Accession Number : ADA625655
Title : Linear-Elastic 2D and 3D Finite Element Contact Analysis of a Hole Containing a Circular Insert in a Fatigue Test Coupon
Descriptive Note : Technical rept.
Corporate Author : DEFENCE SCIENCE AND TECHNOLOGY GROUP FISHERMANS BEND (AUSTRALIA)
Personal Author(s) : Waldman, Witold
Full Text : http://www.dtic.mil/get-tr-doc/pdf?AD=ADA625655
Report Date : Jul 2015
Pagination or Media Count : 97
Abstract : Aircraft structures typically contain large numbers of circular holes that are fitted with fasteners such as bolts or rivets. During the service life of aircraft, fatigue damage often occurs at such holes. The accurate analysis of stress distributions occurring around the boundary of holes in the presence of fasteners is therefore an important consideration during studies of fatigue life and test interpretation activities supporting full-scale fatigue test programs. In the present work, two-dimensional linear-elastic plane elasticity solutions for contact stresses caused by a circular disk inserted into a circular hole in an infinite plate undergoing remote loading have been implemented in a FORTRAN program. These were used to validate the contact stress distributions for a circular hole in an aluminium plate fitted with a titanium fastener that were computed using two-dimensional finite element contact analysis. By application of a finite-width correction factor, the analytical infinite-plate solutions were also used as a point of comparison with the results produced by subsequent two-dimensional and three-dimensional finite element contact analyses of a finite-width fatigue test coupon. The results obtained here are useful for aircraft structural integrity analysis work, and subsequent analyses of contact problems such as this one can be expected to be accurate so long as sufficiently refined finite element meshes are utilised.
Descriptors : *AIRFRAMES , *FATIGUE TESTS(MECHANICS) , *FINITE ELEMENT ANALYSIS , *HOLES(OPENINGS) , *THREE DIMENSIONAL , *TWO DIMENSIONAL , AUSTRALIA , BOLTS , FASTENINGS , FATIGUE LIFE , LIFE EXPECTANCY(SERVICE LIFE) , NUMERICAL ANALYSIS , NUMERICAL METHODS AND PROCEDURES , STRESS CONCENTRATION , STRUCTURAL INTEGRITY
Subject Categories : Aircraft
Distribution Statement : APPROVED FOR PUBLIC RELEASE