A hybrid heater system for aircraft wing ice protection is provided. The hybrid heater system includes a voltage source (102), a carbon nano-tube (CNT) heater (103), a first positive temperature coefficient (PTC) heater (104) disposed in parallel with the CNT heater to form a parallel formation (105) and a second PTC heater (106) disposed in series between the voltage source and the parallel formation.
HYBRID HEATER FOR AIRCRAFT WING ICE PROTECTION
HYBRIDHEIZUNG FÜR DEN EISSCHUTZ VON FLUGZEUGFLÜGELN
APPAREIL DE CHAUFFAGE HYBRIDE POUR LA PROTECTION DES AILES D'AVION CONTRE LE GIVRE
2020-03-18
Patent
Electronic Resource
English