Postbuckling Behavior of Orthotropic Skew Plates
01 May 1973-AIAA Journal (American Institute of Aeronautics and Astronautics Inc. (AIAA))-Vol. 11, Iss: 5, pp 731-733
About: This article is published in AIAA Journal.The article was published on 1973-05-01. It has received 4 citations till now. The article focuses on the topics: Skew & Orthotropic material.
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TL;DR: In this paper, a survey of the general area of buckling and postbuckling of thin-walled, geometrically imperfect, cylinders of various constructions, when subjected to destabilizing loads is presented.
Abstract: Thin-walled cylinders of various constructions are widely used in simple or complex structural configurations. The round cylinder is commonly found in tubing and piping, and in offshore platforms. Depending on their use, these cylinders are subjected (in service) to individual and combined application of external loads. In resisting these loads the system is subject to buckling, a failure mode which is closely associated with the establishment of its load-carrying capacity. Therefore, the system buckling and postbuckling behavior have been the subject of many researchers and investigators both analytical and experimental. The paper is a state-of-the-art survey of the general area of buckling and postbuckling of thin-walled, geometrically imperfect, cylinders of various constructions, when subjected to destabilizing loads. The survey includes discussion of imperfection sensitivity and of the effect of various defects on the critical conditions.
158 citations
TL;DR: In this paper, the postbuckling behavior of a simply supported rectangular thick plate subjected to arbitrary loading conditions is investigated and the applied stress is taken to be a combination of a pure bending stress plus an extensional stress in the plane of the plate.
Abstract: The postbuckling behavior of a simply supported rectangular thick plate subjected to arbitrary loading conditions is investigated. The applied stress is taken to be a combination of a pure bending stress plus an extensional stress in the plane of the plate. Governing equations based on von Karman assumptions are used to solve the postbuckling problem by the Galerkin method. Buckling loads are obtained to compare with the results of Brunelle and Robertson. Postbuckled deflection is shown to increase with the transverse isotropic coefficient 5, and the effects of the in-plane bending stress are found to be quite significant for a thick plate.
19 citations
TL;DR: In this paper, the dynamic von Karman-type equations for large amplitude flexural vibration of an elastic anisotropic skew plate are formulated on the basis of assumed vibration modes of the product form.
5 citations
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References
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TL;DR: In this article, a multi component diffusion coefficient and thermal conductivity of a mixture of species was investigated, where the number of components in the mixture was determined by the multi component Lewis-Semenov number of the mixture.
Abstract: multi component diffusion coefficient, ft/sec binary diffusion coefficient, ft/sec thermal diffusion coefficient, Ib sec/ft enthalpy, z^ h^Ci, ft/sec i enthalpy of species i, ft/sec thermal conductivity of mixture, lb/(sec° R) density-viscosity product, piJL/(pn)r multi component Lewis-Semenov number, Cpp binary Lewis-Semenov number Cpp^a/k thermal Lewis-Semenov number, cpDi/k molecular weight of the mixture, 1 / ( Z-j Ci/
393 citations
01 Jan 1962
TL;DR: In this paper, the inner and outer expansions were used to obtain uniformly valid solutions far downstream from the nose of a slightly blunted body in hypersonic flow, where the influence of nose bluntness on the flow field and body shape was found to be significant due to the formation of a layer of low density, high entropy air enveloping the body.
Abstract: The method of "inner and outer expansions" is used in obtaining uniformly valid solutions far downstream from the nose of a slightly blunted body in hypersonic flow. This technique is applied to the inverse problem, which prescribes the shock wave, leaving the body to be determined. The influence of nose (shock) bluntness on the flow field and body shape is found to be significant due to the formation of a layer of low density, high entropy air enveloping the body. This entropy layer is in many respects analogous to Prandtl's viscous boundary layer. Analytical solutions, which assume an inviscid perfect gas and infinite Mach number, are obtained for hyperbolic and power law shock wave shapes. The hyperbolic shocks correspond to flows past blunted wedges and cones in two and three dimensions, respectively. The second-order results for these two cases yield a displacement thickness due to the entropy layer. The blunt body that produces a paraboloidal shock is found to grow as a power of the distance and the resulting outer flow field is asymptotically represented far downstream by the solution for the analogous constant-energy explosion. Similar results have been obtained for the two -dimensional case of the η = 2/3 power-law shock. INTRODUCTION The aeronautical sciences, in playing a leading role in the exploration of Earth's atmosphere and of space, have been duly concerned with the problem of re-entry aerodynamics and of Presented at ARS International Hypersonics Conference, August 16-18, 1961, Cambridge, Massachusetts; the research reported in this paper was sponsored by the Air Force Office of Scientific Research under Contract no. AF 49(638)-965 as AFOSR TN-61-1271. hughes Staff Doctoral Fellow.
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TL;DR: In this paper, a simple interaction analysis based on the Prandtl boundary-layer equations and the equations of an inviscid noncentered simple wave was proposed to calculate the major features of the interaction between a laminar boundary layer and a supersonic corner expansion wave.
Abstract: There are three distinct effects involved in the interaction of a laminar boundary layer and a supersonic corner expansion wave. These are: the upstream influence effect causing some pressure decay ahead of the corner, transverse pressure gradients in the immediate neighborhood of the corner, and the interaction of the boundary layer downstream with the external flow. Arguments are presented to suggest that, when the flow is locally hypersonic and the wall is highly cooled, the dominant effect is the downstream interaction process. Hence the major features can be calculated by using a simple interaction analysis down stream of the corner based on the Prandtl boundary-layer equations and the equations of an inviscid noncentered simple wave. Numerical results are obtained by using the "cold wall" similarity solution to the boundary-layer equations. These show that pressure decay extends over a region which can be many times larger than the original plate length used to generate the boundary layer.
15 citations
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