subject:(Composite Laminates Failure Mechanism Based Design)

Indian Institute of Science

1. Naik, G Narayana. Development And Design Optimization Of Laminated Composite Structures Using Failure Mechanism Based Failure Criterion.

Degree: PhD, Faculty of Enginering, 2009, Indian Institute of Science

URL: http://etd.iisc.ac.in/handle/2005/469

► In recent years, use of composites is increasing in most fields of engineering such as aerospace, automotive, civil construction, marine, prosthetics, etc., because of its… (more)

Subjects/Keywords: Structural Analysis; Laminated Composites; Composites - Design Optimization; Failure Mechanism Based Failure Criterion; Composite Laminates - Failure Mechanism Based Design; Vector Evaluated Particle Swarm Optimization; Genetic Algorithms; Composite Laminates; Composite Laminae; Composite Structures; Design Optimization; Failure Criterion; Structural Engineering

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APA (6^th Edition):

Naik, G. N. (2009). Development And Design Optimization Of Laminated Composite Structures Using Failure Mechanism Based Failure Criterion. (Doctoral Dissertation). Indian Institute of Science. Retrieved from http://etd.iisc.ac.in/handle/2005/469

Chicago Manual of Style (16^th Edition):

Naik, G Narayana. “Development And Design Optimization Of Laminated Composite Structures Using Failure Mechanism Based Failure Criterion.” 2009. Doctoral Dissertation, Indian Institute of Science. Accessed March 05, 2021. http://etd.iisc.ac.in/handle/2005/469.

MLA Handbook (7^th Edition):

Naik, G Narayana. “Development And Design Optimization Of Laminated Composite Structures Using Failure Mechanism Based Failure Criterion.” 2009. Web. 05 Mar 2021.

Vancouver:

Naik GN. Development And Design Optimization Of Laminated Composite Structures Using Failure Mechanism Based Failure Criterion. [Internet] [Doctoral dissertation]. Indian Institute of Science; 2009. [cited 2021 Mar 05]. Available from: http://etd.iisc.ac.in/handle/2005/469.

Council of Science Editors:

Naik GN. Development And Design Optimization Of Laminated Composite Structures Using Failure Mechanism Based Failure Criterion. [Doctoral Dissertation]. Indian Institute of Science; 2009. Available from: http://etd.iisc.ac.in/handle/2005/469

2. Saarela, Olli. Design System of Composite Laminates.

Degree: 2005, Helsinki University of Technology

URL: http://lib.tkk.fi/Diss/2005/isbn9512278715/

►

A design system of composite laminates has been developed. The system is capable of finding solutions to commonly faced design problems of continuous laminates. The… (more)

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A design system of composite laminates has been developed. The system is capable of finding solutions to commonly faced design problems of continuous laminates. The target laminate is defined with a design specification consisting of constraints and objectives that can be set for important design attributes of laminates. The objectives are accompanied by weighting factors that specify their importance with respect to each other. Two tools are provided for problem solving: one for laminate evaluation, the other for laminate creation. The tools are called, respectively, the laminate evaluation tool and the laminate creation tool. A design specification, a set of candidate laminates, and analysis option settings define a laminate evaluation problem. The problem is solved in two steps. Feasible laminates satisfying all constraints are first sought. The multiobjective design technique is then applied to determine how well these laminates meet the objectives. A design specification, one or several candidate plies, and analysis option settings define a laminate creation problem. The creation process is divided into two phases. Feasible plies are first sought and ranked by creating and evaluating a set of laminates representing ply performance. The design space is constrained and approximate failure analysis techniques are used to obtain a solution in decent time. As a result of the phase, the laminate with the best performance is initially identified for each feasible ply. An attempt to improve the laminate can further be made in an extended design space and with generally accepted failure analysis techniques. The thesis describes the structure of the design system and the theories used in problem solving. Two sets of laminates are evaluated against typical design specifications to demonstrate the performance of the laminate evaluation tool. The performance of the laminate creation tool is demonstrated by solving typical design problems. The results indicate that the developed tools are capable of finding optimal solutions in the specified design space.

Helsinki University of Technology, Laboratory of Lightweight Structures. Series A, ISSN 0785-9503; 2

Advisors/Committee Members: Helsinki University of Technology, Department of Mechanical Engineering, Laboratory of Lightweight Structures.

Subjects/Keywords: composite laminates; multiobjective design; optimisation

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APA (6^th Edition):

Saarela, O. (2005). Design System of Composite Laminates. (Thesis). Helsinki University of Technology. Retrieved from http://lib.tkk.fi/Diss/2005/isbn9512278715/

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Saarela, Olli. “Design System of Composite Laminates.” 2005. Thesis, Helsinki University of Technology. Accessed March 05, 2021. http://lib.tkk.fi/Diss/2005/isbn9512278715/.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Saarela, Olli. “Design System of Composite Laminates.” 2005. Web. 05 Mar 2021.

Vancouver:

Saarela O. Design System of Composite Laminates. [Internet] [Thesis]. Helsinki University of Technology; 2005. [cited 2021 Mar 05]. Available from: http://lib.tkk.fi/Diss/2005/isbn9512278715/.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Saarela O. Design System of Composite Laminates. [Thesis]. Helsinki University of Technology; 2005. Available from: http://lib.tkk.fi/Diss/2005/isbn9512278715/

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Sydney

3. Yuan, Chen. Crushing Responses and Design of CF/EP Composite Structures .

Degree: 2018, University of Sydney

URL: http://hdl.handle.net/2123/20581

► By virtue of their excellent properties of specific strength-to-mass and stiffness-to-mass ratios, carbon fibre reinforced epoxy (CF/EP) structures are becoming increasingly important in various transportation… (more)

Subjects/Keywords: Composite structure; Dynamic response; failure mechanism; Modelling; CFRP; Optimisation design

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APA (6^th Edition):

Yuan, C. (2018). Crushing Responses and Design of CF/EP Composite Structures . (Thesis). University of Sydney. Retrieved from http://hdl.handle.net/2123/20581

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Yuan, Chen. “Crushing Responses and Design of CF/EP Composite Structures .” 2018. Thesis, University of Sydney. Accessed March 05, 2021. http://hdl.handle.net/2123/20581.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Yuan, Chen. “Crushing Responses and Design of CF/EP Composite Structures .” 2018. Web. 05 Mar 2021.

Vancouver:

Yuan C. Crushing Responses and Design of CF/EP Composite Structures . [Internet] [Thesis]. University of Sydney; 2018. [cited 2021 Mar 05]. Available from: http://hdl.handle.net/2123/20581.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Yuan C. Crushing Responses and Design of CF/EP Composite Structures . [Thesis]. University of Sydney; 2018. Available from: http://hdl.handle.net/2123/20581

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

4. Shen, Zeng. Characterisation of low velocity impact response in composite laminates.

Degree: PhD, 2015, University of Hertfordshire

URL: http://hdl.handle.net/2299/16334

► A major concern affecting the efficient use of composite laminates in aerospace industry is the lack of understanding of the effect of low-velocity impact (LVI)… (more)

▼ A major concern affecting the efficient use of composite laminates in aerospace industry is the lack of understanding of the effect of low-velocity impact (LVI) damage on the structural integrity. This project aims to develop further knowledge of the response and damage mechanisms of composite laminates under LVI, and to explore the feasibility of assessing the internal impact damage with a visually inspectable parameter. The response and damage mechanisms of composite laminates under LVI have been investigated experimentally and numerically in this project. Various parameters including the laminates thickness, lay-up configuration, repeated impact, and curing temperature have been examined. The concept and the phenomena of delamination threshold load (DTL) have been assessed in details. It was found that DTL exists for composite laminates, but the determination of the DTL value is not straightforward. There is a suitable value of range between the impact energy and the laminates stiffness/thickness, if the sudden load drop phenomenon in the impact force history is used to detect the DTL value. It is suggested that the potential menace of the delamination initiation may be overestimated. The composite laminates tested in this project demonstrate good damage tolerance capacity due to the additional energy absorption mechanism following the delamination initiation. As a result, the current design philosophy for laminated composite structure might be too conservative and should be reassessed to improve the efficiency further. To explore the feasibility of linking the internal damage to a visually inspectable parameter, quasi-static indentation (QSI) tests have been carried out. The dent depth, as a visually inspectable parameter, has been carefully monitored and assessed in relation to the damage status of the composite laminates. It is proposed that the damage process of composite laminates can be divided into different phases based on the difference in the increasing rate of dent depth. Moreover, the internal damage has been examined under the optical microscope (OM) and the scanning electron microscope (SEM). Residual compressive strength of the damaged specimen has been measured using the compression-after-impact (CAI) test. The results further confirm the findings with regard to the overestimated potential menace of the delamination initiation and the proposed damage process assumption. The proposed damage process assumption has great potential to improve the efficiency and accuracy of both the analytical prediction and the structural health monitoring for damages in composite laminates under low-velocity impact.

Subjects/Keywords: 620.1; composite laminates; low velocity impact; damage mechanism

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Shen, Z. (2015). Characterisation of low velocity impact response in composite laminates. (Doctoral Dissertation). University of Hertfordshire. Retrieved from http://hdl.handle.net/2299/16334

Chicago Manual of Style (16^th Edition):

Shen, Zeng. “Characterisation of low velocity impact response in composite laminates.” 2015. Doctoral Dissertation, University of Hertfordshire. Accessed March 05, 2021. http://hdl.handle.net/2299/16334.

MLA Handbook (7^th Edition):

Shen, Zeng. “Characterisation of low velocity impact response in composite laminates.” 2015. Web. 05 Mar 2021.

Vancouver:

Shen Z. Characterisation of low velocity impact response in composite laminates. [Internet] [Doctoral dissertation]. University of Hertfordshire; 2015. [cited 2021 Mar 05]. Available from: http://hdl.handle.net/2299/16334.

Council of Science Editors:

Shen Z. Characterisation of low velocity impact response in composite laminates. [Doctoral Dissertation]. University of Hertfordshire; 2015. Available from: http://hdl.handle.net/2299/16334

University of South Carolina

5. Albazzan, Mazen. Efficient Design Optimization Methodology for Manufacturable Variable Stiffness Laminated Composite Structures.

Degree: PhD, Mechanical Engineering, 2020, University of South Carolina

URL: https://scholarcommons.sc.edu/etd/5731

► Because of their superior mechanical and environmental properties compared to traditional metals, fiber-reinforced composite materials have earned a widespread acceptance for different structural applications.… (more)

▼ Because of their superior mechanical and environmental properties compared to traditional metals, fiber-reinforced composite materials have earned a widespread acceptance for different structural applications. The tailoring potential of composites to achieve high specific stiffness and strength has promoted them as promising candidates for constructing lightweight structures. From that aspect, designers have tackled the problem of designing composite laminates, which is inherently challenging due to the presence of non-linear, non-convex, and multi-dimensional optimization problems with discrete and continuous design variables. However, despite their increased usage, the possible improvements that can be achieved by composite laminates have not been fully exploited. With the introduction of new manufacturing technologies such as advanced fiber placement, engineers now have the capability to harness the full potential of nonconventional variable stiffness composite laminates using in-plane fiber steering. This can be a blessing as well as a curse for the designer, where the additional improvements can be attained at the expense of an increased complexity of the design problem. To circumvent this difficulty, this research aims to develop appropriate design tools to help unlock the advancements achieved by nonconventional variable stiffness laminates. The purpose is to adopt an efficient design optimization methodology to abandon the traditional usage of straight fiber composite laminates in the favor of exploring the structural improvements that can be achieved by steered laminated composite structures, subject to manufacturing constraints and industry design guidelines. This represents a remarkable step in the development of energy-efficient light-weight structures and in their certification. The complexity of the optimization problem imposes the need for an efficient multi-level optimization approach to achieve a global optimum design. In this work, the importance of including a design-manufacturing mesh is demonstrated in each optimization step of the multi-level optimization framework. In the first step (Stiffness Optimization), a theoretical optimum stiffness distribution parameterized in terms of lamination parameters is achieved that accounts for optimum structural performance while maintaining smoothness and robustness. The design-manufacturing mesh allows the spatial stiffness distribution to be expressed as a B-spline or NURBS surface defined by the control points of the design-manufacturing mesh. The fiber angle distribution is then obtained in the second optimization step (Stacking Sequence Retrieval) to match the optimum stiffness properties from the first optimization step while accounting for the maximum steering constraint and laminate design guidelines to attain manufacturability and feasibility. A bilinear sine angle variation is presented to obtain smooth fiber angle distributions, and the maximum steering constraint is derived to guarantee a certain degree of manufacturability at the… Advisors/Committee Members: Zafer Gürdal, Ramy Harik.

Subjects/Keywords: Mechanical Engineering; Composite Laminate Design Optimization; Composite Structures; Fiber Steered Laminates; Lamination Parameters; Multi-level Optimization; Variable Stiffness Laminates

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Albazzan, M. (2020). Efficient Design Optimization Methodology for Manufacturable Variable Stiffness Laminated Composite Structures. (Doctoral Dissertation). University of South Carolina. Retrieved from https://scholarcommons.sc.edu/etd/5731

Chicago Manual of Style (16^th Edition):

Albazzan, Mazen. “Efficient Design Optimization Methodology for Manufacturable Variable Stiffness Laminated Composite Structures.” 2020. Doctoral Dissertation, University of South Carolina. Accessed March 05, 2021. https://scholarcommons.sc.edu/etd/5731.

MLA Handbook (7^th Edition):

Albazzan, Mazen. “Efficient Design Optimization Methodology for Manufacturable Variable Stiffness Laminated Composite Structures.” 2020. Web. 05 Mar 2021.

Vancouver:

Albazzan M. Efficient Design Optimization Methodology for Manufacturable Variable Stiffness Laminated Composite Structures. [Internet] [Doctoral dissertation]. University of South Carolina; 2020. [cited 2021 Mar 05]. Available from: https://scholarcommons.sc.edu/etd/5731.

Council of Science Editors:

Albazzan M. Efficient Design Optimization Methodology for Manufacturable Variable Stiffness Laminated Composite Structures. [Doctoral Dissertation]. University of South Carolina; 2020. Available from: https://scholarcommons.sc.edu/etd/5731

Indian Institute of Science

6. Mache, Ashok Ranganath. An Advanced Study on Jute-Polyester Composites for Mechanical Design and Impact Safety Applications.

Degree: PhD, Faculty of Engineering, 2018, Indian Institute of Science

URL: http://etd.iisc.ac.in/handle/2005/3532

► Natural fiber-reinforced composites are now finding extensive uses in various fields from household articles to automobiles. These composites can score high compared to common synthetic… (more)

▼ Natural fiber-reinforced composites are now finding extensive uses in various fields from household articles to automobiles. These composites can score high compared to common synthetic fiber-based composites, notably glass fiber-reinforced composites, in areas such as occupational safety and health, and impact on environment. The current research work is motivated by the need for exploring jute fibers as replacement for glass fibers for various engineering design applications including more demanding impact protection applications as in automotive body structures. In the current work, detailed mechanical characterization of jute-polyester (JP) composite laminates till failure has been carried out for tensile, compressive and flexural loads by varying volume fraction of jute fibers. The effect of fiber volume fraction on mechanical properties is shown. Because of the potency of closed thin-walled components as structural energy-absorbers, a comprehensive experimental study has been performed, for the first time, comparing the behaviors of various geometric sections of JP and glass-polyester (GP) composite tubes under axial quasi-static and low velocity impact loading. Additionally, for jute-reinforced plastic panels to be feasible solutions for applications such as automotive interior trim panels, laminates made of such materials should have adequate perforation resistance. Thus, a detailed comparative study has been carried out for assessing the performance of JP laminates vis-a-vis GP plates under low velocity impact perforation conditions. As high-end product design is heavily driven by CAE (Computer-Aided Engineering), the current research work has also focused on the challenging task of developing reliable modeling procedures for explicit finite element analysis using LS-DYNA for predicting load-displacement responses and failures of JP composites under quasi-static and impact loading conditions. In order to extend the applications of JP composites to structurally demanding applications, hybrid laminates made of jute-steel composites and jute with nanoclay-reinforced polyester have been investigated and the considerable enhancement of mechanical properties due to hybridization is shown. Furthermore, a comprehensive study has been conducted on the behavior of JP laminates for varying degrees of moisture content until saturation, and the efficacy of hybrid laminates in this context has been shown. Advisors/Committee Members: Deb, Anindya (advisor).

Subjects/Keywords: Jute-Polyester Composites - Engineering Design Applications; Jute-Polyester Composites; Fiber Reinforced Composites; Biocomposite Materials; Hybrid Jute-Steel Composites; Composite Materials; Jute-Polyester Composite Laminates; Jute-Steel Wire Mesh-Polyester Composite; Jute Fiber-Based Composite Tubes; Jute-Steel Composite; Glass-Polyester Composite Tubes; Jute-Polyester Composite Tubes; Jute-Polyester Laminate; Product Design and Manufacturing

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APA (6^th Edition):

Mache, A. R. (2018). An Advanced Study on Jute-Polyester Composites for Mechanical Design and Impact Safety Applications. (Doctoral Dissertation). Indian Institute of Science. Retrieved from http://etd.iisc.ac.in/handle/2005/3532

Chicago Manual of Style (16^th Edition):

Mache, Ashok Ranganath. “An Advanced Study on Jute-Polyester Composites for Mechanical Design and Impact Safety Applications.” 2018. Doctoral Dissertation, Indian Institute of Science. Accessed March 05, 2021. http://etd.iisc.ac.in/handle/2005/3532.

MLA Handbook (7^th Edition):

Mache, Ashok Ranganath. “An Advanced Study on Jute-Polyester Composites for Mechanical Design and Impact Safety Applications.” 2018. Web. 05 Mar 2021.

Vancouver:

Mache AR. An Advanced Study on Jute-Polyester Composites for Mechanical Design and Impact Safety Applications. [Internet] [Doctoral dissertation]. Indian Institute of Science; 2018. [cited 2021 Mar 05]. Available from: http://etd.iisc.ac.in/handle/2005/3532.

Council of Science Editors:

Mache AR. An Advanced Study on Jute-Polyester Composites for Mechanical Design and Impact Safety Applications. [Doctoral Dissertation]. Indian Institute of Science; 2018. Available from: http://etd.iisc.ac.in/handle/2005/3532

Anna University

7. Sasikumar, M. Behaviour analysis of fibre reinforced composite plates under medium velocity impact; -.

Degree: Mechanical Engineering, 2014, Anna University

URL: http://shodhganga.inflibnet.ac.in/handle/10603/25538

►

In the recent past substantial structural strength light weight and stiffness properties of polymer based composite materials find its application in aircraft and automotive structures… (more)

Subjects/Keywords: Composite laminates; Energy absorbing mechanisms; Energy conservation; Fibre reinforced composite plates; Finite element models; Mechanical engineering; Polymer based composite materials

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APA (6^th Edition):

Sasikumar, M. (2014). Behaviour analysis of fibre reinforced composite plates under medium velocity impact; -. (Thesis). Anna University. Retrieved from http://shodhganga.inflibnet.ac.in/handle/10603/25538

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Sasikumar, M. “Behaviour analysis of fibre reinforced composite plates under medium velocity impact; -.” 2014. Thesis, Anna University. Accessed March 05, 2021. http://shodhganga.inflibnet.ac.in/handle/10603/25538.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Sasikumar, M. “Behaviour analysis of fibre reinforced composite plates under medium velocity impact; -.” 2014. Web. 05 Mar 2021.

Vancouver:

Sasikumar M. Behaviour analysis of fibre reinforced composite plates under medium velocity impact; -. [Internet] [Thesis]. Anna University; 2014. [cited 2021 Mar 05]. Available from: http://shodhganga.inflibnet.ac.in/handle/10603/25538.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Sasikumar M. Behaviour analysis of fibre reinforced composite plates under medium velocity impact; -. [Thesis]. Anna University; 2014. Available from: http://shodhganga.inflibnet.ac.in/handle/10603/25538

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Utah State University

8. Lambert, Michael D. Investigation of the Design and Static Behavior of Cylindrical Tubular Composite Adhesive Joints Utilizing the Finite Element Method and Stress-Based Failure Theories.

Degree: MS, Mechanical and Aerospace Engineering, 2011, Utah State University

URL: https://digitalcommons.usu.edu/etd/1045

► The stress and strength behavior of cylindrical tubular adhesive joints composed of dissimilar materials was explored. This was accomplished with the finite element method… (more)

▼ The stress and strength behavior of cylindrical tubular adhesive joints composed of dissimilar materials was explored. This was accomplished with the finite element method (FEM) and stress-based failure theories. Also, it was shown how a design of experiments (DOE) based method can be used to objectively organize the process of optimizing joint strength by using stress-based failure criteria. The finite element program used in this work was written in-house from scratch to implement the FEM for the purpose of solving both axisymmetric and three-dimensional linear elastic governing equations of static equilibrium. The formulation of the three-dimensional model is presented, and the required operations to arrive to the axisymmetric model are also presented. The axisymmetric model is two dimensional, capable of using four and eight node quadrilateral elements. However, only four node elements are used because a mesh of eight node elements requires more memory and increased mesh refinement. The three-dimensional model is capable of using eight and twenty node brick elements, but only eight node brick elements are used for the same reason. Both of the axisymmetric and three-dimensional models calculate the nodal displacements, strains, stress values for each material, and strength values for each material. The external static loads can be individually applied, or coupled together. The outputs seem to be most useful for interpretation when plotted through-the-thickness (TTT) and along-the-length (ATL) of the joint or tube. Outputs are valid only for materials that behave linearly elastic up to(or near) failure, and the stress-based failure criteria are used to define that limit. A small laboratory-sized joint was modeled to look at the theoretical stress and strength distributions plotted along-the-length of the joint at different radial locations. These stress and strength distributions can be correlated to the type of load being applied because of unique or prominent features seen in the stress and strength distributions. The load can be a uniform temperature change, axial load, torque load, internal and external pressure, and/or bending load. A variance in the stress or strength for different joint sizes and materials is not examined closely due to the many possible combinations of these parameters. Advisors/Committee Members: Thomas H. Fronk, Steven L. Folkman, Yibin Xue, ;.

Subjects/Keywords: Design; Static Behavior; Cylindrical Tubular Composite Adhesive Joints; Finite Element Method; Stress-Based Failure Theories; Engineering; Mechanical Engineering

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APA (6^th Edition):

Lambert, M. D. (2011). Investigation of the Design and Static Behavior of Cylindrical Tubular Composite Adhesive Joints Utilizing the Finite Element Method and Stress-Based Failure Theories. (Masters Thesis). Utah State University. Retrieved from https://digitalcommons.usu.edu/etd/1045

Chicago Manual of Style (16^th Edition):

Lambert, Michael D. “Investigation of the Design and Static Behavior of Cylindrical Tubular Composite Adhesive Joints Utilizing the Finite Element Method and Stress-Based Failure Theories.” 2011. Masters Thesis, Utah State University. Accessed March 05, 2021. https://digitalcommons.usu.edu/etd/1045.

MLA Handbook (7^th Edition):

Lambert, Michael D. “Investigation of the Design and Static Behavior of Cylindrical Tubular Composite Adhesive Joints Utilizing the Finite Element Method and Stress-Based Failure Theories.” 2011. Web. 05 Mar 2021.

Vancouver:

Lambert MD. Investigation of the Design and Static Behavior of Cylindrical Tubular Composite Adhesive Joints Utilizing the Finite Element Method and Stress-Based Failure Theories. [Internet] [Masters thesis]. Utah State University; 2011. [cited 2021 Mar 05]. Available from: https://digitalcommons.usu.edu/etd/1045.

Council of Science Editors:

Lambert MD. Investigation of the Design and Static Behavior of Cylindrical Tubular Composite Adhesive Joints Utilizing the Finite Element Method and Stress-Based Failure Theories. [Masters Thesis]. Utah State University; 2011. Available from: https://digitalcommons.usu.edu/etd/1045

University of Southern California

9. Zhang, Yuzheng. Mechanical behavior and microstructure optimization of ultrafine-grained aluminum alloys and nanocomposites.

Degree: PhD, Materials Science, 2015, University of Southern California

URL: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/613286/rec/4005

► Nanocrystalline (NC) or ultrafine-grained (UFG) materials exhibit significantly improved strength and hardness compared to the coarse grain (CG) counterpart according to the well-known Hall-Petch effect.… (more)

▼ Nanocrystalline (NC) or ultrafine-grained (UFG) materials exhibit significantly improved strength and hardness compared to the coarse grain (CG) counterpart according to the well-known Hall-Petch effect. In this work, aluminum alloy (AA) 5083 was selected as the target material due to its low density, good weldability and excellent corrosion resistance. Refined grain size was achieved by severe plastic deformation techniques including cryomilling and high pressure torsion (HPT) which both introduced large amount of plastic strain into the materials and thus refined grain sizes down to nano-scale. ❧ Despite enhanced strength and hardness, the NC or UFG AA 5083 is very brittle due to the lack of plasticity mechanisms. This brittleness can cause numerous risks and failures during material service or even during production. The major challenge of this work is to restore ductility of the NC or UFG AA 5083 while maintaining its high strength. Toughening approaches described in this work follow the materials science paradigm which says “microstructure connects fabrication with properties”. The mechanical properties of the end products were tailored by altering the microstructure via different processing routes. We seek an optimized microstructure which can balance the strength with the ductility and maximize the fracture toughness of the NC/UFG AA 5083. ❧ Chapter 1 will discuss the general background, modern synthesis methods, strengthening mechanisms and toughening efforts of the NC/UFG materials. Chapter 2 will introduce the methods and experimental procedures for microstructure characterization and deformation mechanism investigation. Chapter 3 will describe an in situ micro-strain measurement of an UFG Al-Mg alloy at sub-micron scale. Chapter 4 will focus on the microstructural evolution of the cryomilled Al/B4C powder during processing. Chapter 5 will investigate the failure mechanisms and the toughening effect of the ductile regions in a trimodal AA 5083 nanocomposite. Chapter 6 will demonstrate the attempt to enhance the toughness by optimizing the morphology and spacing of the ductile regions in the trimodal nanocomposite. At last, chapter 7 will discuss some historic aspects of this work and the challenges that are lying ahead. Advisors/Committee Members: Nutt, Steven R. (Committee Chair), Kassner, Michael E. (Committee Member), Hodge, Andrea M. (Committee Member).

Subjects/Keywords: metal matrix composite; failure mechanism; ultrafine-grained materials; cryomilling

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APA (6^th Edition):

Zhang, Y. (2015). Mechanical behavior and microstructure optimization of ultrafine-grained aluminum alloys and nanocomposites. (Doctoral Dissertation). University of Southern California. Retrieved from http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/613286/rec/4005

Chicago Manual of Style (16^th Edition):

Zhang, Yuzheng. “Mechanical behavior and microstructure optimization of ultrafine-grained aluminum alloys and nanocomposites.” 2015. Doctoral Dissertation, University of Southern California. Accessed March 05, 2021. http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/613286/rec/4005.

MLA Handbook (7^th Edition):

Zhang, Yuzheng. “Mechanical behavior and microstructure optimization of ultrafine-grained aluminum alloys and nanocomposites.” 2015. Web. 05 Mar 2021.

Vancouver:

Zhang Y. Mechanical behavior and microstructure optimization of ultrafine-grained aluminum alloys and nanocomposites. [Internet] [Doctoral dissertation]. University of Southern California; 2015. [cited 2021 Mar 05]. Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/613286/rec/4005.

Council of Science Editors:

Zhang Y. Mechanical behavior and microstructure optimization of ultrafine-grained aluminum alloys and nanocomposites. [Doctoral Dissertation]. University of Southern California; 2015. Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/613286/rec/4005

University of Michigan

10. Basu, Shiladitya. Computational modeling of progressive failure and damage in composite laminates.

Degree: PhD, Mechanical engineering, 2005, University of Michigan

URL: http://hdl.handle.net/2027.42/125294

► Current and future aerospace systems utilize an ever-increasing amount of fiber reinforced composite laminates in various mission critical structural components making it imperative to understand… (more)

▼ Current and future aerospace systems utilize an ever-increasing amount of fiber reinforced composite laminates in various mission critical structural components making it imperative to understand their damage tolerance capacity under a multitude of loading envelopes. Their comparatively low strength under predominantly axial compressive loading severely limits the design loads of such structures. In the current work, a mechanism based lamina level computational methodology is developed for progressive failure analysis (PFA) of composite laminates beyond initial failure. A combination of analytical and micromechanical studies are used to identify the underlying mechanism of failure under predominantly compressive loading. Under such loading, the class of carbon fiber reinforced laminates considered in this thesis fails by fiber kinking. Results from an analytical study dispel the notion of a fixed compressive strength and show that it is a function of the in-situ geometric and material properties and stress state. These observations and finite element based micromechanical studies have identified the in-situ fiber rotation in the presence of initial fiber misalignment and the degradation of the in-situ shear modulus due to microcracking as the two main drivers of the kinking failure mechanism. A previously developed thermodynamics based lamina constitutive model is utilized to develop a PFA methodology for laminated composites. Laminae are assumed to be damaged by microcraking that is manifested in the degradation of the shear modulus and the transverse modulus. The amount of irrecoverable energy, expressed as a thermodynamic state variable S, provides a measure of the damage state inside a lamina. Lamina level coupon tests are used to obtain relations between S and the degrading moduli. These relations in conjunction with the lamina elastic constants and the geometric information such as the lamina thickness and the lamina lay-up are used as the PFA inputs. Damage accumulates in a lamina when an energy balance condition is satisfied and the in-situ secant stiffnesses in shear and in the transverse direction are degraded. The complete laminate response under loading is modeled by the classical lamination theory. Beyond reaching a critical value of S, denoted as S* (obtained experimentally), all lamina moduli are degraded steeply. For numerical implementation, in essence, this models an abrupt catastrophic event in a finite number of gradual steps. This method is demonstrated via numerical examples of single and multi element meshes under uniaxial compression that generate the characteristic load-deflection curves observed for detailed micromechanical studies. The maximum load predictions are seen to match the results obtained with rigorous micromechanical analyses, and corresponding laboratory experiments. The PFA developed in this thesis is demonstrated, verified and validated by modeling the responses of composite panels tested by the author and elsewhere. The PFA predictions are very close to the experimental… Advisors/Committee Members: Waas, Anthony M. (advisor).

Subjects/Keywords: Composite Laminates; Computational; Damage; Failure; Modeling; Progressive

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APA (6^th Edition):

Basu, S. (2005). Computational modeling of progressive failure and damage in composite laminates. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/125294

Chicago Manual of Style (16^th Edition):

Basu, Shiladitya. “Computational modeling of progressive failure and damage in composite laminates.” 2005. Doctoral Dissertation, University of Michigan. Accessed March 05, 2021. http://hdl.handle.net/2027.42/125294.

MLA Handbook (7^th Edition):

Basu, Shiladitya. “Computational modeling of progressive failure and damage in composite laminates.” 2005. Web. 05 Mar 2021.

Vancouver:

Basu S. Computational modeling of progressive failure and damage in composite laminates. [Internet] [Doctoral dissertation]. University of Michigan; 2005. [cited 2021 Mar 05]. Available from: http://hdl.handle.net/2027.42/125294.

Council of Science Editors:

Basu S. Computational modeling of progressive failure and damage in composite laminates. [Doctoral Dissertation]. University of Michigan; 2005. Available from: http://hdl.handle.net/2027.42/125294

Queen Mary, University of London

11. Malhotra, Anjum. Low velocity edge impact on composite laminates : damage tolerance and numerical simulations.

Degree: PhD, 2014, Queen Mary, University of London

URL: http://qmro.qmul.ac.uk/xmlui/handle/123456789/8571 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.667259

► Composite laminates are increasingly being used in more complex structural applications where edges and cut outs are inevitable. These applications include wing skins of military… (more)

▼ Composite laminates are increasingly being used in more complex structural applications where edges and cut outs are inevitable. These applications include wing skins of military and civil aircraft, further aerospace applications as well as automotive panels and critical structures. Composite components in such applications are highly susceptible to damage. Composites behave in a different manner to conventional metallic materials, which has introduced several design problems not previously encountered. One such problem has been the susceptibility of the material to accidental low energy impacts which frequently leave no visible mark on the impacted surface but considerable internal damage. Investigation of the residual strength and stiffness of composites after edge impact has become important for the design of aerospace components. Previously, the research work involved central impact of composite laminates but in this research we are investigating edge impact behaviour of composite laminates as parts of composite structures are particularly vulnerable to impacts, including near the edge of an inspection port or other aperture. Furthermore, impacts to such areas may lead to more severe damage near the edge of the laminate rather than the surface. Thus the present work extends these investigations to impact on the edge of composite laminates. The thesis includes both experimental investigations and finite element simulations of impact damage on the plane of the laminate near the edge (near-edge), and on the edge (on-edge) of composite laminates. A comparison with centre impact with on and near-edge impact is done to understand the damage on the edges and away from the edges. A new design has been developed and implemented to perform edge impact experiments. The research investigated the effects of various parameters like thickness, absorbed energies, force-time histories and damage behaviour of composite laminate. The damage size and mechanisms have been explored. Impact simulation was carried out using finite element code Abaqus. Explicit solution technique of the code was used to analyse the edge impact phenomenon. Results of the finite element analysis were compared with experiments. The residual strength of the laminates under compressive and tensile loading has been measured. Tensions after impact (TAI) tests were conducted to evaluate the residual load carrying capacity. The effect of edge impact on the low velocity impact response and the residual tensile strength is discussed via the test results. This thesis also includes computed tomography as the main technique for micro level damage characterisation and investigates the study of damage mechanisms of glass/epoxy laminates subjected to edge impact with varying energy levels and thickness. Computed Tomography aims to provide damage behaviour such as internal damage state, delaminations during different types of edge impact.

Subjects/Keywords: 620.1; Materials Science; Composite laminates

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APA (6^th Edition):

Malhotra, A. (2014). Low velocity edge impact on composite laminates : damage tolerance and numerical simulations. (Doctoral Dissertation). Queen Mary, University of London. Retrieved from http://qmro.qmul.ac.uk/xmlui/handle/123456789/8571 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.667259

Chicago Manual of Style (16^th Edition):

Malhotra, Anjum. “Low velocity edge impact on composite laminates : damage tolerance and numerical simulations.” 2014. Doctoral Dissertation, Queen Mary, University of London. Accessed March 05, 2021. http://qmro.qmul.ac.uk/xmlui/handle/123456789/8571 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.667259.

MLA Handbook (7^th Edition):

Malhotra, Anjum. “Low velocity edge impact on composite laminates : damage tolerance and numerical simulations.” 2014. Web. 05 Mar 2021.

Vancouver:

Malhotra A. Low velocity edge impact on composite laminates : damage tolerance and numerical simulations. [Internet] [Doctoral dissertation]. Queen Mary, University of London; 2014. [cited 2021 Mar 05]. Available from: http://qmro.qmul.ac.uk/xmlui/handle/123456789/8571 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.667259.

Council of Science Editors:

Malhotra A. Low velocity edge impact on composite laminates : damage tolerance and numerical simulations. [Doctoral Dissertation]. Queen Mary, University of London; 2014. Available from: http://qmro.qmul.ac.uk/xmlui/handle/123456789/8571 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.667259

Clemson University

12. Kemmann, Guy Maximilian. An Experimental Investigation of Combined Symmetric Asymmetric Composite Laminates.

Degree: MS, Mechanical Engineering, 2018, Clemson University

URL: https://tigerprints.clemson.edu/all_theses/2991

► It has been found that certain asymmetric composite laminates exhibit bistability, and are thus called bistable composite laminates. A bistable composite laminate is a composite… (more)

Subjects/Keywords: asymmetric; Bistable; Composite; Laminates; symmetric

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APA (6^th Edition):

Kemmann, G. M. (2018). An Experimental Investigation of Combined Symmetric Asymmetric Composite Laminates. (Masters Thesis). Clemson University. Retrieved from https://tigerprints.clemson.edu/all_theses/2991

Chicago Manual of Style (16^th Edition):

Kemmann, Guy Maximilian. “An Experimental Investigation of Combined Symmetric Asymmetric Composite Laminates.” 2018. Masters Thesis, Clemson University. Accessed March 05, 2021. https://tigerprints.clemson.edu/all_theses/2991.

MLA Handbook (7^th Edition):

Kemmann, Guy Maximilian. “An Experimental Investigation of Combined Symmetric Asymmetric Composite Laminates.” 2018. Web. 05 Mar 2021.

Vancouver:

Kemmann GM. An Experimental Investigation of Combined Symmetric Asymmetric Composite Laminates. [Internet] [Masters thesis]. Clemson University; 2018. [cited 2021 Mar 05]. Available from: https://tigerprints.clemson.edu/all_theses/2991.

Council of Science Editors:

Kemmann GM. An Experimental Investigation of Combined Symmetric Asymmetric Composite Laminates. [Masters Thesis]. Clemson University; 2018. Available from: https://tigerprints.clemson.edu/all_theses/2991

Indian Institute of Science

13. Lakshmanan, P. Studies on Glass Fiber-Reinforced Composites for CAE-Driven Design of Impact Safety Countermeasures.

Degree: PhD, Faculty of Engineering, 2018, Indian Institute of Science

URL: http://etd.iisc.ac.in/handle/2005/3039

► Man-made materials such as fiber-reinforced composites (FRCs) can be tailored for optimum performance in product design applications in terms of strength and weight. The current… (more)

Subjects/Keywords: Glass Fiber Reinforced Composites; Fiber Reinforced Composites; CAE Driven Design; Glass Safety Countermeasures; Composite Materials; Chopped Strand Mat (CSM) Composite Laminates; Woven Roving Mat (WRM) Composite Laminates; Composite Laminates; Glass Fiber Composite Laminates; Vehile Crash Safety Countermeasures; Pure Hand Layup (PHL); Compression Molding Assisted Hand Layup (CMAHL); Vacuum Bagging Assisted Hand Layup (VBAHL); GFRC Plates; Fiber-reinforced Composites (FRCs); Mechanical Engineering

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APA (6^th Edition):

Lakshmanan, P. (2018). Studies on Glass Fiber-Reinforced Composites for CAE-Driven Design of Impact Safety Countermeasures. (Doctoral Dissertation). Indian Institute of Science. Retrieved from http://etd.iisc.ac.in/handle/2005/3039

Chicago Manual of Style (16^th Edition):

Lakshmanan, P. “Studies on Glass Fiber-Reinforced Composites for CAE-Driven Design of Impact Safety Countermeasures.” 2018. Doctoral Dissertation, Indian Institute of Science. Accessed March 05, 2021. http://etd.iisc.ac.in/handle/2005/3039.

MLA Handbook (7^th Edition):

Lakshmanan, P. “Studies on Glass Fiber-Reinforced Composites for CAE-Driven Design of Impact Safety Countermeasures.” 2018. Web. 05 Mar 2021.

Vancouver:

Lakshmanan P. Studies on Glass Fiber-Reinforced Composites for CAE-Driven Design of Impact Safety Countermeasures. [Internet] [Doctoral dissertation]. Indian Institute of Science; 2018. [cited 2021 Mar 05]. Available from: http://etd.iisc.ac.in/handle/2005/3039.

Council of Science Editors:

Lakshmanan P. Studies on Glass Fiber-Reinforced Composites for CAE-Driven Design of Impact Safety Countermeasures. [Doctoral Dissertation]. Indian Institute of Science; 2018. Available from: http://etd.iisc.ac.in/handle/2005/3039

Victoria University of Wellington

14. Lassueur, Loïc. Identifying the Mechanism of Action of Bioactive 1,2-Cyclopropyl Carbohydrates.

Degree: 2015, Victoria University of Wellington

URL: http://hdl.handle.net/10063/5138

► Cyclopropanes and carbohydrates have long been used in the field of drug development. Previous work has shown that 1,2-cyclopropyl carbohydrates display bioactivity in both HeLa… (more)

▼ Cyclopropanes and carbohydrates have long been used in the field of drug development. Previous work has shown that 1,2-cyclopropyl carbohydrates display bioactivity in both HeLa cancer cell lines¹ and in yeast² with a tentatively proposed mechanism of inhibition occurring through an enzymatic cyclopropane ring opening reaction and subsequent formation of a covalent bond with a target enzyme.² A small library of 1,2-cyclopropyl carbohydrate derivatives were synthesised based on known pharmacophores to examine further the potential mechanism of inhibition of such compounds and confirm the occurrence of enzyme-catalysed cyclopropane ring-opening reactions. Initial synthetic efforts were focused on the synthesis of the 1,2-dichlorocyclopropyl carbohydrate 23, which, through the optimisation of an essential C-6 detritylation reaction, was achieved in moderate yields of 32% over 7 steps. Following this, the ethoxycarbonyl substituted 1,2-cyclopropyl carbohydrate 54 was synthesised over 7 steps in a 22% yield through a rhodium acetate-catalysed addition of ethyl diazoacetate (49) to the glucal substrate 40. It was envisioned that if enzymatic cyclopropane ring-opening was occurring to form a C-7 carbanion, this would in turn be stabilised through the potential enolate formation of 54. Use of N,N-ditosylhydrazine in the synthesis of propargyl diazoacetate (58) followed by a rhodium acetate-catalysed cyclopropanation of 58 with substrate 40 resulted in the successful synthesis of 61 over 7 steps in a total yield of 9%. The incorporation of the propargyl substituent in 61 was introduced as a molecular probe in an attempt to isolate the target protein through an affinity purification procedure. The bioactivity of the propargyl derivative 61 was consistent with the synthesised compounds 23 and 54. It was proposed that these compounds undergo an enzymatic cyclopropane ring opening reaction accompanied with a clear diastereoselective preference for the α-stereoisomer of the cyclopropane ring, consistent with a target-based activation of the compounds. Chemical genetic analysis of the resulting bioactive compounds was undertaken using a deletion mutant array of Saccharomyces cerevisiae to elucidate a potential mechanism of action. Analysis of the results showed that, of the 4800 homozygous deletion strains tested in the high-throughput screens, a total of 122 strains were found following validation to sensitise and 68 to give resistance against 23 and 54. These sensitive and resistant mutants were subjected to a validation assay. Following validation, genes whose deletion led to sensitivity or resistance were then subjected to gene ontology term enrichment analysis which showed enrichment in the cytosolic ribosome, SNARE complex and SNAP receptor activity for resistant strains and enrichment in endoplasmic reticulum and endomembrane systems was found for the sensitive strain. Genes whose deletion sensitised to both compounds showed strong enrichment in cellular protein localisation, intra-golgi vesicale-mediated transport and the… Advisors/Committee Members: Teesdale-Spittle, Paul, Harvey, Joanne.

Subjects/Keywords: Cyclopropanes; Drug Design; Chemical Genetics; Mechanism-based

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APA (6^th Edition):

Lassueur, L. (2015). Identifying the Mechanism of Action of Bioactive 1,2-Cyclopropyl Carbohydrates. (Masters Thesis). Victoria University of Wellington. Retrieved from http://hdl.handle.net/10063/5138

Chicago Manual of Style (16^th Edition):

Lassueur, Loïc. “Identifying the Mechanism of Action of Bioactive 1,2-Cyclopropyl Carbohydrates.” 2015. Masters Thesis, Victoria University of Wellington. Accessed March 05, 2021. http://hdl.handle.net/10063/5138.

MLA Handbook (7^th Edition):

Lassueur, Loïc. “Identifying the Mechanism of Action of Bioactive 1,2-Cyclopropyl Carbohydrates.” 2015. Web. 05 Mar 2021.

Vancouver:

Lassueur L. Identifying the Mechanism of Action of Bioactive 1,2-Cyclopropyl Carbohydrates. [Internet] [Masters thesis]. Victoria University of Wellington; 2015. [cited 2021 Mar 05]. Available from: http://hdl.handle.net/10063/5138.

Council of Science Editors:

Lassueur L. Identifying the Mechanism of Action of Bioactive 1,2-Cyclopropyl Carbohydrates. [Masters Thesis]. Victoria University of Wellington; 2015. Available from: http://hdl.handle.net/10063/5138

University of Toronto

15. Wright, Bryan K. Validation of Point and Pressure Loading Models for Simply Supported Composite Sandwich Beams.

Degree: 2012, University of Toronto

URL: http://hdl.handle.net/1807/33590

►

Stiffness and strength models are derived for simply supported composite sandwich panels comprised of fibre-reinforced face sheets and polymer cores subject to symmetric four point… (more)

Subjects/Keywords: composite; sandwich; four point bending; pressure; simply supported; failure mechanism map; 0538

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APA (6^th Edition):

Wright, B. K. (2012). Validation of Point and Pressure Loading Models for Simply Supported Composite Sandwich Beams. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/33590

Chicago Manual of Style (16^th Edition):

Wright, Bryan K. “Validation of Point and Pressure Loading Models for Simply Supported Composite Sandwich Beams.” 2012. Masters Thesis, University of Toronto. Accessed March 05, 2021. http://hdl.handle.net/1807/33590.

MLA Handbook (7^th Edition):

Wright, Bryan K. “Validation of Point and Pressure Loading Models for Simply Supported Composite Sandwich Beams.” 2012. Web. 05 Mar 2021.

Vancouver:

Wright BK. Validation of Point and Pressure Loading Models for Simply Supported Composite Sandwich Beams. [Internet] [Masters thesis]. University of Toronto; 2012. [cited 2021 Mar 05]. Available from: http://hdl.handle.net/1807/33590.

Council of Science Editors:

Wright BK. Validation of Point and Pressure Loading Models for Simply Supported Composite Sandwich Beams. [Masters Thesis]. University of Toronto; 2012. Available from: http://hdl.handle.net/1807/33590

Delft University of Technology

16. Ahmed, A. Computational Modeling of Progressive Failure in FRP Composite Laminates Subjected to Static and Impact Transverse loading.

Degree: 2014, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:4c3b7caa-ea4f-4da6-8005-2bf86767860d ; urn:NBN:nl:ui:24-uuid:4c3b7caa-ea4f-4da6-8005-2bf86767860d ; urn:NBN:nl:ui:24-uuid:4c3b7caa-ea4f-4da6-8005-2bf86767860d ; http://resolver.tudelft.nl/uuid:4c3b7caa-ea4f-4da6-8005-2bf86767860d

► In order to arrive at safe and reliable design of composite structures, understanding of the mechanisms and mechanics of damage growth in these materials is… (more)

▼ In order to arrive at safe and reliable design of composite structures, understanding of the mechanisms and mechanics of damage growth in these materials is of paramount significance. Numerical models, if designed, implemented and used carefully, can be helpful not only to understand the mechanisms and mechanics of damage growth but also to predict the susceptibility of a structure to failure. In this thesis, advanced finite elements and numerical methods are explored to develop an integrated, computationally efficient and reliable numerical framework for the analysis of interacting damage mechanisms in laminated composite plates/shells subjected to transverse quasi-static and dynamic loading. A solid-like shell element is used to obtain a three-dimensional stress state in fiber-reinforced laminated composites. The element is further extended to model mesh-independent matrix cracking by incorporating a discontinuity in the shell mid-surface, shell director and thickness stretching field using the phantom node method. A progressive failure model is developed which is able to simulate impact induced damage in laminated composites. Care is taken to accurately describe the interaction between matrix cracks and delamination damage which is crucial for accurate predictions of fracture phenomena and laminate strength. Furthermore, a time-dependent progressive failure model is developed to simulate crack growth in laminated composites under dynamic loading conditions. The proposed mass discretization schemes for the solid-like shell element ensure efficient performance of the element in implicit as well as explicit elasto-fracture analysis of composite laminates. The presented numerical framework also discusses computational modeling of coupled thermo-mechanics of laminated composites in the presence of cracks. The unified computational model is able to simulate coupled adiabatic-isothermal cracks propagating arbitrarily through the finite element mesh. Advisors/Committee Members: Sluys, L.J..

Subjects/Keywords: composite laminates; finite element method; solid-like shell element; progressive failure

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APA (6^th Edition):

Ahmed, A. (2014). Computational Modeling of Progressive Failure in FRP Composite Laminates Subjected to Static and Impact Transverse loading. (Doctoral Dissertation). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:4c3b7caa-ea4f-4da6-8005-2bf86767860d ; urn:NBN:nl:ui:24-uuid:4c3b7caa-ea4f-4da6-8005-2bf86767860d ; urn:NBN:nl:ui:24-uuid:4c3b7caa-ea4f-4da6-8005-2bf86767860d ; http://resolver.tudelft.nl/uuid:4c3b7caa-ea4f-4da6-8005-2bf86767860d

Chicago Manual of Style (16^th Edition):

Ahmed, A. “Computational Modeling of Progressive Failure in FRP Composite Laminates Subjected to Static and Impact Transverse loading.” 2014. Doctoral Dissertation, Delft University of Technology. Accessed March 05, 2021. http://resolver.tudelft.nl/uuid:4c3b7caa-ea4f-4da6-8005-2bf86767860d ; urn:NBN:nl:ui:24-uuid:4c3b7caa-ea4f-4da6-8005-2bf86767860d ; urn:NBN:nl:ui:24-uuid:4c3b7caa-ea4f-4da6-8005-2bf86767860d ; http://resolver.tudelft.nl/uuid:4c3b7caa-ea4f-4da6-8005-2bf86767860d.

MLA Handbook (7^th Edition):

Ahmed, A. “Computational Modeling of Progressive Failure in FRP Composite Laminates Subjected to Static and Impact Transverse loading.” 2014. Web. 05 Mar 2021.

Vancouver:

Ahmed A. Computational Modeling of Progressive Failure in FRP Composite Laminates Subjected to Static and Impact Transverse loading. [Internet] [Doctoral dissertation]. Delft University of Technology; 2014. [cited 2021 Mar 05]. Available from: http://resolver.tudelft.nl/uuid:4c3b7caa-ea4f-4da6-8005-2bf86767860d ; urn:NBN:nl:ui:24-uuid:4c3b7caa-ea4f-4da6-8005-2bf86767860d ; urn:NBN:nl:ui:24-uuid:4c3b7caa-ea4f-4da6-8005-2bf86767860d ; http://resolver.tudelft.nl/uuid:4c3b7caa-ea4f-4da6-8005-2bf86767860d.

Council of Science Editors:

Ahmed A. Computational Modeling of Progressive Failure in FRP Composite Laminates Subjected to Static and Impact Transverse loading. [Doctoral Dissertation]. Delft University of Technology; 2014. Available from: http://resolver.tudelft.nl/uuid:4c3b7caa-ea4f-4da6-8005-2bf86767860d ; urn:NBN:nl:ui:24-uuid:4c3b7caa-ea4f-4da6-8005-2bf86767860d ; urn:NBN:nl:ui:24-uuid:4c3b7caa-ea4f-4da6-8005-2bf86767860d ; http://resolver.tudelft.nl/uuid:4c3b7caa-ea4f-4da6-8005-2bf86767860d

University of New South Wales

17. Chen, Jingfen. Progressive failure analysis of composite laminates based on elastoplastic and elasto-viscoplastic damage models.

Degree: Engineering & Information Technology, 2013, University of New South Wales

URL: http://handle.unsw.edu.au/1959.4/53027 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:11705/SOURCE01?view=true

► In this work, the progressive failure of composite laminates is studied. Firstly, a combined elastoplastic damage model capable of representing the plastic deformations and degradation… (more)

▼ In this work, the progressive failure of composite laminates is studied. Firstly, a combined elastoplastic damage model capable of representing the plastic deformations and degradation of material stiffness of composite materials has been developed based on continuum damage mechanics and plasticity theory. To simulate the strain rate-dependent effects, a consistency elasto-viscoplastic damage model that accounts for the strain rate-dependent plastic response and stiffness degradation of composites has also been developed. Based on the return mapping algorithm, implicit numerical integration procedures have been developed for the two damage models. Tangent stiffness tensors consistent with the integration algorithms have been derived separately to ensure the computational efficiency of the Newton-Raphson method for solving nonlinear problems in finite element (FE) analysis. The numerical algorithms are implemented in the FE code Abaqus through user-defined subroutines (UMATs).These damage models have been applied to the progressive failure analyses of notched and un-notched composite laminates subjected to in-plane uniaxial tensile loadings at various strain rates. It has been shown that both the combined elastoplastic damage model and the consistency elasto-viscoplastic damage model proposed in this work provide efficient tools for the progressive failure analysis of composite laminates and are capable of delivering more accurate results than several other existing models.Two individual FE models, which include the first material model for composite plies and a cohesive zone model available in Abaqus for interface layers, have been developed and implemented in progressive failure analyses of composite laminates susceptible to delaminations. The progressive failure analyses of notched laminates under in-plane tensile loading and un-notched laminates exhibiting delaminations under out-of-plane transverse impact loading have been performed. The effects of the composites' layup configurations and numbers of through-holes on the mechanical response of fibre-metal laminates have been studied. Close agreement between the predicted results and test data reported in the literature has been demonstrated. It has been shown that, in many cases, the approaches proposed in this work outperform existing modelling techniques. Advisors/Committee Members: Morozov, Evgeny, Engineering & Information Technology, UNSW Canberra, UNSW, Shankar, Krishnakumar, Engineering & Information Technology, UNSW Canberra, UNSW.

Subjects/Keywords: Damage mechanics; Progressive failure analysis; Composite laminates; Plastic deformation; Delamination; Return mapping algorithm; Combined elastoplastic damage model; Consistency elasto-viscoplastic damage model; Abaqus user-defined material subroutine UMAT

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APA (6^th Edition):

Chen, J. (2013). Progressive failure analysis of composite laminates based on elastoplastic and elasto-viscoplastic damage models. (Doctoral Dissertation). University of New South Wales. Retrieved from http://handle.unsw.edu.au/1959.4/53027 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:11705/SOURCE01?view=true

Chicago Manual of Style (16^th Edition):

Chen, Jingfen. “Progressive failure analysis of composite laminates based on elastoplastic and elasto-viscoplastic damage models.” 2013. Doctoral Dissertation, University of New South Wales. Accessed March 05, 2021. http://handle.unsw.edu.au/1959.4/53027 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:11705/SOURCE01?view=true.

MLA Handbook (7^th Edition):

Chen, Jingfen. “Progressive failure analysis of composite laminates based on elastoplastic and elasto-viscoplastic damage models.” 2013. Web. 05 Mar 2021.

Vancouver:

Chen J. Progressive failure analysis of composite laminates based on elastoplastic and elasto-viscoplastic damage models. [Internet] [Doctoral dissertation]. University of New South Wales; 2013. [cited 2021 Mar 05]. Available from: http://handle.unsw.edu.au/1959.4/53027 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:11705/SOURCE01?view=true.

Council of Science Editors:

Chen J. Progressive failure analysis of composite laminates based on elastoplastic and elasto-viscoplastic damage models. [Doctoral Dissertation]. University of New South Wales; 2013. Available from: http://handle.unsw.edu.au/1959.4/53027 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:11705/SOURCE01?view=true

The Ohio State University

18. Zand, Behrad. Modeling of composite laminates subjected to multiaxial loadings.

Degree: PhD, Civil Engineering, 2007, The Ohio State University

URL: http://rave.ohiolink.edu/etdc/view?acc_num=osu1189468229

► A nonlinear strain energy based failure model is proposed for fiber reinforced polymer composites. A new strain energy based failure theory is developed to predict… (more)

Subjects/Keywords: Composite Laminates; Failure Modeling; Biaxial Test; Strain Energy; Orthotropic Materials; Fiber Reinforced Polymers

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APA (6^th Edition):

Zand, B. (2007). Modeling of composite laminates subjected to multiaxial loadings. (Doctoral Dissertation). The Ohio State University. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=osu1189468229

Chicago Manual of Style (16^th Edition):

Zand, Behrad. “Modeling of composite laminates subjected to multiaxial loadings.” 2007. Doctoral Dissertation, The Ohio State University. Accessed March 05, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=osu1189468229.

MLA Handbook (7^th Edition):

Zand, Behrad. “Modeling of composite laminates subjected to multiaxial loadings.” 2007. Web. 05 Mar 2021.

Vancouver:

Zand B. Modeling of composite laminates subjected to multiaxial loadings. [Internet] [Doctoral dissertation]. The Ohio State University; 2007. [cited 2021 Mar 05]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1189468229.

Council of Science Editors:

Zand B. Modeling of composite laminates subjected to multiaxial loadings. [Doctoral Dissertation]. The Ohio State University; 2007. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1189468229

University of Utah

19. Duangmuan, Passakorn. Layer waviness effects on compression strength of composite laminates: progressive failure analysis and experimental validation.

Degree: PhD, Mechanical Engineering, 2012, University of Utah

URL: http://content.lib.utah.edu/cdm/singleitem/collection/etd3/id/817/rec/1470

► Out-of-plane layer waviness, a manufacturing-induced imperfection in multidirectional composite laminates, can produce significant decreases in compressionstrength. To date, failure predictions based on initial “first-ply” failure… (more)

Subjects/Keywords: Composite laminates; Compression strength; Layer waviness

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APA (6^th Edition):

Duangmuan, P. (2012). Layer waviness effects on compression strength of composite laminates: progressive failure analysis and experimental validation. (Doctoral Dissertation). University of Utah. Retrieved from http://content.lib.utah.edu/cdm/singleitem/collection/etd3/id/817/rec/1470

Chicago Manual of Style (16^th Edition):

Duangmuan, Passakorn. “Layer waviness effects on compression strength of composite laminates: progressive failure analysis and experimental validation.” 2012. Doctoral Dissertation, University of Utah. Accessed March 05, 2021. http://content.lib.utah.edu/cdm/singleitem/collection/etd3/id/817/rec/1470.

MLA Handbook (7^th Edition):

Duangmuan, Passakorn. “Layer waviness effects on compression strength of composite laminates: progressive failure analysis and experimental validation.” 2012. Web. 05 Mar 2021.

Vancouver:

Duangmuan P. Layer waviness effects on compression strength of composite laminates: progressive failure analysis and experimental validation. [Internet] [Doctoral dissertation]. University of Utah; 2012. [cited 2021 Mar 05]. Available from: http://content.lib.utah.edu/cdm/singleitem/collection/etd3/id/817/rec/1470.

Council of Science Editors:

Duangmuan P. Layer waviness effects on compression strength of composite laminates: progressive failure analysis and experimental validation. [Doctoral Dissertation]. University of Utah; 2012. Available from: http://content.lib.utah.edu/cdm/singleitem/collection/etd3/id/817/rec/1470

University of Bath

20. Betts, David. Modelling and optimisation of bistable composite laminates.

Degree: PhD, 2012, University of Bath

URL: https://researchportal.bath.ac.uk/en/studentthesis/modelling-and-optimisation-of-bistable-composite-laminates(3a04ff0b-ce60-4b14-98e4-ba23791033f2).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.549838

► Asymmetric composite laminates can have a bistable response to loading. The potentially large structural deformations which can be achieved during snap-through from one stable state… (more)

▼ Asymmetric composite laminates can have a bistable response to loading. The potentially large structural deformations which can be achieved during snap-through from one stable state to another with small and removable energy input make them of interest for a wide range of engineering applications. After 30 years of research effort the shapes and response to applied loads of laminates of general layup can be quantitatively predicted. With attention switching to the incorporation of bistable laminates for practical applications, tools for the design and optimisation of actuated bistable devices are desirable. This thesis describes the analytical and experimental studies undertaken to develop novel modelling and optimisation techniques for the design of actuated asymmetric bistable laminates. These structures are investigated for practical application to morphing structures and the developing technology of piezoelectric energy harvesting. Existing analytical models are limited by the need for a numerical solver to determine stable laminate shapes. As the problem has multiple equilibria, convergence to the desired solution cannot be guaranteed and multiple initial guesses are required to identify all possible solutions. The approach developed in this work allows the efficient and reliable prediction of the stable shapes of laminates with off-axis ply orient at ions in a closed form manner. This model is validated against experimental data and finite element predictions, with an extensive sensitivity study presented to demonstrate the effect of uncertainty and imperfections in the laminate composition. This closed-form solution enables detailed optimisation studies to tailor the design of bistable devices for a range of applications. The first study considers tailoring of the directional stiffness properties of bistable laminates to provide resistance to externally applied loads while allowing low energy actuation. The optimisation formulation is constrained to guarantee bistability and to ensure a useful level of deformation. It is demonstrated that 'cross-symmetric' layups can provide stiffness in an arbitrary loading direction which is five times greater than in a chosen actuation direction.

Subjects/Keywords: 621; composite laminates; energy harvesting; bistability; optimisation

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APA (6^th Edition):

Betts, D. (2012). Modelling and optimisation of bistable composite laminates. (Doctoral Dissertation). University of Bath. Retrieved from https://researchportal.bath.ac.uk/en/studentthesis/modelling-and-optimisation-of-bistable-composite-laminates(3a04ff0b-ce60-4b14-98e4-ba23791033f2).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.549838

Chicago Manual of Style (16^th Edition):

Betts, David. “Modelling and optimisation of bistable composite laminates.” 2012. Doctoral Dissertation, University of Bath. Accessed March 05, 2021. https://researchportal.bath.ac.uk/en/studentthesis/modelling-and-optimisation-of-bistable-composite-laminates(3a04ff0b-ce60-4b14-98e4-ba23791033f2).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.549838.

MLA Handbook (7^th Edition):

Betts, David. “Modelling and optimisation of bistable composite laminates.” 2012. Web. 05 Mar 2021.

Vancouver:

Betts D. Modelling and optimisation of bistable composite laminates. [Internet] [Doctoral dissertation]. University of Bath; 2012. [cited 2021 Mar 05]. Available from: https://researchportal.bath.ac.uk/en/studentthesis/modelling-and-optimisation-of-bistable-composite-laminates(3a04ff0b-ce60-4b14-98e4-ba23791033f2).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.549838.

Council of Science Editors:

Betts D. Modelling and optimisation of bistable composite laminates. [Doctoral Dissertation]. University of Bath; 2012. Available from: https://researchportal.bath.ac.uk/en/studentthesis/modelling-and-optimisation-of-bistable-composite-laminates(3a04ff0b-ce60-4b14-98e4-ba23791033f2).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.549838

University of Limerick

21. Telford, Robert. Hygro-thermal residual stresses in unsymmetrical multi-stable composite laminates.

Degree: 2014, University of Limerick

URL: http://hdl.handle.net/10344/4270

►

peer-reviewed

In this study, an approach to predict and analyse the effects of moisture ingress on residual stresses in multi-stable composite laminates is developed. Residual… (more)

▼

peer-reviewed

In this study, an approach to predict and analyse the effects of moisture ingress on residual stresses in multi-stable composite laminates is developed. Residual stresses are a common consequence of the manufacturing process of composite laminates (e.g. formed thermally, following cool-down from manufacture). Imbalance in these stresses about the mid-plane can lead to warping, and so composite laminates are usually restricted to symmetrical lay-ups. In certain cases, unbalanced residual stresses can be used advantageously, such as in novel morphing structures by use of multi-stable parts. These are parts which feature two or more stable shape configurations, which are obtainable through a force application. With energy only being required to alternate between shapes, multi-stable laminates have been proposed as morphing aerodynamic surfaces for aerospace and wind-energy applications. In these cases (and others in which the laminates are sensitive to residual stresses such as thin plates, ply drop off and bonded repairs) a thorough understanding of the residual stresses (both as-manufactured and in-service) is required. The residual stresses in fibre-resin composites are known to be sensitive to environmental effects, which can be encountered under in-service conditions. One such effect is moisture absorption, which alters the residual stress state of a laminate through matrix swelling and plasticisation. These changes may lead to a change in the laminate’s shape, and in the case of multi-stable laminates, a change in the multi-stable behaviour. Applications based upon these unsymmetrical laminates therefore require consideration to moisture effects at a design stage. In this work, a combined numerical/experimental approach is presented whereby the macro-scale through-thickness residual stresses of dry and saturated unsymmetrical composite laminates can be predicted and analysed. A range of unsymmetrical laminates were manufactured from carbon-fibre reinforced plastic (unidirectional continuous fibres pre-impregnated in a polymer-resin matrix), featuring both square cross-ply and tailored (i.e. featuring local variations in lay-up and/or thickness – representative of laminates that would be used in complex applications) laminate configurations. Following manufacture, the dry laminate shapes were measured, with, in the case of the tailored laminates, laser scanning – a full-field, non-contact surface measuring technique. Three-dimensional continuum based finite element models were created (using the software Abaqus) to simulate the thermal deformation of the laminates. The models were benchmarked using analytical approaches, and subsequently calibrated to match the experimentally measured laminate shapes by means of equivalent orthotropic thermal expansion coefficients, negating the need to account for individual residual stress contributors. Subsequently, laminates were immersed in water until saturation, and the change in shape due to matrix swelling was measured.…

Advisors/Committee Members: Young, Trevor M., Kali-Babu, Katnam.

Subjects/Keywords: residual stresses; manufacturing process; composite laminates

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APA (6^th Edition):

Telford, R. (2014). Hygro-thermal residual stresses in unsymmetrical multi-stable composite laminates. (Thesis). University of Limerick. Retrieved from http://hdl.handle.net/10344/4270

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Telford, Robert. “Hygro-thermal residual stresses in unsymmetrical multi-stable composite laminates.” 2014. Thesis, University of Limerick. Accessed March 05, 2021. http://hdl.handle.net/10344/4270.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Telford, Robert. “Hygro-thermal residual stresses in unsymmetrical multi-stable composite laminates.” 2014. Web. 05 Mar 2021.

Vancouver:

Telford R. Hygro-thermal residual stresses in unsymmetrical multi-stable composite laminates. [Internet] [Thesis]. University of Limerick; 2014. [cited 2021 Mar 05]. Available from: http://hdl.handle.net/10344/4270.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Telford R. Hygro-thermal residual stresses in unsymmetrical multi-stable composite laminates. [Thesis]. University of Limerick; 2014. Available from: http://hdl.handle.net/10344/4270

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of New South Wales

22. Zhang, Zhifang. Assessment of Delaminations in Composite Laminates using Vibration Monitoring.

Degree: Engineering & Information Technology, 2013, University of New South Wales

URL: http://handle.unsw.edu.au/1959.4/53026 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:11704/SOURCE01?view=true

► Fibre-reinforced polymer composite laminates are now commonly used in many structural applications, especially in the aerospace industry, where margins of safety are kept low in… (more)

▼ Fibre-reinforced polymer composite laminates are now commonly used in many structural applications, especially in the aerospace industry, where margins of safety are kept low in order to minimise weight. Timely detection and assessment of delaminations in composite laminates is therefore critical, as they can cause loss of structural integrity affecting the safe operation of the aircraft. Traditional NDI methods are time consuming and expensive since they require aircraft to be grounded for inspections. The current trend therefore is towards implementation of structural health monitoring systems which can monitor the structure in situ without down time. Vibration monitoring is one method which has the potential for such application. Among different methods of vibration monitoring, frequency monitoring is the simplest to implement, requiring only single point measurement, and is accurate and reliable. However, while reductions in natural frequencies clearly indicate the presence of damage, the assessment of the location and severity of the damage from measured shifts in frequencies requires the solution of the inverse problem. There have been few comprehensive studies in the past on the efficacy of delamination assessment from measured frequencies solving the inverse problem, especially for laminated plates.In this thesis, three different methods of solving the inverse problem to estimate delamination parameters from measured frequency shifts are investigated: the graphical method, artificial neural network and surrogate assisted optimisation, all applied initially to composite beams with delaminations at different interfaces. The graphical technique has been extended to the three variable problem of assessing delamination size, axial location and interface location for the first time. The artificial neural network and surrogate assisted optimisation are also applied to the five-variable problem of delaminations in plates (two dimensions and three coordinates for the location). The inverse algorithms techniques are first validated through numerical simulation and their effectiveness and accuracy in predicting delamination parameters are assessed with experimental results from vibration tests conducted on fibre reinforced composite beams and plates with embedded delaminations. The robustness of the inverse algorithms is studied by adding different levels of random artificial noise to the numerical data and their impact on prediction accuracy is determined. Advisors/Committee Members: Shankar, Krishna, Engineering & Information Technology, UNSW Canberra, UNSW, Tahtali, Murat, Engineering & Information Technology, UNSW Canberra, UNSW, Morozov, Evgeny V., Engineering & Information Technology, UNSW Canberra, UNSW.

Subjects/Keywords: Composite laminates; Delamination; Vibration monitoring; Damage detection

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APA (6^th Edition):

Zhang, Z. (2013). Assessment of Delaminations in Composite Laminates using Vibration Monitoring. (Doctoral Dissertation). University of New South Wales. Retrieved from http://handle.unsw.edu.au/1959.4/53026 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:11704/SOURCE01?view=true

Chicago Manual of Style (16^th Edition):

Zhang, Zhifang. “Assessment of Delaminations in Composite Laminates using Vibration Monitoring.” 2013. Doctoral Dissertation, University of New South Wales. Accessed March 05, 2021. http://handle.unsw.edu.au/1959.4/53026 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:11704/SOURCE01?view=true.

MLA Handbook (7^th Edition):

Zhang, Zhifang. “Assessment of Delaminations in Composite Laminates using Vibration Monitoring.” 2013. Web. 05 Mar 2021.

Vancouver:

Zhang Z. Assessment of Delaminations in Composite Laminates using Vibration Monitoring. [Internet] [Doctoral dissertation]. University of New South Wales; 2013. [cited 2021 Mar 05]. Available from: http://handle.unsw.edu.au/1959.4/53026 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:11704/SOURCE01?view=true.

Council of Science Editors:

Zhang Z. Assessment of Delaminations in Composite Laminates using Vibration Monitoring. [Doctoral Dissertation]. University of New South Wales; 2013. Available from: http://handle.unsw.edu.au/1959.4/53026 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:11704/SOURCE01?view=true

King Abdullah University of Science and Technology

23. Selvakumaran, Lakshmi. On micro to mesoscale homogenization of electrical properties for damaged laminated composites (and their potential applications in electrical tomography).

Degree: Physical Science and Engineering (PSE) Division, 2015, King Abdullah University of Science and Technology

URL: http://hdl.handle.net/10754/592653

► Efficient and optimal use of composites in structures requires tools to monitor and capture the complex degradation that can occur within the laminates over time.… (more)

Subjects/Keywords: Mesoscale Homogenization; Electrical Tomography; composite laminates; Damage

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APA (6^th Edition):

Selvakumaran, L. (2015). On micro to mesoscale homogenization of electrical properties for damaged laminated composites (and their potential applications in electrical tomography). (Thesis). King Abdullah University of Science and Technology. Retrieved from http://hdl.handle.net/10754/592653

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Selvakumaran, Lakshmi. “On micro to mesoscale homogenization of electrical properties for damaged laminated composites (and their potential applications in electrical tomography).” 2015. Thesis, King Abdullah University of Science and Technology. Accessed March 05, 2021. http://hdl.handle.net/10754/592653.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Selvakumaran, Lakshmi. “On micro to mesoscale homogenization of electrical properties for damaged laminated composites (and their potential applications in electrical tomography).” 2015. Web. 05 Mar 2021.

Vancouver:

Selvakumaran L. On micro to mesoscale homogenization of electrical properties for damaged laminated composites (and their potential applications in electrical tomography). [Internet] [Thesis]. King Abdullah University of Science and Technology; 2015. [cited 2021 Mar 05]. Available from: http://hdl.handle.net/10754/592653.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Selvakumaran L. On micro to mesoscale homogenization of electrical properties for damaged laminated composites (and their potential applications in electrical tomography). [Thesis]. King Abdullah University of Science and Technology; 2015. Available from: http://hdl.handle.net/10754/592653

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

24. LIU JIALONG. COMPOSITE DESIGN AND OPTIMIZATION THROUGH BIOMIMICRY.

Degree: 2019, National University of Singapore

URL: https://scholarbank.nus.edu.sg/handle/10635/162442

Subjects/Keywords: Composite optimization; biomimicry; failure mechanism; impact mechanism; composite healing; finite element analysis

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APA (6^th Edition):

JIALONG, L. (2019). COMPOSITE DESIGN AND OPTIMIZATION THROUGH BIOMIMICRY. (Thesis). National University of Singapore. Retrieved from https://scholarbank.nus.edu.sg/handle/10635/162442

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

JIALONG, LIU. “COMPOSITE DESIGN AND OPTIMIZATION THROUGH BIOMIMICRY.” 2019. Thesis, National University of Singapore. Accessed March 05, 2021. https://scholarbank.nus.edu.sg/handle/10635/162442.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

JIALONG, LIU. “COMPOSITE DESIGN AND OPTIMIZATION THROUGH BIOMIMICRY.” 2019. Web. 05 Mar 2021.

Vancouver:

JIALONG L. COMPOSITE DESIGN AND OPTIMIZATION THROUGH BIOMIMICRY. [Internet] [Thesis]. National University of Singapore; 2019. [cited 2021 Mar 05]. Available from: https://scholarbank.nus.edu.sg/handle/10635/162442.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

JIALONG L. COMPOSITE DESIGN AND OPTIMIZATION THROUGH BIOMIMICRY. [Thesis]. National University of Singapore; 2019. Available from: https://scholarbank.nus.edu.sg/handle/10635/162442

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Florida

25. Matsumura, Taiki. Effective Safety Measures with Tests Followed by Design Correction for Aerospace Structures.

Degree: PhD, Aerospace Engineering - Mechanical and Aerospace Engineering, 2013, University of Florida

URL: https://ufdc.ufl.edu/UFE0046232

► Analytical and computational prediction tools enable us to design aircraft and spacecraft components with high degree of confidence. While the accuracy of such predictions has… (more)

▼ Analytical and computational prediction tools enable us to design aircraft and spacecraft components with high degree of confidence. While the accuracy of such predictions has been improved over the years, uncertainty continues to be added by new materials and new technology introduced in order to improve performance. This requires us to have reality checks, such as tests, in order to make sure that the prediction tools are reliable enough to ensure safety. While tests can reveal unsafe designs and lead to design correction, these tests are very costly.Therefore, it is important to manage such a design-test-correction cycle effectively.In this dissertation, we consider three important test stages in the lifecycle of an aviation system. First, we dealt with characterization tests that reveal failure modes of new materials or new geometrical arrangements. We investigated the challenge associated with getting the best characterization with a limited number of tests. We have found that replicating tests to attenuate the effect of noise in observation is not necessary because some surrogate models can serve as a noise filter without having replicated data. Instead,we should focus on exploring the design space with different structural configurations in order to discover unknown failure modes. Next, we examined post-design tests for design acceptance followed by possible redesign. We looked at the question of how to balance the desire for better performance achieved by redesign against the cost of redesign. We proposed a design optimization framework that provides tradeoff information between the expected performance improvement by redesign and the probability of redesign, equivalent to the cost of redesign. We also demonstrated that the proposed method can reduce the performance loss due to a conservative reliability estimate. The ultimate test, finally,is whether the structures do not fail in flight. Once an accident occurs, an accident investigation takes place and recommends corrective actions to prevent similar accidents from occurring in the future. With a cost effectiveness study for past accident investigations of airplanes and the Space Shuttle, we conclude that this reactive safety measure is very efficient for a highly safe mode of transportation, i.e., commercial aviation. ( en ) Advisors/Committee Members: HAFTKA,RAPHAEL TUVIA (committee chair), SANKAR,BHAVANI V (committee member), GURLEY,KURTIS R (committee member).

Subjects/Keywords: Accident investigation; Aircraft accidents; Cost efficiency; Cost estimates; Design optimization; Failure modes; Laminates; Modeling; Safety factors; Uncertainty; aviation – design – resource – safty – surrogate

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Matsumura, T. (2013). Effective Safety Measures with Tests Followed by Design Correction for Aerospace Structures. (Doctoral Dissertation). University of Florida. Retrieved from https://ufdc.ufl.edu/UFE0046232

Chicago Manual of Style (16^th Edition):

Matsumura, Taiki. “Effective Safety Measures with Tests Followed by Design Correction for Aerospace Structures.” 2013. Doctoral Dissertation, University of Florida. Accessed March 05, 2021. https://ufdc.ufl.edu/UFE0046232.

MLA Handbook (7^th Edition):

Matsumura, Taiki. “Effective Safety Measures with Tests Followed by Design Correction for Aerospace Structures.” 2013. Web. 05 Mar 2021.

Vancouver:

Matsumura T. Effective Safety Measures with Tests Followed by Design Correction for Aerospace Structures. [Internet] [Doctoral dissertation]. University of Florida; 2013. [cited 2021 Mar 05]. Available from: https://ufdc.ufl.edu/UFE0046232.

Council of Science Editors:

Matsumura T. Effective Safety Measures with Tests Followed by Design Correction for Aerospace Structures. [Doctoral Dissertation]. University of Florida; 2013. Available from: https://ufdc.ufl.edu/UFE0046232

Australian National University

26. Liang, Jiaai. Investigation of Failure Behaviour of a Glass-Fibre Reinforced Thermoplastic Composite .

Degree: 2017, Australian National University

URL: http://hdl.handle.net/1885/143658

► This work focuses on the fibre dominated failure of the woven thermoplastic fibre-reinforced composite. The novel experimental methodology induced failures in different deformation modes for… (more)

Subjects/Keywords: Thermoplastic; Composite; Failure

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APA (6^th Edition):

Liang, J. (2017). Investigation of Failure Behaviour of a Glass-Fibre Reinforced Thermoplastic Composite . (Thesis). Australian National University. Retrieved from http://hdl.handle.net/1885/143658

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Liang, Jiaai. “Investigation of Failure Behaviour of a Glass-Fibre Reinforced Thermoplastic Composite .” 2017. Thesis, Australian National University. Accessed March 05, 2021. http://hdl.handle.net/1885/143658.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Liang, Jiaai. “Investigation of Failure Behaviour of a Glass-Fibre Reinforced Thermoplastic Composite .” 2017. Web. 05 Mar 2021.

Vancouver:

Liang J. Investigation of Failure Behaviour of a Glass-Fibre Reinforced Thermoplastic Composite . [Internet] [Thesis]. Australian National University; 2017. [cited 2021 Mar 05]. Available from: http://hdl.handle.net/1885/143658.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Liang J. Investigation of Failure Behaviour of a Glass-Fibre Reinforced Thermoplastic Composite . [Thesis]. Australian National University; 2017. Available from: http://hdl.handle.net/1885/143658

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Indian Institute of Science

27. Mittal, Anshul. Mechanical Characterization of Adhesively Bonded Jute Composite Joints under Monotonic and Cyclic Loading Conditions.

Degree: MSc Engg, Faculty of Engineering, 2018, Indian Institute of Science

URL: http://etd.iisc.ac.in/handle/2005/3271

► Fiber-reinforced composites comprise an important class of lightweight materials which are finding increasing applications in engineering structures including body components of automobiles and aircraft. Traditionally,… (more)

▼ Fiber-reinforced composites comprise an important class of lightweight materials which are finding increasing applications in engineering structures including body components of automobiles and aircraft. Traditionally, synthetic fibers made of glass, carbon, etc. along with a polymeric resin have constituted the most common composites. However, due to environmental concern, occupational health safety considerations, higher cost, etc., research has been focused on substituting synthetic fibers, especially glass fibers with safer, economic and biodegradable natural fibers. Due to the ease of availability and affordability in terms of cost, woven jute mats, among a wide variety of natural fiber-based reinforcements, offer a good choice in combination with a suitable resin such as polyester or epoxy for fabrication of composite laminates. In structural applications, joining of parts made of jute fiber-reinforced composites (JFRCs) would be a natural requirement. Alternatives to joining processes for metals such as welding, riveting, etc. are required for composites. A joining process of high potential is adhesive bonding which has the advantages of reducing stress concentration, permitting fastening of dissimilar materials, etc. In the present study, adhesively bonded joints of JFRCs and their mechanical behavior are investigated under quasi-static and cyclic loading conditions. Initially, characterization of substrates is carried out under monotonic loading. This is followed by determination of stress- Strain curves, failure load and mean shear strength of bonded joints as functions of joint curing temperature and overlap length using a two-part structural epoxy adhesive. All tests are carried out according to relevant ASTM standards. It has been observed that higher curing temperatures give rise to only marginally high failure load and mean shear stress at failure compared to curing at room temperature. For a given curing temperature, failure load increases while mean shear strength decreases with respect to overlap length in both types of joints. As fatigue failure is a crucial consideration in design, the behavior of adhesively bonded JFRC joints is studied for the first time under cyclic loading conditions leading to the commonly-used S-N curve for characterization of failure of materials at different loading-unloading cycles. Interestingly, the fatigue strength for infinite life of adhesively bonded JFRC joints turns out to be approximately 30% of the quasi-static strength, a correlation which usually applies to materials in general. The effect of joint overlap length on fatigue life is studied and it is observed that the above relation between fatigue and quasi static strength is retained for different overlap lengths. Additionally, insights are provided into failure modes of joints under different loading conditions and for varying overlap lengths. Various empirical predictors such as exponent, power and hybrid models fitting the S-N curve are obtained and their relative efficacy (in terms of Coefficient of… Advisors/Committee Members: Deb, Anindya (advisor).

Subjects/Keywords: Composite Materials; Adhesively Bonded Joints; Jute-fiber Reinforced Polyester Composite Laminates; Epoxy Adhesive; Bonded Joints; Adhesively Bonded Jute Composite Joints; Adhesively-Bonded Jute Fiber-Reinforced Composite; Single Lap Joint; S-N Curve Modeling; LS-DYNA; Fiber-reinforced Composites; Jute Fiber-reinforced Composites (JFRCs); Product Design and Manufacturing

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Mittal, A. (2018). Mechanical Characterization of Adhesively Bonded Jute Composite Joints under Monotonic and Cyclic Loading Conditions. (Masters Thesis). Indian Institute of Science. Retrieved from http://etd.iisc.ac.in/handle/2005/3271

Chicago Manual of Style (16^th Edition):

Mittal, Anshul. “Mechanical Characterization of Adhesively Bonded Jute Composite Joints under Monotonic and Cyclic Loading Conditions.” 2018. Masters Thesis, Indian Institute of Science. Accessed March 05, 2021. http://etd.iisc.ac.in/handle/2005/3271.

MLA Handbook (7^th Edition):

Mittal, Anshul. “Mechanical Characterization of Adhesively Bonded Jute Composite Joints under Monotonic and Cyclic Loading Conditions.” 2018. Web. 05 Mar 2021.

Vancouver:

Mittal A. Mechanical Characterization of Adhesively Bonded Jute Composite Joints under Monotonic and Cyclic Loading Conditions. [Internet] [Masters thesis]. Indian Institute of Science; 2018. [cited 2021 Mar 05]. Available from: http://etd.iisc.ac.in/handle/2005/3271.

Council of Science Editors:

Mittal A. Mechanical Characterization of Adhesively Bonded Jute Composite Joints under Monotonic and Cyclic Loading Conditions. [Masters Thesis]. Indian Institute of Science; 2018. Available from: http://etd.iisc.ac.in/handle/2005/3271

University of Limerick

28. Weidt, David. Computational modelling of energy absorption characteristics of epoxy/CNT nanocomposites.

Degree: 2014, University of Limerick

URL: http://hdl.handle.net/10344/4271

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peer-reviewed

Epoxy-based composite laminates frequently behave as brittle materials under various types of loading, from quasi-static to impact, as they cannot absorb/dissipate enough energy. Matrix… (more)

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peer-reviewed

Epoxy-based composite laminates frequently behave as brittle materials under various types of loading, from quasi-static to impact, as they cannot absorb/dissipate enough energy. Matrix cracks develop due to the brittle nature of epoxy, which after further crack growth can cause delaminations and catastrophic failure. Carbon nanotubes (CNTs) offer promising means for enhancing energy absorption characteristics of epoxy matrices, through CNT crack-bridging, and enhanced nonlinear deformation of the epoxy. However, better understanding of the relationship between process-induced nanocomposite morphologies (e.g. CNT distribution, CNT functionalisation and CNT curvature) and nanocomposite properties is crucial for a successful exploitation of these materials for energy absorbing applications. This work addressed this issue from a computational perspective by focussing on two cases, (1) crack resistance characteristics of epoxy/CNT nanocomposites in tension, and its (2) rate-dependent nonlinear compressive behaviour across different strain rates. It was found in case (1) that CNTs significantly reduce the crack driving force in epoxy and increase strains to failure as a result of the damage propagation at the epoxy-CNT interface. Particularly, enhancements of shear stiffness, shear strength and mode II fracture energy of epoxy-CNT interfaces via CNT functionalisation and minor increases of low sp3-bond densities in the interwall phase of DWCNTs were shown to increase the crack resistance of the nanocomposite. However, major focus was on case (2), and related development of a holistic multiscale modelling approach that links various nanocomposite length scales in a sequential manner. In particular, CNT and interface properties were predicted from molecular mechanics/dynamics and used in a mesoscale model that was formulated within the representative volume element (RVE) concept, nonlinear finite element (FE) framework and employed first-order nonlinear homogenisation. It was found that the nanocomposite nonlinear compressive stress-strain response cannot be accurately captured by 2D RVEs (assuming the plane strain condition), when compared to 3D RVEs, primarily because of the stress transfer effect and the particle interaction accurately captured only in 3D. In general, the multiscale models predicted that the increasing CNT aspect ratio, CNT volume fraction and CNT alignment enhance the nonlinear finite strain compressive response by increasing the yield peak true stress and changing the post-yield deformation behaviour from softening to hardening. Also, the CNT alignment was identified as the major factor for enhancing the nonlinear stress-strain response at both quasi-static and impact rates of strain. However, weak van der Waals (vdWs) bonding at the epoxy/CNT interface as well as CNT curvature significantly limit their reinforcement capabilities as predicted in terms of the nanocomposite Young’s modulus and yield peak stress. The model validation involved the…

Advisors/Committee Members: Lukasz, Figiel, McCarthy, Michael A., IRC.

Subjects/Keywords: epoxy-based laminates; carbon nanotubes; CNTs

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Weidt, D. (2014). Computational modelling of energy absorption characteristics of epoxy/CNT nanocomposites. (Thesis). University of Limerick. Retrieved from http://hdl.handle.net/10344/4271

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Weidt, David. “Computational modelling of energy absorption characteristics of epoxy/CNT nanocomposites.” 2014. Thesis, University of Limerick. Accessed March 05, 2021. http://hdl.handle.net/10344/4271.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Weidt, David. “Computational modelling of energy absorption characteristics of epoxy/CNT nanocomposites.” 2014. Web. 05 Mar 2021.

Vancouver:

Weidt D. Computational modelling of energy absorption characteristics of epoxy/CNT nanocomposites. [Internet] [Thesis]. University of Limerick; 2014. [cited 2021 Mar 05]. Available from: http://hdl.handle.net/10344/4271.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Weidt D. Computational modelling of energy absorption characteristics of epoxy/CNT nanocomposites. [Thesis]. University of Limerick; 2014. Available from: http://hdl.handle.net/10344/4271

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Delft University of Technology

29. Verolme, J.L. The Development of a Design Tool for Fiber Metal Laminate Compression Panels.

Degree: 1995, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:e756a461-fd22-4406-9b1c-3afb76dbad9f ; urn:NBN:nl:ui:24-uuid:e756a461-fd22-4406-9b1c-3afb76dbad9f ; urn:NBN:nl:ui:24-uuid:e756a461-fd22-4406-9b1c-3afb76dbad9f ; http://resolver.tudelft.nl/uuid:e756a461-fd22-4406-9b1c-3afb76dbad9f

Subjects/Keywords: aeronautics; compressive loads; buckling; stiffened panels; failure; design; fiber metal laminates; aluminum

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Verolme, J. L. (1995). The Development of a Design Tool for Fiber Metal Laminate Compression Panels. (Doctoral Dissertation). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:e756a461-fd22-4406-9b1c-3afb76dbad9f ; urn:NBN:nl:ui:24-uuid:e756a461-fd22-4406-9b1c-3afb76dbad9f ; urn:NBN:nl:ui:24-uuid:e756a461-fd22-4406-9b1c-3afb76dbad9f ; http://resolver.tudelft.nl/uuid:e756a461-fd22-4406-9b1c-3afb76dbad9f

Chicago Manual of Style (16^th Edition):

Verolme, J L. “The Development of a Design Tool for Fiber Metal Laminate Compression Panels.” 1995. Doctoral Dissertation, Delft University of Technology. Accessed March 05, 2021. http://resolver.tudelft.nl/uuid:e756a461-fd22-4406-9b1c-3afb76dbad9f ; urn:NBN:nl:ui:24-uuid:e756a461-fd22-4406-9b1c-3afb76dbad9f ; urn:NBN:nl:ui:24-uuid:e756a461-fd22-4406-9b1c-3afb76dbad9f ; http://resolver.tudelft.nl/uuid:e756a461-fd22-4406-9b1c-3afb76dbad9f.

MLA Handbook (7^th Edition):

Verolme, J L. “The Development of a Design Tool for Fiber Metal Laminate Compression Panels.” 1995. Web. 05 Mar 2021.

Vancouver:

Verolme JL. The Development of a Design Tool for Fiber Metal Laminate Compression Panels. [Internet] [Doctoral dissertation]. Delft University of Technology; 1995. [cited 2021 Mar 05]. Available from: http://resolver.tudelft.nl/uuid:e756a461-fd22-4406-9b1c-3afb76dbad9f ; urn:NBN:nl:ui:24-uuid:e756a461-fd22-4406-9b1c-3afb76dbad9f ; urn:NBN:nl:ui:24-uuid:e756a461-fd22-4406-9b1c-3afb76dbad9f ; http://resolver.tudelft.nl/uuid:e756a461-fd22-4406-9b1c-3afb76dbad9f.

Council of Science Editors:

Verolme JL. The Development of a Design Tool for Fiber Metal Laminate Compression Panels. [Doctoral Dissertation]. Delft University of Technology; 1995. Available from: http://resolver.tudelft.nl/uuid:e756a461-fd22-4406-9b1c-3afb76dbad9f ; urn:NBN:nl:ui:24-uuid:e756a461-fd22-4406-9b1c-3afb76dbad9f ; urn:NBN:nl:ui:24-uuid:e756a461-fd22-4406-9b1c-3afb76dbad9f ; http://resolver.tudelft.nl/uuid:e756a461-fd22-4406-9b1c-3afb76dbad9f

Delft University of Technology

30. Tseggai, S. (author). Infinite mining for structural composites.

Degree: 2016, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:226fc8d0-0974-4b51-a779-e145e30e8801

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A wastewater treatment plant is redesigned as an ‘infinite mine’, from which the residues are used for a structural composite. The goal of the project… (more)

Subjects/Keywords: re-use; biomass waste; circular economy; structural composite; material based design

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Tseggai, S. (. (2016). Infinite mining for structural composites. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:226fc8d0-0974-4b51-a779-e145e30e8801

Chicago Manual of Style (16^th Edition):

Tseggai, S (author). “Infinite mining for structural composites.” 2016. Masters Thesis, Delft University of Technology. Accessed March 05, 2021. http://resolver.tudelft.nl/uuid:226fc8d0-0974-4b51-a779-e145e30e8801.

MLA Handbook (7^th Edition):

Tseggai, S (author). “Infinite mining for structural composites.” 2016. Web. 05 Mar 2021.

Vancouver:

Tseggai S(. Infinite mining for structural composites. [Internet] [Masters thesis]. Delft University of Technology; 2016. [cited 2021 Mar 05]. Available from: http://resolver.tudelft.nl/uuid:226fc8d0-0974-4b51-a779-e145e30e8801.

Council of Science Editors:

Tseggai S(. Infinite mining for structural composites. [Masters Thesis]. Delft University of Technology; 2016. Available from: http://resolver.tudelft.nl/uuid:226fc8d0-0974-4b51-a779-e145e30e8801

Open Access Theses and Dissertations