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You searched for subject:(Aircraft composite laminates). Showing records 1 – 6 of 6 total matches.

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1. Kelkar, Ajit Dhundiraj. Analyses of Quasi-Isotropic Composite Plates Under Quasi-Static Point Loads Simulating Low-Velocity Impact Phenomena.

Degree: PhD, Mechanical & Aerospace Engineering, 1985, Old Dominion University

Composite laminates have high strength to density ratios that make them attractive for use in aircraft structures. However, the damage tolerance of these materials… (more)

Subjects/Keywords: Composite laminates; Point loads; Aircraft; Laminates; Applied Mechanics

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

APA (6th Edition):

Kelkar, A. D. (1985). Analyses of Quasi-Isotropic Composite Plates Under Quasi-Static Point Loads Simulating Low-Velocity Impact Phenomena. (Doctoral Dissertation). Old Dominion University. Retrieved from https://digitalcommons.odu.edu/mae_etds/245

Chicago Manual of Style (16th Edition):

Kelkar, Ajit Dhundiraj. “Analyses of Quasi-Isotropic Composite Plates Under Quasi-Static Point Loads Simulating Low-Velocity Impact Phenomena.” 1985. Doctoral Dissertation, Old Dominion University. Accessed October 23, 2019. https://digitalcommons.odu.edu/mae_etds/245.

MLA Handbook (7th Edition):

Kelkar, Ajit Dhundiraj. “Analyses of Quasi-Isotropic Composite Plates Under Quasi-Static Point Loads Simulating Low-Velocity Impact Phenomena.” 1985. Web. 23 Oct 2019.

Vancouver:

Kelkar AD. Analyses of Quasi-Isotropic Composite Plates Under Quasi-Static Point Loads Simulating Low-Velocity Impact Phenomena. [Internet] [Doctoral dissertation]. Old Dominion University; 1985. [cited 2019 Oct 23]. Available from: https://digitalcommons.odu.edu/mae_etds/245.

Council of Science Editors:

Kelkar AD. Analyses of Quasi-Isotropic Composite Plates Under Quasi-Static Point Loads Simulating Low-Velocity Impact Phenomena. [Doctoral Dissertation]. Old Dominion University; 1985. Available from: https://digitalcommons.odu.edu/mae_etds/245


Indian Institute of Science

2. Sudha, J. Fatigue Damage Characterization Of Carbon/Epoxy Laminates Under Spectrum Loading.

Degree: 2007, Indian Institute of Science

 Fibre Reinforced Polymer Composites are extensively used in aircraft structures because of its high specific stiffness, high specific strength and tailorability. Though Fibre Reinforced Polymers… (more)

Subjects/Keywords: Carbon/Epoxy Laminates - Fatigue; Carbon Fiber Reinforced Polymer Laminates; Carbon Fibre Reinforced Epoxy Composites; Aircraft-Composite Structures - Fatigue; Aerospace Materials - Fatigue; Dynamic Mechanical Analysis; Materials Science

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APA (6th Edition):

Sudha, J. (2007). Fatigue Damage Characterization Of Carbon/Epoxy Laminates Under Spectrum Loading. (Thesis). Indian Institute of Science. Retrieved from http://hdl.handle.net/2005/2257

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

Chicago Manual of Style (16th Edition):

Sudha, J. “Fatigue Damage Characterization Of Carbon/Epoxy Laminates Under Spectrum Loading.” 2007. Thesis, Indian Institute of Science. Accessed October 23, 2019. http://hdl.handle.net/2005/2257.

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

MLA Handbook (7th Edition):

Sudha, J. “Fatigue Damage Characterization Of Carbon/Epoxy Laminates Under Spectrum Loading.” 2007. Web. 23 Oct 2019.

Vancouver:

Sudha J. Fatigue Damage Characterization Of Carbon/Epoxy Laminates Under Spectrum Loading. [Internet] [Thesis]. Indian Institute of Science; 2007. [cited 2019 Oct 23]. Available from: http://hdl.handle.net/2005/2257.

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

Council of Science Editors:

Sudha J. Fatigue Damage Characterization Of Carbon/Epoxy Laminates Under Spectrum Loading. [Thesis]. Indian Institute of Science; 2007. Available from: http://hdl.handle.net/2005/2257

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


University of Florida

3. Nadel, Adam. A Comparison of an Integrally Stiffened Beaded Panel Made From Stretch Broken Carbon Fiber and a Honeycomb Core Sandwich Panel.

Degree: MS, Aerospace Engineering - Mechanical and Aerospace Engineering, 2009, University of Florida

 Honeycomb core sandwich panels are commonly used in aircraft construction. They provide a buckling-resistant, lighter-weight alternative to the classic skin and stringer aircraft construction. However,… (more)

Subjects/Keywords: Aircraft; Carbon fibers; Corrosion; Geometry; Honeycomb cores; Honeycombs; Laminates; Sandwiches; Skin; Structural deflection; aircraft, bead, broken, carbon, composite, core, corrosion, fiber, honeycomb, panel, sandwich, sbcf, skin, stretch

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

APA (6th Edition):

Nadel, A. (2009). A Comparison of an Integrally Stiffened Beaded Panel Made From Stretch Broken Carbon Fiber and a Honeycomb Core Sandwich Panel. (Masters Thesis). University of Florida. Retrieved from http://ufdc.ufl.edu/UFE0041283

Chicago Manual of Style (16th Edition):

Nadel, Adam. “A Comparison of an Integrally Stiffened Beaded Panel Made From Stretch Broken Carbon Fiber and a Honeycomb Core Sandwich Panel.” 2009. Masters Thesis, University of Florida. Accessed October 23, 2019. http://ufdc.ufl.edu/UFE0041283.

MLA Handbook (7th Edition):

Nadel, Adam. “A Comparison of an Integrally Stiffened Beaded Panel Made From Stretch Broken Carbon Fiber and a Honeycomb Core Sandwich Panel.” 2009. Web. 23 Oct 2019.

Vancouver:

Nadel A. A Comparison of an Integrally Stiffened Beaded Panel Made From Stretch Broken Carbon Fiber and a Honeycomb Core Sandwich Panel. [Internet] [Masters thesis]. University of Florida; 2009. [cited 2019 Oct 23]. Available from: http://ufdc.ufl.edu/UFE0041283.

Council of Science Editors:

Nadel A. A Comparison of an Integrally Stiffened Beaded Panel Made From Stretch Broken Carbon Fiber and a Honeycomb Core Sandwich Panel. [Masters Thesis]. University of Florida; 2009. Available from: http://ufdc.ufl.edu/UFE0041283

4. Gatti, Maria Cristina Adami. Tenacidade à fratura translaminar dinâmica de um laminado híbrido metal-fibra titânio-grafite de grau aeronáutico.

Degree: PhD, Ciência e Engenharia de Materiais, 2009, University of São Paulo

Diversos critérios de tenacidade à fratura translaminar dinâmica foram determinados para o laminado híbrido metal-fibra TiGra, empregando-se conceitos e metodologias da Mecânica da Fratura Elástica… (more)

Subjects/Keywords: Aircraft composite laminates; Dynamic fracture toughness; Ensaio de Impacto Charpy; Instrumented Charpy impact testing; Laminados compósitos; Materiais aeronáuticos; Tenacidade à fratura dinâmica; Translaminar fracture

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

APA (6th Edition):

Gatti, M. C. A. (2009). Tenacidade à fratura translaminar dinâmica de um laminado híbrido metal-fibra titânio-grafite de grau aeronáutico. (Doctoral Dissertation). University of São Paulo. Retrieved from http://www.teses.usp.br/teses/disponiveis/88/88131/tde-09112009-152941/ ;

Chicago Manual of Style (16th Edition):

Gatti, Maria Cristina Adami. “Tenacidade à fratura translaminar dinâmica de um laminado híbrido metal-fibra titânio-grafite de grau aeronáutico.” 2009. Doctoral Dissertation, University of São Paulo. Accessed October 23, 2019. http://www.teses.usp.br/teses/disponiveis/88/88131/tde-09112009-152941/ ;.

MLA Handbook (7th Edition):

Gatti, Maria Cristina Adami. “Tenacidade à fratura translaminar dinâmica de um laminado híbrido metal-fibra titânio-grafite de grau aeronáutico.” 2009. Web. 23 Oct 2019.

Vancouver:

Gatti MCA. Tenacidade à fratura translaminar dinâmica de um laminado híbrido metal-fibra titânio-grafite de grau aeronáutico. [Internet] [Doctoral dissertation]. University of São Paulo; 2009. [cited 2019 Oct 23]. Available from: http://www.teses.usp.br/teses/disponiveis/88/88131/tde-09112009-152941/ ;.

Council of Science Editors:

Gatti MCA. Tenacidade à fratura translaminar dinâmica de um laminado híbrido metal-fibra titânio-grafite de grau aeronáutico. [Doctoral Dissertation]. University of São Paulo; 2009. Available from: http://www.teses.usp.br/teses/disponiveis/88/88131/tde-09112009-152941/ ;


Indian Institute of Science

5. Sudha, J. Fatigue Damage Characterization Of Carbon/Epoxy Laminates Under Spectrum Loading.

Degree: 2007, Indian Institute of Science

 Fibre Reinforced Polymer Composites are extensively used in aircraft structures because of its high specific stiffness, high specific strength and tailorability. Though Fibre Reinforced Polymers… (more)

Subjects/Keywords: Carbon/Epoxy Laminates - Fatigue; Carbon Fiber Reinforced Polymer Laminates; Carbon Fibre Reinforced Epoxy Composites; Aircraft-Composite Structures - Fatigue; Aerospace Materials - Fatigue; Dynamic Mechanical Analysis; Materials Science

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Sudha, J. (2007). Fatigue Damage Characterization Of Carbon/Epoxy Laminates Under Spectrum Loading. (Thesis). Indian Institute of Science. Retrieved from http://etd.iisc.ernet.in/handle/2005/2257 ; http://etd.ncsi.iisc.ernet.in/abstracts/2878/G21042-Abs.pdf

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

Chicago Manual of Style (16th Edition):

Sudha, J. “Fatigue Damage Characterization Of Carbon/Epoxy Laminates Under Spectrum Loading.” 2007. Thesis, Indian Institute of Science. Accessed October 23, 2019. http://etd.iisc.ernet.in/handle/2005/2257 ; http://etd.ncsi.iisc.ernet.in/abstracts/2878/G21042-Abs.pdf.

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

MLA Handbook (7th Edition):

Sudha, J. “Fatigue Damage Characterization Of Carbon/Epoxy Laminates Under Spectrum Loading.” 2007. Web. 23 Oct 2019.

Vancouver:

Sudha J. Fatigue Damage Characterization Of Carbon/Epoxy Laminates Under Spectrum Loading. [Internet] [Thesis]. Indian Institute of Science; 2007. [cited 2019 Oct 23]. Available from: http://etd.iisc.ernet.in/handle/2005/2257 ; http://etd.ncsi.iisc.ernet.in/abstracts/2878/G21042-Abs.pdf.

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

Council of Science Editors:

Sudha J. Fatigue Damage Characterization Of Carbon/Epoxy Laminates Under Spectrum Loading. [Thesis]. Indian Institute of Science; 2007. Available from: http://etd.iisc.ernet.in/handle/2005/2257 ; http://etd.ncsi.iisc.ernet.in/abstracts/2878/G21042-Abs.pdf

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


University of Florida

6. Liu, Boyang, 1966- ( Dissertant ). Two-level optimization of composite wing structures based on panel genetic optimization.

Degree: PhD, Aerospace Engineering, Mechanics, and Engineering Science, 2001, University of Florida

 The design of complex composite structures used in aerospace or automotive vehicles presents a major challenge in terms of computational cost. Discrete choices for ply… (more)

Subjects/Keywords: Aircraft wings; Buckling; Composite materials; Contiguity; Design optimization; Genetic algorithms; Laminates; Permutations; Skin; Stacking sequence

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

APA (6th Edition):

Liu, Boyang, 1. (. D. ). (2001). Two-level optimization of composite wing structures based on panel genetic optimization. (Doctoral Dissertation). University of Florida. Retrieved from http://ufdc.ufl.edu/UF00100791

Chicago Manual of Style (16th Edition):

Liu, Boyang, 1966- ( Dissertant ). “Two-level optimization of composite wing structures based on panel genetic optimization.” 2001. Doctoral Dissertation, University of Florida. Accessed October 23, 2019. http://ufdc.ufl.edu/UF00100791.

MLA Handbook (7th Edition):

Liu, Boyang, 1966- ( Dissertant ). “Two-level optimization of composite wing structures based on panel genetic optimization.” 2001. Web. 23 Oct 2019.

Vancouver:

Liu, Boyang 1(D). Two-level optimization of composite wing structures based on panel genetic optimization. [Internet] [Doctoral dissertation]. University of Florida; 2001. [cited 2019 Oct 23]. Available from: http://ufdc.ufl.edu/UF00100791.

Council of Science Editors:

Liu, Boyang 1(D). Two-level optimization of composite wing structures based on panel genetic optimization. [Doctoral Dissertation]. University of Florida; 2001. Available from: http://ufdc.ufl.edu/UF00100791

.