Thesis (M. Arch.)--University of Hong Kong, 1995. / Includes special report study entitled: Design of the sun-tracker. Includes bibliographical references.

Thesis (M.Arch.)--University of Hong Kong, 1995. / Includes special report study entitled : Design of the sun-tracker. Includes bibliographical references. Also available in print.

A real-time energy management display is developed and evaluated, and the feasibility and utility of the display in providing real-time guidance and information on the aircraft’s energy state was investigated. Flight simulations were conducted with the UTSI Aviation Systems research flight simulator to validate the display and evaluate its utility for flying along constant specific excess power contours, and directly obtaining specific excess power contours from level acceleration flight test. The display was evaluated for flying optimal paths. This study considered the energy state of the aircraft from the point of view of the relation that exists between specific excess power and the forces in flight. The approach yields as one result a cubic function for the specific excess power, Ps, of the aircraft. We then directly solve for velocity, V as the control parameter for a given Ps, as a function of altitude, H. This technique is then used to build a real-time energy management display that provides guidance and real-time information of the aircraft’s energy state. Flight simulation results proved the display to be successful in obtaining direct Ps contours from level acceleration flight tests and in providing guidance for flights along constant Ps contours at low airspeeds although it was difficult to keep the Ps constant. However flights along zero Ps contours and along constant Ps contours at very high speeds were not successful. The application of the display in flying optimal paths was also not very successful with the current structure of the display. This was due to the fact that the display’s guidance information is provided in a digital format which is very sensitive, and tracking a number for guidance is nearly impossible.

Project Solaris is a unique student project that is carried out at Mälardalen University, Sweden. The project involves all the phases of the development and construction of a solar-powered UAV (unmanned aerial vehicle), where every subproject involves a specific assignment in the development-process. The primary task of this project is the investigation of the energy balance for the entire aircraft. In other words, calculating the power that is generated through the solar panels, and the required power to fly the aircraft and operate all the electronic systems. The total thrust from the motors is 6,6 oz (1,834 N) which is completely sufficient to fly the aircraft during cruise-flight and take-off flight. And the provided energy from the solar panels (87,8381 Wp) is enough to operate the motors and the necessary system, including the battery-charging. As a result of these factors, the aircraft will theoretically have the ability to fly “constantly” without the need of landing. The presented data shows the capacity of the aircraft and all the essential parameters. The calculations have been based on the solar-powered UAV Zephyr Qinetiq, due to the fact that Zephyr successfully have managed to fly both day and night. However, the design of the Solaris aircraft has been a little different, regarding the battery and motor choice. But it’s also important to understand that the installation of the exact same components is not fully necessary to achieve the same goal, which is a 24h-flight.

Dynamic aspects of plate structures

No description available.

Thesis: M.S., Massachusetts Institute of Technology, Department of Aeronautical Engineering, 1924 / by James H. Doolittle. / M.S. / M.S. Massachusetts Institute of Technology, Department of Aeronautical Engineering

Thesis: M.S., Massachusetts Institute of Technology, Department of Aeronautical Engineering, 1929 / Includes bibliographical references (leaf 72). / by Nolan M. Kindell, Dixie Kiefer and Marion E. Crist. / M.S. / M.S. Massachusetts Institute of Technology, Department of Aeronautical Engineering

Thesis: M.S., Massachusetts Institute of Technology, Department of Aeronautical Engineering, 1947 / by Shepard M. Arkin. / M.S. / M.S. Massachusetts Institute of Technology, Department of Aeronautical Engineering

Thesis: M.S., Massachusetts Institute of Technology, Department of Aeronautical Engineering, 1947 / Bibliography: leaves 83-84. / by George Fotieo, Herbert J. Cunningham. / M.S. / M.S. Massachusetts Institute of Technology, Department of Aeronautical Engineering