Thesis (Ph. D.)--West Virginia University, 2009. / Title from document title page. Document formatted into pages; contains xiv, 118 p. : ill. (some col.). Includes abstract. Includes bibliographical references (p. 109-118).

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Thesis--Air Command and Staff College, Air University, Maxwell Air Force Base, April 2005. / "April 2007." Thesis advisor: Lt. Col. James A. Rothenflue. Performed by Air University Press (AUL/LP), Maxwell Air Force Base, Montgomery, Ala. "AU/ACSC/2927/2004-05." Includes bibliographical references (p. 35-37). Also available online from the Air University Research Information Management System (AURIMS) and the DTIC Online Web sites.

Thesis (M.S. in Computer Science) Naval Postgraduate School, September 1995. / "September 1995." Thesis advisor(s): Michael J. Zyda, John S. Falby. Includes bibliographical references (p. 107). Also available online.

Thesis (M.S. in Information Technology Management)--Naval Postgraduate School, June 2005. / Thesis Advisor(s): Joseph A. Sullivan, Rudolph Darken. Includes bibliographical references (p. 113-115). Also available online.

Thesis (MTech (Mechanical Engineering))--Cape Peninsula University of Technology, 2010. / The Cape Peninsula University of Technology (CPUT) Advanced Manufacturing and Technology Laboratory (AMTL) developed an Unmanned Aerial Vehicle (UAV) Technology Demonstrator for the purpose of testing and maturing adaptronic devices. Extending the flight envelope of this unmanned aerial vehicle by increasing its range and endurance is the next step in its development. A seamless variable angle of incidence (sVAI) morphing wing is proposed to increase the lift with little coupling to drag during takeoff; and decrease the drag with little effect on lift during climb, thus increasing the total flight performance of the aircraft. CAD models of the conceptualized sVAI wing and a conventional (CON) wing, as used on the Technology Demonstrator, were modeled. Numerical analyses on these CAD models showed that the sVAI wing concept at a 4° twist decreased the ground roll distance and stall velocity by ±17% and ±31% respectively, as compared to the CON wing in standard takeoff configuration. This allowed for ± 11.7% less power required for takeoff allowing the aircraft to get to its operational altitude quicker, thus saving fuel and reducing energy losses; and increasing range and endurance. The results also showed that the sVAI wing concept could reduce the drag during climb by ± 14%, but the lift is also proportionately reduced thus having little improvement on the climb phase of flight performance. A prototype of the morphing wing was then conceptualized and designed, using a 3D CADmodeler, and then manufactured. The product development chain produced for this morphing wing included two rapid prototyping machines and reverse engineering technologies. The chain allowed for the rapid manufacturing of light weight and intricate parts. The manufactured wing is then incorporated into a test rig to compare the actual morphing ability of the prototype to the theoretical morphing ability of the CADmodel, and thus make flight performance predictions of the actual vehicle. 3D scans were taken of the prototype and then converted to 3D CADfiles. The geometrical and topographical deformation of the prototype was then compared to that of the CAD model showing an average difference of ±1.2% and ±3% at maximum positive and negative configurations, respectively. This allowed one to make the prediction that the sVAI wing will increase the performance of the Technology Demonstrator.

A procedure is developed which offers the potential to validate aircraft simulation models using noisy flight test measurements. The proposed validation procedure is based on the instrumental variable parameter identification method. The instrumental variable method requires a choice of "instruments." For this research, the "instruments" are chosen using the response predicted by an available simulation model. With the “instruments” chosen from the predicted response, it is shown that the parameter estimates are correlated with only the measured input noise vector. In contrast, the generally used least-squares approach is shown to be correlated with both the state and input noise vectors. Several studies are presented to demonstrate the utility of the validation procedure. These studies include input variations and noise variations. The method is demonstrated using longitudinal and lateral/directional axis cases derived from a nonlinear simulation of a high performance fighter aircraft. The results are presented using time response comparisons, eigenvalue comparisons, and identified stability derivative comparisons. The case study results confirm that the instrumental variable method performs better than the least-squares technique when the state noise level is high and the input noise level is relatively low. / Master of Science

International Telemetering Conference Proceedings / October 26-29, 1998 / Town & Country Resort Hotel and Convention Center, San Diego, California / Dryden real-time flight simulators encompass the simulation of pulse code modulation (PCM) telemetry signals. This paper presents a new method whereby the calibration polynomial (from first to sixth order), representing the conversion from counts to engineering units (EU), is numerically inverted in real time. The result is less than onecount error for valid EU inputs. The Newton-Raphson method is used to numerically invert the polynomial. A reverse linear interpolation between the EU limits is used to obtain an initial value for the desired telemetry count. The method presented here is not new. What is new is how classical numerical techniques are optimized to take advantage of modern computer power to perform the desired calculations in real time. This technique makes the method simple to understand and implement. There are no interpolation tables to store in memory as in traditional methods. The NASA F-15 simulation converts and transmits over 1000 parameters at 80 times/sec. This paper presents algorithm development, FORTRAN code, and performance results.

The Chromakey Augmented Virtual Environment (ChrAVE) 3.0 System is a training system created to augment initial, refresher, and proficiency training in helicopter aviation using accurate simulation. Designed around advanced chromakey technologies, this system is deployable, scalable, and flexible, allowing for use in austere environments such as aboard ship or in forward deployed locations. The goal of system development was to prove that a collection of commercially available components could be integrated along with the Virtual Environment Helicopter (VEHELO) 2.0 software package in order to provide a realistic simulated environment in which pilots can practice skill sets that are critical to mission success. The focus of this thesis is the validation of ChrAVE 3.0 as an augmented trainer that can be adapted for use inside an actual aircraft cockpit. By placing the pilot in the most realistic simulation available ChrAVE 3.0 will enhance development of skills such as Terrain Appreciation, Crew Resource Management (CRM), and Situational Awareness (SA). Continuing past research, this thesis will analyze empirical data collected from training flights to further prove its value as an instructional tool. ChrAVE 3.0 is housed in three man-portable containers and can be set up within minutes with little or no prior experience.

Thesis. 1978. E.A.A.--Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics. / MICROFICHE COPY AVAILABLE IN ARCHIVES AND AERONAUTICS. / Bibliography: leaves 130-133. / by C.W. Acree, Jr. / E.A.A.