Self-stiffened composite material panel for use in e.g. fuselage box, in aeronautical field, has reinforcing fibers embedded between two consecutive fiber plies of flanged edges of preforms to form reinforced preforms with reinforced edges

摘要

The panel has a skin (4) and stiffeners (3a) extending in parallel, where the panel is formed from juxtaposed preforms including a stack of fiber plies (Q0-Qj) having a U-shaped section formed by two flanged edges connected to a core (22) via an intermediate elbow (2e). Reinforcing fibers (51) are embedded between two consecutive plies of two flanged edges of the preforms to form reinforced preforms (2a) with reinforced edges (21a), where the plies of the reinforced panel are impregnated with resin. An independent claim is also included for an assembly method for realizing the self-stiffened composite material panel.