Accession Number : AD0675798

Title :   A GENERAL TECHNIQUE FOR BUCKLING ANALYSIS WITH A FINITE ELEMENT SOLUTION APPLICATION,

Corporate Author : BOEING CO RENTON WASH AIRPLANE DIV

Personal Author(s) : Hicks,Gardner W. , Jr

Report Date : 16 FEB 1966

Pagination or Media Count : 219

Abstract : This paper presents some of the basic principles of a particular technique for buckling load analysis. The technique is quite general and is not dependant on any particular one of the many methods of structural analysis but may be used in combination with any of them. Examples are given, based on finite element idealizations and using both the force and displacement methods of structural analysis. The object of the investigations described herein has been to establish the capabilities, potentials, advantages and disadvantages of the method and to establish them sufficiently to permit the evaluation of the method with respect to other buckling analysis techniques. The technique is based on an obvious physical model. In the force (stiffness) formulations an initial deflection (moment) distribution is assumed, moments (deflections) are obtained using the axial load, and the deflections (moments) of the structure required to equilibrate the moments (deflections) are obtained. The deflections (moments) are then considered as new assumptions and the process repeated. Convergence to a buckled shape is rapid, and the critical load is obtained as a ratio between successive unnormalized shapes. (Author)

Descriptors :   (*STRUCTURES, *BUCKLING), AIRFRAMES, LOADS(FORCES), MATRICES(MATHEMATICS), HONEYCOMB CORES, SANDWICH CONSTRUCTION, STRUCTURAL PROPERTIES

Subject Categories : Aircraft
      Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE