Systems and methods are provided for fabricating a preform for a fuselage section of an aircraft. The method includes advancing a series of arcuate mandrel sections (112) in a process direction through an assembly line, placing stringer preforms onto the arcuate mandrel sections (112) via stringer placement stations, uniting the series of arcuate mandrel sections (112) into a combined mandrel; and laying up fiber reinforced material onto the combined mandrel and the stringer preforms.
COMPOSITE ASSEMBLY FOR UNHARDENED FUSELAGE COMPONENTS
VERBUNDANORDNUNG FÜR UNGEHÄRTETE RUMPFKOMPONENTEN
ENSEMBLE COMPOSITE POUR COMPOSANTS DE FUSELAGE NON DURCIS
2022-05-25
Patent
Electronic Resource
English
SAE Technical Papers | 1964