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 conferencePaperOther

Abstract

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, Republic of (South)
Duration: 30 Oct 20181 Nov 2018
Conference number: 7th
https://vtol.org/arf2018

Conference

ConferenceAsian/Australian Rotorcraft Forum 2018
Abbreviated titleARF 2018
CountryKorea, Republic of (South)
CitySeogwipo City, Jeju Island
Period30/10/181/11/18
Internet address

Keywords

  • Additive manufacturing
  • Fatigue crack growth
  • Helicopter fatigue
  • NASGRO

Cite this

Peng, D., Jones, R., Sinha, A., Mathews, N., Singh Raman, R. K., Phan, N., & Nguyen, T. (2019). Analysis of fatigue crack growth in a helicopter component. Paper presented at Asian/Australian Rotorcraft Forum 2018, Seogwipo City, Jeju Island, Korea, Republic of (South).
Peng, D. ; Jones, R. ; Sinha, A. ; Mathews, N. ; Singh Raman, R. K. ; Phan, N. ; Nguyen, T. / Analysis of fatigue crack growth in a helicopter component. Paper presented at Asian/Australian Rotorcraft Forum 2018, Seogwipo City, Jeju Island, Korea, Republic of (South).
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Peng, D, Jones, R, Sinha, A, Mathews, N, Singh Raman, RK, Phan, N & Nguyen, T 2019, 'Analysis of fatigue crack growth in a helicopter component' Paper presented at Asian/Australian Rotorcraft Forum 2018, Seogwipo City, Jeju Island, Korea, Republic of (South), 30/10/18 - 1/11/18, .

Analysis of fatigue crack growth in a helicopter component. / Peng, D.; Jones, R.; Sinha, A.; Mathews, N.; Singh Raman, R. K.; Phan, N.; Nguyen, T.

2019. Paper presented at Asian/Australian Rotorcraft Forum 2018, Seogwipo City, Jeju Island, Korea, Republic of (South).

Research output: Contribution to conferencePaperOther

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T1 - Analysis of fatigue crack growth in a helicopter component

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AU - Jones, R.

AU - Sinha, A.

AU - Mathews, N.

AU - Singh Raman, R. K.

AU - Phan, N.

AU - Nguyen, T.

PY - 2019/1/1

Y1 - 2019/1/1

N2 - 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.

AB - 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.

KW - Additive manufacturing

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KW - NASGRO

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Peng D, Jones R, Sinha A, Mathews N, Singh Raman RK, Phan N et al. Analysis of fatigue crack growth in a helicopter component. 2019. Paper presented at Asian/Australian Rotorcraft Forum 2018, Seogwipo City, Jeju Island, Korea, Republic of (South).