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Thermal behavior of a titanium honeycomb-core sandwich panel
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Ko, William L. Jackson, Raymond H. |
| Copyright Year | 1991 |
| Description | 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. |
| File Size | 428188 |
| Page Count | 14 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19910008120 |
| Archival Resource Key | ark:/13960/t2f81890v |
| Language | English |
| Publisher Date | 1991-01-01 |
| Access Restriction | Open |
| Subject Keyword | Structural Mechanics Finite Element Method Stress Analysis Honeycomb Cores Temperature Effects Temperature Gradients Rectangular Panels Shear Stress Titanium Thermal Buckling Thermal Stresses Depth Loads Forces Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
