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Thermal behavior of a titanium honeycomb-core sandwich panelFinite element thermal stress analysis was performed on a rectangular titanium honecomb-core sandwich panel which is subjected to thermal load with a temperature gradient across its depth. The distributions of normal stresses in the face sheets and the face-sheet/sandwich-core interfacial shear stresses are presented. The thermal buckling of the heated face sheet was analyzed by assuming the face sheet to be resting on an elastic foundation representing the sandwich core. Thermal buckling curves and thermal buckling load surface are presented for setting the limit for temperature gradient across the panel depth.
Document ID
19910008120
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Ko, William L. (NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Jackson, Raymond H. (NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1991
Subject Category
Structural Mechanics
Report/Patent Number
NAS 1.15:101732
NASA-TM-101732
H-1661
Accession Number
91N17433
Funding Number(s)
PROJECT: RTOP 532-09-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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