Design Optimization of Blade Stiffened Laminated Composite Plates for Maximum Buckling Load

Abstract

The buckling load of a blade stiffened laminated composite plate having midplane symmetry is maximized for a given total weight. The thickness of the layers and the width and height of the stiffener are taken as the design variables. Buckling analysis is carried out using a finite element method. The optimization problem is solved using commercially available optimization packages. Due to the highly nonlinear nature of the optimality equations, several local optimum solutions are found. To examine the relationship between the number of local optimums and their relative magnitudes, various combinations of fiber orientation for the laminate layers and the blade stiffener are investigated.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1990
Accession Number
ADA241651

Entities

People

  • Mark R. Achenbach

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms
  • C4I
  • Space

DTIC Thesaurus Topics

  • Composite Materials
  • Computational Fluid Dynamics
  • Computer Programs
  • Computers
  • Equations
  • Finite Element Analysis
  • Geometry
  • Lagrangian Functions
  • Laminates
  • Materials
  • Mechanics
  • Modulus Of Elasticity
  • Optimization
  • Physical Properties
  • Shear Modulus
  • Stress Strain Relations
  • Thickness

Fields of Study

  • Physics

Readers

  • Adaptive Control and Estimation with Uncertainty in Dynamic Systems.
  • Structural Dynamics.