Non-Contact Process to Enhance the Fatigue Life of Aluminum Cold Worked Fastener Holes

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N68335-11-C-0247
Agency Tracking Number: N111-012-1563
Amount: $79,974.00
Phase: Phase I
Program: SBIR
Awards Year: 2011
Solicitation Year: 2011
Solicitation Topic Code: N111-012
Solicitation Number: 2011.1
Small Business Information
PO Box 456, Canal Winchester, OH, -
DUNS: 016525882
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 James Dydo
 CTO/Principal Engineer
 (614) 828-4072
 jrdydo@gatekeyengineering.com
Business Contact
 James Dydo
Title: CTO/Principal Engineer
Phone: (614) 828-4072
Email: jrdydo@gatekeyengineering.com
Research Institution
 Stub
Abstract
Aircraft wing skins contain thousands of fastener holes, which can act as crack initiation sites for structures under severe fatigue conditions. Major cracks have developed around aircraft fastener holes, which can propagate into larger cracks and possible result in catastrophic failure. Compressive residual stresses have been shown to improve fatigue performance for a variety of applications. Current methods of inducing compressive residual stresses in the fastener holes, using cold expansion, do not completely retard the formation and growth of cracks at the entry surface of the holes, since stresses there are lower than at the middle and exit. Gatekey Engineering, Inc., proposes to develop and demonstrate the feasibility of using Electromagnetic Pulse (EM/P) expansion processing to provide deep compressive residual stresses at the entry surface of the hole.

* Information listed above is at the time of submission. *

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