TY - GEN
T1 - Nonlinear aeroelastic analysis using a CFD-based state space ROM
AU - Munteanu, Sorin
AU - Rajadas, John
AU - Chattopadhyay, Aditi
PY - 2006
Y1 - 2006
N2 - A coupled framework of reduced order models (ROMs) for addressing the nonlinear aeroelasticity problem is introduced. A procedure to develop CFD-based reduced order models (ROMs) which capture the essence of an aerodynamic system while reducing the complexity of the computational model is introduced. An Eigensystem Realization Algorithm is used to convert ROM unsteady aerodynamics into the LTI state space model. A reduction in the cost of the realization of the ROM kernel is obtained by the identification of the state-space model. Structural nonlinearities (hardening nonlinearity on the second mode) are included in a nonlinear time invariant structural ROM. Structural ROMs are identified for cases where the thermal load is added and the thermal effect on the aeroelastic response is studied. Aeroelastic analysis is conducted using the nonlinear state space model. The weakened wall-mounted AGARD wing 445.6 has been used for validation. An aeroelastic analysis of a NACA 65A004 composite wing model is also conducted at supersonic speeds including structural nonlinearities due to thermal load. The state-space model is a highly optimized decoupled system while retaining significant details of the aeroelastic system. The proposed approach is computationally efficient while including structural/aerodynamic nonlinearities.
AB - A coupled framework of reduced order models (ROMs) for addressing the nonlinear aeroelasticity problem is introduced. A procedure to develop CFD-based reduced order models (ROMs) which capture the essence of an aerodynamic system while reducing the complexity of the computational model is introduced. An Eigensystem Realization Algorithm is used to convert ROM unsteady aerodynamics into the LTI state space model. A reduction in the cost of the realization of the ROM kernel is obtained by the identification of the state-space model. Structural nonlinearities (hardening nonlinearity on the second mode) are included in a nonlinear time invariant structural ROM. Structural ROMs are identified for cases where the thermal load is added and the thermal effect on the aeroelastic response is studied. Aeroelastic analysis is conducted using the nonlinear state space model. The weakened wall-mounted AGARD wing 445.6 has been used for validation. An aeroelastic analysis of a NACA 65A004 composite wing model is also conducted at supersonic speeds including structural nonlinearities due to thermal load. The state-space model is a highly optimized decoupled system while retaining significant details of the aeroelastic system. The proposed approach is computationally efficient while including structural/aerodynamic nonlinearities.
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M3 - Conference contribution
AN - SCOPUS:34147213581
SN - 1563478080
SN - 9781563478086
T3 - Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
SP - 5188
EP - 5206
BT - Collection of Technical Papers - 47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
T2 - 47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Y2 - 1 May 2006 through 4 May 2006
ER -