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Journal ArticleDOI

Analytical prediction of thermal stresses in composite shells

01 Feb 2020-Vol. 1474, Iss: 1, pp 012018
About: The article was published on 2020-02-01 and is currently open access. It has received 1 citations till now. The article focuses on the topics: Composite number.
Citations
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01 Jun 1985
TL;DR: In this article, the effects of a uniform temperature change on the stresses and deformations of composite tubes are investigated and the accuracy of an approximate solution based on the principle of complementary virtual work is determined.
Abstract: The effects of a uniform temperature change on the stresses and deformations of composite tubes are investigated. The accuracy of an approximate solution based on the principle of complementary virtual work is determined. Interest centers on tube response away from the ends and so a planar elasticity approach is used. For the approximate solution a piecewise linear variation of stresses with the radial coordinate is assumed. The results from the approximate solution are compared with the elasticity solution. The stress predictions agree well, particularly peak interlaminar stresses. Surprisingly, the axial deformations also agree well. This, despite the fact that the deformations predicted by the approximate solution do not satisfy the interface displacement continuity conditions required by the elasticity solution. The study shows that the axial thermal expansion coefficient of tubes with a specific number of axial and circumferential layers depends on the stacking sequence. This is in contrast to classical lamination theory which predicts the expansion to be independent of the stacking arrangement. As expected, the sign and magnitude of the peak interlaminar stresses depends on stacking sequence.

1 citations

References
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Journal ArticleDOI
TL;DR: In this paper, the authors investigated the effects of a uniform temperature change on the stresses and deformations of composite tubes and determined the accuracy of an approximate solution based on the principle of complementary virtual work.
Abstract: This study investigates the effects of a uniform temperature change on the stresses and deformations of composite tubes and determines the accuracy of an approximate solution based on the principle of complementary virtual work. Interest centers on tube response away from the ends and so a planar elasticity approach is used. For the approximate solution a piecewise linear variation of stresses with the radial coordinate is assumed. The results from the approximate solution are compared with the elasticity solution. The stress predictions agree well, particularly peak interlaminar stresses. Surprisingly, the axial deformations also agree well, despite the fact that the deformations predicted by the approximate solution do not satisfy the interface displacement continuity conditions required by the elasticity solution. The study shows that the axial thermal expansion coefficient of tubes with a specific number of axial and circumferential layers depends on the stacking sequence. This is in contrast to classical lamination theory, which predicts that the expansion will be independent of the stacking arrangement. As expected, the sign and magnitude of the peak interlaminar stresses depend on stacking sequence. For tubes with a specific number of axial and circumferential layers, thermally induced interlaminar stresses can be controlled by altering stacking arrangement.

64 citations

Journal ArticleDOI
TL;DR: In this article, the authors considered the thermal stress uncoupled problem of multilayered composite shells and derived differential governing equations for the thermal analysis of shells with constant radii of curvature.
Abstract: This paper considers the thermal stress uncoupled problem of multilayered composite shells. An assumed linear distribution of temperature through the thickness is considered for thick/thin cylindrical and spherical shells including carbon fiber reinforced layers and/or a central soft core. The Carrera's Unified Formulation (CUF) and the Principle of Virtual Displacements (PVD) are extended to derive differential governing equations for the thermal analysis of shells with constant radii of curvature. Classical and refined two-dimensional models are treated in a unified form. Both Equivalent Single Layer (ESL) and Layer-Wise (LW) approaches are considered along with variable order of expansion in the thickness direction, from linear to fourth order. In the case of ESL, the typical zig-zag form of the displacement is accounted for via the Murakami's function. Classical models have also been considered for comparison purposes. The obtained results demonstrate the effectiveness of refined models for a correct ...

51 citations

Journal ArticleDOI
TL;DR: In this paper, the authors extended the Semiloof shell finite element formulation to thermal stress analysis of laminated plates and shells and verified the accuracy of the formulation using sample problems available in the literature.

34 citations

Journal ArticleDOI
TL;DR: In this paper, an expression was developed that makes possible the prediction of Poisson's ratio for unidirectional composites with reference to any pair of orthogonal axes that are normal to the direction of the reinforcing fibers.
Abstract: An expression is developed that makes possible the prediction of Poisson's ratio for unidirectional composites with reference to any pair of orthogonal axes that are normal to the direction of the reinforcing fibers. This prediction appears to be a reasonable one in that it follows the trends of the finite element analysis and the bounding estimates, and has the correct limiting value for zero fiber content. It can only be expected to apply to composites containing stiff, circular, isotropic fibers bonded to a soft matrix material.

29 citations

Journal ArticleDOI
TL;DR: In this article, a failure analysis is performed on analytical expressions of multilayered filament wound structures (FWS) in composite cylinders for the plane-strain and closed-end condition cases, under internal pressure and uniform thermal loading.
Abstract: In this investigation, a failure analysis is performed on analytical expressions of multilayered filament wound structures (FWS) in composite cylinders for the plane-strain and closed-end condition cases, under internal pressure and uniform thermal loading. The multilayer filament wound composite pressure closed-end cylinders are oriented symmetrically and antisymmetrically. The mechanical properties of composite cylinders are investigated considering a glass-epoxy multilayered composite cylinder. The failure analysis is carried out on different orientations of the multilayered composite cylinders. The failure pressure is found to be high at increased temperatures for the plane-strain cases. It is nearly the same for the closed-end case.

26 citations