• Title/Summary/Keyword: taper 매개 변수

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Natural Frequencies of Simply Supported Tapered Beams (단순지지된 변단면 보의 고유진동수)

  • 김준희;김순철;이수곤
    • Journal of KSNVE
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    • v.9 no.3
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    • pp.607-612
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    • 1999
  • Natural frequencies of non-symmetrically tapered beams with simply supported ends were determined by solving the frequency equations. In the case of symmetrically tapered beams. the finite element method was adopted for frequency computation. Computed frequencies of tapered beams were expressed as functions of taper ratio. a. and sectional properties. ( m, n).

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Determination of Eigenvalues of Sinusoidally Tapered Members by Finite Element Method (유한요소법을 이용한 정현상으로 taper진 부재의 고유치 산정)

  • Lee, Soo-Gon;Kim, Soon-Chul
    • Journal of the Computational Structural Engineering Institute of Korea
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    • v.13 no.1
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    • pp.87-95
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    • 2000
  • The two eigenvalues (elastic critical load and natural frequency of lateral vibration) of sinusoidally tapered bats with simply supported ends were determined by the finite element method. For the convenience of structural engineers who are engaged in the structural design or vibration analysis of tapered beam-columns, eigenvalue coefficients were expressed by simple algebraic equations. The validity of each algebraic equation was confirmed by the value of unity for each correlation coefficient. The influence of axial thrust on the lateral vibration frequency was also investigated. For this purpose, the axial thrust was increased successively and the corresponding frequency was calculated. The approximate linear relationship between the axial thrust and the square of the frequency was confirmed lot each of the tapered members.

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Aerodynamic Characteristics of a Three-Dimensional Wing in Heave Oscillation (히브진동하는 3차원 날개 공력특성)

  • Chin, Chul-Soo;Kim, Tae-Wan;Lee, Hyoung-Wook;Han, Cheol-Heui
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.39 no.10
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    • pp.905-911
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    • 2011
  • With the progress of micro actuator technology, studies on the development of micro air flapping wing vehicles are actively undergoing. In the present study, the changes of both lift and thrust characteristics of the wings are investigated using a boundary element method. Lift of the heaving wing is not generated when the wing is beating with smaller frequencies than 1 Hz. Thrust increases with amplitude and frequency. As the wing's taper and aspect ratios increase, both lift and thrust also increase. Results on the pitching oscillation and flapping motion will be included in the future work.