Finite Element Investigation into the Dynamic Instability Characteristics of Laminated Composite Panels
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1990
- Accession Number
- ADA230610
Entities
People
- Walter W. Taylor Jr.
Organizations
- Air Force Institute of Technology