Bending of Elastically Restrained Rectangular Plates Under Uniform Pressure

IF 1.4 4区 工程技术 Q2 ENGINEERING, AEROSPACE
C. Lakshmi Kantham
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引用次数: 1

Abstract

In the bending and vibration of plates it is found that the values of maximum deflection and natural frequencies, respectively, vary considerably from the simply-supported to clamped edge conditions. For an estimation of these characteristics in the intermediate range a generalised boundary condition may be assumed, of which the simply-supported and clamped edges become limiting cases. While Bassali considers the ratio of edge moment to the cross-wise moment as a constant, Newmark, Lurie and Klein and other investigators, in their analyses of various structures, consider that moment and slope at an end are proportional. Here the definition of elastic restraint as given by Timoshenko, α=βM, is followed, where α is the slope at any edge, M the corresponding edge moment per unit length while β is the elastic restraint factor. β→0 and β→∞ represent the two limiting cases of simply-supported and clamped edge conditions.
均匀压力下弹性约束矩形板的弯曲
在板的弯曲和振动中,发现最大挠度值和固有频率值分别在简支和夹紧边缘条件下变化很大。为了在中间范围内估计这些特性,可以假设一个广义的边界条件,其中简支边和夹紧边成为极限情况。Bassali认为边缘弯矩与横向弯矩之比是一个常数,而Newmark、Lurie和Klein以及其他研究人员在对各种结构的分析中,认为弯矩和一端的斜率是成正比的。这里采用Timoshenko给出的弹性约束定义α=βM,其中α为任意边处的斜率,M为单位长度对应的边矩,β为弹性约束因子。β→0和β→∞分别表示简支边条件和夹紧边条件的两种极限情况。
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来源期刊
Aeronautical Journal
Aeronautical Journal 工程技术-工程:宇航
CiteScore
3.70
自引率
14.30%
发文量
86
审稿时长
6-12 weeks
期刊介绍: The Aeronautical Journal contains original papers on all aspects of research, design and development, construction and operation of aircraft and space vehicles. Papers are therefore solicited on all aspects of research, design and development, construction and operation of aircraft and space vehicles. Papers are also welcomed which review, comprehensively, the results of recent research developments in any of the above topics.
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