Shear deformable theories for cylindrical laminates - Equilibrium and buckling with applications

Journal Article · Sat Feb 29 23:00:00 EST 1992 · AIAA Journal (American Institute of Aeronautics and Astronautics); (United States)

DOI:https://doi.org/10.2514/3.10991· OSTI ID:5649080

Simitses, G J; Anastasiadis, J S ^[1]

---

1. Cincinnati, University, OH (United States)

A higher order theory is developed (kinematic relations, constitutive relations, equilibrium equations, and boundary conditions), which includes initial geometric imperfections and transverse shear effects for a laminated cylindrical configuration under the actions of lateral pressure, axial compression, and eccentrically applied torsion. Equilibrium equations and boundary conditions are presented for the higher order shear deformation theory. The perturbation technique is employed and buckling equations are derived for symmetric laminates under the action of uniform axial compression and lateral pressure. Buckling loads are computed for axially compressed cylindrical laminates of finite length and pressure loaded very long configurations. 28 refs.

• OSTI ID: 5649080
• Journal Information: AIAA Journal (American Institute of Aeronautics and Astronautics); (United States), Journal Name: AIAA Journal (American Institute of Aeronautics and Astronautics); (United States) Vol. 30; ISSN 0001-1452; ISSN AIAJA
• Country of Publication: United States
• Language: English

Related Subjects

36 MATERIALS SCIENCE
360603 -- Materials-- Properties
42 ENGINEERING
420200* -- Engineering-- Facilities
Equipment
& Techniques
BORON
BOUNDARY CONDITIONS
COMPOSITE MATERIALS
CONFIGURATION
CYLINDRICAL CONFIGURATION
DEFORMATION
ELEMENTS
EPOXIDES
EQUATIONS
MATERIALS
MATHEMATICAL MODELS
ORGANIC COMPOUNDS
ORGANIC OXYGEN COMPOUNDS
PERTURBATION THEORY
SEMIMETALS
SHELLS