TY - GEN
T1 - Nonlinear response of open/closed-loop aeroelastic system using a discrete state-space approach
AU - Chen, P. C.
AU - Sulaeman, E.
PY - 2003
Y1 - 2003
N2 - A generalized direct simulation method using a discrete time-domain state-space approach for transient response of both open and closed-loop nonlinear aeroelastic systems is developed. Based on a nonlinear parameter scheme that divides the nonlinear system into sub-linear systems, the present method first assembles a set of discrete time-domain state-space equations and then computes the transient response by switching the time-integration procedure between this set of state-space equations. In so doing, various nonlinearities in structures, aerodynamics and/or control systems can be included. The present method is validated by correlating the transient response of a three-degree-of-freedom airfoil section in freeplay with the experimental and numerical results obtained by Conner et al. The stability of a strut-braced wing with buckling effects at two trim conditions is also studied, which shows that the aeroelastic stability of the present strut-braced wing is trim-condition dependent. Such results clearly could not be obtained if using a linear aeroelastic analysis.
AB - A generalized direct simulation method using a discrete time-domain state-space approach for transient response of both open and closed-loop nonlinear aeroelastic systems is developed. Based on a nonlinear parameter scheme that divides the nonlinear system into sub-linear systems, the present method first assembles a set of discrete time-domain state-space equations and then computes the transient response by switching the time-integration procedure between this set of state-space equations. In so doing, various nonlinearities in structures, aerodynamics and/or control systems can be included. The present method is validated by correlating the transient response of a three-degree-of-freedom airfoil section in freeplay with the experimental and numerical results obtained by Conner et al. The stability of a strut-braced wing with buckling effects at two trim conditions is also studied, which shows that the aeroelastic stability of the present strut-braced wing is trim-condition dependent. Such results clearly could not be obtained if using a linear aeroelastic analysis.
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U2 - 10.2514/6.2003-1734
DO - 10.2514/6.2003-1734
M3 - Conference contribution
AN - SCOPUS:85086615134
SN - 9781624101007
T3 - 44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
BT - 44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - 44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference 2003
Y2 - 7 April 2003 through 10 April 2003
ER -