PROBLEM TO BE SOLVED: To provide a boundary layer control device of an aircraft which suppresses boundary layer separation and, thereby, highly contributes to stable flight of the aircraft even upon landing and taking-off of the aircraft in which the separation is easy to occur on a main wing upper surface part, because an intake port opened to the main wing upper surface part and a discharge port opened to a suction side inner circumferential surface on a propulsion engine are communicated by a communication path.SOLUTION: A single or a plurality of intake ports 3 for taking-in air of a main wing upper surface part 2 are opened and provided on the main wing upper surface part 2 of an aircraft 1, a first opening and closing valve 4 which is controlled by an operation system of the aircraft 1 and opens and closes the intake ports 3 is provided on the intake port 3, a single or a plurality of ejection holes 7 for ejecting air taken-in by the intake port 3 are opened and provided on a suction side inner circumferential surface 6 on a propulsion engine 5 of the aircraft 1, and a second opening and closing valve 8 which is controlled by the operation system of the aircraft 1 and opens and closes the ejection holes 7 is provided on the ejection holes 7. Therein, when the first opening and closing valve 4 and the second opening and closing valve 8 are controlled by the operation system of the aircraft 1 and get to an open state, a communication path 9 for communicating the intake ports 3 and the ejection holes 7 to each other are provided between the intake ports 3 and the ejection holes 7.

    【課題】 主翼上面部に剥離が発生しやすい航空機の離着陸時においても、主翼上面部に開口する取込み口と推進機関における吸気側内周面に開口する放出孔間が連通路によって連通されているので、境界層剥離を抑制して航空機の安定飛行に大きく寄与する。【解決手段】 航空機1の主翼上面部2に前記主翼上面部2の空気を取込む取込み口3を単数箇所又は複数箇所開口させて設け前記取込み口3に前記航空機1の操縦系統に制御され前記取込み口3を開閉する第一開閉弁4を備え、前記航空機1の推進機関5における吸気側内周面6に前記取込み口3が取り込んだ空気を放出する放出孔7を単数箇所又は複数箇所開口させて設け前記放出孔7に前記航空機1の操縦系統に制御され前記放出孔7を開閉する第二開閉弁8を備え、前記第一開閉弁4及び前記第二開閉弁8が前記航空機1の操縦系統に制御されて開状態となったときに前記取込み口3と前記放出孔7間を連通させる連通路9を前記取込み口3と前記放出孔7間に設けている。【選択図】図1


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    Titel :

    BOUNDARY LAYER CONTROL DEVICE OF AIRCRAFT


    Weitere Titelangaben:

    航空機の境界層制御装置


    Beteiligte:
    INOUE FUJIO (Autor:in)

    Erscheinungsdatum :

    2016-01-18


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Japanisch


    Klassifikation :

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



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