Name
Abstract | ||
|---|---|---|
Many control laws, such as optimal controllers and classical controllers, have seen their applications to suppressing the aeroelastic vibrations of the aeroelastic system. However, those control laws may not work effectively if the aeroelastic system involves control delay and faults. In this paper, we use the finite-time H∞ adaptive fault-tolerant control technique to deal with the flutter problem of the wing, which is subject to control delay, parameter uncertainties and external disturbances. Then actuator faults are considered in the control design. The theory content of this article includes the modeling of wing flutter and fault-tolerant controller design. By using the Lyapunov–Krasovskii function and the linear matrix inequality (LMI), the stability of the finite-time H∞ adaptive fault-tolerant controller is theoretically proved. Simulation results are given to demonstrate the effectiveness of the scheme. |
Year | DOI | Venue |
|---|---|---|
2016 | 10.1016/j.jfranklin.2016.03.010 | Journal of the Franklin Institute |
Keywords | Field | DocType |
Reentry vehicle,Active flutter suppression,Fault-tolerant control,Control delay | Aeroelasticity,Wing,Control theory,Control theory,Flutter,Control engineering,Fault tolerance,Vibration,Linear matrix inequality,Mathematics,Actuator | Journal |
Volume | Issue | ISSN |
353 | 9 | 0016-0032 |
Citations | PageRank | References |
0 | 0.34 | 0 |
Authors | ||
2 | ||
Name | Order | Citations | PageRank |
|---|---|---|---|
| Mingzhou Gao | 1 | 0 | 0.34 |
| G.-C. Guo | 2 | 0 | 2.37 |