The present study involves the analysis and design optimization of thin and thick laminated composite structures using symbolic computation. The fibre angle and wall thickness of balanced and unbalanced thin composite pressure vessels are optimized subject to a strength criterion in order to maximise internal pressure or minimise weight, and the effects of axial and torsional forces on the optimum design are investigated. Special purpose symbolic computation routines are developed in the C programming language for the transformation of coordinate axes, failure analysis and the calculation of design sensitivities. In the study of thin-walled laminated structures, the analytical expression for the thickness of a laminate under in-plane loading and its sensitivity with respect to the fibre orientation are determined in terms of the fibre orientation using symbolic computation. In the design optimization of thin composite pressure vessels, the computational efficiency of the optimization algorithm is improved via symbolic computation. A new higher-order theory which includes the effects of transverse shear and normal deformation is developed for the analysis of laminated composite plates and shells with transversely isotropic layers. The Mathematica symbolic computation package is employed for obtaining analytical and numerical results on the basis of the higher-order theory. It is observed that these numerical results are in excellent agreement with exact three-dimensional elasticity solutions. The computational efficiency of optimization algorithms is important and therefore special purpose symbolic computation routines are developed in the C programming language for the design optimization of thick laminated structures based on the higher-order theory. Three optimal design problems for thick laminated sandwich plates are considered, namely, the minimum weight, minimum deflection and minimum stress design. In the minimum weight problem, the core thickness and the fibre content of the surface layers are optimally determined by using equations of micromechanics to express the elastic constants. In the minimum deflection problem, the thicknesses of the surface layers are chosen as the design variables. In the minimum stress problem, the relative thicknesses of the layers are computed such that the maximum normal stress will be minimized. It is shown that this design analysis cannot be performed using a classical or shear-deformable theory for the thick panels under consideration due to the substantial effect of normal deformation on the design variables. / Thesis (Ph.D.)-University of Natal, Durban, 1994.

The purpose of this research is to make an investigation into the crashworthiness modelling of Sheet Moulding Compound (SMC) composite materials, and to study the response of SMC composite structures under dynamic loading. The primary research objectives are thus to review classical and advanced material failure models, and to perform numerical simulation of the crash of composite structures using already available material models. Additionally, a new material model is to be developed for implementation into a commercially available finite element package. In parallel with the numerical simulation of the crasrung of an SMC composite structure, experimentation is performed which is used as a source of validation and comparison with the simulation. For this purpose a testing regime is introduced, which may be mirrored in simulation. As any material model requires initial experimental inputs, the purpose of experimentation is twofold, with testing required both for the quantification of the required model inputs and the basic material characterisation before simulation may begin, as well as for the proposed validation and comparison after the simulation has been carried out. Thus the design of the testing methodology, as well as the design, selection and fabrication of the testing equipment and the composite specimens and demonstrators, as well the actual testing itself, are necessary secondary requirements of the project. Once the testing regime has been facilitated and carried out, numerical simulation validation using already available composite material models may then be carried out at various levels. The results are then analysed and validated with the resultant justification of a new model being developed. The critical viewpoint to be delivered throughout is the need for theoretical formulations for material modelling to be extensively researched and validated in terms of their implementabilty and practicality, a key analysis seemingly missing in most technical write-ups. Such analyses are performed and discussed here, rughlighting the volume of additional work that is encompassed by such a study. / Thesis (M.Sc.Eng.)-University of Natal, Durban, 2003.

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Joints provide a path for transfer of load and are important components in an assembly of structures, particularly in translating joint strength improvements directly to significant cost savings. This cost savings is more evident in composite joints since manufacturing of more complex single piece components results in a reduction of both part count and labor. An improvement in joint strength for co-cured composite joints through minimized free-edge delamination was investigated for quasi-isotropic [0/±45/90]s lay-up based on the quantitative assessments of the quasi-static and fatigue strength and qualitative understanding of the fatigue damage initiation and propagation for the [0/±θ/90]s family of co-cured composite joints. A previously proposed co-cured joint concept, the Single Nested Overlap (SNO) joint, was compared against a Straight Laminate (SL) and a single lap joint. The SL represents a "perfect" joint and serves as an upper bound whereas the single lap joint represents the simplest generic joint and is the base design for the SNO joint concept. Three categorized failure types, which represented predominant failure modes in the SL, single lap and SNO joints, along with two different fatigue strength indicators were used for quasi-static and fatigue strength comparison. With fatigue run-out defined at 1 x 106 cycles, the fatigue damage initiation and propagation at high loadings was monitored with an Infrared Thermoelastic Stress Analysis (IR-TSA) technique, while a damage type comparison was used at low loadings. Quasi-static Acoustic Emission (AE) counts were observed to be Fatigue Limit (FL) predictors for [0/±θ/90]s SL and SNO joints. The validity of these FL predictors were also assessed in the damage type comparison.

Thesis (M.App.Sc.) - Carleton University, 2002. / Includes bibliographical references (p. 140-152). Also available in electronic format on the Internet.

Thesis (Ph. D.)--University of Canterbury, 2008. / Typescript (photocopy). Includes bibliographical references. Also available via the World Wide Web.

Thesis (M.Eng.(Metallurgical Engineering))--University of Pretoria, 1999. / Summaries in Afrikaans and English. Includes bibliographical references.

Thesis (M.S.)--Michigan State University. Dept. of Mechanical Engineering, 2008. / Title from PDF t.p. (viewed on July 29, 2009) Includes bibliographical references (p. 108-110). Also issued in print.

Thesis (Ph.D.)--Civil and Environmental Engineering, Georgia Institute of Technology, 2008. / Committee Chair: Rami Haj-Ali; Committee Member: Arash Yavari; Committee Member: Bruce R. Ellingwood; Committee Member: Kenneth M. Will; Committee Member: Richard W. Neu.

Thesis (M.E.)--University of Canterbury, 2006. / Typescript (photocopy). "31st May 2006." Includes bibliographical references (leaves 126-133). Also available via the World Wide Web.