Adaptive control of a nonlinear aeroelastic system

Show simple item record Li, Daochun - Xiang, Jinwu - Guo, Shijun J. - 2011-11-13T23:13:48Z 2011-11-13T23:13:48Z 2011-07-01T00:00:00Z -
dc.identifier.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.
dc.identifier.issn 1270-9638 -
dc.identifier.uri -
dc.description.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. en_UK
dc.publisher Elsevier Science B.V., Amsterdam. en_UK
dc.subject Adaptive control en_UK
dc.subject Aeroelastic airfoil en_UK
dc.subject Nonlinearity en_UK
dc.subject Parametric uncertainty en_UK
dc.title Adaptive control of a nonlinear aeroelastic system en_UK
dc.type Article -

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