Date of Award

12-1990

Document Type

Thesis

Degree Name

Master of Science in Aeronautical Engineering

Department

Department of Aeronautics and Astronautics

First Advisor

Anthony Palazotto, PhD

Abstract

Dynamic instability of a laminated composite panel subjected to a transverse load is studied. Up to cubic variations in the thickness coordinate are included in the inplane displacement field, and only the constant component is kept in the transverse displacement. The transverse shear strains retain only linear displacement terms and vary parabolically through the thickness. The complete quadratic displacement functions are included in the inplane strains. A 36 degree of freedom shell element is used to obtain numerical results. The static snap through load vs displacement curve, as well as the critical collapse load, is examined by invoking the Riks technique along with the Newton-Raphson iteration scheme. The beta-m time marching integration method is employed to evaluate a dynamic response. Two step loads, with the step magnitude slightly below and above the critical collapse load, are introduced in the dynamic analysis. The response resulting from the dynamic analysis matches the displacement on the static load vs displacement curve.

AFIT Designator

AFIT-GAE-ENY-90D-28

DTIC Accession Number

ADA230610

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