A modelling framework for the calculation of structural loads for fatigue life prediction of helicopter airframe components

A modelling framework for determining structural dynamic loads in airframe components has been developed. This paper addresses the flight dynamics and structural modelling tools of the framework and presents the first validation results. Validation of the calculated component strains has been done by means of comparison with strain gauge measurements on the aft-pylon engine frame during scheduled operational flights. Results show a good agreement for the 3/rev vibrations of the component. Trend analyses provides insight in weight, flight speed and altitude dependencies. The proposed framework is capable of calculating structural dynamic loads of an airframe component in a relatively simple and cost-effective way.