Thesis (Ph.D.)--University of Wollongong, 2005. / Typescript. Includes bibliographical references: p. 229-243.

Thesis (Ph. D.)--Florida State University, 2005. / Advisor: Dr. Anjaneyulu Krothapalli, Florida State University, College of Engineering, Dept. of Mechanical Engineering. Title and description from dissertation home page (viewed June 14, 2005). Document formatted into pages; contains xx, 224 pages. Includes bibliographical references.

Thesis (Ph.D.)--RAND Graduate School, 2006. / Includes bibliographical references.

Thesis (Ph. D.)--University of Washington, 2006. / Vita. Includes bibliographical references (leaves 274-285).

A detailed study is proposed for understanding the use of aircraft deicing and anti-icing fluids (ADAF) and optimal use of these fluids in airport operations. A detailed literature review of past and current technologies is conducted and possible opportunities to improve the use of ADAF and relevant recommendations are derived. Mathematical optimization models (e.g. MINLP with binary variables) based on a variety of objectives, which deal with exhaustive sets of system constraints are formulated, developed and applied to case studies. One real-life case study area which routinely carries out aircraft deicing is used for testing the mathematical optimization formulations for optimal use of fluids under budgetary and environmental compliance constraints. Based on the recommendations from one of the best optimization model formulations it is hoped that it will be used for a real-time implementation. Results from these formulations show the models to be robust and applicable. / by Scott E. Ornitz. / Thesis (M.S.C.S.)--Florida Atlantic University, 2009. / Includes bibliography. / Electronic reproduction. Boca Raton, Fla., 2009. Mode of access: World Wide Web.

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The objective of this research is to investigate the techniques and payoffs of integrated aircraft design. Lifting line theory and beam theory are used for the analysis of the aerodynamics and the structures of a composite sailplane wing. The wing is described by 33 - 34 design variables which involve the planform geometry, the twist distribution, and thicknesses of the spar caps, spar webs, and the skin at various stations along the wing. The wing design must satisfy 30 â 31 aeroelastic, structural, aerodynamic, and performance constraints. Two design procedures are investigated. The first, referred to as the iterative, sequential procedure, involves optimizing the aerodynamic design for maximum average cross-country speed at E1 constant structural weight, and then optimizing the the structural design of the resulting wing geometry for minimum weight. This value is then used in another aerodynamic optimization, and the process continues iteratively until the weight converges. The other procedure, the integrated one, simultaneously optimizes the aerodynamic and the structural design variables for either maximum average cross-country speed or minimum weight. The integrated procedure was able to improve the value of the objective function obtained by the iterative procedure in all cases. This shows The objective of this research is to investigate the techniques and payoffs of integrated aircraft design. Lifting line theory and beam theory are used for the analysis of the aerodynamics and the structures of a composite sailplane wing. The wing is described by 33 - 34 design variables which involve the planform geometry, the twist distribution, and thicknesses of the spar caps, spar webs, and the skin at various stations along the wing. The wing design must satisfy 30 â 31 aeroelastic, structural, aerodynamic, and performance constraints. Two design procedures are investigated. The first, referred to as the iterative, sequential procedure, involves optimizing the aerodynamic design for maximum average cross-country speed at E1 constant structural weight, and then optimizing the the structural design of the resulting wing geometry for minimum weight. This value is then used in another aerodynamic optimization, and the process continues iteratively until the weight converges. The other procedure, the integrated one, simultaneously optimizes the aerodynamic and the structural design variables for either maximum average cross-country speed or minimum weight. The integrated procedure was able to improve the value of the objective function obtained by the iterative procedure in all cases. This shows that definite benefits can be gained from taking advantage of aerodynamic/structural interactions during the design process. / Master of Science

Thesis: Sc. D., Massachusetts Institute of Technology. Department of Aeronautical Engineering, 1916. / MIT Institue Archives Thesis Coll.: copy is the Smithsoniam Institution publication. / Publication 2414. Hodgkins fund. Originaly prepared by Hunsaker as his Eng. D. Thesis, Massachusetts Institute of Technology, Dept. of Aeronautical Engineering, 1916. According to the MIT Registrar's Office, this degree was changed to an Sc.D., 1923 June 12. Original thesis did not contain the three plates. / by Jerome C. Hunsaker ... assisted by T. H. Huff, S. B., D. W. Douglas, S. B., H. K. Chow, S. M., and V. E. Clark. / Sc. D.

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