A helicopter engine mounting system is provided for mounting an engine (50) to an aircraft body (54). The aircraft body (54) is supported in flight by a rotary wing system (56) rotating with an operational rotating frequency (P) with a plurality of (N) rotating blades (58), said aircraft body having a persistent in flight operational rotating frequency vibration from said rotating blades. The engine mounting system includes a top fluid chamber fluid engine mount (60t) and a bottom fluid chamber fluid engine mount (60b). The top fluid chamber fluid engine mount (60t) has a bottom end (62) for grounding to said aircraft body (54), and said bottom fluid chamber fluid engine mount (60b) has a bottom end (62) for grounding to said aircraft body. The top fluid chamber fluid engine mount (60t) has a top fluid chamber (64t) distal from said top fluid chamber fluid engine mount bottom end (62). The bottom fluid chamber fluid engine mount (60b) has a bottom fluid chamber (64b) proximate said bottom fluid chamber fluid engine mount bottom end (62). The system also includes an intermediate cradle (65) with a lateral link (4), said lateral link having a first end (68a) for grounding to said aircraft body (54) and a second distal end (68c). The second distal end (68c) is distal from said first end (68a) and is linked to said intermediate cradle (65). The top fluid chamber fluid engine mount bottom end (62) and said bottom fluid chamber fluid engine mount bottom end (62) are each grounded to said aircraft body (54), with said intermediate cradle (65) disposed between said top fluid chamber fluid engine mount (60t) and said bottom fluid chamber fluid engine mount (60b) and said engine (50). A fluid conduit (70) connects said top fluid chamber fluid engine mount top fluid chamber (64t) with said bottom fluid chamber fluid engine mount bottom fluid chamber (64b) wherein a transfer of said persistent in flight operational rotating frequency vibration from said aircraft body (54) to said engine (50) is inhibited.


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    Titel :

    A HELICOPTER ENGINE MOUNTING SYSTEM AND METHODS


    Weitere Titelangaben:

    SYSTEM UND VERFAHREN ZUR MONTAGE EINES HUBSCHRAUBERMOTORS
    SYSTÈME ET PROCÉDÉS DE POSE DE MOTEUR D'HÉLICOPTÈRE


    Beteiligte:

    Erscheinungsdatum :

    2018-07-25


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F16F SPRINGS , Federn



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