You are being redirected because this document is part of your ASTM Compass® subscription.
This document is part of your ASTM Compass® subscription.
If you are an ASTM Compass Subscriber and this document is part of your subscription, you can access it for free at ASTM Compass
Volume 4, Issue 2 (February 2007)
Fatigue Crack Growth Analyses of Aerospace Threaded Fasteners—Part I: State-of-Practice Bolt Crack Growth Analyses Methods
(Received 3 December 2004; accepted 14 November 2006)
Published Online: 01 March 2007
For RefWorks, EndNote, ProCite, Reference Manager, Zoteo, and many others.
For Microsoft Word
To perform accurate crack growth analyses on roll-threaded fasteners, aerospace designers are required to estimate fatigue crack growth in the threads of a nut-loaded, roll-threaded bolt under tensile fatigue conditions. Threaded fasteners are difficult to analyze due to their asymmetrical geometry and fastener fatigue crack growth data are scant, especially for nondimensionalized crack depths of (a/d)<0.1. Thus, aerospace designers must make simplifying assumptions and perform analyses with presumably conservative methods. History has shown that improper design assumptions/methods on other critical aircraft components has led to catastrophic failures. Because many fasteners are flight safety critical, their analyses must be accurate. Five leading methods to determine the stress intensity multiplication factor, Y(a/d), for threaded fasteners, based on experimental data, analytic equations, or FE methods, or a combination there of, are compared. By comparing and considering these five methods together, critical observations are made to guide future research based on these state-of-practice Y(a/d) solution methods.
Olsen, Kirk W.
Senior Engineering Specialist, LORD Corporation, Erie, PA
Stock #: JAI100491
Title Fatigue Crack Growth Analyses of Aerospace Threaded Fasteners—Part I: State-of-Practice Bolt Crack Growth Analyses Methods