Thermal Behavior of a Titanium Honeycomb-Core Sandwich Panel

By National Aeronautics and Space Administration

Finite 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. Ko, William L. and Jackson, Raymond H. Armstrong Flight Research Center NASA-TM-101732, H-1661, NAS 1.15:101732 RTOP 532-09-01...

• Format: Paperback
• Language: English
• ISBN: 1792946554
• ISBN13: 9781792946554
• Release Date: January 1
• Publisher: Independently Published
• Length: 30 Pages
• Weight: 0.21 lbs.
• Dimensions: 0.1" x 8.5" x 11.0"