Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1993. / Vita. Abstract. Includes bibliographical references (leaves 57-59). Also available via the Internet.

No description available.

Thesis (Ph. D.)--Virginia Polytechnic Institute and State University, 1993. / Vita. Abstract. Includes bibliographical references (leaves 135-138). Also available via the Internet.

Altitude excursions particular to high speed aircraft are investigated in this thesis. An aerodynamic database of the XB-70 is created and a longitudinal linear model is constructed for a high speed cruise flight condition. An examination of the unpiloted aircraft dynamics revealed that the excursions were not due to a poorly handling aircraft. Thus, it is theorized that the excursions are due to pilot vehicle interactions. A classical control method developed a loop closure scheme suitable for acceptable control of the aircraft. The results showed that a pilot should close an inner loop with negative attitude feedback and an outer loop with positive flight path feedback. A modern control method analysis using an optimal control pilot model confirmed the preceding conclusions. Based on these results, the cockpit pitch attitude display resolution should be less than 1° so that the pilot will be able to perform the loop closures necessary for constant altitude flight. / Master of Science

Thesis (Ph. D.)--Florida State University, 2005. / Advisor: Dr. Christopher K. W. Tam, Florida State University, College of Arts and Sciences, Dept. of Mathematics. Title and description from dissertation home page (viewed Sept. 21, 2005). Document formatted into pages; contains xv, 118 pages. Includes bibliographical references.

An approach to aerodynamic configuration optimization is presented for the high-speed civil transport (HSCT). Methods to parameterize the wing shape, fuselage shape and nacelle placement are described. Variable-complexity design strategies are used to combine conceptual and preliminary-level design approaches, both to preserve interdisciplinary design influences and to reduce computational expense. The preliminary-design-level analysis methods used to estimate aircraft performance are described. Conceptual-design-level (approximate) methods are used to estimate aircraft weight, supersonic wave drag and drag due to lift, and landing angle of attack. The methodology is applied to the minimization of the gross weight of an HSCT that flies at Mach 2.4 with a range of 5500 n.mi. Results are presented for wing plan form shape optimization and for combined wing and fuselage optimization with nacelle placement. Case studies include both all-metal wings and advanced composite wings. The results indicate the beneficial effect of simultaneous design of an entire configuration over the optimization of the wing alone and illustrate the capability of the optimization procedure. / Ph. D.