Abstract
The purpose of this work is to use level set topology optimization to improve the design of a representative wing box structure for the NASA common research model. The objective is to minimize the total compliance of the structure under aerodynamic and body force loading, where the aerodynamic loading is coupled to the structural deformation. A taxi bump case was also considered, where only body force loads were applied. The trim condition that aerodynamic lift must balance the total weight of the aircraft is enforced by allowing the root angle of attack to change. The level set optimization method is implemented on an unstructured three-dimensional grid, so that the method can optimize a wing box with arbitrary geometry. Fast matching and upwind schemes are developed for an unstructured grid, which make the level set method robust and efficient. The adjoint method is used to obtain the coupled shape sensitivities required to perform aerostructural optimization of the wing box structure.
| Original language | English |
|---|---|
| Title of host publication | 10th AIAA Multidisciplinary Design Optimization Specialist Conference |
| Publication status | Published - 2014 |
| Event | 10th AIAA Multidisciplinary Design Optimization Specialist Conference - SciTech Forum and Exposition 2014 - National Harbor, MD, United States Duration: 13 Jan 2014 → 17 Jan 2014 |
Conference
| Conference | 10th AIAA Multidisciplinary Design Optimization Specialist Conference - SciTech Forum and Exposition 2014 |
|---|---|
| Country | United States |
| City | National Harbor, MD |
| Period | 13/01/14 → 17/01/14 |
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ASJC Scopus subject areas
- Computer Graphics and Computer-Aided Design
- Computer Science Applications
- Software
Cite this
Aerostructural level set topology optimization for a common research model wing. / Dunning, Peter D.; Stanford, Bret K.; Kim, H. Alicia.
10th AIAA Multidisciplinary Design Optimization Specialist Conference. 2014.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Aerostructural level set topology optimization for a common research model wing
AU - Dunning, Peter D.
AU - Stanford, Bret K.
AU - Kim, H. Alicia
PY - 2014
Y1 - 2014
N2 - The purpose of this work is to use level set topology optimization to improve the design of a representative wing box structure for the NASA common research model. The objective is to minimize the total compliance of the structure under aerodynamic and body force loading, where the aerodynamic loading is coupled to the structural deformation. A taxi bump case was also considered, where only body force loads were applied. The trim condition that aerodynamic lift must balance the total weight of the aircraft is enforced by allowing the root angle of attack to change. The level set optimization method is implemented on an unstructured three-dimensional grid, so that the method can optimize a wing box with arbitrary geometry. Fast matching and upwind schemes are developed for an unstructured grid, which make the level set method robust and efficient. The adjoint method is used to obtain the coupled shape sensitivities required to perform aerostructural optimization of the wing box structure.
AB - The purpose of this work is to use level set topology optimization to improve the design of a representative wing box structure for the NASA common research model. The objective is to minimize the total compliance of the structure under aerodynamic and body force loading, where the aerodynamic loading is coupled to the structural deformation. A taxi bump case was also considered, where only body force loads were applied. The trim condition that aerodynamic lift must balance the total weight of the aircraft is enforced by allowing the root angle of attack to change. The level set optimization method is implemented on an unstructured three-dimensional grid, so that the method can optimize a wing box with arbitrary geometry. Fast matching and upwind schemes are developed for an unstructured grid, which make the level set method robust and efficient. The adjoint method is used to obtain the coupled shape sensitivities required to perform aerostructural optimization of the wing box structure.
UR - http://www.scopus.com/inward/record.url?scp=84894470816&partnerID=8YFLogxK
M3 - Conference contribution
BT - 10th AIAA Multidisciplinary Design Optimization Specialist Conference
ER -