The present invention relates to a thermal management system (10) for a hybrid electric aircraft (100), wherein the system comprises: at least one aircraft unit (12) configured to be used in electric propulsion of the aircraft; a first fluid circuit (18) arranged to cool the at least one aircraft unit; an internal combustion engine (28); a second fluid circuit (30) for the internal combustion engine; and a heat exchanger (20), wherein the first fluid circuit is arranged to provide heating to the second fluid circuit via said heat exchanger.


    Access

    Download


    Export, share and cite



    Title :

    AEROSPACE THERMAL MANAGEMENT SYSTEM


    Contributors:

    Publication date :

    2025-07-31


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



    AEROSPACE THERMAL MANAGEMENT SYSTEM

    FRANSSON JOEL / MARTINS FRANCISCO / CARLSON NILS et al. | European Patent Office | 2025

    Free access

    AEROSPACE ELECTRIC PROPULSION THERMAL MANAGEMENT SYSTEM

    CARLSON NILS / CUENCA ALAIN / HELLSING JOHAN et al. | European Patent Office | 2025

    Free access

    AEROSPACE ELECTRIC PROPULSION THERMAL MANAGEMENT SYSTEM

    CARLSON NILS / CUENCA ALAIN / HELLSING JOHAN et al. | European Patent Office | 2025

    Free access

    Structurally integrated thermal management system for aerospace vehicles

    BLANDING DAVID E / MULEY ARUN / COFFMAN JEFFREY C et al. | European Patent Office | 2018

    Free access

    STRUCTURALLY INTEGRATED THERMAL MANAGEMENT SYSTEM FOR AEROSPACE VEHICLES

    DAVID E BLANDING / ARUN MULEY / JEFFREY C COFFMAN et al. | European Patent Office | 2017

    Free access