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Thermoelastic investigation of an aluminium helicopter component under non‐adiabatic conditions
Author(s) -
GALLOTTI A.,
SALERNO A.,
DESIDERATI S.,
FANTONI G.
Publication year - 2008
Publication title -
fatigue and fracture of engineering materials and structures
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.887
H-Index - 84
eISSN - 1460-2695
pISSN - 8756-758X
DOI - 10.1111/j.1460-2695.2008.01220.x
Subject(s) - thermoelastic damping , aluminium , materials science , adiabatic process , thermal diffusivity , stress (linguistics) , coating , component (thermodynamics) , composite material , diffusion , thermal , metallurgy , structural engineering , thermodynamics , engineering , physics , linguistics , philosophy
ABSTRACT Thermoelastic Stress Analysis (TSA) has been used to analyze an aeronautic cross‐shaped structural component, composed of several riveted parts, made of different aluminium alloys. Due to the high thermal diffusivity of aluminium, some parts of the component were not in adiabatic conditions during the test, causing an attenuation of the temperature peaks, linked to the stress distribution. Furthermore, the presence of a thick primer coating altered the TSA results on the component especially at high frequencies. After the removal of the primer from some parts of the surface, a correction procedure was applied to compensate for the heat diffusion, thus obtaining quantitative results, which proved to be in very good agreement with the stress values obtained by strain gauges.