The present invention provides an inlet flow controller. According to the present invention, a hypersonic transfer unit (10) includes a body (20), a control surface (30), and a hypersonic air-breeding engine (40). An engine includes: a cowling (110) having a first cross section area; and a conversing inlet (100) having a throttle (120) having a second cross section area. The flow controller (200) can move between a position of housing and a position of being completely unfolded. The flow controller (200) has a third cross section area smaller than the first cross section area and is formed between an adjacency (220) of the flow controller (200) and an inner surface (114) of the cowling (110) having the flow controller (200) at a position in which a consistent gap (210) is completely unfolded. The difference between the first cross section area and the third cross section area is the same as the second cross section area.

    극초음속 운송수단(10)은 바디(20)와, 조종면(30), 및 극초음속 에어-브리딩 엔진(40)을 갖는다. 엔진은 제1 단면 영역을 갖춘 고정된 카울링(110)과 제2 단면 영역을 갖춘 스로트(120)를 갖춘 컨버징 흡입구(100)를 포함한다. 흐름 제한기(200)는 격납된 위치와 완전하게 전개된 위치 사이에서 이동가능하다. 흐름 제한기(200)는 제1 단면 영역 보다 더 작은 제3 단면 영역을 갖추어, 일괸된 갭(210)이 완전하게 전개된 위치에서 흐름 제한기(200)의 주변(220)과 흐름 제한기(200)를 구비하는 카울링(110)의 내부 표면(114) 사이에서 형성되고, 제1 단면 영역과 제3 단면 영역 사이의 차이가 제2 단면 영역과 대략 동등하다.


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    Titel :

    INLET FLOW RESTRICTOR


    Weitere Titelangaben:

    흡입구 흐름 제한기


    Beteiligte:

    Erscheinungsdatum :

    2017-01-11


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Koreanisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64C AEROPLANES , Flugzeuge



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