An ice protection system (50) for controlling icing on an aircraft surface includes an OAT sensor (40) configured to provide a signal indicative of an OAT, a LWC detector (44) configured to provide a signal indicative of a LWC, an electrothermal device (56) located on the aircraft surface, and an electronic control system (52) configured to determine a critical temperature (TC) at or below which an anti-icing system will be used to preheat the aircraft surface, supply an electrical power having a calculated power level to the electrothermal device, and calculate the power level as being: zero if OAT > TC and LWC = 0, controlled based on OAT and LWC if OAT > TC and LWC > 0, controlled based on OAT and LWC if OAT < TC and LWC > 0, and controlled based on OAT if OAT < TC and LWC = 0.


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    Title :

    AIRCRAFT ICE PROTECTION CONTROL SYSTEM PREHEAT LOGIC


    Additional title:

    VORWÄRMLOGIK FÜR FLUGZEUGEISSCHUTZSTEUERUNGSSYSTEM
    LOGIQUE DE PRÉCHAUFFAGE DE SYSTÈME DE COMMANDE DE PROTECTION CONTRE LE GIVRE D'UN AÉRONEF


    Contributors:

    Publication date :

    2023-04-26


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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