Title:
BOUNDARY LAYER CONTROL DEVICE OF AIRCRAFT
Document Type and Number:
Japanese Patent JP2016008040
Kind Code:
A
Abstract:
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.
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Inventors:
INOUE FUJIO
Application Number:
JP2014141789A
Publication Date:
January 18, 2016
Filing Date:
June 23, 2014
Export Citation:
Assignee:
INOUE FUJIO
International Classes:
B64C21/08; B64D33/02
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