A structural component, including a composite tapered wing spar (1000) including a first fiber layer and a main web, wherein respective longitudinal axes (999) of fibers (1151) making up the first layer at least substantially lying on a plane corresponding to the main web of the wing spar (1000) are curved over at least most of the respective lengths of the fibers.
LATERAL PLY LAYUP OF COMPOSITE SPAR
SEITLICHES LAGEN-LAYUP EINES VERBUNDHOLMS
DRAPAGE À PLI LATÉRAL DE LONGERON COMPOSITE
2016-02-10
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |