In order to reduce the number of necessary actuators, improve reliability and redundancy as well as reducing weight and fuel consumption, a thrust reverser assembly (44) configured for reversing thrust of an aircraft engine (14) is proposed. The thrust reverser assembly (44) comprises flaps (50) and linkage arrangements (52), wherein the flaps (50) are driven between a stowed position and a deployed position by the linkage arrangement (52) due to an axial movement of a part of the engine nacelle (16). The linkage arrangement (52) is configured as a four bar linkage, in particular a double rocker bar linkage (60).

    为了减少必要的致动器的数目、改进可靠性和冗余度、以及减少重量和燃料消耗,提出了一种构造成用于使飞行器发动机(14)的推力反向的推力反向器组件(44)。该推力反向器组件(44)包括风门片(50)和联动装置(52),其中,风门片(50)被联动装置(52)由于发动机短舱(16)的一部分的轴向运动而在收起位置与展开位置之间驱动。联动装置(52)被构造为四杆式联动件,特别地被构造为双摇杆式联动件(60)。


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    Titel :

    THRUST REVERSER ASSEMBLY FOR AN ENGINE NACELLE OF AN AIRCRAFT


    Weitere Titelangaben:

    用于飞行器的发动机短舱的推力反向器组件


    Beteiligte:
    ANDREANI LUC (Autor:in)

    Erscheinungsdatum :

    04.09.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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