Stress field in postbuckled composite stiffeners loaded in compression

Conference · Fri Dec 31 04:00:00 EST 1993

OSTI ID:143202

Uda, N ^[1]; Parnas, L ^[2]; Armanios, E A ^[3]

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1. Kyushu Univ., Fukuoka (Japan). Dept. of Aeronautics and Astronautics
2. Middle East Technical Univ., Ankara (Turkey). Mechanical Engineering Dept.
3. Georgia Institute of Technology, Atlanta, GA (United States). School of Aerospace Engineering

The stress field in a postbuckled I-section composite stiffener under compression is presented. The flange and web elements are symmetric orthotropic laminates and the loaded ends are simply supported. The analysis is based upon a higher-order shear deformation theory. By assuming trigonometric functions in the loading direction for the displacement field, the nonlinear large nonlinear large deflection equations are converted into simultaneous first-order nonlinear ordinary differential equations. These equations can be solved numerically for any boundary condition along the unloaded edges using a two-point boundary condition along the unloaded edges using a two-point boundary value problem solver. Results show that peel stress initiates at the free-edge of the flange. The locations of the maximum peel stress coincide with the failure sites observed in previous experiments.

• OSTI ID: 143202
• Report Number(s): CONF-930246--; ISBN 0-87339-251-5
• Country of Publication: United States
• Language: English

Related Subjects

36 MATERIALS SCIENCE
COMPOSITE MATERIALS
COMPRESSION STRENGTH
MATHEMATICAL MODELS
MECHANICAL PROPERTIES
TENSILE PROPERTIES