TY - JOUR
T1 - Dynamic aeroelastic response and active control of composite thin-walled beam structures in compressible flow
AU - Na, Sungsoo
AU - Song, Ji Seok
AU - Choo, Jeong Hwan
AU - Qin, Zhanming
N1 - Funding Information:
The authors would like to acknowledge the late Professor Liviu Librescu of Virginia Tech, whose help, guidance and support through the years have made this research possible. He will be remembered and deeply missed. S. Na also acknowledges the financial support from National Research Foundation of Korea (NRF) funded by the Ministry of Education, Science and Technology (no. 2010-0001642).
PY - 2011/10/10
Y1 - 2011/10/10
N2 - The dynamic aeroelastic response and its active control of composite beam structures in compressible flow and exposed to gust and explosive type loads are examined. Modeling of the structures is based on a refined composite thin-walled beam theory and incorporate a number of nonclassical effects, such as transverse shear, material anisotropy, warping inhibition, and rotatory inertia. The unsteady compressible aerodynamic loads for arbitrary small motion in the time domain are derived based on the concept of indicial functions. The sliding mode control (SMC) and linear-quadratic Gaussian (LQG) control methodology with sliding mode observer are used for the purpose of control. The beam structures are restricted to circumferentially asymmetric lay-up construction and the influence of ply angle, flight speed, and external excitations on the response and its active control are specifically investigated. A number of conclusions are outlined at the end.
AB - The dynamic aeroelastic response and its active control of composite beam structures in compressible flow and exposed to gust and explosive type loads are examined. Modeling of the structures is based on a refined composite thin-walled beam theory and incorporate a number of nonclassical effects, such as transverse shear, material anisotropy, warping inhibition, and rotatory inertia. The unsteady compressible aerodynamic loads for arbitrary small motion in the time domain are derived based on the concept of indicial functions. The sliding mode control (SMC) and linear-quadratic Gaussian (LQG) control methodology with sliding mode observer are used for the purpose of control. The beam structures are restricted to circumferentially asymmetric lay-up construction and the influence of ply angle, flight speed, and external excitations on the response and its active control are specifically investigated. A number of conclusions are outlined at the end.
UR - http://www.scopus.com/inward/record.url?scp=79960557905&partnerID=8YFLogxK
U2 - 10.1016/j.jsv.2011.05.026
DO - 10.1016/j.jsv.2011.05.026
M3 - Article
AN - SCOPUS:79960557905
SN - 0022-460X
VL - 330
SP - 4998
EP - 5013
JO - Journal of Sound and Vibration
JF - Journal of Sound and Vibration
IS - 21
ER -