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OverviewFinite 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... Full Product DetailsAuthor: National Aeronautics and Space Adm NasaPublisher: Independently Published Imprint: Independently Published Dimensions: Width: 21.60cm , Height: 0.20cm , Length: 27.90cm Weight: 0.095kg ISBN: 9781792946554ISBN 10: 1792946554 Pages: 30 Publication Date: 03 January 2019 Audience: General/trade , General Format: Paperback Publisher's Status: Active Availability: Available To Order ![]() We have confirmation that this item is in stock with the supplier. It will be ordered in for you and dispatched immediately. Table of ContentsReviewsAuthor InformationTab Content 6Author Website:Countries AvailableAll regions |