NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login

Press Enter or click the Search button to begin your search.

Back to Results
Behavior of Compression-Loaded Composite Panels with Stringer Terminations and Impact DamageThe 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.
Document ID
20040087397
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Jegley, Dawn C. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 1998
Subject Category
Structural Mechanics
Report/Patent Number
AIAA Paper 98-1785
Report Number: AIAA Paper 98-1785
Meeting Information
Meeting: AIAA/ASME/ASCE/AHS 39th Structures, Structural Dynamics and Materials Conference
Location: Long Beach, CA
Country: United States
Start Date: January 1, 1998
Sponsors: American Helicopter Society, Inc., American Society of Civil Engineers, American Society of Mechanical Engineers, American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available