日本航空宇宙学会論文集
Online ISSN : 2432-3691
Print ISSN : 1344-6460
ISSN-L : 1344-6460
論文
加減速環境下における超音速軸対称型インテークの制御に関する実験的研究
小島 孝之佐藤 哲也棚次 亘弘榎本 吉也
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ジャーナル フリー

2003 年 51 巻 596 号 p. 459-468

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A control system of variable geometry mixed compression axisymmetric intake is experimentally studied at ONERA S3 supersonic wind tunnel. The acceleration/deceleration of the space plane is simulated by changing the free stream velocity. The intake is successfully controlled with 90% of the maximum total pressure recovery and mass capture ratio. In this experiment, two subjects about control of axisymmetric intake are also cleared. First, the effect of the trapping of the terminal shock by bleed holes causes the disturbances in the terminal shock control system. Second, a special compression form change operation is necessary when the intake compression form change from all external compression to mixed compression.

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© 2003 The Japan Society for Aeronautical and Space Sciences
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