회전익 항공기에 엔진(50)을 장착하는 방법이 제공된다. 상기 방법은 복수(N)의 회전익들이 작동 회전 주파수(P)로 회전하는 회전익 시스템에 의해 외부 공기 공간을 통하여 비행 지지되는 항공기 본체(54)를 갖는 회전익 항공기를 제공하는 단계를 포함하며, 상기 회전익 항공기 본체는 지속적인 비행 작동 회전 주파수 진동을 갖는다. 상기 방법은, 제 1 엔진을 제공하는 단계를 포함하며, 상기 제 1 엔진은 회전익 시스템 작동 회전 주파수(P)에서 회전익 시스템을 회전시키기 위해 동력을 제공하기 위한 것이다.

    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:

    헬리콥터 엔진 장착 시스템 및 방법


    Beteiligte:

    Erscheinungsdatum :

    2017-08-17


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Koreanisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen / F16F SPRINGS , Federn



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