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Numerical Strip-Yield Calculation of CTODMany existing methods to calculate CTOD can be costly and complicated, or apply only to particular configurations. A new numerical method for calculating CTOD was investigated. NASGRO's Boundary Element module NASBEM was adapted to calculate displacements at any point on the crack. Demonstrated for a number of crack configurations: a) finite and infinite domains; b) center and edge cracks; and c) complex cases with several cracks and holes. Great accuracy at minimal computational cost.
Document ID
20070017318
Acquisition Source
Johnson Space Center
Document Type
Conference Paper
Authors
Beek, Joachim (NASA Johnson Space Center Houston, TX, United States)
Forman, Royce (NASA Johnson Space Center Houston, TX, United States)
Date Acquired
August 23, 2013
Publication Date
April 16, 2007
Subject Category
Aircraft Design, Testing And Performance
Meeting Information
Meeting: 10th Joint DOD/NASA/FAA Conference on Aging
Location: Palm Springs, CA
Country: United States
Start Date: April 16, 2007
End Date: April 19, 2007
Sponsors: Federal Aviation Administration, Department of Defense, NASA Headquarters
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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