2309/08 (2013.01); B29K 2995/0018 (2013.01); B29L 2031/3082 (2013.01); B64C 2001/0072 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A co-curable composite material fuselage assembly consisting of:
a co-curable composite material assembly comprising:
a co-curable composite material substrate, said co-curable composite material substrate comprising a co-curable composite material substrate first side and a co-curable composite material substrate second side;
a co-curable UV/visible light-resistant fiberglass layer, said co-curable UV/visible light-resistant fiberglass layer comprising a co-curable UV/visible light-resistant fiberglass layer first side and a co-curable UV/visible light-resistant fiberglass layer second side, only said co-curable UV/visible light-resistant fiberglass layer configured to be in immediate contact with at least one of the co-curable composite material substrate first side and the co-cured composite material substrate second side, said co-curable UV/visible light-resistant fiberglass layer consisting of a single ply layer co-curable UV/visible light-resistant fiberglass layer, said co-curable UV/visible light-resistant fiberglass layer exclusively imparting 100% of a degree of UV/visible light protection imparted to the co-curable composite material substrate by the co-curable UV/visible light-resistant fiberglass layer;
wherein the co-curable UV/visible light-resistant fiberglass layer has a UV/visible light transmittance value of 0% to about 20% for UV/visible light wavelengths ranging from about 200 nm to about 800 nm when the co-curable UV/visible light-resistant fiberglass layer comprises an average thickness ranging from about 2 mils to about 6 mils;
wherein the co-curable composite material substrate in combination with the co-curable UV/visible light-resistant fiberglass layer is configured to form the co-curable composite material fuselage assembly;
wherein the co-curable composite material substrate is co-curable with the co-curable UV/visible light-resistant fiberglass layer at a temperature ranging from about 250° F. to about 370° F.;
wherein the co-curable composite material substrate second side is in direct contact with the co-curable UV/visible light-resistant fiberglass layer first side;
wherein the co-curable UV/visible light-resistant fiberglass layer completely covers the co-curable composite material substrate second side; and
wherein the co-curable composite material substrate assembly does not contain an additional UV/visible light-resistant layer.