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A review of Australian and New Zealand investigations on aeronautical fatigue during the period April 2005 to March 2007 /Clark, Graham. January 2007 (has links)
Mode of access: Internet via World Wide Web. Available at http://hdl.handle.net/1947/4741. / "April 2007"
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Analysis and design of composite curved frames /Mason, Brian H., January 1994 (has links)
Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1994. / Vita. Abstract. Includes bibliographical references (leaves 74-76). Also available via the Internet.
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Advanced aircraft service life monitoring method via flight-by-flight load spectraLee, Hongchul. January 2009 (has links)
Thesis (Ph. D.)--State University of New York at Binghamton, Thomas J. Watson School of Engineering and Applied Science, Department of Mechanical Engineering, 2009. / Includes bibliographical references.
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A methodology for robust structural design with application to active aeroelastic wingsZink, Paul Scott 08 1900 (has links)
No description available.
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Velocity measurements on a lifting rotor/airframe configuration in low speed forward flightLiou, Shiuh-Guang 12 1900 (has links)
No description available.
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The effect of end fixity on the stability of structuresIwamoto, Takaya 12 1900 (has links)
No description available.
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Structural health monitoring of aircraft structures: development of a phased array system.Rocha, Bruno Filipe Ferreira Graca 17 October 2011 (has links)
This work consisted in the research and development of a phased array embedded
system for Structural Health Monitoring (SHM) of aircraft structures. This system is
based on piezoelectric (PZT) transducers to excite fast propagating first symmetric Lamb
wave mode (S0) wavefronts. The intent of this research is to contribute for an increasing
safety and efficient operation of aircraft.
Currently applied ultrasound inspections to aircraft structures in operation, as a
conventional Non Destructive Tests and Evaluations (NDT&E) technique, were
reviewed. Such and the previous development of a Lamb wave based SHM system using
PZT transducers in a network configuration served as the basis and for comparison to the
phased array SHM system developed. Lamb waves’ propagation behaviour was carefully
analyzed and a linear PZT phased array SHM system was developed and experimentally
tested. The PZT phased array was applied to representative aircraft structural aluminum
panels, considering also the existence of structural reinforcements and joints. New
techniques, hardware and software, leading to automated damage detection and location,
were researched, developed and implemented.
Tests for damage detection and location were performed, with the introduction of
damages into the specimens being simulated by surface and through the thickness holes
and cuts. Damages with a maximum dimension of 1mm applied cumulatively to the
specimens subject to different boundary conditions were successfully detected and
located. / Graduate
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Fatigue damage assessment of high-usage in-service aircraft fuselage structure /Mosinyi, Bao Rasebolai. Awerbuch, Jonathan. Lau, Alan C. W. Tan, Tein-Min. January 2007 (has links)
Thesis (Ph.D.)--Drexel University, 2007. / Includes abstract and vita. Includes bibliographical references (leaves 278-291).
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An Effective life extension technology for 7xxx series aluminium alloys by laser shock peening (final report) /Liu Qianchu. January 2008 (has links) (PDF)
Mode of access: Internet via World Wide Web. Available at http://hdl.handle.net/1947/9655. / "September 2008" "AR-014-283" "DSTO-TR-2177" Includes bibliographical references.
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A process for function based architecture definition and modelingArmstrong, Michael James. January 2008 (has links)
Thesis (M. S.)--Aerospace Engineering, Georgia Institute of Technology, 2008. / Committee Chair: Mavris, Dimitri; Committee Member: Garcia, Elena; Committee Member: Soban, Danielle. Part of the SMARTech Electronic Thesis and Dissertation Collection.
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