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Proceedings Paper

Aeroelastic control with self-straining actuators: continuum models
Author(s): A. V. Balakrishnan
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Paper Abstract

The problem of flutter suppression using self-straining actuators has been analyzed using the full continuum model of Goland-Ashley and the time-domain solution thereof developed. The theory yields a necessary condition for flutter to occur as well as a formula for the divergence speed. Aeroelastic modes are shown to be the roots of the determination of a 3 X 3 matrix, which involves the Theodorsen function which has the entire negative real axis including zero as an essential singularity line. Computer calculations are presented for the numerical values of the Goland model where the first pitching mode flutters. It is shown that the flutter speed increases as the twisting control gain alone increases (no bending control). There is a critical value of the gain beyond which the pitching mode is stable but the bending flutters but the flutter speed increases as the pitching control gain is increased. The situation is reversed for the bending control. Here the flutter speed actually decreases as the bending control gain increases (no pitch control). There is a critical value for the gain beyond which the pitching mode ceases to flutter but the bending mode--actually the `clamped/rolling' mode--flutters but the flutter speed decreases as the gain is increased. The effect is similar whatever the value of the pitching control gain. It is noted that increasing control gain may decrease flutter speed in highest-order modes.

Paper Details

Date Published: 24 July 1998
PDF: 11 pages
Proc. SPIE 3323, Smart Structures and Materials 1998: Mathematics and Control in Smart Structures, (24 July 1998); doi: 10.1117/12.316348
Show Author Affiliations
A. V. Balakrishnan, Univ. of California/Los Angeles (United States)


Published in SPIE Proceedings Vol. 3323:
Smart Structures and Materials 1998: Mathematics and Control in Smart Structures
Vasundara V. Varadan, Editor(s)

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