Fatigue analysis for CF-18 component:wing fold shear-tie lug

  1. (PDF, 2 MB)
  2. Get@NRC: Fatigue analysis for CF-18 component:wing fold shear-tie lug (Opens in a new window)
DOIResolve DOI: http://doi.org/10.1016/j.proeng.2010.03.180
AuthorSearch for: ; Search for:
Journal titleProcedia Engineering
Pages16731682; # of pages: 10
SubjectLife prediction; HOLSIP; Short crack; FEM; Fractography; 7050
AbstractThis paper presents the results of a fatigue analysis of a CF-18 aft wing fold shear-tie lug, which involved multiple crack nucleation sites and short crack growth under complex geometry and loading conditions. A three-dimensional (3D) finite element model was developed to simulate the loading applied in the shear-tie lug test and determine the local stress/strain distribution. Short crack data and the subsequent material model, were specifically developed for the lug material (7050-T7452 forging), in which work the Holistic Structural Integrity Process (HOLSIP) approach was used to correlate the short crack model with material microstructural features, such as constituent particles and porosities. After the shear-tie lug fatigue test, quantitative fractography (QF) was carried out to measure the crack growth size. Based on the failure mechanisms, a simplified single crack model was proposed to analyze this multiple crack growth problem, and the life estimation compared well with the test results.
Publication date
AffiliationNRC Institute for Aerospace Research; National Research Council Canada
Peer reviewedYes
NPARC number21276092
Export citationExport as RIS
Report a correctionReport a correction
Record identifierd60e9b05-10f7-47d8-97ad-2c564418afb0
Record created2015-09-23
Record modified2016-05-09
Bookmark and share
  • Share this page with Facebook (Opens in a new window)
  • Share this page with Twitter (Opens in a new window)
  • Share this page with Google+ (Opens in a new window)
  • Share this page with Delicious (Opens in a new window)
Date modified: