Effects of floor location on response of composite fuselage framesExperimental and analytical results are presented which show the effect of floor placement on the structural response and strength of circular fuselage frames constructed of graphite-epoxy composite material. The research was conducted to study the behavior of conventionally designed advanced composite aircraft components. To achieve desired new designs which incorporate improved energy absorption capabilities requires an understanding of how these conventional designs behave under crash type loadings. Data are presented on the static behavior of the composite structure through photographs of the frame specimen, experimental strain distributions, and through analytical data from composite structural models. An understanding of this behavior can aid dynamist in predicting the crash behavior of these structures and may assist the designer achieve improved designs for energy absorption and crash behavior of future structures.
Document ID
19930062812
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Carden, Huey D. (NASA Langley Research Center Hampton, VA, United States)
Jones, Lisa E. (NASA Langley Research Center Hampton, VA, United States)
Fasanella, Edwin L. (Lockheed Engineering & Sciences Co. Hampton, VA, United States)
Date Acquired
August 16, 2013
Publication Date
November 1, 1991
Subject Category
Aircraft Design, Testing And Performance
Meeting Information
Meeting: DOD, NASA, and FAA, Conference on Fibrous Composites in Structural Design