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|Document Type: ||Article|
|Title: ||Adaptive control of a nonlinear aeroelastic system|
|Authors: ||Li, Daochun|
Guo, Shijun J.
|Issue Date: ||2011|
|Citation: ||Daochun Li, Jinwu Xiang, Shijun Guo. Adaptive control of a nonlinear aeroelastic system. Aerospace Science and Technology, Volume 15, Issue 5, July-August 2011, pp343-352.|
|Abstract: ||Aeroelastic two-dimensional wing section with both trailing-edge (TE) and
leading-edge (LE) was investigated in this paper through numerical simulation in
time domain. Structural stiffness and damping in pitch degree of freedom were
represented by nonlinear polynomials. Open-loop limit cycle oscillation (LCO)
characters of two examples were studied, and flutter boundaries with initial
conditions were obtained. Parametric uncertainties in both pitch stiffness and
damping were considered in the design of adaptive control laws to depress LCOs.
Firstly an adaptive controller based on partial feedback linearization was
derived for the wing section with a single TE control surface. Secondly a
structured model reference adaptive control law was designed for the aeroelastic
system with both TE and LE control surfaces. The results show that the designed
control laws are effective for flutter suppression, and that considering damping
uncertainty has positive effect on flutter control. It may reduce convergent
time or increase flutter speed.|
|Appears in Collections:||Staff publications - School of Engineering|
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