Open AccessDesign of the stringer end of the composite centre wing lower panel in the plug-in butt joint form
Author(s) -
Xinhao Yuan,
Qiming Li,
Dezhi Gong
Publication year - 2021
Publication title -
journal of physics. conference series
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.21
H-Index - 85
eISSN - 1742-6596
pISSN - 1742-6588
DOI - 10.1088/1742-6596/1827/1/012102
Subject(s) - wing , stringer , structural engineering , spark plug , composite number , joint (building) , butt joint , engineering , bending , materials science , mechanical engineering , composite material
The outer wing and the central wing of the aircraft are butted at the wing root through rib 1. The load transfer in the connection zone of the wing root is complex. In the plug-in butt form, additional bending moment will be generated, which is the most prone to damage. Based on the analysis of the force transmission in the butt joint area of the wing root, combined with the test data, this paper proves that the main failure mode of the composite central wing lower panel is the delamination failure of the stringer web at the end, and suggestions for optimal design are proposed.