Journal
AEROSPACE SCIENCE AND TECHNOLOGY
Volume 10, Issue 2, Pages 120-126Publisher
ELSEVIER FRANCE-EDITIONS SCIENTIFIQUES MEDICALES ELSEVIER
DOI: 10.1016/j.ast.2005.10.002
Keywords
robust aeroelastic control; flapped wing; Kalman filter; sliding mode observer; blast load
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The performance of a robust control strategy applied to a three-degrees-of- freedom (3-DOF) flap-wing aeroelastic system impacted by a pressure pulse in the subcritical flight speed regime is investigated. The goal of its implementation is to suppress flutter instability and reduce the vibrational level in the subcritical flight speed range. To this end, the linear quadratic Gaussian (LQG) control methodology in conjunction with a sliding mode observer (SMO) are used. Comparisons with the counterpart results obtained via implementation of LQG controller with conventional Kalman filter (KF) are also provided and pertinent conclusions are outlined. (c) 2005 Elsevier SAS. All riahts reserved.
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