OPTIMIZED STRINGER RUN-OUT ZONES IN AIRCRAFT COMPONENTS

摘要

Aircraft component, such as an aircraft wing, that comprises at least one panel (11) of a composite material formed by a skin (13) and at least a stiffening stringer (15) configured by a web (17) and a foot (19) bonded to said skin (13); the stringer (15) having a run-out zone inside said panel (11) subjected to a high load level; the stringer (15) having a web (17) of decreasing height in said run-out zone and a foot (19) having a first section (31) of variable width from an initial value W1 to a final value W2 and a second section (33) with a width W2 in said run-out zone; the foot (19) and the web (17) of said stringer (15) having a decreasing thickness in said run-out zone for improving the load transfer from the stringer (15) to the skin (13).