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.

    A hypersonic vehicle (10) has a body (20), a control surface (30), and a hypersonic air-breathing engine (40). The engine includes a converging inlet (100) having a fixed cowling (110) having a first cross-sectional area and a throat (120) having a second cross-sectional area. A flow restrictor (200) is movable between a stowed position and a fully deployed position. The flow restrictor (200) has a third cross-sectional area that is smaller than the first cross-sectional area, such that a consistent gap (210) is formed between a periphery (220) of the flow restrictor (200) and an inner surface (114) of the cowling (110) with the flow restrictor (200) in the fully deployed position and the difference between the first cross-sectional area and the third cross-sectional area is approximately equal to the second cross-sectional area.


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    Title :

    INLET FLOW RESTRICTOR


    Additional title:

    흡입구 흐름 제한기


    Publication date :

    2023-04-04


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Korean


    Classification :

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



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