Compressive and shear buckling analysis of metal matrix composite sandwich panels under different thermal environments

Conference · Tue Jun 01 04:00:00 EDT 1993

OSTI ID:5992326

Ko, W L; Jackson, R H

Combined inplane compressive and shear buckling analysis was conducted on flat rectangular sandwich panels using the Raleigh-Ritz minimum energy method with a consideration of transverse shear effect of the sandwich core. The sandwich panels were fabricated with titanium honeycomb core and laminated metal matrix composite face sheets. The results show that slightly slender (along unidirectional compressive loading axis) rectangular sandwich panels have the most desirable stiffness-to-weight ratios for aerospace structural applications; the degradation of buckling strength of sandwich panels with rising temperature is faster in shear than in compression; and the fiber orientation of the face sheets for optimum combined-load buckling strength of sandwich panels is a strong function of both loading condition and panel aspect ratio. Under the same specific weight and panel aspect ratio, a sandwich panel with metal matrix composite face sheets has much higher buckling strength than one having monolithic face sheets.

• Research Organization: National Aeronautics and Space Administration, Cleveland, OH (United States). Lewis Research Center
• OSTI ID: 5992326
• Report Number(s): N-93-27263; NASA-TM--4492; H--1900; NAS--1.15:4492; CONF-9307128--; CNN: RTOP 505-63-40
• Country of Publication: United States
• Language: English

Related Subjects

36 MATERIALS SCIENCE
360603* -- Materials-- Properties
ASPECT RATIO
BUCKLING
COMPRESSION STRENGTH
ELEMENTS
FABRICATION
HONEYCOMB STRUCTURES
MATERIALS
MATRIX MATERIALS
MECHANICAL PROPERTIES
MECHANICAL STRUCTURES
METALS
PANELS
SHEAR PROPERTIES
TITANIUM
TRANSITION ELEMENTS