Abstract
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. The Volterra-based ROM is obtained using the derivative of unsteady aerodynamic step-response. Transient responses and Gaussian responses were calculated using ROM and compared with the CFD solver for validation of ROM approach. 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. Aeroelastic analysis is conducted using state space model. A typical section model has been used for validation. An aeroelastic analysis of 3D wing is also conducted at M=0.60. While highly optimized, the state-space model remains a decoupled system and has enough meaningful information about the nature of the aerodynamic system. The proposed approach is computationally efficient without loosing structural/aerodynamic nonlinearities.
| Original language | English (US) |
|---|---|
| Title of host publication | Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference |
| Pages | 5456-5474 |
| Number of pages | 19 |
| Volume | 7 |
| State | Published - 2004 |
| Event | Collect. of Pap. - 45th AIAA/ASME/ASCE/AHS/ASC Struct., Struct. Dyn. and Mater. Conf.; 12th AIAA/ASME/AHS Adapt. Struct. Conf.; 6th AIAA Non-Deterministic Approaches Forum; 5th AIAA Gossamer Spacecraft Forum - Palm Springs, CA, United States Duration: Apr 19 2004 → Apr 22 2004 |
Other
| Other | Collect. of Pap. - 45th AIAA/ASME/ASCE/AHS/ASC Struct., Struct. Dyn. and Mater. Conf.; 12th AIAA/ASME/AHS Adapt. Struct. Conf.; 6th AIAA Non-Deterministic Approaches Forum; 5th AIAA Gossamer Spacecraft Forum |
|---|---|
| Country | United States |
| City | Palm Springs, CA |
| Period | 4/19/04 → 4/22/04 |
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ASJC Scopus subject areas
- Architecture
Cite this
An efficient approach for solving nonlinear aeroelastic phenomenon using reduced-order modeling. / Munteanu, Sorin; Rajadas, John; Nam, Changho; Chattopadhyay, Aditi.
Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Vol. 7 2004. p. 5456-5474.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - An efficient approach for solving nonlinear aeroelastic phenomenon using reduced-order modeling
AU - Munteanu, Sorin
AU - Rajadas, John
AU - Nam, Changho
AU - Chattopadhyay, Aditi
PY - 2004
Y1 - 2004
N2 - 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. The Volterra-based ROM is obtained using the derivative of unsteady aerodynamic step-response. Transient responses and Gaussian responses were calculated using ROM and compared with the CFD solver for validation of ROM approach. 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. Aeroelastic analysis is conducted using state space model. A typical section model has been used for validation. An aeroelastic analysis of 3D wing is also conducted at M=0.60. While highly optimized, the state-space model remains a decoupled system and has enough meaningful information about the nature of the aerodynamic system. The proposed approach is computationally efficient without loosing structural/aerodynamic nonlinearities.
AB - 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. The Volterra-based ROM is obtained using the derivative of unsteady aerodynamic step-response. Transient responses and Gaussian responses were calculated using ROM and compared with the CFD solver for validation of ROM approach. 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. Aeroelastic analysis is conducted using state space model. A typical section model has been used for validation. An aeroelastic analysis of 3D wing is also conducted at M=0.60. While highly optimized, the state-space model remains a decoupled system and has enough meaningful information about the nature of the aerodynamic system. The proposed approach is computationally efficient without loosing structural/aerodynamic nonlinearities.
UR - http://www.scopus.com/inward/record.url?scp=16244407352&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=16244407352&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:16244407352
VL - 7
SP - 5456
EP - 5474
BT - Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
ER -