Cold expansion effects on cracked fastener holes under constant amplitude and spectrum loading in the 2024-T351 aluminum alloy
Source abstract
Abstract
Abstract The increased number of aging aircraft in operation today requires a deeper understanding of fatigue life improvement methods. This research focused on the fatigue life benefit from cold expanded holes with preexisting cracks approximately 1.270 mm (0.050 in.) long under constant amplitude and wing spectrum loading. Holes with preexisting cracks were tested to simulate the worst case scenario of a hole with a crack the size of the detection threshold, 1.270 mm (0.050 in.), present before cold expansion that was not found by Non Destructive Inspection. Test results were compared to crack growth models generated in AFGROW. At high stress levels the AFGROW models yielded non conservative results greater than 150% of the test demonstrated fatigue life.
Source: openaire · Quality: candidate unverified · Source record ↗
Research context
OpenAlex topics: Fatigue and fracture mechanics · Non-Destructive Testing Techniques · Probabilistic and Robust Engineering Design
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
References (17)
Show source-provided references
1. Fatigue Technologies Inc., FTI process specification 8101D cold expansion of holes using the standard split sleeve system and countersink cold expansion (CsCx™), Seattle, WA, USA; 2002.
2. Phillips JL. Sleeve cold working fastener holes. Air Force Materials Laboratory AFML-TR-74-10. 1, D6–26271-6. Wright Patterson Air Force Base; 1974.
3. Air Force Structures, Structures Bulletin EN-SB-08-012, Revision B – Nondestructive inspection capability guidelines for United States Air Force aircraft structures, Wright-Patterson AFB, OH, USA; 2011.
4. American Society for Testing Materials (ASTM). Standard test method for measurement of fatigue crack growth rates (E 647). Am Soc Test Mater, West Conshohocken, PA., USA; 2000.
5. Fatigue Technologies Inc. (FTI), FTI process specification 8101D cold expansion of holes using the standard split sleeve system and countersink cold expansion (CsCx™), Seattle, WA, USA; 2002.
6. Grube · 2011
7. Pilarczyk R, Allred T. Damage tolerance analysis ground rules for A-10A reconfigured post desert storm – Rev W. Aircraft Structural Integrity Program (ASIP). Hill Air Force Base, UT, USA; 2010.
8. Wood · 1979
9. Investigation of cold expansion of short edge margin holes with preexisting cracks in 2024-T351 aluminum alloy10.1111/ffe.12123 ↗
10. LexTech Inc., AFGROW (fracture mechanics and fatigue crack growth analysis software), version 5.1.5.16; 2010.
11. Department of Defense, Composite materials handbook (MIL-HDBK-17-3F). Vol. 3: Polymer matrix composites materials usage, design, and analysis, USA; 2002.
12. Fatigue life improvement in fatigue-aged fastener holes using the cold expansion technique10.1016/S0142-1123(03)00152-X ↗
13. An experimental study of fatigue crack initiation and growth from coldworked holes10.1016/0013-7944(79)90122-X ↗
14. Fracture mechanics consideration of residual stresses introduced by coldworking fastener holes10.1115/1.3224790 ↗
15. Fatigue crack propagation from a cold-worked hole10.1016/j.engfracmech.2006.08.006 ↗
16. Hoeppner DW. Estimation of component life by application of fatigue crack growth threshold knowledge. In: Fatigue, creep, and pressure vessels for elevated temperature service. Presented at: The winter annual meeting of the American Society of Mechanical Engineers, 15–21 November 1981, Washington D.C.; 1981.
17. Hoeppner · 2011