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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    Titel :

    ОГРАНИЧИТЕЛЬ ПОТОКА ВОЗДУХОЗАБОРНИКА


    Erscheinungsdatum :

    24.10.2017


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Russisch


    Klassifikation :

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