Development of Micro Air Vehicle Technology With In-Flight Adaptive-Wing Structure

This is a final report on the research studies completed under NASA Grant NAG 1-03045, “Development of Micro Air Vehicle Technology with In-Flight Adaptrive-Wing Structure.” This project involved the development of variable-camber technology to achieve efficient design of micro air vehicles. Specifically, it focused on the following topics: 1) Low Reynolds number wind tunnel testing of cambered-plate wings. 2) Theoretical performance analysis of micro air vehicles. 3) Design of a variable-camber MAV actuated by micro servos. 4) Test flights of a variable-camber MAV. The results have been disseminated in the form of papers and seminar presentations and 2 master’s theses (see the list of publications). The grant also played an important role in the organization of the 2004 International Micro Air Vehicle Competition hosted by the University of Arizona on April 9-10, 2004.