The invention relates to a cooling device of an aircraft propeller assembly, comprising:-at least one cooling circuit having at least one air inlet equipped with an air inlet baffle (64) movable between a closed position and an open position and at least one air outlet equipped with an air outlet baffle (66) movable between a closed and open position; -at least one actuator (76) coupled to a pair of intake flaps (64) and exhaust flaps (66) by at least one kinematic chain (78, 78 ') such that the intake flaps (64) and exhaust flaps (66) are activated in synchronous movement and are simultaneously in a closed position or an open position This solution reduces the number of actuators and ultimately reduces the onboard weight of the aircraft.

    本发明涉及一种飞行器推进器组件的冷却装置,包括:‑至少一个冷却回路,其具有配备有可在关闭位置和打开位置之间移动的进气挡板(64)的至少一个空气入口以及配备有可在关闭和打开位置之间移动的排气挡板(66)的至少一个空气出口;‑至少一个致动器(76),其通过至少一个运动链(78、78’)联接至一对进气挡板(64)和排气挡板(66),使得所述进气挡板(64)和排气挡板(66)以同步运动激活并同时处于关闭位置或打开位置。这一解决方案减少了致动器的数量并最终减少了飞行器的机载重量。


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    Titel :

    Cooling arrangement for aircraft thruster assembly


    Weitere Titelangaben:

    飞行器推进器组件的冷却装置


    Beteiligte:

    Erscheinungsdatum :

    2023-02-24


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

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



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