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Experimental and analytical study of the effects of floor location on response of composite fuselage framesExperimental and analytical results are presented of the effects of floor placement on the structural response and strength of I-cross section, semi-circular fuselage frames constructed of graphite-epoxy composite material. The composite frame configuration is representative of current conventional aircraft design. Experimental strain distributions are presented from static loading tests of the composite frames and compared with finite element structural models and closed form solutions. An understanding of floor location effects can aid dynamists in predicting the crash behavior of these conventional structures, and may assist the designer in developing crashworthy structures for future aircraft.
Document ID
19920051738
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Jones, Lisa E.
(NASA Langley Research Center Hampton, VA, United States)
Robinson, Martha
(NASA Langley Research Center Hampton, VA, United States)
Fasanella, Edwin L.
(Lockheed Engineering and Sciences Co. Hampton, VA, United States)
Boitnott, Richard L.
(U.S. Army, Aerostructures Directorate, Hampton VA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 92-2473
Meeting Information
Meeting: AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Location: Dallas, TX
Country: United States
Start Date: April 13, 1992
End Date: April 15, 1992
Accession Number
92A34362
Distribution Limits
Public
Copyright
Other

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