Behavior of Compression-Loaded Composite Panels with Stringer Terminations and Impact Damage | Zendy

Dawn C. Jegley | Zendy

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Behavior of Compression-Loaded Composite Panels with Stringer Terminations and Impact Damage

Author(s) -

Dawn C. Jegley

Publication year - 1998

Publication title -

journal of aircraft

Language(s) - English

Resource type - Journals

SCImago Journal Rank - 0.64

H-Index - 94

eISSN - 1533-3868

pISSN - 0021-8669

DOI - 10.2514/2.2390

Subject(s) - stringer , materials science , epoxy , fuselage , composite material , compression (physics) , structural engineering , composite number , finite element method , graphite , engineering

The results of an analytical and experimental study of graphite-epoxy stiffened panels with impact-damaged stringer terminations are presented. Five stitched graphite-epoxy panels with stiffeners with a gradual reduction in either thickness or height were examined. Panels were analyzed using finite element analysis and tested by loading them in axial compression,to a predetermined load. The panels were then subjected to impact damage,and loaded to failure. Axial midplane strains, surface strains, interlaminar strains and failure results are discussed.

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