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Macro aerodynamic devices controlled by micro systems

Lee, Gwo-Bin and Jiang, F. K. and Tsao, Thomas and Tai, Y.-C. and Ho, C. M. (1997) Macro aerodynamic devices controlled by micro systems. In: IEEE Aerospace Conference Proceedings, 1997. Vol.3. IEEE , pp. 255-263. ISBN 0-7803-3741-7 http://resolver.caltech.edu/CaltechAUTHORS:GWOieeeac97

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Abstract

Micro-ElectroMechanical-Systems (MEMS) have emerged as a major enabling technology across the engineering disciplines. In this study, the possibility of applying MEMS to the aerodynamic field was explored. We have demonstrated that microtransducers can be used to control the motion of a delta wing in a wind tunnel and can even maneuver a scaled aircraft in flight tests. The main advantage of using micro actuators to replace the traditional control surface is the significant reduction of radar cross-sections. At a high angle of attack, a large portion of the suction loading on a delta wing is contributed by the leading edge separation vortices which originate from thin boundary layers at the leading edge. We used microactuators with a thickness comparable to that of the boundary layer in order to alter the separation process and thus achieved control of the global motion by minute perturbations.


Item Type:Book Section
Additional Information:© 1997 IEEE. Reprinted with permission. This work is supported by the DARPA ETO office.
Subject Keywords:aircraft testing; microactuators; military aircraft; position control; transducers; wind tunnels
Record Number:CaltechAUTHORS:GWOieeeac97
Persistent URL:http://resolver.caltech.edu/CaltechAUTHORS:GWOieeeac97
Alternative URL:http://dx.doi.org/10.1109/AERO.1997.574871
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:1762
Collection:CaltechAUTHORS
Deposited By: Archive Administrator
Deposited On:17 Feb 2006
Last Modified:26 Dec 2012 08:45

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