A thermoelastic study of an aluminium alloy arm of an helicopter component in non-adiabatic conditions

This study compares the results obtained on a real aluminium alloy component using two strain gauges placed approximately in the region of maximum stress concentration and the result of Thermoelastic stress analysis (TSA), which allows a better spatial resolution. The frequency of the load applied did not allow the achievement of adiabatic conditions, thus producing an error in the stress value measured by the TSA. A correction procedure was used to recover the adiabatic temperature and the correct stress value. Strain gauges results were useful in understanding the kind of correction to apply.