An environmental control system (ECS) of an aircraft includes an inlet (22) for a first medium, an outlet for the first medium, an air cycle machine (30) including a compressor (32), a turbine (34), and a shaft (38) operably coupling the compressor and the turbine, and a plurality of heat exchangers (40, 44) arranged in fluid communication with the air cycle machine. A first heat exchanger of the plurality of heat exchangers is arranged directly downstream from the turbine and heat is transferred to the first medium within the first heat exchanger. A water extractor (52) is arranged directly downstream from the first heat exchanger and a flow path connects the air cycle machine, the plurality of heat exchangers, and the water extractor with the inlet and the outlet.


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    Title :

    OPTIMIZED ENVIRONMENTAL CONTROL SYSTEM FOR MILITARY AIRCRAFT


    Additional title:

    OPTIMIERTES KLIMAREGELUNGSSYSTEM FÜR MILITÄRISCHE FLUGZEUGE
    SYSTÈME DE CONTRÔLE OPTIMISÉ DE CLIMATISATION POUR UN AÉRONEF MILITAIRE


    Contributors:

    Publication date :

    2021-08-11


    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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