An aging aircraft's wing under complex multiaxial spectrum loading

Fatigue assessment and repairing

Keijo Koski (Corresponding Author), J. Tikka, Mika Bäckström, Aslak Siljander, Sauli Liukkonen, Gary Marquis

Research output: Contribution to journalArticleScientificpeer-review

5 Citations (Scopus)

Abstract

The structural responses of an aging aircraft's wing due to operational loading cycles are determined using flight measurement. The stressing in the crack initiation locations in the chemically milled wing skin is a combination of compression, tension and shear. The uniaxial fatigue assessment and observed cracking behaviour indicates that the fatigue assessment should include the multiaxial loading effects. In this paper, the multiaxial fatigue effects are considered by combining the flight measurement results with FE method and engineering judgement. To avoid or repair the cracking of the chemically milled wing skin composite patching is presented for the reconstructive action.
Original languageEnglish
Pages (from-to)652-656
Number of pages5
JournalInternational Journal of Fatigue
Volume28
Issue number5-6
DOIs
Publication statusPublished - 2006
MoE publication typeA1 Journal article-refereed
Event7th International Conference on Biaxial/Multiaxial Fatigue and Fracture - Berlin, Germany
Duration: 28 Jun 20041 Jul 2004

Fingerprint

Cracking
Fatigue
Skin
Aircraft
Aging of materials
Fatigue of materials
Multiaxial Fatigue
Crack Initiation
Repair
Compression
Composite
Engineering
Crack initiation
Cycle
Compaction
Composite materials
Judgment

Keywords

  • wing
  • military aircraft
  • Hawk Mk.51
  • structural fatigue

Cite this

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title = "An aging aircraft's wing under complex multiaxial spectrum loading: Fatigue assessment and repairing",
abstract = "The structural responses of an aging aircraft's wing due to operational loading cycles are determined using flight measurement. The stressing in the crack initiation locations in the chemically milled wing skin is a combination of compression, tension and shear. The uniaxial fatigue assessment and observed cracking behaviour indicates that the fatigue assessment should include the multiaxial loading effects. In this paper, the multiaxial fatigue effects are considered by combining the flight measurement results with FE method and engineering judgement. To avoid or repair the cracking of the chemically milled wing skin composite patching is presented for the reconstructive action.",
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An aging aircraft's wing under complex multiaxial spectrum loading : Fatigue assessment and repairing. / Koski, Keijo (Corresponding Author); Tikka, J.; Bäckström, Mika; Siljander, Aslak; Liukkonen, Sauli; Marquis, Gary.

In: International Journal of Fatigue, Vol. 28, No. 5-6, 2006, p. 652-656.

Research output: Contribution to journalArticleScientificpeer-review

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T1 - An aging aircraft's wing under complex multiaxial spectrum loading

T2 - Fatigue assessment and repairing

AU - Koski, Keijo

AU - Tikka, J.

AU - Bäckström, Mika

AU - Siljander, Aslak

AU - Liukkonen, Sauli

AU - Marquis, Gary

PY - 2006

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AB - The structural responses of an aging aircraft's wing due to operational loading cycles are determined using flight measurement. The stressing in the crack initiation locations in the chemically milled wing skin is a combination of compression, tension and shear. The uniaxial fatigue assessment and observed cracking behaviour indicates that the fatigue assessment should include the multiaxial loading effects. In this paper, the multiaxial fatigue effects are considered by combining the flight measurement results with FE method and engineering judgement. To avoid or repair the cracking of the chemically milled wing skin composite patching is presented for the reconstructive action.

KW - wing

KW - military aircraft

KW - Hawk Mk.51

KW - structural fatigue

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