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Failure mode interaction in fiber re...

Prabhakar, Pavana.

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Failure mode interaction in fiber reinforced laminated composites.

Record Type:	Electronic resources : Monograph/item
Title/Author:	Failure mode interaction in fiber reinforced laminated composites./
Author:	Prabhakar, Pavana.
Description:	162 p.
Notes:	Source: Dissertation Abstracts International, Volume: 74-10(E), Section: B.
Contained By:	Dissertation Abstracts International74-10B(E).
Subject:	Aerospace engineering. -
Online resource:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=3566213
ISBN:	9781303171352

Failure mode interaction in fiber reinforced laminated composites.
Prabhakar, Pavana.

Failure mode interaction in fiber reinforced laminated composites. - 162 p.

Source: Dissertation Abstracts International, Volume: 74-10(E), Section: B.

Thesis (Ph.D.)--University of Michigan, 2013.

A novel computational modeling framework to predict the compressive strength of fiber reinforced polymer matrix composite (FRPC) laminates has been presented. The model development has been motivated by a set of experimental results on the compression response of two different FRPCs. The model accounts for failure mode interaction between kink-banding and interface fracture (or delamination), which are observed in the experimental results. To reduce the size of the computational model, those interfaces that are most susceptible to delamination are first determined through a free-edge stress analysis. Furthermore, 0-axis layers, which are passive in the failure process are represented through an equivalent homogenized model, but the microstructural features of the on-axis layers (zero plies) are retained in the computational model. The predictions of the model matched well with the experimental observations, and they were found to accurately account for failure mechanism interactions. Therefore, this model has the potential to replace the need to carry out large numbers of tests to obtain the compressive strength allowable for FRPC laminates, the latter allowable being an essential element in the design of lightweight FRPC aerostructures.

ISBN: 9781303171352Subjects--Topical Terms:

1002622
Aerospace engineering.

Failure mode interaction in fiber reinforced laminated composites.
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100 1 $a Prabhakar, Pavana. $3 3184889
245 1 0 $a Failure mode interaction in fiber reinforced laminated composites.
300 $a 162 p.
500 $a Source: Dissertation Abstracts International, Volume: 74-10(E), Section: B.
500 $a Adviser: Anthony M. Waas.
502 $a Thesis (Ph.D.)--University of Michigan, 2013.
520 $a A novel computational modeling framework to predict the compressive strength of fiber reinforced polymer matrix composite (FRPC) laminates has been presented. The model development has been motivated by a set of experimental results on the compression response of two different FRPCs. The model accounts for failure mode interaction between kink-banding and interface fracture (or delamination), which are observed in the experimental results. To reduce the size of the computational model, those interfaces that are most susceptible to delamination are first determined through a free-edge stress analysis. Furthermore, 0-axis layers, which are passive in the failure process are represented through an equivalent homogenized model, but the microstructural features of the on-axis layers (zero plies) are retained in the computational model. The predictions of the model matched well with the experimental observations, and they were found to accurately account for failure mechanism interactions. Therefore, this model has the potential to replace the need to carry out large numbers of tests to obtain the compressive strength allowable for FRPC laminates, the latter allowable being an essential element in the design of lightweight FRPC aerostructures.
520 $a Furthermore, the thesis presents a new computational model to predict fiber/matrix splitting failure, a failure mode that is frequently observed in in-plane tensile failure of FRPC's. By considering a single lamina, this failure mechanism was seamlessly modeled through the development of a continuum-decohesive nite element (CDFE). The CDFE was motivated by the variational multiscale cohesive method (VMCM) presented earlier by Rudraraju et al. (2010) at the University of Michigan. In the CDFE, the transition from a continuum to a non-continuum is modeled directly (physically) without resorting to enrichment of the shape functions of the element. Thus, the CDFE is a natural merger between cohesive elements and continuum elements. The predictions of the CDFE method were also found to be in very good agreement with corresponding experimental observations.
590 $a School code: 0127.
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Mechanics. $3 525881
650 4 $a Mechanical engineering. $3 649730
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710 2 $a University of Michigan. $b Aerospace Engineering. $3 2093897
773 0 $t Dissertation Abstracts International $g 74-10B(E).
790 $a 0127
791 $a Ph.D.
792 $a 2013
793 $a English
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=3566213