An aging aircraft's wing under complex multiaxial spectrum loading: Fatigue assessment and repairing

Keijo Koski; J. Tikka; Mika Bäckström; Aslak Siljander; Sauli Liukkonen; Gary Marquis

doi:10.1016/j.ijfatigue.2005.06.053

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 journal › Article › Scientific › peer-review

6 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 language	English
Pages (from-to)	652-656
Number of pages	5
Journal	International Journal of Fatigue
Volume	28
Issue number	5-6
DOIs	https://doi.org/10.1016/j.ijfatigue.2005.06.053
Publication status	Published - 2006
MoE publication type	A1 Journal article-refereed
Event	7th International Conference on Biaxial and Multiaxial Fatigue and Fracture - Berlin, Germany Duration: 28 Jun 2004 → 1 Jul 2004

Keywords

wing
military aircraft
Hawk Mk.51
structural fatigue

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10.1016/j.ijfatigue.2005.06.053

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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.",

keywords = "wing, military aircraft, Hawk Mk.51, structural fatigue",

author = "Keijo Koski and J. Tikka and Mika B{\"a}ckstr{\"o}m and Aslak Siljander and Sauli Liukkonen and Gary Marquis",

year = "2006",

doi = "10.1016/j.ijfatigue.2005.06.053",

language = "English",

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journal = "International Journal of Fatigue",

issn = "0142-1123",

publisher = "Elsevier",

number = "5-6",

note = "7th International Conference on Biaxial and Multiaxial Fatigue and Fracture, ICBMFF ; Conference date: 28-06-2004 Through 01-07-2004",

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

T2 - 7th International Conference on Biaxial and Multiaxial Fatigue and Fracture

AU - Koski, Keijo

AU - Tikka, J.

AU - Bäckström, Mika

AU - Siljander, Aslak

AU - Liukkonen, Sauli

AU - Marquis, Gary

PY - 2006

Y1 - 2006

N2 - 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.

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

U2 - 10.1016/j.ijfatigue.2005.06.053

DO - 10.1016/j.ijfatigue.2005.06.053

M3 - Article

SN - 0142-1123

VL - 28

SP - 652

EP - 656

JO - International Journal of Fatigue

JF - International Journal of Fatigue

IS - 5-6

Y2 - 28 June 2004 through 1 July 2004

ER -

An aging aircraft's wing under complex multiaxial spectrum loading: Fatigue assessment and repairing

Abstract

Keywords

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