Combined-Load Buckling Behavior of Metal-Matrix Composite Sandwich Panels Under Different Thermal Environments
Ko, William L. and Jackson, Raymond H. (1991) Combined-Load Buckling Behavior of Metal-Matrix Composite Sandwich Panels Under Different Thermal Environments. Technical Report NASA TM-4321, Research Engineering, NASA Dryden Flight Research Center.
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Abstract
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 investigated 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.
| EPrint Type: | NASA Technical Memorandum |
|---|---|
| Keywords: | Aspect ratio, Combined load buckling, Compression loads, Honeycomb core, Load tests, Metal matrix composites, Sandwich panels, Sandwich structures, Shear strength, Thermal environments, Thermal stresses |
| Subjects: | (31 - 39) Engineering: (39) Structural Mechanics |
| ID Code: | 320 |
| Deposited On: | 01 September 2004 |
| Additional Information: | 27 pages. |
