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Analysis of Actuator Requirements for Micro UAV Telescoping Wings

[+] Author Affiliations
Terry Sanderson

Raytheon Missile Systems; University of Arizona, Tucson, AZ

Paper No. IMECE2007-43535, pp. 363-368; 6 pages
  • ASME 2007 International Mechanical Engineering Congress and Exposition
  • Volume 10: Mechanics of Solids and Structures, Parts A and B
  • Seattle, Washington, USA, November 11–15, 2007
  • Conference Sponsors: ASME
  • ISBN: 0-7918-4304-1 | eISBN: 0-7918-3812-9
  • Copyright © 2007 by ASME


For many micro UAV uses, maximum air vehicle endurance and/or range is a primary requirement. Maximizing endurance and range requires long span, high aspect ratio wings, but for man-portable and tube launched UAV applications there is rarely enough room to stow adequate wing span. In this work, a simple slip fit telescoping shell wing concept, appropriate for extending the wing span of micro UAVs, was analyzed to determine the actuator force-displacement and power consumption relationships, including consideration of the variable wing load distribution that occurs on a telescoping span wing. The required time scale for actuation is also discussed. These results are a necessary part of selecting an appropriate actuator, whether it is an advanced “smart material” actuator or something as simple as a one-way, one-time coil spring. It was found that a wing span increase of about 85% is probably the optimum amount of extension that can be achieved using this telescoping shell wing concept.

Copyright © 2007 by ASME



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