By Rene J. Francillon, Peter B. Lewis
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Additional info for US Navy Air Wings Flamboyant Markings, 1965-1975
49 Time [sec] 4921,5 4922,0 4922,5 4923,0 4923,5 22 4924,0 0,5260 20 18 0,5258 Load [kN] 14 0,5256 12 10 0,5254 8 6 0,5252 4 2 0 24606 Resistance [Ohm] 16 mean–stress/cycle free-electrical resistance change 24608 24610 Resistance [mm] 24612 24614 Fatigue Cycles 24616 24618 0,5250 24620 Load [kN] Fig. 31 Graph of specimen’s electrical resistance and applied load versus time and fatigue cycles Reinforced (CFRPs) laminates under fatigue loading (Fig. 31). The longitudinal resistance change of the specimens was monitored throughout the fatigue experiment.
Taking into consideration their high aspect ratio, large surface area and excellent electrical properties, they offer benefits of an additional reinforcing phase acting at the nano-scale. This evolution provided the necessary momentum for the development of advanced self-sensing structural materials and created a promising technological path towards the ultimate material engineering goal of providing multi-functional materials. In this chapter we review the aforementioned research of nano-enabled self-sensing concepts.
During the cyclic tensile loading-unloading-reloading experiments (Fig. 27), DR/Ro followed the pattern of loading. The laminates with CNT-doped matrix exhibited enhanced sensitivity and capability to track the loading variations. For all materials tested, the peak of DR/Ro increased with the increase of maximum load. 2 On the Use of Electrical Conductivity for the Assessment of Damage in. . 2 100 200 300 Time (data points) 400 500 Fig. 27 Normalized applied load (P/Pmax) and Normalized Resistance change (DR/Ro) vs.