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The aim of this work is to verify functionality of an aircraft strut made of carbon fiber laminate. This goal was achieved in several steps. The aircraft strut model was manufactured and used for two types of mechanical tests. Prior to the tests, FEM simulations had been executed. The simulations predicted the failure mechanism correctly and offered good estimation of critical load. The functionality of the aircraft strut was verified.

FAILURE ANALYSIS OF CARBON FIBER LAMINATE AIRCRAFT STRUT MODEL