Abstract
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.
Full Text 
Sign-in/Register to access full text options
Sign-in/Register to access full text options 
Published version (
Free)
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
