Abstract
The performance of a robust control strategy applied to a two-dimensional supersonic flap-wing aeroelastic system impacted by a pressure pulse in the subcritical supersonic flight speed regime is analyzed. The piston theory aerodynamic model modified to account for the flap deflection has been considered. The study is carried-out via implementation of the Linear Quadratic Gaussian (LQG) control methodology with sliding mode observer. Its performance toward suppressing flutter, reducing the vibrational level amplitudes, as well as toward eliminating the observation spillover due to the unmeasured states is revealed through numerical simulations, and pertinent conclusions are outlined.
| Original language | English |
|---|---|
| Pages (from-to) | 37-47 |
| Number of pages | 11 |
| Journal | Acta Mechanica |
| Volume | 192 |
| Issue number | 1-4 |
| DOIs | |
| Publication status | Published - 2007 Aug 1 |
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ASJC Scopus subject areas
- Mechanics of Materials
- Computational Mechanics
Cite this
Robust aeroelastic control of two-dimensional supersonic flapped wing systems. / Na, Sung Soo; Librescu, L.; Marzocca, P.; Yoon, G. C.; Rubillo, C.; Bong, K.
In: Acta Mechanica, Vol. 192, No. 1-4, 01.08.2007, p. 37-47.Research output: Contribution to journal › Article
}
TY - JOUR
T1 - Robust aeroelastic control of two-dimensional supersonic flapped wing systems
AU - Na, Sung Soo
AU - Librescu, L.
AU - Marzocca, P.
AU - Yoon, G. C.
AU - Rubillo, C.
AU - Bong, K.
PY - 2007/8/1
Y1 - 2007/8/1
N2 - The performance of a robust control strategy applied to a two-dimensional supersonic flap-wing aeroelastic system impacted by a pressure pulse in the subcritical supersonic flight speed regime is analyzed. The piston theory aerodynamic model modified to account for the flap deflection has been considered. The study is carried-out via implementation of the Linear Quadratic Gaussian (LQG) control methodology with sliding mode observer. Its performance toward suppressing flutter, reducing the vibrational level amplitudes, as well as toward eliminating the observation spillover due to the unmeasured states is revealed through numerical simulations, and pertinent conclusions are outlined.
AB - The performance of a robust control strategy applied to a two-dimensional supersonic flap-wing aeroelastic system impacted by a pressure pulse in the subcritical supersonic flight speed regime is analyzed. The piston theory aerodynamic model modified to account for the flap deflection has been considered. The study is carried-out via implementation of the Linear Quadratic Gaussian (LQG) control methodology with sliding mode observer. Its performance toward suppressing flutter, reducing the vibrational level amplitudes, as well as toward eliminating the observation spillover due to the unmeasured states is revealed through numerical simulations, and pertinent conclusions are outlined.
UR - http://www.scopus.com/inward/record.url?scp=34547655750&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=34547655750&partnerID=8YFLogxK
U2 - 10.1007/s00707-006-0419-3
DO - 10.1007/s00707-006-0419-3
M3 - Article
AN - SCOPUS:34547655750
VL - 192
SP - 37
EP - 47
JO - Acta Mechanica
JF - Acta Mechanica
SN - 0001-5970
IS - 1-4
ER -