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

By: Nasa, National Aeronautics and Space Adm

This is a final report on the research studies, "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.Waszak, Martin R. (Technical Monitor) and Shkarayev, Sergey and Null, William and Wagner, MatthewLangley Research CenterADAPTATION; AERODYNAMICS; TECHNOLOGY ASSESSMENT; LOW REYNOLDS NUMBER; RELIABILITY ANALYSIS; CAMBERED WINGS; WIND TUNNEL TESTS; SERVOMOTORS; FLIGHT TESTS

• Format: Paperback
• Language: English
• ISBN: 1723827487
• ISBN13: 9781723827488
• Release Date: January 1
• Publisher: Independently Published
• Length: 42 Pages
• Weight: 0.27 lbs.
• Dimensions: 0.1" x 8.5" x 11.0"