Micro-Aerial Vehicle
The goal of this project was to design, build and test a Micro-Aerial Vehicle (MAV) for competition in the 2002 International MAV Competition at Brigham Yound University. Topics researched include: gas and electric propulsion, low Reynolds Number aerodynamics, low aspect ratio wings, and micro radio controled electronics. Early comparisons of gas and electric propulsion systems indicated that an electric system would be more reliable, and weigh less at the cost of reduced thrust. An online airfoil database provided by the NASG was used to compare low Reynolds Number airfoils. From these comparisons the Wortmann FX60100 was chosen. Reasearch into low aspect ratio wing effects indicated that wing efficiency would be severly reduced and designs accounted for this. Light weight propulsion and control components were incorporated into the design. Common lithium batteries were chosen as the power source.
An iterative design process was used to generate several concept designs. These designs were refined as components were selected and aerodynamics analysis progressed. Analytical factors considered included: component placement and parameters, wing geometry, sizing, construction techniques, control surface size and location, center of gravity location, and tail placement.
The most promising concept design was fabricated. Windtunnel, lasso, and free flight tests were conducted to verify analytical results. Experimental results were used to further refine the design and augment the overall quality of the aircraft.
The final MAV design had a maximum dimension of 22.4 centimeters and a weight of 77 grams. The plane flew several short flights but was not completed in time for the 2002 MAV competition.