

@mastersthesis {6458,
	title = {On the application of rotating cylinders to micro air vehicles},
	year = {2010},
	note = {U516294},
	school = {The City University (London) (United Kingdom)},
	type = {phdPh.{D}.},
	address = {Ann Arbor},
	abstract = {{\textless}p class=Abstract{\textgreater}An investigation into the feasibility of using rotating circular cylinders as the primary means of generating lift for the class of very small (0.15 n maximum dimension, 50 g weight) unmanned aircraft known as Micro Air Vehicles (MAV) has been carried out. It is hoped that such a design would be able to exploit the large lift generating properties of the rotating cylinder for the purposes of increasing the available payload weight.{\textless}/p{\textgreater} {\textless}p class=Abstract{\textgreater}A preliminary design study was performed to investigate possible configurations for the proposed design, resulting in the selection, for reasons of simplicity, of an arrangement having two rotating cylinders about a central fuselage.{\textless}/p{\textgreater} {\textless}p class=Abstract{\textgreater}Wind tunnel experiments with a simple prototype aircraft were based on the outcome of the preliminary design study and isolated cylinder tests. The tests revealed the effect of propeller wash over the rotors, the influence of the cylinder wake on the tail, and the design of the tail, fin, and fuselage to be of considerable importance to the aerodynamic characteristics and performance of the vehicle.{\textless}/p{\textgreater} {\textless}p class=Abstract{\textgreater}Overall, the study indicated that an aircraft of the proposed configuration and suitable capability was theoretically possible at the MAV scale of flight if an appropriate rotor geometry was chosen. However, the actual construction of a vehicle able to fully provide the desired performance within the constraints placed on platform size and weight was not currently possible using commonly available materials and components. Slightly larger designs (of dimension 0.4 m and weight 250 g) were more realisable, but still lacked in performance. Successful development of this type of design is thus dependent on technological advancement, particularly improvements in power and propulsion systems.{\textless}/p{\textgreater}},
	keywords = {0538:Aerospace engineering, 519716, Aerospace engineering, Applied sciences, Bibliographies, Psychology{\textendash}Abstracting, Statistics},
	url = {http://search.proquest.com/docview/899758700?accountid=14270},
	author = {Badalamenti, C}
}
