Abstract
The robust aeroelastic control of a three-degrees-of-freedom (3DOF) linear and non-linear wing-flap system under sliding mode control (SMC) and operation in supersonic flight speeds is presented. Open- and closed-loop aeroelastic responses to blast and sonic-boom excitation in the wingflap system with uncertainty, as well as flutter analysis, are investigated along with the implementation of a Sliding Mode Observer (SMO). The effectiveness of control in reducing the amplitude of oscillation and preventing flutter instability is demonstrated.
Original language | English |
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Pages (from-to) | 279-288 |
Number of pages | 10 |
Journal | International Journal of Control, Automation and Systems |
Volume | 8 |
Issue number | 2 |
DOIs | |
Publication status | Published - 2010 Apr |
Keywords
- 3DOF airfoil system
- Aeroelasticity
- Sliding mode control
- Sliding mode observer
ASJC Scopus subject areas
- Control and Systems Engineering
- Computer Science Applications