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:

    EINLASSDURCHFLUSSBEGRENZER
    LIMITEUR D'ÉCOULEMENT D'ENTRÉE


    Contributors:

    Publication date :

    2019-11-06


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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