A system for protecting a surface of an aircraft against icing by blasting a quantity of warming air against the surface in order to warm it, this quantity of warming air needing to be at a permissible temperature to which the surface can be exposed without compromising the mechanical integrity thereof. The system includes: structures for bleeding a quantity of bleed air from a pneumatic hot source and for conveying this quantity of bleed air, the quantity of bleed air being at a temperature higher than the permissible temperature; structures for capturing and conveying a quantity of collected air corresponding to a portion of the quantity of warming air after it has been blasted against the surface that is to be warmed, this quantity of collected air being at a temperature lower than the permissible temperature; regulating and mixing structures which regulate the quantities of collected and bleed air in order, by mixing these two quantities, to form the quantity of warming air at the permissible temperature; structures for conveying the quantity of warming air towards and blasting it against the aircraft surface that is to be warmed.


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    Title :

    SYSTÈME POUR AÉRONEF DE PROTECTION CONTRE LE GIVRE PAR AIR CHAUD SOUFFLÉ À PÉNALITÉ ÉNERGÉTIQUE RÉDUITE


    Additional title:

    AIRCRAFT HOT AIR ICE PROTECTION SYSTEM WITH REDUCED ENERGY PENALITY
    HEISSLUFTENTEISUNG MIT VERRINGERTEM ENERGIEVERBRAUCH FÜR FLUGZEUGE


    Contributors:

    Publication date :

    2024-11-20


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    French


    Classification :

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




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