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TSA‐FEM Comparative Analysis of a Helicopter Component under Multiaxial Load
Author(s) -
Colombo D.,
Desiderati S.,
Giglio M.,
Salerno A.
Publication year - 2007
Publication title -
strain
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.477
H-Index - 47
eISSN - 1475-1305
pISSN - 0039-2103
DOI - 10.1111/j.1475-1305.2007.00352.x
Subject(s) - finite element method , structural engineering , component (thermodynamics) , strain gauge , adiabatic process , rotor (electric) , thermoelastic damping , stress (linguistics) , materials science , engineering , mechanical engineering , physics , thermal , linguistics , philosophy , meteorology , thermodynamics
Thermoelastic stress analysis (TSA) is applied to a helicopter titanium tail rotor hub component with complex geometry and subjected to multiaxial loads. The frequency of the loads adopted in the TSA test was 2 Hz because of the fact that hydraulic actuators were used. As a consequence, non‐adiabatic conditions were met in some parts of the component and a correction applied to the raw data obtained by TSA. The reliability of the corrected TSA data was checked by comparing the data with the results of a finite element model, validated previously by strain gauge measures. The good agreement between the experimental and the numerical data shows that TSA can be successfully used for structural components with complex geometry and subjected to multiaxial loads under non‐adiabatic conditions.