OS03F053 Thermoelastic investigation of a large helicopter component under a multi-axial load

• SALERNO Antonio

  Department of Energy, Politecnico di Milano

• DESIDERATI Stefano

  Department of Energy, Politecnico di Milano

抄録

A large aluminum alloy helicopter component under a modulated multi-axial load was investigated using thermoelastic stress analysis. Due to the considerable size of the component, the frequency of the test could not exceed 0.7 Hz. This low frequency and the high thermal diffusivity of the aluminum alloy did not allow the achievement of adiabatic conditions, thus producing an attenuation of the thermoelastic amplitude signal. While TSA allowed to precisely locate the region of appearance of a crack close to the rear vertical attachment, the fatigue crack in the region of the front vertical attachment appeared in a region not corresponding to that of the maximum thermoelastic signal. This inconsistency was explained by the presence of a considerable static component in the loads applied by two of the hydraulic jacks. A correction procedure was performed on the raw TSA amplitude values, in order to recover the adiabatic temperature distribution.

収録刊行物

• Abstracts of ATEM : International Conference on Advanced Technology in Experimental Mechanics : Asian Conference on Experimental Mechanics

  Abstracts of ATEM : International Conference on Advanced Technology in Experimental Mechanics : Asian Conference on Experimental Mechanics 2011.10 (0), _OS03F053--_OS03F053-, 2011

  一般社団法人 日本機械学会

キーワード

• thermoelastic stress analysis
• non adiabatic conditions
• correction procedure

詳細情報

• CRID: 1390282680847323648
• NII論文ID: 110009967600
• DOI: 10.1299/jsmeatem.2011.10._os03f053-
• ISSN: 24242837
• Web Site: https://www.jstage.jst.go.jp/article/jsmeatem/2011.10/0/2011.10__OS03F053-/_pdf
• 本文言語コード: en
• データソース種別:
  • JaLC
  • Crossref
  • CiNii Articles
• 抄録ライセンスフラグ: 使用不可