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Lift Control Using MEMS-Based Moving Trailing-Edge Tabs

[+] Author Affiliations
C. P. van Dam, C. Bauer

University of California at Davis, Davis, CA

D. T. Yen Nakafuji

Lawrence Livermore National Laboratory, Livermore, CA

Paper No. IMECE2002-33990, pp. 235-242; 8 pages
doi:10.1115/IMECE2002-33990
From:
  • ASME 2002 International Mechanical Engineering Congress and Exposition
  • Adaptive Structures and Materials Systems
  • New Orleans, Louisiana, USA, November 17–22, 2002
  • Conference Sponsors: Aerospace Division
  • ISBN: 0-7918-3625-8 | eISBN: 0-7918-1691-5, 0-7918-1692-3, 0-7918-1693-1
  • Copyright © 2002 by ASME

abstract

Micro-electro-mechanical (MEM) translational tabs are introduced for active lift control on aircraft. These tabs are mounted near the trailing edge of lifting surfaces such as aircraft wings and tails, deploy approximately normal to the surface, and have a maximum deployment height on the order of one percent of the section chord. Deployment of the tab effectively changes the sectional camber, thereby changing the aerodynamic characteristics of a lifting surface. Tabs with said deployment height generate a change in the section lift coefficient of approximately ±0.3. The microtab design and the techniques used to fabricate and test the tabs are presented.

Copyright © 2002 by ASME

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