Analysis of fatigue crack growth in a helicopter component

D. Peng, R. Jones, A. Sinha, N. Mathews, R. K. Singh Raman, N. Phan, T. Nguyen

Research output: Contribution to conferencePaper


The aerospace industry is now beginning to adopt Additive Manufacturing (AM) both for new aircraft design and to help improve aircraft availability (aircraft sustainment). However, MIL-STD 1530 highlights that to certify airworthiness the operational life of the airframe must be determined by a damage tolerance analysis. MIL-STD 1530 also states that in this process the role of testing is merely to validate or correct the analysis. Consequently, if AM produced parts are to be used as load carrying members it is important that the da/dN versus ΔK curves be determined and, if possible, a valid mathematical representation determined. In this context it has recently been shown that for AM materials the da/dN versus ΔK curves can be represented reasonably well by the Hartman-Schijve (HS) variant of the NASGRO crack growth equation. This paper builds on these findings to show the HS equation can be used to accurately compute fatigue crack growth in a helicopter airframe component subjected to an industry standard flight load spectra. This finding raises the possibility to use the HS equation to assess the potential for using AM replacement parts for operational helicopters.

Original languageEnglish
Publication statusPublished - 1 Jan 2019
EventAsian/Australian Rotorcraft Forum 2018 - Seogwipo City, Jeju Island, Korea, South
Duration: 30 Oct 20181 Nov 2018
Conference number: 7th


ConferenceAsian/Australian Rotorcraft Forum 2018
Abbreviated titleARF 2018
Country/TerritoryKorea, South
CitySeogwipo City, Jeju Island
Internet address


  • Additive manufacturing
  • Fatigue crack growth
  • Helicopter fatigue

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