Addressing Safety concerns in Hybrid Electric Aircrafts: In-Flight Icing Detection, Moisture Detection in Fuselage and Electrical Wiring and Interconnect System (EWIS)

Abstract Moisture - in the form of water or ice – has adverse consequences on performance an aircraft including wing stall, tail loss thrust, engine flameout, and material damage arising from corrosion electrical shortcuts. During flight, a large flux supercooled droplets surface hybrid electric per unit time could result into icing. A prototype to detect accretion using acoustic emissions is developed. Moreover, during descend, portion frost/ice melts rapidly due rise temperature. If not controlled, may seep inside body through gaps joints. Furthermore, for problem ingression wiring aircrafts, titanium carbonitride-polyvinyl alcohol (TiCN-PVA) composite placed direct contact work as grid health monitoring sensor. For structural parts (floor, bilge, etc.), electrically conductive epoxy carbon black fabricated, characterized SEM, tested DC conductivity under dry wet conditions. Effect different mixing intensities morphology also been explored. Through literature survey trial error, optimized method at laboratory scale preparation black-epoxy presented.