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    기술보고서 게시판 내용
    타이틀 Yawing Mode Flutter of Non-Planar Wing
    저자 Atsushi Kanda
    Keyword Flutter; Reentry Space Vehicle; Yawing Mode; Wind Tunnel Test; Doublet-Point Method
    URL http://send.nal.go.jp/send/jpn/dlpdf.php3/naltr0001451.pdf?id=NALTR0001451
    보고서번호 NAL TR-1451
    발행년도 2002.10
    출처 NAL (National Aerospace Laboratory of Japan)
    ABSTRACT If a winged reentry space vehicle with non-planar wings such as a tip-fin is attached atop a launch rocket, lateral mode oscillation due to an attachment between the vehicle and the rocket and/or the rocket itself may have an effect on the flutter characteristics of the wings. A particular supporting system was developed for wind tunnel tests, which had a yawing elasticity as a lateral mode. Flutter experiments were conducted in NAL-TWT. Flutter characteristics were also computed by with the doublet-point method (DPM). Numerical results are consistent with experimental results.

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