Provided are stiffened stringer panels with integrated plank structures. An example composite panel (100) comprises a skin member (510) having an inner surface (510-A), and a plank (400) on the inner surface. The plank comprises a set of layered laminate plies (420, 422, 424) and extends from a first side (402) to a second side (404). Each laminate ply of the set of layered laminate plies is sized to form a desired geometric profile for each of the first side and the second side. The composite panel further comprises a stringer (520) including a cap portion (521) that spans from the first side of the plank to the second side of the plank to form a first flange portion (524-A) and a second flange portion (524-B), respectively, on the inner surface of the skin member. Base segments of the cap portion conform to the desired geometric profile of respective first and second sides of the plank.
COMPOSITE PLANK SUPPORT FOR STRINGER PANEL
ZUSAMMENGESETZTE PLANKENSTÜTZE FÜR EIN STRINGER-PANEL
SUPPORT DE PLANCHE COMPOSITE POUR PANNEAU DE RAIDISSEUR
25.08.2021
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |