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A study of the structural efficiency of fluted core graphite-epoxy panelsThe structural efficiency of compression-loaded graphite-epoxy sandwich panels with fluted cores is studied to determine their weight saving potential. Graphite-epoxy equilateral triangular elements are used to construct the fluted cores for the sandwich panels. Two panel configurations are considered. One configuration has two layers of triangular elements in the fluted core and the second configuration has only one layer of triangular elements in the core. An optimization code is used to find the minimum weight design for each panel configuration. Laminate ply orientations are limited to approx. 45, 0, and 90 deg. A constraint on the axial stiffness is included in the design process so the panel will conform to typical constraints for aircraft wing structures. Minimum thickness requirements for each laminate and maximum allowable strains are also included. A comparison is made of the calculated structural efficiency of the fluted core panels to the structural efficiency of aluminum transport aircraft structures and simple blade-stiffened graphite-epoxy panels. Limited experimental results are also included for comparison with the analytical predictions and to identify the critical failure mechanisms of graphite-epoxy fluted-core sandwich panels.
Document ID
19900008754
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Jegley, Dawn C. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1990
Subject Category
Structural Mechanics
Report/Patent Number
NAS 1.15:101681
NASA-TM-101681
Accession Number
90N18070
Funding Number(s)
PROJECT: RTOP 505-63-01-09
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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