Second Airframe Division, National Aerospace Laboratory(NAL)
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
航空宇宙技術研究所報告
雑誌名(英)
Technical Report of National Aerospace Laboratory TR-401
巻
401
ページ
15
発行年
1975-01
抄録（英）
The response formulae to calculate r.m.s. displacement of both a rectangular panel and a beam with clamped boundaries have been derived by model analysis.The quantitative estimations of r.m.s. displacement can be done with the knowledge of physical constants of the boundary layer and those of a beam or a plate. Numerical examples have clarified how the dynamic r.m.s. values of displacement are influenced by the edge conditions. In order to make clear the effect of clamping the boundaries dynamic r.m.s. value of a clamped plate or a beam and static deflection of a clamped plate or a beam are to be expressed in terms of percentage share over dynamic r.m.s. displacement of a supported plate or a beam and static deflection of a supported plate or a beam respectively. The results for dynamic r.m.s. displacement ratio and static deflection ratio take 30％, 20％ on the beam problem and 67％, 31％ on the plate problem respectively. The discrepancy between those figures means physically that: 1) On the whole considerable reduction the response level is attained by constraining the edges. 2) But precisely speaking clamping the edges is less effective to the dynamic loading than to the static loading. 3) And it is less effective in the plate problem than in the beam problem for both dynamic and static loading.
境界層内圧力変動による板の振動解析(Ⅱ)-周辺固定板、両端固定梁-
naltr00401.pdf
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