NUMERICAL INVESTIGATION OF STRUCTURAL HEALTHMONITORING OF CRACKED METALLIC AIRCRAFTSTRUCTURAL PANELS REPAIRED WITH A BONDEDFRP COMPOSITE PATCH

摘要

Repair of cracked metallic aircraft structural panels using bonded FRP compositepatches has been recognized as an efficient and cost-effective method to extend the service life ofaging aircraft. In recent years, structural health monitoring of cracked metallic aircraft structuralpanels repaired with a bonded FRP composite patch has received wide attention. In this paper isproposed the method for identifying the shape of a crack in metallic aircraft structural panels repairedwith a bonded FRP composite patch by utilizing the measured values of induced in-plane strains inthe FRP composite patch under cyclic tensile loading. For several examples of crack shape, effects ofnumber of strain measurement points and position of strain measurement plane in the bonded FRPcomposite patch on the identification results are examined. Moreover, effect of measurement error ofstrains on the identification results is also examined. The validity of the present method is found bycomparing the identification results with the exact ones. Finally, for the identified crack, the ranges ofstress intensity factor along the crack front and the growth rates of the crack under cyclic tensileloading are obtained.