Thermal buckling of laminated composite shells

Journal Article · Tue May 01 00:00:00 EDT 1990 · AIAA Journal (American Institute of Aeronautics and Astronautics); (USA)

DOI:https://doi.org/10.2514/3.25130· OSTI ID:6723832

Thangaratnam, R K; Palaninathan, R; Ramachandran, J ^[1]

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1. Indian Institute of Technology, Madras (India)

The linear buckling analysis of laminated composite cylindrical and conical shells under thermal load using the finite element method is reported here. Critical temperatures are presented for various cases of cross-ply and angly-ply laminated shells. The effects of radius/thickness ratio, number of layers, ratio of coefficients of thermal expansion, and the angle of fiber orientation have been studied. The results indicate that the buckling behavior of laminated shell under thermal load is different from that of mechanically loaded shell with respect to the angle of fiber orientation. 6 refs.

• OSTI ID: 6723832
• Journal Information: AIAA Journal (American Institute of Aeronautics and Astronautics); (USA), Journal Name: AIAA Journal (American Institute of Aeronautics and Astronautics); (USA) Vol. 28; ISSN 0001-1452; ISSN AIAJA
• Country of Publication: United States
• Language: English

Related Subjects

42 ENGINEERING
420200* -- Engineering-- Facilities
Equipment
& Techniques
CONFIGURATION
CRITICAL TEMPERATURE
CYLINDRICAL CONFIGURATION
DEFORMATION
DIMENSIONS
EXPANSION
FIBERS
FINITE ELEMENT METHOD
LAYERS
MATERIALS
NUMERICAL SOLUTION
PHYSICAL PROPERTIES
REINFORCED MATERIALS
SHELLS
THERMAL EXPANSION
THERMODYNAMIC PROPERTIES
THICKNESS
TRANSITION TEMPERATURE