Adhesive-bonded composite joint analysis with delaminated surface ply using strain-energy release rate

dc.contributor.author	Chadegani, Alireza
dc.contributor.author	Yang, Chihdar
dc.contributor.author	Smeltzer, Stanley S., III
dc.date.accessioned	2012-05-11T16:37:12Z
dc.date.available	2012-05-11T16:37:12Z
dc.date.issued	2012-03
dc.identifier.citation	Chadegani A., Yang C., and Smeltzer S.S. 2012. "Adhesive-bonded composite joint analysis with delaminated surface ply using strain-energy release rate". Journal of Aircraft. 49 (2): 503-520.	en_US
dc.identifier.issn	0021-8669
dc.identifier.other	WOS: 000302758400016
dc.identifier.uri	http://hdl.handle.net/10057/5100
dc.identifier.uri	http://dx.doi.org/10.2514/1.C031516
dc.description	Click on the DOI link below to access the article (may not be free).	en_US
dc.description.abstract	This paper presents an analytical model to determine the strain energy release rate due to an interlaminar crack of the surface ply in adhesively bonded composite joints subjected to axial tension. Single-lap shear-joint standard test-specimen geometry with thick bondline is followed for model development. The field equations are formulated by using the first-order shear-deformation theory in laminated plates together with kinematics relations and force equilibrium conditions. The stress distributions for the adherends and adhesive are determined after the appropriate boundary and loading conditions are applied and the equations for the field displacements are solved. The system Of second-order differential equations is solved to using the symbolic computation tool Maple 9.52 to provide displacements fields. The equivalent forces at the tip of the prescribed interlaminar crack are obtained based on interlaminar stress distributions. The strain energy release rate of the crac! k is then determined by using the crack closure method. Finite element analyses using the J integral as well as the crack closure method are performed to verify the developed analytical model. It has been shown that the results using the analytical method correlate well with the results from the finite element analyses. An attempt is made to predict the failure loads of the joints based on limited test data from the literature. The effectiveness of the inclusion of bondline thickness is justified when compared with the results obtained from the previous model in which a thin bondline and uniform adhesive stresses through the bondline thickness are assumed.	en_US
dc.language.iso	en_US	en_US
dc.publisher	AMER INST AERONAUT ASTRONAUT	en_US
dc.relation.ispartofseries	Journal of Aircraft;2012, v.49, no.2
dc.subject.classification	ENGINEERING
dc.subject.classification	AEROSPACE
dc.title	Adhesive-bonded composite joint analysis with delaminated surface ply using strain-energy release rate	en_US
dc.type	Article	en_US
dc.description.version	Peer reviewed