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Combined-load buckling behavior of metal-matrix composite sandwich panels under different thermal environments
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Ko, William L. Jackson, Raymond H. |
| Copyright Year | 1991 |
| Description | Combined compressive and shear buckling analysis was conducted on flat rectangular sandwich panels with the consideration of transverse shear effects of the core. The sandwich panel is fabricated with titanium honeycomb core and laminated metal matrix composite face sheets. The results show that the square panel has the highest combined load buckling strength, and that the buckling strength decreases sharply with the increases of both temperature and panel aspect ratio. The effect of layup (fiber orientation) on the buckling strength of the panels was studied in detail. The metal matrix composite sandwich panel was much more efficient than the sandwich panel with nonreinforced face sheets and had the same specific weight. |
| File Size | 842872 |
| Page Count | 30 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19910021249 |
| Archival Resource Key | ark:/13960/t2f818958 |
| Language | English |
| Publisher Date | 1991-09-01 |
| Access Restriction | Open |
| Subject Keyword | Structural Mechanics Honeycomb Cores Thermal Environments Temperature Effects Compression Loads Shear Strength Metal Matrix Composites Aspect Ratio Sandwich Structures Buckling Thermal Stresses Load Tests 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 |
