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Manufacture-structure-performance re...

Claus, Steven John.

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Manufacture-structure-performance relationships for filament-wound composite shells.

Record Type:	Electronic resources : Monograph/item
Title/Author:	Manufacture-structure-performance relationships for filament-wound composite shells./
Author:	Claus, Steven John.
Published:	Ann Arbor : ProQuest Dissertations & Theses, : 1994,
Description:	230 p.
Notes:	Source: Dissertations Abstracts International, Volume: 76-02, Section: B.
Contained By:	Dissertations Abstracts International76-02B.
Subject:	Materials science. -
Online resource:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=9428079
ISBN:	9798641036991

Manufacture-structure-performance relationships for filament-wound composite shells.
Claus, Steven John.

Manufacture-structure-performance relationships for filament-wound composite shells. - Ann Arbor : ProQuest Dissertations & Theses, 1994 - 230 p.

Source: Dissertations Abstracts International, Volume: 76-02, Section: B.

Thesis (Ph.D.)--The Pennsylvania State University, 1994.

This item must not be added to any third party search indexes.

The compressive performance of filament-wound cylinders is lower than comparable shells fabricated from unidirectional tape. The objective of this study was to determine the cause of this reduction in thin filament-wound cylinders by relating the manufacturing procedures to the quality and compressive performance of the cylinder. Various manufacturing procedures were examined to determine the technique which produced the best microstructural and surface quality. This technique involved winding at an elevated temperature and then curing the cylinder with the use of shrink tape. Seven different experiments were designed to determine the effects of crossover-band spacing, scale, winding sequence, mandrel material, symmetry of the laminated-shell regions, through-the-thickness crossover-band location, and winding temperature on the compressive response. To account for the sensitivity of the buckling load to initial imperfections, each specimen was examined to quantify the imperfection level. Thickness imperfections were caused by twisting and misalignments of the tow during winding. Geometric imperfections were measured after the end fixtures were attached to the specimens prior to compression testing. Most imperfections of this type are caused by thermal residual stresses. Single-layer specimens with radius-to-thickness ratios of 160 and 60 buckled in a diamond-shaped mode and exhibited significant postbuckling strength. Multi-layer cylinders with radius-to-thickness ratios of 60 fractured immediately after buckling with no postbuckling strength. Specimens with radius-to-thickness ratios of 18 failed in compression. Fiber undulations in the helical and circumferential-crossover bands reduce the buckling load most when the shape of the winding pattern and the buckling mode are similar. Improvements in performance were observed when cylinders were wound at an elevated temperature and with crossover-bands staggered through the thickness. Flugge's and Donnell's theories were used to compute the critical buckling loads of laminated, geometrically-perfect cylinders with clamped ends. Load reductions between the analyses and experiment of 10 to 60 percent were observed due to the presence of material and geometric imperfections and non-membrane prebuckling effects. The Tsai-Wu failure criterion was able to correctly identify the failure mode.

ISBN: 9798641036991Subjects--Topical Terms:

543314
Materials science.

Manufacture-structure-performance relationships for filament-wound composite shells.
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100 1 $a Claus, Steven John. $3 3544981
245 1 0 $a Manufacture-structure-performance relationships for filament-wound composite shells.
260 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 1994
300 $a 230 p.
500 $a Source: Dissertations Abstracts International, Volume: 76-02, Section: B.
500 $a Publisher info.: Dissertation/Thesis.
500 $a Advisor: Hahn, H. Thomas.
502 $a Thesis (Ph.D.)--The Pennsylvania State University, 1994.
506 $a This item must not be added to any third party search indexes.
506 $a This item must not be sold to any third party vendors.
520 $a The compressive performance of filament-wound cylinders is lower than comparable shells fabricated from unidirectional tape. The objective of this study was to determine the cause of this reduction in thin filament-wound cylinders by relating the manufacturing procedures to the quality and compressive performance of the cylinder. Various manufacturing procedures were examined to determine the technique which produced the best microstructural and surface quality. This technique involved winding at an elevated temperature and then curing the cylinder with the use of shrink tape. Seven different experiments were designed to determine the effects of crossover-band spacing, scale, winding sequence, mandrel material, symmetry of the laminated-shell regions, through-the-thickness crossover-band location, and winding temperature on the compressive response. To account for the sensitivity of the buckling load to initial imperfections, each specimen was examined to quantify the imperfection level. Thickness imperfections were caused by twisting and misalignments of the tow during winding. Geometric imperfections were measured after the end fixtures were attached to the specimens prior to compression testing. Most imperfections of this type are caused by thermal residual stresses. Single-layer specimens with radius-to-thickness ratios of 160 and 60 buckled in a diamond-shaped mode and exhibited significant postbuckling strength. Multi-layer cylinders with radius-to-thickness ratios of 60 fractured immediately after buckling with no postbuckling strength. Specimens with radius-to-thickness ratios of 18 failed in compression. Fiber undulations in the helical and circumferential-crossover bands reduce the buckling load most when the shape of the winding pattern and the buckling mode are similar. Improvements in performance were observed when cylinders were wound at an elevated temperature and with crossover-bands staggered through the thickness. Flugge's and Donnell's theories were used to compute the critical buckling loads of laminated, geometrically-perfect cylinders with clamped ends. Load reductions between the analyses and experiment of 10 to 60 percent were observed due to the presence of material and geometric imperfections and non-membrane prebuckling effects. The Tsai-Wu failure criterion was able to correctly identify the failure mode.
590 $a School code: 0176.
650 4 $a Materials science. $3 543314
650 4 $a Aerospace materials. $3 3433227
650 4 $a Mechanics. $3 525881
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710 2 $a The Pennsylvania State University. $3 699896
773 0 $t Dissertations Abstracts International $g 76-02B.
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791 $a Ph.D.
792 $a 1994
793 $a English
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=9428079