Abolghassem Zabihollah, PEng, PhD Candidate

EVS2-101,

1455 de Maisonneuve Blvd. W.
Montreal, Quebec H3G 1M8 Canada

Tel: (514) 8482424 Ext.7056

E-mail:

Educations

PH.D. Mechanical Engineering 2003-todate

ConcordiaUniversity, Montreal, Canada

M.A.S. Mechanical Engineering, 2000-2003

ConcordiaUniversity, Montreal, Canada

B.S. Mechanical Engineering 1984-1989

Sharif University of Technology, Tehran, Iran

Publications

Ganesan, R. and Zabihollah, A., 2004, “Higher-order Finite Element Formulation for Dynamic Analysis of Laminated Composite Beams,” Proceeding of American Society for Composites 19th Annual Technical Conference, Atlanta, Georgia, October, 2004.

Ganesan, R. and Zabihollah, A., 2005, “Vibration Analysis of Tapered Composite Beams using a Higher-order Finite Element; Part I: Formulation”, Composite Structures,In press.

Ganesan, R. and Zabihollah, A., 2005, “Vibration Analysis of Tapered Composite Beams using a Higher-order Finite Element; Part I: Parametric Study”, Composite Structures, In press.

Ganesan, R. and Zabihollah, A., 2005, “Parametric Study of the Dynamic Response of Composite Beams with Uniform-Thickness and Tapered Laminates”,Proceeding of International Conference on Advances in Structural Dynamics and Its Applications Conference, Visakhapatnam,India, December 2005.

Ahari M., Zabihollah A. and Sedaghati R., 2005, “Optimal Design of ShapeControl of Smart Laminated Beams with Embedded Piezoelectric Sensors and Actuators”, Proceeding of 6th world congress on structural and multidisciplinary optimization, Rio de Janeiro, Brazil, 30 may-3 June 2005.

Zabihollah, A., Sedaghati, R. Ganesan, R., 2005,“Optimal Design Of Smart Laminated Beams Using Layerwise Theory”,Proceeding of 8th Cansmart Meeting International Workshop on Smart Materials and Structures, October 13-14, 2005, Toronto, Ontario, Canada.

Zabihollah, A.andGanesan, R., 2006, “Buckling Analysis of Tapered Composite Beams using a Higher-order Finite Element Formulation”, Journal of Reinforced Plastic, In press.

Zabihollah, A. Sedaghati, R., Ganesan, R., 2006, “Design Optimization of Smart LaminatedComposite Beams using Layerwise Theory”, Proceeding of III European Conference on Computational MechanicsSolids, Structures and Coupled Problems in EngineeringC.A. Mota Soares et.al. (eds.) Lisbon, Portugal, 5–8 June 2006.

Sedaghati, R., Zabihollah, A., Ahari, M., Esmailzadeh,E., 2006, “Sensitivity Analysis and Optimum Design of Adaptive Piezo-laminated Composite Beam” Proceeding of 14th Annual (International) Mechanical Engineering Conference – May 2006, Isfahan University of Technology, Isfahan, Iran.

Sedaghati, R., Zabihollah, A. and Ahari, M.2006, “Sensitivity Analysis and Design Optimization of Smart Laminated Composite Beam with Integrated Piezoelectric Actuators Using Single-layer Theories”, AIAA Journal, In Press.

Zabihollah, A., “Vibration Suppression and Design Optimization of Laminated Smart Composite Structures”, Lecture in Research Day, 31 March 2006, Concordia University, Montreal, Canada.

Zabihollah, A., “Sensitivity analysis and design optimization of smart laminated beams using layerwise theory”, Presentation in CREPEC, 2006, Montreal, Canada.

Zabihollah, A., Sedaghati, R., Ganesan, R., “SensitivityAnalysis andOptimization of Smart Laminated Beamsby Layerwise Theory”, The Eighth International Conference on Computational Structures Technology Las Palmas de Gran Canaria, Spain, 12-15 September 2006.

Research activities:

PhD: Vibration suppression and design optimization of smart laminated structures under random loading.

Abstract

This is the aim of this research to conduct a complete and comprehensive investigation on design optimization of smart laminated composites and their response to random loading. A finite element model based on layerwsie theory will be developed for vibration analysis of laminated composite beams with embedded and bounded piezoelectric sensors and actuators. The study will include the responses of laminated smart structures under random loading as well as the design optimization of smart structures with capability to control the shape and to suppress vibrations under random loading.

M.A.Sc:Vibration analysis of tapered composite beams using conventional and Higher-order finite element formulation

Abstract

Tapered composite beams are being used in various engineering applications such as helicopter yoke, robot arms and turbine blade in which the structure needs to be stiff at one location and flexible at other locations. Laminated tapered beams can be manufactured by terminating some plies at discrete locations. Different types of ply drop-off can be achieved depending on the application. Due to the variety of tapered composite beams and complexity of the analysis, no analytical solution is available at present and therefore finite element method has been used for the calculation of response. In the present thesis, the free vibration response and buckling of different types of tapered composite beams are analyzed first using conventional finite element formulation. Conventional finite element formulation requires large number of elements to obtain acceptable results. In addition, continuity of curvature at element interfaces can not be guaranteed with the use of conventional formulation. As a result, stress distribution across the thickness is not continuous at element interfaces. In order to overcome these limitations, an advanced finite element formulation is developed in the present thesis for vibration and buckling analysis of tapered composite beams based on classical laminate theory and first-order shear deformation theory. The developed formulation is applied to the analysis of various types of tapered composite beams. The efficiency and accuracy of the developed formulation are established in comparison with available solutions, where applicable, as well as with the results obtained using conventional formulation. A detailed parametric study has been conducted on various types of tapered composite beams, all made of NCT / 301 graphite-epoxy, in order to investigate the effects of boundary conditions, laminate configuration, taper angle, the ratio of the length of the thick section to the length of the thin section and the ratio of the height of the thick section, to the height of thin section.